Method for calculating aerodynamic parameters of actual flight orbit based on predetermined flight orbit

Abstract

The invention discloses a method for calculating aerodynamic parameters of an actual flight orbit based on a predetermined flight orbit, and belongs to the field of parameter design and prediction ofaircrafts. The method comprises the steps: for a predetermined flight orbit, collecting key points on the orbit and establishing a point group set; acquiring actual flight parameters of the aircraft when the target aircraft actually moves to a certain point to be measured; traversing all key points of the predetermined flight orbit; if the basic flight parameters of the key points are different from the actual flight parameters of a to-be-measured point, obtaining the actual aerodynamic parameters of the to-be-measured point through Lagrange polynomial interpolation according to the basic flight parameters and the basic aerodynamic parameters associated with all the key points and the actual flight parameters associated with the to-be-measured point; solving actual aerodynamic parameters of all to-be-measured points experienced by the aircraft in the actual motion process, and drawing a surface heat flow cloud chart of the target aircraft. According to the method, the aerodynamic parameter calculation is faster and more accurate, and the rapid calculation capacity of the aerodynamic thermal environment is greatly improved.

Description

technical field [0001] The invention belongs to the field of parameter design and prediction of aircraft, in particular to a method for calculating the aerodynamic parameters of an actual flight track based on a predetermined flight track. Background technique [0002] For aircraft, predicting the flight state, flight trajectory, and aerodynamic parameters of the aircraft is crucial to the rapid optimization design and flight safety of the aircraft. [0003] At present, in the initial design of aircraft, aerodynamic parameters are mainly obtained through engineering calculation or numerical simulation. The accuracy of engineering calculation methods cannot meet the needs of detailed distribution of aerodynamic parameters of complex-shaped aircraft. Numerical simulation will consume a lot of time and cannot meet the overall rapid optimization. The need for iterative design. [0004] In addition, during the actual flight of the aircraft, due to the rapid change of the flight ...

AI Technical Summary

Problems solved by technology

[0003] At present, in the initial design of aircraft, aerodynamic parameters are mainly obtained through engineering calculation or numerical simulation. The accuracy of engineering calculation methods cannot meet the needs of detailed distribution of aerodynamic parameters of complex-shaped aircraft. Numerical simulation will consume a lot of time and cannot meet the overall rapid optimization. The need for iterative design

[0004] In addition, during the actual flight of the aircraft, due to the rapid change of the flight speed and flight attitude, it is difficult to provide real-time aerodynamic data during flight, whether it is engineering calculation method or numerical simulation method, and it is impossible to feed back the flight attitude and parameters of the aircraft in real time. Adjustment, it is impossible to ensure that the aircraft is always flying in the safe pipeline

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