Study on the thermal-mechanics coupling characteristics of composite envelope structure of high altitude stratospheric airship
Abstract
A thermodynamic coupling model of the high latitude stratospheric airship envelope structure is established in this study based on the damage theory of laminated composite. Based on the flight test data, the mechanics response of composite envelope is revealed under different flight altitudes, different pressure difference conditions and different temperature conditions. The mechanical characteristics of the different structural parts of the airship under the same temperature and pressure difference are discussed in depth. The results show that the thermal stress of the composite envelope is small under low temperature and low pressure, and the influence on the envelope material damage is almost negligible. The in-plane shear thermal stress (S12) distribution along the longitudinal axis direction (from head to tail) of the airship gradually increases when the temperature is lower and the pressure difference is smaller, but the thermal stress (S12) along the circumferential central axis direction of the airship almost no change; The in-plane thermal stress (S11) between the two ends of is larger along the longitudinal axis direction of the airship, while the thermal stress (S11) along the circumferential central axis direction of the airship is smaller in the middle. The difference is that the circumferential thermal stress is greater overall than the axial thermal stress. Through the analysis also found that the mechanical properties of composite envelope structure are stable, and almost no damage is observed under low temperature and low pressure thermal-mechanics coupling conditions.Keywords: Thermal-mechanics coupling, Stratospheric airship, Composite envelope, Thermal stress, Damage theory
- Publication:
-
42nd COSPAR Scientific Assembly
- Pub Date:
- July 2018
- Bibcode:
- 2018cosp...42E2097L