A method for calculating the reaction force of an aircraft tail pry

Abstract

The invention relates to the technical field of flight mechanics, and specifically provides a method for calculating the reaction force of an aircraft tail skid support. First, an aircraft body coordinate system is established, and initial parameters are set: aircraft course displacement, aircraft vertical displacement, and pitch angle. Calculate the external forces on the aircraft: aircraft lift, aircraft resistance, pitching moment, main wheel support reaction force and main wheel friction force, and then calculate the motion parameters: pitch angular acceleration, heading acceleration and vertical acceleration through the iterative method Calculate the intermediate parameters at each moment before the tail touches the ground: pitch angular acceleration, pitch moment, main wheel support reaction force and main wheel friction force, estimate the value of the intermediate parameters at the moment of touchdown according to the small disturbance theory, and then calculate the tail touch Tail skid support reaction force at the time of landing, using the size of the tail skid support reaction force to judge the damage level of the tail touching the ground, to avoid maintenance workers not checking properly when the tail of the aircraft touches the ground, causing safety hazards in the subsequent flight of the aircraft.

Description

Technical field [0001] The present invention relates to the field of flight mechanics, and more particularly to a method of calculating aircraft tail branch. Background technique [0002] When the aircraft takes off or landing in a relatively large number of angles, the aircraft designed in accordance with the transportation standards may occur in the end of the machine tail in the end of the operation. When the aircraft occurs, the method taken by the prior art is found and determined by the visual inspection method and determines the external damage of the aircraft, and subsequent maintenance of the aircraft, the prior technology has the following defects: [0003] 1. The sequence of inspection methods is: check the rear collision device of the aircraft, the external service cover, the lower skin of the plane and its connecting firmware, the aircraft touchs the tricks, septum, Connecting clips, fasteners, rear pressure nut structures, etc., the method taken by the prior art lea...

AI Technical Summary

Problems solved by technology

[0003] 1. The inspection sequence of the visual inspection method is: sequentially inspect the rear lower anti-collision device of the aircraft, the external service cover, the rear lower skin of the aircraft and its connecting fasteners, the stringers inside the aircraft touchdown, the bulkhead, Connecting clips, fasteners, aircraft rear pressure bulkhead structure, etc., the means adopted by the existing technology lead to long inspection and maintenance time and high cost

[0004] 2. After the aircraft undergoes severe impact and friction, the damage to its internal structure is often not easy to be detected. These potential damages may cause the failure of the entire structure of the aircraft and affect flight safety. Moreover, the experience of each maintenance worker is different. The tail touchdown damage cannot be correctly judged and repaired in time, which will pose a serious threat to flight safety. Therefore, visual inspection alone cannot completely and accurately check the tail touchdown situation.

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