CN112229611B - Aircraft guide rail emitter testing arrangement - Google Patents
Aircraft guide rail emitter testing arrangement Download PDFInfo
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- CN112229611B CN112229611B CN202010877187.9A CN202010877187A CN112229611B CN 112229611 B CN112229611 B CN 112229611B CN 202010877187 A CN202010877187 A CN 202010877187A CN 112229611 B CN112229611 B CN 112229611B
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- guide rail
- frame
- launching device
- rail launching
- steel wire
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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
- G01M13/00—Testing of machine parts
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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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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention relates to a test device for an aircraft guide rail launching device, which comprises a frame, wherein a plurality of sliding rods which are distributed in parallel along the length direction of the frame are arranged on the frame; the frame is provided with a detection device which is connected with the simulated missile and used for pulling the working state of the simulated missile guide rail launching device, and the frame is also provided with an anti-falling mechanism for preventing the simulated missile from falling off the guide rail launching device. According to the invention, the unlocking force and the locking force of the guide rail launching device are detected by matching the hydraulic cylinder, the steel wire rope and the tension sensor, the traditional manual pump pressing is replaced, the labor intensity of workers is reduced, the detection accuracy is improved, the test efficiency of the guide rail launching device is improved, the operation is simple and convenient, the cost is low, and the repair quality of the guide rail launching device product is effectively improved.
Description
Technical Field
The invention relates to airplane part detection equipment, in particular to a testing device for an airplane guide rail launching device.
Background
The airplane guide rail launching device is a device for restraining the guided missile to move along the course and safely releasing when the guided missile is launched. In the process of hanging, taking off and landing of the guided missile, the guide rail launching device can reliably restrict the longitudinal movement of the guided missile and prevent the guided missile from falling off accidentally; when the missile is launched, the guide rail launching device lock stopper can be reliably unlocked and safely release the missile when the thrust of the missile engine reaches the unlocking force; the unlocking force and the locking force of the locking device of the guide rail launching device are important indexes for ensuring safe separation of missile launching, and the unlocking force and the locking force need to be accurately checked and strictly controlled in the production and repair processes of the guide rail launching device.
The existing common technology adopts a card elasticity dynamometer for measurement, can measure the unlocking force and the locking force of a lock of a guide rail launching device in the horizontal direction, is limited by a measurement space, cannot be provided with a simulated missile during measurement of the card elasticity, and cannot truly simulate the use state of an airplane guide rail launching device when the missile is suspended; the existing customization equipment is limited by equipment space, a simulated missile bomb weighing 300kg needs to be hung on a guide rail launching device by manpower in the test process, a manual pump is adopted for pressurization to drive a loading oil cylinder to retract and tension a steel wire rope, the guide rail launching device is loaded in the horizontal direction, the unlocking force and the locking force are displayed by a digital pressure gauge, the operation process is complicated, the simulated missile is heavy, certain danger exists by means of traditional manpower installation, the working time of multiple persons is consumed, and the overall working efficiency is low.
Disclosure of Invention
In order to solve the technical problem, the invention provides a testing device for an aircraft guide rail launching device. The technical problem to be solved by the invention is realized by adopting the following technical scheme:
a test device for an aircraft guide rail launching device comprises a frame, wherein a plurality of sliding rods are arranged on the frame and distributed in parallel along the length direction of the frame, movable hanging plates for hanging the guide rail launching device are arranged on the sliding rods, and simulated missiles matched with the guide rail launching device are distributed below the movable hanging plates;
the frame is provided with a detection device which is connected with the simulated missile and used for pulling the simulated missile to simulate the working state of the guide rail launching device, and the frame is also provided with an anti-drop mechanism for preventing the simulated missile from being separated from the guide rail launching device.
The movable hanging plate comprises a supporting beam, a ball guide sleeve matched with a corresponding sliding rod to fix the position of the guide rail launching device is arranged on the upper end face of the supporting beam, and a hanging plate for hanging the guide rail launching device is arranged on the lower end face of the supporting beam.
The detection device comprises a hydraulic cylinder installed on the frame, the hydraulic cylinder is connected with a steel wire rope, and the steel wire rope is connected with a tension sensor which is connected with the simulated missile to detect the unlocking force and the locking force of the guide rail launching device.
And the frame is provided with an adjusting mechanism for adjusting the height of the steel wire rope to adapt to different guide rail launching devices.
The adjusting mechanism comprises a fixed pulley which is arranged on the frame and used for changing the direction of the steel wire rope, the fixed pulley is connected with a screw rod which is slidably arranged on the frame, a nut which is in threaded fit with the screw rod and used for driving the screw rod to lift is arranged on the frame, and a limit screw which is used for guaranteeing the screw rod to lift vertically is arranged on the frame.
The anti-falling mechanism is an anti-falling steel wire rope which is connected with the simulated missile and is in a relaxed state when the simulated missile is not under tension.
And a key groove matched with the limit screw is arranged on the screw rod.
The beneficial effects of the invention are: according to the invention, the unlocking force and the locking force of the guide rail launching device are detected by matching the hydraulic cylinder, the steel wire rope and the tension sensor, the traditional manual pump is replaced for pressurizing, the labor intensity of workers is reduced, the detection accuracy is improved, the test efficiency of the guide rail launching device is improved, the operation is simple and convenient, the cost is low, and the repair quality of the guide rail launching device product is effectively improved;
the fixed pulleys are driven by the screw to lift and adapt to guide rail launching devices of different models, the fixed pulleys of different models do not need to be disassembled and assembled to meet the testing requirements, the detection steps are reduced, and the detection efficiency is improved.
Drawings
The invention is further illustrated by the following examples in conjunction with the drawings.
FIG. 1 is a front view of the present invention;
FIG. 2 is a schematic top view of the present invention;
FIG. 3 is a schematic view of the structure of the hanging plate of the present invention;
FIG. 4 is a first schematic structural diagram of an adjusting mechanism according to the present invention;
FIG. 5 is a second schematic structural diagram of an adjusting mechanism according to the present invention;
FIG. 6 is an enlarged view of I of FIG. 4 of the present invention;
FIG. 7 is a schematic diagram of the structure of a simulated missile according to the invention.
Detailed Description
In order to make those skilled in the art better understand the technical solution of the present invention, the present invention will be described more clearly and more completely with reference to the drawings in the following embodiments, and it is understood that the described embodiments are only a part of the present invention, rather than all of the present invention, and based on the embodiments, other embodiments obtained by those skilled in the art without inventive exercise are within the protection scope of the present invention.
As shown in fig. 1 to 7, a testing device for an aircraft guide rail launching device comprises a frame 1, wherein a plurality of sliding rods 2 which are distributed in parallel along the length direction of the frame 1 are arranged on the frame 1, movable hanging plates 3 for hanging the guide rail launching device are arranged on the sliding rods 2, and simulated missiles 4 which are matched with the guide rail launching device are distributed below the movable hanging plates 3; a display screen 7 is arranged on the frame 1; the simulated missile 4 is connected with the guide rail launching device;
the frame 1 is provided with a detection device 5 which is connected with the simulated missile 4 and used for pulling the simulated missile 4 to simulate the working state of the guide rail launching device, and the frame 1 is also provided with an anti-falling mechanism 6 for preventing the simulated missile 4 from falling off the guide rail launching device; and a lifting vehicle 8 for assisting the installation of the simulated missile 4 is arranged below the sliding rod 2.
The movable hanging plate 3 comprises a supporting beam 31, the upper end face of the supporting beam 31 is provided with a ball guide sleeve 32 which is matched with the corresponding sliding rod 2 to fix the position of the guide rail launching device, and the lower end face of the supporting beam 31 is provided with a hanging plate 33 for hanging the guide rail launching device; through set up different hanging points on link plate 33, the guide rail emitter of adaptable different models need not to customize a plurality of activity link plates 3, reduces manufacturing cost.
The detection device 5 comprises a hydraulic cylinder 51 arranged on the frame 1, the hydraulic cylinder 51 is connected with a steel wire rope 52, and the steel wire rope 52 is connected with a tension sensor 53 which is connected with the simulated missile 4 to detect the unlocking force and the locking force of the guide rail launching device; the hydraulic cylinder 51 pulls the steel wire rope 52, so that the steel wire rope 52 pulls the simulated missile 4 and the guide rail launching device, and the unlocking force and the locking force of the guide rail launching device are detected through the tension sensor 53.
An adjusting mechanism 54 for adjusting the height of the steel wire rope 52 to adapt to different guide rail launching devices is arranged on the frame 1; because the heights of the guide rail launching devices of different models are different, if the heights of the guide rail launching devices are not adjusted, the search for the opening locking force and the locking force by the tension sensor 53 is not accurate.
The adjusting mechanism 54 comprises a fixed pulley 541 which is installed on the frame 1 to change the direction of the steel wire rope 52, the fixed pulley 541 is connected with a screw 542 which is installed on the frame 1 in a sliding manner, the frame 1 is provided with a nut 543 which is in threaded fit with the screw 542 to drive the screw 542 to lift, and the frame 1 is provided with a limit screw 544 which ensures that the screw 542 lifts vertically; the fixed pulley 541 changes the direction of the steel wire rope 52, so that the hydraulic cylinder 51 is reasonable in layout, and the occupied space is reduced; the nut 543 is connected with a thrust ball bearing 545, and a turning handle 546 is arranged on the nut 543.
A key groove 542a matched with the limit screw 544 is formed in the screw 542; the frame 1 is provided with an upper bracket 1b which is arranged on a lower bracket 1a of the fixed pulley 541 and an installation screw 542, the lower bracket 1a is provided with a chute 1c, and the fixed pulley 541 is arranged in the chute 1c through a bolt; the thrust ball bearing 545 prevents interference when the nut 543 is rotated, the thrust ball bearing 545 is fixed on the upper bracket 1b, and the screw 542 penetrates through the upper bracket 1b; the handle 546 is rotated to drive the nut 543 to be in threaded fit with the screw 542, and the screw 542 is driven to ascend and descend, so that the height of the fixed pulley 541 is changed to adapt to guide rail launching devices of different models.
The anti-falling mechanism 6 is an anti-falling steel wire rope 61 which is connected with the simulated missile 4 and is in a relaxed state when the simulated missile 4 is not under tension; the simulated missile 4 is provided with a front suspension point 4a and a rear suspension point 4b; the steel wire rope 52 is connected with the front suspension point 4a, and the anti-drop steel wire rope 61 is connected with the rear suspension point 4b; in the process of pulling the simulated missile 4 by the steel wire rope 52, the simulated missile 4 and the guide rail launching device can displace, the anti-drop steel wire rope 61 is gradually tightened, and finally the simulated missile 4 is in a straightening state to limit the displacement of the simulated missile 4, so that the simulated missile 4 is prevented from separating from the guide rail launching device, and the safety and reliability of the test process of the guide rail launching device are ensured.
In the invention, when the guide rail launching device needs to be detected, the first step is as follows: the guide rail launching device is driven to ascend through the lifting car 8, the guide rail launching device is fixed on the guide rail launching device, then the simulated missile 4 is driven to ascend through the lifting car 8 again, the simulated missile 4 is fixed on the guide rail launching device, the steel wire rope 52 is connected with the front suspension point 4a on the simulated missile 4, and the anti-falling steel wire rope 61 is connected with the rear suspension point 4b on the simulated missile 4;
the second step is that: the handle 546 is rotated to drive the nut 543 to be in threaded fit with the screw 542, and the screw 542 is driven to ascend and descend, so that the height of the fixed pulley 541 is changed to be matched with the guide rail launching device of the detected model;
the third step: and starting the hydraulic cylinder 51, pulling the steel wire rope 52, reading the tension value of the tension sensor 53, and detecting the unlocking force and the locking force of the guide rail launching device.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are merely illustrative of the principles of the invention, but that various changes and modifications may be made without departing from the spirit and scope of the invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (2)
1. An aircraft guide rail launcher testing arrangement, includes frame (1), its characterized in that: a plurality of sliding rods (2) which are distributed in parallel along the length direction of the frame (1) are arranged on the frame (1), movable hanging plates (3) for hanging guide rail launching devices are arranged on the sliding rods (2), and simulated missiles (4) matched with the guide rail launching devices are distributed below the movable hanging plates (3);
the frame (1) is provided with a detection device (5) which is connected with the simulated missile (4) and used for pulling the simulated missile (4) to simulate the working state of the guide rail launching device, and the frame (1) is also provided with an anti-falling mechanism (6) for preventing the simulated missile (4) from falling off the guide rail launching device;
the detection device (5) comprises a hydraulic cylinder (51) arranged on the frame (1), the hydraulic cylinder (51) is connected with a steel wire rope (52), and the steel wire rope (52) is connected with a tension sensor (53) which is connected with the simulated missile (4) to detect the unlocking force and the locking force of the guide rail launching device;
the anti-falling mechanism (6) is an anti-falling steel wire rope (61) which is connected with the simulated missile (4) and is in a relaxed state when the simulated missile (4) is not subjected to tension;
the frame (1) is provided with an adjusting mechanism (54) for adjusting the height of the steel wire rope (52) to adapt to different guide rail launching devices;
the adjusting mechanism (54) comprises a fixed pulley (541) which is arranged on the frame (1) to change the direction of the steel wire rope (52), the fixed pulley (541) is connected with a screw rod (542) which is slidably arranged on the frame (1), the frame (1) is provided with a nut (543) which is in threaded fit with the screw rod (542) and drives the screw rod (542) to lift, and the frame (1) is provided with a limit screw (544) which ensures that the screw rod (542) vertically lifts;
and a key groove (542 a) matched with the limit screw (544) is arranged on the screw rod (542).
2. An aircraft guide rail launching device testing device as defined in claim 1, wherein: the movable hanging plate (3) comprises a supporting beam (31), a ball guide sleeve (32) matched with the corresponding sliding rod (2) to fix the position of the guide rail launching device is arranged on the upper end face of the supporting beam (31), and a hanging plate (33) for hanging the guide rail launching device is arranged on the lower end face of the supporting beam (31).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010877187.9A CN112229611B (en) | 2020-08-27 | 2020-08-27 | Aircraft guide rail emitter testing arrangement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010877187.9A CN112229611B (en) | 2020-08-27 | 2020-08-27 | Aircraft guide rail emitter testing arrangement |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112229611A CN112229611A (en) | 2021-01-15 |
| CN112229611B true CN112229611B (en) | 2023-03-31 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010877187.9A Active CN112229611B (en) | 2020-08-27 | 2020-08-27 | Aircraft guide rail emitter testing arrangement |
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| CN (1) | CN112229611B (en) |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5591031A (en) * | 1994-05-31 | 1997-01-07 | Hughes Electronics | Missile simulator apparatus |
| CN103644995B (en) * | 2013-12-20 | 2015-11-18 | 中国航天空气动力技术研究院 | The surface installation of test unlocking force |
| CN109489925A (en) * | 2017-09-12 | 2019-03-19 | 江西洪都航空工业集团有限责任公司 | A kind of device reducing guided missile transverse acceleration in firing mount combination vibration test |
| CN208155161U (en) * | 2018-04-26 | 2018-11-27 | 西安庆安航空试验设备有限责任公司 | For detecting the load testing machine of missile launcher unlocking force |
| CN110065647B (en) * | 2019-04-25 | 2024-05-14 | 沈阳飞研航空设备有限公司 | Lifting adjustment platform in intelligent electric bullet hanging vehicle |
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2020
- 2020-08-27 CN CN202010877187.9A patent/CN112229611B/en active Active
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| CN112229611A (en) | 2021-01-15 |
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