CN110697078B - Undercarriage ejection rod retraction performance testing machine - Google Patents
Undercarriage ejection rod retraction performance testing machine Download PDFInfo
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- CN110697078B CN110697078B CN201911039974.XA CN201911039974A CN110697078B CN 110697078 B CN110697078 B CN 110697078B CN 201911039974 A CN201911039974 A CN 201911039974A CN 110697078 B CN110697078 B CN 110697078B
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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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Abstract
The invention provides a retraction performance testing machine for an undercarriage ejection rod, which comprises an undercarriage component, a testing frame component and a performance testing component, wherein the testing frame component comprises a C-shaped testing frame, a rectangular sleeve cup, a proximity switch, an upright post and a guide rod, the C-shaped testing frame is fixedly connected with a concrete foundation, the rectangular sleeve cup is formed by welding a cup wall plate and a bottom plate, the bottom plate of the rectangular sleeve cup faces upwards, and vertical cylindrical through holes are respectively arranged in the center and four top angles of the bottom plate of the rectangular sleeve cup. The performance testing assembly comprises an impact-proof base plate, a rectangular lifting platform, a pulling pressure sensor, an air cylinder and a connecting shaft, wherein a first end face of the pulling pressure sensor is fixedly connected with the upper end of an air cylinder piston rod, a second end face of the pulling pressure sensor is fixedly connected with a first end face of the connecting shaft, a second end face of the connecting shaft is fixedly connected with the lower surface of the rectangular lifting platform, and the impact-proof base plate is fixedly connected with the upper surface of the rectangular lifting platform. The invention improves the detection precision of the retraction time, lightens the labor intensity of workers and obtains experimental data more fitting to the reality.
Description
Technical Field
The invention relates to the technical field of design and development of performance test devices, in particular to a retraction performance testing machine for an undercarriage ejection rod.
Background
The landing gear ejection rod component is one of the ship-based aircraft key components, and the working performance, reliability and stability of the landing gear ejection rod component are directly related to the flight safety of the ship-based aircraft. Therefore, the retraction performance of the landing gear ejection rod must be subjected to ground test before the loading machine.
In the past, the retraction performance test of the ejection rod of the undercarriage is mostly carried out by adopting a mode of a spring scale and a pull line sensor, and the defects are as follows: 1) low detection precision of the retraction time, 2) inaccurate force control.
Disclosure of Invention
Aiming at the problems of the traditional retraction performance testing machine, the invention provides the retraction performance testing machine for the ejection rod of the undercarriage, which is mainly used for improving the detection precision of retraction time, reducing the labor intensity of workers and obtaining more practical experimental data.
The utility model provides an undercarriage ejection rod retraction performance testing machine, its includes undercarriage subassembly, test rack subassembly and capability test subassembly, the undercarriage subassembly, it includes undercarriage body, undercarriage buffering pillar, buffering pillar piston rod, ejection rod pivot, ejection rod support and ejection rod, the lower fixed surface of the entablature of undercarriage subassembly and C font test shape frame is connected, the undercarriage body with undercarriage buffering pillar fixed connection, undercarriage buffering pillar is equipped with plumbous vertical central hole, the central hole of undercarriage buffering pillar with buffering pillar piston rod connects, the lower extreme of buffering pillar piston rod with the first end fixed connection of ejection rod support, the ejection rod passes through the ejection rod pivot with the second end connection of ejection rod support. The test rack assembly comprises a C-shaped test rack, a rectangular sleeve cup, a proximity switch, a stand column, a first guide rod, a second guide rod, a third guide rod, a fourth guide rod, a pneumatic system and an electric control system, wherein the C-shaped test rack is formed by welding an upper cross beam, a lower cross beam and the stand column, the C-shaped test rack is fixedly connected with a concrete foundation, the rectangular sleeve cup is formed by welding a cup wall plate and a bottom plate, the bottom plate of the rectangular sleeve cup faces upwards, vertical cylindrical through holes are formed in the center and four top corners of the bottom plate of the rectangular sleeve cup respectively, and one end of the cup wall plate of the rectangular sleeve cup is fixedly connected with the upper surface of the lower cross beam of the C-shaped test rack. The performance testing assembly comprises an impact-proof base plate, a rectangular lifting platform, a pulling pressure sensor, an air cylinder piston rod, a displacement sensor, an air cylinder and a connecting shaft, wherein the air cylinder piston rod is connected with a central cylindrical through hole of the rectangular sleeve cup bottom plate, the air cylinder piston rod is suspended from the upper side and the lower side of the rectangular sleeve cup bottom plate, and the air cylinder piston rod is connected with the air cylinder.
Preferably, in the test rack assembly, the first guide rod, the second guide rod, the third guide rod and the fourth guide rod are in clearance fit with cylindrical through holes at four top corners of the rectangular sleeve cup bottom plate respectively and are suspended from the upper side and the lower side of the rectangular sleeve cup bottom plate, the upper end faces of the first guide rod, the second guide rod, the third guide rod and the fourth guide rod are fixedly connected with the lower surface of the rectangular lifting platform respectively, the stand column is fixedly connected with the outer side face of the rectangular sleeve cup, the proximity switch is fixedly connected with the upper end portion of the stand column, and the pneumatic system and the electric control system are both mounted on the ground.
Preferably, in the performance test subassembly, the upper end of cylinder piston rod with draw pressure sensor's first terminal surface fixed connection, draw pressure sensor's second terminal surface with the first terminal surface fixed connection of spiale, the second terminal surface of spiale with the central authorities fixed connection of rectangle lift platform's lower surface, the cylinder with the last fixed surface of the lower beam of the experimental shape frame of C font is connected, displacement sensor is located the inside of cylinder body, the lower surface of protecting against shock backing plate with rectangle lift platform's last fixed surface connects.
Preferably, the diameter of the cylindrical through hole in the center of the rectangular sleeve cup bottom plate is greater than the diameter of the cylinder piston rod, the diameters of the cylindrical through holes on the four top corners of the rectangular sleeve cup bottom plate are equal, and the diameters of the cylindrical through holes on the four top corners of the rectangular sleeve cup bottom plate are respectively greater than the diameters of the first guide rod, the second guide rod, the third guide rod and the fourth guide rod.
Preferably, the spiale, the protecting against shock backing plate rectangle lift platform draw pressure sensor cylinder piston rod, displacement sensor with the axle center of cylinder is on same straight line, the axis of first guide bar, second guide bar, third guide bar and the fourth guide bar is parallel to each other.
Preferably, the proximity switch and the pull pressure sensor are respectively connected with the electronic control system through electric wires, and the air cylinder is connected with the pneumatic system through a pipeline and a pneumatic valve.
Preferably, the proximity switch is located at a position just capable of detecting an initial state when the ejection rod rotates counterclockwise around the ejection rod rotating shaft from an upper limit position, and the proximity switch rapidly sends an electric signal to the electronic control system when the ejection rod is just displaced in a rotating manner.
Compared with the prior art, the invention has the following advantages:
according to the invention, after a mode of adding a pull line sensor to a spring scale is omitted, the loading accuracy and the detection accuracy of the retraction performance test of the undercarriage ejection rod are higher, and finally, the test result is more accurate and close to reality, and a guarantee basis is provided for other subsequent simulation experiments. Compared with the prior experiment, the invention can realize the real-time display and storage of data, provide the failure back-check data, improve the structural design precision of the undercarriage ejection rod, ensure that the undercarriage ejection rod can better meet the actual use requirement, and simultaneously reduce the labor intensity of workers. The invention has the characteristics of reasonable structure, wide application, low manufacturing cost, stable performance, simple and convenient installation and loading implementation and the like, and is suitable for the return performance test of the nose landing gear of different types and models of warplanes.
Drawings
FIG. 1 is a front view of the overall structure of the landing gear ejection rod retraction tester of the present invention;
FIG. 2 is a schematic cross-sectional structure view in the A-A direction of the undercarriage ejection rod retraction performance testing machine of the present invention; and
FIG. 3 is a schematic cross-sectional structure view in the direction B-B of the undercarriage ejection rod retraction performance testing machine of the present invention.
The main reference numbers:
the device comprises a C-shaped test rack 1, an undercarriage buffer support 2, a buffer support piston rod 3, an ejection rod rotating shaft 4, an ejection rod support 5, an ejection rod 6, an impact-proof base plate 7, a rectangular lifting platform 8, a pulling pressure sensor 9, an air cylinder piston rod 10, a displacement sensor 11, an air cylinder 12, a rectangular sleeve cup 13, a proximity switch 14, an upright post 15, a connecting shaft 16, a first guide rod 17, a second guide rod 18, a third guide rod 19, a fourth guide rod 20, a pneumatic system 21 and an electric control system 22.
Detailed Description
The technical contents, structural features, attained objects and effects of the present invention are explained in detail below with reference to the accompanying drawings.
A landing gear ejection rod retraction performance testing machine is shown in figure 1 and comprises a landing gear assembly, a test frame assembly and a performance testing assembly.
The landing gear assembly, as shown in figures 1 and 2, comprises a landing gear body, a landing gear buffer strut 2, a buffer strut piston rod 3, eject pole pivot 4, eject pole support 5 and eject pole 6, the lower fixed surface connection of the entablature of landing gear subassembly and the experimental shape frame of C font 1, landing gear body and landing gear buffering pillar 2 fixed connection, landing gear buffering pillar 2 is equipped with plumbous vertical central hole, landing gear buffering pillar 2's central hole and buffering pillar piston rod 3 are connected, can make relative axial displacement and relative rotation between buffering pillar piston rod 3 and the landing gear buffering pillar 2, the lower extreme of buffering pillar piston rod 3 and the first end fixed connection of eject pole support 5, eject pole 6 holds the connection through the second of ejecting pole pivot 4 and eject pole support 5, eject pole 6 accessible eject pole pivot 4 rotates around eject pole support 5.
The test rack assembly, as shown in fig. 1 and 2, comprises a C-shaped test rack 1, a rectangular sleeve cup 13, a proximity switch 14, a column 15, a first guide rod 17, a second guide rod 18, a third guide rod 19, a fourth guide rod 20, a pneumatic system 21 and an electric control system 22. The C-shaped test frame 1 is formed by welding an upper cross beam, a lower cross beam and a stand column, the C-shaped test frame 1 is fixedly connected with a concrete foundation, a rectangular sleeve cup 13 is formed by welding a cup wall plate and a bottom plate, the bottom plate of the rectangular sleeve cup 13 faces upwards, a vertical cylindrical through hole is formed in the center and four top angles of the bottom plate of the rectangular sleeve cup 13 respectively, and one end of the cup wall plate of the rectangular sleeve cup 13 is fixedly connected with the upper surface of the lower cross beam of the C-shaped test frame 1.
The performance testing assembly, as shown in fig. 1 and fig. 3, includes an impact-proof pad 7, a rectangular lifting platform 8, a pull pressure sensor 9, a cylinder piston rod 10, a displacement sensor 11, a cylinder 12 and a spindle 16. The cylinder piston rod 10 is connected with a central cylindrical through hole of a bottom plate of the rectangular sleeve cup 13, the cylinder piston rod 10 is suspended from the upper side and the lower side of the bottom plate of the rectangular sleeve cup 13, and the cylinder piston rod 10 is connected with the cylinder 12.
As shown in fig. 2, the upper end of the cylinder piston rod 10 is fixedly connected with the first end face of the pulling pressure sensor 9, the second end face of the pulling pressure sensor 9 is fixedly connected with the first end face of the connecting shaft 16, the second end face of the connecting shaft 16 is fixedly connected with the center of the lower surface of the rectangular lifting platform 8, the cylinder 12 is fixedly connected with the upper surface of the lower cross beam of the C-shaped test frame 1, the displacement sensor 11 is located inside the cylinder body and used for detecting the vertical displacement of the cylinder piston rod 10 relative to the cylinder 12, and the lower surface of the impact-proof cushion plate 7 is fixedly connected with the upper surface of the rectangular lifting platform 8.
As shown in fig. 1, the cylinder 12 is a plunger cylinder, the rod chamber is directly connected to the atmosphere, and the rodless chamber is connected to the pneumatic system 21 through a pipeline and a pneumatic valve. When the cylinder piston rod 10 is required to ascend, the pneumatic system 21 inputs compressed air to a rodless cavity of the cylinder 12 through a pipeline to push the cylinder piston rod 10 to ascend; when the cylinder piston rod 10 is required to descend, the pneumatic system 21 enables the rodless cavity of the cylinder 12 to be communicated with the atmosphere through the pneumatic valve, and the cylinder piston rod 10 descends under the action of the gravity of the cylinder piston rod 10 and all components fixedly connected with the cylinder piston rod.
The diameter of the cylindrical through hole in the center of the bottom plate of the rectangular sleeve cup 13 is larger than that of the cylinder piston rod 10, the diameters of the cylindrical through holes in the four top corners of the bottom plate of the rectangular sleeve cup 13 are equal, and the diameters of the cylindrical through holes in the four top corners of the bottom plate of the rectangular sleeve cup 13 are respectively larger than those of the first guide rod 17, the second guide rod 18, the third guide rod 19 and the fourth guide rod 20.
The axes of the connecting shaft 16, the impact-proof base plate 7, the rectangular lifting platform 8, the pulling pressure sensor 9, the cylinder piston rod 10, the displacement sensor 11 and the cylinder 12 are on the same straight line, and the axes of the first guide rod 17, the second guide rod 18, the third guide rod 19 and the fourth guide rod 20 are parallel to each other.
The proximity switch 14 and the pull pressure sensor 9 are respectively connected with the electric control system 21 through electric wires, the air cylinder 12 is connected with the pneumatic system 21 through a pipeline and a pneumatic valve, and detection data of the proximity switch 14 and the pull pressure sensor 9 can be displayed on a display screen of the electric control system 22 in real time and recorded and stored in real time.
The proximity switch 14 is located at a position just capable of detecting the initial state when the ejection rod 6 rotates counterclockwise around the ejection rod rotation shaft 4 from the upper limit position, and the proximity switch 14 rapidly sends an electric signal to the electronic control system 22 when the ejection rod 6 is just displaced rotationally.
The return performance test device for the nose landing gear of the fighter plane is further described by combining the following embodiments:
firstly, placing a testing machine in an initial state, namely that the rectangular lifting platform 8 is at a lower limit position, and the ejection rod 6 is at an upper limit position; then, the electric control system 22 is electrified, the electric control system 22 sends an instruction, the pneumatic system 21 is controlled to drive the cylinder piston rod 10 in the cylinder 12 to move upwards, the rectangular lifting platform 8 and the impact-proof base plate 7 are pushed to reach a working position together through the pull pressure sensor 9 and the connecting shaft 16 which are connected with the pneumatic system, the working position is the relative position of the flight deck of the simulated aircraft carrier, and whether the working position is reached is detected through the displacement sensor 11; during this movement, the first guide rod 17, the second guide rod 18, the third guide rod 19, and the fourth guide rod 20 perform movement guidance.
After the predetermined position is reached, the cylinder rod 10 and all components attached thereto are held stationary in this position by the pneumatic lock of the pneumatic system 21. The ejection rod 6 rotates anticlockwise around the ejection rod rotating shaft 4, the action is driven by other driving mechanisms, and the time point when the ejection rod 6 starts to rotate can be detected through an electronic control system 22 connected with the proximity switch 14; when the ejection rod 6 rotates to the point where the end part of the ejection rod contacts with the impact-proof base plate 7, the rectangular lifting platform 8 and all components fixedly connected with the rectangular lifting platform move downwards together under the action of impact load, and the electric control system 22 can detect the time point when the end part of the ejection rod 6 collides with the impact-proof base plate 7 through the displacement sensor 11.
In the process, because the amount of gas compression is limited, the cylinder piston rod 10 and the component fixedly connected with the cylinder piston rod only descend for a limited distance, and the difference between the time point when the end part of the ejection rod 6 collides with the impact-proof cushion plate 7 and the time point when the ejection rod 6 starts to rotate is the ejection time of the ejection rod 6.
After the whole system is stable, namely all components do not move any more, the electric control system 22 sends an instruction to control the pneumatic system 21 to drive the piston rod 10 of the air cylinder to slowly move upwards at a constant speed, the rectangular lifting platform 8 and the impact-resistant backing plate 7 are pushed to move upwards together through the pulling pressure sensor 9 and the connecting shaft 16 which are connected with the pneumatic system, so that the ejection rod 6 is pushed to rotate clockwise, and the sum of the maximum value detected by the pulling pressure sensor 9 and the weight of the rectangular lifting platform 8, the impact-resistant backing plate 7, the connecting shaft 16, the first guide rod 17, the second guide rod 18, the third guide rod 19 and the fourth guide rod 20 is the stable force of the ejection rod 6 contacting with the aircraft carrier deck. The electronic control system 22 displays and records the detection values of the above items in real time during the experiment process.
The above-mentioned embodiments are merely illustrative of the preferred embodiments of the present invention, and do not limit the scope of the present invention, and various modifications and improvements made to the technical solution of the present invention by those skilled in the art without departing from the spirit of the present invention shall fall within the protection scope defined by the claims of the present invention.
Claims (5)
1. The utility model provides an undercarriage ejection rod retraction performance testing machine, its includes undercarriage subassembly, test rack subassembly and capability test subassembly, the undercarriage subassembly, it includes undercarriage body, undercarriage buffering pillar, buffering pillar piston rod, ejection rod pivot, ejection rod support and ejection rod, the lower fixed surface of the entablature of undercarriage subassembly and C font test shape frame is connected, the undercarriage body with undercarriage buffering pillar fixed connection, undercarriage buffering pillar is equipped with plumbous vertical central hole, the central hole of undercarriage buffering pillar with buffering pillar piston rod connects, the lower extreme of buffering pillar piston rod with the first end fixed connection of ejection rod support, the ejection rod passes through the ejection rod pivot with the second end connection of ejection rod support, its characterized in that, it possesses:
the test frame assembly comprises a C-shaped test frame, a rectangular sleeve cup, a proximity switch, a stand column, a first guide rod, a second guide rod, a third guide rod, a fourth guide rod, a pneumatic system and an electric control system, wherein the C-shaped test frame is formed by welding an upper cross beam, a lower cross beam and the stand column;
the performance testing assembly comprises an impact-proof base plate, a rectangular lifting platform, a pulling pressure sensor, an air cylinder piston rod, a displacement sensor, an air cylinder and a connecting shaft, wherein the air cylinder piston rod is connected with a central cylindrical through hole of the rectangular sleeve cup bottom plate, the air cylinder piston rod is suspended from the upper side and the lower side of the rectangular sleeve cup bottom plate, and the air cylinder piston rod is connected with the air cylinder;
in the test frame assembly, the first guide rod, the second guide rod, the third guide rod and the fourth guide rod are in clearance fit with cylindrical through holes at four top corners of the rectangular sleeve cup bottom plate respectively and are suspended from the upper side and the lower side of the rectangular sleeve cup bottom plate respectively, the upper end surfaces of the first guide rod, the second guide rod, the third guide rod and the fourth guide rod are fixedly connected with the lower surface of the rectangular lifting platform respectively, the stand column is fixedly connected with one outer side surface of the rectangular sleeve cup, the proximity switch is fixedly connected with the upper end part of the stand column, and the pneumatic system and the electric control system are both installed on the ground;
among the capability test subassembly, the upper end of cylinder piston rod with draw pressure sensor's first terminal surface fixed connection, draw pressure sensor's second terminal surface with the first terminal surface fixed connection of spiale, the second terminal surface of spiale with the central authorities fixed connection of rectangle lift platform's lower surface, the cylinder with the last fixed surface of the bottom end rail of the experimental shape frame of C font is connected, displacement sensor is located cylinder body's inside, the lower surface of protecting against shock backing plate with rectangle lift platform's last fixed surface is connected.
2. The landing gear ejection rod retraction performance testing machine according to claim 1, wherein the diameter of the cylindrical through hole in the center of the rectangular sleeve cup bottom plate is larger than the diameter of the cylinder piston rod, the diameters of the cylindrical through holes in four top corners of the rectangular sleeve cup bottom plate are equal, and the diameters of the cylindrical through holes in the four top corners of the rectangular sleeve cup bottom plate are respectively larger than the diameters of the first guide rod, the second guide rod, the third guide rod and the fourth guide rod.
3. The landing gear ejection rod retraction performance testing machine according to claim 1, wherein the spindle, the impact prevention base plate, the rectangular lifting platform, the tension and pressure sensor, the cylinder piston rod, the displacement sensor and the cylinder have axes on the same straight line, and axes of the first guide rod, the second guide rod, the third guide rod and the fourth guide rod are parallel to each other.
4. A landing gear ejection rod retraction performance testing machine according to claim 1 or 3, wherein the proximity switch and the pull pressure sensor are respectively connected to the electronic control system by wires, and the air cylinder is connected to the pneumatic system by a pipeline and a pneumatic valve.
5. A landing gear ejection lever retraction performance testing machine according to claim 1, wherein the proximity switch is located just to detect an initial state when the ejection lever rotates anticlockwise around the ejection lever shaft from an upper limit position, and the proximity switch rapidly sends an electrical signal to the electrical control system when the ejection lever is just rotationally displaced.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911039974.XA CN110697078B (en) | 2019-10-29 | 2019-10-29 | Undercarriage ejection rod retraction performance testing machine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911039974.XA CN110697078B (en) | 2019-10-29 | 2019-10-29 | Undercarriage ejection rod retraction performance testing machine |
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| CN110697078A CN110697078A (en) | 2020-01-17 |
| CN110697078B true CN110697078B (en) | 2020-12-01 |
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| CN201911039974.XA Active CN110697078B (en) | 2019-10-29 | 2019-10-29 | Undercarriage ejection rod retraction performance testing machine |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113232887B (en) * | 2021-05-19 | 2023-03-14 | 中航西安飞机工业集团股份有限公司 | Mechanical life test bed and test method for retractable switch of undercarriage |
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2019
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