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.
吴晓宇.某型飞机尾橇装置收放系统设计与研究[J].民用飞机设计与研 究,2022(4):41-46WU Xiaoyu. Design and research of retraction and extension system for tail bumper device of an aircraft[J]. Civil Aircraft Design and Research,2022,(4):41-46. ( in Chinese)复制