The design and implementation of a laboratory-oriented generalized variable-order digital compensator
Computer design to realize digital filter to be used as compensator in hybrid simulation of Saturn 5 thrust vector control system
Carroll, C. C.↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Mission constraints on solid-propellant motors for unmanned spacecraft.
Mission and planetary vehicles characteristics affecting design of solid propellant motors and thrust vector control systems in planetary orbiters and landers
Cork, M. J.↗
Controllability of nonlinear systems with linearly occurring controls
Nonlinear system controllability by application of linear control vectors
Haynes, G. W.↗
On the determination of the optimal constant output feedback gains for linear multivariable systems
Optimal constant output feedback gains for linear multivariable systems, noting control vector as time invariant function of output vector
Athans, M.↗
Design considerations and requirements for integrating an electric propulsion system into the SERT II and future spacecraft
Electric propulsion systems integration into SERT 2 spacecraft, discussing launch imposed environment, thrust vector control, thrustor breakdown, power conditioning, etc
Rulis, R. J.↗
SERT II - Design requirements for integrating electric propulsion into a spacecraft
Electric propulsion systems integration into SERT 2 spacecraft, discussing launch imposed environment, thrust vector control, thrustor breakdown, power conditioning, etc
Rulis, R. J.↗
Vectoring of the beam from ion bombardment thrusters
Beam vector control from ion bombardment thrustors with dual grid electrostatic, movable screen electrode and discharge chamber extraction systems
Collett, C. R.↗
Redundancy management of electrohydraulic servoactuators by mathematical model referencing
A description of a mathematical model reference system is presented which provides redundancy management for an electrohydraulic servoactuator. The mathematical model includes a compensation network that calculates reference parameter perturbations induced by external disturbance forces. This is accomplished by using the measured pressure differential data taken from the physical system. This technique was experimentally verified by tests performed using the H-1 engine thrust vector control system for Saturn IB. The results of these tests are included in this report. It was concluded that this technique improves the tracking accuracy of the model reference system to the extent that redundancy management of electrohydraulic servosystems may be performed using this method.
Campbell, R. A.↗
Feasibility Study of a Pressure-fed Engine for a Water Recoverable Space Shuttle Booster
Detailed mass properties are presented for a gimbaled, fixed thrust, regeneratively cooled engine having a coaxial pintle injector. The baseline design parameters for this engine are tabulated. Mass properties are also summarized for several other engine configurations i.e., a hinge nozzle using a Techroll seal, a gimbaled duct cooled engine and a regeneratively cooled engine using liquid injection thrust vector control (LITVC). Detailed engine analysis and design trade studies leading to the selection of a regeneratively cooled gimbaled engine and pertaining to the selection of the baseline design configuration are also given.
Gerstl, E.↗
Actuator participation in a bending mode identification system
A hydraulic actuator designed for a thrust vector control system used as a shaker for a vehicle to determine the bending mode frequencies is described. The actuator is used as the prime mover and the frequency sensor for the flexible vehicle in a test tower. Advantages in using the actuator piston position with respect to a commanded position to obtain the bending mode frequencies are shown.
Thompson, Z.↗
Technology for low cost solid rocket boosters.
A review of low cost large solid rocket motors developed at the Lewis Research Center is given. An estimate is made of the total cost reduction obtainable by incorporating this new technology package into the rocket motor design. The propellant, case material, insulation, nozzle ablatives, and thrust vector control are discussed. The effect of the new technology on motor cost is calculated for a typical expandable 260-in. booster application. Included in the cost analysis is the influence of motor performance variations due to specific impulse and weight changes. It is found for this application that motor costs may be reduced by up to 30% and that the economic attractiveness of future large solid rocket motors will be improved when the new technology is implemented.
Ciepluch, C.↗
The staging dynamics of a proposed space shuttle configuration
A mathematical model was developed to simulate the staging dynamics of a proposed space shuttle configuration. Included in the mathematical model is the kinematics and dynamics of the staging mechanism, thrust forces and thrust vector control, rigid-body dynamics, and structural dynamics of both the booster and orbiter stages of the configuration. The mathematical model was incorporated into a computer program so that the staging maneuver could be simulated. Results of the simulations are presented.
Hamilton, D. A.↗
Computation of optimal output-feedback compensators for linear time-invariant systems
The control of linear time-invariant systems with respect to a quadratic performance criterion was considered, subject to the constraint that the control vector be a constant linear transformation of the output vector. The optimal feedback matrix, f*, was selected to optimize the expected performance, given the covariance of the initial state. It is first shown that the expected performance criterion can be expressed as the ratio of two multinomials in the element of f. This expression provides the basis for a feasible method of determining f* in the case of single-input single-output systems. A number of iterative algorithms are then proposed for the calculation of f* for multiple input-output systems. For two of these, monotone convergence is proved, but they involve the solution of nonlinear matrix equations at each iteration. Another is proposed involving the solution of Lyapunov equations at each iteration, and the gradual increase of the magnitude of a penalty function. Experience with this algorithm will be needed to determine whether or not it does, indeed, possess desirable convergence properties, and whether it can be used to determine the globally optimal f*.
Platzman, L. K.↗
Solar electric propulsion thrust subsystem development
The Solar Electric Propulsion System developed under this program was designed to demonstrate all the thrust subsystem functions needed on an unmanned planetary vehicle. The demonstration included operation of the basic elements, power matching input and output voltage regulation, three-axis thrust vector control, subsystem automatic control including failure detection and correction capability (using a PDP-11 computer), operation of critical elements in thermal-vacuum-, zero-gravity-type propellant storage, and data outputs from all subsystem elements. The subsystem elements, functions, unique features, and test setup are described. General features and capabilities of the test-support data system are also presented. The test program culminated in a 1500-h computer-controlled, system-functional demonstration. This included simultaneous operation of two thruster/power conditioner sets. The results of this testing phase satisfied all the program goals.
Masek, T. D.↗
Space Shuttle system solid rocket booster.
Description of the mission and systems requirement of the solid rocket booster as it supports the Shuttle vehicle configuration. The solid booster is equipped with load skirts and linkages that can accommodate full mission loads, a solid propellant motor for delivering required performance, thrust vector control for augmentation of Shuttle vehicle ascent control, staging and separation systems, and electrical subsystems. To recover and reuse the solid booster case a recovery package is provided. The definition of these functional elements of the solid booster are discussed with the requirements placed on each element to satisfy the overall booster objective.
Thomason, H. E.↗
System integration considerations for the Space Shuttle.
Description of some system integration studies which were carried out to define design requirements ensuring compatibility and satisfactory performance of individual Space Shuttle elements. Studies considered include definition of a vehicle concept providing a tradeoff between development and flight costs, evaluation of the need for booster thrust vector control, and analysis of optimum methods for vehicle control in aerodynamic flight.
Silveira, M. A.↗
Effect of engine shroud configuration on the static aerodynamic characteristics of a 0.00563 scale 142-inch diameter solid rocket booster (SA10F)
A test of a 0.563 percent scale space shuttle Solid Rocket Booster (SRB) model, MSFC Model 449, was conducted in a trisonic wind tunnel. Test Mach numbers were 0.4, 0.6, 0.9, 1.2, 1.96, 3.48, 4.0, 4.45, and 4.96. Test angles-of-attack ranged from minus 10 degrees to 190 degrees. Test Reynolds numbers ranged from 3.0 million per foot to 8.6 million per foot. Test roll angles were 0, 11.25, 22.5, 45, and 90 degrees. In addition to the static stability evaluation of the primary SRB configuration, five parametric investigations were made: (1) effect of Reynolds number, (2) effect of engine shroud flare angle, (3) effect of engine shroud length, (4) effect of engine shroud strakes, and (5) effect of engine shroud strakes and trust vector control bottles.
Johnson, J. D.↗
SSME/side loads analysis for flight configuration, revision A
This document describes the dynamic loads analysis accomplished for the Space Shuttle Main Engine (SSME) considering the side load excitation associated with transient flow separation on the engine bell during ground ignition. The results contained herein pertain only to the flight configuration. A Monte Carlo procedure was employed to select the input variables describing the side load excitation and the loads were statistically combined. This revision includes an active thrust vector control system representation and updated orbiter thrust structure stiffness characteristics. No future revisions are planned but may be necessary as system definition and input parameters change.
Holland, W.↗