Crew Escape Capsule Retrorocket Concept. Volume I. Demonstration Program.
Abstract
The retrorocket demonstration program was conducted to evaluate an alternative to the inflatable airbags that are currently used with crew escape capsules to attenuate the landing impact forces. In-house tests indicated that if the vertical impact velocity was ten feet per second or less, the impact forces would be within human tolerances. Analyses revealed that the retrorocket concept could meet this criteria, therefore a demonstration test program was established. A structural steel test vehicle that was configured to simulate the B-1 capsule (weight, center of gravity location, footprint, size and parachute bridle system) was used for the test program. A cluster of four rocket motors with a high level primary thrust and a low level sustainer, that had been developed for the NASA Gemini Program, was installed at the confluence of the three 69.8 foot diameter slotted ring sail recovery chutes and the vehicle bridle system. A mechanical altimeter or telescoping probe was developed to extend down below the vehicle to trigger the rocket ignition at the correct time so as to decelerate the vehicle from 30 ft/sec down to 10 ft/sec or less before ground impact. Eight tests were conducted in developing the demonstration system with the last test a complete retrorocket system test. Test results and the rocket performance computer program indicated the demonstration program met design requirements. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1977
- Accession Number
- ADA042337
Entities
People
- Marvin C. Whitney
Organizations
- Flight Dynamics Laboratory