Aircraft landing gear damping sleeve crack observation equipment

Abstract

The invention relates to detection equipment, in particular to aircraft landing gear damping sleeve crack observation equipment which comprises a transverse moving support, the front end and the rear end of the transverse moving support are fixedly connected with connecting supports, the transverse moving support is rotationally connected with a first lead screw, and the two connecting supports are rotationally connected with second lead screws. Threads at the two ends of the second lead screw are opposite in rotating direction, each connecting support is slidably connected with two lateral moving supports, the two lateral moving supports are connected to the two ends of the second lead screw through threads respectively, two driving shafts are rotatably connected among the four lateral moving supports, and each driving shaft is slidably connected with two conical clamping wheels. And a compression spring is fixedly connected between the two conical clamping wheels, so that damping sleeves with different diameters, lengths and models can be observed.

Description

Technical Field

[0001] The invention relates to a detection device, in particular to a crack observation device for a shock-absorbing sleeve of an aircraft landing gear. Background Art

[0002] Aircraft landing gear is an important component of the aircraft, used to support the operation of the aircraft on the ground and in the air. The shock-absorbing sleeve is the shock-absorbing component of the aircraft landing gear, which is mainly used for shock absorption. Since the shock-absorbing sleeve is the main force-bearing mechanism, higher processes and requirements are required when preparing the shock-absorbing sleeve. Among them, it is necessary to inspect and observe the shock-absorbing sleeve as a whole to ensure that there is no damage or cracks on the tube body of the shock-absorbing sleeve after the shock-absorbing sleeve is processed, which will affect the mechanical properties of the shock-absorbing sleeve. The shock-absorbing sleeve has many lengths and diameters. Therefore, a device that can observe shock-absorbing sleeves of different diameters and lengths is needed to facilitate the inspection and observation of the shock-absorbing sleeve. Summary of the invention

[0003] The purpose of the invention is to provide a device for observing cracks in a shock-absorbing sleeve of an aircraft landing gear, which can observe shock-absorbing sleeves of different diameters and lengths.

[0004] The purpose of the present invention is achieved through the following technical solutions:

[0005] An aircraft landing gear shock-absorbing sleeve crack observation device comprises a transverse moving bracket, both front and rear ends of the transverse moving bracket are fixedly connected to connecting brackets, a first screw rod is rotatably connected to the transverse moving bracket, and both connecting brackets are rotatably connected to a second screw rod, the threads at both ends of the second screw rod have opposite rotation directions, a first power mechanism driving the first screw rod to rotate is fixedly connected to the transverse moving bracket, and the first power mechanism is preferably a servo motor, and a second power mechanism driving the second screw rod to rotate is fixedly connected to the connecting bracket, and the second power mechanism is preferably a servo motor;

[0006] Two side shift brackets are slidably connected to each connecting bracket, and the two side shift brackets are respectively connected to the two ends of the second screw rod through threads. Two driving shafts are rotatably connected between the four side shift brackets, and two conical clamping wheels are slidably connected to each driving shaft. A compression spring is fixedly connected between the two conical clamping wheels. A third power mechanism for driving the driving shaft to rotate is fixedly connected to the side shift bracket, and the third power mechanism is preferably a servo motor;

[0007] Each side shift bracket is fixedly connected to a first telescopic mechanism, and a push bracket is fixedly connected to the telescopic end of each first telescopic mechanism. Each push bracket is provided with a contact ball with clearance fit, and the contact ball can contact the corresponding conical clamping wheel;

[0008] Each side shift bracket is rotatably connected to a rotating sleeve, each rotating sleeve is fixedly connected to a second telescopic mechanism, two side-mounted clamping wheels are rotatably connected between the telescopic ends of the four second telescopic mechanisms, and a fourth power mechanism for driving the rotating sleeve to rotate is fixedly connected to the side shift bracket, and the fourth power mechanism is preferably a servo motor;

[0009] The traverse bracket is slidably connected to a mobile bracket, the mobile bracket is connected to the first screw rod by a thread, the mobile bracket is rotatably connected to a third screw rod, the mobile bracket is slidably connected to a support slider, the support slider is connected to the third screw rod by a thread, and the mobile bracket is fixedly connected to a fifth power mechanism for driving the third screw rod to rotate, and the fifth power mechanism is preferably a servo motor;

[0010] Two fourth telescopic mechanisms are fixedly connected to the supporting slider, and an observation bracket is fixedly connected to the telescopic end of each fourth telescopic mechanism. Each observation bracket is rotatably connected to two moving pulleys, and the two moving pulleys are connected by a moving belt transmission. Each moving belt is provided with an observation device, and each observation bracket is rotatably connected to a plurality of support wheels, which are in contact with the inner side of the moving belt. The observation bracket is fixedly connected to a sixth power mechanism for driving the moving pulley to rotate, and the sixth power mechanism is preferably a servo motor. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] The present invention is further described in detail below with reference to the accompanying drawings and specific implementation methods.

[0012] Figure 1 It is a schematic diagram of the structure of the aircraft landing gear shock-absorbing sleeve crack observation device of the present invention;

[0013] Figure 2 It is a schematic diagram of the structure of the transverse support of the present invention;

[0014] Figure 3 It is a schematic diagram of the side shift bracket structure of the present invention;

[0015] Figure 4 It is a schematic diagram of the structure of the tapered clamping wheel of the present invention;

[0016] Figure 5 It is a schematic diagram of the drive shaft structure of the present invention;

[0017] Figure 6 It is a schematic structural diagram of a first telescopic mechanism of the present invention;

[0018] Figure 7 It is a schematic diagram of the structure of the side-mounted clamping wheel of the present invention;

[0019] Figure 8 It is a schematic diagram of the structure of the mobile support of the present invention;

[0020] Fig. 9It is a schematic diagram of the observation bracket structure of the present invention.

[0021] In the figure:

[0022] Transverse support 11; connecting support 12; first screw rod 13; second screw rod 14;

[0023] Side shift bracket 21; drive shaft 22; conical clamping wheel 23;

[0024] First telescopic mechanism 31; pushing bracket 32; contact ball 33;

[0025] Rotating sleeve 41; second telescopic mechanism 42; side-mounted clamping wheel 43;

[0026] Movable bracket 51; third screw rod 52; supporting slider 53;

[0027] Fourth telescopic mechanism 61; observation bracket 62; moving pulley 63; moving belt 64; observation device 65; support wheel 66. DETAILED DESCRIPTION

[0028] The present invention is further described in detail below with reference to the accompanying drawings.

[0029] like Figures 1 to 9 As shown, in order to achieve the technical effect of "being able to observe shock-absorbing sleeves of different diameters and lengths", the structure and function of a crack observation device for shock-absorbing sleeves of aircraft landing gear are described in detail below;

[0030] A crack observation device for a shock-absorbing sleeve of an aircraft landing gear comprises a traverse bracket 11, wherein both front and rear ends of the traverse bracket 11 are fixedly connected to a connecting bracket 12, a first screw rod 13 is rotatably connected to the traverse bracket 11, and both connecting brackets 12 are rotatably connected to a second screw rod 14, wherein the threads at both ends of the second screw rod 14 have opposite rotation directions, a first power mechanism driving the first screw rod 13 to rotate is fixedly connected to the traverse bracket 11, and the first power mechanism is preferably a servo motor, and a second power mechanism driving the second screw rod 14 to rotate is fixedly connected to the connecting bracket 12, and the second power mechanism is preferably a servo motor;

[0031] Each connecting bracket 12 is slidably connected to two side shift brackets 21, and the two side shift brackets 21 are respectively connected to the two ends of the second screw rod 14 by threads. Two driving shafts 22 are rotatably connected between the four side shift brackets 21, and two conical clamping wheels 23 are slidably connected to each driving shaft 22. A compression spring is fixedly connected between the two conical clamping wheels 23. A third power mechanism for driving the driving shaft 22 to rotate is fixedly connected to the side shift bracket 21, and the third power mechanism is preferably a servo motor;

[0032] Each side shift bracket 21 is fixedly connected to a first telescopic mechanism 31, and a push bracket 32 ​​is fixedly connected to the telescopic end of each first telescopic mechanism 31. Each push bracket 32 ​​is gap-fitted with a contact ball 33, and the contact ball 33 can contact the corresponding conical clamping wheel 23;

[0033] When using, Figure 1 As shown, the shock-absorbing sleeve to be observed and tested is placed horizontally between the four conical clamping wheels 23, and the two ends of the shock-absorbing sleeve are respectively pressed against the inclined surfaces of the four conical clamping wheels 23, and the second power mechanism is started, and the output shaft of the second power mechanism starts to rotate, and the output shaft of the second power mechanism drives the second screw rod 14 to rotate, and when the second screw rod 14 rotates, it drives the side shift bracket 21 to move through the thread, so that the four side shift brackets 21 are moved closer to or away from each other, and then the relative distance between the four conical clamping wheels 23 is adjusted, so that the four conical clamping wheels 23 support the shock-absorbing sleeve;

[0034] Further, the first telescopic mechanism 31 is started. The first telescopic mechanism 31 can be a hydraulic cylinder or an electric push rod. The telescopic end of the first telescopic mechanism 31 drives the push bracket 32 ​​to move, and the push bracket 32 ​​drives the contact ball 33 to move, so that the contact ball 33 contacts the conical clamping wheel 23, and the contact ball 33 squeezes the conical clamping wheel 23, so that the relative distance between the two conical clamping wheels 23 on the same drive shaft 22 is increased, and then by starting the second power mechanism and the first telescopic mechanism 31, the relative positions of the four conical clamping wheels 23 can be adjusted, so that the four conical clamping wheels 23 can support the shock-absorbing sleeves of different diameters and lengths, and can axially limit the shock-absorbing sleeves;

[0035] Further, the third power mechanism is started, and the output shaft of the third power mechanism starts to rotate, and the output shaft of the third power mechanism drives the driving shaft 22 to rotate, and the driving shaft 22 drives the conical clamping wheel 23 to rotate, and the conical clamping wheel 23 contacts the shock-absorbing sleeve, thereby driving the shock-absorbing sleeve to rotate, and then the shock-absorbing sleeve is fully inspected and observed;

[0036] Each side shift bracket 21 is rotatably connected to a rotating sleeve 41, each rotating sleeve 41 is fixedly connected to a second telescopic mechanism 42, two side clamping wheels 43 are rotatably connected between the telescopic ends of the four second telescopic mechanisms 42, and a fourth power mechanism for driving the rotating sleeve 41 to rotate is fixedly connected to the side shift bracket 21, and the fourth power mechanism is preferably a servo motor;

[0037] Furthermore, in order to stably limit the shock-absorbing sleeve, the fourth power mechanism and the second telescopic mechanism 42 can be started, the output shaft of the fourth power mechanism drives the rotating sleeve 41 to rotate, the rotating sleeve 41 drives the second telescopic mechanism 42 to rotate, and the second telescopic mechanism 42 drives the side clamping wheel 43 to move, so that the side clamping wheel 43 contacts the side of the shock-absorbing sleeve, thereby limiting the side of the shock-absorbing sleeve;

[0038] The second telescopic mechanism 42 is started. The second telescopic mechanism 42 may be a hydraulic cylinder or an electric push rod. The telescopic end of the second telescopic mechanism 42 drives the side clamping wheel 43 to move, so that the side clamping wheel 43 contacts the side of the shock-absorbing sleeve, thereby limiting the side of the shock-absorbing sleeve;

[0039] Further, the traverse bracket 11 is slidably connected with a mobile bracket 51, which is connected to the first screw rod 13 by threads, and the mobile bracket 51 is rotatably connected with a third screw rod 52, and the mobile bracket 51 is slidably connected with a support slider 53, which is connected to the third screw rod 52 by threads, and the mobile bracket 51 is fixedly connected with a fifth power mechanism for driving the third screw rod 52 to rotate, and the fifth power mechanism is preferably a servo motor;

[0040] Two fourth telescopic mechanisms 61 are fixedly connected to the support slider 53, and an observation bracket 62 is fixedly connected to the telescopic end of each fourth telescopic mechanism 61. Each observation bracket 62 is rotatably connected to two moving pulleys 63, and the two moving pulleys 63 are connected by a moving belt 64. Each moving belt 64 is provided with an observation device 65. Each observation bracket 62 is rotatably connected to a plurality of support wheels 66, and the support wheels 66 are in contact with the inner side of the moving belt 64. The observation bracket 62 is fixedly connected to a sixth power mechanism for driving the moving pulley 63 to rotate, and the sixth power mechanism is preferably a servo motor.

[0041] Furthermore, in order to be able to detect both the inner and outer sides of the shock-absorbing sleeve at the same time, the first power mechanism is started, and the output shaft of the first power mechanism begins to rotate, and the output shaft of the first power mechanism drives the first screw rod 13 to rotate, and when the first screw rod 13 rotates, it drives the movable bracket 51 to move through the thread, and the movable bracket 51 drives the supporting slider 53 to move, and the supporting slider 53 drives the two fourth telescopic mechanisms 61 to move, and the fourth telescopic mechanism 61 drives the observation bracket 62 to move, and the observation bracket 62 drives the observation device 65 to move; the fifth power mechanism is started, and the output shaft of the fifth power mechanism drives the third screw rod 52 to rotate, and when the third screw rod 52 rotates, it drives the supporting slider 53 to move through the thread, and the supporting slider 53 drives two fourth telescopic mechanisms 61 to move, the fourth telescopic mechanisms 61 drive the observation bracket 62 to move, and the observation bracket 62 drives the observation device 65 to move; the fourth telescopic mechanism 61 is started, and the fourth telescopic mechanism 61 can be a hydraulic cylinder or an electric push rod, and the telescopic end of the fourth telescopic mechanism 61 drives the observation bracket 62 to move, and the observation bracket 62 drives the observation device 65 to move; so that one observation device 65 is located on the outside of the shock-absorbing sleeve, and the other observation device 65 extends into the inside of the shock-absorbing sleeve; through the two observation devices 65 cooperating with the rotation of the shock-absorbing sleeve, the inner and outer sides of the shock-absorbing sleeve are detected and observed at the same time, and the observation device 65 can be a flaw detection device in the prior art, or an observation device;

[0042] Further, such as Fig. 9 As shown, starting the first power mechanism will adjust the positions of the two observation devices 65 at the same time, and then when the position of one observation device 65 needs to be adjusted, the sixth power mechanism is started, and the output shaft of the sixth power mechanism drives the moving pulley 63 to rotate, the moving pulley 63 drives the moving belt 64 to move, and the moving belt 64 drives the observation device 65 to move, thereby adjusting the position of a single observation device 65, or adjusting the relative position between the two observation devices 65. At the same time, when the moving belt 64 drives the observation device 65 to move to the position of the moving pulley 63, since the moving pulley 63 is circular, the observation device 65 will produce a certain arc movement, thereby adjusting the observation angle of the observation device 65 to meet different detection and observation needs.

Claims

1. An aircraft landing gear shock-absorbing sleeve crack observation device, comprising a traverse bracket (11), characterized in that: The front and rear ends of the transverse displacement bracket (11) are fixedly connected to connecting brackets (12), each connecting bracket (12) is slidably connected to two lateral displacement brackets (21), two driving shafts (22) are rotatably connected between the four lateral displacement brackets (21), each driving shaft (22) is slidably connected to two conical clamping wheels (23), and a compression spring is fixedly connected between the two conical clamping wheels (23).

2. The aircraft landing gear shock-absorbing sleeve crack observation device according to claim 1, characterized in that: Each side shift bracket (21) is fixedly connected to a first telescopic mechanism (31), and a push bracket (32) is fixedly connected to the telescopic end of each first telescopic mechanism (31). Each push bracket (32) is gap-fitted with a contact ball (33), and the contact ball (33) can contact the corresponding conical clamping wheel (23).

3. The aircraft landing gear shock-absorbing sleeve crack observation device according to claim 1, characterized in that: Each lateral displacement bracket (21) is rotatably connected to a rotating sleeve (41), each rotating sleeve (41) is fixedly connected to a second telescopic mechanism (42), and two side clamping wheels (43) are rotatably connected between the telescopic ends of the four second telescopic mechanisms (42).

4. The aircraft landing gear shock-absorbing sleeve crack observation device according to claim 1, characterized in that: The two connecting brackets (12) are both rotatably connected to a second screw rod (14), and the threads at both ends of the second screw rod (14) have opposite rotation directions.

5. The aircraft landing gear shock-absorbing sleeve crack observation device according to claim 4, characterized in that: The four side shift brackets (21) are respectively connected to the two ends of the two second screw rods (14) through threads.

6. The aircraft landing gear shock-absorbing sleeve crack observation device according to claim 1, characterized in that: The transverse moving bracket (11) is rotatably connected to a first screw rod (13).

7. The aircraft landing gear shock-absorbing sleeve crack observation device according to claim 6, characterized in that: The transverse bracket (11) is slidably connected to a movable bracket (51), the movable bracket (51) is connected to a first screw rod (13) by means of a thread, the movable bracket (51) is rotatably connected to a third screw rod (52), the movable bracket (51) is slidably connected to a support slider (53), and the support slider (53) is connected to the third screw rod (52) by means of a thread.

8. The aircraft landing gear shock-absorbing sleeve crack observation device according to claim 7, characterized in that: The support slider (53) is fixedly connected to two fourth telescopic mechanisms (61), and the telescopic end of each fourth telescopic mechanism (61) is fixedly connected to an observation bracket (62). Each observation bracket (62) is rotatably connected to two moving pulleys (63), and the two moving pulleys (63) are connected by a moving belt (64). Each moving belt (64) is provided with an observation device (65).

9. The aircraft landing gear shock-absorbing sleeve crack observation device according to claim 8, characterized in that: Each observation bracket (62) is rotatably connected to a plurality of support wheels (66).

10. The aircraft landing gear shock-absorbing sleeve crack observation device according to claim 9, characterized in that: The support wheel (66) is in contact with the inner side of the moving belt (64).

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