JP2007112408A - Method and device for giving wheel of aircraft rotational speed according to speed upon landing and achieving smooth landing - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To prevent an accident caused by a wheel of an aircraft by alleviating the impact on the wheel and a runway upon landing, while in a conventional aircraft, a surface of a tire is replaced for reuse since the wheel rotates rapidly due to the friction against the road surface upon landing, and the temperature of a tire of a large aircraft goes as high as 400°C emitting white smoke due to the frictional heat, though the main body is also fatigued even after the replacement of the surface only, which leads to the accident. <P>SOLUTION: The wheel to be used is provided with the power for obtaining a predetermined rotational frequency before landing. Small power is enough for this purpose since it is not for moving the aircraft body. The speed upon landing is measured by relating a sensor buried in the surface of the runway to a sensor on the aircraft side, and the predetermined rotational frequency is given to the wheel to achieve smooth landing. <P>COPYRIGHT: (C)2007,JPO&INPIT

Description

    The present invention relates to a wheel used during takeoff and landing of an aircraft. Aircraft wheels are also used to take off at take-off, but here are mainly concerned with mitigating the impact between the wheels and the runway during landing.

    In the prior art, aircraft wheels are not particularly problematic with respect to takeoff. When taking off, a large amount of fuel is loaded, so the load on the wheels is large. However, it does not cause a big impact. On the other hand, when landing, a large passenger aircraft sometimes adds a weight of 30 tons per tire. Also, as soon as the vehicle is landed, the wheels suddenly rotate and the temperature of the tire may exceed 400 ° C, raising white smoke. A tire that has received such an impact is changed from 200 to 250 landings, that is, from one month to one and a half months. The replaced tire is recapped and reused five to six times. Even if only this surface is replaced, this recycled tire is dangerous because the other parts are fatigued and sometimes punctured.

    The problem to be solved by the present invention is to mitigate the impact that the wheels of an aircraft receive due to the rapid rotation when landing. Also, by reducing the impact, tire fatigue is reduced and safety is improved.

    Means for solving the above-mentioned problems of the present invention prevents abrupt rotation at the time of landing by giving the wheels of the aircraft a rotation synchronized with the landing speed immediately before landing. In addition, the impact received by the wheel and the tire is reduced, thereby extending the life of the tire and improving the safety by not using the recycled tire.

    As described above, the landing of the aircraft can be made smoother and safer by utilizing the present invention. Since there is no sudden rotation at the landing of the wheel, the life of the tire is extended and there is an economic effect. Safety can be improved if it is not necessary to use recapped recycled tires. The motor used here is small in size because it only needs the output necessary to turn the wheels. Therefore, there is not much increase in the weight of the airframe by providing this system. Conventionally, aircraft have been mainly considered to fly, and due to the focus on brakes after landing, little attention has been paid to rotating the wheels. Some large helicopters have self-propelled wheels. However, its purpose is self-propelled and is different from the present invention.

The aircraft slides on the road surface using the thrust of the engine body as a power source. Therefore, the wheels themselves do not move on the runway with a rotational force. However, some large helicopters are self-propelled. If the aircraft engine is not powered, it is towed by a towing vehicle. In this way, it has been a basic policy of the aircraft not to attach anything unnecessary to make the aircraft as light as possible. However, in the state equipped with a wheel that takes a heavy weight of 30 tons per tire at the time of landing on a large aircraft as in the present situation, some things must be reconsidered. The power of the wheel in the present invention is not a large output that moves the airframe itself, but a small power for giving rotation to the wheel in advance at the time of landing. Therefore, a small device is sufficient. As a specific example of the power, an electric motor is convenient. The motor can be directly connected to the axle and can be decelerated by a reduction gear. If a reduction gear is used, a smaller motor is possible. As a power source for the motor, a method using a battery, a method using electric power using a fuselage engine as a power source, and a method combining both of them, power generation by a small engine, a fuel cell, etc. are possible. The power source is convenient. In an example of a large four-jet passenger aircraft, the power generation capacity is 90 KVA generators for each of the four engines, for a total of 360 KVA. Since the proportion of power used for operating devices is small and there is a lot of room lighting etc., it is a burden that is sufficiently possible if it is used for wheel rotation only during landing. By synchronizing the rotation of the wheel with the ground speed at the time of landing, the wheel and the tire are alleviated from the impact caused by the landing. On the other hand, when the wheel does not rotate in advance, the tire rotates rapidly at the same time as landing, and in a large aircraft, the tire becomes 400 degrees C or more due to friction with the road surface and raises white smoke. In such landings, tires are heavily worn, and large passenger aircraft are reused five to six times with recapping to replace the surface for economy. Even if the cap is recaptured, there is a safety problem because the entire tire is tired and cannot be completely regenerated. On the other hand, when a wheel is given a synchronized rotation, the impact is small and the life of the tire is extended. In addition, since the surface wear is small, a life that does not require recapping is possible. Not using recycled tires leads to improved safety. In order to measure the ground speed at the time of landing, an accurate measurement is performed by a combination of a sensor arranged on the runway and a sensor on the airframe.
FIG. 1 is a plan view showing the positions of wheels of an example of a conventional large passenger aircraft. In this example, the front leg 2 has two tires, the wing main leg 3 has eight tires, and the fuselage main leg 4 has eight tires. FIG. 2 is a three-dimensional view of a set of two tires for the front leg 2. FIG. 3 is a three-dimensional view of eight tires comprising two sets of four tires of the main leg 3 of the wing. FIG. 4 is a three-dimensional view of eight tires comprising two sets of four tires of the main leg 4 of the fuselage. FIG. 5 is a layout diagram of tires when the front legs 2 are viewed from above. FIG. 6 is a layout diagram of tires when the main legs 3 and 4 are viewed from above. Of these, most of the conventional front legs 2 have no brake. The landing order of the tire wheels at the time of landing is such that the two rear wheels of the main leg 4 of the fuselage are grounded, and then the two front wheels are grounded. The main leg 3 of the wing is grounded in the same manner as the main leg 4 of the trunk. Thereafter, the front leg 2 is grounded. The brakes are automatically operated at the same time as the grounding and operate optimally.
Here, regarding the method of installing the motor for rotating the wheel according to the present invention, there are mainly four methods. FIG. 7 is a cross-sectional view showing one method of the two-wheel portion of the main leg. In this system, a disc brake 15 is built in each of the two wheels, and a motor 13 having a planetary gear reduction device 14 for each wheel is built in the main shaft 7. A large passenger plane uses a multi-stage disk, but here it is symbolized and shown as a single-stage disk for simplicity. FIG. 8 is a cross-sectional view showing one method of the two-wheel portion of the main leg. 7 is a system in which a motor 13 and a speed reducer 14 parallel to the main shaft 7 are arranged outside the main shaft 7 while the system of FIG. 7 has the motor 13 and the speed reducer 14 inside the main shaft 7. . FIG. 9 shows a system in which two wheels are directly connected, and a common motor 13 and speed reducer 14 are arranged in the middle part. FIG. 10 shows a system in which two wheels are directly connected and a common brake 15 and a common motor 13 and a reduction gear 14 are arranged. The front leg 2 has a structure excluding the brake 15 shown in FIGS.

Example: A motor with a planetary gear speed reducer is attached to the wheel of an aircraft, and the motor is operated in advance when landing to give rotation to the wheel, and the ground speed at landing and the rotation speed of the wheel circumference are synchronized and smooth. Landing method and apparatus
FIG. 11 is an enlarged detailed view of the left half of FIG. The motor shaft 23 of the motor mounted inside the main shaft 7 and the concentric power shaft 16 are connected via a planetary gear reduction device. There is a disc brake between the motor and the wheels.
Here, the planetary gear reduction device will be described. FIG. 12 is a diagram showing the operating principle of the planetary gear. In FIG. 12a, when the sun gear 36 rotates in the direction of the arrow, the five planetary gears 24 move in the direction of the arrow. FIG. 5B shows a state where the rotation of the planetary gear 24 is not transmitted to the sun gear 36 when the internal gear 25 rotates when the planetary gear 24 moves in the direction of the arrow.
FIG. 13 is an enlarged view of the reduction gear used in the present embodiment applying the principle of FIG. The shafts 18 of the five planetary gears 24 are supported by a disk, and the rotation of the planetary gears becomes the rotational force of the wheels. That is, the rotational force of the sun gear 36 fixed to the motor shaft 23 rotates the five planetary gears 24 and rotates the wheels 5. On the other hand, the rotational force of the wheel rotates the planetary gear 24, but the freewheeling gear 26 rotates according to the principle of FIG. 12B, and the rotational force is not transmitted to the sun gear 36. In FIG. 13, the claw and spring of the freewheeling gear 26 are omitted for simplicity.
The motor 13 incorporating the planetary gear reduction device 14 is installed on the main shaft 7. FIG. 14 is a side view when a large aircraft is landed. Aircraft 1 is just before landing on runway 35 with the front facing up. In order to synchronize the rotation of the wheel with the ground speed at the time of landing, the ground speed is calculated by wireless communication between the ground sensor 38 and the aircraft sensor 44 embedded in the runway surface 35, and the wheel is rotated in synchronization with the ground speed. As for the landing order of the wheels, first, the rear wheels of the main legs 3 and 4 land, and then the front wheels land. Finally, the wheels of the front legs 2 land. When the wheels land, the motor is turned off and acceleration stops, and the wheels are decelerated by automatic braking. After landing, the rotational force of the wheel is not transmitted to the motor by the freewheeling gear. If the rotational force is transmitted to the motor while the wheel is rotating at high speed, the rotation is caused through the speed increasing gear, which is not preferable in terms of the mechanism. However, since the freewheeling gear is fixed when the aircraft is backing, wheel rotation is transmitted to the motor. However, there is no problem if the speed is increased because the speed is low at the time of the back, but this can be prevented by applying a reverse voltage to prevent the rotational resistance from increasing due to the power generation by the reverse rotation of the rotor.
Next, in the case of takeoff, the rotational force of the wheel is not transmitted to the motor by the freewheeling gear. This can also be solved by adding a clutch. However, the clutch is not always necessary because it does not run long distances. It is possible to accelerate the wheel by rotating the motor, but if the power source of the motor is the engine of the fuselage, it is inefficient to change the power to turn the motor.
FIG. 15 is a schematic diagram of the system of this embodiment. Inside the airframe 1 surrounded by a dotted line, in the figure, 42 is a computer, 43 is a controller, 45 is a power source, and 44 is an airframe sensor. Ground sensors 38 are embedded in the runway at regular intervals. The signal of the radio communication 41 between the ground sensor 38 and the airframe sensor 44 is sent to the computer 42 of the airframe, where it is calculated, and the information is sent to the controller 43 to rotate the wheel motor 13. Since the ground speed is different for each wheel, it is measured for each wheel until just before touching.

  It is a top view which shows the position of the wheel of a large passenger aircraft.   FIG. 3 is a three-dimensional view of a set of two wheels of a front leg of the large passenger aircraft shown in FIG. 1.   FIG. 2 is a three-dimensional view of two sets of four wheels of one set of main legs on the wing shown in FIG. 1.   FIG. 2 is a three-dimensional view of two sets of four wheels of a set of main legs in the trunk shown in FIG. 1.   It is a tire arrangement figure of the front leg of a large-sized passenger aircraft.   It is a tire arrangement figure of the main leg of a large-sized passenger aircraft.   It is the schematic of the cross section which shows the system which incorporated the motor and the reduction gear in the inside of the main axis | shaft which connects two wheels of a main leg.   It is the schematic of the cross section which shows the system which has arrange | positioned the motor in parallel with the main axis | shaft outside the main axis | shaft which connects two wheels of a main leg.   It is the schematic of the cross section which shows the system which directly connected the axle | axis which connects two wheels of a main leg, and has arrange | positioned the motor and the reduction gear in the center of the main shaft.   It is the schematic of the cross section which shows the system which has connected the axle | axis which connects two wheels of a main leg directly, and has arrange | positioned the brake, motor, and speed reducer which are shared to two wheels.   FIG. 8 is an enlarged cross-sectional detail view of the left half of the schematic diagram of FIG. 7.   It is a figure which shows the operating principle of a planetary gear.   It is a figure of the principle of operation of a planetary gear speed reducer.   It is a side view which shows the relationship between the state just before landing of a large passenger aircraft, and a ground sensor.   FIG. 15 is a basic circuit diagram of FIG. 14.

Explanation of symbols

1 Large passenger plane body 2 Position of the front leg consisting of the two wheels of the large passenger plane 3 Position of the main leg consisting of the four wheels on the wing of the large passenger plane 4 Position of the main leg consisting of the four wheels on the fuselage of the large passenger plane 5 Tire wheels 6 Column 7 Main shaft 8 connecting two wheels Beam 9 connecting main shaft Tire cross section 10 Wheel 11 Reduction gear device 12 Piston 13 Motor 14 Planetary gear reduction device 15 Brake 16 Power shaft 17 Axle 18 Planetary gear shaft 19 Vehicle bearing 20 Disc rotor 21 Pad 22 Bearing cross section 23 Motor shaft 24 Planetary gear 25 Planetary gear internal gear 26 Free wheeling gear internal gear 27 Free wheeling gear outer ring 28 Motor rotor 29 Permanent magnet 30 Stator 31 Bearing cross section 32 Motor bearing 33 Encoder 34 Motor shell 35 Runway surface 36 Sun Ya 37 freewheeling bearing rollers 38 ground sensor 39 ground trunk 41 Ground Sensor Sensor wiring 40 ground sensor wiring and aircraft sensors wireless communication 42 computer 43 controller 44 aircraft sensors 45 supply gear

Claims (18)

    A method of attaching a motor that applies rotational force to the wheels of an aircraft, activating the motor in advance at the time of landing, rotating the wheels, and synchronizing the ground speed at the time of landing and the rotational speed of the circumference of the wheel to land smoothly.     In order to measure an accurate speed at the time of landing, a sensor is attached to the runway of the airfield to correspond to the sensor attached to the aircraft body. How to make.     A method for smoothly landing an aircraft according to claims 1 and 2, wherein a motor for applying a rotational force to the wheel is coaxially attached to the wheel shaft.     The aircraft according to claim 1, 2, and 3, wherein a motor that applies rotational force to the wheel is used to reduce power by transmitting power to the wheel using a reduction gear. How to land smoothly.     5. A method for smoothly landing an aircraft according to claim 1, wherein a planetary gear is used as a reduction gear.     6. The aircraft according to claim 5, wherein the planetary gear has a freewheeling gear so that forward rotational force from the wheels is not transmitted to the motor shaft of the central sun gear. How to land on.     When the rotational force of the wheel is transmitted to the rotation of the motor, when the motor tries to generate electricity by acting as a generator, the reverse rotation voltage is applied so that the motor does not become a regenerative brake so that the rotation resistance of the wheel A method for smoothly landing an aircraft according to claims 3, 4, 5, and 6, wherein:     Claims 3, 4 and 3, characterized in that the power of the rotating wheel immediately after take-off is transmitted to a power motor and used as a generator, and the power is used. A method for smoothly landing an aircraft according to claim 5.     Claims 1, 2, 3, 4, 5 are characterized in that power generation using an engine of the fuselage body as a power source is used as a power source for a motor that applies rotational force to the wheels. A method for smoothly landing an aircraft according to any one of Items 6, 6, 7, and 8.     A device that attaches a motor that applies rotational force to the wheels of an aircraft, activates the motor in advance when landing, rotates the wheel, and synchronizes the ground speed at the time of landing and the rotational speed of the circumference of the wheel to land smoothly.     11. The aircraft according to claim 10, wherein a sensor is attached to an airfield runway to correspond to a sensor attached to an aircraft body in order to measure an accurate landing speed. apparatus.     12. An apparatus for smoothly landing an aircraft according to claim 10 and 11, wherein a motor for applying a rotational force to the wheel is coaxially attached to the wheel shaft.     The aircraft according to claims 10, 11, and 12, wherein the motor is made small by transmitting power to the wheels by using a speed reducer to the motor that gives rotational force to the wheels. A smooth landing device.     An apparatus for smoothly landing an aircraft according to claims 10, 11, 12, and 13, wherein a planetary gear is used as a reduction gear.     15. The aircraft according to claim 14, wherein the planetary gear has a freewheeling gear so that forward rotational force from the wheels is not transmitted to the motor shaft of the central sun gear. Device to land on.     When the rotational force of the wheel is transmitted to the rotation of the motor, when the motor tries to generate electricity by acting as a generator, the reverse rotation voltage is applied so that the motor does not become a regenerative brake so that the rotation resistance of the wheel An apparatus for smoothly landing an aircraft according to claims 12, 13, 14, and 15, characterized in that     Claims 12, 13, and 15 wherein the power of a wheel rotating immediately after takeoff is transmitted to a motor for use as a generator and the power is used. 14. An apparatus for smoothly landing an aircraft according to item 14.     Claims 10, 11, 12, 13, 14 are characterized in that power generation using the engine of the fuselage body as a power source is used as a power source for a motor that applies rotational force to the wheels. 15. An apparatus for smoothly landing an aircraft according to any one of Items 15, 15, 16, and 17.

Images