Author: R. W. MilliganPublisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Two Dimensional Gaseous Secondary Injection Study of Rocket Thrust Vector Control
Study of Secondary Injection Thrust Vector Control
Author: Harold R. HenryPublisher:
ISBN:
Category :
Languages : en
Pages : 64
Book Description
The report presents the fundamental equations of fluid mechanics have been applied to particular steady-state models of the interaction between secondary and primary fluids. The analysis has resulted in a system of equations and a numerical procedure which is amenable to solution by use of a high speed digital computer. A dimensional analysis has been performed and is presented herein as a guide to the performance of experiments and to the comparison between experimental and theoretical results. An experimental program has been planned within the scope of this project and is presented in the progress report dated July, 1965. The general discussion of three cases for which the shape of the secondary jet has been obtained is presented in the body of the report. A detailed presentation of one of the cases is presented in the appendix. The analysis and computation for the latter case was written as a Master's Thesis. (Author).
Proportional Solid Propellant Secondary Injection Thrust Vector Control Study
Author: Handbuch der grundsätzlichen Forstwirthschaft im Staate Altenburg
Author: An Experimental Investigation of Thrust Vector Control by Secondary Injection
Author: Richard D. GuhsePublisher:
ISBN:
Category : Injections
Languages : en
Pages : 130
Book Description
An experimental investigation was conducted to examine the flow field produced when a secondary gas is injected into a supersonic primary stream. A preliminary analytical investigation revealed that several parameters (such as the primary and secondary gas properties, flow conditions and geometrical parameters) were influential in determining the nature of the flow field produced by secondary injection and the resulting side force. The investigation reported herein is concerned with the results of a systematic variation of these parameters. Experiments were conducted in a Mach 2.0, two-dimensional blow down wind tunnel utilizing air as the primary and secondary gases. The secondary gas was injected through a rectangular slot extending the width of the primary nozzle. The area of the slot was varied from 1/2% to 10% of the primary nozzle throat area in five increments. For each value of slot area the secondary to primary stagnation pressure ratio was varied from 0.301 to 1.175 in six increments. The experiments were conducted for injection normal to the nozzle axis and at an angle of 10 degree upstream of this normal at an axial position where the primary Mach number was 1.90. In each case preliminary diagnostic investigations (optical) were conducted to determine the nature of the flow field.
Secondary Injection Thrust Vector Control
Author: C. A. ZimmermanPublisher:
ISBN:
Category :
Languages : en
Pages : 28
Book Description
On the basis of experimentally acquired data, thrust vector control systems utilizing secondary injection of fluids into supersonic nozzles have been developed. Several widely divergent theoretical and analytical treatments of the phenomena have appeared as new applications were proposed. The paper reviews the several theories and attempts correlation with the experimental data. Secondary injection thrust vector control results from the injection of fluid (gas or liquid) into the primary exhaust stream of the rocket motor through ports in the divergent section of the nozzle. A shock is induced resulting in a pressure unbalance in the exit cone. The resultant side force, controllable in magnitude and direction, can be utilized for precise vehicle control. (Author).
Thrust-vector Control by Secondary Injection
Author: FOY JR. MCCULLOUGHPublisher:
ISBN:
Category :
Languages : en
Pages : 1
Book Description
The technique of thrust-vector control by injection of a fluid into the exhaust stream of a nozzle (secondary injection) was explored. This paper gives a survey of work performed at the Naval Ordnance Test Station during Fiscal Year 1959, previously reported in IDP 765. Both cold-gas (air) data with 3-dimensional and 2dimensional nozzles and data obtained with a liquid-propellant applied-research motor (LPARM) are presented. Fluids studied with the LPARM were N2O4, N2 (gas), H2O, and IRFNA. Physical parameters as well as fluid properties were considered in the tests. Injection of a secondary fluid increases the main thrust of the motor as well as producing a side thrust. Thrust-vector control by secondary injection is simpler and more reliable than mechanical controls and shows promise of becoming a replacement for them. (Author).
Structural and Thermal Optimization of a Thrust Vectoring Nozzle Test Rig for Hybrid Rocket Engine
Author: Samyak RatnakarPublisher:
ISBN:
Category :
Languages : en
Pages : 169
Book Description
Thrust vector control is an important aspect of rocket engine operation. Current trends and prospective propulsion architectures place an increasing need for higher performance and cost-effective thrust vectoring systems. A promising method to address these requirements is a secondary injection thrust vector control system. This operates on the principal of differential injection of secondary fluids into the primary nozzle to affect a change in the vector of the thrust. A study was conducted on a hybrid rocket engine which was married to this kind of secondary injection thrust vector control system. The aim of this study was to obtain data about the combined thermal-structural and fluidic interactions of the propellant with the structure of the rocket engine. The aim of this project was twofold primary to optimize a secondary injection thrust vector control nozzle and secondary to develop a HGITVC system. A CFD study of the nozzle was conducted this was implemented in conjunction with a thermal-structural analysis of the engine. The results obtained from this directed the optimization of both the primary and the secondary nozzles. A detailed valve selection process was carried out for implementation of HGITVC. The nozzle optimization for the HGITVC utilized the Rao method of characteristics. The analysis for hot gas injection based on the valve limit was carried out. The hot gas injection studies were carried out for three non-dimensional axial locations of 1.5, 2 and 2.5.*****Thrust vector control is an important aspect of rocket engine operation. Current trends and prospective propulsion architectures place an increasing need for higher performance and cost-effective thrust vectoring systems. A promising method to address these requirements is a secondary injection thrust vector control system. This operates on the principal of differential injection of secondary fluids into the primary nozzle to affect a change in the vector of the thrust. A study was conducted o
A STUDY OF ROCKET THRUST CONTROL BY GAS INJECTION.
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 123
Book Description
A theoretical and experimental investigation of thrust control by secondary gas injection was completed. Thrust control is treated from the two aspects of thrust modulation and vector control. The thrust modulation study is concerned with the use of injection as a means of throttling the main nozzle flow. The performance (flow throttling and thrust) of a variety of secondary injection configurations was measured with a low pressure-ratio, axially symmetric nozzle as well as a high pressure-ratio, two-dimensional nozzle. The flow throttling results agree with an anlysis based on three flow models and the schlieren photographs (from the two-dimensional tests) show that all three types of flow occur. The vector control study concerns asymmetric secondary gas injection as a means of controlling the direction of the thrust vector.
Thrust Vector Control by Secondary Injection
Author: Douglas Stacey (University of Manitoba student)Publisher:
ISBN:
Category :
Languages : en
Pages : 68
Book Description