JPH0537760Y2 - - Google Patents

Description

[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to a directional control device for an aircraft or a flying object at a large angle of attack.

[Conventional technology]

Conventionally, directional control of aircraft (the purpose of which is to change the nose of an aircraft, missile, etc. to the left or right, and is usually evaluated by the yaw moment) has mainly been performed by moving the tail end of the rudder 3 left or right as shown in Figure 5. This was done by shaking it.

[Problem that the invention attempts to solve]

In the above conventional example, when the aircraft etc. reaches a large angle of attack (see Figure 5), since the rudder 3 is located behind the fuselage 4, the rudder 3 enters the wake of the fuselage 4, and the rudder 3 effect (shown by the broken line in Figure 4)
is not obtained. If the effect of the rudder 3 cannot be obtained at such a large angle of attack, there is a major problem in that the aircraft is likely to spin, leading to a crash.

The purpose of this invention is to solve the above problems and allow aircraft and missiles to fly safely even at large angles of attack.

[Means for solving problems]

The present invention is constructed as follows as a means for solving the above-mentioned conventional problems.

That is, the directional control device at a large angle of attack is characterized by having a pair of left and right plate-like bodies provided near the tip of the fuselage so that they can be independently extended and retracted on the left and right sides.

[Effect]

If the plate-shaped body 1 does not extend from the tip of the fuselage,
As shown in FIG. 2, the separation vortex 10 from the fuselage is symmetrical and no lateral force acts on the tip of the fuselage, but
As shown in Fig. 3, when the plate-shaped body 1 is fed out to one side, the separation vortex 10' becomes asymmetrical, and a lateral force is generated.
This force is generated forward of the center of gravity, creating a yaw moment and enabling directional control.

〔Example〕

An embodiment of this invention will be described with reference to FIGS. 1 to 4. In FIG. 1, reference numeral 1 denotes a plate-like body provided near the front end of an aircraft fuselage 4 so as to be able to be extended and retracted in the left and right lateral directions, and the figure shows a state in which only one side is extended. It usually flies in a retracted state.

Normally, the separated vortex 10 at a large angle of attack in the cross section of the tip of the fuselage is symmetrical as shown in FIG.

When the plate-like bodies 1 on the right and left sides are let out to the outside of the fuselage 4 at a large angle of attack, the separation vortex 10' in the cross section of the fuselage tip becomes asymmetrical as shown in FIG. Lateral forces act. For this reason, since there is a distance from the center of gravity 5 of the aircraft to the tip of the fuselage, a yawing moment is generated that changes the nose of the aircraft to the left or right, making directional control possible.

As shown in FIG. 4, when the normal rudder 3 alone is used, the effect as a rudder cannot be obtained at a large angle of attack, that is, approximately 45 degrees or more, but when the plate member 1 is extended,
As shown by the solid curve in the figure, the effect can be obtained even at large angles of attack of 70 degrees or more. The feeding and feeding operations of the plate-shaped body 1 are performed by a hydraulic actuator (not shown) in response to operation signals from a pilot.

Note that the plate-shaped body may have any structure as long as it does not deform due to wind pressure. As an example, the following numerical values may be used, such as the length of protrusion from the surface of the fuselage.

The protrusion length is 0.1 to 0.3 times the body radius R of the attachment part (for example, if R = 50 cm, about 5 cm to 15 cm), and the longitudinal width is 0.01 to 0.03 times the body length (for example, if the body length is about 20 m, 20 cm to (about 60cm), it is sufficient to have a certain length of protrusion on the outside of the fuselage, but it is easier to operate if it is perpendicular to the fuselage surface.

However, the position of the protrusion is extremely important, and when viewed in cross section, the optimum angle is considered to be around 90° to 150° from directly below the fuselage.

[Effect of idea]

As explained above, according to the present invention, directional control is possible even at large angles of attack, where conventional rudders were ineffective, and recovery from a spin state is possible, contributing to flight safety.

[Brief explanation of the drawing]

FIG. 1 is a perspective view of an aircraft equipped with a device according to an embodiment of the present invention, and FIG. 2 is a diagram showing airflow in a cross section of the fuselage tip in a state where the plate-like body of the embodiment is retracted. FIG. 3 is a cross-sectional view of the plate-like body of the embodiment when it is unwound, taken along the - arrow line in FIG. 1, FIG. The figure is a perspective view of a conventional aircraft. 1... Plate body, 3... Rudder, 4... Fuselage (of the aircraft), 5... Center of gravity.

Claims (1)

[Scope of utility model registration request] A directional control device at a large angle of attack, characterized by having a pair of left and right plate-like bodies provided near the tip of a fuselage so that they can be independently extended and retracted on the left and right sides.