JPH024199A - Steering device for missile - Google Patents

Abstract

PURPOSE:To achieve the remarkable reduction of an air resistance without deteriorating the maneuverability of a missile by providing steering wings, capable of being advanced and/or retreated into and/or out of a fuselage, and an actuator advancing and retreating said steering wings. CONSTITUTION:The fuselage 1 of a missile having main wings 5 and tail wings 6 at the rear part thereof is provided with two pieces of left and right steering wings 4 at the fore part thereof in parallel substantially to the main wings 5. Said steering wing 4 is provided with a semicircular shape spread rearwardly and is constituted so as to be capable of being pivoted about a worm wheel 3 provided before the steering wing 4 while the worm wheel 3 is meshed with a worm 2' attached to the shaft of an actuator 2 whereby the steering wing 4 is received into or extracted out of the fuselage 1 through the opening of the fuselage 1 by the movement of the shaft of the actuator. Both of the steering wings 4 are attached with an angle of attachment theta with respect to the axis of the missile and, therefore, rudder surface aerodynamic forces in the same direction may be generated when they are extracted out of the fuselage 1.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a steering system for a flying object such as a missile.

[Conventional technology]

The conventional steering system for flying bodies is 1 as shown in Fig. 6.
Lift was adjusted by rotating nine wings 4, which were exposed on the side of the fuselage 1, around an axis 4'.

[Problem to be solved by the invention]

In the above-mentioned conventional steering system, even when little or no lift is required, such as when the flying object is cruising or carrying a mother aircraft, the entire steering blade is exposed to the airflow, so that it is exposed to air resistance. It was becoming k. This air resistance is undesirable in terms of system performance, as it reduces the flight range of the flying object and deteriorates the acceleration performance of the mother aircraft.

The present invention solves the above-mentioned problems of the conventional ones, and does not cause a decrease in the motion performance of the flying object.
The aim is to achieve a significant reduction in air resistance.

[Means to solve the problem]

The steering device for a flying object according to the present invention includes a steering wing that can move forward and backward into and out of the fuselage, and an actuator that moves the steering wing back and forth.

[Effect]

In the present invention, when little or no lift is required, such as when carrying a mother plane or when flying in a cruise, the steering device is retracted into the fuselage, thereby reducing air resistance. Furthermore, during flight, air resistance can be minimized by pulling the steering device out of the fuselage to the minimum extent necessary to obtain the control surface aerodynamic force necessary to maintain the attitude angle of the flying object.

Furthermore, when a plurality of steering wings are used, the roll attitude angle of the flying object can be controlled by controlling the extension of each of them to the outside of the fuselage.

〔Example〕

An embodiment of the present invention will be described with reference to FIGS. 1 to 4. The main jl! Two steering blades 4 are provided on the left and right sides in parallel with 5. As shown in FIG. 1 (2), the steering jI4 has a fan-shaped shape that expands toward the rear, and is rotatable around the worm wheel 3 provided at the front of the steering jI4. The worm wheel 3 meshes with the worm 2' on the shaft of the actuator 2, and as the shaft of the actuator moves, the worm wheel 3 passes through the opening in the body and is housed in the body 1, as shown by the arrow in the figure, and the body 1 It is meant to be pulled outside. In addition, the both-edge rudder blades 4 are
As shown in Fig. 1 (03), it is attached at an angle θ to the axis of the flying body, and when pulled out from the fuselage 1, it generates a control surface aerodynamic force in the same direction.

This embodiment is constructed as described above, and when carrying the mother aircraft, the steering blade 4t-actuator 2 is connected as shown in FIG.
When the worm wheel 3 is operated, it can be rotated around the worm wheel 3 and housed in the body 1, thereby reducing its air resistance.

After launch, the left and right steering wings 4 are pulled out from the fuselage 1 by the operation of the actuator 2, but as shown in FIG.
Unbalance is created in the control surface air cuffs of both edge rudder blades to generate a rolling moment of 8t, thereby puncturing the flying object's turning surface in the direction of the target.

After the puncture ends, as shown in FIG. 4, the flying object generates a control surface air cuff that adjusts the areas outside the fuselage of both edge rudder blades 4 to be equal to obtain the required pitching moment 9. The roll attitude angle is maintained by appropriately pulling out the left and right steering wings 4 and adjusting their area outside the fuselage.

Further, during cruising flight of the flying vehicle, air resistance can be reduced by pulling out the steering wing 4'f to a minimum extent outside the fuselage 1 so as to obtain the necessary control surface aerodynamic force.

In this embodiment, as shown by curve Arc in FIG. 5, the air resistance against lift force is reduced compared to the conventional rotary steering system (curve B).

In addition, in the above embodiment, the fan-shaped steering blade is rotated around its front end,
However, the present invention is not limited to this, and any suitable mechanism that can adjust the area of the steering wing outside the fuselage may be adopted.

〔Effect of the invention〕

As explained above, the present invention makes it possible to minimize air resistance when control surface aerodynamic force is not required or during cruise flight by moving the control blades into and out of the fuselage. Flight performance and compatibility with the mother aircraft can be improved.

[Brief explanation of the drawing]

Fig. 1 shows an embodiment of the present invention, Fig. 1 (4) is a plan view thereof, Fig. 1 [F]) is a side view thereof, and Figs. 2 to 4 respectively show the above embodiment. (4) in Figures 2 to 4 is a perspective view, and 03) in Figures 2 to 4 are respectively in Figure 2). or A-A, B- in Figure 4 (4)
B, C-C arrow views, FIG. 5 is a diagram showing the lift force-air resistance of the above embodiment and the conventional rotary type steering blade, and FIG. 6 is an explanatory diagram of the conventional rotary type steering device for a flying body. It is. DESCRIPTION OF SYMBOLS 1... Flying body fuselage, 2... Actuator, 3... Worm wheel, 4... Steering wing, 5... Main wing, 6... Tail wing, 7... Control surface aerodynamic force

Claims (1)

[Claims] A steering device for a flying body, comprising a steering wing that can move in and out of the fuselage and an actuator that moves the steering wing back and forth.