A strut type landing gear for a basic trainer aircraft

Abstract

The application relates to the technical field of airplane landing gears, in particular to a strut type landing gear of a basic trainer airplane, which comprises a first hydraulic rod, a second hydraulic rod, a first supporting rod and a second supporting rod, and also comprises a tire; the bottom end of the first hydraulic rod is provided with a first telescopic rod; the bottom end of the first telescopic rod is fixedly installed with a second base shaft; the two ends of the second base shaft are both rotationally connected with rotating shafts; one end of each rotating shaft is fixedly installed with a spoke pipe; one end of the spoke pipe is fixedly installed with a wheel hub; the tire is arranged on the inner wall of the wheel hub; when the tire of the trainer airplane just touches the ground, the tire pressure of the tire can be monitored according to a pressure sensor; when the tire pressure is monitored to be too high, the controller controls the exhaust valve to exhaust the air in the tire; the elasticity of the tire is reduced through pressure relief, so that the bouncing degree of the tire when landing on the ground is obviously reduced, and the safety is improved, and the landing accident caused by bouncing is avoided.

Description

Technical Field

[0001] This invention relates to the field of aircraft landing gear technology, specifically a basic strut-type landing gear for a trainer aircraft. Background Technology

[0002] Landing gear is an aircraft landing device used to support the aircraft, absorb landing energy, and cushion landing and takeoff impact loads. To meet ground stability requirements, landing gear is usually flared outward to increase the lateral wheel track. There are two common landing gear configurations: flared strut landing gear and flared rocker arm landing gear.

[0003] Strut-type landing gear is a standard configuration on trainer aircraft, typically installed in the fuselage area. A search revealed patent CN110576966A, which discloses a strut-type landing gear comprising a shock absorber strut, a strut, an upper torque arm, a lower torque arm, and wheels. The strut-type landing gear is connected to the fuselage via a spherical bearing on the upper part of the outer cylinder of the shock absorber strut and two lugs at one end of the strut. The two lugs at the other end of the strut are connected to the upper torque arm, which is connected to the outer cylinder. The lower torque arm is connected to the piston rod of the shock absorber strut. This invention's strut-type landing gear, through the arrangement of the shock absorber strut, strut, and torque arm, solves the problem of lateral wheelbase in strut-type landing gears.

[0004] Based on the aforementioned patents and in light of real-world problems, the following issues still exist:

[0005] Firstly, when the landing gear tires first touch the ground, due to the high speed of the trainer aircraft, if the tire pressure is too high, the elasticity will be greater, and the trainer aircraft is prone to bouncing too high, which can easily lead to a landing accident. On the other hand, if the landing gear tire pressure is too low, the wear on the wheel rims and tires will be greater after the trainer aircraft lands. This has limitations and needs to be improved. Summary of the Invention

[0006] The purpose of this invention is to provide a basic strut-type landing gear for trainer aircraft to solve the problems mentioned in the background art.

[0007] The technical solution of this invention is: a strut-type landing gear for a basic trainer aircraft, comprising a first hydraulic strut, a second hydraulic strut, a first support strut, and a second support strut, and further comprising:

[0008] The tire has a first telescopic rod at the bottom of the first hydraulic rod, a second base shaft fixedly installed at the bottom of the first telescopic rod, and a rotating shaft rotatably connected to both ends of the second base shaft. A spoke tube is fixedly installed at one end of the rotating shaft, and a wheel hub is fixedly installed at one end of the spoke tube. The tire is set on the inner wall of the wheel hub, and the tire can be set in an outward flared posture, which is consistent with the solution used in the prior art.

[0009] An air pump is provided. A second fixed sleeve is fixedly installed on the outer wall of the first hydraulic rod. The air pump is installed on the outer wall of the second fixed sleeve. An air supply pipe is connected to the bottom of the air pump. One end of the air supply pipe is split into two. An air inlet ring is fixedly installed on one side of the outer wall of the spoke tube. An annular plate is rotatably connected to one side of the air inlet ring. The annular plate is sleeved with the bottom end of the air supply pipe.

[0010] The intake ring, spoke tube, and tire are all hollow structures, and the intake ring, spoke tube, and tire are connected. A pressure sensor is fixedly installed on the inner wall of the tire near the wheel hub. The pressure sensor is electrically connected to a controller. A vent pipe is provided on the inner wall of the wheel hub. One end of the vent pipe extends through the inner wall of the tire. An exhaust valve is provided on the inner wall of the vent pipe. The exhaust valve, pressure sensor, and controller are all electrically connected. The controller controls the exhaust valve to open and exhausts air through the vent pipe to relieve tire pressure.

[0011] Preferably, the outer wall of the first hydraulic rod is connected to an oil inlet pipe and an oil return pipe, and one end of the oil inlet pipe and the oil return pipe is connected to an oil tank.

[0012] Preferably, a first fixing sleeve is fixedly installed on the outer wall of the first hydraulic rod, a third base shaft is fixedly installed on the inner wall of the first fixing sleeve, the third base shaft is rotatably connected to the bottom end of the first support rod, a connector is fixedly installed on one end of the second support rod, a fifth base shaft is fixedly installed on the inner wall of the connector, and one end of the first support rod is rotatably connected to the fifth base shaft.

[0013] Preferably, one end of the second support rod is rotatably connected to a fourth base shaft, and both ends of the fourth base shaft are fixedly mounted with a first fixed base.

[0014] Preferably, a base block is fixedly provided at the top end of the first hydraulic rod, and a seventh base shaft is rotatably connected through the outer wall of the base block, with a second fixed base fixedly installed at both ends of the seventh base shaft.

[0015] Preferably, the outer wall of the seventh base shaft is rotatably connected to a mounting bracket, a second hydraulic rod is fixedly installed on one side of the outer wall of the mounting bracket, a second telescopic rod is provided at one end of the second hydraulic rod, and a sixth base shaft is rotatably connected to one end of the second telescopic rod, the sixth base shaft being fixedly installed on the inner wall of the connector.

[0016] Preferably, the side of the connector located between the fifth base shaft and the sixth base shaft is close to and parallel to the side of the first support rod near the sixth base shaft. The angle between the first support rod and the second support rod can be controlled by the connector, and the connector can also limit the angle between the first support rod and the second support rod.

[0017] Preferably, both the first hydraulic rod and the second hydraulic rod are electrically connected to the controller.

[0018] This invention provides an improved strut-type landing gear for a basic trainer aircraft, which has the following improvements and advantages compared to the prior art:

[0019] Firstly, this invention can monitor the tire pressure of the trainer aircraft as soon as the tire touches the ground using a pressure sensor. When the tire pressure is detected to be too high, the controller controls the exhaust valve to release the air from the tire. By depressurizing the tire, its elasticity is reduced, and the degree of bouncing upon landing is significantly reduced, thereby improving safety and avoiding landing accidents caused by bouncing.

[0020] Secondly, this invention can start the air pump via the controller after the aircraft begins to taxi. The air pump supplies airflow into the intake ring through the air supply pipe, and then into the tire through the spoke tube, thereby inflating and pressurizing the tire. This prevents damage to the wheel rim and excessive tire wear due to insufficient tire pressure during taxiing, and improves the durability of the tire. Attached Figure Description

[0021] The present invention will be further explained below with reference to the accompanying drawings and embodiments:

[0022] Figure 1 This is an overall perspective view of the present invention;

[0023] Figure 2 This is a perspective view of the tire portion in this invention;

[0024] Figure 3 This is another perspective view of the overall three-dimensional view of the present invention;

[0025] Figure 4 This is a perspective view of the first support rod and the second support rod in this invention;

[0026] Figure 5 This is a perspective view of the connector portion in this invention;

[0027] Figure 6 This is a perspective view of the first hydraulic rod portion in this invention;

[0028] Figure 7 This is a cross-sectional view of the tire portion in this invention;

[0029] Figure 8 yes Figure 7 Enlarged view of part A in the middle;

[0030] Figure 9 This is a cross-sectional structural diagram of the intake ring portion in this invention.

[0031] Explanation of reference numerals in the attached figures:

[0032] 1. First hydraulic rod; 2. First telescopic rod; 3. First fixed sleeve; 4. First support rod; 5. Second support rod; 6. First fixed base; 7. Annular plate; 8. Mounting bracket; 9. Oil tank; 10. Second fixed base; 11. Base block; 12. Oil inlet pipe; 13. Oil return pipe; 14. Air pump; 15. Air supply pipe; 16. Tire; 17. Inlet ring; 18. Wheel hub; 19. Spoke tube; 20. Second base shaft; 21. Vent pipe; 22. Exhaust valve; 23. Second hydraulic rod; 24. Connecting piece; 25. Second fixed sleeve; 26. Third base shaft; 27. Fourth base shaft; 28. Fifth base shaft; 29. ​​Sixth base shaft; 30. Seventh base shaft; 31. Pressure sensor. Detailed Implementation

[0033] The present invention will now be described in detail, and the technical solutions in the embodiments of the present invention will be clearly and completely described. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0034] This invention provides an improved strut-type landing gear for a basic trainer aircraft. The technical solution of this invention is as follows:

[0035] like Figures 1-9 As shown, a basic trainer aircraft strut landing gear includes a first hydraulic strut 1, a second hydraulic strut 23, a first support strut 4, and a second support strut 5, and also includes:

[0036] The tire 16 has a first telescopic rod 2 at the bottom of the first hydraulic rod 1, a second base shaft 20 fixedly installed at the bottom of the first telescopic rod 2, and a rotating shaft rotatably connected to both ends of the second base shaft 20. A spoke tube 19 is fixedly installed at one end of the rotating shaft, and a wheel hub 18 is fixedly installed at one end of the spoke tube 19. The tire 16 is located on the inner wall of the wheel hub 18.

[0037] The air pump 14 has a second fixed sleeve 25 fixedly installed on the outer wall of the first hydraulic rod 1. The air pump 14 is installed on the outer wall of the second fixed sleeve 25. The bottom of the air pump 14 is connected to an air supply pipe 15. One end of the air supply pipe 15 is split into two. An air intake ring 17 is fixedly installed on one side of the outer wall of the spoke tube 19. An annular plate 7 is rotatably connected to one side of the air intake ring 17. The annular plate 7 is sleeved with the bottom end of the air supply pipe 15. When the air pump 14 is started, the air pump 14 supplies airflow through the air supply pipe 15 into the air intake ring 17, and then enters the tire 16 through the spoke tube 19 to inflate and pressurize the tire 16. This prevents damage to the wheel hub 18 and excessive wear of the tire 16 due to insufficient tire pressure during gliding, and improves the durability of the tire 16.

[0038] The air intake ring 17, spoke tube 19, and tire 16 are all hollow structures, and the air intake ring 17, spoke tube 19, and tire 16 are connected. A pressure sensor 31 is fixedly installed on the inner wall of the tire 16 near the hub 18. The pressure sensor 31 is electrically connected to a controller. An air vent pipe 21 is provided on the inner wall of the hub 18. One end of the air vent pipe 21 extends through the inner wall of the tire 16. An exhaust valve 22 is provided on the inner wall of the air vent pipe 21. The exhaust valve 22, pressure sensor 31, and controller are all electrically connected. When the tire 16 of the trainer aircraft just touches the ground, the tire pressure of the tire 16 can be monitored by the pressure sensor 31. When the tire pressure of the tire 16 is detected to be too high, the controller controls the exhaust valve 22 to release the air in the tire 16. By depressurizing the tire 16, its elasticity is reduced, and the degree of bouncing when it lands is significantly reduced, thereby improving safety and avoiding landing accidents caused by bouncing.

[0039] Furthermore, the outer wall of the first hydraulic rod 1 is connected to an oil inlet pipe 12 and an oil return pipe 13 respectively. One end of the oil inlet pipe 12 and the oil return pipe 13 is connected to an oil tank 9. An oil pump is installed at the bottom of the oil tank 9. The hydraulic oil in the oil tank 9 is pumped into the first hydraulic rod 1 through the oil inlet pipe 12 by the oil pump to fully extend the first telescopic rod 2.

[0040] Furthermore, a first fixing sleeve 3 is fixedly installed on the outer wall of the first hydraulic rod 1, and a third base shaft 26 is fixedly installed on the inner wall of the first fixing sleeve 3. The third base shaft 26 is rotatably connected to the bottom end of the first support rod 4. A connector 24 is fixedly installed on one end of the second support rod 5, and a fifth base shaft 28 is fixedly installed on the inner wall of the connector 24. One end of the first support rod 4 is rotatably connected to the fifth base shaft 28. This structure makes the first support rod 4 and the second support rod 5 form a structure similar to a hinge.

[0041] Furthermore, one end of the second support rod 5 is rotatably connected to a fourth base shaft 27, and both ends of the fourth base shaft 27 are fixedly installed with a first fixed base 6, which is installed in the mounting compartment at the belly of the trainer aircraft.

[0042] Furthermore, a base block 11 is fixedly installed at the top of the first hydraulic rod 1, and a seventh base shaft 30 is rotatably connected through the outer wall of the base block 11. A second fixed base 10 is fixedly installed at both ends of the seventh base shaft 30, and the second fixed base 10 is installed in the mounting compartment at the belly of the trainer aircraft.

[0043] Furthermore, a mounting bracket 8 is rotatably connected to the outer wall of the seventh base shaft 30. A second hydraulic rod 23 is fixedly installed on one side of the outer wall of the mounting bracket 8. A second telescopic rod is provided at one end of the second hydraulic rod 23. A sixth base shaft 29 is rotatably connected to one end of the second telescopic rod. The sixth base shaft 29 is fixedly installed on the inner wall of the connector 24.

[0044] Furthermore, the side of the connector 24 located between the fifth base shaft 28 and the sixth base shaft 29 is close to and parallel to the side of the first support rod 4 near the sixth base shaft 29. The angle between the first support rod 4 and the second support rod 5 is controlled by the connector 24. This arrangement allows for angle adjustment between the first support rod 4 and the second support rod 5 from 0° to 180°, while also limiting the angle between the first support rod 4 and the second support rod 5.

[0045] Furthermore, both the first hydraulic rod 1 and the second hydraulic rod 23 are electrically connected to the controller.

[0046] The strut-type landing gear used in this design is installed in the belly of the trainer aircraft. A storage compartment can be set in the belly of the trainer aircraft for the retraction of the landing gear, thereby making the fuselage of the trainer aircraft smoother, reducing wind resistance, and increasing the flight speed and maneuverability of the trainer aircraft.

[0047] When the landing gear of the trainer aircraft needs to be extended, the second hydraulic rod 23 is activated, which extends the second telescopic rod, thereby pushing the connecting piece 24 until the first support rod 4 and the second support rod 5 are aligned in a straight line. At this time, the first hydraulic rod 1 is pushed to a vertically downward position. Then, hydraulic oil is pumped into the first hydraulic rod 1 through the oil inlet pipe 12 by the oil tank 9 to fully extend the first telescopic rod 2. When the trainer aircraft is ready to land, the fully extended downward tire 16 enables the trainer aircraft to glide and land.

[0048] The system can be set to monitor the tire pressure of the trainer aircraft's tire 16 as soon as it touches the ground, based on the pressure sensor 31. When the tire pressure of the tire 16 is detected to be too high, the controller controls the exhaust valve 22 to release the air from the tire 16. By depressurizing the tire 16, its elasticity is reduced, and the degree of bouncing when it touches the ground is significantly reduced, thereby improving safety and avoiding landing accidents caused by bouncing.

[0049] In addition, after the aircraft begins to taxi, the air pump 14 can be activated by the controller. The air pump 14 supplies airflow into the intake ring 17 through the air supply pipe 15, and then into the tire 16 through the spoke pipe 19, so as to inflate the tire 16 and prevent damage to the wheel hub 18 and excessive wear of the tire 16 due to insufficient tire pressure during taxiing, thereby improving the durability of the tire 16.

[0050] The foregoing description enables those skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A strut-type landing gear for a basic trainer aircraft, comprising a first hydraulic strut, a second hydraulic strut, a first support strut, and a second support strut, characterized in that: Also includes: The tire has a first telescopic rod at the bottom of the first hydraulic rod, a second base shaft fixedly installed at the bottom of the first telescopic rod, and a rotating shaft rotatably connected to both ends of the second base shaft. A spoke tube is fixedly installed at one end of the rotating shaft, and a wheel hub is fixedly installed at one end of the spoke tube. The tire is disposed on the inner wall of the wheel hub. An air pump is provided. A second fixed sleeve is fixedly installed on the outer wall of the first hydraulic rod. The air pump is installed on the outer wall of the second fixed sleeve. An air supply pipe is connected to the bottom of the air pump. One end of the air supply pipe is split into two. An air inlet ring is fixedly installed on one side of the outer wall of the spoke tube. An annular plate is rotatably connected to one side of the air inlet ring. The annular plate is sleeved with the bottom end of the air supply pipe. The intake ring, spoke tube, and tire are all hollow structures, and the intake ring, spoke tube, and tire are connected. A pressure sensor is fixedly installed on the inner wall of the tire near the wheel hub. The pressure sensor is electrically connected to a controller. A vent pipe is provided on the inner wall of the wheel hub. One end of the vent pipe extends through the inner wall of the tire. An exhaust valve is provided on the inner wall of the vent pipe. The exhaust valve, pressure sensor, and controller are all electrically connected. A first fixing sleeve is fixedly installed on the outer wall of the first hydraulic rod, and a third base shaft is fixedly installed on the inner wall of the first fixing sleeve. The third base shaft is rotatably connected to the bottom end of the first support rod. A connector is fixedly installed on one end of the second support rod, and a fifth base shaft is fixedly installed on the inner wall of the connector. One end of the first support rod is rotatably connected to the fifth base shaft. One end of the second support rod is rotatably connected to a fourth base shaft, and both ends of the fourth base shaft are fixedly mounted with a first fixed base. A base block is fixedly installed at the top of the first hydraulic rod, and a seventh base shaft is rotatably connected through the outer wall of the base block. A second fixed base is fixedly installed at both ends of the seventh base shaft. The outer wall of the seventh base shaft is rotatably connected to a mounting bracket. A second hydraulic rod is fixedly installed on one side of the outer wall of the mounting bracket. A second telescopic rod is provided at one end of the second hydraulic rod. A sixth base shaft is rotatably connected to one end of the second telescopic rod. The sixth base shaft is fixedly installed on the inner wall of the connector. The connector is located on one side between the fifth base shaft and the sixth base shaft, and is close to the side of the first support rod near the sixth base shaft. The connector allows for 0°-180° angle adjustment between the first support rod and the second support rod, and also allows for angle limitation between the first support rod and the second support rod.

2. The strut-type landing gear for a basic trainer aircraft according to claim 1, characterized in that: The outer wall of the first hydraulic rod is connected to an oil inlet pipe and an oil return pipe, and one end of the oil inlet pipe and the oil return pipe is connected to an oil tank.

3. The strut-type landing gear for a basic trainer aircraft according to claim 1, characterized in that: Both the first hydraulic rod and the second hydraulic rod are electrically connected to the controller.

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