CN205738073U - A kind of helicopter of VTOL horizontal flight - Google Patents

A kind of helicopter of VTOL horizontal flight Download PDF

Info

Publication number
CN205738073U
CN205738073U CN201620331411.3U CN201620331411U CN205738073U CN 205738073 U CN205738073 U CN 205738073U CN 201620331411 U CN201620331411 U CN 201620331411U CN 205738073 U CN205738073 U CN 205738073U
Authority
CN
China
Prior art keywords
rotor
helicopter
wing
degree
fuselage
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN201620331411.3U
Other languages
Chinese (zh)
Inventor
倪德玉
Original Assignee
倪德玉
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 倪德玉 filed Critical 倪德玉
Priority to CN201620331411.3U priority Critical patent/CN205738073U/en
Application granted granted Critical
Publication of CN205738073U publication Critical patent/CN205738073U/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Abstract

This utility model provides the helicopter of a kind of VTOL horizontal flight, including fuselage, rotor mechanism, wing structure, landing gear, actuating unit, operating mechanism, drive mechanism;Fuselage includes head, waist and tail, and rotor mechanism includes dual rotary rotor mechanism, and fuselage file 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;By designing dual rotary rotor mechanism and rotatable DCB Specimen mechanism simultaneously, take into account VTOL and quick horizontal flight, rotor mechanism is separately mounted to head and the afterbody of helicopter hull, and can do around fuselage central shaft and front and back rotate, bigger than existing helicopter voyage 56 times, guarantee that flight safety reduces to produce and operation cost, can apply in various aircrafts, can realize that helicopter voyage is remote, flight speed is fast, safety coefficient is high, manipulate easy many notable prominent technique effects.

Description

A kind of helicopter of VTOL horizontal flight
Technical field
This utility model belongs to the technical field of Flight Vehicle Design, and more specifically, this utility model relates to one can be quick VTOL 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 one put down Row king bolt oar is responsible for aircraft and is risen and flight forward, and the responsible control aircraft simultaneously setting a lateral rotation after fuselage is left The minor spiral oar of right heading;The second be above helicopter before set a propeller, after set a spiral Oar, 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, consumption Oil mass is big.And the military upper helicopter used do not require nothing more than helicopter can rapid vertical landing, and require in level It also is able to keep certain speed during flight.Generally the distribution engine of helicopter is by transversely arranged for multiple electromotors, this Can expand the overall front face area of aircraft, resistance increases;If one side power failure in addition, also by the balance to helicopter Adversely affect.
In prior art, Do335 arrow formula fighter plane is a kind of " pulling in front and others push behind " driving aircraft, is characterized in two to send out Motivation is 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 are all the most outstanding, by It is fixed wing airplane in Do335, needs longer takeoff and landing airstrips, do not possess the energy of VTOL or STOL Power, again because the end of World War II and the appearance of jet plane, early has dropped out the arena of history of aircraft.
For increasing power performance and transport capacity, the column dual rotors layout helicopter CH-46 sea knight of helicopter 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 suitable Ying Xingqiang.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 is strong, and because its voyage is limited, type waits for a long time very much other shortcoming, 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 of the existing U.S., is characterized in that electromotor and propeller blade are symmetrically mounted on and flies The tip of machine both sides wing, it is possible to rotate around wing, thus realize vertical lift and horizontal flight.By contrast, vert rotation Wing aircraft have concurrently conventional helicopters and with propeller (rotor) drive into the advantage of fixed wing airplane, superior performance.But, vert Gyroplane has born major defect, and the electromotor of tilt rotor aircraft is placed in the wing tip of fixed-wing, makes fixed-wing become and is subject to The cantilever beam that power is severe, this is the major reason causing stable hidden danger, and meanwhile, this propeller blade is symmetrically mounted on aircraft two Side, the gravity and the gravitation point that form tilting rotor are arranged vertically with fuselage, will also result in the vertical liter of aircraft from amechanical angle Fall and many technological deficiencies and the potential safety hazard such as horizontal flight and operation safety.
In above-mentioned three kinds of aircraft of prior art, the electronic degree of V-22 " osprey " is the highest, and once break down nothing Method is saved, and safety coefficient is relatively low, and when one group of propeller blade damages, aircraft cannot be avoided crash accident, there is civil nature difficulty The problem such as 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, that safety coefficient the is relatively low state of the art, This utility model is intended to provide the helicopter of a kind of VTOL horizontal flight, can be taken into account by creative design simultaneously Rapid vertical landing and high-speed horizontal flight, be separately positioned on head and the afterbody of the helicopter hull longitudinal axis by rotor mechanism, And can do around fuselage datum and front and back rotate, big 5-6 times of existing helicopter voyage of ratio, it is ensured that flight safety reduces and produces and fortune Battalion's cost, this helicopter has the advantages that voyage is remote, manipulation is easy, safety coefficient is high, has extensively for helicopter field General practicality and using value.
This utility model is achieved through the following technical solutions:
This utility model provides the helicopter of a kind of VTOL horizontal flight, including fuselage, rotor mechanism, wing machine Structure, landing gear mechanism, actuating unit, operating mechanism, drive mechanism;Fuselage includes head, waist and tail, rotor mechanism Including dual rotary rotor mechanism, the i.e. fuselage file of the longitudinal axis of helicopter arranges the DCB Specimen mechanism of controllable rotating.
This utility model provides in above-mentioned helicopter, and dual rotary rotor mechanism includes front rotor mechanism, rear rotor mechanism, Front rotor mechanism includes front rotor rotational mechanism, front powerplant module and front rotor, and front powerplant module is turned by front rotor with front rotor Motivation structure control realization 90 degree is to the y direction head of 0 degree of helicopter towards controllable rotating;Rear rotor mechanism is dynamic after including Power unit, rear rotor and rear rotor rotational mechanism, rear powerplant module and rear rotor are realized 90 degree by rear rotor rotational mechanism controls The reverse tail of the longitudinal axis to 180 degree of helicopters is towards controllable rotating, and front rotor and rear rotor are correspondingly arranged propeller blade.
In this utility model, propeller blade overlap parallel rotating.
Meanwhile, this utility model provide a kind of VTOL horizontal flight helicopter, including fuselage, rotor mechanism, Wing structure, landing gear mechanism, actuating unit, operating mechanism, drive mechanism;Fuselage includes head, waist and tail, directly The longitudinal axis i.e. waist both sides of liter aircraft are provided with organizes wing structure more, and many group wing structure are arranged vertically waist, many Group rotor blade mechanism is symmetrical set, controllable rotating.
In this utility model, the wing structure that waist both sides are arranged includes Duo Zu rotor blade mechanism, specifically includes Be arranged side by side two or more sets rotatable wings being symmetrical set, rotatable wing realize symmetrical 0 degree can to 90 degree Control rotates.
Further, this utility model provide a kind of can the helicopter of high velocity vertical landing horizontal flight, including fuselage, rotation Wing mechanism, wing structure, landing gear mechanism, actuating unit, operating mechanism, drive mechanism;Fuselage include head, waist and Tail, rotor mechanism includes dual rotary rotor mechanism, and the i.e. fuselage file of the longitudinal axis of helicopter arranges rotatable DCB Specimen machine Structure, waist both sides can be provided with and organize wing structure more, and many group wing structure are arranged vertically waist.
This utility model provides in the above-mentioned helicopter realizing high velocity vertical landing horizontal flight, and waist both sides set Putting wing structure, wing structure includes Duo Zu rotor blade mechanism, specifically includes and is arranged side by side that two or more sets symmetrical set The rotatable wing put, rotatable wing can realize symmetrical 0 degree to 90 degree controllable rotating;Dual rotary rotor mechanism specifically wraps Including front rotor mechanism, rear rotor mechanism, front rotor mechanism includes front powerplant module, front rotor and front rotor rotational mechanism, front dynamic Power unit and front rotor are realized 90 degree to 0 degree heads towards controllable rotating by front rotor rotational mechanism controls;Rear rotor mechanism bag Including rear powerplant module, rear rotor and rear rotor rotational mechanism, rear powerplant module and rear rotor are real by rear rotor rotational mechanism controls Existing 90 degree to 180 degree tails are towards controllable rotating;Front rotor and rear rotor are correspondingly arranged propeller blade.
In this utility model, the wing tip often organizing wing is connected by wing connecting mechanism;Wing includes that high lift device, leading edge are stitched The wing, droope snoot, trailing edge flap and spoiler, rotor blade mechanism can comprise one group of aileron.
In this utility model, propeller blade realizes overlapping parallel rotating.
In this utility model, propeller blade is made up of 2,3,4,5,6 or 8 leaves.
In this utility model, landing gear mechanism includes nose-gear and rear undercarriage.
In this utility model, body joint can be positioned below one group of nose-gear, tail have two groups after undercarriage.
In this utility model, arranging many group wings can increase upper surface of the airfoil boundary-layer energy, delays upper surface air-flow to divide From, make helicopter adapt to the flight condition under different condition, reach the purpose of quick landing;The master that slat and wing flap crack Acting on and delay the air-flow of aerofoil surface to separate exactly, the effect of wing flap mainly increases wing camber and area.
In this utility model, rotatable DCB Specimen mechanism is arranged on the head of helicopter hull and the tail of fuselage Portion, while helicopter keeps the overall front face area that monomotor is less, possesses again bimotored strong impetus, makes The horizontal flight power obtaining helicopter is far longer than resistance, the purpose of the high-speed flight that is up to the standard;Helicopter each several part weight The center of gravity of the point of resultant force of power, referred to as helicopter;The position at place, action of gravity force, is position of centre of gravity;By going straight up to Three of the center of gravity of airplane mutually perpendicular, coordinate axess on the basis of body, are 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 helicopter center of gravity And the axis of vertical axes is the transverse axis of helicopter;By helicopter center of gravity and to be perpendicular to the axis of the longitudinal axis and transverse axis be straight Rise the vertical uranium of aircraft;When helicopter flight, airflow function, on helicopter, will produce steering force to helicopter Square, is allowed to rotate around transverse axis, vertical shaft and the longitudinal axis, and with change of flight attitude, helicopter each several part can be with helicopter center of gravity Move and move.
When the above-mentioned helicopter using this utility model to provide the most stably rises, acted on by four power: Lift (L), gravity (W), pulling force (P), resistance (D), now lift > gravity, the one that this utility model provides can high velocity vertical The helicopter of landing horizontal flight, is arranged on the vertical of helicopter hull by front rotor rotational mechanism, rear rotor rotational mechanism On axle, Duo Zu rotor blade mechanism is arranged on the transverse axis of helicopter hull, and wing rotational angle is 0 degree, current rotor to Heading rotates in 90 degree and rotates, when after rotor rotation in tail direction rotates 90 degree, power is all arranged in goes straight up to fly On the longitudinal axis of machine fuselage, in take-off process, front rotor and rear rotor act on helicopter center of gravity jointly so that helicopter Lift is far longer than helicopter gravity, pulling force more than resistance, it is achieved quickly taking off of helicopter.
When the above-mentioned helicopter horizontal flight aloft using this utility model 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;This utility model provides A kind of can the helicopter of high velocity vertical landing horizontal flight, it is controlled that Duo Zu rotor blade mechanism realizes symmetrical 0-90 degree Rotating, current rotor is when heading turns to 0 degree, when rear rotor turns to 180 degree to tail direction, and the whole cloth of power Put on the longitudinal axis of helicopter hull so that helicopter thrust is far longer than helicopter resistance, change helicopter Flight speed, it is achieved the high-speed horizontal flight of helicopter.
When the above-mentioned helicopter using this utility model 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 a left side Right symmetrical 0 degree to 90 degree controllable rotating, current rotor rotates in heading 90 degree, when after rotor in 90 degree of tail direction Rotating, power is all arranged on the longitudinal axis of helicopter hull, and front rotor and rear rotor act on helicopter center of gravity jointly, Make helicopter lift less than helicopter gravity, thrust more than resistance, change the flight speed of helicopter, it is achieved go straight up to The rapid vertical of aircraft declines.
When the above-mentioned helicopter using this utility model 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 When heading turns to 90 degree, when rear rotor turns to 90 degree to tail direction, power is all arranged in helicopter On the vertical shaft of fuselage, front rotor and rear main rotor act on helicopter center of gravity jointly so that helicopter lift is far longer than Helicopter gravity, changes the flying height of helicopter, it is achieved the rapid vertical of helicopter takes off.
When the above-mentioned helicopter using this utility model 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, currently revolves When flapwise heading turns to 90 degree, when rear rotor turns to 90 degree to tail direction, power is all arranged in goes straight up to fly On the vertical shaft of machine fuselage, front rotor and rear main rotor act on helicopter center of gravity jointly so that helicopter lift is the least In helicopter gravity, change the flying height of helicopter, it is achieved the vertical landing of helicopter.
Be suitable for that this utility model provides a kind of can the helicopter of high velocity vertical landing horizontal flight time, can be according to not Same state of flight, control rotor mechanism and wing structure realize the rotation of different angles;Current rotor, rear rotor and go straight up to fly When machine vertical shaft is in equidirectional, when the most front rotor, rear rotor, Duo Zu rotor blade mechanism are concurrently residing in 90 degree, helicopter can To realize VTOL, left and right flight, the flare maneuver such as to turn-take on the spot.
Be suitable for that this utility model provides a kind of can the helicopter of high velocity vertical landing horizontal flight time, current rotor Rotated 90 degree by front rotor rotational mechanism controls to heading, when rotor blade mechanism rotates to 0 degree, i.e. front rotor with go straight up to When aircraft longitudinal axis is in opposite direction, helicopter can do low-medium speed horizontal flight.
Be suitable for that this utility model provides a kind of can the helicopter of high velocity vertical landing horizontal flight time, when after rotor Turned to heading by front rotor rotational mechanism controls to tail direction rotation 90 degree, front rotor by rear rotor rotational mechanism controls When dynamic 90 degree, 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) this utility model provide a kind of can the helicopter of high velocity vertical landing horizontal flight, set by creative Meter can take into account rapid vertical landing and high-speed horizontal flight simultaneously, and rotor mechanism is separately positioned on the helicopter hull longitudinal axis Head and afterbody, it is possible to do around fuselage datum and front and back rotate, big 5-6 times of existing helicopter voyage of ratio, it is ensured that flight safety Reducing and produce and operation cost, this helicopter has the advantages that voyage is remote, manipulation is easy, safety coefficient is high, for going straight up to fly Machine field has wide applicability and using value.
(2) this utility model provides a kind of and the helicopter of high velocity vertical landing horizontal flight can be that a kind of voyage is remote, flies Line 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 this utility model provides.
Fig. 2 is shown as the helicopter top view that this utility model provides.
Fig. 3 is shown as the helicopter perspective view that this utility model provides.
Fig. 4 is shown as the helicopter flight state diagram one that this utility model provides.
Fig. 5 is shown as the helicopter flight state diagram two that this utility model provides.
Fig. 6 is shown as the helicopter flight state diagram three that this utility model provides.
Fig. 7 is shown as the helicopter flight state diagram four that this utility model provides.
Fig. 8 is shown as the helicopter flight state diagram five that this utility model provides.
Fig. 9 is shown as the helicopter flight state principle figure one that this utility model provides.
Figure 10 is shown as the helicopter flight state principle two that this utility model provides.
Figure 11 is shown as the helicopter flight state principle three that this utility model provides.
Figure 12 is shown as the helicopter flight state principle four that this utility model provides.
Figure 13 is shown as the helicopter flight state principle five that this utility model provides.
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-.
Detailed description of the invention
In conjunction with accompanying drawing 1-13, illustrate for embodiment, but, this utility model is not limited to following embodiment.
In this utility model, for the ease of describing, by a kind of can be 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, Butut direction right, 0 degree, 90 degree, 180 degree etc. the description foundation Figure of description 1 such as position relationship, the anglec of rotation determines.
See accompanying drawing 1, in the helicopter that this utility model provides, with along the fuselage axis direction axle by the center of gravity of airplane Line is the longitudinal axis, to pass through the axis of the center of gravity of airplane vertical axes along wing direction as transverse axis;Front rotor rotational mechanism is along the longitudinal axis Turning to and be 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, revolves afterwards Wing rotating mechanism turns to along the longitudinal axis and is set as 90 degree with tail vertical direction, and rear rotor rotational mechanism turns to same with tail along the longitudinal axis To being set as 180 degree.
Embodiment one:
Seeing accompanying drawing 1,2, this utility model 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, and the longitudinal axis of helicopter i.e. fuselage (1) file is arranged controlled The DCB Specimen mechanism rotated.
This utility model provides in the helicopter of VTOL horizontal flight, and dual rotary rotor mechanism includes front gyroplane Structure, rear rotor mechanism, front rotor mechanism includes front powerplant module (3), front rotor (4) and front rotor rotational mechanism (2), front power Unit (3) and front rotor (4) by front rotor rotational mechanism (2) control realization head towards controllable rotating;Rear rotor mechanism includes Rear powerplant module (6), rear rotor (7) and rear rotor rotational mechanism (5), rear powerplant module (6) is turned by rear rotor with rear rotor (7) Motivation structure (5) control realization tail is towards controllable rotating;Front rotor (4) and rear rotor (7) are correspondingly arranged propeller blade.
In this utility model, front powerplant module (3) is controlled preferential realization with front rotor (4) by front rotor rotational mechanism (2) 90 degree of y direction heads to 0 degree of helicopter are towards controllable rotating.
In this utility model, rear powerplant module (6) is controlled preferential realization with rear rotor (7) by rear rotor rotational mechanism (5) 90 degree of y direction tails to 180 degree of helicopters are towards controllable rotating.
In this utility model, propeller blade overlap parallel rotating.
In this utility model, propeller blade is made up of 2,3,4,5,6 or 8 leaves.
In this utility model, landing gear mechanism includes nose-gear (11) and rear undercarriage (12).
In this utility model, fuselage (1) head has one group of nose-gear (11), tail have two groups after undercarriage (12)。
Embodiment two:
Seeing accompanying drawing 3,4, this utility model 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, and many group wing structure are arranged vertically aircraft The longitudinal axis i.e. fuselage (1) middle part, Duo Zu rotor blade mechanism (8) is symmetrical set, controllable rotating.
This utility model provides in the helicopter of VTOL horizontal flight, and both sides, fuselage (1) middle part are provided with wing Mechanism, wing structure includes Duo Zu rotor blade mechanism (8), specifically includes and be arranged side by side what two or more sets were symmetrical set Rotatable wing;The wing tip often organizing wing is connected by wing connecting mechanism (9).
This utility model provides in the helicopter of VTOL horizontal flight, and the rotatable wing of preferential employing realizes 0 degree To 90 degree of controllable rotatings.
In this utility model, wing includes high lift device, leading edge slat, droope snoot, trailing edge flap and spoiler.
In this utility model, rotor blade mechanism (8) comprises one group of aileron (10).
In this utility model, landing gear mechanism includes nose-gear (11) and rear undercarriage (12).
In this utility model, 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, this utility model 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) include head, Fuselage (1) middle part and tail, rotor mechanism includes dual rotary rotor mechanism, and the longitudinal axis of helicopter i.e. fuselage (1) file is arranged 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 directly Rise the longitudinal axis i.e. fuselage (1) middle part of aircraft.
This utility model provides in the helicopter of VTOL horizontal flight, and both sides, fuselage (1) middle part are provided with wing Mechanism, wing structure includes Duo Zu rotor blade mechanism (8), specifically includes and be arranged side by side what two or more sets were symmetrical set Rotatable wing, rotatable wing can realize symmetrical 0 degree to 90 degree controllable rotating;The wing tip often organizing wing is connected by wing Mechanism (9) connects.
This utility model provides in the helicopter of VTOL horizontal flight, and dual rotary rotor mechanism includes front gyroplane Structure, rear rotor mechanism, front rotor mechanism includes front powerplant module (3), front rotor (4) and front rotor rotational mechanism (2), front power Unit (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 Mechanism 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 right Propeller blade should be set.
In this utility model, wing includes high lift device, by leading edge slat, droope snoot, trailing edge flap and spoiler group Becoming, rotor blade mechanism (8) comprises one group of aileron (10).
In this utility model, propeller blade overlap parallel rotating.
In this utility model, propeller blade is made up of 2,3,4,5,6 or 8 leaves.
In this utility model, landing gear mechanism includes nose-gear (11) and rear undercarriage (12).
In this utility model, 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;Mutually perpendicular, with body as base by three of helicopter center of gravity Accurate coordinate axes, is axis, can be divided into the longitudinal axis, transverse axis, vertical shaft;Along fuselage (1) axis, by the axis of helicopter center of gravity The longitudinal axis for helicopter;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, gas Stream acts on helicopter, helicopter will be produced operating torque, is allowed to rotate around transverse axis, vertical shaft and the longitudinal axis, to change Becoming flight attitude, helicopter each several part can move with the movement of center of gravity.
In this utility model, arranging many group wings can increase upper surface of the airfoil boundary-layer energy, delays upper surface air-flow to divide From, make helicopter adapt to the flight condition under different condition, reach the purpose of quick landing;It is main that slat and wing flap crack Effect delays the air-flow of aerofoil surface to separate exactly, and the effect of wing flap mainly increases wing camber and area.
In this utility model, 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 less overall front face area of monomotor, possess again bimotored by force Strength power so that the horizontal flight power of helicopter is far longer than resistance, the purpose of the high-speed flight that is up to the standard.
This utility model provides the helicopter of a kind of VTOL horizontal flight, can be held concurrently by creative design simultaneously Turn round and look at rapid vertical landing and high-speed horizontal flight, rotor mechanism is separately positioned on helicopter hull (1) longitudinal axis head and Afterbody, it is possible to do around fuselage (1) longitudinal axis and front and back rotate, big 5-6 times of existing helicopter voyage of ratio, it is ensured that flight safety reduces Producing and operation cost, this helicopter has the advantages that voyage is remote, manipulation is easy, safety coefficient is high, leads for helicopter Territory has wide applicability and using value.
Embodiment five:
When the helicopter of a kind of VTOL horizontal flight using this utility model to provide, can fly according to different Row state, control rotor mechanism and wing structure realize the rotation of different angles;Current rotor (4), rear rotor (7) and go straight up to fly When machine vertical shaft is in equidirectional, when the most front rotor (4), rear rotor (7), Duo Zu rotor blade mechanism (8) are concurrently residing in 90 degree, directly Rise the flare maneuvers such as aircraft 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 this utility model provides, current rotor (4) by Front rotor rotational mechanism (2) control when heading turns to 0 degree, when after rotor (7) controlled by rear rotor rotational mechanism (5) When turning to 90 degree to tail direction, when rotor blade mechanism (8) rotates to 0 degree, at i.e. front rotor (4) and the helicopter longitudinal axis When 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 this utility model provides, when after rotor (7) by Rear rotor rotational mechanism (5) control to turn to tail direction 180 degree, front rotor (4) by front rotor rotational mechanism (2) control to When heading turns to 0 degree, when the most front rotor shaft and rear rotor shaft are in equidirectional with the helicopter longitudinal axis simultaneously, whirler When wing 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, be allowed to Rotating around transverse axis, vertical shaft and the longitudinal axis, 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 this utility model provides quickly, high-speed flight time:
When helicopter aloft quickly, high-speed flight time, acted on by four power: lift (L), gravity (W), pulling force (P), resistance (D), now lift > gravity, this utility model provide helicopter by front rotor rotational mechanism (2), rear rotor Rotating mechanism (5) is arranged on the longitudinal axis of helicopter hull (1), and Duo Zu rotor blade mechanism is arranged on helicopter hull (1) on transverse axis, wing rotational angle is 0 degree, and current rotor (4) rotates rotation in 90 degree to heading, when after rotor (7) Rotating 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 so that helicopter lift is far longer than aircraft gravity, pulling force More than resistance, it is achieved quick, the high-speed flight of helicopter, state of flight sees accompanying drawing 9.
2. during the helicopter horizontal flight aloft that this utility model provides:
When helicopter horizontal flight aloft, 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;Many groups rotor blade of the helicopter that this utility model provides Mechanism (8) realizes symmetrical 0-90 degree controllable rotating, current rotor (4) when heading turns to 0 degree, when after rotor (7), when turning to 180 degree to tail direction, power is all arranged on the longitudinal axis of helicopter hull (1) so that aircraft thrust Being far longer than aircraft drag, change the flight speed of helicopter, it is achieved the high-speed horizontal flight of helicopter, state of flight is joined See accompanying drawing 10.
3. when the helicopter level that this utility model 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 controlled rotation Turn, current rotor (4) rotates in heading 90 degree, when after rotor (7) rotate in 90 degree of tail direction, the whole cloth of power Putting on the longitudinal axis of helicopter hull (1), front rotor (4) and rear rotor (7) act on helicopter center of gravity jointly so that straight Rise airplane ascensional force less than helicopter gravity, thrust more than resistance, change the flight speed of helicopter, it is achieved helicopter Level declines, and state of flight sees accompanying drawing 11.
4. when the helicopter that this utility model provides takes off vertically:
When helicopter is when taking off vertically, acted on by two power: lift (L), gravity (W), now lift > weight Power, Duo Zu rotor blade mechanism (8) realizes being 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), Front rotor (4) and rear main rotor (7) act on helicopter center of gravity jointly so that helicopter lift is far longer than helicopter Gravity, changes the flying height of helicopter, it is achieved the rapid vertical of helicopter takes off, and state of flight sees accompanying drawing 12.
5. during the helicopter vertical landing that this utility model provides:
When helicopter is in vertical landing, acted on by two power: lift (L), gravity (W), now lift < weight Power, Duo Zu rotor blade mechanism (8) realizes symmetrical 0 degree to 90 degree controllable rotating, and current rotor (4) rotates to heading During 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 axle, front rotor (4) and rear main rotor (7) act on helicopter center of gravity jointly so that helicopter lift is far smaller than directly Rise aircraft gravity, change the flying height of helicopter, it is achieved the vertical landing of helicopter, state of flight sees accompanying drawing 13.
This utility model provides the helicopter of a kind of VTOL horizontal flight to be that a kind of voyage is remote, flight speed fast, Safety coefficient is high, manipulate the dual-purpose helicopter of easy military and civilian.
As it has been described above, this utility model can preferably be realized, the above embodiments are only to of the present utility model excellent Select embodiment to be described, not scope of the present utility model is defined, without departing from this utility model design spirit On the premise of, various deformation that the technical solution of the utility model is made by those of ordinary skill in the art and improvement, all should fall Enter in the protection domain that this utility model determines.

Claims (10)

1. a helicopter for VTOL horizontal flight, including fuselage, rotor mechanism, wing structure, landing gear, moves Force mechanisms, operating mechanism, drive mechanism, fuselage includes head, waist and tail, it is characterised in that rotor mechanism includes Dual rotary rotor mechanism, 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 characterised in that described dual rotary Rotor mechanism includes front rotor mechanism, rear rotor mechanism, and front rotor 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 mechanism includes rear powerplant module, rear rotor and rear rotor rotational mechanism, and rear powerplant module is turned by rear rotor with rear rotor Dynamic 90 degree to 180 degree helicopter tails of mechanism controls are towards controllable rotating, and front rotor and rear rotor are correspondingly arranged propeller blade Sheet.
3. a helicopter for VTOL horizontal flight, including fuselage, rotor mechanism, wing structure, landing gear, moves Force mechanisms, operating mechanism, drive mechanism, fuselage includes head, waist and tail, it is characterised in that indulging of helicopter Axle i.e. waist both sides are provided with organizes wing structure more, and many group wing structure are arranged vertically waist, organize rotor blade more Mechanism is symmetrical set, controllable rotating.
The helicopter of a kind of VTOL horizontal flight the most as claimed in claim 3, it is characterised in that in described fuselage The wing structure that both sides, portion are arranged includes Duo Zu rotor blade mechanism, specifically includes and is arranged side by side that two or more sets symmetrical set The rotatable wing put, symmetrical 0 degree to the 90 degree controllable rotating of rotatable wing;Often group wing wing tip is by wing connecting mechanism Connect.
5. a helicopter for VTOL horizontal flight, including fuselage, rotor mechanism, wing structure, landing gear, moves Force mechanisms, operating mechanism, drive mechanism, fuselage includes head, waist and tail, it is characterised in that rotor mechanism includes Dual rotary rotor mechanism, the rotatable DCB Specimen mechanism of fuselage file layout, waist both sides are provided with organizes wing structure more, 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 characterised in that in described fuselage Both sides, portion are provided with wing structure, and wing structure includes Duo Zu rotor blade mechanism, specifically includes and is arranged side by side two or more sets The rotatable wing being symmetrical set, 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 characterised in that described dual rotary Rotor mechanism specifically includes front rotor mechanism, rear rotor mechanism, and front rotor mechanism includes front powerplant module, front rotor and front rotor Rotating 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 mechanism includes rear powerplant module, rear rotor and rear rotor rotational mechanism, and rear powerplant module is turned by rear rotor with rear rotor 90 degree to 180 degree tails of motivation structure control realization are towards controllable rotating, 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 characterised in that In described wing structure, the wing tip often organizing wing is connected by wing connecting mechanism, wing include 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.
CN201620331411.3U 2016-04-19 2016-04-19 A kind of helicopter of VTOL horizontal flight Active CN205738073U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201620331411.3U CN205738073U (en) 2016-04-19 2016-04-19 A kind of helicopter of VTOL horizontal flight

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201620331411.3U CN205738073U (en) 2016-04-19 2016-04-19 A kind of helicopter of VTOL horizontal flight

Publications (1)

Publication Number Publication Date
CN205738073U true CN205738073U (en) 2016-11-30

Family

ID=57374645

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201620331411.3U Active CN205738073U (en) 2016-04-19 2016-04-19 A kind of helicopter of VTOL horizontal flight

Country Status (1)

Country Link
CN (1) CN205738073U (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105775117A (en) * 2016-04-19 2016-07-20 倪德玉 Helicopter taking off and landing vertically and flying horizontally and application thereof
CN110626494A (en) * 2019-09-22 2019-12-31 江富余 Tandem three-rotor helicopter

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105775117A (en) * 2016-04-19 2016-07-20 倪德玉 Helicopter taking off and landing vertically and flying horizontally and application thereof
CN105775117B (en) * 2016-04-19 2019-03-22 倪德玉 A kind of helicopter of VTOL horizontal flight and its application
CN110626494A (en) * 2019-09-22 2019-12-31 江富余 Tandem three-rotor helicopter

Similar Documents

Publication Publication Date Title
CN105775117B (en) A kind of helicopter of VTOL horizontal flight and its application
EP3439951B1 (en) Rotating wing assemblies for tailsitter aircraft
CN103979104B (en) One can variant X-type wing vertical landing minute vehicle
CN202011472U (en) Tilting duct unmanned aerial vehicle
CN106864746A (en) It is a kind of can VTOL the rotor canard configuration aircraft of tailstock formula three
CN205022861U (en) VTOL fixed wing aircraft
CN103587683A (en) Small-sized aircraft with tiltable rotor wings
CN102120489A (en) Tilt ducted unmanned aerial vehicle
CN202728574U (en) Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function
CN104743112B (en) Novel tilt wing aircraft
CN108001679A (en) Three shrouded propeller power modes can VTOL fixed-wing unmanned vehicle
CN104085532A (en) Layout scheme and control method of tilt rotor transport aircraft
CN205022862U (en) Power device and fixed wing aircraft with mechanism of verting
CN106828918A (en) A kind of Three-wing-surface vertically taking off and landing flyer
CN106927040A (en) It is a kind of can VTOL the rotor tailless configuration aircraft of tailstock formula four
CN105818980A (en) Novel large-lift-force vertical take-off and landing aircraft
CN108639328A (en) A kind of New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone
CN106915459A (en) A kind of hybrid tilting rotor wing unmanned aerial vehicle
CN107352029A (en) A kind of electronic multiaxis tilting rotor wing unmanned aerial vehicle system
CN111315655A (en) Assembly of three composite wings for air, water, land or space vehicles
CN106240814A (en) A kind of power-controlled tail sitting posture mixed layout vertically taking off and landing flyer
CN205738073U (en) A kind of helicopter of VTOL horizontal flight
CN108528692A (en) A kind of folded wing double-rotor aerobat and its control method
CN105083550A (en) Fixed-wing aircraft realizing vertical take-off and landing
CN110775250A (en) Variant tilt-rotor aircraft and working method thereof

Legal Events

Date Code Title Description
C14 Grant of patent or utility model
GR01 Patent grant