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| Design of Charge Structure Tester and Test of Low-temperature Aging |
| Received:July 27, 2016 Revised:January 15, 2017 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7643/ issn.1672-9242.2017.01.009 |
| KeyWord:structure tester propellant low-temperature aging |
| Author | Institution |
| LI Xiao-huan |
China Airborne Missile Academy, Luoyang , China |
| CAO Fu-qi |
China Airborne Missile Academy, Luoyang , China |
| SHEN Xin |
Military Representative Office Positioned in China Airborne Missile Academy, Luoyang , China |
| LI Yan-li |
The 46th Institute of the Sixth Academy of CASIC, Huhhot , China |
| YUN Sheng |
The 46th Institute of the Sixth Academy of CASIC, Huhhot , China |
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| Abstract: |
| Objective To explore method and mechanism on low-temperature aging test for charge structure of solid rocket engine and provide support for predicting and extending the service life of solid engine. Methods Structure tester was designed to facilitate experimental testing through simulation to determine the strain of certain level of charge pore size, and low-temperature aging test was carried out at -10 ℃ and -35 ℃. Non-destructive test was carried out to the structural tester after aging. Then the grain was taken off to prepare propellant sample to conduct fast tensile mechanical property test at room-temperature and low-temperature. Results A three-section connection type structure tester was designed to make sure not to destroy the stress load of the grain born and to ensure the sampling convenience and safety. The non-destructive testing showed that the grain inside the structure tester did not produce cracks and debonding phenomena after being stored at low temperature for a long term; the mechanical properties of the grain at room temperature had no significant change; the maximum tensile strength at low temperature was increased to some extent and the maximum elongation decreased significantly. After low-temperature aging test at -10 ℃ and -35 ℃, the maximum elongation decreased by 24% and 40% respectively. Conclusion Micro-damage produces inside the propellant and the capacity to withstand low-temperature rapid response (corresponding to low-temperature impact ignition state) decrease significantly, which should cause great concern． |
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