JPH0579798A - Altering device for aerodynamic property of missile - Google Patents

Abstract

PURPOSE:To obtain a high aiming probability for a target behind a master aircraft by providing separating means for separating additional wings in the air, and air speed sensing means for sensing, when the speed of a missile launched rearward from the aircraft reaches near '0', it and operating the separating means. CONSTITUTION:Additional wings 4, in which the position of aerodynamic center to the center 10 of gravity is inverted, are detachably mounted at the rear of steering wings 3 of a missile 1 by blasting bolts 9. A differential pressure sensor 5 is provided and so composed that the aerodynamic center is disposed at the front from the center 10 of gravity with respect to the missile 1 until the missile 1 launched rearward of a master aircraft is separated from an inertial speed given by the aircraft by its own propulsion unit. The bolts 9 are blasted by a signal of the sensor 5 sensing, about when the air speed becomes '0' due to cancelling of the inertial speed by the own propulsion speed, it thereby to separate the wings 4 to move the aerodynamic center rearward from the center 10 of gravity, and hence the missile 1 obtains a stable aerodynamic force to obtain high aiming probability to a target.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an aerodynamic characteristic changing device for ensuring aerodynamic stability of an air-to-air vehicle launched rearward from an aircraft.

[0002]

2. Description of the Related Art When an aircraft equipped with a conventional air-to-air projectile launches a projectile backward toward a rear target while moving forward, the projectile is initially given by the aircraft speed. Since the inertial velocity is high, the vehicle moves in parallel with the aircraft and moves backward (back) in a posture in which the head is aimed at the rear target. However, when the self-propelled speed due to the thrust of the nozzle injection or the like increases, the reverse speed gradually decreases, becomes 0, and then changes to the forward speed. That is, the airspeed seen from the direction of the flying body was negative immediately after the launch, but after a while it becomes 0, and then shifts to positive.

[0003]

The above-mentioned conventional flying object has the following problems to be solved.

That is, in general, in order to maintain aerodynamic stability during flight of a flying body, the rear wing is made larger than the front wing, and the aerodynamic center is located rearward with respect to the center of gravity so as to give a weathercock effect. Is configured.

However, as described above, when the projectile is fired toward the rear, the airspeed is negative for a while, so that the air flow is from the rear of the projectile to the front. Therefore, the aerodynamic center is located in front of the center of gravity with respect to the air flow, and there is a problem that the aerodynamic instability becomes uncontrollable until the airspeed becomes positive.

In order to solve the above problems, the present invention is positive even if the airspeed is negative, and
It is an object of the present invention to provide an aerodynamic characteristic changing device for a flying object that can always position the aerodynamic center of the flying object behind the center of gravity.

[0007]

As a means for solving the above problems, the present invention is detachably fixed near the rear of the front wing of a flying body and moves the aerodynamic center forward with respect to the center of gravity of the flying body. An additional wing having a required wing area, a detaching means for detaching the additional wing in the air, and detecting when the airspeed of a projectile launched rearward from the aircraft reaches near zero. Another object of the present invention is to provide an aerodynamic characteristic changing device for a flying object, characterized by comprising an airspeed detecting means for operating the releasing means.

[0008]

Since the present invention is constructed as described above, it has the following actions.

That is, since an additional wing having a wing area necessary for moving the aerodynamic center forward with respect to the center of gravity of the flying body is detachably fixed near the rear of the front wing of the flying body, it is rearward from the mother aircraft. The airflow flows from the rear to the front of the projectile while the projectile fired toward the air is retreating aerobically, whereas the aerodynamic center is located on the wake side of the center of gravity. Aerodynamically stable.

When the self-propelled device for the flying object reduces the retreating speed of the flying object to zero speed, the speed detecting means detects it and activates the removing means of the additional wing to fly the additional wing. After leaving the body, the aerodynamic center of the flying body returns to the rear of the normal position of the center of gravity. Therefore,
Even if the retreat speed of the flying body becomes 0 and it changes to the forward speed this time, even if the air flow starts to flow from the front to the rear of the flying body, the aerodynamic center is on the wake side with respect to the center of gravity To do.

[0011]

DESCRIPTION OF THE PREFERRED EMBODIMENTS An aerodynamic characteristic changing device for a flying vehicle according to a first embodiment of the present invention will be described with reference to FIGS.

FIG. 1 is a view immediately after a projectile equipped with the apparatus of this embodiment is launched rearward from a mother machine (not shown). (A) is a side view, (b) is B of (a). 2B is a cross-sectional view taken along the arrow B, FIG. 2 is a view of the flying body after the additional wing which is the main member of the apparatus of this embodiment is removed, and FIG.
(B) is a BB arrow sectional view of (a).

In FIG. 1, 1 is a flying body, 2 is a rear wing of the flying body 1, 3 is a steering wing forming a front wing of the flying body 1, 4 is a rear side of the steering wing 3, and an explosion occurs. The additional blade is detachably fixed by the operation of the bolt 9 (explosion rupture). Each of the rear wing 2, the steering wing 3, and the additional wing 4 is mounted as a set of four pieces, one at each position that divides the outer circumference of the body of the flying body 1 into four equal parts as viewed in the axial direction. There is. The wing area of the additional wing 4 is such that the aerodynamic center of the flying body 1 is in front of the center of gravity (when the additional wing 4 is included) 10 of the flying body 1, that is, in FIG. ) Has been determined to be the required position on the right side. The aerodynamic center of the flying body 1 is arranged behind the center of gravity 10, that is, on the left side of FIG. 1A in a state where the additional wings 4 are removed, that is, in a state close to normal.

Reference numeral 5 denotes a differential pressure sensor which constitutes an airspeed detecting means, and is composed of a tube body having open front and rear ends, which is supported on the outside of the fuselage substantially parallel to the machine axis of the flying body 1. The difference (dynamic pressure difference) is always detected, and when it becomes close to 0, the explosion bolt 9 is actuated via the differential pressure detector 6 and the power supply 7 to separate the additional blade 4 from the flying body 1 as described later. Let 6 is a differential pressure detector that detects the differential pressure from the front and rear pressures of the differential pressure sensor 5, and issues an energization command to the power supply 7 at the required time when it is close to 0, 7 is a power supply for exploding the explosion bolt 9, Reference numeral 8 is a wire for energizing the explosion bolt 9 from the power source 7, 9 is an explosion bolt for fixing the additional wing 4 to the body of the flying body 1 as shown in FIG. 1B, 10 is a center of gravity, and 11 is It is a steering device for the steering wing 3 shown in the connection. It should be noted that the center of gravity 10 slightly moves back and forth due to the attachment and detachment of the additional wing 4, but the center of gravity position when examining whether the aerodynamic center is before or after that is the center of gravity position at that time. Nor.

Next, the operation of the above configuration will be described. In Fig. 1 (a), the projectile is fired backwards and generates thrust to the right in the figure, but since the aircraft that is the mother aircraft originally travels to the left in the figure, Flying to the left side of the figure by inertia (while gradually decreasing the speed). Under this condition, the airflow is flowing in the direction of the outline arrow in the figure, and the aerodynamic center is closer to the right side of the figure by the additional vanes 4 and is behind the airflow from the center of gravity 10 so that aerodynamic stability is maintained. There is.

The differential pressure sensor 5 detects the pressure difference between the front and rear (dynamic pressure difference).
As soon as the value becomes smaller than a certain value, the flying vehicle 1 will move to the right in the figure. Therefore, an additional blade separation signal is generated via the differential pressure detector 6 and sent to the power supply 7, and the electrical output from the power supply 7 causes an explosion bolt. 9 is operated to separate the additional blade 4. As a result, the center of aerodynamics moves to the rear of the center of gravity 10, that is, to the left in the figure.

FIG. 2 shows a state in which the additional wing 4 is separated. Under this condition, the wing on the left side of the figure, that is, the rear wing 2, is large, so the aerodynamic center is closer to the left side as described above, and the center of gravity 10 is on the right side, Moreover, the air flow starts to flow in the direction opposite to that shown in Fig. 1 as shown by the white arrow in the figure, and the flying body 1 moves to the right side of the figure.
Is aerodynamically stable.

In the state of FIG. 1, when the acceleration of the flying body 1 is small, it may be possible that the flying time to the left side of the drawing is long, and during that time, the steering device 11 controls the attitude by the steering wing 3. It is also possible.

In the first embodiment described above, the pressure type differential pressure sensor 5 is used to know the air speed, that is, the air advancing direction. However, the air speed detecting means may be any as long as it does not deviate from the purpose. Means may be used. FIG. 3 shows an example of a weather vane sensor shown as the second embodiment, which is a wind vane 21 and a rotation sensor 22.
This is an example of a combination of.

In addition, in the first embodiment, the additional wings 4 are fixed to the fuselage of the flying vehicle 1 by two explosion bolts 9 each, but it is not limited to fixing to the fuselage. FIG. 4 shows an example in which the additional wing 4 is fixed to the steering wing 3 as a third embodiment. A fixing metal fitting 23 for fixing the rear wing 3 of the steering wing 3 to the front edge of the additional wing 4 is provided therein. This is an example of charging the explosive bolts 9 and connecting both.

As described above, according to the first to third embodiments, the additional blade 4 is provided behind the steering blade 3 of the flying body 1 so that the position of the aerodynamic center with respect to the center of gravity 10 is reversed. A projectile 1 which is detachably attached by an explosion bolt 9 and which is provided with a differential pressure sensor 5 and fired to the rear of the aircraft until the inertial velocity given by the aircraft is released by the self-propelled device. When the aerodynamic center is located in front of the center of gravity 10 when viewed from 1, the inertial speed and the self-propelled speed cancel each other out, and the airspeed becomes near 0. Explosion bolt 9 is blown away, and additional wing 4 is removed, which causes the center of aerodynamics to center of gravity 10.
Since it is moved rearward, the aerodynamic center will always be located behind the center of gravity 10 with respect to the air flow, while the spacecraft 1 is retreating and after moving forward. There is an advantage that the body 1 can obtain aerodynamic stability. As a result, the flying body 1 can always perform the initial control, and there is an advantage that the accuracy of approach to the target can be improved.

[0022]

Since the present invention is constructed as described above, it has the following effects.

That is, even if the airspeed of the flying object launched rearward from the mother aircraft is changed from negative to positive, the aerodynamic center is always on the rear side of the airflow with respect to the center of gravity, so aerodynamic stability is maintained, As a result, stable control is always guaranteed, and a high encounter probability can be obtained for a target behind the mother machine.

[Brief description of drawings]

1A and 1B are views of a flying vehicle including an aerodynamic characteristic changing device for a flying vehicle according to a first embodiment of the present invention, in which FIG. 1A is a side view and FIG. 1B is a BB arrow in FIG. Sectional view,

FIG. 2 is a diagram showing a state where the additional blade is detached in the first embodiment, (a) is a side view, (b) is a sectional view taken along the line BB of (a),

FIG. 3 is a partially enlarged view of a weather vane sensor according to a second embodiment of the present invention, showing a cross section of a flying body in a fuselage side;

FIG. 4 is a partial perspective view schematically showing a fixed state of an additional blade according to a third embodiment of the present invention.

[Explanation of symbols]

 1 Flying body 2 Rear wing 3 Steering wing (front wing) 4 Additional wing 5 Differential pressure sensor 6 Differential pressure detector 7 Power supply 8 Wiring 9 Explosion bolt 10 Center of gravity 11 Steering device 21 Weather vane 22 Rotation sensor 23 Fixing bracket

Claims (1)

[Claims] 1. An additional wing which is detachably fixed near the rear of a front wing of a flying body and has a wing area necessary to move the aerodynamic center forward with respect to the center of gravity of the flying body, and the additional wing. Is provided in the air, and an airspeed detecting means for detecting the airspeed of the flying object fired rearward from the mother aircraft when the airspeed reaches near 0 and activating the airspeed detecting means. An aerodynamic characteristic changing device for a flying vehicle, which is characterized by