Project SQUID. Application of the Ram Rocket as a Helicopter Propulsion System
Abstract
A theoretical analysis of the influence of powerplant type on the range and load carrying capacity of conventional rotary wing aircraft is presented. Those propulsion systems considered for the conventional helicopter are the reciprocating engine, rocket, ramjet, pulsejet, and ram rocket. It is shown that the ram rocket helicopter is superior in range and load carrying capacity to all other propulsion schemes considered for tip speeds of 600 ft/sec and above and for ranges less than 88 miles. The theoretical analysis of a "hybrid" helicopter composed of two ram rocket engines mounted at the wing tips and used in conjunction with a conventional piston engine shows that this system can realize improvements in load carrying capacity for a given range up to as much as 100% when compared to the conventional helicopter. Similarly, improvements in range of up to 90% for the same load carrying capacity can be obtained with this helicopter propulsion system. A conventional liquid rocket motor is shown to be the optimum jet propulsion device for use on the "hybrid" helicopter, and the effect of rocket specific impulse is shown to be negligible for the short operating time required of the rocket motors. Samples of the details of the theoretical analysis are presented and the conclusions are synthesized in graphical form.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 23, 1953
- Accession Number
- ADA952662
Entities
People
- J. E. Jr Scott
- J. V. Charyk
Organizations
- Princeton University