本发明公开了一种提升高超声速飞行器结构热试验模拟精度的控制方法,涉及航天航空复杂环境模拟领域,提升高超声速飞行器结构热试验模拟精度的控制方法包括基于交流调压电路,建立高超声速飞行器结构热试验多温区耦合时滞系统的输入电能表达式;基于热力学和传热学,建立高超声速飞行器结构热试验多温区耦合时滞系统的输出能量表达式;基于能量守恒定律,联立所述输入电能表达式和所述输出能量表达式建立高超声速飞行器结构热试验多温区耦合时滞系统模型。本发明解决了现有高超声速飞行器结构热试验系统仅仅停留在单一温区理论模型,无法全面描述多维度系统状态,从而存在模拟精度低的问题。
The invention discloses a control method for improving the thermal test simulation precision of a hypersonic aircraft structure, and relates to the field of aerospace complex environment simulation. Establishing an input electric energy expression of the hypersonic aircraft structure thermal test multi-temperature-zone coupling time-delay system; based on thermodynamics and heat transfer theory, an output energy expression of the hypersonic aircraft structure thermal test multi-temperature-zone coupling time-delay system is established; and based on the law of conservation of energy, the input electric energy expression and the output energy expression are combined to establish a hypersonic aircraft structure thermal test multi-temperature-zone coupling time-delay system model. The method solves the problem that an existing hypersonic aircraft structure thermal test system only stays in a single-temperature-zone theoretical model and cannot comprehensively describe the state of a multi-dimensional system, so that the simulation precision is low.
一种提升高超声速飞行器结构热试验模拟精度的控制方法
2024-07-19
Patent
Elektronische Ressource
Chinesisch
IPC: | B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen |