JPH0516896A - Short distance take-off system of aircraft - Google Patents

Abstract

PURPOSE:To shorten a take-off ground in, run an aircraft short distance take-off system being applied to a runway in an airfield or a flying-off deck, etc., on a mother ship. CONSTITUTION:In an aircraft short distance take-off system with an upgrade incline forming a route where wheels of aircraft 1 are passed through, the upgrade of an incline A where a front wheel 3 of the aircraft 1 passes through and that of an incline B, where main wheels in the rear passes through are varied from each other.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an aircraft short-range take-off device applied to a runway of an airfield or a flight deck of a mother ship.

[0002]

2. Description of the Related Art An example of a conventional aircraft short-range take-off device is shown in FIG. A slope C having a climbing slope is formed at the tip of the runway or flight deck on which the aircraft 1 takes off.

Since the aircraft 1 receives an upward load from the main landing gear 2 and the nose gear 3 by climbing up the slope C at the time of takeoff, an upward speed is applied to the center of gravity of all the aircraft before leaving the slope C. This reduces the required runway length compared to takeoff on a flat runway.

[0004]

The above-mentioned conventional short-distance take-off device for an aircraft utilizes the reaction force from the ground because the main leg and the nose landing route are on the same slope during take-off gliding. It is not possible to change the attitude of the aircraft appropriately, and therefore it is necessary to increase the takeoff run distance.

An object of the present invention is to provide a short-distance take-off device for an aircraft, which can appropriately change the attitude of the aircraft during take-off and gliding by utilizing the reaction force from the ground to shorten the take-off and gliding distance. Is.

[0006]

SUMMARY OF THE INVENTION The present invention is a short range take-off system for an aircraft having an uphill slope forming a path through which the wheels of the aircraft pass. The feature is that the slope with the passing slope is different from each other.

[0007]

According to the present invention, since the slope of the ascending slope that the wheels in front of the aircraft pass and the slope of the ascending slope that the wheels in the rear pass are different, the reaction force received by the wheels from both slopes is different. The attitude of the aircraft is properly controlled to obtain a large wing lift, and the takeoff distance of the aircraft is shortened.

[0008]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A first embodiment of the present invention will be described with reference to FIGS. An aircraft 1 having a plurality of main landing gears 2 and one front landing gear 3 provided in front of the main landing gears 2 forms a wheel path of the front landing gear 3 and a wheel path of the main landing gear 2 at the tip of the runway for takeoff gliding. The slope A and the slope B are configured to have different climbing slopes, and the slope A is disposed above the slope B. Further, the runway portions behind the slopes A and B are configured to be horizontal at the same height.

On a slope A which forms a wheel path of the front legs 3, a track 4 of an aircraft ejection device (hereinafter referred to as a catapult) similar to that used in a normal aircraft carrier is installed. A lashing device 6 (hereinafter referred to as a launch bar) attached to the front leg 3 can be hooked on a hook 5 that moves along the catapult track 4.

In this embodiment, the aircraft is designated by reference numeral 1a in FIG.
As shown by, the catapult starts acceleration in a horizontal position, and when sufficient speed is obtained, the nose is raised until the nose is raised and the maximum wing lift is obtained, as indicated by reference numeral 1b. Push up. After that, both the wheels of the front landing gear 3 and the wheels of the main landing gear 2 reach the slopes of the climbing slopes A and B, and the center of gravity of the vehicle body obtains an upward speed. After that, when the wheels of the front legs 3 leave the slope A, the force applied to the wheels of the main legs 2 generates a moment that lowers the nose of the aircraft, and this moment is used to move the aircraft from the maximum lift posture to the aerial acceleration posture. Transition to.

As described above, in the present embodiment, the attitude and center-of-gravity velocity of the aircraft during take-off gliding can be appropriately controlled by the distribution of the slopes of the slopes A and B, and the distance required for take-off gliding can be shortened. .

A second embodiment of the present invention will be described with reference to FIG. The slope distribution of slope A and slope B as in the first embodiment which minimizes the takeoff run of the aircraft is:
Varies depending on aircraft model, weight, center of gravity, etc. In the present embodiment, in order to deal with this, the slope B can be rotated about the axis in the width direction of the runway with the branch line 7 of the slope A and the slope B as the central axis.

In the present embodiment, the slope B is rotated around the branch point 7 to change the slope of the slope B with respect to the slope of the slope A depending on the aircraft model, weight, center of gravity position and the like.
As a result, the attitude of the aircraft during gliding can be controlled more appropriately according to the aircraft model, weight, position of the center of gravity, etc., and the distance required for takeoff gliding can be shortened.

Although each of the above embodiments relates to a short-range take-off device for an aircraft of the type having a front leg in front of the main landing gear, the present invention has a rear leg having a tail wheel behind the main landing gear. It goes without saying that it can also be applied to aircraft of the type.

[0015]

As described above, the aircraft short-distance take-off device of the present invention is configured such that the slope of the ascending slope through which the front wheels of the aircraft pass and the slope of the ascending slope through which the rear wheels pass are different. The position of the front and rear wheels and the force received by the aircraft from the runway during the takeoff run of the aircraft can be controlled by the slope of the runway slope to shorten the takeoff run distance of the aircraft.

[Brief description of drawings]

FIG. 1 is an overall configuration diagram of a first embodiment of the present invention.

FIG. 2 is an enlarged view of a portion A of FIG. 1 showing details of a front leg and a catapult hook of the embodiment.

FIG. 3 is a functional explanatory diagram of the embodiment.

FIG. 4 is an overall configuration diagram of a second embodiment of the present invention.

FIG. 5 is an overall configuration diagram of a conventional aircraft short-range take-off device.

[Explanation of symbols] 1 Aircraft 2 Main landing gear 3 Front landing gear 4 Catapult orbit 5 Catapult hook 6 Launch bar 7 Branch line between slope A and slope B A, B slope

Claims (1)

Claim: What is claimed is: 1. A short take-off device for an aircraft having an ascending slope forming a path through which an aircraft wheel passes, wherein a slope through which a front wheel of the aircraft passes and a slope through which a rear wheel passes. A short-range take-off device for aircraft characterized by different slopes from each other.