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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: 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 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: 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: ALABAMA UNIV IN HUNTSVILLE RESEARCH INST. Publisher: ISBN: Category : Languages : en Pages : 152
Book Description
The secondary injection is a method of thrust vector control for the missile flight. In this method, a fluid is injected into the rocket expansion nozzle, causing an aerodynamic obstruction in the main stream of the nozzle. This obstruction then produces a shock wave and a boundary layer separation accompanied by a positive pressure region on the wall near the injection port, resulting in a side force amplification for the thrust vector control. The objective of this study is to compare the two types of secondary injections in the aspects of performance in terms of effectiveness and efficiency, and of system weight so as to provide a first step in the approach to the solution of the problem. (Author).
Author: National Research Council Publisher: National Academies Press ISBN: 0309266564 Category : Science Languages : en Pages : 115
Book Description
On June 15, 2011, the Air Force Space Command established a new vision, mission, and set of goals to ensure continued U.S. dominance in space and cyberspace mission areas. Subsequently, and in coordination with the Air Force Research Laboratory, the Space and Missile Systems Center, and the 14th and 24th Air Forces, the Air Force Space Command identified four long-term science and technology (S&T) challenges critical to meeting these goals. One of these challenges is to provide full-spectrum launch capability at dramatically lower cost, and a reusable booster system (RBS) has been proposed as an approach to meet this challenge. The Air Force Space Command asked the Aeronautics and Space Engineering Board of the National Research Council to conduct an independent review and assessment of the RBS concept prior to considering a continuation of RBS-related activities within the Air Force Research Laboratory portfolio and before initiating a more extensive RBS development program. The committee for the Reusable Booster System: Review and Assessment was formed in response to that request and charged with reviewing and assessing the criteria and assumptions used in the current RBS plans, the cost model methodologies used to fame [frame?] the RBS business case, and the technical maturity and development plans of key elements critical to RBS implementation. The committee consisted of experts not connected with current RBS activities who have significant expertise in launch vehicle design and operation, research and technology development and implementation, space system operations, and cost analysis. The committee solicited and received input on the Air Force launch requirements, the baseline RBS concept, cost models and assessment, and technology readiness. The committee also received input from industry associated with RBS concept, industry independent of the RBS concept, and propulsion system providers which is summarized in Reusable Booster System: Review and Assessment.
Author: DP Mishra Publisher: CRC Press ISBN: 1351708414 Category : Technology & Engineering Languages : en Pages : 364
Book Description
The book follows a unified approach to present the basic principles of rocket propulsion in concise and lucid form. This textbook comprises of ten chapters ranging from brief introduction and elements of rocket propulsion, aerothermodynamics to solid, liquid and hybrid propellant rocket engines with chapter on electrical propulsion. Worked out examples are also provided at the end of chapter for understanding uncertainty analysis. This book is designed and developed as an introductory text on the fundamental aspects of rocket propulsion for both undergraduate and graduate students. It is also aimed towards practicing engineers in the field of space engineering. This comprehensive guide also provides adequate problems for audience to understand intricate aspects of rocket propulsion enabling them to design and develop rocket engines for peaceful purposes.
Author: National Research Council Publisher: National Academies Press ISBN: 0309102472 Category : Technology & Engineering Languages : en Pages : 288
Book Description
Rocket and air-breathing propulsion systems are the foundation on which planning for future aerospace systems rests. A Review of United States Air Force and Department of Defense Aerospace Propulsion Needs assesses the existing technical base in these areas and examines the future Air Force capabilities the base will be expected to support. This report also defines gaps and recommends where future warfighter capabilities not yet fully defined could be met by current science and technology development plans.
Author: Paul D. Nance
Author: Paul D. Nance
Author: Carver G. Kennedy
Author: Carver G. Kennedy
Author: 
Author: 
Author: ALABAMA UNIV IN HUNTSVILLE RESEARCH INST.
Author: National Research Council
Author: DP Mishra
Author: 
Author: National Research Council