CN218662412U - Flight testing device - Google Patents
Flight testing device Download PDFInfo
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- CN218662412U CN218662412U CN202222199248.8U CN202222199248U CN218662412U CN 218662412 U CN218662412 U CN 218662412U CN 202222199248 U CN202222199248 U CN 202222199248U CN 218662412 U CN218662412 U CN 218662412U
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- rigid coupling
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- support
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The utility model discloses a flight testing device, which comprises a supporting device, wherein the supporting device comprises a supporting mechanism, the supporting mechanism is fixedly connected on the outer wall of a frame body, and a moving mechanism is fixedly connected on the bottom surface of the frame body; the displacement device comprises a first displacement mechanism, the bottom of the first displacement mechanism is fixedly connected to the top of the frame body, and the top of the first displacement mechanism is fixedly connected with a second displacement mechanism; the positioning device comprises a positioning plate, the bottom surface of the positioning plate is fixedly connected with the top of the second displacement mechanism, the top surface of the positioning plate is fixedly connected with three restraint mechanisms, and the restraint mechanisms correspond to three landing gears of the airplane respectively. The aircraft is placed on the locating plate, and restraint mechanism rigid coupling is at the locating plate top, and restraint mechanism carries on spacingly to the undercarriage, guarantees the stability in the test procedure.
Description
Technical Field
The utility model relates to an aviation flight technical field especially relates to a flight testing arrangement.
Background
Various flight attitudes can appear in the flight process of the aircraft, and when the flight attitudes are in states of diving, rolling and climbing, relative displacement can appear between oil liquid of an aircraft oil tank and an oil tank oil outlet, so that an aircraft engine cannot acquire the fuel oil in the aircraft oil tank, and the aircraft engine is flamed out, and the risk of crash is caused. At present, various postures of the aircraft are simulated by adopting the test bed in the industry, but the mode of fixing the aircraft by the existing test bed is complicated, the operation is complex, and the test efficiency is influenced.
Therefore, a flight test device is needed to solve the above problems.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a flight testing arrangement to solve the problem that prior art exists.
In order to achieve the above object, the utility model provides a following scheme: the utility model provides a flight test device, include:
the supporting device comprises a supporting mechanism, the supporting mechanism is fixedly connected to the outer wall of the frame body, and the bottom surface of the frame body is fixedly connected with a moving mechanism;
the displacement device comprises a first displacement mechanism, the bottom of the first displacement mechanism is fixedly connected to the top of the frame body, and the top of the first displacement mechanism is fixedly connected with a second displacement mechanism;
the positioning device comprises a positioning plate, the bottom surface of the positioning plate is fixedly connected with the top of the second displacement mechanism, three constraint mechanisms are fixedly connected with the top surface of the positioning plate, and the constraint mechanisms are respectively arranged corresponding to three undercarriage of the airplane.
Preferably, the supporting mechanism includes two supporting cantilevers, one end of each of the two supporting cantilevers is respectively and fixedly connected to two opposite sidewalls of the frame body, the other end of each of the two supporting cantilevers is fixedly connected to an air cylinder, a supporting plate is disposed below the frame body, output ends of the two air cylinders are respectively and fixedly connected to two ends of the supporting plate, and a rubber layer is fixedly connected to the bottom surface of the supporting plate.
Preferably, first displacement mechanism includes the first stand that shifts, the first stand bottom surface rigid coupling that shifts is in support body top one side, support body top opposite side corresponds and is provided with the second stand that shifts, first stand lateral wall rigid coupling that shifts has first motor, first motor output runs through first stand rigid coupling that shifts has the one end of the connecting block that shifts, the other end of the connecting block that shifts pass through the axis of rotation with the second is shifted the stand and is rotated and be connected.
Preferably, the second displacement mechanism comprises a second motor, the bottom of the second motor is fixedly connected with the top of the displacement connecting block, and the output end of the second motor is fixedly connected with the bottom surface of the positioning plate.
Preferably, the restraint mechanism includes the location stand, the location stand with locating plate top surface rigid coupling, the location stand rigid coupling has first wire rope's one end, first wire rope's other end rigid coupling has the one end of length adjustment subassembly, the other end rigid coupling of length adjustment subassembly has the one end of second wire rope, the other end rigid coupling of second wire rope has the tight regulation subassembly, the tight regulation subassembly with aircraft undercarriage looks adaptation.
Preferably, the length adjustment subassembly includes first threaded rod, first threaded rod one end with first wire rope rigid coupling, first threaded rod other end threaded connection has the one end of screw thread adjustable ring, the other end threaded connection of screw thread adjustable ring has the one end of second threaded rod, the other end of second threaded rod with second wire rope rigid coupling.
Preferably, the tightness adjusting assembly comprises a limiting cylinder, the bottom of the limiting cylinder is fixedly connected with the second steel wire rope, the inner wall of the limiting cylinder is in threaded connection with a limiting column, a through hole is formed in the center of the limiting column, the bottom of the inner cavity of the limiting cylinder is fixedly connected with a steel wire ring, and the steel wire ring penetrates through the through hole of the limiting column.
Preferably, the moving mechanism comprises a plurality of wheels, the wheels are fixedly connected with four corners of the bottom surface of the frame body respectively, and the supporting plate is located between the wheels.
The utility model discloses a following technological effect: the utility model discloses a supporting mechanism rigid coupling is on the support body outer wall, supporting mechanism descends at flight testing arrangement during operation, closely laminate with ground, play stabilizing action to flight testing arrangement during operation, the moving mechanism rigid coupling is in the support body bottom, moving mechanism help flight testing arrangement shift position, first indexing mechanism rigid coupling is at the support body top surface, first indexing mechanism vertical direction adjustment pitch angle, second indexing mechanism bottom surface rigid coupling is at first indexing mechanism top surface, second indexing mechanism horizontal direction adjustment direction angle, the bottom surface and the second indexing mechanism top surface rigid coupling of locating plate, the aircraft is placed on the locating plate, the constraining mechanism rigid coupling is at the locating plate top, the constraining mechanism carries on spacingly to the undercarriage, guarantee the stability in the test procedure.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the embodiments will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic structural view of the present invention;
fig. 2 is a top view of the present invention;
FIG. 3 is an enlarged view of a portion A1 in FIG. 2;
FIG. 4 is a partial enlarged view of A2 in FIG. 2;
wherein, 1, the frame body; 2. positioning a plate; 3. a support cantilever; 4. a cylinder; 5. a support plate; 6. a rubber layer; 7. a first displacement column; 8. a second displacement upright post; 9. a first motor; 10. a rotating shaft; 11. a position-changing connecting block; 12. a first wire rope; 13. a second wire rope; 14. a first threaded rod; 15. a second threaded rod; 16. a limiting cylinder; 17. a limiting column; 18. a bead ring; 19. a wheel; 20. positioning the upright post; 21. a second motor; 22. and a threaded adjusting ring.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts all belong to the protection scope of the present invention.
In order to make the above objects, features and advantages of the present invention more comprehensible, the present invention is described in detail with reference to the accompanying drawings and the detailed description.
Referring to fig. 1-4, the utility model provides a flight testing arrangement, include:
the supporting device comprises a supporting mechanism, the supporting mechanism is fixedly connected to the outer wall of the frame body 1, and the bottom surface of the frame body 1 is fixedly connected with a moving mechanism;
the displacement device comprises a first displacement mechanism, the bottom of the first displacement mechanism is fixedly connected to the top of the frame body 1, and the top of the first displacement mechanism is fixedly connected with a second displacement mechanism;
and the positioning device comprises a positioning plate 2, the bottom surface of the positioning plate 2 is fixedly connected with the top of the second displacement mechanism, three constraint mechanisms are fixedly connected to the top surface of the positioning plate 2, and the three constraint mechanisms are respectively arranged corresponding to three undercarriage of the airplane.
The supporting mechanism is fixedly connected to the outer wall of the frame body 1, the supporting mechanism descends when the flight testing device works and is tightly attached to the ground, the flight testing device works and is stabilized, the moving mechanism is fixedly connected to the bottom of the frame body 1, the moving mechanism helps the flight testing device to move, the first shifting mechanism is fixedly connected to the top surface of the frame body 1, the pitching angle of the first shifting mechanism is adjusted in the vertical direction, the bottom surface of the second shifting mechanism is fixedly connected to the top surface of the first shifting mechanism, the direction angle of the second shifting mechanism is adjusted in the horizontal direction, the bottom surface of the positioning plate 2 is fixedly connected to the top surface of the second shifting mechanism, the aircraft is placed on the positioning plate 2, the constraining mechanism is fixedly connected to the top of the positioning plate 2, the constraining mechanism limits the undercarriage, stability in the testing process is guaranteed, the set constraining mechanism can simplify the operation flow of fixing the aircraft, time consumption is reduced, and flight testing efficiency is improved.
According to the further optimization scheme, the supporting mechanism comprises two supporting cantilevers 3, one ends of the two supporting cantilevers 3 are fixedly connected to two opposite side walls of the support body 1 respectively, the other ends of the two supporting cantilevers 3 are fixedly connected with air cylinders 4, a supporting plate 5 is arranged below the support body 1, output ends of the two air cylinders 4 are fixedly connected with two ends of the supporting plate 5 respectively, and a rubber layer 6 is fixedly connected to the bottom surface of the supporting plate 5.
Support 3 rigid couplings of cantilever on the lateral wall of 1 both sides of support body, support cantilever 3 and play the effect with cylinder 4 outside extension, increase and 5 top surface rigid coupling scopes of backup pad, 5 bottom surface rigid couplings of backup pad have rubber layer 6 to increase frictional force, through 4 output drive backup pads 5 of cylinder and ground contact when testing arrangement needs work, increase testing arrangement's stability, when testing arrangement needs shift position driving backup pad 5 through 4 output of cylinder leaves ground.
Further optimize the scheme, first displacement mechanism includes first stand 7 that shifts, and first 7 bottom surfaces of stand rigid couplings that shift are in 1 top one side of support body, and 1 top opposite side of support body corresponds and is provided with the second stand 8 that shifts, and first 7 lateral walls of stand rigid couplings that shift have first motor 9, and first motor 9 output runs through the one end that first stand 7 rigid couplings that shifts have connecting block 11 that shifts, and the other end that shifts connecting block 11 passes through axis of rotation 10 and is connected with the rotation of second stand 8 that shifts.
First stand 7 and the second stand 8 rigid coupling that shifts are in support body top surface both sides, and first stand 7 and the second that shifts set up the connecting block 11 that shifts between the stand 8, and connecting block 11 top rigid coupling second shifting mechanism shifts, and first motor 9 rigid coupling is in the first stand 7 outside, and first motor 9 is servo motor, and the output drive connecting block 11 of first motor 9 rotates, realizes the regulation to the every single move angle of the vertical direction of aircraft.
Further optimize the scheme, the second deflection mechanism includes the second motor 21, the bottom of the second motor 21 is fixedly connected with the top of the deflection connecting block 11, and the output end of the second motor 21 is fixedly connected with the bottom surface of the positioning plate 2.
The bottom of the second motor 21 is fixedly connected with the deflection connecting block 11, the output end of the second motor 21 is fixedly connected with the positioning plate 2, the second motor 21 is a servo motor, and the second motor 21 drives the positioning plate 2 to rotate so as to realize the direction adjustment of the horizontal angle of the aircraft.
Further optimization scheme, restraint mechanism includes location stand 20, and location stand 20 and 2 top surface rigid couplings of locating plate, location stand 20 rigid coupling have the one end of first wire rope 12, and the other end rigid coupling of first wire rope 12 has the one end of length adjustment subassembly, and the other end rigid coupling of length adjustment subassembly has the one end of second wire rope 13, and the other end rigid coupling of second wire rope 13 has the tight regulation subassembly, tight regulation subassembly and aircraft undercarriage looks adaptation.
Three location stand 20 bottom surface and 2 top surface rigid couplings of locating plate, three location stand 20 corresponds three undercarriage respectively, location stand 20 is connected with the one end of first wire rope 12, the other end rigid coupling of first wire rope 12 has the one end of length adjustment subassembly, the length adjustment subassembly can be adjusted wire rope's length, the other end rigid coupling of length adjustment subassembly has the one end of second wire rope 13, the other end rigid coupling of second wire rope 13 has the tight regulation subassembly, tight regulation subassembly and aircraft undercarriage looks adaptation, carry out stable fixed to the aircraft undercarriage, ensure that the aircraft can not drop among the test procedure, the operation flow of fixed aircraft can be simplified to the restraint mechanism that sets up, time consumption is reduced, promote flight test efficiency.
Further optimize the scheme, the length adjustment subassembly includes first threaded rod 14, and 14 one end of first threaded rod and first wire rope 12 rigid coupling, 14 other end threaded connection of first threaded rod have the one end of screw thread adjustable ring 22, and the other end threaded connection of screw thread adjustable ring 22 has the one end of second threaded rod 15, and the other end and the second wire rope 13 rigid coupling of second threaded rod 15.
The first threaded rod and the second threaded rod 15 are in threaded connection through the threaded adjusting ring 22, when the aircraft landing gear is fixed, the lengths of the first steel wire rope 12 and the second steel wire rope 13 are adjusted by rotating the first threaded rod 14 and the second threaded rod 15, the fact that the lengths reach a proper length is guaranteed, the steel wire ring 18 is sleeved on the landing gear, and then the landing gear is locked through adjusting the tightness adjusting assembly, so that the landing gear can be better fixed to the aircraft.
Further optimize the scheme, the tight regulation subassembly includes a spacing section of thick bamboo 16, and 16 bottoms rigid couplings of a spacing section of thick bamboo have second wire rope 13, and 16 inner wall threaded connection of a spacing section of thick bamboo have spacing post 17, and the through-hole has been seted up at spacing post 17 center, and 16 inner chamber bottoms rigid couplings of a spacing section of thick bamboo have steel wire winding 18, and steel wire winding 18 runs through the through-hole of spacing post 17.
The steel wire ring 18 is fixed with the bottom of the inner wall of the limiting cylinder 16, the steel wire ring 18 penetrates through a through hole formed in the center of the limiting column 17, the steel wire ring 18 sleeves the aircraft landing gear, the inner wall of the limiting cylinder 16 is in threaded connection with the limiting column 17, and the tightness degree of the steel wire ring 18 can be adjusted by displacing the limiting column 17 through rotation to fix the aircraft landing gear.
In a further optimized scheme, the moving mechanism comprises a plurality of wheels 19, the wheels 19 are fixedly connected with four corners of the bottom surface of the frame body 1 respectively, and the supporting plate 5 is positioned among the wheels 19.
A plurality of wheels 19 rigid couplings are in 1 bottom surface four corners of support body, and wheel 19 adopts the universal wheel, for prior art does not give unnecessary details here, and wheel 19's effect can be rotated, makes things convenient for whole testing arrangement's removal, and backup pad 5 lies in and can ensure between a plurality of wheels 19 that do not influence the rotation of a plurality of wheels 19 after backup pad 5 packs up.
In the description of the present invention, it is to be understood that the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are merely for convenience of description of the present invention, and do not indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
The above-mentioned embodiments are only described in the preferred embodiments of the present invention, but not limited to the scope of the present invention, and various modifications and improvements made by the technical solutions of the present invention by those skilled in the art should fall within the protection scope defined by the claims of the present invention without departing from the design spirit of the present invention.
Claims (8)
1. A flight testing apparatus, comprising:
the support device comprises a support mechanism, the support mechanism is fixedly connected to the outer wall of the frame body (1), and the bottom surface of the frame body (1) is fixedly connected with a moving mechanism;
the displacement device comprises a first displacement mechanism, the bottom of the first displacement mechanism is fixedly connected to the top of the frame body (1), and the top of the first displacement mechanism is fixedly connected with a second displacement mechanism;
the positioning device comprises a positioning plate (2), the bottom surface of the positioning plate (2) is fixedly connected with the top of the second displacement mechanism, three constraint mechanisms are fixedly connected to the top surface of the positioning plate (2), and the constraint mechanisms are respectively arranged corresponding to three undercarriage of the airplane.
2. A flight testing apparatus according to claim 1, characterised in that: the support mechanism comprises two support cantilevers (3), one ends of the two support cantilevers (3) are fixedly connected to two opposite side walls of the support body (1) respectively, the other ends of the two support cantilevers (3) are fixedly connected with cylinders (4), a support plate (5) is arranged below the support body (1), the output ends of the cylinders (4) are fixedly connected with the two ends of the support plate (5) respectively, and a rubber layer (6) is fixedly connected to the bottom surface of the support plate (5).
3. A flight testing apparatus according to claim 1, characterised in that: first displacement mechanism includes first stand (7) that shifts, first stand (7) bottom surface rigid coupling that shifts is in support body (1) top one side, support body (1) top opposite side correspondence is provided with second stand (8) that shifts, first stand (7) lateral wall rigid coupling that shifts has first motor (9), first motor (9) output runs through first stand (7) rigid coupling that shifts has the one end of connecting block (11) that shifts, the other end of connecting block (11) that shifts pass through axis of rotation (10) with second stand (8) that shifts rotate and connect.
4. A flight testing device according to claim 3, wherein: the second deflection mechanism comprises a second motor (21), the bottom of the second motor (21) is fixedly connected with the top of the deflection connecting block (11), and the output end of the second motor (21) is fixedly connected with the bottom surface of the positioning plate (2).
5. A flight testing device according to claim 1, characterised in that: restraint mechanism is including location stand (20), location stand (20) with locating plate (2) top surface rigid coupling, location stand (20) rigid coupling has the one end of first wire rope (12), the other end rigid coupling of first wire rope (12) has the one end of length adjustment subassembly, the other end rigid coupling of length adjustment subassembly has the one end of second wire rope (13), the other end rigid coupling of second wire rope (13) has the tight regulation subassembly, the tight regulation subassembly with undercarriage looks adaptation.
6. A flight testing device according to claim 5, wherein: the length adjustment subassembly includes first threaded rod (14), first threaded rod (14) one end with first wire rope (12) rigid coupling, first threaded rod (14) other end threaded connection has the one end of screw thread adjustable ring (22), the other end threaded connection of screw thread adjustable ring (22) has the one end of second threaded rod (15), the other end of second threaded rod (15) with second wire rope (13) rigid coupling.
7. A flight testing device according to claim 6, wherein: the tightness adjusting assembly comprises a limiting cylinder (16), the bottom of the limiting cylinder (16) is fixedly connected with the second steel wire rope (13), the inner wall of the limiting cylinder (16) is in threaded connection with a limiting column (17), a through hole is formed in the center of the limiting column (17), the bottom of the inner cavity of the limiting cylinder (16) is fixedly connected with a steel wire ring (18), and the steel wire ring (18) penetrates through the through hole of the limiting column (17).
8. A flight testing apparatus according to claim 2, wherein: the moving mechanism comprises a plurality of wheels (19), the wheels (19) are fixedly connected with the four corners of the bottom surface of the frame body (1) respectively, and the supporting plate (5) is positioned between the wheels (19).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222199248.8U CN218662412U (en) | 2022-08-19 | 2022-08-19 | Flight testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222199248.8U CN218662412U (en) | 2022-08-19 | 2022-08-19 | Flight testing device |
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| Publication Number | Publication Date |
|---|---|
| CN218662412U true CN218662412U (en) | 2023-03-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222199248.8U Active CN218662412U (en) | 2022-08-19 | 2022-08-19 | Flight testing device |
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| CN (1) | CN218662412U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116119024A (en) * | 2023-04-17 | 2023-05-16 | 成都沃飞天驭科技有限公司 | Aircraft test platform and design method thereof |
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2022
- 2022-08-19 CN CN202222199248.8U patent/CN218662412U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116119024A (en) * | 2023-04-17 | 2023-05-16 | 成都沃飞天驭科技有限公司 | Aircraft test platform and design method thereof |
| CN116119024B (en) * | 2023-04-17 | 2023-07-18 | 成都沃飞天驭科技有限公司 | Aircraft test platform and design method thereof |
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