JPH0399198A - Complex steering device - Google Patents

Abstract

PURPOSE:To reduce the number of parts and reduce a cost of a complex steering device by a method wherein an actuator for oscillating and driving a locker arm is connected to one end of the locker arm and a push-pull rod to enable a jet vane to be oscilllated is connected to the other end of the locker arm. CONSTITUTION:An intermediate part of a locker arm 2 is connected to a steering shaft 3a of a steering wing 3, a linear actuator 1 is connected to one end of the arm 2 so as to oscillate and drive the arm. A push-pull rod 4 is connected to the other end of the arm 2, and a vane arm 5a having a jet vane 5 oscillatebly connected thereto is connected to the other end of the rod 4. With such an arrangement, a simultaneous driving of the wind 3 and the vane 5 can be performed by the actuator 1, and one arm 2 can be commonly used for an operation of the wind 3 and the vane 5, so that it is possible to reduced an occupying space for the device and its weight. In addition, the number of component parts is reduced and its cost can be reduced.

Description

[Detailed description of the invention] [Industrial application field] The present invention relates to a steering system for a flying aircraft.

[Prior Art] In the conventional steering system for a flying aircraft, as shown in FIG. The drive source of the jet pan includes an actuator lb,
Separate drive sources were used for each. Note that the steering blade 3 here refers to an aerodynamic steering blade, and the jet vane 5 is located inside the rocket nozzle 02 and swings in a desired direction, changing the direction of the jet flow (nozzle jet flow) and controlling the direction of thrust. Refers to the vane that attempts to convert. That is, all of them are components used for directional control of the aircraft.

[Problem to be solved by the invention]

The conventional steering device described above has the following problems to be solved.

In other words, because the steering device and jet vane deflection device are installed in the limited space of the steering section of the aircraft being flown, the space and weight allowed for each device are relatively severely restricted, making design, assembly, and maintenance difficult. etc. involved many difficulties and time consumption.

[Means to solve the problem]

The present invention provides a means for solving the above-mentioned problems, and includes a steering wing pivotally supported at the rear of a flying aircraft, a rocker arm whose intermediate portion is connected to a steering shaft of the steering wing, and a rocker arm connected to one end of the rocker arm. To provide a composite steering system, comprising: an actuator that drives a jet vane; and a push bull rod, which has one end connected to the other end of the rocker arm and the other end connected to be able to swing a jet vane. That is. In addition, in the above structure, the expression ``a flying aircraft'' refers not only to so-called flying aircraft, but also to any aircraft that attempts to fly.

[Effect]

Since the present invention is structured as described above, it has the following effects.

That is, a rocker arm is connected to the steering shaft of the steering blade, and an actuator is connected to one end of the rocker arm, and a push-pull rod is connected to the other end of the rocker arm, which is swingably connected to the jet hone. The horns sway at the same time. As a result, a common driving source can be achieved between the steering blade and the jet vane.

〔Example) An embodiment of the present invention will be explained with reference to FIG. 1 and FIG. 2.

1r:jJ is an exploded perspective view of the main parts of the composite steering system of this embodiment, and FIG. 2 is a three-sided view thereof. That is, the second
In the figure, (a) is a longitudinal cross-sectional view of aircraft 01, (
b) is a bb arrow view of (a), and (C) is a right side view of (a), that is, a view seen from the rear of the aircraft 01. Note that the same reference numerals are given to the same constituent members as in the conventional example, and explanations thereof will be omitted unless necessary.

In FIGS. 1 and 2, an intermediate portion of a rocker arm 2 is connected to the steering shaft 3a of the steering blade 3, and a linear actuator 1 is connected to one end of the mouth rocker arm 2, which is shown near the connecting portion. The rocker arm 2 is actuated to swing in the direction of the double arrow. A push-pull rod 4 is connected to the other end of the Ronoka arm 2, and the other end of the push-pull rod 4 is connected to the tip of a jet hone arm 5a to which a jet hone 5 is swingably connected.

Next, the effect of the above-mentioned construction precepts will be explained. For example, in FIG. 2(b), when the linear actuator l operates in the protruding direction, the rotor arm 2 rotates counterclockwise about point a, and the steering blade 3 also rotates counterclockwise. Since the bush pull rod 4 is pushed by the rotation of the rocker arm 2, the Hoene arm 5a also rotates counterclockwise, and the jet shaft 5 also rotates counterclockwise around point b. When the linear actuator 1 operates in the retracting direction, the steering wheel R3 and the jet vane 5 rotate in the opposite direction, that is, clockwise. In this way, the steering blade 3 and the jet vane 5 always rotate in the same direction by the operation of the linear actuator 1. Since the direction of the airflow whose direction is changed by the steering blade 3 and the direction of the jet flow whose direction is changed by the jet vane 5 are the same, the direction of the reaction force is also the same, and these reaction forces are added. This contributes to the direction change of the aircraft Ol, achieving efficient direction control. Note that the linear actuator 1 does not simply extend or retract a certain amount, but responds by the necessary amount based on a given command.
It is designed to perform infinitely fine directional control.

As described above, according to this embodiment, the steering blade 3 and the jet vane 5 can be driven simultaneously by one linear actuator l, and I rocker arms 2 are commonly used to operate the steering blade 3 and the jet vane 5. This reduces the space and weight the equipment occupies, making it easier to design, assemble,
This has the advantage that maintenance is easier and requires less time. In addition, since the number of parts is frozen, reliability is improved, parts procurement becomes easier, and costs are reduced.

〔Effect of the invention〕

Since the present invention is configured as described above, it has the following effects.

That is, since aerodynamic steering and l&force deflection are possible with a single actuator, the number of parts is reduced, and as a result, the mounting volume and weight are reduced, design, assembly, and maintenance are easier, and reliability is improved. Moreover, cost reduction is achieved.

[Brief explanation of drawings]

Fig. 1 is an exploded perspective view of the main parts of a composite steering system according to an embodiment of the present invention, Fig. 2 is a three-sided view of the above embodiment, and (a) is a longitudinal cross-sectional view of the aircraft body. ) is (b-b arrow view of al,
(C) is a right side view of (a) (showing the right half of the figure seen from the rear of the aircraft), and FIG. 3 is a diagram showing a conventional example corresponding to FIG. 2. DESCRIPTION OF SYMBOLS 1... Linear actuator, 2... Rocker arm, 3... Steering blade, 3a... Steering shaft, 4
...Push-Pull Rondo, 5...Jenotobane,
5a... Hehn arm.

Claims (1)

[Claims] A steering wing pivotally supported at the rear of a flying aircraft, a rocker arm coupled at its intermediate portion to a steering shaft of the steering wing, an actuator connected to one end of the rocker arm to swing the rocker arm, and the other end of the rocker arm. What is claimed is: 1. A composite steering device comprising: a push-pull rod having one end connected to the jet vane and a push-pull rod having the other end connected to the jet vane in a swingable manner.