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).

This lecture series provided an introduction to modern ramjet technology. Applications to missiles were especially emphasized. The survey and characterization of various types of ramjets were followed by the discussion of ramjet components. Three of the lectures dealt with the main types of subsonic combustion ramjets. One lecture was devoted to supersonic combustion ramjets. Titles include: Ramjet Air Induction System Design for Tactical Missile Application; Aspects of Engine and Airframe Integration for Ramjet and Ramrocket Powered Missiles; Integral Boost, Heat Protection, Port Covers and Transition; Special Problems of Ramjet with Solid Fuel; and Solid Propellant Ramrockets.

This report describes the main accomplishments of a collaborative Canadian-Dutch project known as the Integral Rocket Ramjet Demonstration Program (IRRDP) to investigate the key technologies of air-breathing missile propulsion through the design, fabrication, & testing of a solid fuel ducted rocket engine with an integral booster for a medium-range air-launched missile. It begins by discussing the requirements for an integral rocket ramjet engine, then reviews activities related to the development of a missile design tool & performance prediction tool, computational fluid dynamics evaluation of the intake & port covers, development of a new solid propellant for a gas generator used in ducted rocket propulsion, modelling of the ramjet combustor in a water tunnel, combustion tests, modelling & propellant development for the nozzle-less booster, and the final design.

The book is an amazing collection of technical papers dealing with hybrid rockets. Once perceived as a niche technology, for about a decade, hybrid rockets have enjoyed renewed interest from both the propulsion technical community and industry. Hybrid motors can be used in practically all applications where a rocket is employed, but there are certain cases where they present a superior fit, such as sounding rockets, tactical missile systems, launch boosters and the emerging field of commercial space transportation. The novel space tourism business, indeed, will benefit from their safety and lower recurrent development costs. The subjects addressed in the book include the cutting edge technology employed to push forward this relatively new propulsion concept, spanning systems to improve fuel regression rate, control of the mixture ratio to optimize performance, computational fluid dynamics applied to the simulation of the internal ballistics, and some other novel system applications.

With contributions from the leading researchers and scientists in the field, this volume is a compendium of the latest advances in tactical missile propulsion. The objectives of the book are to provide today's designer with a summary of the advances in potential propulsion systems as well as provide a discussion of major design and selection considerations. Authors were chosen for their demonstrated knowledge of and excellence in their respective fields to ensure a complete and up-to-date summary of the latest research and developments.