WO2018224033A1 - 一种仿甲虫鞘翅机翼航空器 - Google Patents

一种仿甲虫鞘翅机翼航空器 Download PDF

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Publication number
WO2018224033A1
WO2018224033A1 PCT/CN2018/090417 CN2018090417W WO2018224033A1 WO 2018224033 A1 WO2018224033 A1 WO 2018224033A1 CN 2018090417 W CN2018090417 W CN 2018090417W WO 2018224033 A1 WO2018224033 A1 WO 2018224033A1
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WIPO (PCT)
Prior art keywords
wing
aircraft
beetle
blade
rotor
Prior art date
Application number
PCT/CN2018/090417
Other languages
English (en)
French (fr)
Inventor
杨卫华
Original Assignee
昆明鞘翼科技有限公司
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
Priority claimed from CN201710434379.0A external-priority patent/CN107097929A/zh
Priority claimed from CN201710434378.6A external-priority patent/CN107226193A/zh
Priority claimed from CN201710444204.8A external-priority patent/CN107244410A/zh
Priority claimed from CN201710443781.5A external-priority patent/CN107140181A/zh
Priority claimed from CN201710484996.1A external-priority patent/CN107140182A/zh
Priority claimed from CN201710484967.5A external-priority patent/CN107264779A/zh
Application filed by 昆明鞘翼科技有限公司 filed Critical 昆明鞘翼科技有限公司
Publication of WO2018224033A1 publication Critical patent/WO2018224033A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft

Definitions

  • the invention relates to an aircraft using a wing of a simulated insect wing as a horizontal wing, in particular to a beetle-like sheath-wing wing aircraft, belonging to the technical field of aircraft.
  • Aircraft can be divided into two categories: fixed wing and rotary wing.
  • Fixed wings are commonly used in horizontal take-off and landing aircraft (such as jet passenger aircraft), while rotating wings are commonly used in vertical take-off and landing aircraft (such as helicopters).
  • the fixed-wing aircraft has high flight speed and simple operation, but it needs to rely on the runway for take-off and landing; while the rotary-wing aircraft can take off and land vertically without relying on the runway for take-off and landing, and the adaptability is strong, but the mechanism is out of control. Complex, slow flight speed and low fuel efficiency.
  • the handling load is much larger than that of the fixed-wing aircraft, increasing the probability of human error.
  • Fifth it is impossible to enlarge: Since the diameter and speed of the rotor are not limited by the speed of the airfoil, the diameter of the rotor is generally more than ten meters. The size of the aircraft is limited and cannot be made larger.
  • the above-mentioned defects of the vertical take-off and landing aircraft come from the contradiction that the wing has to take both the vertical take-off and the horizontal flight to meet the two flight modes, and a more targeted technical method is needed to coordinate it.
  • the technical problem to be solved by the present invention is how to coordinate the contradiction between the two flight modes of the vertical take-off and the horizontal flight of the aircraft.
  • the aircraft can be used to coordinate the vertical take-off and landing of the aircraft by using the beetle-like sheath-wing wing.
  • the present invention provides a beetle-like sheath-wing wing aircraft, including a fuselage 1, a wing 2, a rotary wing 4, a horizontal propulsion device 5, and a wing of a beetle-like coleoptera as a horizontal wing of an aircraft.
  • the wing 2 of the beetle sheath is hinged to the aircraft fuselage 1.
  • the wing of the beetle sheath can automatically complete the sag and flattening movement according to the force of different flight conditions in the air; the beetle sheathed wing aircraft is installed above There is a rotating wing 4, which realizes vertical take-off and landing by the rotating wing.
  • the wing of the beetle-like coleoptera When the aircraft moves up and down vertically, the wing of the beetle-like coleoptera automatically hangs down under the action of gravity and the airflow under the rotor, and tends to be parallel with the fuselage, avoiding the wing down.
  • the occlusion of the washing airflow and the aeroelastic vibration eliminate the interference of the wing to the rotating wing, reduce the resistance of the aircraft's take-off and landing, and lower the center of gravity of the entire aircraft, greatly improving the flight stability of the aircraft; the beetle sheath-wing wing aircraft installation horizontal propulsion device 5 Horizontal flight is achieved by horizontal propulsion, and the wing of the beetle-like coleoptera is automatically lifted up and flattened by the airfoil lift when the aircraft is flying horizontally. Wing, flight level required to provide lift. In the state of the aircraft hovering, the wing of the parasitic beetle can be automatically swayed like a wind vane
  • the wing of the beetle sheathed wing mimics the beetle sheath wing function design, including a set of cantilever 2-1 and wing body 2-2.
  • One end of the cantilever 2-1 is fixed on the fuselage 1 and the other end passes through the free hinge 6 and the wing body.
  • the wing body 2-2 can be freely rotated around the free hinge 6 and automatically complete the sagging or upswing in the air according to the force conditions of different flight conditions.
  • the wing body 2-2 can be designed as a folding or telescopic structure, so that the entire wing can be expanded to a length greater than the height of the body, and the height of the body is exceeded. The wingspan limits, thereby increasing the lift of the aircraft.
  • the length of the cantilever 2-1 needs to ensure that the wing body 2-2 is completely turned down to leave sufficient space between the fuselage 1 to reduce the shielding of the lower washing airflow; preferably, the inner side of the wing body 2-2 is
  • the spacing of the body 1 should generally be greater than 1/2 of the width of the body 1, which is determined according to actual needs.
  • the limiting device 2-3 is a limit mechanism such as an ordinary tie rod or a limit card slot and a limit protrusion, and is specifically determined according to actual needs.
  • the limiting device prevents the rolling instability caused by the unbalanced force while restraining the fixed position of the wing up and down, and ensures that the rigid wing on the left and right sides of the aircraft can be flattened to a stable position.
  • the sagging and the flattening of the wing 2 of the beetle-like coleoptera can be performed by using the gravity of the wing to sag naturally, and using the airfoil lift to overcome the natural gravity of the wing, and the physical principle can be used in the wing.
  • the automatic deformation under the flight state allows the aircraft to have adaptive capabilities, reduce the complexity of manual operations, and improve the fault tolerance.
  • the sagging and upswing of the wing 2 of the beetle sheath can also be forcedly completed by manual operation of an ordinary mechanical or electric control mechanism, that is, the manual adjustment is performed while the wing is adaptively adjusted, and the machine is improved.
  • the flexibility and reliability of wing work greatly enhance the coordination and robustness of aircraft flight.
  • the fuselage 1 of the aircraft is in the form of a sheet, the width of the fuselage is much smaller than the height and the length, and the front and cross sections are narrow and long, and the aspect ratio and the aspect ratio of the fuselage shape are generally greater than 4 ( Specifically, it is determined according to actual needs), thereby greatly reducing the air resistance when the aircraft is flying horizontally or vertically.
  • the vertical body aspect ratio is greater than the aspect ratio
  • the horizontal fuselage the aspect ratio is greater than the aspect ratio
  • the special geometry of the aircraft fuselage ensures the airflow of the fuselage for the horizontal direction and the vertical direction They are unobstructed and form good vertical takeoff and landing and horizontal flight aerodynamic characteristics.
  • the sheet-like aircraft fuselage 1 has a unitary structure or a combined structure of the nacelle 1-1 and the deflector 1-2, and the deflector 1-2 has a continuous surface structure. That is, the outer dimensions of the aircraft body meet the height and length far greater than the width, and can be realized by a monolithic fuselage structure that satisfies the condition, and a fuselage and a nacelle can be combined to form a fuselage, and the length of the fuselage is extended by the deflector or Width, to meet the body aspect ratio and aspect ratio requirements.
  • the baffle can be placed at any position of the upper, lower, middle, front, and rear portions of the nacelle, depending on actual needs.
  • the windward surface of the fuselage 1 and the deflector 1-2 has a symmetrical wedge shape, and the windward surface contour is streamlined to reduce air resistance.
  • the rotor 4 of the aircraft is a retractable rotor, using a set of rotor blades 4-3 that can be fully deployed and fully collapsed in flight, and the rotor blades 4-3 pass through the blade bushings 4-2.
  • the rotor drive shaft 4-1 is connected. When the aircraft takes off and land, the drive shaft 4-1 rotates in the forward direction, and the rotor blades 4-3 are sequentially driven to rotate forward by the blade bushings 4-2, so that all the blades are fully deployed to generate maximum lift; when the aircraft is flying horizontally, the aircraft is driven. When the shaft 4-1 stops rotating, the rotor blades 4-3 will reversely revolve under the action of the oncoming airflow, and finally completely collapse and overlap, and deform into a shape with little air resistance.
  • the retractable rotor realizes the automatic retraction of the rotor through the ratchet action of the blade sleeve and the use of centrifugal force and wind force.
  • the working state of the rotor blade can be automatically adjusted according to the flight conditions, and the horizontal flight of the vertical take-off and landing aircraft rotor is significantly eliminated. Resistance and vibration.
  • the number of the rotor blades 4-3 can be determined as 1, 2, 3, 4, 5, 6, 7, 8 or even more according to needs (the specific number is selected according to actual needs), and the forward and backward rotation of the rotor blades
  • the automatic locking position can be achieved by a locking mechanism on the blade drive bushing or at the blade root.
  • Each blade can be coupled to the rotor drive shaft 4-1 via a paddle bushing 4-2.
  • the blade bushing 4-2 has a ratchet-like one-way locking function that can positively drive the rotary deployment lock and
  • the reverse unidirectional locking structure includes, but is not limited to, each blade bushing 4-2 has upper and lower joint faces respectively matched with the blade bushings of the upper and lower adjacent blades,
  • the joint surface 4-2-1 cooperates with the upper joint surface of the lower blade sleeve, and the upper joint surface 4-2-2 cooperates with the lower joint surface of the upper blade sleeve; the next blade blade is the active blade, The rest are driven blades; the rotor drive shaft 4-1 is connected with the sleeve of the active blade.
  • the rotor drive shaft drives the sleeve of the active blade, according to the mutual cooperation relationship between the upper and lower blade sleeves, the lower part The blade bushing will drive the upper blade bushing in turn to drive the rotor blade to rotate.
  • the angle of each adjacent blade is divided into 360° circumferential angle.
  • a triangular truss can also be used to connect the three blades and the drive shaft, and the three blades are respectively hinged to the three corners of the truss, and can be driven by the drive shaft to form an angle of 120° with each other.
  • the entire rotor may have a folded fan shape, a rectangular shape, a circular shape, or a polygonal shape.
  • the working state of the rotor blade is synchronized with the flight condition of the aircraft, and the working mechanism of the rotor blade is coordinated with the flight of the aircraft, so that the rotor has an adaptive ability to automatically change the aerodynamic shape according to the flight condition of the aircraft, and is completely completed during the flight. Expanded or fully contracted, the transformation process is natural, stable and continuous.
  • the rotor working state can be automatically adjusted according to the flight condition of the aircraft.
  • the opening and closing, the combination of time, natural conversion, smooth transition, no additional manual intervention, adaptive sexuality makes flight control simplified, safe and reliable.
  • the retractable rotor of the aircraft is reasonable in design, simple and natural, and realizes the natural conversion, smooth transition and effective compatibility of the rotor working state in the two modes of vertical take-off and horizontal flight.
  • the sheet-shaped fuselage of the aircraft is mounted with one or more large-area fin fins 3 (the specific number is selected according to actual needs), and the relative motion state of the fins and the airflow is changed by rotating the fins to generate force or change
  • the combined state of the fins generates a moment, and the force or moment generated by the fins is applied to the sheet fuselage to control the attitude of the aircraft.
  • the fins 3 are rotatable about the fin wing shaft, and can be manually operated by a conventional mechanical or electric steering mechanism, rotated about the fin shaft axis, and unfolded or flattened integrally with the sheet fuselage.
  • the fins 3 can be disposed on the head, the back, the abdomen, the tail, and the waist of the body 1, or can be used in pairs or in pairs, and can be determined according to actual needs.
  • the imitation beetle sheath-wing wing aircraft can be separately controlled and seamlessly connected during vertical take-off and landing, and the horizontal propulsion device 5 can be closed when the vehicle is taken off vertically, and then raised to a suitable height to start horizontal propulsion, and the horizontal flight reaches a certain speed. Gradually closing the rotary wing 4, the landing process is reversed.
  • the adaptive operation of the wing 2 of the beetle sheath the strong coupling relationship between the vertical take-off and the horizontal flight drive mechanism is reduced, so that the flight mode is more converted. Natural, smoother, easier, and safer.
  • the invention can complete the sag and flattening movement according to the flight condition in the air, and the wing hangs down when the aircraft moves up and down vertically and is parallel with the fuselage, avoiding the lower side.
  • the occlusion of the washing airflow and the aeroelastic vibration effectively eliminate the interference of the wing to the rotating wing, reduce the resistance to take-off and landing, and lower the center of gravity of the entire aircraft, greatly improving the flight stability of the aircraft; when flying at the aircraft level, the machine resembling the beetle
  • the wing is turned flat and becomes a fixed wing that provides the lift required for horizontal flight. In the state of the aircraft hovering, the wing of the completely drooping beetle sheath can also be automatically winded like a wind vane, safe and efficient.
  • the combined use of the sheet-shaped fuselage of the invention can ensure that the airflow of the airframe is unobstructed for both the horizontal direction and the vertical direction, and the air resistance during forward flight or vertical take-off and landing of the aircraft is greatly reduced, and a good vertical takeoff and landing and level are formed.
  • the aerodynamic characteristics of the flight; the use of the baffle can extend the length or width of the fuselage to meet the aspect ratio and aspect ratio requirements of the fuselage.
  • the use of the retractable rotor can not only expand the blade when the aircraft takes off and land, but also generate the maximum lift. It can also reduce the air resistance when the aircraft is flying horizontally, and adjust the working state of the rotor blade according to the flight conditions. Eliminate the horizontal flight resistance and vibration of the rotor.
  • the invention can effectively coordinate the contradiction between the vertical take-off and the horizontal flight, solve the mutual influence between the rotating wing and the fixed wing, and can adapt according to the flight state.
  • the ground automatically changes the shape and aerodynamic characteristics of the wing, which removes the strong coupling relationship between the vertical take-off and lowering drive mechanism and the horizontal flight drive mechanism, effectively avoiding the conflict between the orthogonal drives, effectively reducing manual intervention and effectively It improves the fault tolerance, flight safety and flight efficiency of flight control. It has the advantages of mechanism coordination, simple structure, low cost, high reliability and good adaptability. It can be widely used in manned aircraft or drones.
  • Figure 1 is a schematic view showing the state in which the aircraft wing of the present invention is in a sag.
  • FIG. 2 is a schematic view showing the aircraft wing of the present invention in an upturned flat state.
  • Figure 3 is a schematic diagram of the wing synchronization mechanism of the present invention.
  • Figure 4 is a front elevational view of the aircraft of the present invention.
  • Fig. 5 is a schematic view showing the state in which the retractable rotor is folded in the embodiment of the present invention.
  • Fig. 6 is a schematic view showing the rotation of the retractable rotor according to the embodiment of the present invention.
  • Figure 7 is a cross-sectional view showing the mutual engagement of the upper and lower sleeves of the retractable rotor blade of the embodiment of the present invention.
  • Fig. 8 is a cross-sectional view showing the A-A of the upper and lower bushings of the retractable rotor blade according to the embodiment of the present invention.
  • Fig. 9 is a cross-sectional view showing the B-B of the upper and lower sleeves of the retractable rotor blade according to the embodiment of the present invention.
  • the beetle sheath-wing wing aircraft includes a fuselage 1, a wing 2, a rotary wing 4, a horizontal propulsion device 5, and a wing of a beetle-like coleoptera as a horizontal wing of an aircraft, a beetle-like beetle
  • the wing 2 of the coleoptera is hinged to the aircraft fuselage 1.
  • the wing of the beetle sheath can automatically complete the sag and flattening movement according to the flight conditions in the air; the rotor 4 is installed above the beetle sheath wing aircraft.
  • the rotary wing realizes vertical take-off and landing.
  • the wing of the beetle sheath-winged wing When the aircraft moves up and down vertically, the wing of the beetle sheath-winged wing automatically hangs down under the action of gravity and rotor under the airflow, and tends to be parallel with the fuselage, avoiding the occlusion of the wing to the lower washing airflow and the gas bomb. Vibration, eliminating the interference of the wing to the rotating wing, reducing the resistance of the aircraft's take-off and landing, and moving the center of gravity of the entire aircraft down, greatly improving the flight stability of the aircraft.
  • the imitation beetle sheath-wing wing aircraft is equipped with a horizontal propulsion device 5, which realizes horizontal flight through horizontal propulsion.
  • the wing of the beetle-like coleoptera When the aircraft is flying horizontally, the wing of the beetle-like coleoptera is automatically turned up and flattened into a fixed wing under the lift of the airfoil, providing the lift required for horizontal flight. .
  • the wing of the beetle-like coleoptera can sag automatically like a wind vane.
  • the wings of the beetle-like coleoptera are automatically deformed under the corresponding flight conditions, which makes the aircraft adaptive, reduces the complexity of manual operations, and improves the fault tolerance.
  • the imitation beetle sheath-wing wing aircraft can be separately controlled and seamlessly connected during vertical take-off and horizontal flight.
  • the horizontal propulsion device 5 can be turned off. After rising to a suitable height, the horizontal propulsion is started. After the horizontal flight reaches a certain speed, the aircraft is gradually closed. Rotating wing 4, the landing process is reversed, through the adaptive work of the wing 2 of the beetle sheathed wing, reducing the strong coupling relationship between the vertical take-off and landing drive mechanism and the horizontal flight drive mechanism, making the flight mode conversion more natural, It's smoother, easier, and safer.
  • the wing of the beetle sheath-like wing mimics the beetle sheath wing function design, including a set of cantilever 2-1 and wing body 2-2.
  • One end of the cantilever 2-1 is fixed on the fuselage 1 and the other end passes through the free hinge 6 and the wing body 2 2, the wing body 2-2 can be freely rotated around the free hinge 6 and automatically sag or fold up and flatten according to the force of different flight conditions in the air.
  • the wing body 2-2 is designed as a conventional folding structure, so that the entire wing can be expanded to a length greater than the height of the fuselage, and the height of the fuselage is limited to the wing span, thereby improving the aircraft lift.
  • the length of the cantilever 2-1 ensures that after the wing body 2-2 is completely turned down, the inner side is spaced from the body 1 by a distance of 1/2 of the width of the body 1, leaving sufficient space between the body 1.
  • the wing 2 of the beetle sheathed wing is rotated, the precise position of the rotation is controlled by setting the ordinary rod stopper 2-3, and the wings on the left and right sides are synchronously turned over.
  • the limiting device prevents the rolling instability caused by the unbalanced force while restraining the fixed position of the wing up and down, and ensures that the rigid wing on the left and right sides of the aircraft can be flattened to a stable position.
  • the fuselage 1 of the aircraft is in the form of a sheet.
  • the width of the fuselage is much smaller than the height and length.
  • the front and cross sections are narrow and long.
  • the aspect ratio and aspect ratio of the fuselage are >4, which greatly reduces Air resistance when the aircraft is flying forward or taking off and landing vertically.
  • the fuselage 1 of the aircraft is a vertical sheet-like monolithic structure.
  • the aspect ratio of the fuselage is larger than the aspect ratio.
  • the special geometry of the fuselage ensures that the airflow in the horizontal and vertical directions is unobstructed and well formed. Vertical takeoff and landing and horizontal flight aerodynamic characteristics.
  • the rotor 4 of the aircraft is a retractable rotor, using a set of rotor blades 4-3 that can be fully deployed and fully collapsed in flight, and the rotor blades 4-3 are driven by the blade bushings 4-2 and rotors.
  • the shaft 4-1 is connected. When the aircraft takes off and land, the drive shaft 4-1 rotates in the forward direction, and the rotor blades 4-3 are sequentially driven to rotate forward by the blade bushings 4-2, so that all the blades are fully deployed to generate maximum lift; when the aircraft is flying horizontally, the aircraft is driven.
  • the rotor blades 4-3 When the shaft 4-1 stops rotating, the rotor blades 4-3 will reversely revolve under the action of the oncoming airflow, and finally completely collapse and overlap, and deform into a shape with little air resistance.
  • the retractable rotor realizes the automatic retraction of the rotor through the ratchet action of the blade sleeve and the use of centrifugal force and wind force.
  • the working state of the rotor blade can be automatically adjusted according to the flight conditions, and the horizontal flight of the vertical take-off and landing aircraft rotor is significantly eliminated. Resistance and vibration.
  • the number of rotor blades 4-3 is two, and the automatic locking position of the rotor blades in the forward direction is realized by a locking mechanism on the blade drive bushing or the blade root, that is, each blade is
  • the blade bushing 4-2 is connected to the rotor drive shaft 4-1, and the blade bushing 4-2 has a one-way locking function like a ratchet, which can drive the rotary expansion lock position and the reverse free rotation to fold and follow.
  • Each blade bushing 4-2 has upper and lower joint faces respectively matched with the blade bushings of the upper and lower adjacent blades, and the lower joint face 4-2-1 is combined with the lower blade bushing Face cooperation, the upper joint surface 4-2-2 is matched with the lower joint surface of the upper blade bushing; the next blade blade is the active blade, and the rest is the driven blade; the rotor drive shaft 4-1 and the active paddle The sleeves of the blades are connected.
  • the rotor drive shaft drives the sleeve of the active blade, according to the mutual cooperation relationship between the upper and lower blade sleeves, the lower blade sleeve will drive the upper blade sleeve to drive the rotor in turn.
  • the blades rotate, and when the rotor blades are fully deployed, the angles of the adjacent blades are divided into 360° circumferential angles.
  • the blades are reversely revolved under the action of the oncoming wind force, and then folded in a folded fan shape with overlapping angles and zero angles.
  • the working state of the rotor blade is synchronized with the flight condition of the aircraft.
  • the working mechanism of the rotor blade is coordinated with the flight of the aircraft, so that the rotor has the self-adaptive ability to automatically change the aerodynamic shape according to the flight condition of the aircraft, and is fully deployed during the flight or Completely contracted, the conversion process is natural, stable and continuous.
  • the rotor working state can be automatically adjusted according to the flight condition of the aircraft.
  • the flight control is simplified, the safety is high, and the reliability is good.
  • the retractable rotor of the aircraft is reasonable in design, simple and natural, and realizes the natural conversion, smooth transition and effective compatibility of the rotor working state in the two modes of vertical take-off and horizontal flight.
  • the back of the aircraft fuselage is equipped with a large-area fin-shaped fin 3, which is generated by changing the relative motion state of the fin and the airflow by rotating the fins or generating a moment by changing the combined state of the fins, so that the fins are generated. Force or moment is applied to the sheet fuselage to control the attitude of the aircraft.
  • the fins 3 are rotatable about the fin wings, are manually operated by a conventional mechanical control mechanism, are pivoted about the fin shafts, and are unfolded or flattened integrally with the sheet fuselage.
  • the beetle sheath-wing wing aircraft includes a fuselage 1, a wing 2, a rotary wing 4, a horizontal propulsion device 5, and a wing of a beetle-like coleoptera as a horizontal wing of an aircraft, a beetle-like beetle
  • the wing 2 of the coleoptera is hinged to the aircraft fuselage 1.
  • the wing of the beetle sheath can automatically complete the sag and flattening movement according to the flight conditions in the air; the rotor 4 is installed above the beetle sheath wing aircraft.
  • the rotary wing realizes vertical take-off and landing.
  • the wing of the beetle sheath-winged wing When the aircraft moves up and down vertically, the wing of the beetle sheath-winged wing automatically hangs down under the action of gravity and rotor under the airflow, and tends to be parallel with the fuselage, avoiding the occlusion of the wing to the lower washing airflow and the gas bomb. Vibration, eliminating the interference of the wing to the rotating wing, reducing the resistance of the aircraft's take-off and landing, and moving the center of gravity of the entire aircraft down, greatly improving the flight stability of the aircraft.
  • the imitation beetle sheath-wing wing aircraft is equipped with a horizontal propulsion device 5, which realizes horizontal flight through horizontal propulsion.
  • the wing of the beetle-like coleoptera When the aircraft is flying horizontally, the wing of the beetle-like coleoptera is automatically turned up and flattened into a fixed wing under the lift of the airfoil, providing the lift required for horizontal flight. .
  • the wing of the beetle-like coleoptera can sag automatically like a wind vane.
  • the imitation beetle sheath-wing wing aircraft can be separately controlled and seamlessly connected during vertical take-off and horizontal flight.
  • the horizontal propulsion device 5 can be turned off. After rising to a suitable height, the horizontal propulsion is started. After the horizontal flight reaches a certain speed, the aircraft is gradually closed. Rotating wing 4, the landing process is reversed, through the adaptive work of the wing 2 of the beetle sheathed wing, reducing the strong coupling relationship between the vertical take-off and landing drive mechanism and the horizontal flight drive mechanism, making the flight mode conversion more natural, It's smoother, easier, and safer.
  • the wing of the beetle sheath-like wing mimics the beetle sheath wing function design, including a set of cantilever 2-1 and wing body 2-2.
  • One end of the cantilever 2-1 is fixed on the fuselage 1 and the other end passes through the free hinge 6 and the wing body 2 2, the wing body 2-2 can be freely rotated around the free hinge 6 and automatically sag or fold up and flatten according to the force of different flight conditions in the air.
  • the wing body 2-2 is designed as a conventional telescopic structure, so that the entire wing can be expanded to a length greater than the height of the fuselage, and the height of the fuselage is limited to the wing span, thereby improving the aircraft lift.
  • the length of the cantilever 2-1 ensures that after the wing body 2-2 is completely turned down, the inner side is spaced from the body 1 by a distance of 2/3 of the width of the body 1, leaving sufficient space between the body 1.
  • the wing 2 of the beetle sheathed wing is rotated, the precise position of the rotation is controlled by setting the limit device 2-3 of the ordinary band-restricted card slot structure, and the wings on the left and right sides are synchronously turned over.
  • the limiting device prevents the rolling instability caused by the unbalanced force while restraining the fixed position of the wing up and down, and ensures that the rigid wing on the left and right sides of the aircraft can be flattened to a stable position.
  • the sagging and the flattening of the wing 2 of the beetle sheathed wing are completed by the conventional mechanical control while utilizing the gravity of the wing to sag naturally, using the airfoil lift to overcome the natural upward adjustment of the wing's gravity.
  • the mechanism assists the operation to improve the flexibility and reliability of the wing work and enhance the coordination and robustness of the aircraft flight.
  • the fuselage 1 of the aircraft is in the form of a sheet.
  • the width of the fuselage is much smaller than the height and length.
  • the front and cross sections are narrow and long.
  • the aspect ratio and aspect ratio of the fuselage are ⁇ 6, and the aspect ratio is adopted.
  • the horizontal fuselage is larger than the aspect ratio, which greatly reduces the air resistance when the aircraft is flying forward or vertically, ensuring that the airflow is unobstructed for the horizontal and vertical directions, forming a good vertical takeoff and landing and level. Flight aerodynamic characteristics.
  • the sheet-shaped aircraft fuselage 1 adopts a combined structure of a nacelle 1-1 and a baffle 1-2.
  • the deflector 1-2 has a continuous surface structure and is disposed at an upper position of the nacelle, the fuselage 1 and the deflector 1 -
  • the windward surface section of the 2 is a symmetrical wedge shape, and the windward surface contour is streamlined to reduce air resistance.
  • the rotor 4 of the aircraft is a retractable rotor, using a set of rotor blades 4-3 that can be fully deployed and fully collapsed in flight, and the rotor blades 4-3 are driven by the blade bushings 4-2 and rotors.
  • the shaft 4-1 is connected. When the aircraft takes off and land, the drive shaft 4-1 rotates in the forward direction, and the rotor blades 4-3 are sequentially driven to rotate forward by the blade bushings 4-2, so that all the blades are fully deployed to generate maximum lift; when the aircraft is flying horizontally, the aircraft is driven.
  • the rotor blades 4-3 When the shaft 4-1 stops rotating, the rotor blades 4-3 will reversely revolve under the action of the oncoming airflow, and finally completely collapse and overlap, and deform into a shape with little air resistance.
  • the retractable rotor realizes the automatic retraction of the rotor through the ratchet action of the blade sleeve and the use of centrifugal force and wind force.
  • the working state of the rotor blade can be automatically adjusted according to the flight conditions, and the horizontal flight of the vertical take-off and landing aircraft rotor is significantly eliminated. Resistance and vibration.
  • the number of rotor blades 4-3 is six, and the automatic locking position of the rotor blades in the forward direction is realized by a locking mechanism on the blade drive bushing or the blade root, that is, each blade is
  • the blade bushing 4-2 is connected to the rotor drive shaft 4-1, and the blade bushing 4-2 has a one-way locking function like a ratchet, which can drive the rotary expansion lock position and the reverse free rotation to fold and follow.
  • Each blade bushing 4-2 has upper and lower joint faces respectively matched with the blade bushings of the upper and lower adjacent blades, and the lower joint face 4-2-1 is combined with the lower blade bushing Face cooperation, the upper joint surface 4-2-2 is matched with the lower joint surface of the upper blade bushing; the next blade blade is the active blade, and the rest is the driven blade; the rotor drive shaft 4-1 and the active paddle The sleeves of the blades are connected.
  • the rotor drive shaft drives the sleeve of the active blade, according to the mutual cooperation relationship between the upper and lower blade sleeves, the lower blade sleeve will drive the upper blade sleeve to drive the rotor in turn.
  • the blades rotate, and when the rotor blades are fully deployed, the angles of the adjacent blades are divided into 360° circumferential angles.
  • the blades are reversely revolved under the action of the oncoming wind force, and then folded in a folded fan shape with overlapping angles and zero angles.
  • the working state of the rotor blade is synchronized with the flight condition of the aircraft.
  • the working mechanism of the rotor blade is coordinated with the flight of the aircraft, so that the rotor has the self-adaptive ability to automatically change the aerodynamic shape according to the flight condition of the aircraft, and is fully deployed during the flight or Completely contracted, the conversion process is natural, stable and continuous.
  • the rotor working state can be automatically adjusted according to the flight condition of the aircraft.
  • the opening and opening, the combination of time, natural conversion, smooth transition, no additional manual intervention, and adaptability, The flight control is simplified, the safety is high, and the reliability is good.
  • the back and tail of the aircraft fuselage are respectively equipped with a large-area fin fins 3, which are changed by changing the relative motion state of the fins and the airflow by rotating the fins or generating a moment by changing the combined state of the fins, so that the fins
  • the force or moment generated by the wing is applied to the sheet fuselage to control the attitude of the aircraft.
  • the fins 3 are rotatable about the fin wings, are manually operated by a conventional electric steering mechanism, are pivoted about the fin shaft, and are unfolded or flattened integrally with the sheet fuselage.
  • the beetle sheath-wing wing aircraft includes a fuselage 1, a wing 2, a rotary wing 4, a horizontal propulsion device 5, and a wing of a beetle-like coleoptera as a horizontal wing of an aircraft, a beetle-like beetle
  • the wing 2 of the coleoptera is hinged to the aircraft fuselage 1.
  • the wing of the beetle sheath can automatically complete the sag and flattening movement according to the flight conditions in the air; the rotor 4 is installed above the beetle sheath wing aircraft.
  • the rotary wing realizes vertical take-off and landing.
  • the wing of the beetle sheath-winged wing When the aircraft moves up and down vertically, the wing of the beetle sheath-winged wing automatically hangs down under the action of gravity and rotor under the airflow, and tends to be parallel with the fuselage, avoiding the occlusion of the wing to the lower washing airflow and the gas bomb. Vibration, eliminating the interference of the wing to the rotating wing, reducing the resistance of the aircraft's take-off and landing, and moving the center of gravity of the entire aircraft down, greatly improving the flight stability of the aircraft.
  • the imitation beetle sheath-wing wing aircraft is equipped with a horizontal propulsion device 5, which realizes horizontal flight through horizontal propulsion.
  • the wing of the beetle-like coleoptera When the aircraft is flying horizontally, the wing of the beetle-like coleoptera is automatically turned up and flattened into a fixed wing under the lift of the airfoil, providing the lift required for horizontal flight. .
  • the wing of the beetle-like coleoptera can sag automatically like a wind vane.
  • the wings of the beetle-like coleoptera are automatically deformed under the corresponding flight conditions, which makes the aircraft adaptive, reduces the complexity of manual operations, and improves the fault tolerance.
  • the imitation beetle sheath-wing wing aircraft can be separately controlled and seamlessly connected during vertical take-off and horizontal flight.
  • the horizontal propulsion device 5 can be turned off. After rising to a suitable height, the horizontal propulsion is started. After the horizontal flight reaches a certain speed, the aircraft is gradually closed. Rotating wing 4, the landing process is reversed, through the adaptive work of the wing 2 of the beetle sheathed wing, reducing the strong coupling relationship between the vertical take-off and landing drive mechanism and the horizontal flight drive mechanism, making the flight mode conversion more natural, It's smoother, easier, and safer.
  • the wing of the beetle sheath-like wing mimics the beetle sheath wing function design, including a set of cantilever 2-1 and wing body 2-2.
  • One end of the cantilever 2-1 is fixed on the fuselage 1 and the other end passes through the free hinge 6 and the wing body 2 2, the wing body 2-2 can freely rotate around the free hinge 6 and complete the sagging or upswing in the air according to the force conditions of different flight conditions.
  • the length of the cantilever 2-1 ensures that after the wing body 2-2 is completely turned down, the inner side of the wing body 2-2 is spaced apart from the body 1 by more than 3/5 of the width of the body 1, leaving sufficient space between the body 1.
  • the precise position of the rotation is controlled by setting the limit device 2-3 of the ordinary limit-bump structure, and the wings on the left and right sides are synchronously turned over.
  • the limiting device prevents the rolling instability caused by the unbalanced force while restraining the fixed position of the wing up and down, and ensures that the rigid wing on the left and right sides of the aircraft can be flattened to a stable position.
  • the sagging and the flattening of the wing 2 of the beetle-like coleoptera are manually assisted by the common electric control mechanism to improve the flexibility and reliability of the wing work, and greatly improve the coordination and robustness of the aircraft flight. .
  • the fuselage 1 of the aircraft is in the form of a sheet.
  • the width of the fuselage is much smaller than the height and length.
  • the front and cross sections are narrow and long.
  • the aspect ratio and aspect ratio of the fuselage are >8, and the aspect ratio is adopted.
  • the horizontal fuselage is larger than the aspect ratio, which greatly reduces the air resistance during forward flight or vertical take-off and landing of the aircraft, ensuring that the airflow is unobstructed for the horizontal and vertical directions, forming a good vertical takeoff and landing and horizontal flight. Aerodynamic characteristics.
  • the sheet-shaped fuselage of the aircraft adopts a combined structure of a nacelle 1-1 and a baffle 1-2, and the baffle 1-2 has a continuous surface structure and is disposed at a rear position of the nacelle.
  • the windward surface of the fuselage 1 and the deflector 1-2 has a symmetrical wedge shape, and the windward contour is streamlined to reduce air resistance.
  • the rotor 4 of the aircraft is a retractable rotor, using a set of rotor blades 4-3 that can be fully deployed and fully collapsed in flight, and the rotor blades 4-3 are driven by the blade bushings 4-2 and rotors.
  • the shaft 4-1 is connected. When the aircraft takes off and land, the drive shaft 4-1 rotates in the forward direction, and the rotor blades 4-3 are sequentially driven to rotate forward by the blade bushings 4-2, so that all the blades are fully deployed to generate maximum lift; when the aircraft is flying horizontally, the aircraft is driven.
  • the rotor blades 4-3 When the shaft 4-1 stops rotating, the rotor blades 4-3 will reversely revolve under the action of the oncoming airflow, and finally completely collapse and overlap, and deform into a shape with little air resistance.
  • the retractable rotor realizes the automatic retraction of the rotor through the ratchet action of the blade sleeve and the use of centrifugal force and wind force.
  • the working state of the rotor blade can be automatically adjusted according to the flight conditions, and the horizontal flight of the vertical take-off and landing aircraft rotor is significantly eliminated. Resistance and vibration.
  • the number of rotor blades 4-3 is three, and the automatic locking position of the rotor blades in the forward direction is realized by a locking mechanism at the root of the blade, that is, a triangular truss is used to connect the three blades and the drive shaft.
  • the three blades are respectively hinged to the three corners of the truss, and are driven by the drive shaft to form an angle of 120° with each other, so that all the blades are fully deployed to generate maximum lift.
  • the drive shaft is stopped, and the rotor is paddle.
  • the reverse folding of the blade is naturally reset to the triangle in the original state of the rotor, which minimizes the air resistance of the rotor.
  • the centrifugal force and the aerodynamic force are used to automatically adjust the working state of the rotor blade according to the flight conditions, eliminating the vertical take-off and landing aircraft rotor. Horizontal flight resistance and vibration.
  • the working state of the rotor blades is synchronized with the flight condition of the aircraft.
  • the working mechanism of the rotor blades is coordinated with the flight of the aircraft, so that the rotor has the ability to automatically change the aerodynamic shape according to the flight conditions of the aircraft, and fully expand or fully contract during flight.
  • the natural conversion, smooth transition and effective compatibility of the rotor working state in the two modes of vertical take-off and horizontal flight are realized.

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Abstract

一种仿甲虫鞘翅机翼航空器，属于航空技术领域。采用仿甲虫鞘翅的机翼（2）作为航空器的水平翼，将左右两个仿甲虫鞘翅的机翼（2）通过自由铰链（6）与机身（1）连接，让仿甲虫鞘翅的机翼（2）可在空中根据不同飞行工况的受力情况自动完成下垂和展平的收放动作；航空器上方安装有收放式旋转翼（4），通过旋转翼（4）实现垂直起降，仿甲虫鞘翅的机翼（2）在航空器垂直起降时下垂收合而与机身（1）趋于平行，回避机翼（2）对下洗气流的遮挡和气弹振动，消除机翼（2）对旋转翼（4）的干扰；航空器安装水平推进装置（5）实现水平飞行，仿甲虫鞘翅的机翼（2）在航空器水平飞行时上翻展平成为固定翼，提供水平飞行所需升力。该仿甲虫鞘翅机翼航空器具有机理协调、结构简单、成本低廉、可靠性高、适应性好等优点，可广泛应用于载人或无人机等。

Description

一种仿甲虫鞘翅机翼航空器 技术领域
本发明涉及一种利用仿昆虫翼的机翼作为水平机翼的航空器，具体的是一种仿甲虫鞘翅机翼航空器，属于航空器技术领域。
背景技术
航空器可分为固定翼和旋转翼两大类，固定翼常见于水平起降航空器(如喷气式客机)，而旋转翼常见于垂直起降航空器(如直升机)。就现有技术水平而言，固定翼航空器飞行速度高、操作简便，但需依托跑道起降；而旋转翼航空器可以垂直起降，不需依托跑道起降，适应性强，但是机理失调，操控复杂，飞行速度慢，燃油效率低。
目前，垂直起降航空器还存在一些无法克服的固有缺陷。一是飞行速度有极限：受翼尖绝对速度必须小于音速的限制，旋转翼航空器的理论速度不能超过420公里/小时。二是可靠性低；旋翼桨叶的挥舞产生机械振动，增加了铰链的磨损，使得其可靠性总是不如固定翼航空器。三是横滚稳定性差：两侧旋翼的升力不均匀，会导致旋转翼航空器发生横滚，在几秒钟内就会倾覆失控。四是操控复杂：直升机的旋翼虽然提供了飞行的机动性，但同时也造成了飞行操控的复杂性。使得操控负荷远远大于固定翼飞机，加大了人为失误的概率。五是无法做大：由于旋翼直径和转速受到翼尖速度不能超过音速的限制，旋翼直径一般最大就是十几米，航空器尺寸受限，无法做得更大。六是飞行机理失调：直升机虽然发展了近70年，但是飞行机理内在的协调性差，充满了先天性的矛盾。七是采用固定翼的矛盾：很多新型复合式垂直起降航空器尝试采用固定翼，但却面临小面积固定翼效果有限、而大面积固定翼会对垂直起降时的下洗气流造成遮挡的矛盾。
总之，垂直起降航空器的上述缺陷来源于机翼既要兼顾垂直起降又要满足水平飞行两种飞行模式而产生的矛盾，需要一种较有针对性的技术方法来对其进行协调。
发明内容
本发明要解决的技术问题是如何协调航空器在垂直起降与水平飞行两种飞行模式转换中产生的矛盾，通过提出一种仿甲虫鞘翅机翼航空器，利用仿甲虫鞘翅机翼协调航空器垂直起降与水平飞行转换时的矛盾，并配合片状机身、增加鳍翼和采用收放式旋翼，有效提高飞行控制反应的速度、灵敏度、容错能力和安全性等。
为解决上述技术问题，本发明提供一种仿甲虫鞘翅机翼航空器，包括机身1、机翼2、旋转翼4、水平推进装置5，采用仿甲虫鞘翅的机翼作为航空器的水平翼，仿甲虫鞘翅的机翼2与航空器机身1铰接，仿甲虫鞘翅的机翼可在空中根据不同飞行工况的受力情况自 动完成下垂和展平的收放动作；仿甲虫鞘翅机翼航空器上方安装有旋转翼4，通过旋转翼实现垂直起降，航空器垂直起降时仿甲虫鞘翅的机翼在重力和旋翼下洗气流作用下自动下垂收合而与机身趋于平行，避免机翼对下洗气流的遮挡和气弹振动，消除机翼对旋转翼的干扰，减少航空器起降的阻力，并使整个航空器重心下移，大幅提高航空器飞行稳定性；仿甲虫鞘翅机翼航空器安装水平推进装置5，通过水平推进实现水平飞行，航空器水平飞行时仿甲虫鞘翅的机翼在翼型升力作用下自动上翻展平成为固定翼，提供水平飞行所需升力。在航空器悬停状态下，仿甲虫鞘翅的机翼完全下垂以后还可以像风向标一样自动顶风，安全高效。
所述仿甲虫鞘翅的机翼模仿甲虫鞘翅功能设计，包括一组悬臂2-1与翼体2-2，悬臂2-1的一端固定在机身1上，另一端通过自由铰链6与翼体2-2连接，翼体2-2可以围绕自由铰链6自由转动、在空中根据不同飞行工况的受力情况自动完成下垂收合或上翻展平。当所述翼体2-2的下垂空间受限时，可将翼体2-2设计为折叠式或伸缩式结构，使整个机翼展开时能够长度大于机身高度，突破机身高度对于机翼翼展的限制，从而提高航空器升力。
所述悬臂2-1的长度需保证翼体2-2完全下翻后在机身1之间留出足够的空间，以减少对下洗气流的遮挡；作为优选，翼体2-2内侧与机体1的间距一般应大于机体1宽度的1/2，具体根据实际需要确定。
所述仿甲虫鞘翅的机翼2转动时，通过设置限位装置2-3控制其转动的精确位置，并保证左右两侧机翼同步翻转。限位装置2-3为普通拉杆或限位卡槽、限位凸块等限位机构，具体根据实际需要确定。限位装置在限制机翼上下翻动后固定位置的同时，避免由于受力不平衡而出现的横滚失稳，并保证航空器左右两侧的刚性机翼能够展平到某一稳定的位置。
所述仿甲虫鞘翅的机翼2的下垂收合和上翻展平的完成，既可以利用机翼重力自然下垂、利用翼型升力克服机翼重力自然上翻，利用物理原理机翼可在相应的飞行状态下自动变形，让航空器具备自适应能力，降低人工操作的繁复程度，提高容错率。此外，仿甲虫鞘翅的机翼2的下垂收合和上翻展平也可以通过普通机械式或电动操控机构人工操作强制完成，即在机翼进行自适应调整的同时运用人工操作辅助，提高机翼工作的灵活性和可靠性，大大提高航空器飞行的协调性与鲁棒性。
所述航空器的机身1为片状，机身的宽度远远小于高度和长度，其正断面和横断面呈窄长形，机身外形的高宽比和长宽比一般均应大于4(具体根据实际需要确定)，从而大幅 减小飞行器水平飞行或垂直起降时的空气阻力。作为立式机身高宽比大于长宽比，而作为卧式机身则长宽比大于高宽比；通过所述飞行器机身的特殊几何形状，保证机身对于水平方向和垂直方向的气流均无遮挡，形成良好的垂直起降和水平飞行气动特性。
所述片状的航空器机身1为整体式结构或机舱1-1与导流板1-2的组合结构，导流板1-2为连续表面结构。即飞行器机身外形尺寸满足高度和长度远远大于宽度，可以采用满足条件的整体式机身结构实现，也可采用导流板与机舱组合形成机身，通过导流板延伸机身的长度或宽度，满足机身外形高宽比和长宽比要求。采用导流板延伸机身的长度或宽度时，可将导流板设置于机舱的上部、下部、中部、前部、后部的任一位置，具体根据实际需要选择。所述机身1和导流板1-2的迎风面断面为对称的楔形、迎风面轮廓线为流线型，以减少空气阻力。
所述航空器的旋转翼4为收放式旋翼，采用一组可以在飞行中完全展开和完全收合的旋翼桨叶4-3，旋翼桨叶4-3则通过桨叶轴套4-2与旋翼驱动轴4-1连接。航空器起降时驱动轴4-1正向旋转，并通过桨叶轴套4-2依次驱动旋翼桨叶4-3正向旋转，使所有桨叶完全展开产生最大升力；航空器水平飞行时，驱动轴4-1停止旋转，旋翼桨叶4-3将在迎面气流的作用下反向自由回旋，最终完全收合重叠，变形为一个空气阻力很小的形状。收放式旋翼通过桨叶轴套的棘轮作用和利用离心力和风力的作用实现旋翼的自动收放，可以根据飞行工况自动调整旋翼桨叶的工作状态，显著消除垂直起降航空器旋翼水平飞行的阻力和振动。
所述旋翼桨叶4-3的数目可以根据需要确定为1、2、3、4、5、6、7、8甚至更多(具体数量根据实际需要选择)，旋翼桨叶的正向依次展开的自动锁位可以通过在桨叶驱动轴套上或桨叶根部设置锁位机构的方法实现。可以将每个桨叶均通过桨叶轴套4-2与旋翼驱动轴4-1连接，桨叶轴套4-2具有类似棘轮的单向锁止功能，可以正向驱动旋转展开锁位和逆向自由旋转收合后顺；单向锁止结构包括但不限于每个桨叶轴套4-2具有上下两个结合面分别与上下两个相邻桨叶的桨叶轴套相配合，下结合面4-2-1与下桨叶轴套的上结合面配合，上结合面4-2-2与上桨叶轴套的下结合面配合；最下一叶桨叶为主动桨叶，其余为从动桨叶；旋翼驱动轴4-1与主动桨叶的轴套相连接，当旋翼驱动轴驱动主动桨叶的轴套时，根据上下桨叶轴套之间的相互配合关系，下方的桨叶轴套将依次驱动上方的桨叶轴套带动旋翼桨叶旋转，当旋翼桨叶正向完全展开后各相邻桨叶的夹角均分360°圆周角。也可采用三角形桁架连接三片桨叶与驱动轴，三片桨叶分别与桁架的三个角铰接，可由驱动轴带动展开相互间呈120°夹角等。当旋翼驱动轴停止驱动时，桨叶在迎面风力作用下 逆向自由回旋，后顺收合，相互重叠，各相邻桨叶的夹角为零；根据桨叶与驱动轴之间连接关系的不同，一组桨叶逆向收合自然复位至旋翼原始状态后，整个旋翼可以呈折扇形、矩形、圆形、或多边形形状。
所述旋翼桨叶的工作状态与航空器的飞行状况保持同步，旋翼桨叶的工作机理与航空器的飞行相互协调，使得旋翼具有根据航空器飞行状况自动改变气动外形的自适应能力，在飞行过程中完全展开或者完全收缩，转化过程自然、平稳、连续，旋翼工作状态可根据航空器飞行状况自动调整，该开时开，该合时合，自然转换，平稳过渡，不需要额外的人工干预，具有自适应性，使得飞行操控简化、安全性高、可靠性好。所述航空器的收放式旋翼，设计合理，简洁自然，实现了垂直起降和水平飞行两种工作模式下旋翼工作状态的自然转换、平稳过渡和有效兼容。
所述航空器的片状机身上安装有一个或多个大面积片状鳍翼3(具体数量根据实际需要选择)，通过转动鳍翼改变鳍翼与气流的相对运动状态产生作用力或通过改变鳍翼的组合状态产生力矩，使鳍翼产生的力或力矩施加于片状机身，控制航空器的航行姿态。所述鳍翼3可围绕鳍翼轴转动，可以通过常规机械或电动式操控机构人工操作，以鳍翼轴为轴心转动，展开或收平与片状机身形成一体。鳍翼3可设置于机身1的头部、背部、腹部、尾部、腰部，也可以前后成对使用或上下成对使用，具体根据实际需要确定。
所述仿甲虫鞘翅机翼航空器垂直起降和水平飞行时可以分别操控、无缝衔接，垂直起飞时可以关闭水平推进装置5，升高到合适高度后启动水平推进，水平飞行达到一定速度后再逐渐关闭旋转翼4，降落过程则相反，通过仿甲虫鞘翅的机翼2的自适应工作，降低垂直起降的驱动机构和水平飞行的驱动机构之间的强烈耦合关系，使得飞行模式的转换更加自然，更加顺畅，更加简易，更加安全。
本发明通过采用仿甲虫鞘翅的机翼，可以在空中根据飞行工况完成下垂和展平的收放动作，机翼在航空器垂直起降时下垂收合而与机身趋于平行，回避对下洗气流的遮挡和气弹振动，有效消除机翼对旋转翼的干扰，减少起降的阻力，并使整个航空器重心下移，大幅提高航空器飞行稳定性；在航空器水平飞行时，仿甲虫鞘翅的机翼上翻展平成为固定翼，可以提供水平飞行所需升力。在航空器悬停状态下，完全下垂的仿甲虫鞘翅的机翼还可以像风向标一样自动顶风，安全高效。
本发明片状机身的配合使用，可以保证机身对于水平方向和垂直方向的气流均无遮挡，大幅减小飞行器正向飞行或垂直起降时的空气阻力，形成良好的垂直起降和水平飞行气动特性；而导流板的采用则可以延伸机身的长度或宽度，满足机身外形高宽比和长宽比要求。 收放式旋翼的采用，既可以在航空器起降时展开桨叶而产生最大升力，也可以在航空器水平飞行时收合桨叶而减小空气阻力，根据飞行工况调整旋翼桨叶的工作状态，消除旋翼水平飞行阻力和振动。
与现有技术相比，本发明能有效地协调垂直起降与水平飞行两种状态转换时所产生的矛盾，解决旋转翼与固定翼之间的相互影响，并能根据飞行状态进行自适应性地自动改变机翼的形态和气动特征，解除了垂直起降驱动机构和水平飞行驱动机构之间的强烈耦合关系，有效避免了正交驱动之间的相互冲突，有效减少了人工操作介入，有效提高了飞行控制的容错能力、飞行安全和飞行效率；具有机理协调、结构简单、成本低廉、可靠性高、适应性好等优点，可广泛应用于载人航空器或无人机等。
附图说明
图1是本发明航空器机翼处于下垂收合状态示意图。
图2是本发明航空器机翼处于上翻展平状态示意图。
图3是本发明机翼同步机构原理图。
图4是本发明航空器正视示意图。
图5是本发明实施例收放式旋翼收合状态示意图。
图6是本发明实施例收放式旋翼旋转展开示意图。
图7是本发明实施例收放式旋翼桨叶的上下两轴套相互配合剖视图。
图8是本发明实施例收放式旋翼桨叶的上下两轴套相互配合A-A剖视图。
图9是本发明实施例收放式旋翼桨叶的上下两轴套相互配合B-B剖视图。
图中标号：1-机身，1-1-机舱，1-2-导流板，2-机翼，2-1-悬臂，2-2-翼体，2-3-限位装置，3-鳍翼，4-旋转翼，4-1-桨叶轴，4-2桨叶轴套，4-2-1-桨叶轴套的下结合面，4-2-2-桨叶轴套的上结合面，4-3桨叶，5-水平推进装置，6-自由铰链。
具体实施方式
下面结合附图对本发明的具体实施方式作进一步详尽描述，实施例中未注明的技术或产品，均为现有技术或可以通过购买获得的常规产品。
实施例1：参见图1-9，本仿甲虫鞘翅机翼航空器包括机身1、机翼2、旋转翼4、水平推进装置5，采用仿甲虫鞘翅的机翼作为航空器的水平翼，仿甲虫鞘翅的机翼2与航空器机身1铰接，仿甲虫鞘翅的机翼可在空中根据飞行工况自动完成下垂和展平的收放动作；仿甲虫鞘翅机翼航空器上方安装有旋转翼4，通过旋转翼实现垂直起降，航空器垂直起降时仿甲虫鞘翅的机翼在重力和旋翼下洗气流作用下自动下垂收合而与机身趋于平 行，避免机翼对下洗气流的遮挡和气弹振动，消除机翼对旋转翼的干扰，减少航空器起降的阻力，并使整个航空器重心下移，大幅提高航空器飞行稳定性。仿甲虫鞘翅机翼航空器安装水平推进装置5，通过水平推进实现水平飞行，航空器水平飞行时仿甲虫鞘翅的机翼在翼型升力作用下自动上翻展平成为固定翼，提供水平飞行所需升力。航空器悬停状态下，仿甲虫鞘翅的机翼完全下垂以后还可以像风向标一样自动顶风。仿甲虫鞘翅的机翼在相应的飞行状态下自动变形，让航空器具备了自适应能力，降低人工操作的繁复程度，提高容错率。
仿甲虫鞘翅机翼航空器垂直起降和水平飞行时可以分别操控、无缝衔接，垂直起飞时可以关闭水平推进装置5，升高到合适高度后启动水平推进，水平飞行达到一定速度后再逐渐关闭旋转翼4，降落过程则相反，通过仿甲虫鞘翅的机翼2的自适应工作，降低垂直起降的驱动机构和水平飞行的驱动机构之间的强烈耦合关系，使得飞行模式的转换更加自然，更加顺畅，更加简易，更加安全。
仿甲虫鞘翅的机翼模仿甲虫鞘翅功能设计，包括一组悬臂2-1与翼体2-2，悬臂2-1的一端固定在机身1上，另一端通过自由铰链6与翼体2-2连接，翼体2-2可以围绕自由铰链6自由转动、在空中根据不同飞行工况的受力情况自动完成下垂收合或上翻展平。翼体2-2设计为常规折叠式结构，使整个机翼展开时能够长度大于机身高度，突破机身高度对于机翼翼展的限制，从而提高航空器升力。悬臂2-1的长度保证翼体2-2完全下翻后，其内侧与机体1的间距大于机体1宽度的1/2，在机身1之间留出足够的空间。仿甲虫鞘翅的机翼2转动时，通过设置普通拉杆限位装置2-3，控制其转动的精确位置，并保证左右两侧机翼同步翻转。限位装置在限制机翼上下翻动后固定位置的同时，避免由于受力不平衡而出现的横滚失稳，并保证航空器左右两侧的刚性机翼能够展平到某一稳定的位置。
航空器的机身1为片状，机身的宽度远远小于高度和长度，其正断面和横断面呈窄长形，机身外形的高宽比和长宽比均＞4，从而大幅减小飞行器正向飞行或垂直起降时的空气阻力。航空器的机身1为立式片状整体式结构，机身的高宽比大于长宽比，通过机身的特殊几何形状，保证机身对于水平方向和垂直方向的气流均无遮挡，形成良好的垂直起降和水平飞行气动特性。
航空器的旋转翼4为收放式旋翼，采用一组可以在飞行中完全展开和完全收合的旋翼桨叶4-3，旋翼桨叶4-3则通过桨叶轴套4-2与旋翼驱动轴4-1连接。航空器起降时驱动轴4-1正向旋转，并通过桨叶轴套4-2依次驱动旋翼桨叶4-3正向旋转，使所有桨叶完全展开产生最大升力；航空器水平飞行时，驱动轴4-1停止旋转，旋翼桨叶4-3将在迎面气 流的作用下反向自由回旋，最终完全收合重叠，变形为一个空气阻力很小的形状。收放式旋翼通过桨叶轴套的棘轮作用和利用离心力和风力的作用实现旋翼的自动收放，可以根据飞行工况自动调整旋翼桨叶的工作状态，显著消除垂直起降航空器旋翼水平飞行的阻力和振动。
旋翼桨叶4-3的数目为两片，旋翼桨叶的正向依次展开的自动锁位通过在桨叶驱动轴套上或桨叶根部设置锁位机构的方法实现，即将每个桨叶均通过桨叶轴套4-2与旋翼驱动轴4-1连接，桨叶轴套4-2具有类似棘轮的单向锁止功能，可以正向驱动旋转展开锁位和逆向自由旋转收合后顺；每个桨叶轴套4-2具有上下两个结合面分别与上下两个相邻桨叶的桨叶轴套相配合，下结合面4-2-1与下桨叶轴套的上结合面配合，上结合面4-2-2与上桨叶轴套的下结合面配合；最下一叶桨叶为主动桨叶，其余为从动桨叶；旋翼驱动轴4-1与主动桨叶的轴套相连接，当旋翼驱动轴驱动主动桨叶的轴套时，根据上下桨叶轴套之间的相互配合关系，下方的桨叶轴套将依次驱动上方的桨叶轴套带动旋翼桨叶旋转，当旋翼桨叶正向完全展开后各相邻桨叶的夹角均分360°圆周角。当旋翼驱动轴停止驱动时，桨叶在迎面风力作用下逆向自由回旋后顺收合，呈相互重叠、夹角为零的折扇形。
旋翼桨叶的工作状态与航空器的飞行状况保持同步，旋翼桨叶的工作机理与航空器的飞行相互协调，使得旋翼具有根据航空器飞行状况自动改变气动外形的自适应能力，在飞行过程中完全展开或者完全收缩，转化过程自然、平稳、连续，旋翼工作状态可根据航空器飞行状况自动调整，该开时开，该合时合，自然转换，平稳过渡，不需要额外的人工干预，具有自适应性，使得飞行操控简化、安全性高、可靠性好。航空器的收放式旋翼，设计合理，简洁自然，实现了垂直起降和水平飞行两种工作模式下旋翼工作状态的自然转换、平稳过渡和有效兼容。
航空器的片状机身背部安装有一个大面积片状鳍翼3，通过转动鳍翼改变鳍翼与气流的相对运动状态产生作用力或通过改变鳍翼的组合状态产生力矩，使鳍翼产生的力或力矩施加于片状机身，控制航空器的航行姿态。鳍翼3可围绕鳍翼轴转动，通过常规机械式操控机构人工操作，以鳍翼轴为轴心转动，展开或收平与片状机身形成一体。
实施例2：参见图1-9，本仿甲虫鞘翅机翼航空器包括机身1、机翼2、旋转翼4、水平推进装置5，采用仿甲虫鞘翅的机翼作为航空器的水平翼，仿甲虫鞘翅的机翼2与航空器机身1铰接，仿甲虫鞘翅的机翼可在空中根据飞行工况自动完成下垂和展平的收放动作；仿甲虫鞘翅机翼航空器上方安装有旋转翼4，通过旋转翼实现垂直起降，航空器垂直起降时仿甲虫鞘翅的机翼在重力和旋翼下洗气流作用下自动下垂收合而与机身趋于平行，避免 机翼对下洗气流的遮挡和气弹振动，消除机翼对旋转翼的干扰，减少航空器起降的阻力，并使整个航空器重心下移，大幅提高航空器飞行稳定性。仿甲虫鞘翅机翼航空器安装水平推进装置5，通过水平推进实现水平飞行，航空器水平飞行时仿甲虫鞘翅的机翼在翼型升力作用下自动上翻展平成为固定翼，提供水平飞行所需升力。航空器悬停状态下，仿甲虫鞘翅的机翼完全下垂以后还可以像风向标一样自动顶风。
仿甲虫鞘翅机翼航空器垂直起降和水平飞行时可以分别操控、无缝衔接，垂直起飞时可以关闭水平推进装置5，升高到合适高度后启动水平推进，水平飞行达到一定速度后再逐渐关闭旋转翼4，降落过程则相反，通过仿甲虫鞘翅的机翼2的自适应工作，降低垂直起降的驱动机构和水平飞行的驱动机构之间的强烈耦合关系，使得飞行模式的转换更加自然，更加顺畅，更加简易，更加安全。
仿甲虫鞘翅的机翼模仿甲虫鞘翅功能设计，包括一组悬臂2-1与翼体2-2，悬臂2-1的一端固定在机身1上，另一端通过自由铰链6与翼体2-2连接，翼体2-2可以围绕自由铰链6自由转动、在空中根据不同飞行工况的受力情况自动完成下垂收合或上翻展平。翼体2-2设计为常规伸缩式结构，使整个机翼展开时能够长度大于机身高度，突破机身高度对于机翼翼展的限制，从而提高航空器升力。悬臂2-1的长度保证翼体2-2完全下翻后，其内侧与机体1的间距大于机体1宽度的2/3，在机身1之间留出足够的空间。仿甲虫鞘翅的机翼2转动时，通过设置普通带限位卡槽结构的限位装置2-3，控制其转动的精确位置，并保证左右两侧机翼同步翻转。限位装置在限制机翼上下翻动后固定位置的同时，避免由于受力不平衡而出现的横滚失稳，并保证航空器左右两侧的刚性机翼能够展平到某一稳定的位置。仿甲虫鞘翅的机翼2的下垂收合和上翻展平的完成，在利用机翼重力自然下垂、利用翼型升力克服机翼重力自然上翻进行自适应调整的同时，通过常规机械式操控机构人工辅助操作，提高机翼工作的灵活性和可靠性，增强航空器飞行的协调性与鲁棒性。
航空器的机身1为片状，机身的宽度远远小于高度和长度，其正断面和横断面呈窄长形，机身外形的高宽比和长宽比均≥6，采用长宽比大于高宽比的卧式机身，从而大幅减小飞行器正向飞行或垂直起降时的空气阻力，保证机身对于水平方向和垂直方向的气流均无遮挡，形成良好的垂直起降和水平飞行气动特性。片状的航空器机身1采用机舱1-1与导流板1-2的组合结构，导流板1-2为连续表面结构，设置于机舱的上部位置，机身1和导流板1-2的迎风面断面为对称的楔形、迎风面轮廓线为流线型，以减少空气阻力。
航空器的旋转翼4为收放式旋翼，采用一组可以在飞行中完全展开和完全收合的旋翼桨叶4-3，旋翼桨叶4-3则通过桨叶轴套4-2与旋翼驱动轴4-1连接。航空器起降时驱动 轴4-1正向旋转，并通过桨叶轴套4-2依次驱动旋翼桨叶4-3正向旋转，使所有桨叶完全展开产生最大升力；航空器水平飞行时，驱动轴4-1停止旋转，旋翼桨叶4-3将在迎面气流的作用下反向自由回旋，最终完全收合重叠，变形为一个空气阻力很小的形状。收放式旋翼通过桨叶轴套的棘轮作用和利用离心力和风力的作用实现旋翼的自动收放，可以根据飞行工况自动调整旋翼桨叶的工作状态，显著消除垂直起降航空器旋翼水平飞行的阻力和振动。
旋翼桨叶4-3的数目为六片，旋翼桨叶的正向依次展开的自动锁位通过在桨叶驱动轴套上或桨叶根部设置锁位机构的方法实现，即将每个桨叶均通过桨叶轴套4-2与旋翼驱动轴4-1连接，桨叶轴套4-2具有类似棘轮的单向锁止功能，可以正向驱动旋转展开锁位和逆向自由旋转收合后顺；每个桨叶轴套4-2具有上下两个结合面分别与上下两个相邻桨叶的桨叶轴套相配合，下结合面4-2-1与下桨叶轴套的上结合面配合，上结合面4-2-2与上桨叶轴套的下结合面配合；最下一叶桨叶为主动桨叶，其余为从动桨叶；旋翼驱动轴4-1与主动桨叶的轴套相连接，当旋翼驱动轴驱动主动桨叶的轴套时，根据上下桨叶轴套之间的相互配合关系，下方的桨叶轴套将依次驱动上方的桨叶轴套带动旋翼桨叶旋转，当旋翼桨叶正向完全展开后各相邻桨叶的夹角均分360°圆周角。当旋翼驱动轴停止驱动时，桨叶在迎面风力作用下逆向自由回旋后顺收合，呈相互重叠、夹角为零的折扇形。
旋翼桨叶的工作状态与航空器的飞行状况保持同步，旋翼桨叶的工作机理与航空器的飞行相互协调，使得旋翼具有根据航空器飞行状况自动改变气动外形的自适应能力，在飞行过程中完全展开或者完全收缩，转化过程自然、平稳、连续，旋翼工作状态可根据航空器飞行状况自动调整，该开时开，该合时合，自然转换，平稳过渡，不需要额外的人工干预，具有自适应性，使得飞行操控简化、安全性高、可靠性好。
航空器的片状机身背部和尾部分别安装有一个大面积片状鳍翼3，通过转动鳍翼改变鳍翼与气流的相对运动状态产生作用力或通过改变鳍翼的组合状态产生力矩，使鳍翼产生的力或力矩施加于片状机身，控制航空器的航行姿态。鳍翼3可围绕鳍翼轴转动，通过常规电动式操控机构人工操作，以鳍翼轴为轴心转动，展开或收平与片状机身形成一体。
实施例3：参见图1-4，本仿甲虫鞘翅机翼航空器包括机身1、机翼2、旋转翼4、水平推进装置5，采用仿甲虫鞘翅的机翼作为航空器的水平翼，仿甲虫鞘翅的机翼2与航空器机身1铰接，仿甲虫鞘翅的机翼可在空中根据飞行工况自动完成下垂和展平的收放动作；仿甲虫鞘翅机翼航空器上方安装有旋转翼4，通过旋转翼实现垂直起降，航空器垂直起降时仿甲虫鞘翅的机翼在重力和旋翼下洗气流作用下自动下垂收合而与机身趋于平行，避免 机翼对下洗气流的遮挡和气弹振动，消除机翼对旋转翼的干扰，减少航空器起降的阻力，并使整个航空器重心下移，大幅提高航空器飞行稳定性。仿甲虫鞘翅机翼航空器安装水平推进装置5，通过水平推进实现水平飞行，航空器水平飞行时仿甲虫鞘翅的机翼在翼型升力作用下自动上翻展平成为固定翼，提供水平飞行所需升力。航空器悬停状态下，仿甲虫鞘翅的机翼完全下垂以后还可以像风向标一样自动顶风。仿甲虫鞘翅的机翼在相应的飞行状态下自动变形，让航空器具备了自适应能力，降低人工操作的繁复程度，提高容错率。
仿甲虫鞘翅机翼航空器垂直起降和水平飞行时可以分别操控、无缝衔接，垂直起飞时可以关闭水平推进装置5，升高到合适高度后启动水平推进，水平飞行达到一定速度后再逐渐关闭旋转翼4，降落过程则相反，通过仿甲虫鞘翅的机翼2的自适应工作，降低垂直起降的驱动机构和水平飞行的驱动机构之间的强烈耦合关系，使得飞行模式的转换更加自然，更加顺畅，更加简易，更加安全。
仿甲虫鞘翅的机翼模仿甲虫鞘翅功能设计，包括一组悬臂2-1与翼体2-2，悬臂2-1的一端固定在机身1上，另一端通过自由铰链6与翼体2-2连接，翼体2-2可以围绕自由铰链6自由转动、在空中根据不同飞行工况的受力情况完成下垂收合或上翻展平。悬臂2-1的长度保证翼体2-2完全下翻后，其内侧与机体1的间距大于机体1宽度的3/5，在机身1之间留出足够的空间。仿甲虫鞘翅的机翼2转动时，通过设置普通限位凸块式结构的限位装置2-3，控制其转动的精确位置，并保证左右两侧机翼同步翻转。限位装置在限制机翼上下翻动后固定位置的同时，避免由于受力不平衡而出现的横滚失稳，并保证航空器左右两侧的刚性机翼能够展平到某一稳定的位置。仿甲虫鞘翅的机翼2的下垂收合和上翻展平的完成，通过普通电动操控机构人工辅助操作，提高机翼工作的灵活性和可靠性，大大提高航空器飞行的协调性与鲁棒性。
航空器的机身1为片状，机身的宽度远远小于高度和长度，其正断面和横断面呈窄长形，机身外形的高宽比和长宽比均＞8，采用长宽比大于高宽比的卧式机身，大幅减小飞行器正向飞行或垂直起降时的空气阻力，保证机身对于水平方向和垂直方向的气流均无遮挡，形成良好的垂直起降和水平飞行气动特性。航空器的片状机身采用机舱1-1与导流板1-2的组合结构，导流板1-2为连续表面结构，设置于机舱的后部位置。机身1和导流板1-2的迎风面断面为对称的楔形、迎风面轮廓线为流线型，以减少空气阻力。
航空器的旋转翼4为收放式旋翼，采用一组可以在飞行中完全展开和完全收合的旋翼桨叶4-3，旋翼桨叶4-3则通过桨叶轴套4-2与旋翼驱动轴4-1连接。航空器起降时驱动轴4-1正向旋转，并通过桨叶轴套4-2依次驱动旋翼桨叶4-3正向旋转，使所有桨叶完全 展开产生最大升力；航空器水平飞行时，驱动轴4-1停止旋转，旋翼桨叶4-3将在迎面气流的作用下反向自由回旋，最终完全收合重叠，变形为一个空气阻力很小的形状。收放式旋翼通过桨叶轴套的棘轮作用和利用离心力和风力的作用实现旋翼的自动收放，可以根据飞行工况自动调整旋翼桨叶的工作状态，显著消除垂直起降航空器旋翼水平飞行的阻力和振动。
旋翼桨叶4-3的数目为三片，旋翼桨叶的正向依次展开的自动锁位通过在桨叶根部设置锁位机构的方法实现，即采用三角形桁架连接三片桨叶与驱动轴，三片桨叶分别与桁架的三个角铰接，由驱动轴带动相互间展开呈120°夹角，使所有桨叶完全展开产生最大升力，航空器水平飞行时则让驱动轴停转，旋翼的桨叶逆向收合自然复位至旋翼原始状态时的三角形，使旋翼的空气阻力降为最小，利用离心力和空气动力的作用而根据飞行工况自动调整旋翼桨叶的工作状态，消除垂直起降航空器旋翼水平飞行阻力和振动。旋翼桨叶的工作状态与航空器的飞行状况保持同步，旋翼桨叶的工作机理与航空器的飞行相互协调，使得旋翼具有根据航空器飞行状况自动改变气动外形的能力，在飞行过程中完全展开或者完全收缩，实现垂直起降和水平飞行两种工作模式下旋翼工作状态的自然转换、平稳过渡和有效兼容。
上面结合附图对本发明的技术内容作了说明，但本发明的保护范围并不限于所述内容，在本领域的普通技术人员所具备的知识范围内，还可以在不脱离本发明宗旨的前提下对本发明的技术内容做出各种变化，凡在本发明的精神和原则之内，所做的任何修改、等同替换、改进等，均应包含在本发明的保护范围之内。

Claims (10)

  1. 一种仿甲虫鞘翅机翼航空器，其特征在于：所述航空器包括机身(1)、机翼(2)、旋转翼(4)、水平推进装置(5)，采用仿甲虫鞘翅的机翼作为航空器的水平翼，仿甲虫鞘翅的机翼(2)与航空器机身(1)铰接，仿甲虫鞘翅的机翼可在空中根据不同飞行工况的受力情况自动完成下垂和展平的收放动作；仿甲虫鞘翅机翼航空器上方安装有旋转翼(4)，通过旋转翼实现垂直起降，航空器垂直起降时仿甲虫鞘翅的机翼在重力和旋翼下洗气流作用下自动下垂收合而与机身趋于平行，避免机翼对下洗气流的遮挡和气弹振动，消除机翼对旋转翼的干扰；仿甲虫鞘翅机翼航空器安装水平推进装置(5)，通过水平推进实现水平飞行，航空器水平飞行时仿甲虫鞘翅的机翼在翼型升力作用下自动上翻展平成为固定翼，提供水平飞行所需升力。
  2. 根据权利要求1所述的仿甲虫鞘翅机翼航空器，其特征在于：所述仿甲虫鞘翅的机翼模仿甲虫鞘翅功能设计，包括一组悬臂(2-1)与翼体(2-2)，悬臂(2-1)的一端固定在机身(1)上，另一端通过自由铰链(6)与翼体(2-2)连接，翼体(2-2)可以围绕自由铰链(6)自由转动、在空中根据不同飞行工况的受力情况自动完成下垂收合或上翻展平；当所述翼体(2-2)的下垂空间受限时，可将翼体(2-2)设计为折叠式或伸缩式结构，使整个机翼展开时能够长度大于机身高度，突破机身高度对于机翼翼展的限制，从而提高航空器升力。
  3. 根据权利要求2所述的仿甲虫鞘翅机翼航空器，其特征在于：所述悬臂(2-1)的长度需保证翼体(2-2)完全下翻后在机身(1)之间留出足够的空间，一般翼体(2-2)内侧与机体(1)之间的最小距离应大于机体(1)宽度的1/2。
  4. 根据权利要求2所述的仿甲虫鞘翅机翼航空器，其特征在于：所述仿甲虫鞘翅的机翼(2)转动时，通过设置限位装置(2-3)控制其转动的精确位置，并保证左右两侧机翼同步翻转；所述仿甲虫鞘翅的机翼(2)的下垂收合和上翻展平的完成，可以利用机翼重力自然下垂、利用翼型升力克服机翼重力自然上翻，也可以通过操控机构人工操作完成。
  5. 根据权利要求1所述的仿甲虫鞘翅机翼航空器，其特征在于：所述航空器的机身(1)为片状，机身的宽度远远小于高度和长度，其正断面和横断面呈窄长形，机身外形的高宽比和长宽比一般均应大于4，从而大幅减小飞行器正向飞行或垂直起降时的空气阻力。
  6. 根据权利要求5所述的仿甲虫鞘翅机翼航空器，其特征在于：所述片状的航空器机身(1)为整体式结构或机舱(1-1)与导流板(1-2)的组合结构，导流板(1-2)为连 续表面结构；所述机身(1)和导流板(1-2)的迎风面断面为对称的楔形、迎风面轮廓线为流线型，以减少空气阻力。
  7. 根据权利要求1或5所述的仿甲虫鞘翅机翼航空器，其特征在于：所述航空器的旋转翼(4)为收放式旋翼，采用一组可以在飞行中完全展开和完全收合的旋翼桨叶(4-3)，旋翼桨叶(4-3)则通过桨叶轴套(4-2)与旋翼驱动轴(4-1)连接；航空器起降时驱动轴(4-1)正向旋转，并通过桨叶轴套(4-2)依次驱动旋翼桨叶(4-3)正向旋转，使所有桨叶完全展开产生最大升力；航空器水平飞行时，驱动轴(4-1)停止旋转，旋翼桨叶(4-3)将在迎面气流的作用下反向自由回旋，最终完全收合重叠，变形为一个空气阻力很小的形状；收放式旋翼通过桨叶轴套的棘轮作用和利用离心力和风力的作用实现旋翼的自动收放，可以根据飞行工况自动调整旋翼桨叶的工作状态，显著消除垂直起降航空器旋翼水平飞行的阻力和振动。
  8. 根据权利要求7所述的仿甲虫鞘翅机翼航空器，其特征在于：所述旋转翼(4)的旋翼桨叶(4-3)的数目可以根据需要确定为1、2、3、4、5、6、7、8甚至更多，每个桨叶均通过桨叶轴套(4-2)与旋翼驱动轴(4-1)连接；桨叶轴套(4-2)具有类似棘轮的单向锁止功能，可以正向驱动旋转展开锁位和逆向自由旋转收合后顺；单向锁止结构包括但不限于每个桨叶轴套(4-2)具有上下两个结合面分别与上下两个相邻桨叶的桨叶轴套相配合，下结合面(4-2-1)与下桨叶轴套的上结合面配合，上结合面(4-2-2)与上桨叶轴套的下结合面配合；最下一叶桨叶为主动桨叶，其余为从动桨叶；旋翼驱动轴(4-1)与主动桨叶的轴套相连接，当旋翼驱动轴驱动主动桨叶的轴套时，根据上下桨叶轴套之间的相互配合关系，下方的桨叶轴套将依次驱动上方的桨叶轴套带动旋翼桨叶旋转，当旋翼桨叶正向完全展开后各相邻桨叶的夹角均分360°圆周角；当旋翼驱动轴停止驱动时，桨叶在迎面风力作用下逆向自由回旋，后顺收合，相互重叠，相邻桨叶的夹角为零。
  9. 根据权利要求1或5所述的仿甲虫鞘翅机翼航空器，其特征在于：所述航空器的片状机身上安装有一个或多个大面积片状鳍翼(3)，通过转动鳍翼改变鳍翼与气流的相对运动状态产生作用力或通过改变鳍翼的组合状态产生力矩，使鳍翼产生的力或力矩施加于片状机身，控制航空器的航行姿态。
  10. 根据权利要求7所述的仿甲虫鞘翅机翼航空器，其特征在于：所述仿甲虫鞘翅机翼航空器垂直起降和水平飞行时可以分别操控、无缝衔接，垂直起飞时可以关闭水平推进装置(5)，升高到合适高度后启动水平推进，水平飞行达到一定速度后再逐渐关闭旋 转翼(4)，降落过程则相反，通过仿甲虫鞘翅的机翼(2)的自适应工作，降低垂直起降的驱动机构和水平飞行的驱动机构之间的强烈耦合关系，使得飞行模式的转换更加自然，更加顺畅，更加简易，更加安全。
PCT/CN2018/090417 2017-06-09 2018-06-08 一种仿甲虫鞘翅机翼航空器 WO2018224033A1 (zh)

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CN201710434378.6A CN107226193A (zh) 2017-06-09 2017-06-09 一种减小航空器机身飞行阻力的方法
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