Aircraft aerodynamic layout adjusting method and device and electronic equipment

Abstract

The invention discloses an aircraft pneumatic layout adjusting method and device and electronic equipment, and belongs to the technical field of aircraft design. According to transverse course combination stability parameters and aileron-rudder crosslinking parameters corresponding to the flight trajectory state points, trajectory state points are divided into a traditional control strategy or a coupling control strategy controllable area or a non-controllable area according to the parameters, and by adjusting the corresponding transverse course combination stability parameters and aileron-rudder crosslinking parameters, the trajectory state points in the non-controllable area are adjusted to the controllable area; the initial pneumatic layout is adjusted according to the adjusted parameters; The coupling controllable interval is fully utilized, the coupling effect between the transverse direction and the heading direction of the aircraft is utilized, the requirement for the control capacity of the aircraft is greatly reduced, the control potential of the aircraft is fully excavated to relax the design constraint of the control capacity, and therefore the requirement for the structural size of a control surface is reduced, and the weight of the whole aircraft and the energy consumption of a steering engine are reduced.

Description

technical field [0001] The invention relates to an aircraft aerodynamic layout adjustment method, device and electronic equipment, belonging to the field of aircraft design. Background technique [0002] When designing an aircraft, the overall and aerodynamic disciplines first design the overall raw data and aerodynamic raw data, obtain data such as overall parameters, aerodynamic parameters, and expected flight envelopes, and then provide the obtained data to the control profession to make the control profession according to the above-mentioned parameters for control system design. [0003] In the existing method, when designing the aerodynamic layout, the traditional static stability criterion is often used to preliminarily and optimize the adjustment of the aerodynamic layout. The above-mentioned aerodynamic layout design method is mainly suitable for aircraft with a narrow flight range. For aircraft with a large flight airspace and speed range, the above method needs to...

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Problems solved by technology

The above-mentioned aerodynamic layout design method is mainly suitable for aircraft with a narrow flight range. For aircraft with a large flight airspace and speed range, the above method needs to take into account the aerodynamic characteristics of the full speed range and the entire airspace range, especially large In the state of Mach number and high angle of attack, the size of the control rudder surface of the designed aircraft is very large, thus increasing the weight of the whole machine and the energy consumption of the steering gear

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