A Simplified Method for Load Simulation of Helicopter Tail Section Fatigue Test
A fatigue test and load simulation technology, applied in the direction of aircraft component testing, etc., can solve the problems of complex loading schemes and inapplicable tail fatigue tests, and achieve the effect of simplifying the loading scheme
Active Publication Date: 2022-01-07
CHINA HELICOPTER RES & DEV INST
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Problems solved by technology
After simplification, there are still 9 loading points and 17 load elements in the AC313 helicopter tail boom static test. This loading scheme is still too complicated to apply to the tail section fatigue test
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Embodiment Construction
[0027] The technical solutions of the present invention will be described more clearly and completely below.
[0028] Take the tail section of the AC313 helicopter as an example. The load that constitutes the fatigue damage of the tail section of the helicopter is mainly caused by the change of the flight state and the low-cycle fatigue load caused by the ground-air-ground cycle of flight take-off and landing. During the tail section fatigue test, the ground state of the tail section → air state → ground The state constitutes a ground-air-ground load cycle. The load on the ground state of the helicopter's tail section is the load generated by its own weight. No simplification is required during the fatigue test. Therefore, only the load simplification of the helicopter's tail section in the air flight state needs to be considered. Method, the stress level of each flight state of the tail section of AC313 helicopter was analyzed, and the stress level in the tail 13 frame area w...
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The invention discloses a method for simplifying the load simulation of a helicopter tail section fatigue test, comprising: determining the tail 13 frame area and the tail 1 frame area as key control areas for load simplification; selecting the load applied in the tail section fatigue test as 3 loading points and 5 loading points Loading elements; extract the theoretically calculated bending moments of the tail 1 frame and tail 13 frame in each state of the helicopter; determine the test load that affects the load of the tail 13 frame and tail 1 frame; calculate and determine the tail rotor test load and tail beam according to the force balance Test load: Apply the determined test load to the finite element model of the tail section, analyze the stress distribution under the test load, and compare it with the stress distribution under the theoretical load of the tail section. The method of the present invention selects the load applied in the tail section fatigue test to be 3 loading points such as the hub center of the tail rotor, the aerodynamic center of the flat tail and the center of the tail beam, and 5 load elements such as the test load of the tail rotor, the test load of the tail rotor and the test load of the tail beam , which greatly simplifies the loading scheme and is suitable for tail section fatigue tests.
Description
technical field [0001] The invention belongs to the technical field of helicopter structural fatigue, and relates to a simplified method for simulating a fatigue test load of a helicopter tail section. Background technique [0002] In the real working conditions, the tail section of the helicopter not only bears the concentrated load of the tail rotor and the horizontal tail, but also bears the mass inertial load and the aerodynamic load of the shape. Simplified processing. In the static test of the tail beam of the AC313 helicopter, there are still 9 loading points and 17 load elements after the simplification. This loading scheme is still too complicated and is not suitable for the tail section fatigue test. [0003] Due to the need to apply reciprocating dynamic loads and the long test period for the tail section fatigue test, it is necessary to establish a set of fatigue test load simplification simulation methods that are relatively simple and can relatively truly refl...
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IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 朱定金吴堂珍王玉合刘晓同王召勇
Owner CHINA HELICOPTER RES & DEV INST