JP2509544Y2 - Cover structure of aircraft - Google Patents

Description

[Detailed description of the device]

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The invention of the present application relates to a cover structure for a load for improving stealth performance of an aircraft, particularly a fighter. More specifically, when mounting weapons such as missiles, exterior fuel tanks, and other aircraft loads on the fuselage (conformal loading method), the radar reflection area of these loads is reduced to reduce The present invention relates to devising a cover structure for improving overall stealth performance.

[0002]

2. Description of the Related Art As a mounting means for mounting a load such as a weapon on an aircraft, a pylon equipment system (FIG. 7A) in which a load 23 is mounted on the end of a wing 21 and a load 23 is mounted on a fuselage 22 of the aircraft. There are two methods, an interior method (FIG. 7 (b)) for interior installation and a conformal mounting method (FIG. 7 (c)) for mounting the mounted object 23 on the side of the fuselage 22 of the aircraft in a close-contact or semi-embedded manner.

Although the pylon equipment system is highly versatile and inexpensive, it requires a pylon, and since the weapons 23 are arranged under the wings 21, the aerodynamic characteristics change (especially resistance increase) is large, and the weapons 23 are mounted. This is a method having drawbacks such as remarkable deterioration in performance. The interior method is generally used when the radar reflection area of the aircraft itself is small.It has the best stealth performance, but it is inferior in versatility because it requires consideration of weapons etc. from the initial stage of aircraft design. Moreover, the degree of freedom of weapons etc. is low. In addition, because of the interior, the volume inside the machine increases, so the resistance increases due to an increase in the cross-sectional area of the machine and an increase in the wetted area, resulting in performance degradation when the weapon is not mounted. The conformal loading method is a method proposed to overcome the disadvantages of the pylon equipment method and improve the aerodynamic characteristics and weapon loading capacity.

[0004]

However, the above-mentioned conformal mounting system has a drawback that the stealth property is not good because the tip of a weapon such as a missile is exposed. In other words, in the conformal mounting method, the radar reflection area of the weapon (forehead, seeker, etc.) is large, so even if the radar reflection area of the aircraft itself is small, the stealth performance of the entire aircraft will be inferior. There was a problem that it was not suitable for the weapon loading method. In particular, stealth at the time of head-on, which is the most important in the actual battle phase (when face-to-face enemies, that is, when facing a front opponent), becomes a problem.

An object of the invention of this application is to provide a simple and highly flexible stealth performance improving means for reducing the radar reflection area at the time of head-on in the conformal mounting system in order to solve the above-mentioned problems. .

[0006]

In order to solve the above-mentioned problems, the invention of this application is arranged in front of a load 3 attached to a fuselage 2 of an aircraft, and is attached to the fuselage 2. A cover structure 1 for a radar wave that reduces a radar reflection area of an on-board object 3 has a cover structure for an aircraft on-board object having an inclined surface 4 of a radio wave absorber that inclines with respect to the traveling direction of the aircraft. In addition, the inclination angle of the inclined surface 4 of the cover 1 with respect to the traveling direction of the aircraft is 30 ° to 6 °.
The range is 0 °.

[0007]

The radio wave emitted from the partner aircraft when the head is on corresponds to the front of the aircraft body. The inclined surface 4 of the cover 1 that covers the forehead of the mounted object 3 absorbs this radio wave.
It works to reflect.

[0008]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the invention of this application will be described with reference to FIGS. 1 to 3 show a side view, a bottom view and a front view, respectively, of one embodiment of the invention of this application. 1 is
It is a cover for an aircraft payload attached to the aircraft fuselage 2. The cover 1 is arranged in front of the missile 3 which is also attached to the body 2, and covers the missile. 4 is
It is an inclined surface of the cover 1 inclined with respect to the traveling direction of the aircraft.

The cover 1 has four inclined surfaces 4 as shown in the figure.
Polygons such as pyramids, cones, etc.
Any shape may be used as long as it has a shape that covers the forehead of the mounted object 3. It is desirable that the entire surface is composed of this inclined surface 4 when viewed from the front of the aircraft so that the radar can be reflected when the head is on. The hem of cover 1 does not have to be flat,
It may be formed to fit the shape of the forehead of the payload (missile 3). The cover 1 may be made of a radio wave absorber such as a ferrite-based paint or a ceramic-based composite material. Further, for example, a conventional structure material described in JP-A-1-260298 may be used. You can

The inclined surface 4 is 30 degrees with respect to the progress A of the aircraft in consideration of aerodynamic resistance and radio wave reflectivity when the head is on.
It is desirable to have a tilt angle θ between 0 ° and 60 °. In addition,
The payload (missile 3) may be attached to fuselage 2,
It may be mounted by embedding it in the middle body 2.

This cover 1 is thrown away or retracted into the body when using a weapon or the like. This dumping and retracting method will be described with reference to FIGS. 4 and 5. Discarding the cover
As shown in FIG. 4, for example, the weapon cover 1 is connected to the fuselage fuselage with the lock pin 5, and when used, the lock pin 5 is removed and at the same time, the explosive powder 6 is ignited and the injection force is covered through the orifice 7. And cover 1 is ejected. As shown in FIG. 5, the cover is pulled in by stopping the apex of the cover 1 of a regular triangular pyramid with a hinge 8 and pulling one surface 9 with an actuator 10.

The control when the missile 3 is used is shown in FIG.
Control system. Control panel 11
Then, the mission computer 12 is controlled and the ACS (Ar
A control signal is sent to the player by sending a signal for discarding or retracting the cover 1 and a control signal for launching the weapon 3 via the mament control set) 13.

[0013]

[Effects of the Invention] By providing a cover for the mounted object, it is possible to easily and inexpensively realize low stealth characteristics without using a high-cost, low-versus-purpose interior system.
Can take defensive measures. By placing the cover in front of the mounted object, it is possible to secure stealthiness at the time of head-on, which is particularly important in actual battle. Furthermore, by using the cover of the electromagnetic wave absorber provided with the inclined surface, the above-described effect is achieved with a simple structure.

[Brief description of drawings]

FIG. 1 is a side view of a cover according to an embodiment of the present invention.

FIG. 2 is a bottom view of the cover of FIG.

FIG. 3 is a front view of the cover of FIG.

FIG. 4 is a structural diagram illustrating a method of discarding a cover.

FIG. 5 is a structural diagram illustrating a method for retracting the cover.

FIG. 6 Missile control block diagram

7A is an explanatory diagram of a pylon equipment system, FIG. 7B is an explanatory diagram of an interior system, and FIG. 7C is an explanatory diagram of a conformal mounting system.

[Explanation of symbols] 1 cover 4 inclined surface

Continuation of the front page (56) Reference JP-A-1-260298 (JP, A) JP-A-56-137100 (JP, A) Actual opening 3-118195 (JP, U) Actual opening 1-1151092 (JP , U) Actual Kaihei 3-121998 (JP, U)

Claims (2)

(57) [Scope of utility model registration request] 1. A cover for a radar wave, which is arranged in front of a load attached to a fuselage of an aircraft and is attached to the fuselage to reduce a radar reflection area of the load, the cover being in a traveling direction of the aircraft. A structure for covering an aircraft mounted object, which has an inclined surface of a radio wave absorber that is inclined with respect to it. 2. The cover structure for an aircraft mount according to claim 1, wherein an inclination angle of the inclined surface with respect to a traveling direction of the aircraft is in a range of 30 ° to 60 °.