JPH02246898A - Landing of aeroplane - Google Patents

Abstract

PURPOSE:To prevent the abrasion and melting of a wheel tire and prevent the burst of the wheel tire and shorten the time up to the realization of taxing speed and reduce the shock on rebounding by revolving the wheels in the normal direction before grounding. CONSTITUTION:Tires 5 and 5 are revolved beforehand in the normal direction at a landing revolution speed by allowing a motor 6 to conduct. Therefore, at a landing point, the tire 5 having the landing revolution speed obtains the landing speed of a plane body in a drastically short time. Therefore, the slip of the tire 5 for a runway is reduced by that portion, and the heat generation can be reduced drastically, and the abrasion and melting of the tire 5 due to the heat generation and the burst of the tire can be surely prevented. Further, the bound angle is reduced for the grounding angle of the tire in the normal revolution, and the shock on rebounding is reduced by that portion. In the brake application after grounding, a DC motor 6 acts for the power generation brake, and the heat generation in a conventional brake device can be reduced.

Description

[Detailed description of the invention] [Industrial application field] The present invention relates to a method for landing an airplane.

[Prior Art] As is well known, an airplane is provided with landing gear wheels for takeoff, landing, and taxiing, and tires are mounted on the landing gear wheels.

[Problems to be Solved by the Invention] When an airplane lands, the landing gear is stationary, so there is a large speed difference between the ground speed of the aircraft and the rotational speed (zero speed) of the landing gear.

In other words, as shown in Fig. 4, the rotational speed of the landing gear whose rotational speed ω is zero increases rapidly due to the ground speed of the aircraft at the time of landing t1, and after a time of 1゛1°, the landing speed of the landing gear reaches ωL. reach Then, the vehicle is sequentially decelerated by braking, and reaches the taxiing speed ωT after time T2.

At the above-mentioned time Tea, the tires of the landing gear slip on the runway, and the heat generation causes wear and melting, which may further cause the tires to parse.

Also, the time T1. to reach the taxiing speed ωT. Ten T2 is
The shorter the length, the better from the viewpoint of traffic control at busy airfields.

Furthermore, as is well known, a three-point landing is preferable, but if the tail wheel lands first and the leg wheels land later and bounces, the landing angle θ will change as shown in FIG.

and bound angle θ2. becomes equal, which is undesirable because the impact when the wheels land on the ground again becomes large.

The present invention aims to provide a landing method for an airplane that prevents the abrasion and melting of the leg tires during landing, and prevents them from collapsing due to these, shortens the time required to reach taxiing speed, and reduces the impact upon rebound. The purpose is

[Means for Solving the Problems] The method for landing an airplane according to the present invention is characterized in that the landing gear is rotated in the normal direction before landing.

The rotational speed of the landing gear at the time of landing is preferably set to a value as close as possible to the landing speed of the aircraft body.

Furthermore, although a DC motor is preferably used as the means for rotating the casters, a hydraulic motor may also be used.

[Operation] In the method of landing an airplane configured as described above,
Since the landing gear wheels are rotated forward in advance at a landing rotation speed that is extremely close to the landing speed of the aircraft, the time it takes for the landing gear rotation speed to reach the landing speed of the aircraft is greatly shortened compared to the conventional method. This reduces tire slippage, reduces heat generation, and prevents tire abrasion, melting, and damage caused by these.

Also, the time to reach taxiing speed is therefore reduced.

Furthermore, the bounce angle at the time of bouncing is much smaller than the landing angle, and the impact at the time of rebound is reduced.

Furthermore, a DC motor is used as the rotation means, and the DC motor is used for dynamic braking to reduce heat generated by the braking device.

[Example] FIG. 1 shows an apparatus for implementing the invention.

In the figure, the boss portion 2 of the leg 1 has a pair of bearings 3.
A shaft 4 is rotatably supported through the shaft 3, and double tires 5.5 are mounted on both ends of the shaft 4.

A rotor 7 constituting a DC motor 6 is integrally provided in the center of the shaft 4, and a magnetic field 8 is provided in the boss portion 2. Therefore, the electric motor 6 can be energized to rotate the tires 5.5 via the shaft 4, and the motor 6 can also be used for dynamic braking. Note that the DC motor 6 is not limited to this, and a hydraulic motor may be used, and the tire 5 may be a single tire.

At the time of landing, as shown in FIG. 2, the motor 6 is energized to rotate the tires 5.5 forward at the landing speed ωP in advance. It is desirable that this rotational speed ωP match the landing speed ωL of the aircraft. However, since the impact load upon landing is as large as about 2@ of the static load, and a large deflection occurs in the tires 5, it is difficult to match it accurately. , the landing speed of the aircraft is set to a value extremely close to the landing speed ωL.

For example, set the aircraft landing speed ωL to 125 to 150 m1Ie/h.
(200 to 240 km/h), then the rotational speed ωP at landing is 17.7 to 2 when the tire radius R = 0.5 m.
1.3 rotations/sec, 11.8 when R=0°75m
The tire 5 is rotated forward at a value as close as possible to ~14° 1 rotation/sec.

Therefore, at the time of landing t1, the landing rotation speed ωP
The tire 5 at the time T1. compared to the extremely short time T
1, the landing speed of the aircraft reaches ωL.

Therefore, the slippage of the tires 5 on the runway is reduced accordingly, and the heat generation is greatly reduced, and wear and tear of the tires 5 due to heat generation, melting, and damage caused by these are reliably prevented.

Also, the time T r until the taxiing speed ωT is reached
+72 is greatly reduced compared to the conventional time T r -172.

Further, as shown in FIG. 3, the bounce angle is smaller than the landing angle θ1 of the tire 5 rotating in the direction of the arrow, θ2. Therefore, only on rebound! ! The attack becomes smaller.

Furthermore, during braking after landing, the DC motor 6 performs a dynamic braking action, thereby reducing the heat generated by the conventional braking device.

[Effects of the Invention] Since the present invention is configured as described above, it is possible to reduce tire slip on the runway, reliably prevent tire abrasion, melting, and damage caused by these, and shorten the interval between tire replacements. It can be extended for a long time and is economical.

In addition, the time required to reach taxiing speed can be shortened, contributing to airfield control.

In addition, it is possible to reduce the rebound 'ms, improve riding comfort, and contribute to the strength design of the aircraft body and equipment.

Furthermore, when a DC motor is used as the rotating means, the motor can be used for dynamic braking, reducing heat generation of conventional braking devices and improving durability.

[Brief explanation of drawings]

FIG. 1 is a front sectional view showing an apparatus for carrying out the present invention, and FIG.
The figure is a timing chart showing the wheel rotation speed, Figure 3 is a side view showing the behavior of the tire during bounding, and Figures 4 and 5 are the results of the conventional method.
This is a drawing corresponding to the figure. ω...Role rotation speed ωP...Rotation speed upon landing
ωL...Aircraft landing speed 5...Tires 6
...DC motor factor diagram Book October 13, 1989 Director-General of the National License Agency Address 2-12-26 Higashitogura, Kokubunji City, Tokyo
Name Nippo Sangyo Co., Ltd. Representative Yuya Abe

Claims (1)

[Claims] An airplane landing method characterized by rotating the gear wheels in the normal direction before landing.