Rocket Engine Thrust Vector Control Operation Through Secondary Injection

1964 ◽  
Author(s):  
A. B. Billet
Keyword(s):  
Vector Control ◽  
Rocket Engine ◽  
Control Operation ◽  
Thrust Vector Control ◽  
Engine Thrust ◽  
Thrust Vector ◽  
Secondary Injection

scholarly journals Development of a structural schematic of a bifunctional system for rocket engine thrust vector control

2018 ◽  
Vol 2018 (4) ◽  
pp. 57-67 ◽  
Author(s):  
G.A. Strelnykov ◽  
◽  
E.L. Tokareva ◽  
N.S. Pryadko ◽  
A.D. Yhnatev ◽  
...  
Keyword(s):  
Vector Control ◽  
Rocket Engine ◽  
Thrust Vector Control ◽  
Engine Thrust ◽  
Thrust Vector

scholarly journals Increasing the efficiency of an interceptor system for rocket engine thrust vector control

2020 ◽  
Vol 2020 (4) ◽  
pp. 13-28
Author(s):  
H.O. Strelnykov ◽  
◽  
O.L. Tokareva ◽  
O.D. Ihnatiev ◽  
N.S. Pryadko ◽  
...  
Keyword(s):  
Supersonic Flow ◽  
Vector Control ◽  
Rocket Engine ◽  
Control Force ◽  
Thrust Vector Control ◽  
Engine Thrust ◽  
Gas Dynamic ◽  
Working Medium ◽  
Combined Control ◽  
Thrust Vector

This work is concerned with studying the static and dynamic characteristics of the gas-dynamic (interceptor) subsystem of a combined system for thrust vector control and identifying ways to increase its efficiency. The combined control system includes a mechanical and a gas-dynamic subsystem. The gas-dynamic thrust vector control subsystem is the most important and reliable part of the combined control system. Consideration is given to disturbing the supersonic flow by installing a solid obstacle (interceptor) in the middle part of the rocket engine nozzle. An important advantage of this method to gas-dynamically control the rocket engine thrust vector is that the thrust vector control loss of the specific impulse is nearly absent because the control force is produced without any consumption of the working medium. Injection through the interceptor protects it against exposure to the nozzle supersonic flow and produces an additional lateral force. By now, the optimum height of the mass supply opening in the interceptor that maximizes the control force has not been determined, and the dynamic characteristics of this system have not been studied. The aim of this work is to find the optimum position of the opening for working medium supply through the interceptor that maximizes the added control force and to determine the effect of the transfer functions of the interceptor system components on the characteristics of the control force production transient. As a result of the study of the static characteristics of the supersonic flow disturbance in a nozzle with an interceptor through which a secondary working medium is injected, it is concluded that in terms of thrust vector control efficiency and interceptor protection the injection opening should be situated in the upper part of the interceptor. The transfer function of interceptor control of the liquid-propellant rocket engine thrust vector is obtained with account for the production of an additional control force by the injection of a liquid propellant component. It is found that the loss of stability of the operation of an injection interceptor unit depends on the transient of the working medium injection control valve.

scholarly journals Dynamic characteristics of a combined system for rocket engine thrust vector control

2019 ◽  
Vol 2019 (3) ◽  
pp. 16-29
Author(s):  
E.L. Tokareva ◽  
◽  
N.S. Pryadko ◽  
K.V. Ternova ◽  
◽  
...  
Keyword(s):  
Vector Control ◽  
Dynamic Characteristics ◽  
Rocket Engine ◽  
Combined System ◽  
Thrust Vector Control ◽  
Engine Thrust ◽  
Thrust Vector

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

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.

Theoretical Aspects of Thrust Vector Control by Secondary Gas Injection in Rocket Nozzles

1968 ◽  
Vol 72 (686) ◽  
pp. 171-177 ◽  
Author(s):  
John H. Neilson ◽  
Alastair Gilchrist ◽  
Chee K. Lee
Keyword(s):  
Vector Control ◽  
Three Dimensional ◽  
Two Dimensional ◽  
Three Dimensional Flow ◽  
Side Force ◽  
Thrust Vector Control ◽  
Dimensional Flow ◽  
Two Dimensional Flow ◽  
Thrust Vector ◽  
Secondary Injection

This work deals with theoretical aspects of thrust vector control in rocket nozzles by the injection of secondary gas into the supersonic region of the nozzle. The work is concerned mainly with two-dimensional flow, though some aspects of three-dimensional flow in axisymmetric nozzles are considered. The subject matter is divided into three parts. In Part I, the side force produced when a physical wedge is placed into the exit of a two-dimensional nozzle is considered. In Parts 2 and 3, the physical wedge is replaced by a wedge-shaped “dead water” region produced by the separation of the boundary layer upstream of a secondary injection port. The modifications which then have to be made to the theoretical relationships, given in Part 1, are enumerated. Theoretical relationships for side force, thrust augmentation and magnification parameter for two- and three-dimensional flow are given for secondary injection normal to the main nozzle axis. In addition, the advantages to be gained by secondary injection in an upstream direction are clearly illustrated. The theoretical results are compared with experimental work and a comparison is made with the theories of other workers.

scholarly journals Thrust Vector Control of an Upper-Stage Rocket with Multiple Propellant Slosh Modes

2012 ◽  
Vol 2012 ◽  
pp. 1-18 ◽  
Author(s):  
Jaime Rubio Hervas ◽  
Mahmut Reyhanoglu
Keyword(s):  
Vector Control ◽  
Center Of Mass ◽  
Nonlinear Feedback ◽  
Thrust Vector Control ◽  
Engine Thrust ◽  
Mass Spring Model ◽  
Upper Stage ◽  
Thrust Vector ◽  
Mass Spring ◽  
Main Engine

The thrust vector control problem for an upper-stage rocket with propellant slosh dynamics is considered. The control inputs are defined by the gimbal deflection angle of a main engine and a pitching moment about the center of mass of the spacecraft. The rocket acceleration due to the main engine thrust is assumed to be large enough so that surface tension forces do not significantly affect the propellant motion during main engine burns. A multi-mass-spring model of the sloshing fuel is introduced to represent the prominent sloshing modes. A nonlinear feedback controller is designed to control the translational velocity vector and the attitude of the spacecraft, while suppressing the sloshing modes. The effectiveness of the controller is illustrated through a simulation example.

scholarly journals Numerical Simulation of Nozzle Flow Field with Secondary Injection Thrust Vector Control

2018 ◽  
Vol 179 ◽  
pp. 01003
Author(s):  
H.R. Noaman ◽  
Tang Hai Bin ◽  
Elsayed Khalil
Keyword(s):  
Vector Control ◽  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Stagnation Pressure ◽  
Injection Angle ◽  
Thrust Vector Control ◽  
Thrust Vector ◽  
Shock Impingement ◽  
Secondary Injection

Numerical simulations are performed to characterize the secondary injection thrust vector control. For this objective the following measurements were taken: considering the flow to be compressible and turbulent using Realizable k-ε turbulence model accompanied by enhanced wall treatment, the comparison between the CFD results and the experimental results shows a very good agreement. Then a parametric study on injection mass flow rate (changing secondary stagnation pressure) with the same injection location and injection angle is done. The results stated that increasing the injectant mass flow rate lead to shock impingement from opposite wall at secondary stagnation pressure 1.4 of the primary stagnation pressure.

Sign in / Sign up

Export Citation Format

Share Document