Integral hybrid-boost/solid-fuel ramjet propulsion for lightweight tactical missiles
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Authors
Woods, Paul C.
Subjects
Advisors
Netzer, David W.
Date of Issue
1995-12
Date
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
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)
Type
Thesis
Description
Series/Report No
Department
Aeronautical Engineering
Astronautical Engineering
Organization
Identifiers
NPS Report Number
Sponsors
Funding
Format
49 p.
Citation
Distribution Statement
Approved for public release; distribution is unlimited.