JPH03217798A - Guided missile - Google Patents

Abstract

PURPOSE:To obtain a roll control mechanism which takes out or takes in spoilers on a plurality of rear stabilizing surfaces by a method wherein a ring is driven by one set of driving device and a shaft transmitting the power of the driving device while the driving device is controlled by a controller including a roll angular acceleration detector. CONSTITUTION:A ring 6 can be revolved about the axis of a rocket motor 4 and spoilers 7 are attached to the ring 6 while the spoilers 7 can be taken out and/or taken into the surface of stabilizing surfaces 5 and the shaft 8 rotates the ring 6. When roll control is necessitated, a control signal is outputted from a controller 10 including a roll detector and the driving device 9 rotates the driving shaft 8 by a necessary amount to turn the ring 6 operated in conjunction with the shaft 8. The spoilers 7 are attached to the ring 6 and the spoilers 7 are taken out of respective stabilizing surfaces 5 in accordance with the rotation of the shaft 8. A pressure around the spoiler 7A is increased by taking the spoiler 7a into airstream A whereby an aeronautical force FA is generated in the stabilizing surface 7A.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] This invention relates to adding roll controllability to a guided flying vehicle by improving its stabilizing wing.

[Prior Art] During the flight of a guided flying object, roll stabilization or roll rate suppression is attempted to prevent rolling of the aircraft from the necessity of final guidance accuracy.

However, in a forewing-steering guided flying vehicle in which the steering wing is mounted at the front of the aircraft, roll control using the forward steering wing is often extremely difficult due to aerodynamic interference between the front and rear wings. In this case, it is necessary to add some kind of roll control mechanism to the stabilizing wing section at the rear of the fuselage. However, normal guided flying vehicles have a rocket motor at the rear of the aircraft. It is difficult to incorporate the above roll control mechanism inside the fuselage. because. The rocket motor is located on the center line of the fuselage axis, and this control mechanism must be placed on the outer circumference of the fuselage, avoiding this area. In addition, because of the requirement for roll steering that it must not affect the pitch and yaw planes of the aircraft, control is usually imposed to always operate the wing in a manner that is free from the wing on the opposite side of the aircraft.

Figure 4 is a schematic diagram of a conventional guided flying object, where ke) is the guidance control section and (3) is the projectile. (4) is a rocket motor. (2A). f2B). (2D) is each steering blade, (5A), (5B). (5D) is each stabilizing wing. Figure 5 shows an overview of roll steering.
When roll moment to the aircraft is required. (2A)
．． T283. (2C), (2D) Each of the control vanes steers in the same direction, and the aerodynamic force is applied to each of the control vanes of FA, FB, FC, and FD. L.A. LB. Obtain the roll moment applied to the LC and LD aircraft. However, this roll moment is normal. The effect is reduced by a reverse roll moment on the stabilizing wing (5) due to interference between the front and rear wings, called an induced roll moment.

Also, FA, FB, FC. FD is an equivalent force, and considering the direction of each force, the total force is the pitch plane, yaw force.
Both surfaces are zero, and only roll moment is generated in the aircraft.

[Problem to be solved by the invention] That's all. As explained above, in a forewing steering guided flying vehicle,
First of all, efforts are made to ensure roll control using only the front control blade, but in many cases this is not possible. usually. It is necessary to add a roll control mechanism to the rear stabilizing wing. However, there is a rocket motor in the rear fuselage. The problem was that it was difficult to incorporate this mechanism inside the fuselage.

This invention uses a single drive device placed in the guidance control section at the front of the fuselage, a shaft that transmits power to the rear of the fuselage, and a link mechanism using a ring, thereby eliminating the use of space near the center axis of the fuselage where the rocket motor is located. in. This paper proposes a roll control mechanism that moves multiple rear spoilers in and out.

[Means for Solving the Problems] A guided flying object according to the present invention has a spoiler that goes in and out from the wing surface of each stabilizer wing attached to a ring that is rotatable around the fuselage axis, and this ring is placed at the front of the fuselage. The aircraft is driven by a single drive device and a shaft that transmits the power, and this drive device is controlled by a control device that includes a roll angular acceleration detector placed near the ring at the rear of the fuselage.

[Operation] In this invention, the spoilers placed on the plurality of stabilizer wings at the rear of the fuselage are fixed to a ring that rotates around the aircraft axis, and this ring is moved by a drive device located in the guidance control section at the front of the fuselage. Each spoiler is extended from above in the same direction of rotation, and the aerodynamic force generated by the spoilers creates a roll moment on the aircraft, ensuring roll control.

In addition, by placing a control device including a roll angular acceleration detector at the rear of the aircraft. Aircraft response due to spoiler. Detection is faster than when the detector is placed in the guidance control section. Roll control characteristics are also improved.

[Embodiment 1] Figure 1 shows an embodiment of the present invention, which includes a guidance control section (l) at the front of the fuselage, a steering wing (2), a projectile (3), and a rocket motor (4) at the rear of the fuselage. The stabilizer blade (5) is completely the same as the conventional device described above, and (6) is a ring that can rotate around the axis of the rocket motor (4). f7》 is attached to this ring, and a spoiler (8) that can go in and out from above the wing surface of the stabilizing wing (5) is a shaft that rotates the ring (6). (9) is the drive device placed in the guidance control section,
(10) is a drive device (
9) a control device; (11) is a signal line from the control device to the drive device (9);

Examples of the operation of the apparatus configured as described above are shown in FIGS. 2 and 3. When some kind of roll control is required. A control signal is issued from a control device (lO) containing a roll detector, which causes a drive device (9) to turn the drive shaft (8) by the required amount, thereby rotating the ring (6) interlocked therewith. A spoiler (7) is attached to the ring (6) and rotates as it rotates. A spoiler [7] is ejected from each stabilizing wing (5). Figure 2 shows the air flow around one stabilizing blade (5A). (A) is the airflow. By exposing the spoiler (7A) to the airflow, the pressure around the spoiler (7A) increases. Aerodynamic force FA is generated on the stabilizing wing (7A). Figure 3 is a view of the entire aircraft from the rear. Drive shaft (8
) by rotating the ring (6) and advancing the spoiler (7), each spoiler [7A) . (7B).
(7C), (7D) each stabilizing wing (5A). (5
B). (5C). (5D) Aerodynamic force FA, FB
, FC, and FD, and generate roll moments LA, LB, LC, and LD around the aircraft.

At this time, the forces applied to the aircraft cancel each other out and become zero, as can be seen by considering the direction of the force on each wing.

[Effects of the Invention] This invention is as explained above. A simple structure in which a spoiler in each stabilizer wing is engaged with one ring, and a drive device placed in the guidance control unit moves these spoilers in and out from above the wing surface of the stabilizer wing allows the rocket motor to be located at the center of the aircraft axis. This has the effect of ensuring roll control of the flying object without using nearby space.

In addition, by placing a control device that includes a roll angular acceleration detector at the rear of the aircraft, it is possible to detect the aircraft's response to the spoiler more quickly than when the detector is placed in the guidance control section, which also improves roll control characteristics. It also has the effect of being covered.

[Brief explanation of drawings]

FIG. 1 is a diagram showing an embodiment of the present invention, FIGS. 2 and 3 are explanatory diagrams of the operation of an embodiment of the present invention, and FIG. 4 is a schematic diagram of a conventional front wing steering guided flying body. FIG. 5 is an explanatory diagram of the conventional operation. In the figure, (1) is the guidance control section. (2) is the steering blade, (3
) is the projectile, and (4) is the rocket motor. (5) is a stable wing. (6) is a ring, (7) is a spoiler. (8) is the shaft, (9) is the drive device, and (10) is the control device. (1
1) is the signal line, (2A). (2B). (2G
)． (2D) each has one steering blade. (5Al, (5
B). (5G), (5D) One stabilizing blade each, FA, FB
, FC, FD are aerodynamic forces, LA, LB, LC. LD is roll moment. A is the airflow, and B and C are the directions of rotation. In addition. The same reference numerals in each figure indicate the same or corresponding parts. Figure 2 Figure 3 Figure I Figure 4 Figure 5 LB

Claims (1)

[Claims] A fuselage consisting of a guidance control section, a projectile, a rocket motor,
a plurality of control wings attached to the guidance control unit located on the front side of the fuselage for changing the flight direction;
In a guided flying object that is attached to the rocket motor forming the rear side of the fuselage and includes a plurality of stabilizing wings for stabilizing the flight attitude, a spoiler that moves in and out of the wing surface of the plurality of stabilizing wings. a ring to which the spoiler is fixed and is rotatable around the axis of the fuselage; a shaft connecting this ring; and a shaft located in the guidance control section at the front of the fuselage, which drives the shaft and rotates the ring; A guided flight vehicle characterized by comprising a drive device that moves the spoiler in and out from each stabilizing wing, and a control device for the drive device located at the rear of the aircraft body that detects roll angular acceleration and performs roll stabilization. body.