CN110816815B

CN110816815B - Human-sensing device of aircraft flight control system

Info

Publication number: CN110816815B
Application number: CN201910967957.6A
Authority: CN
Inventors: 沈金玲; 刘国庆; 王伟志
Original assignee: South China Aircraft Industry Co Ltd of China Aviation Industry General Aircraft Co Ltd
Current assignee: South China Aircraft Industry Co Ltd of China Aviation Industry General Aircraft Co Ltd
Priority date: 2019-10-12
Filing date: 2019-10-12
Publication date: 2023-06-30
Anticipated expiration: 2039-10-12
Also published as: CN110816815A

Abstract

The application provides a people feel device of aircraft flight control system, people feel device includes load mechanism control box 10, becomes arm mechanism 20, spring mechanism 30, wherein: the load mechanism control box 10 is respectively connected with an on-board atmosphere data system, a flight parameter system and an on-board power supply, and the load mechanism control box 10 is electrically connected with the arm changing mechanism 20; one end of the arm changing mechanism 20 is connected with a pull rod, the other end of the arm changing mechanism 20 is connected with a spring mechanism 30, and the pull rod is connected with a control surface.

Description

Human-sensing device of aircraft flight control system

Technical Field

The invention is applied to a traditional mechanical booster flight control system, and particularly relates to a human-sensing device of an aircraft flight control system.

Background

The human sensing device is an indispensable part of a flight control system, with the continuous development of aircraft design and manufacturing technology, the flying height and speed of the aircraft are continuously increased, and the change rate of the displacement of the rod force rod caused by the continuous expansion of the flying height and speed of the aircraft is greatly influenced by the change rate of overload, so that the control of a driver is directly influenced.

The pitching operability of the aircraft is the characteristic that a pilot pushes and pulls a steering column to control the deflection of a control surface, so that the aircraft rotates around a transverse axis to change the elevation angle. The pilot pushes the rod forward, so that the elevation angle of the aircraft can be reduced; conversely, pulling the rod backward increases the elevation angle. The aircraft is lifted or lowered by the deflection of the control surface. When the control surface deflects, the additional force generated creates a moment on the control surface shaft, which is transmitted to the steering column and attempts to return the steering column to the neutral position, and the pilot must exert a force on the steering column to balance it, which is referred to as the steering column force. The larger the deflection angle of the control surface or the larger the flight dynamic pressure is, the larger the rod force is; conversely, the smaller the control surface deflection angle or the smaller the flight dynamic pressure, the smaller the rod force. In order that the pilot's stick force does not change too much throughout the flight speed and altitude variation range to meet the pilot's general maneuvering habits, the effects of flight speed and altitude on maneuvering must be eliminated.

Disclosure of Invention

The invention aims to improve a control surface control system in a mechanical flight control system, and a human-sensing device changes the transmission ratio of a main system along with the rapid pressure and also changes the magnitude of a simulated load along with the rapid pressure. The steering performance is improved, the steering technology of a driver is ensured to be consistent all the time, and the dangerous situation of the aircraft caused by overlarge steering during high-speed flight is avoided.

The application provides a people feel device of aircraft flight control system, people feel device includes load mechanism control box 10, becomes arm mechanism 20, spring mechanism 30, wherein:

the load mechanism control box 10 is respectively connected with an on-board atmosphere data system, a flight parameter system and an on-board power supply, and the load mechanism control box 10 is electrically connected with the arm changing mechanism 20;

one end of the arm changing mechanism 20 is connected with a pull rod, the other end of the arm changing mechanism 20 is connected with a spring mechanism 30, and the pull rod is connected with a control surface.

Preferably, one end of the arm changing mechanism 20 is connected to the control surface pull rod through a connecting joint 21, and the other end of the arm changing mechanism 20 is connected to the spring mechanism 30 through a connecting joint 25.

Preferably, the arm change mechanism 20 is connected to the steering column via a connection joint 22.

Preferably, the arm changing mechanism 20 includes an arm changing motor 26, a ball screw 23 and a housing 24, the arm changing motor 26 is connected with the ball screw 23 through a reduction gear, and the arm changing motor 26 and the ball screw 23 are disposed in the housing 24.

Preferably, the spring mechanism 30 comprises a compression spring 31, a sleeve 32, a piston rod 33, wherein: the compression spring 31 is sleeved outside the piston rod 33, and the sleeve 32 is sleeved outside the compression spring 31.

Preferably, the arm changing mechanism 20 is a screw.

Preferably, one end of the arm-changing mechanism 20 is hinged to the pull rod.

Preferably, the other end of the arm changing mechanism 20 is hinged with a spring mechanism 30.

The invention has the beneficial effects that: the problem of difficult operation of a driver caused by low control surface efficiency due to overlarge change rate of the overload caused by overlarge speed and overlarge change rate of the displacement of the steering rod is solved, and the method can be widely applied to an aircraft control system with the problem; compared with the foreign cam type hydraulic drive spring mechanism with the rapid compression, the invention has the advantages of simple structure, mature and simple processing technology, lower failure rate of an on-board power supply than the traditional hydraulic energy source and high reliability of the system by adopting electric drive.

Drawings

FIG. 1 is a schematic diagram of a human sensing device according to the present invention;

fig. 2 is a schematic structural diagram of an arm-changing mechanism provided by the invention;

FIG. 3 is a schematic view of a spring mechanism according to the present invention;

wherein: 10-a load mechanism control box; 20-arm changing mechanism; 30-a spring mechanism; 21-a connection joint; 22-connecting joints; 23-screw rod; 24-a housing; 25-connecting joints; 26-arm-changing motor; 31-a piston rod; 32-a sleeve; 33-spring.

Detailed Description

The invention provides a human-sensing device of an aircraft flight control system, which comprises a load mechanism control box, an arm changing mechanism and a spring mechanism, wherein the load mechanism control box is connected with the arm changing mechanism; the load mechanism control box is connected with the on-board air data system, the flight parameter system and the on-board power supply, and sends an adjusting signal to the arm changing mechanism through calculation according to the change of the height and the speed of the airplane, so that the ball screw is controlled to move up and down, the transmission ratio from the steering rod to the control surface and the spring mechanism is changed, the compression amount of the spring mechanism is changed, and the changed simulated load is output. The movable arm position and the working state of the arm changing mechanism are displayed on the control panel.

It can be seen that the present application incorporates a means for automatically changing the transmission ratio of the steering system into the steering system from the steering column to the control surface, automatically changing the transmission ratio of the steering column to the control surface and the spring mechanism. Through the human sensing device, when the rapid compression is large, the movable arm of the arm changing mechanism is arranged at the large arm position, the transmission ratio is reduced, the compression amount of the spring is increased, and the rod force of the driver is also increased; conversely, when the rapid pressure decreases, the arm changing mechanism is adjusted to the forearm position, the transmission ratio increases, and the lever force transmitted back to the driver decreases. Therefore, the pilot can keep consistent driving technology under different flight states, and the control difficulty caused by low efficiency of the flight control surface can be improved.

Specifically, the load mechanism control box receives an airspeed signal and a steering column displacement signal sent by the aircraft, outputs an actuating signal of the variable-arm electric mechanism according to a given control rule, and simultaneously feeds back a stroke voltage to the load mechanism control box in real time through a control interface by a displacement sensor in the variable-arm electric mechanism, and when the stroke voltage value reaches a stroke voltage at a preset position, the load mechanism control box blocks and outputs the actuating signal of the electric mechanism. The control box has BIT function, and when the arm-changing mechanism is out of order, the control box can send an alarm signal to the avionics system.

Specifically, the arm changing mechanism is composed of an arm changing motor 26, a ball screw 23, a housing 24, and the like, and is connected to the control surface tie rod, the steering column, and the spring mechanism through

mechanical joints

21, 22, and 25, respectively. The arm changing mechanism receives a control instruction sent by the load mechanism control box, drives the arm changing motor 26 to move, drives the screw rod to move up and down along a-a, and rotates along a b-b axis as a whole, so that the aim of changing the transmission ratio of the steering rod to the control surface and the spring mechanism to the steering rod is fulfilled; when the load mechanism control box 10 is cut off from excitation, the arm changing mechanism 20 immediately stops moving, and the relative movement of the screw nut and the ball screw 23 is locked; the variable arm mechanism 20 has a current limiting protection function when the external load exceeds the rated load of the variable arm mechanism.

Specifically, the spring mechanism is composed of a compression spring 31, a sleeve 32 and a piston rod 33, and two ends of the spring mechanism are respectively connected with the arm changing mechanism and the on-machine adjusting mechanism through pull rods. The piston rod of the spring mechanism is driven to stretch and retract according to the input of the arm changing mechanism, and the compression amount of the spring 31 is changed, so that the magnitude of the driving rod force is changed.

A specific embodiment of the present invention will be further described with reference to fig. 2. The invention relates to a human sensing device of an aircraft flight control system, which comprises a load mechanism control box, an arm changing mechanism and a spring mechanism, wherein the human sensing device is shown in figure 3, and the principle of the human sensing device is shown in figure 1. The arm changing mechanism is composed of a ball screw 23, a housing 24, an arm changing motor 26, and the like, and is connected with a control surface pull rod, a steering rod and a spring mechanism through

mechanical joints

21, 22 and 25, respectively. The variable arm mechanism receives a control instruction sent by the load mechanism control box, drives the variable arm mechanism to move, drives the screw rod to move up and down along a-a, drives the whole variable arm mechanism to rotate along a b-b axis, feeds back the rotating speed and the position of the variable arm motor in real time, and when the stroke voltage value reaches the stroke voltage at a preset position, the load mechanism control box 10 blocks and outputs an actuating signal of the electric mechanism, the variable arm mechanism stops working, and one-time adjustment is completed, so that the aim of changing the transmission ratio from a driving rod to a control surface and from a spring mechanism to a driving rod is fulfilled; when the load mechanism control box 10 is de-energized, the arm change mechanism immediately stops moving, and the relative movement of the screw nut and the ball screw 23 is locked.

Claims

1. A human-sensing device of an aircraft flight control system, characterized in that the human-sensing device comprises a load mechanism control box (10), a variable arm mechanism (20) and a spring mechanism (30), wherein:

the load mechanism control box (10) is respectively connected with an on-board atmospheric data system, a flight parameter system and an on-board power supply, and the load mechanism control box (10) is electrically connected with the arm changing mechanism (20);

one end of the arm changing mechanism (20) is connected with a control surface pull rod through a first connecting joint (21), and the control surface pull rod is connected with a control surface; the other end of the arm changing mechanism (20) is connected with the spring mechanism (30) through a second connecting joint (25); the arm changing mechanism (20) is connected with the steering column through a third connecting joint (22); the arm changing mechanism (20) comprises an arm changing motor (26), a ball screw (23) and a shell (24), wherein the arm changing motor (26) is connected with the ball screw (23) through a reduction gear, and the arm changing motor (26) and the ball screw (23) are arranged in the shell (24); the spring mechanism (30) comprises a compression spring (31), a sleeve (32) and a piston rod (33), wherein: the compression spring (31) is sleeved outside the piston rod (33), and the sleeve (32) is sleeved outside the compression spring (31);

the arm changing mechanism receives a control instruction sent by the load mechanism control box, drives the arm changing motor to move, drives the screw rod to move up and down along a-a, and integrally rotates along a b-b axis, so that the transmission ratio of the steering rod to the control surface and the spring mechanism to the steering rod is changed.

2. The device according to claim 1, wherein one end of the arm-changing mechanism (20) is hinged to the control surface tension rod.

3. The human sensing device according to claim 2, wherein the other end of the arm changing mechanism (20) is hinged with a spring mechanism (30).