A Composite Control Method for Aircraft Front Wheel Electric Steering and Swing Reduction
A compound control and turning control technology, applied in the direction of AC motor control, control system, aircraft parts, etc., can solve the problems such as non-adjustable parameters of front landing gear swing reduction, inability to adapt to various road surfaces and operating conditions, etc., to reduce weight , simplify the structure, increase the effect of flexibility
Active Publication Date: 2021-01-01
LANDING GEAR ADVANCED MFG
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Problems solved by technology
In the common hydraulic anti-sway actuator, the hydraulic oil chamber plays the role of anti-sway of the landing gear, but this method has the disadvantages that the anti-sway parameters of the front landing gear cannot be adjusted, and cannot adapt to various road surfaces and operating conditions.
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[0033] The technical solutions in the present invention are clearly and completely described below in combination with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.
[0034] Such as figure 1 As shown, a compound control method for aircraft front wheel electric steering and swing reduction provided by the present invention includes the following steps:
[0035] 1. Receive a turning or sway reduction control command, and determine the corresponding control mode according to the control command. The control mode includes a turning control mode and a sway control mode, the turning command corresponds to the turning control mode, and the swayi...
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The invention discloses a composite control method for electric turning and pendulum reduction of a front wheel of an airplane, and relates to the control technology of turning and pendulum reductionof the airplane. The composite control method comprises the steps of determining different control modes through different control instructions, obtaining a target value of motor torque / current through closed-loop control in a turning control mode, obtaining a target value of damping torque / current through damping calculation in a pendulum reduction control mode, generating PWM adjusting signals through the same torque / current controller according to the target value, and finally realizing operation control on the same motor through the same motor driving unit according to the PWM adjusting signals to achieve the purpose of turning or pendulum reduction; and by the control method, the functions of turning and pendulum reduction share one set of motor actuating mechanism, the structure ofthe actuating mechanism is simplified, and the weight of a landing gear is reduced.
Description
technical field [0001] The invention belongs to the control field of aircraft turning and swing reduction, and in particular relates to a compound control method for electric steering and swing reduction of aircraft front wheels. Background technique [0002] At present, turning and swing reduction are two important functions of an aircraft. The former is an active operating system, and the latter is a passive damping system. Action execution often requires the use of different actuators. In the common hydraulic anti-sway actuator, the hydraulic oil chamber plays the role of anti-sway of the landing gear, but this method has the disadvantages that the anti-sway parameters of the nose landing gear cannot be adjusted, and cannot adapt to various road surfaces and operating conditions. [0003] With the trend of full electricization of small aircraft, the functions of nose wheel turning and sway reduction can only be realized by full electric mechanism. At the same time, as t...
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IPC IPC(8): B64C25/34B64C25/50H02P27/08
CPCB64C25/34B64C25/50H02P27/085Y02T50/40
Inventor 李隆鹏路红伟赵云峰陈各立邓志云胡纯刘琳博
Owner LANDING GEAR ADVANCED MFG