Integral hybrid-boost/solid-fuel ramjet propulsion for lightweight tactical missiles
By:  Paul C. Woods
Publisher: Naval Postgraduate School; Available from National Technical Information Service
Published: 1995
Place of publication: Monterey, Calif; Springfield, Va
Language: eng
Number of pages: 49
Description: 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)
Notes: Thesis advisor(s): David W. Netzer.

"December 1995."

Thesis (Degree of Aeronautical and Astronautical Engineer) Naval Postgraduate School, December 1995.

Includes bibliographical references.

Approved for public release; distribution unlimited.

Also available online.

Mode of access: World Wide Web.

System requirements: Adobe Acrobat Reader.

US Navy (USN) author.

dk/dk cc:9996 10/1/96