JPH0626799A - Missile - Google Patents

Abstract

PURPOSE:To prevent a decrease in an accuracy of a measuring instrument due to a rolling motion and to rapidly turn a missile by bringing a direction of a lift of a main wing into coincidence with a predetermined turning acceleration direction without rolling a body at the time of turning the missile. CONSTITUTION:The missile comprises a main wing supporting cylinder 3 attached to bodies 1a, 1b rotatable around a body axis 5, a plurality of main wings 2 attached to the cylinder 3, and means for rotating the cylinder 3 around the axis 5. Only the wings 2 and the cylinder 3 are rotated around the axis without rotating the bodies at the time of turning the missile.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a flying body which requires a bank when turning.

[0002]

2. Description of the Related Art In a conventional flying body which requires a bank at the time of turning, as shown in FIG. It is necessary to roll the whole body 16 so that the lift direction 6 generated by the main wing) coincides with the required turning acceleration direction 7 (see FIG. 7B) to bring the flying body into a banked state. In addition, 4 in FIG. 7 is a body 1.
It is a tail that is provided in the shape of a cross at the rear of.

[0003]

In the above-mentioned conventional flying body, the following problems occur because the entire body makes a roll motion at the time of initial turning motion. (1) By the roll motion of the measuring device fixed to the body,
Measurement accuracy deteriorates. Also, in order to prevent this, the roll rate can be set to an upper limit, and swift turning cannot be performed. (2) Since the entire flying body makes a roll motion, the moment of inertia is large and the roll response is low, so that swift turning cannot be performed.

The present invention is intended to provide a flying object which can solve the above problems.

[0005]

[Means for Solving the Problems] The flying object of the present invention is
A main wing support cylinder rotatably mounted on the fuselage about the machine axis, a plurality of main wings mounted on the main wing support cylinder, and means for rotating the main wing support cylinder about the machine axis.

[0006]

In the present invention, when the flying body makes a turn,
The main wing support cylinder makes a rotational motion (roll motion) around the machine axis together with the main wing so that the lift direction of the main wing and the required turning acceleration direction coincide with each other. Therefore, the roll motion of the measuring device fixed to the body disappears, the body does not rotate around the machine axis, and the inertia moment for the body decreases.

[0007]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A first embodiment of the present invention will be described with reference to FIGS. The flying body has a cylindrical body, and between the front body 1a and the rear body 1b, a cylindrical main wing support cylinder 3 is rotatably arranged around a machine axis 5 of the flying body to support the main wing. Two main wings 2 extending in mutually opposite directions are attached to the cylinder 3, and ailerons 1 are provided at the trailing edges of each main wing 2.
1 is provided.

A swash plate 10 is arranged in the main wing support cylinder 3, and the swash plate 10 has an annular front plate 10a and a bearing 10 on the front plate 10a.
It is provided with an annular rear plate 10b which is rotatably contacted via c. The plurality of projections 20 provided on the outer periphery of the rear plate 10b are inserted into the corresponding plurality of axial grooves 24 on the inner periphery of the main wing support cylinder 3 and are engaged with each other. Is slidable in the main wing support cylinder 3 in the direction of the machine axis 5 of the flying body 1, and the rear plate 10b of the swash plate 10 rotates around the machine axis 5 together with the main wing support cylinder 3. There is.

A servo device 9 is provided at the rear of the front body 1a.
Is disposed and extends rearward in the direction of the machine axis 5 and is connected to two rods 9b attached to the swash plate 10 at positions on both sides in the diametrical direction of the front plate 10a.

Rear plate 10 of swash plate 10
Two seat plates 21 projecting rearward are provided at positions on both diametrical sides of b, and each seat plate 21 has a lever 2 extending rearward.
The front end of 2 is pivotally attached, and the rear end of the lever 22 is aileron 1.
It is pivotally attached to the upper end of a lever 23 fixed to the aileron 11 via a shaft 11a on the hinge line 1. The lever 23 fixed to the aileron 11 is shown in FIG.
The lever 23 of the left aileron 11 on the front side is arranged so as to face upward, and the lever 23 of the right aileron 11 on the rear side is arranged so as to face downward. Therefore,
When the swash plate 1 moves in the direction of the axle 5,
The aileron 11 can rotate around the hinge line 11a as shown by an arrow 13 in FIG. 2 to take a steering angle by a link mechanism formed by levers 22 and 23, and the aileron 11 on the left side and the aileron 11 on the right side. The rear edges of the ailerons 11 are movable in the opposite vertical directions. In addition, 4 is a tail blade provided at the rear end portion of the rear body 1b.

In the present embodiment constructed as described above, when the rod 9a of the servo device 9 moves in the direction of the machine shaft 5 as indicated by the arrow 12 in FIG. 2, the swash plate 10 moves the machine shaft 5 accordingly. Move in the direction of. As a result, the aileron 11 of the main wing 2 takes the steering angle via the link mechanism including the levers 22 and 23. Also, the left wing 2
The trailing edge of the aileron 11 and the trailing edge of the aileron 11 of the right main wing 2 move in opposite vertical directions.

By operating the aileron 11, the main wing 2
At, an aerodynamic rolling moment occurs.
As a result, the rear plate 1 of the swash plate 10
Main wing support cylinder 3 engaging with protrusion 20 of 1b via groove 24
Rotates about the machine axis 5, and the main wing 2 accordingly rotates about the machine axis 5 as indicated by an arrow 8 in FIG. 5B.

As described above, in this embodiment, the main wing 2 is rotated around the machine axis 5 by rotating the main wing support cylinder 3 around the machine axis 5, and the lift direction 6 of the main wing 2 is changed as shown in FIG. Match with the required turning acceleration direction 7 and fly 1
Makes a turn. Moreover, in this case, the main wing support cylinder 3 is the main wing 2
With the rotation of the machine shaft 5, the other parts of the machine body do not rotate. Therefore, since the measuring device fixed to the body does not roll, the measurement accuracy does not deteriorate. Further, since only the main wing support cylinder 3 and the main wing 2 rotate, the moment of inertia can be reduced to improve the roll responsiveness of the flying body, and swift turning can be performed.

The second embodiment of the present invention will be described with reference to FIG. In the present embodiment, a main wing support cylinder 3 that is rotatably arranged around the axis of the flying body and supports the main wing 2 is provided between the front body 1a and the rear body 1b of the flying body. The gear 15a provided on the inner circumference is attached to the body 1a.
A gear 15 rotated by a servo device 14 provided at the rear part of the rear
The main wing support cylinder 3 is rotated by the servo device 14 around the machine axis of the flying body by engaging with b.

Also in this embodiment, the same operation and effect as those of the first embodiment can be obtained.

Although the above embodiment has two main wings, the present invention can be applied to a flying body having three or more main wings, and a full-wing type flight without a tail. It can also be applied to the body.

[0017]

The present invention has the structure described in the claims. When the flying body turns, only the main wing and the main wing support cylinder are rotated around the machine axis to lift the main wing and the required turning acceleration. Since the directions are matched, the following effects are produced. (1) Since the rolling motion of the measuring device fixed to the body is eliminated, the measurement accuracy is improved. In addition, since it is possible to increase the roll rate, which was conventionally kept low in relation to this accuracy, a more swift turning of the flying body is realized. (2) Since the moment of inertia for the fuselage can be reduced when the flying body turns, the roll responsiveness is improved, and more rapid turning of the flying body is realized.

[Brief description of drawings]

FIG. 1 is a device layout view of a first embodiment of the present invention.

FIG. 2 is an explanatory diagram of a control system of the first embodiment.

FIG. 3 shows a main wing support cylinder and a main wing portion of the first embodiment,
It is a perspective view which fractures | ruptures and shows.

FIG. 4 is an explanatory diagram of a main wing support cylinder and a rear plate of a swash plate according to the first embodiment.

FIG. 5 is a schematic view of the first embodiment at the time of initial turning motion, and FIG.
FIG. 5A shows a state before turning, and FIG. 5B shows a state where the lift direction of the main wing and the required turning acceleration direction coincide with each other during turning.

FIG. 6 is a perspective view showing a part of a second embodiment of the present invention in a cutaway manner.

FIG. 7 is a schematic diagram of a conventional flying body at the time of initial turning, in which FIG. 7 (a) shows a state before turning, and FIG. 7 (b) shows turning and the lift direction of the main wing and the required turning acceleration direction match. Shows the state.

[Explanation of symbols]

 1 Fuselage 1a Front fuselage 1b Rear fuselage 2 Main wing 3 Main wing support cylinder 4 Tail wing 5 Axle 6 Lifting direction 7 Required turning acceleration direction 9 Servo device 9a, 9b Rod 10 Swash plate 10a Front plate of swash plate 10b Rear plate 11 of swash plate 11 Aileron 14 Servo device 15a, 15b Gear 20 Protrusion 22 and 23 Lever

Claims (1)

[Claims] 1. A main wing support cylinder rotatably mounted on the fuselage around the machine axis, a plurality of main wings mounted on the main wing support cylinder, and means for rotating the main wing support cylinder around the machine axis. And a flying body.