Design method for the influence of deformation difference between aircraft and mechanical control system on maneuvering control

Abstract

The invention discloses a method for designing the influence of deformation differences between an aircraft and a mechanical control system on maneuvering maneuvers, comprising the following steps: 1) according to the requirements of the resultant force and moment during the maneuvering of the aircraft, calculating the rudder surfaces required for the longitudinal, lateral and directional maneuvering of the aircraft Skewness; 2) Calculate the deviation of the mechanical control system relative to the deformation of the aircraft during the maneuvering process of the aircraft; 3) Calculate the cockpit control displacement and control force of the aircraft during the maneuvering process of the aircraft; 4) Repeat the steps according to the different target overloads during the maneuvering of the aircraft 1-Step 3, obtain the vertical, horizontal and heading cockpit control displacements, control force gradients and lever displacement gradients of the corresponding target overloads during maneuvering, and the present invention realizes the determination of the real mechanical control system characteristics of the aircraft in flight The process, as well as the actual design and determination method of aircraft maneuvering and control characteristics, ensure the consistency of flight and design, correct the error of mechanical control system characteristics, improve the safety of aircraft flight, and improve the control quality.

Description

technical field [0001] The invention relates to the technical field of aircraft maneuverability stability design, in particular to a design method for the influence of deformation differences between an aircraft and a mechanical control system on maneuvering control. Background technique [0002] At present, although control systems using electrical transmission and optical transmission are more and more widely used in modern aircraft, aircraft using mechanical systems are still the mainstream of aircraft currently in service. [0003] Fighters and bombers controlled by mechanical systems belong to the second-generation aircraft technology. For example, the MiG-21 and MiG-23 of the Soviet Union and the J-7 and J-8 of China all use hydraulic power-assisted mechanical control systems, although they have become the main force at present. A large number of third- and fourth-generation fighters and bombers of the military have introduced fly-by-wire control systems, but if the ar...

AI Technical Summary

Problems solved by technology

[0003] Fighters and bombers controlled by mechanical systems belong to the second-generation aircraft technology. For example, the MiG-21 and MiG-23 of the Soviet Union and the J-7 and J-8 of China all use hydraulic power-assisted mechanical control systems, although they have become the main force at present. A large number of third- and fourth-generation fighters and bombers of the military have introduced fly-by-wire control systems, but if the arrangement between the drive mechanism (steering gear) and the amplification mechanism (booster) in the fly-by-wire control system is unreasonable, it will also cause relative deformation. Moreover, aircraft operated by mechanical systems are still the mainstream of active combat aircraft and a large number of civilian and general-purpose aircraft.

[0004] At present, domestic and foreign descriptions of the design of aircraft maneuvering and control characteristics have not yet mentioned the consideration of the mutual deformation of the aircraft body and mechanical systems. Although many aircraft have corrected the aircraft system according to the flight test results, there is a lack of systematic determination and analysis methods.

Images