Aircraft off-ground grounding detection device based on wheel load and rotating speed

Abstract

The utility model provides an airplane off-ground grounding detection device based on wheel load and rotating speed, and belongs to the technical field of aviation. Comprising an undercarriage body, a pulley is arranged at the movable end of the undercarriage body, a first sensor used for detecting the stress load of the pulley and a second sensor used for detecting the rotating speed of the pulley are arranged on the undercarriage body, and the first sensor and the second sensor are in acting connection with a display module. According to the airplane off-ground and grounding detection device based on the wheel load and the rotating speed, the pulley stress value detected by the first sensor and the pulley rotating speed value detected by the second sensor can be displayed by the display module, a driver can judge the off-ground / grounding condition of an airplane according to the observed values, and the effect of improving driving safety is achieved.

Description

Technical Field

[0001] The utility model relates to the field of aviation technology, in particular to an aircraft take-off and touchdown detection device based on wheel load and rotation speed. Background Art

[0002] During the take-off and landing process of an aircraft, it is crucial to accurately detect whether the aircraft is off the ground and on the ground for flight safety. The traditional detection method mainly relies on the pilot's experience to observe the distance of the aircraft from the ground with the naked eye, so as to retract the landing gear in time before take-off; before the aircraft touches the ground, the landing gear needs to be lowered so that the pulley on the landing gear can rub against the ground. When the aircraft slows down, it means that the pulley has touched the ground, that is, the aircraft has touched the ground.

[0003] However, before takeoff, the distance of the aircraft from the ground cannot be accurately estimated by naked eye observation alone, resulting in the pilot being unable to accurately judge the timing of the aircraft's takeoff. In addition, when encountering a slippery or uneven runway, the aircraft may continue to glide for a distance after landing, resulting in an unclear change in speed, making it difficult for the pilot to confirm that the aircraft has touched the ground. There are certain safety hazards, so it is necessary to provide a detection device for detecting whether the aircraft has taken off and touched the ground. Utility Model Content

[0004] In view of the above problems, the utility model provides an aircraft take-off and touchdown detection device based on wheel load and rotation speed.

[0005] In order to achieve the above-mentioned invention object, the technical solution adopted by the utility model is as follows:

[0006] Provided is an aircraft take-off and touchdown detection device based on wheel load and rotation speed, which is used to detect the aircraft landing gear load and the rotation speed of a pulley. The device comprises a landing gear body, a pulley is arranged at the movable end of the landing gear body, a first sensor for detecting the force load on the pulley, and a second sensor for detecting the rotation speed of the pulley are arranged on the landing gear body, and a display module is operatively connected to the first sensor and the second sensor.

[0007] Furthermore, the first sensor adopts a column force sensor, which includes a fixed end and a movable end. The fixed end of the column force sensor is provided with a mounting frame, and the pulley is rotatably arranged on the mounting frame. The movable end of the column force sensor is connected to a load-bearing plate, and the load-bearing plate is connected to the movable end of the landing gear.

[0008] Furthermore, a shock absorber is provided between the landing gear body and the pulley, the shock absorber includes a damping spring shock absorber, a mounting plate is fixedly provided at the movable end of the landing gear, one end of the damping spring shock absorber is fixedly provided on the mounting plate, and the other end of the damping spring shock absorber is fixedly connected to the load-bearing plate.

[0009] Furthermore, a support member for connecting to the mounting frame is provided on the mounting plate, and the support member includes a mounting tube and a slide rod coaxially slidably connected, one end of the mounting tube is vertically fixed on the mounting plate, and one end of the slide rod is fixed on the mounting frame.

[0010] Furthermore, the second sensor adopts a wheel speed sensor, which includes a magnetic induction sensor head and a ring gear. The ring gear is coaxially fixed on the hub of the pulley, and the magnetic induction sensor head is set on the mounting frame. The magnetic induction sensor head is facing the outer side of the ring gear, and a gap is left between the magnetic induction sensor head and the ring gear.

[0011] Furthermore, a cleaning piece for cleaning the magnetic induction sensor head is provided on the mounting frame, and the cleaning piece includes a wiping block, one end of which is rotatably arranged on the mounting frame, and the other end of the wiping block can be rotated between the gear ring and the magnetic induction sensor head and is in active contact with the end face of the magnetic induction sensor head. A driving piece is provided on the mounting frame for driving the wiping block to rotate in / out of the gap.

[0012] The beneficial effects of the utility model are as follows: the pulley force value detected by the first sensor and the pulley speed value detected by the second sensor can be displayed by the display module, and the pilot can judge the liftoff / grounding condition of the aircraft based on the observed values. Compared with the traditional detection method, the aircraft liftoff and grounding detection device based on wheel load and speed of the present application has the effect of improving driving safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is a schematic diagram of the overall structure of an aircraft take-off and touchdown detection device based on wheel load and rotation speed according to an embodiment of the present application.

[0014] Figure 2 This is a schematic structural diagram from another perspective of an aircraft lift-off and touchdown detection device based on wheel load and rotation speed according to an embodiment of the present application.

[0015] Figure 3 This is a schematic diagram of the support frame structure of an aircraft lift-off and touchdown detection device based on wheel load and rotation speed according to an embodiment of the present application.

[0016] Among them, 1. landing gear body; 2. pulley; 3. column force sensor; 4. wheel speed sensor; 41. magnetic induction sensor head; 42. gear ring; 5. mounting frame; 6. load-bearing plate; 7. shock-absorbing part; 71. damping spring shock absorber; 8. mounting plate; 9. support part; 91. mounting cylinder; 92. slide rod; 10. cleaning part; 101. wiping block; 102. driving part. DETAILED DESCRIPTION

[0017] In order to better understand the above technical solution, the above technical solution will be described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0018] The present application embodiment discloses an aircraft take-off and touchdown detection device based on wheel load and rotation speed, referring to Figure 1 , Figure 2 and Figure 3 , including a landing gear body 1, a pulley 2 installed at the movable end of the landing gear body 1, a first sensor for detecting the force load of the pulley 2, and a second sensor for detecting the rotation speed of the pulley 2 are installed on the landing gear body 1, and the first sensor and the second sensor are operatively connected to a display module.

[0019] In the embodiment of the present application, the display module can be a display screen, and a control module connected to the first sensor, the second sensor and the display screen is installed in the cockpit of the aircraft. The control module can specifically be a computer control system. The driver can monitor the force of the pulley 2 and the rotation speed of the pulley 2 in real time through the display screen. During the take-off process of the aircraft, the pressure on the pulley 2 will gradually decrease. When the first sensor detects that the force is less than the pressure threshold preset in the control module, it indicates that the aircraft has left the ground; in addition, when the aircraft leaves the ground, the pulley 2 no longer rolls along the runway, and its rotation speed decreases. When the second sensor detects that the rotation speed is less than the rotation speed threshold preset in the control module, it can also indicate that the aircraft has left the ground. During the descent of the aircraft, when the pulley 2 touches the ground, the pressure on it will increase. When the first sensor detects that the force is greater than the pressure threshold, it indicates that the aircraft has touched the ground; similarly, when the aircraft touches the ground, the pulley 2 rolls along the runway, and its rotation speed is significantly greater than the speed of the pulley 2 rotating due to air resistance in the air. When the second sensor detects that the rotation speed is greater than the rotation speed threshold, it can also indicate that the aircraft has touched the ground. The pressure threshold and speed threshold can be set by the staff in the control module based on experience and experimental data. The pilot can judge the aircraft's take-off / landing conditions by comparing the observed values ​​with the preset pressure threshold and speed threshold, which has the effect of improving driving safety.

[0020] In other embodiments of the present application, the control module is also operatively connected to an alarm device, which can be specifically a three-color lamp. When the first sensor detects that the pressure on pulley 2 is less than the pressure threshold, and the second sensor detects that the rotation speed of pulley 2 is less than the rotation speed threshold, the green light of the three-color lamp is on, indicating that the aircraft has left the ground; when the first sensor detects that the pressure on pulley 2 is greater than the pressure threshold, and the second sensor detects that the rotation speed of pulley 2 is greater than the rotation speed threshold, the red light of the three-color lamp is on, indicating that the aircraft has touched the ground. The three-color lamp directly displays the lift-off / grounding status of the aircraft, which is more convenient for the pilot to make judgments.

[0021] Specifically, the first sensor adopts a column force sensor 3, which includes a fixed end and a movable end. The fixed end of the column force sensor 3 is bolted to a mounting frame 5, and the pulley 2 is rotatably set on the mounting frame 5. The movable end of the column force sensor 3 is bolted to a load-bearing plate 6, and the load-bearing plate 6 is installed on the movable end of the landing gear.

[0022] In the embodiment of the present application, before the aircraft takes off, the pulley 2 rolls along the runway and is subjected to the gravity of the aircraft; when the aircraft touches the ground, the pulley 2 contacts the ground and is subjected to the impact force of the ground. In both cases, the force applied to the pulley 2 can be detected by the column force sensor 3 and displayed on the display screen.

[0023] Furthermore, a shock absorber 7 is installed between the landing gear body 1 and the pulley 2, and the shock absorber 7 includes a damping spring shock absorber 71. The movable end of the landing gear is bolted to a mounting plate 8, one end of the damping spring shock absorber 71 is bolted to the mounting plate 8, and the other end of the damping spring shock absorber 71 is bolted to the load-bearing plate 6.

[0024] When the pulley 2 rolls along the runway, the vibration-proof capability of the pulley 2 can be improved through the vibration-reducing effect of the damping spring shock absorber 71 .

[0025] When the aircraft touches the ground, the pulley 2 is subjected to the impact force of the ground, so that the elastic parts inside the damping spring shock absorber 71 and the column force sensor 3 will deform when subjected to force. In order to prevent the elastic parts of the two from being damaged due to excessive deformation, a support member 9 for connecting the mounting frame 5 is installed on the mounting plate 8. The support member 9 includes a mounting cylinder 91 and a sliding rod 92 that are coaxially slidably connected. One end of the mounting cylinder 91 is vertically welded and fixed on the mounting plate 8, and one end of the sliding rod 92 is welded and fixed on the mounting frame 5.

[0026] When the impact force on the pulley 2 is too large, the elastic parts of the damping spring shock absorber 71 and the column force sensor 3 are compressed and deformed. After the sliding rod 92 slides back into the installation tube 91, the end of the installation tube 91 away from the installation plate 8 abuts against the installation frame 5, which can prevent the elastic parts from continuing to compress and deform and cause damage.

[0027] Specifically, the second sensor adopts a wheel speed sensor 4, which includes a magnetic induction sensor head 41 and a ring gear 42. The ring gear 42 is coaxially welded and fixed on the hub of the pulley 2, and the magnetic induction sensor head 41 is bolted to the mounting frame 5. The magnetic induction sensor head 41 is opposite to the outer side of the ring gear 42, and a gap is left between the magnetic induction sensor head 41 and the ring gear 42.

[0028] In the embodiment of the present application, before and after the aircraft takes off, the pulley 2 will roll along the runway, and when the aircraft takes off, the pulley 2 is not subject to the friction of the ground, and the rotation speed is significantly lower than its rotation speed on the runway. The rotation speed change of the pulley 2 can be detected by the wheel speed sensor 4, and the value is displayed on the display screen.

[0029] In the case of long-term use, the magnetic induction sensor head 41 of the wheel speed sensor 4 is easily contaminated by impurities in the air, thereby causing inaccurate measurement data. Therefore, a cleaning member 10 for cleaning the magnetic induction sensor head 41 is installed on the mounting frame 5. The cleaning member 10 includes a wiping block 101, one end of which is rotatably arranged on the mounting frame 5, and the other end of the wiping block 101 can be rotated between the ring gear 42 and the magnetic induction sensor head 41 and movably contact with the end face of the magnetic induction sensor head 41. A driving member 102 for driving the wiping block 101 to rotate in / out of the gap is installed on the mounting frame 5.

[0030] In the embodiment of the present application, the wiping block 101 can be made of sponge, and the driving member 102 can be a small motor, which is mounted on the mounting frame 5 and is in transmission connection with the wiping block 101. Before the aircraft takes off and before the aircraft lands, the wiping block 101 can be driven by the motor to rotate to wipe the magnetic induction sensor head 41.

[0031] The implementation principle of the aircraft take-off and touchdown detection device based on wheel load and rotation speed in the embodiment of the present application is as follows: the force value of the pulley 2 detected by the first sensor and the rotation speed value of the pulley 2 detected by the second sensor can be displayed on the display screen, and the pilot can judge the take-off / touchdown status of the aircraft based on the observed values. Compared with the traditional detection method, the aircraft take-off and touchdown detection device based on wheel load and rotation speed in the present application has the effect of improving driving safety.

[0032] It should be understood by those skilled in the art that, although preferred embodiments of the present invention have been described, those skilled in the art may make additional changes and modifications to these embodiments once they are aware of the basic creative concepts. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present invention. Obviously, those skilled in the art may make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. An aircraft take-off and touchdown detection device based on wheel load and rotation speed, used to detect the aircraft landing gear load and the rotation speed of a pulley (2), characterized in that: The invention comprises a landing gear body (1), a pulley (2) being arranged at the movable end of the landing gear body (1), a first sensor for detecting the force load of the pulley (2) and a second sensor for detecting the rotation speed of the pulley (2) being arranged on the landing gear body (1), and a display module being operatively connected to the first sensor and the second sensor.

2. The aircraft take-off and touchdown detection device based on wheel load and rotation speed according to claim 1, characterized in that: The first sensor adopts a column-type force sensor (3), the column-type force sensor (3) comprises a fixed end and a movable end, the fixed end of the column-type force sensor (3) is provided with a mounting frame (5), the pulley (2) is rotatably arranged on the mounting frame (5), the movable end of the column-type force sensor (3) is connected to a bearing plate (6), and the bearing plate (6) is connected to the movable end of the landing gear.

3. The aircraft take-off and touchdown detection device based on wheel load and rotation speed according to claim 2, characterized in that: A vibration damper (7) is provided between the landing gear body (1) and the pulley (2), the vibration damper (7) comprising a damping spring damper (71), a mounting plate (8) is fixedly provided at the movable end of the landing gear, one end of the damping spring damper (71) is fixedly provided on the mounting plate (8), and the other end of the damping spring damper (71) is fixedly connected to the load-bearing plate (6).

4. The aircraft take-off and touchdown detection device based on wheel load and rotation speed according to claim 3, characterized in that: The mounting plate (8) is provided with a support member (9) for connecting to the mounting frame (5), and the support member (9) comprises a mounting tube (91) and a slide rod (92) which are coaxially slidably connected, one end of the mounting tube (91) is vertically fixed on the mounting plate (8), and one end of the slide rod (92) is fixed on the mounting frame (5).

5. The aircraft take-off and touchdown detection device based on wheel load and rotation speed according to claim 2, characterized in that: The second sensor is a wheel speed sensor (4), which comprises a magnetic induction sensor head (41) and a gear ring (42). The gear ring (42) is coaxially fixedly arranged on the hub of the pulley (2), and the magnetic induction sensor head (41) is arranged on a mounting frame (5). The magnetic induction sensor head (41) faces the outer side of the gear ring (42), and a gap is left between the magnetic induction sensor head (41) and the gear ring (42).

6. The aircraft take-off and touchdown detection device based on wheel load and rotation speed according to claim 5, characterized in that: The mounting frame (5) is provided with a cleaning member (10) for cleaning the magnetic induction sensor head (41), the cleaning member (10) comprising a wiping block (101), one end of the wiping block (101) being rotatably arranged on the mounting frame (5), the other end of the wiping block (101) being capable of rotating between the gear ring (42) and the magnetic induction sensor head (41) and being in active contact with the end surface of the magnetic induction sensor head (41), and the mounting frame (5) being provided with a driving member (102) for driving the wiping block (101) to rotate in / out of the gap.

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