CN216309380U - Mechanics loading mechanism capable of simulating pneumatic load - Google Patents
Mechanics loading mechanism capable of simulating pneumatic load Download PDFInfo
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- CN216309380U CN216309380U CN202120840903.6U CN202120840903U CN216309380U CN 216309380 U CN216309380 U CN 216309380U CN 202120840903 U CN202120840903 U CN 202120840903U CN 216309380 U CN216309380 U CN 216309380U
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Abstract
The utility model relates to test equipment, in particular to aerodynamic load simulation equipment, and particularly relates to a mechanical loading mechanism capable of simulating aerodynamic load. The mechanism comprises a base body, wherein a tested piece mounting structure is arranged on the base body; a force loading mechanism is provided around the test piece X, Y, Z. According to the technical scheme, the tested piece is subjected to force application at X, Y, Z, so that the technical problem of pneumatic load application is effectively solved, and the function of pneumatic load simulation is realized.
Description
Technical Field
The utility model relates to test equipment, in particular to aerodynamic load simulation equipment, and particularly relates to a mechanical loading mechanism capable of simulating aerodynamic load.
Background
The flight load is one of the working conditions of the real environment in the air and can directly influence the separation process of the device, so that the flight load must be simulated in the ground test process to improve the confidence coefficient of the test result and ensure the safety of test flight, and then one set of flight load simulation loading test system is needed for simulating the working condition of the flight load to the maximum extent in the ground test process of a prototype, thereby effectively verifying the design effect and improving the delivery quality of products.
Disclosure of Invention
The technical problems solved by the utility model are as follows: a mechanical loading mechanism capable of simulating pneumatic load is provided.
The technical scheme of the utility model is as follows: a mechanics loading mechanism capable of simulating pneumatic load comprises a base body, wherein a tested piece mounting structure is arranged on the base body; a force loading mechanism is provided around the test piece X, Y, Z. According to the technical scheme, the tested piece is subjected to force application at X, Y, Z, so that the technical problem of pneumatic load application is effectively solved, and the function of pneumatic load simulation is realized.
Preferably, the X direction is the heading. The technical scheme limits the position of a coordinate system, facilitates the calculation of loading force and the design of a hardware mechanism.
Preferably, the X-direction force loading mechanism comprises a sliding plate, and in the test state, the device is in a pre-flight position and is stopped against the end face of the sliding plate. The technical scheme fully considers the separation stroke of the device and can ensure the effective loading of force in the whole stroke.
Preferably, the Y direction is vertical, the Y direction at least comprises two force application points, and the force application points are positioned in the opposite directions of the separation direction of the device. The technical scheme further discloses the Y-direction, and the implementability of the technical scheme is improved.
Preferably, Z-direction force loading mechanisms are arranged on two sides of the heading direction. The technical scheme further discloses an arrangement mode of the z-direction force loading mechanism, and stability and reliability of force loading are guaranteed.
Preferably, two force application points, namely a point A and a point B, are distributed on one side of the sailing direction, and one force application point, namely a point C, is distributed on the other side of the sailing direction; point C is located between points a and B. The technical scheme further discloses an arrangement mode of the z-direction force loading mechanism, and the stability and the reliability of force loading are further ensured.
Preferably, the mechanism is particularly suitable for the separation simulation test of the aircraft onboard device. The technical scheme discloses an environment which is most suitable for the mechanism to be applied, the effect of the mechanism can be effectively exerted under the environment, and the technical purpose is guaranteed to be achieved.
Drawings
FIG. 1 is a schematic view of an experimental state of an embodiment;
FIG. 2 is a schematic view of an embodiment force loading mechanism.
Detailed Description
As shown in fig. 1, the present embodiment includes an X-direction loading assembly 1, a Y-direction loading assembly 2, a Z-direction loading assembly 3, a beam 4 and a control assembly 5, the X-direction loading assembly 1 is installed at two ends of the beam 4, the Y-direction loading assembly 2 is installed in the middle of the beam 4, and the Z-direction loading assembly 3 is installed at two sides of the beam 4 through a replaceable interface unit 6. The X-direction loading assembly 1, the Y-direction loading assembly 2 and the Z-direction loading assembly 3 can move on the cross beam 4. The control assembly 5 controls the loading force of each loading channel. When the device is used, the loading assembly and the mounting position of the loading assembly are adjusted according to the size and the loading requirement of the airborne device.
The loading assembly is shown in fig. 2 and comprises an air cylinder 11, an outer frame 12, an inner frame 13 and a sliding plate 14, wherein the inner frame 13 is arranged on the outer frame 12, the air cylinder 11 is connected with the sliding plate 14 and is arranged on the inner frame 13, the position of the air cylinder can be adjusted on the inner frame 13, and the air cylinder can be locked at the required position according to the requirement.
Before the test, the X-direction loading assembly 1 and the sliding plate 14 of the Z-direction loading assembly 3 are adjusted according to the separation stroke requirement of the airborne device, the X-direction loading assembly 1 is installed according to the length of the airborne device, the interface unit 6 with proper thickness is selected and installed according to the width of the airborne device, and then the Z-direction loading assembly 3 is installed.
The onboard device is installed on the cross beam 4 through the switching device, then the X-direction loading assembly 1 is moved to the front end face and the rear end face of the onboard device 7 and is tightly attached to the front end face and the rear end face of the onboard device, and the Y-direction loading assembly 2 and the Z-direction loading assembly 3 are moved to the designated loading positions and are tightly attached to the loading points of the onboard device 7. Finally, the control unit 5 applies the required forces and torques to the weapon.
Claims (7)
1. A mechanics loading mechanism capable of simulating pneumatic load is characterized by comprising a base body, wherein a tested piece mounting structure is arranged on the base body; a force loading mechanism is provided around the test piece X, Y, Z.
2. A mechanical loading mechanism capable of simulating aerodynamic loading according to claim 1, wherein the X direction is heading.
3. A mechanical loading mechanism capable of simulating aerodynamic loads according to claim 2, wherein the X-direction force loading mechanism comprises a sliding plate (14), and the pre-flight position of the airborne device is stopped on the end surface of the sliding plate (14) in the test state.
4. A mechanical loading mechanism capable of simulating pneumatic loading according to claim 1 wherein the Y direction is vertical and the Y direction includes at least two points of application, and the points of application are opposite to the direction of separation of the airborne device.
5. A mechanical loading mechanism capable of simulating pneumatic loads according to claim 2, wherein Z-direction force loading mechanisms are arranged on both sides of the heading.
6. A mechanical loading mechanism capable of simulating pneumatic load according to claim 5, wherein two force application points, namely a point A and a point B, are distributed on one side of the sailing direction, and one force application point, namely a point C, is distributed on the other side of the sailing direction; point C is located between points a and B.
7. A mechanical loading mechanism capable of simulating aerodynamic loads according to claim 1, wherein the mechanism is particularly suitable for use in a separation simulation test of devices on board an aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120840903.6U CN216309380U (en) | 2021-04-22 | 2021-04-22 | Mechanics loading mechanism capable of simulating pneumatic load |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120840903.6U CN216309380U (en) | 2021-04-22 | 2021-04-22 | Mechanics loading mechanism capable of simulating pneumatic load |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216309380U true CN216309380U (en) | 2022-04-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120840903.6U Active CN216309380U (en) | 2021-04-22 | 2021-04-22 | Mechanics loading mechanism capable of simulating pneumatic load |
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| CN (1) | CN216309380U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114778056A (en) * | 2022-06-13 | 2022-07-22 | 中国飞机强度研究所 | Test system and method for dynamic impact mechanical property test of light airplane structure |
-
2021
- 2021-04-22 CN CN202120840903.6U patent/CN216309380U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114778056A (en) * | 2022-06-13 | 2022-07-22 | 中国飞机强度研究所 | Test system and method for dynamic impact mechanical property test of light airplane structure |
| CN114778056B (en) * | 2022-06-13 | 2022-09-02 | 中国飞机强度研究所 | Test system and method for testing dynamic impact mechanical property of light airplane structure |
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