JPS61101800A - Steering gear for guided missile - 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 (Field of Industrial Application) This invention relates to an improvement in a steering device for a guided flying vehicle.

[Conventional technology]

FIG. 3 is a schematic diagram of the guidance control section and steering wing of a conventional guided spacecraft, where (1) is the guidance section and (2) is the control section.

(3) is a steering blade, and (4) is a steering shaft.

The conventional steering device is configured as described above, and when changing the flying direction of the guided flying object, the steering shaft (4) in the control unit (2) is rotated by a signal from the guiding unit (1). The steering angle was determined by the steering blade (3) fixed to the steering shaft (4), and the aerodynamic force applied to the blade was utilized. One steering wing (3) is attached to one steering shaft (4) from the fuselage control section (2), and this steering shaft (4) is a drive shaft that changes the steering angle of the wing. It is also the axis that transmits the aerodynamic force to the aircraft. In other words, the rotation axis of the steering blade (3) and the steering axis coincide.

[Problem that the invention seeks to solve]

In the conventional steering device as described above, the point of application of the aerodynamic force (aerodynamic center) to the steering blade (3) is located on the steering shaft (4),
Moment (hinge moment) to this steering shaft (4)
becomes O, and when steering, steering @ (4) is steering'!
Only the torque required to rotate &+31 is required. However, in reality, the aerodynamic center moves significantly due to changes in the angle of attack of one aircraft, the rudder pile of the control blade (3), etc., and a hinge moment due to aerodynamic force is generated relative to the steering NI+41. Therefore, in order to hold and fix the steering blade (3), a torque must be applied to the steering shaft (4) to overcome this hinge moment. -Also, when changing the steering angle, more torque is required. If this hinge moment is large, the required torque for the steering shaft (4) will also be large, and there is a problem in that the steering mechanism cannot be made larger.

This invention was made to improve this problem, and the object is to provide a device that reduces the hinge moment applied to the steering shaft even if the aerodynamic center of each steering blade moves depending on the angle of attack and rudder angle. shall be.

[Means for solving problems]

The steering device according to the present invention separates the rotation axis of the steering blade from the steering shaft, and connects the steering blade to the pin that is the rotation axis.

It is held at two points on the pinion gear attached to the steering shaft.9
Further, as this gear rotates, a sector gear attached to a steering blade that meshes with this gear is moved to perform steering.

[Effect]

In this invention, the steering blade is driven by rotating the steering shaft located at a portion different from the rotation center of the blade, so that even if the aerodynamic center of the steering blade moves, the hinge moment applied to the steering shaft itself can be reduced compared to the conventional one. can be significantly suppressed.

〔Example〕

FIG. 1 is a configuration diagram showing an embodiment of this invention! :1.
(ll-(4) is exactly the same as the conventional device described above. (5) is a pinion gear attached to the tip of the steering shaft (4), and (6) is a pinion gear attached to the tip of the steering shaft (3). 2) is a sector gear attached to the steering wing (3) whose rotation center is the pin (6) that engages with the pinion gear (5), and (8) is the centerline of the fuselage. .

The pinion gear (5) and pin (6) are located parallel to the fuselage centerline (8).

FIG. 2 shows an example of the operation of the steering device configured as described above. (9) is the center line of the steering wing (3), and (δ) is the angle between the center line (9) of this wing and the fuselage center line (8).

This angle is usually called the rudder angle, where the angle is the flow of air entering the cloud, α0) is the aerodynamic center of the steering blade (3), and (Fo) is the aerodynamic force applied to this aerodynamic center. (Fl), (Fz
) is a component force of the aerodynamic force (FO) and is a force that acts on the nine aircraft, and is applied to the pin (6) and pinion gear (5), respectively.

Also.

(Mp) is the moment applied to the pinion gear (5).

When making the steering blade (3) take the steering angle (δ), the steering axis (
4).

The pinion (5) rotates once, and the steering blade (3) rotates around the pin (6) together with the sector gear (7) that meshes with it. Air force (FO) when there is air flow (3)
) and the position of the aerodynamic center tlo), 1 minute force (Fl)
, (F2) is expressed by Equation (1) and Equation (2) when the steering angle is small. Here, Ih and 12 are the distance between the pin (6) and the aerodynamic center (101), and the distance between the pin (6) and the pinion gear (5), respectively, and R1 is the pitch radius of the pinion gear (5). In this case, the moment (Mp) applied to the pinion gear (5) is as shown in equation (3).On the other hand, in the conventional steering system, the moment l-MH applied to the steering shaft (4) is expressed by the aerodynamic center Qα If the distance between and the steering axis (4), that is, the center of rotation, is ll as above, then M+
(= ls · FO---------[41. Normally, 11 of equation (4) is considered to be .

M, (MH------(61), and the hinge moment applied to the steering shaft (4) can be significantly reduced compared to the conventional one.

In the above embodiment, the pin (6) is the steering tiII +4
1. It is located in front of the pinion gear (5) and sector gear (7).

The same effect can be expected even if the pin (6) is placed backwards and placed in the opposite direction.

〔Effect of the invention〕

As explained above, this invention has a simple structure in which the steering blade is driven by the rotation of the steering shaft located at a part different from the rotation center of the blade and the accompanying gear, so that even if the aerodynamic center of the steering blade moves, the steering remains This has the effect of greatly suppressing the hinge moment applied to the shaft itself.

[Brief explanation of drawings]

FIG. 1 is a configuration 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 schematic diagram of a conventional steering system. In the figure, (1) is the guide section, (2) is the control section, and (3) is the guide section.
is for steering, +41 is for steering shaft, (5) is for pinion gear,
(6) is a pin. (7) is sector gear, +81. (91 is the center line,
aO+ is the aerodynamic center point, (δ) is the steering angle, (A) is the air flow, (Fo), (F+), (F2) is the aerodynamic force,
(Mp) is the moment. Note that the same reference numerals in each figure indicate the same or corresponding parts.

Claims (1)

[Claims] a steering wing for changing the direction of motion of the guided vehicle;
In a guided flying vehicle that is equipped with a steering shaft for causing the steering wing to take a steering angle, the steering wing is attached to the fuselage via a pin that rotationally engages with the fuselage, and the steering wing is further attached to the fuselage mounting side. A sector gear having the pin as a rotational center axis is provided, a pinion gear that meshes with the sector gear is provided on the steering shaft, and the steering blade is configured to adjust the steering angle by the steering shaft output via a pair of gears with the pin as the rotational center. A steering device with a guide body, characterized by: