JPH02161299A - Steering device for guided missile - Google Patents

Abstract

PURPOSE:To provide the attach angle of a body in a wide range without limiting by the stalling angle of a main wing and to steer without strong aerodynamic interference at main and rear wings by employing a steering device using a main wing to be missiled while sliding longitudinally. CONSTITUTION:A main wing 3 is longitudinally moved at a necessary distance through a main wing longitudinal driving shaft 7 by a motor-driven longitudinal driver 5 by a necessary control command signal generated by a control instructing unit 6. The center of gravity X of a body coincides with the position of the front wing 3 in a state before the guidance of missile, and it starts with the small wing 4 having no steering angle. The small wing 4 is steered at the time of start of the guidance to generate a vertical force F3 at the small wing 4 to generate a head raising moment around the center of gravity to alter the attack angle of the body. The main wing 3 is longitudinally slid at a necessary distance at the time of start to alter the quantity of the moment generated around the center of gravity X by a vertical force F2 to be applied to the main wing, and the missile is flown while varying the balance attack angle of the body.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to an improvement in a steering device for a guided flying vehicle guided by a main wing steering method.

[Conventional technology]

Figure 7 is a schematic diagram of a guided flying object guided by the conventional main wing steering system, in which (1) is the fuselage, (2) is the rear wing, (
3) is the main wing, (A) is the air flow, 00 is the center of gravity p ('')
is the vertical force applied to the rear wing, (F'2) is the main l! LVc
This is the applied vertical force.

A guided flying object guided by conventional main wing steering is configured as described above, and when attempting to fly guided, the vertical force (Fl) applied to the rear wing of the M center (X) rotation and the vertical force applied to the main wing are generated. As the moments due to (F2) are balanced, the flying body will fly while maintaining a constant angle of attack of about 9 degrees.

At that time, in order to change the angle of attack required for guidance, by changing the rudder angle of the main wing (3), the vertical force (F2) applied to the main wing is changed and
, 2) II normal force (, F2) VC! A method of changing the b moment was used.

[Problem to be solved by the invention]

In the conventional steering system for a guided flying object guided by main wing steering as described above, the rudder angle of the main wing (31) and the angle of attack of the aircraft are limited to within the stall angle of the main wing (3). ) takes the rudder angle, a strong wake vortex is generated, which causes the main J
M! There were problems such as strong aerodynamic interference between the AT and the rear 18 (2+).

This invention was made in order to improve this problem, and in a guided flying object guided by main wing steering, two
The purpose is to obtain a steering system in which the angle of attack of the aircraft is not limited by the stall angle of the main wing (3) and strong aerodynamic interference does not occur between the main wing (3) and the rear wing (2). Means for Solving the Problems] A steering system according to the present invention includes a main wing that slides in the axis direction by an electric longitudinal drive device provided in the fuselage, and a rudder instead of the conventional main wing that changes the steering angle. It is equipped with a small wing that is adjustable in angle and located at the nose.

[Effect]

In this invention, before starting a guided flight, the center of gravity of the aircraft is aligned with the main X, and the rudder angle of the small wing is set to zero.When starting the guided flight, the rudder angle of the small wing is first adjusted to control the aircraft. After changing the attitude, the aircraft performs guided flight while changing the angle of attack of the aircraft by sliding the main wing by the required amount in the direction of the aircraft axis.

〔Example〕

FIG. 1 is a diagram showing an embodiment of the present invention.
(31 is exactly the same as the conventional device described above.

(4) is a small wing that can change the rudder angle and is located in the nose; (5)
is the electric longitudinal drive device for sliding the main jlE (31) in the axis direction, (6) is the control command device for generating the control command signal necessary for guidance, and (7) is the main g (31
The main true front and back drive shaft is connected to and moves back and forth by the electric front and rear drive device 1t51, (8) is the small wing drive shaft connected to the small 1It (41), (9) rotates the small wing drive shaft (8) A small blade drive device for causing the small blade (4) to take a rudder angle, α
G is a main wing front and rear guide rail provided on the fuselage (1), on which the main wing (3) and the main front and rear drive shaft (7) slide back and forth.

Examples of the steering device configured as described above are shown in FIGS. 2 and 3.

FIG. 2 shows an example of the operation of the present invention before the start of guidance.

The main wing (3) is located near the rear end of the main wing front and rear guide rail t1α and coincides with the center of gravity of the aircraft, and the small wing (4) has no steering angle.

The third factor is an example of the operation of the present invention after the start of guidance, in which the winglet (4) is in a state where the rudder angle is determined by the winglet drive device (9), and the control command device (6) generates In response to a necessary control command signal, the main wing (3) is moved back and forth by the required amount via the main true longitudinal drive shaft (7) by the dynamic longitudinal drive device (51). ) indicates the case where the rice is at the frontmost position.

The principle of operation in this embodiment is shown in FIGS. 4 to 6. In the figure, (F3) is the vertical force applied to the winglet.

Figure 4 shows the state before the guided flight, where the two aircraft's centers of gravity (force and forward direction) are the same, and the small wing (4) is flying without any rudder angle. ing.

Figure 5 shows the state at the start of guided flight. By adjusting the rudder angle of the winglet (4), a vertical force (TP5) is generated on the winglet (4), causing the head to rotate around the center of gravity. A lifting moment is generated and the aircraft's angle of attack changes. As a result, a vertical force (Fl) is generated on the rear wing and a vertical force (F2) is generated on the main wing.

Figure 6 shows the hood and the state at the time of guided flight, and shows the main wing (3
) by the required amount to change the amount of moment generated around the center of gravity (X) by the vertical force (F2) applied to the main wing.
Try to fly while adjusting the angle of attack to 'kf'.

〔Effect of the invention〕

As explained above, this invention uses a steering system 1lli that uses a main wing that attempts to fly while sliding back and forth in contrast to the conventional main wing that attempts to fly while varying the rudder angle. This has the effect that the angle can be controlled over a wide range without being limited by the stall angle of the main wing, and that steering can be performed without strong aerodynamic interference between the main wing and the rear wing.

[Brief explanation of the drawing]

FIG. 1 is a diagram showing one embodiment of the present invention, and FIG. FIG. 3 is an operational diagram of an embodiment of the present invention, and FIG. 4 is a diagram. 5 and 6 are explanatory diagrams of the operating principle in an embodiment of the present invention, and FIG. 7 is a schematic diagram of a conventional steering device. In the equation, (1) is the fuselage, (2) is the rear wing, and (3) is the main wing. (4) is a small wing, (5) is an electric longitudinal drive device, (6) is a control command device, (7) is a main true longitudinal drive shaft, and (8) is a small wing drive shaft. (9) is the small wing drive device, and q[1 is the main wing front and rear guide rail. (A) is the air flow, (X) is the center of gravity, (Fl) is the vertical force applied to the rear wing, (F2) is the vertical force r applied to the main wing, and (Fs) is the vertical force applied to the small wing. Note that the same reference numerals in each figure indicate the same or corresponding parts.

Claims (1)

[Claims] In a steering system for a guided flying object guided by a main wing steering system, the steering system is composed of a fuselage, a rear wing fixed to the fuselage, and a main wing for changing the direction of movement of the guided flying object, and is guided by a main wing steering method. a small wing that can change the rudder angle and is located at the nose of the aircraft; an electric longitudinal drive device that slides the main wing in the axial direction; and a control command that generates control command signals necessary for guidance. a main true longitudinal drive shaft connected to the main wing and moved back and forth by the electric longitudinal drive device; a small wing drive shaft connected to the small wing;
a small wing drive device for rotating the small wing drive shaft and causing the small wing to take a rudder angle; and a main wing longitudinal guide provided on the fuselage for sliding the main wing and the main wing longitudinal drive shaft back and forth. A steering device for a guided flying body characterized by being equipped with a rail.