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  • Other Sources  (2,908)
  • NASA Technical Reports  (2,908)
  • AIRCRAFT PROPULSION AND POWER  (1,211)
  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (948)
  • SPACECRAFT PROPULSION AND POWER  (749)
  • 1975-1979  (2,908)
  • 1900-1904
Collection
  • Other Sources  (2,908)
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  • NASA Technical Reports  (2,908)
Keywords
Years
Year
  • 1
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    Aircraft Energy Efficiency (ACEE) status report (1979)
    In:  CASI
    Details
    Publication Date: 2009-11-17
    Description: Fuel efficiency in aeronautics, for fuel conservation in general as well as for its effect on commercial aircraft operating economics is considered. Projects of the Aircraft Energy Efficiency Program related to propulsion are emphasized. These include: (1) engine component improvement, directed at performance improvement and engine diagnostics for prolonged service life; (2) energy efficient engine, directed at proving the technology base for the next generation of turbofan engines; and (3) advanced turboprop, directed at advancing the technology of turboprop powered aircraft to a point suitable for commercial airline service. Progress in these technology areas is reported.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 1-58
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  • 2
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    Application of numerical optimization techniques to high speed inlet bleed system design (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-10
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Inlet Workshop; p 280-287
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  • 3
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    Nonlinear effects in thermal stress analysis of a solid propellant rocket motor (1976)
    In:  CASI
    Details
    Publication Date: 2006-08-09
    Description: Direct characterization procedures were used to determine the relaxation modulus as a function of time, temperature, and state of strain. Using the quasi-elastic method of linearviscoelasticity, these properties were employed in a finite element computer code to analyze a thick-walled, nonlinear viscoelastic cylinder in the state of plane strain bonded to a thin (but stiff) elastic casing and subjected to slow thermal cooling. The viscoelastic solution is then expressed as a sequence of elastic finite element solutions. The strain-dependent character of the relaxation modulus is included by replacing the single relaxation curve used in the linear viscoelastic theory by a family of relaxation functions obtained at various strain levels. These functions may be regarded as a collection of stress histories or responses to specific loads (in this case, step strains) with which the cooldown solution is made to agree by iterations on the modulus and strain level.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center Advan. in Eng. Sci., Vol. 1; p 111-135
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  • 4
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    High-performance-vehicle technology (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Propulsion needs of high performance military aircraft are discussed. Inlet performance, nozzle performance and cooling, and afterburner performance are covered. It is concluded that nonaxisymmetric nozzles provide cleaner external lines and enhanced maneuverability, but the internal flows are more complex. Swirl afterburners show promise for enhanced performance in the high altitude, low Mach number region.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 445-462
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  • 5
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    Vertical Takeoff and Landing (VTOL) propulsion technology (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Propulsion problems and advanced technology requirements of VTOL aircraft are discussed. Specific topics covered include inlets with high angle of attack capability, rapid thrust modulation fans, and propulsion-system/aircraft-control integration.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 409-444
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  • 6
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    Hypersonic propulsion (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Research on hydrogen fueled scramjet engines for hypersonic flight is reviewed. Component developments, computational methods, and preliminary ground tests of subscale scramjet engine modules at Mach 4 and 7 are emphasized. Airframe integration, structures, and flow diagnostics are also discussed. It is shown that mixed-mode perpendicular and parallel fuel injection controls heat release over a wide Mach range and the fixed geometry inlet gives good performance over a wide range of Mach numbers.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 387-408
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  • 7
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    Control technology (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: An overview of engine control technology is presented with emphasis on gas turbine engine controls. The role of the government, and NASA in particular, in advancing this technology is discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 329-344
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  • 8
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    Supersonic propulsion technology (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Propulsion concepts for commercial supersonic transports are discussed. It is concluded that variable cycle engines, together with advanced supersonic inlets and low noise coannular nozzles, provide good operating performance for both supersonic and subsonic flight. In addition, they are reasonably quiet during takeoff and landing and have acceptable exhaust emissions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 345-386
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  • 9
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    Mechanical components (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Research on bearings, gears, seals, and rotor dynamics (specifically high speed balancing and dampers) is presented. The research pertains to problems in both aircraft turbine engines and helicopter transmissions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 273-308
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  • 10
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    Instrumentation technology (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Some of the efforts made in applying technologically new tools to today's propulsion measurement problems are described. They include: (1) a blade-tip clearance system; (2) a pulsed thermocouple system used to measure gas temperature with a thermocouple at temperatures above the melting point of the thermocouple; (3) an optical technique for measuring blade flutter; (4) a probe for dynamic flow and flow angle measurement; and (5) a laser anemometer system for rapidly mapping the flow profiles between the blades of a rotating compressor.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 309-328
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  • 11
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    Turbomachinery technology (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: A technology assessment of turbomachinery is presented. The design of the fan, compressor, and turbine components for future advanced aircraft engines is discussed. Basic flow characteristics in compressors and turbines and the heat transfer phenomena in cooled turbines are also discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 231-272
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  • 12
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    Computational fluid mechanics of internal flow (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Major solution techniques for internal computational fluid mechanics are discussed and some examples are presented. The major steps involved in developing a large computer code are then discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 187-230
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  • 13
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    Alternative jet aircraft fuels (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Potential changes in jet aircraft fuel specifications due to shifts in supply and quality of refinery feedstocks are discussed with emphasis on the effects these changes would have on the performance and durability of aircraft engines and fuel systems. Combustion characteristics, fuel thermal stability, and fuel pumpability at low temperature are among the factors considered. Combustor and fuel system technology needs for broad specification fuels are reviewed including prevention of fuel system fouling and fuel system technology for fuels with higher freezing points.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 129-148
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  • 14
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    Materials and structures technology (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Materials and structures performance limitations, particularly for the hot section of the engine in which these limitations limit the life of components, are considered. Failure modes for components such as blades, vanes, and combustors and how they are affected by the environment for such components are discussed. Methods used to improve the materials used for such components are: (1) application of directional structures to turbine components for high strength at high temperatures; (2) improved coatings to increase oxidation and corrosion resistance; (3) increase strength and stiffness with reduced weight by applying higher specific properties of composite materials; and (4) cost effective processing such as near net shape powder methods applied to disks. Life prediction techniques developed to predict component life accurately in advance of service and progress in improving the intermediate and cold section components of turbine engines are covered.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 149-186
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  • 15
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    Noise reduction (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: The turbofan engine's noise-producing components are discussed in terms of efficient and economical noise reduction techniques that do not penalize the engine performance or weight significantly. Specific topics covered include fan noise, acoustic suppression, jet noise technology, combustor noise, and aircraft noise prediction.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 85-128
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  • 16
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    Emission reduction (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Control of the gaseous pollutant emissions of aircraft engines is considered in terms of the emission standards for six classes of aircraft engines. Emphasis is placed on combustor design concepts to significantly reduce emissions levels and lean-burning techniques to lower flame temperature, to reduce the oxides of nitrogen in the gaseous emissions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 59-84
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  • 17
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    Selected topics from the structural acoustics program for the B-1 aircraft (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: The major elements of the structural acoustics program for the B-1 aircraft are considered. Acoustic pressures measured at 280 sites on the surface of the vehicle were used to develop pressure models for a resizing of airframe components for aircraft No. 4 (A/C4). Acoustical fatigue design data for two dynamically complex structural configurations were acquired in laboratory programs, the conceptions for and executions of which detailed significant departures from the conventional. Design requirements for mechanical fasteners for configurations other than these two made use of analytical extensions of regrettably limited available information.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., Pt. 3; p 55-68
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  • 18
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    Vibration investigation of a large transport helicopter (1977)
    In:  CASI
    Details
    Publication Date: 2004-11-29
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull. Part 3 Sept. 1977; p 139-147
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  • 19
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    The plume impingement test program at AEDC utilizing the S-2 ullage motors (November 1973), section 1 (1976)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: Proposed experiments for analyzing rocket plumes are reported. Two groups of experiments were studied: (1) those that would help define some of the parameters that characterize the plume and (2) those that would enable evaluation of some of the contamination effects of the plume environment on various items of interest. The items investigated, the purpose of the investigation, are given in tabular form.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: The Effects of Solid Rocket Motor Effluents on Selected Surfaces and Solid Particle Size, Distribution, and Composition for Simulated Shuttle Booster Separation Motors; p 12-95
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  • 20
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    The small motor plume/material impingement test program at MSFC utilizing nine different propellant formulations (April and May 1974), section 2 (1976)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: The relative effects of several candidate SSRM propellant formulations and their plume impingement effects on HRSI and RCC materials were evaluated. Nine solid propellant formulations were tested. The selected propellant matrix allowed an evaluation of propellants with and without metal additives, with and without burning rate catalyst, and low (approximately 1927 C) and high (approximately 2649 C) combustion temperatures. Motors were fired at a simulated SRB staging altitude of 3.96 km (130,000 ft) (nominal). The altitude pressure was predicted to drop approximately 0.6 km (20,000 ft) during a motor firing. All motors were loaded with 1.8 to 2.3 kg (4 to 5 lb) of propellant and burned for approximately 2 s.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: The Effects of Solid Rocket Motor Effluents on Selected Surfaces and Solid Particle Size, Distribution, and Composition for Simulated Shuttle Booster Separation Motors; p 96-151
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  • 21
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    The large motor plume/material impingement test program at AEDC utilizing the four selected propellants from the small motor tests at MSFC (July, August, and September 1974), section 3 (1976)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: Efforts made to determine the vulnerability of Orbiter and ET materials located at various positions within exhaust plumes from test SSRM's using four different propellant formulations are discussed. Data also cover the effect on TPS materials from a single SSRM plume and dual SSRM plumes, and definitions of test SSRM plume environment at material specimen locations.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: The Effects of Solid Rocket Motor Effluents on Selected Surfaces and Solid Particle Size, Distribution, and Composition for Simulated Shuttle Booster Separation Motors; p 152-203
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  • 22
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    A new formulation for the epsilon method applied to the minimum-time-to-climb problem (1978)
    In:  CASI
    Details
    Publication Date: 2006-03-02
    Description: Balakrishnan's epsilon technique is used to compute minimum-time profiles for the F-104 airplane. This technique differs from the classical gradient method in that a quadratic penalty on the error in satisfying the equation of motion is included in the cost function to be minimized as a means of eliminating the requirement of satisfying the equations of motion. Although the number of unknown independent functions is increased to include the state variables, the evaluation of the gradient of the cost function is simplified, resulting in considerable computational savings, thereby making it appear feasible to use the epsilon method for real-time application.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Washington Fourth Inter-Center Control Systems Conf.; p 423-434
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  • 23
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    Optimal control of a supersonic inlet to minimize frequency of inlet unstart (1978)
    In:  CASI
    Details
    Publication Date: 2006-03-02
    Description: A preliminary investigation into the use of modern control theory for the design of controls for a supersonic inlet is described. In particular, the task of controlling a mixed-compression supersonic inlet is formulated as a linear optimal stochastic control and estimation problem. An inlet can exhibit an undesirable instability due to excessive inlet normal shock motion. For the optimal control formulation of the inlet problem, a non quadratic performance index, which is equal to the expected frequency of inlet unstarts, is used. This physically meaningful performance index is minimized for a range of inlet disturbance and measurement noise covariances.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA, Washington Fourth Inter-Center Control Systems Conf.; p 323-335
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  • 24
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    In-flight three-dimensional boundary layer and wake measurements from a swept supercritical wing (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: Three-dimensional boundary layer and wake velocity profiles were measured in flight on the supercritical wing of the F-111 transonic aircraft technology aircraft. These data, along with pressure distributions, were obtained to establish a data base with which data obtained by three-dimensional analytical techniques could be correlated. Only a brief summary of the total data base is given. The data presented represented one chord station at a wing leading-edge sweep angle of 26 deg. They cover an angle of attack range from 6 degs to 9 degs at free-stream Mach numbers from 0.85 to 0.90. A brief discussion of the techniques used to obtain the boundary layer and wake profiles is included.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 643-655
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  • 25
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    Aircraft engines (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Thrust and weight requirements of aircraft engines in general are discussed. The characteristics and operating principles of various types of air breathing and rocket engines are described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Soviet Aircraft and Rockets (NASA-TT-F-770); p 81-139
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  • 26
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    Proportioning the airplane for lateral stability (1976)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Proportioning for lateral aircraft control included: (1) directional stability (slope of curve of yawing moment coefficient against sideslip), and (2) effective dihedral factor (slope of curve of rolling moment coefficient against sideslip). Basic forces influencing the directional stability of aircraft are indicated. Propeller side force, basic fuselage yaw, and vertical tail side force contributed to yaw moment about center of gravity.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Collected Works of Charles J. Donlan; 6 p
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  • 27
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    Propellant mass usage and flow measurement (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Practices are outlined for the design, installation, checkout, calibration, and operation of a system to be used for measuring propellant flow in a liquid monopropellant rocket engine. Design guidelines rather than detailed specifications are provided for the critical components of each portion of the system. System elemental uncertainties are presented in an appendix.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Handbook of Recommended Practices for the Determination of Liquid Monopropellant Rocket Engine Performance; 32 p
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  • 28
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    Status of cavity noise phenomena measurement and suppression on the B-1 aircraft (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: During the B-1 aircraft development, an extensive program of weapons bay cavity noise measurement and suppression studies was performed using wind tunnel models, flight test measurements, and aircraft design modifications. Substantial cavity noise reduction was demonstrated during flight test operations. The unsuppressed cavity noise level of 170 dB was reduced to values less than 150 dB with external retractable spoilers upstream of the cavity opening.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., Pt 1; p 59-66
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  • 29
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    Basic stages in the development of the theory of Ramjet Engines (RJE) (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Basic periods in the history of the development of ramjet engine theory are cited. The periods include the first experimental tests as well as the development of basic ideas and theoretical development of the cosmic ramjet engine.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Washington Essays on the History of Rocketry and Astronautics, Vol. 1; p 229-238
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  • 30
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    Spin tests of 1/16-scale models of the N3N-3 landplane and seaplane, 12 January 1940 (1976)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: The test program included the study of both the seaplane and landplane types. On both versions of the model, the effects of loading changes and control dispositions were examined, and on the seaplane, the effect of the cowled and uncowled engine was investigated.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Collected Works of Charles J. Donlan; 37 p
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  • 31
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    Spin tests of a 1/20-scale model of the XF4U-1 airplane, 12 July 1939 (1976)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: These tests were performed to determine the spinning characteristics of the 1/20-scale model of the XF4U-1 airplane. Effects of loading changes and various control dispositions using both the original and modified vertical tail surfaces were studied. Subsequent tests were made to determine the effects of additional tail modifications.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Collected Works of Charles J. Donlan; 47 p
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  • 32
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    Pressure measurement (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Practices are outlined for the design, installation, checkout, calibration, and operation of a pressure measuring system to be used during tests of a liquid monopropellant rocket engine. Appendixes include: (1) pressure measurement system elemental uncertainties; (2) short- and long-term pressure measurement system uncertainty; (3) shunt calibration of pressure transducers; (4) special considerations for vacuum measurement; and (5) methods of determining the dynamic characteristics of pressure transducers. Design guidelines are provided for the critical components of each portion of the system to provide a pressure measurement system which meets the performance criteria specified.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Handbook of Recommended Practices for the Determination of Liquid Monopropellant Rocket Engine Performance; 76 p
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  • 33
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    Spin tests of a 1/20-scale model of the XP-39 airplane, 15 March 1939 (1976)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: The tests were performed to determine the spinning characteristics of a 1/20-scale model of the Bell XP-39 airplane. Effects of loading changes and of various control dispositions were studied. Subsequent tests were performed to determine the effect of a change in wing dihedral.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Collected Works of Charles J. Donlan; 23 p
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  • 34
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    Lateral stability and control tests of the XP-77 airplane in the NACA full-scale tunnel, 16 June 1944 (1976)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Tests were made in the NACA full-scale tunnel to determine the lateral stability and control characteristics of the XP-77 airplane. Measurements were made of the forces and moments on the airplane at various angles of attack and angles of yaw. The measurements were made with the propeller removed and with the propeller installed and operating at various thrust coefficients, and with the landing flaps retracted and deflected. The effects of aileron, elevator, and rudder deflection on control surface effectiveness and hinge moments were determined. The tests were planned to obtain the data required to evaluate as completely as possible the Army Air Force requirements on lateral stability and control for pursuit-type airplanes.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Collected Works of Charles J. Donlan; 84 p
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  • 35
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    Temperature measurement (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: The design, installation, checkout, calibration, and operation of a temperature measuring system to be used during tests of a liquid monopropellant rocket engine are discussed. Appendixes include: (1) temperature measurement system elemental uncertainties, and (2) tables and equations for use with thermocouples and resistance thermometers. Design guidelines are given for the critical components of each portion of the system to provide an optimum temperature measurement system which meets the performance criteria specified.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Handbook of Recommended Practices for the Determination of Liquid Monopropellant Rocket Engine Performance; 36 p
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  • 36
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    Force and impulse measurement (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Practices are outlined for the design, installation, checkout, calibration, and operation of a thrust measurement system to be used during tests of a liquid monopropellant rocket engine. Appendixes include: (1) thrust measurement system elemental uncertainties; (2) short- and long-term thrust measurement system uncertainty; and (3) shunt calibration of force transducers.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Handbook of Recommended Practices for the Determination of Liquid Monopropellant Rocket Engine Performance; 28 p
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  • 37
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    Data reduction and performance determination (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Definitions, algorithms, and procedures for the reduction of monopropellant thruster measurements to performance parameters are provided. A brief discussion of acquisition and recording systems is also included. Emphasis is placed upon monopropellant hydrazine engines, and some parameters relate specifically to the catalytic decomposition of hydrazine (e.g., percent ammonia dissociation). Performance of other types of monopropellant thrusters may, however, be determined by using procedures similar to those discussed. Two appendixes are included: (1) theoretical performance of monopropellant hydrazine; and (2) calculation of rotational performance.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Handbook of Recommended Practices for the Determination of Liquid Monopropellant Rocket Engine Performance; 45 p
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  • 38
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    Opportunities for aerodynamic-drag reduction (1975)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Methods for reducing aerodynamic drag to improve aircraft performance and reduce fuel consumption are discussed. The techniques considered are: (1) pressure drag reduction, (2) supercritical airfoils, (3) subcritical airfoils, (4) induced drag reduction by over-the-wing blowing and increased aspect ratio, and (5) friction drag reduction by laminar flow control and slot injection. It is stated that a 50 percent reduction from current drag values is expected through the application of these techniques.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA/Univ. Conf. on Aeron.; p 323-352
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  • 39
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    Some trends in aircraft design: Structures (1975)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Trends and programs currently underway on the national scene to improve the structural interface in the aircraft design process are discussed. The National Aeronautics and Space Administration shares a partnership with the educational and industrial community in the development of the tools, the criteria, and the data base essential to produce high-performance and cost-effective vehicles. Several thrusts to build the technology in materials, structural concepts, analytical programs, and integrated design procedures essential for performing the trade-offs required to fashion competitive vehicles are presented. The application of advanced fibrous composites, improved methods for structural analysis, and continued attention to important peripheral problems of aeroelastic and thermal stability are among the topics considered.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA/Univ. Conf. on Aeron.; p 213-272
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  • 40
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    Trends in aircraft noise control (1975)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Flight vehicles are characterized according to their manner of operation and type of propulsion system; and their associated sources of noise are identified. Available noise reduction technology as it relates to engine cycle design and to powerplant component design is summarized. Such components as exhaust jets, fans, propellers, rotors, blown flaps, and reciprocating-engine exhausts are discussed, along with their noise reduction potentials. Significant aircraft noise reductions are noted to have been accomplished by the application of available technology in support of noise certification rules. Further noise reductions to meet more stringent future noise regulations will require substantial additional technology developments. Improved analytical prediction methods, and well-controlled validation experiments supported by advanced-design aeroacoustic facilities, are required as a basis for an effective integrated systems approach to aircraft noise control.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA/Univ. Conf. on Aeron.; p 103-130
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  • 41
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    Normal shock and restart controls for a supersonic airbreathing propulsion system (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-28
    Description: Results of experimental investigations to control a supersonic mixed-compression inlet coupled to a turbojet engine are presented. Special instrumentation and servoactuators were developed to have sufficiently fast dynamic response so that basic propulsion system dynamics were the main limitation to controllability. In some cases servoactuator input signals were electronically limited to simulate moderate performance flight hardware.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA, Washington Fourth Inter-Center Control Systems Conf.; p 299-321
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  • 42
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    Flight test techniques for low speed airfoil evaluation (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-21
    Description: Techniques for in-flight evaluation of new airfoils by modifying a single engine general aviation aircraft and measuring and recording airfoil surface pressures, airfoil wake pressures, and aircraft angle of attack and airspeed are presented. Included are descriptions of the aircraft modifications, instrumentation, data reduction techniques, illustrations of typical results and comments on new equipment for flight test applications.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 623-642
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  • 43
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    Propulsive effects due to flight through turbulence (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A simple and straightforward analysis is presented for evaluating the approximate magnitude of the propulsive effect for various types of airplane (soaring glider, light airplane, fighter, and transport). The airplane, subject to vertical gust disturbances, is assumed to be constrained to fly at constant airspeed and constant pitch angle. Changes in the magnitude and direction of the lift vector are taken into account. It is shown that the thrust effects due to turbulence vary as the square of the turbulence intensity and are quite small for moderate turbulence. Only for rather severe turbulence are the effects large enough to be given any consideration. The thrust coefficient is 10-20% of the drag coefficient of a soaring glider.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft; 12; July 197
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  • 44
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    Comparison of sonic boom minimization results in real and isothermal atmospheres (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The method of Seebass and George (1972, 1974) for minimizing certain features of the pressure signature and yielding the corresponding F function and equivalent area distribution A in an isothermal atmosphere is modified to provide the same capability for a real atmosphere. The appropriate equations of George and Plotkin (1969) describing horizontal advance, ray tube area, and signature propagation are used.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft; 12; May 1975
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  • 45
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    Materials and processes for space shuttle's engines (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: It is pointed out that over 50 different alloys are used in construction of the space shuttle main engines (SSME). Primary construction of the SSME is by welding or brazing of wrought and cast components. Welding processes involve both gas tungsten-arc welds and electron-beam welds. Electroforming has been developed as a process to fabricate and bond structural members for the SSME. Important aspects in the selection of materials and processes are related to weight saving considerations and the high-pressure hydrogen environment. Special problems and their solution in the case of various engine components are discussed, giving attention to the oxidizer preburner, the high pressure oxidizer turbopump, and the heat exchanger.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 46
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    Parallel-burn options for dual-fuel single-stage orbital transports (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A parallel-burn version of a single-stage vehicle for transport from the earth to low-earth orbit using two fuels and rocket propulsion is considered. New engine results were incorporated in vehicle performance and design studies. The results indicate that a hydrogen-cooled gas generator cycle engine provides attractive vehicle performance and that there is little incentive for increasing the chamber pressure beyond 27 MPa.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets; 15; Jan
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  • 47
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    Toward scramjet aircraft (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The possibility for civil, military, and remotely-piloted aviation above Mach 5 is discussed with reference to the scramjet. Actively cooled aircraft structures of low weight are described, together with jet nozzle design and combustion parameters. The scramjet is seen as operating alone or in tandem with ramjet propulsion, which would power an aircraft up to scramjet speeds. Attention is given to the specific impulse of the scramjet engine, with hydrogen as the primary fuel. Applications include: advanced reconnaissance and interceptor aircraft, strategic cruise (both aircraft and missiles), highly-maneuverable interceptor missiles, transports, aircraft-type launch vehicles, first stages for Space Shuttle launching craft, and single-stage-to-orbit vehicles. Research has focused on increasing the propulsion power of the scramjet engine, while reducing drag on the accompanying airframe.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 16; Feb. 197
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  • 48
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    Advanced supersonic cruise aircraft technology (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A multidiscipline approach is taken to the application of the latest technology to supersonic cruise aircraft concept definition, and current problem areas are identified. Particular attention is given to the performance of the AST-100 advanced supersonic cruise vehicle with emphasis on aerodynamic characteristics, noise and chemical emission, and mission analysis. A recently developed aircraft sizing and performance computer program was used to determine allowable wing loading and takeoff gross weight sensitivity to structural weight reduction.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Acta Astronautica; 4; Jan
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  • 49
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    New evidence of the mechanisms of noise generation and radiation of a subsonic jet (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Acoustical Society of America; vol. 57
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  • 50
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    Streamtube analysis of a hydrogen-burning scramjet exhaust and simulation technique (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A scramjet/airframe integration program and a technique for simulating thermally perfect scramjet exhaust flows (freon/argon gas blends) is studied to extend the technique to more complicated flows approaching the actual exhaust flow in complexity. The state of the flow and the accuracy of the substitute gas simulation are analyzed in the case of a shock discontinuity present. Findings are: scramjet exhaust flow is essentially frozen throughout the expansion at Mach 6 and Mach 8; flow behind moderate shocks remains frozen; the technique can accurately track static distributions in scramjet exhaust flows (shocked or unshocked).
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Journal of Aircraft; 14; Sept
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  • 51
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    Hypersonic transport technology (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The possibility of developing a hypersonic commercial transport (HST) for the early 21st century is explored in terms of potential performance characteristics and recent advances in propulsion and structures technology. Range-gross weight characteristics indicate that a 200 passenger, Mach 6 aircraft with a range of 9200 km (5000 n.mi.) would have a gross take-off weight not too different from that of current wide-body subsonic transports. The low cruise sonic boom overpressures generated by the HST opens the possibility of supersonic overland flight which, if permitted, would greatly increase the attractiveness of this type of aircraft. Recent advances in hypersonic propulsion systems and long-lived hypersonic aircraft structure are also discussed. The airframe-integrated scramjet and the actively-cooled airframe structure are identified as the most promising candidates for the HST and current approaches are described in some detail.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Acta Astronautica; 4; Jan
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  • 52
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    The oblique wing - Aircraft design for transonic and low supersonic speeds (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: In tests at transonic speeds a conventional 'subsonic' wing turned at an oblique angle to the flow has demonstrated lift-drag ratios higher than conventional swept-back or delta wings. When returned to its straight position, perpendicular to the flow, such a wing would minimize the display of energy and noise in the airport environment. Following a brief review of theoretical and experimental results, the paper discusses various characteristics of the oblique wing as they relate to aircraft design. Topics covered are lift-drag ratio, flight control and trim and aeroelastic stability. The possibility of an all-wing aircraft for flight at Mach 2 is suggested.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Acta Astronautica; 4; Jan
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  • 53
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    Problems inherent in using aircraft for radio oceanography studies (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Some of the disadvantages relating to altitude stability and proximity to the ocean are described for radio oceanography studies using aircraft. The random oscillatory motion introduced by the autopilot in maintaining aircraft altitude requires a more sophisticated range tracker for a radar altimeter than would be required in a satellite application. One-dimensional simulations of the sea surface (long-crested waves) are performed using both the JONSWAP spectrum and the Pierson-Moskowitz spectrum. The results of the simulation indicate that care must be taken in trying to experimentally verify instrument measurement accuracy. Because of the relatively few wavelengths examined from an aircraft due to proximity to the ocean and low velocity compared to a satellite, the random variation in the sea surface parameters being measured can far exceed an instrument's ability to measure them.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IEEE Transactions on Antennas and Propagation; AP-25; Jan. 197
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  • 54
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    Hypersonic technology-approach to an expanded program (1976)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: An overview of research, testing, and technology in the hypersonic range. Military and civilian hypersonic flight systems envisaged, ground testing facilities under development, methods for cooling the heated airframe, and use of hydrogen as fuel and coolant are discussed extensively. Air-breathing hypersonic cruise systems are emphasized, the airframe-integrated scramjet configuration is discussed and illustrated, materials proposed for hypersonic vehicles are reviewed, and test results on hypersonic flight (X-15 research aircraft) are indicated. Major advances and major problems in hypersonic flight and hypersonic technology are outlined, and the need for a hypersonic flying-laboratory research craft is stressed.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 14; Dec. 197
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  • 55
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    Aeroacoustics: STOL noise; Airframe and airfoil noise (1976)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The papers in this volume reflect the progress in aeroacoustic research which has been made in the field of VTOL and V/STOL aircraft noise. The research was directed mainly at developing better methods for predicting noise generation and propagation, at determining the effects of pressure fluctuations on surfaces and interior noise, and at developing noise abatement techniques. Among the topics covered are: scrubbing noise of externally blown flaps; propulsive-lift noise of an upper-surface-blown flap configuration; the aeroacoustic characteristics of model slot nozzles with straight flaps; fluctuating pressures on aircraft wing and flap surfaces associated with powered-lift systems; acoustic characteristics of a large upper-surface-blown configuration with turbofan engines; the effect of forward speed on jet/flap interaction noise; and airframe noise in the far field.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
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  • 56
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    A review of some tilt-rotor aeroelastic research at NASA-Langley (1976)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An overview of an experimental and analytical research program conducted within the Aeroelasticity Branch of the NASA Langley Research Center for studying the aeroelastic and dynamic characteristics of tilt-rotor VTOL aircraft is presented. Selected results from several joint NASA/contractor investigations of scaled models in the Langley transonic dynamics tunnel are shown and discussed with a view toward delineating various aspects of dynamic behavior peculiar to proprotor aircraft. Included are such items as proprotor/pylon stability, whirl flutter, gust response, and blade flapping. Theoretical predictions, based on analyses developed at Langley, are shown to be in agreement with the measured stability and response behavior.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft; 13; May 1976
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  • 57
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    Feasibility of modern airships - Preliminary assessment (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Attention is given to the NASA program, Feasibility Study of Modern Airships, initiated to investigate potential research and technology programs associated with airship development. A historical survey of the program is presented, including the development of past airship concepts, aerodynamical and design improvements, structure and material concepts, and research in controls, avionics, instrumentation, flight operations, and ground handling. A mission analysis was carried out which considered passenger and cargo transportation, heavy-lift, short-haul applications, surveillance missions, and the transportation of natural gas. A vehicle parametric analysis examined the entire range of airship concepts, discussing both conventional airships and hybrids. Various design options were evaluated, such as choice of structural materials, use of boundary-layer control, and choice of lifting gas.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft; 14; Nov. 197
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  • 58
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    Shuttle carrier aircraft flight tests (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Since the Space Shuttle will need to be transported from its place of assembly to the launch site, a method has been developed whereby the Shuttle rides piggyback on a modified Boeing 747, called the Shuttle carrier aircraft (SCA). This paper describes tests of the SCA in its mated configuration. Tests include: flutter, found to decrease when fiberglass and wood fairings were added to the base of each supporting pylon; stability and control, found to be acceptable after damping with control pulses; noise and buffet, found high but acceptable; and climb, in which drag was marked but acceptable with the special rated thrust (SRT) power setting. Simulated launch maneuvers were undertaken at an airspeed of 273 KCAS. Transport of the Shuttle takes place with the Shuttle tail cone on, at a cruise speed of 288 KCAS at an altitude of 22,000 feet.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
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  • 59
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    Comment on 'Heat-pipe reactors for space power applications' (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Energy; 2; May-June
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  • 60
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    Comments on 'Feasibility study of a hybrid airship operating in ground effect' (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft; 15; Feb. 197
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  • 61
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    Monte Carlo investigation of thrust imbalance of solid rocket motor pairs (1976)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The Monte Carlo method of statistical analysis is used to investigate the theoretical thrust imbalance of pairs of solid rocket motors (SRMs) firing in parallel. Sets of the significant variables are selected using a random sampling technique and the imbalance calculated for a large number of motor pairs using a simplified, but comprehensive, model of the internal ballistics. The treatment of burning surface geometry allows for the variations in the ovality and alignment of the motor case and mandrel as well as those arising from differences in the basic size dimensions and propellant properties. The analysis is used to predict the thrust-time characteristics of 130 randomly selected pairs of Titan IIIC SRMs. A statistical comparison of the results with test data for 20 pairs shows the theory underpredicts the standard deviation in maximum thrust imbalance by 20% with variability in burning times matched within 2%. The range in thrust imbalance of Space Shuttle type SRM pairs is also estimated using applicable tolerances and variabilities and a correction factor based on the Titan IIIC analysis.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets; 13; Apr. 197
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  • 62
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    Toward a new V/STOL generation (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: While many V/STOL problems are now better understood and technology has progressed to the point where higher thrust/weight ratios and greater stability augmentation are achievable, a number of still existing insufficiencies provide a sobering reminder that learning in ground testing and simulation, and careful methodical planning, are a prerequisite for any research and development program. The present paper is centered on the major technical problems for the Navy Type multimission V/STOL aircraft. The aircraft's configurations with and without forward lift fan are discussed, along with the propulsion systems, testing techniques, controls, displays, flight dynamics, and ground/flow field interactions.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 15; Nov. 197
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  • 63
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    Some considerations in the design of transport aircraft /The W. Rupert Turnbull Lecture for 1975/ (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The slow landing speeds (30 mph, 65 mph) and light wing loading required for safety in the early days of aviation are shown to be irrelevant to safe landings of propeller-driven aircraft, while increases in wing loading and landing speed have been accompanied by improved safety records. This is attributed to length of runway and time available for approach maneuvers, plus immunity to wind gusts and turbulence conferred by higher wing loadings. Aerodynamical and mechanical aspects of safe landing are discussed, with no mention of instruments. Fuel savings achievable through high aspect ratio, variable sweep angle, and supercritical airfoils are also considered.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
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  • 64
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    Solution of the minimum time-to-climb problem by matched asymptotic expansions (1976)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Application of singular perturbation techniques to trajectory optimization problems of flight mechanics is discussed. The method of matched asymptotic expansions is used to obtain an approximate solution to the aircraft minimum time-to-climb problem. Outer, boundary-layer, and composite solutions are obtained to zeroth and first orders. A stability criterion is derived for the zeroth-order boundary-layer solutions (the theory requires a form of boundary-layer stability). A numerical example is considered for which it is shown that the stability criterion is satisfied and a useful numerical solution is obtained. The zeroth-order solution proves to be a poor approximation, but the first-order solution gives a good approximation for both the trajectory and the minimum time-to-climb. The computational cost of the singular perturbation solution is considerably less than that of a steepest descent solution. Thus singular perturbation methods appear to be promising for the solution of optimal control problems.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA Journal; 14; July 197
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  • 65
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    Compatibility of take-off and landing with mission and manoeuvre performance requirements for fighter aircraft (1975)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: By means of an aircraft synthesis program, the effect of engine cycle, thrust to weight ratio, and wing parameter combination on field and flight performance has been investigated. For three different engine/intake configurations, thrust to weight ration and wing loading were varied. Each combination represents an aircraft designed to meet a specified mission radius. Using different lift systems and ground deceleration devices, the conditions are shown under which a matching of flight and field performance is economically feasible.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AGARD Take-off and Landing; 7 p
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  • 66
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    Fretting in aircraft turbine engines (1975)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: The problems created by fretting in turbine engines are discussed. The areas of greatest wear identified with the fan, compressor, and turbine blade mountings being the most critical items. Various methods for reducing or eliminating fretting in a turbine engine are described. Vacuum deposition of coatings by sputtering and ion plating are recommended as an economic method of applying thin films to inhibit fretting.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Specialists Meeting on Fretting in Aircraft Systems; 17 p
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  • 67
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    Parameter estimation of powered-lift STOL aircraft characteristics including turbulence and ground effects (1975)
    In:  CASI
    Details
    Publication Date: 2012-05-19
    Description: Longitudinal aerodynamic coefficients are estimated from data recorded during flight tests of a powered-lift STOL aircraft. A comparison is made between the coefficient values determined by the regression and quasilinearization identification techniques from records taken during elevator pulse maneuvers. The results show that for these tests the regression method provides less scatter in coefficient estimates and provides better correlation with the predicted values. Special techniques are developed which allow identification of the coefficients from records taken during landing maneuvers in which the aircraft encounters turbulence while flying in ground effect. Flight test results are presented to illustrate the effects of air turbulence and ground proximity on the estimated coefficient values.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AGARD Methods for Aircraft State and Parameter Identification; 10 p
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  • 68
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    Rotorcraft derivative identification from analytical models and flight test data (1975)
    In:  CASI
    Details
    Publication Date: 2012-05-19
    Description: A general procedure is presented for systematic development of rotorcraft models for use in systems identification, which includes fuselage and rotor degrees of freedom (DOF). Formulations for rigid blade flap and lag as well as the normal mode representation of an elastic blade are developed for hingeless and articulated rotor systems. The method of multiblade coordinates is used to obtain linear constant coefficient state variable models of various levels of approximation. Two of the approximate models, a 6 DOF, are identified from a nonlinear articulated helicopter computer simulation. The results demonstrate the accuracy attainable for each model. Advanced results outline the status of rotorcraft modeling and systems identification and indicate areas that require further investigation.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AGARD Methods for Aircraft State and Parameter Identification; 31 p
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  • 69
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    CTOL concepts and technology development (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Various developments in the Aircraft Energy Efficiency (ACEE) program are discussed. Terminal-area operations are considered with emphasis on the Terminal Configured Vehicle program. Consideration is also given to aircraft systems studies and economics (including noise reduction programs), coal-derived fuels for aviation systems (including LH2-fueled aircraft), and transport-aircraft concepts (including laminar flow control).
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 16; July-Aug
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  • 70
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    Quality assurance and control in the production and static tests of the solid rocket boosters for the Space Shuttle (1979)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The paper surveys the various aspects of design and overhaul of the solid rocket boosters. It is noted that quality control is an integral part of the design specifications. Attention is given to the production process which is optimized towards highest quality. Also discussed is the role of the DCA (Defense Contract Administration) in inspecting the products of subcontractors, noting that the USAF performs this role for prime contractors. Fabrication and construction of the booster is detailed with attention given to the lining of the booster cylinder and the mixing of the propellant and the subsequent X-ray inspection.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Astronautik; 16; 2, 19; 1979
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  • 71
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    Current leakage for low altitude satellites - Modeling applications (1979)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: To simulate the behavior of a high voltage solar cell array in the ionospheric plasma environment, the large (90 ft x 55 ft diameter) vacuum chamber was used to measure the high-voltage plasma interactions of a 3 ft x 30 ft conductive panel. The chamber was filled with Nitrogen and Argon plasma at electron densities of up to 1,000,000 per cu cm. Measurements of current flow to the plasma were made in three configurations: (a) with one end of the panel grounded, (b) with the whole panel floating while a high bias was applied between the ends of the panel, and (c) with the whole panel at high negative voltage with respect to the chamber walls. The results indicate that a simple model with a constant panel conductivity and plasma resistance can adequately describe the voltage distribution along the panel and the plasma current flow. As expected, when a high potential difference is applied to the panel ends more than 95% of the panel floats negative with respect to the plasma.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 72
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    Nonlinear singularly perturbed optimal control problems with singular arcs (1979)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Singular perturbation techniques are studied for dealing with singular arc problems by analyzing a relatively low-order but otherwise general system. This system encompasses many flight mechanic problems including Goddard's problem and a version of the minimum time-to-climb problem. Boundary layer solutions are constructed which are stable and reach the outer solution in a finite time. A uniformly valid composite solution is then formed from the reduced and boundary layer solutions. The value of the approximate solution is that it is relatively easy to obtain and does not involve singular arcs. To illustrate the utility of the results, the technique is used to obtain an approximate solution of a simplified version of the aircraft minimum time-to-climb problem.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
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  • 73
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    Assessment of airframe noise (1979)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A component method of airframe noise prediction is used to predict levels of operational and proposed aircraft airframe noise to assess the contribution of airframe noise to community noise levels. This is done after first evaluating the prediction method using newly acquired detailed measurements from full-scale aircraft and models. In the course of the evaluation, modeling techniques of airframe noise sources are examined with attention to scaling. Finally, when used to predict approach airframe EPNLs, the levels fell about 10 EPNdB below current noise regulations and about 5 EPNdB below proposed noise regulations.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft; 16; Dec. 197
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  • 74
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    Examination of the flap-lag stability of rigid articulated rotor blades (1979)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A critical examination of flap-lag stability of a centrally hinged, spring-restrained rigid blade in both hover and forward flight is presented. Several differences in the equations of motion for blade flap-lag stability in the existing literature are identified. A rigorous and systematic development of these equations for a rigid articulated blade in forward flight shows the existence of some linear aerodynamic coupling terms associated with blade steady-state flapping and lagging in the perturbation equations. The differences identified are shown to be associated with whether or not the lag hinge flaps with the blade. The implications of these differences on stability are examined, and it is shown that the pitch-lag coupling terms associated with a hinge arrangement in which the lag hinge flaps with the blade have a marked influence on flap-lag stability, depending on the system parameters.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft; 16; Dec. 197
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  • 75
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    Aircraft operator - Would you buy higher DOC to lower noise and fuel use (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A method of optimization of the direct operating cost (DOC) and the effective perceived noise (in units of EPNdB) in aircraft is proposed. A computer program was used to generate a variety of aircraft designs meeting certain specifications, where wing loading, aspect ratio, cruise altitude, wing sweepback, and speed was varied, and DOC for each case was calculated. The higher aspect ratio, in combination with the appropriate wing loadings, cruise altitudes and wing sweep, is found to reduce the noise and the fuel used.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 15; Apr. 197
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  • 76
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    High temperature reformation of aluminum and chlorine compounds behind the Mach disk of a solid-fuel rocket exhaust (1976)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Chemical reactions expected to occur among the constituents of solid-fuel rocket engine effluents in the hot region behind a Mach disk are analyzed theoretically. With the use of a rocket plume model that assumes the flow to be separated in the base region, and a chemical reaction scheme that includes evaporation of alumina and the associated reactions of 17 gas species, the reformation of the effluent is calculated. It is shown that AlClO and AlOH are produced in exchange for a corresponding reduction in the amounts of HCl and Al2O3. For the case of the space shuttle booster engines, up to 2% of the original mass of the rocket fuel can possibly be converted to these two new species and deposited in the atmosphere between the altitudes of 10 and 40 km. No adverse effects on the atmospheric environment are anticipated with the addition of these two new species.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Atmospheric Environment; 10; 9, 19; 1976
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  • 77
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    Aeroacoustics: Jet noise, combustion and core engine noise (1976)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The papers in this volume deal essentially with the question whether the amplification of noise is due to the jet noise phenomenon or perhaps an interaction of airframe and core engine noise. In the area of jet noise suppression, various promising suppressor concepts are examined. The swirling flow jet noise suppressor is shown to provide significant noise reduction with minimal thrust losses. Progress in the aircraft engine core noise problem is reflected by seven research-type papers. Two possible mechanisms are seen to be responsible for core noise. One is the direct noise radiated from the turbulent combustion in the primary combuster and transmitted through the turbine, passing out the nozzle into the far field. The other mechanism is the noise that is emitted from hot spots being convected through the turbine. Which of these mechanisms (or perhaps both mechanisms) is responsible for core noise, and what are the coupling mechanisms of core engine noise and jet noise are the questions confronting researchers.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 78
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    How good is jet lift VTOL technology (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The status of technologies for jet-lift V/STOL aircraft is examined, and a critical review of the performance of jet-lift VTOL aircraft built to date is made. Most jet-lift aircraft have suffered from adverse propulsion-induced effects during takeoff and landing. Flight dynamics of jet-lift aircraft have suffered from shortcomings in static and dynamic stability, control characteristics, and flight path control. Some of the main problems to be considered during the selection of a propulsion system arrangement for a V/STOL fighter are discussed. At present, experimental and analytical data on supersonic V/STOL configurations are insufficient to permit evaluating propulsion system arrangements.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Astronautics and Aeronautics; 15; Dec. 197
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  • 79
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    Lift/cruise fan VTOL aircraft (1977)
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    Publication Date: 2011-08-17
    Description: The paper gives an overview of the technology related to lift/cruise fan VTOL aircraft, covering propulsion systems, thrust deflection, flight dynamics, controls, displays, aerodynamics, and configurations. Piloting problems are discussed, and the need for integration of power management and thrust-vector controls is pointed out. Major components for a high-bypass-ratio lift/cruise fan propulsion system for VTOL aircraft have been tested.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 15; Dec. 197
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  • 80
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    Tilt-proprotor perspective (1977)
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    Publication Date: 2011-08-17
    Description: The general tilt-proprotor concept is discussed, and a more detailed look at the XV-15 aircraft is taken. The special features of the two-engine system, engine control system, and flight control system are mentioned. The main objectives of the XV-15 program are to (1) verify rotor/pylon/wing/dynamic stability and aircraft performance over a representative operational envelope, (2) assess the handling qualities and establish a safe operating envelope, and (3) investigate gust sensitivity, effects of downwash, and hover operation. With regard to rotor/pylon stability, one challenge is to be able to predict a parameter's value and then build hardware to match. The analytical program has gained some respect through aeroelastic and full-scale XV-3 demonstrations. Special concern centers around the thrust and power management system when flying at high speed when very small changes in rotor collective pitch represent large changes in thrust and power. Demonstration of the system awaits wind-tunnel and flight testing.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 15; Dec. 197
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  • 81
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    Remotely piloted aircraft in the civil environment (1977)
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    Publication Date: 2011-08-17
    Description: Remotely piloted aircraft (RPA's) are of increasing interest to the military and others, as evidenced by a number of technology and development programs that are currently funded or planned. These programs have led to a number of test aircraft with significant capabilities, and future remotely piloted aircraft are forecast to become even more capable as the technology in a number of important subsystem areas is progressing at a rapid rate. As the size, weight and cost of RPA's is reduced, the prospect of using them for civilian applications becomes more likely.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Mechanism and Machine Theory; 12; 1977
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  • 82
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    RPRV research focus on HiMAT (1976)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A review is presented of the F-15 Remotely Piloted Research Vehicle (RPRV) project. The F-15 RPRV is air-launched from a B-52 at 50,000 ft. Following launch a series of research maneuvers are performed during an unpowered descent to a recovery altitude. Another RPRV program considered is the Highly Maneuverable Aircraft Technology (HiMAT) program. This program is designed to use RPRVs to speed the technology transition from wind tunnel to flight and to reduce the cost of aeronautical experiments. It is pointed out that HiMAT will make extensive use of composite materials.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 14; Apr. 197
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  • 83
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    Optimum exhaust velocity for laser-driven rockets (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The laser-driven rocket in which remotely generated laser power is used to heat propellant belongs basically to the class of specific-impulse limited propulsion systems if difficult missions are considered. It was previously established that trip time reaches a minimum as specific impulse is varied for payload transfers from low earth orbit to synchronous orbit and return via laser-driven rocket propulsion, the computations being based on the perigee-propulsion laser drive described by Minovitch (1972). The present study shows that such minimum occur for all missions and that optimum specific impulse is primarily determined by the mission difficulty. More generally, this optimum specific impulse maximizes payload kinetic energy achievable with a fixed jet power and propulsion time. A formula relating propulsion time parameter to payload ratio is obtained for estimating mission capabilities of laser-driven rockets.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets; 12; Nov. 197
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  • 84
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    X-24B flight test program (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The X-24B is an air launched, rocket powered research aircraft. A number of its design features constitute a tradeoff between aerodynamics and heating considerations. A vehicle description is given and test program objectives are discussed along with operational procedures and aspects of energy management. Attention is also given to X-24B handling qualities, approach and landing, wind tunnel data and simulation, and proposed X-24C vehicle requirements.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
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  • 85
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    ATS-6 - Cesium bombardment engine north-south stationkeeping experiment (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Two 0.004 N thrust cesium bombardment ion thrustors have been developed and used for north-south stationkeeping in the geostationary Applications Technology Satellite-6 (ATS-6). The thrustor subsystems are mounted on the north and south faces of the earth viewing module such that 0.0026 N of thrust is applied normal to the orbit plane and 0.0036 N is applied radially upward. The change in the orbit inclination of the satellite is maintained at zero by operating the two thrustors alternately so that their thrust components, normal to the orbital plane, are symmetrically applied about the nodal crossings. Initial operation of the thrustors was successful. There was no interference with the satellite communications systems and the predicted spacecraft operating potential was verified. Subsequent trials failed due to a defect in the operation of the propellant reservoirs in zero g. A feed line valve is under development to correct this difficulty.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IEEE Transactions on Aerospace and Electronic Systems; AES-11; Nov. 197
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  • 86
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    A note on correlation description (1976)
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    Publication Date: 2011-08-16
    Description: The paper suggests some modifications to definitions of correlation functions made by Freeman and Bennett (1974) specifically for comparing measured quantities with those predicted by rotor theories, with reference to rotorcraft flight simulation. Special attention is paid to the quality of correlation, determined by a quality factor relating the measured and computed entities. Correlation criteria (mean load and rotor performance, overall amplitude and phase, harmonic altitude and harmonic phase) are examined, along with phase angle correlation criteria (harmonic phase defined by sine-cosine relation and harmonic phase defined by a first positive peak rotor azimuth position)
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: American Helicopter Society; vol. 21
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  • 87
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    Conceptual design of reduced energy transports (1976)
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    Publication Date: 2011-08-16
    Description: The paper reports the results of a conceptual design study of new near-term fuel-conservative aircraft. A parametric study was made to determine the effects of cruise Mach number and fuel cost on the optimum configuration characteristics and relative economic performance. Supercritical wing technology and advanced engine cycles were assumed. For each design, the wing geometry was selected to maximize an economic figure of merit which reflects the potential rate of return on investment. Based on the results of the parametric study, a reduced energy configuration was selected. Compared with existing transport design, the reduced energy design has a higher aspect ratio wing with lower sweep, and cruises at a slightly lower Mach number. It yields about 30% more seat-miles/gal than current wide-body aircraft. At the higher fuel costs anticipated in the future, the reduced energy design has about the same economic performance as existing designs with the same technology level. As an example of a far-term technology application, a design with a composite material wing was also investigated.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft; 13; Aug. 197
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  • 88
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    On the response of superpressure balloons to displacements from equilibrium density level (1976)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The response of a superpressure balloon to an initial displacement from its constant-density floating level is examined. An approximate solution is obtained to the governing vertical equation of motion for constant-density superpressure balloons. This solution is used to filter out neutrally buoyant oscillations in balloon records despite the nonlinear behavior of the balloon. The graph depicting the pressure data after deconvolution between the raw pressure data and the normalized balloon wavelet shows clearly the strong filtering-out of the neutral buoyancy oscillations.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Applied Meteorology; 15; Apr. 197
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  • 89
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    The NASA structures and materials research program for supersonic cruise aircraft (1976)
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    Publication Date: 2011-08-16
    Description: The structures and materials part of the NASA Supersonic Cruise Aircraft Research (SCAR) program is reviewed. It is pointed out that in more than three years of work significant new technology has been generated. The aircraft configurations which are efficient aerodynamically have aeroelastic problems that must be alleviated by configuration changes, active controls, or additional structural mass. An approach involving the application of advanced composite materials has the highest potential for structural weight reduction. Attention is given to the structural concepts for an arrow-wing supersonic aircraft and the techniques used in the investigations. It is expected that continuing research in SCAR structures and materials should bring high payoffs in the late 1980s.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 14; May 1976
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  • 90
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    Generalized dynamic engine simulation techniques for the digital computers (1975)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: Recently advanced simulation techniques have been developed for the digital computer and used as the basis for development of a generalized dynamic engine simulation computer program, called DYNGEN. This computer program can analyze the steady state and dynamic performance of many kinds of aircraft gas turbine engines. Without changes to the basic program, DYNGEN can analyze one- or two-spool turbofan engines. The user must supply appropriate component performance maps and design point information. Examples are presented to illustrate the capabilities of DYNGEN in the steady state and dynamic modes of operation. The analytical techniques used in DYNGEN are briefly discussed, and its accuracy is compared with a comparable simulation using the hybrid computer. The impact of DYNGEN and similar digital programs on future engine simulation philosophy is also discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Power Plant Controls for Aero-Gas Turbine Eng.; 23 p
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  • 91
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    High-lift aerodynamics: Trends, trades, and options (1975)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: The trend toward the utilization of higher maximum lift coefficient with increased aircraft size and cruise velocities is discussed. The impact of this trend on the need for tradeoffs between cruise performance and takeoff, climb, and landing performance is examined. Theoretical methods for the analysis of the two-dimensional characteristics of flap systems are described and compared with experimental data. Four powered-lift concepts are described to outline some of the options currently being developed. Two jet-flap theories are described which provide analytical methods for estimation of the three-dimensional aerodynamic high-lift performance characteristics of powered lift systems.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AGARD Take-off and Landing; 11 p
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  • 92
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    Effect of endwall cooling on secondary flows in turbine stator vanes (1977)
    In:  CASI
    Details
    Publication Date: 2012-05-19
    Description: An experimental investigation was performed to determine the effect of endwall cooling on the secondary flow behavior and the aerodynamic performance of a coreturbine stator vane. The investigation was conducted in a cold-air, full-annular cascade, where three-dimensional effects could be obtained. Two endwall cooling configurations were tested. In the first configuration, the cooling holes were oriented so that the coolant was injected in line with the inviscid streamline direction. In the second configuration, the coolant was injected at an angle of 15 deg to the inviscid streamline direction and oriented toward the vane pressure surface. In both cases the stator vanes were solid and uncooled so that the effect of endwall cooling could be obtained directly. Total-pressure surveys were taken downstream of the stator vanes over a range of cooling flows at the design, mean-radius, critical velocity ratio of 0.778. Changes in the total-pressure contours downstream of the vanes were used to obtain the effect of endwall cooling on the secondary flows in the stator. Comparisons were made between the two cooled-endwall configurations and with the results obtained previously for solid endwalls.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Secondary Flows in Turbomachines; 29 p
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  • 93
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    Importance of helicopter dynamics to the mathematical model of the helicopter (1975)
    In:  CASI
    Details
    Publication Date: 2012-05-19
    Description: A mathematical model of the helicopter requires appropriate representation of the constituent elements of rotor dynamics. General-purpose programs that model a variety of configurations for a broad range of operating conditions result in varying and incompatible levels of sophistication. Analysis of specific dynamic problems facilitates the identification of configuration parameters which determine system behavior. For the present analysis, the nonlinear equations of a torsionally rigid hingeless rotor are linearized about an equilibrium condition to determine flap-lag stability characteristics in hover. A collocation method was used to obtain the coupled natural frequencies and modes. These modes allow exact treatment of the effect of elastic coupling which more than compensates for the destabilizing inertial coupling. The sensitivity of damping to the number of modes was found to be small, and reasonable accuracy was obtained the first flapwise and edgewise coupled modes. The range of destabilizing precone was found to be small.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AGARD Methods for Aircraft State and Parameter Identification; 12 p
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  • 94
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    Investigation of interior noise in a twin-engine light aircraft (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: This paper describes experimental studies of interior noise in a twin-engine, propeller-driven, light aircraft. An analytical model for this type of aircraft is also discussed. Results indicate that interior noise levels in this aircraft due to propeller noise can be reduced by reducing engine rpm at constant airspeed (about 3 dB), and by synchrophasing the twin engines/propellers (perhaps up to 12 dB). Ground tests show that the exterior noise pressure imposed on the fuselage consists of a complex combination of narrow-band harmonics due to propeller and engine exhaust sources. This noise is reduced by about 20-40 dB (depending on the frequency) by transmission through the sidewall to the cabin interior. The analytical model described uses modal methods and incorporates the flat-side geometrical and skin-stringer structural features of this light aircraft.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft; 15; Apr. 197
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  • 95
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    High-flying Mini-Sniffer RPV - Mars bound (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The Mini-Sniffer is a small unmanned survey aircraft developed by NASA to conduct turbulence and atmospheric pollution measurements from ground level to an altitude of 90,000 ft. Carrying a 25-lb air sampling apparatus, the Mini-Sniffer typically cruises for one hour at 70,000 ft before being remotely piloted back to earth. A hydrazine monopropellant engine powers the craft, while a PCM telemetering system and a radar transponder provide control functions. Development of a high-performance low-Reynolds-number airfoil could make the research craft suitable for a low-altitude terrain-following mission on Mars.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 16; June 197
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  • 96
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    The Quiet Short-Haul Research Aircraft /QSRA/ (1979)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The Quiet Short-Haul Research Aircraft (QSRA), designed to expand the technology base of the upper-surface blowing propulsive-lift principle in order to establish criteria for the U.S. aircraft industry and for advanced STOL aircraft, is considered. The aircraft, which includes a three-axis, single channel, limited authority series type stability augmentation system, and a high-speed data system is described. Also discussed are STOL and acoustic performance, and handling qualities, particularly thrust effects. The QSRA has demonstrated its ability, even with the critical engine inoperative, to approach at 66 knots (wing loading of 83 lb/sq ft) and on a 9 degree glidepath; to maneuver in a 700-ft radius turn, and to land in an FAA field length of 1450 ft (over a 35-ft obstacle).
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
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  • 97
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    Annealing kinetics of electron-irradiated GaAs heteroface solar cells in the range 175-200 C (1979)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Annealing of electron-irradiation damage in GaAs solar cells is important for space applications. This paper describes studies conducted to understand this annealing process. GaAs heteroface solar cells were irradiated with 10 to the 15th 1-MeV electrons/sq cm followed by thermal annealing. An activation energy for annealing of 1.25 + or - 0.14 eV and a frequency factor of (3.7 + or - 1.9) x 10 to the 9th per sec were determined. A small component of the irradiation damage which does not anneal measurably at 200 C was observed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Applied Physics Letters; 35; Sept. 15
    Format: text
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  • 98
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    QCSEE - The key to future short-haul air transport (1979)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The paper describes the design and test procedure for the QCSEE (quiet, clean, short-haul experimental engine). The engines designed for the YC-14 and YC-15 STOL aircraft, both use a very low fan pressure ratio to keep jet-flap noise about 3 dB below total system noise. Other noise reducing features discussed are the low tip speed fans and a carefully selected number of fan blades and vanes with adequate spacing between them. Attention is also given to the development of a low emissions combustor, and reduction of fan frame weight, through the use of graphite/epoxy material. The YC-15 engine also employs variable pitch fans to provide thrust reversal, thus saving weight. Finally, it is noted that the tests have proven that the engines could be configurated to meet the needs of a powered lift system without excessively compromising performance or weight.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ICAO Bulletin; 34; Apr. 197
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  • 99
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    Recent V/STOL aircraft designs (1979)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The paper reviews the V/STOL aircraft designs pursued by industry from 1971 to 1978, with emphasis on the 1975-1978 period. Consideration is given to those designs pertaining to vertical-attitude and horizontal-attitude V/STOL types. These are divided into such concepts as tilting jet engine, lift/cruise engine, lift engine, lift/cruise fan, ejector augmentor, tilt rotor, stowed rotor, and rotor wing.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: American Helicopter Society; vol. 24
    Format: text
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  • 100
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    Electrets used in measuring rocket exhaust effuents from a Space Shuttle model (1979)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The study evaluates the use of electrets as a new contamination-detecting device designed to assess the chemical composition of rocket effluents. Evaluation of electret effectiveness revealed that electrets have multipollutant-measuring capability, simplicity of deployment and rapidity of assessment. Advantages of electrets are small size, light weight and cost-effectiveness. It is shown that electrets compare favorably with other HCl measuring devices. In particular, the summary of the measured data from electrets and HCl detectors is within the limits of computed HCl concentrations from the NASA/MSFC multilayer diffusion model.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Applied Meteorology; 18; Jan. 197
    Format: text
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