Experimental device for simulating steering of airplane

Abstract

The utility model provides an experimental device for simulating aircraft steering, and relates to the field of aircraft steering detection devices. The experimental device comprises a base, a first cross beam and two second cross beams, the base comprises a vertical shaft, and the first cross beam is rotatably arranged on the vertical shaft around the axis of the vertical shaft; the two second cross beams are symmetrically arranged on the first cross beam with the vertical shaft as the center and are perpendicular to the first cross beam and the vertical shaft. The two second cross beams are provided with laser radar installation positions, and when the vertical shaft corresponds to the center position of the contact point of the front wheels of the tractor carrying aircraft, the two laser radar installation positions correspond to the installation positions of the two laser radars at the tail of the tractor one to one. In use, the two laser radars are installed on the two second cross beams respectively; the rotation process of the airplane relative to the tractor can be simulated only by rotating the first cross beam in situ without moving the airplane model, so that the detection research experiment process of the steering angle of the airplane is greatly simplified, and the space required by an experiment site is also greatly saved.

Description

Technical Field

[0001] The utility model relates to the technical field of an aircraft steering detection device, in particular to an experimental device for simulating aircraft steering. Background Art

[0002] Aircraft tractors are vehicles used to tow or push aircraft. They are essential ground support equipment for modern airports. They are divided into two types: with-bar and without-bar. The without-bar tractor has been rapidly developed due to its convenience and speed, and has become the main way of aircraft towing. However, since the without-bar tractor does not have the shear pin on the towing bar, if oversteering occurs, it is likely to cause direct damage to the structure and hydraulic system of the front landing gear. Therefore, it is necessary to consider configuring an effective oversteering protection device.

[0003] In the prior art, the protection method for over-steering of aircraft includes torque limitation, which is achieved by installing force sensors on the clamping devices in front and behind the wheels, and calculating the torque applied to the front landing gear based on the measurement value of the force sensor. However, many aircraft landing gears do not have torque limits, but only angle limits. Therefore, in other contact detection methods, the aircraft angle is measured by installing angle sensors at specific positions on the aircraft, which has low accuracy and complex installation. Therefore, more and more people use non-contact angle detection to detect the yaw angle of the aircraft relative to the tractor, thereby limiting its maximum deflection angle and achieving over-steering monitoring protection.

[0004] However, in actual situations, both the tractor and the aircraft are very large and heavy, which brings great inconvenience to the experimental verification process of the non-contact angle detection over-steering protection scheme. In addition, the tractor needs to pull the aircraft forward and constantly change the angle, which requires a large experimental site space to complete. Utility Model Content

[0005] The utility model aims to provide an experimental device for simulating the turning of an aircraft, so as to solve the technical problems existing in the prior art that it is very inconvenient to detect the turning angle of the aircraft and a large experimental site is required.

[0006] The utility model provides an experimental device for simulating aircraft steering, comprising a base, a first crossbeam and two second crossbeams, wherein the base comprises a vertical shaft, the first crossbeam is rotatably arranged on the vertical shaft around the axis of the vertical shaft; the two second crossbeams are symmetrically arranged on the first crossbeam with the vertical shaft as the center, and the second crossbeams are perpendicular to the first crossbeam and the vertical shaft; the two second crossbeams are both provided with laser radar installation positions, and when the vertical shaft is matched with the center position of the contact point of the front wheels of the tractor carrying the aircraft, the two laser radar installation positions correspond one by one to the installation positions of the two laser radars at the rear of the tractor.

[0007] Further, along the extension direction of the first crossbeam, the position of the second crossbeam is adjustable; and / or, along the extension direction of the second crossbeam, the position of the second crossbeam is adjustable.

[0008] Furthermore, the experimental device further comprises a connecting frame, and the first crossbeam and the second crossbeam are connected by the connecting frame;

[0009] The connecting frame is provided with a first through slot, through which the connecting frame can be slidably mounted outside the first cross beam, and the relative positions of the connecting frame and the first cross beam can be fixed; and / or, the connecting frame is provided with a second through slot, in which the second cross beam can be slidably inserted, and the relative positions of the second cross beam and the connecting frame can be fixed.

[0010] Furthermore, the first crossbeam is provided with a socket, the socket matches the vertical shaft, and the first crossbeam is rotatably mounted on the vertical shaft through the socket.

[0011] Furthermore, the experimental device also includes a plurality of bushings, which match the vertical shaft, are sleeved outside the vertical shaft and are arranged in sequence along the axial direction of the vertical shaft; and the first crossbeam is supported above the bushings.

[0012] Furthermore, the cross section of the first beam is rectangular.

[0013] Furthermore, the second cross beam is a rectangular tube.

[0014] Furthermore, a radar bracket is provided at one end of the second crossbeam, and the laser radar installation position is set on the radar bracket.

[0015] Furthermore, the radar bracket includes a lower bracket and an upper bracket, the lower bracket is provided with a third through slot, and the lower bracket is fixedly sleeved outside the second cross beam through the third through slot; the upper bracket is fixedly connected to the lower bracket, and the upper surface of the upper bracket forms the laser radar installation position.

[0016] Furthermore, the base also includes a chassis, and the vertical shaft is fixedly connected to the chassis; the chassis body is provided with scales along the circumferential direction, and the scales are used to indicate the relative rotation angle between the aircraft and the aircraft tractor.

[0017] Furthermore, the first crossbeam is also provided with a hanging ear, the hanging ear is provided with a hanging hole, the hanging hole is used to hang a pointer, and the pointer is used to indicate a scale.

[0018] The experimental device for simulating aircraft steering provided by the utility model can produce the following beneficial effects:

[0019] The experimental device for simulating aircraft steering provided by the utility model, when in use, two laser radars for monitoring aircraft steering that need to be installed on the aircraft tractor during field detection are respectively installed at the laser radar installation positions on the two second beams; by rotating the first beam, the aircraft model and the first beam can be made to rotate relative to each other, that is, only the first beam needs to be rotated in situ without moving the aircraft model, so as to simulate the rotation process of the aircraft relative to the tractor, which greatly simplifies the experimental process of detecting and studying the steering angle of the aircraft when the aircraft tractor is pulling the aircraft forward, and also greatly saves the space required for the experimental site. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings in the following description are only embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0021] Figure 1 A schematic diagram of the structure of an experimental device provided in an embodiment of the utility model;

[0022] Figure 2 One of the structural schematic diagrams of the chassis of the experimental device provided in the embodiment of the utility model;

[0023] Figure 3 A second structural schematic diagram of a chassis of an experimental device provided in an embodiment of the utility model;

[0024] Figure 4 A schematic diagram of the structure of the vertical axis of the experimental device provided by the embodiment of the utility model;

[0025] Figure 5 A schematic diagram of the structure of a shaft sleeve of an experimental device provided by an embodiment of the utility model;

[0026] Figure 6 A schematic diagram of the structure of a first crossbeam of an experimental device provided in an embodiment of the utility model;

[0027] Figure 7 A schematic diagram of the structure of a connecting frame of an experimental device provided by an embodiment of the utility model;

[0028] Figure 8 A schematic diagram of the structure of a second crossbeam of an experimental device provided in an embodiment of the utility model;

[0029] Fig. 9 A schematic diagram of the structure of an upper bracket of an experimental device provided in an embodiment of the utility model;

[0030] Fig.10 A schematic structural diagram of a lower bracket of an experimental device provided in an embodiment of the utility model.

[0031] Description of reference numerals:

[0032] 100-base; 110-chassis; 111-disk body; 112-insertion tube; 120-vertical shaft;

[0033] 200-sleeve;

[0034] 300-first crossbeam; 310-jack; 320-hanging ear; 321-hanging hole;

[0035] 400-connecting frame; 410-first through slot; 420-second through slot;

[0036] 500 - second beam;

[0037] 600- radar bracket; 610- lower bracket; 611- third through slot; 620- upper bracket; 621- installation plane. DETAILED DESCRIPTION

[0038] In order to make the above-mentioned purposes, features and advantages of the utility model more obvious and easy to understand, the specific embodiments of the utility model are described in detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described here are only used to explain the utility model and are not used to limit the utility model.

[0039] This embodiment provides an experimental device for simulating aircraft steering, such as Figure 1 As shown, the experimental device includes a base 100, a first crossbeam 300 and two second crossbeams 500, the base 100 includes a vertical shaft 120, the first crossbeam 300 is rotatably arranged on the vertical shaft 120 around the axis of the vertical shaft 120; the two second crossbeams 500 are symmetrically arranged on the first crossbeam 300 with the vertical shaft 120 as the center, and the second crossbeams 500 are perpendicular to the first crossbeam 300 and the vertical shaft 120; the two second crossbeams 500 are both provided with laser radar installation positions, and when the vertical shaft 120 is matched with the center position of the contact point of the front wheel of the tractor carrying the aircraft, the two laser radar installation positions correspond one by one to the installation positions of the two laser radars at the rear of the tractor.

[0040] The experimental device for simulating aircraft turning provided in this embodiment, when in use, two laser radars for monitoring aircraft turning that need to be installed on the aircraft tractor during field detection are respectively installed at the laser radar installation positions on the two second beams 500; by rotating the first beam 300, the aircraft model and the first beam 300 can be made to rotate relative to each other, that is, only the first beam 300 needs to be rotated in situ without moving the aircraft model, so as to simulate the rotation process of the aircraft relative to the tractor, which greatly simplifies the experimental process of detecting and studying the steering angle of the aircraft when the aircraft tractor is pulling the aircraft forward, and also greatly saves the space required for the experimental site.

[0041] Specifically, in this embodiment, the position of the second cross beam 500 is adjustable along the extension direction of the first cross beam 300. In this configuration, the spacing between the two second cross beams 500 can be adjusted, so as to simulate tractors with different rear widths.

[0042] In this embodiment, the position of the second cross beam 500 can also be adjusted along the extension direction of the second cross beam 500. In this arrangement, the length of the two second cross beams 500 close to the side of the aircraft model can be adjusted, so as to simulate tractors with different tail lengths.

[0043] More specifically, in this embodiment, if Figure 1 and Figure 7 As shown, the experimental device also includes a connecting frame 400, through which the first beam 300 and the second beam 500 are connected; the connecting frame 400 is provided with a first through slot 410, through which the connecting frame 400 can be slidably sleeved on the outside of the first beam 300, and the relative positions of the connecting frame 400 and the first beam 300 can be fixed; the connecting frame 400 is provided with a second through slot 420, in which the second beam 500 can be slidably inserted, and the relative positions of the second beam 500 and the connecting frame 400 can be fixed. Further, the groove wall of the first through slot 410 and the groove wall of the second through slot 420 of the connecting frame 400 can be provided with threaded holes, so that when the second beam 500 is slidably adjusted to the target position, the relative positions of the connecting frame 400 and the first beam 300 and the relative positions of the connecting frame 400 and the second beam 500 can be fixed by tightening screws respectively. In addition, the present embodiment is configured in such a way that the experimental device can be disassembled and assembled, so it is convenient to move.

[0044] Specifically, in this embodiment, Figure 1 and Figure 6As shown, the first crossbeam 300 is provided with a socket 310, the socket 310 matches the vertical shaft 120, and the first crossbeam 300 is rotatably mounted on the vertical shaft 120 through the socket 310. Further, in this embodiment, the socket 310 is a through hole, so that the position of the first crossbeam 300 is adjustable along the axial direction of the vertical shaft 120. In this way, the height of the first crossbeam 300 can match the tail height of the aircraft tractor, so that tractors with different tail heights can be simulated.

[0045] Specifically, in this embodiment, Figure 1 and Figure 5 As shown, the experimental device also includes a plurality of sleeves 200, which match the vertical shaft 120, are sleeved outside the vertical shaft 120 and are arranged in sequence along the axial direction of the vertical shaft 120; the first crossbeam 300 is supported on the sleeve 200. In this arrangement, different numbers of sleeves 200 are arranged outside the vertical shaft 120, so that the first crossbeam 300 can be supported at different heights, so that the height of the laser radar installation position corresponds to the height when it is installed at the rear of the tractor, which is very convenient. Of course, in other embodiments of the present application, the first crossbeam 300 can also be fixed at the desired height position by fixing parts such as set screws.

[0046] Specifically, in this embodiment, Figure 1 and Figure 7 As shown, the cross section of the first cross beam 300 is rectangular, and accordingly, the cross section of the first through slot 410 of the connecting frame 400 is also rectangular. In this arrangement, the connecting frame 400 is not easy to rotate around the first cross beam 300, and the contact surfaces of the first cross beam 300 and the connecting frame 400 are both flat, which is convenient for fixing the relative positions of the two with screws.

[0047] Specifically, in this embodiment, Figure 1 , Figure 7 and Figure 8 As shown, the second crossbeam 500 is a rectangular tube. Under this setting form, the cross section of the second crossbeam 500 is rectangular, and accordingly, the cross section of the second through slot 420 of the connecting frame 400 is also rectangular, and the second crossbeam 500 is not easy to rotate; moreover, the contact surfaces of the second crossbeam 500 and the connecting frame 400 are both flat, which is convenient for fixing the relative positions of the two with screws. In addition, the second crossbeam 500 is tubular and has a hollow structure, so the overall weight is relatively light, which can reduce the weight of the entire experimental device; moreover, due to its light weight, when the position of the second crossbeam 500 is adjusted along the axial direction to the lengths of the two sides of the first crossbeam 300 are unequal, the entire experimental device is not easy to tip over to the longer side of the second crossbeam 500, and the stability of the entire experimental device is relatively good.

[0048] Specifically, in this embodiment, Figure 1As shown, a radar bracket 600 is provided at one end of the second crossbeam 500 . The radar bracket 600 has a mounting plane 621 , forming a laser radar mounting position. The solid-state laser radar is mounted on the mounting plane 621 of the radar bracket 600 .

[0049] More specifically, in this embodiment, if Figure 1 , Fig. 9 and Fig.10 As shown, the radar bracket 600 includes a lower bracket 610 and an upper bracket 620. The lower bracket 610 is provided with a third through slot 611. The lower bracket 610 is fixedly sleeved outside the second crossbeam 500 through the third through slot 611. The upper bracket 620 is fixedly connected to the lower bracket 610, and the upper surface of the upper bracket 620 forms a mounting plane 621. Furthermore, since the second crossbeam 500 is a rectangular tube, the cross section of the third through slot 611 of the lower bracket 610 is also rectangular, so that the radar bracket 600 and the radar thereon are not easy to rotate relative to the second crossbeam 500.

[0050] Furthermore, a threaded hole is provided on the groove wall of the third through groove 611 of the lower bracket 610 , so that after the lower bracket 610 is sleeved on the second cross beam 500 , the lower bracket 610 and the second cross beam 500 can be fixed by a set screw.

[0051] Specifically, in this embodiment, the base 100 further includes a chassis 110, and the vertical shaft 120 is fixedly connected to the chassis 110; the disc body 111 of the chassis 110 is provided with scales along the circumferential direction, and the scales are used to indicate the relative rotation angles of the aircraft and the aircraft tractor. In this way, the relative deflection angles of the aircraft model and the experimental device can be observed more quickly and intuitively. More specifically, the scales can be pasted on the upper surface of the disc body 111, or the scales can be directly engraved on the upper surface of the disc body 111.

[0052] More specifically, in this embodiment, if Figures 1 to 4 As shown, the chassis 110 also includes an insertion tube 112, which is vertically fixed to the disk body 111, for example, by welding; the vertical shaft 120 is inserted into the insertion tube 112. Further, the bottom of the disk body 111 and the insertion tube 112 are provided with connecting fixing holes, and the end surface of the vertical shaft 120 is provided with a threaded hole, and the screw is fixed to the threaded hole of the vertical shaft 120 after passing through the fixing hole of the chassis 110, that is, after the vertical shaft 120 is inserted into the insertion tube 112, it is also fastened by the screw, so that the connection reliability of the vertical shaft 120 and the chassis 110 is higher. Furthermore, the bottom of the disk body 111 can be provided with a receiving groove for accommodating the fastening screw.

[0053] Preferably, in this embodiment, the disk body 111 of the chassis 110 is a circular disk, and the cannula 112 is arranged at the center of the disk body 111. Such an arrangement is conducive to maintaining the stability of the entire experimental device. Of course, in other embodiments of the present application, the disk body 111 is not limited to a circular disk, but can also be a square disk, etc.

[0054] Specifically, in this embodiment, the disk body 111 is further provided with three non-collinear threaded holes, and preferably, the three threaded holes are evenly arranged along the circumferential direction of the disk body 111. In this way, an adjustment screw can be installed in the threaded hole from the bottom of the disk body 111, so that the levelness of the chassis 110 and the entire experimental device can be adjusted by screwing the adjustment screw.

[0055] Specifically, in this embodiment, Figure 6 As shown, the first crossbeam 300 is also provided with a hanging ear 320, and the hanging ear 320 is provided with a hanging hole 321, and the hanging hole 321 is used to hang a pointer, and the pointer is used to indicate the scale. Preferably, in this embodiment, the first crossbeam 300 is centrally arranged on the vertical axis 120, and the hanging ear 320 is centrally arranged on the first crossbeam 300. In this way, along the extension direction of the first crossbeam 300, the first crossbeam 300 is not easy to tilt to one side, and the entire experimental device is more stable.

[0056] Finally, it should be noted that, in this article, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprises" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device that includes a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0057] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. Various modifications to the embodiments will be apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but will conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An experimental device for simulating aircraft turning, It is characterized in that The invention comprises a base (100), a first crossbeam (300) and two second crossbeams (500), wherein the base (100) comprises a vertical shaft (120), the first crossbeam (300) is rotatably arranged on the vertical shaft (120) around the axis of the vertical shaft (120); the two second crossbeams (500) are symmetrically arranged on the first crossbeam (300) with the vertical shaft (120) as the center, and the second crossbeams (500) are perpendicular to the first crossbeam (300) and the vertical shaft (120); the two second crossbeams (500) are both provided with laser radar installation positions, and when the vertical shaft (120) is matched with the center position of the contact point of the front wheel of the tractor carrying the aircraft, the two laser radar installation positions correspond one by one to the installation positions of the two laser radars at the rear of the tractor.

2. The experimental device for simulating aircraft turning according to claim 1, It is characterized in that Along the extension direction of the first crossbeam (300), the position of the second crossbeam (500) is adjustable; And / or, along the extension direction of the second crossbeam (500), the position of the second crossbeam (500) is adjustable.

3. The experimental device for simulating aircraft turning according to claim 2, It is characterized in that The experimental device further comprises a connecting frame (400), and the first crossbeam (300) and the second crossbeam (500) are connected via the connecting frame (400); The connecting frame (400) is provided with a first through slot (410), and the connecting frame (400) can be slidably mounted outside the first crossbeam (300) through the first through slot (410), and the relative positions of the connecting frame (400) and the first crossbeam (300) can be fixed; and / or, the connecting frame (400) is provided with a second through slot (420), and the second crossbeam (500) can be slidably inserted into the second through slot (420), and the relative positions of the second crossbeam (500) and the connecting frame (400) can be fixed.

4. The experimental device for simulating aircraft turning according to claim 1, It is characterized in that The first crossbeam (300) is provided with a socket (310), the socket (310) matches the vertical shaft (120), and the first crossbeam (300) is rotatably mounted on the vertical shaft (120) through the socket (310).

5. The experimental device for simulating aircraft turning according to claim 4, It is characterized in that The experimental device further comprises a plurality of shaft sleeves (200), wherein the shaft sleeves (200) match the vertical shaft (120), are sleeved outside the vertical shaft (120) and are arranged in sequence along the axial direction of the vertical shaft (120); and the first crossbeam (300) is supported above the shaft sleeves (200).

6. The experimental device for simulating aircraft turning according to claim 1, It is characterized in that The cross section of the first crossbeam (300) is rectangular; And / or, the second crossbeam (500) is a rectangular tube.

7. The experimental device for simulating aircraft turning according to claim 6, It is characterized in that A radar bracket (600) is provided at one end of the second crossbeam (500), and the laser radar installation position is arranged on the radar bracket (600).

8. The experimental device for simulating aircraft turning according to claim 7, It is characterized in that The radar bracket (600) comprises a lower bracket (610) and an upper bracket (620), wherein the lower bracket (610) is provided with a third through slot (611), and the lower bracket (610) is fixedly sleeved outside the second crossbeam (500) through the third through slot (611); the upper bracket (620) is fixedly connected to the lower bracket (610), and the upper surface of the upper bracket (620) forms the laser radar installation position.

9. The experimental device for simulating aircraft turning according to claim 1, It is characterized in that The base (100) further comprises a chassis (110), and the vertical shaft (120) is fixedly connected to the chassis (110); a plate body (111) of the chassis (110) is provided with scales along a circumferential direction, and the scales are used to indicate the relative rotation angle between the aircraft and the aircraft tractor.

10. The experimental device for simulating aircraft turning according to claim 9, It is characterized in that The first crossbeam (300) is further provided with a hanging ear (320), and the hanging ear (320) is provided with a hanging hole (321), and the hanging hole (321) is used to hang a pointer, and the pointer is used to indicate a scale.

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