技术领域technical field
本发明涉及飞行器疲劳试验领域，具体而言，涉及一种飞行器舱门疲劳试验装置。The invention relates to the field of aircraft fatigue tests, in particular to an aircraft cabin door fatigue test device.
背景技术Background technique
飞行器疲劳试验是指重复模拟飞行器正常使用过程中的一系列动作以及受到的载荷，加速试验件的老化，以考核试验件的疲劳寿命。对于含有台阶的飞行器舱门来说，疲劳试验要模拟飞行器舱门的收放动作，以及进行踩踏力的加载。The aircraft fatigue test refers to repeatedly simulating a series of actions and loads during the normal use of the aircraft, and accelerating the aging of the test piece to assess the fatigue life of the test piece. For the aircraft door with steps, the fatigue test should simulate the retracting action of the aircraft door and the loading of the stepping force.
传统的飞行器舱门疲劳试验往往是通过人工操作来完成一系列动作和加载，不仅劳动强度大、试验周期长，而且还可能对试验件和人员造成损伤。对于加载试验来说，人工操作往往达不到理想的加载精度和试验频率。The traditional aircraft door fatigue test is often done by manual operation to complete a series of actions and loading, which is not only labor-intensive and the test period is long, but also may cause damage to the test piece and personnel. For loading tests, manual operations often fail to achieve ideal loading accuracy and test frequency.
因此，需要为飞行器疲劳试验设计自动化试验台，可以利用机械作动装置完成疲劳试验的一系列动作和加载要求，从而节约人力成本和时间成本，同时提高试验精度和可靠性。Therefore, it is necessary to design an automated test bench for aircraft fatigue tests, which can use mechanical actuation devices to complete a series of actions and loading requirements of fatigue tests, thereby saving labor costs and time costs, while improving test accuracy and reliability.
发明内容Contents of the invention
有鉴于此，本发明提供了一种飞行器舱门疲劳试验装置，其能够实现飞行器舱门的收放动作，以及对舱门台阶进行踩踏力的加载，从而完成飞行器舱门的疲劳试验。In view of this, the present invention provides an aircraft door fatigue test device, which can realize the retractable action of the aircraft door, and load the step of the door with a stepping force, thereby completing the fatigue test of the aircraft door.
根据本发明的一方面，提供了一种飞行器舱门疲劳试验装置，包括：According to an aspect of the present invention, a kind of aircraft hatch door fatigue test device is provided, comprising:
收放机构，用于模拟飞行器舱门的收放动作；以及The retractable mechanism is used to simulate the retractable action of the aircraft door; and
加载机构，用于对飞行器舱门的台阶施加加载力。The loading mechanism is used for applying loading force to the steps of the aircraft hatch.
根据实施例，本发明的飞行器舱门疲劳试验装置，还包括：According to an embodiment, the aircraft door fatigue test device of the present invention also includes:
试验台架，用于安装所述收放机构和/或所述加载机构。The test bench is used for installing the retractable mechanism and/or the loading mechanism.
根据实施例，所述收放机构包括：According to an embodiment, the retractable mechanism includes:
舱门收放气缸，其活塞杆与摇臂连接，以使得所述活塞杆的直线运动转变为所述摇臂的摆动运动；以及the door retractable cylinder, the piston rod of which is connected to the rocker arm, so that the linear motion of the piston rod is transformed into the swing motion of the rocker arm; and
摇臂，其一端设置有滑轮，用于与所述飞行器舱门接触，以带动所述飞行器舱门完成收放动作。One end of the rocker arm is provided with a pulley, which is used to contact with the aircraft door to drive the aircraft door to complete the retracting action.
根据实施例，所述收放机构还包括：According to an embodiment, the retractable mechanism further includes:
舱门收放气缸连接件，其固定于所述试验台架，用于与所述舱门收放气缸的固定端连接；以及The hatch door retractable cylinder connector is fixed on the test bench and is used to connect with the fixed end of the hatch door retractable cylinder; and
摇臂连接件，其固定于所述试验台架，用于与所述摇臂的另一端连接。The rocker arm connecting piece is fixed on the test bench and is used for connecting with the other end of the rocker arm.
根据实施例，所述加载机构包括：According to an embodiment, the loading mechanism includes:
多个加载气缸，每个所述加载气缸的活塞杆用于对所述飞行器舱门的台阶施加加载力。A plurality of loading cylinders, the piston rod of each loading cylinder is used to apply loading force to the steps of the aircraft hatch.
根据实施例，所述加载机构还包括：According to an embodiment, the loading mechanism further includes:
力传感器，设置在每个所述加载气缸的活塞杆的末端，用于测量所述加载力；以及a force sensor disposed at the end of the piston rod of each of said loading cylinders for measuring said loading force; and
加载气缸连接件，其固定于所述试验台架，用于连接所述加载气缸。The loading cylinder connecting piece is fixed on the test bench and is used for connecting the loading cylinder.
根据实施例，所述加载机构还包括：According to an embodiment, the loading mechanism further includes:
方向调节机构，与所述力传感器连接，用于改变所述加载力的施加方向。The direction adjusting mechanism is connected with the force sensor and is used to change the direction of applying the loading force.
根据实施例，所述加载机构还包括：According to an embodiment, the loading mechanism further includes:
计算机控制系统，用于基于所测量的加载力来控制所述加载气缸。A computer control system for controlling the loading cylinder based on the measured loading force.
附图说明Description of drawings
图1示出根据本发明实施例的飞行器舱门疲劳试验装置的结构示意图。Fig. 1 shows a schematic structural diagram of an aircraft door fatigue test device according to an embodiment of the present invention.
图2示出根据本发明实施例的飞行器舱门疲劳试验装置的收放机构的结构示意图。Fig. 2 shows a schematic structural view of a retractable mechanism of an aircraft door fatigue test device according to an embodiment of the present invention.
图3示出根据本发明实施例的飞行器舱门疲劳试验装置的收放机构应用于试验台架的结构示意图。Fig. 3 shows a schematic structural view of the retractable mechanism of the aircraft door fatigue test device applied to the test bench according to the embodiment of the present invention.
图4示出根据本发明实施例的飞行器舱门疲劳试验装置的加载机构的结构示意图。Fig. 4 shows a schematic structural diagram of a loading mechanism of an aircraft door fatigue test device according to an embodiment of the present invention.
图5示出根据本发明实施例的飞行器舱门疲劳试验装置的加载机构应用于试验台的结构示意图。Fig. 5 shows a structural schematic diagram of the application of the loading mechanism of the aircraft door fatigue test device to the test bench according to the embodiment of the present invention.
具体实施方式detailed description
以下参照附图具体描述本发明实施例的飞行器舱门疲劳试验装置。The aircraft door fatigue test device of the embodiment of the present invention will be described in detail below with reference to the accompanying drawings.
图1示意性示出根据本发明实施例的飞行器舱门疲劳试验装置的结构。如图1所示，根据本实施例的飞行器舱门疲劳试验装置，包括：Fig. 1 schematically shows the structure of an aircraft door fatigue test device according to an embodiment of the present invention. As shown in Figure 1, the aircraft door fatigue test device according to the present embodiment includes:
收放机构1，用于模拟飞行器舱门的收放动作；以及The retractable mechanism 1 is used to simulate the retractable action of the aircraft door; and
加载机构2，用于对飞行器舱门的台阶施加加载力。The loading mechanism 2 is used to apply loading force to the steps of the aircraft hatch.
如图1所示，根据本实施例的飞行器舱门疲劳试验装置，还包括：As shown in Figure 1, the aircraft door fatigue test device according to the present embodiment also includes:
试验台架3，用于安装收放机构1和/或加载机构2。如以下将结合附图详细说明的，根据本发明实施例的飞行器舱门疲劳试验装置的收放机构和加载机构可以根据需要单独地或者组合地安装于试验台架。The test bench 3 is used for installing the retractable mechanism 1 and/or the loading mechanism 2 . As will be described in detail below with reference to the accompanying drawings, the retractable mechanism and the loading mechanism of the aircraft door fatigue test device according to the embodiment of the present invention can be installed on the test bench individually or in combination as required.
进一步地，图2示意性地示出根据本发明实施例的飞行器舱门疲劳试验装置的收放机构的结构。Further, Fig. 2 schematically shows the structure of the retractable mechanism of the aircraft door fatigue test device according to the embodiment of the present invention.
如图2所示，收放机构包括：As shown in Figure 2, the retractable mechanism includes:
舱门收放气缸4，其收放气缸活塞杆5，与摇臂6通过旋转部8连接，以使得气缸活塞杆5的直线运动转变为摇臂2的摆动运动；以及The door retractable cylinder 4, which retracts the cylinder piston rod 5, is connected with the rocker arm 6 through the rotating part 8, so that the linear motion of the cylinder piston rod 5 is converted into the swing motion of the rocker arm 2; and
摇臂6，其一端设置有滑轮7，其与飞行器舱门的接触为滚动摩擦，以带动飞行器舱门完成收放动作。The rocking arm 6 is provided with a pulley 7 at one end, and its contact with the aircraft door is rolling friction, so as to drive the aircraft door to complete the retracting action.
进一步地，如图2所示，收放机构还包括：Further, as shown in Figure 2, the retractable mechanism also includes:
收放气缸连接件10，其固定于试验台架，用于通过旋转部9与舱门收放气缸4的固定端连接；以及Retractable cylinder connector 10, which is fixed on the test bench, is used to connect with the fixed end of the door retractable cylinder 4 through the rotating part 9; and
摇臂连接件12，其固定于试验台架，用于通过旋转部11与摇臂6的另一端连接。The rocker arm connecting piece 12 is fixed on the test bench and is used to connect with the other end of the rocker arm 6 through the rotating part 11 .
根据实施例，收放机构还包括舱门收放控制阀，用于控制舱门收放气缸活塞杆5的直线运动。According to the embodiment, the retracting mechanism further includes a door retracting control valve for controlling the linear movement of the piston rod 5 of the door retracting cylinder.
如上所述，图3示出根据本发明实施例的飞行器舱门疲劳试验装置的收放机构单独地应用于试验台架的示意图。在仅对飞行器舱门进行收放动作疲劳试验的情况下，试验台架仅安装收放机构，并且试验台架的顶端框架13安装飞行器舱门。As mentioned above, FIG. 3 shows a schematic diagram of the retractable mechanism of the aircraft door fatigue test device according to the embodiment of the present invention applied separately to the test bench. In the case of only carrying out the fatigue test of retractable action on the aircraft hatch, the test bench is only equipped with a retractable mechanism, and the top frame 13 of the test bench is equipped with the aircraft hatch.
图4示出根据本发明实施例的飞行器舱门疲劳试验装置的加载机构的结构。Fig. 4 shows the structure of the loading mechanism of the aircraft door fatigue test device according to the embodiment of the present invention.
如图4所示，加载机构包括：As shown in Figure 4, the loading mechanism includes:
加载气缸14，其加载气缸活塞杆15，用于对飞行器舱门的台阶施加加载力。The loading cylinder 14, which loads the cylinder piston rod 15, is used to apply a loading force to the steps of the aircraft hatch.
进一步地，如图4所示，加载机构还可以包括：Further, as shown in Figure 4, the loading mechanism may also include:
力传感器16，设置在加载气缸活塞杆15的末端，用于测量加载力；以及A force sensor 16 is arranged at the end of the loading cylinder piston rod 15 for measuring the loading force; and
加载气缸连接件17，固定于试验台架，用于连接加载气缸14。The loading cylinder connecting piece 17 is fixed on the test bench and is used for connecting the loading cylinder 14 .
另外，如图4所示，加载机构还可以包括：In addition, as shown in Figure 4, the loading mechanism may also include:
方向调节机构18，与力传感器16连接，用于改变加载力的施加方向。例如，可以垂直加载模拟踩踏力，也可以以一定角度加载模拟气动载荷力。另外，通过组合多个加载气缸的布置方式，可以完成对飞行器舱门多个方位、多个层次的加载需求。The direction adjusting mechanism 18 is connected with the force sensor 16 and is used to change the direction of the loading force. For example, simulated pedaling forces can be loaded vertically, or aerodynamic loads can be loaded at an angle. In addition, by combining the arrangement of multiple loading cylinders, the loading requirements of multiple orientations and multiple levels of the aircraft hatch can be fulfilled.
根据实施例，加载机构还可以包括：According to an embodiment, the loading mechanism may also include:
计算机控制系统，用于基于所测量的加载力来控制加载气缸。A computer control system for controlling the loading cylinder based on the measured loading force.
如上所述，在仅对飞行器舱门的台阶进行踩踏力疲劳试验的情况下，如图5所示，本发明的飞行器舱门疲劳试验装置的加载机构可以单独安装在试验台架的横梁19上。As mentioned above, under the situation that only the step of aircraft hatch is carried out stepping force fatigue test, as shown in Figure 5, the loading mechanism of aircraft hatch fatigue test device of the present invention can be separately installed on the crossbeam 19 of test stand .
综上所述，本发明提供了一种飞行器舱门疲劳试验装置，可以实现舱门收放动作以及对舱门台阶进行踩踏力的加载，其采用气动能源提供动力，具有很高的清洁性和便捷性。To sum up, the present invention provides an aircraft door fatigue test device, which can realize the door retraction action and the loading of the stepping force on the door steps, which uses pneumatic energy to provide power, and has high cleanliness and safety. Convenience.
另外，本发明利用气缸和摇臂进行舱门收放的作动形式，简单可靠，适用性强；并且通过利用多个气缸进行组合加载的布置方式，具有一定的可扩展性。In addition, the present invention utilizes the air cylinder and the rocker arm to retract and retract the cabin door, which is simple, reliable, and highly applicable; and it has a certain degree of expandability through the arrangement of multiple air cylinders for combined loading.
并且，本发明将飞行器舱门收放功能和加载功能集成在一起，实现飞行器舱门疲劳试验的自动化，节约了人力成本和时间成本，提高了试验精度和可靠性。Moreover, the present invention integrates the aircraft door retractable function and the loading function, realizes the automation of the aircraft door fatigue test, saves labor costs and time costs, and improves test accuracy and reliability.
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710429734.5ACN106989919A (en) | 2017-06-08 | 2017-06-08 | A kind of aircraft door fatigue experimental device |
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710429734.5ACN106989919A (en) | 2017-06-08 | 2017-06-08 | A kind of aircraft door fatigue experimental device |
| Publication Number | Publication Date |
|---|---|
| CN106989919Atrue CN106989919A (en) | 2017-07-28 |
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710429734.5APendingCN106989919A (en) | 2017-06-08 | 2017-06-08 | A kind of aircraft door fatigue experimental device |
| Country | Link |
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| CN (1) | CN106989919A (en) |
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| Date | Code | Title | Description |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication | Application publication date:20170728 |