AU2021106880A4 - Aircraft and method for achieving vertical take-off and landing and horizontal flight by segmented tilting bottom-driven plate wings - Google Patents
Aircraft and method for achieving vertical take-off and landing and horizontal flight by segmented tilting bottom-driven plate wings Download PDFInfo
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- AU2021106880A4 AU2021106880A4 AU2021106880A AU2021106880A AU2021106880A4 AU 2021106880 A4 AU2021106880 A4 AU 2021106880A4 AU 2021106880 A AU2021106880 A AU 2021106880A AU 2021106880 A AU2021106880 A AU 2021106880A AU 2021106880 A4 AU2021106880 A4 AU 2021106880A4
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- 238000006243 chemical reaction Methods 0.000 claims abstract description 11
- 238000007664 blowing Methods 0.000 claims abstract description 4
- 230000007246 mechanism Effects 0.000 claims description 26
- 230000001360 synchronised effect Effects 0.000 claims description 11
- 241000283070 Equus zebra Species 0.000 claims description 5
- 239000002131 composite material Substances 0.000 claims description 2
- 239000007769 metal material Substances 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 13
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
-
- 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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/04—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
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- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
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Abstract
The present invention relates to an aircraft and a method for achieving vertical
take-off and landing (VTOL) and horizontal flight by segmented tilting bottom-driven
plate wings. Each large-area plate wing is transversely divided into a plurality of
movable strip-shaped plate wings and fixed strip-shaped plate wings; the fixed
strip-shaped plate wings are rigidly connected with a fuselage without moving parts; the
movable strip-shaped plate wings are connected with the fuselage through horizontal
hinges and can be tilted longitudinally; lower parts of the movable strip-shaped plate
wings are fixedly connected with driving devices, so that the movable strip-shaped plate
wings tilt as a louver; when tilting to horizontal, the movable strip-shaped plate wings
are combined into a large-area plate wing, and the driving devices of each segment are
connected in series one behind another, thereby blowing high-speed airflow from the
lower part of the wing along a tangential direction to achieve horizontal flight; and
when tilting to vertical, strip-shaped air inlets are opened, the driving devices of each
segment are connected in parallel one behind another, so that air is sucked from a
position above the wing and exhausted to a position below the wing, thereby achieving
VTOL. The present invention takes into account different requirements of horizontal
flight and VTOL, improves the VTOL capability and the flight efficiency, achieves the
smooth conversion of flight modes, and has stable working and intuitive, safe, reliable,
simple and feasible operation.
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Description
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The present invention belongs to the technical field of aviation.
At present, the vertical take-off and landing (VTOL) aircraft still have some
insurmountable inherent defects. Firstly, the efficiency is low; and a thrust-to-weight
ratio of the existing VTOL aircraft is less than 1, so that the flight efficiency is low.
Secondly, because the absolute speed of a wingtip must be less than the speed of sound,
the theoretical speed of a rotary wing aircraft cannot exceed 420 km/h, thereby limiting
the flight speed. Thirdly, the mechanical vibration is generated by the flapping of rotor
blades, thereby increasing the wear of hinges and causing low reliability.
To solve the above technical problems, the present invention provides an aircraft,
in which a large-area plate wing is divided into a plurality of segments so that an air
inlet channel can be opened conveniently to enhance the lift of VTOL and take into
account horizontal flight, wherein the aircraft includes a fuselage, wings, a take-off and
landing mechanism, a driving mechanism and an operating mechanism. Large-area plate
wings and a sheet-like fuselage with a height-width ratio greater than or equal to 4 are
adopted; and each large-area plate wing is transversely divided into a plurality of
strip-shaped plate wings, which include movable strip-shaped plate wings and fixed
strip-shaped plate wings alternately arranged as zebra stripes. A plurality of driving
devices (such as propellers or jet engines) are arranged below each movable
strip-shaped plate wing side by side. The fixed strip-shaped plate wings are located
between a front movable strip-shaped plate wing and a rear movable strip-shaped plate wing, and are rigidly connected with the fuselage without moving parts. The movable strip-shaped plate wings are located at front ends and rear ends of the fixed strip-shaped plate wings, are connected with the fuselage through horizontal hinges, and can tilt longitudinally; and lower parts of the movable strip-shaped plate wings are fixedly connected with driving devices, so that the driving devices and the movable strip-shaped plate wings can rotate jointly at a tilting angle greater than 95°. Synchronizing mechanisms are arranged between the movable strip-shaped plate wings and the driving devices below the movable strip-shaped plate wings to ensure the synchronous rotation of all segments. The movable strip-shaped plate wings can be combined with the fixed strip-shaped plate wings to form an integral plate wing for adapting to the horizontal flight, and can also be opened transversely as a louver to form strip-shaped air inlets for achieving the VTOL and flying backwards in a hovering state.
In the case of horizontal flight, the movable strip-shaped plate wings together with the driving devices below the movable strip-shaped plate wings are located at a horizontal
position so that the strip-shaped plate wings are spliced to form an integral plate wing;
the driving devices are connected in series one behind another; and high-speed air is blown from the lower part of the wing along a tangential direction to push a plate wing
aircraft to fly forwards. In the case of VTOL, the movable strip-shaped plate wings
together with the driving devices below the movable strip-shaped plate wings are rotated to a vertical position so that air inlets are exposed from the wing; the driving
devices of each segment are connected in parallel one behind another; and air is sucked from a position above the wing and exhausted to a position below the wing, to form a
differential pressure lift for achieving the VTOL.
The number and density of the movable strip-shaped plate wings and the fixed strip-shaped plate wings can be flexibly selected as needed. For a segmented
bottom-driven aircraft, a front movable strip-shaped plate wing with a longitudinally
rotating horizontal aileron must be arranged at a frontmost end of the large-area plate wing to control the up-and-down pitching of the aircraft; and a rear movable
strip-shaped plate wing with transversely rotating grid vertical tail wings must be arranged at a rearmost end of the large-area plate wing to control the left-and-right yawing of the aircraft. A plurality of middle movable strip-shaped plate wings and fixed strip-shaped plate wings can be arranged between the two movable strip-shaped plate wings as needed. The number of the fixed strip-shaped plate wings can be flexibly set between 0 and n. When the number of the fixed strip-shaped plate wings is greater than
1 and equal to n, the number of the middle movable strip-shaped plate wings should be
equal to n-i. A plurality of driving devices (such as propellers or jet engines) are arranged below
the movable strip-shaped plate wings side by side; an even number of the driving
devices are laterally bilaterally symmetrically arranged in each segment; and the
number of the driving devices of each segment may be 2, 4, 6, 8 or more. The driving devices of each segment are fixed with movable strip-shaped plate wings directly above
the driving devices and can rotate longitudinally along a transverse rotating shaft as a louver.
In a horizontal flight mode, the driving devices below each movable strip-shaped
plate wing are connected in series to jointly drive the airflow to flow to the rear of the plate wings; and the driving devices thereof segment are densely arranged. In a VTOL
mode, the driving devices under each movable strip-shaped plate wing are connected in
parallel, and respectively drive the airflow to flow below the plate wings. A distance between the front driving device and the rear driving device (or a distance between two
adjacent movable strip-shaped plate wings) should be greater than or equal to three times the diameter D of the air inlets of the driving devices.
A crank-rocker synchronizing mechanism (or other mechanical synchronizing
mechanism and electronic synchronizing mechanism) is arranged between each movable strip-shaped plate wing and the driving device below the movable strip-shaped
plate wing to ensure the synchronous rotation of all segments.
The synchronizing mechanism can tilt more than 95° (the tilting angle is greater than or equal to 95°) around the sheet-like fuselage through the movable strip-shaped
plate wing rotating shaft, thereby ensuring that the aircraft can fly backwards in a hovering state and improving the maneuverability. In the case of forced landing due to no power, the rising airflow will force the movable strip-shaped plate wings to be flattened out and spliced with the fixed strip-shaped plate wings to form an integral large-area plate wing. The large-area plate wing, the sheet-like fuselage, the aileron and the winglets form a relatively large box just as a parachute, which ensures the slow landing of the plate wing aircraft and improves the safety of the aircraft. The frontmost one and the rearmost one of the movable strip-shaped plate wings are relatively special. The frontmost movable strip-shaped plate wing is called the front movable strip-shaped plate wing; a horizontal aileron capable of rotating longitudinally is arranged at a front lower part of the front movable strip-shaped plate wing; and the up-and-down pitching of the aircraft can be controlled by the longitudinal rotation of the horizontal aileron. The rearmost movable strip-shaped plate wing is called the rear movable strip-shaped plate wing; grid vertical tail wings capable of transversely rotating are arranged at a rear lower part of the rear movable strip-shaped plate wing; and the left-and-right yawing of the aircraft can be controlled by the transverse rotation of the grid vertical tail wings. Due to the segmented tilting, whether in a state of VTOL or horizontal flight, the up-and-down pitching of the aircraft can be controlled by the longitudinal rotation of the horizontal aileron; and the left-and-right yawing of the aircraft can be controlled by the transverse rotation of the grid vertical tail wings, thereby achieving the seamless conversion between the VTOL mode and the horizontal flight mode.
Large winglets are arranged on the left and right of the large-area plate wing, to not
only reduce wingtip turbulence and overcome induced drag, but also stabilize the vertical tail wing. In addition, the large winglets can also strengthen support of the
wings and improve rigidity of the fuselage.
For the movable strip-shaped plate wings, except that the rear movable strip-shaped plate wing should be widened appropriately with the consideration of
yawing and the differential pressure lift, the remaining movable strip-shaped plate wings should not be too wide to meet the air intake requirements. The fixed strip-shaped plate wings can be widened appropriately to meet the requirements of differential pressure lift. The width of the rear movable strip-shaped plate wing is generally 1/1-1/6 of the length thereof; the widths of the front movable strip-shaped plate wing and the middle movable strip-shaped plate wing are generally 1/4-1/10 of the lengths thereof; and the widths of the fixed strip-shaped plate wings are generally 1/2-1/8 of the lengths thereof. The main body of the plate wing is in a horizontal state whether in the horizontal flight mode or the VTOL mode. The movable strip-shaped plate wings are in the horizontal state in the horizontal flight mode and longitudinally rotate to a vertical state in the VTOL mode. Since the movable strip-shaped plate wings longitudinally rotating to the vertical state are of a strip shape, a small height and a staggered distribution in front and back, the main body of the plate wing is still in the horizontal state in the VTOL mode, thereby effectively resisting the influence of crosswind, overcoming the
"Door Panel Effect" existing in the historical and existing aircrafts for achieving VTOL
by tilting wings, and effectively improving the stability and safety of VTOL. Both the movable strip-shaped plate wings and the fixed strip-shaped plate wings
are of a thin shell structure and are made of high-strength composite materials or
high-strength light metal materials. Contour lines of the large-area plate wings are curves of upper surfaces of low-speed airfoils. In the case of horizontal flight, the
airflow subjects to downwash on the upper surface of the plate wing through the airfoil
to generate lift; and the driven airflow can also be subjected to forced downwash on the
lower surface of the plate wing to generate lift, which is greater than that of the general
fixed wing. The thrust-to-weight ratio in the VTOL mode is greater than 1; and the
thrust-to-weight ratio in the horizontal flight mode is greater than 5.
The plate wings are designed to be strip-shaped segmented combined plate wings,
thereby taking into account different requirements of horizontal flight and VTOL as
well, and further improving the VTOL capability and the flight efficiency. Meanwhile,
the driving devices and the strip-shaped plate wings above the driving devices are designed to synchronously and longitudinally rotate along a transverse rotating shaft as a louver, thereby achieving continuous, smooth and seamless conversion between the horizontal flight mode and the VTOL mode, effectively overcoming the world-class problem of controlling abrupt changes when the horizontal flight mode and VTOL mode are converted to each other, achieving natural transition of control modes of the operating mechanism, smooth change of control parameters and no abrupt change in control effect, taking into account the different requirements of the horizontal flight and the VTOL, solving a problem of flight mode conversion, reducing the control difficulty of the VTOL aircraft, significantly improving the flight efficiency, and achieving stable working and intuitive, safe, reliable, simple and feasible operation.
In the present invention, the fuselage of the aircraft is a sheet-like fuselage, which forms a relatively large box together with the plate wings, the aileron and the winglets.
The box can improve the stability during horizontal flight, and can form an airflow duct during VTOL for guiding the jet airflow of the driving devices downwards to achieve
apparent ground effect, which can increase the elasticity of air in the case of take-off
and landing to alleviate the impact of take-off and landing. In the case of forced landing due to no power, the rising airflow will force the movable strip-shaped plate wings to be
flattened out and spliced with the fixed strip-shaped plate wings to form an integral
large-area plate wing. The large-area plate wing, the sheet-like fuselage, the aileron and the winglets form a relatively large box just as a parachute, which ensures the slow
landing of the aircraft. In addition, the VTOL mode of front air intake and rear air exhaust straightens out a movement path of the airflow, which is more scientific and
reasonable than that of the take-off and landing mode of vertical downward air exhaust
(such as helicopter), thereby preventing wind-drifting sand on the ground from blocking the sight line and damaging the machine.
According to the present invention, the aircraft can fully take into account two
flight conditions of VTOL and high-speed flight, and has the advantages of natural mode conversion, high flight efficiency, low wing loading, high safety and stability,
simple structure, simple and convenient operation, low cost, easy popularization and the like.
To solve the above technical problems, the present invention also provides a
method for achieving VTOL and horizontal flight by segmented bottom-driven plate wings. The method includes the following steps: for an aircraft with large-area plate
wings, designing the large-area plate wings as combined wings, transversely dividing
each large-area plate wing into a plurality of movable strip-shaped plate wings and fixed strip-shaped plate wings, and alternately arranging the movable strip-shaped plate wings and the fixed strip-shaped plate wings (the specific number and density can be selected
flexibly as needed) as zebra stripes, so that the movable strip-shaped plate wings can tilt
to be combined with the fixed strip-shaped plate wings to form an integral plate wing
for adapting to horizontal flight and can also be transversely opened as a louver to form strip-shaped air inlets for achieving VTOL; fixing an even number (the number of
driving devices of each segment may be 2, 4, 6, 8 or more, which is determined according to actual needs) of driving devices (such as propellers orjet engines) below
the movable strip-shaped plate wings side by side in a bilaterally symmetrical manner,
wherein the driving devices of each segment together with the movable strip-shaped plate wings right above the driving devices can tilt longitudinally around a transverse
rotating shaft, and a synchronizing mechanism is arranged between the movable
strip-shaped plate wings to ensure the synchronous rotation of the driving devices of all segments as the louver; in the case of horizontal flight, rotating the movable
strip-shaped plate wings together with the driving devices below the movable
strip-shaped plate wings to a horizontal position so that the movable strip-shaped plate
wings are spliced with the fixed strip-shaped plate wings to form an integral plate wing,
connecting the driving devices of each segment in series one behind another, and
blowing high-speed airflow at the lower part of the integral plate wing to the rear of the
wing along a tangential direction through the driving devices, thereby pushing the
aircraft to fly forwards; and in the case of VTOL, rotating the movable strip-shaped
plate wings together with the driving devices below the movable strip-shaped plate
wings to a vertical position so that the movable strip-shaped plate wings above the driving devices are opened transversely to expose strip-shaped air inlets, connecting the driving devices of each segment in parallel one behind another, sucking air from a position above the wing and exhausting air to a position below the wing by the driving devices, forming a negative-pressure region above the wing and a positive-pressure region below the wing, and utilizing a differential pressure lift formed by the negative-pressure region and the positive-pressure region to achieve the VTOL.
Fig. 1 is a schematic side view of a segmented bottom-driven aircraft/plate wing in a horizontal flight state according to the present invention.
Fig. 2 is a schematic vertical view of the segmented bottom-driven aircraft/plate wing in the horizontal flight state according to the present invention.
Fig. 3 is a schematic rear view of the segmented bottom-driven aircraft/plate wing in the horizontal flight state according to the present invention.
Fig. 4 is a schematic side view of the segmented bottom-driven aircraft/plate wing
in a VTOL state according to the present invention. Fig. 5 is a schematic vertical view of the segmented bottom-driven aircraft/plate
wing in the VTOL state according to the present invention.
Fig. 6 is a schematic rear view of the segmented bottom-driven aircraft/plate wing in the VTOL state according to the present invention.
Fig. 7 is a schematic diagram of an airfoil NACA4412. Fig. 8 is a schematic diagram of a plate wing with a thin shell structure of the
segmented bottom-driven aircraft/plate wing according to the present invention.
Fig. 9 is a schematic diagram of the control principle of up-pitching movement of the segmented bottom-driven aircraft/plate wing in horizontal flight according to the
present invention.
Fig. 10 is a schematic diagram of the control principle of down-pitching movement of the segmented bottom-driven aircraft/plate wing in horizontal flight according to the
present invention.
Fig. 11 is a schematic diagram of the control principle of right movement of the segmented bottom-driven aircraft/plate wing in horizontal flight according to the present invention.
Fig. 12 is a schematic diagram of the control principle of left movement of the segmented bottom-driven aircraft/plate wing in horizontal flight according to the present
invention. Fig. 13 is a schematic diagram of the control principle of up-pitching movement of the segmented bottom-driven aircraft/plate wing in VTOL according to the present
invention.
Fig. 14 is a schematic diagram of the control principle of down-pitching movement
of the segmented bottom-driven aircraft/plate wing in VTOL according to the present invention.
Fig. 15 is a schematic diagram of the control principle of right movement of the segmented bottom-driven aircraft/plate wing in VTOL according to the present
invention.
Fig. 16 is a schematic diagram of the control principle of left movement of the segmented bottom-driven aircraft/plate wing in VTOL according to the present
invention.
Fig. 17 is a schematic diagram of pulling-backward and flattening-out of a rocker of the segmented bottom-driven aircraft/plate wing in synchronous tilting according to the present invention.
Fig. 18 is a schematic diagram of pushing-forward and drooping of the rocker of the segmented bottom-driven aircraft/plate wing in synchronous tilting according to the
present invention. Fig. 19 is a schematic diagram of the superposition of pulling-backward and
pushing-forward of the rocker of the segmented bottom-driven aircraft/plate wing in
synchronous tilting according to the present invention. In the figures, 1-horizontal aileron, 2-horizontal aileron hinge, 3-driving device,
4-front movable strip-shaped plate wing/frontmost movable strip-shaped plate wing,
5-fixed strip-shaped plate wing, 6-sheet-like fuselage, 7-upright column, 8-middle movable strip-shaped plate wing, 9-rear movable strip-shaped plate wing/rearmost movable strip-shaped plate wing, 10-grid vertical tail wing, 1-large winglet, 12-cabin,
13-rear wheel, 14-front wheel, 15-cross bar, 16-pull rope, 17-movable strip-shaped plate
wing rotating shaft, 18-rocker crank, 19-rocker hinge, 20-rocker straight-bar, 21-rear
axle, and 22-airfoil NACA4412.
The present invention will be further described in detail in combination with the accompanying drawings.
Embodiment 1: As shown in Figs. 1-19, an aircraft for achieving VTOL and horizontal flight by
segmented tilting bottom-driven plate wings includes a fuselage, wings, a take-off and landing mechanism, a driving mechanism and an operating mechanism. A sheet-like
fuselage with large-area plate wings and a height-width ratio of 4 is adopted. Each
large-area plate wing is transversely divided into movable strip-shaped plate wings capable of tilting and a fixed strip-shaped plate wing; the movable strip-shaped plate
wings and the fixed strip-shaped plate wing are alternately arranged as zebra stripes;
and four propellers are arranged below each movable strip-shaped plate wing side by side as driving devices. The movable strip-shaped plate wings are integrally fixed with
the propellers and tilt down around the sheet-like fuselage through a movable strip-shaped plate wing rotating shaft at a tilting angle of up to 95°, so that the movable
strip-shaped plate wings can tilt to horizontal and is combined with the fixed
strip-shaped plate wing to form a horizontal integral wing for adapting to horizontal flight, and can also transversely tilt downwards as a louver to open strip-shaped air
inlets for achieving VTOL.
In the present embodiment, the plate wing is divided into two movable strip-shaped plate wings and one fixed strip-shaped plate wing; and four propellers are arranged
below each movable strip-shaped plate wing side by side as the driving devices, for a total of eight propellers. The four propellers of each driving device together with the movable strip-shaped plate wing directly above the four propellers synchronously rotate as the louver along a transverse rotating shaft through a crank-rocker mechanism. No matter how the movable strip-shaped plate wings tilt, a main body of the plate wing is in a horizontal state whether in a horizontal flight mode or a VTOL mode. The movable strip-shaped plate wings are in the horizontal state in the horizontal flight mode and longitudinally rotate to a vertical state in the VTOL mode. Since the movable strip-shaped plate wings longitudinally rotating to the vertical state are of a strip shape, a small height and a staggered distribution in front and back, the main body of the plate wing is still in the horizontal state in the VTOL mode, thereby effectively resisting the influence of crosswind, overcoming the "Door Panel Effect" existing in the historical and existing aircraft for achieving VTOL by tilting wings, and effectively improving the stability and safety of VTOL. In the case of forced landing due to no power, the rising airflow will force the movable strip-shaped plate wings to be flattened out and spliced with the fixed strip-shaped plate wing to form an integral large-area plate wing.
The large-area plate wing, the sheet-like fuselage, the aileron and the winglets form a relatively large boxjust as a parachute, which ensures the slow landing of the aircraft.
In the present embodiment, two movable strip-shaped plate wings, i.e., a front
movable strip-shaped plate wing and a rear movable strip-shaped plate wing, are provided; and one fixed strip-shaped plate wing is located between the two movable
strip-shaped plate wings. The width of the rear movable strip-shaped plate wing is 1/2 of the length thereof; the widths of the front movable strip-shaped plate wing and the
middle movable strip-shaped plate wing are 1/8 of the lengths thereof; and the width of
the fixed strip-shaped plate wing is 1/4 of the length thereof (the width of the fixed strip-shaped plate wing is twice the diameter D of the propellers). A horizontal aileron
capable of rotating longitudinally is arranged at a front lower part of the front movable
strip-shaped plate wing, for controlling the up-and-down pitching of the aircraft; and four grid vertical tail wings capable of transversely rotating are arranged at a rear lower
part of the rear movable strip-shaped plate wing, for controlling the left-and-right yawing of the aircraft. In the horizontal flight mode, the driving devices below the front movable strip-shaped plate wing and the rear movable strip-shaped plate wing are connected in series to jointly drive the airflow to flow to the rear of the plate wing, thereby driving the aircraft to achieve horizontal flight. In the VTOL mode, the driving devices below the front movable strip-shaped plate wing and the rear movable strip-shaped plate wing are connected in parallel to jointly drive the airflow to flow to a position below the plate wing, thereby driving the aircraft to achieve VTOL. A distance between the two driving devices is equal to three times the diameter D of the propellers.
Due to the segmented tilting, whether in a state of VTOL or horizontal flight, the
up-and-down pitching of the aircraft can be controlled by the longitudinal rotation of the
horizontal aileron; and the left-and-right yawing of the aircraft can be controlled by the transverse rotation of the grid vertical tail wing, thereby completely solving the problem
of abrupt changes in control effects of the operating mechanism when the flight mode is converted, and achieving natural transition of control modes, smooth change of control
parameters, and seamless conversion of the flight modes.
The aircraft provided by the present invention can achieve the continuous, smooth and seamless conversion between the horizontal flight mode and the VTOL mode,
effectively overcomes the problem of controlling abrupt changes when the horizontal
flight mode and VTOL mode are converted to each other, achieves natural transition of control modes of the operating mechanism, smooth change of control parameters and no
abrupt change in control effect, takes into account the different requirements of the horizontal flight and the VTOL, solves a problem of flight mode conversion, reduces the
control difficulty of the VTOL aircraft, significantly improves the flight efficiency, and
achieves stable working and intuitive, safe, reliable, simple and feasible operation. Embodiment 2:
As shown in Figs. 1-19, a method for achieving VTOL and horizontal flight by
segmented tilting bottom-driven plate wings according to the present invention includes the following steps: for an aircraft having a sheet-like fuselage (the height-width ratio of
the fuselage is 5) with large-area plate wings, designing the large-area plate wings as combined wings, transversely dividing each large-area plate wing into three movable strip-shaped plate wings and two fixed strip-shaped plate wings, and alternately arranging the movable strip-shaped plate wings and the fixed strip-shaped plate wings as zebra stripes, so that the movable strip-shaped plate wings can tilt to be combined with the fixed strip-shaped plate wings to form an integral plate wing for adapting to horizontal flight and can also be transversely opened as a louver to form strip-shaped air inlets for achieving VTOL; fixing a segment (or group) of propellers below each movable strip-shaped plate wing side by side as driving devices, wherein an even number (the number of driving devices of each group is 4) of driving devices are arranged in a bilaterally symmetrical manner, the driving devices of each segment together with the movable strip-shaped plate wings right above the driving devices can tilt longitudinally around a transverse rotating shaft, and a synchronizing mechanism is arranged between the movable strip-shaped plate wings to ensure the synchronous rotation of the driving devices of all segments as the louver; in the case of horizontal flight, rotating the movable strip-shaped plate wings together with the driving devices below the movable strip-shaped plate wings to a horizontal position so that the movable strip-shaped plate wings are spliced with the fixed strip-shaped plate wings to form an integral plate wing, connecting the driving devices of each segment in series one behind another, and blowing high-speed airflow at the lower part of the integral plate wing to the rear of the wing along a tangential direction through the driving devices, thereby pushing the aircraft to fly forwards; and in the case of VTOL, rotating the movable strip-shaped plate wings together with the driving devices below the movable strip-shaped plate wings to a vertical position so that the movable strip-shaped plate wings above the driving devices are opened transversely to expose strip-shaped air inlets, connecting the driving devices of each segment in parallel one behind another, sucking air from a position above the wing and exhausting air to a position below the wing by the driving devices, forming a negative-pressure region above the wing and a positive-pressure region below the wing, and utilizing a differential pressure lift formed by the negative-pressure region and the positive-pressure region to achieve the VTOL.
The method according to the present invention takes into account the different requirements of horizontal flight and VTOL by adopting the transversely segmented
tilting combined large-area plate wings, thereby achieving the smooth conversion
between the horizontal flight mode and the VTOL mode while further improving the
VTOL capability and the flight efficiency, and effectively overcoming a problem of
controlling abrupt changes when the horizontal flight mode and VTOL mode are converted to each other. The large-area plate wing is transversely divided into a plurality of strip-shaped
plate wings, wherein both the frontmost strip-shaped plate wing and the rearmost
strip-shaped plate wing are movable strip-shaped plate wings; one movable strip-shaped
plate wing and two fixed strip-shaped plate wings are arranged between the frontmost movable strip-shaped plate wing and the rearmost movable strip-shaped plate wing; and
the lower parts of the movable strip-shaped plate wings are fixedly connected with driving devices, so that the driving devices and the movable strip-shaped plate wings
can rotate jointly. The fixed strip-shaped plate wings are located between the front
strip-shaped plate wing and the rear strip-shaped plate wing and are rigidly connected with the fuselage without moving parts. The movable strip-shaped plate wings and the
fixed strip-shaped plate wings are arranged alternately. The width of the rearmost
strip-shaped plate wing is 1/2 of the length thereof; the widths of the remaining movable strip-shaped plate wings are 1/8 of the lengths thereof; and the widths of the fixed
strip-shaped plate wings are 1/4 of the lengths thereof. The frontmost strip-shaped plate wing of the large-area combined plate wing is a
movable strip-shaped plate wing; a horizontal aileron capable of rotating longitudinally
is arranged at a front lower part of the front movable strip-shaped plate wing, i.e., the frontmost movable strip-shaped plate wing is designed to be a special movable
strip-shaped plate wing with the horizontal aileron, so that the horizontal aileron is
integrally connected with the front movable strip-shaped plate wing to achieve
synchronous longitudinal rotation and can longitudinally rotate around the front
movable strip-shaped plate wing through a hinge, and the up-and-down pitching of the plate wing aircraft can be controlled by the longitudinal rotation of the horizontal aileron. The rearmost strip-shaped plate wing of the large-area combined plate wing is a movable strip-shaped plate wing; grid vertical tail wings capable of transversely rotating are arranged at a rear lower part of the rear movable strip-shaped plate wing, i.e., the rearmost movable strip-shaped plate wing is designed to be a special movable strip-shaped plate wing with vertical tail wings, so that the grid vertical tail wings are integrally connected with the movable strip-shaped plate wings to achieve synchronous longitudinal rotation and can transversely rotate around the rear movable strip-shaped plate wing through a hinge, and the left-and-right yawing of the plate wing aircraft can be controlled by the transverse rotation of the grid vertical tail wings. Whether in the horizontal flight mode or the VTOL mode, the horizontal aileron can rotate down to control the plate wing aircraft to pitch down, and rotate up to control the plate wing aircraft to pitch up; and the grid vertical tail wings can rotate clockwise to control the plate wing aircraft to yaw to the left, and can rotate counterclockwise to control the plate wing aircraft to yaw to the right, thereby achieving the natural transition of control modes and the smooth change of control parameters, and solving the problem of abrupt change in control effect of the operating mechanism when the flight mode is converted.
A crank-rocker mechanism is adopted as a synchronizing mechanism between each
movable strip-shaped plate wing and the driving device; and each movable strip-shaped plate wing together with the driving device is fixed on the same crank rocker, and is
integrally connected with a rocker straight-bar through a rocker hinge. All the driving
devices and the movable strip-shaped plate wings rotate synchronously; and the rotation
angles of all the driving devices and the movable strip-shaped plate wings can be
controlled by pushing and pulling the rocker straight-bar. The rocker straight-bar can be
pushed and pulled to control the rotation angles of all the driving devices and the
movable strip-shaped plate wings to be greater than 95, thereby ensuring that the
movable strip-shaped plate wings can be integrated with the plate wing to achieve
horizontal flight and can also synchronously rotate to a vertical position to open the
strip-shaped air inlets for achieving VTOL. The rotation angle of the synchronizing mechanism should ensure that an axis of each driving device can also rotate back for more than 5° after rotating to the vertical position, thereby achieving backward flight.
In the horizontal flight mode, the driving devices of each segment are connected in
series to jointly drive the airflow to flow to the rear of the plate wing; and the driving
devices of the same segment can be arranged densely. In the VTOL mode, the driving
devices of each segment are connected in parallel, and respectively drive the airflow to flow to a position below the wing. A distance between two adjacent segments (two groups) of driving devices, i.e., a distance between two adjacent movable strip-shaped
plate wings, is greater than three times the diameter D of the air inlets of the driving
devices.
The movable strip-shaped plate wings are in a horizontal state in the horizontal flight mode and longitudinally rotate to a vertical state in the VTOL mode. The movable
strip-shaped plate wings rotating to the vertical state have a relatively small width and are staggered in front and back, so that the main body of the whole plate wing is still in
the horizontal state in the VTOL mode; and the main body of the large-area combined
plate wing can keep horizontal in both the horizontal flight mode and the VTOL mode, thereby effectively resisting the influence of crosswind and overcoming the "Door Panel
Effect" existing in the aircraft for achieving VTOL by tilting wings, and improving the
stability of VTOL. In the case of forced landing due to no power, the rising airflow will force the movable strip-shaped plate wings to be flattened out and spliced with the fixed
strip-shaped plate wings to form an integral large-area plate wing. The large-area plate wing, the sheet-like fuselage, the aileron and the winglets form a relatively large box
just as a parachute, which ensures the slow landing of the aircraft and improves the
safety of the plate wing aircraft. Large down-folded winglets can also be arranged on the left and right of the
combined plate wing, to reduce wingtip turbulence, overcome induced drag, play a role
of stable regulation and control of the vertical tail wings, strengthen support of the wings, and improve rigidity of the fuselage. The large-area combined plate wing is of a
thin shell structure and is made of high-strength aluminum alloy materials. Contour lines of the plate wings are curves of upper surfaces of low-speed airfoils. In the case of horizontal flight, the airflow can be subjected to downwash on the upper surface of the plate wing through the airfoil to generate lift; and the driven airflow can also be subjected to forced downwash on a lower surface of the plate wing to generate lift, which is greater than that of the general fixed wing, so that the thrust-to-weight ratio in the VTOL mode is greater than 1, and the thrust-to-weight ratio in the horizontal flight mode is greater than 5.
Claims (11)
1. An aircraft for achieving vertical take-off and landing (VTOL) and horizontal flight by segmented tilting bottom-driven plate wings, comprising a fuselage, wings, a take-off and landing mechanism, a driving mechanism and an operating mechanism,
wherein large-area plate wings are adopted; each large-area plate wing is transversely divided into movable strip-shaped plate wings (4, 8 and 9) capable of tilting
longitudinally and fixed strip-shaped plate wings (5); the movable strip-shaped plate wings (4, 8 and 9) and the fixed strip-shaped plate wings (5) are alternately arranged as
zebra stripes; a plurality of driving devices (3) are arranged below each movable
strip-shaped plate wing (4, 8 and 9) side by side; the movable strip-shaped plate wings (4, 8 and 9) are integrally fixed with the driving devices (3) and tilt around a sheet-like
fuselage (6) through a movable strip-shaped plate wing rotating shaft (17) at a tilting
angle greater than 95°, so that the movable strip-shaped plate wings (4, 8 and 9) can tilt to horizontal and is combined with the fixed strip-shaped plate wings (5) to form a
horizontal integral wing for adapting to horizontal flight, and can also tilt downwards as
a louver to open strip-shaped air inlets for achieving VTOL and flying backwards in a hovering state.
2. The aircraft for achieving VTOL and horizontal flight by segmented tilting
bottom-driven plate wings according to claim 1, wherein 0, 1, 2, 3, 4, 5, 6 or more fixed strip-shaped plate wings (5) can be provided; each movable strip-shaped plate wing (4,
8 and 9) is at least provided with a front movable strip-shaped plate wing (4) and a rear
movable strip-shaped plate wing (9); 0, 1, 2, 3, 4, 5, 6 or more middle movable strip-shaped plate wings (8) can be provided; and when the number of the fixed
strip-shaped plate wings (5) is greater than or equal to 1 and is equal to n, the number of
the middle movable strip-shaped plate wings (8) should be equal to n-. 3. The aircraft for achieving VTOL and horizontal flight by segmented tilting
bottom-driven plate wings according to claim 1, wherein each movable strip-shaped plate wing (4, 8 and 9) is driven to tilt by a crank-rocker mechanism (18, 19 and 20) and keeps synchronization; a rocker crank (18) is fixed below each movable strip-shaped plate wing (4, 8 and 9) and is connected with a rocker straight-bar (20) through a rocker hinge (19); when the rocker straight-bars (20) are pulled forwards, the movable strip-shaped plate wings (4, 8 and 9), the driving devices (3) and the rocker cranks (18) can be tilted downwards around the sheet-like fuselage (6) more than 95° through the movable strip-shaped plate wing rotating shaft (17), to open the strip-shaped air inlets in an upper surface of the wing; all driving devices (3) of each segment are located at vertical positions connected in parallel one behind another at this moment; air is sucked by the driving devices (3) from a position above the fixed strip-shaped plate wings (5) and then is exhausted to a position below the fixed strip-shaped plate wings (5), thereby forming a negative-pressure region above the fixed strip-shaped plate wings (5), forming a positive-pressure region below the fixed strip-shaped plate wings (5), lifting the aircraft to hover by a differential pressure lift formed by the negative-pressure region and the positive-pressure region, and achieving VTOL; when the rocker straight-bars (20) are pulled backwards, the movable strip-shaped plate wings (4, 8 and
9), the driving devices (3) and the rocker cranks (18) can be tilted upwards around the sheet-like fuselage (6) to horizontal and then are combined with the fixed strip-shaped
plate wings (5) to form a horizontal integral wing; all driving devices (3) of each
segment are located at vertical positions connected in series one behind another at this moment; and high-speed airflow is blown from the lower part of the wing to a position
behind the wing through the driving devices (3) along a tangential direction to push the aircraft to move forwards, thereby achieving horizontal flight.
4. The aircraft for achieving VTOL and horizontal flight by segmented tilting
bottom-driven plate wings according to claim 1, wherein the frontmost one and the rearmost one of the movable strip-shaped plate wings (4, 8 and 9) are relatively special;
the frontmost movable strip-shaped plate wing is called a front movable strip-shaped
plate wing (4); a horizontal aileron (1) capable of rotating longitudinally around the front movable strip-shaped plate wing (4) is arranged at a front lower part of the front
movable strip-shaped plate wing (4); the up-and-down pitching of the aircraft can be controlled by the longitudinal rotation of the horizontal aileron (1); the rearmost movable strip-shaped plate wing is called a rear movable strip-shaped plate wing (9); grid vertical tail wings (10) capable of transversely rotating on the rear movable strip-shaped plate wing (9) are arranged at a rear lower part of the rear movable strip-shaped plate wing (9); the left-and-right yawing of the aircraft can be controlled by the transverse rotation of the grid vertical tail wings (10); and due to the segmented synchronous tilting, whether in a state of VTOL or horizontal flight, the up-and-down pitching of the aircraft can be controlled by the longitudinal rotation of the horizontal aileron (1), and the left-and-right yawing of the aircraft can be controlled by the transverse rotation of the grid vertical tail wings (10), thereby achieving the seamless conversion between a VTOL mode and a horizontal flight mode.
5. The aircraft for achieving VTOL and horizontal flight by segmented tilting
bottom-driven plate wings according to claim 1, wherein large winglets (11) are arranged on the left and right of the large-area plate wing.
6. The aircraft for achieving VTOL and horizontal flight by segmented tilting
bottom-driven plate wings according to claim 1, wherein the movable strip-shaped plate wings (4, 8 and 9) are in a horizontal state in the horizontal flight mode, and vertically
rotate to a vertical state in the VTOL mode; the fixed strip-shaped plate wings (5) are in
the horizontal state in both the horizontal flight mode and the VTOL mode; the movable strip-shaped plate wings (8), which longitudinally rotate to the vertical state, are of a
strip shape, a small height and a staggered distribution in front and back; and a main body of the large-area plate wing is still in a horizontal state in the VTOL mode.
7. The aircraft for achieving VTOL and horizontal flight by segmented tilting
bottom-driven plate wings according to claim 1, wherein the fixed strip-shaped plate wings (5) can be appropriately widened to meet the demand of differential pressure lift;
for the movable strip-shaped plate wings (4, 8 and 9), except that the rear movable
strip-shaped plate wing (9) should be widened appropriately with the consideration of yawing and the differential pressure lift, the front movable strip-shaped plate wing (4)
and the middle movable strip-shaped plate wing (8) should not be too wide to meet the air intake requirements; the width of the rear movable strip-shaped plate wing (9) is generally 1/1-1/6 of the length thereof; the widths of the front movable strip-shaped plate wing (4) and the middle movable strip-shaped plate wing (8) are generally
1/4-1/10 of the lengths thereof; and the widths of the fixed strip-shaped plate wings are generally 1/2-1/8 of the lengths thereof.
8. The aircraft for achieving VTOL and horizontal flight by segmented tilting
bottom-driven plate wings according to claim 1, wherein driving devices (3) are arranged below the movable strip-shaped plate wings (4, 8 and 9); in the horizontal
flight mode, two adjacent driving devices (3) are connected in series to jointly drive the
airflow to flow to the rear of the wing, and the driving devices (3) in the same segment can be arranged densely; in the VTOL mode, two adjacent driving devices (3) are
connected in parallel to respectively drive the airflow to flow to a position below the
wing; and a distance between the two adjacent driving devices (3) (or a distance
between two adjacent movable strip-shaped plate wings) should generally be greater than or equal to three times the diameter D of the air inlets of the driving devices (3).
9. The aircraft for achieving VTOL and horizontal flight by segmented tilting bottom-driven plate wings according to claim 1, wherein the movable strip-shaped plate
wings (4, 8 and 9) can tilt around the sheet-like fuselage (6) more than 95° through the
movable strip-shaped plate wing rotating shaft (17).
10. The aircraft for achieving VTOL and horizontal flight by segmented tilting
bottom-driven plate wings according to claim 1, wherein the large-area plate wing is of a thin shell structure and is made of high-strength composite materials or high-strength
light metal materials; contour lines of the wings (4, 5, 8 and 9) are curves of upper
surfaces of low-speed airfoils; in the case of horizontal flight, the airflow can be subjected to downwash on the upper surface of the wing through the airfoil to generate
lift, and the driven airflow can also be subjected to forced downwash on the lower
surface of the wing to generate lift, which is greater than that of the general fixed wing; the thrust-to-weight ratio in the VTOL mode is greater than 1; and the thrust-to-weight
ratio in the horizontal flight mode is greater than 5.
11. A method for achieving VTOL and horizontal flight by segmented tilting bottom-driven plate wings, comprising the following steps: for an aircraft with
large-area plate wings, designing the large-area plate wings as combined wings,
transversely dividing each large-area plate wing into a plurality of movable strip-shaped plate wings and fixed strip-shaped plate wings, and alternately arranging the movable
strip-shaped plate wings and the fixed strip-shaped plate wings, so that the movable
strip-shaped plate wings can tilt to be combined with the fixed strip-shaped plate wings to form an integral plate wing for achieving horizontal flight and can also be
transversely opened as a louver to form strip-shaped air inlets for achieving VTOL;
fixing an even number of driving devices below the movable strip-shaped plate wings side by side in a bilaterally symmetrical manner, wherein the driving devices of each
segment together with the movable strip-shaped plate wings right above the driving
devices can tilt longitudinally around a transverse rotating shaft, and a synchronizing mechanism is arranged between the movable strip-shaped plate wings to ensure the
synchronous rotation of the driving devices of all segments; in the case of horizontal
flight, rotating the movable strip-shaped plate wings together with the driving devices below the movable strip-shaped plate wings to a horizontal position so that the movable
strip-shaped plate wings are spliced with the fixed strip-shaped plate wings to form an
integral plate wing, connecting the driving devices of each segment in series one behind another, and blowing high-speed airflow at the lower part of the integral plate wing to
the rear of the wing along a tangential direction through the driving devices, thereby pushing the aircraft to fly forwards; and in the case of VTOL, rotating the movable
strip-shaped plate wings together with the driving devices below the movable
strip-shaped plate wings to a vertical position so that the movable strip-shaped plate wings above the driving devices are opened transversely to expose strip-shaped air
inlets, connecting the driving devices of each segment in parallel one behind another,
sucking air from a position above the wing and exhausting air to a position below the wing by the driving devices, forming a negative-pressure region above the wing and a
positive-pressure region below the wing, and utilizing a differential pressure lift formed by the negative-pressure region and the positive-pressure region to achieve the VTOL; the method achieves the smooth conversion between a horizontal flight mode and a VTOL mode while improving the VTOL capability and the flight efficiency by transversely tilting the combined large-area plate wings in segments and taking into account different requirements of horizontal flight and VTOL, and effectively overcomes a problem of controlling abrupt changes when the horizontal flight mode and
VTOL mode are converted to each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| AU2021106880A AU2021106880A4 (en) | 2021-08-24 | 2021-08-24 | Aircraft and method for achieving vertical take-off and landing and horizontal flight by segmented tilting bottom-driven plate wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| AU2021106880A AU2021106880A4 (en) | 2021-08-24 | 2021-08-24 | Aircraft and method for achieving vertical take-off and landing and horizontal flight by segmented tilting bottom-driven plate wings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| AU2021106880A4 true AU2021106880A4 (en) | 2021-11-25 |
Family
ID=78610649
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| AU2021106880A Ceased AU2021106880A4 (en) | 2021-08-24 | 2021-08-24 | Aircraft and method for achieving vertical take-off and landing and horizontal flight by segmented tilting bottom-driven plate wings |
Country Status (1)
| Country | Link |
|---|---|
| AU (1) | AU2021106880A4 (en) |
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2021
- 2021-08-24 AU AU2021106880A patent/AU2021106880A4/en not_active Ceased
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