Gantry test workbench
Through the design of the gantry test workbench, the problem of aircraft drop attitude testing is solved by using flexible ropes and rectangular frame structures, and effective observation and verification of the aircraft drop process is achieved, ensuring the safety and design verification of the aircraft during the release process.
Patent Information
- Application Number
- CN202421122342.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-05-22
- Publication Date
- 2024-12-24
- Estimated Expiration
- 2034-05-22
AI Technical Summary
During the release of the aircraft, it is difficult to effectively test and verify the aircraft's whereabouts and attitude, resulting in incomplete design verification and affecting the success of the flight test.
A gantry test workbench was designed, using a gantry frame with cross beams and support beams. The aircraft was connected to the flexible rope, which controlled its drop height and prevented impact. Combined with a rectangular frame, connecting plate and pulley structure, the suspension and attitude observation of the aircraft were realized. .
Through the suspension of the flexible rope and the rectangular frame structure, effective testing and verification of the aircraft's drop posture is achieved, ensuring that the aircraft is not damaged during the drop, and the drop height is controlled to meet the needs of design verification.
Smart Images
Figure CN222224441U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aircraft release posture, in particular to a gantry test workbench. Background Art
[0002] During the design process of an aircraft, various design indicators need to be verified, including the aircraft's carrying capacity, key indicators of the aircraft's internal structure, and the aircraft's flight attitude as it changes with altitude. These indicators are crucial to whether the aircraft can conduct flight tests, so the test before the aircraft's flight test is extremely important.
[0003] The working scenario of the aircraft is that it is transported by a mother aircraft or other equipment. When mounted, a rack is provided on the mother aircraft, and then the aircraft is mounted on the rack for transportation, and then released according to demand.
[0004] Therefore, in order to improve the design of the aircraft, it is necessary to conduct tests to observe and verify the posture of the aircraft at different falling heights during the release process of the aircraft. Utility Model Content
[0005] The utility model aims to provide a gantry test workbench to solve the problem of testing the falling posture of an aircraft during the release process of the aircraft.
[0006] In order to achieve the above purpose, the utility model adopts the following technical solutions:
[0007] The gantry test workbench comprises a gantry main body with a crossbeam, a support beam fixedly connected to the gantry is arranged below the crossbeam, the support beam is parallel to the crossbeam, and a plurality of connection parts for connecting to the aircraft's hanger are arranged on the support beam in the length direction; two hangers are arranged on the lower side of the crossbeam, the hangers are arranged at both ends in the length direction of the crossbeam, the hangers are provided with hollow parts, a flexible rope is freely inserted in the hollow part, and the end of the flexible rope is used to connect to the aircraft after falling naturally.
[0008] On the basis of the above scheme and as a preferred scheme of the above scheme: a rectangular frame is provided on the lower side of the crossbeam, the upper part of the rectangular frame is fixedly connected to the crossbeam, and the lower part is the supporting beam.
[0009] On the basis of the above scheme and as a preferred scheme of the above scheme: a first connecting plate is respectively arranged at both ends of the upper part of the rectangular frame, and the first connecting plate is respectively provided with through holes on both sides of the length direction of the rectangular frame, and at least one U-shaped connecting piece is arranged above each first connecting plate, and external threads are arranged at both ends of the connecting piece. The connecting piece is inserted into the through hole from the top of the beam downward so that the beam is in the recess of the connecting piece, and the two ends of the connecting piece are respectively inserted into one of the through holes of the first connecting plate on both sides of the length direction of the rectangular frame, and a nut is arranged below the first connecting plate to threadably cooperate with the external thread of the connecting piece.
[0010] On the basis of the above scheme and as a preferred scheme of the above scheme: the hanger includes a second connecting plate fixedly connected to the upper part of the rectangular frame, two downwardly extending mounting plates are arranged on the second connecting plate, a rotatable pulley is arranged between the two mounting plates, the pulley simultaneously connects the two mounting plates through a rotating shaft, and the pulley, the two mounting plates and the second connecting plate surround the hollow part.
[0011] On the basis of the above scheme and as a preferred scheme of the above scheme: the flexible rope is freely placed on the upper side of the pulley, and the two ends of the flexible rope fall freely from the two sides of the support beam respectively.
[0012] On the basis of the above scheme and as a preferred scheme of the above scheme: the connecting part is an L-shaped plate, and one L-shaped plate is respectively arranged on both sides of the two end directions of the support beam, the upper end of the L-shaped plate is fixedly connected to the support beam, and the lower end is provided with a through hole, and the through hole can be provided with a screw for connecting the aircraft's bracket.
[0013] In order to solve the problem of testing the falling posture of an aircraft during the release process of the aircraft, the utility model has the following beneficial effects:
[0014] When the gantry test workbench of the utility model is in use, the connecting part is used to fix the connection to the bracket for mounting the aircraft, and then the aircraft to be tested is mounted on the bracket, wherein the two flexible ropes correspond to the front and rear ends of the aircraft, and the two ends of the flexible ropes are connected to the two sides of the aircraft, and then the test begins.
[0015] During the test, the connection between the pylon and the aircraft is released and unlocked, and then the aircraft begins to fall while the falling posture is observed and verified.
[0016] Among them, the reserved length at both ends of the flexible rope is used to control the falling height limit of the aircraft during the test. At the same time, the suspension of the aircraft by the flexible rope prevents the aircraft from colliding with the ground during the falling process and causing unnecessary damage to the aircraft.
[0017] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS
[0018] Figure 1 This is a schematic diagram of the structure of the gantry test workbench of the utility model;
[0019] Figure 2 It is a schematic diagram of the connection part of the utility model;
[0020] Figure 3 It is a partial schematic diagram of the pendant of the utility model. DETAILED DESCRIPTION
[0021] The technical solutions in the embodiments of the present utility model are clearly and completely described below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present utility model, rather than all the embodiments.
[0022] See also Figure 1-3 The utility model discloses a gantry test workbench, which can be used to test the falling posture of an aircraft 600 after being released from a hanger 601, and solve the problem of observing and verifying the falling posture of the aircraft 600 during the release process of the aircraft 600 through the test.
[0023] In the embodiments of the present disclosure, Figure 1 As shown, the gantry test workbench includes a gantry body 100 with a crossbeam 101, a support beam 203 fixedly connected to the gantry is arranged below the crossbeam 101, the support beam 203 is parallel to the crossbeam 101, and a plurality of connection parts 400 for connecting the bracket 601 of the aircraft 600 are arranged in the length direction of the support beam 203; two hangers 300 are arranged on the lower side of the crossbeam 101, the hangers 300 are arranged at both ends of the length direction of the crossbeam 101, and the hangers 300 are provided with a hollow part 305, and a flexible rope 500 is freely inserted in the hollow part 305, and the end of the flexible rope 500 is used to connect to the aircraft 600 after falling naturally.
[0024] When the gantry test workbench of the utility model is in use, the connection portion 400 is used to fix the connection to the bracket 601 for mounting the aircraft 600, and then the aircraft 600 to be tested is mounted on the bracket 601, wherein the two flexible ropes 500 correspond to the front and rear ends of the aircraft 600, and the two ends of the flexible ropes 500 are connected to the two sides of the aircraft 600, and then the test begins.
[0025] During the test, the connection between the unlocking bracket 601 and the aircraft 600 is released, and then the aircraft 600 starts to fall while the falling posture is observed and verified.
[0026] The falling height limit of the aircraft 600 during the test is controlled by the reserved length at both ends of the flexible rope 500. At the same time, the flexible rope 500 suspends the aircraft 600 to prevent the aircraft 600 from colliding with the ground during the falling process, causing unnecessary damage to the aircraft 600.
[0027] In the embodiment of the present disclosure, in order to obtain an optimized design structure, a rectangular frame 200 is provided on the lower side of the crossbeam 101, and the upper part of the rectangular frame 200 is fixedly connected to the crossbeam 101. Figure 1 The lower part of the rectangular frame 200 shown in FIG. 1 is a support beam 203 .
[0028] In the embodiments of the present disclosure, Figure 3 As shown, a first connecting plate 201 is respectively provided at both ends of the upper part of the rectangular frame 200, and the first connecting plate 201 is respectively provided with through holes 202 on both sides of the length direction of the rectangular frame 200, and at least one U-shaped connecting piece 204 is provided above each first connecting plate 201, and both ends of the connecting piece 204 are provided with external threads, and the connecting piece 204 is inserted into the through hole 202 from the top of the crossbeam 101 downward, so that the crossbeam 101 is in the concave part of the connecting piece 204, and the two ends of the connecting piece 204 are respectively inserted into one of the through holes 202 on both sides of the length direction of the first connecting plate 201, and a nut 205 is provided below the first connecting plate 201 to be threadedly matched with the external threads of the connecting piece 204. The connection between the rectangular frame 200 and the crossbeam 101 is detachable, which is convenient for later maintenance.
[0029] In the embodiments of the present disclosure, Figure 3 As shown, the hanger 300 includes a second connecting plate 301 fixedly connected to the upper part of the rectangular frame 200, two mounting plates 302 extending downward are arranged on the second connecting plate 301, a rotatable pulley 303 is arranged between the two mounting plates 302, the pulley 303 is connected to the two mounting plates 302 at the same time through a rotating shaft 304, and the pulley 303, the two mounting plates 302 and the second connecting plate 301 form a hollow part 305. Further, the flexible rope 500 is freely placed on the upper side of the pulley 303, and the two ends of the flexible rope 500 fall freely from the two sides of the support beam 203 respectively. Generally, the flexible rope 500 passes through the top of the pulley 303, and the middle part of the flexible rope 500 is freely placed in the upward groove of the pulley 303. The purpose of setting the pulley 303 is that the posture of the aircraft 600 during the falling process during the test is uncertain, but the pulley 303 has negligible constraints on the movement of the flexible rope 500, which can minimize the influence of the flexible rope 500 on the falling posture of the aircraft 600.
[0030] In the embodiments of the present disclosure, Figure 2As shown, in order to facilitate the setting of the corresponding pylon 601 on the workbench during testing and meet the requirement of reducing processing costs, the connecting part 400 is an L-shaped plate 401, and an L-shaped plate 401 is respectively set on both sides of the two ends of the support beam 203. The upper end of the L-shaped plate 401 is fixedly connected to the support beam 203, and the lower end is provided with a through hole 402, and the through hole 402 can be provided with a screw for connecting the pylon 601 of the aircraft 600. When the pylon 601 is set, the pylon 601 can be fixed to the lower end of the L-shaped plate 401 by screws.
[0031] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes within the technical scope disclosed by the present invention according to the technical scheme and the utility model concept of the present invention, which should be covered by the protection scope of the present invention.
Claims
1. Gantry test bench, characterized in that: The invention comprises a gantry main body (100) having a crossbeam (101), wherein a support beam (203) fixedly connected to the gantry is arranged below the crossbeam (101), the support beam (203) is parallel to the crossbeam (101), and a plurality of connection parts (400) for connecting a hanger (601) of an aircraft (600) are arranged in the length direction of the support beam (203); two hangers (300) are arranged on the lower side of the crossbeam (101), the hangers (300) are arranged at both ends of the crossbeam (101) in the length direction, and the hangers (300) are provided with a hollow part (305), and a flexible rope (500) is freely inserted in the hollow part (305), and the end of the flexible rope (500) is used to be connected to the aircraft (600) after naturally falling.
2. The gantry test bench according to claim 1, characterized in that: A rectangular frame (200) is provided on the lower side of the crossbeam (101); the upper part of the rectangular frame (200) is fixedly connected to the crossbeam (101), and the lower part is the support beam (203).
3. The gantry test bench according to claim 2, characterized in that: A first connecting plate (201) is respectively arranged at both ends of the upper part of the rectangular frame (200), and through holes (202) are respectively arranged on both sides of the first connecting plate (201) in the length direction of the rectangular frame (200). At least one U-shaped connecting piece (204) is arranged above each of the first connecting plates (201), and both ends of the connecting piece (204) are provided with external threads. The connecting piece (204) is inserted downward from the top of the crossbeam (101) into the through hole (202), so that the crossbeam (101) is located in the recess of the connecting piece (204), and both ends of the connecting piece (204) are respectively inserted into one of the through holes (202) on both sides of the first connecting plate (201) in the length direction of the rectangular frame (200), and a nut (205) is arranged below the first connecting plate (201) to be threadedly matched with the external thread of the connecting piece (204).
4. The gantry test bench according to claim 2, characterized in that: The hanging component (300) comprises a second connecting plate (301) fixedly connected to the upper part of the rectangular frame (200); two downwardly extending mounting plates (302) are arranged on the second connecting plate (301); a rotatable pulley (303) is arranged between the two mounting plates (302); the pulley (303) simultaneously connects the two mounting plates (302) via a rotating shaft (304); the pulley (303), the two mounting plates (302) and the second connecting plate (301) form the hollow portion (305).
5. The gantry test workbench according to claim 4, characterized in that: The flexible rope (500) is freely placed on the upper side of the pulley (303), and the two ends of the flexible rope (500) fall freely from the two sides of the support beam (203) respectively.
6. The gantry test bench according to claim 1, characterized in that: The connecting portion (400) is an L-shaped plate (401), and one L-shaped plate (401) is respectively arranged on both sides of the support beam (203) at both ends. The upper end of the L-shaped plate (401) is fixedly connected to the support beam (203), and the lower end is provided with a through hole (402), and a screw for connecting a bracket (601) of the aircraft (600) can be arranged in the through hole (402).