Flying saucer method of flight and wing ring machine

Abstract

The maximum lift of the wing ring machine can reach tens of thousands of tons, which is the best lift device of the disc-shaped aircraft. However, the existing wing ring flying disc technology can only obtain horizontal driving force through an additional engine, and the additional engine will inevitably compress the effective load capacity, increase energy consumption and pollution. The present application can drive the flying disc to move forward, turn, brake and fly backward without additional engine, and the technical scheme is that the wing piece or fluid generator of the wing ring repeats the same deflection process when passing through a specific section each time in consecutive two or more than three circumferential movements. The present application can greatly improve the cargo distribution speed and reduce the cost of the air freight flying disc by setting the release sub-machine manipulator and / or the recovery sub-machine manipulator. The radial channel cabin of the present application connects multiple cabins into one, greatly increases the effective load space of the flying disc, and solves the lift loss and strength decrease caused by the airspeed difference of different radius wing sections of the large wing ring machine, and improves the lift and mechanical strength of the flying disc.

Description

Technical Field

[0001] This invention relates to wing ring aircraft technology, and more particularly to disc-shaped aircraft technology using wing ring aircraft as lift devices. Background Technology

[0002] The term "ring machine" encompasses ring-shaped rotorcraft, ring-shaped wind turbines, ring-shaped water turbines, and ring-shaped propellers, while the "ring disc" is a disc-shaped aircraft that uses a ring machine as its lift mechanism.

[0003] Luo Conggui's patent application, "Wing Ring and Device and Method with Wing Ring" (Publication No. CN103195662A), comprehensively describes wing ring aircraft technology. While the specification of that application mentions the deflection device for the engine and winglets, it makes no mention of or implication of the deflection method and technical effects described in this application. Furthermore, Figures 47 and 48 in the specification show that existing wing ring flying saucers can only obtain horizontal driving force through an additional engine; otherwise, horizontal movement is impossible. This severely reduces the effective payload and increases energy consumption and pollution. Is it possible to find a method and device that can propel a flying saucer forward, turn, brake, and fly inverted without the need for an additional engine?

[0004] Figures 47-50 in the specification of this application also show that existing wing-ring flying saucer technology cannot simultaneously set up a central cabin (as shown in Figures 47-48) and an outer ring cabin (as shown in Figures 49-52), let alone achieve communication and connection between the two cabins. How can a wing-ring flying saucer simultaneously possess two types of cabins and enable them to communicate and connect with each other? Summary of the Invention

[0005] Large annular gyroplanes have very large wing ring diameters and high annular truss linear velocity, resulting in significant centrifugal forces. Current annular gyroplane technology can only thicken the annular truss to resist these forces, but this increases the aircraft's weight. The question is whether it's possible to significantly improve the annular truss's resistance to centrifugal disintegration without increasing material usage or upgrading material grades.

[0006] Unmanned logistics aircraft and unmanned delivery rotorcraft have both appeared in China, and airborne delivery is becoming the primary mode of express delivery. Wing-ring flying saucers are clearly the best choice for logistics and delivery aircraft. The question is whether a larger wing-ring flying saucer can carry dozens or even hundreds of smaller logistics aircraft or even smaller delivery aircraft to the work area to perform logistics and delivery tasks separately. Furthermore, the question is whether these logistics and delivery aircraft can be safely and quickly launched and recovered during flight or while hovering over the work area.

[0007] Large wing-shaped aircraft have a large diameter. The farther the wing segments are from the center, the faster their linear velocity (airspeed) and the greater their lift. Conversely, the closer the wing segments are to the center, the slower their linear velocity (airspeed) and the more cumbersome they become. How can we make all the wing segments rotate at the same linear velocity?

[0008] Large wing ring machines have a large diameter and a high linear velocity of their wing rings, resulting in significant centrifugal forces on the ring-shaped truss. The challenge is to substantially improve their resistance to centrifugal disintegration without increasing the weight or material grade of the ring truss.

[0009] I. Technical Solution for UFO Level Flight

[0010] This invention is a method for providing horizontal driving force for disc-shaped aircraft or disc-shaped submarines that use a wing ring engine as a lift device.

[0011] Overall solution: In any disc-shaped aircraft or disc-shaped submarine that uses a wing ring as a lift device, the wing ring's blades or fluid generator repeat the same deflection process each time they pass through a specific section during two or more consecutive circular motions.

[0012] The term "fluid generator" refers to a device capable of ejecting or generating fluid, such as a jet engine, propeller engine, powerful fan, steam ejector, water jet ejector, and magnetohydrodynamic generator, etc.

[0013] The term "repetition" refers not only to "uninterrupted repetition" (i.e., repeating the deflection process one after another), but also to "interrupted repetition" (i.e., the process of deflection is interspersed with a process of no deflection or / and a deflection process that is not exactly the same).

[0014] The term "specific road segment" refers not only to road segments where the midpoint and / or length are set to be fixed, but also to road segments where the midpoint and / or length are set to be movable or / and changeable. Any road segment where the starting and ending points do not coincide is considered a "specific road segment" in this paper. Furthermore, even if the starting and ending points coincide, the deflection angle of the wing or fluid generator does not remain constant throughout a single circular motion. This will disrupt the previously uniform upward lift of the wing rings, generating a horizontal component force, which essentially still falls under the category of a "specific road segment" as defined in this paper.

[0015] The reason why disc-shaped aircraft that use a wing ring as a lift mechanism must be equipped with an additional engine dedicated to providing forward and turning power is that existing wing rings can only provide axial aerodynamics (i.e. lift) but cannot provide horizontal driving force.

[0016] On the same circumference of an existing wing ring aircraft, the angle of attack of each winglet, the angle between the wingspan direction (i.e., the direction the wingspan points) and the central axis of the wing ring, and the angle between the direction of the force emitted by each fluid generator and the tangent of the wing ring, can only be uniform. If they deflect, they can only deflect at the same angle simultaneously. Therefore, an existing wing ring aircraft can only generate a resultant force consistent with the axis, which means only lift for a flying saucer.

[0017] This invention causes the wing's angle of attack, wingspan direction, or fluid direction to deflect only in specific sections, thereby splitting the uniform upward lift into a horizontal force. This invention utilizes this force to propel the flying saucer forward, turn, brake, or fly backward (meaning fly directly backward without turning around). The wing-ring flying saucer has a hovering function; therefore, when the direction of the horizontal driving force is reversed, the flying saucer can brake safely.

[0018] Sub-scheme 1: As in the overall scheme, but with more than one specific road segment.

[0019] Sub-scheme 2: Similar to the overall scheme, and in the "two or more consecutive circular motions, each time passing through a specific section," the vane or fluid generator merely "repeates the same deflection process" throughout its respective entire process. However, the entire processes of the two consecutive motions are different deflection processes, or even completely opposite deflection processes (for example, the previous entire process consists of two or more "vane first tilts up, then returns to its original position" deflection actions, while the subsequent entire process consists of two or more "vane first tilts down, then..."). The process consists of two or more deflection actions, one of which is "the fluid force initially deflects inward towards the tangent of the circle, then returns to its original direction." For example, the first complete process might consist of two or more deflection actions where the fluid force initially deflects inward towards the tangent of the circle, then returns to its original direction. Since the deflection processes are opposite, the horizontal driving forces generated by the two deflections must be in opposite directions, thus enabling the flying saucer to obtain the force required for left and right turns and backward flight.

[0020] Sub-scheme 3: Similar to the overall scheme, the deflection process of the winglets either changes the wingspan direction or the angle of attack of the winglets.

[0021] Changing the wingspan pointing refers to altering the angle between the wingspan pointing direction and the wing ring or the centerline of the wing ring aircraft. Changing the wingspan pointing direction not only allows the winglets to propel the flying saucer forward quickly but also keeps the saucer level (without tilting the centerline). Changing the winglet angle of attack can involve either a complete deflection of the winglets (as in some large three-bladed wind turbines) or a deflection of only the flaps, ailerons, or slats (as in most aircraft wings). Changing the winglet angle of attack involves tilting the centerline of the flying saucer forward, diverting a portion of the aircraft's lift into a horizontal direction, thus propelling the saucer forward.

[0022] Sub-scheme four: As in sub-scheme one, but making the specific road segments described in the two sub-schemes a group of road segments symmetrical at the midpoint.

[0023] This "midpoint" refers to the point that divides the specific road segment into two equal parts, and the two "midpoints" are located at the two intersections of the same circumference and the same diameter (e.g., Figure 5(q and Q). Based on the symmetry of the two midpoints, we can also... Figure 5 That would make a and A symmetric, and b and B symmetric (but it is not necessary to do so to achieve the present invention).

[0024] Sub-scheme five: as in sub-scheme four, but with a number of road segment groups greater than 1.

[0025] Sub-scheme six: Similar to sub-scheme four, but with the wingspans of the same wing ring or different wing rings pointing in opposite directions in the two specific road sections, thereby achieving greater thrust and preventing the annular truss from being stretched or crushed. This "opposite wingspan direction" refers to the attached... Figure 8 As shown, the winglets passing through section ab deflect upwards and tilt upwards, while the winglets passing through section AB deflect downwards and tilt downwards (the so-called ab and AB sections are found in...). Figure 5 ).

[0026] II. Technical Solution for Powered Deflector Circular Aircraft

[0027] Powered deflector ring engines belong to the category of ring rotorcraft, ring propellers, or ring wind turbines.

[0028] Overall design: At least one blade or fluid generator on the wing ring is equipped with a deflection device. The deflection device can initiate deflection at the beginning of a specific segment in its circular motion trajectory and terminate deflection at the end of the specific segment. The blade deflection device can change the wingspan pointing and / or the blade angle of attack, and the fluid generator deflection device can change the angle between the direction of the fluid force and the tangent of the wing ring circumference.

[0029] Sub-scheme 1: As in the overall scheme, with no fewer than two wing rings, and at least two wing rings having the same center but different radii.

[0030] Sub-scheme 1: As in the overall scheme, and the wing ring has at least one type of centripetal force device, and there are no fewer than three of the same type of centripetal force devices on the same circumference, which are arranged in a ring array; the centripetal force device is a device that can generate a force pointing towards the central axis of the wing ring.

[0031] Centripetal force devices come in various forms, among which the most convenient to use are the winglets on the wing ring and the fluid generator.

[0032] The lifting blades, which move in a circular motion as the wing ring rotates, have their lower pressure side tilted towards or toward the central axis of the wing ring (e.g., Figure 28 , Figure 29 and Figure 30 In the wing 5, or Figure 31 In the winglet 6), the lift of the winglet will generate a component force toward the central axis of the wing ring, which becomes a source of centripetal force.

[0033] A fluid generator that drives the wing ring to rotate and moves in a circular motion along with the wing ring will also generate a centripetal force when the direction of the fluid force is deflected to the outside of the tangent of its circular motion trajectory.

[0034] The term "tangent to the circular trajectory" refers to the tangent to the circular trajectory formed by the circular motion of a fluid (such as a high-pressure airflow) nozzle or similar part (such as the center of a propeller). For example... Figure 32 As shown, AC is the tangent, and AD is the fluid ray (jet direction). With the tangent AC as the boundary, the side where the arc AB is located is the inside of the tangent, and the other side (i.e., the side where the fluid ray AD is located) is the outside of the tangent.

[0035] II. A technical solution for a disc-shaped wing ring machine

[0036] Overall design: The number of wing rings shall not be less than two, and they shall have radial passage compartments.

[0037] Using a ring-shaped rotorcraft, ring-shaped propeller, or ring-shaped wind turbine as the lift mechanism, with no fewer than two wing rings, the key feature is that it has a radial passage nacelle (a nacelle erected along the radial or diametrical direction), and the radial passage nacelle either exists independently (meaning there is only one type of nacelle, not that there can only be one radial passage nacelle), or it forms a combined nacelle together with the ring nacelle and / or the central nacelle.

[0038] Sub-option 1: As in the overall option, but with a release robot and / or a recovery robot.

[0039] A "sub-aircraft" refers to an aircraft with autonomous flight capabilities carried by a mother aircraft that is larger than the mother aircraft itself, such as smaller wing ring saucers, gyroplanes, and fixed-wing aircraft.

[0040] The mother aircraft refers to the wing-ring flying saucer that carries the daughter aircraft.

[0041] The release manipulator is a device that can stably hold the sub-machine, send it out of the mother machine, and then release it to let it fly away. Because the sub-machine has already achieved the same cruising speed as a large aircraft before it is released from the grasp of the synchronous release manipulator, it can fly autonomously immediately after being released, and may even ignite the autonomous flight vehicle only after it has been released from the grasp.

[0042] A recovery robot arm is a device that can grasp, restrain, or wrap around a returning aircraft that approaches its mother aircraft and retrieve it back to the mother aircraft. As long as the aircraft is close to the mother aircraft and flies in sync with it (i.e., in the same direction and at the same speed), the robot arm or net can accurately and stably grab or net it.

[0043] Since the aircraft already has the same airspeed as the mother aircraft when it is sent back to return and flies synchronously with the mother aircraft, the so-called "takeoff" is actually just "separation". The mother aircraft already has a cruising speed, so even for fixed-wing aircraft, "takeoff" and "landing" do not require taxiing at all, and can ignite and fly autonomously after separating from the mother aircraft.

[0044] Because this "takeoff" and "landing" method does not require a runway, multiple aircraft entrances and exits can be set on various cabins of the wing ring flying saucer. Each aircraft entrance and exit is equipped with a release aircraft manipulator and a recovery aircraft manipulator, thus enabling safe mass takeoff and landing (the entire fleet takes off and lands at the same time, or even one fleet takes off while another fleet lands).

[0045] Sub-option 2: Similar to the overall option, and its annular gyroplane, annular propeller, or annular wind turbine is a powered deflector annular machine, that is, it uses a powered deflector annular machine as its lift mechanism.

[0046] Beneficial effects

[0047] (I) The beneficial effects of the flying saucer level flight method and the powered deflector ring aircraft:

[0048] 1. It is the only technical solution to date that enables wing-shaped ring flying saucers (i.e., disc-shaped wing-shaped ring aircraft or ring-shaped wing-shaped ring aircraft) to achieve high-speed flight;

[0049] 2. It can move forward, turn, brake, and fly backward at high speed without the need for an additional engine to provide horizontal driving force;

[0050] 3. Significantly reduces construction costs and the weight of the flying saucer;

[0051] 4. Significantly reduces energy consumption and air pollution;

[0052] 5. It can ensure that the wing ring aircraft will not be squeezed or stretched flat during high-speed flight;

[0053] 6. It can offset part of the centrifugal force on the ring truss, thus achieving the purpose of reducing the weight of the ring truss and significantly increasing the net load capacity.

[0054] 7. It enables a larger wing ring flying saucer to carry dozens or hundreds of smaller logistics aircraft or even smaller express delivery aircraft to the work area to perform logistics and express delivery tasks separately, and to realize the group take-off and landing of the sub-aircraft.

[0055] (II) Beneficial effects of a disc-shaped ring machine:

[0056] 1. Enabling airfoils with different radii to achieve the same linear velocity (airspeed) is beneficial for maximizing the lift and mechanical strength of the entire aircraft.

[0057] 2. A wing-ring flying saucer with an outer ring cabin is provided, breaking the old convention that the cabin of a disc-shaped aircraft can only be located on the central axis.

[0058] 3. It greatly increases the sightseeing window, passenger and cargo distribution channel, and effective carrying space of the wing ring flying saucer.

[0059] 4. It can greatly improve logistics speed, especially the speed and security of express delivery, while reducing logistics and express delivery costs. Attached Figure Description

[0060] I. Explanation of reference numerals in attached drawings:

[0061] 1. Annular truss of a ring rotor; 2. Annular truss of the outer wing ring; 3. Annular truss of the inner wing ring; 4. Flat-cut airfoil; 5. Airfoil; 6. Curved airfoil; 7. Virtual connection between the two ends of the curved airfoil; 8. Airfoil with non-deflectable wingspan direction; 9. Airfoil with deflectable angle of attack or wingspan direction; 9-1 Handle of airfoil 9; 10. Hydraulic telescopic rod; 11. A pivot (the dynamic connection point between the bottom end of the hydraulic telescopic rod and the annular truss 2 of the outer wing ring or airfoil 9); 12. B pivot (airfoil 9) 13. C-axis (dynamic connection point between the top of the hydraulic telescopic rod and the handle of the wing 9); 14. D-axis (dynamic connection point between the bottom of the hydraulic telescopic rod and the inner annular truss 3); 15. Annular nacelle; 15-1. Annular nacelle with a smaller radius; 15-2. Annular nacelle with a larger radius; 16. Central nacelle; 17. Radial nacelle; 18. Cross section of the annular truss of the upper annular rotor; 19. Cross section of the annular truss of the lower annular rotor; 20. Flying saucer (annular rotorcraft); 21. Elevator; 22. Nacelle floor; 23. Jet engine; 24. Jet engine air intake; 25. Jet engine exhaust nozzle; 26. Bearing connecting the jet engine and the wing or annular truss; 27. Bearing connecting the jet engine and the top of the hydraulic telescopic rod; 28. Propeller engine; 29. Connecting rod; 39. Circular track with a groove-shaped cross-section (track ring); 40. Chassis ring (circular chassis); 41. Wheel of the railcar; 44. Track coupling ring; 45. Direction of movement of the flying saucer; 46. Direction of rotation of the wing ring.

[0062] II. Description of the attached drawings:

[0063] Figure 1 A side view of a winged ring flying saucer (a cross-sectional view along the diameter);

[0064] Figure 2 A top view of a wing ring;

[0065] Figure 3 : Figure 2A schematic diagram of the connection between the wing blade 9 and its deflection device and the annular truss 1 shown (a cross-sectional view along the radial direction);

[0066] Figure 4 Schematic diagram of the principle of a dynamic deflector ring engine;

[0067] Figure 5 : Schematic diagram of the deflection path setting method for winglets or fluid generating devices that provide level flight power;

[0068] Figure 6 : A schematic diagram illustrating the principle of obtaining horizontal driving force by deflecting the wingspan direction;

[0069] Figure 7 : A schematic diagram illustrating the principle of obtaining horizontal driving force by deflecting the wingspan direction;

[0070] Figure 8 : A schematic diagram illustrating the principle of obtaining horizontal driving force by deflecting the wingspan direction;

[0071] Figure 9 : A schematic diagram illustrating the principle of obtaining horizontal driving force by deflecting the direction of fluid jet;

[0072] Figure 10 : A schematic diagram illustrating the principle of obtaining horizontal driving force by deflecting the direction of fluid jet;

[0073] Figure 11 A schematic diagram of a deflection device for a jet engine and its connection with the airfoil;

[0074] Figure 12 : Figure 11 A schematic diagram of the deflection action of a jet engine in a scene;

[0075] Figure 13 A schematic diagram of a deflection device for a propeller engine and its connection with the airfoil;

[0076] Figure 14 A schematic diagram showing the connection between the two ends of the winglet 9 and the two annular trusses 1 via deflection devices;

[0077] Figure 15 A top view of a modular cabin;

[0078] Figure 16 A top view of a modular cabin;

[0079] Figure 17 A schematic diagram of a cross-section of a wing-ring flying saucer along its diameter;

[0080] Figure 18 A top view of a wing ring;

[0081] Figure 19A schematic diagram of a cross-section of a wing-ring flying saucer along its diameter;

[0082] Figure 20 A schematic diagram of the structure of a wing-ring flying saucer, which is a cross-sectional view along the diameter direction;

[0083] Figure 21 A schematic diagram of the structure of a wing-ring flying saucer, which is a cross-sectional view along the diameter direction;

[0084] Figure 22 A schematic diagram of the structure of a wing-ring flying saucer, which is a cross-sectional view along the diameter direction;

[0085] Figure 23 A schematic diagram of the structure of a wing-ring flying saucer, which is a cross-sectional view along the diameter direction;

[0086] Figure 24 : A schematic diagram of the structure of a wing-ring flying saucer, shown in top view;

[0087] Figure 25 A schematic diagram of the structure of a wing-ring flying saucer, which is a cross-sectional view along the diameter direction;

[0088] Figure 26 A top view of a wing ring;

[0089] Figure 27 A top view of a wing ring;

[0090] Figure 28 A top view of a wing ring;

[0091] Figure 29 A top view of a wing ring;

[0092] Figure 30 A top view of a wing ring;

[0093] Figure 31 A top view of a wing ring;

[0094] Figure 32 Schematic diagram of the concept of "outer side of tangent". Detailed Implementation

[0095] Example 1:

[0096] A type of winged ring flying saucer, consisting of two Figure 2 The wing ring shown is connected to a ring-shaped nacelle 15, and the specific connection method is as follows: Figure 1 As shown (two wing rings, two rail coupling rings 44 and an annular cabin 15 constitute a disc-shaped wing ring machine, and the annular cabin 15 is dynamically connected to the two wing rings 9 through the upper and lower rail coupling rings 44).

[0097] In this example, the two wing rings rotate in opposite directions, and the wing 9 has a lifting airfoil shape, so the air pressure on the side of the wing facing upward is lower than that on the side facing downward when cutting through the air.

[0098] In this example, the engine can be an electric motor or an internal combustion engine. The engine can be installed at a suitable position on the annular frame (frame ring) 40, and the engine can be connected to the wheel 41 of the railcar so that the engine drives the wheel 41 to rotate, and the wheel 41 drives the wing ring to rotate.

[0099] The number of engines depends on the power requirements. It can be one engine per wheel, one engine per wheel set, or even one engine every few wheel sets.

[0100] The key settings are as follows:

[0101] The connection method between each winglet 9 and the annular truss 1 of the wing ring can be seen in Figure 3 The end of the handle 9-1 of the vane 9 is dynamically connected to the outer ring truss 2 via the B pivot 12. The top of the hydraulic rod 10 is dynamically connected to the handle 9-1 of the vane 9 via the C pivot 13; the bottom of the hydraulic telescopic rod 10 is dynamically connected to the outer ring truss 2 via the A pivot 11.

[0102] Then, two sets of signal transmitters, X1 and X2, are installed on the annular nacelle 15. Their specific locations can be found in [the relevant documentation / reference]. Figure 4 The X1 and X2 azimuths. Group X1 has three signal transmitters: a, q, and b; group X2 has three signal transmitters: A, Q, and B (see...). Figure 5 ).

[0103] Meanwhile, a signal receiver is set on each winglet 9. The task of the signal receiver is to receive the signals emitted by each winglet as it passes through a, q, b, A, Q, B and transmit them to the motor control device. The control device executes the signal command to make the motor rotate forward, reverse, or stop, thereby causing the hydraulic telescopic rod 10 to extend, shorten, or stop.

[0104] The X1 and X2 signal transmitters of the small, low-speed winged ring-shaped flying saucer can be reduced by one. This is because only a small amount of load-bearing capacity N remains (e.g., ...). Figure 6 or Figure 7 As shown in the figure, when the force N is too large, the wing ring, which should remain perfectly round, may be squeezed or stretched flat, thus hindering its mechanical properties.

[0105] Therefore, large or high-speed ring-shaped flying saucers should ensure that X1 and X2 simultaneously bear equal forces N (e.g., Figure 8 (As shown), the following settings must be made for this:

[0106] 1. b and B always only send a motor stop signal to keep the hydraulic rod in its initial state.

[0107] 2. The signals A and Q must be opposite, and the signals a and q must be opposite, in order to change the hydraulic rod from extension (or shortening) to contraction (or extension).

[0108] Third, the signals emitted by q and Q must be opposite, and the signals emitted by a and A must be opposite, in order to make the wingspan directions of the winglet in the X1 and X2 directions be opposite (e.g., Figure 8 ).

[0109] Fourth, the initial length of the hydraulic telescopic rod 10, that is, the length required to fix the wingspan direction at the initial angle, must have an appropriate amount of extension to ensure that it can extend when at the initial length and retract when at the initial length, and that the maximum extension length and the maximum retraction length are equal.

[0110] Fifth, it must be ensured that the signal receiver will only receive the signal emitted by each point and execute the instruction when it reaches each of points a, q, b, A, Q, and B (without being interfered with by signals from other points).

[0111] The lift mechanism of the ring-wing flying saucer is the ring-wing engine, which can only generate upward lift. Therefore, the ring-wing flying saucer must be equipped with an additional engine to provide horizontal driving force. This embodiment, however, can derive a stable horizontal component from the upward lift of the ring-wing engine (e.g., Figure 6 , Figure 7 , Figure 8 The force N in the middle.

[0112] Due to the above configuration, when winglet 9 passes point a or A, its signal receiver receives a forward or reverse rotation command, activating the forward or reverse rotation circuit. The motor rotates in the forward or reverse direction, driving the hydraulic telescopic rod 10 to extend or retract, causing winglet 9 to tilt up or down, continuously increasing the wingspan deflection angle and the horizontal thrust. Similarly, when winglet 9 passes point b or B, its signal receiver receives a reverse or forward rotation command, causing the motor to rotate in the reverse or forward direction. The hydraulic telescopic rod 10 then begins to retract or extend, continuously decreasing the wingspan deflection angle and the horizontal thrust. Similarly, when winglet 9 passes point b or B, its signal receiver receives a stop command, the motor stops rotating, and the hydraulic telescopic rod 10 stops moving. At this time, the hydraulic telescopic rod 10 retracts (or extends) to its initial length, winglet 9 returns to its initial wingspan angle, and the horizontal thrust generated by winglet 9 returns to zero.

[0113] Since each winglet follows the previous winglet, while the horizontal thrust generated by the previous winglet continues to decrease, the horizontal thrust generated by the next winglet continues to increase, thus obtaining continuous and stable horizontal power.

[0114] Example 2:

[0115] Based on Example 1, two sets of symmetrical signal transmitters are added to the Y1 and Y2 positions of the annular cabin 15. The installation method is exactly the same as the two sets at the X1 and X2 positions, only the orientation is different (see [reference]). Figure 4 When you only need to move forward, just open X1 and X2; when you need to turn, open Y1 and Y2.

[0116] Example three:

[0117] Based on Example 1 or Example 2, the four signal transmitters a, A, q, and Q in the Y1 and Y2 directions, which originally could only emit single forward or reverse signals, are modified to emit both forward and reverse signals. The UFO directional control stick is then used as the reverse controller for these forward / reverse signals. When the control stick is in the vertical position, a, A, q, and Q should stop emitting any signals, so that the winglets do not deflect when passing through the Y1 and Y2 directions. When the control stick is moved to the left, the left-turn circuit should be activated, causing the signals emitted by a, A, q, and Q to cause the low-pressure surface of the winglets to tilt to the left of the original direction of travel (e.g., ...). Figure 8 When the control lever is moved to the right, the right-turn circuit should be activated, causing the signals from a, A, q, and Q to cause the low-pressure surface of the winglets to tilt to the right of the original forward direction (i.e., the low-pressure surfaces of the two winglets 9 are oriented towards the opposite side of the original forward direction). Figure 8 (The opposite is shown).

[0118] This example makes it very easy to make left and right turns.

[0119] Example 4:

[0120] Based on Example 3, the four signal transmitters (a, A, q, Q) at the X1 and X2 positions are also set up in the same way as in Example 3.

[0121] When the directional stick is pushed forward, the low-pressure surfaces of the winglets in the X1 and X2 directions tilt forward, thus allowing the aircraft to fly forward. When the directional stick is pulled back, the low-pressure surfaces of the winglets in the X1 and X2 directions tilt backward, thus allowing the aircraft to decelerate quickly, achieve braking (hovering) within a short distance, or even quickly turn from forward to backward (flying backward without turning around).

[0122] Example five:

[0123] In Examples 1 to 4, each blade or fluid generator in each wing ring is equipped with a deflection device. In this example, the number of blades or fluid generators equipped with deflection devices is reduced, to a minimum of one (when there is more than one, they should still be arranged in a ring array (i.e., the distance between each pair is equal).

[0124] Example 6:

[0125] Based on any one of Examples 1 to 4, make the following modifications:

[0126] The original winglets 9 (and their wingspan pointing deflection devices) were replaced with the wings (and their deflection control devices) of the existing aircraft with flaps, ailerons and / or slats.

[0127] This flying saucer can change the wing's angle of attack simply by deflecting its flaps, ailerons, or slats. Because the angle of attack is changed only in a "specific section," the wing generates lift only in that section, making the lift greater or less in that section than in other sections, thus causing a slight tilt of the wing ring. Due to this tilt, the aircraft's overall lift is decomposed into a horizontal driving force.

[0128] Example 7:

[0129] Based on Example 1, the following modifications are made:

[0130] The existing wingspan pointing deflection device is replaced with a deflection device that allows the blades to deflect as a whole, which is found in existing large three-bladed wind turbines. The blade deflection device is placed inside the annular truss 1 of the wing ring, and the root of the blade 9 is connected to it. This allows the deflection device to deflect the wing ring 9 as a whole, thereby directly changing the blade angle of attack and obtaining the horizontal driving force.

[0131] Example 8:

[0132] Based on any one of Examples 1 to 4, make the following modifications:

[0133] The wing deflection device configured on each winglet 9 is removed, making it a winglet 8 with a non-deflectable wingspan direction, and a jet engine 23 is installed at the end of each winglet (e.g., Figure 11 As shown, the jet engine 23 is dynamically connected to the winglet 9 via the bearing 26, while the hydraulic rod 10 is dynamically connected to the wing ring 9 via the bearing 11 and to the jet engine 23 via the bearing 27.

[0134] By controlling the extension and retraction of the hydraulic rod (e.g., in...) Figure 12 In the state shown, the thrust generated by the jet engine 23 is deviated from the tangential direction in a "specific section," thereby generating horizontal thrust. The specific principle is as follows:

[0135] exist Figure 9 and Figure 10In the diagram, the circle represents the annular truss of the wing ring. The thick solid arrow indicates the direction of the force exerted by the wing or fluid generator that has reached this position and deflected at an angle. (If the wing or fluid generator does not deflect when it reaches this position, the direction of its force will be the same as the tangent of the wing ring, i.e., the direction indicated by the thin dashed arrow in the diagram, in which case it would be impossible to generate horizontal driving force.) The thick dashed arrow in the diagram represents the component of this deflected force in the horizontal forward direction of the wing ring (i.e., the component that is converted into horizontal driving force). The thin solid arrow in the diagram represents the direction of the force exerted by the wing or fluid generator when it reaches this position. Since the wing or fluid generator does not deflect when it reaches this position, the direction of its force is the same as the direction of the tangent of the wing ring.

[0136] Although each rotating vane or fluid generator does not continuously generate horizontal driving force, however, Figure 9 and Figure 10 As shown, because each vane or fluid generator produces a horizontal driving force pointing in the same direction on the same road segment, and this driving force is produced one after another, continuously on the same road segment ( Figure 9 and Figure 10 This only shows the deflection dynamics at two positions in each segment. In reality, the horizontal component forces generated by each blade or fluid generator on this segment will form a continuous horizontal resultant force N with stable magnitude and direction.

[0137] Note: Figure 9 The behavior only manifests as a change in power steering on a single road segment, while Figure 10 This describes the situation where the power steering is simultaneously adjusted on two road segments (i.e., these two road segments). Figure 5 The path shown is from segment a to segment b, and the path shown is from segment A to segment B.

[0138] Example 9: Based on Example 8, move the jet engine 23 and its associated hydraulic telescopic rod 10 onto the wing ring truss (all jet engines 23 should be arranged in a ring array).

[0139] Example 10: Based on Example 8 or Example 9, replace the jet engine 23 with a propeller engine 28 (e.g., Figure 13 (As shown).

[0140] Example 11:

[0141] Based on any of Examples 1 to 9, add a circular central nacelle 16 and four strip-shaped radial nacelles 17. The radial nacelles 17 connect and communicate between the central nacelle 16 and the annular nacelle 15 from four directions, thus forming... Figure 15 The disc-shaped cabin shown.

[0142] Figure 18 This is a schematic diagram of the radial cross-section of the wing-ring flying saucer in this example.

[0143] Example 12:

[0144] Based on Example 11, the size of the central engine room 16 was expanded, and its original configuration was... Figure 2 The wing ring shown is replaced with Figure 18 The wing ring shown, the deflection device of the wing piece 9 and its connection with the ring truss of the wing ring are exactly the same as in Example 11. The two ends of the wing piece 8 are fixedly connected to the two ring trusses respectively.

[0145] Radial section of the whole machine as shown Figure 19 As shown.

[0146] Example 13:

[0147] Based on Example 12, the original winglet 9 is removed, and its top view of the wing ring is as follows. Figure 25 Each of its winglets 9 is connected to two annular trusses 1 at both ends, the connection method of which is described in [details omitted]. Figure 14 .

[0148] The radial section of the entire machine in this example is as follows: Figure 20 As shown.

[0149] When horizontal flight propulsion is required, activate Figure 14 The one (or two) hydraulic rods 10 shown extend or shorten, thereby causing the wing segment 9 to deflect in direction. If both hydraulic rods 10 are activated simultaneously, the wing segment 9 will deflect in direction even faster.

[0150] Example 14:

[0151] Based on Example 13, the shape of the nacelle is further modified, and the position of the track coupling ring 44 is moved, so that the connection between the winglet 9 and the nacelle changes from vertical to horizontal. The radial section of the entire aircraft in this example is shown below. Figure 21 As shown.

[0152] The advantage of changing to a left-right lateral connection is that it reduces the weight of the track coupling ring, and the number of wheels on each track car can be reduced from 5 to 3 (only one wheel needs to be placed on the top and bottom, and one wheel on the left or right).

[0153] Example 15:

[0154] Building upon Example 14, the size of the flying saucer is further increased. In this example, the entire aircraft is viewed from the side as follows: Figure 22 As shown, viewed from above Figure 24 As shown.

[0155] The wing ring used in this example consists of two wing rings with the same center but different radii. Two wing rings with different radii on the same plane can rotate in the same or opposite directions, while any two wing rings with the same radius on different planes must rotate in opposite directions.

[0156] Since two wing rings on the same level do not necessarily rotate at the same angular velocity, winglets with different radii can obtain the same linear velocity (airspeed), which is beneficial to maximizing the lift and mechanical strength of the whole aircraft.

[0157] Example 16:

[0158] Based on Example 15, all the lower-level wing rings, their deflection devices, and the track coupling rings are removed, resulting in a flatter flying saucer (such as...). Figure 23 ).

[0159] Example 17:

[0160] Based on Examples 12, 13, 14, or 15, the cabin is transformed into... Figure 16 The shape shown. The radial section of the entire machine in this example is as follows. Figure 25 As shown.

[0161] Example 18:

[0162] Based on any of the above examples, waterproof seals are made for the cabin, wing ring, deflection device, etc., to adapt to water landing, floating and submerging.

[0163] Example 19: Based on any of the above examples, equip the flying saucer with a ring-shaped or circular airbag to adapt to landing and floating on water.

[0164] Example 20: Based on Example 18 or Example 19, replace the jet engine with a high-pressure water jet injector.

[0165] Example 21:

[0166] Based on any of the above examples, a ring-shaped array of landing gear is provided, with all landing gear connected to the ring-shaped cabin 15, the central cabin 16, or the annular frame (frame ring) 40.

[0167] Example 22:

[0168] In the examples above, both wing ring aircraft are equipped with deflection devices for winglets or hydrodynamic vehicles, along with corresponding signal transmitting and receiving devices. In this example, the deflection device and corresponding signal transmitting and receiving devices for one of the wing rings are removed, leaving only one wing ring with these devices. This means only one wing ring generates the horizontal force component, which is sufficient for certain applications of wing ring aircraft.

[0169] Example twenty-three:

[0170] like Figure 5 q is the midpoint of road segment ab, and Q is the midpoint of road segment AB. These two specific road segments actually form a group of road segments symmetrical about their midpoints.

[0171] In any of the above-mentioned preferred embodiments, all of its midpoint symmetrical road segment groups have three pairs of symmetrical points: one is the starting point of the two road segments, the second is the ending point of the two road segments, and the third is the midpoint of the two road segments.

[0172] In this example, the length of any segment in the segment group is increased or decreased, so that the starting and ending points of the two segments are asymmetrical (but the midpoints of the two segments are still symmetrical).

[0173] Example 24:

[0174] Based on the above examples, two road segments of the same length in one or more groups of road segments with symmetrical midpoints are changed to have different lengths (but the line connecting the midpoints of the two road segments still passes through the center of the wing ring).

[0175] The so-called "midpoint symmetrical road segment group", such as Figure 5 : q is the midpoint of segment ab, Q is the midpoint of segment AB, these two midpoints are on the same straight line and are equidistant from the center of the wing ring.

[0176] Example 25:

[0177] On any wing ring flying saucer, the method described in Example 1, Example 2, Example 3... or Example 9 of the best embodiment is used to set the wing blades or fluid generator of its wing ring to "repeat the same deflection process each time it passes through a specific road segment in two or more consecutive circular motions, wherein the start and end points of the specific road segment do not coincide."

[0178] Example 26:

[0179] Based on any type of wing-ring flying saucer, the following settings are made:

[0180] Several portals for releasing and recovering sub-aircraft are set on the wing ring saucer, which serves as the mother aircraft. Each portal is accompanied by a robotic arm for releasing and recovering sub-aircraft. All the portals on the annular cabin can be arranged in a circular array, all the portals on the central cabin can be arranged in a circular or rectangular array, and all the portals on the radial passage cabin can be arranged in a line array.

[0181] The mother aircraft can launch rotorcraft (flying saucers, gyroplanes, helicopters, etc.) from hovering or in flight. During launch, the mother aircraft simply uses a robotic arm to grasp the rotorcraft and send it outside the cabin. Then, the rotorcraft (flying saucer, gyroplane, helicopter, etc.) is ignited and started. Once its rotor reaches a safe speed, the robotic arm can be released, allowing the rotorcraft to fly away on its own.

[0182] The mother aircraft can also launch fixed-wing aircraft while hovering or cruising. If the mother aircraft is cruising, the aircraft can start its engines after detaching from the manipulator (ensuring the nose of the aircraft faces the direction of travel of the mother aircraft). Since the aircraft's speed before detaching from the manipulator is the same as the mother aircraft's speed, it can immediately enter autonomous flight after detachment. If the mother aircraft is hovering, the aircraft's engines must be started and brought to the required safe flight speed before detaching from the manipulator to ensure the aircraft has sufficient initial velocity when the manipulator is released (to ensure a safe glide during descent). The mother aircraft can only launch fixed-wing aircraft while hovering at a sufficiently high altitude.

[0183] Example twenty-seven:

[0184] Any wing-ring flying saucer with a central or annular cabin shall have several downward-facing hatches on the underside of its circular or annular cabin. All such hatches shall be arranged in a circular, rectangular, or linear array, with the distance between them such that they do not interfere with each other and that safety is ensured when launching and recovering the aircraft.

[0185] Such a hatch should be located outside the sweep range of the annular rotor to prevent the hatch from being blocked by the rotating annular rotor.

[0186] When the aircraft group returns to below the mother aircraft, the formation of the aircraft group must correspond to the array of the aforementioned hatches (one aircraft per hatch), and they must hover or fly synchronously with the mother aircraft (in the same direction and at the same airspeed). Then, the hatches of the array are opened, a recovery net is dropped to cover and secure each corresponding aircraft, and then the net cable is retrieved upwards to hoist the aircraft back into the cabin.

[0187] Example 28:

[0188] Based on Example 5, the recycling net is replaced with a robotic arm that can extend and retract.

[0189] When the group of aircraft takes off, each aircraft is held by a robotic arm extending outside the cabin. Then, all aircraft are adjusted to the same horizontal flight attitude, and the robotic arms are released and retracted. Since the initial speed of each aircraft is the same when the robotic arms are released, the aircraft will glide forward and downward. At this point, the engines can be started to allow for autonomous flight.

[0190] The portal of the recycling sub-machine and the extension position of its robotic arm can be below, above, or to the side of the UFO.

[0191] Example 29:

[0192] On any type of wing ring flying saucer, a sub-aircraft group release device is set up according to the method described in any of Examples 1 to 5, and a sub-aircraft group recovery device is set up according to the method described in Example 6 or Example 7.

[0193] Designate the top, upper part, or above the flying saucer as one takeoff and landing area (Area 1), the bottom, lower part, or below the flying saucer as another takeoff and landing area (Area 2), and the area surrounding the flying saucer as another takeoff and landing area (Area 3). Select any two of these three areas to simultaneously launch and land carrier-based aircraft.

[0194] Based on the principle of "minimizing interference," the optimal combination of areas for group takeoff and landing is Zone 1 + Zone 3, followed by Zone 1 + Zone 2 and Zone 2 + Zone 3. In the Zone 1 + Zone 3 combination, it is best to designate Zone 1 as the recovery zone and Zone 3 as the release zone.

[0195] Example 30:

[0196] On any type of ring-shaped flying saucer, its ring-shaped rotor, ring-shaped propeller, or ring-shaped wind turbine can be viewed from above as shown in Figure 27 and from the side as shown in Figure 28. Figure 28 As shown. Its lifting blades (blades that generate lift when cutting through the air) generate a force pointing towards the center of the wing ring because the low-pressure surface is tilted towards the central axis.

[0197] Example 31:

[0198] On any type of ring-shaped flying saucer, its ring-shaped rotor, ring-shaped propeller, or ring-shaped wind deflector is shown in Figure 26 from the side view. Figure 29 Its oblique airfoil has a lifting airfoil shape (it generates lift when cutting through the air, and the lift is directed towards the central axis of the airfoil ring).

[0199] Example 32:

[0200] On any type of ring-shaped flying saucer, its ring-shaped rotor, ring-shaped propeller, or ring-shaped wind turbine can be viewed from above (Figure 26) or from the side (Figure 26). Figure 30 Its oblique airfoil has a lifting airfoil shape (it generates lift when cutting through the air, and the lift is directed towards the central axis of the airfoil ring).

[0201] Example 33:

[0202] Any type of ring-shaped flying saucer, with its ring-shaped rotor, ring-shaped propeller, or ring-shaped wind turbine, appears as follows when viewed from above: Figure 26 Side view as shown Figure 31 As shown. Its curved airfoil has a lifting airfoil shape, and the lift of its upturned airfoil section points towards the central axis of the airfoil ring.

[0203] Example 34:

[0204] Any ring-shaped flying saucer has ring-shaped rotors, propellers, or wind turbines whose wingspans point parallel to the central axis of the ring. The low-pressure surface of these ring-shaped blades is directly opposite the central axis of the ring (the chord line is parallel to the tangent of the ring's circumference). There are at least three such blades on a single circumference of the same ring, and these blades are equidistant from each other on that circumference.

[0205] The low-pressure side of a blade refers to the side of the blade with lower air pressure when the blade cuts through the air.

[0206] Example thirty-five:

[0207] In any disc-shaped aircraft that uses a ring rotor, ring propeller, or ring wind turbine as its lift device, all the blades of its ring rotor have the end with the smaller chord pointing towards the axis (e.g., Figure 24 or Figure 26 (As shown).

Claims

1. A method for level flight of a flying saucer, a method for generating horizontal driving force in a disc-shaped aircraft or underwater vehicle using a wing ring as a lift device, wherein the wing ring has winglets or fluid generators connected to it and capable of circular motion around its rotation axis, and the number of winglets or fluid generators is greater than one, characterized in that: A specific segment is set on the circular motion trajectory of the vane or fluid generator, and the vane or fluid generator repeats the same deflection process each time it passes through the specific segment in two or three consecutive circular motions; the deflection process is the deflection process of a single vane or a single fluid generator, and it is the deflection process that occurs in the specific segment, which is located on the circular motion trajectory of the vane or fluid generator, and not on the motion trajectory caused by the overall deflection of the wing ring.

2. The method according to claim 1, characterized in that: Make the specific road segment more than 1 segment.

3. The method according to claim 1, characterized in that: in In two or more consecutive circular motions, each time the blade or fluid generator passes through a specific section, it only repeats the same deflection process throughout its own process. However, the two processes are different deflection processes, or even completely opposite deflection processes.

4. The method according to claim 1, characterized in that: The deflection process of a wing can be either a change in the wing's direction of attack or a change in the wing's angle of attack.

5. The method according to claim 2, characterized in that: Make the two specific road segments into a group of road segments that are symmetrical at the midpoint.

6. The method according to claim 5, characterized in that: The number of road segment groups is greater than 1.

7. The method according to claim 5, characterized in that: By having the wingspans of the same wing ring or the wings of different wing rings point in opposite directions in the two specific road segments, greater thrust can be obtained and the ring truss can be prevented from being stretched or crushed.

8. A powered deflector ring engine, belonging to the category of ring rotorcraft, ring propellers, or ring wind turbines, has a winglet or fluid generator connected to the ring and capable of circular motion around the ring's rotation axis, characterized by: At least one of the blades or fluid generators on the wing ring is equipped with a deflection device. The deflection device can start deflecting at the beginning of a specific segment in its circular motion trajectory and end deflecting at the end of the specific segment. The blade deflection device can either change the wingspan direction or change the blade angle of attack. One end of the deflection device is connected to the blade or fluid generator, and the other end is directly or indirectly connected to the annular truss of the wing ring.

9. The wing ring machine according to claim 8, characterized in that: The number of wing rings is not less than two, and at least two wing rings have the same center but different radii.

10. The wing ring machine according to claim 8, characterized in that: The wing ring has at least one type of centripetal force device, and there are no fewer than three centripetal force devices of the same type on the same circumference, arranged in a circular array; the centripetal force device is a device that can generate a force pointing towards the central axis of the wing ring.

11. A wing-ring flying saucer, belonging to the category of ring-shaped gyroplanes, ring-shaped propellers, or ring-shaped wind turbines, is a disc-shaped aircraft or underwater vehicle that uses a wing ring as a lift device. The wing ring has winglets or fluid generators connected to it and capable of circular motion around its rotation axis. Its characteristics are: The number of wing rings is not less than two, and each wing ring has a radial passageway. The radial passageway is either independent or forms a combined nacelle together with the annular nacelle and / or the central nacelle. The radial passageway serves as a passageway for communication between other nacelles in the combined nacelle. The annular rotorcraft, annular propeller, or annular wind turbine belongs to the powered deflector annular rotorcraft as described in claim 8.

12. The wing-ring flying saucer according to claim 11, characterized in that: It has a release robot and / or a recovery robot.

13. The wing-ring flying saucer according to claim 11, characterized in that: The powered deflector ring engine as described in claim 8 is used as its lift mechanism.

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