A load simulation test apparatus for an aircraft suspension device

Abstract

This invention provides a load simulation test device for aircraft suspension systems. In this device, the suspension unit includes a slide rail fixed to a test bench and a pair of hanging blocks connected to the aircraft suspension system. The hanging blocks are slidably mounted on the slide rail. The center of gravity simulation frame includes a frame and two pairs of hanging rings respectively connected to the hooks of the suspension system. The frame has center of gravity holes corresponding to the hanging rings, and pins pass through the center of gravity holes and pin holes on the connecting seat. A drive component is fixed to the test bench. A tension sensor is mounted on the drive component and connected to the connecting seat, such that the drive component moves the connecting seat, pulling the center of gravity simulation frame, thereby applying or releasing loads to the aircraft suspension system. This invention uses a pair of slidable hanging blocks, allowing the aircraft suspension system to slide left and right after being clamped during testing to adjust the attachment points of the two sets of hooks and the center of gravity position of the loaded cargo. It also enables rapid clamping of the suspension system and allows for load simulation tests at different center of gravity positions of the two sets of attachment points with simple operation.

Description

Technical Field

[0001] This invention belongs to the field of aircraft suspension system maintenance technology, specifically relating to a load simulation test device for aircraft suspension systems. Background Technology

[0002] Aircraft suspension systems are devices installed under the wings or fuselage of an aircraft to suspend heavy cargo such as fuel tanks. Aircraft suspension systems typically have two sets of hooks, each used to suspend cargo with different loads. During maintenance, it is necessary to simulate the actual load conditions of the aircraft suspension system to adjust its mechanical performance. Existing load simulation test benches for aircraft suspension systems use weights for loading during simulations, and employ two separate devices to load the two sets of hooks. This method cannot simultaneously simulate loads at different center-of-gravity positions of the two sets of hooks, making the operation cumbersome and unsuitable for production needs. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to overcome the shortcomings of existing load simulation test benches for aircraft suspension devices, which use weights for loading and cannot simultaneously simulate tests of two sets of suspension points at different center of gravity positions. The present invention provides a load simulation test device for aircraft suspension devices. Using this load simulation test device, ground load simulation tests of two sets of suspension points at different center of gravity positions of aircraft suspension devices can be easily operated.

[0004] To achieve the above objectives, the technical solution provided by this invention is:

[0005] A load simulation test device for aircraft suspension systems is characterized in that the load simulation test device includes a support unit, a suspension unit, a center of gravity simulation unit, a drive unit, and a load monitoring unit.

[0006] The support unit is used to support the suspension unit, center of gravity simulation unit, drive unit and load monitoring unit, and the support unit includes a platform;

[0007] The suspension unit includes a slide rail and a hanging block.

[0008] The slide rail is fixed to the upper part of the platform.

[0009] The mounting blocks are in pairs and are used to connect the aircraft suspension system to be tested for ground load simulation.

[0010] The hanging block is slidably mounted on the slide rail;

[0011] The center of gravity simulation unit is located below the suspension unit and includes, from top to bottom, a center of gravity simulation frame, a pin, and a connecting seat.

[0012] The center of gravity simulation frame includes a frame and two pairs of hanging rings for connecting to two sets of hooks on the aircraft suspension system. The frame has center of gravity holes corresponding to the two pairs of hanging rings.

[0013] The pin passes through the center hole and the pin hole on the connector.

[0014] The drive unit is used to drive the center of gravity simulation unit to move up and down, and includes drive components.

[0015] The drive unit is fixed to the frame;

[0016] The load monitoring unit is used to detect and display the loads applied to the aircraft suspension system. The load monitoring unit includes a tension sensor and a display.

[0017] A tension sensor is mounted on the output of the drive unit and connected to the connecting seat, so that: the drive unit moves the connecting seat up and down, pulling the center of gravity simulation frame, thereby applying or releasing loads on the aircraft suspension system, and the tension sensor detects the magnitude of the applied load.

[0018] The display is electrically connected to the tension sensor to show the magnitude of the applied load.

[0019] Furthermore, the center of gravity simulation frame also includes a protrusion protruding from the frame corresponding to the hanging ring. The protrusion includes a pair of lugs, the hanging ring is positioned between the pair of lugs, and the lugs and the hanging ring are connected by bolts and nuts, so that the hanging ring can rotate relative to the lugs.

[0020] Furthermore, the driving component is a hydraulic cylinder, and the driving unit also includes a hydraulic station that provides power to the hydraulic cylinder.

[0021] Furthermore, the load simulation test equipment includes a separate test bench and a control console; the test bench includes a support unit, a suspension unit, a center of gravity simulation unit, and a drive unit, and includes a tension sensor for load monitoring; the hydraulic station is located in the control console.

[0022] Furthermore, the console also includes a control panel for operators to monitor the load simulation test equipment, with the load monitoring unit's display located on the control panel.

[0023] Furthermore, the test bench includes an upper part, a lower part, and an open cavity located between the upper part and the lower part; a slide rail is fixed to the upper part, and a drive unit is installed in the lower part; the lower part has a through hole facing the cavity, and a part of the center of gravity simulation frame is located in the cavity and passes through the through hole.

[0024] Furthermore, the hanger includes a sliding member and a latching member connected together. The sliding member slides within a slide rail, and the latching member includes a hook and a stop. The hook is used to hook the aircraft suspension device, and the stop is mounted to the hook and can rotate relative to the hook and lock to prevent the aircraft suspension device from detaching from the hanger.

[0025] Furthermore, the load simulation test equipment also includes a control switch, which is fixed to the hanging block so that the push rod of the control switch is aligned with the trigger switch of the aircraft suspension device.

[0026] Furthermore, the connector includes a disc portion and a U-shaped portion, the drive unit is connected to the disc portion, the pin hole is located on the U-shaped portion, and the center of gravity simulation frame is inserted into the U-shaped portion.

[0027] The advantages of this invention are:

[0028] 1. The load simulation test equipment for aircraft suspension devices of the present invention includes a support unit, a suspension unit, a center of gravity simulation unit, a drive unit, and a load monitoring unit. The slide rail of the suspension unit is fixed to the platform of the support unit. A pair of hanging blocks of the suspension unit for connecting the aircraft suspension device can slide relative to the slide rail. Two pairs of hanging rings on the center of gravity simulation frame of the center of gravity simulation unit are correspondingly suspended on two sets of hooks of the aircraft suspension device. The drive unit's drive component pulls the center of gravity simulation frame downward through the pin and connecting seat of the center of gravity simulation unit, thereby applying a load to the aircraft suspension device. The load monitoring unit detects and displays the applied load. The present invention adopts a pair of sliding hanging block structures, which allows the aircraft suspension device to slide left and right after being clamped during the simulation test to adjust the hanging points of the two sets of hooks and the center of gravity position of the corresponding loaded cargo. It also enables quick clamping of the suspension device and allows for ground load simulation tests at different center of gravity positions of the two sets of hanging points with simple operation.

[0029] 2. By setting up independent test benches and control consoles, the test benches include hydraulic cylinders and components connected to the aircraft suspension system, while the control consoles include hydraulic stations and control panels for operators to monitor the load simulation test equipment. This isolates the operating platform where the aircraft suspension system is located from the operating platform where the operators conducting the simulation test are located, ensuring the safety of both the product and personnel.

[0030] 3. A control switch fixed to the mounting block is provided. The push rod of the control switch is aligned with the trigger switch of the aircraft suspension device, which can check parameters such as the linkage operation flexibility and trigger force of the suspension device during simulated loading. Attached Figure Description

[0031] The features and advantages of the invention will become more readily apparent from the following description with reference to the accompanying drawings, which are not drawn to scale and some features are enlarged or reduced to show details of specific parts.

[0032] Figure 1 This is a schematic perspective view of a load simulation test apparatus for an aircraft suspension device according to an exemplary embodiment of the present invention;

[0033] Figure 2 This is a schematic front view of a load simulation test apparatus for an aircraft suspension device according to an exemplary embodiment of the present invention;

[0034] Figure 3 This is a schematic perspective view of a test bench in a load simulation test apparatus for an aircraft suspension device according to an exemplary embodiment of the present invention.

[0035] Figure 4 This is a schematic perspective view of a slide rail in a load simulation test apparatus for an aircraft suspension device according to an exemplary embodiment of the present invention.

[0036] Figure 5A This is a schematic perspective view of a hanging block in a load simulation test apparatus for an aircraft suspension device according to an exemplary embodiment of the present invention;

[0037] Figure 5B This is a schematic side view of a hanging block in a load simulation test apparatus for an aircraft suspension device according to an exemplary embodiment of the present invention;

[0038] Figure 6 This is a schematic perspective view of the mounting structure of the hanging block and control switch in a load simulation test device for an aircraft suspension device according to an exemplary embodiment of the present invention.

[0039] Figure 7 This is a schematic perspective view of a center of gravity simulation frame in a load simulation test apparatus for an aircraft suspension device according to an exemplary embodiment of the present invention.

[0040] Figure 8 This is a schematic perspective view of a pin in a load simulation test apparatus for an aircraft suspension device according to an exemplary embodiment of the present invention.

[0041] Figure 9 This is a schematic perspective view of a connecting seat in a load simulation test apparatus for an aircraft suspension device according to an exemplary embodiment of the present invention;

[0042] Figure 10 This is a schematic perspective view of the mounting structure of the tension sensor and the hydraulic cylinder in a load simulation test device for an aircraft suspension device according to an exemplary embodiment of the present invention.

[0043] Figure 11 This is a schematic perspective view of a load simulation test apparatus for an aircraft suspension device according to an exemplary embodiment of the present invention, wherein the load simulation test apparatus includes a test bench and a control console;

[0044] Figure 12 yes Figure 11 A perspective view of a control console in a load simulation test apparatus for an aircraft suspension device according to an exemplary embodiment of the present invention, showing the hydraulic station in the control console.

[0045] In the picture:

[0046] 11-Frame, 111-Upper part, 112-Lower part, 113-Cavity, 114-Handle, 115-Lifting hook, 116-Anchor bolt, 117-Door, 118-Through hole, 119-Control switch power supply socket;

[0047] 21-Slide rail, 211-Hole in slide rail;

[0048] 22-Hanging block, 221-Sliding part, 222-Snap fastener, 2221-Hook, 2222-Stop part;

[0049] 31-Center of gravity simulation frame, 311-Frame, 312-Hanging ring, 313-Center of gravity hole, 314-Lug;

[0050] 32-Pin;

[0051] 33-Connector, 331-Disc, 332-U-shaped part, 333-Pin hole;

[0052] 41-Driver;

[0053] 42-Hydraulic station;

[0054] 51-Tension sensor;

[0055] 52 - Monitor;

[0056] 61-Control switch;

[0057] 1000 - Aircraft suspension system;

[0058] 100 - Test bench;

[0059] 200-Control console, 201-Control panel, 202-Emergency switch, 203-Power switch. Detailed Implementation

[0060] The present invention will now be described in detail with reference to the accompanying drawings and exemplary embodiments thereof. It should be noted that the following detailed description of the present invention is for illustrative purposes only and is not intended to limit the scope of the invention.

[0061] First refer to Figure 1 and Figure 2As an exemplary embodiment of the present invention, the load simulation test equipment for aircraft suspension devices may include a support unit, a suspension unit, a center of gravity simulation unit, a drive unit, and a load monitoring unit.

[0062] The support unit can be used to support the suspension unit, center of gravity simulation unit, drive unit, and load monitoring unit. It is a major load-bearing structural component and the main structure for mounting aircraft suspension devices and drive units, etc. The support unit may include a platform 11. In some embodiments of the present invention, such as... Figure 3 As shown, the test bench 11 may include an upper part 111, a lower part 112, and an open cavity 113 located between the upper part 111 and the lower part 112. The lower part 112 of the test bench 11 has a through hole 118 facing the cavity 113 to accommodate, fix, and support the various components of the load simulation test equipment. The test bench 11 may also include two handles 114 located on the upper part 111 for operators to lift the test bench 11 by hand to move it. Two lifting hooks 115 may also be provided on the left and right end faces of the upper part 111 for lifting the entire load simulation test equipment by means of lifting equipment.

[0063] Return to reference Figure 1 and Figure 2 The platform 11 can also be provided with anchor bolts 116 below the lower part 112 to securely fix the platform 11. The number of anchor bolts 116 can be four.

[0064] The suspension unit may include a slide rail 21 and mounting blocks 22. The slide rail 21 is fixed to the upper part of the test bench 11, particularly to the upper portion 111 of the test bench 11. The slide rail 21 is the main load-bearing element and also the main element for realizing dual loads. The mounting blocks 22 are a pair and are used to connect the aircraft suspension device 1000 to be tested for ground load simulation.

[0065] In certain embodiments, such as Figure 4 As shown, the slide rail 21 can be generally rectangular in shape and has a groove in which the hanging block 22 slides. The bottom of the groove of the slide rail 21 can be provided with a plurality of holes 211, shown in two rows in the figure, which are used to connect the slide rail 21 to the frame 11, for example by means of screws.

[0066] Two hanging blocks 22 are slidably mounted on the slide rail 21, i.e., they can slide left and right. Both hanging blocks 22 can slide relative to the slide rail 21, which allows for easy adjustment of the position of the two hanging blocks 22 when installing the aircraft suspension device during simulation tests, thereby achieving quick clamping of the suspension device. After clamping, the two hanging blocks 22 can also be slid left and right together to adjust the position of the aircraft suspension device suspended on it, and thus adjust the position of the attachment points of the two sets of hooks in the suspension device, thereby simultaneously adjusting the center of gravity of the loaded cargo.

[0067] In some embodiments of the present invention, such as Figure 5A and Figure 5B As shown, the hanging block 22 may include a sliding member 221 and a fastener 222 connected together. The sliding member 221 is generally cuboid, and its front and rear ends can be engaged in the grooves of the slide rail 21 and slide within the grooves to adjust its position. The fastener 222 includes a hook 2221 and a stop 2222. The hook 2221 is used to hook the aircraft suspension device 1000. The hook 2221 is fixed to the slider 221 by bolts passing through holes in the hook 2221 and holes in the slider 221 (specifically, four are shown in the figure). The stop 2222 is installed to the hook 2221, preferably by bolts and nuts. The stop 2222 is rotatable relative to the hook 2221 between an open position and a closed position. In the open position, the aircraft suspension device 1000 is allowed to be hooked on the hook 2221. In the closed position, the stop 2222 is securely fastened to the hook 2221 and locked to prevent the aircraft suspension device 1000 from detaching from the hook block 22.

[0068] Continue to refer to Figure 1 and Figure 2 In an exemplary embodiment of the present invention, the load simulation test equipment may further include a control switch 61, which may be the same as a corresponding switch on an aircraft, for a more realistic simulation. Figure 6As clearly shown, the control switch 61 can be fixed to the hanging block 22, specifically to the sliding member 221 of the hanging block 22, such that the push rod of the control switch 61 is aligned with the side of the hook 2221 of the hanging block 22, thereby aligning with the trigger switch of the aircraft suspension device 1000. When the required load is applied, pressing the control switch 61 applies a triggering force to the trigger switch of the aircraft suspension device 1000. At this time, it is checked whether the aircraft suspension device 1000 will detach from the hook 2221 of the hanging block 22. If it does not detach, the aircraft suspension device 1000 needs to be adjusted to regulate the triggering force until the aircraft suspension device 1000 can detach smoothly under the action of the control switch 61. Through this process, parameters such as the linkage operation flexibility and triggering force of the aircraft suspension device 1000 can be checked during simulated load. A power supply socket 119 for supplying power to the control switch 61 can be provided at the bottom of the cavity 113 of the test bench 11.

[0069] Refer again Figure 1 and Figure 2 The center of gravity simulation unit is located below the suspension unit and may include a center of gravity simulation frame 31, a pin 32 and a connecting seat 33 arranged sequentially from top to bottom.

[0070] like Figure 7 As shown, the center of gravity simulation frame 31 is a component that simulates the center of gravity of cargo mounted on the aircraft suspension device 1000. It may include a frame 311 and two pairs of hanging rings 312 for connecting to two sets of hooks on the aircraft suspension device 1000. The hanging rings 312 are the main components connecting the aircraft suspension device and the simulated load. The cross-section of the hanging rings 312 completely simulates the real load and is an important part for checking the linkage operation flexibility and accurate disengagement of the aircraft suspension device 1000. A part of the center of gravity simulation frame 31 is located in the cavity 113 of the test bench 11, and a part passes through the through hole 118 of the test bench 11.

[0071] The frame 311 may have center-of-gravity holes 313 corresponding to the two pairs of hanging rings 312 respectively. The two pairs of hanging rings 312 are a pair of hanging rings located on the outside, that is, a pair of hanging rings that stand upright, and a pair of hanging rings located on the inside, that is, a pair of hanging rings that are suspended horizontally.

[0072] In some alternative embodiments, the center of gravity simulation frame 31 may also include protrusions protruding from the frame 311 corresponding to the hanging rings 312. The protrusions include a pair of lugs 314, with the hanging rings 312 positioned between the pair of lugs 314. The lugs 314 and the hanging rings 312 are connected by bolts and nuts, allowing the hanging rings 312 to rotate relative to the lugs 314. Thus, the pair of hanging rings in use can be erected vertically and hooked onto the hooks of the aircraft suspension device 1000, while the pair of hanging rings not in use can be placed horizontally to avoid obstructing the aircraft suspension device 1000.

[0073] For example, the two center-of-gravity holes 313 can be arranged in a vertical row, but with different sizes. The smaller center-of-gravity hole 313 located above corresponds to a pair of hanging rings located on the inner side, while the larger center-of-gravity hole 313 located below corresponds to a pair of hanging rings located on the outer side.

[0074] See now Figure 8 The pin 32 can be roughly cylindrical in shape and passes through the center of gravity hole 313 and the connecting seat 33 to simulate the center of gravity position of the loaded cargo. The head of the pin 32 at one axial end has a larger diameter to axially position the connecting seat 33 and the center of gravity simulation frame 31. Figure 2 As shown, the pin 32 has two pins with the same shape but different sizes. One of these two pins is used. When in use, the smaller one is inserted into the smaller center of gravity hole 313 of the center of gravity simulation frame 31 to simulate the center of gravity position under a small load, while the larger one is inserted into the larger center of gravity hole 313 of the center of gravity simulation frame 31 to simulate the center of gravity position under a large load.

[0075] In a preferred embodiment of the present invention, reference is made to Figure 9 The connecting seat 33 may include a disc portion 331 and a U-shaped portion 332. The disc portion 331 is used to fix the connecting seat 33 and is machined with a plurality of circumferentially equally spaced holes. The center of gravity simulation frame 31 can be inserted into the U-shaped portion 332. The U-shaped portion 332 is provided with pin holes 333 for two pins 32 to pass through. The arrangement of the two pin holes 333 is the same as the arrangement of the two center of gravity holes 313, and will not be described again here. As shown, the applied load value can be marked on the U-shaped portion 332 of the connecting seat 33 at the position corresponding to the pin holes 333.

[0076] Now refer to Figure 1 and Figure 2 The drive unit is used to drive the center of gravity simulation unit to move up and down, and may include a drive component 41. The output part of the drive component 41 can reciprocate up and down. The drive component 41 may be a linear motor or a hydraulic cylinder, etc., and the present invention is not limited thereto. The drive component 41 may be fixed to the platform 11, particularly installed in the lower part 112 of the platform 11 and connected to the bottom of the lower part 112. The lower part 112 may be equipped with a door 117 that is easy to open and close, so as to facilitate the inspection of the internal drive component 41.

[0077] The load monitoring unit is used to detect and display the load applied to the aircraft suspension device 1000. The load monitoring unit may include a tension sensor 51 and a display 52.

[0078] The tension sensor 51 can be mounted on the output portion of the drive member 41, particularly by interference fit, and can be connected to the connecting seat 33, particularly through a hole in the disc portion 331 of the connecting seat 33, so that the drive member 41 can drive the connecting seat 33 to move up and down, thereby pulling the center of gravity simulation frame 31, and thus applying or releasing a load on the aircraft suspension device 1000, and the tension sensor 51 can detect the magnitude of the load applied to the aircraft suspension device 1000. The display 52 can be electrically connected to the tension sensor 51 to display the magnitude of the applied load. Those skilled in the art will understand that the display 52 can be set at any position on the load simulation test equipment, as long as the operator can observe the display 52.

[0079] Now refer to Figure 11 and Figure 12 In an exemplary embodiment of the present invention, the load simulation test equipment may include a separate test bench 100 and a control console 200. The test bench 100 may include a support unit, a suspension unit, a center of gravity simulation unit, and a drive unit, and includes a tension sensor 51 of the load monitoring unit. The control console 200 may have a generally L-shaped structure, with the lower half being a hollow box and the upper half being an electrical control cabinet that is thinner than the lower half, and a control panel 201 provided on the outside. The control panel 201 allows operators to monitor the load simulation test equipment, and the display 52 of the load monitoring unit may be located in the control panel 201.

[0080] In some embodiments, an emergency switch 202 may also be provided on the control panel 201 to turn the test equipment of the present invention on and off in the event of an emergency. A power switch 203 may also be provided on the control panel 201 to control the power supply to and from the test equipment.

[0081] like Figure 12 As shown, if the drive component 41 in the drive unit is a hydraulic cylinder, it may also include a hydraulic station 42 that provides power to the hydraulic cylinder. The hydraulic station 42 can be connected to the hydraulic cylinder via pipelines. The hydraulic station 42 may consist of an oil tank, a suction filter, an air filter, an oil pump, a motor, a check valve, a solenoid relief valve, an oil supply switch, a pressure reducing valve, a throttle valve, and a solenoid directional valve, all of which are existing mature technologies. The hydraulic station 42 can be installed in the hollow box in the lower half of the control console 200, and the box can be equipped with a door that is easy to open and close for maintenance and other operations on the hydraulic station 42.

[0082] The control panel 201 can also be equipped with a pressure gauge to indicate the oil pump pressure of the hydraulic station 42, an indicator light to indicate whether the test equipment is operating normally, and a loading switch to start and stop load loading.

[0083] Therefore, by setting up independent test benches and control consoles, the test bench includes hydraulic cylinders and components connected to the aircraft suspension system, and the control console includes a hydraulic station and a control panel for operators to monitor the load simulation test equipment, thus isolating the operating platform where the aircraft suspension system is located from the operating platform where the operators conducting the simulation test are located, ensuring the safety of the product and personnel.

[0084] This invention can employ a PLC system to implement its various functions, such as controlling the drive components, particularly adjusting the hydraulic station pump pressure to control the reciprocating motion of the cylinder rod, thereby loading the aircraft suspension system. Through technologies such as position sensors, limit switches, and visual recognition, since the two sets of hanging rings are matched with different simulated load center-of-gravity positions, the system can automatically determine the simulated load based on the hanging rings used, automatically load the simulation program, and automatically simulate the test process according to the technological steps, while also possessing a function to prevent misoperation. This can be achieved by combining existing mature technologies.

[0085] The working process and principle of the load simulation test equipment for aircraft suspension devices of the present invention:

[0086] Step 1: Move a pair of hanging blocks 22 of the test equipment to adjust the position of the two hanging blocks 22, and hang the aircraft suspension device 1000 on the two hanging blocks 22;

[0087] Step 2: Slide the two hanging blocks 22, hang the pair of hanging rings 312 on the inner side of the center of gravity simulation frame 31 on the corresponding inner set of the two sets of hooks of the aircraft suspension device 1000, and insert the pin 32 into the smaller center of gravity hole 313 located above. Then, actuate the drive component 41. In particular, control the hydraulic pump pressure of the hydraulic station 42 through the control console 200 to make the cylinder rod move up and down to load the suspension device 1000. The load value is collected by the tension sensor 51 and displayed on the display 52.

[0088] Step 3: Slide the two hanging blocks 22, hang the pair of hanging rings 312 on the outer side of the center of gravity simulation frame 31 on the corresponding outer set of the two sets of hooks of the aircraft suspension device 1000, and insert the pin 32 into the larger center of gravity hole 313 located below, and then perform a process similar to step 2.

[0089] Step 4: After the simulation test is over, first remove the hanging ring 312 of the center of gravity simulation frame 31 from the hook of the aircraft suspension device 1000, and then remove the aircraft suspension device 1000 from the hanging block 22.

[0090] As described above, the present invention employs a pair of slidable hanging block structures, which allows the aircraft suspension device to slide left and right after being clamped during simulation tests to adjust the attachment points of the two sets of hooks and the center of gravity of the corresponding loaded cargo. It also enables quick clamping of the suspension device and allows for ground load simulation tests with different center of gravity positions of the two sets of attachment points with simple operation.

[0091] The features mentioned and / or shown in the foregoing description of exemplary embodiments of the present invention may be combined in the same or similar manner with one or more other embodiments, combined with features in other embodiments, or substituted for corresponding features in other embodiments. Such combinations or substitutions should also be considered as including within the scope of protection of the present invention.

Claims

1. A load simulation test apparatus for an aircraft suspension device, characterized by: The load simulation test equipment includes a support unit, a suspension unit, a center of gravity simulation unit, a drive unit, and a load monitoring unit; The support unit is used to support the suspension unit, the center of gravity simulation unit, the drive unit and the load monitoring unit, and the support unit includes a frame; The suspension unit includes a slide rail and a hanging block. The slide rail is fixed to the upper part of the platform. The mounting blocks are a pair, used to connect the aircraft suspension device to be tested for ground load simulation, and the mounting blocks are slidably mounted on the slide rail; The center of gravity simulation unit is located below the suspension unit and includes a center of gravity simulation frame, a pin, and a connecting seat arranged sequentially from top to bottom. The center of gravity simulation frame includes a frame and two pairs of hanging rings for connecting to two sets of hooks of the aircraft suspension device. The frame has center of gravity holes corresponding to the two pairs of hanging rings. The pin passes through the center hole and the pin hole on the connector. The driving unit is used to drive the center of gravity simulation unit to move up and down, and includes a driving component. The drive component is fixed to the platform; The load monitoring unit is used to detect and display the load applied to the aircraft suspension system. The load monitoring unit includes a tension sensor and a display. The tension sensor is mounted on the output of the drive unit and connected to the connecting seat, such that: the drive unit moves the connecting seat up and down to pull the center of gravity simulation frame, thereby applying or releasing a load on the aircraft suspension device, and the tension sensor detects the magnitude of the applied load. The display is electrically connected to the tension sensor to show the magnitude of the applied load.

2. The load simulation test equipment for aircraft suspension devices according to claim 1, characterized in that: The center of gravity simulation frame also includes a protrusion that protrudes from the frame and is corresponding to the hanging ring. The protrusion includes a pair of lugs, the hanging ring is positioned between the pair of lugs, and the lugs and the hanging ring are connected by bolts and nuts, so that the hanging ring can rotate relative to the lugs.

3. The load simulation test equipment for aircraft suspension devices according to claim 1 or 2, characterized in that: The driving component is a hydraulic cylinder, and the driving unit further includes a hydraulic station that provides power to the hydraulic cylinder.

4. The load simulation test equipment for aircraft suspension devices according to claim 3, characterized in that: The load simulation test equipment includes an independent test bench and a control console; The test bench includes the support unit, the suspension unit, the center of gravity simulation unit, and the drive unit, and also includes the tension sensor of the load monitoring unit; The hydraulic station is located in the control console.

5. The load simulation test equipment for aircraft suspension devices according to claim 4, characterized in that: The console also includes a control panel for operators to monitor the load simulation test equipment, and the display of the load monitoring unit is located in the control panel.

6. The load simulation test equipment for aircraft suspension devices according to claim 1 or 2, characterized in that: The platform includes an upper portion, a lower portion, and an open cavity located between the upper portion and the lower portion; The slide rail is fixed to the upper portion, and the drive component is installed in the lower portion; The lower portion has a through hole facing the cavity, and a part of the center of gravity simulation frame is located in the cavity and passes through the through hole.

7. The load simulation test equipment for aircraft suspension devices according to claim 1 or 2, characterized in that: The hanging block includes a sliding member and a fastening member connected together. The sliding member slides within the slide rail. The fastening member includes a hook and a stop. The hook is used to hook the aircraft suspension device. The stop is installed to the hook and can rotate and lock relative to the hook to prevent the aircraft suspension device from detaching from the hanging block.

8. The load simulation test equipment for aircraft suspension devices according to claim 1 or 2, characterized in that: It also includes a control switch, which is fixed to the hanging block such that the push rod of the control switch is aligned with the trigger switch of the aircraft suspension device.

9. The load simulation test equipment for aircraft suspension devices according to claim 1 or 2, characterized in that: The connector includes a disc portion and a U-shaped portion, the drive member is connected to the disc portion, the pin hole is located on the U-shaped portion, and the center of gravity simulation frame is inserted into the U-shaped portion.

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