Landing Performance Study for Four Wheels Twin Tandem Landing Gear Based on Drop Test

Abstract

The drop tests of a twin tandem landing gear with different filling parameters are carried out in two different landing attitudes (level and tail-down). The overload coefficient and power absorption efficiency are obtained. Curves of dynamic oscillation and pressure change for the pitch damper are obtained. The results show that twin tandem landing gear has a good ability to absorb the work of landing impact. Under landing weight, the vertical overload coefficients during level landing and tail-down landing are 1.14 and 1.07, respectively, when the corresponding efficiencies of its buffer system are 80.9% and 83.3%. During tail-down landing, the work absorbed by the pitch damper accounts for only 14.9% of the maximum pitching kinetic energy of the trolley. When the orifice diameter of the pitch damper keeps the same, its peak axial load does not change significantly with the change of its initial pressure. When the initial pressure of the pitch damper keeps the same, the decrease of its orifice diameter is beneficial to the vibration attenuation of the trolley. The smaller recoil channel may lead to a significant increase in the peak pressure of the pitch damper, which should be a consideration in its design.

Landing Impact Load Analysis and Validation of a Civil Aircraft Nose Landing Gear

“…This figure shows that both the loads at the WA center and GC point and both the loads in the vertical and longitudinal directions were all in good agreement between the simulation and test, validating both the accuracy and comprehensiveness of the work previously performed. Compared with other studies on the drop test [4,8,17,32,33], the longitudinal tire loads are basically similar in shape, as are the vertical history loads, but the longitudinal loads of the wheel axle, as described before, were not obtained in previous tests. This test result proves that a significant load difference between the WA and GC exists and could motivate other researchers to conduct WA load research.…”

“…In the last ten years, various experts have conducted test research. Xue Caijun conducted a drop test for the Seagull-300 aircraft [29]; D. Scoot Norwood conducted a full aircraft landing test for F-35 fighters [30]; Zhang Zihao researched drop test equipment [31]; Fang Wei carried out a four-wheeled landing gear drop test [32].…”

Keandalan Komponen Nose Wheel Assy pada Pesawat Cessna

“…Bila kegagalan potensial sudah teridentifikasi, maka tindakan perbaikan atau penggantian dapat dilakukan. Artinya tindakan perbaikan dapat dilakukan tergantung pada kondisi prestasinya di mana riset ini sesuai dengan desain konseptual yang harus di lakukan pada suatu perwatan sesuai dengan (Kim, Han and Choi, 2018;Rismayanti et al, 2019;Fang, Zhu and Wang, 2022) KESIMPULAN Berdasarkan penafsiran nilai beta (β) tipe laju kegagalan komponen Landing Gear pada pesawat Cessna adalah meningkat, pada flight Hours yang dimana nilai β = 3.513864 pada nose wheel assy adalah β>1, yang mengindikasikan terjadinya kegagalan aus (wear out). Kegagalan tipe ini mempunyai sifat meningkatkan laju kegagalan (failure rate increasing) dengan semakin tingginya penggunaannya sedangkan pada flight cycle yang dimana nilai β = 1.258549 pada nose wheel assy adalah β>1, yang mengindikasikan terjadinya kegagalan aus (wear out).…”

Effects of Pitch Stabilization Buffer on the Dynamic Performance of Frame-Type Landing Gear

“…Wei et al proposed an improved landing gear drop-shock dynamics model, which modified the friction mechanics model to more accurately simulate the whole process of the landing gear drop-shock test [13]. Wei et al completed the landing shock test of four-wheeled landing gear in horizontal landing and tail-sinking landing conditions, and obtained the effect of stabilizer buffer inflation pressure on the landing gear loads [14].…”