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  • Other Sources  (12)
  • 1
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    Airframe effects on a top-mounted fighter inlet system (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: (Previously cited in issue 07, p. 963, Accession no. A82-19212)
    Keywords: AERODYNAMICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Top-mounted inlet system feasibility for transonic-subsonic fighter aircraft applications (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: To inlet flow field and engine inlet performance data for an advanced fighter aircraft configuration were obtained over the Mach 0.6 to 2.0 range. The studies not only provided extensive data for the baseline arrangement, but also evaluated the effects of key aircraft configuration variables (inlet location, canopy-dorsal integration, wing leading-edge extension planform area, and variable incidence canards) on top inlet performance. In order to set these data in the context of practical aircraft systems top inlet performance is compared with that of more conventional inlet/airframe integrations. The results of these evaluations show that, for the top inlet configuration tested, relatively good inlet performance and compatibility characteristics are maintained during subsonic and transonic maneuver. However, at supersonic speeds, flow expansion over the forebody and wings causes an increase in local inlet Mach number subsequently reduces inlet performance levels. These characteristics infer that although top inlets many not pose a viable design option for aircraft requiring a high degree of supersonic maneuverability, they have distinct promise for vehicles with subsonic and transonic maneuver capabilities.
    Keywords: AERODYNAMICS
    Type: AGARD Aerodyn. of Power Plant Installation; 17 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Top-mounted inlet system feasibility for transonic-supersonic fighter aircraft (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The more salient findings are presented of recent top inlet performance evaluations aimed at assessing the feasibility of top-mounted inlet systems for transonic-supersonic fighter aircraft applications. Top inlet flow field and engine-inlet performance test data show the influence of key aircraft configuration variables-inlet longitudinal position, wing leading-edge extension planform area, canopy-dorsal integration, and variable incidence canards-on top inlet performance over the Mach range of 0.6 to 2.0. Top inlet performance data are compared with those or more conventional inlet/airframe integrations in an effort to assess the viability of top-mounted inlet systems relative to conventional inlet installations.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-81292 , A-8575
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Control system estimation and design for aerospace vehicles (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The selection of an estimator which is unbiased when applied to structural parameter estimation is discussed. The mathematical relationships for structural parameter estimation are defined. It is shown that a conventional weighted least squares (CWLS) estimate is biased when applied to structural parameter estimation. Two approaches to bias removal are suggested: (1) change the CWLS estimator or (2) change the objective function. The advantages of each approach are analyzed.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-127456
    Format: application/pdf
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  • 5
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    Control system estimation and design for aerospace vehicles with time delay (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The problems of estimation and control of discrete, linear, time-varying systems are considered. Previous solutions to these problems involved either approximate techniques, open-loop control solutions, or results which required excessive computation. The estimation problem is solved by two different methods, both of which yield the identical algorithm for determining the optimal filter. The partitioned results achieve a substantial reduction in computation time and storage requirements over the expanded solution, however. The results reduce to the Kalman filter when no delays are present in the system. The control problem is also solved by two different methods, both of which yield identical algorithms for determining the optimal control gains. The stochastic control is shown to be identical to the deterministic control, thus extending the separation principle to time delay systems. The results obtained reduce to the familiar optimal control solution when no time delays are present in the system.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-127464
    Format: application/pdf
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  • 6
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    Design of non-interacting multivariable discrete time systems (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The theory of decoupling a multivariable system with the help of state variable feedback is applied to discrete time systems. The system differential equations in the continuous time domain are converted to a discrete time representation. A discrete time controller is designed to control the overall input to the system such that a specified desired decoupled output response is obtained. The decoupled system behaves as a set of single-input, single-output systems and state variable techniques can be easily applied to control each output individually. Control is achieved by periodically sampling the inputs and all the states and feeding them back through a controller. For linear time invariant systems the control is time invariant. The basic theory of decoupling involves feeding back all the states twice, first to decouple the system and then to achieve a desired response. The states of the system are computed with the help of a state estimator which calculates all the present states of the system so that on-line control can be applied to real time systems. The theory is applied to a model of a nuclear rocket engine.
    Keywords: ELECTRONICS
    Type: NASA-CR-125574
    Format: application/pdf
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  • 7
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    Airframe effects on top-mounted inlet systems for VSTOL fighter aircraft (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Inlet flow-field and compressor-face performance data were obtained for a 0.095-scale model of a VSTOL fighter-attack aircraft configuration with twin top-mounted inlets. Tests were conducted at Mach numbers from 0.6 to 2.0 and at angles of attack and sideslip up to 27 deg and 12 deg, respectively. The effects of inlet location, wing leading-edge extension planform area, canopy-dorsal integration, and variable incidence canards were determined. The results show that distortion at the compressor face when maneuvering is relatively low (20% or less) at Mach numbers up to 0.9. However, at Mach numbers of 1.2 and above, maneuverability may be restricted because of high distortion or low pressure recovery (80% or less) or both.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 81-2631 , V/STOL Conference; Dec 07, 1981 - Dec 09, 1981; Palo Alto, CA
    Format: text
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  • 8
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    Control system design using optimization techniques Final report (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Optimization techniques for control of fuel valve systems for air breathing jet engines and 40-60 inlet control problems
    Keywords: ELECTRONICS
    Type: NASA-CR-109405
    Format: application/pdf
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  • 9
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    Research in and application of state variable feedback design of guidance control systems for aerospace vehicles Progress report (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Weighted least squares parameter estimation, Kalman filter, and random search problems for aerospace guidance control system design
    Keywords: ELECTRONICS
    Type: NASA-CR-109451
    Format: application/pdf
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  • 10
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    The control of nonlinear stochastic control systems under discounted performance criteria (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Control algorithm for optimization of nonlinear stochastic processes with discounted performance criteria
    Keywords: MATHEMATICS
    Type: NASA-CR-116417
    Format: application/pdf
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