Author: Michael A. WittPublisher:
ISBN:
Category :
Languages : en
Pages : 52
Book Description
Investigation in the Feasibility of Using Solid Fuel Ramjets for High Supersonic/low Hypersonic Tactical Missiles
Author: Michael A. WittAn Investigation Into the Feasibility of Using a Dual-Combustion Mode Ramjet in a High Mach Number Tactical Missile
Author: Clifford B. VaughtPublisher:
ISBN:
Category :
Languages : en
Pages : 84
Book Description
An investigation into the feasibility of using a solid fuel, dual combustion mode ramjet in a high Mach number tactical missile was conducted to determine the regimes where this propulsion plant might be superior to a conventional solid fuel ramjet. The results of the study show that at Mach 6, 80,000 feet, with a temperature rise combustion efficiency of 90%, the DMRJ performance exceeded that of the SFRJ by 20% at near stoichiometric overall fuel-to-air ratios, neglecting mixing losses in the supersonic combustor. It also appears that eta delta T must be greater than 70% in order for the DMRJ to outperform the conventional SFRJ. Keywords: Ramjet, Scramjet, Dual combustion ramjet, Supersonic combustion, Solid fuel propulsion.
Scientific and Technical Aerospace Reports
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1460
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
33rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
Author: Design and Testing of a Caseless Solid-fuel Integral-rocket Ramjet Engine for Use in Small Tactical Missiles
Author: Keith J. FrugeHypersonic Missile Nonproliferation
Author: Richard H. SpeierPublisher: Rand Corporation
ISBN: 0833099167
Category : History
Languages : en
Pages : 155
Book Description
Hypersonic missiles--specifically hypersonic glide vehicles and hypersonic cruise missiles--are a new class of threat because they are capable both of maneuvering and of flying faster than 5,000 kilometers per hour. These features enable such missiles to penetrate most missile defenses and to further compress the timelines for a response by a nation under attack. Hypersonic missiles are being developed by the United States, Russia, and China. Their proliferation beyond these three could result in other powers setting their strategic forces on hair-trigger states of readiness. And such proliferation could enable other powers to more credibly threaten attacks on major powers. The diffusion of hypersonic technology is under way in Europe, Japan, Australia, and India--with other nations beginning to explore such technology. Proliferation could cross multiple borders if hypersonic technology is offered on world markets. There is probably less than a decade available to substantially hinder the potential proliferation of hypersonic missiles and associated technologies. To this end, the report recommends that (1) the United States, Russia, and China should agree not to export complete hypersonic missile systems or their major components and (2) the broader international community should establish controls on a wider range of hypersonic missile hardware and technology.
Integral Hybrid-boost/solid-fuel Ramjet Propulsion for Lightweight Tactical Missiles
Author: Paul C. WoodsPublisher:
ISBN:
Category :
Languages : en
Pages : 49
Book 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).
Government Reports Announcements & Index
Author: Feasibility and Design Definition Study of the Ramjet High Altitude Supersonic Target
Author: J. A. EngellandPublisher:
ISBN:
Category :
Languages : en
Pages : 80
Book Description
The report presents the results of a preliminary feasibility study and preliminary design definition of a ramjet engine installation in an advanced high altitude supersonic target vehicle. The air vehicle used in the study is an adaptation of Beech Model 1069 which was flown with the first hybrid rocket motor, and the ramjet is a scaled-down version of the Marquardt MA206-XAA engine. The vehicle description and configuration are given, and the propulsion system is defined. The study indicates that the selected configuration is feasible to demonstrate supersonic flight of a ramjet engine. Simulation of flight profiles suggests that a variety of maneuvers can be flown with a simple automatic flight control system, a step-type fuel control device, and an elastometric positive fuel expulsion arrangement. Launch conditions required for the functioning of the ramjet can be met by the F-4C type aircraft and external boosters will not be required. Review of the equipment necessary for support of the system shows that existing equipment and modification of existing equipment will provide most of the support equipment necessary. Tasks necessary to complete the design are summarized. A program schedule for a flight demonstration program is included. (Author).
Author: Abraham Cohen