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| Model Flight Test Design to Measure Re-entry Aero-thermal-dynamic Environments |
| Received:February 04, 2021 Revised:February 24, 2021 |
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| DOI：10.7643/issn.1672-9242.2021.03.009 |
| KeyWord:re-entry flight model flight test temperature measurement pressure measurement vibration measurement |
| Author | Institution |
| KANG Tian |
Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang , China |
| JIANG Hua-bing |
Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang , China |
| SHAN Ji-xiang |
Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang , China |
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| Abstract: |
| To collect aero-thermal-dynamic environments of a blunt conical re-entry body and establish the environmental prediction method, a model flight test based on uncontrolled rocket was designed. The impact velocity was determined by transition and turbulent lasting time. The environmental parameters and sensor locations were discussed.. According to the nominal trajectory, several predicting methods were employed to get the exterior and interior temperature, static and fluctuate pressure, vibration environments during the flight, including trajectory coupled aerothermodynamics computing model, empirical formula of fluctuate pressure, vibration extrapolation based on similar vehicle. The maximum temperature, pressure and vibration were computed, and major specifications were defined. The exterior air temperature ranges 0~400 ℃, and the maximum rate is up to 20 ℃/s. The piezo-resistive pressure sensor ranges up to 25 PSI, and the piezo-electric pressure sensor ranges up to 5 PSI. Pressure sensors work under 220 ℃ with temperature compensation. The vibration acceleration ranges –100g~+100g. |
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