CN105775117B - A kind of helicopter of VTOL horizontal flight and its application - Google Patents
A kind of helicopter of VTOL horizontal flight and its application Download PDFInfo
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- CN105775117B CN105775117B CN201610245385.7A CN201610245385A CN105775117B CN 105775117 B CN105775117 B CN 105775117B CN 201610245385 A CN201610245385 A CN 201610245385A CN 105775117 B CN105775117 B CN 105775117B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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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
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Abstract
The invention discloses a kind of helicopter of VTOL horizontal flight and its application, helicopter includes fuselage, rotor mechanism, wing structure, landing gear, power mechanism, operating mechanism, transmission mechanism；Fuselage includes head, waist and tail, and rotor mechanism includes dual rotary rotor mechanism, and fuselage file arranges rotatable bispin wing mechanism, and waist two sides may be provided with multiple groups wing structure, and multiple groups wing structure is arranged vertically waist；By designing dual rotary rotor mechanism and rotatable bispin wing mechanism simultaneously, take into account VTOL and quick horizontal flight, rotor mechanism is separately mounted to the head and tail portion of helicopter hull, and front and back rotation can be done around fuselage central axis, it is 5-6 times bigger than existing helicopter voyage, ensure that flight safety reduces production and operation cost, it can be applied in various aircrafts, it can be achieved that helicopter voyage is remote, flying speed is fast, safety coefficient is high, the easy many significant technical effects outstanding of manipulation.
Description
Technical field
The invention belongs to the technical fields of Flight Vehicle Design, and more specifically, the present invention relates to one kind can rapid vertical landing
Can high-speed horizontal flight helicopter technical field.
Background technique
At present the helicopter that at home and abroad uses generally there are two types of, the first: be set right above fuselage one it is flat
Row big propeller is responsible for aircraft rising and flight forward, while the responsible control aircraft left side an of lateral rotation is set behind fuselage
The small propeller of right heading；Be for second above helicopter before set a propeller, behind set a spiral
Paddle, the shortcoming of both aircrafts is the floating force and support force for not utilizing air adequately, so flying speed is slow, consumption
Oil mass is big.And the helicopter used in military affairs do not require nothing more than helicopter can rapid vertical landing, and require in level
Also certain speed is able to maintain when flight.The distribution engine of usual helicopter be multiple engines are transversely arranged, this
The overall front face area of aircraft can be expanded, resistance increases；Furthermore if one side power failure, also by the balance to helicopter
It adversely affects.
Do335 arrow formula fighter plane is a kind of " pulling in front and others push behind " driving aircraft in the prior art, its main feature is that two are sent out
Longitudinally configuration is on body central axes for motivation, while aircraft holding monomotor lesser whole front face area, but also with
Bimotored strong impetus.Its maneuvering performance, mobility, especially acceleration and gyroscopic characteristics be all it is very outstanding, by
It is fixed wing aircraft in Do335, needs longer takeoff and landing airstrips, do not have the energy of VTOL or short take-off and landing
Power, and because of the end of World War II and the appearance of jet plane, early have dropped out the arena of history of aircraft.
For the power performance and transport capacity for increasing helicopter, column dual rotors are laid out helicopter CH-46 sea knight
Transport helicopter comes into being, its main feature is that respectively having a rotor system before and after helicopter, to enhance transport capacity, and suitable
Ying Xingqiang.It can be compared with flying under harsh weather, naval then transports on warship or executes search and rescue aid equipment with this helicopter
Task.CH-46 is the double paddles of tandem, can with VTOL or short take-off and landing, hovering, flexibly and easily, battlefield survival and
Transport capacity is strong, and because of its voyage is limited, type is waited for a long time very much other disadvantages, on August 1st, 2015, U. S. Marine Corps 774 is medium-sized
Helicopter squadron carries out last farewell flight, and CH46 retires from active service from USN from this, gradually by osprey V-22 series
Replace.
V-22 " osprey " tilt rotor aircraft in the existing U.S., its main feature is that engine and screw blade be symmetrically mounted on it is winged
The tip of machine two sides wing, and can be rotated around wing, to realize vertical lift and horizontal flight.In contrast, it verts rotation
Wing aircraft have both conventional helicopters and with propeller (rotor) drive into fixed wing aircraft the advantages of, superior performance.But it verts
Gyroplane has born major defect, and the engine of tilt rotor aircraft is placed in the wing tip of fixed-wing, make fixed-wing become by
The severe cantilever beam of power, this be cause to stablize the major reason of hidden danger, meanwhile, this screw blade is symmetrically mounted on aircraft two
Side, the gravity and gravitation point for forming tilting rotor are arranged vertically with fuselage, will also result in the vertical liter of aircraft from amechanical angle
Many technological deficiencies and the security risk such as drop and horizontal flight and operational safety.
In above-mentioned three kinds of aircraft of the prior art, the electronic degree of V-22 " osprey " is too high, once failure nothing
Method is saved, and safety coefficient is lower, and when one group of screw blade damages, aircraft not can avoid crash accident, and there are civil nature difficulty
The problems such as larger.Therefore, it is necessary to carry out upgrading on the basis of existing helicopter, existing problem and shortage is overcome.
Summary of the invention
More difficult, the lower state of the art of safety coefficient is manipulated for objectively existing for helicopter both at home and abroad at present,
It, can be simultaneously by creative design the present invention intends to provide a kind of helicopter of VTOL horizontal flight and its application
Rapid vertical landing and high-speed horizontal flight are taken into account, rotor mechanism is separately positioned on to head and the tail of the helicopter hull longitudinal axis
Portion, and front and back rotation can be done around fuselage datum, it is 5-6 times bigger than existing helicopter voyage, it is ensured that flight safety reduces production
And operation cost, the helicopter have the characteristics that voyage is remote, manipulation is easy, safety coefficient is high, have for helicopter field
There are wide applicability and application value.
What the invention is realized by the following technical scheme:
The present invention provides a kind of helicopter of VTOL horizontal flight, including fuselage, rotor mechanism, wing structure,
Landing gear mechanism, power mechanism, operating mechanism, transmission mechanism；Fuselage includes head, waist and tail, rotor mechanism packet
Include dual rotary rotor mechanism, the longitudinal axis, that is, fuselage file arrangement controllable rotating bispin wing mechanism of helicopter.
The present invention is provided in above-mentioned helicopter, and dual rotary rotor mechanism includes preceding rotor rotational mechanism, rear rotor rotational
Mechanism, preceding rotor rotational mechanism include preceding rotor rotational mechanism, preceding powerplant module and preceding rotor, preceding powerplant module and preceding rotor by
Preceding rotor rotational mechanism controls realize the y direction heads of 90 degree to 0 degree helicopters towards controllable rotating；Rotor rotational afterwards
Mechanism includes rear powerplant module, rear rotor and rear rotor rotating mechanism, and rear powerplant module and rear rotor are by rear rotor rotating mechanism
Control realizes that 90 degree of reversed tails of the longitudinal axis to 180 degree helicopter are correspondingly arranged towards controllable rotating, preceding rotor and rear rotor
Propeller blade.
In the present invention, propeller blade is overlapped parallel rotating.
Meanwhile the present invention provides a kind of helicopter of VTOL horizontal flight, including fuselage, rotor mechanism, wing
Mechanism, landing gear mechanism, power mechanism, operating mechanism, transmission mechanism；Fuselage includes head, waist and tail, is gone straight up to winged
The longitudinal axis of machine, that is, waist two sides are provided with multiple groups wing structure, and multiple groups wing structure is arranged vertically waist, multiple groups rotation
Favourable turn wing mechanism is symmetrical set, controllable rotating.
In the present invention, the wing structure of waist two sides setting includes multiple groups rotor blade mechanism, is specifically included side by side
Arrange that two or more sets rotatable wings being symmetrical set, rotatable wing realize 0 degree to 90 degree of bilateral symmetry controllable rotation
Turn.
Further, the present invention provide it is a kind of can high velocity vertical landing horizontal flight helicopter, including fuselage, gyroplane
Structure, wing structure, landing gear mechanism, power mechanism, operating mechanism, transmission mechanism；Fuselage includes head, waist and machine
Tail, rotor mechanism include dual rotary rotor mechanism, and the longitudinal axis, that is, fuselage file of helicopter arranges rotatable bispin wing mechanism,
Waist two sides may be provided with multiple groups wing structure, and multiple groups wing structure is arranged vertically waist.
The present invention is provided in the helicopter of above-mentioned realization high velocity vertical landing horizontal flight, and machine is arranged in waist two sides
Wing mechanism, wing structure include multiple groups rotor blade mechanism, specifically include and are arranged side by side what two or more sets were symmetrical set
Rotatable wing, rotatable wing can realize 0 degree to 90 degree controllable rotating of bilateral symmetry；Before dual rotary rotor mechanism specifically includes
Rotor rotational mechanism, rear rotor rotating mechanism, preceding rotor rotational mechanism include preceding powerplant module, preceding rotor and preceding rotor rotational machine
Structure, preceding powerplant module and preceding rotor realize 90 degree to 0 degree heads towards controllable rotating by preceding rotor rotational mechanism controls；Rotor afterwards
Rotating mechanism includes rear powerplant module, rear rotor and rear rotor rotating mechanism, and rear powerplant module and rear rotor are by rear rotor rotational
Mechanism controls realize 90 degree to 180 degree tail towards controllable rotating；Preceding rotor and rear rotor are correspondingly arranged propeller blade.
In the present invention, the wing tip of every group of wing is connected by wing connecting mechanism；Wing include high lift device, leading edge slat,
Droope snoot, trailing edge flap and spoiler, rotor blade mechanism may include one group of aileron.
In the present invention, propeller blade realizes overlapping parallel rotating.
In the present invention, propeller blade is made of 2,3,4,5,6 or 8 leaves.
In the present invention, landing gear mechanism includes nose-gear and rear undercarriage.
In the present invention, body joint can be positioned below one group of nose-gear, undercarriage after tail has two groups.
The application that the present invention further provides the helicopters using above-mentioned offer in various helicopters is, it can be achieved that straight
Liter aircraft range is remote, flying speed is fast, safety coefficient is high, the easy many significant technical effects outstanding of manipulation.
In the present invention, setting multiple groups wing can increase upper surface of the airfoil boundary-layer energy, delay upper surface air-flow to separate, make
Helicopter adapts to the flight condition under different condition, achievees the purpose that quick landing；The main function that slat and wing flap crack
The air-flow of aerofoil surface is exactly delayed to separate, the effect of wing flap mainly increases wing camber and area.
In the present invention, rotatable bispin wing mechanism is mounted on the head of helicopter hull and the tail portion of fuselage,
While helicopter keeps monomotor lesser whole front face area, but also with bimotored strong impetus, so that directly
The horizontal flight power for rising aircraft is far longer than resistance, achievees the purpose that horizontal high-speed flight；Helicopter each section gravity
Point of resultant force, the referred to as center of gravity of helicopter；Position where gravity force, is position of centre of gravity；Pass through helicopter
Three of center of gravity are mutually perpendicular, reference axis on the basis of body, are axis, can be divided into the longitudinal axis, horizontal axis, vertical shaft；Along machine
Body axis, the axis by helicopter center of gravity are the longitudinal axis of helicopter；Pass through helicopter center of gravity along wing direction and hangs down
The axis of the straight longitudinal axis is the horizontal axis of helicopter；It is by helicopter center of gravity and winged to go straight up to perpendicular to the axis of the longitudinal axis and horizontal axis
The vertical uranium of machine；When helicopter flight, airflow function will generate operating torque to helicopter, make on helicopter
Rotated around horizontal axis, vertical shaft and the longitudinal axis, with change of flight posture, helicopter each section can with the movement of helicopter center of gravity and
It is mobile.
When using above-mentioned helicopter stable rising in the sky provided by the invention, effect by four power: lift
(L), gravity (W), pulling force (P), resistance (D), lift > gravity, one kind provided by the invention can high velocity vertical landing levels at this time
The helicopter of flight preceding rotor rotational mechanism, rear rotor rotating mechanism is arranged on the longitudinal axis of helicopter hull, multiple groups
Rotor blade mechanism is arranged on the horizontal axis of helicopter hull, and wing rotational angle is 0 degree, and current rotor turns to heading
Rotation in 90 degree dynamic, when back spin flapwise tail direction rotates rotation in 90 degree, power is all arranged in the vertical of helicopter hull
On axis, in take-off process, preceding rotor and rear rotor collective effect are in helicopter center of gravity, so that helicopter lift is much big
It is greater than resistance in helicopter gravity, pulling force, realizes that the rapid vertical of helicopter takes off.
When using above-mentioned helicopter horizontal flight in the sky provided by the invention, effect by four power: lift
(L), gravity (W), pulling force (P), resistance (D), thrust is greater than resistance at this time, and lift is equal to gravity；One kind provided by the invention can
The helicopter of high velocity vertical landing horizontal flight, multiple groups rotor blade mechanism realize bilateral symmetry 0-90 degree controllable rotating, when
When preceding rotor turns to 0 degree to heading, when back spin flapwise tail direction turns to 180 degree, power is all arranged in directly
On the longitudinal axis for rising airframe, so that helicopter thrust is far longer than helicopter resistance, change the flight speed of helicopter
Degree, realizes the high-speed horizontal flight of helicopter.
When using above-mentioned helicopter provided by the invention in level decline, effect by four power: lift (L),
Gravity (W), pulling force (P), resistance (D), thrust > resistance, lift < gravity, multiple groups rotor blade mechanism realize left and right pair at this time
Claim 0 degree to 90 degree controllable rotating, current rotor is to rotating in 90 degree of heading, when 90 degree interior turn of back spin flapwise tail direction
Dynamic, power is all arranged on the longitudinal axis of helicopter hull, and preceding rotor and rear rotor collective effect make in helicopter center of gravity
It obtains helicopter lift and is less than helicopter gravity, thrust greater than resistance, change the flying speed of helicopter, realization is gone straight up to winged
The rapid vertical of machine declines.
When using above-mentioned helicopter provided by the invention when taking off vertically, effect by two power: lift (L),
Gravity (W), at this time lift > gravity, the realization of multiple groups rotor blade mechanism are symmetrical set, controllable rotating, and current rotor is to machine
When head direction turns to 90 degree, when back spin flapwise tail direction turns to 90 degree, power is all arranged in helicopter hull
Vertical shaft on, preceding rotor and rear main rotor collective effect are gone straight up in helicopter center of gravity so that helicopter lift is far longer than
Aircraft gravity changes the flying height of helicopter, realizes that the rapid vertical of helicopter takes off.
When using above-mentioned helicopter provided by the invention in vertical landing, effect by two power: lift (L),
Gravity (W), at this time lift < gravity, multiple groups rotor blade mechanism realize bilateral symmetry 0-90 degree controllable rotating, current rotor to
When heading turns to 90 degree, when back spin flapwise tail direction turns to 90 degree, power is all arranged in helicopter machine
On the vertical shaft of body, preceding rotor and rear main rotor collective effect are in helicopter center of gravity, so that helicopter lift is far smaller than straight
Aircraft gravity is risen, changes the flying height of helicopter, realizes the vertical landing of helicopter.
Be applicable in one kind provided by the invention can high velocity vertical landing horizontal flight helicopter when, can be according to different
State of flight, controls rotor mechanism and wing structure realizes the rotation of different angle；Current rotor, rear rotor and helicopter are vertical
When axis is in equidirectional, i.e., when preceding rotor, rear rotor, multiple groups rotor blade mechanism are in 90 degree simultaneously, helicopter can be real
Show VTOL, control the flare maneuvers such as fly, turn-take on the spot.
Be applicable in one kind provided by the invention can high velocity vertical landing horizontal flight helicopter when, current rotor is by preceding
Rotor rotational mechanism controls rotate 90 degree, when rotor blade mechanism is rotated to 0 degree to heading, i.e., preceding rotor and helicopter
When the longitudinal axis is in opposite direction, helicopter can do low-medium speed horizontal flight.
Be applicable in one kind provided by the invention can high velocity vertical landing horizontal flight helicopter when, when after rotor by rear
Rotor rotational mechanism controls rotate 90 to 90 degree of tail direction rotation, preceding rotor from preceding rotor rotational mechanism controls to heading
When spending, i.e., when preceding rotor and rear rotor are in equidirectional with the helicopter longitudinal axis simultaneously, helicopter can do high speed and complete
Fast horizontal flight.
Using helicopter as provided above obtain it is following the utility model has the advantages that
(1) present invention provide it is a kind of can high velocity vertical landing horizontal flight helicopter, can by creative design
Rapid vertical landing and high-speed horizontal flight are combined, rotor mechanism is separately positioned on to the head of the helicopter hull longitudinal axis
And tail portion, and front and back rotation can be done around fuselage datum, it is 5-6 times bigger than existing helicopter voyage, it is ensured that flight safety reduces
Production and operation cost, the helicopter have the characteristics that voyage is remote, manipulation is easy, safety coefficient is high, helicopter are led
Domain has wide applicability and application value.
(2) present invention provide it is a kind of can the helicopter of high velocity vertical landing horizontal flight be that a kind of voyage is remote, flight speed
Degree is fast, safety coefficient is high, the easy dual-purpose helicopter of military and civilian of manipulation.
Detailed description of the invention
Fig. 1 is shown as helicopter main view provided by the invention.
Fig. 2 is shown as helicopter top view provided by the invention.
Fig. 3 is shown as helicopter schematic perspective view provided by the invention.
Fig. 4 is shown as helicopter flight state diagram one provided by the invention.
Fig. 5 is shown as helicopter flight state diagram two provided by the invention.
Fig. 6 is shown as helicopter flight state diagram three provided by the invention.
Fig. 7 is shown as helicopter flight state diagram four provided by the invention.
Fig. 8 is shown as helicopter flight state diagram five provided by the invention.
Fig. 9 is shown as helicopter flight state principle figure one provided by the invention.
Figure 10 is shown as helicopter flight state principle two provided by the invention.
Figure 11 is shown as helicopter flight state principle three provided by the invention.
Figure 12 is shown as helicopter flight state principle four provided by the invention.
Figure 13 is shown as helicopter flight state principle five provided by the invention.
In Fig. 1-13: rotor rotational after rotor, 5- before powerplant module, 4- before rotor rotational mechanism, 3- before 1- fuselage, 2-
Rotor after powerplant module, 7- after mechanism, 6-, 8- rotor blade mechanism, 9- wing connecting mechanism, 10- aileron, 11- nose-gear,
Undercarriage after 12-.
Specific embodiment
In conjunction with attached drawing 1-13, illustrate that still, the present invention is not limited to following embodiments for embodiment.
In the present invention, for ease of description, by it is a kind of can each portion in the helicopter of high velocity vertical landing horizontal flight
The description of the relative positional relationship of part is with reference to the accompanying drawings 1 Butut mode to be described, such as: containing upper and lower, left and right, 0
Degree, 90 degree, the positional relationships such as 180 degree, the description foundation Figure of description 1 such as rotation angle Butut direction determine.
Referring to attached drawing 1, in helicopter provided by the invention, it is with the axis for passing through the center of gravity of airplane along fuselage axis direction
The longitudinal axis, using along wing direction by the center of gravity of airplane and the axis of vertical axes is horizontal axis；Preceding rotor rotational mechanism is turned to along the longitudinal axis
It is set as 0 degree in the same direction with head, preceding rotor rotational mechanism is turned to along the longitudinal axis is set as 90 degree with head vertical direction, and rear rotor turns
Motivation structure is turned to along the longitudinal axis is set as 90 degree with tail vertical direction, and rear rotor rotating mechanism is turned to along the longitudinal axis and set in the same direction with tail
It is set to 180 degree.
Embodiment one:
Referring to attached drawing 1,2, the present invention provides a kind of helicopter of VTOL horizontal flight, including fuselage (1), rotor
Mechanism, wing structure, landing gear mechanism, power mechanism, operating mechanism, transmission mechanism；Fuselage (1) includes head, in fuselage (1)
Portion and tail, rotor mechanism include dual rotary rotor mechanism, the longitudinal axis, that is, fuselage (1) file arrangement controllable rotating of helicopter
Bispin wing mechanism.
The present invention is provided in the helicopter of VTOL horizontal flight, and dual rotary rotor mechanism includes preceding rotor rotational machine
Structure (2), rear rotor rotating mechanism (5), preceding rotor rotational mechanism (2) include preceding powerplant module (3), preceding rotor (4) and preceding rotor
Rotating mechanism (2), preceding powerplant module (3) and preceding rotor (4) are controlled by preceding rotor rotational mechanism (2) and realize head towards controllable rotation
Turn；Rotor rotating mechanism (5) includes rear powerplant module (6), rear rotor (7) and rear rotor rotating mechanism (5), rear powerplant module afterwards
(6) being controlled with rear rotor (7) by rear rotor rotating mechanism (5) realizes tail towards controllable rotating；Preceding rotor (4) and rear rotor
(7) it is correspondingly arranged propeller blade.
In the present invention, preceding powerplant module (3) and preceding rotor (4) are controlled by preceding rotor rotational mechanism (2) and preferentially realize 90 degree
To the y direction head of 0 degree of helicopter towards controllable rotating.
In the present invention, rear powerplant module (6) and rear rotor (7) are controlled by rear rotor rotating mechanism (5) and preferentially realize 90 degree
To the y direction tail of 180 degree helicopter towards controllable rotating.
In the present invention, propeller blade is overlapped parallel rotating.
In the present invention, propeller blade is made of 2,3,4,5,6 or 8 leaves.
In the present invention, landing gear mechanism includes nose-gear (11) and rear undercarriage (12).
In the present invention, fuselage (1) head has one group of nose-gear (11), undercarriage after tail has two groups
(12)。
Embodiment two:
Referring to attached drawing 3,4, the present invention provides a kind of helicopter of VTOL horizontal flight, including fuselage (1), rotor
Mechanism, wing structure, landing gear mechanism, power mechanism, operating mechanism, transmission mechanism；Fuselage (1) includes head, in fuselage (1)
Portion and tail, fuselage (1) on both sides of the middle may be provided with multiple groups wing structure, and multiple groups wing structure is arranged vertically the longitudinal axis of aircraft i.e.
In the middle part of fuselage (1), multiple groups rotor blade mechanism (8) is symmetrical set, controllable rotating.
The present invention is provided in the helicopter of VTOL horizontal flight, and fuselage (1) on both sides of the middle is provided with wing structure,
Wing structure includes multiple groups rotor blade mechanism (8), specifically includes revolving of being arranged side by side that two or more sets are symmetrical set
The favourable turn wing；The wing tip of every group of wing is connected by wing connecting mechanism (9).
The present invention is provided in the helicopter of VTOL horizontal flight, preferentially realizes 0 degree to 90 using rotatable wing
Spend controllable rotating.
In the present invention, wing includes high lift device, leading edge slat, droope snoot, trailing edge flap and spoiler.
In the present invention, rotor blade mechanism (8) includes one group of aileron (10).
In the present invention, landing gear mechanism includes nose-gear (11) and rear undercarriage (12).
In the present invention, fuselage (1) head has one group of nose-gear (11), undercarriage after tail has two groups
(12)。
Embodiment three:
Referring to attached drawing 1,2,3,4, the present invention provides a kind of helicopter of VTOL horizontal flight, including fuselage (1),
Rotor mechanism, wing structure, landing gear mechanism, power mechanism, operating mechanism, transmission mechanism；Fuselage (1) includes head, fuselage
(1) middle part and tail, rotor mechanism include dual rotary rotor mechanism, and the longitudinal axis, that is, fuselage (1) file arrangement of helicopter can revolve
The bispin wing mechanism turned, fuselage (1) on both sides of the middle may be provided with multiple groups wing structure, multiple groups wing structure be arranged vertically go straight up to it is winged
In the middle part of the longitudinal axis, that is, fuselage (1) of machine.
The present invention is provided in the helicopter of VTOL horizontal flight, and fuselage (1) on both sides of the middle is provided with wing structure,
Wing structure includes multiple groups rotor blade mechanism (8), specifically includes revolving of being arranged side by side that two or more sets are symmetrical set
The favourable turn wing, rotatable wing can realize 0 degree to 90 degree controllable rotating of bilateral symmetry；The wing tip of every group of wing is by wing connecting mechanism
(9) it connects.
The present invention is provided in the helicopter of VTOL horizontal flight, and dual rotary rotor mechanism includes preceding rotor rotational machine
Structure (2), rear rotor rotating mechanism (5), preceding rotor rotational mechanism (2) include preceding powerplant module (3), preceding rotor (4) and preceding rotor
Rotating mechanism (2), preceding powerplant module (3) and preceding rotor (4) are controlled by preceding rotor rotational mechanism (2) and realize 90 degree to 0 degree heads
Towards controllable rotating；Rotor rotating mechanism (5) includes rear powerplant module (6), rear rotor (7) and rear rotor rotating mechanism (5) afterwards,
Powerplant module (6) realizes that 90 degree revolve to 180 degree tail towards controllable by the control of rear rotor rotating mechanism (5) with rear rotor (7) afterwards
Turn；Preceding rotor (4) and rear rotor (7) are correspondingly arranged propeller blade.
In the present invention, wing includes high lift device, is made of leading edge slat, droope snoot, trailing edge flap and spoiler, rotation
Favourable turn wing mechanism (8) includes one group of aileron (10).
In the present invention, propeller blade is overlapped parallel rotating.
In the present invention, propeller blade is made of 2,3,4,5,6 or 8 leaves.
In the present invention, landing gear mechanism includes nose-gear (11) and rear undercarriage (12).
In the present invention, fuselage (1) head has one group of nose-gear (11), undercarriage after tail has two groups
(12)。
Example IV:
Referring to attached drawing 9 to attached drawing 13, the point of resultant force of helicopter each section gravity, the referred to as center of gravity of helicopter；
Position where gravity force, is position of centre of gravity；By three of helicopter center of gravity it is mutually perpendicular, using body as base
Quasi- reference axis, is axis, can be divided into the longitudinal axis, horizontal axis, vertical shaft；Along fuselage (1) axis, pass through the axis of helicopter center of gravity
For the longitudinal axis of helicopter；Along wing direction by helicopter center of gravity and the axis of vertical axes is the horizontal axis of helicopter；
It is the vertical uranium of helicopter by helicopter center of gravity and perpendicular to the axis of the longitudinal axis and horizontal axis；When helicopter flight, gas
Stream acts on helicopter, will generate operating torque to helicopter, be allowed to rotate around horizontal axis, vertical shaft and the longitudinal axis, to change
Become flight attitude, helicopter each section can be moved with the movement of center of gravity.
In the present invention, setting multiple groups wing can increase upper surface of the airfoil boundary-layer energy, delay upper surface air-flow to separate, make
Helicopter adapts to the flight condition under different condition, achievees the purpose that quick landing；The main function that slat and wing flap crack
The air-flow of aerofoil surface is exactly delayed to separate, the effect of wing flap mainly increases wing camber and area.
In the present invention, rotatable bispin wing mechanism is mounted on the helicopter longitudinal axis, the i.e. head of fuselage (1) and fuselage
Tail portion, while helicopter keeps monomotor lesser whole front face area, but also with bimotored powerful dynamic
Power achievees the purpose that horizontal high-speed flight so that the horizontal flight power of helicopter is far longer than resistance.
The present invention provides a kind of helicopter of VTOL horizontal flight, can be combined fastly by creative design
Rotor mechanism is separately positioned on the head and tail portion of helicopter hull (1) longitudinal axis by fast VTOL and high-speed horizontal flight,
And front and back rotation can be done around fuselage (1) longitudinal axis, it is 5-6 times bigger than existing helicopter voyage, it is ensured that flight safety reduces production
And operation cost, the helicopter have the characteristics that voyage is remote, manipulation is easy, safety coefficient is high, have for helicopter field
There are wide applicability and application value.
Embodiment five:
It, can be according to different flight shapes when using a kind of helicopter of VTOL horizontal flight provided by the invention
State, controls rotor mechanism and wing structure realizes the rotation of different angle；Current rotor (4), rear rotor (7) and helicopter are vertical
When axis is in equidirectional, i.e., when preceding rotor (4), rear rotor (7), multiple groups rotor blade mechanism (8) are in 90 degree simultaneously, go straight up to winged
The flare maneuvers such as VTOL may be implemented in machine, left and right flies, turn-takes on the spot, referring to attached drawing 4, attached drawing 5.
When being applicable in a kind of helicopter of VTOL horizontal flight provided by the invention, current rotor (4) You Qianxuan
Wing rotating mechanism (2) controls when turning to 0 degree to heading, when after rotor (7) controlled to machine from rear rotor rotating mechanism (5)
When tail direction turns to 90 degree, when rotor blade mechanism (8) rotation is to 0 degree, i.e., before rotor (4) and the helicopter longitudinal axis be in same
When direction, helicopter can do low-medium speed horizontal flight, referring to attached drawing 6.
When being applicable in a kind of helicopter of VTOL horizontal flight provided by the invention, when after rotor (7) by back spin
Wing rotating mechanism (5), which is controlled, to be turned to 180 degree, preceding rotor (4) to tail direction and is controlled from preceding rotor rotational mechanism (2) to head
When direction turns to 0 degree, i.e., when preceding rotor shaft and rear rotor shaft are in equidirectional with the helicopter longitudinal axis simultaneously, rotor blade machine
When structure (8) rotates, helicopter can do high speed and full speed horizontal flight, referring to attached drawing 7, attached drawing 8.
Embodiment six:
When helicopter flight, airflow function will generate operating torque to helicopter, be allowed on helicopter
It is rotated around horizontal axis, vertical shaft and the longitudinal axis, with change of flight posture, helicopter each section can be moved with the movement of the center of gravity of airplane.
1. helicopter provided by the invention quickly, high-speed flight when:
When helicopter in the sky quickly, high-speed flight when, effect by four power: lift (L), gravity (W), pulling force
(P), resistance (D), lift > gravity at this time, helicopter provided by the invention is by preceding rotor rotational mechanism (2), rear rotor rotational
Mechanism (5) is arranged on the longitudinal axis of helicopter hull (1), and multiple groups rotor blade mechanism is arranged in helicopter hull (1)
On horizontal axis, wing rotational angle is 0 degree, current rotor (4) to rotating in 90 degree of heading rotation, when after rotor (7) to machine
Tail direction rotates rotation in 90 degree, and power is all arranged on the longitudinal axis of helicopter hull (1), in take-off process, preceding rotation
The wing (4) and rear rotor (7) collective effect are in the center of gravity of airplane, so that helicopter lift is far longer than aircraft gravity, pulling force is greater than
Resistance realizes quick, the high-speed flight of helicopter, and state of flight is referring to attached drawing 9.
2. when helicopter provided by the invention horizontal flight in the sky:
When helicopter horizontal flight in the sky, effect by four power: lift (L), gravity (W), pulling force (P),
Resistance (D), thrust is greater than resistance at this time, and lift is equal to gravity；The multiple groups rotor blade mechanism of helicopter provided by the invention
(8) realize bilateral symmetry 0-90 degree controllable rotating, when current rotor (4) turns to 0 degree to heading, when after rotor (7) to
When tail direction turns to 180 degree, power is all arranged on the longitudinal axis of helicopter hull (1), so that aircraft thrust is much
Greater than aircraft drag, change the flying speed of helicopter, realizes the high-speed horizontal flight of helicopter, state of flight is referring to attached
Figure 10.
3. helicopter level provided by the invention declines:
When helicopter is in level decline, effect by four power: lift (L), gravity (W), pulling force (P), resistance
(D), thrust > resistance, lift < gravity, multiple groups rotor blade mechanism (8) realize 0 degree to 90 degree of bilateral symmetry controllable rotation at this time
Turn, current rotor (4) to rotating in 90 degree of heading, when after rotor (7) rotated into 90 degree of tail direction, power whole cloth
It sets on the longitudinal axis of helicopter hull (1), preceding rotor (4) and rear rotor (7) collective effect are in helicopter center of gravity, so that directly
It rises airplane ascensional force and is less than helicopter gravity, thrust greater than resistance, change the flying speed of helicopter, realize helicopter
Level decline, state of flight is referring to attached drawing 11.
4. helicopter provided by the invention takes off vertically:
When helicopter is when taking off vertically, the effect by two power: lift (L), gravity (W), lift > is heavy at this time
Power, multiple groups rotor blade mechanism (8) realization are symmetrical set, and controllable rotating, current rotor (4) turns to 90 to heading
When spending, when rear rotor (7) turns to 90 degree to tail direction, power is all arranged on the vertical shaft of helicopter hull (1),
Preceding rotor (4) and rear main rotor (7) collective effect are in helicopter center of gravity, so that helicopter lift is far longer than helicopter
Gravity changes the flying height of helicopter, realizes that the rapid vertical of helicopter takes off, state of flight is referring to attached drawing 12.
5. when helicopter vertical landing provided by the invention:
When helicopter is in vertical landing, the effect by two power: lift (L), gravity (W), lift < is heavy at this time
Power, multiple groups rotor blade mechanism (8) realize 0 degree to 90 degree controllable rotating of bilateral symmetry, and current rotor (4) rotates to heading
When to 90 degree, when rear rotor (7) turns to 90 degree to tail direction, power is all arranged in the vertical of helicopter hull (1)
On axis, preceding rotor (4) and rear main rotor (7) collective effect are in helicopter center of gravity, so that helicopter lift is far smaller than straight
Aircraft gravity is risen, changes the flying height of helicopter, realizes the vertical landing of helicopter, state of flight is referring to attached drawing 13.
The helicopter that the present invention provides a kind of VTOL horizontal flight is that a kind of voyage is remote, flying speed is fast, safety
Coefficient is high, manipulates the easy dual-purpose helicopter of military and civilian.
As described above, the present invention can be realized preferably, the above embodiments are only to preferred implementation side of the invention
Formula is described, and is not intended to limit the scope of the present invention, and without departing from the spirit of the design of the present invention, this field is general
The various changes and improvements that logical technical staff makes technical solution of the present invention, should all fall into present invention determine that protection scope
It is interior.
Claims (3)
1. a kind of helicopter of VTOL horizontal flight, including it is fuselage, rotor mechanism, wing structure, landing gear, dynamic
Force mechanisms, operating mechanism, transmission mechanism, fuselage include head, waist and tail, which is characterized in that rotor mechanism includes
Dual rotary rotor mechanism, fuselage file arrange dual rotary rotor mechanism；Waist two sides are provided with wing structure, wing structure
Including multiple groups rotor blade mechanism, multiple groups rotor blade mechanism is arranged vertically waist, specifically include be arranged side by side two groups or
The rotatable wing that multiple groups are symmetrical set, 0 degree to 90 degree controllable rotating of rotatable wing bilateral symmetry；Dual rotary gyroplane
Structure specifically includes preceding rotor mechanism, rear rotor mechanism, and preceding rotor mechanism includes preceding powerplant module, preceding rotor and preceding rotor rotational machine
Structure, preceding powerplant module and preceding rotor realize 90 degree to 0 degree heads towards controllable rotating by preceding rotor rotational mechanism controls；Rotor afterwards
Mechanism includes rear powerplant module, rear rotor and rear rotor rotating mechanism, and rear powerplant module and rear rotor are by rear rotor rotating mechanism
Control realizes 90 degree and is correspondingly arranged propeller blade to 180 degree tail towards controllable rotating, preceding rotor and rear rotor；Described can
In rotor blade, the wing tip of the every side each group wing of fuselage connects into a big wing structure, wing packet by wing connecting mechanism
Include high lift device, leading edge slat, droope snoot, trailing edge flap and spoiler.
2. the helicopter of VTOL horizontal flight as described in claim 1, which is characterized in that the rotor mechanism
In, propeller blade is made of 2,3,4,5,6 or 8 leaves.
3. the helicopter of VTOL horizontal flight as described in claim 1, which is characterized in that the rotor mechanism
In, propeller blade is overlapped parallel rotating.
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| CN106585975A (en) * | 2017-01-22 | 2017-04-26 | 云南集优科技有限公司 | Compact unmanned aerial vehicle |
| CN108100247A (en) * | 2018-01-29 | 2018-06-01 | 中国空气动力研究与发展中心高速空气动力研究所 | One kind can the long endurance unmanned vehicle layout of folding and unfolding VTOL |
| US11008093B2 (en) * | 2018-03-22 | 2021-05-18 | Aurora Flight Sciences Corporation | Systems and methods for reducing the propeller noise |
| US20200223537A1 (en) * | 2019-01-16 | 2020-07-16 | Bell Textron Inc. | Tandem tiltrotor aircraft |
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| CN110371285B (en) * | 2019-07-19 | 2020-12-08 | 苏州高博软件技术职业学院 | Blade-rotatable horizontal lift four-wheel type rotor unmanned aerial vehicle |
| CN110282125B (en) * | 2019-07-19 | 2020-12-08 | 苏州高博软件技术职业学院 | Aircraft based on blade-rotatable vertical double-wheel type moving wing pushing |
| CN110254712B (en) * | 2019-07-19 | 2020-12-08 | 苏州高博软件技术职业学院 | Two-horizontal two-vertical blade-rotatable four-wheel type rotor unmanned aerial vehicle |
| CN110282124B (en) * | 2019-07-19 | 2020-12-08 | 苏州高博软件技术职业学院 | Blade-rotatable horizontal four-wheel type moving-wing aircraft combined with fixed wings |
| CN110254705B (en) * | 2019-07-19 | 2020-12-08 | 苏州高博软件技术职业学院 | Single-wheel type moving-wing aircraft with rotatable and horizontal blades and fixed wings |
| WO2021155532A1 (en) * | 2020-02-06 | 2021-08-12 | XDynamics Limited | An unmanned aerial vehicle |
| CN112429197A (en) * | 2020-11-26 | 2021-03-02 | 广东国士健科技发展有限公司 | Flat flapping wing low-altitude aircraft |
| US11987350B2 (en) | 2021-06-03 | 2024-05-21 | Textron Innovations Inc. | Winged tiltrotor aircraft |
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