Solid-State Thrust Vector Control Systems

Computational fluid dynamics methodology was used in characterising jet vane based thrust vector control systems of tactical missiles. Three-dimensional Reynolds Averaged Navier-Stokes equations were solved along with two-equation turbulence model for different operating conditions. Nonlinear regression analysis was applied to the detailed CFD database to evolve a mathematical model for the thrust vector control system. The developed model was validated with series of ground based 6-Component static tests. The proven methodology is applied toa new configuration.Defence Science Journal, Vol. 65, No. 4, July 2015, pp. 261-264, DOI: http://dx.doi.org/10.14429/dsj.65.7960

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Maintenance and Support of Hydraulic Thrust Vector Control Systems for Long-Term Unattended Storage

Journal of Engineering for Industry ◽

10.1115/1.3667556 ◽

1963 ◽

Vol 85 (1) ◽

pp. 108-114 ◽

Cited By ~ 1

Author(s):

Nicholas N. Fruktow ◽

Leo E. Gatzek

Keyword(s):

Vector Control ◽

Control Systems ◽

Storage Period ◽

General Nature ◽

Thrust Vector Control ◽

Long Term Storage ◽

Ballistic Missiles ◽

Operational Readiness ◽

Thrust Vector

Second-generation ballistic missiles are being developed for compatibility with the concept of long-term storage in permanent underground housing, with missiles in firing position, and in a condition of full operational readiness. It is intended that operational status be maintainable without major interruption over a three-year storage period. This report investigates the various factors which are considered to significantly influence the capability of hydraulic thrust vector control systems to remain in a state of operational readiness when subjected to such periods of inert storage as components of total missile configurations. The following sections present a detailed outline of technical difficulties which may be encountered, information and data resulting from applicable test programs, and the general nature of solutions to apparent problems. The design concept of a storable hydraulic thrust control system is considered to be feasible, but may be effectively achieved only by fulfillment of certain stringent design requirements and by further development of preservation techniques to preclude the need for in-field maintenance.

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The Evaluation of Thrust Vector Control Systems for Advanced, Controllable, Solid-propelled Interceptor Motors

10.4271/730942 ◽

1973 ◽

Author(s):

D. C. Sayles

Keyword(s):

Vector Control ◽

Control Systems ◽

Thrust Vector Control ◽

Thrust Vector

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The Practical Design of Fluid Injection Thrust Vector Control Systems

10.4271/640205 ◽

1964 ◽

Author(s):

R. M. Salemka

Keyword(s):

Vector Control ◽

Control Systems ◽

Fluid Injection ◽

Thrust Vector Control ◽

Practical Design ◽

Thrust Vector

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Rocket engine thrust vector control by detonation product injection into the supersonic portion of the nozzle

Technical mechanics ◽

10.15407/itm2020.04.029 ◽

2020 ◽

Vol 2020 (4) ◽

pp. 29-34

Author(s):

S.S. Vasyliv ◽

◽

H.O. Strelnykov ◽

Keyword(s):

Supersonic Flow ◽

Vector Control ◽

Control Systems ◽

Main Shock ◽

Rocket Engine ◽

Lateral Force ◽

Detonation Products ◽

Thrust Vector Control ◽

Engine Thrust ◽

Thrust Vector

For solving non-traditional problems of rocket flight control, in particular, for the conditions of impact of a nuclear explosion, non-traditional approaches to the organization of the thrust vector control of a rocket engine are required. Various schemes of gas-dynamic thrust vector control systems that counteract impact actions on the rocket were studied. It was found that the dynamic characteristics of traditional gas-dynamic thrust vector control systems do not allow one to solve the problem of counteracting impact actions on the rocket. Appropriate dynamic characteristics can provide a perturbation of the supersonic flow by injecting into the nozzle the detonation products with the main shock wave propagating in the supersonic flow. This way to perturb the supersonic flow in a rocket engine nozzle is investigated in this paper. In order to identify the principles of producing control forces and provide a perturbation of the supersonic flow by injecting into the nozzle the detonation products with the main shock wave propagating in the supersonic flow, a computer simulation of the nozzle flow was performed. The nozzle of the 11D25 engine developed by Yuzhnoye State Design Office and used in the third stage of the Cyclone-3 launch vehicle was taken as a basis. The thrust vector control scheme relies on the use of the main fuel component detonation. The evolution of the detonation wave in the supersonic flow of the combustion chamber nozzle was simulated numerically. According to the nature of the perturbation propagation in the nozzle, the lateral force from the perturbation has an alternating character with the perturbation stabilization in sign and magnitude when approaching the critical nozzle section. The value of the relative lateral force is sufficient for counteracting large disturbing moments of short duration. Thus, the force factors that can be used to control the rocket engine thrust vector are identified. Further research should focus on finding the optimal location of the detonation product injection in order to prevent mutual compensation of force factors.

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