JPH0811794A - Aircraft with exterior equipment on board - Google Patents

Abstract

PURPOSE:To dispense with the control angle change of an aircraft even in the case of the airframe weight being changed by the presence of exterior equipment. CONSTITUTION:External equipment 5 is mounted in close contact in the position of the fuselage upper face 3 on the upper side of the main wing reference face 2 of an aircraft 1 in which a Mach cone does not intersect the main wing whichever point of the outline becomes an apex, and exterior equipment 6 is mounted in close contact in the position of the fuselage lower face 4 where a Mach cone intersects the main wing at least at one point whichever point of the outline becomes an apex. Appropriate lift and pitching moment can be thereby obtained to weight change caused by the presence of the exterior equipments 5, 6, and control angle change due to the presence of the exterior equipments is dispensed with.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an aircraft equipped with an exterior component that does not require a change in steering angle depending on the presence or absence of the exterior component.

[0002]

2. Description of the Related Art Regarding the outer surface shape of a conventional aircraft body, as shown in FIGS.
As for the fuselage shape of the aircraft 01, the upper surface 03 of the fuselage has a concave shape near the center of the main wing, and the lower surface 04 of the fuselage has a shape protruding downward near the main wing. I was getting the effect.

(1) While the aircraft 01 is flying at transonic or supersonic speed, a negative pressure is generated near the upper surface of the main wing on the upper surface side of the main wing reference plane 02 where the fuselage cross-sectional area is once reduced due to the depression. As a result, the lift is increased.

(2) While the aircraft 01 is flying at transonic or supersonic speed, on the lower surface side of the main wing reference plane 02, an increase in pressure occurs near the main wing where the fuselage cross-sectional area increases once due to overhang. As a result, the lift is increased. Due to the effects of the fuselage shape of the above (1) and (2), the lift is increased and the flight performance of the aircraft is improved.

[0005]

In a conventional aircraft, the amount of lift gain is uniquely determined by the outer shape of the aircraft. Therefore, when the weight of the aircraft changes due to the launch of a flying body, the elevator or the like may change. It will be necessary to change the steering angle of the aircraft and re-trim the aircraft.

For this reason, the pilot is required to perform an operation for retrimming the aircraft each time the projectile of the flying object is fired or the like, which imposes an excessive burden. The present invention is intended to solve the above problems.

[0007]

The exterior mounted aircraft of the present invention has a Mach cone for exterior components above the main wing reference plane of the aircraft, regardless of which point of the exterior is the vertex determined by the design Mach number. Is closely attached to the position of the upper surface of the fuselage of the aircraft that does not intersect the main wing, and for exterior parts below the reference plane of the main wing of the aircraft, even if any point of the outer shape becomes the vertex determined by the design Mach number, It is characterized in that the cone is closely mounted at the position of the lower surface of the fuselage intersecting the main wing at at least one point.

[0008]

In the above description, the exterior component mounted below the main wing reference surface generates a high-pressure airflow during transonic or supersonic flight of the aircraft, which hits the lower surface of the main wing to increase lift. When the exterior parts are dropped, the pressure on the bottom surface of the wing drops,
Lifting power is reduced. That is, the lift can be increased or decreased without changing the steering angle.

Further, the exterior component mounted on the upper side of the main wing reference surface increases the pressure on the upper surface side of the rear fuselage at the time of transonic or supersonic flight of the aircraft, thereby obtaining a pitching moment for raising the nose. . At this time, since the Mach cone does not intersect the main wing, the lift does not change. When an exterior component is dropped, a pitching moment for lowering the nose occurs.

As described above, it is possible to obtain appropriate lift and pitching moment with respect to the weight change caused by mounting and dropping of the exterior parts, so that it is not necessary to change the steering angle depending on the presence or absence of the exterior parts.

[0011]

DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described with reference to FIGS. In the aircraft according to the present embodiment shown in FIGS. 1 and 2, the Mach cone does not intersect with the main wing even if any point of the outer shape becomes the apex determined by the design Mach number, and the aircraft 1
Of the radio wave / infrared gimmick body (hereinafter referred to as decoy) injection device 5 which is an exterior component closely attached to the upper surface 3 of the main wing of the main wing reference surface 2 and its outer shape is determined by the design Mach number. Even at the top, at least one point of the Mach cone intersects with the main wing, and is equipped with a flying body 6 that is an exterior component closely attached to the lower fuselage lower surface 4 of the main wing reference surface 2 of the aircraft 1. There is.

In the above description, when the flying body 6 and the decoy ejecting device 5 are mounted, the weight of the aircraft 1 is heavier than when nothing is mounted. Therefore, it is necessary to trim with increased lift during flight.

While the aircraft 1 is transonic or supersonic,
Since the air flow is compressed in the Mach cone drawn with the point on the flying body 6 as the apex, the pressure is higher than that in the free flow. Since this high-pressure airflow hits the lower surface of the main wing, the lift is increased.

However, even if the Mach cone drawn with the points on the flying body 6 as vertices covers the entire main wing,
The pitching moment of the aircraft 1 generated by the high-pressure airflow is nose-down. This pitching / moment change can be canceled by the aerodynamic effect of the decoy injection device 5 mounted on the upper surface 3 of the rear body.

That is, since the pressure of the air flow around the decoy injection device 5 projecting upward from the upper surface of the fuselage becomes high, the rear fuselage is pushed downward, resulting in a pitching moment for raising the nose. . Since the Mach cone having a point on the decoy injection device 5 as its apex does not intersect the main wing, the presence or absence of the decoy injection device 5 does not affect the wing lift.

As described above, the lift of the entire machine and the pitching moment can be changed by mounting the exterior parts, and it is not necessary to change the steering angle depending on the presence or absence of the exterior parts.

[0017]

EFFECTS OF THE INVENTION In the aircraft equipped with exterior products of the present invention, the exterior products are closely attached to the position of the upper surface of the fuselage above the main wing reference plane of the aircraft in which the Mach cone does not intersect the main wing at any point of the outer shape. No matter which point of the outer shape is the apex, the external parts are closely attached to the bottom surface of the fuselage where the Mach cone intersects the main wing at at least one point. It is possible to obtain an appropriate lift and pitching moment for changes in weight, and there is no need to change the rudder angle depending on the presence or absence of exterior parts.

[Brief description of drawings]

FIG. 1 is an explanatory diagram of an aircraft according to an embodiment of the present invention.

FIG. 2 is an explanatory diagram of an operation according to the above embodiment.

FIG. 3 is an explanatory view of a conventional device, (a) is a plan view,
(B) is a side view.

[Explanation of symbols]

 1 aircraft 2 wing reference plane 3 upper surface of fuselage 4 lower surface of fuselage 5 decoy injection device 6 flying body

Claims (1)

[Claims] 1. The exterior parts of the aircraft above the main wing reference plane are in close contact with the position of the upper surface of the fuselage of the aircraft where the Mach cone does not intersect the main wing even if any point of the outline becomes the apex determined by the design Mach number. The outer surface of the aircraft below the reference plane of the main wing of the fuselage lower surface of the fuselage where the Mach cone intersects with the main wing at at least one point regardless of which point on the outer shape becomes the apex determined by the design Mach number. An exterior-equipped aircraft characterized by being closely attached to the position.