THERMAL PROTECTION OF ROCKET-MOTOR STRUCTURES
Journal Article
·
· Aerospace Eng.
OSTI ID:4750502
The relative merits of several methods of thermal protection are compared for liquid-rocket motors operating at high temperatures, long durations, and with restart. It is concluded that the most promising light-weight designs employ high-density polycrystalline and pyrolytic graphites as the liner materials. However, designs employing tungsten and tantalum carbide, although heavier, are also of interest as they could offer increased erosion resistance in some propellant systems. (auth)
- Research Organization:
- Aeronautronic Div. of Ford Motor Co., Los Angeles
- NSA Number:
- NSA-17-013848
- OSTI ID:
- 4750502
- Journal Information:
- Aerospace Eng., Journal Name: Aerospace Eng. Vol. Vol: 22: No. 1
- Country of Publication:
- Country unknown/Code not available
- Language:
- English
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