WO2018072756A1 - Système d'alimentation pour envol, aéronef, et procédé d'obtention d'un vol en palier, de décollage/atterrissage vertical, de tangage et de roulis destiné à un aéronef - Google Patents

Système d'alimentation pour envol, aéronef, et procédé d'obtention d'un vol en palier, de décollage/atterrissage vertical, de tangage et de roulis destiné à un aéronef Download PDF

Info

Publication number
WO2018072756A1
WO2018072756A1 PCT/CN2017/107309 CN2017107309W WO2018072756A1 WO 2018072756 A1 WO2018072756 A1 WO 2018072756A1 CN 2017107309 W CN2017107309 W CN 2017107309W WO 2018072756 A1 WO2018072756 A1 WO 2018072756A1
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
disk
ring
power
air
Prior art date
Application number
PCT/CN2017/107309
Other languages
English (en)
Chinese (zh)
Inventor
刘德庆
Original Assignee
刘德庆
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 刘德庆 filed Critical 刘德庆
Publication of WO2018072756A1 publication Critical patent/WO2018072756A1/fr

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C15/00—Attitude, flight direction, or altitude control by jet reaction
    • B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C17/00—Aircraft stabilisation not otherwise provided for
    • B64C17/02—Aircraft stabilisation not otherwise provided for by gravity or inertia-actuated apparatus
    • B64C17/06—Aircraft stabilisation not otherwise provided for by gravity or inertia-actuated apparatus by gyroscopic apparatus

Definitions

  • the present invention relates to the field of aircraft, and in particular to a flight power system, an aircraft, and a method for leveling, vertically taking off, pitching, and rolling the aircraft.
  • a fixed-wing aircraft is an aircraft that produces forward thrust or tension from a power unit, generates lift from a fixed wing of the fuselage, and is heavier than air in the atmosphere.
  • fixed-wing aircraft have to undergo long acceleration or deceleration during take-off or landing, and it is difficult to turn and cannot realize immediate steering.
  • the helicopter is lifted off by a pair or several rotors and can take off and land in heavy air. Although the helicopter can take off and land vertically, the airflow induced by the helicopter rotor will diverge around, resulting in a large loss of airflow power and a slower flight speed. Moreover, the helicopter rotor is huge and exposed, and it is easy to cause serious accidents due to touching objects.
  • the object of the present invention is to overcome the deficiencies in the prior art, to provide a flight dynamic system and an aircraft with good dynamic balance, good stability, and strong power, and to make the aircraft fly flat, vertical takeoff and landing, and pitch. , roll method.
  • the first solution provided by the present invention is as follows:
  • a flight power system is applied to an aircraft, comprising an energy storage unit and a driving unit, the energy storage unit powering the driving unit, and further comprising an annular power disk, the power disk ring being disposed on an aircraft a body, a circumference of a disk surface of the power disk is provided with a plurality of turbine blades, and the driving unit drives the power disk to rotate;
  • An air inlet ring is formed on an upper portion of the aircraft body, and an air outlet ring is formed on a lower portion;
  • the wind is generated by the rotation of the power disk, and the airflow is sucked from the upper air inlet ring, and is ejected from the lower air outlet ring to form a recoil airflow under the aircraft body to lift the aircraft body.
  • the circular power disk has excellent dynamic balance characteristics, and the gyro effect generated by the high-speed rotation of the power disk makes the aircraft obtain great flight stability.
  • the energy storage unit includes one or more of electric energy, fuel, and compressed air.
  • the power disk is provided with a plurality of the turbine blades on one side and a plurality of driving blades on the other side;
  • the driving unit is a plurality of fans, and the plurality of fans are disposed on the aircraft body and drive the power disk to rotate by the driving blades.
  • the combination of the fan and the drive blades makes the aircraft more powerful.
  • the drive unit is a number of fans. When a single fan fails, it will hardly affect the flight. The failure of multiple fans is negligible.
  • the power source of the aircraft is more stable and the flight is safer.
  • the fan can be evenly arranged with respect to the circumference of the power disk, so that the driving force of the power disk is relatively stable and the dynamic balance is better.
  • the fan is evenly disposed with respect to the circumference of the power disk.
  • the flight power system further includes an annular support disk, the support disk ring is disposed on the aircraft body, and the support disk is provided with a collecting air ring;
  • the power disk is rotatably connected to the support disk, a gap is formed between the air collecting ring and the power disk, the driving blade is disposed in the gap, and the wind of each fan flows to the gap in.
  • the gap is a drainage air channel of the power disk
  • the wind of the fan is directed to the driving blades of the power disk, which makes the wind of the fan more concentrated, reduces the wind energy loss of the fan, and makes the driving force of the power disk more powerful.
  • a plurality of air inlets are arranged on the circumference of the support disk, and the number of the air inlets is the same as the number of the fans, and each of the fans respectively supplies air into the gap through the air inlets;
  • the air collecting ring includes a plurality of arches disposed on the support plate, the air inlet is disposed on a plurality of the plurality of arches, and the arched portion of the air inlet is disposed The height is higher than the height of the remaining arches.
  • the power disk and the support disk are both integrally formed profiles.
  • a plurality of rollers are arranged on the circumference of the support disk, and the rollers are used for supporting the power disk, and the axis of the roller is parallel to the contact surface of the power disk.
  • the power disk is connected to the aircraft body through a roller, and the roller has a supporting function on the power disk.
  • the power disk contacts the roller, and drives the lower roller to rotate together, and the setting of the roller becomes sliding friction. Friction reduces the starting resistance of the power disk.
  • the axis of the roller is parallel to the contact surface of the power disk, and the contact surface of the power disk and the roller is a slope.
  • the axis of the roller is parallel to the slope of the power disk, that is, the power disk and the roller are in line contact.
  • the advantage of this arrangement is that the roller is on the power disk.
  • the support stability is better, making the positioning of the power disk more accurate.
  • the power disk can be suspended in high-speed rotation, that is, air-suspended when rotating at high speed, without mechanical wear, reducing the loss of kinetic energy.
  • a plurality of air inlet ring spoilers are disposed on the circumference of the air inlet ring, and an inclination direction of the air inlet ring spoiler is the same as a rotation direction of the power disk.
  • the air inlet ring Relative to the direction of rotation of the power disk, the air inlet ring is provided in the same direction, and the air inlet direction is adjusted and combed by the air inlet ring to make the aircraft body obtain more spin stress, which is beyond the operation of the balanced power disk. Rotational momentum balancing is required to achieve spin maneuvering of the aircraft body.
  • a driving device for adjusting the inclination angle of the air inlet ring spoiler is further included.
  • the invention further includes a servo motor and an annular guide vane, wherein the guide vane is disposed on the aircraft body The outer edge of the airflow flows from the air outlet ring to the air deflector, and the servo motor drives a shape change of the air deflector.
  • a guide vane with a drive motor allows the flight direction of the aircraft to be adjusted, and the different directions of the airflow through the guide vane to the air outlet ring cause the aircraft to either rise or float, or advance, or retreat, or Tilt, or recline, or roll left and right.
  • the flow guide wing includes a flexible solar panel disposed on a surface thereof.
  • a plurality of air outlet spoilers are disposed on the circumference of the air outlet ring, and the air flow ring spoiler changes the air flow of the air outlet ring from a tangential direction to a radial direction, and the air flow direction of the air outlet ring Said on the flow wing.
  • the airflow that is sucked in and entangled by the wind ring is used to convert the airflow into a radial jet, which not only realizes the spin momentum balance of the spin airflow itself, but also fully utilizes the kinetic energy it carries to offset the rotation.
  • the effect of airflow on the spin of the aircraft body The flow of the flow guide vanes is diverted by the guide vanes, thereby changing the state of flight of the aircraft.
  • the air outlet spoiler includes a first end and a second end, the first end being tangent to the power disk, and the second end being the same as a radial direction of the power disk.
  • the circular motion of the power disk drives the airflow to rotate, and the rotating airflow enters from the first end and is led out from the second end.
  • top of the aircraft is provided with a parachute.
  • the second solution provided by the present invention is as follows:
  • An aircraft comprising an aircraft body, the aircraft body having a dome-shaped dish, and further comprising the above-described flight power system.
  • the wind is generated by the rotation of the power disk, and the airflow is sucked from the upper air inlet ring, and is ejected from the lower air outlet ring to form a recoil airflow under the aircraft body to lift the aircraft body, and the ring shape is
  • the power disk has excellent dynamic balance characteristics, and the gyro effect generated by the high-speed rotation of the power disk makes the aircraft obtain great stability.
  • the aircraft body has a dome-shaped dish shape, and there is no sharp point in the direction of flight force. It can be considered as no pole, balanced force, and flight stability.
  • the power disk is provided with a plurality of the turbine blades on one side and a plurality of driving blades on the other side;
  • the driving unit is a plurality of fans, and the plurality of fans are disposed on the aircraft body and drive the power disk to rotate by the driving blades.
  • the drive unit is a number of fans, which makes the aircraft's power sufficient.
  • the failure of a single fan will hardly affect the flight.
  • the failure of multiple fans will hardly occur.
  • the power source of the aircraft is more stable and the flight is safer.
  • the fan can provide a stable direction of power, and the uniform arrangement of the circumference of the power disk also makes the driving force of the power disk uniform and stable, and the dynamic balance is better.
  • the flight power system further includes an annular support disk, and the support disk ring is disposed on the aircraft
  • the support plate is provided with an annular air collecting ring;
  • the power disk is rotatably connected to the support disk, a gap is formed between the air collecting ring and the power disk, the driving blade is disposed in the gap, and the wind of each fan flows to the gap in.
  • the flying power system, the aircraft and the method for flying, vertical take-off, pitch and roll of the aircraft, using the high-speed rotating power disk as the main power source, the annular power disk and the dome-shaped aircraft body It has good dynamic balance performance, no force sharp point, and achieves a certain degree of infinite flight.
  • the third solution provided by the present invention is as follows:
  • An aircraft leveling method based on the above aircraft implementation includes the following steps:
  • the fourth solution provided by the present invention is as follows:
  • An aircraft vertical take-off and landing method includes the following steps:
  • the fifth solution provided by the present invention is as follows:
  • An aircraft pitching method based on the above aircraft implementation includes the following steps:
  • the sixth solution provided by the present invention is as follows:
  • An aircraft roll method includes the following steps:
  • FIG. 1 is a schematic cross-sectional view showing an essential part of an aircraft according to an embodiment of the present invention
  • FIG. 2 is a schematic view showing an aircraft parked on a water surface according to an embodiment of the present invention
  • FIG. 3 is a schematic enlarged structural view of a flight power system according to an embodiment of the present invention.
  • Figure 4 shows a top perspective view of an aircraft provided by an embodiment of the present invention
  • Figure 5 is a plan view showing a power disk according to an embodiment of the present invention.
  • Figure 6 is a front elevational view showing a power disk according to an embodiment of the present invention.
  • Figure 7 is a bottom plan view of a power disk according to an embodiment of the present invention.
  • FIG. 8 is a partially enlarged schematic view showing the power disk support of the flight power system according to the embodiment of the present invention.
  • Figure 9 is a plan view showing an aircraft provided by an embodiment of the present invention.
  • Figure 10 is a bottom plan view of an aircraft provided by an embodiment of the present invention.
  • FIG. 11 is a schematic structural diagram of a spin control system according to an embodiment of the present invention.
  • FIG. 12 is a schematic structural view of an air outlet ring spoiler and a power disk steering provided by an embodiment of the present invention
  • FIG. 13 is a schematic diagram showing the structure of a flat aircraft motion control of an aircraft according to an embodiment of the present invention.
  • FIG. 14 is a schematic view showing a direction of a flat flying airflow of an aircraft according to an embodiment of the present invention.
  • FIG. 15 is a schematic diagram showing a structure of a helicopter control system according to an embodiment of the present invention.
  • Figure 16 is a schematic view showing the structure of the head of the aircraft according to the embodiment of the present invention.
  • FIG. 17 is a schematic diagram showing a structure of a dive maneuver control of an aircraft according to an embodiment of the present invention.
  • FIG. 18 is a schematic structural view showing the steering ring of the air inlet ring and the steering of the power disk according to the embodiment of the present invention.
  • FIG. 19 is a schematic structural view showing the inclination adjustment of the air inlet ring spoiler wing according to the embodiment of the present invention.
  • a flight power system, an aircraft, and a method of flying, vertical take-off, pitch, and roll of the aircraft will be described more fully hereinafter with reference to the associated drawings.
  • a preferred embodiment of a flight power system, an aircraft, and a method of advancing, vertically hoisting, pitching, and rolling the aircraft is illustrated in the drawings.
  • the method of flying power systems, aircraft, and aircraft flying, vertical take-off, pitching, and rolling can be implemented in many different forms and is not limited to the embodiments described herein. Rather, the purpose of providing these embodiments is to make the disclosure of the flight power system, the aircraft, and the method of aircraft flight, vertical takeoff, pitch, roll, and roll more thorough.
  • the aircraft 100 includes an aircraft body 10 having a dome-shaped dish shape similar to a flying saucer in a film and television work, or similar in shape to a dome hat.
  • the structural material of the aircraft body 10 can be made of the same material as the aircraft.
  • the aircraft body 10 is subjected to internal pressure, and a hard aluminum having high tensile strength and fatigue resistance is required as a skin material.
  • the frame of the aircraft body 10 is made of super-hard aluminum, and the reinforcing frame subjected to a large load is made of high-strength structural steel or titanium alloy.
  • the aircraft body 10 is hollow, and the hollow interior is an accommodation space.
  • the interior of the aircraft body 10 can be divided into several parts, such as a cockpit, a passenger compartment, a storage compartment, a restroom, and the like.
  • the dove side of the aircraft body 10 is provided with a hatch 11 for accessing and exiting the aircraft body 10. After the hatch 11 is opened, a ladder (not shown) can be retracted for the occupants to return to the ground.
  • a giant parachute is also darkly placed on the top of the aircraft body 10, and is ejected in an emergency to achieve safe landing of the aircraft 100.
  • the underside of the aircraft body 10 is provided with a landing gear 12 for attachment means for supporting the aircraft 100 and for ground movement when taking off or landing on the ground.
  • the landing gear 12 of the aircraft 100 can be received in the aircraft body 10 after take-off.
  • the aircraft 100 can not only take off and descend on the ground, but also can be applied to the water surface due to its light and circular infinite structure performance.
  • the aircraft 100 parked on the surface of the water can be used as a leisure platform and a mother ship.
  • Figure 2 shows a schematic view of the aircraft 100 moored to the surface of the water.
  • the aircraft 100 further includes a flight power system 20 that powers the aircraft 100 to drive the aircraft 100 to fly.
  • the flying power system 20 includes an energy storage unit 21, a drive unit, a power disk 23, and a support disk 24.
  • the flying power system 20 includes an energy storage unit 21 and a driving unit.
  • the driving unit in this embodiment is a plurality of fans 22, and the fan is specifically an axial fan, which will be described in detail below. It can be understood that the fan 22 can be a turbofan engine in addition to the axial fan.
  • the energy storage unit 21 provides power to the blower 22.
  • the energy storage unit 21 may be electric energy, fuel or compressed air, and provides the flight power of the aircraft 100 by converting the electric energy or thermal energy of the energy storage unit 21 into the kinetic energy of the fan 22 .
  • the energy storage unit 21 has the advantages of being safe and pollution-free, but the energy stored by the energy storage unit 21 is relatively low.
  • the fuel energy storage unit 21 has the advantages of high energy storage and strong power supply, but the flammability and explosiveness of the fuel make it low in carrying safety, and the combustion also generates certain pollution. Therefore, different types of energy storage units 21 should be selected according to actual use requirements.
  • the energy storage unit 21 is evenly distributed on the aircraft body 10, so that the force of the aircraft 100 is more balanced, which is advantageous for the balance and stability of the flight.
  • the power disk 23 and the support disk 24 are annular, both of which are disposed on the aircraft body 10.
  • the support disk 24 is concentrically disposed on the outer edge of the aircraft body 10, and the support disk 24 is fixed relative to the aircraft body 10.
  • the power disk 23 is rotatably coupled to the support disk 24, i.e., the power disk 23 is rotatable relative to the support disk 24, and the rotation relative to the support disk 24 is relative to the rotation of the aircraft body 10.
  • both the power disk 23 and the support disk 24 are annular, and both are integrally formed profiles.
  • the integrally formed power disk 23 is compact and complete, and has less air leakage during the entrainment of the airflow, reducing kinetic energy loss.
  • the material of the power disk 23 can be made of carbon fiber, which has the characteristics of light weight and high strength.
  • one side of the power disk 23 is provided with a plurality of turbine blades 231, and the other side is provided with a plurality of driving blades 232.
  • a plurality of fans 22 are disposed on the aircraft body 10 and drive the power disk 23 to rotate by the drive blades 232.
  • the driving blade 232 is for increasing the force receiving area of the power disk 23, that is, increasing the driving force applied to the power disk 23.
  • the turbine blades 231 are used to generate a directionally stable wind.
  • the drive unit is a plurality of fans 22. When a single fan 22 fails, the flight is hardly affected, and the simultaneous failure of the plurality of fans 22 is minimal.
  • the power source of the aircraft 100 is more stable and the flight is safer.
  • the fan 22 is evenly disposed on the circumference of the power disk 23, so that the driving force of the power disk 23 is relatively stable and the dynamic balance is better.
  • fans 22 are uniformly disposed on the aircraft body 10 in a circumferential direction, and the fan 22 is an axial fan.
  • the aircraft body 10 is uniformly provided with 32 electric energy storage units 21 on the circumference. It can be understood that the number of the fans 22 can also be 6, 12, etc., and the energy storage unit 21 can also be other numbers.
  • the wind of the blower 22 blows the drive power disk 23 on the drive blade 232, and the turbine blade 231 causes the airflow to produce a directional flow.
  • the combination of the fan 22 and the drive blades 232 allows for sufficient power to the aircraft 100.
  • the power disk 23 can be viewed as a giant fan placed in the aircraft body 10 that illuminates the flow of airflow around the aircraft body 10.
  • the support disk 24 is provided with an annular air collecting ring 241, and the power disk 23 is rotatably coupled to the support disk 24.
  • a gap is formed between the air collecting ring 241 and the power disk 23, and the driving blade 232 is disposed in the gap.
  • the wind of each fan 22 flows toward the gap, and an annular air flow is formed in the gap between the air collecting ring 241 and the power disk 23, and the annular air flow pushes the driving blade 232 to drive the power disk 23 to rotate.
  • the air collecting ring 241 is uniformly provided with the same number of air inlets 242 as the number of the fan 22, and is eight in this embodiment.
  • Each fan 22 supplies air to the gap between the air collecting ring 241 and the power disk 23 through the air inlet 242.
  • the gap has a collecting effect on the wind, so that the wind of the fan 22 is more concentrated, and the wind energy loss of the fan 22 is reduced.
  • the driving force received by the power disk 23 is made stronger.
  • the air collecting ring 241 is an annular arch on the supporting plate 24, but the height of the arching is different, the air collecting ring 241 provided with the air inlet 242 is arched higher, and the other part is lower arched. .
  • the arched state of the collecting ring 241 in FIG. 8 is a normal arching state.
  • the arched state of the collecting ring 241 in Fig. 3 is the inlet of the blower 22.
  • a plurality of rollers 25 are provided on the upper circumference of the support disk 24.
  • the rollers 25 are used to support the power disk 23, and the axis of the roller 25 is parallel to the contact surface of the power disk 23.
  • the power disk 23 is disposed on the support disk 24 via a roller 25, and the roller 25 has a support for the power disk 23.
  • the power disk 23 is in contact with the roller 25, and drives the roller 25 to rotate together.
  • the sliding friction of the wheel 25 and the support disk 24 is rolling friction, which reduces the power disk 23.
  • Start resistance The axis of the roller 25 is parallel to the contact surface of the power disk 23, the contact surface of the power disk 23 and the roller 25 is inclined, and the axis of the roller 25 is parallel to the slope of the power disk 23, that is, the power disk 23 and the roller 25 are in line contact.
  • the power disk 23 Due to the high speed rotation, the power disk 23 forms a positive pressure below it, thereby separating from the roller 25 to form a suspended state of the air bearing.
  • the suspended power disk 23 has no mechanical contact with the components of the aircraft 100, so there is no kinetic energy loss due to mechanical friction, which improves the kinetic energy utilization of the power disk.
  • the roller 25 can be selected as a bearing, and the bearing has high support rigidity, small wear during rotation, and good mechanical strength.
  • an air inlet ring 30 is disposed on an upper portion of the aircraft body 10, and an air outlet ring 40 is disposed at a lower portion of the aircraft body 10.
  • the airflow is driven by the rotation of the power disk 23 to flow into and out of the air inlet ring 30.
  • the ring 40 flows out.
  • the gas ejected from the lower portion of the aircraft body 10 creates a reverse momentum to lift the aircraft 100.
  • the aircraft body 10 With the rotation of the airflow induced by the power disk 23, the aircraft body 10 produces a degree of non-autonomous rotation, and such non-autonomous rotation of the aircraft body 10 prevents the aircraft 100 from flying properly. Therefore, in order to solve the non-autonomous rotation of the aircraft 100 and improve the utilization of the flying action energy, the aircraft 100 further includes a spin control system 50.
  • the spin control system 50 includes an air inlet ring 30 and an air outlet ring 40.
  • the power unit that is, when the power disk 23 rotates, the airflow of the air inlet ring 30 and the air outlet ring 40 flows, and the air outlet ring 40 is provided with a plurality of air outlet spoilers 41, and the air outlet ring spoiler 41 connects the power disk 23
  • the tangential airflow is converted to a radial airflow.
  • the power disk 23 is sucked in and entrained, and the high-speed rotating airflow is converted into the radially jetted airflow, that is, the spin momentum balance of the spin airflow itself is realized, and the kinetic energy carried by the spin airflow is fully utilized.
  • the spin control system 50 resolves the non-autonomous rotation of the aircraft 100 caused by the power disk 23 on the aircraft 100, reducing kinetic energy losses due to the non-autonomous rotation of the aircraft 100.
  • the direction of the arrow in the figure is the steering of the power disk 23, and the shape of the air outlet ring spoiler 41 is such that one end is tangent to the circle of the power disk 23, and the other end is the same as the radial direction of the power disk 23. That is, one end of the air outlet spoiler 41 is tangential to the aircraft body 10 by the inner end of the aircraft body 10, and the outer edge of the aircraft body 10 is the same as the radial direction of the aircraft body 10.
  • the circular motion of the power disk 23 drives the airflow to rotate, and the rotating airflow is introduced through the tangential end of the airflow ring spoiler 41 and the direction of rotation of the power disk 23, and is derived from the same end in the radial direction of the circular motion of the power disk 23.
  • the self-rotation of the aircraft 100 is subtly suppressed while the gas flow energy of the power disk 23 is wasted.
  • the aircraft 100 thus also includes a servo motor 61 and an annular guide vane 60.
  • the guide vane 60 is disposed on the air outlet ring 40, and the air flow is guided by the air outlet ring 40 to the flow wing 60.
  • the servo motor drives the shape of the guide vane 60 to change. Assuming that the guide vanes 60 with the drive motor make the flight direction of the aircraft 100 adjustable, the different guidance of the airflow to the air outlet ring 40 by the guide vanes 60 causes the aircraft 100 to either rise, or float, or advance, or Retreat, or lean forward, or recline, or roll left and right.
  • the flow of air ejected radially from the air outlet ring 40 is directed to the flow wing 60, which corresponds to the direction control unit of the aircraft 100, and the direction of the air flow is directed by the change in shape of the air guide vane 60 such that the aircraft 100 has a different Flight direction.
  • the shape of the guide vane 60 is controlled by the servo motor. Since the guide vane 60 is disposed on the air outlet ring 40, the guide vane 60 is annular, and the shape change is continuous, so that the aircraft 100 can be oriented in various directions. The reversing direction enables precise control of the flight direction of the aircraft 100.
  • the aircraft 100 is propelled to the right for advancement, and the right side is the nose of the aircraft 100.
  • the right guide vane 60 is bent into the interior of the aircraft body 10, and the airflow ejected from the air outlet ring 40 is directed to the left side of the aircraft 100, and then continuously turned outward until the left guide vane 60 is turned over.
  • the airflow radially discharged from the air outlet ring 40 is also diverted to the left.
  • the guide vanes 60 on both sides of the middle portion are folded downward at 90°, and the flow guiding direction is vertically downward.
  • the direction of the airflow in this state is as shown in FIG. 14, and the aircraft 100 receives a constant lifting force and a driving force that advances to the right, thereby achieving the leveling of the aircraft 100.
  • the guide vane 60 when the guide vane 60 is bent downward by 90°, the guide vane 60 directs the wind ejected from the air outlet ring 40 downward, and the circumference of the aircraft 100 is evenly pressed.
  • the upward recoil force caused by the jetted airflow the aircraft 100 is subjected to a vertically upward torsion force, and the aircraft 100 flies vertically upward.
  • the radial outflow of the air outlet ring 40 of the aircraft 100 is directed vertically downward by the guide vanes 60, and the lifting force of the aircraft 100 is achieved by the collision of the air flow.
  • the radial airflow of the air outlet ring 40 is directed to the left side of the aircraft 100, and then continuously turned outward until The guide vanes 60 on the left are bent downward at 90°.
  • the radial air outlet of the air outlet ring 40 on the right side of the aircraft 100 is straightly led out by the guide vane 60, and then gradually led out obliquely downward to the left until the left side is turned vertically downward, and the derived wind direction change is continuous. of.
  • the force on the left side of the aircraft 100 is greater than the right side, thereby achieving a swooping maneuver when the aircraft 100 is flying to the right.
  • the aircraft 100 can be lifted upright or tilted upwards.
  • the different ways can be selected according to the actual lifting and landing conditions.
  • the continuous change of the shape of the annular guide vane 60 is controlled by a servo motor, and the guide vane 60 is a flexible member.
  • the guide vane 60 of the embodiment adopts a flexible solar panel as a surface layer. Converting solar energy into electrical energy and enhancing the power reserve of the aircraft 100.
  • a mechanism such as a screw rod is disposed inside the guide vane 60, and the shape of the guide vane 60 is changed by the movement of the internal screw rod link by the servo motor.
  • the spin control system 50 further includes an air inlet ring 30.
  • the air inlet ring 30 is provided with a plurality of air inlet ring spoilers 31.
  • the inclination direction of the air inlet ring spoiler 31 is the same as the direction of rotation of the power disk 23.
  • the direction of the arrow in the figure is the direction of rotation of the power disk 23, and the direction of inclination of the inlet ring disturbing blade 31 is the same as that of the power disk.
  • An air inlet ring spoiler 31 is provided on the air inlet ring 30 of the aircraft body 10 in the same oblique direction as the power disk 23 is turned.
  • the air inlet ring spoiler 31 causes the aircraft body 10 to obtain a rotation that is the same as the direction of rotation of the power disk 23, thereby balancing the aforementioned non-autonomous spin.
  • the inclination angle of the air inlet ring spoiler 31 is variable, and the inclination angle of the air inlet ring spoiler 31 is controlled by the servo motor. 311 control, as shown in Figure 19.
  • the fan 22 is activated, and the gas induced by the fan 22 flows, and a surrounding airflow is formed through the gap between the air collecting ring 241 of the support disk 24 and the power disk 23.
  • the surrounding airflow flows toward the drive blades 232 provided in the gap to drive the power disk 23 to rotate.
  • the turbine blades 231 on the power disk 23 cause the flow of the gas between the intake ring 30 and the air outlet ring 40 when the power disk 23 is rotated.
  • the air inlet ring spoiler 31 on the air inlet ring 30 has the same direction of rotation as the power disk 23, so that the aircraft body 10 obtains a rotational stress that balances its non-autonomous rotation.
  • the air outlet ring 40 is provided with an air outlet spoiler 41, and the air flow 23 is sucked and wrapped by the air outlet ring to reduce the airflow which is rotated at a high speed into a radial discharge.
  • the outer edge of the aircraft body 10 is also provided with a guide vane 60, and the radially ejected airflow flow guide vane 60 is transformed by the shape of the guide vane 60 to change the state of flight of the aircraft 100.
  • the flying power system, the aircraft and the method for making the aircraft level, vertical take-off, pitch, and roll have the following beneficial effects:
  • the annular power disk has excellent dynamic balance characteristics, and the gyro effect generated by the high-speed rotation of the power disk enables the aircraft to obtain huge flying action energy.
  • the flight power system has a simple structure, good dynamic balance, strong stability and strong kinetic energy.
  • the combination of the fan and the driving blade makes the aircraft powerful.
  • the drive unit is a number of fans. When a single fan fails, it will hardly affect the flight. The failure of multiple flow fans is negligible.
  • the power source of the aircraft is more stable and the flight is safer.
  • the fan is evenly arranged with respect to the circumference of the power disk, so that the driving force of the power disk is relatively stable and the dynamic balance is better.
  • the power disk is connected to the support plate by rollers, which reduces the starting resistance of the power disk.
  • the power disk can be suspended in high-speed rotation, and the power of the power disk is fully utilized. At the same time, the power disk in the suspended state, that is, the aircraft body has no mechanical contact, which greatly reduces the noise of the aircraft.
  • the aircraft body has a dome-shaped dish with a power disk on the upper ring.
  • the infinite structure of the circular dish-shaped aircraft makes the aircraft have no force and sharp points during flight, which can fully resolve the influence of the ambient airflow and obtain a better flight experience.
  • the aircraft can be parked on the surface or on the water surface.
  • the application environment is diverse and the adaptability to the parking platform is strong.
  • the power disk of the invention is suspended during operation, has no mechanical contact with the aircraft body, and the air outlet is located below the aircraft body, and the power device is located inside the aircraft body and at the edge, which can reduce the noise of the aircraft during flight and realize the low-noise flight of the aircraft. .
  • attitude and motion control such as plane flight, vertical takeoff and landing, pitch and roll are realized, and the control precision is high and the flexibility is good.
  • the flight power system, the aircraft and the method for flying, vertical take-off, pitch and roll of the aircraft provided by the embodiments of the invention have good dynamic balance, strong stability and strong kinetic energy, so that the aircraft can obtain huge Flight stability and higher security.
  • the aircraft can fully resolve the influence of the ambient airflow during the flight, achieve a variety of attitude and motion control, control accuracy is higher, flexibility is better, and can achieve low-noise flight, thus obtaining a better flight experience.
  • the aircraft has a variety of application environments and is highly adaptable to the mooring platform.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Wind Motors (AREA)

Abstract

L'invention concerne un système d'alimentation pour envol, destiné à être utilisé dans un aéronef (100), comprenant une unité de stockage d'énergie (21) et une unité d'entraînement, l'unité de stockage d'énergie fournissant de l'énergie pour l'unité d'entraînement, et comprenant également un disque de puissance en forme d'anneau (23). Le disque de puissance entoure un corps d'aéronef (10), de multiples pales de turbine (231) sont disposées de manière circonférentielle sur une surface du disque d'alimentation, et l'unité d'entraînement entraîne le disque d'alimentation en rotation; un anneau d'entrée d'air (30) est formé sur une partie supérieure du corps d'aéronef, et un anneau de sortie d'air (40) est formé au niveau d'une partie inférieure du corps d'aéronef; lorsque le disque de puissance tourne, de l'air s'écoule entre l'anneau d'entrée d'air et l'anneau de sortie d'air. La présente invention concerne également un aéronef équipé dudit système d'alimentation pour envol et un procédé pour obtenir un vol en palier, un décollage/atterrissage vertical, un tangage et un roulis pour un aéronef. Au fur et à mesure que la rotation du disque de puissance produit un effet d'aspiration d'air et que la direction d'agencement des pales de turbine est fixe, l'écoulement d'air est aspiré de l'anneau d'entrée d'air à l'anneau de sortie d'air au moyen de la rotation du disque d'alimentation entraîné par l'unité d'entraînement. Le disque de puissance en forme d'anneau présente de bonnes caractéristiques d'équilibre dynamique, et l'effet gyroscopique provoqué par la rotation rapide du disque d'alimentation permet à l'aéronef d'obtenir une grande stabilité.
PCT/CN2017/107309 2016-10-21 2017-10-23 Système d'alimentation pour envol, aéronef, et procédé d'obtention d'un vol en palier, de décollage/atterrissage vertical, de tangage et de roulis destiné à un aéronef WO2018072756A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201610921248.0A CN106364665B (zh) 2016-10-21 2016-10-21 飞行动力系统及飞行器
CN201610921248.0 2016-10-21

Publications (1)

Publication Number Publication Date
WO2018072756A1 true WO2018072756A1 (fr) 2018-04-26

Family

ID=57895871

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2017/107309 WO2018072756A1 (fr) 2016-10-21 2017-10-23 Système d'alimentation pour envol, aéronef, et procédé d'obtention d'un vol en palier, de décollage/atterrissage vertical, de tangage et de roulis destiné à un aéronef

Country Status (2)

Country Link
CN (1) CN106364665B (fr)
WO (1) WO2018072756A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106379534B (zh) * 2016-10-21 2018-11-23 刘德庆 自旋控制系统及飞行器
CN106364665B (zh) * 2016-10-21 2018-11-23 刘德庆 飞行动力系统及飞行器
CN108995808A (zh) * 2018-08-31 2018-12-14 耿天侃 可垂直起降可悬停的环形翼碟形飞行器

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5072892A (en) * 1989-12-01 1991-12-17 Carrington Alfred C Aerodynamic device
EP0534611A1 (fr) * 1991-09-24 1993-03-31 A.H. Beck Foundation Co., Inc. Perfectionnements aux avions
CN2437594Y (zh) * 2000-05-17 2001-07-04 高恒伟 环翼直升机
CN1907807A (zh) * 2006-08-09 2007-02-07 黄革雄 一种固定机翼飞行器垂直起降的方法及飞行器
US20100116924A1 (en) * 2005-09-20 2010-05-13 Bastian Family Holdings, Inc. Stabilizing power source for a vehicle
CN106364665A (zh) * 2016-10-21 2017-02-01 刘德庆 飞行动力系统及飞行器
CN106379534A (zh) * 2016-10-21 2017-02-08 刘德庆 自旋控制系统及飞行器
CN206087305U (zh) * 2016-10-21 2017-04-12 刘德庆 自旋控制系统及飞行器
CN206218208U (zh) * 2016-10-21 2017-06-06 刘德庆 飞行动力系统及飞行器

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3123320A (en) * 1964-03-03 slaughter
US2996266A (en) * 1958-03-20 1961-08-15 Rebasti Antonio Device for obtaining the sustentation of supporting surfaces of aircraft
DE1456032A1 (de) * 1965-07-06 1968-12-12 Herbert Glass Rotierende Flugscheibe
CN100354182C (zh) * 2003-07-16 2007-12-12 肖立峰 伞翼喷气飞行器

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5072892A (en) * 1989-12-01 1991-12-17 Carrington Alfred C Aerodynamic device
EP0534611A1 (fr) * 1991-09-24 1993-03-31 A.H. Beck Foundation Co., Inc. Perfectionnements aux avions
CN2437594Y (zh) * 2000-05-17 2001-07-04 高恒伟 环翼直升机
US20100116924A1 (en) * 2005-09-20 2010-05-13 Bastian Family Holdings, Inc. Stabilizing power source for a vehicle
CN1907807A (zh) * 2006-08-09 2007-02-07 黄革雄 一种固定机翼飞行器垂直起降的方法及飞行器
CN106364665A (zh) * 2016-10-21 2017-02-01 刘德庆 飞行动力系统及飞行器
CN106379534A (zh) * 2016-10-21 2017-02-08 刘德庆 自旋控制系统及飞行器
CN206087305U (zh) * 2016-10-21 2017-04-12 刘德庆 自旋控制系统及飞行器
CN206218208U (zh) * 2016-10-21 2017-06-06 刘德庆 飞行动力系统及飞行器

Also Published As

Publication number Publication date
CN106364665A (zh) 2017-02-01
CN106364665B (zh) 2018-11-23

Similar Documents

Publication Publication Date Title
WO2018072757A1 (fr) Système de commande à auto-rotation et véhicule de vol
US9487286B2 (en) Lift and propulsion device, and heavier-than-air aircraft provided with such a device
US8016226B1 (en) Vertical take off and landing aircraft system with energy recapture technology
US11485477B2 (en) Flying apparatus
RU2670356C2 (ru) Выполненный с возможностью вертикального взлета летательный аппарат
CN106004287B (zh) 两栖多功能垂直起降飞行器
JP4603222B2 (ja) 飛行機及び飛行機の操縦方法
US5516060A (en) Vertical take off and landing and horizontal flight aircraft
US2382460A (en) Aircraft
CN100340765C (zh) 一种动力传输装置
US20180222579A1 (en) Lift rotor and vertical or short take-off and/or landing hybrid aerodyne comprising same
CA2864580A1 (fr) Mecanisme de reglage d'ailes
CA2195581A1 (fr) Aeronef trimodal gyrostabilise
WO2018072756A1 (fr) Système d'alimentation pour envol, aéronef, et procédé d'obtention d'un vol en palier, de décollage/atterrissage vertical, de tangage et de roulis destiné à un aéronef
CN109515704B (zh) 基于摆线桨技术的涵道卷流旋翼飞行器
CN112334386A (zh) 垂直起飞和着陆的个人飞行设备
US6837457B2 (en) Aircraft rotor and aircraft
JP2022530223A (ja) 垂直離着陸航空機、および関連する制御方法
US20120099983A1 (en) Torque Balanced, Lift Rotor Module, Providing Increased Lift, With Few or No Moving Parts
US7427047B2 (en) Powered aircraft including inflatable and rotatable bodies exhibiting a circular cross-section perpendicular to its rotation axis and in order to generate a lift force
CN206087305U (zh) 自旋控制系统及飞行器
US20030122033A1 (en) Ring-shaped wing helicopter
CN101362510A (zh) 用于流体动力学装置的推力转向护罩
CN110949663B (zh) 桨尖射流的自转旋翼机及其实现垂直跳跃起飞的方法
CN206218208U (zh) 飞行动力系统及飞行器

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 17862866

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 17862866

Country of ref document: EP

Kind code of ref document: A1