NASA NTRS · 19640017068
Feasibility of mars landing and return missions
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Syvertson, C. A.. 1964-06-12. Ames research center mars mission studies introduction. https://ntrs.nasa.gov/citations/19640017068
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Dynamic behavior of Surveyor landing system and surface material during lunar landing
The lunar module (LM) landing phase is one of the most critical phases of the entire Apollo mission. Landing impact is of critical concern because at no other time during the LM mission is there less opportunity for vehicle control. To assure a successful landing, the alightment system must not only provide required shock attenuation for protection of crew and structure, but must also assure stability against overturning after touchdown. The paper discusses important design features of the alightment system, such as geometric arrangement, energy absorber characteristics, and deployment mechanisms. Performance characteristics of the vehicle at touchdown, as found analytically, are presented. Model and full-size testing of the landing system is briefly discussed.
Spacecraft landing systems technology, materials and hardware, model impact testing and para-sail landing rocket program