This paper aims at the airframe strength problem of a carrier-based UAV in the process of arresting and landing. With the fuselage structure as the main research object, a ground hindered simulation test plan is designed, including the fuselage structure, the fuselage and wings before and after false, and hindered hook component. The corresponding device is set up. Adopting the ground test and the coupled simulation, the dynamic response of the ship block resistance under the impact of the fuselage structure is analyzed. The test and simulation results show that the maximum longitudinal overload of the middle fuselage attenuates along the two main transmission paths from the rear fuselage to the front fuselage, and the peak load of the lower transmission path point is significantly higher than that of the upper transmission path point. It is found that the maximum overload point is at the arresting joint and the strain danger point is at the front section of the belly beam. The overload error of test and simulation at each measuring point on the medium fuselage structure is within 5% and the strain error is within 8%, which verify the validity of test results and the feasibility of the rigid-flexible coupling numerical simulation method. The joint analysis of ground arresting test and numerical simulation can provide important reference for the design of structural strength of carrier-based UAV, and provide basis for the subsequent analysis of arresting landing of carrier-based UAV and prediction of fuselage structural response.
XIONG Wenqiang
,
ZHANG Run
,
ZHANG Xiaoqing
,
ZHU Xiaolong
,
GAO Zongzhan
,
LIU Xiaoming
,
HE Min
,
YAO Xiaohu
. Analysis of impact response of mid-fuselage ground arresting in a carrier-based UAV[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019
, 40(12)
: 222892
-222892
.
DOI: 10.7527/S1000-6893.2019.22892
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