Hot Gas Secondary Injection Thrust Vector Control Demonstration Program PDF Download
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Author: Carver G. Kennedy Publisher: 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).
Author: Carver G. Kennedy Publisher: 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).
Author: Carver G. Kennedy Publisher: 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).
Author: Paul D. Nance Publisher: 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.
Author: Paul D. Nance Publisher: ISBN: Category : Languages : en Pages : 144
Book Description
This program has the end objective of demonstrating a flightweight hot gas secondary injection thrust vector control (HGSITVC) for large solid propellant rocket motors. Effort reviewed in the second quarterly report includes the design of a full scale test pintle valve to be used in the development testing. Two of the test pintle valves were fabricated and tested on a 6,000 lb class demonstration test motor. Test results indicate that the pintle valve design is highly satisfactory for continuation of testing in the subscale test motor development program. During the first static test, valve No. 1 was exposed to low mass flow and long duration to insure survivability of the pintle valve. Valve No. 2 was exposed to approximately the same mass flow planned for the full scale 120 in. demonstration test motor. Test data verify that the valve successfully held up under simulated large motor environment. Test results will be utilized to improve the test motor design and incorporate slight modifications in pintle valves No. 3 and 4 for the second test motor. The second demonstration test (TU-521.02 motor) is scheduled for testing during the third quarter of the program.
Author: Carver G. Kennedy
Author: Carver G. Kennedy
Author: Carver G. Kennedy
Author: Paul D. Nance
Author: Paul D. Nance
Author: 
Author: United States. National Aeronautics and Space Administration
Author: 
Author: 
Author: 
Author: United States. National Aeronautics and Space Administration