Positioning assembly cooperative control method suitable for full-active posture-adjusting butt joint of large section of aircraft
A positioning component and cooperative control technology, which is applied in the direction of electric controllers, general control systems, and controllers with specific characteristics, etc., can solve the problems of time-consuming, complicated operations and low efficiency during the attitude adjustment and docking process
Pending Publication Date: 2022-06-28
SHANGHAI AIRCRAFT MFG
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Problems solved by technology
[0006] The technical problem to be solved by the present invention is to overcome the need for operators to intervene and manually fine-tune the position of the positioning components in the process of fully active attitude adjustment and docking of most sections of the existing aircraft so as to release the excessive stress that the large sections of the aircraft may bear. Due to the defects of complicated operations, long time-consuming and low efficiency during the attitude adjustment and docking process, a new positioning component cooperative control method for fully active attitude adjustment and docking for most sections of the aircraft is proposed
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[0029] The preferred embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings. The following descriptions are exemplary and not limiting of the present invention, and any other similar situations also fall within the protection scope of the present invention.
[0030] In the following detailed description, directional terms, such as "left", "right", "upper", "lower", "front", "rear", etc., are used with reference to the directions described in the drawings. Components of embodiments of the present invention may be oriented in a variety of different orientations, and directional terminology is used for purposes of illustration and not limitation.
[0031] For the fully active attitude docking process of the large section of the aircraft, the large section of the aircraft is connected with a plurality of positioning components. Typically, there are multiple positioning assemblies that are connected or otherwise ...
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The invention discloses a positioning assembly cooperative control method suitable for full-active attitude adjustment butt joint of a large section of an aircraft, and the method comprises the following steps: monitoring the space vector force borne by each positioning assembly during the full-active attitude adjustment butt joint period; whether the space vector force borne by the positioning assembly exceeds the maximum stress threshold value or not is checked, if not, full-active posture adjusting butt joint continues to be executed, and if yes, the following motion compensation steps are executed; selecting a reference positioning assembly and calculating an interpolation speed used for compensating the space vector force borne by the reference positioning assembly as a unit speed; calculating interpolation speeds of other positioning assemblies according to the unit speed; and the compensation motion of each positioning assembly is synchronously controlled. According to the invention, cooperative control is carried out on the positioning assembly based on the stress monitoring and the vector fitting result of the stress and the interpolation algorithm, automatic stress release of the large section of the aircraft in the full-active attitude adjustment docking process can be realized, and the method has the advantages of high execution efficiency and simple personnel operation.
Description
technical field [0001] The invention relates to the attitude adjustment and docking of large sections of the aircraft, in particular to the fully active attitude adjustment docking scene of the large aircraft sections, and in particular to a positioning component coordinated control method suitable for the fully active attitude adjustment docking of the large aircraft sections. Background technique [0002] In the process of assembling or assembling most parts of the aircraft, the precise control of the attitude adjustment and docking process is particularly critical. The main body of the mechanism is directly damaged or the service life is reduced due to the force. Among them, the large part of the aircraft generally refers to the larger parts of the aircraft before riveting and forming, including such as the nose, front fuselage, mid-fuselage, wings, mid-rear fuselage, rear fuselage, horizontal tail, etc. of the aircraft, or The segment assembly after the above-mentioned ...
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IPC IPC(8): G05B11/42
CPCG05B11/42G05B19/41G01L5/00
Inventor 董正建姬煜琦王平张帅
Owner SHANGHAI AIRCRAFT MFG