RU2521862C1 - Vertical take-off and landing aircraft - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to rotorcraft, namely, to VTOL aircraft. VTOL aircraft consists of wings actuator, cabin, engines and fan. Wings drive consists of four frames composed by guides of the wing pipe bearings, angle pieces and strips. Wings can generate air flow. Wings and pulleys are secured to toothed belts. Pulleys and levers for control over wing angle of attack are fitted on two shafts. Guide bearings allow levers welded to the left and right frames to run therein. There are two driven sprockets and guard sheet. Angle of attack of the wings does not vary at flight at straight section atop and at bottom. Wings can vary said angle of attack at flight in semicircle.

EFFECT: efficient vertical takeoff and landing, higher efficiency of power plant.

4 cl, 12 dwg

Description

The invention "Aircraft of vertical take-off and landing" relates to the field of aviation, in particular to aircraft of vertical take-off and landing.

1. The aircraft vertical take-off and landing consists of a device 1 for the movement of the wings 43, cockpit 2, engines 3, fan 4, characterized in that the device 1 for the movement of the wings consists of four trusses, which are formed from guides 19 for the direction of movement of the pipe bearings wings, corners 12 and strips 22; wings 43, which are able to create air flow; toothed belts 10 to which wings 43 are attached; pulleys 9; two shafts 11 on which the pulleys 9 are planted; levers 20 control angles of attack of wings 43; guide rails 29 of the levers 20 welded to the right and left trusses; two driven sprockets 7 and a sheet of fencing (see figure 1 - figure 12).

2. The aircraft of vertical take-off and landing according to claim 1 is characterized in that the wings 43 of the device 1 for the movement of wings have the ability to move in straight sections at the top and bottom, while the angle of attack of wing 43 does not change when moving in straight sections at the top and bottom ( see figure 1 - figure 12).

3. The aircraft vertical take-off and landing according to claim 1, characterized in that the wings 43 of the device 1 for movement of the wings have the ability to change the angle of attack when moving in a semicircle (see figure 1, figure 2).

4. The aircraft of vertical take-off and landing according to claim 1 is characterized in that it has the ability to change the direction of air flow when changing the angle of inclination of the device 1 for the movement of the wings relative to the cabin 2 (see figure 1 - figure 11).

State of the art

There are vertical take-off aircraft, but the rotor principle is applied in them. In particular, "Autogyro with vertical take-off and vertical landing" [B.A. Polovinkin, RF patent No. 2463213 dated April 21, 2008 for the invention “Autogyro with vertical take-off and vertical landing”, RU 2463213 according to the application No. 2010146347], also a patent for the utility model “Aircraft” [A.D. Girgidov, R.A. Girgidov, RF patent No. 121488 of 06/13/2012 for the invention of "Aircraft", RU 121488 according to application No. 2012124445]. In this invention, the "aircraft vertical take-off and landing" reliability is higher than that of a helicopter, gyroplane with vertical take-off and vertical landing and the aircraft [A.D. Girgidov, R.A. Girgidov RF patent No. 121488 of June 13, 2012 for the invention of “Aircraft”, RU 121488 according to application No. 2012124445], since in a helicopter and gyroplane with vertical take-off and landing and in an aircraft, the support of the structure occurs on the rotor bearing, and Aircraft vertical takeoff and landing many bearings on the wings.

Disclosure of invention

Aircraft of vertical take-off and landing is an aircraft heavier than air of the aerodynamic principle of action. The lifting force and traction necessary for translational motion are created using moving wings.

The wings move with the help of timing belts, to which they are attached. Moving wings create lift and therefore, an aircraft of vertical take-off and landing can rise directly from the parking lot.

Aircraft of vertical take-off and landing can take off and hang in the air, descend and land anywhere, it does not need a runway.

Since the wings have tight protection, the aircraft of vertical take-off and landing can safely land in the taiga in a clearing, because tree branches are not dangerous to it.

The aircraft of vertical take-off and landing is intended for the transport of people and goods.

By increasing the installation and the number of sections, you can get a lot of lift with a slight increase in engine power.

Brief Description of the Drawings

Figure 1 shows a General view of the aircraft vertical take-off and landing in two projections. The aircraft of vertical take-off and landing consists of a device for the movement of wings 1, cockpit 2, gas turbine engines 3, fan 4 (with a variable angle of installation of the blades). From the drive sprocket 6, the chain drive to the sprockets 7. The worm gearbox 8 is designed to change the angle of inclination of the device for the movement of the wings 1 relative to the cabin 2. Aluminum pipes 46 are used to mount the fan 4. The ends of the shaft 39 are supported by brackets 41. The torque is transmitted from gas turbine engines 3 through gearboxes 5 to the steel shaft 39. The gearbox 35 is used to take power from the shaft 39 to rotate the fan 4.

Figure 2 shows a part of the device for the movement of the wings. The wings 43 are attached to the toothed belts 10. The toothed belts 10 are driven by pulleys 9. The guides 19 of the bearings are shown.

Figure 3 shows a diagram of a change in the angle of attack (angle of attack of about 20-23 degrees) of the wings when the wing moves from an upper position to a lower semicircle. The wing, moving in the guides 19, pulls the bearing of the lever 20 along the guide 29. The bearing, which moves along the guide 29, moves from position 1 ′ to position 2 ′. At this time, the front lever bearing from position 1 ″ goes into position 2 ″ and is caught by the rounded part of the lower guide 29, and the rear bearing of the lever 20 is released. With further movement of the wing, the rear bearing is completely released and the angle of attack of the wing holds the front bearing, position 3 ″. This happens when the wing moves from top to bottom.

Figure 4 shows how the angle of attack of the wing changes when it moves from the bottom up. The lower guide 29 of the lever bearing 20 at a distance of 1.5 m from the central axis of the circle deviates from the horizontal position towards the guide 19 and approaches a distance of 0.25 m to it. The normal distance between the guides 19 and 29 is 0.27 m. The front lever bearing fits the center axis of the circle, position 4 ′. At this time, an additional guide 32 of the rear lever bearing is gripped, position 4 ″. The wing, moving along the guide 19, pulls the rear lever bearing, position 5 ″, while the front lever bearing, position 5 ′, passes the gap between the guides. When reaching the 6 ″ position with the rear lever bearing, the front lever bearing is gripped by the additional guide 33, position 6 ′. When the front lever bearing takes position 7 ′, the rear lever bearing is gripped by rounding the upper guide 29, position 7 ″. With further movement of the wing, the front bearing is released.

Figure 5 shows a pipe 14 in section. Bronze inserts 17 serve to strengthen the pipe 14. Balls 18 in the inserts 17 serve to reduce the braking of the pipe 14 when displaced in the axial direction. Shown is the lower part of the bracket 25, which is mounted on the belt 10. The extreme left and right ribs 15 of the wing are shown. Shows the lever 20 changes the angle of attack of the wing and the ring 31 for mounting on the pipe. The plate 27 of the lever 20 is shown, in which the bearing axis 28 is mounted, which is located in the guide 29. The bracket 30 is shown, which holds the guide 29.

The bracket 30 is welded to the guide 19.

Figure 6 shows the front of the device for moving wings: a titanium shaft 11, four driving pulleys 9, an asterisk 7, guides 19, 29, bearing rings 21 for bearings, angles 12 (landing rings 21 are welded to them), brackets 30, spacers pipes 13.

7 shows a bracket, consisting of a lower part 25 of the bracket and the upper part 45 of the bracket. A clip 44 is shown for attaching the lower part 25 of the bracket to the belt 10. Inside the belt 10, a steel cable 34 is shown.

On Fig shows the left truss, consisting of: guides 19, 29, 23, corners 12, brackets 30, strips 22, corners 24, rings 26.

Figure 9 shows the wing structure: a central tube 14 to which five ribs 15 and two spars 16 are attached. Rib 15 and its section are shown. Spar 16 and its side view are shown.

Figure 10 shows the lever 20 changes the angle of attack of the wing. Shown plate 27, ring 31.

11 shows a gearbox 5 of a gas turbine engine 3. A steel shaft 39 is shown on which drive sprockets are located 6. Through a gearbox 35 for power take-off, torque is transmitted to the fan via shaft 37. From gearbox 35 using two shafts and controlled clutches, rotation is transmitted to the gearbox 36, then through the shaft 40 the rotation is transmitted to the gearbox 38, and from it to the worm gearbox 8, which serve to control the angle of inclination of the device for the movement of the wings.

12 shows a pulley 9 and a driven sprocket 7.

The implementation of the invention

The aircraft vertical take-off and landing consists of a device for the movement of the wings 1, cockpit 2, gas turbine engines 3, fan (with a variable angle of installation of the blades) 4. Figure 1.

Torque from the engines 3 through the drive sprocket 6 is transmitted to the driven sprocket 7.

In the front of the device, the driven sprocket is mounted on the shaft on the right side, and in the rear of the device, the driven sprocket is mounted on the shaft on the left side. This is done so that there are uniform tensile forces on the upper and lower parts of the belts.

A drawing of a device for moving wings is shown in figure 2.

The wings 43 are attached to the toothed belts 10. The movement of the belts is carried out using pulleys 9, which are mounted on a titanium shaft 11. See Fig.6.

Titanium alloy shaft. Diameter 0.04 m, length 4.442 m.

The bearings of the shaft are three bearings 180208. The bearings on the shaft are fixed with spring thrust rings.

The bearing rings 21 of the bearings are welded to the corners of the 12 trusses. See Fig.6, Fig.8.

The seat ring in the middle part is welded to a double corner, because in the middle two farms are welded together.

The bearing in the middle part of the shaft 11 is fixed in the seat ring 21 by the spring thrust inner rings, and the bearings at the ends of the shaft are freely positioned in the seat rings. This is done so that there is no pinching of the bearings as a result of thermal expansion of the shaft 11.

From the right end of the titanium shaft 11 at a distance of 2.204 m is the center of the middle bearing. From the center of the middle bearing at a distance of 0.055 m to the center of the hubs, two pulleys 9 made of aluminum alloy are planted on the keys on the dowels. Between the centers of the first pulleys and second pulleys is a distance of 2.045 m.

From the centers of the extreme pulleys to the centers of the extreme bearings, the distance is 0.09 m. A driven sprocket 7 is mounted on the key on the left end of the titanium shaft 11.

The seat rings 21 are made of titanium alloy. The inner diameter is 0.08 m, the outer diameter is 0.1 m. The height of the middle ring is 0.04 m, the outer rings are 0.025 m each. Asterisk 7 is made of a titanium alloy.

Pulleys 9 made of aluminum alloy. The diameter of the protrusions is 2 m, the diameter of the hub is 0.08 m, the length of the hub is 0.04 m, eight spokes are 0.022 m in diameter, the rim is 0.031 m wide, and the height is 0.02 m. See FIG. 12.

The farm is made of guides 19, along which the bearings of the pipes 14 of the wings, the half rings 23, the corners 12, 24, the strips 22, the brackets 30 and the ring 26 to which the cab bracket is mounted move. See FIG.

The guides 19, in which the bearings of the wing pipe 14 move, are made of a titanium alloy in the form of a channel.

The upper and side walls are 0.004 m thick and the bottom is 0.003 m, because all load acts on the top wall. The height of the walls is 0.035 m. The distance between the walls where the bearing is moving is 0.065 m.

The guide 23 of the half rings along which the bearings of the tubes of the wings 14 move from top to bottom and from bottom to top is made of a titanium alloy with a thickness of the outer and side walls of 0.006 m and an inner wall of thickness of 0.003 m. See Fig. 8.

Corners 12 are made of titanium. The size of the long side is 0.004 m, the short one is 0.03 m. The thickness of the long shelf is 0.004 m, the short one is 0.003 m.

Corner 24 is made of titanium. The length of the long side is 0.035 m, the short side is 0.015 m, the thickness is 0.003 m.

The length of the middle corner 24 of the farm is 1.5 m.

Strips 22 of titanium serve to give stability to the farm, the width of 0.02 m, the thickness of 0.002 m. All parts are connected by welding.

8 brackets 30 are welded to the guide 19. The brackets are trimmed off of the 0.4-meter guide 19. The holes for the bolts are made in the brackets for fastening the spacer tubes 13. The spacer tubes 13 are made of aluminum alloys. Outer diameter 0.03 m, inner diameter 0.017 m, M20 thread. For fastening pipes, bolts and studs are used. The length of the spacer pipe 2.19 m. See Fig.6.

At the side trusses of the installation, guides 29 of the bearings of the lever 20 for holding the angle of attack of the wing 43 are welded to the brackets 30.

On Fig shows the left farm installation, and the right is a mirror image of the left.

Holding the angle of attack of the wing (angle of attack of about 20-23 degrees) occurs under the action of the lever 20, figure 5, figure 10.

The lever is made in the form of two triangular frames having a central ring 31, which is mounted on the wing tube 14 and is fastened with an M8 bolt.

The frame is made of titanium. In the section forming the frame is a rectangle with sides 0.04 m and 0.02 m, wall thickness 0.001 m. The frames are welded to the titanium ring 31, the inner diameter is 0.03 m, the outer diameter is 0.05 m, the thickness is 0.02 m Figure 10.

A titanium plate 27 with an opening for mounting the bearing axis 28 is welded to the lower ends of the frame. The plate thickness is 0.005 m. The plate is in the form of a square with a side of 0.04 m.

There is a distance of 0.2 m between the upper surface of the lever and the hole. The long sides of the frame form an angle of approximately 23 degrees.

An axis 28 with a bearing 180203 is inserted into the hole of the plate 27.

The bearing moves along the guide 29, which is mounted using the bracket 30 to the farm. Guide 29 is made of a titanium alloy in the form of a channel, the width is 0.05 m and two walls of 0.023 m each, the thickness of the entire channel is 0.003 m.

Changing the angle of attack of the wing is shown in Fig.3.

The wing, moving in the guides 19, pulls the bearing of the lever 20 along the guide 29.

The distance from the guide 19 to the guide 29 is 0.27 m.

The bearing, which moves along the guide 29, moves from position 1 ′ to position 2 ′. At this time, the front lever bearing from position 1 ″ goes into position 2 ″ and is caught by the rounded portion of the lower guide 29, and the rear lever bearing is released.

The radius of curvature of the exciting part of the guide 29 is approximately 1 m and is located from the center of the circumference of the guide 23 at a distance of 0.35 m in O ₂ .

With further movement of the wing, the rear bearing is completely released and the angle of attack of the wing holds the front bearing, position 3 ″. This happens when the wing moves from top to bottom.

Figure 4 shows how the angle of attack of the wing changes when it moves from the bottom up.

The lower guide 29 of the lever bearing 20 at a distance of 1.5 m from the central axis of the circle deviates from a horizontal position toward the guide 19 and approaches a distance of 0.25 m to it.

The front lever bearing fits the center axis of the circle, position 4 ′.

At this time, an additional guide 32 of the rear lever bearing is gripped, position 4 ″.

The wing, moving along the guide 19, pulls the rear lever bearing, position 5 ″, while the front lever bearing, position 5 ′, passes the gap between the guides.

When reaching the 6 ″ position with the rear lever bearing, the front lever bearing is gripped by the additional guide 33, position 6 ′.

When the front lever bearing takes position 7 ′, the rear lever bearing is gripped by rounding the upper guide 29, position 7 ″. With further movement of the wing, the front bearing is released. The radius of the rounded section of the guide 29 is approximately 0.7 m and the center is in O ₃ .

The wing, having reached the upper position, will continue to move under the control of the rear bearing, as shown in Fig.3.

The wing device is shown in Fig.9. Five ribs 15 are fixed on the wing pipe 14 with the help of special M8 screws. The ribs are made of aluminum alloy. Rib length 0.9 m, thickness 0.005 m, stiffener 0.005 m, rib thickness 0.003 m.

The ribs are connected by spars 16. The spars are made of aluminum alloy. The spar thickness is 0.005 m. The length of the spar is 2 m. The wing frame is covered with a special dense fabric.

The tube 14 of the wing 43 is made of a titanium alloy. The outer diameter of the pipe is 0.03 m, the inner diameter is 0.024 m, length 2.178 m.

On both sides, bronze inserts 17 are pressed into the pipe. FIG. 5. Bearings 180206 are pressed onto the ends of the pipe 14. The bearings and inserts are fixed with M4 set screws, two on each side of the bearing (not shown).

In the bronze inserts 17, spherical recesses are made from the outer ends, in which balls 18 are freely located. The diameter of the ball is slightly smaller than the diameter of the recess and is equal to 0.014 m. The recess is covered by a plate so that the ball does not fall out.

The ball is set so that when the pipe with the wing moves axially, there would be little braking about the guide 19, the gap between the balls and the guides 19 is 0.003 m on both sides.

At a distance of 0.048 m from the left edge of the pipe 14, a lever 20 of the angle of attack position is installed. The action of the lever 20 is described above.

From the left edge of the pipe 14 at a distance of 0.082 m is the bracket for attaching the pipe 14 to the belt 10, the lower part 25 of the bracket is shown.

At a distance of 0.112 m from the left edge of the pipe, the left extreme rib 15 of the wing is fixed. From the right edge of the wing pipe 14 at a distance of 0.035 m, there is a second bracket for attaching the pipe to the belt, the lower part 25 is shown.

At a distance of 0.066 m from the right end of the pipe 14, the extreme right rib 15 is fixed.

The wing tube 14 is attached to the toothed belts 10 using a split bracket, which is also a sliding bearing, shown in Fig.7.

The bracket consists of the upper half 45 and the lower part 25, which are connected using two M8 bolts.

The lower part 25 with two clamps 44 with a diameter of 0.006 and with M6 thread is attracted to the cable 34 of the belt 10. The diameter of the steel cable is 0.006 m. The belt is made of elastic plastic.

The width of the bracket is 0.025 m, the thickness of the upper part is 0.006 m, the base of the lower part 25 is 0.01 m.

Plastic bushings with a thickness of 0.002 m are installed in the bracket in order to ensure free rotation and movement of the pipe.

To ensure the movement of the wings, a timing belt 10 is used. See FIG. 7.

Belt pitch 0.08 m. The number of teeth on one belt is 229. Belt width is 0.025 m, thickness is 0.015 m. Depression Depth is 0.008 m.

The belts are driven by pulleys 9, Fig.6, Fig.12. The center distance between the pulleys is 6.0184 m. The pulleys are made of aluminum alloy.

The diameter of the pulley 9 along the projections is 2 m. The hub of the pulley with a diameter of 0.08 m, the inner diameter of 0.04 m, the length of the hub is 0.04 m. Eight spokes with a diameter of 0.0225 m. The rim is 0.031 m wide, the cross-section of the rim is 0.02 m, the depth of the depression is 0.008 m. The pulley 9 is mounted on the shaft 11 on the key.

The drive is carried out from two gas turbine engines 3, Fig 1, Fig 11. The torque is transmitted from the gas turbine engines 3 through gearboxes 5 to the steel shaft 39. The supports of the ends of the shaft 39 are the brackets 41 (Fig. 1).

On the shaft 39, with a diameter of 0.03 m and a length of 4.52 m, two drive sprockets 6 are mounted on the dowels from two sides. A double roller chain Pr-12.7-18.2 is used to transmit torque.

The drive sprocket 6 has a pitch diameter of 0.1255 m, steel, hardened. Number of teeth 31.

The maximum number of revolutions is 76 rpm. Linear speed of approximately 30 m / s.

Driven sprocket 7 is made of titanium, a crown of steel, hardened. The outer diameter of the hub is 0.08 m, the inner is 0.04 m, the length of the hub is 0.05 m. The width of the rim cross section is 0.0225 m, the height is 0.01 m. The height of the crown section is 0.015 m, the width is 0.0225 m. Eight spokes diameter 0.022 m. Number of teeth 247. Dividing diameter 0.9985 m.

The left engine 3 is engaged on the rear driven sprocket, and the right on the front driven sprocket. This is to ensure that the load on the upper and lower branches of the toothed belts is uniform. If one of the engines fails, the second will provide a smooth descent to the ground.

In the gearbox 35, power is taken to rotate the fan 4 through the shaft 37. Using the fan, the apparatus rotates in one direction or another, depending on the angle of rotation of the blades. The fan is attached to the cabin using pipes 46 (figure 1). 1 m diameter fan

The gearbox 35 has a dual gear that rotates two more gears. These two wheels through shafts and controlled couplings are connected to two gear wheels of the gearbox 36.

Depending on which clutch is engaged, the middle gear starts to rotate in one direction or another. Through the shaft 40 connected to this gear, the rotation is transmitted to the gear in the gearbox 38.

Further, through the gear set on the shaft 42, the rotation is transmitted to the worm gears 8.

Depending on where the shaft 42 rotates, the front of the installation rises or lowers relative to the cab.

The entire installation is lined with titanium sheet, 0.5 mm thick. The sheet is mounted on trusses, and front and rear on special corners. See figure 1.

The weight of the device.

2 farms - 130 kg. 2 farms - 207 kg

36 wing tubes - 91 kg. 2 titanium shafts - 51 kg.

180 ribs - 153 kg. 8 aluminum pulleys - 136 kg.

2 titanium stars - 43 kg. 16 spacer tubes - 46 kg.

Titanium sheet 60 square meters. m - 135 kg. 72 bearings - 20 kg.

Total - 1012 kg.

The approximate weight of the device is 1110 kg.

Lift and power.

When the wings move, the air flow is thrown down. The speed of movement of the wings is 60 m / s.

Therefore, the air velocity through the installation can reach 60 m per second.

According to the well-known formula, we calculate the lifting force.

F = C · ρ · S · ν ^2/2 = 1 24 · 1.29 · · 3600/2 = 55728 H

The resistance force is approximately equal to 20%. Equal 11145 H.

Required power.

Fv = 11145 * 60 = 668736 W.

Engines of 400 kW are required.

The flue gas reaction of running gas turbine engines will increase lift.

Moving forward will occur when the installation is tilted, i.e. the front part will be pulled to the cab. Tilt can be up to 10 degrees.

With an increase in the oncoming speed, the lifting force will increase, because will increase the speed of the wing to the free stream.

When using lighter materials for installation and increasing the speed of the wings, you can significantly increase the lifting force, because it grows in proportion to the square of the speed.

Claims (4)

1. The aircraft for vertical take-off and landing consists of a device for the movement of wings, a cabin, engines, a fan, characterized in that the device for movement of the wings consists of four trusses, which are formed from guides for guiding the movement of the bearings of the pipes of the wings, corners and strips; wings that have the ability to create air flow; toothed belts to which wings are attached; pulleys; two shafts on which the pulleys are mounted; leverage to control the angles of attack of the wings; guide bearings of levers welded to the right and left trusses; two driven sprockets and a sheet of fencing. 2. The aircraft of vertical take-off and landing according to claim 1 is characterized in that the wings of the device for moving wings have the ability to move in straight sections at the top and bottom, while the angle of attack of the wing does not change when moving in straight sections at the top and bottom. 3. The aircraft vertical take-off and landing according to claim 1, characterized in that the wings of the device for the movement of the wings have the ability to change the angle of attack when moving in a semicircle. 4. The aircraft of vertical take-off and landing according to claim 1 is characterized in that it has the ability to change the direction of air flow when changing the angle of inclination of the device for moving wings relative to the cockpit.

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