Testing equipment for front undercarriage of training aircraft

Abstract

The invention relates to the technical field of aircraft landing gear testing, in particular to training aircraft nose landing gear testing equipment which comprises a base and a nose landing gear body, a portal frame is fixedly arranged at the top end of the base, a movable frame is movably connected to the outer surface of the portal frame, and a transverse rod is fixedly arranged on the inner side wall of the movable frame. Two clamping assemblies are symmetrically arranged on the outer surface of the transverse rod, and each clamping assembly comprises a clamping plate connected to the outer surface of the transverse rod in a sliding mode. Through the base, the portal frame, the nose landing gear body, the movable frame, the cross rod, the clamping assembly, the rotating table, a first mounting base, a first rotating support and a second rotating support, the clamping assembly comprises two clamping plates slidably connected to the outer surface of the cross rod, and the two second rotating shafts can be sequentially inserted into rotating grooves by moving the clamping plates; the first rotating support and the second rotating support are conveniently matched with the first rotating shafts with different heights through bending deformation, the first servo motor is started to drive the first rotating shafts to rotate, and therefore the testing and installing efficiency is improved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft landing gear testing, in particular to a front landing gear testing device for a training aircraft. Background Art

[0002] A trainer aircraft is an aircraft specifically used to train pilots, usually designed for basic flight training and the cultivation of advanced flying skills. Trainer aircraft usually have better maneuverability so that novice pilots can learn flight operations more easily. The front landing gear of a trainer aircraft is an important component that supports the aircraft for takeoff and landing. The front landing gear is usually located at the nose or nose of the aircraft. The main functions of the front landing gear include: supporting the weight of the aircraft, ground steering control, and landing impact energy absorption. The front landing gear of a trainer aircraft usually includes a main structure, tires, a vibration reduction system, and a steering system. The front landing gear of a trainer aircraft needs to be subjected to a steering test during the production process.

[0003] The patent document with the announcement number CN117944916A in my country discloses an adaptive semi-retractable front landing gear system for unmanned trainer aircraft, including an adaptive semi-retractable mechanism, the adaptive semi-retractable mechanism includes a front wheel fork, a front start pillar, a limit rod, a sliding sleeve and a linear drive; the front start pillar is installed on the body structure of the unmanned aircraft and can rotate axially; the middle part of the front wheel fork is rotatably installed at the lower end of the front start pillar; the sliding sleeve is arranged outside the front start pillar; one end of the limit rod is rotatably connected to the sliding sleeve, and the other end is rotatably connected to the outer side of the upper end of the front wheel fork; there is a limit platform on the inner side of the upper end of the front wheel fork, the limit platform is located between the front start pillar and the limit rod and points to the inner side of the limit rod; the linear drive is installed on the front start pillar and connected to the sliding sleeve. The invention is unique and innovative, simple and reliable, and achieves integrated and multifunctional comprehensive utilization. It can be used for unmanned trainer aircraft front landing gear retraction and extension fault simulation training, and can also be used for fixed-wing unmanned aircraft as a front landing gear that can adaptively adjust and control the angle of attack of the unmanned aircraft.

[0004] The existing front landing gear of trainer aircraft has differences in appearance and main structure dimensions, which makes the installation and positioning of the front landing gear time-consuming and laborious during the steering test, thus affecting the efficiency of the steering test. Summary of the invention

[0005] Based on this, it is necessary to provide a training aircraft front landing gear test equipment to address the existing technical problems.

[0006] In order to solve the problems of the prior art, the technical solution adopted by the present invention is:

[0007] A training aircraft front landing gear test equipment, comprising a base and a front landing gear body, a gantry is fixedly arranged on the top of the base, a movable frame is movably connected to the outer surface of the gantry, a cross bar is fixedly arranged on the inner side wall of the movable frame, two clamping assemblies are symmetrically arranged on the outer surface of the cross bar, the clamping assemblies each comprise a clamping plate slidably connected to the outer surface of the cross bar, a clamping block is fixedly arranged at the end of the clamping plate, a rotating groove is provided on the side wall of the clamping block, the front landing gear body comprises a connecting tube, a rotating shaft 1 is inserted in the middle of the connecting tube, a groove is provided at the top of the rotating shaft 1, a connecting rod 1 is fixedly arranged on the inner side wall of the groove, two wing plates are symmetrically fixedly arranged on the side wall of the connecting tube, and the ends of the wing plates are A rotating shaft 2 is fixedly provided, and the rotating shaft 2 is sequentially inserted into the interior of the rotating groove, the bottom end of the rotating shaft 1 passes through a connecting tube and is fixedly provided with a connecting seat, the bottom end of the connecting seat is fixedly provided with a telescopic rod, the bottom end of the telescopic rod is fixedly provided with a connecting block, and two tires are symmetrically rotatably connected to the side wall of the connecting block, a top plate is fixedly provided at the top of the gantry, and the top plate is in a convex shape, a servo motor 1 is fixedly provided on the surface of the top plate, and the output end of the servo motor 1 passes through the top plate and is fixedly provided with a rotating table, the bottom end of the rotating table is rotatably connected to a mounting seat 1, the bottom end of the mounting seat 1 is rotatably connected to a rotating bracket 1, the bottom end of the rotating bracket 1 is rotatably connected to a rotating bracket 2, and the bottom end of the rotating bracket 2 is rotatably connected to the outer surface of the connecting rod 1.

[0008] Furthermore, a mounting groove is provided in the middle of the connecting tube for the rotating shaft 1 to be plugged in, the outer dimensions of the rotating shaft 1 are matched with the inner dimensions of the mounting groove, a connecting rod 2 is fixedly provided on the side wall of the connecting tube, a spring is wound around the outer surface of the telescopic rod, and both ends of the spring are fixedly connected to the bottom end of the connecting seat and the bottom end of the connecting block in sequence to facilitate the rotation of the rotating shaft 1.

[0009] Furthermore, the outer surface of the connecting tube close to the lower part of the connecting rod 2 is rotatably connected to a sleeve, and the outer surface of the connecting tube close to the sleeve is sleeved with two limiting rings, a buffer bracket 1 is rotatably connected to the side wall of the sleeve, and the bottom end of the buffer bracket 1 is rotatably connected to the buffer bracket 2, and the bottom end of the buffer bracket 2 is rotatably connected to the side wall of the connecting block, thereby improving the rotation stability of the rotating shaft 1.

[0010] Furthermore, a bidirectional screw is rotatably connected to the inner side wall of the movable frame near the cross bar, and a screw slide is rotatably connected to the side wall of the clamping plate in turn. The screw slide is symmetrically threadedly connected to the outer surface of the bidirectional screw, and a slide groove 1 is provided on the side wall of the clamping plate near the screw slide for the cross bar to be plugged in. The outer dimensions of the cross bar are matched with the inner dimensions of the slide groove 1 in turn, thereby improving the stability of the clamping plates moving toward each other.

[0011] Furthermore, a servo motor 2 is fixedly mounted on the side wall of the movable frame, the output end of the servo motor 2 is fixedly mounted on the end of the bidirectional screw rod through a coupling, and a limit block is provided on the middle sleeve of the bidirectional screw rod, thereby improving the efficiency of the clamping plates moving toward each other.

[0012] Furthermore, the movable frame is rotatably connected to a mounting seat 2 near the bottom end of the connecting tube, the bottom end of the mounting seat 2 is rotatably connected to a hydraulic cylinder 2, the output end of the hydraulic cylinder 2 is provided with a connecting component 1, the connecting component 1 includes a mounting seat 3 fixed at the output end of the hydraulic cylinder 2, the bottom end of the mounting seat 3 is rotatably connected to a connecting head, the bottom end of the connecting head is rotatably connected to the outer surface of the connecting rod 2, thereby improving the stability of the connecting tube support.

[0013] Furthermore, two hydraulic cylinders 1 are symmetrically fixed on the surface of the top plate, and the output ends of the two hydraulic cylinders 1 are successively passed through the top plate and fixed on the top of the movable frame. The outer surface of the movable frame is symmetrically provided with two slide grooves 2, and the internal dimensions of the slide grooves 2 are successively adapted to the external dimensions of the gantry, thereby improving the convenience of adjusting the height of the movable frame.

[0014] Furthermore, a connecting component 2 is provided at the bottom end of the second rotating bracket, and the second connecting component includes a connecting head block rotatably connected to the bottom end of the second rotating bracket, a card groove 1 is provided at the bottom end of the second rotating bracket near the connecting head block, and a card groove 2 is provided on the side wall of the connecting head block, and the card groove 2 and the card groove 1 are both semicircular for the connection of the connecting rod 1, and a connecting plate is fixedly provided at the other end of the connecting head block, and a card groove 3 is provided on the side wall of the second rotating bracket for the connection of the connecting plate, and a thread groove 1 is provided on the side wall of the connecting plate, and a thread groove 2 is provided on the inner side wall of the card groove 3 near the thread groove 1, and the interiors of the thread groove 1 and the thread groove 2 are threadedly connected with threaded rods in sequence, which improves the convenience of connecting the second rotating bracket and the connecting rod 1.

[0015] A training aircraft front landing gear test device comprises the following steps:

[0016] S1: Installation of the connecting tube. The operator inserts the two rotating shafts into the rotating groove in sequence, starts the servo motor 2 to drive the bidirectional screw to rotate, thereby driving the screw slide to drive the two clamping blocks to move toward each other, thereby clamping the wing plate, and then starts the hydraulic cylinder 2 to adjust the distance between the connecting head and the connecting rod 2, so that the connecting head is sleeved on the outer surface of the connecting rod 2, and the connecting tube is supported by three points.

[0017] S2: To install the rotating bracket 2, the operator rotates the mounting base 1, the rotating bracket 1 and the rotating bracket 2 in sequence to adjust the distance between the bottom end of the rotating bracket 2 and the connecting rod 1, rotates the connecting head block to open the slot 1, and then passes the connecting head block and the connecting plate through the bottom end of the connecting rod 1 in sequence, and then rotates the connecting head block to make the connecting rod 1 snap into the inside of the slot 1 and the slot 2 in sequence, and thread the threaded rod into the inside of the thread groove 1 and the thread groove 2 in sequence.

[0018] S3: Turn and look sideways, start hydraulic cylinder 1 to drive the movable frame to slide vertically on the outer surface of the gantry, so as to adjust the height of the movable frame and the ground, so that the two tires are supported on the surface of the base to simulate the weight of the trainer fuselage, and then start servo motor 1 to drive the rotating table to rotate synchronously. When the rotating table rotates, it drives the mounting seat 1, rotating bracket 1, rotating bracket 2 and rotating shaft 1 to rotate in sequence, thereby driving the tires to rotate, so as to realize the steering test.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] First, a front landing gear test device for a training aircraft in the present invention comprises a base, a gantry, a front landing gear body, a movable frame, a cross bar, a clamping assembly, a rotating table, a mounting seat 1, a rotating bracket 1, and a rotating bracket 2. The clamping assembly comprises two clamping plates slidably connected to the outer surface of the cross bar. The movable clamping plates can sequentially insert two rotating shafts 2 into the inside of the rotating groove. The rotating bracket 1 and the rotating bracket 2 are conveniently adapted to the rotating shaft 1 of different heights by bending and deforming. The servo motor 1 is started to drive the rotating shaft 1 to rotate, thereby improving the efficiency of the test installation.

[0021] Secondly, a front landing gear test device for a training aircraft in the present invention can open the first clamping slot by rotating the connecting head block, so that the connecting head block and the connecting plate pass through the groove and then the connecting plate is rotated, so that the first connecting rod is clamped in the inside of the first clamping slot and the second clamping slot, thereby improving the convenience of connecting the second rotating bracket with the first connecting rod;

[0022] Thirdly, a front landing gear test device for a trainer aircraft in the present invention is provided with a bidirectional screw, a second servo motor, a limit block and a screw slide. Starting the second servo motor can drive the screw slide to slide toward each other on the outer surface of the bidirectional screw, thereby improving the convenience of adjusting the distance between the two clamping plates. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of the front three-dimensional structure of the present invention;

[0024] Figure 2 It is a side view stereoscopic structural schematic diagram of the present invention;

[0025] Figure 3 It is a schematic diagram of the front view of the three-dimensional structure of the movable frame of the present invention;

[0026] Figure 4 It is a schematic diagram of the main structure of the front landing gear of the present invention;

[0027] Figure 5 It is a schematic diagram of the three-dimensional structure of the main frame of the present invention from a side view;

[0028] Figure 6 It is a schematic diagram of the three-dimensional structure of the buffer bracket of the present invention from a side view;

[0029] Figure 7 It is a schematic diagram of the three-dimensional structure of the rotating bracket of the present invention from a side view;

[0030] Figure 8 It is a schematic diagram of the cross-sectional structure of the rotating bracket of the present invention in two views;

[0031] Fig. 9 It is a schematic diagram of the front three-dimensional structure of the clamping assembly of the present invention.

[0032] The numbers in the figure are: 1, base; 2, gantry; 3, front landing gear body; 301, connecting tube; 302, rotating shaft 1; 303, groove; 304, connecting rod 1; 305, wing plate; 306, rotating shaft 2; 307, connecting seat; 308, telescopic rod; 309, connecting block; 3010, tire; 3011, limiting ring; 3012, sleeve; 3013, spring; 3014, buffer bracket 1; 3015, buffer bracket 2; 3016, connecting rod 2; 3017, mounting groove; 4, movable frame; 5, cross bar; 6, clamping assembly; 601, clamping plate; 602, clamping block; 603, rotating groove; 604 , screw slide; 605, slideway one; 7, top plate; 8, servo motor one; 9, hydraulic cylinder one; 10, rotary table; 11, mounting seat one; 12, rotating bracket one; 13, rotating bracket two; 14, bidirectional screw; 15, servo motor two; 16, mounting seat two; 17, hydraulic cylinder two; 18, slideway two; 19, limit block; 20, connecting component one; 2001, mounting seat three; 2002, connector; 21, slot one; 22, connecting component two; 2201, connector block; 2202, slot two; 2203, connecting plate; 2204, threaded rod; 2205, thread groove one; 23, slot three; 24, thread groove two. DETAILED DESCRIPTION

[0033] In order to further understand the features, technical means, specific objectives and functions of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0034] refer to Figures 1 to 9A front landing gear test device for a trainer aircraft shown in the figure comprises a base 1 and a front landing gear body 3, a gantry 2 is fixedly arranged on the top of the base 1 by welding, the gantry 2 and the base 1 are both made of cast iron and are perpendicular to each other, a movable frame 4 is movably connected to the outer surface of the gantry 2 to support and limit, a cross bar 5 is fixedly arranged on the inner side wall of the movable frame 4 by welding, the cross bar 5 is made of stainless steel and is cylindrical, two clamping assemblies 6 are symmetrically arranged on the outer surface of the cross bar 5, the clamping assemblies 6 each comprise a clamping plate 601 slidably connected to the outer surface of the cross bar 5, a clamping block 602 is fixedly arranged at the end of the clamping plate 601 to form an integrated structure, a rotating groove 603 is opened on the side wall of the clamping block 602, and the front landing gear body 3 comprises a connecting tube 301, the connecting tube 30 1 is plugged with a rotating shaft 1 302 in the middle, a groove 303 is provided at the top of the rotating shaft 1 302, a connecting rod 1 304 is fixedly provided on the inner side wall of the groove 303 by welding, and the connecting rod 1 304 is cylindrical, and two wing plates 305 are symmetrically fixedly provided on the side wall of the connecting tube 301, and the ends of the wing plates 305 are fixedly provided with a rotating shaft 2 306 to form an integrated structure, and the rotating shaft 2 306 can drive the connecting tube 301 to rotate and be stored by rotating, and the rotating shaft 2 306 is sequentially plugged into the inside of the rotating groove 603, and the two clamping plates 601 are moved sequentially to improve the convenience of clamping and installing the two rotating shafts 2 306, so as to facilitate the adaptation of the front landing gear body 3 of different sizes, and the bottom end of the rotating shaft 1 302 passes through the connecting tube 301 and is fixedly provided with a connecting rod 304 by welding The bottom end of the connecting seat 307 is fixed with a telescopic rod 308, and the bottom end of the telescopic rod 308 is fixed with a connecting block 309. The side wall of the connecting block 309 is symmetrically connected to two tires 3010. The rotation of the rotating shaft 302 can drive the tires 3010 to rotate synchronously, thereby changing the rotation direction of the tires 3010. The top of the gantry 2 is fixed with a top plate 7 by welding. The top plate 7 is in a convex shape. The surface of the top plate 7 is fixed with a servo motor 8 by bolts. The output end of the servo motor 8 passes through the top plate 7 and is fixed with a rotating table 10 through a coupling. The bottom end of the rotating table 10 is rotatably connected to a mounting seat 11. The bottom end of the mounting seat 11 is rotatably connected to a rotating bracket 12. The bottom end of the rotating bracket 12 is rotatably connected to a rotating bracket 13, the bottom end of the rotating bracket 13 is provided with a connecting component 22, and the connecting component 22 includes a connecting head block 2201 rotatably connected to the bottom end of the rotating bracket 13, a card slot 21 is provided at the bottom end of the rotating bracket 13 near the connecting head block 2201, and a card slot 2202 is provided on the side wall of the connecting head block 2201. The card slot 2202 and the card slot 1 21 are both semicircular for the connection of the connecting rod 1 304, and a connecting plate 2203 is fixedly provided at the other end of the connecting head block 2201, and a card slot 3 23 is provided on the side wall of the rotating bracket 13 for the connection of the connecting plate 2203, and a thread groove 1 2205 is provided on the side wall of the connecting plate 2203, and a thread groove 24 is provided on the inner side wall of the card slot 3 23 near the thread groove 1 2205.The inside of the thread groove 1 2205 and the thread groove 24 are threadedly connected with the thread rod 2204 in sequence, which improves the convenience of connecting the rotating bracket 2 13 and the connecting rod 1 304.

[0035] The bottom end of the rotating bracket 13 is rotatably connected to the outer surface of the connecting rod 1 304. When the mounting seat 11, the rotating bracket 12 and the rotating bracket 13 are rotated, the distance between the bottom end of the rotating bracket 13 and the top end of the rotating shaft 1 302 can be adjusted, so as to facilitate the adaptation of the rotating shaft 1 302 of different heights. The servo motor 18 is started to drive the rotating table 10 to rotate synchronously. When the rotating table 10 rotates, the mounting seat 11, the rotating bracket 12, the rotating bracket 13 and the rotating shaft 1 302 are driven to rotate synchronously in turn, thereby driving the tire 3010 to rotate, so as to realize the steering test. During the rotation test, the rotating bracket 12 and the rotating bracket 13 can automatically adapt to the distance between the top end of the rotating shaft 302 and the rotating table 10 by rotating, thereby improving the convenience and efficiency of the test installation and positioning.

[0036] Furthermore, a mounting groove 3017 is provided in the middle of the connecting cylinder 301 for the rotating shaft 302 to be plugged in, the outer dimensions of the rotating shaft 302 are matched with the inner dimensions of the mounting groove 3017, a connecting rod 2 3016 is fixedly provided on the side wall of the connecting cylinder 301, a spring 3013 is wound around the outer surface of the telescopic rod 308, and both ends of the spring 3013 are fixedly connected to the bottom end of the connecting seat 307 and the bottom end of the connecting block 309 in turn, the compression deformation of the spring 3013 can buffer the transmission of the tire 3010 to the rotating shaft 302, and facilitate the vibration of the rotating shaft 302 and the connecting cylinder 301.

[0037] Furthermore, the outer surface of the connecting tube 301 close to the connecting rod 2 3016 is rotatably connected to the sleeve 3012, and the outer surface of the connecting tube 301 close to the sleeve 3012 is sleeved with two limiting rings 3011, and the side wall of the sleeve 3012 is rotatably connected to a buffer bracket 1 3014, and the bottom end of the buffer bracket 1 3014 is rotatably connected to a buffer bracket 2 3015. The buffer bracket 1 3014 and the buffer bracket 2 3015 can be compressibly deformed when rotating to further buffer the rotating shaft 1 302, and the bottom end of the buffer bracket 2 3015 is rotatably connected to the side wall of the connecting block 309, thereby improving the stability of the rotation and insertion of the rotating shaft 1 302.

[0038] Furthermore, the movable frame 4 is rotatably connected to the inner wall of the cross bar 5 with a bidirectional screw 14, and the side wall of the clamping plate 601 is in turn rotatably connected to a screw slide 604. The screw slide 604 is symmetrically threadedly connected to the outer surface of the bidirectional screw 14. The side wall of the clamping plate 601 near the screw slide 604 is provided with a slide groove 605 for the cross bar 5 to be plugged in. The external dimensions of the cross bar 5 are adapted to the internal dimensions of the slide groove 605 in turn, thereby improving the stability of the clamping plate 601 in moving toward each other.

[0039] Furthermore, a servo motor 2 15 is fixedly provided on the side wall of the movable frame 4, and the output end of the servo motor 2 15 is fixedly provided on the end of the bidirectional screw rod 14 through a coupling. The middle sleeve of the bidirectional screw rod 14 is provided with a limit block 19. Starting the servo motor 2 15 can drive the bidirectional screw rod 14 to rotate, thereby driving the screw rod slide 604 to move toward each other, thereby improving the efficiency of the clamping plate 601 moving toward each other.

[0040] Furthermore, the movable frame 4 is rotatably connected to a mounting seat 2 16 near the bottom end of the connecting tube 301, and the bottom end of the mounting seat 2 16 is rotatably connected to a hydraulic cylinder 2 17. A connecting component 1 20 is provided at the output end of the hydraulic cylinder 2 17. The connecting component 1 20 includes a mounting seat 3 2001 fixed to the output end of the hydraulic cylinder 2 17, and the bottom end of the mounting seat 3 2001 is rotatably connected to a connecting head 2002. The bottom end of the connecting head 2002 is rotatably connected to the outer surface of the connecting rod 2 3016. The structure of the connecting head 2002 is the same as that of the rotating bracket 2 13 and the connecting component 22, which improves the convenience of connecting 2022 with the connecting rod 2 3016, thereby realizing three-point support for the connecting tube 301 and improving the stability of the support of the connecting tube 301.

[0041] Furthermore, two hydraulic cylinders 9 are symmetrically fixed on the surface of the top plate 7, and the output ends of the two hydraulic cylinders 9 are successively passed through the top plate 7 and fixed on the top of the movable frame 4. The outer surface of the movable frame 4 is symmetrically provided with two slide grooves 18, and the internal dimensions of the slide grooves 18 are successively adapted to the external dimensions of the gantry 2, thereby improving the convenience of height adjustment of the movable frame 4.

[0042] A training aircraft front landing gear test device comprises the following steps:

[0043] S1: The connecting tube 301 is installed. The operator inserts the two rotating shafts 306 into the rotating groove 603 in sequence, starts the servo motor 15 to drive the bidirectional screw 14 to rotate, thereby driving the screw slide 604 to drive the two clamping blocks 602 to move toward each other, thereby clamping the wing plate 305, and then starts the hydraulic cylinder 17 to adjust the distance between the connecting head 2002 and the connecting rod 3016, so that the connecting head 2002 is sleeved on the outer surface of the connecting rod 3016, and the connecting tube 301 is supported by three points.

[0044] S2: The rotating bracket 13 is installed. The operator rotates the mounting base 11, the rotating bracket 12 and the rotating bracket 13 in sequence to adjust the distance between the bottom end of the rotating bracket 13 and the connecting rod 304, rotates the connecting head block 2201 to open the slot 21, and then passes the connecting head block 2201 and the connecting plate 2203 through the bottom end of the connecting rod 304 in sequence, and then rotates the connecting head block 2201 to make the connecting rod 304 be clamped in the inside of the slot 1 21 and the slot 2202 in sequence, and threadedly connects the threaded rod 2204 in the inside of the thread groove 1 2205 and the thread groove 24 in sequence.

[0045] S3: Turn and look sideways, start the hydraulic cylinder 19 to drive the movable frame 4 to slide vertically on the outer surface of the gantry 2, so as to adjust the height of the movable frame 4 and the ground, so that the two tires 3010 are supported on the surface of the base 1 to simulate the weight of the trainer fuselage, and then start the servo motor 18 to drive the rotating table 10 to rotate synchronously. When the rotating table 10 rotates, it drives the mounting seat 11, the rotating bracket 12, the rotating bracket 2 13 and the rotating shaft 1 302 to rotate in turn, thereby driving the tire 3010 to rotate, so as to realize the steering test. By observing the rotating shaft When the inspection is completed, the operator drives the hydraulic cylinder 19 in reverse to drive the movable frame 4 to move vertically. The operator first releases the connection between the rotating bracket 213 and the rotating shaft 302, and then releases the connection between the connecting head 2002 and the connecting rod 2 3016. Finally, the servo motor 215 is driven in reverse to make the bidirectional screw 14 rotate counterclockwise, thereby loosening the clamping block 602 from both ends of the rotating shaft 306 for easy removal and replacement 3.

[0046] The above embodiments only express one or several implementation modes of the present invention, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the present invention. It should be pointed out that, for a person of ordinary skill in the art, several modifications and improvements can be made without departing from the concept of the present invention, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention patent shall be subject to the attached claims.

Claims

1. A training aircraft nose landing gear test device, comprising a base (1) and a nose landing gear body (3), characterized in that: A gantry (2) is fixedly provided on the top of the base (1), a movable frame (4) is movably connected to the outer surface of the gantry (2), a cross bar (5) is fixedly provided on the inner side wall of the movable frame (4), two clamping assemblies (6) are symmetrically provided on the outer surface of the cross bar (5), each of the clamping assemblies (6) comprises a clamping plate (601) slidably connected to the outer surface of the cross bar (5), a clamping block (602) is fixedly provided at the end of the clamping plate (601), and a rotating groove (603) is provided on the side wall of the clamping block (602); The front landing gear body (3) comprises a connecting tube (301), a rotating shaft (302) is inserted in the middle of the connecting tube (301), a groove (303) is provided at the top end of the rotating shaft (302), a connecting rod (304) is fixedly provided on the inner side wall of the groove (303), two wing plates (305) are symmetrically fixedly provided on the side wall of the connecting tube (301), and the ends of the wing plates (305) are fixedly provided with rotating shaft (2). 306), the second rotating shaft (306) is sequentially inserted into the interior of the rotating groove (603), the bottom end of the first rotating shaft (302) passes through the connecting tube (301) and is fixedly provided with a connecting seat (307), the bottom end of the connecting seat (307) is fixedly provided with a telescopic rod (308), the bottom end of the telescopic rod (308) is fixedly provided with a connecting block (309), and the side wall of the connecting block (309) is symmetrically rotatably connected with two tires (3010); A top plate (7) is fixedly provided at the top of the gantry (2), and the top plate (7) is in a convex shape. A servo motor (8) is fixedly provided on the surface of the top plate (7). The output end of the servo motor (8) passes through the top plate (7) and is fixedly provided with a rotating platform (10). The bottom end of the rotating platform (10) is rotatably connected to a mounting seat (11). The bottom end of the mounting seat (11) is rotatably connected to a rotating bracket (12). The bottom end of the rotating bracket (12) is rotatably connected to a rotating bracket (13). The bottom end of the rotating bracket (13) is rotatably connected to the outer surface of a connecting rod (304).

2. A training aircraft front landing gear test equipment according to claim 1, characterized in that: A mounting groove (3017) is provided in the middle of the connecting tube (301) for the rotation shaft 1 (302) to be plugged in, and the outer dimensions of the rotation shaft 1 (302) are matched with the inner dimensions of the mounting groove (3017). A connecting rod 2 (3016) is fixedly provided on the side wall of the connecting tube (301), and a spring (3013) is wound around the outer surface of the telescopic rod (308), and the two ends of the spring (3013) are fixedly connected to the bottom end of the connecting seat (307) and the bottom end of the connecting block (309) in sequence.

3. A training aircraft front landing gear test equipment according to claim 2, characterized in that: The outer surface of the connecting tube (301) close to the lower part of the second connecting rod (3016) is rotatably connected to a sleeve (3012), and the outer surface of the connecting tube (301) close to the sleeve (3012) is sleeved with two limiting rings (3011), and a buffer bracket 1 (3014) is rotatably connected to the side wall of the sleeve (3012), and the bottom end of the buffer bracket 1 (3014) is rotatably connected to a buffer bracket 2 (3015), and the bottom end of the buffer bracket 2 (3015) is rotatably connected to the side wall of the connecting block (309).

4. The front landing gear test equipment for a training aircraft according to claim 1, characterized in that: The movable frame (4) is rotatably connected to a bidirectional screw rod (14) on the inner side wall close to the cross bar (5), and the side wall of the clamping plate (601) is in turn rotatably connected to a screw rod slide (604), and the screw rod slide (604) is symmetrically threadedly connected to the outer surface of the bidirectional screw rod (14). The side wall of the clamping plate (601) close to the screw rod slide (604) is provided with a slide groove (605) for the cross bar (5) to be plugged in, and the outer dimensions of the cross bar (5) are adapted to the inner dimensions of the slide groove (605) in turn.

5. The front landing gear test equipment for a training aircraft according to claim 4, characterized in that: A servo motor 2 (15) is fixedly mounted on the side wall of the movable frame (4); an output end of the servo motor 2 (15) is fixedly mounted on the end of a bidirectional screw rod (14) via a coupling; a limit block (19) is provided in the middle sleeve of the bidirectional screw rod (14).

6. A training aircraft front landing gear test equipment according to claim 5, characterized in that: The movable frame (4) is rotatably connected to a mounting seat 2 (16) near the bottom end of the connecting tube (301), and the bottom end of the mounting seat 2 (16) is rotatably connected to a hydraulic cylinder 2 (17). The output end of the hydraulic cylinder 2 (17) is provided with a connecting assembly 1 (20), and the connecting assembly 1 (20) includes a mounting seat 3 (2001) fixedly arranged at the output end of the hydraulic cylinder 2 (17), and the bottom end of the mounting seat 3 (2001) is rotatably connected to a connecting head (2002), and the bottom end of the connecting head (2002) is rotatably connected to the outer surface of the connecting rod 2 (3016).

7. The front landing gear test equipment for a training aircraft according to claim 1, characterized in that: Two hydraulic cylinders (9) are symmetrically fixed on the surface of the top plate (7), and the output ends of the two hydraulic cylinders (9) are sequentially passed through the top plate (7) and fixed on the top of the movable frame (4). Two slide grooves (18) are symmetrically provided on the outer surface of the movable frame (4), and the internal dimensions of the slide grooves (18) are sequentially matched with the external dimensions of the gantry (2).

8. The front landing gear test equipment for a training aircraft according to claim 1, characterized in that: The bottom end of the second rotating bracket (13) is provided with a second connecting assembly (22), and the second connecting assembly (22) includes a connecting head block (2201) rotatably connected to the bottom end of the second rotating bracket (13). The bottom end of the second rotating bracket (13) close to the connecting head block (2201) is provided with a first card slot (21), and the side wall of the connecting head block (2201) is provided with a second card slot (2202). The second card slot (2202) and the first card slot (21) are both semicircular for the first connecting rod (304) to be plugged in. A connecting plate (2203) is fixedly provided at the other end of the connecting block (2201); a third clamping groove (23) is provided on the side wall of the second rotating bracket (13) for clamping the connecting plate (2203); a first thread groove (2205) is provided on the side wall of the connecting plate (2203); a second thread groove (24) is provided on the inner side wall of the third clamping groove (23) near the first thread groove (2205); the insides of the first thread groove (2205) and the second thread groove (24) are threadedly connected with a threaded rod (2204) in sequence.

9. A training aircraft front landing gear test device, using the training aircraft front landing gear test device as claimed in any one of claims 1 to 8, characterized in that: The following steps are involved: S1: The connecting tube (301) is installed. The operator inserts the two rotating shafts (306) into the rotating groove (603) in sequence, starts the servo motor (15) to drive the bidirectional screw (14) to rotate, thereby driving the screw slide (604) to drive the two clamping blocks (602) to move towards each other, thereby clamping the wing plate (305), and then starts the hydraulic cylinder (17) to adjust the distance between the connecting head (2002) and the connecting rod (3016), so that the connecting head (2002) is sleeved on the outer surface of the connecting rod (3016), and the connecting tube (301) is supported by three points. S2: Install the rotating bracket 2 (13). The operator rotates the mounting base 1 (11), the rotating bracket 1 (12) and the rotating bracket 2 (13) in sequence to adjust the distance between the bottom end of the rotating bracket 2 (13) and the connecting rod 1 (304). The operator rotates the connecting head block (2201) to open the slot 1 (21). The connecting head block (2201) and the connecting plate (2203) are then passed through the bottom end of the connecting rod 1 (304). The operator then rotates the connecting head block (2201) to allow the connecting rod 1 (304) to be sequentially engaged with the inside of the slot 1 (21) and the slot 2 (2202). The operator then threadedly connects the threaded rod (2204) to the inside of the thread groove 1 (2205) and the thread groove 2 (24). S3: Turning to the side, the hydraulic cylinder 1 (9) is started to drive the movable frame (4) to slide vertically on the outer surface of the gantry (2), thereby adjusting the height of the movable frame (4) and the ground, so that the two tires (3010) are supported on the surface of the base (1) to simulate the weight of the trainer fuselage, and then the servo motor 1 (8) is started to drive the rotating table (10) to rotate synchronously. When the rotating table (10) rotates, it drives the mounting seat 1 (11), the rotating bracket 1 (12), the rotating bracket 2 (13) and the rotating shaft 1 (302) to rotate in sequence, thereby driving the tires (3010) to rotate, so as to achieve the steering test.

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