Digital compensation of the thrust vector control system Technical report, 1 Oct. 1967 - 31 Jan. 1968
Digital compensation of thrust vector control system
Phillips, C. L.↗
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Design of high power electromechanical actuator for thrust vector control
NASA-Marshall has undertaken the development of electromechanical actuators (EMAs) for thrust vector control (TVC) augmentation system implementation. The TVC EMA presented has as its major components two three-phase brushless dc motors, a two-pass gear-reduction system, and a roller screw for rotary-to-linear motion conversion. System control is furnished by a solid-state electronic controller and power supply; a pair of resolvers deliver position feedback to the controller, such that precise positioning is achieved. Peformance comparisons have been conducted between the EMA and comparable-performance hydraulic systems applicable to TVCs.
Cowan, J. R.↗
Digital compensation of the thrust vector control system Technical report, 28 May 1966 - 28 Sep. 1966
Sampled data control, quantization effects, and transfer function for Saturn 5 thrust vector control
Phillips, C. L.↗
All-fluid amplifier development for liquid rocket secondary injection thrust vector control Final report
Staged vortex amplifier with integral gas generators for liquid rocket secondary injection thrust vector control
Delozier, T. R.↗
Studies of thrust vector control of large space vehicles Final report
Display systems, fluid amplification techniques, stochastic processes, and thrust vector control systems
Boland, J. S., III↗
Design and test of a high power electromechanical actuator for thrust vector control
NASA-Marshall is involved in the development of electromechanical actuators (EMA) for thrust-vector control (TVC) system testing and implementation in spacecraft control/gimballing systems, with a view to the replacement of hydraulic hardware. TVC system control is furnished by solid state controllers and power supplies; a pair of resolvers supply position feedback to the controller for precise positioning. Performance comparisons between EMA and hydraulic TVC systems are performed.
Cowan, J. R.↗
Investigation of gaseous secondary injection thrust vector control considering primary nozzle overexpansion, frequency response, and injection angle
Performance characteristics of gaseous secondary injection thrust vector control in overexpanded primary nozzles under sea level conditions
Source record↗
The Study of Optimization of Thrust Vector Control Systems
Reliability analyses and failure probabilities of S-4B stage automatic pilots and hydraulic thrust vector control system configurations, and compatibility with actuator
Mc Intosh, J. W.↗
Analytical investigation of side jet supersonic stream interaction including vortex flow in rocket nozzles for thrust vector control
Analytical investigation of side jet supersonic stream interaction including vortex flow in rocket nozzles for thrust vector control
Comparin, R. A.↗
Spin vector control for a spinning space station. Volume 2 - Analytic manual Final report
Computer manual for calculating dynamic vector control of dual spin space station
Guderian, W.↗
Comparative study of thrust-vector-control systems for large, solid-fueled launch vehicles. Volume 1 - Summary
Comparative analysis of several advanced thrust vector control system designs applied to large, solid propellant launch vehicles
Budris, G. D.↗
Measurement of forces and moments from a thrust vector controlled rocket on a five component test stand.
Test stand for measurement of forces and moments from thrust vector controlled rocket, analyzing dynamic characteristics of hydrostatic supports
Moore, J. W.↗
Glycosyl residue composition of cell wall extracts from stems of P. deltoides WT, vector control and PdGAUT4-KD plants
Glycosyl residue composition of cell wall extracts from stems of P. deltoides WT, vector control and PdGAUT4-KD plants
bio engineered↗
Thrust vector control requirements for launch vehicles using a 260-inch solid rocket first stage
Gimbaled nozzle and liquid injection thrust vector control requirements for solid rocket two stage launch vehicles
Borsody, J.↗
PAB3D Simulations of a Nozzle with Fluidic Injection for Yaw Thrust-Vector Control
An experimental and computational study was conducted on an exhaust nozzle with fluidic injection for yaw thrust-vector control. The nozzle concept was tested experimentally in the NASA Langley Jet Exit Test Facility (JETF) at nozzle pressure ratios up to 4 and secondary fluidic injection flow rates up to 15 percent of the primary flow rate. Although many injection-port geometries and two nozzle planforms (symmetric and asymmetric) were tested experimentally, this paper focuses on the computational results of the more successful asymmetric planform with a slot injection port. This nozzle concept was simulated with the Navier-Stokes flow solver, PAB3D, invoking the Shih, Zhu, and Lumley algebraic Reynolds stress turbulence model (ASM) at nozzle pressure ratios (NPRs) of 2,3, and 4 with secondary to primary injection flow rates (w(sub s)/w(sub p)) of 0, 2, 7 and 10 percent.
Deere, Karen A.↗
Some aspects of gaseous secondary injection with application to thrust vector control
Two dimensional sonic nonreacting gaseous secondary injection into supersonic primary stream with turbulent boundary layer for application to thrust vector control
Doyle, H.↗
Viking thrust vector control dynamics using hybrid coordinates to model vehicle flexibility and propellant slosh
Viking vehicle structural flexibility and propellant sloshing effects on thrust vector control dynamics, obtaining computer simulated responses for hybrid and discrete coordinate models
Fleischer, G. E.↗
Preliminary Investigation on Battery Sizing Investigation for Thrust Vector Control on Ares I and Ares V Launch Vehicles
An investigation into the merits of battery powered Electro Hydrostatic Actuation (EHA) for Thrust Vector Control (TVC) of the Ares I and Ares V launch vehicles is described. A top level trade study was conducted to ascertain the technical merits of lithium-ion (Li-ion) and thermal battery performance to determine the preferred choice of an energy storage system chemistry that provides high power discharge capability for a relatively short duration.
Miller, Thomas B.↗