JPS6247759B2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION [Industrial Application Field] The present invention relates to a triangular hang glider structure forming a swept angle wing and having a flexible sail stretched thereon.

[Conventional technology]

The general body framework of this type of hang glider used in the past and in the present invention will be explained with reference to FIG. In the same figure, for example, an aluminum alloy with a diameter of 40 mm to 50 mm and a wall thickness of 1 mm is used.
Insert each free end side of a central member 1 called a keel made of pipe material of about mm to 1.5 mm and left and right members 2 and 3 called spar located on the left and right sides from the open part of the U-shaped plate 4, The central member 1 and the left and right members 2 and 3 are pivotally fixed by bolts and nuts, which will be described later, and arranged at a fixed angle on the same plane, for example, at an angle of 45° or 50°, and the central member 1 and are orthogonal, and the left and right members 2 and 3
A crossing member 5 called a cross bar that intersects diagonally with the crossbar is connected and fixed at each crossing portion by bolts and nuts, which will be described later.

In addition, from the intersection of the central member 1 and the intersecting member 5, a linear guide member 6 and a triangular control member 7 that widen at the end extend upward and downward, respectively, at a constant angle with respect to the axes of the central member 1 and the intersecting member 5. It is attached,
An upper tension line 8 called a landing tension line passes through the upper part of the guide member 6 to the front and rear sides of the central member 1 and to the intersection of the left and right members 2 and 3 and the cross member 5, and is approximately cross-shaped when viewed in plan. The free ends thereof are fixed to the front and rear of the central member 1 and to the intersection portions of the left and right members 2 and 3 and the cross member 5 with bolts and nuts as described later.

Lower tension wires 9 called flight tension wires extend from the left and right bases of the control member 7 in the front-rear and left-right directions.
However, these also extend in a substantially T-shape when viewed from above, and their respective free ends are located at the front and rear of the central member 1 and at the intersections between the left and right members 2 and 3 and the intersecting member 5, as will be described later. It is fixed with bolts and nuts.

Further, as for the detailed structure of the frame of the fuselage, one free end of the central member 1 which is the front side in the glide direction of the fuselage is inserted from the open side of the U-shaped plate 4 as shown in FIG. , Natsuto 1
Although it is not visible in the figure, the left and right members 2 and 3 are secured using bolts 1 and 3 in the same way.
I try to fix it with nuts.

Further, the upper tension wire 8 extending in the front-rear direction through the guide member 6 and the lower tension wire 9 extending in the front-rear direction from the control member 7 have holes at each end as shown in FIGS. 2 and 3. Tongues 12, 13 and 14, 15
The front tongues 12 and 14 are located above and below the U-shaped plate 4, and a bolt 10 is inserted into each hole as a common member, and a nut 11 is similarly used for fixing. side tongue 13,1
5 is a bolt 1 located above and below the rear side of the central member 1.
6. It is fixed with a nut 17.

The intersection portion between the left member 2 and the cross member 5 can be connected and fixed by bolts 18 and nuts 19 as shown in FIG. Similarly, perforated tongues 20 and 21 are fixed to each end of the lower tension wire 9 extending in the left-right direction from 7, and the bolt 18 is connected to the tongue 21 and the guide member 5 using the bolt 18 and nut 19 as common members. , left member 2, tongue 20
are connected and fixed by nuts 19 passing through each of them.

Although the intersecting portion between the right member 3 and the intersecting member 5 is not shown, they are similarly connected and fixed using other bolts and nuts.

Further, the intersection portion between the central member 1 and the intersecting member 5 is the fifth
As shown in the figure, the bolts 22 and nuts 23 are used to connect and fix the connection.
An L-shaped support member 25 fixed to the lower part of the guide member 6 is arranged above the central member 1, and the bolt 22 is passed through each member through the saddle 26, and the nut 23 The connection is fixed.

The wings are constructed by stretching flexible sails on the frame of the aircraft body shown in FIG. 1, and the flexible sails 27 are stretched on the frame of the aircraft body as shown in FIG. The sail 27 is formed into a substantially triangular shape, and the center member and left and right edges of the sail 27 are formed with pocket stitched portions 28 and 29 that are opened through each other in the longitudinal direction. , the left and right members 2 and 3 are inserted through each.

This sail 27 is stretched during the assembly of the fuselage frame, and is attached to the center member 1 and the left and right members 2 and 3.
Using the U-shaped plate 4 as a pivotal fulcrum, rotate the U-shaped plates 4 in the closing direction so that they are aligned, and in this state insert the rear ends of the left and right members 2 and 3 into the openings of the left and right blind stitched parts 29 at the top of the sail 27. Insert from
While inserting the central member 1 from the rear end into the front opening of the bag-stitched part 28, the central member 1 and the left and right members 2, 3 are inserted into the bag-stitched parts 28, 29 of the sail 27 along their longitudinal directions, and then The left and right members 2 and 3 are opened at a predetermined angle with respect to the center member 1, and the crossing member 5
are connected, and each member is assembled as described above.

In this case, a play hole 32 as shown in FIG. 5 is formed in a part of the sail 27 as well as a part of the bag-stitched part 28 at the intersection of the central member 1 and the cross member 5, and the guide is guided through the play hole 32. A member 6 and a control member 7 are each projected through the vertical direction.

A similar free hole (not shown) is also formed in a portion of the sail 27 corresponding to the intersection of the left and right members 2, 3 and the crossing member 5, along with a portion of the blind stitched portion 29.

As shown in FIG. 6, from the top of the control member 7 of the hang glider, a support 34 for supporting and suspending the operator 33 is vertically disposed below, and the control member 7 can be operated by moving the control member 7 back and forth, left and right. The center of gravity of the aircraft can be changed by changing the position of the pilot 33, and the gliding direction can be raised, lowered, or turned to the right or left to selectively control its course.

[Problem that the invention seeks to solve]

By the way, in the hang glider structure with the above configuration, it is generally known that the glide ratio can be improved by increasing the aspect ratio of the aircraft, but this does not mean that it can be set without limit. For example, the intersection angle of the left and right members 2 and 3 is about 110° to 130°, and the longitudinal dimension is 5.5 m.
The inventors have confirmed through various experiments that a certain level of airframe performance can be expected by making the longitudinal dimension of the central member 1 about 2 m to 2.7 m.

However, simply widening the tip angle of the aircraft, called the nose angle, increasing the lengths of the left and right members 2 and 3, and shortening the length of the center member 1, will conversely affect the stability of the aircraft during actual gliding. It was also confirmed that the aircraft became uneasy and difficult to operate and became dangerous.

The present invention takes this point into consideration and aims to stabilize the glide performance of this type of aircraft, thereby improving its maneuverability.

[Means for solving problems]

In order to achieve the above object, the present invention has a configuration in which the central member and the left and right members are connected at their respective distal ends, and the axes of the left and right members intersect at approximately equal angles with respect to the axis of the central member. and the rear ends of the left and right members constitute the frame of the fuselage, with the rear ends of the left and right members being free ends, and a bag-stitched part that extends along the center and left and right edges of the flexible, generally triangular sail and has a through opening in the front and rear. inserting the central member and the left and right members into each of the bag-stitched parts of the sail, and partially fixing at least the rear of each bag-stitched part to the rear sides of the central member and the left and right members to form wings of the fuselage; and the intersecting members that are substantially orthogonal to the axis of the central member and obliquely intersecting to the axes of the left and right members are connected at their respective intersecting parts, and the central member and the left and right members are fixed by the intersecting members, and the intersecting parts of the central member and the intersecting members are fixed. A guide member that extends upward and a control member that hangs downward are connected, and a constant tension is applied from the upper side of the guide member and the lower left and right sides of the control member to the front and rear of the central member and the intersection portions of the left and right members and the intersecting member. In a hang glider in which the above-mentioned members are fixedly connected by tensioning upper and lower tension wires, the blind-stitched part of the center part of the sail is wrapped along the axial direction of the center member and with the center member as the axis. When the sail is in the shape of a U-shape and has a constant width, it can be hung from the underside of the sail, and the bag-stitched part hanging down in the band acts as a vertically stabilizing wing for the fuselage.

〔Example〕

Embodiments of the present invention will be described below based on the accompanying drawings.

Since the frame structure of the fuselage is basically the same as that shown in Fig. 1, the details thereof will be omitted, but one embodiment of the present invention will be explained based on Figs. 7 to 15 together with Fig. 1. To explain using the same reference numerals for the same or equivalent parts as in the conventional example, for example, there is a central member 1 called a keel made of aluminum alloy pipe material with a diameter of 40 mm to 50 mm and a wall thickness of about 1 mm to 1.5 mm, and on the left and right sides of the central member 1. The free end sides of the left and right members 2 and 3 (called spar) are inserted through the open part of the U-shaped plate 4, and are pivoted and fixed with bolts and nuts, which will be described later, so that they are fixed at a certain angle on the same plane, for example, the central member. 1 and the left and right members 2 and 3 are arranged to intersect each other at an angle of 45° or 50°, and a crossing member 5 called a cross bar is orthogonal to the central member 1 and diagonally intersects with the left and right members 2 and 3. are connected and fixed at each intersection using bolts and nuts, which will be described later.

In addition, from the intersection of the central member 1 and the intersecting member 5, a linear guide member 6 and a triangular control member 7 that widen at the end extend upward and downward, respectively, at a constant angle with respect to the axes of the central member 1 and the intersecting member 5. It is attached,
An upper tension line 8 called a landing tension line passes through the upper part of the guide member 6 to the front and rear sides of the central member 1 and to the intersection of the left and right members 2 and 3 and the cross member 5, and is approximately cross-shaped when viewed in plan. The free ends thereof are fixed to the front and rear of the central member 1 and to the intersection portions of the left and right members 2 and 3 and the cross member 5 with bolts and nuts as described later.

Lower tension wires 9 called flight tension wires extend from the left and right bases of the control member 7 in the front-rear and left-right directions.
However, these also extend in a substantially T-shape when viewed from above, and their respective free ends are located at the front and rear of the central member 1 and at the intersections between the left and right members 2 and 3 and the intersecting member 5, as will be described later. It is fixed with bolts and nuts.

Further, as a detailed structure of the fuselage frame, one free end of the central member 1, which is the front side in the glide direction of the fuselage, is inserted from the open side of the U-shaped plate 4 as shown in FIG. The bolts 10 and nuts 1 are inserted from the open side of the U-shaped plate 4.
Although not visible in the figure, the left and right members 2 and 3 are similarly fixed with other bolts and nuts.

Further, the upper tension wire 8 extending in the front-rear direction through the guide member 6 and the lower tension wire 9 extending in the front-rear direction from the control member 7 each have a perforated tongue at each end as shown in FIGS. 7 and 8. 12, 13 and 14, 15 are fixed, the front tongues 12, 14 are located above and below the U-shaped plate 4, a bolt 10 is inserted into each hole as a common member, and a nut 11 is similarly shared and fixed. The rear tongues 13 and 15 are located above and below the rear side of the central member 1 and are fixed with bolts 16 and nuts 17.

The intersection portion between the left member 2 and the cross member 5 can be connected and fixed by bolts 18 and nuts 19 as shown in FIG. Similarly, perforated tongues 20 and 21 are fixed to each end of the lower tension wire 9 extending in the left-right direction from 7, and the bolt 18 is connected to the tongue 21 and the guide member 5 using the bolt 18 and nut 19 as common members. , left member 2, tongue 20
are connected and fixed by nuts 19 passing through each of them.

Although the intersecting portion between the right member 3 and the intersecting member 5 is not shown, they are similarly connected and fixed using other bolts and nuts.

Further, the intersection portion between the central member 1 and the intersecting member 5 is the first
As shown in Figure 0, the bolts 22 and nuts 23 are used to connect and fix the connection.
4 is arranged, and an L-shaped support member 25 fixed to the lower part of the guide member 6 is arranged above the central member 1,
A bolt 22 is commonly used to pass through each of the above members via a saddle 26, and the bolts 22 are connected and fixed by a nut 23.

Flexible sails are stretched over the frame of the aircraft body shown in FIG. The sail 27 is stretched over the frame to form a substantially triangular shape, and the center portion and the left and right edges of the sail 27 are provided with bag-stitched portions 28 which are opened through in the longitudinal direction, respectively.
29 is formed, and the central member 1 and the left and right members 2 and 3 are penetrated through these blind stitched portions 28 and 29, respectively.

FIG. 12 shows a state in which the right member 3 is inserted into a blind stitched portion 29 formed along the right edge of the sail 27. As shown in FIG.

Although the left member 2 is not shown in the drawings, it is similarly inserted through the blind stitched portion 29 along the left edge of the sail 27.

In this case, a tape 30 is fixed to the top of the triangular sail 27, as shown in FIG. However, if the blind stitched portions 29 on the left and right edges of the sail 27 are formed up to the vicinity of the triangular top of the sail 27, the left and right members 2 and 3 will penetrate through the blind stitched portions 29 on the left and right edges. After being inserted, when the sail 27 is opened at a predetermined angle and assembled, the top of the sail 27 is fixed by the left and right blind stitched parts 29, and the sail 27 does not necessarily have to be fixed with the tape 30.
The tops of 7 do not roll up and slide in the axial direction of the left and right members 2, 3 or the center member 1.

A tape 31 as shown in FIG. 8 is fixed to the rear end of the bag-stitched portion 28, and this tape 31 is placed along the rear lower side of the central member 1, and the common bolt 16 is inserted and fixed with a nut 17. Although not shown, the rear sides of the left and right blind stitched portions 29 are also partially fixed at the rear sides of the left and right members 2 and 3, respectively, so that the sail 27 can slide in the axial direction of the central member 1 and the left and right members 2 and 3. is prevented.

Further, a bag-stitched portion 28 formed in the center of the sail 27 has a U-shaped cross section and hangs down from the back side of the sail 27, and a part of the central member 1 is attached to this bag-stitched portion 28 with a sufficient margin. It has been inserted.

This sail 27 is stretched during the assembly of the fuselage frame, and is attached to the center member 1 and the left and right members 2 and 3.
Using the U-shaped plate 4 as a pivotal fulcrum, rotate the U-shaped plates 4 in the closing direction so that they are aligned, and in this state insert the rear ends of the left and right members 2 and 3 into the openings of the left and right blind stitched parts 29 at the top of the sail 27. Insert from
While inserting the central member 1 from the rear end into the front opening of the bag-stitched part 28, the central member 1 and the left and right members 2, 3 are inserted into the bag-stitched parts 28, 29 of the sail 27 along their longitudinal directions, and then The left and right members 2 and 3 are opened at a predetermined angle with respect to the center member 1, and the crossing member 5
can be connected, and each member can be assembled as described above.

In this case, a play hole 32 as shown in FIG. 10 is formed in a part of the sail 27 as well as a part of the bag stitched part 28 at the intersection of the central member 1 and the cross member 5. A member 6 and a control member 7 are respectively projected vertically.

A similar free hole (not shown) is also formed in a portion of the sail 27 corresponding to the intersection of the left and right members 2, 3 and the crossing member 5, along with a portion of the blind stitched portion 29.

As shown in FIG. 11, from the top of the control member 7 of such a hang glider, a support 34 for supporting and suspending a pilot 33 is vertically disposed below, and the control member 7 can be operated by moving the control member 7 back and forth and left and right. Person 33
By changing the position of the aircraft, the center of gravity of the aircraft can be changed, and its course can be selectively controlled by raising or lowering its glide direction, or turning to the right or left.

In the above configuration, when the aircraft glides, sail 2
Positive pressure acts on the lower surface of the sail 7, and negative pressure acts on the upper surface in a well-known manner to generate lift, and the sail 27 inflates uniformly from the bottom to the top.

At this time, the sail 27 of the bag-stitched portion 28 into which the central member 1 has been inserted and accommodated while forming a gap with sufficient margin is lifted above the axis of the central member 1 by the above-mentioned action. It is stretched in a band-like manner along the axis, particularly in the state shown in FIG. 11. Here, when no wind pressure acts on the sail 27, the bag-stitched portion 28 does not have a constant shape and is in a slack state.

Therefore, when the aircraft is gliding, the blind stitched portion 28 forms a band-shaped wall with a constant width along the center front and back of the sail 27, and this band-shaped wall forms vertically stabilizing wings of the aircraft, thereby preventing the aircraft from moving forward. This prevents unstable gliding in which the nose of the aircraft swings to the left or right from a balanced state, thereby maintaining good directional stability of the aircraft.

In this case, by fixing the rear end of the bag stitched portion 28 to the rear side of the central member 1 via the tape 31,
It is possible to effectively prevent the band-like wall of the bag-stitched portion 28 formed by the lifting force applied to the sail 27 from deforming.

That is, as shown in FIG.
That is, it starts from a position separated by a certain distance from the intersection of the center member 1 and the left and right members 2 and 3, and the rear end of the bag stitched portion 28 extends to the end of the sail 27, and in this case, the back end of the bag stitched portion 28 As shown in FIG. 13, the upper edge of the rear end ends at the rear side of the central member 1, and a pouch 35 is formed inside the rear end of the bag-stitched portion 28 along the axis of the central member 1.
As shown in FIG. 3, a removable tape 36 is attached to the rear end opening of the pouch 35 to open and close it.

A small hole 37 passing through the sail 27 is formed in the upper side of the pouch 35, as shown in FIGS. 8 and 13.

The pouch 35 houses a plate 38 that is lightweight and does not easily deform, such as an aluminum plate, and one end of a string piece 39 is fixed to the plate 38, and the other end is inserted through the small hole 37. A hook 40 is fixed by leading out from above 27.

The hook 40 is connected to the guide member 6 as shown in FIG.
It passes through the top of the center member 1 and is hooked and locked onto the rear part of the upper tension wire 8 which is stretched across the front and rear of the central member 1.

In this case, a stopper 41 is caulked at a predetermined position midway at the rear of the tension wire 8.
By locking the hook 40 to 1, the hook 40
The string piece 37 is designed to prevent the tension wire 8 from sliding down along the inclination of the tension wire 8, and the tension wire 8 is constantly pulled down in a certain angle direction, that is, in a direction crossing the tensioning direction of the tension wire 8. By applying the desired tension, as shown in FIG. 14, the sail 27 spreads around the center of the rear side of the sail 27 centering on the plate 38 housed in the pouch 35 to form a fixed area that is slightly larger than the area of the plate 38. A flat surface is formed, and this flat surface always forms an inclined surface 42 that is upwardly inclined with respect to the axis of the central member 1.

Therefore, when the aircraft is gliding, the part of the sail 27 above the trailing edge of the bag stitched part 28 formed in the center part of the flexible sail 27 is stretched in front and behind the central member 1 in order to prevent sudden changes in airflow. A flexible sail 27 is fixed to the rear part of the upper tension wire 8 with a constant tension by a string piece 39, and includes the rear end of the bag-stitched part 28.
A part of the flexible sail 27 is formed by forming a flat surface with a constant area near the center of the rear side, and by constantly forming an inclined surface 42 whose tail is upwardly inclined with respect to the axis of the central member 1. By fixedly tensioning the sail 27, the tension of the sail 27 will not change excessively in the event of a sudden change in airflow, and as a result, the stability of the aircraft body can be maintained.

In this case, if the flat surface of the rear end of the sail 27 along the axial direction of the central member 1 accommodates the plate 38 in the pouch 35 and closes the opening of the pouch 35, which can be opened and closed, this can be held stably. As a result, it can be formed as a substantially uniform flat surface that partially extends to the sail 27 in the vicinity of the plate body 38, and the string piece 39 can be stretched in a direction that resists the tension of the upper tension wire 8. By doing so, the flat surface becomes the central member 1.
It can be formed as a constant inclined surface 42 that rises rearward along the axis of the hook 4 attached to the string piece 39.
Stopper 41 with 0 caulked and fixed to the tension wire 8
It can be fixedly and uniformly formed simply by locking it.

〔Effect of the invention〕

As described above, according to the present invention, the bag-stitched part through which the central member is inserted is made to hang downward in a U-shape from the lower surface of the sail in the middle, so that the central member has sufficient room within the bag-stitched part, and It is possible to store the central member and form a band-shaped standing wall of a constant width in the axial direction of the central member by wrapping the bag-stitched portion around the central member, thereby forming a vertically stabilizing wing of the fuselage.
The directional stability of the aircraft glide can be ensured.
In addition, the part of the sail above the trailing edge of the bag-stitched part that has been inserted through the center member is fixed with a constant tension to the rear part of the upper tension wire that is stretched on the front and back of the center member with a piece of string, so that the rear part of the sail is fixed at a constant tension. By forming the area as a flat surface and fixedly forming this flat surface as an inclined surface that rises rearward along the axis of the central member, the stability of the aircraft's gliding can be ensured. This type of aircraft requires a simple structure that can be easily assembled, disassembled, transported, and stored.Without complicating the structure of this type of aircraft, the aircraft can be easily assembled, disassembled, transported, and stored by simply making some changes to the wing structure, which consists of the fuselage frame and sail. We were able to improve the glide performance of the aircraft while maintaining stable maneuverability.

[Brief explanation of the drawing]

FIG. 1 is an upper perspective view showing the framework of a conventional fuselage structure and the framework of the present invention, FIG. 2 is a vertical sectional view of the main part showing the front part of the conventional fuselage structure, and FIG. FIG. 4 is an enlarged perspective view of essential parts showing the center left part of the fuselage structure corresponding to FIG. 2, and FIG. FIG. 6 is a partially sectional side view showing the central part of the fuselage corresponding to FIGS. 2 and 3; FIG. 6 is a lower perspective view showing the gliding state of the fuselage corresponding to FIGS. 2 to 5; 7 is a vertical sectional view of the main part showing the front part of the fuselage structure according to the present invention, and FIG.
FIG. 9 is an enlarged perspective view of essential parts showing the center left part of the fuselage structure corresponding to FIGS. 7 and 8; The figure is a partially sectional side view showing the center part of the fuselage corresponding to Figures 7 and 8, Figure 11 is a lower perspective view showing the gliding state of the fuselage, and Figure 12 is a view of the fuselage structure. FIG. 13 is a partially enlarged sectional view of the right side part, and FIG. 14 is an enlarged sectional view of the main part of the rear part of the fuselage structure.
The figure is an upper perspective view partially corresponding to FIG.
FIG. 5 is an enlarged perspective view of the main part of FIG. 10. 1... Central member, 2, 3... Left and right members, 5...
Cross member, 6... Guide member, 7... Control member, 8
...Upper tension wire, 9...Lower tension wire, 27...Sale, 28, 29...Bag sewing part, 35...Small bag, 3
8... Plate body, 39... String piece, 42... Inclined surface.

Claims (1)

[Scope of Claims] 1. The center member and the left and right members are connected at their distal ends, and the axes of the left and right members intersect at approximately equal angles to the axis of the center member, and each rear of the center member and the left and right members is In addition to forming the frame of the fuselage with free ends, a bag-stitched part is formed that extends along the central part and left and right edges of the flexible, generally triangular sail, and has a through opening in the front and rear. the members are inserted into each bag-stitched part of the sail, and at least the rear of each bag-stitched part is partially fixed to the rear sides of the center member and the left and right members to form wings of the fuselage, and Crossing members that are substantially orthogonal and oblique to the axes of the left and right members are connected at their respective crossing portions, the center member and the left and right members are fixed by the crossing members, and the guide extends upward to the crossing portions of the center member and the crossing members. Connect the members and the control member that hangs downward, and tension vertical tension lines with a constant tension from the upper side of the guide member and the lower left and right sides of the control member, respectively, to the front and rear of the center member, and to the intersection of the left and right members and the crossing member. In a hang glider in which each of the above members is fixedly connected,
The bag-stitched part of the center part of the sail is arranged along the axis of the center member and wraps around the center member in a substantially U-shaped band of a constant width that can hang down on the underside of the sail. A hang glider structure characterized by a structure in which the bag-stitched portion acts as a vertically stabilizing wing for the aircraft. 2. The part of the sail above the trailing edge of the bag-stitched part formed in the central part of the flexible sail is fixed with a constant tension to the rear part of the upper tension wire that is stretched in front and behind the central member with a piece of string. , the vicinity of the rear center of the flexible sail, including the rear end of the bag-stitched portion, is formed into a flat surface of a certain area, and this flat surface is turned into an inclined surface with an upward slope toward the rear of the axis of the central member. A hang glider structure according to claim 1, characterized in that the hang glider structure is formed.