CN105775117A - Helicopter taking off and landing vertically and flying horizontally and application thereof - Google Patents
Helicopter taking off and landing vertically and flying horizontally and application thereof Download PDFInfo
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- CN105775117A CN105775117A CN201610245385.7A CN201610245385A CN105775117A CN 105775117 A CN105775117 A CN 105775117A CN 201610245385 A CN201610245385 A CN 201610245385A CN 105775117 A CN105775117 A CN 105775117A
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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 helicopter taking off and landing vertically and flying horizontally and application thereof. The helicopter comprises a fuselage, rotor mechanisms, wing mechanisms, an undercarriage device, a power mechanism, a control mechanism and a transmission mechanism. The fuselage comprises a nose, a fuselage middle part and a tail. The rotor mechanisms comprise double rotating rotor mechanisms. Rotary double-rotor mechanisms are longitudinally arranged on the fuselage. The multiple wing mechanisms are perpendicularly arranged on the two sides of the fuselage middle part. As both the double rotating rotor mechanisms and the rotary double-rotor mechanisms are designed, both vertical taking-off and landing and rapid horizontal flying are achieved; as the rotor mechanisms are installed on the nose and the tail of the fuselage of the helicopter respectively and can rotate front and back around the center axis of the fuselage, the range of the helicopter is 5-6 times larger than that of an existing helicopter, flight safety is ensured, production and operation cost is reduced, the design can be applied to various aircrafts, and the significant technical effects of a large range, a high flight speed, a high safety coefficient and control easiness of the helicopter can be achieved.
Description
Technical field
The invention belongs to the technical field of Flight Vehicle Design, more specifically, the present invention relates to a kind of can rapid vertical landing can the technical field of helicopter of high-speed horizontal flight.
Background technology
The helicopter at home and abroad used at present generally has two kinds, the first: it is directly over fuselage, to set a parallel king bolt oar be responsible for aircraft rising and flight forward, after fuselage, sets the minor spiral oar of the responsible control aircraft left and right heading of a lateral rotation simultaneously；The second be above helicopter before set a propeller, after set a propeller, the weak point of both aircrafts is the most sufficiently to utilize floating force and the support force of air, so flight speed is slow, fuel consumption is big.And the military upper helicopter used do not require nothing more than helicopter can rapid vertical landing, and require also to be able to keep certain speed when horizontal flight.Generally the distribution engine of helicopter is by transversely arranged for multiple electromotors, and this can expand the overall front face area of aircraft, and resistance increases；If one side power failure, also will adversely affect the balance of helicopter in addition.
In prior art, Do335 arrow formula fighter plane is a kind of " pulling in front and others push behind " driving aircraft, it is characterized in two electromotors to be longitudinally arranged on body axis, while aircraft keeps the overall front face area that monomotor is less, possesses again bimotored strong impetus.Its maneuvering performance, mobility, especially acceleration and gyroscopic characteristics is all the most outstanding, owing to Do335 is fixed wing airplane, need longer takeoff and landing airstrips, do not possesses the ability of VTOL or STOL, again because the end of World War II and the appearance of jet plane, early have dropped out the arena of history of aircraft.
For increasing power performance and the transport capacity of helicopter, column dual rotors layout helicopter CH-46 sea knight's transport helicopter arises at the historic moment, and is characterized in before and after helicopter being respectively arranged with a rotor system, thus strengthens transport capacity, and strong adaptability.Can fly under relatively harsh weather, naval then transports to equipment on warship with this helicopter or performs search and rescue aid task.CH-46 is the double oar of tandem, can be with VTOL or STOL, hovering, flexibly and easily, battlefield survival and transport capacity are strong, because its voyage is limited, type waits for a long time very much other shortcoming, on August 1st, 2015, Medium Helicopter squadron of U. S. Marine Corps 774 carries out last farewell flight, and CH46 retires from active service from USN from this, is gradually replaced by osprey V-22 series.
V-22 " osprey " tilt rotor aircraft of the existing U.S., is characterized in that electromotor and propeller blade are symmetrically mounted on the tip of aircraft both sides wing, it is possible to rotate around wing, thus realizes vertical lift and horizontal flight.By contrast, tilt rotor aircraft have concurrently conventional helicopters and with propeller (rotor) drive into the advantage of fixed wing airplane, superior performance.But, tilt rotor aircraft has born major defect, the electromotor of tilt rotor aircraft is placed in the wing tip of fixed-wing, fixed-wing is made to become the cantilever that stress is severe, this is the major reason causing stable hidden danger, and meanwhile, this propeller blade is symmetrically mounted on aircraft both sides, the gravity and the gravitation point that form tilting rotor are arranged vertically with fuselage, will also result in vertical lift and the horizontal flight of aircraft from amechanical angle and run many technological deficiencies and the potential safety hazards such as safety.
In above-mentioned three kinds of aircraft of prior art, the electronic degree of V-22 " osprey " is the highest, once breaks down and cannot save, and safety coefficient is relatively low, and when one group of propeller blade damages, aircraft cannot be avoided crash accident, there is the problems such as civil nature difficulty is bigger.Accordingly, it would be desirable to carry out upgrading on the basis of existing helicopter, overcome existing problem and shortage.
Summary of the invention
More difficult for objectively there is manipulation the most both at home and abroad for helicopter, the state of the art that safety coefficient is relatively low, it is contemplated that in the helicopter and the application thereof that provide a kind of VTOL horizontal flight, rapid vertical landing and high-speed horizontal flight can be taken into account by creative design simultaneously, rotor mechanism is separately positioned on head and the afterbody of the helicopter hull longitudinal axis, and can do around fuselage datum and front and back rotate, big 5-6 times of existing helicopter voyage of ratio, guarantee that flight safety reduces to produce and operation cost, it is remote that this helicopter has voyage, manipulation is easily, the feature that safety coefficient is high, for helicopter field, there is wide applicability and using value.
The present invention is achieved through the following technical solutions:
The present invention provides the helicopter of a kind of VTOL horizontal flight, including fuselage, rotor mechanism, wing structure, landing gear mechanism, actuating unit, operating mechanism, drive mechanism；Fuselage includes head, waist and tail, and rotor mechanism includes dual rotary rotor mechanism, and the i.e. fuselage file of the longitudinal axis of helicopter arranges the DCB Specimen mechanism of controllable rotating.
The present invention provides in above-mentioned helicopter, dual rotary rotor mechanism includes front rotor rotational mechanism, rear rotor rotational mechanism, front rotor rotational mechanism includes that front rotor rotational mechanism, front powerplant module and front rotor, front powerplant module and front rotor are realized 90 degree of y direction heads to 0 degree of helicopter towards controllable rotating by front rotor rotational mechanism controls；Rear rotor rotational mechanism includes rear powerplant module, rear rotor and rear rotor rotational mechanism, rear powerplant module and rear rotor are realized 90 degree of reverse tails of the longitudinal axis to 180 degree of helicopters towards controllable rotating by rear rotor rotational mechanism controls, and front rotor and rear rotor are correspondingly arranged propeller blade.
In the present invention, propeller blade overlap parallel rotating.
Meanwhile, the present invention provides the helicopter of a kind of VTOL horizontal flight, including fuselage, rotor mechanism, wing structure, landing gear mechanism, actuating unit, operating mechanism, drive mechanism；Fuselage includes head, waist and tail, and the longitudinal axis of helicopter i.e. waist both sides are provided with organizes wing structure more, and many group wing structure are arranged vertically waist, and Duo Zu rotor blade mechanism is symmetrical set, controllable rotating.
In the present invention, the wing structure that waist both sides are arranged includes Duo Zu rotor blade mechanism, specifically includes two or more sets rotatable wings being symmetrical set that are arranged side by side, and rotatable wing realizes symmetrical 0 degree to 90 degree controllable rotating.
Further, the present invention provide a kind of can the helicopter of high velocity vertical landing horizontal flight, including fuselage, rotor mechanism, wing structure, landing gear mechanism, actuating unit, operating mechanism, drive mechanism；Fuselage includes head, waist and tail, rotor mechanism includes dual rotary rotor mechanism, the i.e. fuselage file of the longitudinal axis of helicopter arranges rotatable DCB Specimen mechanism, and waist both sides can be provided with and organize wing structure more, and many group wing structure are arranged vertically waist.
The present invention provides in the above-mentioned helicopter realizing high velocity vertical landing horizontal flight, waist both sides arrange wing structure, wing structure includes Duo Zu rotor blade mechanism, specifically including two or more sets rotatable wings being symmetrical set that are arranged side by side, rotatable wing can realize symmetrical 0 degree to 90 degree controllable rotating；Dual rotary rotor mechanism specifically includes front rotor rotational mechanism, rear rotor rotational mechanism, front rotor rotational mechanism includes that front powerplant module, front rotor and front rotor rotational mechanism, front powerplant module and front rotor are realized 90 degree to 0 degree heads towards controllable rotating by front rotor rotational mechanism controls；Rear rotor rotational mechanism includes that rear powerplant module, rear rotor and rear rotor rotational mechanism, rear powerplant module and rear rotor are realized 90 degree to 180 degree tails towards controllable rotating by rear rotor rotational mechanism controls；Front rotor and rear rotor are correspondingly arranged propeller blade.
In the present invention, the wing tip often organizing wing is connected by wing connecting mechanism；Wing includes that high lift device, leading edge slat, droope snoot, trailing edge flap and spoiler, rotor blade mechanism can comprise one group of aileron.
In the present invention, propeller blade realizes overlapping parallel rotating.
In the present invention, propeller blade is made up 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, tail have two groups after undercarriage.
The present invention further provides the helicopter that above-mentioned offer is provided application in various helicopters, can realize that helicopter voyage is remote, flight speed is fast, safety coefficient is high, manipulate easy many notable prominent technique effects.
In the present invention, arranging many group wings can increase upper surface of the airfoil boundary-layer energy, delays upper surface air-flow to separate, makes helicopter adapt to the flight condition under different condition, reach the purpose of quick landing；The Main Function that slat cracks with wing flap is exactly that the air-flow delaying aerofoil surface separates, and the effect of wing flap mainly increases wing camber and area.
In the present invention, rotatable DCB Specimen mechanism is arranged on the head of helicopter hull and the afterbody of fuselage, while helicopter keeps the overall front face area that monomotor is less, possesses again bimotored strong impetus, the horizontal flight power making helicopter is far longer than resistance, the purpose of the high-speed flight that is up to the standard；The point of resultant force of helicopter each several part gravity, the referred to as center of gravity of helicopter；The position at place, action of gravity force, is position of centre of gravity；, coordinate axes by body on the basis of mutually perpendicular by three of helicopter center of gravity, is axis, can be divided into the longitudinal axis, transverse axis, vertical shaft；Along fuselage axis, by the longitudinal axis that axis is helicopter of helicopter center of gravity；Along wing direction by the transverse axis that axis is helicopter of helicopter center of gravity vertical axes；By helicopter center of gravity the vertical uranium that axis is helicopter that is perpendicular to the longitudinal axis and transverse axis；When helicopter flight, airflow function, on helicopter, will produce operating torque to helicopter, is allowed to rotate around transverse axis, vertical shaft and the longitudinal axis, and with change of flight attitude, helicopter each several part can move with the movement of helicopter center of gravity.
nullWhen the above-mentioned helicopter using the present invention to provide the most stably rises，Acted on by four power: lift (L)、Gravity (W)、Pulling force (P)、Resistance (D)，Now lift ＞ gravity，The present invention provide a kind of can the helicopter of high velocity vertical landing horizontal flight，By front rotor rotational mechanism、Rear rotor rotational mechanism is arranged on the longitudinal axis of helicopter hull，Duo Zu rotor blade mechanism is arranged on the transverse axis of helicopter hull，Wing rotational angle is 0 degree，Current rotor rotates in heading rotates 90 degree，After when, rotor rotates in tail direction rotates 90 degree，Power is all arranged on the longitudinal axis of helicopter hull，In take-off process，Front rotor and rear rotor act on helicopter center of gravity jointly，Helicopter lift is made to be far longer than helicopter gravity、Pulling force is more than resistance，The rapid vertical realizing helicopter takes off.
When the above-mentioned helicopter horizontal flight aloft using the present invention to provide, acted on by four power: lift (L), gravity (W), pulling force (P), resistance (D), now thrust is more than resistance, and lift is equal to gravity；The present invention provide a kind of can the helicopter of high velocity vertical landing horizontal flight, Duo Zu rotor blade mechanism realizes symmetrical 0-90 degree controllable rotating, current rotor is when heading turns to 0 degree, when rear rotor turns to 180 degree to tail direction, power is all arranged on the longitudinal axis of helicopter hull, make helicopter thrust be far longer than helicopter resistance, change the flight speed of helicopter, it is achieved the high-speed horizontal flight of helicopter.
When the above-mentioned helicopter using the present invention to provide declines in level, acted on by four power: lift (L), gravity (W), pulling force (P), resistance (D), now thrust ＞ resistance, lift ＜ gravity, Duo Zu rotor blade mechanism realizes symmetrical 0 degree to 90 degree controllable rotating, current rotor rotates in heading 90 degree, after when, rotor rotates in 90 degree of tail direction, power is all arranged on the longitudinal axis of helicopter hull, front rotor and rear rotor act on helicopter center of gravity jointly, make helicopter lift less than helicopter gravity, thrust is more than resistance, change the flight speed of helicopter, the rapid vertical realizing helicopter declines.
When the above-mentioned helicopter using the present invention to provide is when taking off vertically, acted on by two power: lift (L), gravity (W), now lift ＞ gravity, Duo Zu rotor blade mechanism realizes being symmetrical set, controllable rotating, current rotor is when heading turns to 90 degree, when rear rotor turns to 90 degree to tail direction, power is all arranged on the vertical shaft of helicopter hull, front rotor and rear main rotor act on helicopter center of gravity jointly, helicopter lift is made to be far longer than helicopter gravity, change the flying height of helicopter, the rapid vertical realizing helicopter takes off.
When the above-mentioned helicopter using the present invention to provide is in vertical landing, acted on by two power: lift (L), gravity (W), now lift ＜ gravity, Duo Zu rotor blade mechanism realizes symmetrical 0-90 degree controllable rotating, current rotor is when heading turns to 90 degree, when rear rotor turns to 90 degree to tail direction, power is all arranged on the vertical shaft of helicopter hull, front rotor and rear main rotor act on helicopter center of gravity jointly, helicopter lift is made to be far smaller than helicopter gravity, change the flying height of helicopter, realize the vertical landing of helicopter.
Be suitable for that the present invention provides a kind of can the helicopter of high velocity vertical landing horizontal flight time, can control rotor mechanism according to different state of flights and wing structure realize the rotation of different angles；When current rotor, rear rotor and helicopter vertical shaft are in equidirectional, when the most front rotor, rear rotor, Duo Zu rotor blade mechanism are concurrently residing in 90 degree, helicopter can realize VTOL, left and right flight, the flare maneuver such as turn-take on the spot.
Be suitable for that the present invention provides a kind of can the helicopter of high velocity vertical landing horizontal flight time, current rotor is rotated 90 degree by front rotor rotational mechanism controls to heading, when rotor blade mechanism rotates to 0 degree, when before i.e., rotor and the helicopter longitudinal axis are in opposite direction, helicopter can do low-medium speed horizontal flight.
Be suitable for that the present invention provides a kind of can the helicopter of high velocity vertical landing horizontal flight time, when rear rotor is rotated 90 degree by front rotor rotational mechanism controls to heading to tail direction rotation 90 degree, front rotor by rear rotor rotational mechanism controls, when the most front rotor and rear rotor are in equidirectional with the helicopter longitudinal axis simultaneously, helicopter can do high speed and horizontal flight at full speed.
Helicopter as provided above is used to obtain following beneficial effect:
(1) present invention provide a kind of can the helicopter of high velocity vertical landing horizontal flight, rapid vertical landing and high-speed horizontal flight can be taken into account by creative design simultaneously, rotor mechanism is separately positioned on head and the afterbody of the helicopter hull longitudinal axis, and can do around fuselage datum and front and back rotate, big 5-6 times of existing helicopter voyage of ratio, guarantee that flight safety reduces to produce and operation cost, this helicopter has the advantages that voyage is remote, manipulation is easy, safety coefficient is high, has wide applicability and using value for helicopter field.
(2) present invention provides a kind of can the helicopter of high velocity vertical landing horizontal flight be that a kind of voyage is remote, flight speed is fast, safety coefficient is high, manipulate the dual-purpose helicopter of easy military and civilian.
Accompanying drawing explanation
Fig. 1 is shown as the helicopter front view that the present invention provides.
Fig. 2 is shown as the helicopter top view that the present invention provides.
Fig. 3 is shown as the helicopter perspective view that the present invention provides.
Fig. 4 is shown as the helicopter flight state diagram one that the present invention provides.
Fig. 5 is shown as the helicopter flight state diagram two that the present invention provides.
Fig. 6 is shown as the helicopter flight state diagram three that the present invention provides.
Fig. 7 is shown as the helicopter flight state diagram four that the present invention provides.
Fig. 8 is shown as the helicopter flight state diagram five that the present invention provides.
Fig. 9 is shown as the helicopter flight state principle figure one that the present invention provides.
Figure 10 is shown as the helicopter flight state principle two that the present invention provides.
Figure 11 is shown as the helicopter flight state principle three that the present invention provides.
Figure 12 is shown as the helicopter flight state principle four that the present invention provides.
Figure 13 is shown as the helicopter flight state principle five that the present invention provides.
In Fig. 1-13: undercarriage after rotor after powerplant module, 7-after rotor rotational mechanism, 6-after rotor, 5-before powerplant module, 4-before rotor rotational mechanism, 3-before 1-fuselage, 2-, 8-rotor blade mechanism, 9-wing connecting mechanism, 10-aileron, 11-nose-gear, 12-.
Specific embodiment
In conjunction with accompanying drawing 1-13, illustrate for embodiment, but, the present invention is not limited to following embodiment.
In the present invention, for the ease of describing, by a kind of can in the helicopter of high velocity vertical landing horizontal flight the description of the relative position relation of each parts be with reference to the accompanying drawings 1 Butut mode be described, such as: containing upper and lower, left and right, 0 degree, 90 degree, position relationship, the anglecs of rotation etc. such as 180 degree describe and determine according to the Butut direction of Figure of description 1.
See accompanying drawing 1, in the helicopter that the present invention provides, with along fuselage axis direction by the axis of the center of gravity of airplane as the longitudinal axis, with along wing direction by the axis of the center of gravity of airplane vertical axes as transverse axis；Front rotor rotational mechanism turns to along the longitudinal axis and is set as 0 degree with head in the same direction, front rotor rotational mechanism turns to along the longitudinal axis and is set as 90 degree with head vertical direction, rear rotor rotational mechanism turns to along the longitudinal axis and is set as 90 degree with tail vertical direction, and rear rotor rotational mechanism turns to along the longitudinal axis and is set as 180 degree with tail in the same direction.
Embodiment one
:
Seeing accompanying drawing 1,2, the present invention provides the helicopter of a kind of VTOL horizontal flight, including fuselage (1), rotor mechanism, wing structure, landing gear mechanism, actuating unit, operating mechanism, drive mechanism；Fuselage (1) includes head, fuselage (1) middle part and tail, and rotor mechanism includes dual rotary rotor mechanism, and the longitudinal axis of helicopter i.e. fuselage (1) file arranges the DCB Specimen mechanism of controllable rotating.
The present invention provides in the helicopter of VTOL horizontal flight, dual rotary rotor mechanism includes front rotor rotational mechanism (2), rear rotor rotational mechanism (5), front rotor rotational mechanism (2) includes front powerplant module (3), front rotor (4) and front rotor rotational mechanism (2), front powerplant module (3) and front rotor (4) by front rotor rotational mechanism (2) control realization head towards controllable rotating；Rear rotor rotational mechanism (5) includes rear powerplant module (6), rear rotor (7) and rear rotor rotational mechanism (5), rear powerplant module (6) and rear rotor (7) by rear rotor rotational mechanism (5) control realization tail towards controllable rotating；Front rotor (4) and rear rotor (7) are correspondingly arranged propeller blade.
In the present invention, front powerplant module (3) is controlled preferentially to realize 90 degree of y direction heads to 0 degree of helicopter towards controllable rotating by front rotor rotational mechanism (2) with front rotor (4).
In the present invention, rear powerplant module (6) is controlled preferentially to realize 90 degree of y direction tails to 180 degree of helicopters towards controllable rotating by rear rotor rotational mechanism (5) with rear rotor (7).
In the present invention, propeller blade overlap parallel rotating.
In the present invention, propeller blade is made up 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), tail have two groups after undercarriage (12).
Embodiment two
:
Seeing accompanying drawing 3,4, the present invention provides the helicopter of a kind of VTOL horizontal flight, including fuselage (1), rotor mechanism, wing structure, landing gear mechanism, actuating unit, operating mechanism, drive mechanism；Fuselage (1) includes head, fuselage (1) middle part and tail, both sides, fuselage (1) middle part can be provided with organizes wing structure more, many group wing structure are arranged vertically the longitudinal axis i.e. fuselage (1) middle part of aircraft, and Duo Zu rotor blade mechanism (8) is symmetrical set, controllable rotating.
The present invention provides in the helicopter of VTOL horizontal flight, and both sides, fuselage (1) middle part are provided with wing structure, and wing structure includes Duo Zu rotor blade mechanism (8), specifically includes two or more sets rotatable wings being symmetrical set that are arranged side by side；The wing tip often organizing wing is connected by wing connecting mechanism (9).
The present invention provides in the helicopter of VTOL horizontal flight, and the rotatable wing of preferential employing realizes 0 degree to 90 degree 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) comprises 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), tail have two groups after undercarriage (12).
Embodiment three
:
Seeing accompanying drawing 1,2,3,4, the present invention provides the helicopter of a kind of VTOL horizontal flight, including fuselage (1), rotor mechanism, wing structure, landing gear mechanism, actuating unit, operating mechanism, drive mechanism；Fuselage (1) includes head, fuselage (1) middle part and tail, rotor mechanism includes dual rotary rotor mechanism, the longitudinal axis of helicopter i.e. fuselage (1) file arranges rotatable DCB Specimen mechanism, both sides, fuselage (1) middle part can be provided with organizes wing structure more, and many group wing structure are arranged vertically the longitudinal axis i.e. fuselage (1) middle part of helicopter.
The present invention provides in the helicopter of VTOL horizontal flight, both sides, fuselage (1) middle part are provided with wing structure, wing structure includes Duo Zu rotor blade mechanism (8), specifically including two or more sets rotatable wings being symmetrical set that are arranged side by side, rotatable wing can realize symmetrical 0 degree to 90 degree controllable rotating；The wing tip often organizing wing is connected by wing connecting mechanism (9).
The present invention provides in the helicopter of VTOL horizontal flight, dual rotary rotor mechanism includes front rotor rotational mechanism (2), rear rotor rotational mechanism (5), front rotor rotational mechanism (2) includes front powerplant module (3), front rotor (4) and front rotor rotational mechanism (2), front powerplant module (3) and front rotor (4) by front 90 degree to 0 degree heads of rotor rotational mechanism (2) control realization towards controllable rotating；Rear rotor rotational mechanism (5) includes rear powerplant module (6), rear rotor (7) and rear rotor rotational mechanism (5), rear powerplant module (6) and rear rotor (7) by rear 90 degree to 180 degree tails of rotor rotational mechanism (5) control realization towards controllable rotating；Front rotor (4) and rear rotor (7) are correspondingly arranged propeller blade.
In the present invention, wing includes high lift device, is made up of leading edge slat, droope snoot, trailing edge flap and spoiler, and rotor blade mechanism (8) comprises one group of aileron (10).
In the present invention, propeller blade overlap parallel rotating.
In the present invention, propeller blade is made up 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), tail have two groups after undercarriage (12).
Embodiment four
:
See accompanying drawing 9 to accompanying drawing 13, the point of resultant force of helicopter each several part gravity, the referred to as center of gravity of helicopter；The position at place, action of gravity force, is position of centre of gravity；, coordinate axes by body on the basis of mutually perpendicular by three of helicopter center of gravity, is axis, can be divided into the longitudinal axis, transverse axis, vertical shaft；Along fuselage (1) axis, by the longitudinal axis that axis is helicopter of helicopter center of gravity；Along wing direction by the transverse axis that axis is helicopter of helicopter center of gravity vertical axes；By helicopter center of gravity the vertical uranium that axis is helicopter that is perpendicular to the longitudinal axis and transverse axis；When helicopter flight, airflow function, on helicopter, will produce operating torque to helicopter, is allowed to rotate around transverse axis, vertical shaft and the longitudinal axis, and with change of flight attitude, helicopter each several part can move with the movement of center of gravity.
In the present invention, arranging many group wings can increase upper surface of the airfoil boundary-layer energy, delays upper surface air-flow to separate, makes helicopter adapt to the flight condition under different condition, reach the purpose of quick landing；The Main Function that slat cracks with wing flap is exactly that the air-flow delaying aerofoil surface separates, and the effect of wing flap mainly increases wing camber and area.
In the present invention, rotatable DCB Specimen mechanism is arranged on the helicopter longitudinal axis, the i.e. head of fuselage (1) and the afterbody of fuselage, while helicopter keeps the overall front face area that monomotor is less, possesses again bimotored strong impetus, the horizontal flight power making helicopter is far longer than resistance, the purpose of the high-speed flight that is up to the standard.
The present invention provides the helicopter of a kind of VTOL horizontal flight, rapid vertical landing and high-speed horizontal flight can be taken into account by creative design simultaneously, rotor mechanism is separately positioned on head and the afterbody of helicopter hull (1) longitudinal axis, and can do around fuselage (1) longitudinal axis and front and back rotate, big 5-6 times of existing helicopter voyage of ratio, guarantee that flight safety reduces to produce and operation cost, this helicopter has the advantages that voyage is remote, manipulation is easy, safety coefficient is high, has wide applicability and using value for helicopter field.
Embodiment five
:
When the helicopter of a kind of VTOL horizontal flight using the present invention to provide, can be according to different state of flights, control rotor mechanism and wing structure realize the rotation of different angles；When current rotor (4), rear rotor (7) are in equidirectional with helicopter vertical shaft, when the most front rotor (4), rear rotor (7), Duo Zu rotor blade mechanism (8) are concurrently residing in 90 degree, the flare maneuvers such as helicopter can realize VTOL, flying in left and right, turn-takes on the spot, see accompanying drawing 4, accompanying drawing 5.
When being suitable for the helicopter of a kind of VTOL horizontal flight that the present invention provides, current rotor (4) is controlled when heading turns to 0 degree by front rotor rotational mechanism (2), when rear rotor (7) is controlled to turn to 90 degree to tail direction by rear rotor rotational mechanism (5), when rotor blade mechanism (8) rotates to 0 degree, when before i.e., rotor (4) and the helicopter longitudinal axis are in equidirectional, helicopter can do low-medium speed horizontal flight, sees accompanying drawing 6.
When being suitable for the helicopter of a kind of VTOL horizontal flight that the present invention provides, when rear rotor (7) by rear rotor rotational mechanism (5) control to turn to tail direction 180 degree, front rotor (4) controlled to turn to 0 degree to heading by front rotor rotational mechanism (2) time, when the most front rotor shaft and rear rotor shaft are in equidirectional with the helicopter longitudinal axis simultaneously, when rotor blade mechanism (8) rotates, helicopter can do high speed and horizontal flight at full speed, sees accompanying drawing 7, accompanying drawing 8.
Embodiment six:
When helicopter flight, airflow function, on helicopter, will produce operating torque to helicopter, is allowed to rotate around transverse axis, vertical shaft and the longitudinal axis, and with change of flight attitude, helicopter each several part can move with the movement of the center of gravity of airplane.
1. the helicopter that the present invention provides quickly, high-speed flight time:
nullWhen helicopter is the quickest、During high-speed flight，Acted on by four power: lift (L)、Gravity (W)、Pulling force (P)、Resistance (D)，Now lift ＞ gravity，The helicopter that the present invention provides is by front rotor rotational mechanism (2)、Rear rotor rotational mechanism (5) is arranged on the longitudinal axis of helicopter hull (1)，Duo Zu rotor blade mechanism is arranged on the transverse axis of helicopter hull (1)，Wing rotational angle is 0 degree，Current rotor (4) rotates in heading rotates 90 degree，After when, rotor (7) rotates in tail direction rotates 90 degree，Power is all arranged on the longitudinal axis of helicopter hull (1)，In take-off process，Front rotor (4) and rear rotor (7) act on the center of gravity of airplane jointly，Helicopter lift is made to be far longer than aircraft gravity、Pulling force is more than resistance，Realize the quick of helicopter、High-speed flight，State of flight sees accompanying drawing 9.
2. during the helicopter horizontal flight aloft that the present invention provides:
When helicopter horizontal flight aloft, being acted on by four power: lift (L), gravity (W), pulling force (P), resistance (D), now thrust is more than resistance, and lift is equal to gravity；Duo Zu rotor blade mechanism (8) of the helicopter that the present invention provides realizes symmetrical 0-90 degree controllable rotating, current rotor (4) is when heading turns to 0 degree, when rear rotor (7) turns to 180 degree to tail direction, power is all arranged on the longitudinal axis of helicopter hull (1), aircraft thrust is made to be far longer than aircraft drag, change the flight speed of helicopter, it is achieved the high-speed horizontal flight of helicopter, state of flight sees accompanying drawing 10.
3. when the helicopter level that the present invention provides declines:
When helicopter declines in level, acted on by four power: lift (L), gravity (W), pulling force (P), resistance (D), now thrust ＞ resistance, lift ＜ gravity, Duo Zu rotor blade mechanism (8) realizes symmetrical 0 degree to 90 degree controllable rotating, current rotor (4) rotates in heading 90 degree, after when, rotor (7) rotates in 90 degree of tail direction, power is all arranged on the longitudinal axis of helicopter hull (1), front rotor (4) and rear rotor (7) act on helicopter center of gravity jointly, make helicopter lift less than helicopter gravity, thrust is more than resistance, change the flight speed of helicopter, the level realizing helicopter declines, state of flight sees accompanying drawing 11.
4. when the helicopter that the present invention provides takes off vertically:
When helicopter is when taking off vertically, acted on by two power: lift (L), gravity (W), now lift ＞ gravity, Duo Zu rotor blade mechanism (8) realizes being symmetrical set, controllable rotating, current rotor (4) is when heading turns to 90 degree, when rear rotor (7) turns to 90 degree to tail direction, power is all arranged on the vertical shaft of helicopter hull (1), front rotor (4) and rear main rotor (7) act on helicopter center of gravity jointly, helicopter lift is made to be far longer than helicopter gravity, change the flying height of helicopter, the rapid vertical realizing helicopter takes off, state of flight sees accompanying drawing 12.
5. during the helicopter vertical landing that the present invention provides:
When helicopter is in vertical landing, acted on by two power: lift (L), gravity (W), now lift ＜ gravity, Duo Zu rotor blade mechanism (8) realizes symmetrical 0 degree to 90 degree controllable rotating, current rotor (4) is when heading turns to 90 degree, when rear rotor (7) turns to 90 degree to tail direction, power is all arranged on the vertical shaft of helicopter hull (1), front rotor (4) and rear main rotor (7) act on helicopter center of gravity jointly, helicopter lift is made to be far smaller than helicopter gravity, change the flying height of helicopter, realize the vertical landing of helicopter, state of flight sees accompanying drawing 13.
The present invention provides the helicopter of a kind of VTOL horizontal flight to be that voyage is remote, flight speed is fast, safety coefficient is high, manipulate the dual-purpose helicopter of easy military and civilian for one.
As mentioned above; can preferably realize the present invention; the above embodiments are only to be described the preferred embodiment of the present invention; not the scope of the present invention is defined; on the premise of designing spirit without departing from the present invention; various deformation that technical scheme is made by those of ordinary skill in the art and improvement, all should fall in the protection domain that present invention determine that.
Claims (10)
1. the helicopter of a VTOL horizontal flight, including fuselage, rotor mechanism, wing structure, landing gear, actuating unit, operating mechanism, drive mechanism, fuselage includes head, waist and tail, it is characterized in that, rotor mechanism includes dual rotary rotor mechanism, and the i.e. fuselage file of the longitudinal axis of helicopter arranges the DCB Specimen mechanism of controllable rotating.
The helicopter of a kind of VTOL horizontal flight the most as claimed in claim 1, it is characterized in that, described dual rotary rotor mechanism includes front rotor rotational mechanism, rear rotor rotational mechanism, front rotor rotational mechanism includes front rotor rotational mechanism, front powerplant module and front rotor, front powerplant module and front rotor by 90 degree to 0 degree helicopter heads of front rotor rotational mechanism controls towards controllable rotating；Rear rotor rotational mechanism includes rear powerplant module, rear rotor and rear rotor rotational mechanism, and rear powerplant module and rear rotor are by 90 degree to 180 degree helicopter tails of rear rotor rotational mechanism controls towards controllable rotating, and front rotor and rear rotor are correspondingly arranged propeller blade.
3. the helicopter of a VTOL horizontal flight, including fuselage, rotor mechanism, wing structure, landing gear, actuating unit, operating mechanism, drive mechanism, fuselage includes head, waist and tail, it is characterized in that, the longitudinal axis of helicopter i.e. waist both sides are provided with organizes wing structure more, many group wing structure are arranged vertically waist, and Duo Zu rotor blade mechanism is symmetrical set, controllable rotating.
The helicopter of a kind of VTOL horizontal flight the most as claimed in claim 3, it is characterized in that, the wing structure that described waist both sides are arranged includes Duo Zu rotor blade mechanism, specifically include two or more sets rotatable wings being symmetrical set that are arranged side by side, symmetrical 0 degree to the 90 degree controllable rotating of rotatable wing；Often group wing wing tip is connected by wing connecting mechanism.
5. the helicopter of a VTOL horizontal flight, including fuselage, rotor mechanism, wing structure, landing gear, actuating unit, operating mechanism, drive mechanism, fuselage includes head, waist and tail, it is characterized in that, rotor mechanism includes dual rotary rotor mechanism, fuselage file arranges rotatable DCB Specimen mechanism, and waist both sides are provided with organizes wing structure more, and many group wing structure are arranged vertically waist.
The helicopter of a kind of VTOL horizontal flight the most as claimed in claim 5, it is characterized in that, described waist both sides are provided with wing structure, wing structure includes Duo Zu rotor blade mechanism, specifically include two or more sets rotatable wings being symmetrical set that are arranged side by side, symmetrical 0 degree to the 90 degree controllable rotating of rotatable wing.
The helicopter of a kind of VTOL horizontal flight the most as claimed in claim 5, it is characterized in that, described dual rotary rotor mechanism specifically includes front rotor rotational mechanism, rear rotor rotational mechanism, front rotor rotational mechanism includes that front powerplant module, front rotor and front rotor rotational mechanism, front powerplant module and front rotor are realized 90 degree to 0 degree heads towards controllable rotating by front rotor rotational mechanism controls；Rear rotor rotational mechanism includes rear powerplant module, rear rotor and rear rotor rotational mechanism, and rear powerplant module and rear rotor are realized 90 degree to 180 degree tails towards controllable rotating by rear rotor rotational mechanism controls, and front rotor and rear rotor are correspondingly arranged propeller blade.
8. the helicopter of the VTOL horizontal flight as described in claim 1,3,5 or 6 any one, it is characterized in that, in described wing structure, the wing tip often organizing wing is connected by wing connecting mechanism, and wing includes high lift device, leading edge slat, droope snoot, trailing edge flap and spoiler.
9. the helicopter of the VTOL horizontal flight as described in claim 1,2,5 or 7 any one, it is characterised in that in described rotor mechanism, propeller blade is made up of 2,3,4,5,6 or 8 leaves.
10. the helicopter of the VTOL horizontal flight as described in claim 1,2,5 or 7 any one, it is characterised in that in described rotor mechanism, propeller blade overlap parallel rotating.
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| Publication number | Priority date | Publication date | Assignee | Title |
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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 |
| CN110254712A (en) * | 2019-07-19 | 2019-09-20 | 苏州高博软件技术职业学院 | Two horizontal two vertical blades can turn four wheeled dynamic wing unmanned plane |
| CN110254705A (en) * | 2019-07-19 | 2019-09-20 | 苏州高博软件技术职业学院 | Blade with fixed-wing can turn Horizontal single-wheel formula and move rotor aircraft |
| CN110282125A (en) * | 2019-07-19 | 2019-09-27 | 苏州高博软件技术职业学院 | It can turn vertical dicycly based on blade and move the aircraft that the wing pushes |
| CN110282124A (en) * | 2019-07-19 | 2019-09-27 | 苏州高博软件技术职业学院 | It can turn horizontal four wheeled dynamic rotor aircraft in conjunction with the blade of fixed-wing |
| CN110294116A (en) * | 2018-03-22 | 2019-10-01 | 极光飞行科学公司 | For reducing the system and method for propeller noise |
| CN110371285A (en) * | 2019-07-19 | 2019-10-25 | 苏州高博软件技术职业学院 | Blade can turn the four wheeled dynamic wing unmanned plane of horizontal lift |
| EP3683142A1 (en) * | 2019-01-16 | 2020-07-22 | Bell Textron Inc. | Tandem tiltrotor aircraft |
| CN111766888A (en) * | 2019-06-27 | 2020-10-13 | 北京京东尚科信息技术有限公司 | Aircraft-based control method and aircraft |
| 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 |
| WO2021155532A1 (en) * | 2020-02-06 | 2021-08-12 | XDynamics Limited | An unmanned aerial vehicle |
| US11987350B2 (en) | 2021-06-03 | 2024-05-21 | Textron Innovations Inc. | Winged tiltrotor aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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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 |
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| CN110294116A (en) * | 2018-03-22 | 2019-10-01 | 极光飞行科学公司 | For reducing the system and method for propeller noise |
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| EP3683142A1 (en) * | 2019-01-16 | 2020-07-22 | Bell Textron Inc. | Tandem tiltrotor aircraft |
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| CN110371285A (en) * | 2019-07-19 | 2019-10-25 | 苏州高博软件技术职业学院 | Blade can turn the four wheeled dynamic wing unmanned plane of horizontal lift |
| CN110282124A (en) * | 2019-07-19 | 2019-09-27 | 苏州高博软件技术职业学院 | It can turn horizontal four wheeled dynamic rotor aircraft in conjunction with the blade of fixed-wing |
| CN110282125A (en) * | 2019-07-19 | 2019-09-27 | 苏州高博软件技术职业学院 | It can turn vertical dicycly based on blade and move the aircraft that the wing pushes |
| CN110254705A (en) * | 2019-07-19 | 2019-09-20 | 苏州高博软件技术职业学院 | Blade with fixed-wing can turn Horizontal single-wheel formula and move rotor aircraft |
| CN110254712A (en) * | 2019-07-19 | 2019-09-20 | 苏州高博软件技术职业学院 | Two horizontal two vertical blades can turn four wheeled dynamic wing unmanned plane |
| 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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