某型飞机尾橇装置收放系统设计与研究

Design and research of retraction and extension system for tail bumper device of an aircraft

尾橇装置是飞机最小离地速度科目试飞中的核心装置,在做科目试飞滑跑过程中,尾橇装置可以吸收飞机尾部与地面撞击产生的冲击能量。尾橇装置的收放系统性能需要满足两个设计指标:一是在飞机离地起飞后尾橇装置能够达到完全收起状态,以减小该装置暴露在蒙皮外的部分对飞机气动外形的影响;二是在飞机地面停机状态下,尾橇装置能够达到完全伸长状态,以保证下一次最小离地速度科目试飞时有足够大的缓冲行程用以吸收冲击能量。针对该尾橇装置设计了一套收放系统,分析了其收放原理,并通过MSC.ADAMS软件和AMEsim系统控制模型联合仿真计算其收放性能,研究了气囊初始充压对收放性能的影响。结果表明:该收放系统设计合理、性能可靠,在气囊初始充压4 bar时可以同时满足两个收放设计指标的要求。

The tail bumper device is the core device in the flight test of the minimum take-off speed. During the ground taxing of flight test, the tail bumper device can absorb the impulse energy generated by the impact between the tail of the aircraft and the ground. The retraction and extension system needs to meet two design requirements: one is to fully retract the tail bumper after the aircraft take-off from the ground for reducing the influence of the exposed part of the device on the aerodynamic profile of the aircraft;another is that the tail bumper can be fully extended when the aircraft is down on the ground to ensure that the next test flight has enough stroke to absorb the impact energy. This paper designs a set of retraction and extension system for the tail bumper device and the principle of the retraction and extension is analyzed. The retractable performance is calculated by MSC.ADAMS and AMEsim co-simulation. The effect of initial inflating pressure of air membrane on retraction performance is researched by the model. The results show that the design of the retraction and extension system is reasonable and the performance is reliable. When the initial inflating pressure is 4 bar, it can meet the two retractable design requirements at the same time.