Static test supporting platform for front fuselage of light aircraft main body

Abstract

The invention discloses a static test supporting platform for a front fuselage of a light aircraft main body, and relates to the field of static tests of aircraft main bodies. The aircraft comprises an aircraft body, the rear fuselage of the aircraft body is clamped by a fixing mechanism, the fixing mechanism comprises a fixing disc arranged on the aircraft body, a first sliding groove is fixedly formed in the surface of the fixing disc, the first sliding groove is slidably connected with one end of a connecting rod, and the other end of the connecting rod is rotatably installed on a clamping block; the clamping blocks are rotationally installed on the disc support, the disc support is rotationally installed on the fixed disc, a rotating handle is fixedly installed on the disc support, a hole is formed in the fixed disc, and the hole is in threaded connection with a fixing bolt. The position of the clamping block can be conveniently adjusted by rotating the rotating handle, so that the clamping block is tightly attached to rear fuselages of aircraft main bodies of different models, stability and safety in the test process are ensured, in addition, the fixing reliability is enhanced through the design of the fixing bolts, and the test efficiency is improved. Accidents caused by unstable fixation in the test process are effectively prevented, and the accuracy and reliability of the test are improved.

Description

Technical Field

[0001] The invention belongs to the field of static test of aircraft bodies, and in particular relates to a static test support platform for the front fuselage of a light aircraft body. Background Art

[0002] The static strength test of the aircraft body is also called static test. It mainly tests the performance of the aircraft body structure and is an important part of the aircraft body finalization. When the aircraft body is subjected to static strength test, the aircraft body needs to be fixed and supported, especially the aircraft body support position should be as far away from the static strength test area as possible to ensure the accuracy of the static test; and the light aircraft body front fuselage static test support platform is a device specially designed to support and fix the light aircraft body front fuselage for static testing. Static test is an important test link in the aviation industry. It is used to evaluate the strength, stiffness and stability of the aircraft body structure when subjected to various static loads. The support platform usually includes a series of precise mechanisms and components, such as fixing mechanisms, lifting mechanisms, sliding mechanisms, etc. These mechanisms and components work together to accurately adjust the posture and position of the aircraft body to ensure the accuracy and reliability of the test.

[0003] After searching, the Chinese patent number CN101788397A proposed a method for supporting static tests on the front fuselage of a light aircraft main body. The method for supporting static tests on the front fuselage of a light aircraft main body is to set two clamps at the straight frame of the rear fuselage of the aircraft main body. The clamps are tightly engaged with the fuselage, and each clamp is connected to two columns set on both sides of the fuselage. The width of the clamp edge strip is not greater than the width of the fuselage frame edge strip where it is set. One of the clamps is set at the straight frame of the fuselage between the wing of the aircraft main body and the horizontal tail of the aircraft main body, and the other clamp is set at the tail end of the aircraft main body after the horizontal tail of the aircraft main body is disassembled. A longitudinal member is added to the fuselage between the two clamps, and the longitudinal member is a long stringer on the fuselage. The method for supporting static tests on the front fuselage of a light aircraft main body of the present invention is simple to operate, has little impact on the test results, has high accuracy, and low cost. It effectively solves the problem of supporting the light aircraft main body for the overall static strength test of the front fuselage, and has great practical application value;

[0004] However, during specific test operations, the position of the clamp at the rear fuselage needs to be adjusted accordingly based on the actual situation of the light aircraft body, which means that the aircraft body of the same test model requires multiple corresponding clamps; which means that when the model of the test aircraft body changes, the clamps need to be remade based on the new fuselage. Summary of the invention

[0005] In view of the problems in the related technology, the present invention proposes a static test support platform for the front fuselage of a light aircraft to overcome the above-mentioned technical problems existing in the existing related technology.

[0006] In order to solve the above technical problems, the present invention is achieved through the following technical solutions:

[0007] The present invention is a static test support platform for the front fuselage of a light aircraft body, comprising an aircraft body, wherein the rear fuselage of the aircraft body is clamped by a fixing mechanism, wherein the fixing mechanism comprises a fixing disc arranged on the aircraft body, wherein a first slide groove is fixedly installed on the surface of the fixing disc, wherein one end of a connecting rod is slidably connected to the first slide groove, wherein the other end of the connecting rod is rotatably installed on a clamping block, wherein the clamping block is rotatably installed on a disc bracket, wherein the disc bracket is rotatably installed on the fixing disc, wherein a rotating handle is fixedly installed on the disc bracket, wherein a hole is provided on the fixing disc, wherein a fixing bolt is threadedly connected to the hole, and wherein the fixing bolt conflicts with the rotating handle;

[0008] Turn the rotating handle to drive the disc bracket to rotate, so that one end of the connecting rod slides in the first slide groove, and the other end gathers toward the center of the disc bracket, driving the three clamping blocks to gather toward the center at the same time to clamp the rear fuselage of the aircraft body. Subsequently, the fixing bolt is screwed into the hole to fix the rotating handle. During operation, the fixing mechanism needs to be adjusted according to the actual situation of the light aircraft body to match the setting position of the fuselage.

[0009] Furthermore, the fixed disc is fixedly mounted on a connecting member, the connecting member is fixedly mounted on a fixed top plate, a moving rod is fixedly mounted on the bottom of the fixed top plate, and the moving rod is slidably connected to the inside of the fixed rod.

[0010] Furthermore, the fixed rod is fixedly mounted on a fixed bottom plate, and a lifting mechanism is provided between the movable rod and the fixed rod, and the lifting mechanism is used to control the movable rod to rise or fall.

[0011] Furthermore, the lifting mechanism includes a first threaded rod arranged inside the fixed rod, the first threaded rod is rotatably installed inside the fixed rod, the first threaded rod is fixedly installed with a worm wheel, the worm wheel is meshed with a worm, and the worm wheel is rotatably installed inside the fixed rod.

[0012] Furthermore, the connecting parts, fixed top plate, movable rod, fixed rod, fixed bottom plate and lifting mechanism are each provided in two groups, and their parts and installation methods are the same. The other group of the connecting parts, fixed top plate, movable rod, fixed rod, fixed bottom plate and lifting mechanism is used to support the front fuselage of the aircraft body, and the fixed bottom plate is slidably connected to the workbench.

[0013] Furthermore, the workbench is provided with a second slide groove, a sliding block is fixedly installed at the bottom of the fixed base plate, the sliding block is slidably connected to a guide rod, and the guide rod is fixedly installed inside the second slide groove.

[0014] Furthermore, the workbench is provided with a third slide groove and a fourth slide groove, and a second threaded rod and a third threaded rod are rotatably installed inside the third slide groove and the fourth slide groove.

[0015] Furthermore, the second threaded rod and the third threaded rod are threadedly connected with a fixed base block, and the fixed base block is fixedly installed on the bottom of the fixed base plate.

[0016] Furthermore, the fixed base block is slidably connected inside the third sliding groove and the fourth sliding groove.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. The light aircraft main body front fuselage static test support platform proposed by the present invention realizes the stable clamping of the aircraft main body rear fuselage through the innovative clamping and fixing mechanism. By turning the rotating handle, the position of the clamping block can be conveniently adjusted to make it fit closely to the aircraft main body rear fuselage of different models, thereby ensuring the stability and safety during the test. In addition, the design of the fixing bolts further enhances the reliability of the fixation, effectively prevents accidents caused by unstable fixation during the test, and improves the accuracy and reliability of the test.

[0019] 2. The support platform of the present invention is equipped with a height-adjustable lifting mechanism. By rotating the worm and the worm gear, the height of the aircraft body support can be easily adjusted. This design allows the operator to flexibly adjust the posture and height of the aircraft body according to the specific requirements of the test, thereby more accurately simulating various situations in actual flight. This height adjustability not only improves the flexibility of the test, but also greatly simplifies the operation process and reduces the difficulty of the test.

[0020] 3. The support platform of the present invention also has a convenient support position adjustment function. By rotating the second threaded rod and the third threaded rod, the support positions of the front fuselage and the rear fuselage of the aircraft body can be adjusted respectively. This design allows the operator to accurately adjust the support position according to the actual size and shape of the aircraft body and the specific needs of the test to ensure that the aircraft body is in the best state during the test. This function not only improves the accuracy and reliability of the test, but also makes the present invention have good adaptability to aircraft bodies of different models and sizes.

[0021] Of course, any product implementing the present invention does not necessarily need to achieve all of the advantages described above at the same time. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions of the embodiments of the invention, the drawings required for describing the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the invention. For ordinary technicians in this field, other drawings can be obtained based on the following drawings without creative work.

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

[0024] Figure 2 It is a front view of the present invention;

[0025] Figure 3 It is an enlarged view of point A of the present invention;

[0026] Figure 4 It is a schematic diagram of the fixing mechanism of the present invention;

[0027] Figure 5 A top view of the present invention;

[0028] Figure 6 It is a schematic diagram of a workbench of the present invention.

[0029] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0030] 1. Aircraft body; 2. Workbench; 3. Fixed disc; 4. First slide groove; 5. Connecting rod; 6. Clamping block; 7. Disc bracket; 8. Turning handle; 9. Hole; 10. Fixing bolt; 11. Connecting piece; 12. Fixed top plate; 13. Moving rod; 14. Fixed rod; 15. Fixed bottom plate; 16. First threaded rod; 17. Worm gear; 18. Worm; 19. Second slide groove; 20. Sliding block; 21. Guide rod; 22. Third slide groove; 23. Fourth slide groove; 24. Second threaded rod; 25. Third threaded rod; 26. Fixed base block. DETAILED DESCRIPTION

[0031] The following will be combined with the drawings in the embodiments of the invention to clearly and completely describe the technical solutions in the embodiments of the invention. Obviously, the described embodiments are only part of the embodiments of the invention, not all of the embodiments. Based on the embodiments in the invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the invention.

[0032] In the description of the present invention, it is necessary to understand that the terms "opening", "upper", "lower", "top", "middle", "inside" and the like indicating orientation or positional relationship are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the components or elements referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as limiting the invention.

[0033] See also Figure 1-Figure 6 As shown, the present invention is a static test support platform for the front fuselage of a light aircraft body, comprising an aircraft body 1, wherein the rear fuselage of the aircraft body 1 is clamped by a fixing mechanism, wherein the fixing mechanism comprises a fixing disc 3 arranged on the aircraft body 1, wherein a first slide groove 4 is fixedly installed on the surface of the fixing disc 3, wherein the first slide groove 4 is slidably connected to one end of a connecting rod 5, wherein the other end of the connecting rod 5 is rotatably installed on a clamping block 6, wherein the clamping block 6 is rotatably installed on a disc bracket 7, wherein the disc bracket 7 is rotatably installed on the fixing disc 3, wherein a rotating handle 8 is fixedly installed on the disc bracket 7, wherein a hole 9 is provided on the fixing disc 3, wherein a fixing bolt 10 is threadedly connected to the hole 9, and wherein the fixing bolt 10 conflicts with the rotating handle 8.

[0034] The working principle of the static test support platform for the front fuselage of the main body of a light aircraft proposed by the present invention is to first rotate the rotating handle 8, and drive the disc bracket 7 to rotate by rotating the rotating handle 8, thereby driving one end of the connecting rod 5 to slide along the inside of the first slide groove 4, and the other end to gather toward the center position of the disc bracket 7, thereby driving the three clamping blocks 6 to gather toward the center position of the disc bracket 7 at the same time, thereby achieving clamping of the rear fuselage of the aircraft body 1, and then the fixing bolt 10 can be threadedly connected to the inside of the hole 9, so that the fixing bolt 10 forms a resistance to the rotating handle 8 to prevent the rotating handle 8 from rotating during the static test.

[0035] It is worth noting that during specific test operations, the fixing mechanism needs to be adjusted according to the actual situation of the light aircraft body 1, so that the rear fuselage can be adjusted accordingly to match the fuselage at the set position, so as to better fasten and support the aircraft body 1. The fixing mechanism has a certain universality in supporting different positions of the fuselage, and also has a certain universality for different models of test aircraft bodies 1.

[0036] Furthermore, the three clamping blocks 6 may be made of rubber material on one side close to the outer wall of the aircraft body 1 to prevent damage to the outer wall of the aircraft body 1 when the aircraft body 1 is fixed.

[0037] In one embodiment, for the above-mentioned fixed disc 3, the fixed disc 3 is fixedly mounted on the connecting member 11, the connecting member 11 is fixedly mounted on the fixed top plate 12, a moving rod 13 is fixedly mounted on the bottom of the fixed top plate 12, and the moving rod 13 is slidably connected to the inside of the fixed rod 14.

[0038] In one embodiment, for the above-mentioned fixed rod 14, the fixed rod 14 is fixedly installed on the fixed base plate 15, and a lifting mechanism is provided between the moving rod 13 and the fixed rod 14, and the lifting mechanism is used to control the moving rod 13 to rise or fall.

[0039] In one embodiment, for the above-mentioned lifting mechanism, the lifting mechanism includes a first threaded rod 16 arranged inside the fixed rod 14, the first threaded rod 16 is rotatably installed inside the fixed rod 14, the first threaded rod 16 is fixedly installed with a worm gear 17, the worm gear 17 is meshed with a worm 18, and the worm 18 is rotatably installed inside the fixed rod 14.

[0040] In one embodiment, for the above-mentioned connecting member 11, the connecting member 11, the fixed top plate 12, the moving rod 13, the fixed rod 14, the fixed bottom plate 15 and the lifting mechanism are each provided with two groups, and their parts and installation methods are the same. The other group of connecting members 11, the fixed top plate 12, the moving rod 13, the fixed rod 14, the fixed bottom plate 15 and the lifting mechanism are used to support the front fuselage of the aircraft body 1, and the fixed bottom plate 15 is slidably connected to the workbench 2.

[0041] The working principle of the static test support platform for the front fuselage of a light aircraft body proposed by the present invention is that when the height of the aircraft body 1 needs to be raised, the operator rotates the worm 18 to drive the worm wheel 17 to rotate, thereby driving the first threaded rod 16 to rotate, thereby driving the moving rod 13, the fixed top plate 12 and the connecting piece 11 to rise, and then driving the aircraft body 1 to rise.

[0042] Furthermore, when it is necessary to lower the height of the support of the aircraft body 1, the operator rotates the worm 18, thereby driving the worm wheel 17 to rotate, and then driving the first threaded rod 16 to rotate, thereby driving the moving rod 13, the fixed top plate 12 and the connecting member 11 to descend, and then driving the aircraft body 1 to descend, so that corresponding adjustments can be made according to the requirements of the test, thereby improving the flexibility of the device.

[0043] It is worth noting that the worm 18 and the worm wheel 17 are self-locking, thereby preventing the first threaded rod 16 from rotating during the static test of the aircraft body 1, thereby causing the aircraft body 1 to move up and down, thereby causing inaccuracy in the test.

[0044] In one embodiment, for the above-mentioned workbench 2, the workbench 2 is provided with a second slide groove 19, and a sliding block 20 is fixedly installed at the bottom of the fixed base plate 15. The sliding block 20 is slidably connected to a guide rod 21, and the guide rod 21 is fixedly installed inside the second slide groove 19.

[0045] In one embodiment, for the above-mentioned workbench 2, the workbench 2 is provided with a third sliding groove 22 and a fourth sliding groove 23, and a second threaded rod 24 and a third threaded rod 25 are rotatably installed inside the third sliding groove 22 and the fourth sliding groove 23.

[0046] In one embodiment, for the second threaded rod 24 , the second threaded rod 24 and the third threaded rod 25 are threadedly connected with a fixed base block 26 , and the fixed base block 26 is fixedly installed at the bottom of the fixed base plate 15 .

[0047] In one embodiment, for the fixed base block 26 , the fixed base block 26 is slidably connected inside the third sliding groove 22 and the fourth sliding groove 23 .

[0048] The working principle of the static test support platform for the front fuselage of a light aircraft body proposed by the present invention is that when the support position of the rear fuselage of the aircraft body 1 needs to be adjusted, the nose position needs to be temporarily supported, so the worm 18 can be rotated, thereby driving the worm wheel 17 to rotate, and then driving the first threaded rod 16 to rotate, thereby driving the moving rod 13, the fixed top plate 12 and the connecting member 11 to rise or fall, thereby supporting the nose position of the aircraft body 1, and at the same time, the second threaded rod 24 can be rotated, so that the fixed base block 26 moves along the third slide groove 22, thereby driving the connecting member 11 to be fine-tuned, so that the support position of the front fuselage of the aircraft body 1 can be better adjusted.

[0049] It is worth noting that the side of the connecting member 11 close to the aircraft body 1 is in the form of an arc surface, so that it can better fit the outer wall of the aircraft body 1, and the connecting member 11 is made of soft material, so that when supporting the aircraft body 1, it will not cause damage to the outer wall of the aircraft body 1.

[0050] Similarly, when the clamping position of the rear fuselage of the aircraft body 1 needs to be adjusted, the operator rotates the third threaded rod 25, so that the fixed base block 26 moves along the fourth slide groove 23, thereby better adjusting the supporting and fixing position of the rear fuselage of the aircraft body 1.

[0051] Furthermore, the guide rod 21 plays a guiding role. When the fixed base plate 15 moves along the workbench 2, the guide rod 21 limits the fixed base plate 15 to prevent the fixed base plate 15 from rotating.

[0052] Finally, the worm 18, the second threaded rod 24 and the third threaded rod 25 can be externally connected to a power device such as a drive motor, thereby saving manpower and making the rotation more stable.

[0053] In the description of this specification, the description with reference to the terms "one embodiment", "example", "specific example", etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0054] The preferred embodiments of the invention disclosed above are only used to help illustrate the invention. The preferred embodiments do not describe all the details in detail, nor do they limit the invention to the specific embodiments described. Obviously, many modifications and changes can be made based on the content of this specification. This specification selects and specifically describes the embodiments in order to better explain the principles and practical applications of the invention, so that those skilled in the art can better understand and use the invention. The invention is limited only by the claims and their full scope and equivalents.

Claims

1. A light aircraft main body front fuselage static test support platform, comprising an aircraft main body (1), characterized in that: The rear fuselage of the aircraft body (1) is clamped by a fixing mechanism, the fixing mechanism comprising a fixing disc (3) arranged on the aircraft body (1), a first slide groove (4) fixedly installed on the surface of the fixing disc (3), one end of a connecting rod (5) being slidably connected to the first slide groove (4), the other end of the connecting rod (5) being rotatably installed on a clamping block (6), the clamping block (6) being rotatably installed on a disc bracket (7), the disc bracket (7) being rotatably installed on the fixing disc (3), a rotating handle (8) being fixedly installed on the disc bracket (7), the fixing disc (3) being provided with a hole (9), a fixing bolt (10) being threadedly connected to the hole (9), the fixing bolt (10) being in conflict with the rotating handle (8); The rotating handle (8) is turned to drive the disc bracket (7) to rotate, so that one end of the connecting rod (5) slides in the first slide groove (4) and the other end gathers toward the center of the disc bracket (7), driving the three clamping blocks (6) to gather toward the center at the same time to clamp the rear fuselage of the aircraft body (1). Subsequently, the fixing bolt (10) is screwed into the hole (9) to fix the rotating handle (8). During operation, the fixing mechanism needs to be adjusted according to the actual situation of the light aircraft body (1) to match the fuselage setting position.

2. A light aircraft main body front fuselage static test support platform according to claim 1, characterized in that: The fixed disc (3) is fixedly mounted on a connecting member (11), the connecting member (11) is fixedly mounted on a fixed top plate (12), a moving rod (13) is fixedly mounted on the bottom of the fixed top plate (12), and the moving rod (13) is slidably connected to the inside of the fixed rod (14).

3. A light aircraft main body front fuselage static test support platform according to claim 2, characterized in that: The fixed rod (14) is fixedly mounted on a fixed bottom plate (15); a lifting mechanism is provided between the moving rod (13) and the fixed rod (14); the lifting mechanism is used to control the moving rod (13) to rise or fall.

4. A light aircraft main body front fuselage static test support platform according to claim 3, characterized in that: The lifting mechanism comprises a first threaded rod (16) arranged inside the fixed rod (14), the first threaded rod (16) being rotatably mounted inside the fixed rod (14), the first threaded rod (16) being fixedly mounted with a worm wheel (17), the worm wheel (17) being meshed with a worm (18), and the worm (18) being rotatably mounted inside the fixed rod (14).

5. A light aircraft main body front fuselage static test support platform according to claim 4, characterized in that: The connecting member (11), the fixed top plate (12), the moving rod (13), the fixed rod (14), the fixed bottom plate (15) and the lifting mechanism are provided in two groups, and the parts and installation methods thereof are the same. The other group of the connecting member (11), the fixed top plate (12), the moving rod (13), the fixed rod (14), the fixed bottom plate (15) and the lifting mechanism is used to support the front fuselage of the aircraft body (1), and the fixed bottom plate (15) is slidably connected to the workbench (2).

6. A light aircraft main body front fuselage static test support platform according to claim 5, characterized in that: The workbench (2) is provided with a second slide groove (19), and a sliding block (20) is fixedly installed at the bottom of the fixed base plate (15). The sliding block (20) is slidably connected to a guide rod (21), and the guide rod (21) is fixedly installed inside the second slide groove (19).

7. A light aircraft main body front fuselage static test support platform according to claim 6, characterized in that: The workbench (2) is provided with a third slide groove (22) and a fourth slide groove (23), and a second threaded rod (24) and a third threaded rod (25) are rotatably mounted inside the third slide groove (22) and the fourth slide groove (23).

8. A light aircraft front fuselage static test support platform according to claim 7, characterized in that: The second threaded rod (24) and the third threaded rod (25) are threadedly connected to a fixed base block (26), and the fixed base block (26) is fixedly mounted on the bottom of the fixed base plate (15).

9. A light aircraft main body front fuselage static test support platform according to claim 8, characterized in that: The fixed base block (26) is slidably connected inside the third sliding groove (22) and the fourth sliding groove (23).

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