Author: A.B. BilletPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Rocket Engine Thrust Vector Control Operation Through Secondary Injection by A.B.Billet
Author: A.B. BilletRocket Engine Thrust Vector Control Operation Through Secondary Injection
Author: A. B. BilletPublisher:
ISBN:
Category : Rocket engines
Languages : en
Pages : 7
Book Description
Thrust Vector Control of Rocket Engines by Secondary Injection
Author: R. C. ParkinsonTwo Dimensional Gaseous Secondary Injection Study of Rocket Thrust Vector Control
Author: R. W. MilliganStructural 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
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).
Hot Gas Secondary Injection Thrust Vector Control Demonstration Program
Author: Paul D. NancePublisher:
ISBN:
Category :
Languages : en
Pages : 81
Book Description
This program was established to design, develop, and demonstrate a hot gas secondary injection thrust vector control system (HGSITVC) for large solid propellant rocket motors. Phase 1 of the program is concerned with the design, analysis, and optimization of a 156 in. dia motor HGSITVC system. The data from this baseline design will be used to design six test pintle valves for demonstration on 65 in. dia test motors. Phase 2 consists of designing a four-valve 120 in. dia motor HGSITVC system using the basic designs and design data developed under Phase 1. The 120 in. dia test motor will be designed, fabricated, and tested to demonstrate four full scale 156 in. dia motor pintle valves. The pintle valve will use a proven tungsten-to-tungsten valve seating arrangement and a pressure balance technique to minimize actuation force requirements. A baseline 156 in. dia demonstration test motor which uses available proven MINUTEMAN hardware was designed. The test motor will expose the full scale 156 in. pintle valve to simulated flow and operational pressure environments. The propellant for the demonstration test motor was tailored to define the required formulation, and the major components for the first Phase 1 test were ordered. Four satisfactory orifice forgings were shipped.
Hot Gas Secondary Injection Thrust Vector Control Demonstration Program
Author: Carver G. KennedyPublisher:
ISBN:
Category :
Languages : en
Pages : 99
Book Description
This program was established to design, develop, and demonstrate a hot gas secondary injection thrust vector control system (HGSITVC) for large solid propellant rocket motors. Phase I of the program was the design, analysis, and optimization of a 156 in. diameter motor HGSITVC system. The data from this baseline design was used to design four test pintle valves for demonstration on 65 in. diameter test motors. Phase II consisted of designing a four valve, 120 in. diameter motor HGSITVC system using the basic designs and design data developed under Phase I. The 120 in. diameter test motor demonstrated four full scale 156 in. diameter motor pintle valves. The 156 in. diameter motor uses 16 pintle valves of the design tested. (Author).
Hot Gas Secondary Injection Thrust Vector Control Demonstration Program
Author: Carver G. KennedyPublisher:
ISBN:
Category :
Languages : en
Pages : 382
Book Description
This program was established to design, develop, and demonstrate a hot gas secondary injection thrust vector control system (HGSITVC) for large solid propellant rocket motors. Phase I of the program was the design, analysis, and optimization of a 156 in. diameter motor HGSITVC system. The data from this baseline design was used to design four test pintle valves for demonstration on 65 in. diameter test motors. Phase II consisted of designing a four valve, 120 in. diameter motor HGSITVC system using the basic designs and design data developed under Phase I. The 120 in. diameter test motor demonstrated four full scale 156 in. diameter motor pintle valves. The 156 in. diameter motor uses 16 pintle valves of the design tested. (Author).
Chamber Gas Secondary Injection Thrust Vector Control for High Performance Solid Rocket Motors
Author: J. R. StevensPublisher:
ISBN:
Category :
Languages : en
Pages : 60
Book Description
The primary objectives of this program are (1) to demonstrate a thrust vector control (TVC) system optimized for overall propulsion efficiency for advanced upper-stage ICBM rocket motors, and (2) to provide the data and technology necessary for design of future TVC systems. The proposed TVC system is comprised of four poppet valves mounted 90 deg apart on a submerged nozzle. Three nonactuated versions of the submerged hot gas valve were evaluated by static testing. The primary difference between the three designs was the length of the dam enshrouding the centerbody and pintle in the subsonic portion of the valve. (Author).