JPH02133297A - Vertical tall type para-plane with tab - Google Patents

Abstract

PURPOSE:To counteract the inclination of an airframe resulted from the rotation al reaction force of a propeller and make the recovery of stability from rolling and yawing possible by making tabs provided on the upper and lower sides of a vertical tail to generate torque in the direction that rotates a main body in the same rotational direction as the propeller by the slip stream of the propel ler. CONSTITUTION:The slip stream of a propeller flowing both the sides of a verti cal tail 7 alters direction when it dashes against tabs 7R and 7L, causing a force in the direction of an arrow R on the tab 7R and a force in the direction of an arrow L on the tab 7L respectively as the component force of the reaction force generated on that occasion. Since these respective forces act on the upper and lower parts of a virtually horizontal frame 5 as couple of forces, torque in the direction of an arrow T, namely, of anticlockwise rotation against the proceeding direction is generated on the frame 5, which, consequently, works to offset the anti-torque of a propeller 3 rotating in anticlockwise direction, and the liquidation of rightward inclination of the airframe and the ideal rectilin ear propagation innate to para-plane are obtained.

Description

DETAILED DESCRIPTION OF THE INVENTION Field of the Invention The present invention relates to a so-called parabrane, and more particularly to a vertical stabilizer for improving its roll and yaw stability.

[Prior Art] A paraplane is a parachute-type airplane in which a main body and a propulsion device such as a propeller are attached to a parachute, and a person is on board or flies through the air by remote control. 5. Simply attach Para/NEET 1 to main body 2 as shown in figure 5.
It was constructed by simply installing a vertical stabilizer 6 on a frame 5 extending to the rear of a structure containing a propeller 3 with a driving means and wheels 4 for landing and sliding.

[Problems to be Solved by the Invention] The conventional parabrane described above has the following problems to be solved.

That is, there is a drawback in that the roll axis of the aircraft body (main body, etc. excluding the parachute) rotates (tilts) in a direction opposite to the propeller rotation direction common to the propeller shaft.

This is due to the anti-I torque generated by the rotational force of the propeller, but in fixed-wing aircraft, as a countermeasure against anti-torque, it can be solved by giving the engine side thrust, counter rudder, etc. an effect to turn the nose in the opposite direction to the anti-torque. are doing. However, in the case of a paraplane, the parachute and the aircraft are suspended by a rope, so even if the aircraft changes direction, the parachute does not follow.

For example, if the aircraft tilts to the right as shown in Figure 4, there will be a horizontal distance difference between the parachute's wind pressure center and the aircraft's center of gravity, and the self-propelled aircraft will experience a moment relative to the parachute's wind pressure center. occurs, so when viewed on a plane, the fifth
As shown in the figure, the paraplane makes a right turn.

That is, conventional paraplanes have a problem of lacking roll stability and yaw stability.

Incidentally, the propeller is generally configured to rotate to the left (counterclockwise) with respect to the direction of travel, and FIGS. 4 and 5 are also shown based on this.

[Means to solve the problem]

The present invention provides a parachute as a means for solving the above problems.
A main body suspended below the parachute, a propulsion propeller installed on the main body, and a vertical member installed in the wake of the rotating propeller and supported by a member extending from the main body. It is characterized by comprising a tail fin, and tabs provided on the upper and lower sides of the vertical tail fin, which generate torque in the direction of rotating the main body in the same direction as the rotation of the propeller by the wind pressure of the wake generated by the propeller. The aim is to provide a tab-equipped vertical stabilizer type paraplane.

[Effect]

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

In other words, the tabs installed on the upper and lower sides of the vertical stabilizer generate torque in the wake of the propeller to rotate the main body in the same direction as the propeller rotation, thereby canceling out the tilting of the aircraft due to the rotational reaction force of the propeller. , restore roll stability and yaw stability.

〔Example〕

An embodiment of the present invention will be described with reference to FIGS. 1 to 3. Note that the propeller rotates counterclockwise with respect to the direction of travel.

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

In these figures, 5 is a frame extending behind the main body (not shown), 7 is a vertical tail, and 7R is provided on the rear upper side of the vertical tail 7. The tab 7L, which is curved to the right so as to receive the component force of the wind pressure in the direction, is also provided on the rear lower side of the vertical stabilizer 7, and is bent to the left so as to receive the component force of the wind pressure in the direction of the arrow in Fig. 1. This is a tab with a warp. The other configurations are the same as those in the conventional example shown in FIGS. 4 and 5, and are not shown in the drawings, and if necessary, they will be designated by the same reference numerals as in the conventional example, such as main body 2.

Next, the operation of the above embodiment will be explained. As shown by the arrows in Figure 2, the propeller wake flowing on both sides of the vertical stabilizer 7 hits the tabs 7R and 7L and changes direction, and as a component of the reaction force generated at this time, a force in the direction of the arrow R in Figure 1 is generated. Tab 71?
, a force in the direction of the arrow is applied to the tab 7L, respectively. These respective forces act as a couple on the upper and lower sides of the almost horizontal frame 5, so the frame 5 has an arrow T shown in FIG.
It generates a counterclockwise torque with respect to the direction of travel, that is, the direction of travel. Therefore, the anti-torque of the propeller 3 rotating to the left is canceled out, and the rightward tilt of the aircraft body is eliminated, and accordingly, the rightward turning of the aircraft body is eliminated, and the ideal straight-line performance inherent to a paraplane is obtained.

In the above description, it is assumed that the propeller wake hits the tabs 7R and 7L, but since the aircraft is moving, the propeller wake naturally includes airflow accompanying the progress. Further, the flow behind the propeller is not a uniform flow but a spiral swirling flow.

It is preferable that the warpage imparted to the tabs 7R and 7L be determined through experiments by actually flying the paraplane. Further, in order to make the couple of tabs 7R and 7L effective, it is preferable that the center of the propeller wake coincides with the vicinity of the horizontal center of the vertical tail 7 in the vertical direction.

In the above embodiments, the tab 7R7L is provided on the tail end side of the vertical stabilizer 7, but it may be provided on the front end side depending on the case. Alternatively, it is also free to provide them at both the front and rear ends.

However, as the tab moves forward, lateral stability is lost, so there is a limit to its movement. Furthermore, it is not necessary to use two frames 5 on the left and right sides, and as long as the torque from the tabs IR and 7L can be sufficiently transmitted to the main body 2, a frame with one straight pipe or other suitable structure may be used. may be used.

In addition, although the above embodiment has been described as an example having a propeller that rotates counterclockwise with respect to the traveling direction, it goes without saying that in the case of a propeller that rotates clockwise, the direction of the warp of the tab is reversed.

As described above, according to this embodiment, the tab provided on the vertical stabilizer generates 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. By canceling out the inclination around the roll axis and eliminating the unexpected turning in the horizontal direction that occurs due to the inclination of the aircraft, it is possible to obtain a separate plane with excellent roll stability and yaw stability.

〔Effect of the invention〕

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

That is, since the counter torque caused by propeller rotation is canceled by the tab, a separate plane with excellent maneuverability can be obtained.

This effect is particularly evident in remotely controlled baraplanes where maneuverability is important.

In addition, with conventional methods using the side thrust of the engine or the counterweight of the aircraft, the force that cancels out the reaction torque is constant, and it is not possible to obtain a cancellation force that corresponds to the generated reaction torque. The structure of the invention takes advantage of the property that the propeller wake increases as the propeller rotation increases, so if the size and angle of the tabs are set appropriately in advance, it is possible to obtain a couple that corresponds to the counter torque generated. It has excellent effects.

[Brief explanation of drawings]

Fig. 1 is a perspective view of the vicinity of the vertical stabilizer of 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. 4 shows the conventional example from the rear.・The view shown in FIG. 5 is a plan view of FIG. 4. ■-parachute, 2-body, 3-propeller, 4-wheels, 5-frame, 7...-vertical tail, 7R, 7L tabs.

Claims (1)

[Claims] A parachute, a main body suspended below the parachute, a propulsion propeller provided on the main body, and a member provided in the wake of the rotating propeller and supported by a member extending from the main body. and tabs provided on the upper and lower sides of the vertical stabilizer that generate torque in the direction of rotating 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 stabilizer type paraplane with a tab.