Aspects are examined of an investigation by the Marshall Space Flight Center into the conceptual feasibility of increasing the thrust performance of the Space Shuttle Main Engine (SSME) by using a conical nozzle extension fitted with an ablative insert in order to achieve a low-cost, near-term gain in payload. The ablating insert would provide a controlled increase in nozzle expansion ratio during launch and early climbout (first 30-60 seconds) so as to reduce thrust loss from nozzle over-expansion in the lower atmosphere. Summaries are given of JPL studies in the area of: defining the near-wall flow environment in the extended nozzle insert region; selecting potential insert materials; conceptualizing an extension/insert geometrical configuration; and identifying future experimental efforts necessary to verify the feasibility of the concepts.
Thrust improvement with ablative insert nozzle extension
1986-02-01
Miscellaneous
No indication
English
Thrust improvement with ablative insert nozzle extension
AIAA | 1986
|Ablative Thrust Chamber Feasibility
NTIS | 1963
Shuttle subscale ablative nozzle tests
AIAA | 1980
|Shuttle subscale ablative nozzle tests
NTRS | 1980
|Shuttle Subscale Ablative Nozzle Tests
AIAA | 1982
|