Secondary Injection Thrust Vector Control Power Plant Linearisation using Fuzzy Logic for a Launch Vehicle

2002 ◽  
Vol 52 (4) ◽  
pp. 409-416
Author(s):  
S. Subha Rani ◽  
S. Sibi ◽  
P.P. Mohanlal
Keyword(s):  
Fuzzy Logic ◽  
Power Plant ◽  
Vector Control ◽  
Launch Vehicle ◽  
Thrust Vector Control ◽  
Control Power ◽  
Thrust Vector ◽  
Secondary Injection

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 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.

High redundancy electromechanical actuator for thrust vector control of a launch vehicle

2019 ◽  
Vol 91 (8) ◽  
pp. 1122-1132 ◽  
Author(s):  
Biju Prasad B. ◽  
Biju N. ◽  
Radhakrishna Panicker M.R.
Keyword(s):  
Fault Detection ◽  
Vector Control ◽  
Design Methodology ◽  
Launch Vehicle ◽  
Human Beings ◽  
Electromechanical Actuator ◽  
Content Type ◽  
Thrust Vector Control ◽  
Thrust Vector ◽  
Control Application

Purpose The purpose of this paper is to design an electromechanical actuator which can inherently tolerate a stuck or loose failure without any need for fault detection isolation and reconfiguration. Design/methodology/approach Generalized design methodology for a thrust vector control application is adopted to reduce the design iterations during the initial stages of the design. An optimum ball screw pitch is selected to minimize the motor sizing and maximize the load acceleration. Findings A high redundancy electromechanical actuator for thrust vector control has lower self-inertia and higher reliability than a direct drive simplex configuration. This configuration is a feasible solution for thrust vector control application because it offers a more acceptable and graceful degradation than a complete failure. Research limitations/implications Future work will include testing on actual hardware to study the transient disturbances caused by a fault and their effect on launch vehicle dynamics. Practical implications High redundancy electromechanical actuator concept can be extended to similar applications such as solid motor nozzle in satellite launch vehicles and primary flight control system in aircraft. Social implications High redundancy actuators can be useful in safety critical applications involving human beings. It can also reduce the machine downtime in industrial process automation. Originality/value The jam tolerant electromechanical actuator proposed for the launch vehicle application has a unique configuration which does not require a complex fault detection isolation and reconfiguration logic in the controller. This enhances the system reliability and allows a simplex controller having a lower cost.

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