Loading system with anti-toppling protection device

Abstract

The invention belongs to the technical field of structural strength tests, and particularly relates to a loading system with an anti-toppling protection device, a loading frame is connected with a fixed frame through a driving device, and a loading device is mounted on the loading frame; during a loading test, the movable structure of the aircraft moves according to a set mode, the loading device applies a follow-up load to the movable structure of the aircraft, the driving device drives the loading frame, and the loading device and the movable structure of the aircraft are kept relatively static; the stop device comprises a locking structure and a power stop pin. The power stop pin is fixed on the fixed frame, the locking structure is fixedly installed on the loading frame, a plurality of pin shaft holes are formed in the locking structure, and the pin shaft holes are distributed along the locking structure relative to the motion trail of the power stop pin; when the stop pin of the power stop pin extends out, the stop pin is inserted into the pin shaft hole to limit the movement of the loading frame, the loading frame can be effectively fixed at any position, and the loss of a test piece after falling is prevented.

Description

Technical Field

[0001] The present invention belongs to the technical field of structural strength testing, and in particular relates to a loading system with an anti-dumping protection device. Background Art

[0002] The prevention of tipping in this application means preventing two objects from moving relative to each other. Whether the movable structures in the aircraft structure (such as flaps, slats, rudders, elevators, spoilers, ailerons, etc.) can work normally directly determines the flight safety and mission execution capability of the aircraft. The movable structure function test is the most effective method to inspect and test the failure mode, safety and reliability of wing retraction and extension. It is an important ground verification test that needs to be conducted before the aircraft is finalized. Conducting aircraft movable wing function tests plays an irreplaceable role in the development process of new aircraft and is an important part of the aircraft structure strength test.

[0003] The functional test of the movable structure applies a dynamic load of variable direction and magnitude to the movable structure during its movement. Therefore, the loading device needs to move synchronously with the movable structure. The traditional method is to fix the loading device on the loading frame and control the loading frame to follow the movement through the driving mechanism. In order to prevent the frame and the test piece from moving out of sync or the frame driving mechanism from accidentally failing, causing the loading frame to tip over and damage the test piece, a stop block is set at the extreme position of the loading frame movement. When the loading frame moves to this position, the stop block limits the rotation of the loading frame, thereby protecting the test piece. The existing protection device can protect the test piece by tipping over the frame at the extreme position, but cannot protect the test piece by tipping over the loading frame at any position.

[0004] The present invention can effectively fix the loading frame at any position, prevent the loading frame from tipping over significantly, and effectively protect the test piece. Summary of the invention

[0005] In order to solve the above problems, the present application provides a loading system with an anti-dumping protection device, comprising:

[0006] Fixed frames, loading frames, loading devices, planes and stop devices;

[0007] The loading frame is connected to the fixed frame through a driving device, and the loading device is installed on the loading frame; during the loading test, the movable structure of the aircraft moves according to the set mode, the loading device applies a follow-up load to the movable structure of the aircraft, and the driving device drives the loading frame, the loading device and the movable structure of the aircraft to remain relatively still;

[0008] The stopping device includes: a locking structure and a power stop pin; the power stop pin is fixed on the fixed frame, the locking structure is fixedly installed on the loading frame, and the locking structure has a plurality of pin shaft holes, which are distributed along the movement trajectory of the locking structure relative to the power stop pin; when the stop pin of the power stop pin is extended, it is inserted into the pin shaft hole to limit the movement of the loading frame.

[0009] Preferably, the power stop pin includes: an accumulator, an actuator and an emergency system; the piston rod of the actuator is equipped with a stop pin, the accumulator is connected to the rodless chamber of the actuator, and the emergency system is connected to the rod chamber of the actuator. During the test, the emergency system pressurizes the rod chamber, the piston rod is retracted, and the hydraulic oil in the rodless chamber is pressed into the accumulator; when the emergency system is in emergency protection, the hydraulic oil in the accumulator enters the rodless chamber, the piston rod is extended, and the stop pin is inserted into the pin shaft hole of the locking structure, thereby limiting the movement of the loading frame to prevent it from colliding with the aircraft.

[0010] Preferably, the outlet of the accumulator is provided with a pressure gauge.

[0011] Preferably, the power stop pin includes: a gas generating device, a pneumatic actuator and an emergency system; the piston rod of the actuator is installed with a stop pin. During the test, the rod chamber of the pneumatic actuator is kept at a low pressure, the gas generating device is connected to the rodless chamber, there is no gas in the rodless chamber, and the piston rod is retracted; when the emergency system is in emergency protection, the gas generating device generates gas that enters the rodless chamber, the piston rod extends, and the stop pin is inserted into the pin shaft hole of the locking structure, thereby limiting the movement of the loading frame to prevent it from colliding with the aircraft.

[0012] Preferably, the gas generating device is filled with a plurality of mutually isolated chemical agents, and when the emergency system is in emergency protection, the plurality of chemical agents are mixed to generate gas which is pushed into the rodless cavity.

[0013] Preferably, the emergency system has a manual emergency switch and an automatic emergency switch, and when the control module of the automatic emergency switch detects a failure of the drive device, the emergency system is activated.

[0014] Preferably, the emergency system has a manual emergency switch and an automatic emergency switch. During the test, when the control module of the automatic emergency switch detects through a sensor that the movable structure of the aircraft and the loading frame are in relative motion, the emergency system is activated.

[0015] Preferably, the stopping device further comprises a manual pin, which is manually pushed and inserted into the pin shaft hole of the locking structure.

[0016] The advantages of the present application include: the device can effectively fix the loading frame at any position to prevent damage to the test piece after tipping over; the device is simple and convenient to install and disassemble, and is light and easy to install. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1It is a schematic diagram of a loading frame and a stop device according to a preferred embodiment of the present application.

[0018] Figure 2 It is a schematic diagram of the principle of a power stop pin in a preferred embodiment of the present application.

[0019] Figure 3 It is a schematic diagram of the power stop pin structure of a preferred embodiment of the present application. DETAILED DESCRIPTION

[0020] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0021] like Figure 1-Figure 2 As shown, the present application provides a loading system with an anti-dumping protection device, comprising:

[0022] A fixed frame, a loading frame 1, a loading device, an aircraft and a stop device;

[0023] The loading frame 1 is connected to the fixed frame through a driving device, and the loading device is installed on the loading frame 1; during the loading test, the movable structure of the aircraft moves according to the set mode, the loading device applies a follow-up load to the movable structure of the aircraft, and the driving device drives the loading frame 1, the loading device and the movable structure of the aircraft to remain relatively still;

[0024] The stopping device includes: a locking structure 32 and a power stop pin 222; the power stop pin 222 is fixed on the fixed frame, the locking structure 32 is fixedly installed on the loading frame 1, and the locking structure 32 has a plurality of pin shaft holes, which are distributed along the movement trajectory of the locking structure 32 relative to the power stop pin 222; when the stop pin 22 of the power stop pin 222 is extended, it is inserted into the pin shaft hole to limit the movement of the loading frame 1.

[0025] In some optional embodiments, the power stop pin 222 includes: an accumulator 21, an actuator 24 and an emergency system 23; the piston rod of the actuator 24 is equipped with a stop pin 22, the accumulator 21 is connected to the rodless chamber of the actuator 24, and the emergency system 23 is connected to the rod chamber of the actuator 24. During the test, the emergency system 23 pressurizes the rod chamber, the piston rod is retracted, and the hydraulic oil in the rodless chamber is pressed into the accumulator 21; when the emergency system 23 is in emergency protection, the hydraulic oil in the accumulator 21 enters the rodless chamber, the piston rod is extended, and the stop pin 22 is inserted into the pin shaft hole of the locking structure 32, thereby limiting the movement of the loading frame 1 to prevent it from colliding with the aircraft.

[0026] In some optional embodiments, a pressure gauge is provided at the outlet of the accumulator.

[0027] The above technical features can show whether the accumulator is normal.

[0028] In some optional embodiments, the power stop pin includes: a gas generating device, a pneumatic actuator and an emergency system; the piston rod of the actuator is installed with a stop pin. During the test, the rod chamber of the pneumatic actuator is kept at a low pressure, the gas generating device is connected to the rodless chamber, there is no gas in the rodless chamber, and the piston rod is retracted; when the emergency system is in emergency protection, the gas generating device generates gas that enters the rodless chamber, the piston rod extends, and the stop pin is inserted into the pin shaft hole of the locking structure, thereby limiting the movement of the loading frame to prevent it from colliding with the aircraft.

[0029] In some optional embodiments, the gas generating device is filled with multiple mutually isolated chemical agents. When the emergency system is in emergency protection, the multiple chemical agents are mixed to generate gas that is pushed into the rodless cavity. The above technical features can make the stop device a separate module without the need for the hydraulic system to provide hydraulic oil. When the stop device has a manual pin, the manual pin is manually pushed into the pin shaft hole of the locking structure to achieve both manual and emergency working modes.

[0030] In some optional embodiments, the emergency system has a manual emergency switch and an automatic emergency switch, and when a control module of the automatic emergency switch detects a failure of the drive device, the emergency system is activated.

[0031] In some optional embodiments, the emergency system has a manual emergency switch and an automatic emergency switch. During the test, when the control module of the automatic emergency switch detects relative movement between the movable structure of the aircraft and the loading frame through a sensor, the emergency system is activated.

[0032] In some optional embodiments, the stopping device further comprises a manual pin, which is manually pushed and inserted into the pin shaft hole of the locking structure.

[0033] The advantages of the present application include: the device can effectively fix the loading frame at any position to prevent damage to the test piece after tipping over; the device is simple and convenient to install and disassemble, and is light and easy to install.

[0034] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A loading system with an anti-dumping protection device, characterized in that: include: Fixed frames, loading frames, loading devices, planes and stop devices; The loading frame is connected to the fixed frame through a driving device, and the loading device is installed on the loading frame; during the loading test, the movable structure of the aircraft moves according to the set mode, the loading device applies a follow-up load to the movable structure of the aircraft, and the driving device drives the loading frame, the loading device and the movable structure of the aircraft to remain relatively still; The stopping device comprises: a locking structure and a power stopping pin; The power stop pin is fixed on the fixed frame, and the locking structure is fixedly installed on the loading frame. The locking structure has multiple pin shaft holes, and the pin shaft holes are distributed along the movement trajectory of the locking structure relative to the power stop pin; when the stop pin of the power stop pin is extended, it is inserted into the pin shaft hole to limit the movement of the loading frame.

2. The loading system with anti-dumping protection device according to claim 1, characterized in that: The power stop pin includes: an accumulator, an actuator and an emergency system; the piston rod of the actuator is equipped with a stop pin, the accumulator is connected to the rodless chamber of the actuator, and the emergency system is connected to the rod chamber of the actuator. During the test, the emergency system pressurizes the rod chamber, the piston rod is retracted, and the hydraulic oil in the rodless chamber is pressed into the accumulator; when the emergency system is in emergency protection, the hydraulic oil in the accumulator enters the rodless chamber, the piston rod is extended, and the stop pin is inserted into the pin shaft hole of the locking structure, thereby limiting the movement of the loading frame to prevent it from colliding with the aircraft.

3. The loading system with anti-dumping protection device according to claim 2, characterized in that: The outlet of the accumulator is provided with a pressure gauge.

4. The loading system with anti-dumping protection device according to claim 1, characterized in that: The dynamic stop pin includes: a gas generating device, a pneumatic actuator and an emergency system; the piston rod of the actuator is installed with a stop pin. During the test, the rod chamber of the pneumatic actuator is kept at a low pressure, the gas generating device is connected to the rodless chamber, there is no gas in the rodless chamber, and the piston rod is retracted; when the emergency system is in emergency protection, the gas generating device generates gas that enters the rodless chamber, the piston rod extends, and the stop pin is inserted into the pin shaft hole of the locking structure, thereby limiting the movement of the loading frame to prevent it from colliding with the aircraft.

5. The loading system with anti-dumping protection device according to claim 4, characterized in that: The gas generating device is filled with a variety of chemical agents that are isolated from each other. When the emergency system is in emergency protection, the various chemical agents are mixed to generate gas that is pushed into the rodless cavity.

6. The loading system with an anti-dumping protection device according to claim 2 or 4, characterized in that: The emergency system has a manual emergency switch and an automatic emergency switch. When a control module of the automatic emergency switch detects a failure of the drive device, the emergency system is started.

7. The loading system with an anti-dumping protection device according to claim 2 or 4, characterized in that: The emergency system has a manual emergency switch and an automatic emergency switch. During the test, when the control module of the automatic emergency switch detects the relative movement between the movable structure of the aircraft and the loading frame through the sensor, the emergency system is activated.

8. The loading system with anti-dumping protection device according to claim 1, characterized in that: The stopping device also has a manual pin, which is manually pushed and inserted into the pin shaft hole of the locking structure.

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