Load simulation method for cataplane landing gear

Abstract

The invention discloses a load simulation method for a cataplane landing gear, and belongs to the field of strength design of the cataplane landing gear. The load simulation method mainly comprises the following steps: analyzing stress on the whole cataplane, a nose gear and a main landing gear of a cataplane, so as to establish a corresponding mechanic equilibrium equation; establishing a nose gear simulation analysis model, a main landing gear simulation analysis model and a whole cataplane dynamic simulation analysis model according to the nose gear mechanic equilibrium equation; finally, correcting the whole cataplane dynamic simulation analysis model according to testing gravity center data and a front main landing gear load curve during practical catapult launching of the cataplane. The corrected model is the model capable of being used for catapult launching load simulation of the cataplane, problems in load design and analysis of the landing gear during catapult launching of the cataplane are solved, and the flight test verification of a carrier-based aircraft in an aircraft carrier platform and a land-based training ground is guaranteed.

Description

technical field [0001] The invention belongs to the field of aircraft landing gear strength design, and in particular relates to a method for simulating the load of an aircraft landing gear for catapult takeoff. Background technique [0002] Catapult technology is a linear propulsion technology, suitable for short-stroke launching equipment with large loads, and has broad application prospects in military, civil and industrial fields. The take-off technology of carrier-based aircraft mainly includes roll-off, hydraulic catapult take-off, steam catapult take-off and electromagnetic catapult (EMALS) take-off technology. To take off smoothly with a short glide distance (about 100 meters), an auxiliary tool is necessary, which is catapult takeoff. Therefore, as far as the loading mode is concerned, it is not only different from the conventional land-based take-off of the aircraft, but also very different from the inclined-board ski-jump take-off of the aircraft. During catapul...

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Problems solved by technology

Obviously, the construction of the above-mentioned dynamic model of the landing gear is not affected by the ejection aids. Therefore, the analysis of the aircraft nose landing gear (that is, the main action point of the ejection take-off) has limitations. At this time, it is impossible to continue to use the old land-based aircraft's conventional take-off and roll algorithm. A new simulation model and calculation method must be established to simulate the dynamic change process of the landing gear. At the same time, the dynamic response process of the aircraft body needs to be considered

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