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  • Other Sources  (227)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (227)
  • 2015-2019
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  • 1983  (227)
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  • 2015-2019
  • 1990-1994
  • 1980-1984  (227)
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  • 1
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    HZE particle shielding using confined magnetic fields (1983)
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    Publication Date: 2011-08-18
    Description: The great rigidities characteristic of high energy heavy ion (HZE) particles are judged to preclude near term use of confined magnetic fields of reasonable dimensions and strengths for small spacecraft shielding on long duration manned missions. It is noted that a Mars mission-class shield, although effective against solar protons, would be useless for HZE particles unless the mass and size of the shield are increased by several orders of magnitude (to yield a shield comparable to those contemplated for permanent space stations).
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 20; 629
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  • 2
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    On vibration control of tethered satellite systems (1983)
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    Publication Date: 2011-08-18
    Description: The general dynamics of a shuttle supported tethered subsatellite system taking into account the longitudinal and three dimensional transverse vibrations is considered. It is noted that control of inherently unstable dynamics during retrieval of the subsatellite can be carried out by letting the rate of change length depend on the state variables in an appropriate manner. Control laws using linear feedback of inplane state variables and nonlinear feedback of out-of-plane state variables are proposed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 317-327
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  • 3
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    A design procedure for active control of beam vibrations (1983)
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    Publication Date: 2011-08-18
    Description: The transverse vibrations of beams is discussed and a methodology for the design of an active damping device is given. The Bernoulli-Euler equation is used to derive a transcendental transfer function, which relates a torque applied at one end of the beam to the rotational position and velocity at that point. The active damping device consists of a wire, a linear actuator and a short torque arm attached to one end of the beam. The action of the actuator varies a tension in the wire and creates a torque which opposes the rotation of the beam and thus damps vibration. A design procedure for such an active damper is given. This procedure shows the relationships and trade-offs between the actuator stroke, power required, stress levels in the wire and beam and the geometry of the beam and wire. It is shown that by consideration of the frequency response at the beam natural frequencies, the aforementioned relationships can be greatly simplified. Similarly, a simple way of estimating the effective damping ratios and eigenvalue locations of actively controlled beams is presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 305-316
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  • 4
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    Orbiting chains and rings (1983)
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    Publication Date: 2011-08-18
    Description: Two very different, highly flexible, space structures proposed during the last decade which involve analytical solution of certain partial differential equations are discussed. The first structure is an array, or hanging chain of aluminum beads which would serve as a convenient communicator if, under the influence of the Earth's gravity gradient, it assumes a local vertical orientation as it circles the Earth. Two passive schemes have been proposed for damping the rigid modes: twist the wire at the ends to provide non-zero moment of inertia about the vertical, thereby inducing relative motion of the two tips during rigid pitch or roll, and thus exercising a damper; and introduce weak lossy springs between the end sections and the main section; thereby providing linear coupling between the springs and all the in-plane (pitch) modes. The second structure is a complete ring of satellites cabled together at synchronous altitude. By a slight increase in altitude, the cable is in tension. This configuration is, however, unstable, and an active feedback control scheme is required to stabilize it. A possible scheme involves local cable length adjustment based on measurement of local altitude and shape variations and their rates.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 329-336
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  • 5
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    Number and placement of control system sensors considering possible failures (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A methodology has been presented which is intended to assist the designer of a control system for a large space structure to decide how many sensors should be incorporated in the system and where they should be placed on the structure. This approach is intended to be especially useful in the early stages of the evolution of the system, before a complete control system concept has been defined. This methodology is based on a quantitative measure of the observability of the system for a given set of sensors. The effect of possible component failures during the mission period was incorporated in the measure. The question of sensor placement is then resolved by finding the locations which maximize the performance measure. The number of components to use cannot be determined by optimizing the measure because the observability always improves with increased number of sensors if they are optimally located. However, the improvement in the measure with component number can be determined, and this information can be used along with data on cost, power required, etc., to decide how many sensors to use.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 253-268
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  • 6
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    Active Control of Space Structures (ACOSS) model 2 (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A complete description of the active control of space structures model #2 which is a simple but realistic evaluation model is given. The design of this system was driven by the desire to incorporate certain attributes into the overall system characteristics. The desired features were structural design based on realistic sizes and weights; a simple unclassified optical system with associated performance measures and tolerance; and a set of disturbances typical of equipment vibration and attitude control (slew). The resulting model is described in detail along with the resulting mode shapes and natural frequencies of the system. A description of the line-of-sight performance measure including theory and implementation is given.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 195-210
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  • 7
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    Introduction and survey on continuum models for repetitive lattice structures (1983)
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    Publication Date: 2011-08-18
    Description: A brief introduction and survey to aid and familiarize researchers interested in the use of continuum modeling procedures applied towards large space structure technology are presented. The use of such structural models for the distributed control of large flexible lattice structures offers a significant advantage over a numerical approach.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 63-70
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  • 8
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    Control of flexible structures: A systematic overview of the problem (1983)
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    Publication Date: 2011-08-18
    Description: A way of designing a control system using a finite model that accounts for the distributed nature of the control problem in a systematic way is described. This is accomplished by using a mode description of the system and from that description determining the number of modes that must be retained based on the performance and the disturbance descriptions. The design then uses a full order model that includes all of the dynamics: sensor, actuator, disturbance and flexible motion. The designs that result are simple, robust, perform well and have the added distinction of being easy to implement.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 49-61
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  • 9
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    Minimum information modelling of structural systems with uncertain parameters (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Work is reviewed wherein the design of active structural control is formulated as the mean-square optimal control of a linear mechanical system with stochastic parameters. In practice, a complete probabilistic description of model parameters can never be provided by empirical determinations, and a suitable design approach must accept very limited a priori data on parameter statistics. In consequence, the mean-square optimization problem is formulated using a complete probability assignment which is made to be consistent with available data but maximally unconstrained otherwise through use of a maximum entropy principle. The ramifications of this approach for both robustness and large dimensionality are illustrated by consideration of the full-state feedback regulation problem.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 71-88
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  • 10
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    On the analytical modeling of the nonlinear vibrations of pretensioned space structures (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Pretensioned structures are receiving considerable attention as candidate large space structures. A typical example is a hoop-column antenna. The large number of preloaded members requires efficient analytical methods for concept validation and design. Validation through analyses is especially important since ground testing may be limited due to gravity effects and structural size. The present investigation has the objective to present an examination of the analytical modeling of pretensioned members undergoing nonlinear vibrations. Two approximate nonlinear analysis are developed to model general structural arrangements which include beam-columns and pretensioned cables attached to a common nucleus, such as may occur at a joint of a pretensioned structure. Attention is given to structures undergoing nonlinear steady-state oscillations due to sinusoidal excitation forces. Three analyses, linear, quasi-linear, and nonlinear are conducted and applied to study the response of a relatively simple cable stiffened structure.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 11
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    Control structure interactions in large space structures Analysis using energy approach (1983)
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    Publication Date: 2011-08-18
    Description: A simple energy approach to study the problem of control structure interactions in large space structures is presented. For the illustrative cases of free-free beam and free rectangular plate, the vibrational energy imparted during operation of constant and pulsed thrusters is found in a nondimensional form. Then based on a parametric study, suggestions are made on the choice of the thruster location and parameters to minimize the control structure interactions.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Aeronautical Society of India, Journal (ISSN 0001-9267); 35; 59-67
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  • 12
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    Approximation in control of flexible structures, theory and application (1983)
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    Publication Date: 2011-08-18
    Description: The sense in which the feedback control law based on an approximate finite dimensional model of a continuous structure approximates a control law which is optimal for the distributed, or infinite dimensional, model of the structure is studied. From the analysis of the various control and stability issues associated with this basis question, useful information for designing finite dimensional compensators which produce near-optimal performance in infinite dimensional systems is gained. Some of the important predictions that can be made about large-order finite dimensional control laws, using the theory of infinite dimensional Riccati equations are indicated.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 383-389
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  • 13
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    Analysis of structural perturbations in systems via cost decomposition methods (1983)
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    Publication Date: 2011-08-18
    Description: It has long been common practice to analyze linear dynamic systems by decomposing the total response in terms of individual contributions which are easier to analyze. Examples of this philosophy include the expansion of transfer functions using: (1) the superposition principle, (2) residue theory and partial fraction expansions, (3) Markov parameters, Hankel matrices, and (4) regular and singular perturbations. This paper summarizes a new and different kind of expansion designed to decompose the norm of the response vector rather than the response vector itself. This is referred to as "cost-decomposition' of the system. The notable advantages of this type of decomposition are: (a) easy application to multi-input, multi-output systems, (b) natural compatibility with Linear Quadratic Gaussian Theory, (c) applicability to the analysis of more general types of structural perturbations involving inputs, outputs, states, parameters. Property (c) makes the method suitable for problems in model reduction, measurement/actuator selections, and sensitivity analysis.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 465-475
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  • 14
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    Fixed-order dynamic compensation through optimal projection (1983)
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    Publication Date: 2011-08-18
    Description: This paper reviews a formulation for the design of fixed-order dynamic compensation for flexible mechanical systems which is based upon explicit optimality conditions derived under the minimum data/maximum entropy stochastic modelling approach. The optimality conditions give rise to the novel concept of "optimal projection' which provides significant insight with regard to the compensator structure and permits earlier, more restricted and/or ad hoc design schemes to be seen as special cases of the present formulation.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 409-425
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  • 15
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    Hardware verification of distributed/adaptive control (1983)
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    Publication Date: 2011-08-18
    Description: Adaptive control techniques are studied for their future application to the control of large space structures, where uncertain or changing parameters may destabilize standard control system designs. The approach used is to examine an extended Kalman filter estimator, in which the state vector is augmented with the unknown parameters. The associated Riccatti equation is linearized about the case of exact knowledge of the parameters. By assuming that parameter variations occur slowly, the filter complexity is reduced further yet. Simulations on a two degree-of-freedom oscillator demonstrate the parameter-tracking capability of the filter, and an implementation on the JPL Flexible Beam Facility using an incorrect model shows the adaptive filter/optimal control to be stable where a standard Kalman filter/optimal control design is unstable.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 337-350
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  • 16
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    The TOYSAT structural control experiment (1983)
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    Publication Date: 2011-08-18
    Description: The Lockheed TOYSAT experiment is described. The experiment was designed to test hypothesis concerning the application of optimal control theory to flexible spacecraft. The theory is presented, and results described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 269-285
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  • 17
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    Control of reflector vibrations in large spaceborne antennas by means of movable dampers (1983)
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    Publication Date: 2011-08-18
    Description: A simple approach to the design of feedback controls for damping the vibrations in large spaceborne antennas with flexible dish reflectors is proposed. The feedback controls consist of movable velocity-feedback dampers whose positions are determined by minimizing the rate of change of total vibrational energy at any time. The performance of the proposed feedback controls is studied via computer simulations.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ASME, Transactions, Journal of Applied Mechanics (ISSN 0021-8936); 50; Sept
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  • 18
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    Identification of structural dynamics systems using least-square lattice filters (1983)
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 19, no. 2987, Accession no. A82-38965
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: (ISSN 0731-5090)
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  • 19
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    Booster and orbiter configurations (1983)
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    Publication Date: 2011-08-18
    Description: In the recent Future Space Transportation System (FSFS) study, a mission model was selected and a baseline vehicle which best met model requirements was shaped. This baseline was then analyzed for flight performance, structural and subsystem weight, and operation. Figures related to a payload of 150,000 lb in a 20-ft-diam by 90-ft-long envelope became the baseline. The existence of both space-based orbital transfer vehicles (OTVs) and a space station was assumed, taking into account a transfer of the payload from the launch vehicle to OTVs at the space station for final delivery to geosynchronous orbit (GEO). A computer-aided engineering system called Aerospace Vehicle Interactive Design (AVID) was employed in connection with baseline vehicle development. It was found that approximately three-fifth of the payload weight would be cryogenic propellants for OTVs. Attention is given to problems regarding the packaging of cryogenic tankage, a payload shroud, and studies of staging for two different booster propulsion units.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics (ISSN 0004-6213); 21; June 198
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  • 20
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    Optimum wing sizing of a single-stage-to-orbit vehicle (1983)
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    Publication Date: 2011-08-18
    Description: (Previously cited in issue 06, p. 822, Accession no. A82-17822)
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 21
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    Structures and mechanisms - Streamlining for fuel economy (1983)
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    Publication Date: 2011-08-18
    Description: The design of prospective NASA space station components which inherently possess the means for structural growth without compromising initial system characteristics is considered. In structural design terms, space station growth can be achieved by increasing design safety factors, introducing dynamic isolators to prevent loads from reaching the initial components, or preplanning the refurbishment of the original structure with stronger elements. Design tradeoffs will be based on the definition of on-orbit loads, including docking and maneuvering, whose derived load spectra will allow the estimation of fatigue life. Improvements must be made in structural materials selection in order to reduce contamination, slow degradation, and extend the life of coatings. To minimize on-orbit maintenance, long service life lubrication systems with advanced sealing devices must be developed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 21; Mar. 198
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  • 22
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    Thermal control - Heat buses will operate like a public utility (1983)
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    Publication Date: 2011-08-18
    Description: Active thermal control for the NASA space station concept requires long life heat rejection, highly versatile thermal transport, and efficient system integration. By a significant margin, the heat radiator will be the largest and most exposed portion of the space station thermal system. Transport requirements encompass the collection and movement of thermal energy from the space station's heat sources to the radiator heat sink at required temperature levels. In a decentralized thermal system, each space station module would collect and reject all of the waste heat generated, thereby requiring no module interconnections. This scheme does not, however, allow waste heat from one module to be used by another. In a centralized system, heat must be transported across module boundaries. A high capacity monogroove heat pipe has been developed to simplify space radiators design and operation.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 21; Mar. 198
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  • 23
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    Control - Demands mushroom as station grows (1983)
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    Publication Date: 2011-08-18
    Description: The NASA space station, which is presently in the planning stage, is to be composed of both rigid and nonrigid modules, rotating elements, and flexible appendages subjected to environmental disturbances from the earth's atmospheric gravity gradient, and magnetic field, as well as solar radiation and self-generated disturbances. Control functions, which will originally include attitude control, docking and berthing control, and system monitoring and management, will with evolving mission objectives come to encompass such control functions as articulation control, autonomous navigation, space traffic control, and large space structure control. Attention is given to the advancements in modular, distributed, and adaptive control methods, as well as system identification and hardware fault tolerance techniques, which will be required.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 21; Mar. 198
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  • 24
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    Large space structures raise testing challenges (1983)
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    Publication Date: 2011-08-18
    Description: The testing approaches and techniques necessary for combined ground and space verification for large space structures (LSS) to be deployed and assembled in space are explored. The size of LSS precludes full ground tests, thereby requiring assemblies, components, and their interactions to be examined on orbit. Ground tests involving drop tests and zero-g aircraft flights can be performed with scale models, but need computational compensation to eliminate gravitational and torque effects that do not occur in space. Structural rigidity also varies from ground to space, and can partly be accounted for in ground tests by using cable supports, although numerical modelling must remove the effects of the cables' presence. Long-term funding is recommended for on-orbit tests of components in order to build a data base for later testing and actual construction of LSS.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics (ISSN 0004-6213); 21; Oct. 198
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  • 25
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    Exceedance statistics of accelerations resulting from thruster firings on the Apollo-Soyuz mission (1983)
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    Publication Date: 2011-08-18
    Description: Spacecraft acceleration resulting from firings of vernier control system thrusters is an important consideration in the design, planning, execution and post-flight analysis of laboratory experiments in space. In particular, scientists and technologists involved with the development of experiments to be performed in space in many instances required statistical information on the magnitude and rate of occurrence of spacecraft accelerations. Typically, these accelerations are stochastic in nature, so that it is useful to characterize these accelerations in statistical terms. Statistics of spacecraft accelerations are summarized. Previously announced in STAR as N82-12127
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4560); 20; May-June
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  • 26
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    Control of space stations (1983)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: A study is made to develop controllers for the NASA-JSC Triangular Space Station and evaluate their performances to make recommendations for structural design and/or control alternatives. The control system design assumes the rigid body of the Space Station and developes the lumped parameter control system by using the Inverse Optimal Control Theory. In order to evaluate the performance of the control system, a Parameter Estimation algorithm is being developed which will be used in modeling an equivalent but simpler Space Station model. Finally, a scaled version of the Space Station is being built for the purpose of physical experiments to evaluate the control system performance.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Johnson (Lyndon B.) Space Center The 1983 NASA/ASEE Summer Faculty Fellowship Research Program Research Reports; NASA. Johnson (Lynd
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  • 27
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    Orbital Maneuvering Vehicle Simulation System On-Board Processing Logic (1983)
    In:  CASI
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    Publication Date: 2014-09-11
    Description: The control logic for an Orbital Maneuvering Vehicle (OMV) Simulation system is developed. In order that better control over the vehicle can be exercised, several modifications to the vehicle are suggested. The need of better position feedback leads to the development of an alternative simpler but more reliable navigation system which is also discussed. The control logic is presented in pseudocode form, and can be implemented in FORTRAN and/or MACRO II.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Res. Rept.: 1983 NASA(ASEE Summer Faculty Fellowship Program; 67 p
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  • 28
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    Minimum impulse limit cycle design to compensate for measurement uncertainties (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 19, p. 2997, Accession no. A82-38972
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 6; 432-436
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  • 29
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    Aeroassisted orbit transfer window opens on missions (1983)
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    Publication Date: 2011-08-18
    Description: Studies of aeroassisted spacecraft orbit transfer conducted over the last two decades have produced an extensive literature and a well developed technology base, which suggest the obtainability of substantial performance improvements over all-propulsive spacecraft maneuvers. In such cases as that of multipass aerobraking, in which the vehicle is transferred from its approach velocity to a highly elliptic orbit about the planet by means of a rocket burn, followed by the circularization of the orbit through many high altitude atmospheric passes, the technology appears to be ready for application. In most other areas of aeroassisted orbit transfer, further work is required to reduce design risks to acceptable levels.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics (ISSN 0004-6213); 21; 36-43
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  • 30
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    Large Deployable Reflector (LDR) - A concept for an orbiting submillimeter-infrared telescope for the 1990s (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The history and background of the Large Deployable Reflector (LDR) are reviewed. The results of the June 1982 Asilomar (CA) workshop are incorporated into the LDR science objectives and telescope concept. The areas where the LDR may have the greatest scientific impact are in the study of star formation and planetary systems in the own and nearby galaxies and in cosmological studies of the structure and evolution of the early universe. The observational requirements for these and other scientific studies give rise to a set of telescope functional requirements. These, in turn, are satisfied by an LDR configuration which is a Cassegrain design with a 20 m diameter, actively controlled, segmented, primary reflector, diffraction limited at a wavelength of 30 to 50 microns. Technical challenges in the LDR development include construction of high tolerance mirror segments, surface figure measurement, figure control, vibration control, pointing, cryogenics, and coherent detectors. Project status and future plans for the LDR are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Optical Engineering (ISSN 0091-3286); 22; 725-731
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  • 31
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    Control of large spaceborne antenna systems with flexible booms by mechanical decoupling (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A simple practical method for designing antenna-feed attitude control systems for large deployable spaceborne antenna systems with long flexible booms is proposed. The basic idea is to mechanically decouple the antenna-feed from the boom so that the feed-attitude control system can be designed without taking the boom dynamics into consideration, thus avoiding a complex control problem involving an infinite-dimensional distributed parameter system. The validity of the proposed method is substantiated by analytical and numerical studies using a mathematical model for the flexible boom which could undergo both bending and torsional vibrations. This approach leads to simple antenna-feed attitude control systems which are amenable to physical implementation.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Franklin Institute, Journal (ISSN 0016-0032); 315; May-June
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  • 32
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    Structures and subsystems (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: New and improved materials combined with efficient structural design concepts have made an essential contribution towards the shaping of the present transportation system (STS), and now, for the replacement of the STS in the year 2005, new materials and novel designs are being studied to identify the technologies which should be developed for a low-cost future space transportation system (FSTS). Three basic structural arrangements were considered for the FSTS orbiter. They include a nonintegral tank arrangement, an integral-tank arrangement, and a hybrid of the first two. Three representative arrangements regarding wall constructions are considered. Each employs a blade-stiffened aluminum tank with reinforced closed-cell-foam cryogenic insulation. Attention is given to an aluminum-alloy structure, a graphite-epoxy structure, a graphite-polyimide structure, a carbon-carbon surface panel structure, a graphite-composite fuselage structure, serviceability and all-weather considerations, and structural concept ratings.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics (ISSN 0004-6213); 21; June 198
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  • 33
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    Experimental demonstration of static shape control (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 03, p. 344, Accession no. A82-13998
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: (ISSN 0731-5090)
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  • 34
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    System identification of large flexible structures by using simple continuum models (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Simple continuum models for the representation of large truss beams and truss platforms are constructed and employed in the solution of system identification problems permitting the significant reduction of the number of structural parameters. Two simple and easily computer-implemented algorithms are presented for the estimation of a simple model's equivalent structural parameters, and analytical and numerical solutions are given for the truss beam and truss platform cases in order to illustrate the basic concepts. It is found that model simplicity, in conjunction with the principle of least square erors, yields a feasible integration of structural and identification problems.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of the Astronautical Sciences (ISSN 0021-9142); 31; Jan
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  • 35
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    A concept for global crop forecasting (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The mission, instrumentation, and design concepts for microwave radiometer satellites for continuous crop condition forecasting and monitoring on a global basis are described. Soil moisture affects both crop growth and the dielectric properties of the soil, and can be quantified by analysis of reflected radiance passively received by orbiting spacecraft. A dedicated satellite reading a swath 200 km across, with 1 km and 1 K temperature resolution, could track the time-varying changes of solid moisture, sea ice, and water surface temperature. Launched by the Shuttle into an interim orbit, a boost would place the satellite in a 400 or 700 km orbit. Resolution requirements indicate a 45-725 m diam antenna, with 70 dB gain, operating at frequencies of 1.08, 2.03, and 4.95 GHz to ensure atmospheric transparency. Alternative structural concepts include either double-layer tetrahedral or single-layer geodesic trusses as the basic structural members. An analysis of the electrostatic positioning of the parabolic antenna membrane is outlined.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: vol. 36; Feb. 198
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  • 36
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    Research in structures and materials for future space transportation systems - An overview (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: (Previously cited in issue 14, p. 2544, Accession no. A79-34703)
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 37
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    Specular effects of Shuttle Orbiter radiators on a typical payload (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: (Previously cited in issue 17, p. 2894, Accession no. A81-39083)
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 38
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    Use of electromagnetic models in the optimal control of large space antennas (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A general approach to the optimal control of large space antennas based on their RF/structural characteristics is described. The approach consists of defining a cost functional based on the degradation of the RF performance of the antenna and using the structural model as the dynamic system. The method is applied to the design of an optimal controller for a 55-m, wrap-rib offset-fed antenna. Simulation results show that control energy consumption is reduced to aproximately one third of the energy used to achieve the same RF performance with traditional control strategies.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 39
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    Static shape forming for an electrostatically controlled membrane mirror (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A design concept is described permitting the static construction of a flexible membrane reflector for use in a radiometer spacecraft. The scheme utilizes electrostatic forces to actively shape the membrane toward a specified reflector surface with a required degree of precision. The formulations of the required electrostatic attractive forces, and stress and strain distributed in the membrane are presented in this paper in terms of curvilinear coordinates. An example is given to illustrate a variety of spherical membrane characteristics associated with different boundary conditions.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 40
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    Lifting entry vehicle mass reduction through integrated thermostructural/trajectory design (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 05, p. 749, Accession no. A80-18335
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 20; 589-596
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  • 41
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    Automatic thermal control switches (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 24, p. 3750, Accession no. A82-48067
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 20; 553-558
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  • 42
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    Energy consumption analysis of the Venus Deep Space Station (DSS-13) (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: This report continues the energy consumption analysis and verification study of the tracking stations of the Goldstone Deep Space Communications Complex, and presents an audit of the Venus Deep Space Station (DSS 13). Due to the non-continuous radioastronomy research and development operations at the station, estimations of energy usage were employed in the energy consumption simulation of both the 9-meter and 26-meter antenna buildings. A 17.9% decrease in station energy consumption was experienced over the 1979-1981 years under study. A comparison of the ECP computer simulations and the station's main watt-hour meter readings showed good agreement.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: The Telecommun. and Data Acquisition Rept.; p 114-123
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  • 43
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    Large space structures controls research and development at Marshall Space Flight Center: Status and future plans (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Work performed in Large Space Structures Controls research and development program at Marshall Space Flight Center is described. Studies to develop a multilevel control approach which supports a modular or building block approach to the buildup of space platforms are discussed. A concept has been developed and tested in three-axis computer simulation utilizing a five-body model of a basic space platform module. Analytical efforts have continued to focus on extension of the basic theory and subsequent application. Consideration is also given to specifications to evaluate several algorithms for controlling the shape of Large Space Structures.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center Structural Dyn. and Control of Large Space Struct., 1982; p 215-220
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  • 44
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    Partitioning of large space structures vibration control computations (1983)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The vibration control of large space structures is studied. It is found to be computationally demanding. Distribution of the vibration control computations among central and local processors can significantly reduce the throughput required from the central processor and may also result in improved performance due to reduced transport lag.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center Structural Dyn. and Control of Large Space Struct., 1982; p 195-200
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  • 45
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    Research on the control of large space structures (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The research effort on the control of large space structures at the University of Houston has concentrated on the mathematical theory of finite-element models; identification of the mass, damping, and stiffness matrix; assignment of damping to structures; and decoupling of structure dynamics. The objective of the work has been and will continue to be the development of efficient numerical algorithms for analysis, control, and identification of large space structures. The major consideration in the development of the algorithms has been the large number of equations that must be handled by the algorithm as well as sensitivity of the algorithms to numerical errors.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center Structural Dyn. and Control of Large Space Struct., 1982; p 221-233
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  • 46
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    A program plan for the development of fault tolerant large space systems (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The need for fault tolerance in Large Space systems is discussed. The unique characteristics of LSS which affect fault tolerance are described. The status of fault tolerant research for LSS is described. A program plan to validate and demonstrate the concept of fault tolerance for LSS is developed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center Structural Dyn. and Control of Large Space Struct., 1982; p 175-180
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  • 47
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    Component number and placement in large space structure control (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Studies are carried out to assist the designer of the control system for a large flexible space structure in his choice of how many actuators and sensors to incorporate in the system, and where to locate them on the structure. The degree of controllability and minimum control energy strategy for driving the system are described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center Structural Dyn. and Control of Large Space Struct., 1982; p 161-174
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  • 48
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    Robust precision pointing control of large space platform payloads (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Large space structure (LSS) secondary controllers to enhance inherent damping, and primary controllers for controlling rigid-body modes and structural modes are discussed. It was concluded that LSS control is stable and robust and offers promise. Further investigation is needed on the effects of actuator/sensor bandwidth.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center Structural Dyn. and Control of Large Space Struct., 1982; p 121-134
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  • 49
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    Control of structures in space (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Various topics related to the control of large space structures are discussed. Equations of motion for distributed systems, eigenvalue problems, modal equations, control implementation, and the Langley beam experiment are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center Structural Dyn. and Control of Large Space Struct., 1982; p 111-120
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  • 50
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    The dynamics and control of large flexible space structures (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Large, flexible orbiting systems proposed for possible use in communications, electronic orbital based mail systems, and solar energy collection are discussed. The size and low weight to area ratio of such systems indicate that system flexibility is now the main consideration in the dynamics and control problem. For such large, flexible systems, both orientation and surface shape control will often be required. A conceptual development plan of a system software capability for use in analysis of the dynamics and control of large space structures technology (LSST) systems is discussed. This concept can be subdivided into four different stages: (1) system dynamics; (2) structural dynamics; (3) application of control algorithms; and (4) simulation of environmental disturbances. Modeling the system dynamics of such systems in orbit is the most fundamental component. Solar radiation pressure effects and orbital and gravity gradient effects are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center Structural Dyn. and Control of Large Space Struct., 1982; p 91-110
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  • 51
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    An analytical investigation of shape control of large space structures by applied temperatures (1983)
    In:  Other Sources
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    Publication Date: 2018-12-01
    Description: An analytical procedure for the static shape control of flexible space structures subjected to thermal distortions is developed which is based on prescribing temperatures in control elements having much higher coefficients of thermal expansion than the main structure. The temperatures at the control elements are defined so as to minimize the overall thermal distortion of the structure from its ideal shape, and a matrix equation is obtained which can be solved for the set of optimum control temperatures. A formulation of the procedure for continuous structures governed by differential equations and a formulation for discrete (finite element modeled) structures governed by matrix equations are presented. The equations from the continuous formulation are employed for the shape control of a simple beam distorted by nonuniform heating, and the discrete formulation is applied in a general purpose finite-element structural analysis computer program for the shape control of a 750 m radiometer antenna reflector dish subjected to orbital heating. A reduction in thermal distortion by a factor of nearly 50 was obtained with the use of only seven control elements. Results for four different sets of control locations for the antenna are presented in which reductions in distortion of up to a factor of four were obtained.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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    Study of robotics systems applications to the space station program (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Applications of robotics systems to potential uses of the Space Station as an assembly facility, and secondarily as a servicing facility, are considered. A typical robotics system mission is described along with the pertinent application guidelines and Space Station environmental assumptions utilized in developing the robotic task scenarios. A functional description of a supervised dual-robot space structure construction system is given, and four key areas of robotic technology are defined, described, and assessed. Alternate technologies for implementing the more routine space technology support subsystems that will be required to support the Space Station robotic systems in assembly and servicing tasks are briefly discussed. The environmental conditions impacting on the robotic configuration design and operation are reviewed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-173703 , NAS 1.26:173703 , KTR-108
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    Space station needs, attributes, and architectural options. Volume 1. Executive summary (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The initial space station should be manned, placed in 28.5 deg orbit, and provide substantial economic, performance, and social benefits. The most beneficial space station capabilities include: a space test facility; a transport harbor; satellite servicing and assembly; and an observatory. A space industrial park could be added once further development effort validates the cost and expanding commercial market for space processed materials. The potential accrued gross mission model benefit derived from these capabilities is $5.9B without the industrial park, and $9.3B with it. An unclassified overview of all phases of the study is presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-173710 , NAS 1.26:173710 , SA-SSP-RP007
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    Space station needs, attributes and architectural options. Volume 3, attachment 1, task 1: Mission requirements (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The development and systems architectural requirements of the space station program are described. The system design is determined by user requirements. Investigated topics include physical and life science experiments, commercial utilization, U.S. national security, and remote space operations. The economic impact of the space station program is analyzed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-173716 , NAS 1.26:173716 , LMSC/D889718-VOL-3/1-TASK-1
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    Space station needs, attributes and architectural options study (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: All the candidate Technology Development missions investigated during the space station needs, attributes, and architectural options study are described. All the mission data forms plus additional information such as, cost, drawings, functional flows, etc., generated in support of these mission is included with a computer generated mission data form.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-173699 , NAS 1.26:173699 , D180-27477-7-VOL-7-3
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  • 56
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    Space station needs, attributes, and architectural options: Technology development (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The technology development of the space station is examined as it relates to space station growth and equipment requirements for future missions. Future mission topics are refined and used to establish a systems data base. Technology for human factors engineering, space maintenance, satellite design, and laser communications and tracking is discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-173697 , NAS 1.26:173697 , MDC-H0538
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  • 57
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    Tanker orbit transfer vehicle and method (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method and apparatus for transportation between orbits are presented. A tanker orbit transfer vehicle includes two stages each of which includes a fuel container. The first stage may be left in an intermediate parking orbit while the second stage goes on to carry out a mission, thereafter to return to rendezvous and dock with the first stage. Fuel carried by the first stage may be utilized for travel of the two stages between the starting orbit and the parking orbit, and for return to the starting orbit. An aerobrake may be included in the system for use in the return to the initial orbit.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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    Development of deployable structures for large space platforms. Volume 2: Design development (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Design evolution, test article design, test article mass properties, and structural analysis of deployable platform systems are discussed. Orbit transfer vehicle (OTV) hangar development, OTV hangar concept selection, and manned module development are discussed. Deployable platform systems requirements, material data base, technology development needs, concept selection and deployable volume enclosures are also discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-170914 , NAS 1.26:170914 , SSD-83-0094-2-VOL-2
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  • 59
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    Observations of charging dynamics (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Plasma data from the University of California, San Diego, Auroral Particles experiments on Applied Technology satellites 5 and 6 are used to investigate the dynamics of natural charging events. Both eclipse and daylight charging events are considered, and typical responses are illustrated by data from specific events. Two different physical processes are found to be involved in the charging process. One of these is straightforward: the spacecraft structure potential responds rapidly to changes in the environment, typically changing by hundreds of volts in a few seconds. The other process is more subtle: differential charging and potential barrier formation precede structural charging and determine the time scale; typically, tens of minutes are required for the potential to change by several hundreds of volts. The latter process is found to be predominately responsible for daylight charging on both spacecraft.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Geophysical Research (ISSN 0148-0227); 88; July 1
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  • 60
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    Benefits and costs of low thrust propulsion systems (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The results of costs/benefits analyses of three chemical propulsion systems that are candidates for transferring high density, low volume STS payloads from LEO to GEO are reported. Separate algorithms were developed for benefits and costs of primary propulsion systems (PPS) as functions of the required thrust levels. The life cycle costs of each system were computed based on the developmental, production, and deployment costs. A weighted criteria rating approach was taken for the benefits, with each benefit assigned a value commensurate to its relative worth to the overall system. Support costs were included in the costs modeling. Reference missions from NASA, commercial, and DoD catalog payloads were examined. The program was concluded reliable and flexible for evaluating benefits and costs of launch and orbit transfer for any catalog mission, with the most beneficial PPS being a dedicated low thrust configuration using the RL-10 system.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-1248
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    Space station propulsion system trade study (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: This study evaluates alternative space station propulsion system options for a range of space station configurational and operational architectures. Space station propulsion requirements ranging from those representative of the first generation space station to those of an advanced space station with a space based OTV are considered. A methodology for comparing the candidate propulsion technologies is developed which considers design/development/qualification and operational costs, system mass, performance, reliability, and other relevant parameters. Advanced propulsion systems are shown to reduce space station costs by providing higher performance but to require a larger front end investment for development and qualification. This study indicates that if the full potential of such systems is to be realized, then low cost implementations of this technology must be developed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-1220
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    Hypersonic shock tunnel heat transfer tests of the Space Shuttle SILTS pod configuration (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Heat transfer measurements have been made on a 0.0175-scale NASA Space Shuttle orbiter model having a simulated SILTS (Shuttle Infrared Leeside Temperature Sensor) pod on top of the vertical tail. Heat transfer distributions were measured both on the pod and on the vertical tail. The test program covered Mach numbers of 8, 11 and 16 in air, at Reynolds numbers from 100,000 to 18 million, based on model length. The angle of attack ranged from 30 deg to 40 deg at sideslip angles from -2 to +2 deg. Data were obtained with 92 thin film assistance thermometers located on the SILTS pod and on the upper 30 percent of the vertical tail. Heat transfer rates measured on the vertical tail show good agreement with flight data obtained from missions STS-1, -2 and -3. The variation of heat transfer to the pod with Reynolds number, Mach number and angle of attack is discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-1535
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    Effects of nonequilibrium and surface catalysis on Shuttle heat transfer - A review (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: It is pointed out that the Space Shuttle Orbiter is a hypersonic glide reentry vehicle which spends much of its entry time at relatively tenuous altitudes in which chemical nonequilibrium predominates in the shock layer. On the windward side, dissociation nonequilibrium exists in the inviscid layer and recombination nonequilibrium exists in the boundary layer. The present investigation is concerned with an evaluation of various flowfield predictions, taking into account a comparison of equilibrium and nonequilibrium flowfields coupled with reacting axisymmetric analog boundary-layer solutions and the results of viscous-shock-layer solutions with flight temperature/heat-flux measurements near the windward centerline for the Shuttle flights STS-2, STS-3, and STS-5.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-1485
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  • 64
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    Weight trends for a fully reusable advanced single-stage Shuttle (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The rate at which subsystem weights grow with vehicle gross weight is assessed and is shown to be critical to the efficiency of large earth-to-orbit transports. Some subsystems grow as the square of vehicle size, others grow as the cube of vehicle size, and still others remain nearly constant irrespective of vehicle size. The overall trend, however, is a reduction in the inerts as a percentage of gross as the vehicle size is increased. For this reason, the larger the vehicle, the greater the payload weight delivered per pound of vehicle manufactured. Other critical issues addressed include the effects of wing loading and wing size on wing weight, the effect of entry planform loading on thermal protection system weight, the impact of power demand on cooling system and prime power weight, and tank fineness ratio on insulation weight. The effects of body shape and various internal packaging arrangements on weight and balance are also discussed. Of greatest impact on overall vehicle weight is body shape and internal packaging and could account for weight savings of up to 30 percent in body structure. Other subsystems are important but the savings are much smaller in relation to overall vehicle weight - individually less than one percent.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAWE PAPER 1554
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  • 65
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    Subsatellite studies of wave, plasma, and chemical injections from Spacelab (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Previously cited in issue 06, p. 822, Accession no. A82-17775
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: (ISSN 0022-4560)
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  • 66
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    Cryogenic fluid management experiment trunnion fatigue verification (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A subcritical liquid hydrogen orbital storage and transfer experiment was designed for flight in the Shuttle cargo bay. The Cryogenic Fluid Management Experiment (CFME) includes a liquid hydrogen tank supported in a vacuum jacket by two fiberglass epoxy trunnion mounts. This composite material was selected for the trunnions since it provides desirable strength, weight and thermal characteristics for supporting cryogenic tankage. An experimental program was conducted to provide material property and fatigue data for S-glass epoxy composite materials at ambient and liquid hydrogen temperatures and to verify structural integrity of the CFME trunnion supports.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-0911
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  • 67
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    Thermal-protection requirements for near-earth aero-assisted orbital-transfer vehicle missions (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The thermal protection required for decelerating and maneuvering spacecraft by aerodynamic forces is determined for return missions from geosynchronous to low-earth orbits. The effect of vehicle configuration on surface heating rates and selection of heat-shield materials is analyzed. Effects of the current widespread estimates in the structure of atmospheric density are also evaluated. It is shown that nonequilibrium radiation can be a major source of surface heating during atmospheric entry and a significant factor to heat-shielding requirements. It is also demonstrated that drag-brake concepts have application to a broad range of orbital-transfer missions, because of the favorable trade-offs with aeromaneuvering vehicles in volumetric efficiency, retrothrust plane-change capability, and heat-protection requirements. In addition, the results of this study indicate that the aero-assist technique produces small penalties in vehicle payload capacity for drag-brake concepts, because of the system's heat protection requirements, and is highly attractive relative to all-propulsive orbital-change maneuvers.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-1513
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  • 68
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    Aerothermodynamic design considerations of an aerobraked spacecraft (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The major aerothermodynamic design issues that influenced the VOIR (Venus Orbiting Image Radar) airbrake and mission design are discussed. In the discussion of aerobrake heating, it is pointed out that the heat transfer to the deployed aerobrake is a function of the flow regime encountered during the periapsis pass, the perapsis altitude, and the brake surface geometry. The discussion of spacecraft thermal protection encompasses separated flow heating, aerobrake backface radiation, total solar cell heating, and undeployed aerobrake effects. The aerobrake is designed to protect the spacecraft thermally by limiting the integrated entry heating to the critical solar cell arrays (located on three sides of the spacecraft) due to flow impingement heating, separated flow heating, and backface radiation heating. It is explained that these design considerations led to the selection of a flat-faced aerobrake design located on the front of the spacecraft to provide maximum spacecraft thermal protection. The 8.4-m equivalent diameter aerobrake eliminates direct flow impingement heating and lowers separated flow heating on the spacecraft.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-1510
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  • 69
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    A study of space station needs, attributes, and architectural options, volume 2, technical. Book 2: Mission implementation concepts (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Space station systems characteristics and architecture are described. A manned space station operational analysis is performed to determine crew size, crew task complexity and time tables, and crew equipment to support the definition of systems and subsystems concepts. This analysis is used to select and evaluate the architectural options for development.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-173690 , NAS 1.26:173690 , GDC-ASP-83-003
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  • 70
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    Space station needs, attributes and architectural options study. Volume 7-5A: Data book. Mission analysis part A (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The mission analysis printouts for the mission driven scenario A-1 are presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-173701 , NAS 1.26:173701 , D180-27477-7-VOL-7-5A
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  • 71
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    Space station needs, attributes and architectural options study. Volume 7-4B: Data book, architecture, technology and programmatics, part B (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The remote manipulating system, the pointing control system, and the external radiator for the core module of the space station are discussed. The principal interfaces for four basic classes of user and transportation vehicles or facilities associated with the space station were examined.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-173685 , NAS 1.26:173685 , D180-27477-7-VOL-7-4B
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  • 72
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    Space station needs, attributes and architectural options study. Volume 7-2: Data book. Commercial missions (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The history of NASA's materials processing in space activities is reviewed. Market projections, support requirements, orbital operations issues, cost estimates and candidate systems (orbiter sortie flight, orbiter serviced free flyer, space station, space station serviced free flyer) for the space production of semiconductor crystals are examined. Mission requirements are identified for materials processing, communications missions, bioprocessing, and for transferring aviation maintenance training technology to spacecraft.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-173719 , NAS 1.26:173719 , D180-27477-7-VOL-7-2
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  • 73
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    Space station needs, attributes, and architectural options: Mission requirements (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Space station missions and their requirements are discussed. Analyses of the following four mission categories are summarized: (1) commercial, (2) technology, (3) operation, and (4) science and applications. The requirements determined by the study dictate a very strong need for a manned space station to satisfy the majority of the missions. The station is best located at a 28.5-deg inclination and initially (1992 era) requires a crew of four (three for mission payloads) and a mission power of 25 kW. A space platform in a polar orbit is needed to augment the station capability; it initially would be a 15-kW system, located in a sun-synchronous orbit.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-173693 , NAS 1.26:173693 , MDC-H0533
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  • 74
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    Orbiter-based construction equipment study. The HPA/DTA technology advancement plan (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Satellite berthing mechanism, umbilicals for fluid and electrical interfaces, EVA service platform, and large mass berthing mechanism are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-174605 , NAS 1.26:174605 , DRL-T-1701 , DRD-SE957T
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  • 75
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    Shuttle measured contaminant environment and modeling for payloads. Preliminary assessment of the space telescope environment in the shuttle bay (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A baseline gaseous and particulate environment of the Shuttle bay was developed based on the various measurements which were made during the first four flights of the Shuttle. The environment is described by the time dependent pressure, density, scattered molecular fluxes, the column densities and including the transient effects of water dumps, engine firings and opening and closing of the bay doors. The particulate conditions in the ambient and on surfaces were predicted as a function of the mission time based on the available data. This basic Shuttle environment when combined with the outgassing and the particulate contributions of the payloads, can provide a description of the environment of a payload in the Shuttle bay. As an example of this application, the environment of the Space Telescope in the bay, which may be representative of the environment of several payloads, was derived. Among the many findings obtained in the process of modeling the environment, one is that the payloads environment in the bay is not substantially different or more objectionable than the self-generated environment of a large payload or spacecraft. It is, however, more severe during ground facilities operations, the first 15 to 20 hours of the flight, during and for a short period after ater was dumped overboard, and the reaction control engines are being fired.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-85111 , NAS 1.15:85111
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  • 76
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    Design for temperature and thermal buckling constraints employing a noneigenvalue formulation (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A numerical procedure for simultaneous consideration of structural/thermal interactions during aircraft design is presented, with an emphasis on reentry vehicles such as the Orbiter. It has been shown that sequential design is inappropriate for reentry vehicles, due to the degradation of the material properties at elevated reentry temperatures. Attention is focused on thermal buckling, using an analytical technique that involves requiring that the stability matrix be positive definite, with the diagonal terms on the Gauss-Doolittle factor of the matrix also constrained to be positive. A finite element method is employed to calculate the derivative of the diagonal matrix, with optimization achieved by minimization of the mass of the structure and thermal protection system. Sample calculations are presented in terms of the aluminum structure and insulation for a section of the Orbiter wing bay.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: (ISSN 0022-4560)
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  • 77
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    Conceptual design and evaluation of selected Space Station concepts, volume 2 (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The partially closed cycle environmental control and Life Support Subsystems is examined. Components of the system include air pressure control, heat control, water management, air and water quality monitors, fire detection and suppression, personnel escape, and EVA support subsystems.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-87384 , JSC-19521-VOL-2 , NAS 1.15:87384
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  • 78
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    Conceptual design and evaluation of selected Space Station concepts, volume 1 (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Space Station configuration concepts are defined to meet the NASA Headquarters Concept Development Group (CDG) requirements. Engineering and programmatic data are produced on these concepts suitable for NASA and industry dissemination. A data base is developed for input to the CDG's evaluation of generic Space Station configurations and for use in the critique of the CDG's generic configuration evaluation process.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-87383 , JSC-19521-VOL-1 , NAS 1.15:87383
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  • 79
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    Conceptual design and evaluation of selected Space Station concepts: Executive summary (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of a space station conceptual design and evaluation study are summarized. The study represented a temporary focusing. Three space station configurations are characterized for user and crew requirements, operation and safety accommodations, engineering considerations including assembly and growth, structural dynamics, communications, thermal control and power systems, as well as system cost.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-87382 , JSC-19521-EXEC-SUMM , NAS 1.15:87382
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  • 80
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    Space station: Cost and benefits (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Costs for developing, producing, operating, and supporting the initial space station, a 4 to 8 man space station, and a 4 to 24 man space station are estimated and compared. These costs include contractor hardware; space station assembly and logistics flight costs; and payload support elements. Transportation system options examined include orbiter modules; standard and extended duration STS fights; reusable spacebased perigee kick motor OTV; and upper stages. Space station service charges assessed include crew hours; energy requirements; payload support module storage; pressurized port usage; and OTV service facility. Graphs show costs for science missions, space processing research, small communication satellites; large GEO transportation; OVT launch costs; DOD payload costs, and user costs.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-173718 , NAS 1.26:173718 , SSD-83-0045 , RI-33SSV133636
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  • 81
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    Space station needs, attributes and architectural options. Volume 3, task 1: Mission requirements (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The mission requirements of the space station program are investigated. Mission parameters are divided into user support from private industry, scientific experimentation, U.S. national security, and space operations away from the space station. These categories define the design and use of the space station. An analysis of cost estimates is included.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-173712 , NAS 1.26:173712 , LMSC/D889718-VOL-3-TASK-1
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  • 82
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    A study of space station needs, attributes and architectural options. Final briefing: Cost working group discussion session (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The economic factors involved in the design and utilization of the space station are investigated. Topics include the economic benefits associated with research and production, the orbit transfer vehicle, and satellite servicing. Program costs and design options are examined. The possibilities of financing from the private sector are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-173713 , NAS 1.26:173713
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  • 83
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    Space station needs, attributes, and architectural options: Space station program cost analysis (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report documents the principal cost results (Task 3) derived from the Space Station Needs, Attributes, and Architectural Options study conducted for NASA by the McDonnell Douglas Astronautics Company. The determined costs were those of Architectural Options (Task 2) defined to satisfy Mission Requirements (Task 1) developed within the study. A major feature of this part of the study was the consideration of realistic NASA budget constraints on the recommended architecture. Thus, the space station funding requirements were adjusted by altering schedules until they were consistent with current NASA budget trends.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-173696 , NAS 1.26:173696 , MDC-H0541
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  • 84
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    Thermally induced spin rate ripple on spacecraft with long radial appendages (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A thermally induced spin rate ripple hypothesis is proposed to explain the spin rate anomaly observed on ISEE-B. It involves the two radial 14.5 meter beryllium copper tape ribbons going in and out of the spacecraft hub shadow. A thermal lag time constant is applied to the thermally induced ribbon displacements which perturb the spin rate. It is inferred that the averaged thermally induced ribbon displacements are coupled to the ribbon angular motion. A possible exponential build up of the inplane motion of the ribbon which in turn causes the spin rate ripple, ultimately limited by damping in the ribbon and spacecraft is shown. It is indicated that qualitative increase in the oscillation period and the thermal lag is fundamental for the period increase. found that numerical parameter values required to agree with in orbit initial exponential build up are reasonable; those required for the ripple period are somewhat extreme.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-85058 , NAS 1.15:85058
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  • 85
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    Capture-ejector satellites (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A satellite in the form of a large rotating rim which can be used to boost spacecraft from low-Earth orbit to higher orbits is described. The rim rotates in the plane of its orbit such that the lower portion of the rim is traveling at suborbital velocity, while the upper portion is travelling at greater than orbital velocity. Ascending spacecraft or payloads arrive at the lowest portion of the rim at suborbital velocities, where the payloads are released on a trajectory for higher orbits; descending payloads employ the reverse procedure. Electric thrusters placed on the rim maintain rim rotational speed and altitude. From the standpoint of currently known materials, the capture-ejector concept may be useful for relatively small velocity increments.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-85686 , NAS 1.15:85686
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  • 86
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    Development of deployable structures for large space platform systems. Volume 1: Executive summary (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The preponderance of study effort was devoted toward the deployable platform systems study which culminated in the detailed design of a ground test article for future development testing. This design is representative of a prototype square-truss, single-fold building-block design that can construct deployable platform structures. This prototype design was selected through a comprehensive and traceable selection process applied to eight competitive designs. The selection process compared the competitive designs according to seven major selection criteria, i.e., design versatility, cost, thermal stability, meteoroid impact significance, reliability, performance predictability, and orbiter integration suitability. In support of the foregoing, a materials data base, and platform systems technology development needs were established. An erectable design of an OTV hangar was selected and recommended for further design development. This design was selected from five study-developed competitive single-fold and double-fold designs including hard-shell and inflatable designs. Also, two deployable manned module configurations, i.e., a hard-shell and an inflatable design were each developed to the same requirements as the composite of two Space station baseline habitat modules.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-170913 , NAS 1.26:170913 , SSD-83-0094-1-VOL-1
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  • 87
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    Interactive analysis of a large aperture Earth Observations Satellite (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A system level design and analysis has been conducted on an Earth Observation Satellite (EOS) system using the Interactive Design and Evaluation of Advanced Spacecraft (IDEAS) computer-aided design and analysis program. The IDEAS program consists of about 40 user-friendly technical modules and an interactive graphics display. The reflector support system and feed mast of the EOS spacecraft are constructed with a box-truss structural concept, a lattice configuration which can be packaged for delivery in a single Shuttle flight and deployed in orbit. The deployed spacecraft consists of a 120-m by 60-m parabolic reflector, a 120-m-long support structure, and a 30-m feed arc beam on the focal axis. The spacecraft was modeled for structural, thermal, and control systems analysis and structural elements were designed. On-orbit dynamic and thermal loading analyses were conducted and spacecraft weights were determined.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAWE PAPER 1556
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  • 88
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    Initial '80s Development of Inflated Antennas (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: State of the art technology was considered in the definition and documentation of a membrane surface suitable for use in a space reflector system for long durations in orbit. Requirements for a metal foil-plastic laminate structural element were determined and a laboratory model of a rigidized element to test for strength characteristics was constructed. Characteristics of antennas ranging from 10 meters to 1000 meters were determined. The basic antenna configuration studied consists of (1) a thin film reflector, (2) a thin film cone, (3) a self-rigidizing structural torus at the interface of the cone and reflector; and (4) an inflation system. The reflector is metallized and, when inflated, has a parabolic shape. The cone not only completes the enclosure of the inflatant, but also holds the antenna feed at its apex. The torus keeps the inflated cone-reflector from collapsing inward. Laser test equipment determined the accuracy of the inflated paraboloids.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-166060 , NAS 1.26:166060 , LTR-82-GF-107
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  • 89
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    Attitude control and drag compensation propulsion system for Gravity Probe-B spacecraft (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An on board propulsion system for attitude control and drag compensation is presented which uses helium boiloff gas from an experiment package dewar as propellant. This boiloff gas would normally be vented nonpropulsively. Use of a small allowable temperature range in the dewar is exploited to store helium and accommodate incompatibilities in dewar heat leak and thruster demand flow over periods of more than one orbit. A relatively detailed thermodynamics analysis of the two phase helium dewar and simulation of pressure loss through the helium distribution system is included.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-82517 , NAS 1.15:82517
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  • 90
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    Ablation of carbonaceous materials in a hydrogen-helium arc-jet flow (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The stagnation-point ablation rates of a graphite, a carbon-carbon composite, and four carbon-phenolic materials are measured in an arc-jet wind tunnel with a 50% hydrogen-50% helium mixture as the test gas. Flow environments are determined through measurements of static and impact pressures, heat-transfer rates to a calorimeter, and radiation spectra, and through numerical calculation of the flow through the wind tunnel, spectra, and heat-transfer rates. The environments so determined are: impact pressure approx. 3 atm, Mach number approx. 2.1, convective heat-transfer rate approx. 14 kw/sq cm, and radiative heat-transfer rate approx. 7 kw/sq cm in the absence of ablation. Ablation rates are determined from the measured rates of mass loss and recession of the ablation specimens. Compared with the predicted ablation rates obtained by running RASLE and CMA codes, the measured rates are higher by about 15% for all tested materials.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-84346 , A-9286 , NAS 1.15:84346
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  • 91
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    Performance of an ablator for Space Shuttle inorbit repair in an arc-plasma airstream (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An ablator patch material performed well in an arc plasma environment simulating nominal Earth entry conditions for the Space Shuttle. Ablation tests using vacuum molded cones provided data to optimize the formulation of a two part polymer system for application under space conditions. The blunt cones were made using a Teflon mold and a state of the art caulking gun. Char stability of formulations with various amounts of catalyst and diluent were investigated. The char was found to be unstable in formulations with low amounts of catalyst and high amounts of diluent. The best polymer system determined by these tests was evaluated using a half tile patch in a multiple High Temperature Reusable surface Insulation tile model. It was demonstrated that this ablator could be applied in a space environment using a state of the art caulking gun, would maintain the outer mold line of the thermal protection system during entry, and would keep the bond line temperature at the aluminum tile interface below the design limit.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-2150 , A-9112 , NAS 1.60:2150
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  • 92
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    Passive Orbital Disconnect Strut (PODS 3), structural and thermal test program (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A test program is undertaken to verify that the lifetime of a shuttle launchable dewar can be increased by using passive orbital disconnect struts (PODS). A detailed design is performed on the cold end (PODS-III) portion of the strut. Structural analysis of the thin-wall fiberglass tube allows selection of the optimum winding angle and tube dimensions. Structural tests on the thin-wall fiberglass tube measure both the tension and compression modulus at ambient and LN2 temperatures, the radial deflection versus side load, and the ultimate compression strength of the tube at LN2 temperature. The thermal expansion of the fiberglass tube plus Invar is also measured down to 78 K. The axial gap at the wedge portion of the stem is set based on these data. The PODS-III test article parts are fabricated and assembled using a detailed assembly procedure. The thermal conductants in the orbital configuration was measured for body temperatures between 5 and 40 K. This temperature range covers the predicted ground hold and orbit temperatures for vapor-cooled supports. The test results are then compared with heat leak values predicted before the test began. Side load, axial compression load, and tension load tests conclude the test program.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-166473 , NAS 1.26:166473
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  • 93
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    Space station needs, attributes and architectural options study system working group briefing (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Space Transportation System assumptions, trades, manifesting, buildup, characteristics, and ground operations are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-172952 , NAS 1.26:172952
    Format: application/pdf
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  • 94
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    Space station needs, attributes and architectural options study mission requirement working group briefing (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Requirements sources, requirements flow, orbit selection mission model, key missions, integrated, phased requirements, and mission benefits are addressed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-172951 , NAS 1.26:172951
    Format: application/pdf
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  • 95
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    Space station needs, attributes and architectural options study costing working group briefing (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The interface between tasks and the sequence of information flow are charted. The mission model and the requirements of each mission. These requirements along with the mission model schedule resulted in a further definition of the mission payloads, the Space Station architecture and the STS requirements was developed in task 2. The information was used to estimate the cost parameters necessary to generate cost estimates for the system with the aid of cost models for the Missions, Space Station and Space Transportation.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-172950 , NAS 1.26:172950
    Format: application/pdf
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  • 96
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    Space station needs, attributes and architecture options study technology development working group briefing (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The structural criteria for a space station is lack of risk by the technology employed. Orbiter technology can be transferred for use in construction with improvement in three areas: fiber optic data bus, water reclamation, and; improved space suit design.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-172949 , NAS 1.26:172949
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  • 97
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    Space station needs, attributes and architectural options study review report (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A manned space station (SS) produces a significant net economic benefit over its cost, as well as providing substantial social and performance benefits. The largest space station benefits arise from the ability of the SS to warehouse parts, orbit replacement units (ORUs) and fuel and thereby increase the Space Transportation System (STS) load factor. Substantial other benefits are made possibly by the basing of a returnable orbital transfer vehicles (ROTV) and the servicing of geosynchronous Earth orbit (GEO) satellites at the SS. It is recommended that a manned space station be placed in a 28.5 degree inclination orbit in 1990. This SS can be designed to grow, to be maintained and to incorporate new technology as it becomes available. It should be augmented with unmanned space platforms at both 28.5 degree and polar inclinations. These platforms are designed to have very high commonality with the SS resource models.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-172947 , NAS 1.26:172947
    Format: application/pdf
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  • 98
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    Analysis of gap heating due to stepped tiles in the shuttle thermal protection system (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Analytical methods used to investigate entry gap heating in the Shuttle orbiter thermal protection system are described. Analytical results are given for a fuselage lower-surface location and a wing lower-surface location. These are locations where excessive gap heating occurred on the first flight of the Shuttle. The results of a study to determine the effectiveness of a half-height ceramic fiber gap filler in preventing hot-gas flow in the tile gaps are also given.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-2209 , L-15636 , NAS 1.60:2209
    Format: application/pdf
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  • 99
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    Space station needs, attributes and architectural options study commercialization working group briefing (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The benefits for each of the following commercial areas was investigated: communications, remote sensing, materials processing in space, low Earth orbit (LEO) satellite assembly, testing, and servicing, and space tourism. In each case, where economic benefits are derived, the costs for accomplishing tasks with the Space Station are compared with the cost with the Space Transportation System only.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-172948 , NAS 1.26:172948
    Format: application/pdf
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  • 100
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    The measurements of vehicle glow on the Space Shuttle (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: From the combined data set of glow observations on STS-3, STS-4 and STS-5 some of the properties of the shuttle glow were observed. Comparison of the STS-3 (240 km) and STS-5 (305 km) photographs show that the intensity of the glow is about a factor of 3.5 brighter on the low altitude (STS-3) flight. The orbiter was purposely rotated about the x axis in an experiment on STS-5 to observe the dependence of the intensity on the angle of incidence between the spacecraft surface normal and the velocity vector. For a relatively large angle between the velocity vector and the surface normal there is an appreciable glow, provided the surface is not shadowed by some other spacecraft structure. As the angle becomes less the glow intensifies. The grating experiments (STS-4 photography only, STS-5 image intensifier photography) provided a preliminary low resolution spectra of the spacecraft glow. Accurate wavelength calibrations of the STS-5 instrument permitted measuring of the spectrum and intensity of the Earth's airglow.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-85360 , NAS 1.15:85360 , LMSC-D940124
    Format: application/pdf
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