CN113933040B - Helicopter cockpit door durability testing device and operation method - Google Patents
Helicopter cockpit door durability testing device and operation method Download PDFInfo
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- CN113933040B CN113933040B CN202111221728.3A CN202111221728A CN113933040B CN 113933040 B CN113933040 B CN 113933040B CN 202111221728 A CN202111221728 A CN 202111221728A CN 113933040 B CN113933040 B CN 113933040B
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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
Abstract
The application relates to the technical field of helicopter cabin doors, in particular to a helicopter cockpit door durability test device and an operation method, wherein the helicopter cockpit door durability test device comprises a loading table, an inner unlocking mechanism, an outer unlocking mechanism, a power mechanism, a flexible pulling piece and an induction mechanism; the inner unlocking mechanism and the outer unlocking mechanism are respectively arranged on the inner side and the outer side of the cabin door; one end of the power mechanism is arranged on the loading table, and the other end of the power mechanism is arranged on the inner side surface of the cabin door through the flexible pulling piece. According to the application, on one hand, the opening and closing conditions of the cabin door can be effectively simulated by arranging the inner unlocking mechanism, the outer unlocking mechanism and the power mechanism, so that a reliable experimental basis is provided for durability test of the cabin door; on the other hand, the flexible pull piece can more reasonably simulate that a human hand touches the cabin door handle, and further data reliability of the cabin door durability simulation test is improved. In addition, the sensing mechanism enables all states of the cabin door to be monitored and recorded when the cabin door is opened and closed, and the obtained data can provide reference for research personnel to optimize the design of the cabin door, so that the durability of the driving cabin door is further improved.
Description
Technical Field
The application relates to the technical field of helicopter cabin doors, in particular to a helicopter cockpit door durability test device and an operation method.
Background
In the existing field of helicopter cockpit doors, the normal and stable opening and closing of the helicopter cockpit door is related to the cockpit safety of a pilot and the flight safety of a helicopter, so before the helicopter cockpit door is installed on the helicopter and applied, the durability of the helicopter cockpit door needs to be tested, and therefore, a safe and reliable testing device is urgently needed for testing the durability of the helicopter cockpit door.
Disclosure of Invention
Aiming at the technical problems, the application provides a durability testing device for a helicopter cockpit door, which aims to solve the problem that a safe and reliable testing device is needed for testing the durability of the helicopter cockpit door in the prior art.
In order to achieve the above purpose, the technical scheme adopted by the application is as follows:
the application provides a durability test device for a helicopter cockpit door, which comprises a loading platform for installing the cockpit door, an inner unlocking mechanism, an outer unlocking mechanism, a power mechanism, a flexible pulling piece and an induction mechanism for detecting the opening and closing condition and speed of the cockpit door; the inner unlocking mechanism is movably arranged on the inner side of the cockpit door; the outer unlocking mechanism is arranged on the outer side of the cockpit door; one end of the power mechanism is adjustably arranged on the loading table, and the other end of the power mechanism is telescopically arranged on the inner side surface of the driving cabin door through the flexible pulling piece; wherein the power mechanism and the cockpit door are arranged at an inclined angle; the flexible pulling piece can be connected with the inner handle of the cockpit door and the power mechanism in a stretching and torsion mode.
Further, the power mechanism comprises a first cylinder; one end of the first cylinder is arranged on the loading table, the other end of the first cylinder is connected with the flexible pulling piece, and the first cylinder and the driving cabin door are arranged at an inclined angle.
Further, the power mechanism further comprises an angle limiting part for limiting the movable range of the power mechanism; the angle limiting part is arranged on the loading table, and the power mechanism is movably arranged on the angle limiting part.
Further, the inner unlocking mechanism comprises a second cylinder and an inner inhaul cable; one end of the second cylinder is arranged on the inner side of the driving cabin door through an inner supporting part, the other end of the second cylinder is movably connected with one end of the inner pull lock, and the other end of the inner pull rope is connected with an inner unlocking part of the driving cabin door.
Further, the outer unlocking mechanism comprises a third cylinder and an outer inhaul cable; one end of the third cylinder is arranged on the outer side of the cockpit door through an outer supporting part, the other end of the third cylinder is movably connected with one end of the outer pull lock, and the other end of the outer pull cable is connected with an outer unlocking part of the cockpit door.
Further, the sensing mechanism comprises a plurality of upper proximity sensors for monitoring the opening and closing conditions of the cockpit door; the upper proximity sensor is arranged on the inner side of the cockpit door.
Further, the sensing mechanism further comprises a lower proximity sensor for monitoring the closing speed of the cockpit door; the lower proximity sensor is arranged at the bottom of the cockpit door.
Further, the flexible pulling piece is a nylon pulling rope.
The application provides an operation method of a helicopter cockpit door durability test device, which adopts the helicopter cockpit door durability test device and comprises the following steps:
firstly, opening the cockpit door from the inside of the cockpit door, unlocking the cockpit door from the inside by an inner unlocking mechanism, and driving the flexible pulling piece to push the cockpit door to push out from the inside by a power mechanism;
then the cockpit door is closed from the inside of the cockpit door, and the power mechanism drives the flexible pulling piece to pull the cockpit door until the cockpit door is closed;
then the cockpit door is opened from the outside of the cockpit door, the cockpit door is unlocked from the outside by the external unlocking mechanism, and the power mechanism drives the flexible pulling piece to push the cockpit door to push out from the inside;
finally, the cockpit door is closed from the outside of the cockpit door, and the power mechanism drives the flexible pulling piece to pull the cockpit door until the cockpit door is closed;
the above steps are one cycle of operation.
The technical scheme has the following advantages or beneficial effects:
the application provides a durability test device and an operation method of a helicopter cockpit door, wherein the durability test device comprises a loading platform for installing the cockpit door, an inner unlocking mechanism, an outer unlocking mechanism, a power mechanism, a flexible pulling piece and an induction mechanism for detecting the opening and closing condition and speed of the cockpit door; the inner unlocking mechanism is movably arranged on the inner side of the cockpit door; the outer unlocking mechanism is arranged on the outer side of the cockpit door; one end of the power mechanism is adjustably arranged on the loading table, and the other end of the power mechanism is telescopically arranged on the inner side surface of the cockpit door through a flexible pulling piece; wherein the power mechanism and the cockpit door are arranged at an inclined angle; the flexible pulling piece can be connected with the inner handle of the cockpit door and the power mechanism in a stretching and torsion mode. According to the application, on one hand, by arranging the inner unlocking mechanism, the outer unlocking mechanism and the power mechanism, the actual condition of opening and closing the cockpit door from the inside and the outside of the cockpit of the helicopter can be effectively simulated, so that a reliable experimental basis is provided for the durability test of the cockpit door of the helicopter; on the other hand, the arrangement of the flexible pulling piece can more reasonably simulate that a human hand contacts with the handle of the cockpit door so as to open and close the cockpit door, thereby further improving the data reliability of the cockpit door durability simulation test. More importantly, the setting of the induction mechanism enables various states of the driving cabin door in the opening and closing process to be monitored and recorded in real time, and if the cabin door cannot be opened and closed normally, the cabin door is opened and closed at too high speed, violent closing is caused, and the like, the obtained relevant experimental data can provide reference for research personnel to improve and optimize the structural design of the driving cabin door, so that the durability of the driving cabin door is further improved.
Drawings
The application and its features, aspects and advantages will become more apparent from the detailed description of non-limiting embodiments with reference to the following drawings. Like numbers refer to like parts throughout. The drawings are not intended to be drawn to scale, emphasis instead being placed upon illustrating the principles of the application.
Fig. 1 is a schematic diagram showing a perspective structure of a durability test device for a helicopter cockpit door according to embodiment 1 of the present application;
fig. 2 is a schematic diagram showing a perspective structure of a durability test device for a cockpit door of a helicopter provided in embodiment 1 of the present application at another view angle;
fig. 3 is a schematic diagram of a perspective structure of a helicopter cockpit door durability test apparatus provided in embodiment 1 of the present application with a cockpit door to be detected separated from the apparatus;
fig. 4 is a schematic diagram showing a perspective view of another view of a cockpit door to be detected separated from the device in the durability test device for a cockpit door of a helicopter provided in embodiment 1 of the present application.
Detailed Description
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the present application.
It will be understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, steps, operations, devices, components, and/or groups thereof.
The terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," and the like, as used herein, refer to an orientation or positional relationship based on that shown in the drawings, merely for convenience of description and to simplify the description, and do not denote or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus are not to be construed as limiting the application.
The terms "first," "second," "third," and the like, as used herein, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Unless specifically stated or limited otherwise, the terms "mounted," "connected," and "coupled" should be construed broadly, as if they were fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present application will be understood in specific cases by those of ordinary skill in the art.
The following description of the technical solutions according to the embodiments of the present application refers to the accompanying drawings, which are included to illustrate only some embodiments of the application, and not all embodiments. Accordingly, the following detailed description of the embodiments of the application, as presented in the figures, is not intended to limit the scope of the application, as claimed, but is merely representative of selected embodiments of the application. All other embodiments, which can be made by a person skilled in the art without making any inventive effort, are intended to fall within the scope of the present application.
Example 1:
in the existing field of helicopter cockpit doors, the normal and stable opening and closing of the helicopter cockpit door is related to the cockpit safety of a pilot and the flight safety of a helicopter, so before the helicopter cockpit door is installed on the helicopter and applied, the durability of the helicopter cockpit door needs to be tested, and therefore, a safe and reliable testing device is urgently needed for testing the durability of the helicopter cockpit door.
As will be understood with reference to fig. 1 to 4, the durability test device for a helicopter cockpit door 1 provided in embodiment 1 of the present application includes a loading platform 2 for installing the cockpit door 1, an inner unlocking mechanism 3, an outer unlocking mechanism 4, a power mechanism 5, a flexible pulling member 6, and an induction mechanism 7 for detecting the opening and closing condition and speed of the cockpit door 1; the inner unlocking mechanism 3 is movably arranged on the inner side of the cockpit door 1; the outer unlocking mechanism 4 is arranged on the outer side of the cockpit door 1; one end of the power mechanism 5 is adjustably arranged on the loading platform 2, and the other end of the power mechanism 5 is telescopically arranged on the inner side surface of the cockpit door 1 through a flexible pulling piece 6; wherein the power mechanism 5 and the cockpit door 1 are arranged at an inclined angle; the flexible pull 6 connects the inner handle 11 of the cockpit door 1 with the power mechanism 5 in a tensile and torsional manner.
According to the durability testing device for the helicopter cockpit door 1, when the cockpit door 1 is detected, the cockpit door 1 to be detected is firstly arranged on the loading table 2, when the cockpit door 1 is opened and closed from the inside, the inner unlocking mechanism 3 works to unlock the cockpit door 1 from the inside, then the power mechanism 5 works to push the cockpit door 1 to be opened from the inside, and when the cockpit door 1 is closed, the power mechanism 5 pulls the inner handle 11 of the cockpit door 1 until the cockpit door is closed; when the outer unlocking mechanism 4 works to unlock the cockpit door 1 from the outside, the power mechanism 5 pushes the cockpit door 1 outwards to open the cockpit door 1 from the outside while pulling the outer handle of the cockpit door 1, and when the cockpit door is closed, the outer unlocking mechanism 4 is pulled reversely, and the power mechanism 5 is pulled reversely, so that the cockpit door 1 is driven to be closed from the outside, wherein the opening from the inside and the outside is counted as one opening and closing round. According to the application, on one hand, the inner unlocking mechanism 3, the outer unlocking mechanism 4 and the power mechanism 5 are arranged, so that the actual condition of opening and closing the cockpit door 1 from the inside and the outside of the cockpit of the helicopter can be effectively simulated, and a reliable experimental basis is provided for the durability test of the cockpit door 1 of the helicopter; on the other hand, the arrangement of the flexible pull piece 6 can more reasonably simulate that a human hand contacts with the handle of the cockpit door 1 to open and close the cockpit door, so that the data reliability of the durability simulation test of the cockpit door 1 is further improved. More importantly, the induction mechanism 7 enables various states of the cockpit door 1 in the opening and closing process to be monitored and recorded in real time, for example, the cockpit door cannot be opened and closed normally, violent closing is caused by too high opening and closing speed of the cockpit door, and the obtained relevant experimental data can provide reference for research personnel to improve and optimize the structural design of the cockpit door 1, so that the durability of the cockpit door 1 is further improved.
Further, the power mechanism 5 includes a first cylinder 51; one end of the first cylinder 51 is arranged on the loading platform 2, in particular in hinged connection, the other end of the first cylinder 51 is connected with the flexible pulling piece 6, and the first cylinder 51 and the driving cabin door 1 are arranged at an inclined angle. Further, the power mechanism 5 further includes an angle limiting portion 52 for limiting the movable range of the power mechanism 5; the angle limiting portion 52 is disposed on the loading table 2, and the power mechanism 5 is movably disposed on the angle limiting portion 52. Because the air cylinder has the advantages of sensitive response, strong adaptability, convenient operation and control and the like, the first air cylinder 51 is arranged, so that the air cylinder can effectively simulate the opening and closing of the cockpit door 1 by hands by matching with the flexible pulling piece 6 when the air cylinder stretches out and stretches back, the structural design is reasonable, the implementation is easy, and a reasonable simulation device is provided for the durability test of the helicopter cockpit door; the first air cylinder 51 which is hinged with the loading platform 2 can rotate in a preset range, and the rotation angle of the first air cylinder 51 can be effectively limited by the arrangement of the angle limiting part 52, so that abnormal opening and closing of the cockpit door 1 are avoided, and a reasonable experimental basis is further provided for durability test of the cockpit door 1.
Further, the inner unlocking mechanism 3 includes a second cylinder 31 and an inner stay 32; one end of the second cylinder 31 is arranged on the inner side of the cockpit door 1 through an inner supporting part 33, the other end of the second cylinder 31 is movably connected with one end of an inner pull lock, and the other end of the inner pull rope 32 is connected with an inner unlocking part 34 of the cockpit door 1. Through setting up second cylinder 31, interior guy wire 32 and interior supporting part 33, when opening cockpit door 1 from inside, at first need open interior unblock portion 34 through interior release mechanism 3, and at this moment, second cylinder 31 work drives interior guy wire 32 pulling interior unblock portion 34 of being connected with it in order to unlock cockpit door 1 from inside, and its overall structure design is simple and reasonable, easily realizes, further improves cockpit door 1 durability testing arrangement's simulation test rationality.
Further, the outer unlocking mechanism 4 includes a third cylinder 41 and an outer stay 42; one end of the third cylinder 41 is arranged outside the cockpit door 1 through an outer supporting portion 43, the other end of the third cylinder 41 is movably connected with one end of an outer pull lock, and the other end of the outer pull cable 42 is connected with an outer unlocking portion 44 of the cockpit door 1. By providing the third cylinder 41, the outer stay 42 and the outer support portion 43, when the cockpit door 1 is opened from the outside, the third cylinder 41 is operated to pull the outer stay 42, and the outer stay 42 pulls the outer unlocking portion 44 to unlock the cockpit door 1 from the outside, and similarly, based on the above-described arrangement, the simulation test rationality of the durability test device for the cockpit door 1 can be further improved in cooperation with the aforementioned power mechanism 5.
Further, the sensing mechanism 7 comprises a plurality of upper proximity sensors 71 for monitoring the opening and closing conditions of the cockpit door 1; the upper proximity sensor 71 is provided inside the cockpit door 1. By arranging the upper proximity sensor 71, specifically, in this embodiment, the upper portion and the lower portion of the side edge of the cockpit door 1 are respectively provided with an upper proximity sensor 71, so that the opening and closing condition of the cockpit door 1 and the corresponding parameters in the opening and closing process can be recorded, thereby providing a reasonable basis for the durability test result of the cockpit door 1, and further providing a theoretical basis for the research and development personnel to improve and optimize the durability of the cockpit door 1.
Further, the sensing mechanism 7 further comprises a lower proximity sensor 72 for monitoring the closing speed of the cockpit door 1; the lower proximity sensor 72 is provided at the bottom of the cockpit door 1. Through setting up down proximity sensor 72 for the cockpit door 1 all can be recorded at the speed parameter of opening and close the in-process, thereby cooperate the aforesaid to go up proximity sensor 71, provide reasonable basis for cockpit door 1's durability test result, specifically, be provided with two down proximity sensor 72 in the bottom of cockpit door 1 in this embodiment, through detecting the speed of closing the hatch door, can effectively detect whether there is "violent door closing" phenomenon, further provide theoretical basis for research personnel improvement optimizing cockpit door 1's durability.
Further, the flexible pull 6 includes, but is not limited to, a nylon pull cord. Through setting up the flexible piece 6 that draws that is made by nylon stay cord, can simulate the people's hand from inside to open and close cockpit door 1 better, cooperate first cylinder 51 to effectively improve cockpit door 1 durability testing arrangement's operational reliability, further improve the accuracy of test result.
The application provides an operation method of a helicopter cockpit door durability test device, which adopts the helicopter cockpit door durability test device and comprises the following steps:
firstly, the cockpit door 1 is opened from the inside of the cockpit door 1, the cockpit door 1 is unlocked from the inside by the inner unlocking mechanism 3, and the power mechanism 5 drives the flexible pull piece 6 to push the cockpit door 1 to be pushed out from the inside;
then the cockpit door 1 is closed from the inside of the cockpit door 1, and the power mechanism 5 drives the flexible pulling piece 6 to pull the cockpit door 1 until the cockpit door 1 is closed;
then the cockpit door 1 is opened from the outside of the cockpit door 1, the cockpit door 1 is unlocked from the outside by the external unlocking mechanism 4, and the power mechanism 5 drives the flexible pull piece 6 to push the cockpit door 1 to be pushed out from the inside;
finally, the cockpit door 1 is closed from the outside of the cockpit door 1, and the power mechanism 5 drives the flexible pulling piece 6 to pull the cockpit door 1 until the cockpit door 1 is closed;
the above steps are one cycle of operation.
In summary, according to the durability test device and the operation method for the helicopter cockpit door provided by the application, on one hand, the actual condition of opening and closing the cockpit door from the inside and the outside of the helicopter cockpit can be effectively simulated by arranging the inner unlocking mechanism, the outer unlocking mechanism and the power mechanism, so that a reliable experimental basis is provided for the durability test of the helicopter cockpit door; on the other hand, the arrangement of the flexible pulling piece can more reasonably simulate that a human hand contacts with the handle of the cockpit door so as to open and close the cockpit door, thereby further improving the data reliability of the cockpit door durability simulation test. More importantly, the setting of the induction mechanism enables various states of the driving cabin door in the opening and closing process to be monitored and recorded in real time, if the cabin door cannot be opened and closed normally, the cabin door is opened and closed at too high speed, violent closing is caused, and the like, the obtained relevant experimental data can provide reasonable basis for research and development personnel to improve and optimize the structural design of the driving cabin door, so that the durability of the driving cabin door is further improved.
The foregoing description is only of the preferred embodiments of the present application and is not intended to limit the scope of the application, and all equivalent structural changes made by the present application and the accompanying drawings, or direct or indirect application in other related technical fields, are included in the scope of the present application.
Claims (7)
1. The durability testing device for the helicopter cockpit door is characterized by comprising a loading platform for installing the cockpit door, an inner unlocking mechanism, an outer unlocking mechanism, a power mechanism, a flexible pulling piece and an induction mechanism for detecting the opening and closing condition and the speed of the cockpit door; the inner unlocking mechanism is movably arranged on the inner side of the cockpit door; the outer unlocking mechanism is arranged on the outer side of the cockpit door; one end of the power mechanism is adjustably arranged on the loading table, and the other end of the power mechanism is telescopically arranged on the inner side surface of the driving cabin door through the flexible pulling piece; wherein the power mechanism and the cockpit door are arranged at an inclined angle; the flexible pulling piece can be connected with the inner handle of the cockpit door and the power mechanism in a stretching and torsion mode; the inner unlocking mechanism comprises a second cylinder and an inner inhaul cable; one end of the second cylinder is arranged on the inner side of the driving cabin door through an inner supporting part, the other end of the second cylinder is movably connected with one end of the inner pull lock, and the other end of the inner pull rope is connected with an inner unlocking part of the driving cabin door; the outer unlocking mechanism comprises a third cylinder and an outer inhaul cable; one end of the third cylinder is arranged on the outer side of the cockpit door through an outer supporting part, the other end of the third cylinder is movably connected with one end of the outer pull lock, and the other end of the outer pull cable is connected with an outer unlocking part of the cockpit door.
2. The helicopter cockpit door durability test apparatus of claim 1 wherein said power mechanism includes a first cylinder; one end of the first cylinder is arranged on the loading table, the other end of the first cylinder is connected with the flexible pulling piece, and the first cylinder and the driving cabin door are arranged at an inclined angle.
3. The helicopter cockpit door durability test apparatus of claim 2 wherein said power mechanism further includes an angle stop for limiting the range of motion of said power mechanism; the angle limiting part is arranged on the loading table, and the power mechanism is movably arranged on the angle limiting part.
4. The helicopter cockpit door durability test apparatus of claim 1 wherein said sensing mechanism includes a plurality of upper proximity sensors for monitoring the status of the cockpit door open and close; the upper proximity sensor is arranged on the inner side of the cockpit door.
5. The helicopter cockpit door durability test apparatus of claim 4 wherein said sensing mechanism further includes a lower proximity sensor for monitoring the cockpit door closing speed; the lower proximity sensor is arranged at the bottom of the cockpit door.
6. The helicopter cockpit door durability test apparatus of claim 1 wherein said flexible pull member is a nylon pull cord.
7. A method of operating a helicopter cockpit door durability test apparatus employing a helicopter cockpit door durability test apparatus according to any one of claims 1-6 comprising: firstly, opening the cockpit door from the inside of the cockpit door, unlocking the cockpit door from the inside by an inner unlocking mechanism, and driving the flexible pulling piece to push the cockpit door to push out from the inside by a power mechanism; then the cockpit door is closed from the inside of the cockpit door, and the power mechanism drives the flexible pulling piece to pull the cockpit door until the cockpit door is closed; then the cockpit door is opened from the outside of the cockpit door, the cockpit door is unlocked from the outside by the external unlocking mechanism, and the power mechanism drives the flexible pulling piece to push the cockpit door to push out from the inside; finally, the cockpit door is closed from the outside of the cockpit door, and the power mechanism drives the flexible pulling piece to pull the cockpit door until the cockpit door is closed; the above steps are one cycle of operation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111221728.3A CN113933040B (en) | 2021-10-20 | 2021-10-20 | Helicopter cockpit door durability testing device and operation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111221728.3A CN113933040B (en) | 2021-10-20 | 2021-10-20 | Helicopter cockpit door durability testing device and operation method |
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| Publication Number | Publication Date |
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| CN113933040A CN113933040A (en) | 2022-01-14 |
| CN113933040B true CN113933040B (en) | 2023-09-29 |
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| CN202111221728.3A Active CN113933040B (en) | 2021-10-20 | 2021-10-20 | Helicopter cockpit door durability testing device and operation method |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104897389A (en) * | 2015-06-19 | 2015-09-09 | 庆铃汽车（集团）有限公司 | Vehicle door opening and closing durability tester |
| CN105374093A (en) * | 2015-11-18 | 2016-03-02 | 江苏科技大学 | ATM (Automatic teller machine) protective tank door electronic system and control method |
| CN109629906A (en) * | 2018-12-28 | 2019-04-16 | 陕西中航气弹簧有限责任公司 | A kind of helicopter cockpit door latching mechanism |
| CN112781859A (en) * | 2021-03-09 | 2021-05-11 | 矩阵数据科技(上海)有限公司 | Method for testing performance of four doors and one cover of pure electric vehicle |
| CN113063580A (en) * | 2021-03-31 | 2021-07-02 | 东风商用车有限公司 | Door lock system endurance test bench and endurance test method |
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2021
- 2021-10-20 CN CN202111221728.3A patent/CN113933040B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104897389A (en) * | 2015-06-19 | 2015-09-09 | 庆铃汽车（集团）有限公司 | Vehicle door opening and closing durability tester |
| CN105374093A (en) * | 2015-11-18 | 2016-03-02 | 江苏科技大学 | ATM (Automatic teller machine) protective tank door electronic system and control method |
| CN109629906A (en) * | 2018-12-28 | 2019-04-16 | 陕西中航气弹簧有限责任公司 | A kind of helicopter cockpit door latching mechanism |
| CN112781859A (en) * | 2021-03-09 | 2021-05-11 | 矩阵数据科技(上海)有限公司 | Method for testing performance of four doors and one cover of pure electric vehicle |
| CN113063580A (en) * | 2021-03-31 | 2021-07-02 | 东风商用车有限公司 | Door lock system endurance test bench and endurance test method |
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| CN113933040A (en) | 2022-01-14 |
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