Author: Publisher:
ISBN:
Category : Injections
Languages : en
Pages : 292
Book Description
Proportional Solid Propellant Secondary Injection Thrust Vector Control Study
Author: Two Dimensional Gaseous Secondary Injection Study of Rocket Thrust Vector Control
Author: R. W. MilliganHot 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).
NASA Scientific and Technical Reports
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information DivisionPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 428
Book Description
A Selected Listing of NASA Scientific and Technical Reports
Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information DivisionPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 436
Book Description
Scientific and Technical Aerospace Reports
Author: Solid Rocket Thrust Vector Control
Author: United States. National Aeronautics and Space AdministrationPublisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 212
Book Description
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).
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.