Add to ORKGA rocket of the 1000-pound-thrust class using liquid oxygen and JP-4 fuel as propellant was installe...
Thermal performance and structural integrity are experimentally evaluated in the Langley 8-ft high t...
Design and development of sensors for measuring ablative changes in space vehicle heat shield during...
Convective and equilibrium radiation heat transfer prediction for Project Fire reentry vehicl
Design and operation of make wire, light pipe, and spring wire sensors to measure in-flight thermal ...
The purpose of this project is to develop a flight ready apparatus of the microgravity ignition expe...
Flight reentry heating instrumentations required for ballistic entry simulation of radiative and con...
Ablating materials tested at combined radiative and convective heating for manned reentry vehicle he...
Design, operation and construction of event recorder for monitoring heat ablation dat
Facilities for simulating entry environment and response of ablative materials to simulated entry en...
This paper presents the methods by which NASA has designed, built, tested, and certified pyrotechnic...
System for measuring the output energy of pyrotechnic devices discharges the reaction products into ...
The hydrogen burnoff igniter, a pyrotechnic device used to burn off excess hydrogen gas near the Spa...
Thermostructural analysis was performed on generic crew exploration vehicle (GCEV) heat shielded wal...
The development of computer codes for the thrust chamber of a rocket of which the propellant gas is ...
A rocket of the 1000-pound-thrust class using liquid oxygen and JP-4 fuel as propellant was installe...
Thermal performance and structural integrity are experimentally evaluated in the Langley 8-ft high t...
Design and development of sensors for measuring ablative changes in space vehicle heat shield during...
Convective and equilibrium radiation heat transfer prediction for Project Fire reentry vehicl
Design and operation of make wire, light pipe, and spring wire sensors to measure in-flight thermal ...
The purpose of this project is to develop a flight ready apparatus of the microgravity ignition expe...
Flight reentry heating instrumentations required for ballistic entry simulation of radiative and con...
Ablating materials tested at combined radiative and convective heating for manned reentry vehicle he...
Design, operation and construction of event recorder for monitoring heat ablation dat
Facilities for simulating entry environment and response of ablative materials to simulated entry en...
This paper presents the methods by which NASA has designed, built, tested, and certified pyrotechnic...
System for measuring the output energy of pyrotechnic devices discharges the reaction products into ...
The hydrogen burnoff igniter, a pyrotechnic device used to burn off excess hydrogen gas near the Spa...
Thermostructural analysis was performed on generic crew exploration vehicle (GCEV) heat shielded wal...
The development of computer codes for the thrust chamber of a rocket of which the propellant gas is ...
A rocket of the 1000-pound-thrust class using liquid oxygen and JP-4 fuel as propellant was installe...
Thermal performance and structural integrity are experimentally evaluated in the Langley 8-ft high t...
Design and development of sensors for measuring ablative changes in space vehicle heat shield during...