JPS63318499A - Aircraft dropping body - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

[Detailed Description of the Invention] [Industrial Application Field] This invention relates to improving the construction safety of aircraft droplets such as external fuel tanks and electronic pumping pods that are mounted on aircraft and dropped during flight. It is.

[Conventional technology]

FIG. 3 is a diagram showing, for example, a conventional aircraft drop object, and in FIG. 9, (1) is a fuselage having a certain function.

(2) is a stabilizing wing attached along the axis direction of the fuselage fil in order to stabilize the flight after dropping.

A conventional aircraft drop vehicle is constructed as described above.

When this projectile is dropped from an aircraft, even if an angle of attack occurs on the projectile, which is the angle between the two aircraft axis directions and the flight speed vector, the stabilizing wing (2) attached to the rear of the center of gravity of the entire projectile A lift force is generated in the dog than in the fuselage, and the axis of the droplet is directed in a direction that reduces this angle of attack, so that the flight speed vector and the axis direction coincide.

This effect is usually called aerodynamic stability.

The condition for this to hold is that the point of action of the aerodynamic force of the entire aircraft is behind the double center of gravity, and once it enters stable flight, unless some disturbance is added, the flight path will be free-falling. Follow the trajectory. In addition, if there is no stability g (21), it is normal that there is no aerodynamic stability with only the fuselage (1).

When dropping from an aircraft, it is desirable for the projectile to detach from the aircraft quickly.If the projectile has sufficient aerodynamic stability, the projectile will be able to move upward, excluding vibration components such as pitching. Since no lift is generated and the aircraft essentially falls freely, the risk of contact or collision with an aircraft is reduced.

[Problem that the invention seeks to solve]

In conventional aircraft droplets such as those mentioned above.

If the size of the stabilizer wing (2) is limited due to various limitations of the aircraft and the stability of the projectile is weak, the vibration component of the pitching immediately after it is dropped may cause its motion to be dangerous to the aircraft. be. This is because of the injection force and turbulence of air flow under the aircraft wing when separating from the aircraft.
Considering the projectile in the vertical plane, when a force is applied to raise the projectile's head, the projectile's restoring moment is weak, and until it returns to a stable flight state, it continues to generate lift force, which causes the projectile to move further than the free fall trajectory by that amount of lift. Approach the aircraft side. The problem is that this approach increases as the disturbance is stronger and the stability is weaker, and in the worst case, it can lead to a collision with an aircraft.

This invention was made to solve the above-mentioned problems, and its object is to obtain an aircraft projectile with good separation characteristics from an aircraft.

[Failure to solve the problem]

When the aircraft drop object according to this invention is mounted on a mother aircraft.

It has the same external shape as a conventional projectile, and after being dropped from the mother aircraft, the drop is detected, the stopper is removed, and the stabilizing wing is slid backwards against the fuselage using a spring.

This enhances aerodynamic stability.

[Effect]

In this invention. After the stabilizer wing section, which consists of multiple stabilizer wings and the tail section of the fuselage, is dropped from the mother aircraft, the stopper is removed and the paneka slides nine axes to the rear. This increases the aerodynamic stability of the projectile. This is because when the stabilizing wing moves rearward, the point of action of the aerodynamic force of the two aircraft as a whole moves rearward by a large amount, and this amount of movement is larger than the amount of movement of the center of gravity. Therefore, aerodynamic stability is enhanced.

〔Example〕

FIG. 1 is a diagram showing an embodiment of the present invention.

(1) is a fuselage with a certain function, (2) is a stabilizing wing, (3 is
) was attached to the front of the stable Af21. torso fil
Sting along the machine axis, (4) is a slide groove provided along the machine axis at the rear of the fuselage (1), (5) is when mounted on the mother aircraft, Sting (3), stable, , it +21 is positioned forward The stopper (6) detects the drop,
A wire (7) is used to release the stopper (5), and a spring (7) is used to extend the sting (3) and the stabilizing wing (2) rearward.

An aircraft drop configured as described above, when loaded onto the mother aircraft,
The stabilizer wing (2) is located forward of the fuselage (11) by the stopper (5). Figure 2 shows an example of the operation after being dropped from the mother aircraft. In Figure 2, the stabilizer wing (2), the Sting (3)
) slides toward the rear of the machine axis by the force of the spring (7), changing the shape of the entire projectile and increasing its aerodynamic stability.

〔Effect of the invention〕

As explained above, this invention is applicable to cases where the aerodynamic stability of a projectile dropped from an aircraft is weak, after the projectile is dropped.

By extending the stabilizing wings to the rear of the aircraft axis, it increases aerodynamic stability and has the effect of increasing the safety of dropping from an aircraft.

[Brief explanation of drawings]

Fig. 1 is a diagram showing an embodiment of the present invention, Fig. 2 is an operational diagram of an embodiment of the invention, and Fig. 3 is a diagram showing a conventional aircraft drop object. The fuselage, (2) is a stabilizing wing, (3) is a sting, (4) is a slide groove, (5) is a stopper, 76) is a wire, and (7) is a spring. Note that the same reference numerals in each figure indicate the same or corresponding parts.

Claims (1)

[Claims] In an aircraft drop vehicle that is equipped with a plurality of stabilizing wings at the rear of the fuselage for obtaining flight stability after being dropped from an aircraft, the fuselage tail section to which the plurality of stabilizing wings are attached is separated from the main body, and the fuselage tail section is separated from the main body. A stay attached to the front side facing toward the center axis of the fuselage, a slide groove provided at the rear of the main body along the center axis of the fuselage in which the stay can move back, and the stay fixed to the front side of the slide groove. an aircraft drop object, comprising: a stopper that detects dropping from a mother aircraft and releases the stopper; and a spring that is compressed and attached between the front end of the slide groove and the front end of the stay. .