FOAM RUNWAY FOR LANDING LIFTING REENTRY CRAFT.
SYSTEMS ENGINEERING GROUP WRIGHT-PATTERSON AFB OHIO
Pagination or Media Count:
The design constraint which horizontal landing imposes upon a fixed-geometry hypersonic-maneuvering lifting body reentry craft is reviewed. Two representative manned, lifting-body, flight-test, research vehicles M2-F2 and HL-10 are examined to show the volume and weight penalty due to landing gear and landing engine. The fundamental reasons why the landing-design constraint exists are reexamined and several means by which the constraint might be relaxed are postulated. Two similar concepts in which aqueous detergent foam would be used to create a synthetic atmosphere or a synthetic lake with a controlled density profile are described and the principles by which these concepts would relax the design constraint and simultaneously remove the weight and volume penalty of landing gear, landing engine, and other landing-assist devices are discussed. An operational concept is described. A development program including analytical study model tests and flight tests is proposed. Author
- Terminal Flight Facilities
- Spacecraft Trajectories and Reentry