平流层飞艇在升空全过程受到复杂外界环境影响，针对其多物理场耦合的复杂升空问题建立了基于MATLAB和ADAMS联合仿真的新型热力耦合分析方法。该方法利用MATLAB建立了详细的飞艇升空热力耦合数学模型，通过时域离散及牛顿迭代法解耦获得各参数曲线，并基于ADAMS建立动力学环境下的飞艇模型，开发了ADAMS环境下实时读取飞艇变质量数据的CONSUB子程序，通过施加解耦后的力场及调用变质量子程序实现对平流层飞艇变质量升空全过程的可视化仿真控制。文中利用上述方法对某型号平流层飞艇进行热力耦合分析，获取其升空过程中的运动轨迹及姿态、气囊气体温度等规律。结果表明，气囊内外压差的设计最小值对飞艇速度的实时控制不显著，同时囊内气体在平流层阶段出现温度回升现象。分析表明该方法能高效、准确地模拟平流层飞艇在复杂多物理场耦合下的变质量升空全过程并获取各项热力参数，对飞艇升空过程参数控制及优化设计具有重要的参考价值。

A new coupling thermodynamics analysis method based on the ADAMS and MATLAB joint simulation was proposed for ascent stage of stratospheric airship in complex external environment and multi-physical coupling conditions. An accurate thermal-mechanical coupling mathematical model for ascent of airship was built by using MATLAB in this method. Based on this method, the discrete time-domain method and Newton iterative algorithm were used to decouple the model to obtain relevant parameter curves. The model of airship was established in dynamic environment of ADAMS and a CONSUB subroutine which is available to retrieve the variable data of the airship mass in real time was developed. The visualized simulation control for the ascent stage of variable mass stratospheric airship was realized by applying the decoupled load and calling the subroutine. The coupling thermodyna-mics analysis of a certain stratospheric airship was performed using the above method to obtain the rules of trajectory, attitude and air temperature in air bag. The results show that the design minimum of the pressure difference between the inside and outside of the airbag is not significant for real-time control of airship speed, and the temperature of gas in the air bag rises during the stratosphere stage. The analysis indicates that this method can efficiently and accurately simulate the ascent of stratospheric airship with variable mass under the coupling of complex multi-physical conditions and obtain thermodynamic parameters. This method is of great reference value for the parameter control and optimization design of airship.