WO2020156018A1 - 低能耗高速飞行方法及其翼环机 - Google Patents

低能耗高速飞行方法及其翼环机 Download PDF

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Publication number
WO2020156018A1
WO2020156018A1 PCT/CN2020/000028 CN2020000028W WO2020156018A1 WO 2020156018 A1 WO2020156018 A1 WO 2020156018A1 CN 2020000028 W CN2020000028 W CN 2020000028W WO 2020156018 A1 WO2020156018 A1 WO 2020156018A1
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Prior art keywords
wing ring
wing
ring
telescopic
ring mechanism
Prior art date
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PCT/CN2020/000028
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English (en)
French (fr)
Inventor
罗琮贵
郑小燕
Original Assignee
罗琮贵
郑小燕
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Publication date
Application filed by 罗琮贵, 郑小燕 filed Critical 罗琮贵
Priority to EP20748862.8A priority Critical patent/EP3901029A4/en
Publication of WO2020156018A1 publication Critical patent/WO2020156018A1/zh
Priority to US17/391,574 priority patent/US20220153409A9/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
    • B64C39/062—Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/001—Flying saucers
    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
    • A63H27/00—Toy aircraft; Other flying toys
    • A63H27/02—Model aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
    • B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
    • B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C35/00—Flying-boats; Seaplanes
    • B64C35/001—Flying-boats; Seaplanes with means for increasing stability on the water
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C35/00—Flying-boats; Seaplanes
    • B64C35/008—Amphibious sea planes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D9/00—Adaptations of wind motors for special use; Combinations of wind motors with apparatus driven thereby; Wind motors specially adapted for installation in particular locations
    • F03D9/30—Wind motors specially adapted for installation in particular locations
    • F03D9/32—Wind motors specially adapted for installation in particular locations on moving objects, e.g. vehicles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/90—Mounting on supporting structures or systems
    • F05B2240/92—Mounting on supporting structures or systems on an airbourne structure
    • F05B2240/921—Mounting on supporting structures or systems on an airbourne structure kept aloft due to aerodynamic effects
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/72—Wind turbines with rotation axis in wind direction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/728—Onshore wind turbines
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
    • Y02P70/50—Manufacturing or production processes characterised by the final manufactured product

Definitions

  • the invention relates to a low-energy-consumption high-speed flight method and the related technical fields of wing-ring aircraft--technical fields such as wing-ring flying saucers, high-altitude power generating rings, and dish-shaped contra-pull flying suspensions.
  • the earliest high-altitude power generation ring could only tie the ground traction cable to the lower end of the wing ring machine close to the central axis. Only in this way can the wing ring mechanism be forced to recline, so that the ring surface of the wing ring is inclined to face the wind and realizes rotation. Although the horizontal rotation wing ring machine realizes the waist side cable, it must be equipped with vertical fins, otherwise the wing ring cannot rotate. If the vertical fins are not installed, how can the high-altitude power ring realize the waist-side tethering?
  • the existing dish-shaped anti-pull flying suspension can obtain horizontal thrust in the east-west direction only by changing the windward area of the opposing sides.
  • This is a way to obtain horizontal thrust for the wing-ring flying saucer, and it is also a low-energy high-speed flight method.
  • the specific method is to tilt the wing ring axially, so that the direction of the overall lift of the wing ring is tilted, so that part of the lift is converted into horizontal thrust, so that it can be realized under the premise of no jet engine and no deflection of the wing at all.
  • the present invention can be used in aircrafts and submarines (such as a dish-shaped submarine, or a single power generating ring or a double-body pair of power generating ring driven by ocean currents).
  • the so-called “axial tilt of the wing ring” means the overall deflection of the wing ring, rather than the deflection of a single wing inside the wing ring.
  • the so-called “overall lift of the wing ring” refers to the combined force of the lift generated by all the wings of the wing ring.
  • the wing ring of the wing ring flying saucer originally runs vertically, so the lift generated by all the wings of the wing ring forms a vertical upward force F (see Figure 19).
  • F vertical upward force
  • the central axis of the wing ring is inclined, the direction of the resultant force F will inevitably incline, so a horizontal component force F2 must be produced, which is the horizontal thrust.
  • the horizontal component F2 When the axial direction of the wing ring tends to the direction of the flying saucer, the horizontal component F2 will point forward to drive the flying saucer forward.
  • the horizontal component F2 When the axis of the wing ring is inclined to the rear of the flying saucer, the horizontal component F2 will point to the rear, which forces the flying saucer to brake and reverse. Since the wing ring can hover in the air, there is no risk of braking or reversing.
  • the horizontal component F2 When the axis of the wing ring tends to the left or right of the flying saucer's forward direction, the horizontal component F2 will point to the left or right, thereby driving the flying saucer to turn left or right.
  • the present invention provides an extremely economical, low-energy, low-noise high-speed flight method. This method is especially suitable for wing-ring flying saucers, so that large wing-ring flying saucers can be equipped with nearly a thousand large jet engines without any jet engines. Horizontal thrust!
  • the wing ring only needs to be deflected by 2° to obtain a horizontal thrust of 1422.22 tons (that is, 64,000 tons ⁇ 2 ⁇ 90), which is equivalent to the thrust of 102 Taihang turbofan 10 engines! If the deflection is 20°, the horizontal thrust will be as high as 14,220 tons, which is equivalent to installing 1020 turbofan 10 engines! (The thrust of the turbofan 10 is 132KN, about 14 tons)
  • the ring-shaped rail car in the vehicle-track coupling ring of the wing ring mechanism It is equivalent to running in a laboratory environment, the operating conditions are much higher than the test train, and it is a horizontal rigid ring.
  • the wheel set of the circular rail car is completely coupled with the track, and there is no possibility of derailment and rollover. Therefore, the existing The technical conditions are enough for the wing ring flying saucer to fly at high speed!
  • the wing ring flying saucer can completely replace the jet engine with an electric motor, a turboshaft engine or an internal combustion engine, and the wing ring mechanism is essentially equivalent to a ring-shaped high-speed rail with no carriage but a wing running on a ring track, so even if the turboshaft engine is used, its Energy efficiency is also much higher than that of traditional helicopters and jet airplanes. If electric motors and internal combustion engines are used, energy efficiency will be higher and energy consumption will be lower. Therefore, the present invention is not only a high-speed flight method, but also a low-energy high-speed flight method!
  • jet engines Since jet engines often account for about one-third of the total cost of aircraft, jet engines have a much shorter service life and much higher inspection and maintenance costs. Therefore, replacing jet engines with electric motors, internal combustion engines or turboshaft engines will not Greatly reduce the cost of aircraft and inspection and maintenance costs. Because the wing-ring flying saucer can take off and landing vertically and hover in the air, it does not need to spend a lot of airport construction and maintenance fees, so the overall operating cost of the wing-ring flying saucer will be much lower than that of traditional aircraft.
  • (1) Similarly, it can achieve forward, left and right turning and braking and reversing flight movements without the need of a jet engine. Compared with the sequential deflection of a single wing, the structure is simpler, and the deflection mechanism does not need to move in a circle with the wing ring. Conducive to the simplification of small wing-ring flying saucers (especially wing-ring flying saucers and flying saucer toys).
  • the high-altitude power generation ring and the contra-pull flying suspension can easily realize the waist-side cable connection, so that the operation of the wing ring to rotate in the wind becomes simple and easy.
  • the wing ring deflection device is composed of a telescopic device and a dynamic connecting device.
  • the telescopic device refers to a hydraulic telescopic rod, a pneumatic telescopic rod, a spiral telescopic rod, and a tooth A telescopic rod, a folding telescopic rod, an inflatable and contractible airbag or any other device that can reciprocately change the distance between its two ends.
  • the function of the telescopic device is to force the wing ring rotating device to deflect, deflect the wing ring originally parallel to the wind direction or the advancing direction, and face the wind or advancing direction with an inclined surface, so as to realize self-rotation or generate horizontal thrust.
  • the movable connection device can be arranged at one or more of the three positions of the two ends and the middle section of the telescopic device, specifically one, two, or three locations, and the rotating pair should be selected for each location.
  • Mobile pair, or other dynamic connection methods are all based on whether it can play the following two functions at the same time when combined with the telescopic device: one is to be able to transmit the thrust from the telescopic device enough to cause the deflection of the wing ring; the other is The mutual resistance caused by the change of the angle between the wing ring rotating device and the telescopic device can be avoided.
  • the movable connection device should be able to move, rotate, bend or other adaptive changes accordingly to avoid mechanical damage purpose.
  • the wing ring is the abbreviation of the ring-shaped wing wheel, which is a wing wheel that is connected and supported by a ring-shaped truss, such as ring-shaped rotor, ring-shaped wind wheel, ring-shaped gas wheel, ring-shaped water wheel and ring-shaped propeller Wait.
  • a ring-shaped truss such as ring-shaped rotor, ring-shaped wind wheel, ring-shaped gas wheel, ring-shaped water wheel and ring-shaped propeller Wait.
  • the wing ring rotating device has two parts that cannot be separated but can rotate relative to each other (the two rotate in opposite directions, or rotate asynchronously in the same direction, or one is stationary and the other rotates). Either only one is connected to one wing ring, or both are connected to one wing ring.
  • the wing ring rotating device In addition to the vehicle-rail coupling ring, the wing ring rotating device also has a non-wheel coupling ring.
  • the former completely relies on the wheels to achieve the three functions of load, driving and coupling, while the latter achieves these three functions without relying on the wheels completely or partly.
  • the wheel coupling ring is not impossible to wheel, nor can it only use the principle of electromagnetic or superconductivity.
  • the most typical non-wheel coupling ring has a magnetic levitation coupling ring and a magnetic drive coupling ring, that is, a device that relies on the principle of permanent magnet or electromagnetic repulsion or superconductivity to achieve one or both of the two functions of levitation and driving.
  • Either the rail ring or the frame ring of the vehicle rail coupling ring or the suspension coupling ring is fixedly connected with the wing ring to form a complete wing ring mechanism.
  • the part of one wing ring mechanism that does not rotate with the wing ring is connected with the other wing ring mechanism that does not rotate synchronously with the wing ring to form a wing ring mechanism with two wing rings. More details of the wing-ring mechanism can be found in Luo Conggui's technical patent specification and paper on the wing-ring machine.
  • Preferred solution 1 As in the general solution, the movable connection device is located at any two or three of the two ends and the middle section of the telescopic device.
  • the movable connection device belongs to or includes a rotating pair, a moving pair or a bendable device.
  • the bendable device must be able to replace the function of the kinematic pair.
  • Preferred solution 3 As in preferred solution 2, the rotating pair allows the telescopic device or the wing ring rotating device to deflect or swing in more than two directions.
  • Preferred solution four as in preferred solution two, the moving pair can allow the telescopic device to move in the horizontal direction (here it is assumed that the ring surface is in a horizontal state before the wing ring is deflected).
  • the cross section of the ring track of the wing ring rotating device is a concave trapezoid or a convex trapezoid
  • the wheel circumference of the coupled wheel that is, the rolling surface in contact with the rail
  • the wing ring rotating device has a set of wheels arranged in a magenta shape, and the wheels of the mignon array surround the track from three directions and are coupled with it.
  • the fringe-shaped opening can face the outside of the circle (as shown in Figs. 15 and 16), or it can face the inside of the circle.
  • the present invention is used to start the telescopic device after rising to a predetermined height to deflect the wing ring as a whole so that the wing ring can be inclined to face the wind, so as to rotate by the wind.
  • This is an aircraft or submarine that uses a wing ring mechanism as a lift device.
  • the wing ring mechanism is the "a kind of wing ring mechanism" mentioned above, or any other type that can make the wing ring deflect Wing ring mechanism.
  • a wing-ring flying saucer with an outer ring cabin is essentially a ground-effect aircraft. It can fly close to the level and take off and land vertically. It is very convenient for surface takeoff and landing. As long as waterproof measures are taken, it can float and snorkel, which is very convenient.
  • One of the preferred solutions such as the overall solution, with a circular nacelle, a dish-shaped nacelle, a net-shaped nacelle, a cross-shaped nacelle, a radial nacelle, or other types of nacelles.
  • Radial nacelle refers to a nacelle that runs parallel to or overlaps the diameter or radius of the wing ring or wing ring rotating device.
  • the net-shaped nacelle is composed of two radial nacelles with different directions. The number of radial nacelles in each direction is greater than one.
  • the "intersection" includes two ways of intersecting vertically or non-vertically. The net-shaped nacelle and the radial nacelle are not only conducive to the vertical airflow, but also the weight of the flying saucer, and the construction of an open high-altitude platform.
  • the wing ring mechanism is connected to the upper end of the rope, and the lower end of the cable is connected to the ground connection point.
  • the wing ring mechanism is the "a kind of wing ring mechanism" mentioned above,
  • the upper end of the cable is connected to a part on the side of the wing ring mechanism that does not rotate with the wing ring.
  • An aerostat refers to a device or object that has no support or engine but can be suspended in the air.
  • the upper end of the cable can be connected to the side of the wing ring aircraft or the wing ring flying saucer (as shown in Figure 3, Figure 4, and Figure 5) ). Therefore, only one remote control device needs to be configured, and the telescopic device can be remotely activated after the wing ring aircraft or flying saucer rises to a predetermined height to make the wing ring deflect (tilt) as a whole, so that the wing ring rotates obliquely toward the wind.
  • the high-altitude power generation loop can operate in high-altitude or low-altitude wind like the previous high-altitude power generation loop, and the best operating position is the high-altitude stratosphere.
  • the invention has the advantages that no vertical fins and a single fin deflection mechanism are required, so that the cable can be connected to the side of the power generating ring, thereby greatly increasing the convenience of operation.
  • the connecting body that can prevent the two from separating from each other is a cable, a connecting rod or a bracket, and the number of cables, connecting rods or brackets is not less than 2, and there are at least two cables and two connecting bodies.
  • Rods or two brackets, their upper ends are respectively connected to both sides of the central axis of the aerostat or aircraft in the upwind layer (instead of focusing on the central axis position), and the lower ends of the two cables are respectively connected to the downwind layer Both sides of the central axis of the aerostat or aircraft (instead of focusing on the central axis).
  • the contra-pull flying suspension is a pure wind-driven aircraft, which can be used at high altitude for many years without the use of high-altitude hedging wind group upper and lower wind layers (such as stratospheric east wind layer and westerly layer).
  • Fixed-point hovering or free cruising, and high-altitude wind power can be used to generate electricity stably during hovering or cruising.
  • the wing ring mechanism or wing ring flying saucer used as aerostats for both or one of the two sides of the pull after rising to the east or west wind layer of the set height, only need to directly activate the telescopic device to deflect the wing ring to make the wing
  • the ring faces the wind obliquely, and then the power input to the motor can be stopped, the wind will drive the wing ring to rotate to continue to maintain lift, and the rotating wing ring can be used to push the motor to continue to rotate and output current.
  • the wing ring mechanism or wing ring flying saucer of the present invention when the wing ring changes from active rotation to wind-driven rotation, there is no need to install and activate vertical fins, nor to deflect the axis of the whole machine ( Therefore, the cabin of the wing-ring flying saucer can always be kept horizontal), so the overall structure and operating procedures have been greatly simplified, and the flight stability has been enhanced.
  • the horizontal thrust in the north-south direction can be obtained, without installing and starting any engine that provides thrust in the north-south direction, it can realize free cruising in all directions, and at the same time increase the strength of the connecting body. And the flight stability of the aerostat or aircraft in two different wind layers.
  • the high-altitude power generation ring in the east wind layer has at least one wing ring to the southeast, and the high-altitude power generation ring in the westerly layer has at least one wing ring to the southwest, so You can get the resultant force pointing north, which is the horizontal thrust of the whole machine to the north.
  • the whole machine On the basis of obtaining the driving force in the north-south direction, if the pulling force of the east and the west is balanced, the whole machine must cruise in the direction of true south or true north; if the pulling force of the east and west is unbalanced and the power in the north-south direction is comprehensively controlled, The whole machine must cruise in the southeast, southwest, northeast, northwest and other directions. Therefore, this machine can realize free cruising in all directions.
  • Figure 1 A schematic diagram of the structure of a wing ring mechanism (side view)
  • Figure 2 A schematic diagram of the structure of a wing ring mechanism (top view)
  • Figure 3 Schematic diagram of a high-altitude power generation ring (side view)
  • Figure 4 Schematic diagram of a high-altitude power generation ring (side view)
  • Figure 5 A schematic diagram of the structure of a telescopic flying suspension (side view)
  • Figure 6 A schematic diagram of the structure of a telescopic flying suspension (top view)
  • Figure 7 A schematic diagram of the structure of a wing-ring flying saucer (top view)
  • Figure 8 A schematic diagram of the structure of a wing ring flying saucer (side view)
  • Figure 9 A schematic diagram of the structure of a wing-ring flying saucer (top view)
  • Figure 10 A schematic diagram of the structure of a wing-ring flying saucer (top view)
  • Figure 11 A schematic diagram of the structure of a wing ring flying saucer (side view)
  • Figure 12 A cross-sectional view of a wing-ring flying saucer (cut along the diameter of the flying saucer)
  • Figure 13 A schematic diagram of the structure of a wing ring flying saucer (side view)
  • Figure 14 A schematic diagram of the structure of a wing ring flying saucer (side view)
  • Figure 15 A partial close-up view of a rail coupling ring with a pin-shaped wheel set
  • Figure 16 A cross-sectional view of a coupled wheel and rail
  • Figure 17 A cross-sectional view of a coupled wheel and rail
  • Figure 18 A cross-sectional view of a coupled wheel and rail
  • Figure 19 The schematic diagram of the horizontal thrust generated by the deflection of the wing ring (side view diagram)
  • 1 Wing ring mechanism; 1-1: Wing ring; 1-2: Vehicle-rail coupling ring; 1-3: Wing; 1-4: Wing support; 1-5: Motor; 1-6: Wheel; 1-7: Wheel frame; 1-8: Frame ring; 1-9: Track ring; 2: Wing ring deflection device; 2-1: Rotating pair; 2-2: Telescopic rod; 3: Cable tie point; 4 : Cable; 5: moving pair; 6: moving pair; 7: axial section of wheel; 8: cross section of rail; 9: central nacelle; 9-1: radial section of central nacelle; 10: outer ring nacelle; 10-1: radial section of the outer ring nacelle; 11: radial nacelle; 11-1: radial section of the radial nacelle.
  • This example is a wing ring mechanism composed of two upper and lower wing ring mechanisms 1.
  • Each wing ring mechanism 1 in FIG. 2 includes the wing ring 1-1 and the rail coupling ring 1-2 shown in FIG. 1.
  • Each wing ring deflection device 2 of FIG. 2 includes the telescopic rod 2-2 shown in FIG. 1 and two rotating pairs 2-1 at both ends thereof.
  • each rotating pair 2-1 must allow the configured telescopic rod 2-2 to swing in two mutually perpendicular directions, and one of the directions coincides with the diameter of the wing ring.
  • each telescopic rod 2-2 needs to be provided with a remote control switch, so that they can be remotely controlled to make a telescopic action in time and control the length of their extension.
  • the rail coupling ring 1-2 in this example can also be replaced by a magnetic levitation coupling ring or other types of wing ring rotating devices (the same in all the following examples).
  • Each wing ring mechanism 1 in Figure 3 and Figure 4 is the same as the wing ring mechanism 1 in Figure 1, including a wing ring 1-1 and a rail coupling ring 1-2.
  • This example is based on the first example. Set as follows:
  • a number of motors that can freely switch to electric mode or power generation mode are respectively provided for the two vehicle-rail coupling rings 1-2, all the motors are in a circular array, and each motor is powered by a wheel.
  • the cable tethering point 3 is set at any part of the telescopic rod 2-2 that will not be telescopic, and then the lower end of the cable 4 is connected to the ground tethering point.
  • a cable is arranged in the cable 4, and the upper end of the cable is electrically connected to the motor.
  • a wing angle of attack deflection device is also provided for each wing.
  • How to use this high-altitude power generating ring first transmit electricity to the motor, so that it drives the wing ring to rotate, leading the entire aircraft to the sky. After reaching the set height, first remotely control the remaining three telescopic rods 2-2 to extend, so that the two wing rings are deflected as a whole, with the ring surface obliquely facing the wind (as shown in Figure 4), while controlling the wing angle of the lower wing ring to deflect The device adjusts the angle of attack of all fins to a negative value (if the original angle of attack is a°, then adjust it to -a°), so that the wind naturally drives its rotation. Then cut off the power and let the high-altitude strong wind drive the wing ring to rotate, thereby maintaining the lift and driving the generator to generate electricity.
  • the extension length of the telescopic rod 2-2 should be set as follows: the telescopic rod 2-2 provided with the cable tie point 3 should not extend at all, and even the telescopic device can be replaced by an ordinary connecting rod. Assuming that the extension length of the telescopic rod 2-2 in the same radial direction is L, the extension length of the other two telescopic rods 2-2 in the vertical radial direction should be half of L.
  • Two high-altitude power generation loops are activated successively, so that they respectively enter the easterly layer and the westerly layer of the stratosphere (or the easterly layer and the westerly layer on the top of the trade wind belt). After they pull the rope in the opposite wind direction, start the operation method described in Example 2 so that the two forms are as shown in Figure 5.
  • the opening angle of the two By adjusting the opening angle of the two, the pulling force of the east and west sides can be adjusted. When the tension of the two sides reaches a balance, the whole machine will hover. When the pulling force of the two sides is out of balance, the whole machine will cruise east or west.
  • the advantage of this example is that it can generate power pointing in the north-south direction, so that it does not need to deflect individual fins in turn to achieve true free cruising in all directions.
  • the telescopic rod 2-2 with the cable tie point 3 in the third example can be replaced by an ordinary connecting rod without telescopic function, but this example cannot, otherwise the wing ring will not be able to deflect to the north and south sides.
  • each wing ring mechanism 1 includes a set of wing ring 1-1 and rail coupling ring 1-2 at the corresponding position in Fig. 1.
  • the outer ring nacelle 10 is first added to make it a wing ring flying saucer, and as shown in Figure 7, the outer ring nacelle 10 is connected to the wing ring rotating device 2 through the moving pair 5 (that is, As shown in Figure 8, it is connected to the telescopic device 2-2 of the wing ring rotating device 2). It can be seen that there must be a dynamic connection between the wing ring deflection device 2 and the outer ring nacelle 10, which is different from the first example.
  • the flying saucer only needs the horizontal thrust of forward or backward, all rotating pairs 2-1 only need to be able to deflect forward and backward. If you need to turn left and right, then all the turning pairs 2-1 must also be able to deflect to the left and right. If it is necessary to directly extend and retract the left and right telescopic rods 2-2 without adaptive adjustment of the front and rear telescopic rods 2-2, then the rotating pair 2-1 cannot only deflect around two mutually perpendicular axial directions, but must be able to rotate around. More axial deflection (preferably a universal rotating pair like a bowl bearing).
  • any two telescopic rods 2-2 with opposite telescopic directions and opposite up and down positions can also be combined into one.
  • both ends must move synchronously (when one end extends a certain length, the other end must retract the same length) , But when set up in this way, it is necessary to reserve enough retraction space for both ends, otherwise the two ends must be mutually restricted and cannot be extended or cannot be extended enough.
  • Example 5 adjust the front, back, left, and right of the wing-ring flying saucer to the orientation shown in Figure 10.
  • Example 5 The biggest difference between this example and Example 5 and Example 6 is that the wing ring deflection device 2 forms a fixed connection with the nacelle, and there is no relative movement between the two, and any two telescopic rods with opposite telescopic directions and opposite up and down positions 2 It is impossible for 2 to become one unit or remain on the same axis at all times as in Example 5 and Example 6.
  • any telescopic rod 2-2 makes a telescopic action, it will inevitably swing, so the setting of the rotating pair must be adapted to its swing requirements (as shown in Figure 14).
  • Example 8 The matters that must be paid attention to when setting the rotating pair 2-1 in this example and the above examples can be seen in Example 8.
  • the number of telescopic rods 2-2 is not more than 4. However, if the diameter of the wing ring mechanism is larger, more telescopic rods 2-2 need to be added to provide the thrust and stability required for wing ring deflection. After the extension rods 2-2 are added, all the extension rods 2-2 are preferably still in a circular array. For any additional telescopic rods 2-2, their respective extension lengths are equal to half of the sum of the extension lengths of the two telescopic rods 2-2 that are closest to both sides on the same circumferential line. As for the setting of the movable connecting device, it is more complicated. Examples 1 and 5 are involved respectively. Here, we only take the setting of the rotating pair as an example.
  • the number of telescopic rods 2-2 is greater than or less than 4, and assuming that the number of telescopic devices is N, then, when N is a singular number, the number of deflectable axes of the rotating pair (or combination of rotating pair) configured for each telescopic device It should not be less than N (because the telescopic device needs to swing in N directions); when N is an even number, the number of deflectable axes of the rotating pair (or combination of rotating pair) configured for each telescopic device should not be less than N ⁇ 2 (The telescopic device only needs to swing in N ⁇ 2 directions). Only when N is 2, the situation is special.
  • the swing directions of two telescopic devices are the same or parallel, then the number of pivotable axes of the rotating pair (or combination of rotating pair) configured for each telescopic device only needs to be not less than 1; If the swing directions of the two telescopic devices are intersecting (for example, the two telescopic devices alternately expand and contract instead of synchronously), then the number of deflectable axes of each telescopic device configuration rotating pair (or rotating pair combination) should not be less than 2.
  • the wing ring flying saucer must have horizontal thrust in four directions: forward, backward, and left and right turning. Therefore, the wing ring mechanism must have at least 3 telescopic devices. However, except for particularly small flying saucers such as toys or airplane models, the telescopic devices should be 4 The above is appropriate, because 4 can facilitate the operation of the thrust in the four directions, and 4 telescopic devices can ensure the power and stability required for the deflection of the wing ring, and the four telescopic devices are preferably in a circular array, so each of them The rotating pair must be able to reciprocate around two mutually perpendicular axes.
  • wing ring flying saucers require more than 6 telescopic devices for their wing ring mechanism due to their larger diameters. The actual number is sufficient to ensure the driving force and stability required for wing ring deflection.
  • Example 1 to Example 7 the vehicle-rail coupling ring is modified as follows: as shown in Figure 15 and Figure 16, the wheel set is changed to a wheel set in a fringe-shaped arrangement, and the wheels in the fringe-shaped array are surrounded in three directions
  • the track is coupled with it, and the opening of the square shape can be left or right, but it is not convenient to go up or down.
  • Example 1 to Example 7 modify the vehicle-rail coupling ring 1-2.
  • the wing ring mechanism 1 in Examples 2 to 7 includes a rail coupling ring 1-2 and a wing ring 1-1 (such as the rail coupling ring 1-2 and the wing ring 1-1 in Figure 1 of Example 1).
  • the specific modification is to replace the circular track in the vehicle-rail coupling ring with a trapezoidal or convex trapezoidal track with a concave cross section, and the wheels are correspondingly replaced with a wheel circumference (that is, the rolling surface in contact with the rail) that is convex.
  • Raised trapezoid or recessed trapezoid (rails and wheels as shown in Figure 17, Figure 18).
  • the advantage of this example is that only one wheel is needed on a section to realize coupling and torque transmission.
  • the structure is simple, the cost is low, and the dead weight is small. It is especially suitable for smaller flying saucers, especially toy flying saucer airplanes.
  • Example 5 On the basis of Example 5, Example 6, and Example 7, waterproof measures should be taken to prevent the wing-ring flying saucer from sinking when it is landing on the water. It is also possible to add airbags with the same shape as the projection shape of the nacelle at the bottom of each nacelle of the flying saucer, and to equip the airbag with rapid inflation and extraction devices to increase buoyancy when the load is too heavy.

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Abstract

一种低能耗高速飞行方法、采用该方法的翼环机构（1）、翼环飞碟、以及采用翼环机构的高空发电环和对拉飞悬机。该飞行方法使翼环飞碟的翼环（1-1）轴向倾斜，从而使翼环整体升力的指向发生倾斜，获得水平推力。该翼环机构具有翼环、翼环旋转装置和翼环偏转装置（2），翼环偏转装置由伸缩装置和动连接装置组成。该翼环飞碟以翼环机构为升力装置。该高空发电环具有翼环机构和缆绳（4），翼环机构连接缆绳上端，缆绳下端连接于地面拴接点，缆绳上端连接到所述翼环机构侧边的不随翼环旋转的部位。该对拉飞悬机采用两个或两组浮空器或航空器分别处于两个风向相反的风层中，两者之间通过任一种能够防止两者相互脱离的连接体相互连接。

Description

低能耗高速飞行方法及其翼环机 技术领域
本发明涉及一种低能耗高速飞行方法及其相关翼环机技术领域——翼环飞碟、高空发电环和碟状对拉飞悬机等技术领域。
背景技术和技术问题
过去，一切航空器都不可能低能耗地高速飞行，而人类的一切碟状航空器(包括翼环飞碟)如不配置喷气发动机，就只能缓慢飞行，即使配置了喷气发动机，航速也难以超过直升机，根本不可望喷气式固定翼飞机之项背。依次偏转翼片的方法可以获得巨大水平推力，但需要给翼环的每个翼片配置偏转装置(详见罗琮贵的WO/2019/033691和CN110282133A)，这对小型翼环飞碟(尤其飞碟航模玩具)就过于复杂和昂贵。如果完全不配置喷气发动机、完全不偏转翼片，那么翼环飞碟如何才能低能耗、低噪音地高速飞行？
最早的高空发电环只能将地面牵引缆系于翼环机下端靠近中轴线之处，只有这样才能迫使翼环机构后仰，从而使翼环环面斜向迎风，实现自转。而水平自转翼环机虽然实现了腰侧系缆，但必须加装竖向翼片，否则翼环无法自转。如果不加装竖向翼片，那么高空发电环如何才能实现腰侧系缆？
现有碟状对拉飞悬机只需改变对拉双方的迎风面积，就能获得东西方向水平推力，但要获得南北方向的驱动力，就需要依次偏转翼片或加装水平动力装置。如果不偏转单个翼片，也不加装水平推力装置，翼环飞碟如何获得南北方向的驱动力？
如下技术方案可以完全解决上述技术难题。
技术方案
一、“一种低能耗高速飞行方法”技术方案：
总体方案：这是使翼环飞碟获得水平推力的方法，也是一种低能耗高速飞行方法。具体方法是：使翼环轴向倾斜，从而使翼环整体升力的指向发生倾斜，从而使升力中的一部分转化为水平推力，从而在完全不配置喷气发动机、完全不偏转翼片的前提下实现低能耗、低噪音的高速飞行。本发明可用于航空器，也可用于潜航器(比如碟状潜艇，又如以洋流驱动发 电的单体发电环或双体对拉发电环)。
此所谓“翼环轴向倾斜”，也就是翼环整体偏转，而不是翼环内部单个翼片的偏转。此所谓“翼环整体升力”，指该翼环全部翼片所产生的升力的合力。
技术原理：
翼环飞碟的翼环原本中轴线是垂直走向，因此翼环全部翼片所产生的升力形成一个垂直向上的合力F(见于图19)。当翼环中轴线倾斜，合力F的指向必然随之倾斜，因此必然产生一个水平方向的分力F2，这个分力就是水平推力。
当翼环的轴向倾向于飞碟前进方向，水平方向的分力F2就会指向前方，从而驱使飞碟前进。当翼环的轴向倾向于飞碟的后方，水平方向的分力F2就会指向后方，从而迫使飞碟刹车、倒车，由于翼环飞碟可以空中悬停，因此刹车、倒车不存在任何危险性。当翼环的轴向倾向于飞碟前进方向的左侧或右侧，水平方向的分力F2就会指向左侧或右侧，从而驱使飞碟左转弯或右转弯。
本发明提供了一种极为经济的低能耗、低噪音的高速飞行方法，这种方法尤其适用于翼环飞碟，使大型翼环飞碟无需配置任何喷气发动机，就能具备近千台大型喷气发动机的水平推力！
比如一个配置有100付安225翼片的飞碟，其理论最大升力为：
100付×640吨/付＝6.4(万吨)。
显然，当翼环轴向偏转90°(即从垂直变为水平)，其本来垂直向上的升力就全部转化为水平推力。
因此，翼环每偏转1°，就会有1/90的升力转化为水平推力。
因此，翼环只需偏转2°，就能得到水平推力1422.22吨(即6.4万吨×2÷90)，相当于102个太行涡扇10发动机的推力！如果偏转20°，水平推力就会高达1.422万吨，相当于额外安装了1020个涡扇10发动机！(涡扇10的推力为132KN，约为14吨)
显然，任何现有航空器都不可能安装成百上千个航空发动机，即使全部升力都用来搭载发动机也不可能！
由于翼环飞碟的环状动力系统中的所有发动机皆推动同一个刚性环体旋转，不需要保证同一时间里全部发动机同步正常工作，即使大部分发动机不能正常工作，其最大恶果也仅限于翼环转速变慢，升力和飞行速度下降而已，启动冗余发动机即可。如果需要，翼环飞碟只需设置动力切断装置，就能在全部发动机皆遭遇故障停车时马上转换为自转旋翼机模式，从而确保缓慢安全降落。
由于大型客机和大型运输机的标准起飞空速是268.54公里～287.06公里/小时，因此只要 大型翼环上的机翼线速度达此空速，翼环飞碟就能平稳起飞，只要能平稳起飞，当翼环偏转、升力指向倾斜，就必然得到足以使飞碟高速飞行的水平推力。目前，中国京沪高铁最高运行速度已达486.1公里/小时，中国南车研制的500公里试验列车的最高试验时速已达到605公里/小时，而翼环机构的车轨耦合环中的环状轨道车相当于在实验室环境中运行，运行条件远远高于试验列车，而且是一个水平状态的刚体环，环状轨道车的轮组与轨道完全耦合，不存在脱轨翻车的可能性，因此现有技术条件足以让翼环飞碟高速飞行！
由于翼环飞碟能完全以电动机、涡轴发动机或内燃机取代喷气发动机，而翼环机构旋转时实质相当于一列没有车箱却有机翼的环形高铁在环形轨道上奔驰，因此即使采用涡轴发动机，其能效也远高于传统直升机和喷气式飞机，如果采用电动机和内燃机，则能效更高、能耗更低，因此本发明不仅是高速飞行方法，而且是低能耗高速飞行方法！
由于喷气发动机往往占飞机总造价的三分之一左右，而喷气发动机相比之下使用寿命短得多，检测、维修费用却高得多，因此以电动机、内燃机或涡轴发动机取代喷气发动机会极大地降低航空器的造价和检测、维修费用。由于翼环飞碟能够垂直起降、空中悬停，不需要耗费大笔机场建设费、维护费，因此翼环飞碟的整体运营费用会远远低于传统飞机。
技术效果：
(一)同样完全无需配置喷气发动机，就能实现前进、左右转弯和刹车倒车等飞行动作，而且与单个翼片依次偏转相比结构更简单，而且偏转机构无需随同翼环作圆周运动，更有利于小型翼环飞碟(尤其翼环飞碟航模和飞碟玩具)的简化。
(二)同样能够产生巨大的水平推力，使大型翼环飞碟实现低能耗、低噪音高速飞行！
(三)由于不偏转翼片，翼环形态始终不变，陀螺效应更强，抗强风防倾覆能力更强。
(四)由于低能耗、低噪音并且抗强风防倾覆，因此此种飞碟是未来城市交通的最佳选择。
(五)使高空发电环和对拉飞悬机能够简易地实现腰侧接缆，从而使翼环迎风自转的操作变得简单易行。
二、“一种翼环机构”技术方案
总体方案：具有翼环、翼环旋转装置和翼环偏转装置，所述翼环偏转装置由伸缩装置和动连接装置组成，所述伸缩装置指液压伸缩杆、气压伸缩杆、螺旋伸缩杆、齿条伸缩杆、折叠伸缩杆、可膨胀收缩的气囊或其他任何一种能够往复改变其自身两端之间的距离的装置。
所述伸缩装置的作用是迫使翼环旋转装置偏转，使原本平行于风向或前进方向的翼环偏 转而以斜面朝向风向或前进方向，从而实现自转或产生水平推力。
所述动连接装置可设置于所述伸缩装置的两端和中段这三处位置中的一处或两处以上，具体应是一处、两处或三处，并且各处具体应选用转动副、移动副或其他动连接方式，均以其与伸缩装置组合后能否同时起到如下两个作用为取舍标准：其一是能够传递伸缩装置发出的足以造成翼环偏转的推力；其二是能够避免翼环旋转装置与伸缩装置相互夹角改变而引起的相互抵抗。当所述伸缩装置发生伸缩运动而使翼环和翼环旋转装置的轴向发生偏转，所述动连接装置应能随之发生移动、转动、弯折或其他适应性变化，达到避免机械损伤的目的。
所述翼环，是环状翼轮的简称，是以环状桁架连接、支撑翼片的翼轮，比如环状旋翼、环状风轮、环状气轮、环状水轮和环状螺旋桨等。
所述翼环旋转装置具有不能分离却能相对旋转运动的两部分(此两者或者朝相反方向旋转，或者朝同一方向不同步旋转，或者一者静止不动，另一者旋转)，此两者或者仅一者与一个翼环连接，或者两都各与一个翼环连接。
翼环旋转装置除了车轨耦合环，还有非轮耦合环，前者完全依靠车轮实现负重、驱动及耦合连接三功能，而后者实现此三个功能却完全地或部分地不依靠车轮，因此非轮耦合环并非不能轮，也并非只能利用电磁原理或超导原理。最典型的非轮耦合环有磁悬浮耦合环和磁驱动耦合环，也就是依靠永磁或电磁的两极相斥原理或超导原理实现悬浮、驱动两功能中的一种或两种的装置。
车轨耦合环或悬浮耦合环的轨道环和车架环两者中任一者与翼环作固定连接皆可构成一个完整的翼环机构。一个翼环机构的不随翼环旋转的部位与另一个翼环机构的不随翼环同步旋转的连接，即组成一个具有两个翼环的翼环机构。翼环机构的更多详情可见于罗琮贵发表的翼环机技术专利说明书和论文。
优选方案一：如总方案，所述动连接装置处于所述伸缩装置的两端和中段这三处中的任意两处或三处。
优选方案二：如总方案，所述动连接装置属于或包含有转动副、移动副或可弯折装置。可弯折装置必须能够取代所述运动副的作用。
优选方案三：如优选方案二，所述转动副允许伸缩装置或翼环旋转装置向两个以上方向偏转或摆动。
优选方案四：如优选方案二，所述移动副能允许伸缩装置在水平方向上移动(这里假设翼环未发生偏转前环面处于水平状态)。
优选方案五：如总方案，所述翼环旋转装置的环形轨道的横截面呈凹陷的梯形或凸起的梯形，而与之相耦合的车轮的轮周(即是与轨道接触的滚压面)则相应地呈凸起的梯形或凹 陷的梯形(如图17或图18所示)。
本方案的优点是使车轨耦合环结构简单、成本低、自重小，特别适用于较小型的飞碟，尤其是玩具类飞碟航模。
优选方案五：如总方案，所述翼环旋转装置中具有品字形排列的车轮组，品字形阵列的车轮从三个方向包围轨道而与之相耦合。所述品字形的开口可以朝向圆外(如图15和图16)，也可以朝向圆内。
技术原理：
(一)之所以能使翼环飞碟前进、转弯或倒退，其原理可见于本文“一种低能耗高速飞行方法”技术方案之“技术原理”。
(二)高空发电环、对拉飞悬机利用本发明，在上升到预定高度后再启动伸缩装置，使翼环整体偏转从而使翼环得以斜向迎风，从而在风力推动下自转。
有益效果：
详见于本文“一种低能耗高速飞行方法技术方案”之“有益效果”。
三、“一种翼环飞碟”技术方案：
总体方案：这是一种以翼环机构为升力装置的航空器或潜航器，所述翼环机构是前文所述的“一种翼环机构”，或是其他任一种能够使其翼环偏转的翼环机构。
有外环机舱的翼环飞碟实质也是一种地效飞行器，能够贴近水平飞行，又能垂直起降，十分便于水面起降，只要做好防水措施，就能浮游和潜航，是一种十分便利的空中、水面、水下三栖交通运输工具。
优选方案之一：如总体方案，具有环状机舱、碟状机舱、网状机舱、十字形机舱、径向机舱或其他类型的机舱。
径向机舱，指舱体走向平行于或重叠于翼环或翼环旋转装置的直径或半径的机舱。网状机舱，由两种走向不同的径向机舱交叉组成，每种走向的径向机舱的数量都大于1。所述“交叉”，包括垂直相交或不垂直相交两种交叉方式。网状机舱和径向机舱既有利于垂直方向气流通过，又有利于飞碟轻量化，并有利于构建开放性高空平台。
四、“一种高空发电环”技术方案：
这是一种高空风力发电装置，具有翼环机构和缆绳，翼环机构连接绳缆上端，缆绳下端连接于地面拴接点，所述翼环机构是前文所述的“一种翼环机构”，所述缆绳上端连接到所述翼环机构侧边的不随翼环旋转的部位。
浮空器，指自身既无支撑物，又无发动机，却能够悬浮在空中的装置或物体。
由于采用前文所述的“一种翼环机构”和“一种翼环飞碟”，因此缆绳上端可以连接到翼环机或翼环飞碟的侧边(如图3、图4、图5所示)。也因此只需要配置一个遥控装置，就可以在翼环机或飞碟升到预定高度后遥控启动伸缩装置伸长，使翼环整体偏转(倾侧)，从而使翼环斜向迎风自转。
所述高空发电环和先前的高空发电环一样可以运行于高空或低空的风中，最佳运行位置是高空平流层。
本发明的优点在于无须加装竖向翼片，也无需加装单个翼片的偏转机构，就能让缆绳连接到发电环的侧边，从而大大增加运行的便利性。
五、“一种对拉飞悬机”技术方案：
总体方案：两个或两组浮空器或航空器分别处于两个风向相反的风层中，两者之间通过任一种能够防止两者相互脱离的连接体(如缆绳、连杆或支架等)相互连接，所述两者中最少有一者属于前文所述的“一种翼环机构”或前文所述的“一种翼环飞碟”。
优选方案一：如总方案，所述能够防止两者相互脱离的连接体是缆绳、连杆或支架，缆绳、连杆或支架的数量不小于2，并且其中最少有两条缆绳、两根连杆或两个支架，它们的上端分别连接到处于上风层的浮空器或航空器的中轴线的两侧(而不是集中于中轴线位置)，这两条缆绳的下端分别连接到处于下风层的浮空器或航空器的中轴线的两侧(而不是集中于中轴线位置)。
有益效果和技术原理：
对拉飞悬机是一种纯风力航空器，可以在不配置动力装置的情况下仅凭高空对冲风组上下风层(比如平流层东风层和西风层)的风力对拉就可以长年在高空定点悬停或自由巡航，并且在悬停或巡航过程中可以利用高空风力平稳发电。本发明中作为对拉双方或其中一方浮空器的翼环机构或翼环飞碟，上升到设定高度的东风层或西风层后只需直接启动其伸缩装置使翼环偏转，就能使翼环斜向迎风，然后就可以停止向电机输入电源，转由风力驱动翼环自转而继续维持升力，并利用自转的翼环推动电机继续旋转而输出电流。
本发明中的翼环机构或翼环飞碟，它们的翼环在从主动旋转变为风力驱动旋转的过程中，既不需要加装和启用竖向翼片，也不需要偏转整机的轴线(因而翼环飞碟的机舱能始终保持水平状态)，因此整机结构和操作程序都得到较大简化，飞行稳定性也得到加强。
尤其是优选方案，仅通过调整翼环斜面的朝向，就能获得南北方向的水平推力，无需安 装和启动任何提供南北方向推力的引擎就能够实现八方自由巡航，同时也增加了连接体的强度，以及分处于两个不同风层中的浮空器或航空器的飞行稳定性。
和此前的各种对拉飞悬机一样，只需调整对拉双方的迎风面积，本方案的对拉飞悬机就能得到东西方向的水平推力，不同的是，本方案只需调整对拉双方翼环的环面与水平面的夹角，就能使双方承受到不同的风压，整机就会随受到较大风压的一方的风向运动。
获得南北方向的水平推力的方法和原理详见于“实施例”例四之“本例使用方法和原理”。只要调整整机所承受的东西方向和南北方向的力，就能使整机(两个浮空器的组合体)向任何方向自由航行。
本例使用方法和原理(如图6)：
通过控制伸缩杆2-2使处于东风层的高空发电环最少有一个翼环的环面倾向于东南方向，使处于西风层的高空发电环最少有一个翼环的环面倾向于西南方向，这样就能得到指向北方的合力，这就是整机向北的水平推力。
本来，当两方的翼环都倾向于南方，风力会给两个发电环造成两个方向相反的扭矩，使北侧缆绳拴接点产生向后行的趋势，但是，由于南北两条缆绳是时刻绷紧的，北侧的两个缆绳拴接点通过北侧缆绳相互对拉，从而相互抵消了向后行的扭矩，因此两个发电环各自的两个缆绳拴接点仍然保持并列(即两者的连线垂直于风向)，因此两方由于翼环分别倾向于东南方和西南方所获得的扭矩就会形成一个指向北方的合力。
同理，只要使两方翼环分别倾向于东北方和西北方，就会获得指向南方的水平推力。
在取得南北方向上的驱动力的基础上，如果使东西两方的拉力平衡，则整机必然朝正南或正北方向巡航；如果使东西两方的拉力失衡并综合调控南北方向的动力，则整机必然朝东南、西南、东北、西北等方向巡航。因此，本机可实现八方自由巡航。
附图说明
一、图号和图面名称：
图1：一种翼环机构的结构示意图(侧视)
图2：一种翼环机构的结构示意图(俯视)
图3：一种高空发电环的结构示意图(侧视)
图4：一种高空发电环的结构示意图(侧视)
图5：一种对拉飞悬机的结构示意图(侧视)
图6：一种对拉飞悬机的结构示意图(俯视)
图7：一种翼环飞碟的结构示意图(俯视)
图8：一种翼环飞碟的结构示意图(侧视)
图9：一种翼环飞碟的结构示意图(俯视)
图10：一种翼环飞碟的结构示意图(俯视)
图11：一种翼环飞碟的结构示意图(侧视)
图12：一种翼环飞碟的剖面图(沿飞碟直径剖切)
图13：一种翼环飞碟的结构示意图(侧视)
图14：一种翼环飞碟的结构示意图(侧视)
图15：一种具有品字形轮组的车轨耦合环局部特写图
图16：一种相耦合的轮与轨的横截面图
图17：一种相耦合的轮与轨的横截面图
图18：一种相耦合的轮与轨的横截面图
图19：翼环偏转而产生水平推力的原理示意图(侧视示意图)
二、图面标记：
1：翼环机构；1-1：翼环；1-2：车轨耦合环；1-3：翼片；1-4：翼片支座；1-5：电机；1-6：车轮；1-7：车轮架；1-8：车架环；1-9：轨道环；2：翼环偏转装置；2-1：转动副；2-2：伸缩杆；3：缆绳拴接点；4：缆绳；5：移动副；6：运动副；7：轮的轴向截面；8：轨的横截面；9：中央机舱；9-1：中央机舱的径向截面；10：外环机舱；10-1：外环机舱的径向截面；11：径向机舱；11-1：径向机舱的径向截面。
实施例：
例一：
本例是一个由上下两个翼环机构1组成的翼环机构，图2的每个翼环机构1都包含着图1所示的翼环1-1及车轨耦合环1-2。图2的每个翼环偏转装置2包含有图1所示的伸缩杆2-2及其两端的两个转动副2-1。本例中每个转动副2-1都必须能让所配置的伸缩杆2-2在两个相互垂直的方向上摆动，并且其中一个方向重合于翼环的直径。
此外，需要给每个伸缩杆2-2设置遥控开关，以便遥控它们适时作出伸缩动作并控制它们伸出的长度。本例中的车轨耦合环1-2也可以由磁悬浮耦合环或其他类型的翼环旋转装置代替(以下各例皆同)。
例二：
图3、图4中的每个翼环机构1都与图1中的翼环机构1一样，包含翼环1-1和车轨耦合环1-2，本例是在例一的基础上作如下设置：
给两个车轨耦合环1-2分别设置若干个能够自由切换为电动模式或发电模式的电机，全部电机呈环形阵列，且每个电机皆与一个轮作动力连接。
缆绳拴接点3设置在任一个伸缩杆2-2的不会作伸缩运动的部位，然后将缆绳4的下端连接到地面拴接点。
缆绳4内设有电缆，电缆的上端与电机作电路连接。
另外，对于下翼环(即处于下位的翼环机构1所包含的翼环)，还要给其每个翼片都配置翼片迎角偏转装置。
这个高空发电环的使用方法：先向电动机输电，使之带动翼环旋转，引领整机升空。到达设定高度后，先遥控其余三个伸缩杆2-2伸长，使两个翼环整体偏转，以环面斜向迎风(如图4)，同时操控下翼环的翼片迎角偏转装置，将其全部翼片迎角调为负值(如原迎角为a°，则调整为-a°)，以便于风力自然驱动其旋转。然后切断电源，让高空强风驱动翼环旋转，从而保持升力并带动发电机发电。
对于伸缩杆2-2的伸出长度应作如下设置：设置缆绳拴接点3的伸缩杆2-2应完全不伸出，甚至该伸缩装置可以由普通连杆代替。假设与其处于同一径向上的那个伸缩杆2-2的伸出长度为L，那么其余两个处于垂直径向上的伸缩杆2-2的伸出长度应是L的一半。
例三：
取两个例二所述的高空发电环，将它们的缆绳对接，即成为一组无需地面牵引缆提供拉力的高空对拉发电环，而且它们实质成为能够长期在平流层或对流层顶层悬停或沿东西方向巡航的对拉飞悬机(如图5)。
使用方法：
先后启动两个高空发电环，使它们分别进入平流层的东风层和西风层(或信风带顶部的东风层和西风层)。待它们在相反风向作用下拉紧缆绳之后启动例二所述的操作方法，使两者的形态如同图5所示。通过调节两者张开的角度，就能调节东西双方的拉力，当双方的对拉力达到平衡，整机就会悬停，当双方对拉力失衡，整机就会向东或向西巡航。
例四：
将例三的缆绳4从一条增加到两条(如图6)。
本例的优点在于能够产生指向南北方向的动力，从而无需依次偏转单个翼片而实现真正意义上的八方自由巡航。
请注意：例三中设置有缆绳拴接点3的那个伸缩杆2-2可以由无伸缩功能的普通连杆代替，而本例中却不能，否则翼环就无法向南北两侧偏转。
本例使用方法和原理(详见于“一种对拉飞悬机”技术方案之“有益效果和技术原理”。例五：
如图7、图8、图9，其每个翼环机构1都包含有图1相应位置上的一组翼环1-1和车轨耦合环1-2。
本例是在例一的基础上首先增设外环机舱10，使之成为一个翼环飞碟，并且如图7所示，外环机舱10通过移动副5与翼环旋转装置2连接(亦即是如图8所示，与翼环旋转装置2当中的伸缩装置2-2连接)。可见，翼环偏转装置2与外环机舱10之间必须是动连接，这点与例一不同。
当飞碟需要前进，只需操控前后两个伸缩杆2-2作相反的伸长动作即可(如图9)，此时前后两个伸缩杆2-2会相互靠拢，这就是翼环偏转装置2与外环机舱10之间必须是动连接的原因所在，否则伸缩杆2-2会被机舱限制而无法动作。此时左右两个伸缩杆并无滑动位移的需要，它们的两端只需伸出相同的长度以适应翼环机构1的偏转即可，两端伸出长度之和等于前后伸缩杆2-2的伸出长度。
如需在该飞碟前进或后退过程向左或向右转弯，操控左或右两个伸缩杆2-2向上伸出，从而使翼环倾向于左方或右方即可。
关于本例中转动副的设置：
如该飞碟仅需前进或后退的水平推力，全部转动副2-1只要能向前后方向偏转即可。如果需要左右转弯，那么全部转动副2-1还必须能向左右方向偏转。如果需要在前后伸缩杆2-2不作适应性伸缩调整的情况下直接伸缩左右伸缩杆2-2，那么转动副2-1就不可仅仅能绕两个相互垂直的轴向偏转，而必须能绕更多的轴向偏转(最好是如同碗状轴承那样的万向转动副)。
额外说明：
本例飞碟需要前进或后退时，并非必须前后两个或两组伸缩杆2-2同时伸出，只要其中一个或一组伸缩杆2-2向上伸出即可(但水平推力会减半)。
本例中任意两个伸缩方向相反且上下位置相对的伸缩杆2-2也可以合二为一，那样的话其两端必须同步运动(当一端伸出若干长度，另一端必然回缩相等长度)，但是如此设置时，必须给两端预留足够的回缩空间，否则两端必然相互限制而无法伸出或无法伸出足够长度。
例六：
在例五的基础上，将翼环飞碟的前后左右调整为图10所示的方位。
当需要前进或后退的水平推力，只需操控前后两组伸缩杆2-2作出相应伸缩即可，如果需要左转或右转的水平推力，只需操控左右两组伸缩杆2-2作出相应伸缩即可(如图11)。
例七：
在例一的翼环机构的基础上增加中央机舱9、外环机舱10和径向通道舱11，使之成为一个翼环飞碟(如图12、图13和图14所示)。
本例与例五、例六最大的不同是：翼环偏转装置2与机舱之间形成固定连接，两者之间不能相对运动，并且任意两个伸缩方向相反且上下位置相对的伸缩杆2-2都不可能如同例五、例六那样成为一体或上下始终保持在同一轴线上。任一伸缩杆2-2作出伸缩动作时其本身都必然发生摆动，因此转动副的设置必须适应其摆动所需(如图14所示)。
关于设置本例及以上各例中的转动副2-1必须注意的事项，可见于例八。
例八：
以上各例中，伸缩杆2-2的数量皆未大于4。但是，如果翼环机构的直径较大，就需要增设更多的伸缩杆2-2，以提供翼环偏转所需的推力和稳定性。增设伸缩杆2-2之后，全部伸缩杆2-2最好仍是呈环形阵列。增设的任一个伸缩杆2-2，它们各自的伸出长度等于同一圆周线上处于其两旁距离最近的两个伸缩杆2-2伸出长度之和的一半。至于动连接装置的设置则比较复杂，例一和例五分别有所涉及，这里进一步仅以设置转动副为例。
当伸缩杆2-2的数量等于4，则请参阅例五、例六和例八。
当伸缩杆2-2的数量大于或小于4，且假设伸缩装置数量为N，那么，当N是单数，则每个伸缩装置所配置的转动副(或转动副组合)的可偏转轴向数就应不小于N(因为伸缩装置需要在N个方向上摆动)；当N是偶数，则每个伸缩装置所配置的转动副(或转动副组合)的可偏转轴向数就应不小于N÷2(伸缩装置只需要在N÷2个方向上摆动)。只有当N为2时，情况较为特殊，如两个伸缩装置摆动方向相同或平行，那么每个伸缩装置所配置的转动副(或转动副组合)的可偏转轴向数只需不小于1；如两个伸缩装置摆动的方向是交叉的(比如两者交替伸缩而非同步伸缩)，那么每个伸缩装置配置转动副(或转动副组合)的可偏转轴向数就应不小于2。
翼环飞碟必须具备前进、后退和左右转弯四个方向的水平推力，因此其翼环机构的伸缩 装置最少必须有3个，但是除玩具或航模等特别小型的飞碟外，伸缩装置应以4个以上为宜，因为4个才能便于操作四个方向的推力，而且4个伸缩装置才能保证翼环偏转所需的动力和稳定性，而四个伸缩装置又以环形阵列为宜，因此其中每一个所配置的转动副都必须能够绕两个相互垂直的轴线往复旋转方可。
而大、中型翼环飞碟由于直径较大，其翼环机构的伸缩装置就需要在6个以上，实际数量多少以保证翼环偏转所需的推动力和稳定性为度。
例九：
在例一至例七的基础上，对其车轨耦合环作如下修改：图15、图16所示，将其车轮组改为品字形排列的车轮组，品字形阵列的车轮从三个方向包围轨道而与之相耦合，品字形的开口向左或向右皆可，但不便于向上或向下。
例十：
在例一至例七的基础上，修改其车轨耦合环1-2。例二至例七中的翼环机构1包含有车轨耦合环1-2和翼环1-1(如例一之图1中的车轨耦合环1-2和翼环1-1)。具体修改是，将车轨耦合环中的环形轨道换为横截面呈凹陷的梯形或凸起的梯形的轨道，车轮也相应地换为轮周(即是与轨道接触的滚压面)呈凸起的梯形或凹陷的梯形(轨道和车轮如图17、图18)。
本例的优点是在一个截面上只需要一个轮就能实现耦合及传递扭矩，结构简单、成本低、自重小，特别适用于较小型的飞碟，尤其是玩具类飞碟航模。
例十一：
在例五、例六、例七的基础上作好防水措施，使翼环飞碟在降落水面时不至于透水沉没。还可以在飞碟各机舱底部增设形状与机舱投影形状相一致的气囊，并给气囊配置快速充气、抽气装置，以便在载重过大时增加浮力。
例十二：
在任一种翼环飞碟的基础上，作好防水措施，并给每个翼片(尤其是下翼环的每个翼片)增加迎角偏转装置，而且该迎角偏转装置必须能使翼片偏转到足够大的负迎角(以便切入水中产生向下的推力)。在需要潜入水中或进一步下潜时，只需加大下翼环的偏转度，使其一部分切入水中，并且使每个翼片(尤其是下翼环的每个翼片)偏转到足够大的负迎角。需要上升或出水时则实施相反的操作。

Claims (11)

  1. 一种低能耗高速飞行方法，使翼环飞碟获得水平推力的方法，其特征是：使翼环轴向倾斜，从而使翼环整体升力的指向发生倾斜，从而使升力中的一部分转化为水平推力。
  2. 一种翼环机构，具有翼环、翼环旋转装置和翼环偏转装置，其特征是：所述翼环偏转装置由伸缩装置和动连接装置组成，所述伸缩装置指液压伸缩杆、气压伸缩杆、螺旋伸缩杆、齿条伸缩杆、折叠伸缩杆、可膨胀收缩的气囊或其他任何一种能够往复改变其自身两端之间的距离的装置。
  3. 根据权利要求2的一种翼环机，其特征是：所述动连接装置处于所述伸缩装置的两端和中段这三处中的任意两处或三处。
  4. [根据细则91更正 23.03.2020]　
    根据权利要求2所述的一种翼环机构，其特征是：所述动连接装置属于或包含有转动副，移动副或可弯折装置。
  5. 根据权利要求4所述的一种翼环机构，其特征是：所述转动副能允许伸缩装置或翼环旋转装置向两个以上方向偏转或摆动。
  6. 根据权利要求4所述的一种翼环机构，其特征是：所述移动副能允许伸缩装置在水平方向上移动。
  7. 一种翼环飞碟，以翼环机构为升力装置的航空器或潜航器，其特征是：所述翼环机构是权利要求2的一种翼环机构，或是其他任一种能够使其翼环偏转的翼环机构。
  8. [根据细则91更正 23.03.2020]　
    根据权利要求7的一种翼环飞碟，其特征是：具有环状机舱、碟状机舱、网状机舱、十字形机舱、径向机舱或其他类型的机舱。
  9. 一种高空发电环，高空风力发电装置，具有翼环机构和缆绳，翼环机构连接绳缆上端，缆绳下端连接于地面拴接点，其特征是：所述翼环机构属于权利要求2的所述的一种翼环机构，所述缆绳上端连接到所述翼环机构侧边的不随翼环旋转的部位。
  10. [根据细则91更正 23.03.2020]　
    一种对拉飞悬机，两个或两组浮空器或航空器分别处于两个风向相反的风层中，两者之间通过任一种能够防止两者相互脱离的连接体相互连接，其特征是：所述两者中最少有一者属于权利要求2所述的一种翼环机构或权利要求7所述的一种翼环飞碟。
  11. [根据细则91更正 23.03.2020]　
    根据权利要求10的一种对拉飞悬机，其特征是：所述能够防止两者相互脱离的连接体是缆绳、连杆或支架，缆绳、连杆或支架的数量不小于2，并且其中最少有两条缆绳、两根连杆或两个支架，它们的上端分别连接到处于上风层的浮空器或航空器的中轴线的两侧，这两条缆绳的下端分别连接到处于下风层的浮空器或航空器的中轴线的两侧。
PCT/CN2020/000028 2019-02-03 2020-02-04 低能耗高速飞行方法及其翼环机 WO2020156018A1 (zh)

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