Study of test and evaluation on integral rocket-ramjets for tactical missiles PDF Download
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Author: Hisahiro Nakayama
Publisher:
ISBN:
Category :
Languages : en
Pages : 14
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Author: Hisahiro Nakayama
Publisher:
ISBN:
Category :
Languages : en
Pages : 14
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Book Description
Author: C. E. Franklin
Publisher:
ISBN:
Category : Combustion
Languages : en
Pages : 642
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Author: Keith J. Fruge
Publisher:
ISBN:
Category :
Languages : en
Pages : 51
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Author: C. E. Franklin
Publisher:
ISBN:
Category : Combustion
Languages : en
Pages : 174
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Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 98
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Author: Emil J. Eichblatt
Publisher: AIAA (American Institute of Aeronautics & Astronautics)
ISBN:
Category : History
Languages : en
Pages : 440
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Book Description
Test and evaluation (T&E) provides the means for determining to what extent the weapon satisfies its requirements, how well it functions in the operational environment, and whether or not it should continue into production. Among the topics addressed here: performance, flight, simulation, electromag
Author: United States. Congress. House. Committee on Appropriations. Subcommittee on Department of Defense
Publisher:
ISBN:
Category : United States
Languages : en
Pages : 1540
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702
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Author: Paul C. Woods
Publisher:
ISBN:
Category :
Languages : en
Pages : 49
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An investigation was conducted to determine the feasibility of a small, low-cost, caseless, hybrid-booster/solid-fuel ramjet (H/SFRJ) that utilizes a common fuel grain and has no ejectables. Performance of an air-to-ground missile with a solid propellant booster and SFRJ sustainer, capable of being fired from an unmanned aerial vehicle or helicopter was obtained using an Air Force computer code. A H/SFRJ motor was then designed analytically and compared to the generated computer output. The results showed that a H/SFRJ that has performance equal to a solid-booster SFRJ is feasible. The final missile design had a range of 20 nm, a flight Mach number of 2.0, a diameter and length of 5 and 99 inches respectively, and weighed 82 lb. Caseless hybrid rockets with erodible nozzles were tested to validate assumptions made in the design analysis. In addition, transition from hybrid-rocket booster to solid-fuel ramjet sustainer was demonstrated. (MM).
Author:
Publisher:
ISBN:
Category : Industrial engineering
Languages : en
Pages : 204
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