JP2540066B2 - Vertical stabilizer paraplane with tabs - Google Patents

Description

Description: FIELD OF THE INVENTION The present invention relates to so-called paraplanes, and more particularly to a vertical stabilizer for improving its roll stability and yaw stability.

[Prior Art] A paraplane is a parachute type aircraft in which a propelling device such as a main body and a propeller is attached to a parachute, and a person is boarding the airplane or flying by remote control in the air. Simply parachute 1 and body 2 as shown in
The vertical tail 6 is simply provided on the frame 5 extending to the rear of the structure having the propeller 3 having the drive means and the wheels 4 for landing and gliding flights.

[Problems to be Solved by the Invention]

The above conventional paraplane has the following problems to be solved.

That is, there is a drawback that rotation (inclination) occurs with respect to the roll axis of the machine body (main body excluding the parachute) in a direction opposite to the propeller rotation direction common to propeller machines.

This is due to the anti-torque generated by the rotating force of the propeller, but in fixed wing aircraft, as a countermeasure against anti-torque, the side thrust of the engine and the rudder rudder, etc. should be applied in advance in order to solve the problem. There is. However, in the case of a paraplane, the parachute and the fuselage are suspended by ropes, so the parachute does not follow even if the direction of the fuselage changes.

Further, for example, if the airframe leans to the right as shown in FIG. 4, a horizontal distance difference occurs between the center of wind pressure of the parachute and the center of gravity of the airframe, and the self-propelled airframe exerts a moment on the center of wind pressure of the parachute. Therefore, when viewed in a plane, the paraplane makes a right turn as shown in FIG.

That is, the conventional paraplane has a problem of lacking roll stability and yaw stability.

The propeller is generally configured to rotate counterclockwise (counterclockwise) with respect to the traveling direction, and FIGS. 4 and 5 are also based on this.

[Means for solving the problem]

As a means for solving the above problems, the present invention is provided in a parachute, a main body suspended below the parachute, a propeller for propelling the main body, and a wake when the propeller rotates. And a vertical tail supported by a member extended from the main body, and a torque in a direction to rotate the main body in the same direction as the rotation of the propeller due to the wind pressure of the wakes provided on the upper side and the lower side of the vertical tail generated by the propeller. It is intended to provide a vertical wing-type paraplane with tabs, which is characterized by comprising a tab for generating

[Action]

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

That is, the tabs provided on the upper and lower sides of the vertical stabilizer generate torque in the direction of rotating the main body in the same direction as the rotation of the propeller due to the wake of the propeller, so that the tilt of the aircraft due to the reaction force of the propeller is canceled. , Roll stability and yaw stability are restored.

〔Example〕

An embodiment of the present invention will be described with reference to FIGS. The propeller is rotated counterclockwise with respect to the traveling direction.

FIG. 1 is a perspective view of the vicinity of a vertical tail of a paraplane according to the present embodiment as viewed from diagonally left rear and above, FIG. 2 is a plan view, and FIG. 3 is a left side view.

In these figures, 5 is a frame extending to the rear of a main body (not shown), 7 is a vertical tail, 7R is provided on the upper rear side of the vertical tail 7, and is indicated by the arrow R in FIG. The tab 7L, which is curved to the right so as to receive the force component of the wind pressure in the direction, is also provided at the lower rear part of the vertical stabilizer 7, and to the left so as to receive the component force of the wind pressure in the direction of arrow L in FIG. It is a tab with a warp. Other configurations are the same as those in FIGS. 4 and 5 of the conventional example, and are not shown. When necessary, the main body 2 is designated by the same reference numeral as that of the conventional example.

Next, the operation of the above embodiment will be described. As shown by the arrow in Fig. 2, the wake of the propeller flowing on both sides of the vertical stabilizer 7 hits the tabs 7R and 7L and changes its direction. As a component force of the reaction force generated at that time, the force in the direction of arrow R in Fig. 1 is generated. To tab 7R and a force in the direction of arrow L to tab 7L. Since these respective forces act as a couple on the frame 5 which is substantially horizontal, the direction of the arrow T shown in FIG.
That is, a counterclockwise torque is generated in the traveling direction. Therefore, the counter torque of the propeller 3 rotating counterclockwise is canceled, the rightward leaning of the airframe is eliminated, and accordingly, the rightward turning of the airframe is eliminated, and the ideal straight traveling characteristic of the paraplane is obtained.

In the above description, the wake of the propeller hits the tabs 7R and 7L. However, since the airframe is moving, the wake of the propeller naturally includes the airflow associated with the movement. The wake behind the propeller is not a uniform flow but a spiral swirling flow. It is desirable that the warp given to the tabs 7R and 7L should be given as a result of an experiment by actually flying the paraplane. Also, tabs 7R, 7
In order to effectively show the couple of L, it is desirable that the vertical tail 7 be configured so that the center of the wake of the propeller matches the vicinity of the horizontal center in the vertical direction.

Although the tabs 7R and 7L are provided on the tail end side of the vertical tail 7 in the above embodiment, they may be provided on the front end side in some cases. Alternatively, it can be freely provided at both front and rear ends. However, there is a limit to the movement because the lateral stability is lost as the tab position moves forward. Further, it is not necessary to use two right and left frames 5, and if the structure is such that the torque from the tabs 7R, 7L can be sufficiently transmitted to the main body 2, for example, a single straight pipe or a frame with a purpose or the like is used. It may be used.

It should be noted that the above embodiment has been described with respect to an example having a propeller that rotates counterclockwise with respect to the traveling direction, but it goes without saying that the direction of warp of the tab is reversed in the case of a propeller that rotates clockwise.

As described above, according to the present embodiment, the tab provided on the vertical stabilizer generates torque in the direction in which the main body rotates in the same direction as the rotation of the propeller due to the wake of the propeller, so that the anti-torque of the rotation of the propeller causes It is possible to cancel the inclination around the roll axis, eliminate the unexpected turning in the horizontal direction that accompanies the inclination of the machine body, and obtain a paraplane excellent in roll stability and yaw stability.

〔The invention's effect〕

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

That is, since the anti-torque caused by the rotation of the propeller is canceled by the tab, a paraplane having excellent maneuverability can be obtained.

Especially, the effect is further enhanced in the remote-controlled paraplane where maneuverability is important.

In addition, in the conventional method using the side thrust of the engine or the counterweight of the airframe, the force for canceling the anti-torque is constant, and it is not possible to obtain the canceling force according to the generated anti-torque. The configuration of the invention utilizes the property that the propeller wake increases as the propeller rotation increases, so it is possible to obtain a couple according to the generated anti-torque by properly setting the tab size and angle in advance. It has an excellent effect.

[Brief description of drawings]

FIG. 1 is a perspective view of the vicinity of a vertical stabilizer according to an embodiment of the present invention, FIG. 2 is a plan view of FIG. 1, FIG. 3 is a left side view of FIG. 1, and FIG. As seen, FIG. 5 is a plan view of FIG. 1 ... parachute, 2 ... main body, 3 ... propeller, 4 ... wheels, 5 ... frame, 7 ... vertical tail, 7R, 7L ... tab.

Claims (1)

(57) [Claims] 1. A parachute, a main body suspended below the parachute, a propeller for propelling the main body, and a propeller provided in the wake of the propeller rotating and extending from the main body. A vertical tail supported by the member, and tabs which are provided on the upper and lower sides of the vertical tail and generate a torque in a direction to rotate the main body in the same direction as the rotation of the propeller by the wind pressure of the wake generated by the propeller. A vertical wing-tailed paraplane with a tab characterized by comprising: