Main wheel braking force testing device for unmanned transport plane

Abstract

The utility model provides a device for testing the braking force of a main wheel of an unmanned aerial vehicle, which relates to the field of development of unmanned aerial vehicle testing equipment and comprises a ribbon clamping mechanism connected with the main wheel in a clasping manner. A fixed support mechanism is welded to the outer wall of the ribbon clamping mechanism, and a cantilever supporting pipe is fixedly installed on the fixed support mechanism. One end of the cantilever supporting pipe is provided with a clamping seat, and the position where the clamping seat is located is used for positioning and installing an electronic hoist scale. A hook of the electronic hoist scale is used for being connected with a force application structure. The device adopts a pure mechanical structure, does not need a complex electromechanical control system, can be conveniently carried to an external field needing to be tested, and further realizes on-site host wheel braking force testing.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) testing equipment development, specifically to a device for testing the braking force of the main wheel of an unmanned transport aircraft. Background Technology

[0002] A certain type of unmanned transport aircraft uses hydraulic brakes. Each of its left and right main wheels is independently controlled by an electric servo motor that drives a brake valve push rod. If the braking force of the left and right main wheels is inconsistent and exceeds the permissible range during the landing roll, or if improper braking and deceleration strategies occur during the ground roll, resulting in brake lock-up, the aircraft's landing distance will be prolonged, it may veer off course, or even run off the runway, leading to a safety accident. To ensure the braking safety of the unmanned transport aircraft, it is necessary to periodically test the braking force of the main wheels after changing the brake fluid or during routine maintenance to determine the optimal braking force.

[0003] Traditional aircraft braking force testing equipment is mostly complex electromechanical integrated control equipment, which requires a power supply and is expensive, bulky, and inconvenient to carry around and use in the field. Utility Model Content

[0004] The purpose of this invention is to provide a device for testing the braking force of the main wheel of an unmanned transport aircraft. This device adopts a purely mechanical structure, requires no complex electromechanical control system, and can be easily carried to the field where testing is needed, thereby realizing on-site testing of the braking force of the main wheel. Its test data can provide data support for the formulation of braking speed control and deceleration strategies during aircraft ground landing and taxiing. It does not require complex special testing equipment and has the advantages of being portable, simple in structure, easy to operate, convenient to use, and low in cost.

[0005] To achieve the above-mentioned technical features, the purpose of this utility model is as follows: a braking force testing device for the main wheel of an unmanned transport aircraft, including a cable tie clamp mechanism for tightly connecting with the main wheel;

[0006] A fixed support mechanism is welded to the outer wall of the cable tie clamp mechanism, and a cantilever support pipe is fixedly installed on the fixed support mechanism.

[0007] One end of the cantilever support tube is provided with a retainer, the location of which is used to position and install the electronic crane scale;

[0008] The hooks of the electronic crane scale are used to connect the force-applying structure.

[0009] Preferably, the cable tie clamping mechanism includes a first cable tie and a second cable tie, which are hinged together by a hinge mechanism. The free ends of the first and second cable ties after being fitted onto the main wheel are locked and fixed by a locking mechanism.

[0010] Preferably, the hinge mechanism includes a first hinge seat fixed on the outer wall of the first cable tie end, the first hinge seat being hingedly connected to a second hinge seat via a first pin, and the second hinge seat being fixed on the outer wall of the second cable tie end.

[0011] Preferably, the locking mechanism includes a first fixing seat fixed on the outer wall of the free end of the first cable tie and a second fixing seat fixed on the outer wall of the free end of the second cable tie, and the first fixing seat and the second fixing seat are fixedly connected by a plurality of first bolt assemblies.

[0012] Preferably, the fixed support mechanism includes a bottom fixed seat fixed on the outer wall of the cable tie clamp mechanism. The top surface of the bottom fixed seat is provided with an arc-shaped groove for positioning the cantilever support tube. A pressure cap is fixedly installed on the top of the bottom fixed seat by a second bolt assembly. The bottom end surface of the pressure cap is provided with an arc-shaped groove for positioning the cantilever support tube.

[0013] Preferably, the electronic crane scale is suspended from the location of the mounting bracket by a sling hook, and a limit bolt is installed on the top of the mounting bracket.

[0014] Preferably, the force-applying structure is a hand-pull ring for manual force application or a loading bucket for placing counterweights.

[0015] Preferably, during the loading process, if the required load weight is less than or equal to 20kg, a hand-operated pull ring is installed, and the load is applied by slowly pulling by hand. If the required load weight is greater than 20kg, a loading bucket is suspended, and an appropriate weight of base counterweight is pre-placed in the bucket before sand is slowly added to the loading bucket for loading.

[0016] The present invention has the following beneficial effects:

[0017] 1. This utility model device adopts a purely mechanical structure, without the need for a complex electromechanical control system. It can be easily carried to the field where testing is required, thereby realizing on-site testing of the main wheel braking force. Its test data can provide data support for the formulation of braking speed control and deceleration strategies during aircraft ground landing and taxiing. It does not require complex special testing equipment and has the advantages of being portable, simple in structure, easy to operate, convenient to use, and low in cost.

[0018] 2. By employing the aforementioned cable tie clamp mechanism, this utility model can conveniently and reliably lock the entire testing device to the main wheel.

[0019] 3. The hinge mechanism described above facilitates the opening, closing, and installation of the first and second cable ties.

[0020] 4. The present invention can quickly lock the ends of the first cable tie and the second cable tie through the above-mentioned locking mechanism, thereby achieving the locking and fixing of the first cable tie and the second cable tie with the main wheel.

[0021] 5. This utility model can easily achieve reliable installation of the cantilever support pipe through the fixed support mechanism. The bottom fixed seat is used to install the cantilever support pipe. The cantilever support pipe can slide back and forth in the fixed support mechanism to achieve the length adjustment of the loading arm. The cantilever lengths of the left and right main wheels should be the same during the test. The longer the cantilever, the smaller the required loading weight.

[0022] 6. The loading bucket, counterweight iron blocks or stones, sand and other materials of this utility model can be easily obtained near the test site. They can basically be sourced locally and generally do not require special equipment, thus enhancing the flexibility of use. Attached Figure Description

[0023] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0024] Figure 1 This is a first-person perspective 3D view of the present invention.

[0025] Figure 2 This is a two-dimensional view of the present invention from a second perspective.

[0026] Figure 3 This is a three-dimensional view of the present invention from a third perspective.

[0027] Figure 4 This is a four-dimensional view of the present invention.

[0028] Figure 5 This is a five-dimensional view of the present invention.

[0029] Figure 6 This is an embodiment of the present invention using a hand-operated pull ring.

[0030] In the diagram: 1. Landing gear strut; 2. Second bolt assembly; 3. Pressure cap; 4. Bottom fixing seat; 5. Cantilever support tube; 6. Fixed support mechanism; 7. Hinge mechanism; 8. Second cable tie; 9. Locking mechanism; 10. Second fixing seat; 11. First bolt assembly; 12. First fixing seat; 13. First cable tie; 14. Main wheel; 15. Wheel axle; 16. Limit bolt; 17. Card seat; 18. Sling; 19. Electronic crane scale; 20. Hook; 21. Loading bucket; 22. First hinge seat; 23. Second hinge seat; 24. First pin; 25. Top socket; 26. Hand pull ring. Detailed Implementation

[0031] The embodiments of this utility model will be further described below with reference to the accompanying drawings.

[0032] Example 1:

[0033] See Figure 1-6 A braking force testing device for the main wheel of an unmanned transport aircraft includes a cable tie clamp mechanism for tightly connecting with the main wheel 14; a fixed support mechanism 6 is welded to the outer wall of the cable tie clamp mechanism, and a cantilever support pipe 5 is fixedly installed on the fixed support mechanism 6; a bracket 17 is provided at one end of the cantilever support pipe 5, and the location of the bracket 17 is used to position and install an electronic crane scale 19; a force-applying structure is connected to the hook 20 of the electronic crane scale 19.

[0034] By adopting the above-mentioned testing device, which uses a purely mechanical structure and does not require a complex electromechanical control system, it can be easily carried to the field where testing is needed, thereby realizing on-site testing of the main wheel braking force. Its test data can provide data support for the formulation of braking speed control and deceleration strategies during aircraft ground landing and taxiing. It does not require complex special testing equipment and has the advantages of being portable, simple in structure, easy to operate, convenient to use, and low in cost.

[0035] The aforementioned testing device is used to periodically measure and test the braking force of drones after brake fluid changes or during routine maintenance. A simple rigid load-bearing cantilever bracket is designed, using a cable tie clamp mechanism to secure it to the main wheel. The load-bearing cantilever support tube can slide back and forth within the fixed support mechanism 6 to adjust the length of the loading arm. During testing, the aircraft is first lifted to suspend the wheels. The braking force testing device is then installed on the main wheel. An electronic scale and loading accessories are installed at the front end of the load-bearing cantilever support tube, connected to a ground inspection laptop (a dedicated ground testing and debugging laptop). The main wheel is positioned according to the test conditions. The braking force is applied to the main wheel by controlling the brake servo motor via a program. The wheel is then slowly pulled manually or the weight of the suspended object is gradually increased until it rotates. The braking force is then controlled by an electric... The sub-scale automatically saves the peak loading force and records the push stroke of the brake servo motor and the corresponding loading weight. Thus, within the full stroke range of the brake servo motor, using the zero position as a reference, multiple push stroke tests are performed on the left and right main wheels with a certain step extension, and the weight data that can drive the wheels to rotate is recorded for each test. Multiple sets of data for the left and right main wheels are compared and analyzed. If necessary, the braking force of the left and right wheels is corrected and compensated by adjusting the push stroke value of the electric servo motor in the control program. This process is repeated until the braking force values ​​of the left and right wheels reach equilibrium. The test data can provide data support for the formulation of braking speed control and deceleration strategies during aircraft ground landing roll. It requires no complex specialized testing equipment and has advantages such as portability, simple structure, easy operation, convenient use, and low cost.

[0036] Furthermore, the cable tie clamping mechanism includes a first cable tie 13 and a second cable tie 8, which are hinged together by a hinge mechanism 7. The free ends of the first cable tie 13 and the second cable tie 8 after being fitted onto the main wheel 14 are locked and fixed by a locking mechanism 9. By adopting the above-mentioned cable tie clamping mechanism, the entire testing device can be reliably locked to the main wheel 14.

[0037] When testing is required, the cable tie clamp mechanism is locked and fixed to the main wheel 14 on site. The clamp is made of stainless steel and is easy to carry.

[0038] Furthermore, the hinge mechanism 7 includes a first hinge seat 22 fixed to the outer wall of the end of the first cable tie 13. The first hinge seat 22 is hingedly connected to a second hinge seat 23 via a first pin 24. The second hinge seat 23 is fixed to the outer wall of the end of the second cable tie 8. The hinge mechanism 7 facilitates the opening, closing, and installation of the first cable tie 13 and the second cable tie 8.

[0039] Furthermore, the locking mechanism 9 includes a first fixing seat 12 fixed to the outer wall of the free end of the first cable tie 13 and a second fixing seat 10 fixed to the outer wall of the free end of the second cable tie 8. The first fixing seat 12 and the second fixing seat 10 are fixedly connected by a plurality of first bolt assemblies 11. The locking mechanism 9 described above enables quick locking of the ends of the first cable tie 13 and the second cable tie 8, thereby achieving the locking and fixing of the first cable tie 13 and the second cable tie 8 to the main wheel.

[0040] Furthermore, the fixed support mechanism 6 includes a bottom fixed seat 4 fixed to the outer wall of the cable tie clamp mechanism. The top surface of the bottom fixed seat 4 is provided with an arc-shaped groove for positioning the cantilever support tube 5. A pressure cap 3 is fixedly installed on the top of the bottom fixed seat 4 by the second bolt assembly 2. The bottom end face of the pressure cap 3 is provided with an arc-shaped groove for positioning the cantilever support tube 5. The fixed support mechanism 6 can easily and reliably install the cantilever support tube 5. The bottom fixed seat 4 is used to install the cantilever support tube 5. The cantilever support tube 5 can slide back and forth within the fixed support mechanism 6 to adjust the length of the loading arm. The cantilever lengths of the left and right main wheels should be the same during the test. The longer the cantilever, the smaller the required loading weight.

[0041] Furthermore, the electronic crane scale 19 is hooked to the location of the card holder 17 by the sling 18, and the top of the card holder 17 is equipped with a limit bolt 16.

[0042] The electronic crane scale 19 with the above structure has a peak hold storage function. The hook at the lower end of the electronic crane scale 19 is equipped with a spring safety lock to prevent the hand pull ring or the loaded bucket from falling off at will.

[0043] Furthermore, the force-applying structure employs a hand-operated pull ring 26 for manual force application or a loading bucket 21 for placing the counterweight. The loading bucket, counterweight iron blocks or stones, and sand can all be easily obtained near the test site; they are generally readily available locally and do not require special equipment.

[0044] Furthermore, during the loading process, if the required load weight is less than or equal to 20kg, a hand-operated pull ring is installed, and the load is applied by slowly pulling by hand. If the required load weight is greater than 20kg, a loading bucket 21 is suspended, and an appropriate weight of base counterweight is pre-placed inside the bucket before sand is slowly added to the loading bucket 21 for loading.

[0045] Example 2:

[0046] A method for testing the braking force of the main wheel of an unmanned transport aircraft using a braking force testing device includes the following steps:

[0047] Step 1, lifting the main engine wheel:

[0048] The aircraft was lifted using jacks, allowing the left and right main landing gear wheels to be suspended at a certain height off the ground.

[0049] Step 2, securing the cable tie clamp mechanism:

[0050] Install the cable tie clamp mechanism of the braking force testing device on the main aircraft wheel and tighten the fastening bolts;

[0051] Step 3, Fixed installation of cantilever support tube 5:

[0052] The cantilever support pipe 5 is fixedly installed on the top of the cable tie clamp mechanism via the fixed support mechanism 6, and the cantilever length of the cantilever support pipe 5 is adjusted according to the required braking force.

[0053] Step 4, Connection of electronic crane scale 19 and force-applying structure:

[0054] Electronic crane scales 19 are installed at the front end of the cantilever support tube 5, and a force-applying structure for applying test force is connected to the electronic crane scales 19.

[0055] Step 5, Connection preparation before testing:

[0056] Connect the ground inspection book to the aircraft interface, power on the aircraft, start the aircraft ground inspection and debugging program on the ground inspection book, align the main engine wheel position according to the test state, and then control the brake servo motor to brake the main engine wheel and maintain it through the ground inspection book.

[0057] Step 6, test force application and data collection:

[0058] Force is applied to the cantilever support pipe 5 through the force-applying structure until the machine wheel rotates, and the corresponding data is collected during the test.

[0059] Step 7, Data Analysis:

[0060] Analyze the collected data;

[0061] Step 8, Output the results:

[0062] Based on the data analysis results, a braking speed control and deceleration strategy was developed for the aircraft during ground landing roll.

[0063] Preferably, step 6 specifically involves the following process:

[0064] Step 6.1: Slowly pull the suspended weight at the front end of the testing device by hand or gradually increase the weight until the main wheel 14 rotates;

[0065] Step 6.2: Read and record the peak value of the loading force on the electronic crane scale 19, and read and record the push stroke of the brake servo motor on the ground inspection book;

[0066] Step 6.3: According to the test procedure, within the full stroke range of the brake servo motor, with zero position as the reference, perform multiple push stroke tests on the left and right main wheels with a certain step extension amount, and record the weight data that can drive the wheels to rotate respectively.

[0067] Step 6.4: Compare and analyze multiple sets of data for the left and right main engine wheels respectively;

[0068] Step 6.5: Based on the data analysis results, adjust the push stroke value of the electric servo motor in the control program as appropriate to correct and compensate the braking force of the left and right main wheels, so as to ensure that the braking force of the left and right main wheels can be balanced and consistent when they brake at the same time, and the deviation value is within the allowable range of the process.

[0069] Step 6.6: After adjusting the program values, conduct another braking force test on the left and right main wheels to verify and record the relevant data;

[0070] Step 7: Analyze the collected data, specifically as follows:

[0071] The test data are checked and analyzed against the test process. If the test data meets the process requirements, it is considered qualified. If it is not qualified, the program data is further fine-tuned and optimized, and the braking force test is performed again until it is qualified.

[0072] Step 8 also includes:

[0073] Organize and archive the experimental data for easy reference when formulating braking, speed control, and deceleration strategies for aircraft during ground landing roll.

[0074] Example 3:

[0075] In the specific testing process, the adjustments and compensations for the program data are roughly as follows: If the measured braking force is 20kg when the push rod travel of the left main wheel brake servo is 5mm and the measured braking force is 18kg when the push rod travel of the right main wheel brake servo is 5mm, then the push rod travel of the right main wheel brake servo needs to be increased in the program to make its braking force reach 20kg, so as to ensure that the braking force of the left and right wheels is consistent when braking at the same time.

[0076] Example 4:

[0077] The issue of braking speed control and deceleration strategies for aircraft during ground landing roll is roughly as follows: The length of the ground landing roll is an important parameter reflecting aircraft performance. Developing an optimal braking speed control and deceleration strategy can minimize the ground landing roll distance. During the ground landing roll, braking can control the roll speed and gradually reduce deceleration. However, the specific braking force to be used, and how to set and adjust the braking force during the roll, requires the development of a plan and strategy, setting relevant parameters in the program, and verifying and optimizing through experiments. When the roll speed is high, the braking force should be smaller, and as the roll speed decreases, the braking force can be gradually increased.

Claims

1. An unmanned transport vehicle host wheel brake force testing device, characterized by, The strap clamping mechanism is used to be connected with the host wheel (14); The outer wall of the strap clamping mechanism is welded with a fixed support mechanism (6), and the cantilever support pipe (5) is fixedly installed on the fixed support mechanism (6); One end of the cantilever support pipe (5) is provided with a clamping seat (17), and the clamping seat (17) is used to position and install an electronic hanging scale (19); The hook (20) of the electronic hanging scale (19) is used to connect a force applying structure.

2. The unmanned vehicle host wheel brake force testing device according to claim 1, characterized in that: The strap clamping mechanism includes a first strap (13) and a second strap (8), the first strap (13) and the second strap (8) are connected through a hinge mechanism (7), and the free end of the first strap (13) and the second strap (8) after being sleeved on the host wheel (14) is locked and fixed through a locking mechanism (9).

3. The unmanned vehicle host wheel brake force testing device according to claim 2, characterized in that: The hinge mechanism (7) includes a first hinge seat (22) fixed on the outer wall of the end of the first strap (13), the first hinge seat (22) is connected with a second hinge seat (23) through a first pin shaft (24), and the second hinge seat (23) is fixed on the outer wall of the end of the second strap (8).

4. The unmanned vehicle host wheel brake force testing device according to claim 2, characterized in that: The locking mechanism (9) includes a first fixed seat (12) fixed on the outer wall of the free end of the first strap (13) and a second fixed seat (10) fixed on the outer wall of the free end of the second strap (8), and the first fixed seat (12) and the second fixed seat (10) are fixedly connected through a plurality of first bolt assemblies (11).

5. The unmanned vehicle host wheel brake force testing device of claim 1, wherein: The fixed support mechanism (6) includes a bottom fixed seat (4) fixed on the outer wall of the strap clamping mechanism, the top surface of the bottom fixed seat (4) is provided with an arc-shaped groove for positioning the cantilever support pipe (5), and the top of the bottom fixed seat (4) is fixedly installed with a gland (3) through a second bolt assembly (2), and the bottom end surface of the gland (3) is provided with an arc-shaped groove for positioning the cantilever support pipe (5).

6. The unmanned vehicle host wheel brake force testing device of claim 1, wherein: The electronic hanging scale (19) is hooked on the position of the clamping seat (17) through a sling (18), and the top of the clamping seat (17) is installed with a limiting bolt (16).

7. The unmanned vehicle host wheel brake force testing device of claim 1, wherein: The force applying structure adopts a hand pull ring (26) for manual force applying or a loading bucket (21) for placing a counterweight.

8. The unmanned vehicle host wheel brake force testing device of claim 7, wherein: During loading, if the required loading weight is less than or equal to 20 kg, a hand pull ring is installed, and the loading is directly performed by slowly pulling the hand to apply force, if the required loading weight is greater than 20 kg, the loading bucket (21) is hung, appropriate weight of the base counterweight is pre-installed in the bucket, and then sand is slowly added to the loading bucket (21) for loading.

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