Flight control simulator tension and compression load test system field calibration device

Abstract

The on-site calibration device of the tensile and compressive load test system of a flight control simulator of the present invention comprises a structural frame, a loading mechanism, a standard measuring unit, a host computer and a fine-tuning mechanism; the loading mechanism, the standard measuring unit and the calibrated force sensor are connected in sequence and then installed on the structural frame; the fine-tuning mechanism supports the loading mechanism, and the loading mechanism, the standard measuring unit and the calibrated force sensor are placed in the same straight line by fine-tuning the position of the loading mechanism; the standard measuring unit is wirelessly connected to the host computer; and the calibrated force sensor is connected to the flight control simulator.

Description

Technical Field

[0001] The invention relates to the field of metrology calibration, and in particular to an on-site calibration device for a tensile and compressive load test system of a flight control simulator. Background Art

[0002] A large number of ground simulation tests are required before the aircraft's first flight, including main flight control system tests, high lift system tests, oil pressure system tests, takeoff gear system tests, etc.

[0003] The flight control ground simulation test requires the construction of a test bench that is one-to-one with the aircraft, including the nose, fuselage, left wing, right wing, tail wing, test room and stair railings.

[0004] The aircraft's primary flight control system is used to control the aircraft, achieve longitudinal, lateral and heading control and trim in the air, air deceleration control, and control after the aircraft touches down or aborts takeoff. The aircraft's high lift system consists of ten symmetrical leading edge slats and four trailing edge slats on the wing. Their function is to change the wing's curvature and area by extending the slats downward and deflecting the slats backward, thereby increasing the lift of the aircraft during takeoff and the lift and drag during landing, thereby reducing the aircraft's takeoff and taxiing distance.

[0005] In the main flight control system and high lift system test, a large number of force sensors are needed to monitor the force value, and the maximum force value can reach 100kN. The accuracy of the force sensor directly affects the entire main flight control system and high lift system test. Therefore, the calibration of the sensor and the entire control system is very important and necessary. Since the control system cannot be transported to the laboratory for calibration, the sensor and the entire control system can only be calibrated on-site.

[0006] At present, the tensile and compressive load test systems of flight control simulators are disassembled for calibration. The sensors are removed and sent to the metrology laboratory for calibration, and the data acquisition system of the test system control cabinet is also sent to the metrology laboratory for calibration. Such separate calibration cannot fully judge the measurement accuracy of the entire system. The on-site overall calibration method can avoid using the characteristic indicators of the force sensor as the indicators of the system on the one hand, and on the other hand, make the force direction of the calibrated force sensor the same as the force direction during normal work, so as to reproduce the original state to the greatest extent and ensure the authenticity of the data. Summary of the invention

[0007] The purpose of the present invention is to provide a field calibration device for a tensile and compressive load test system of a flight control simulator, so as to solve the problem of field calibration of a tensile and compressive load test system of a flight control simulator.

[0008] In order to achieve the above-mentioned purpose, the present invention provides an on-site calibration device for a tensile and compressive load test system of a flight control simulator, comprising a structural frame, a loading mechanism, a standard measuring unit, a host computer and a fine-tuning mechanism; the loading mechanism, the standard measuring unit and the calibrated force sensor are connected in sequence and installed on the structural frame; the fine-tuning mechanism supports the loading mechanism, and the loading mechanism, the standard measuring unit and the calibrated force sensor are placed in the same straight line by fine-tuning the position of the loading mechanism; the standard measuring unit is wirelessly connected to the host computer; and the calibrated force sensor is connected to the flight control simulator.

[0009] The above-mentioned on-site calibration device of the tensile and compressive load test system of the flight control simulator, wherein the structural frame includes a base, a rudder support and a movable end; the movable end is placed horizontally at one end of the base, can move on one end of the base, and is fixedly connected to the base after moving into position; a rudder support is respectively provided on the other end of the base and the movable end; the loading mechanism, the standard measuring unit and the calibrated force sensor are connected in series in sequence, and the two ends are respectively connected to the two rudder supports.

[0010] The above-mentioned on-site calibration device of the tensile and compressive load test system of the flight control simulator, wherein the rudder support laterally connected to the movable end can move laterally on the movable end, and then be fixedly connected to the movable end laterally after moving into position.

[0011] The above-mentioned flight control simulator tensile and compressive load test system on-site calibration device, wherein two rows of threaded holes are arranged at one end of the base, and different threaded holes in the same row have different distances from the rudder support at the other end of the base, and the two rows of threaded holes are used to respectively connect the two lateral sides of the movable end.

[0012] The above-mentioned flight control simulator tensile and compressive load test system on-site calibration device, wherein the movable end is horizontally provided with two T-slot bars, and a T-nut is placed in the T-slot bar, and the T-nut can move in the T-slot bar, and the rudder support is connected to the T-nut by a screw.

[0013] The above-mentioned flight control simulator tensile and compressive load test system on-site calibration device, wherein the rudder support includes a mounting plate, a U-shaped mounting seat and a latch, the U-shaped mounting seat is fixedly connected to a surface of the mounting plate, and the opening faces away from the surface; the U-shaped mounting seat is provided with a latch hole; and threaded holes are provided on both sides of the mounting plate.

[0014] The above-mentioned flight control simulator tensile and compressive load test system on-site calibration device, wherein the standard measurement unit includes a standard force sensor, a charge amplifier and a wireless measurement and control device; the standard force sensor converts the standard force information into a corresponding charge output, the output is conditioned and amplified by the charge amplifier to be converted into a voltage and A / D converted, and then transmitted to the host computer by wireless transmission through the wireless measurement and control device.

[0015] The above-mentioned flight control simulator tension and compression load test system on-site calibration device, wherein the loading mechanism adopts electro-hydraulic servo control technology, uses a servo oil source and an actuator as a power source and an actuator, and uses a digital computer as a load control and data processing center.

[0016] The above-mentioned on-site calibration device of the tensile and compressive load test system of the flight control simulator, wherein the fine-tuning mechanism is a mechanical mechanism based on the lifting and lowering transmission of the worm gear and screw screw, which realizes the lifting and lowering fine-tuning of the entire series combination of the loading mechanism, the standard force sensor and the calibrated force sensor, ensuring that the force angle error is less than 1°.

[0017] Compared with the prior art, the beneficial technical effects of the present invention are:

[0018] The on-site calibration device for the tensile and compressive load test system of the flight control simulator of the present invention realizes the on-site calibration of the tensile and compressive load test system of the flight control simulator by developing a calibration device composed of a fine-tuning mechanism, a loading mechanism and a structural frame. The combination of the fine-tuning mechanism and the structural frame ensures that the loading mechanism can correctly apply the standard force along the central axis of the standard force sensor and the calibrated force sensor.

[0019] The on-site calibration device for the tensile and compressive load test system of the flight control simulator of the present invention can solve the problem of the size of various sensors to be calibrated, ensuring that each sensor can have enough space for installation;

[0020] The on-site calibration device for the tensile and compressive load test system of the flight control simulator of the present invention is based on a standard measurement unit of a wireless sensor network, and can place a data processing terminal for on-site calibration together with a host computer (flight control simulator) of the calibrated force sensor, so as to facilitate digital comparison during the calibration process, reduce the time difference between the output value of the calibrated device and the standard output value during the calibration process, and enable the calibration work to be carried out smoothly;

[0021] The on-site calibration device for the tensile and compressive load test system of the flight control simulator of the present invention adopts an electro-hydraulic servo mechanism for loading, uses an oil source and an actuator as a power source and an actuator, uses a digital computer as a load control and data processing center, and is equipped with a data acquisition, displacement sensor and force sensor excitation module and a safety protection module, etc., so that both force value control and displacement control can be achieved;

[0022] The on-site calibration device of the flight control simulator tension and compression load test system of the present invention adopts a fine-tuning mechanism of a worm gear and screw screw lifting transmission on one side, and an up and down moving mechanism of a T-slot and a T-slot screw on the other side. The two cooperate to make the force direction of the calibrated force sensor the same as the force direction during normal operation, thereby reproducing the original state to the greatest extent. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The on-site calibration device of the flight control simulator tension and compression load test system of the present invention is provided by the following embodiments and drawings.

[0024] Figure 1 A top view of an on-site calibration device for a tensile and compressive load test system for a flight control simulator according to a preferred embodiment of the present invention.

[0025] Figure 2 Schematic diagram of the fine-tuning mechanism in a preferred embodiment of the present invention.

[0026] Figure 3 Schematic diagram of the structure of the movable end in a preferred embodiment of the present invention, wherein (a) is a side view and (b) is a top view.

[0027] Figure 4 Schematic diagram of the structure of the rudder support in a preferred embodiment of the present invention, wherein (a) is a side view and (b) is a top view. DETAILED DESCRIPTION

[0028] The following will be combined Figure 1 to Figure 4 The on-site calibration device for the tensile and compressive load test system of the flight control simulator of the present invention is further described in detail.

[0029] Figure 1 Shown is a top view of a field calibration device for a tensile and compressive load test system of a flight control simulator according to a preferred embodiment of the present invention; Figure 2 Shown is a schematic diagram of the fine-tuning mechanism in a preferred embodiment of the present invention.

[0030] See also Figure 1 , the on-site calibration device of the flight control simulator tension and compression load test system of this embodiment includes a structural frame, a loading mechanism 20, a standard measurement unit 30, a host computer 40 and a fine-tuning mechanism 50;

[0031] The loading mechanism 20, the standard measuring unit 30 and the calibrated force sensor 60 are sequentially connected and installed on the structural frame;

[0032] The fine-tuning mechanism 50 supports the loading mechanism 20, and makes the loading mechanism 20, the standard measuring unit 30 and the calibrated force sensor 60 be in the same straight line by fine-tuning the position of the loading mechanism 20;

[0033] The standard measurement unit 30 is wirelessly connected to the host computer 40 ; the calibrated force sensor 60 is connected to the flight control simulator 70 .

[0034] The structural frame is used to install and fix the loading mechanism, the standard measuring unit and the calibrated force sensor; the standard measuring unit includes a standard force sensor, and the loading mechanism applies force to the standard force sensor and the calibrated force sensor through force transmission; the fine-tuning mechanism ensures that the loading mechanism, the standard measuring unit and the calibrated force sensor are on the same straight line, so that the force is transmitted in a straight line, ensuring that the force measured by the standard force sensor is the same as the force measured by the calibrated force sensor; the force measured by the calibrated force sensor is displayed by the flight control simulator, and the force measured by the standard force sensor is displayed by the host computer, and the measurement results of the standard force sensor and the calibrated force sensor are compared to achieve the calibration of the calibrated force sensor.

[0035] Continue to see Figure 1 The structural frame includes a base 11, a rudder support 12 and a movable end cross 13; the movable end cross 13 is placed at one end of the base 11, can be moved on one end of the base 11, and is fixedly connected to the base 11 after being moved into position; a rudder support 12 is respectively provided on the other end of the base 11 and the movable end cross 13; the loading mechanism 20, the standard measuring unit 30 and the calibrated force sensor 60 are connected in series in sequence, and the two ends are respectively connected to the two rudder supports 12.

[0036] Preferably, the rudder support 12 connected to the movable end cross 13 can be moved on the movable end cross 13, and then fixedly connected to the movable end cross 13 after being moved into position.

[0037] Preferably, two rows of threaded holes 111 are provided at one end of the base 11, and different threaded holes 111 in the same row have different distances from the rudder support 12 at the other end of the base 11. The two rows of threaded holes 111 are used to connect the two sides of the movable end crossbar 13 respectively, so as to realize the movement of the movable end crossbar 13 on the base 11, so as to adapt to the length of the series connection of the loading mechanism 20, the standard measurement unit 30 and the calibrated force sensor 60. Because different types of standard force sensors and calibrated force sensors have different sizes, the series connection lengths of the loading mechanism 20, the standard measurement unit 30 and the calibrated force sensor 60 are different, and the series combination of the loading mechanism 20, the standard measurement unit 30 and the calibrated force sensor 60 is installed between the other end of the base 11 and the movable end crossbar 13, as shown in FIG. Figure 1 shown.

[0038] Figure 3 The figure shows a schematic diagram of the structure of the movable end in a preferred embodiment of the present invention, wherein (a) is a side view, and (b) is an AA view in (a); Figure 4The figure shows a schematic structural diagram of a rudder support in a preferred embodiment of the present invention, wherein (a) is a side view and (b) is a top view.

[0039] See also Figure 3 The movable end is horizontally provided with two T-shaped slots 131 , and a T-shaped nut is placed in the T-shaped slot 131 , and the T-shaped nut can move in the T-shaped slot 131 .

[0040] See also Figure 4 and Figure 1 The rudder support includes a mounting plate 121, a U-shaped mounting seat 122 and a latch 123. The U-shaped mounting seat 122 is fixedly connected to a surface of the mounting plate 121, and the opening faces away from the surface; a latch hole 124 is provided on the U-shaped mounting seat 122; and threaded holes 125 are provided on both sides of the mounting plate 121.

[0041] The rudder support is connected to the T-nut in the movable end transverse T-slot 131 through the threaded hole 125 of the mounting plate 121 and the screw. After tightening the screw, the T-nut is fastened on the movable end transversely, that is, the position of the T-nut is fixed, and the installation position of the rudder support is fixed. By moving the T-nut, the position of the T-nut on the movable end transversely can be changed, that is, the position of the rudder support on the movable end transversely can be changed.

[0042] The latch hole 124 and the latch 123 on the U-shaped mounting seat 122 are used to mount the loading mechanism 20 or the calibrated force sensor 60 .

[0043] The standard measurement unit 30 includes a standard force sensor, a charge amplifier and a wireless measurement and control device; the standard force sensor converts the standard force information into a corresponding charge output, which is conditioned and amplified by the charge amplifier and converted into a voltage and subjected to A / D conversion, and then transmitted to the host computer 40 by the wireless measurement and control device in a wireless transmission manner. The use of wireless transmission avoids the restrictive problems caused by wiring during on-site calibration.

[0044] The loading mechanism adopts electro-hydraulic servo control technology, with servo oil source and actuator as power source and actuator, digital computer as load control and data processing center, equipped with data acquisition, displacement sensor and force sensor excitation module and safety protection module. The servo oil source is responsible for providing pressure oil for the system; the substation has the functions of pressure display, pressure reduction and oil circuit disconnection; the protection module is installed with servo valve and safety control element; the actuator is installed with built-in displacement sensor and built-in force sensor; the upper computer is responsible for human-machine interaction and data display processing.

[0045] See also Figure 2The fine-tuning mechanism is a mechanical mechanism based on the lifting and lowering transmission of the worm gear and the screw screw, which realizes the lifting and lowering fine-tuning of the entire loading mechanism, the standard force sensor and the calibrated force sensor in series, ensuring that the force angle error is less than 1°. This structure has a large transmission ratio, stable operation, low noise, self-locking reverse stroke, and can easily stay at any position.

[0046] Although the preferred embodiments of the present invention have been disclosed as above, they are not intended to limit the present invention. Any technical personnel in this field can make possible changes and modifications to the technical solutions of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments by the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. On-site calibration device for the tensile and compressive load test system of a flight control simulator, characterized in that: It includes a structural frame, a loading mechanism, a standard measuring unit, a host computer and a fine-tuning mechanism; The loading mechanism, the standard measuring unit and the calibrated force sensor are sequentially connected and installed on the structural frame; The fine-tuning mechanism supports the loading mechanism, and the loading mechanism, the standard measuring unit and the calibrated force sensor are placed in the same straight line by fine-tuning the position of the loading mechanism; The standard measurement unit is wirelessly connected to the host computer; the calibrated force sensor is connected to the flight control simulator; The structural frame comprises a base, a rudder support and a movable end; the movable end is disposed horizontally at one end of the base, can move on the one end of the base, and is fixedly connected to the base after being moved into position; a rudder support is disposed on each of the other end of the base and the movable end; the loading mechanism, the standard measuring unit and the calibrated force sensor are connected in series in sequence, and the two ends are connected to the two rudder supports respectively; The rudder support connected to the movable end transversely can move in the movable end transversely, and then be fixedly connected to the movable end transversely after being moved into position; Two rows of threaded holes are arranged at one end of the base, and different threaded holes in the same row have different distances from the rudder support at the other end of the base, and the two rows of threaded holes are used to connect the two lateral sides of the movable end respectively; The movable end is provided with two T-shaped slots horizontally, and T-shaped nuts are placed in the T-shaped slots. The T-shaped nuts can move in the T-shaped slots, and the rudder support is connected to the T-shaped nuts by screws; The rudder support comprises a mounting plate, a U-shaped mounting seat and a latch, wherein the U-shaped mounting seat is fixedly connected to a surface of the mounting plate, and the opening faces away from the surface; a latch hole is provided on the U-shaped mounting seat; and threaded holes are provided on both sides of the mounting plate; The fine-tuning mechanism is a mechanical mechanism based on the lifting and lowering transmission of a worm gear and a screw screw, which realizes the lifting and lowering fine-tuning of the entire series combination of a loading mechanism, a standard force sensor and a calibrated force sensor, ensuring that the force application angle error is less than 1°.

2. The on-site calibration device for the tensile and compressive load test system of a flight control simulator according to claim 1, characterized in that: The standard measurement unit includes a standard force sensor, a charge amplifier and a wireless measurement and control device; the standard force sensor converts the standard force information into a corresponding charge output, the output is conditioned and amplified by the charge amplifier to be converted into a voltage and subjected to A / D conversion, and then transmitted to the host computer by wireless transmission through the wireless measurement and control device.

3. The on-site calibration device for the tensile and compressive load test system of a flight control simulator according to claim 1, characterized in that: The loading mechanism adopts electro-hydraulic servo control technology, with servo oil source and actuator as power source and actuator, and digital computer as load control and data processing center.

Images