A loading system with anti-tip protection

Abstract

The application belongs to the technical field of structural strength test, and particularly relates to a loading system with anti-toppling protection device. A loading frame is connected with a fixed frame through a driving device, and a loading device is installed on the loading frame. During loading test, a movable structure of an airplane moves according to a set mode, the loading device applies follow-up load to the movable structure of the airplane, and the driving device drives the loading frame and the loading device to keep relative static with the movable structure of the airplane. The stop device comprises a locking structure and a power stop 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 is provided with a plurality of pin shaft holes, and the pin shaft holes are distributed along the movement track of the locking structure relative to the power stop pin. When the stop pin of the power stop pin is extended, the stop pin is inserted into the pin shaft hole to limit the movement of the loading frame. The device can effectively fix the loading frame at any position and prevent the test piece from being damaged after toppling.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of structural strength test, and particularly relates to a loading system with a protection device against tilting. BACKGROUND

[0002] The application prevents tilting, that is, prevents relative movement of two objects, and whether a movable structure (such as a flap, a slot wing, a rudder, an elevator, a spoiler, a aileron, etc.) in an aircraft structure can normally work directly determines flight safety and mission execution capability of the aircraft. Movable structure function test is the most effective method for checking and testing failure mode, safety and reliability of wing surface retraction and release, and is an important ground verification test before aircraft finalization. The movable structure function test plays an irreplaceable role in the process of developing a new aircraft and is an important part of aircraft structural strength test.

[0003] The movable structure function test applies variable direction and variable size dynamic load to the movable structure during movement of the movable structure. Therefore, the loading device needs to move synchronously with the movable structure. In the traditional method, the loading device is fixed to a loading frame, and the loading frame is controlled to move synchronously by a driving mechanism. In order to prevent the movable structure from being damaged due to tilting of the loading frame at the limit position and accidental failure of the driving mechanism of the frame, a stopper is arranged at the limit position of the loading frame. When the loading frame moves to the limit position, the stopper limits rotation of the loading frame, thereby protecting the movable structure. The existing protection device can protect the movable structure from tilting of the loading frame at the limit position, but cannot protect the movable structure from tilting of the loading frame at any position.

[0004] The application can effectively fix the loading frame at any position, prevent the loading frame from tilting greatly, and effectively protect the movable structure. SUMMARY

[0005] In order to solve the above problems, the application provides a loading system with a protection device against tilting, which comprises:

[0006] a fixed frame, a loading frame, a loading device, an aircraft and a stopper device;

[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 loading test, the movable structure of the aircraft moves in a set manner, the loading device applies synchronous 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 keep relatively static.

[0008] The stop device comprises a locking structure and a power stop pin; the power stop pin is fixed on a fixed frame, and the locking structure is fixedly installed on a loading frame; the locking structure is provided with a plurality of pin shaft holes distributed along the movement track of the power stop pin; when the stop pin of the power stop pin extends, the stop pin is inserted into the pin shaft hole to limit the movement of the loading frame.

[0009] Preferably, the power stop pin comprises an accumulator, an actuator cylinder and an emergency system; the piston rod of the actuator cylinder is provided with the stop pin; the accumulator is communicated with the rodless cavity of the actuator cylinder; the emergency system is communicated with the rod cavity of the actuator cylinder; in the test, the rod cavity is pressurized by the emergency system, the piston rod is retracted, and the hydraulic oil in the rodless cavity is pressed into the accumulator; when the emergency system is in emergency protection, the hydraulic oil in the accumulator enters the rodless cavity, the piston rod extends, the stop pin is inserted into the pin shaft hole of the locking structure, thereby limiting the movement of the loading frame and preventing the loading frame from colliding with the airplane.

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

[0011] Preferably, the power stop pin comprises a gas generating device, a pneumatic actuator cylinder and an emergency system; the piston rod of the actuator cylinder is provided with the stop pin; in the test, the rod cavity of the pneumatic actuator cylinder is kept at low pressure, the gas generating device is communicated with the rodless cavity, and the rodless cavity is free of gas; when the emergency system is in emergency protection, the gas generating device generates gas to enter the rodless cavity, 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 and preventing the loading frame from colliding with the airplane.

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

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

[0014] Preferably, the emergency system has a manual emergency switch and an automatic emergency switch; in the test, when the control module of the automatic emergency switch detects that the movable structure of the airplane moves relative to the loading frame through a sensor, the emergency system is started.

[0015] Preferably, the stop device further has a manual pin; the manual pin is manually pushed to be inserted into the pin shaft hole of the locking structure.

[0016] The advantages of the present application include that the device can effectively fix the loading frame at any position, prevent loss caused by the test piece after tilting, and is simple and convenient to install and dismount. BRIEF DESCRIPTION OF DRAWINGS

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

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

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

[0020] In order to make the technical scheme of the application and its advantages clearer, the technical scheme of the application will be further described in detail below with reference to the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the application, and are only used to explain the application, but not to limit the application. It should be noted that, for the purpose of description, only parts related to the application are shown in the drawings, and other related parts can be referred to the usual design. In the case of no conflict, the embodiments in the application and the technical features in the embodiments can be combined to obtain new embodiments.

[0021] As Figures 1-2 shown, the application provides a loading system with anti-toppling protection device, comprising:

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

[0023] The loading frame 1 is connected with the fixed frame through the driving device, and the loading device is installed on the loading frame 1. During loading test, the movable structure of the aircraft moves according to the set mode, the loading device applies 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 keep relatively static.

[0024] The stop device comprises: locking structure 32 and power stop pin 222; the power stop pin 222 is fixed on the fixed frame, and 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 track 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 alternative embodiments, the power stop pin 222 comprises an accumulator 21, an actuator 24, and an emergency system 23; the piston rod of the actuator 24 is provided with the stop pin 22, the accumulator 21 is in communication with the rodless cavity of the actuator 24, and the emergency system 23 is in communication with the rod cavity of the actuator 24; in the test, the emergency system 23 pressurizes the rod cavity, the piston rod is retracted, and the hydraulic oil in the rodless cavity 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 cavity, the piston rod is extended, 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 and preventing it from colliding with the aircraft.

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

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

[0028] In some alternative embodiments, the power stop pin comprises a gas generating device, a pneumatic actuator, and an emergency system; the piston rod of the actuator is provided with the stop pin, in the test, the rod cavity of the pneumatic actuator is kept at low pressure, the gas generating device is in communication with the rodless cavity, the rodless cavity is gas-free, and the piston rod is retracted; when the emergency system is in emergency protection, the gas generating device generates gas to enter the rodless cavity, 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 and preventing it from colliding with the aircraft.

[0029] In some alternative embodiments, the gas generating device is filled with multiple mutually isolated chemical agents, and when the emergency system is in emergency protection, the multiple chemical agents are mixed to generate gas to push into the rodless cavity. The above technical features can make the stop device become a separate module without the need for a 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 realize two working modes of manual and emergency.

[0030] In some alternative embodiments, the emergency system has a manual emergency switch and an automatic emergency switch, and the control module of the automatic emergency switch starts the emergency system when detecting a failure of the driving device.

[0031] In some alternative embodiments, the emergency system has a manual emergency switch and an automatic emergency switch, and in the test, the control module of the automatic emergency switch starts the emergency system when detecting a relative movement between the movable structure of the aircraft and the loading frame through a sensor.

[0032] In some alternative embodiments, the stop device further has a manual pin, and the manual pin is manually pushed into the pin shaft hole of the locking structure.

[0033] The advantages of the application include: the device can realize effective fixing of the loading frame at any position, prevent loss caused by the test piece after tilting, and is simple and convenient to install and dismount, and is light and easy to install.

[0034] The above is only a specific embodiment of the application, but the protection scope of the application is not limited thereto, any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the application, which should be covered in the protection scope of the application. Therefore, the protection scope of the application should be subject to the protection scope of the claims.

Claims

1. A loading system with anti-toppling protection, characterized in that, The application relates to a loading device for movable structures of an airplane, comprising: a fixed frame, a loading frame, a loading device, an airplane and a stop device; the loading frame is connected with the fixed frame through a driving device, and the loading device is installed on the loading frame; during loading test, the movable structure of the airplane moves in a set mode, the loading device applies follow-up load to the movable structure of the airplane, and the driving device drives the loading frame, the loading device and the movable structure of the airplane to keep 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, the locking structure is provided with a plurality of pin shaft holes which are distributed along the movement track of the power stop pin; when the stop pin of the power stop pin is extended, the stop pin is inserted into the pin shaft hole to limit the movement of the loading frame; the power stop pin comprises an accumulator, an actuating cylinder and an emergency system; a piston rod of the actuating cylinder is provided with the stop pin, the accumulator is communicated with a rodless cavity of the actuating cylinder, the emergency system is communicated with a rod cavity of the actuating cylinder, during the test, the emergency system pressurizes the rod cavity, the piston rod is retracted, and hydraulic oil in the rodless cavity is pressed into the accumulator; when the emergency system is in emergency protection, the hydraulic oil in the accumulator enters the rodless cavity, the piston rod is extended, the stop pin is inserted into the pin shaft hole of the locking structure, thereby limiting the movement of the loading frame and preventing the loading frame from colliding with the airplane, or the power stop pin comprises a gas generating device, a pneumatic actuating cylinder and an emergency system; a piston rod of the actuating cylinder is provided with the stop pin, during the test, the rod cavity of the pneumatic actuating cylinder is kept at low pressure, the gas generating device is communicated with the rodless cavity, the rodless cavity is free of gas, and the piston rod is retracted; when the emergency system is in emergency protection, the gas generating device generates gas to enter the rodless cavity, the piston rod is extended, the stop pin is inserted into the pin shaft hole of the locking structure, thereby limiting the movement of the loading frame and preventing the loading frame from colliding with the airplane.

2. A loading system with anti-toppling protection as claimed in claim 1, characterized in that A pressure gauge is arranged at the outlet of the accumulator.

3. A loading system with anti-toppling protection as claimed in claim 1, characterized in that The gas generating device is filled with a plurality of mutually isolated chemical agents; when the emergency system is in emergency protection, the plurality of chemical agents are mixed to generate gas to push into the rodless cavity.

4. The loading system with anti-topple protection device of claim 1, wherein, The emergency system is provided with a manual emergency switch and an automatic emergency switch; when the control module of the automatic emergency switch detects that the driving device is faulty, the emergency system is started.

5. The loading system with anti-topple protection device of claim 1, wherein, During the test, when the control module of the automatic emergency switch detects that the movable structure of the airplane and the loading frame move relatively through a sensor, the emergency system is started.

6. The loading system with anti-topple protection as claimed in claim 1, characterized in that, The stop device is further provided with a manual pin; the manual pin is manually pushed to be inserted into the pin shaft hole of the locking structure.

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