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AIAA JOURNAL 1963年第6期1卷 1375-1380页

作者： CARTWRIGHT, WF MASSINGILL, EC TRUEBLOOD, RD General Motors Corporation Goleta Calif.

The use of passive nutation dampers to confine the angular velocity of spinning vehicles to the axis of major moment of inertia is reviewed briefly. A physical description of the damper action is given and a simple set of approximate equations provided. Exact solutions of the equations describing the motion of the circular constraint nutation damper are compared with experimental results that verify the analysis. Expressions suitable for preliminary damper design are derived, with a short discussion of multiple dampers and fluid dampers. © 1963 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

关键词： Nutation Damping Coefficient of Friction Fluid Flow Artificial Satellites control system design Numerical Integration Power Supplies Earth

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AIRCRAFT PERFORMANCE BENEFITS FROM MODERN control systemS TECHNOLOGY

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Journal of Aircraft 1970年第6期7卷 550-553页

作者： HOLLOWAY RB JOHANNES PMBURRISRP The Boeing Company Wichita Kansas U.S. Air Force Wright-Patterson Air Force Base Ohio

This paper discusses potential gains in airplane performance which may be offered by some applications of modern flight controls technology. The concepts examined include relaxation of inherent static stability ride quality control, flutter margin control, and maneuver load control. A brief description of each concept, and examples of potential benefits in terms of weight and/or drag improvements are included.

关键词： Aircraft Performance control system design Flight control design Supersonic Airplane Stability Augmentation Aircraft design Structural Weight Landing Gear Mean Aerodynamic Chord Dutch Roll

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Survey of dynamic analysis methods for flight control design

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Journal of Aircraft 1969年第2期6卷 81-98页

作者： Robinson, Alfred C. Battelle Memorial Institute ColumbusOH United States

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RELATIVE INFLUENCE OF ATMOSPHERIC PROPERTIES ON LAUNCH VEHICLE design

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JOURNAL OF SPACECRAFT AND ROCKETS 1967年第2期4卷 224-&页

作者： BIEBER, RE Lockheed Missiles & Space Company Huntsville Ala.

The relative influence of various atmospheric properties and disturbances on launch vehicle flight dynamic response is studied. Results are obtained for the Atlantic Missile Range Reference Atmosphere and a dynamic model of the Saturn V vehicle. The aerodynamic loading during boosted flight is influenced only slightly by the choice of reference atmosphere for that launch site over the corresponding standard or extreme atmospheric model. For winds/turbulence analyses, a digital filter for separating detailed wind profiles into a low- frequency component (winds) and a high-frequency component (turbulence) is proposed. For a Saturn V vehicle with “attitude” control, the effect of turbulence on the predicted control system and structural load response is small relative to the wind contribution. This is shown for various discrete and random representations of the wind and turbulence processes. © 1967 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

关键词： Launch Vehicle design Harmonic Analysis Atlantic Missile Range Spectral Density Dynamic Response control system design Attitude control system Aerodynamic Loads Air Force Base Dynamic Pressure

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DYNAMICS OF VARIABLE THRUST, PUMP FED, BIPROPELLANT, LIQUID ROCKET ENGINE system

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JET PROPULSION 1957年第1期27卷 35-43页

作者： GORE, MR CARROLL, JJ Aerojet-General Corporation Azusa Calif.

Principal dynamic characteristics established over broad thrust range by analog computer simulation of nonlinear physical elements;several basic types of control elements studied, and control system capable of meeting... 详细信息

关键词： Liquid Rocket Engine Bipropellants Thrust Rocket Engine Performance control system design Frequency Response Nonlinear Equation Chamber Pressure Closed Loop control Turbine Wheels

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ADVANCED SPACECRAFT STABILIZATION AND control TECHNIQUES

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JOURNAL OF SPACECRAFT AND ROCKETS 1968年第12期5卷 1377-+页

作者： SABROFF, AE TRW Systems Redondo Beach Calif.

Technology is very near to reaping the benefits of modern control theory, and such application will become commonplace with the advent of onboard (or online ground-based), general-purpose digital computation. Gains in the capabilities of advanced SCS will initiate complementary technological gains in the control logic, control sensors, and control power subsystems disciplines;and the predictable advances in these areas will allow considerable latitude for corresponding spacecraft stabilization and control systems improvements. Although the basic SCS categories are well understood, significant value still is placed upon how a specific set of requirements is satisfied within their framework. The hybrid system provides the greatest flexibility, but there has been little exploration of its quantitative advantages over the various competing systems. © 1968 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

关键词： Interplanetary Spacecraft control system design Inertial Guidance systems Aerospace system Unmanned system Attitude control system Earth Orbiting Geophysical Observatory Hybrid Propellants Spacecraft Attitude

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HANDLING QUALITIES FOR PILOT control OF APOLLO LUNAR-LANDING SPACECRAFT

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JOURNAL OF SPACECRAFT AND ROCKETS 1966年第5期3卷 632-&页

作者： CHEATHAM, DC HACKLER, CT NASA Manned Spacecraft Center Houston Texas

Piloted simulations of the lunar-landing maneuver were conducted at the Manned Spacecraft Center to determine control problems and required handling qualities of lunar-landing spacecraft. The studies examined control problems and handling qualities required to complete the final approach to landing starting from ranges of 2000 to 3000 ft from the desired landing site. Results of the simulation studies indicated that satisfactory handling qualities could be obtained with control powers of the order of 10 deg/sec²for the rate command control using proportional firing thrusters, and that control powers of the order of 5 deg/sec²provided satisfactory handling qualities for the rate command control system employing on-off thruster firing logic. Within a satisfactory range of maximum rate command and control power available, the pilots tolerated equivalent time constants up to 1 sec in the proportional system and equivalent time constants of the order of 3 sec in the on-off thruster logic control system. In addition, the simulation studies showed that the direct on-off logic control system (no rate feed-back) would probably not provide satisfactory control handling qualities for the lunar landing. © 1966 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

关键词： Handling Qualities Lunar Landing Spacecrafts Pilot control control system design Manned Spacecraft Command and control systems Pilot Attitude control system Flight Vehicle

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