WO2018072757A1 - 自旋控制***及飞行器 - Google Patents
自旋控制***及飞行器 Download PDFInfo
- Publication number
- WO2018072757A1 WO2018072757A1 PCT/CN2017/107313 CN2017107313W WO2018072757A1 WO 2018072757 A1 WO2018072757 A1 WO 2018072757A1 CN 2017107313 W CN2017107313 W CN 2017107313W WO 2018072757 A1 WO2018072757 A1 WO 2018072757A1
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- Prior art keywords
- ring
- aircraft
- air
- power
- disk
- Prior art date
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- 238000009987 spinning Methods 0.000 title abstract 3
- 230000033001 locomotion Effects 0.000 claims abstract description 19
- 230000008859 change Effects 0.000 claims description 18
- 238000004146 energy storage Methods 0.000 claims description 18
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- 239000000446 fuel Substances 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
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- 229910000746 Structural steel Inorganic materials 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
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- 239000004917 carbon fiber Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
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- 230000002708 enhancing effect Effects 0.000 description 1
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- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
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Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/001—Flying saucers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
- B64C39/062—Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings
- B64C39/064—Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings with radial airflow
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
Definitions
- the present invention relates to the field of aircraft, and in particular to a spin control system and an 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 and to provide a spin control system and an aircraft that can resolve spin stress and improve kinetic energy utilization.
- the first solution provided by the present invention is as follows:
- a spin control system is applied to an aircraft, the aircraft comprising a power unit for circular motion, the spin control system comprising an air inlet ring and an air outlet ring, the air intake ring when the power unit rotates And the airflow of the air outlet ring,
- the air outlet ring is provided with a plurality of air outlet ring spoilers, and the air outlet ring spoiler converts the tangential air flow of the power unit into a radial air flow.
- the airflow that is sucked in and entangled by the airflow ring to convert the high-speed rotating airflow into the radial jetted airflow achieves the spin momentum balance of the spin airflow itself, and fully utilizes the kinetic energy it carries.
- the spin control system resolves the self-rotation of the aircraft caused by the power unit on the aircraft, reducing the loss of kinetic energy due to self-rotation.
- a servo motor drives a shape change of the guide vane.
- the flow of air ejected radially from the air outlet ring guides the flow wing, which is equivalent to the direction control unit of the aircraft, and the direction of the air flow is guided by the change of the shape of the air guide wing so that the aircraft has different flight directions.
- the shape of the guide vane is controlled by the servo motor. Since the guide vane ring is arranged on the air outlet ring, the guide vane is annular, and the shape change is continuous, so that the aircraft can be reversed in all directions to achieve the right Precise control of the flight direction of the aircraft.
- the outlet ring spoiler is shaped such that one end is tangent to a circle of circular motion of the power unit and the other end is in the same radial direction as the circular motion of the power unit.
- the circular motion of the power unit drives the airflow to rotate.
- the rotating airflow is introduced through the tangential end of the airflow ring spoiler and the direction of rotation of the power unit, and is derived from the same end in the radial direction of the circular motion of the power unit, which is subtly suppressed.
- the self-rotation of the aircraft, while at the same time wasted the gas flow energy of the power unit.
- the inlet ring is circumferentially provided with a plurality of inlet ring spoilers, the direction of inclination of the inlet ring spoiler being the same as the steering of the power unit.
- the power unit When the power unit rotates, it induces the same airflow, which causes the indirect rotation of the aircraft body in the opposite direction, which makes the aircraft unable to fly normally.
- An air inlet ring spoiler is provided on the air inlet ring of the aircraft body in the same oblique direction as the power unit steering.
- the air intake ring turbulence wing causes the aircraft body to obtain a rotation similar to the direction of rotation of the power unit, thereby balancing the above-mentioned non-autonomous self-rotation.
- the angle of inclination of the air inlet ring spoiler is variable, and the angle of inclination of the air inlet ring is controlled by a motor.
- the inclination angle of the air inlet ring is variable to ensure that the aircraft body can always obtain a suitable spin stress.
- the second solution provided by the present invention is as follows:
- An aircraft including an aircraft body, further comprising the spin control system described above.
- the airflow that is sucked in and entangled by the airflow ring to convert the high-speed rotating airflow into the radial jetted airflow achieves the spin momentum balance of the spin airflow itself, and fully utilizes the kinetic energy it carries.
- the spin control system resolves the self-rotation of the aircraft caused by the power unit on the aircraft, reducing the loss of kinetic energy due to self-rotation.
- control system further includes a servo motor and an annular guide vane disposed on an outer edge of the aircraft body, the air flow flowing from the air outlet ring
- the servo motor drives a shape change of the guide vane on the guide vane.
- the spin control system further includes a servo motor and an annular guide vane, the guide vane ring is disposed on the air outlet ring, and the air flow flows from the air outlet ring
- the servo motor drives a shape change of the guide vane on the guide vane.
- the flow of air ejected radially from the air outlet ring guides the flow wing, which is equivalent to the direction control unit of the aircraft, and the direction of the air flow is guided by the change of the shape of the air guide wing so that the aircraft has different flight directions.
- the shape of the guide vane is controlled by the servo motor. Since the guide vane ring is arranged on the air outlet ring, the guide vane is annular, and the shape change is continuous, so that the aircraft can be reversed in all directions to achieve the right Precise control of the flight direction of the aircraft.
- the outlet ring spoiler is shaped such that one end is tangent to a circle of circular motion of the power unit and the other end is in the same radial direction as the circular motion of the power unit.
- the circular motion of the power unit drives the airflow to rotate.
- the rotating airflow is introduced through the tangential end of the airflow ring spoiler and the direction of rotation of the power unit, and is derived from the same end in the radial direction of the circular motion of the power unit, which is subtly suppressed.
- the self-rotation of the aircraft, while at the same time wasted the gas flow energy of the power unit.
- the inlet ring is circumferentially provided with a plurality of inlet ring spoilers, the direction of inclination of the inlet ring spoiler being the same as the steering of the power unit.
- the power unit When the power unit rotates, it induces the same airflow, which causes the indirect rotation of the aircraft body in the opposite direction, which makes the aircraft unable to fly normally.
- An air inlet ring spoiler is provided on the air inlet ring of the aircraft body in the same oblique direction as the power unit steering.
- the air intake ring turbulence wing causes the aircraft body to obtain a rotation similar to the direction of rotation of the power unit, thereby balancing the above-mentioned non-autonomous self-rotation.
- the angle of inclination of the air inlet ring spoiler is variable, and the angle of inclination of the air inlet ring is controlled by a motor.
- the inclination angle of the air inlet ring is variable.
- the spin control system further includes an energy storage unit and a drive unit, the drive unit including a fan, the energy storage unit being evenly distributed on the aircraft body to power the fan.
- the spin control system further includes a power disk and a support disk, the power disk and the support disk being in the shape of a disk, both of which are disposed on the aircraft body.
- the power disk and the support disk are both annular and both are integrally formed; the power disk is rotatably coupled to the support disk.
- one side of the power disk is provided with a plurality of turbine blades and the other side is provided with a plurality of drive blades.
- the support disk is provided with an annular air collecting ring, and a gap is formed between the air collecting ring and the power disk, and the driving blade is disposed in the gap.
- the air collecting ring is an annular arch on the support plate
- the support disk is circumferentially provided with a plurality of rollers for supporting the power disk, the axis of the roller being parallel to the contact surface of the power disk.
- the contact surface of the power disk and the roller is a slope, and the power disk is in line contact with the roller.
- 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.
- spin control system and an aircraft will be described more fully hereinafter with reference to the associated drawings.
- Preferred embodiments of the spin control system and aircraft are given in the drawings.
- spin control systems and aircraft may be implemented in many different forms and are not limited to the embodiments described herein. Rather, the purpose of providing these embodiments is to make the disclosure of the spin control system and aircraft more thorough and comprehensive.
- 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 used in addition to In addition to the axial flow fan, it can also be a turbofan engine.
- 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 in the shape of a disk, and both 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, and when a single fan 22 fails, the flight is hardly affected, and the 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 aircraft is made The power of 100 is abundant. It will be appreciated that 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 two wind directions of the axial flow fan of the present embodiment can drive the forward and reverse rotation of the power disk 23.
- 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.
- the power disk 23 is an embodiment of the power unit, and the power disk 23 can be regarded as a large-sized fan, and the flow of the airflow is induced by the rotation of the power disk 23.
- the power unit can also be a plurality of turbofan engines, such as a plurality of circumferentially distributed turbofan engines, that can illuminate the flow of the airflow.
- 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 rotates at a high speed, a negative pressure is formed below it, and is separated from the roller 25 to form a suspended state of the air bearing.
- the suspended power disk 23 is in 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 is preferably 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.
- the addition of a guide vane 60 with a drive motor allows the flight direction of the aircraft 100 to be adjusted, and the impediment of the airflow to the air outlet ring 40 through the guide vane 60 causes the aircraft 100 to either rise, or float, or advance, Or back, or lean forward, or back, 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 a servo motor. Since the guide vane 60 is disposed on the air outlet ring 40, The guide vanes 60 are annular and their shape changes are continuous, so that the aircraft 100 can be reversed in various directions to achieve 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 intake ring spoiler 31 obtains the same rotation of the aircraft body 10 as the direction of rotation of the power disk 23, thereby balancing the above-described 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.
- the rotational speed of the power disk 23 is large, the non-autonomous rotational stress of the aircraft body 10 is also large, and thus the spin stress generated by the aircraft body 10 itself should also be large.
- the inclination of the air inlet ring spoiler 31 is increased by the servo motor 311 to achieve the purpose of increasing the spin stress of the aircraft body 10. The principle is similar when the speed is small, and will not be described here.
- 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 airflow that is sucked and wrapped by the power unit and the high-speed rotation is converted into a radial jet by the air outlet ring
- the airflow that is, achieves the spin momentum balance of the spin airflow itself, and fully utilizes the kinetic energy it carries.
- the spin control system resolves the self-rotation of the aircraft caused by the power unit on the aircraft, reducing the loss of kinetic energy due to self-rotation.
- the direction of the airflow is directed by a change in the shape of the deflector such that the aircraft has a different direction of flight.
- the guide vanes are annular, and the shape changes are continuous, so that the aircraft can be reversed in all directions to achieve precise control of the flight direction of the aircraft.
- the spoiler of the air inlet ring with the same direction of rotation of the power disk rotates when the power disk rotates to draw or discharge the wind.
- the aircraft body obtains the same spin stress of the power disk steering, and the rotary maneuver is stronger. Provides more powerful power for the aircraft to balance the non-autonomous rotation of the aircraft body caused by the rotation of the power disk.
- the power unit has different rotational speeds, and the direction of the airflow ring spoiler can be changed according to the speed of the power unit, so that the power unit obtains a larger spin stress.
- the aircraft body has a dome-shaped dish shape, and the upper ring is provided with an air inlet ring and an air outlet 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.
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
一种飞行器(100),包括一做圆周运动的动力单元、进风环(30)和出风环(40),动力单元转动时,进风环和出风环的气流流通,出风环上设有若干出风环扰流翼(41),出风环扰流翼将动力单元的切向气流转变为径向气流。所述飞行器利用出风环扰流翼将动力单元吸入并裹挟而高度旋转的气流转变为径向喷出的气流,实现了自旋气流自身的自旋动量平衡,确保了正常飞行。
Description
相关申请的交叉引用
本申请要求于2016年10月21日提交中国专利局的申请号为2016109212495、名称为“自旋控制***及飞行器”的中国专利申请的优先权,其全部内容通过引用结合在本申请中。
本发明涉及飞行器领域,具体而言,涉及一种自旋控制***及飞行器。
目前较为常见的飞行器有固定翼飞机和直升机。固定翼飞机是指由动力装置产生前进的推力或拉力,由机身的固定机翼产生升力,在大气层内飞行的重于空气的航空器。但是固定翼飞机在起飞或降落时均要经过较长的加速或减速,且转弯困难,不能实现即时转向。
直升机借助一副或者几副旋翼升空,能垂直起飞和降落的重于空气的航空器。直升机虽然能够垂直起飞和降落,但直升机旋翼所引动的气流会向周围发散,造成了气流动力的大量损失,飞行速度较慢。且直升机旋翼巨大而外露,极易因触碰物体而发生严重事故。
发明内容
有鉴于此,本发明的目的是为了克服现有技术中的不足,提供一种可化解自旋应力、提高动能利用的自旋控制***及飞行器。
为解决上述问题,本发明提供的第一解决方案如下:
一种自旋控制***,应用于飞行器,所述飞行器包括一做圆周运动的动力单元,所述自旋控制***包括进风环和出风环,所述动力单元转动时,所述进风环和所述出风环的气流流通,
所述出风环上设有若干出风环扰流翼,所述出风环扰流翼将所述动力单元的切向气流转变为径向气流。
利用出风环扰流翼将动力单元吸入并裹挟而高速旋转的气流转变为径向喷出的气流,即实现了自旋气流自身的自旋动量平衡,又充分利用了其携带的动能。自旋控制***化解了飞行器上的动力单元所引起的飞行器的自旋转,减少了因自旋转而产生的动能损失。
在示例性实施例中,还包括伺服电机以及呈环状的导流翼,所述导流翼环设于所述出风环,所述气流由所述出风环流向所述导流翼上,所述伺服电机驱动所述导流翼的形状变化。
径向从出风环中喷出的气流流向导流翼,导流翼相当于飞行器的方向控制单元,由导流翼形状的变化来引导气流方向从而使得飞行器具有不同的飞行方向。通过伺服电机对导流翼进行形状的控制,由于导流翼环设于出风环,导流翼呈环状,其形状的变化是连续的,从而实现飞行器可向各个方向换向,实现对飞行器飞行方向的精准控制。
在示例性实施例中,所述出风环扰流翼的形状为一端与所述动力单元的圆周运动的圆相切,另一端与所述动力单元圆周运动的径向方向相同。
动力单元的圆周运动带动气流旋转,旋转的气流通过出风环扰流翼与动力单元转动方向的相切的一端导入,从与动力单元圆周运动的径向方向相同的一端导出,巧妙地抑制了飞行器的自旋转,同时有没有浪费动力单元的气流动能。
在示例性实施例中,所述进风环圆周设有若干进风环扰流翼,所述进风环扰流翼的倾斜方向与所述动力单元的转向相同。
动力单元在转动时引动同向的气流,该气流会引起飞行器本体的反方向的非自主转动,这会使飞行器无法正常飞行。在飞行器本体的进风环上设置与动力单元转向相同倾斜方向的进风环扰流翼。在动力单元引动气体流动时,进风环扰流翼使的飞行器本体获得一个与动力单元转动方向相同的旋转,从而平衡掉了上述的非自主自旋转。
在示例性实施例中,所述进风环扰流翼的倾斜角度可变,所述进风环扰流翼的倾角由一电机控制。
由于动力单元的转动速度可变,为保证飞行器本体始终能获得较为合适的自旋应力,进风环扰流翼的倾斜角度可变。
为解决上述问题,本发明提供的第二解决方案如下:
一种飞行器,包括飞行器本体,还包括上述的自旋控制***。
利用出风环扰流翼将动力单元吸入并裹挟而高速旋转的气流转变为径向喷出的气流,即实现了自旋气流自身的自旋动量平衡,又充分利用了其携带的动能。自旋控制***化解了飞行器上的动力单元所引起的飞行器的自旋转,减少了因自旋转而产生的动能损失。
在示例性实施例中,所述控制***还包括伺服电机以及呈环状的导流翼,所述导流翼环设于所述飞行器本体的外沿,所述气流由所述出风环流向所述导流翼上,所述伺服电机驱动所述导流翼的形状变化。
在示例性实施例中,所述自旋控制***还包括伺服电机以及呈环状的导流翼,所述导流翼环设于所述出风环,所述气流由所述出风环流向所述导流翼上,所述伺服电机驱动所述导流翼的形状变化。
径向从出风环中喷出的气流流向导流翼,导流翼相当于飞行器的方向控制单元,由导流翼形状的变化来引导气流方向从而使得飞行器具有不同的飞行方向。通过伺服电机对导流翼进行形状的控制,由于导流翼环设于出风环,导流翼呈环状,其形状的变化是连续的,从而实现飞行器可向各个方向换向,实现对飞行器飞行方向的精准控制。
在示例性实施例中,所述出风环扰流翼的形状为一端与所述动力单元的圆周运动的圆相切,另一端与所述动力单元圆周运动的径向方向相同。
动力单元的圆周运动带动气流旋转,旋转的气流通过出风环扰流翼与动力单元转动方向的相切的一端导入,从与动力单元圆周运动的径向方向相同的一端导出,巧妙地抑制了飞行器的自旋转,同时有没有浪费动力单元的气流动能。
在示例性实施例中,所述进风环圆周设有若干进风环扰流翼,所述进风环扰流翼的倾斜方向与所述动力单元的转向相同。
动力单元在转动时引动同向的气流,该气流会引起飞行器本体的反方向的非自主转动,这会使飞行器无法正常飞行。在飞行器本体的进风环上设置与动力单元转向相同倾斜方向的进风环扰流翼。在动力单元引动气体流动时,进风环扰流翼使的飞行器本体获得一个与动力单元转动方向相同的旋转,从而平衡掉了上述的非自主自旋转。
在示例性实施例中,所述进风环扰流翼的倾斜角度可变,所述进风环扰流翼的倾角由一电机控制。
由于动力单元的转动速度可变,为保证飞行器本体始终能获得较为合适的自
旋应力,进风环扰流翼的倾斜角度可变。
在示例性实施例中,所述自旋控制***还包括储能单元和驱动单元,所述驱动单元包括风机,所述储能单元均布于所述飞行器本体上,为所述风机提供动力。
在示例性实施例中,所述自旋控制***还包括动力盘和支承盘,所述动力盘和支承盘呈圆盘状,二者均环设于飞行器本体上。
在示例性实施例中,所述动力盘和所述支承盘均为圆环状,二者均为一体成型;所述动力盘转动连接于所述支承盘。
在示例性实施例中,所述动力盘的一面设有若干涡轮叶片,另一面设有若干驱动叶片。
在示例性实施例中,所述支承盘设有圆环状的聚风环,所述聚风环与动力盘之间形成间隙,驱动叶片设于间隙中。
在示例性实施例中,所述聚风环为所述支撑盘上的圆环状拱起
在示例性实施例中,所述支承盘上圆周设有若干滚轮,所述滚轮用于支撑所述动力盘,所述滚轮的轴线与所述动力盘的接触面平行。
在示例性实施例中,所述动力盘与所述滚轮的接触面为斜面,所述动力盘与所述滚轮线接触。
为使本发明的上述目的、特征和优点能更明显和易懂,下文特举较佳实施例,并配合所附附图,做详细说明如下。
为了更清楚地说明本发明实施例的技术方案,下面将对实施例中所需要使用的附图作简单地介绍,应当理解,以下附图仅示出了本发明的某些实施例,因此不应被看作是对范围的限定,对于本领域普通技术人员来讲,在不付出创造性劳动的前提下,还可以根据这些附图获得其他相关的附图。
图1示出了本发明实施例所提供的飞行器的主剖面示意图;
图2示出了本发明实施例所提供的飞行器泊于水面的示意图;
图3示出了本发明实施例所提供的飞行动力***的放大结构示意图;
图4示出了本发明实施例所提供的飞行器的俯视透视图;
图5示出了本发明实施例所提供的动力盘的俯视图;
图6示出了本发明实施例所提供的动力盘的主视图;
图7示出了本发明实施例所提供的动力盘的仰视图;
图8示出了本发明实施例所提供的飞行动力***的动力盘支承局部放大示意图;
图9示出了本发明实施例所提供的飞行器的俯视图;
图10示出了本发明实施例所提供的飞行器的仰视图;
图11示出了本发明实施例所提供的自旋控制***的结构示意图;
图12示出了本发明实施例所提供的出风环扰流翼与动力盘转向的结构示意图;
图13示出了本发明实施例所提供的飞行器的平飞机动控制结构示意图;
图14示出了本发明实施例所提供的飞行器的平飞气流方向示意图;
图15示出了本发明实施例所提供的飞行器的直升控制结构示意图;
图16示出了本发明实施例所提供的飞行器的昂头机动控制结构示意图;
图17示出了本发明实施例所提供的飞行器的俯冲机动控制结构示意图;
图18示出了本发明实施例所提供的进风环扰流翼与动力盘转向的结构示意图;
图19示出了本发明实施例所提供的进风环扰流翼倾角调节的结构示意图。
主要元件符号说明:
100-飞行器;10-飞行器本体;11-舱门;12-起落架;20-飞行动力***;21-储能单元;22-风机;23-动力盘;231-涡轮叶片;232-驱动叶片;24-支承盘;241-聚风环;242-进风口;25-滚轮;30-进风环;31-进风环扰流翼;311、61-伺服电机;40-出风环;41-出风环扰流翼;50-自旋控制***;60-导流翼。
为了便于理解本发明,下面将参照相关附图对自旋控制***及飞行器进行更全面的描述。附图中给出了自旋控制***及飞行器的优选实施例。但是,自旋控制***及飞行器可以通过许多不同的形式来实现,并不限于本文所描述的实施例。相反地,提供这些实施例的目的是使对自旋控制***及飞行器的公开内容更加透彻全面。
需要说明的是,当元件被称为“固定于”另一个元件,它可以直接在另一个元件上或者也可以存在居中的元件。当一个元件被认为是“连接”另一个元件,它可以是直接连接到另一个元件或者可能同时存在居中元件。相反,当元件被称作“直接在”另一元件“上”时,不存在中间元件。本文所使用的术语“垂直的”、“水平的”、“左”、“右”
以及类似的表述只是为了说明的目的。
除非另有定义,本文所使用的所有的技术和科学术语与属于本发明的技术领域的技术人员通常理解的含义相同。本文中在自旋控制***及飞行器的说明书中所使用的术语只是为了描述具体的实施例的目的,不是旨在限制本发明。本文所使用的术语“及/或”包括一个或多个相关的所列项目的任意的和所有的组合。
下面结合附图,对本发明的具体实施方式作详细说明。
实施例
如图1所示,飞行器100包括飞行器本体10,飞行器本体10呈圆顶的碟状,与在影视作品中的飞碟形状类似,或与圆顶礼帽的形状类似。飞行器本体10的结构材料可采用与飞机相同的材料,飞行器100在高空飞行时,飞行器本体10承受内压力,需要采用抗拉强度高、耐疲劳的硬铝作蒙皮材料。飞行器本体10的框架采用超硬铝,承受较大载荷的加强框采用高强度结构钢或钛合金。
飞行器本体10呈中空状,中空的内部为容置空间,飞行器本体10内部可分隔成若干部分,如驾驶舱、乘务仓、储物仓、洗手间等。飞行器本体10的圆顶侧面上设有舱门11,用于在飞行器本体10内进出,开启舱门11后可收放云梯(图中未示出),供乘员们返回地面。
飞行器本体10顶部还暗设有巨型降落伞,紧急情况下弹射张开,实现飞行器100的安全降落。
飞行器本体10的底面上设有起落架12,起落架12用于起飞或降落地面滑行时支撑飞行器100并用于地面移动的附件装置。飞行器100在起飞后起落架12可收容于飞行器本体10中。
需要说明的是,本飞行器100凭其质轻、圆形的无极结构性能,不仅可以在地面上起飞和下降,还可以应用于水面上。停于水面的飞行器100可以作为休闲平台和母船使用。图2示出了飞行器100泊于水面的示意图。
请一并参阅图3和图4,飞行器100还包括飞行动力***20,飞行动力***20为飞行器100提供动力,驱动飞行器100飞行。飞行动力***20包括储能单元21、驱动单元、动力盘23和支承盘24。
飞行动力***20包括储能单元21和驱动单元,本实施例中的驱动单元为若干风机22,风机具体为轴流风机,下文做详细描述。可以理解,风机22除了可
以是轴流风机以外,还可以是涡扇发动机。
储能单元21为风机22提供动力。储能单元21可以为电能、燃料或压缩空气,通过将储能单元21的电能或热力能转化为风机22的动能,从而为飞行器100提供飞行动力。
可以理解,电能储能单元21具有安全、无污染的优点,但是电能储能单元21所能储存的能量相对较低。燃料储能单元21具有储能高,提供的动力强劲等优点,但是燃料的易燃易爆性使其携带的安全性低,且燃烧还会产生一定的污染。所以应根据实际使用需求选用不同类型的储能单元21。储能单元21圆周均布于飞行器本体10上,使得飞行器100的受力更加平衡,有利于飞行的平衡性与稳定性。
动力盘23和支承盘24呈圆盘状,二者均环设于飞行器本体10上。支承盘24同心环设于飞行器本体10的外沿,支承盘24相对于飞行器本体10固定。动力盘23转动连接于支承盘24中,即动力盘23可相对支承盘24转动,相对支承盘24的转动即为相对飞行器本体10的转动。
具体的,动力盘23和支承盘24均为圆环状,二者均为一体成型的型材。一体成型的动力盘23结构紧凑,完整,在裹挟气流时,气流泄露少,减少了动能损失。动力盘23的材料可以选用碳纤维,具有质轻,强度高的特性。
请一并参阅图5到图7,动力盘23的一面设有若干涡轮叶片231,另一面设有若干驱动叶片232。若干风机22设于飞行器本体10上并通过驱动叶片232驱动动力盘23转动。
上述,驱动叶片232用于增大动力盘23的受力面积,即增大对动力盘23施加的驱动力。涡轮叶片231用于产生方向稳定的风力。驱动单元为若干个风机22,当单个风机22发生故障,几乎不会影响飞行,多个风机22故障的情况微乎其微。飞行器100的动力源更加的稳定,飞行更加安全。另外,风机22相对动力盘23圆周均匀设置,使得动力盘23的驱动力较为稳定,动平衡性更好。
本实施例中,8个风机22圆周均匀的设于飞行器本体10上,风机22为轴流风机,飞行器本体10上圆周均匀的设有32个电能储能单元21。可以理解,风机22的数量还可以是6个,12个等,储能单元21也可以是其他的数量。
风机22的风吹向驱动叶片232上驱动动力盘23转动,通过涡轮叶片231使得气流产生定向的流动。采用风机22和驱动叶片232的组合方式,使得飞行器
100的动力充沛。可以理解,动力盘23可看做置于飞行器本体10中的巨型风扇,引动飞行器本体10周围气流的流动。
支承盘24设有圆环状的聚风环241,动力盘23转动连接于支承盘24中。聚风环241与动力盘23之间形成间隙,驱动叶片232设于间隙中。每一风机22的风流向该间隙,聚风环241与动力盘23的间隙中形成环形气流,环形气流推动驱动叶片232从而驱动动力盘23转动。该聚风环241上圆周均布有与风机22数量相同的进风口242,本实施例为8个。每一风机22通过该进风口242向聚风环241与动力盘23的间隙中供风,该间隙对风有一个聚拢的效果,使得风机22的风更加集中,减少了风机22的风能损失,使得动力盘23受到的驱动力更加强劲。本实施例的轴流风机的两个风向可以驱动动力盘23的正反转。
需要说明的是,聚风环241为支撑盘24上的圆环状拱起,但拱起的高度不同,设有进风口242的聚风环241处拱起较高,其余部分拱起较低。请一并参阅图8,图8中聚风环241的拱起状态为常态的拱起态。图3中的聚风环241的拱起状态为风机22的进风处。需要说明的是,动力盘23为动力单元的一种实施方式,动力盘23可看做一种大型的风扇,通过动力盘23的转动而引动气流的流动。可以理解动力单元还可以是圆周分布的多个涡扇发动机等其他的可以引动气流流动的动力装置。
支承盘24上圆周设有若干滚轮25,滚轮25用于支撑动力盘23,滚轮25的轴线与动力盘23的接触面平行。
动力盘23通过滚轮25设于支承盘24上,滚轮25对动力盘23有一个支承的作用。在动力盘23转动的起始,动力盘23与滚轮25接触,并带动滚轮25一起转动,滚轮25的设置变动力盘23与支承盘24的滑动摩擦为滚动摩擦,减小了动力盘23的启动阻力。滚轮25的轴线与动力盘23的接触面平行,动力盘23与滚轮25的接触面为斜面,滚轮25的轴线与动力盘23斜面平行,即动力盘23与滚轮25为线接触,这种布置的优点在于,滚轮25对动力盘23的支撑稳定性更好,使得动力盘23的定位更加准确。动力盘23由于高速旋转,会使其下方形成负压,从而与滚轮25分离,形成气承的悬浮态。悬浮态的动力盘23与飞行器100的部件物机械接触,因而没有因机械摩擦而引起的动能损失,提高了动力盘的动能利用率。
需要说明的是,为满足使用强度,滚轮25优选为轴承,轴承的支撑刚度高,转动时的磨损小,具有较好的机械强度。
请一并参阅图9和图10,飞行器本体10上部设有进风环30,飞行器本体10下部设有出风环40,通过动力盘23的转动带动气流由进风环30流进由出风环40流出。由飞行器本体10下部喷出的气体形成反向的冲力,从而将飞行器100托起。
伴随动力盘23所引动的气流旋转,飞行器本体10产生一定程度的非自主旋转,而飞行器本体10的这种非自主旋转使得飞行器100无法正常飞行。因而为解决飞行器100的非自主旋转,提高飞行动能的利用率,飞行器100还包括自旋控制***50。
如图11所示,自旋控制***50包括进风环30和出风环40。动力单元,即动力盘23转动时,进风环30和出风环40的气流流通,出风环40上设有若干出风环扰流翼41,出风环扰流翼41将动力盘23的切向气流转变为径向气流。
利用出风口扰流翼41将动力盘23吸入并裹挟而高速旋转的气流转变为径向喷出的气流,即实现了自旋气流自身的自旋动量平衡,又充分利用了其携带的动能。自旋控制***50化解了飞行器100上的动力盘23所引起的飞行器100的非自主旋转,减少了因飞行器100非自主旋转而产生的动能损失。
如图12所示,图中的箭头方向为动力盘23的转向,出风环扰流翼41的形状为一端与动力盘23的圆相切,另一端与动力盘23的径向方向相同,即出风环扰流翼41一端靠飞行器本体10内端与飞行器本体10相切,靠飞行器本体10外沿与飞行器本体10的径向方向相同。
动力盘23的圆周运动带动气流旋转,旋转的气流通过出风环扰流翼41与动力盘23转动方向的相切的一端导入,从与动力盘23圆周运动的径向方向相同的一端导出,巧妙地抑制了飞行器100的自旋转,同时有没有浪费动力盘23的气流动能。
上述可知,动力盘23所裹挟的气流通过出风环扰流翼41在飞行器本体10的径向喷出,喷出的方向恒定并且在径向上的气流并不能起到将飞行器100托起的作用。因而飞行器100还包括伺服电机61以及呈环状的导流翼60。
请一并参阅图13至图17,导流翼60环设于出风环40,气流由出风环40流向导流翼60上,伺服电机驱动导流翼60的形状变化。加设带有驱动电机的导流翼60使得飞行器100的飞行方向变得可调,通过导流翼60对出风环40的气流的不通导向使得飞行器100或上升、或悬浮、或前行、或后退、或前倾、或后仰、或左右横滚。
径向从出风环40中喷出的气流流向导流翼60,导流翼60相当于飞行器100的方向控制单元,由导流翼60形状的变化来引导气流方向从而使得飞行器100具有不同的飞行方向。通过伺服电机对导流翼60进行形状的控制,由于导流翼60环设于出风环40,
导流翼60呈环状,其形状的变化是连续的,从而实现飞行器100可向各个方向换向,实现对飞行器100飞行方向的精准控制。
具体的,如图13所示,以飞行器100向右飞行为前进,右侧为飞行器100的机头。右侧的导流翼60向飞行器本体10内弯折,将出风环40喷出的气流平直的导向飞行器100的左侧,而后连续的向外翻转,直到左侧的导流翼60翻转至水平,同样将出风环40径向喷出的气流向左导流。可以理解,由于导流翼60形状的连续变化,中部两侧的导流翼60向下呈90°翻折,导流方向垂直向下。该状态下的气流方向如图14所示,飞行器100受到恒定不变的托起力和向右前进的驱动力,从而实现飞行器100的平飞。
如图15所示,当导流翼60圆周向下弯折90°时,导流翼60将出风环40喷出的风竖直向下导流,飞行器100圆周受力均匀,由向下喷射的气流所引起的向上的反冲力,飞行器100受到竖直向上的托力,飞行器100竖直向上飞行。飞行器100的出风环40的径向出风由导流翼60向后竖直向下导出,由气流的对冲实现对飞行器100的托起力。
如图16所示,当右侧的导流翼60向下弯折90°,而后连续向外翻转,直到左侧的导流翼60呈水平展平状。飞行器100右侧出风环40的径向出风由导流翼60竖直向下导出,而后逐渐向左斜下方导出,直到左侧变为水平向左导出,该导出的风向变化是连续的。飞行器100右侧的受力大于左侧,从而实现飞行器100在向右侧飞行时的昂头机动。
如图17所示,当右侧的导流翼60向飞行器本体10内弯折,从而将出风环40的径向气流平直的导向飞行器100的左侧,而后连续的向外翻转,直到左侧的导流翼60呈90°向下弯折。飞行器100右侧出风环40的径向出风由导流翼60向后平直导出,而后逐渐向左斜下方导出,直到左侧变为竖直向下导出,该导出的风向变化是连续的。飞行器100左侧的受力大于右侧,从而实现在飞行器100向右侧飞行时的俯冲机动。
可以理解,飞行器100既可以竖直起升,也可以倾斜向上起升,下降时同理,可根据实际起升、降落场地情况来选用不同的方式。
需要说明的是,圆环状的导流翼60的形状的连续变化由伺服电机控制,导流翼60为一种柔性的部件,本实施例的导流翼60采用柔性太阳能电板做面层,将太阳能转化成电能,增强飞行器100的供电储备。导流翼60内部设有丝杆连杆等机构,通过伺服电机联动内部的丝杆连杆的运动从而改变导流翼60的形状。
自旋控制***50还包括进风环30,进风环30圆周设有若干进风环扰流翼31,进风环扰流翼31的倾斜方向与动力盘23的转动方向相同。
如图18所示,图中的箭头方向即为动力盘23的转动方向,进风环扰流翼31的倾斜方向与动力盘的转向相同。动力盘23在转动时引动同向的气流,该气流会引起飞行器本体10的反方向的非自主转动,这会使飞行器100无法正常飞行。在飞行器本体10的进风环30上设置与动力盘23转向相同倾斜方向的进风环扰流翼31。在动力盘23引动气体流动时,进风环扰流翼31使的飞行器本体10获得一个与动力盘23转动方向相同的旋转,从而平衡掉了上述的非自主自旋转。
由于动力盘23的转动速度可变,为保证飞行器本体10始终能获得较为合适的自旋应力,进风环扰流翼31的倾斜角度可变,进风环扰流翼31的倾角由伺服电机311控制。
如图19所示,若动力盘23的转速较大,飞行器本体10的非自主旋转应力也较大,因而飞行器本体10自身所产生的自旋应力也应较大。通过伺服电机311调整增大进风环扰流翼31的倾角,从而达到增加飞行器本体10的自旋应力的目的。速度较小时的原理类似,在此不做赘述。
本飞行器的工作原理如下:
启动风机22,风机22引动的气体流动,通过支承盘24的聚风环241与动力盘23之间的间隙形成环绕气流。环绕气流流向设于该间隙中的驱动叶片232从而驱动动力盘23转动。动力盘23上的涡轮叶片231使得动力盘23转动时,引起进风环30和出风环40之间的气体流动。进风环30上的进风环扰流翼31与动力盘23的转动方向相同,使得飞行器本体10获得平衡其非自主旋转的旋转应力。同时,出风环40上设有出风环扰流翼41,利用出风环扰流翼41将动力盘23吸入并裹挟而高速旋转的气流转变为径向喷出。飞行器本体10的外沿还环设有导流翼60,径向喷出的气流流向导流翼60通过导流翼60变换形状而导流,从而改变飞行器100飞行的状态。
应注意到:相似的标号和字母在下面的附图中表示类似项,因此,一旦某一项在一个附图中被定义,则在随后的附图中不需要对其进行进一步定义和解释。
以上所述实施例仅表达了本发明的几种实施方式,其描述较为具体和详细,但并不能因此而理解为对本发明专利范围的限制。应当指出的是,对于本领域的普通技术人员来说,在不脱离本发明构思的前提下,还可以做出若干变形和改进,这些都属于本发明的保护范围。因此,本发明专利的保护范围应以所附权利要求为准。
1.利用出风环扰流翼将动力单元吸入并裹挟而高速旋转的气流转变为径向喷出的
气流,即实现了自旋气流自身的自旋动量平衡,又充分利用了其携带的动能。自旋控制***化解了飞行器上的动力单元所引起的飞行器的自旋转,减少了因自旋转而产生的动能损失。
2.由导流翼形状的变化来引导气流方向从而使得飞行器具有不同的飞行方向。导流翼呈环状,其形状的变化是连续的,从而实现飞行器可向各个方向换向,实现对飞行器飞行方向的精准控制。
3.与动力盘转动方向相同的进风环的扰流翼旋向使得动力盘转动将风吸入或排出时,飞行器本体获得更大的于动力盘转向相同的自旋应力,旋转机动性更强,为飞行器提供更加强劲的动力以平衡因动力盘的旋转而引起的飞行器本体非自主旋转。
4.动力单元具有不同的转速,进风环扰流翼的方向可根据动力单元的速度进行变化,从而使得动力单元获得更大的自旋应力。
5.飞行器本体呈圆顶的碟状,其上环设有进风环和出风环。圆碟状的飞行器的无极结构,使得飞行器在飞行时无受力锐点,可充分化解环境气流的影响,获得较佳的飞行体验。
在这里示出和描述的所有示例中,任何具体值应被解释为仅仅是示例性的,而不是作为限制,因此,示例性实施例的其他示例可以具有不同的值。
Claims (19)
- 一种自旋控制***,配置成飞行器,所述飞行器包括一做圆周运动的动力单元,所述自旋控制***包括进风环和出风环,所述动力单元转动时,所述进风环和所述出风环的气流流通,其特征在于,所述出风环上设有若干出风环扰流翼,所述出风环扰流翼将所述动力单元的切向气流转变为径向气流。
- 根据权利要求1所述的自旋控制***,其特征在于,所述出风环扰流翼的形状为一端与所述动力单元的圆周运动的圆相切,另一端与所述动力单元圆周运动的径向方向相同。
- 根据权利要求1或2所述的自旋控制***,其特征在于,所述进风环圆周设有若干进风环扰流翼,所述进风环扰流翼的倾斜方向与所述动力单元的转向相同。
- 根据权利要求3所述的自旋控制***,其特征在于,所述进风环扰流翼的倾斜角度可变,所述进风环扰流翼的倾角由一电机控制。
- 根据权利要求1-4任一项所述的自旋控制***,其特征在于,所述自旋控制***还包括伺服电机以及呈环状的导流翼,所述导流翼环设于所述出风环,所述气流由所述出风环流向所述导流翼上,所述伺服电机驱动所述导流翼的形状变化。
- 一种飞行器,包括飞行器本体,其特征在于,还包括如权利要求1所述的自旋控制***。
- 根据权利要求6所述的飞行器,其特征在于,所述自旋控制***还包括伺服电机以及呈环状的导流翼,环状的所述导流翼设于所述飞行器本体的外沿,所述气流由所述出风环流向所述导流翼上,所述伺服电机驱动所述导流翼的形状变化。
- 根据权利要求6所述的自旋控制***,其特征在于,所述自旋控制***还包括伺服电机以及呈环状的导流翼,所述导流翼环设于所述出风环,所述气流由所述出风环流向所述导流翼上,所述伺服电机驱动所述导流翼的形状变化。
- 根据权利要求6-8任一项所述的飞行器,其特征在于,所述进风环圆周设有若干进风环扰流翼,所述进风环扰流翼的倾斜方向与所述动力单元的转向相同。
- 根据权利要求9所述的飞行器,其特征在于,所述进风环扰流翼的形状为一端与所述动力单元的圆周运动的圆相切,另一端与所述动力单元圆周运动的径向方向相 同。
- 根据权利要求9或10所述的飞行器,其特征在于,所述进风环扰流翼的倾斜角度可变,所述进风环扰流翼的倾角由一电机控制。
- 根据权利要求6所述的飞行器,其特征在于,所述自旋控制***还包括储能单元和驱动单元,所述驱动单元包括风机,所述储能单元均布于所述飞行器本体上,为所述风机提供动力。
- 根据权利要求12所述的飞行器,其特征在于,所述自旋控制***还包括动力盘和支承盘,所述动力盘和支承盘呈圆盘状,二者均环设于飞行器本体上。
- 根据权利要求13所述的飞行器,其特征在于,所述动力盘和所述支承盘均为圆环状,二者均为一体成型;所述动力盘转动连接于所述支承盘。
- 根据权利要求13或14所述的飞行器,其特征在于,所述动力盘的一面设有若干涡轮叶片,另一面设有若干驱动叶片。
- 根据权利要求13-15任一项所述的飞行器,其特征在于,所述支承盘设有圆环状的聚风环,所述聚风环与动力盘之间形成间隙,驱动叶片设于间隙中。
- 根据权利要求16所述的飞行器,其特征在于,所述聚风环为所述支撑盘上的圆环状拱起
- 根据权利要求13-17任一项所述的飞行器,其特征在于,所述支承盘上圆周设有若干滚轮,所述滚轮配置成支撑所述动力盘,所述滚轮的轴线与所述动力盘的接触面平行。
- 根据权利要求18所述的飞行器,其特征在于,所述动力盘与所述滚轮的接触面为斜面,所述动力盘与所述滚轮线接触。
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FR3125278A1 (fr) * | 2021-07-19 | 2023-01-20 | Gfic | Propulseur vectoriel silencieux |
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CN106379534B (zh) * | 2016-10-21 | 2018-11-23 | 刘德庆 | 自旋控制***及飞行器 |
CN106364665B (zh) * | 2016-10-21 | 2018-11-23 | 刘德庆 | 飞行动力***及飞行器 |
DE102019000682B4 (de) * | 2019-01-30 | 2022-07-14 | Kmtc Vortifer Projektgesellschaft Mbh | Flugkörper für Transport und Verkehr |
JP7284685B2 (ja) * | 2019-10-24 | 2023-05-31 | 株式会社Subaru | 円盤型垂直離着陸機 |
CN110963035A (zh) * | 2019-12-18 | 2020-04-07 | 王力丰 | 以压缩空气为动力源的个人飞行器及其运行方法 |
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CN206218208U (zh) * | 2016-10-21 | 2017-06-06 | 刘德庆 | 飞行动力***及飞行器 |
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CN1480376A (zh) * | 2003-07-16 | 2004-03-10 | 肖立峰 | 伞翼喷气飞行器 |
US20130140405A1 (en) * | 2005-09-14 | 2013-06-06 | Wfk & Associates, Llc | Integral Powered Wing Aircraft Utilizing Full Rotary Disc Stacking With Aeronautical Enhancements |
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CN106379534A (zh) * | 2016-10-21 | 2017-02-08 | 刘德庆 | 自旋控制***及飞行器 |
CN206087305U (zh) * | 2016-10-21 | 2017-04-12 | 刘德庆 | 自旋控制***及飞行器 |
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FR3125278A1 (fr) * | 2021-07-19 | 2023-01-20 | Gfic | Propulseur vectoriel silencieux |
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