CN117141743B - Bearing and releasing device for full-aircraft drop test of aircraft - Google Patents
Bearing and releasing device for full-aircraft drop test of aircraft Download PDFInfo
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- CN117141743B CN117141743B CN202311412375.4A CN202311412375A CN117141743B CN 117141743 B CN117141743 B CN 117141743B CN 202311412375 A CN202311412375 A CN 202311412375A CN 117141743 B CN117141743 B CN 117141743B
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- 238000012360 testing method Methods 0.000 title claims abstract description 23
- 230000007246 mechanism Effects 0.000 claims abstract description 18
- 230000000149 penetrating effect Effects 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 5
- 238000004146 energy storage Methods 0.000 description 5
- 239000000203 mixture Substances 0.000 description 4
- 230000004044 response Effects 0.000 description 2
- 210000003437 trachea Anatomy 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000009863 impact test Methods 0.000 description 1
- 230000005012 migration Effects 0.000 description 1
- 238000013508 migration Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
Abstract
The invention discloses a bearing and releasing device for an aircraft full-aircraft drop test, which belongs to the technical field of aircraft tests and comprises a base, wherein the front end of the base is provided with a quick release mechanism, the rear end of the base is provided with two front height adjusting seats and two rear height adjusting seats side by side, the upper parts of the two front height adjusting seats are respectively fixedly connected with a front hinging seat, the two front hinging seats are jointly hinged with an H-shaped support arm, the upper parts of the two rear height adjusting seats are respectively fixedly connected with a rear hinging seat, the two rear hinging seats are jointly hinged with an H-shaped crushing rod, the two upper sides of the H-shaped crushing rod are respectively hinged with a vertical support arm, and the front ends of the two vertical support arms are respectively hinged with the two sides of the top of the H-shaped support arm.
Description
Technical Field
The invention relates to the technical field of aircraft tests, in particular to a bearing and releasing device for an aircraft full-aircraft drop test.
Background
The full-aircraft landing vibration of the fixed-wing carrier-based aircraft is one of key technologies for aircraft design and research, and the carrier-based aircraft evaluates the strength of the aircraft under all boundary landing conditions through full-size aircraft landing tests which need to be implemented in a laboratory. Aircraft landing gear and fuselage components are required to withstand significant impact loads without structural failure, thereby verifying the structural integrity of the fuselage.
When the whole aircraft is in a drop test, firstly, the aircraft is lifted to a preset height through a lifting device, the aircraft landing gear wheels are rotated in a reverse course through an aircraft wheel rotating device to simulate the aircraft landing course speed, the aircraft is suddenly released after the aircraft reaches the preset course speed, the aircraft performs free falling motion, the aircraft applies wing lifting force with the size equal to the weight of the aircraft when the aircraft touches a ground force measuring platform, a test data acquisition system is triggered before the aircraft touches the force measuring platform, and a time course curve of signals acquired by various sensors after the aircraft touches the force measuring platform is recorded.
In order to verify the dynamic response of an aircraft body, the reliability of important parts, overload borne by a driver, passengers and airborne equipment and the like under the special working condition that the carrier-based aircraft is hooked by free flight, the carrier-based aircraft needs to pass a landing impact test of a whole aircraft structure, the landing load of the aircraft and the dynamic response of the aircraft body and the important equipment caused by the landing ground load are checked in a laboratory environment, and the sinking speed of a nose landing gear is much higher than that of a main landing gear due to the pitching moment in the process, which is also a difficulty in realizing the working condition in the laboratory environment. There is a need for a load release device for an aircraft full-aircraft drop test.
Disclosure of Invention
In order to solve the technical problems, the invention provides a bearing and releasing device for an aircraft full-aircraft drop test.
The technical scheme of the invention is as follows: the utility model provides an aircraft all-aircraft is bears release device for shock test, includes the base, the front end of base is equipped with quick release mechanism, and the rear end of base is equipped with two front altitude mixture control seats and two back altitude mixture control seats side by side, two the top of front altitude mixture control seat is fixedly connected with a front hinge seat respectively, and two on the front hinge seat jointly articulated have an H type support arm, two on the back altitude mixture control seat respectively fixedly connected with a back hinge seat, two on the back hinge seat jointly articulated have an H type crushing pole, the top both sides of H type crushing pole are articulated respectively have a vertical support arm, two the front end of vertical support arm respectively with H type support arm top both sides are articulated, quick release mechanism's top articulates has the triangle-shaped bracing piece that falls, two summit departments above the triangle-shaped bracing piece respectively one-to-one with the top both sides of H type support arm are articulated;
the quick release mechanism comprises a release seat, an upper sliding groove is formed in the upper side of the release seat, a sliding block is connected in the upper sliding groove in a sliding mode, a first air cylinder is arranged on the lower side of the release seat, the telescopic end of the first air cylinder is hinged to the sliding block, a sliding hinging seat is fixedly connected to the upper side of the sliding block, the upper end of the sliding hinging seat is hinged to the lower end of the inverted triangle support rod, a connecting plate is fixedly connected to the rear end of the sliding block, a trigger block is hinged to the rear end of the connecting plate, and a fixing plate used for clamping the trigger block is fixedly connected to the rear side of the release seat.
Further, the front side top of fixed plate is equipped with the joint groove, the below of joint groove is equipped with the stopper, the rear side of triggering the piece is equipped with spacing post, the rear side fixedly connected with joint board of triggering the piece, the below of joint board with the stopper joint, the rear side of joint board with spacing post joint, the rear side of fixed plate articulates there is the latch hook, the upper end and the joint board joint of latch hook, the rear side inner wall fixedly connected with second cylinder of fixed plate, the flexible end of second cylinder with the lower extreme of latch hook is connected, fixedly connected with energy storage ware on the base, the energy storage ware with first cylinder with the second cylinder is linked together through the trachea.
Description: through spacing post and connecting plate joint to ensure when the aircraft did not reach predetermined gesture, the joint board can not move forward under the effect of aircraft gravity.
Further, the lock hook comprises a lock hook shaft, the right end of the lock hook shaft is fixedly connected with the fixed plate, the left end of the lock hook shaft is rotatably connected with a hook body, a hook is arranged above the hook body, and a hinge mechanism is fixedly connected below the hook body; the hinge mechanism comprises two side plates, the two side plates are respectively and fixedly connected to the left side and the right side below the hook body, a sliding hole is respectively formed in the lower portion of each side plate, a hinge shaft is arranged between the two sliding holes, and the telescopic end of the second air cylinder is fixedly connected with the middle of the hinge shaft.
Description: through the coupler body with the latch hook axle rotates to be connected, and then makes couple and joint butt, and then makes the unable forward movement of trigger piece, makes the articulated shaft reciprocate in the slide hole through the slide hole, avoids because articulated shaft horizontal migration's in-process leads to curb plate below to take place the displacement about with the articulated shaft, leads to the flexible end of second cylinder crooked.
Further, the joint board includes the plate body, the front side of plate body is equipped with screw rod one, the plate body pass through screw rod one with trigger piece fixed connection, the below of plate body is equipped with spacing mouth, spacing mouth with stopper joint, the rear side of plate body is equipped with the arc wall, the arc wall with spacing post joint, the below of arc wall is equipped with the joint, the joint with couple butt.
Description: the plate body is fixed on the trigger block through threads, so that the clamping plate is convenient to replace.
Further, two transverse sliding grooves are formed in the release seat in a front-back penetrating mode, a sliding plate is arranged between the two transverse sliding grooves, and the upper sliding groove is located on the upper side of the sliding plate.
Description: the transverse sliding groove provides space for the sliding block to slide back and forth so as to ensure smoothness of the sliding block during sliding.
Further, the front height adjusting seat and the rear height adjusting seat comprise panels, a plurality of heightening blocks are arranged below the panels, mounting holes are formed in four corners of the panels and the heightening blocks, a second screw rod is arranged in each mounting hole, and the panels and the heightening blocks are connected with the base in a threaded mode through the second screw rods sequentially penetrating through the mounting holes in the panels and the heightening blocks.
Description: the height of the H-shaped crushing rod and the H-shaped support arm is adjusted by superposing the heightening blocks.
Further, a groove for supporting the aircraft body is arranged above the vertical support arm.
Description: the connection with the aircraft body is facilitated through the groove.
Further, the sliding block comprises a sliding rod which is in sliding connection with the inner portion of the upper sliding groove, two sides of the sliding rod are rotationally connected with a sliding shell, a sliding hinge seat is fixedly connected to the top of the sliding shell, and the lower portion of the front side of the sliding shell is hinged to the telescopic end of the first cylinder.
Description: through slide bar and last spout sliding connection, after the back removal of triangle-shaped bracing piece falls, the sliding shell rear end upwards moves.
Further, the front side of base fixedly connected with PLC controller, PLC controller and energy storage ware electric connection.
Description: the energy accumulator is convenient to control to supply air to the second air cylinder and the first air cylinder through the PLC.
The invention also provides a using method of the bearing and releasing device for the full-aircraft drop test of the aircraft, which comprises the following steps:
s1, connecting a rear mounting point of an airplane with the vertical support arm; during the test, the aircraft is released, so that the aircraft rotates back and forth around the rear mounting point;
s2, when the airplane rotates forwards, the vertical support arm rotates downwards to drive the lower end of the inverted triangle support rod to move towards the rear side, so that the rear end of the sliding block is driven to tilt upwards, and the front side of the trigger block is further driven to move upwards, so that the trigger block is separated from the fixed plate;
s3, the first air cylinder drives the sliding block and the inverted triangle support rod to retract forwards, the vertical support arm is crushed downwards and is separated from the airplane, and the airplane performs free falling motion.
The beneficial effects of the invention are as follows:
the bearing and releasing device provided by the invention can simulate the special working condition that the sinking speed of the nose landing gear is larger than that of the main landing gear caused by free flying and hooking under the laboratory environment, the trigger block is quickly separated from the fixed plate by adjusting the posture of the aircraft, the sliding block is quickly slid forwards under the tension of the first air cylinder, the dropping speed of the vertical support arm is further higher than that of the aircraft, the aircraft quickly loses the acting point, the influence of the slow dropping speed of the vertical support arm on the landing of the aircraft is avoided, and the bearing of huge impact load on each part of the landing gear and the aircraft body of the aircraft is favorably studied without structural failure, so that the structural integrity of the aircraft body can be better verified.
Drawings
FIG. 1 is a perspective view of the overall structure of the present invention;
FIG. 2 is an enlarged view at A in FIG. 1;
FIG. 3 is a schematic view of the quick release mechanism of the present invention;
FIG. 4 is a schematic perspective view of a latch hook according to the present invention;
FIG. 5 is a schematic view of a card plate according to the present invention;
FIG. 6 is a schematic view of the structure of the front height adjustment seat of the present invention;
the device comprises a 1-base, a 2-quick release mechanism, a 3-front height adjusting seat, a 4-rear height adjusting seat, a 5-front hinging seat, a 6-H-shaped support arm, a 7-rear hinging seat, an 8-H-shaped crushing rod, a 9-vertical support arm, a 10-inverted triangle support rod, a 21-release seat, a 22-upper sliding groove, a 23-sliding block, a 24-first cylinder, a 25-sliding hinging seat, a 26-connecting plate, a 27-triggering block, a 28-fixing plate, a 281-clamping groove, a 282-limiting block, a 283-limiting post, a 271-clamping plate, 284-locking hooks, 285-second cylinder, a 11-energy accumulator, a 2841-locking hook shaft, a 2842-hook body, a 2843-hook, a 2844-hinging mechanism, a 2711-plate body, a 2712-screw rod I, a 2713-limiting opening, a 2714-arc-shaped groove, a 2715-clamping joint, a 28441-side plate, a 28442-sliding hole, a 28443-hinging shaft, a 29-transverse sliding groove, a 291-31-panel, a 32-lifting block, a 285-sliding plate, a mounting hole, a 285-33-second cylinder, a sliding plate, a 231-sliding rod, a 231-sliding shell and a 231-PLC (controller).
Detailed Description
Example 1: as shown in fig. 1, a bearing and releasing device for an aircraft full aircraft drop test comprises a base 1, wherein a quick release mechanism 2 is arranged at the front end of the base 1, two front height adjusting seats 3 and two rear height adjusting seats 4 are arranged at the rear end of the base 1 side by side, a front hinging seat 5 is fixedly connected above the two front height adjusting seats 3, an H-shaped support arm 6 is fixedly connected above the two front hinging seats 5 together, a rear hinging seat 7 is fixedly connected above the two rear height adjusting seats 4 respectively, a vertical support arm 9 is hinged at two sides above an H-shaped crushing rod 8,H-shaped crushing rod 8 respectively, the front ends of the two vertical support arms 9 are hinged at two sides of the top of the H-shaped support arm 6 respectively, an inverted triangle support rod 10 is hinged above the quick release mechanism 2, and two vertex positions above the inverted triangle support rod 10 are hinged at two sides of the top of the H-shaped support arm 6 respectively in a one-to-one correspondence manner;
as shown in fig. 3, the quick release mechanism 2 comprises a release seat 21, an upper sliding chute 22 is arranged on the upper side of the release seat 21, a sliding block 23 is connected in a sliding manner in the upper sliding chute 22, a first air cylinder 24 is arranged on the lower side of the release seat 21, a telescopic end of the first air cylinder 24 is hinged with the sliding block 23, a sliding hinge seat 25 is fixedly connected above the sliding block 23, the upper end of the sliding hinge seat 25 is hinged with the lower end of the inverted triangle support rod 10, the rear end of the sliding block 23 is fixedly connected with a connecting plate 26, the rear end of the connecting plate 26 is hinged with a trigger block 27, and a fixing plate 28 for clamping the trigger block 27 is fixedly connected on the rear side of the release seat 21;
the front side top of fixed plate 28 is equipped with joint groove 281, the below of joint groove 281 is equipped with stopper 282, the rear side of trigger piece 27 is equipped with spacing post 283, the rear side fixedly connected with joint board 271 of trigger piece 27, the below and the stopper 282 joint of joint board 271, the rear side and the spacing post 283 joint of joint board 271, the rear side of fixed plate 28 articulates there is latch hook 284, the upper end and the joint of joint board 271 of latch hook 284, the rear side inner wall fixedly connected with second cylinder 285 of fixed plate 28, the flexible end and the lower extreme of latch hook 284 of second cylinder 285 are connected, fixedly connected with energy storage 11 on the base 1, energy storage 11 is linked together through the trachea with first cylinder 24 and second cylinder 285.
As shown in fig. 4, the latch hook 284 includes a latch hook shaft 2841, the right end of the latch hook shaft 2841 is fixedly connected with the fixing plate 28, the left end of the latch hook shaft 2841 is rotatably connected with a hook body 2842, a hook 2843 is arranged above the hook body 2842, and a hinge mechanism 2844 is fixedly connected below the hook body 2842; the hinge mechanism 2844 includes two side plates 28441, two side plates 28441 are respectively fixedly connected to the left and right sides below the hook 2842, a sliding hole 28442 is respectively arranged below the two side plates 28441, a hinge shaft 28443 is arranged between the two sliding holes 28442, and the telescopic end of the second air cylinder 285 is fixedly connected to the middle of the hinge shaft 28443.
As shown in fig. 5, the clamping plate 271 includes a plate body 2711, a screw rod 2712 is disposed on the front side of the plate body 2711, the plate body 2711 is fixedly connected with the trigger block 27 through the screw rod 2712, a limiting opening 2713 is disposed below the plate body 2711, the limiting opening 2713 is clamped with the limiting block 282, an arc-shaped groove 2714 is disposed on the rear side of the plate body 2711, the arc-shaped groove 2714 is clamped with the limiting post 283, a clamping connector 2715 is disposed below the arc-shaped groove 2714, and the clamping connector 2715 is abutted with the hook 2843.
As shown in fig. 2, two lateral sliding grooves 29 are formed in the release seat 21 in a penetrating manner, a slide plate 291 is provided between the two lateral sliding grooves 29, and the upper sliding groove 22 is located on the upper side of the slide plate 291.
As shown in fig. 6, the front height-adjusting seat 3 and the rear height-adjusting seat 4 each comprise a panel 31, a plurality of heightening blocks 32 are arranged below the panel 31, mounting holes 33 are formed in four corners of the panel 31 and the heightening blocks 32, two screws 34 are arranged in the four mounting holes 33, and the panel 31 and the heightening blocks 32 are in threaded connection with the base 1 by sequentially penetrating the four screws 34 through the mounting holes 33 in the panel 31 and the heightening blocks 32.
The sliding block 23 comprises a sliding rod 231 which is slidably connected inside the upper sliding chute 22, two sides of the sliding rod 231 are rotatably connected with a sliding shell 232, a sliding hinge seat 25 is fixedly connected to the top of the sliding shell 232, and the lower front side of the sliding shell 232 is hinged to the telescopic end of the first cylinder 24.
Example 2: this embodiment differs from embodiment 1 in that a recess 91 for supporting the aircraft body is provided above the vertical arm 9 for connection with the aircraft body.
Example 3: the difference between this embodiment and embodiment 2 is that the front side of the base 1 is fixedly connected with a PLC controller 12, and the PLC controller 12 is electrically connected with the accumulator 11.
The accumulator 11 is conveniently controlled by the PLC controller 12 to supply air to the second cylinder 285 and the first cylinder 24.
Example 4: the embodiment describes a method for using the bearing and releasing device for the full-aircraft drop test of the embodiment 3, which comprises the following steps:
s1, firstly connecting a rear mounting point of an airplane with a vertical support arm 9; during the test, the aircraft is released, so that the aircraft rotates back and forth around the rear mounting point;
s2, when the airplane rotates forwards, the vertical support arm 9 rotates downwards to drive the lower end of the inverted triangle support rod 10 to move to the rear side, further drive the rear end of the sliding block 23 to tilt upwards, further drive the front side of the trigger block 27 to move upwards, and further enable the trigger block 27 to be separated from the fixed plate 28;
s3, the first air cylinder 24 drives the sliding block 23 and the inverted triangle support rod 10 to retract forwards, the vertical support arm 9 is crushed downwards and is separated from the airplane, and the airplane performs free falling motion.
The PLC controller 12, the second air cylinder 285, the accumulator 11, and the first air cylinder 24 used in the above embodiments are commercially available products, so long as the functions of the present invention can be implemented, and those skilled in the art can select and use them according to conventional general knowledge, and are not particularly limited herein.
Claims (5)
1. The bearing and releasing device for the aircraft full aircraft drop test is characterized by comprising a base (1), wherein a quick release mechanism (2) is arranged at the front end of the base (1), two front height adjusting seats (3) and two rear height adjusting seats (4) are arranged at the rear end of the base (1) side by side, a front hinging seat (5) is fixedly connected above the two front height adjusting seats (3) respectively, an H-shaped support arm (6) is hinged on the two front hinging seats (5) together, a rear hinging seat (7) is fixedly connected above the two rear height adjusting seats (4) respectively, an H-shaped crushing rod (8) is hinged on the two rear hinging seats (7) together, a vertical support arm (9) is hinged on two sides above the H-shaped crushing rod (8) respectively, the front ends of the two vertical support arms (9) are hinged on two sides of the top of the H-shaped support arm (6) respectively, a reverse triangular support arm (10) is hinged on the two reverse triangular support arms (2) respectively, and two triangular support arms (10) are hinged on the two sides of the reverse triangular support arm (10) respectively;
the quick release mechanism (2) comprises a release seat (21), an upper sliding groove (22) is formed in the upper side of the release seat (21), a sliding block (23) is connected to the upper sliding groove (22) in a sliding mode, a first air cylinder (24) is arranged on the lower side of the release seat (21), the telescopic end of the first air cylinder (24) is hinged to the sliding block (23), a sliding hinging seat (25) is fixedly connected to the upper side of the sliding block (23), the upper end of the sliding hinging seat (25) is hinged to the lower end of the inverted triangle support rod (10), a connecting plate (26) is fixedly connected to the rear end of the sliding block (23), a trigger block (27) is hinged to the rear end of the connecting plate (26), and a fixing plate (28) used for clamping the trigger block (27) is fixedly connected to the rear side of the release seat (21).
A clamping groove (281) is formed in the upper portion of the front side of the fixing plate (28), a limiting block (282) is arranged below the clamping groove (281), a limiting column (283) is arranged on the rear side of the triggering block (27), the clamping plate (271) is fixedly connected to the rear side of the triggering block (27), the lower portion of the clamping plate (271) is clamped with the limiting column (283), a lock hook (284) is hinged to the rear side of the fixing plate (28), the upper end of the lock hook (284) is clamped with the clamping plate (271), a second cylinder (285) is fixedly connected to the inner wall of the rear side of the fixing plate (28), the telescopic end of the second cylinder (285) is connected with the lower end of the lock hook (284), an energy accumulator (11) is fixedly connected to the base (1), and the energy accumulator (11) is communicated with the first cylinder (24) and the second cylinder (285) through air pipes;
the lock hook (284) comprises a lock hook shaft (2841), the right end of the lock hook shaft (2841) is fixedly connected with the fixed plate (28), the left end of the lock hook shaft (2841) is rotatably connected with a hook body (2842), a hook (2843) is arranged above the hook body (2842), and a hinging mechanism (2844) is fixedly connected below the hook body (2842); the hinging mechanism (2844) comprises two side plates (28441), the two side plates (28441) are respectively and fixedly connected to the left side and the right side below the hook body (2842), a sliding hole (28442) is respectively arranged below the two side plates (28441), a hinging shaft (28443) is arranged between the two sliding holes (28442), and the telescopic end of the second air cylinder (285) is fixedly connected with the middle part of the hinging shaft (28443);
the clamping plate (271) comprises a plate body (2711), a screw rod I (2712) is arranged on the front side of the plate body (2711), the plate body (2711) is fixedly connected with the triggering block (27) through the screw rod I (2712), a limiting opening (2713) is formed in the lower portion of the plate body (2711), the limiting opening (2713) is clamped with the limiting block (282), an arc-shaped groove (2714) is formed in the rear side of the plate body (2711), the arc-shaped groove (2714) is clamped with the limiting post (283), a clamping head (2715) is arranged below the arc-shaped groove (2714), and the clamping head (2715) is abutted with the hook (2843);
a groove (91) for supporting the aircraft body is arranged above the vertical support arm (9);
the sliding block (23) comprises a sliding rod (232) which is connected inside the upper sliding groove (22) in a sliding mode, sliding shells (231) are connected to the two sides of the sliding rod (232) in a rotating mode, the sliding hinge seat (25) is fixedly connected to the top of the sliding shells (231), and the lower portion of the front side of the sliding shells (231) is hinged to the telescopic end of the first air cylinder (24).
2. The bearing and releasing device for the full-aircraft drop test of the aircraft according to claim 1, wherein two transverse sliding grooves (29) are formed in the releasing seat (21) in a front-back penetrating manner, a sliding plate (291) is arranged between the two transverse sliding grooves (29), and the upper sliding groove (22) is located on the upper side of the sliding plate (291).
3. The bearing and releasing device for the aircraft full-aircraft drop test according to claim 1, wherein the front height adjusting seat (3) and the rear height adjusting seat (4) comprise a panel (31), a plurality of heightening blocks (32) are arranged below the panel (31), mounting holes (33) are formed in four corners of the panel (31) and the heightening blocks (32), two screws (34) are arranged in the four mounting holes (33), and the panel (31) and the heightening blocks (32) are connected with the base (1) in a threaded manner through the four two screws (34) sequentially penetrating through the mounting holes (33) in the panel (31) and the heightening blocks (32).
4. The bearing and releasing device for the full-aircraft drop test of the aircraft according to claim 1, wherein a PLC (programmable logic controller) 12 is fixedly connected to the front side of the base (1), and the PLC 12 is electrically connected with the energy accumulator (11).
5. A method of using a load release device for a full aircraft drop test as defined in any one of claims 1 to 4, comprising the steps of:
s1, firstly connecting a rear mounting point of an airplane with the vertical support arm (9); during the test, the aircraft is released, so that the aircraft rotates back and forth around the rear mounting point;
s2, when the airplane rotates forwards, the vertical support arm (9) rotates downwards to drive the lower end of the inverted triangle support rod (10) to move to the rear side, further drive the rear end of the sliding block (23) to tilt upwards, further drive the front side of the trigger block (27) to move upwards, and further enable the trigger block (27) to be separated from the fixed plate (28);
s3, the first air cylinder (24) drives the sliding block (23) and the inverted triangle support rod (10) to withdraw forwards, the vertical support arm (9) is crushed downwards and is separated from the airplane, and the airplane performs free falling movement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311412375.4A CN117141743B (en) | 2023-10-30 | 2023-10-30 | Bearing and releasing device for full-aircraft drop test of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311412375.4A CN117141743B (en) | 2023-10-30 | 2023-10-30 | Bearing and releasing device for full-aircraft drop test of aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN117141743A CN117141743A (en) | 2023-12-01 |
| CN117141743B true CN117141743B (en) | 2024-01-16 |
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| CN202311412375.4A Active CN117141743B (en) | 2023-10-30 | 2023-10-30 | Bearing and releasing device for full-aircraft drop test of aircraft |
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