Landing Characteristics of the Apollo Spacecraft with Deployed-Heat-Shield Impact Attenuation Systems
Abstract
An experimental investigation was made to determine the landing characteristics of a 1/4-scale dynamic model of the Apollo spacecraft command module using two different active (heat shield deployed prior to landing) landing systems for impact attenuation. One landing system (configuration 1) consisted of six hydraulic struts and eight crushable honeycomb struts. The other landing system (configuration 2), consisting of four hydraulic struts and six strain straps, was lighter. Tests made on water and the hard clay-gravel composite landing surfaces simulated parachute letdown (vertical) velocities of 23 ft/sec (7.0 m/s) (full scale). Landings made on the sand landing surface simulated vertical velocities of 30 ft/sec (9.1 m/s). Horizontal velocities of from 0 to 50 ft/sec (15 m/s) were simulated. Landing attitudes ranged from -30 degrees to 20 degrees , and the roll attitudes were 0 degrees, 90 degrees, and 180 degrees.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1966
- Accession Number
- ADA455658
Entities
People
- Sandy M. Stubbs
Organizations
- National Aeronautics and Space Administration