CN210071501U - Fatigue test device for main landing gear beam of airplane - Google Patents
Fatigue test device for main landing gear beam of airplane Download PDFInfo
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- CN210071501U CN210071501U CN201920453385.5U CN201920453385U CN210071501U CN 210071501 U CN210071501 U CN 210071501U CN 201920453385 U CN201920453385 U CN 201920453385U CN 210071501 U CN210071501 U CN 210071501U
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- landing gear
- pull frame
- fixedly connected
- gear beam
- oil press
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Abstract
The utility model discloses a fatigue test device for a main landing gear beam of an airplane, which comprises a rack, a landing gear beam, a connecting device, a middle pull frame, a front pull frame, an upper reinforcing plate, a lower reinforcing plate and an oil press; the rear end of the connecting device is of a flange structure and is fixedly connected with the rack, and the front end of the connecting device is of a fork-shaped structure and is fixedly connected with the rear end of the lifting frame beam; the upper end of the middle pull frame is fixedly connected with the lower middle concave ring of the landing gear beam, and the lower end of the middle pull frame is of a connecting structure matched with the oil press; the lower end and the front end of the front pull frame are of a connecting structure matched with an oil press, and the rear end of the front pull frame is fixedly connected with the front end of the landing gear beam; the upper reinforcing plate is fixedly connected with the upper front end of the landing gear beam; the lower reinforcing plate is fixedly connected with the lower front end of the landing gear beam; the oil press is connected with the lower end of the middle pull frame and applies upward thrust to the middle pull frame; the hydraulic press is connected with the lower end and the front end of the front pull frame, downward and transverse pulling forces are respectively applied to the front pull frame, and the fatigue test of the crack position of the main landing frame beam of a certain airplane can be realized by the device.
Description
Technical Field
The utility model belongs to the technical field of the aircraft device, concretely relates to aircraft main landing gear roof beam fatigue test device.
Background
The airplane is in a state of stopping flying and waiting for repair due to the crack fault of a certain airplane landing gear beam, and the use of airplane equipment is greatly influenced. In order to reduce the stress level of the main landing gear crack of a certain type of airplane and slow down the crack propagation rate, the research on the bonding repair technology of the outfield composite material of the landing gear beam crack of a certain type of airplane needs to be developed urgently, and a landing gear beam crack fatigue test scheme is formulated.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model provides an aircraft owner landing gear roof beam fatigue test device can realize the fatigue test of the main landing gear roof beam crackle position of certain type aircraft, verifies the achievement of repair technique, guarantees aircraft landing gear beam structure's flight safety in utilization.
Realize the technical scheme of the utility model as follows:
a fatigue test device for a main landing gear beam of an airplane comprises a rack, a landing gear beam, a connecting device, a middle pull frame, a front pull frame, an upper reinforcing plate, a lower reinforcing plate and an oil press;
the rear end of the connecting device is of a flange structure and is fixedly connected with the rack, and the front section of the connecting device is of a fork-shaped structure and is fixedly connected with the rear end of the landing gear beam;
the upper end of the middle pull frame is fixedly connected with the concave ring at the lower middle part of the landing gear beam, and the lower end of the middle pull frame is of a connecting structure matched with the oil press;
the lower end and the front end of the front pull frame are of connecting structures matched with an oil press, and the rear end of the front pull frame is fixedly connected with the front end of a landing gear beam;
the upper reinforcing plate is fixedly connected with the upper front end of the landing gear beam;
the lower reinforcing plate is fixedly connected with the lower front end of the landing gear beam;
the oil press is connected with the lower end of the middle pull frame and applies upward thrust to the middle pull frame; the oil press is connected with the lower end and the front end of the front pull frame and respectively applies downward and transverse pulling forces to the front pull frame.
Further, the connecting device comprises a left clamping plate, a right clamping plate, a flange bottom plate and reinforcing ribs, wherein the left clamping plate and the right clamping plate are fixedly connected to form a fork-shaped structure and then are fixedly connected with the flange bottom plate, and the reinforcing ribs are respectively fixedly connected with the side walls of the left clamping plate and the right clamping plate and fixedly connected with the flange bottom plate.
Has the advantages that:
the utility model discloses a stable in structure, intensity is high, and the stress point is the same with landing gear roof beam stress point in certain type aircraft flight, can effectively carry out fatigue test to the assigned position to owing to increased the reinforcing plate and avoided influencing going on of fatigue test because of the weak position of part of landing gear roof beam, guarantee that the fatigue test result is correct with lower reinforcing plate.
Drawings
Fig. 1 is an axial view of the overall structure of the present invention.
Fig. 2 is a front view of the overall structure of the present invention.
Figure 3 is an axial view of the landing gear beam.
Fig. 4 is an axial view of the coupling device.
Wherein, 1-a rack; 2-a landing gear beam; 3-a connecting means; 4-middle pull frame; 5-a front pulling frame; 6-upper reinforcing plate; 7-lower reinforcing plate; 8-bolt; 9-a nut; 10-oil press; 11-left splint; 12-right splint; 13-flange bottom plate; 14-reinforcing ribs.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings by way of examples.
As shown in fig. 1 and 2, the utility model provides an aircraft main landing gear beam fatigue test device, which comprises a rack 1, a landing gear beam 2, a connecting device 3, a middle pull frame 4, a front pull frame 5, an upper reinforcing plate 6, a lower reinforcing plate 7, a bolt 8, a nut 9 and an oil press 10;
as shown in fig. 4, the connecting device 3 is composed of a left clamping plate 11, a right clamping plate 12, a flange bottom plate 13 and reinforcing ribs 14;
wherein the front pulling frame 5 consists of a left front pulling frame and a right front pulling frame;
the bolt 8 and the nut 9 have various specifications;
the rear end of the connecting device 3 is of a flange structure and is fixedly connected with the rack 1 through a bolt 8 and a nut 9, and the front section of the connecting device is of a fork-shaped structure and is fixedly connected with the rear end of the landing gear beam 2 through a bolt and a nut;
the lower end of the middle pull frame 4 is of a thrust connection structure, and the upper end of the middle pull frame is fixedly connected with a concave ring at the lower middle part of the landing gear beam 2 through bolts and nuts;
the lower end of the front pull frame 5 is of a tension connecting structure, the front end of the front pull frame is of a tension connecting mechanism, and the rear end of the front pull frame is fixedly connected with the front end of the landing gear beam 2 through bolts and nuts;
the upper reinforcing plate 6 is fixedly connected with the upper front end of the landing gear beam 2 through bolts and nuts;
the lower reinforcing plate 7 is fixedly connected with the lower front end of the landing gear beam 2 through bolts and nuts;
when a fatigue test of a main landing gear beam of a certain type of airplane is carried out, firstly, the landing gear beam 2 is fixed on a rack by a connecting device 3 through a bolt 8 and a nut 9; then, the upper end of the middle pull frame 4 is fixedly connected with the concave ring at the lower middle part of the landing gear beam 2 through bolts and nuts, and the rear end of the front pull frame 5 is fixedly connected with the front end of the landing gear beam 2 through bolts and nuts; then, the upper reinforcing plate 6 is fixedly connected with the upper front end of the landing gear beam 2 through bolts and nuts, and the lower reinforcing plate 7 is fixedly connected with the lower front end of the landing gear beam 2 through bolts and nuts, so that when a fatigue test is performed on a fatigue test point shown in fig. 3, other weak parts on the landing gear cannot influence the performance of the fatigue test; finally, an oil press 10 provides upward thrust for the middle pull frame 4, downward tension and transverse tension for the front pull frame 5, so that the stress condition of the landing gear beam in the flight of a certain airplane is simulated, the stress condition of the landing gear when the certain airplane is lifted and dropped is simulated by applying the thrust and the tension discontinuously, and the fatigue test of the landing gear beam of the certain airplane is completed.
In summary, the above is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (2)
1. A fatigue test device for a main landing gear beam of an airplane is characterized by comprising a rack, a landing gear beam, a connecting device, a middle pull frame, a front pull frame, an upper reinforcing plate, a lower reinforcing plate and an oil press;
the rear end of the connecting device is of a flange structure and is fixedly connected with the rack, and the front section of the connecting device is of a fork-shaped structure and is fixedly connected with the rear end of the landing gear beam;
the upper end of the middle pull frame is fixedly connected with the concave ring at the lower middle part of the landing gear beam, and the lower end of the middle pull frame is of a connecting structure matched with the oil press;
the lower end and the front end of the front pull frame are of connecting structures matched with an oil press, and the rear end of the front pull frame is fixedly connected with the front end of a landing gear beam;
the upper reinforcing plate is fixedly connected with the upper front end of the landing gear beam;
the lower reinforcing plate is fixedly connected with the lower front end of the landing gear beam;
the oil press is connected with the lower end of the middle pull frame and applies upward thrust to the middle pull frame; the oil press is connected with the lower end and the front end of the front pull frame and respectively applies downward and transverse pulling forces to the front pull frame.
2. An aircraft main landing gear beam fatigue test device according to claim 1, wherein said attachment means comprises a left clamp plate, a right clamp plate, a flange base plate and a reinforcing rib, the left clamp plate and the right clamp plate are fixedly connected to form a fork-shaped structure and then fixedly connected to the flange base plate, and the reinforcing rib is fixedly connected to the side walls of the left clamp plate and the right clamp plate respectively and fixedly connected to the flange base plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920453385.5U CN210071501U (en) | 2019-04-04 | 2019-04-04 | Fatigue test device for main landing gear beam of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920453385.5U CN210071501U (en) | 2019-04-04 | 2019-04-04 | Fatigue test device for main landing gear beam of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210071501U true CN210071501U (en) | 2020-02-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201920453385.5U Active CN210071501U (en) | 2019-04-04 | 2019-04-04 | Fatigue test device for main landing gear beam of airplane |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112461648A (en) * | 2020-10-06 | 2021-03-09 | 湖北超卓航空科技股份有限公司 | Testing device for fatigue performance detection of sample piece |
| CN117382909A (en) * | 2023-12-07 | 2024-01-12 | 山西助我飞科技有限公司 | Fatigue characteristic testing assembly for undercarriage |
-
2019
- 2019-04-04 CN CN201920453385.5U patent/CN210071501U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112461648A (en) * | 2020-10-06 | 2021-03-09 | 湖北超卓航空科技股份有限公司 | Testing device for fatigue performance detection of sample piece |
| CN117382909A (en) * | 2023-12-07 | 2024-01-12 | 山西助我飞科技有限公司 | Fatigue characteristic testing assembly for undercarriage |
| CN117382909B (en) * | 2023-12-07 | 2024-02-09 | 山西助我飞科技有限公司 | Fatigue characteristic testing assembly for undercarriage |
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