CN104048874B - A kind of load following loading system for aircraft flap reliability test - Google Patents
A kind of load following loading system for aircraft flap reliability test Download PDFInfo
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Abstract
The present invention relates to a kind of load following loading system for aircraft flap reliability test, it comprises bearing wall, it is characterized in that, it also comprises bracing member, load loads adjustment unit, load Detection and adjustment unit, wherein, wing flap is arranged on wing, and wing is arranged on bearing wall at its wing root place; Above-mentioned bracing member comprises two root posts and crossbeam, and it supports above-mentioned load and loads adjustment unit, load Detection and adjustment unit; Above-mentioned load loading unit comprises torque motor, cable wire, and above-mentioned torque motor is arranged on above-mentioned bracing member, and wing flap is applied reactive force, and above-mentioned cable wire is connected with torque motor; Above-mentioned load Detection and adjustment unit, it comprises angle sensor device, slide track component and coaster assembly. The present invention is provided with multiple loading point on wing flap aerofoil, and one loads point corresponding to a set of loading system, and it can simulate the size of real-time aerofoil aerodynamic load, direction and equivalent operating point.
Description
Technical field
The present invention relates to aircraft reliability test field, particularly relate to a kind of load following loading system for aircraft flap reliability test.
Background technology
Wingflap mechanism is the important high lift device of aircraft, it is mainly used in the pneumatic separation delaying on wing, it is to increase the critical angle of attack of aircraft, and increases the lift coefficient of wing. The reliability of wingflap mechanism is directly connected to aircraft flight safety, for exposing the potential failure mode of wingflap mechanism, and improves its reliability level, it is necessary to wingflap mechanism is carried out reliability test; And aerodynamic load suffered in wing flap moving process is the principal element affecting its Movement function reliability. In addition, wingflap mechanism volume is big, weight big, structure and function principle is complicated, and therefore the following loading of wing flap aerodynamic load has just become the core content of its reliability test.
In prior art, paper " loading method is tested in the interview of aircraft structure movable wing " proposes two pressurized strut loading scheme, in aerofoil moving process, aerofoil position transducer reads aerofoil positional information in real time, the curved line relation of Controlling System according to aerofoil positional information and with each pressurized strut pressure adjusts the size of each pressurized strut hydraulic pressure pressure in real time, and the load of size, direction and required loading that each pressurized strut makes a concerted effort is matched. Its shortcoming is: the following loading scope that (a) can realize is less, is not suitable for the running gear that wing flap, hatch door etc. need to realize folding and unfolding in a big way; B () each loading point all needs to install a set of following loading system, it is difficult to adapt to the more situation loading point.
China 201210528949.X patent, No. 201120541107.9 patent, No. 201120000929.6 patent etc. propose mobile pressurized strut scheme, its principle of work and power is close, situation about loading in a big way can be adapted to preferably, but its shortcoming is: (a) can not control each direction loading the suffered load of point respectively; B () to meet the requirement of following loading on a large scale, then needs the hydraulic pressure pressurized strut of greater depth, suitability is poor.
China's No. 201110430890.6 Patent design is a kind of based on the following loading system of servomotor and cable wire, but the program only can control size and the direction of load, can not control load point of application, is only applicable to the loading of the simple load of single-point. The column type guide rod strength and stiffness of the program are low, and guide rod and slide block are that sliding friction and contact surface are too short, it is difficult to bear bigger upsetting moment, easily cause Block failure. In addition, the guide rod of the program is vertically placed, and guide rod length required in following loading situation on a large scale is longer. Thus, the program is difficult to adapt to the following loading situation on a large scale that aircraft flap etc. bears complicated big load.
In view of above-mentioned defect, creator of the present invention obtains this creation finally through long-time research and practice.
Summary of the invention
It is an object of the invention to provide a kind of load following loading system for aircraft flap reliability test, in order to overcome above-mentioned technological deficiency.
For achieving the above object, the present invention provides a kind of load following loading system for aircraft flap reliability test, and it comprises bearing wall, it is characterised in that, it also comprises bracing member, load loads adjustment unit, load Detection and adjustment unit, wherein,
Wing flap is arranged on wing, and wing is arranged on bearing wall at its wing root place;
Above-mentioned bracing member comprises two root posts and crossbeam, and it supports above-mentioned load and loads adjustment unit, load Detection and adjustment unit;
Above-mentioned load loading unit comprises torque motor, cable wire, and above-mentioned torque motor is arranged on above-mentioned bracing member, and wing flap is applied reactive force, and above-mentioned cable wire is connected with torque motor, and loading force conducts to above-mentioned load Detection and adjustment unit;
Above-mentioned load Detection and adjustment unit, it comprises angle sensor device, slide track component and coaster assembly, above-mentioned angle sensor device arranges and is on the torsion bar that wing flap is connected, the angle of detection wing flap in real time, and transferring in a controller, above-mentioned controller controls above-mentioned load Detection and adjustment unit action;
Above-mentioned coaster assembly is arranged on slide track component, and coaster assembly is connected with above-mentioned cable wire, and above-mentioned slide track component is connected with above-mentioned bracing member.
Further, above-mentioned slide track component comprises a slide rail, two coasters, two servomotors, two rhizoid thick sticks, two line shift sensors, and above-mentioned slide rail two ends are separately installed with a servomotor, a rhizoid thick stick and a line shift sensor;
Above-mentioned servomotor drives coaster to move along slide rail by leading screw;
The position of above-mentioned line shift sensor Real-Time Monitoring coaster on slide rail.
Further, above-mentioned coaster assembly comprises feed screw nut, pulley, coaster main body and roller, and above-mentioned coaster main body upper end is provided with feed screw nut, for being connected with leading screw; Its lower end is provided with pulley, for walking around above-mentioned cable wire; Above-mentioned coaster main body both sides are separately installed with 4 rollers in rectangular layout, and the inner side of each roller is provided with flange.
Further, the Component composition that above-mentioned slide rail is "T"-shaped by 3 cross sections becomes, and forms two bar-shaped troughs; Two coasters are arranged in two bar-shaped troughs of slide rail respectively.
Further, one end of above-mentioned cable wire is connected with wing flap by leverage, is provided with pulling force sensor between cable wire and leverage;
The other end of above-mentioned cable wire walks around coaster and pulley respectively, is finally connected on capstan winch, and above-mentioned capstan winch is driven by torque motor.
Further, also comprise a wing flap drive-motor, on it is arranged on above-mentioned bearing wall, drive wing flap motion by torsion bar.
Further, above-mentioned column and crossbeam form " door " shape supporting structure, and are welded by section bars such as two channel-section steels respectively, and crossbeam is provided with pulley.
Further, above-mentioned slide rail is that angled manner is installed on above-mentioned bracing member by two slide rail joints at its two ends respectively.
The useful effect of the present invention compared with prior art is: the present invention is provided with multiple loading point on wing flap aerofoil, and one loads point corresponding to a set of loading system. In loading procedure, the loading direction that each loading point loads is identical, controls its point of application made a concerted effort by controlling the size of each loading point load. In wing flap moving process, angle sensor device Real-Time Monitoring wing flap position, and this position signal is passed to controller, controller adjusts load size and direction accordingly. Meanwhile, supervisory signal is fed back to controller by pulling force sensor and line shift sensor respectively, to realize the closed-loop control of system.
Slide rail in the present invention is at a certain angle in tilting location arrangements, slide rail required in same loading range situation and leading screw length are short, and thus produce following two useful effects: (a) in the case, move distance needed for coaster is short, movement velocity is low, the servomotor that power can be adopted less; B following loading scope that () can adapt to is relatively big, generally allows aerofoil to rotate more than 90 degree, can meet the following loading of the aircraft typical mechanism maneuvering loads such as general hatch door, flap slat, landing gear.
In addition, slide rail can be made up of section bars such as general steel plate, channel-section steel, I-beams, and tooling cost is low, and strong relative to common cylinder shape guide rod supporting capacity. Coaster can undertake upper and lower to load, transverse load and upsetting moment, suitability is strong. The key parts such as leading screw, motor, controller can adopt goods shelf products, and system building cost is low. Loading direction and size are by electric machine control, it is not necessary to the complex apparatus such as hydraulic power source, and pilot system volume is little, easy to operate. Controlling System adopts closed-loop control, loading accuracy height.
Accompanying drawing explanation
Fig. 1 is the stereographic map of the present invention for the load following loading system of aircraft flap reliability test;
Fig. 2 is the control principle schematic of the present invention for the load following loading system of aircraft flap reliability test;
Fig. 3 is the structure iron of wingflap mechanism of the present invention and drive system thereof;
Fig. 4 is the slide rail-pulley mechanism local structure schematic diagram of the present invention;
Fig. 5 is the slide rail-pulley mechanism one-piece construction schematic diagram of the present invention.
Embodiment
Below in conjunction with accompanying drawing, to above-mentioned being described in more detail with other technology feature and advantage of the present invention.
The present invention is provided with multiple loading point on wing flap aerofoil, and one loads point corresponding to a set of loading system. In loading procedure, the loading direction that each loading point loads is identical, controls its point of application made a concerted effort by controlling the size of each loading point load. In wing flap moving process, angle sensor device Real-Time Monitoring wing flap position, and this position signal is passed to controller, controller adjusts load size and direction accordingly. Meanwhile, supervisory signal is fed back to controller by pulling force sensor and line shift sensor respectively, to realize the closed-loop control of system.
Refer to shown in Fig. 1-5, the present invention is used for the load following loading system of aircraft flap reliability test, it comprises bearing wall 1, wing flap drive-motor 2 is arranged on bearing wall on 1, drive wing flap 5 to move by torsion bar 4, torsion bar 4 is provided with angle sensor device 3, also comprise a wing flap drive-motor 2 for monitoring the position of wing flap 5, it is arranged on bearing wall on 1, drives wing flap 5 to move by torsion bar 4.
Also comprise bracing member, load loading adjustment unit, load Detection and adjustment unit, bracing member comprises two root posts 13 and crossbeam 14, its support loads loads adjustment unit, load Detection and adjustment unit, column 13 and crossbeam 14 form " door " shape supporting structure, and be welded by section bars such as two channel-section steels respectively, crossbeam 14 is provided with pulley 18.
Load loading unit comprises torque motor 19, cable wire 17, and torque motor 19 is arranged on bracing member, and wing flap is applied reactive force, and cable wire 17 is connected with torque motor 19, and loading force conducts to load Detection and adjustment unit;
Load Detection and adjustment unit, it comprises angle sensor device 3, slide track component and coaster assembly, and angle sensor device 3 arranges and is on the torsion bar 4 that wing flap 5 is connected, in real time the angle of detection wing flap 5, and transfer in a controller, controller control load Detection and adjustment unit action;
Coaster assembly is arranged on slide track component, and coaster assembly is connected with cable wire 17, and slide track component is connected with bracing member.
Slide track component comprises a slide rail 9, two coasters, two servomotor 11, two rhizoid thick sticks, 12, two line shift sensors 16, and slide rail 9 two ends are separately installed with a servomotor 11, rhizoid thick stick 12 and a line shift sensor 16; Slide rail 9 is installed on bracing member in angled manner by two slide rail joints 10 respectively at its two ends.
Servomotor 11 drives coaster to move along slide rail 9 by leading screw 12;
The position of line shift sensor 16 Real-Time Monitoring coaster on slide rail 9.
Coaster assembly comprises feed screw nut 15, pulley 18, coaster main body 21 and roller 2, and coaster main body 21 upper end is provided with feed screw nut 15, for being connected with leading screw 12; Its lower end is provided with pulley 18, for walking around cable wire 17; Coaster main body 21 both sides are separately installed with 4 rollers 22 in rectangular layout, and the inner side of each roller 22 is provided with flange.
The Component composition that slide rail 9 is "T"-shaped by 3 cross sections becomes, and forms two bar-shaped troughs; Two coasters are arranged in two bar-shaped troughs of slide rail 9 respectively, thus, coaster can undertake simultaneously upper and lower to load, transverse load and upsetting moment.
One end of cable wire 17 is connected with wing flap 5 by leverage 8, is provided with pulling force sensor 7 between cable wire 17 and leverage 8;
The other end of cable wire 17 walks around coaster and pulley 18 respectively, is finally connected on capstan winch 20, and capstan winch 20 is driven by torque motor 19.
Wing flap load following loading Systematical control principle is: the in advance relation curve in matching wing flap position and each loading point load size, direction; In wing flap 5 moving process, the position of angle sensor device 3 Real-Time Monitoring wing flap 5, and this position signal is passed to controller; Composing according to wing flap position and test load, controller adjusts each loading point load size in real time by torque motor 19, adjusts loading direction in real time by servomotor 11, leading screw 12, coaster and slide rail 9; Meanwhile, load signal is fed back to controller by pulling force sensor 7, and coaster position signal is fed back to controller by line shift sensor 16, to realize the closed-loop control of loading system, ensures precision and the real-time of following loading. Upper monitoring computer provides operator-machine-interface, for following loading system being monitored and control.
The foregoing is only the better embodiment of the present invention, it is only explanation property for invention, but not restrictive. Those skilled in the art is understood, and it can be carried out many changes in the spirit and scope that invention claim limits, even equivalence, but all will fall within the scope of protection of the present invention.
Claims (8)
1., for a load following loading system for aircraft flap reliability test, it comprises bearing wall (1), it is characterised in that, it also comprises bracing member, load loads adjustment unit, load Detection and adjustment unit, wherein,
Wing flap (5) is arranged on wing (6), and wing (6) is arranged on bearing wall (1) at its wing root place;
Described bracing member comprises two root posts (13) and crossbeam (14), and it supports described load and loads adjustment unit, load Detection and adjustment unit;
Described load loading unit comprises torque motor (19), cable wire (17), described torque motor (19) is arranged on described bracing member, wing flap is applied reactive force, described cable wire (17) is connected with torque motor (19), and loading force conducts to described load Detection and adjustment unit;
Described load Detection and adjustment unit, it comprises angle sensor device (3), slide track component and coaster assembly, described angle sensor device (3) arranges and is on the torsion bar (4) that wing flap (5) is connected, detect the angle of wing flap (5) in real time, and transferring in a controller, described controller controls described load Detection and adjustment unit action;
Described coaster assembly is arranged on slide track component, and coaster assembly is connected with described cable wire (17), and described slide track component is connected with described bracing member.
2. the load following loading system for aircraft flap reliability test according to claim 1, it is characterized in that, described slide track component comprises a slide rail (9), two coasters, two servomotors (11), two rhizoid thick sticks (12), two line shift sensors (16), and described slide rail (9) two ends are separately installed with a servomotor (11), a rhizoid thick stick (12) and a line shift sensor (16);
Described servomotor (11) drives coaster to move along slide rail (9) by leading screw (12);
The position of described line shift sensor (16) Real-Time Monitoring coaster on slide rail (9).
3. the load following loading system for aircraft flap reliability test according to claim 2, it is characterized in that, described coaster assembly comprises feed screw nut (15), pulley (18), coaster main body (21) and roller (2), described coaster main body (21) upper end is provided with feed screw nut (15), for being connected with leading screw (12); Its lower end is provided with pulley (18), for walking around described cable wire (17); Described coaster main body (21) both sides are separately installed with 4 rollers (22) in rectangular layout, and the inner side of each roller (22) is provided with flange.
4. the load following loading system for aircraft flap reliability test according to claim 3, it is characterised in that, the Component composition that described slide rail (9) is "T"-shaped by 3 cross sections becomes, and forms two bar-shaped troughs; Two coasters are arranged in two bar-shaped troughs of slide rail (9) respectively.
5. the load following loading system for aircraft flap reliability test according to claim 3, it is characterized in that, one end of described cable wire (17) is connected with wing flap (5) by leverage (8), is provided with pulling force sensor (7) between cable wire (17) and leverage (8);
The other end of described cable wire (17) walks around coaster and pulley (18) respectively, is finally connected on capstan winch (20), and described capstan winch (20) is driven by torque motor (19).
6. the load following loading system for aircraft flap reliability test according to claim 2, it is characterized in that, also comprise a wing flap drive-motor (2), it is arranged on described bearing wall on (1), drives wing flap (5) motion by torsion bar (4).
7. the load following loading system for aircraft flap reliability test according to claim 3, it is characterized in that, described column (13) and crossbeam (14) form " door " shape supporting structure, and be welded by section bars such as two channel-section steels respectively, crossbeam (14) is provided with pulley (18).
8. the load following loading system for aircraft flap reliability test according to claim 7, it is characterized in that, described slide rail (9) is installed on described bracing member in angled manner by two slide rail joints (10) respectively at its two ends.
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