CN107416200A - A kind of electronic compound rotor aircraft - Google Patents
A kind of electronic compound rotor aircraft Download PDFInfo
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- CN107416200A CN107416200A CN201710165753.1A CN201710165753A CN107416200A CN 107416200 A CN107416200 A CN 107416200A CN 201710165753 A CN201710165753 A CN 201710165753A CN 107416200 A CN107416200 A CN 107416200A
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- Prior art keywords
- rotor
- rearmounted
- wing
- aircraft
- steering wheel
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
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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
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
A kind of electronic compound rotor aircraft, it is related to unmanned aerial vehicle design field, it is existing in fixed-wing cruising phase to solve existing compound rotor aircraft, more rotor power systems turn into deadweight, have lost the performance of compound rotor aircraft, or the excess drive force of dynamical system be present, the problem such as cause dynamical system efficiency low, including fixed-wing component, rotor assemblies and inclining rotary mechanism, rotor assemblies include four sets of dynamical systems, the rotor plane keep level of preposition rotor；Rearmounted rotor motor is symmetrically mounted on the both ends of rotating shaft, and rotating shaft is arranged on the end of tail supporting rod by tee pipe fitting, and the rotor plane of rearmounted rotor sets 10 degree of the upper counterangle；Avionics system is powered for dynamical system, and inclining rotary mechanism includes steering wheel and linkage, and inclining rotary mechanism steering wheel is verted by steering wheel rocking arm drivening rod mechanism drive shaft, realizes synchronously verting for rearmounted rotor.The present invention is applied to include civil aviaton and military numerous areas, is applicable not only to the model of an airplane, unmanned plane, is equally applicable to manned aircraft.
Description
Technical field
The present invention relates to unmanned aerial vehicle design field, and in particular to the compound flight that a kind of more rotors are combined with fixed-wing
Device.
Background technology
The application of the more rotors in SUAV field at present will be far more than fixed-wing unmanned plane.Multi-rotor unmanned aerial vehicle can hang down
Straight landing and hovering, the feature or advantage have adapted to most of demands to unmanned plane application scenario currently on the market, but more rotations
The wing will lean on the pulling force that its rotor provides to overcome gravity all the time under any state, the endurance and effective load that this will be to more rotors
Remake into greatly limitation, its flight time most twenty or thirty minutes, in heavy－duty the flight time even foreshorten to a few minutes,
In addition the flying speed of multi-rotor aerocraft is also very limited.
Fixed Wing AirVehicle offsets gravity in flight by lift caused by wing, and dynamical system only overcomes resistance,
Because lift-drag ratio of the Fixed Wing AirVehicle in cruise can typically reach 10 or so, it is believed that in the case of equivalent weight,
The dynamical system of fixed-wing only needs to pay the cost of the dynamical system 1/10 of more rotors, so as to which Fixed Wing AirVehicle is in terms of endurance
There is big advantage compared with multi-rotor aerocraft, in addition, the load of Fixed Wing AirVehicle and stability are typically also better than
Multi-rotor aerocraft.But limitation of the landing of Fixed Wing AirVehicle to place is bigger, or need bulky launching cradle system
System.Exactly the shortcoming limits the large-scale promotion application of fixed-wing unmanned plane.
According to the advantage and disadvantage of more rotors and fixed-wing, some research staff of aviation field have found a kind of fixed-wing and more
Rotor is combined while has the aircraft of both advantages concurrently, is roughly divided into two classes, and one kind is directly on the fixed-wing of positive routine
More rotor systems are directly added in face, and more rotor power systems and fixed-wing dynamical system are separate, in VTOL more revolve
Wing system work fixed-wing system does not work, fixed-wing cruising phase fixed-wing power system operational and more rotor systems not work
Make, though the advantages of such composite wing has had more rotors and fixed-wing concurrently, in fixed-wing cruising phase, more rotor power systems
As deadweight, the performance of compound rotor aircraft greatly have lost；Another kind of is the power by the power of more rotors and fixed-wing
It is combined into one, airborne power system was not only consolidated as the power but also power when being cruised as fixed-wing, such aircraft of more rotors
The dynamical system utilization rate of aircraft is so improved, eliminates deadweight during fixed-wing cruise, but thus also bring excess drive force
The problem of, the lift needed during such aircraft vertical landing is greater than the gravity of itself, and needs to use when fixed-wing cruises
Thrust is only the 1/10 of such aircraft weight, and the dynamical system of high thrust works under low thrust for a long time, although dynamical system
The utilization rate of system improves, but dynamical system is extremely inefficient.
Among the known fixed-wing with VTOL function, directly added immediately above in the fixed-wing of positive routine
The scheme of more rotor systems similar " the CW-10 rocs " and " CW-20 rocs " that has Chengdu Autotek S. r. l. in length and breadth
Unmanned plane, as it was previously stated, greatly being lost as deadweight in the more rotor systems of fixed-wing cruising phase the shortcomings that such aircraft
The performance of Fixed Wing AirVehicle.
The dynamical system of the dynamical system of more rotors and fixed-wing is combined into one the fixed-wing with VTOL function
Scheme have tilting rotor composite aircraft and tailstock formula aircraft, existing scheme has " V22 " osprey being on active service,
" the electronic unmanned plane of the tilting rotors of Fire Fly 6 ", Air China's industry Chengdu " VD200 " unmanned plane etc., as previously described such fly
The shortcomings that row device is excess drive force, and in cruise, dynamical system is less efficient.
To sum up, multi-rotor aerocraft has the advantage of VTOL and hovering, but its load-carrying and endurance in the prior art
It is very restricted, wind loading rating is not also strong.
Fixed Wing AirVehicle has heavy－duty, long endurance and the stronger advantage of wind resistance, but its landing need to rely on
Certain runway, or need bulky ejection system.
The compound aircraft some of existing more rotors and fixed-wing when fixed-wing pattern is cruised more rotor systems completely into
It has lost the performance of fixed-wing pattern for deadweight, some dynamical systems in fixed-wing mode flight are superfluous, dynamical system during cruise
That unites is less efficient.
The content of the invention
To solve, existing compound rotor aircraft is existing to be turned into the present invention in fixed-wing cruising phase, more rotor power systems
Deadweight, have lost the performance of compound rotor aircraft, or the excess drive force of dynamical system be present, cause dynamical system efficiency low etc.
The problem of, propose a kind of new electronic compound rotor aircraft.
Electronic compound rotor aircraft, including fixed-wing component, the fixed-wing component include wing, fuselage, tail supporting rod, hang down
Tail, horizontal tail and avionics system；The vertical fin is connected with fuselage by tail supporting rod, and horizontal tail is symmetrically mounted on above vertical fin；Also include
Rotor assemblies and inclining rotary mechanism, the rotor assemblies include two preposition rotors, two preposition rotor motors, two rearmounted rotors
With two rearmounted rotor motors, preposition rotor motor is symmetrically and fixedly mounted to the wing of fuselage both sides by preposition flight support bar
On, the rotor plane keep level of preposition rotor；Rearmounted rotor motor is symmetrically mounted on the both ends of rotating shaft, and the rotating shaft passes through three
Way pipe fitting is arranged on the end of tail supporting rod, and the rotor plane of the rearmounted rotor sets 10 degree of the upper counterangle；
The avionics system includes power supervisor and two sets of electric power systems, and a set of electric power system supplies for preposition rotor motor
Electricity, another set of electric power system are powered for rearmounted rotor motor；
The inclining rotary mechanism includes inclining rotary mechanism steering wheel and linkage, and the inclining rotary mechanism steering wheel is fixed on vertical fin covering
On, one end of linkage is connected with steering wheel rocking arm, and the other end and the rotating shaft of linkage are connected；The inclining rotary mechanism steering wheel leads to
Cross steering wheel rocking arm drivening rod mechanism drive shaft to vert, realize synchronously verting for rearmounted rotor.
Beneficial effects of the present invention：
First, electronic compound rotor aircraft of the invention was both used as by two rearmounted rotors of design of inclining rotary mechanism and revolved
The power of the wing system power as fixed-wing system again, dynamical system utilization rate is higher, when reducing fixed-wing mode flight
Deadweight；By designing the position of preposition rotor and rearmounted rotor relative CG and the upper counterangle of rearmounted rotor so that fixed
The efficiency of dynamical system reaches highest when wing pattern is cruised.So not only the energy with more rotors hangs down the electronic compound rotor aircraft
The advantages such as straight landing, hovering, long endurance, heavy－duty, speed also with fixed-wing be high and the wind resistance advantage such as by force.
2nd, the present invention can distribute battery proportioning according to practical flight task, lead to because employing two sets of electric power systems
Supplying cell weight of the increase to preposition rotor is crossed, reduces the supplying cell weight to rearmounted rotor, can be to sacrifice fixed-wing
The cruise time of pattern causes more rotor mode working times of the electronic compound rotor aircraft to increase；By reducing to preposition
The supplying cell weight of rotor, increase the supplying cell weight to rearmounted rotor, when can be to sacrifice the work of more rotor modes
Between the fixed-wing cruise operation time of the electronic compound rotor aircraft increased；The electronic compound rotor aircraft can meet more
Kind mission mode.
3rd, inclining rotary mechanism of the invention is the linkage of servos control, simple in construction, lighter in weight.
4th, dynamical system of the invention is motor, gently more many than traditional dynamical system, so preposition rotor moves
The increased deadweight of Force system is less, and dynamical system lasts a long time and reliably, environmental suitability is stronger.
5th, electronic compound rotor aircraft of the invention can be applied to the numerous areas for including civil aviaton and military affairs, not only be applicable
In the model of an airplane, UAV, manned aircraft is equally applicable to.
Brief description of the drawings
Fig. 1 is the structural representation of electronic compound rotor aircraft of the present invention；
Fig. 2 is the top view of electronic compound rotor aircraft of the present invention；
Structural representation when Fig. 3 is electronic compound rotor aircraft of the present invention more rotor mode VTOL；
Structural representation when Fig. 4 is electronic compound rotor aircraft transition flight of the present invention；
Structural representation when Fig. 5 is electronic compound rotor aircraft fixed-wing pattern cruise of the present invention；
Fig. 6 is the close-up schematic view of electronic compound rotor aircraft inclining rotary mechanism of the present invention.
In figure：1st, wing, 2, preposition rotor, 3, fuselage, 4, inner aileron, 5, outer aileron, 6, elevator, 7, direction
Rudder, 8, rotating shaft, 9, inclining rotary mechanism steering wheel, 10, rearmounted rotor, 11, tail supporting rod, 12, preposition flight support bar, 13, preposition rotor
Motor, 14, inner aileron steering wheel, 15, outer aileron steering wheel, 16, horizontal tail, 17, elevator steering wheel, 18, vertical fin, 19, rudder
Steering wheel, 20, steering wheel rocking arm, 21, inclining rotary mechanism connecting rod, 22, collar connecting rod, 23, tee pipe fitting, 24, rearmounted rotor motor, 25,
Vertical fin covering.
Embodiment
Embodiment one, illustrate present embodiment, a kind of electronic compound rotor aircraft with reference to Fig. 1 to Fig. 6, including consolidate
Determine wing component, the fixed-wing component includes wing 1, fuselage 3, tail supporting rod 11, vertical fin 18, horizontal tail 16, inner aileron 4, outside
Aileron 5, rudder 7, elevator 6 and avionics system；
Wing 1 includes port wing and starboard wing, and left and right wing is symmetrically arranged on the both sides of fuselage 3.Inner aileron 4 includes a left side
Inner aileron and Right Inboard aileron, are symmetrically arranged on left and right inboard.Inner aileron steering wheel 14 includes left and right inner aileron
Steering wheel, left and right inner aileron are motor-driven come the rolling of drive control fixed-wing pattern by inner aileron steering wheel 14.
Outer aileron 5 includes left-external side aileron and right outer aileron, is symmetrically arranged on the outside of the wing of left and right.Outer aileron rudder
Machine 15 includes the steering wheel of left and right outer aileron, and left and right outer aileron is by outer aileron steering wheel 15 come drive control fixed-wing pattern
Rolling it is motor-driven.
The vertical fin 18 is connected with fuselage 3 by tail supporting rod 11, and rudder 7 is fixed by rudder steering wheel 19 come drive control
The yawing maneuvering of wing pattern.
Horizontal tail 16 includes left horizontal tail and right horizontal tail, and left and right horizontal tail is symmetrically arranged on 18 top, and the vertical fin 18 is T-shaped tail
The wing.Elevator 6 includes left elevator and right elevator, and elevator steering wheel 17 includes left elevator steering wheel and right elevator steering wheel,
Elevator 6 is motor-driven come the pitching of drive control fixed-wing pattern by elevator steering wheel 17.
Also include rotating shaft 8, rotor assemblies and inclining rotary mechanism, the rotor assemblies include four sets of dynamical systems, often cover power
System is made up of rotor+motor, i.e.,：Two preposition rotors 2, for drive two preposition rotors 2 preposition rotor motor 13, two
Individual rearmounted rotor 10, for driving the rearmounted rotor motor 24 of two rearmounted rotors 10；
The preposition rotor 2 puts rotor and right preposition rotor including left front, and preposition rotor motor 13 puts rotor including left front
Motor and right preposition rotor motor, the preposition rotor in left and right are driven by the preposition rotor motor 13 in left and right respectively, preposition flight support bar
12 put flight support bar and right preposition flight support bar including left front, and the preposition rotor motor 13 in left and right passes through the preposition rotor branch in left and right
Strut 12 is connected on port wing and starboard wing 1.
The rearmounted rotor 10 puts rotor and right rearmounted rotor including left back, and rearmounted rotor motor 24 puts rotor including left back
Motor and right rearmounted rotor motor, the rearmounted rotor 10 in left and right are driven by the rearmounted rotor motor 24 in left and right.The rearmounted rotor motor in left and right
24 are fixedly mounted on the both ends of rotating shaft 8.
The rotor plane keep level of the preposition rotor 2；The rotating shaft 8 is arranged on tail supporting rod 11 by tee pipe fitting 23
End, the rotor plane of the rearmounted rotor 10 sets 10 degree of the upper counterangle；
The inclining rotary mechanism includes inclining rotary mechanism steering wheel 9 and linkage, and the inclining rotary mechanism steering wheel 9 is fixed on vertical fin illiteracy
On skin 25, linkage one end is connected with steering wheel rocking arm 20, and the other end and the rotating shaft 8 of linkage are connected；The inclining rotary mechanism
Steering wheel 9 is verted by the drivening rod mechanism drive shaft 8 of steering wheel rocking arm 20, realizes that latter two puts synchronously verting for rotor 10.
Avionics system component includes power supervisor and two sets of electric power systems, under the control of power supervisor, two sets of confessions
Electric system is respectively that preposition rotor motor 13 and rearmounted rotor motor 24 are powered.
The fixation contour of flange of electronic compound rotor aircraft described in present embodiment uses high mounted wing, t-tail arrangement.
Linkage described in present embodiment includes connecting rod 21 and collar connecting rod 22；The steering wheel rocking arm 20, which is connected in, to incline
On rotation mechanism steering wheel 9 and positioned at the side of vertical fin 18, collar connecting rod 22 is fixed in rotating shaft 8 and contacted with tee pipe fitting 23 pair
Together, the steering wheel rocking arm 20 is parallel with collar connecting rod 22 and is connected by connecting rod 21；Inclining rotary mechanism steering wheel 9 passes through steering wheel rocking arm
20th, connecting rod 21 and collar connecting rod 22 make rotating shaft 8 and the rearmounted synchronous axial system of rotor 10.
The position of centre of gravity of electronic compound rotor aircraft described in present embodiment preposition rotor 2 and the wing of back-mounted rotary 10 it
Between, it is 1 that preposition rotor 2, which arrives the ratio between centroidal distance of aircraft with rearmounted rotor 10,：3, the preposition rotor carrying in VTOL
The 3/4 of required thrust, the 1/4 of thrust needed for rearmounted rotor offer.Make center of gravity away from rearmounted rotor, can be by reducing back-mounted rotary
The efficiency of dynamical system when the maximum thrust of the wing is to improve cruise.So that two rearmounted rotors add maximum thrust together to meet to fly
The acceleration of row device and requirement of climbing, the maximum thrust of single rearmounted rotor meet the cruise requirement of aircraft, two rearmounted rotors
Not only as rotor system power but also as the power of fixed-wing system, improve the utilization rate of dynamical system, reduce such
Deadweight of the aircraft in fixed-wing mode flight.
In present embodiment, as more rotor modes when setting electronic composite wing aircraft vertical landing and hovering, by revolving more
The transition process of the wing to fixed-wing is referred to as transition mode, is fixed-wing pattern when climbing and cruising.
Under more rotor modes, power supervisor controls two preposition rotor motors 13 to drive two preposition rotors 2 respectively,
Two rearmounted rotor motors 24 drive two rearmounted rotors 10 to work respectively；
Under transition mode, when accelerating, inclining rotary mechanism controls two rearmounted rotors 10 synchronously to tilt forward 30 degree, in the shape
Aircraft level is maintained to accelerate to stalling speed under state；
After horizontal velocity exceedes stalling speed, four sets of dynamical system Close Alls, lead to during aircraft gliding
Cross inclining rotary mechanism and continue to tilt forward rearmounted rotor 10 to level, start two rearmounted rotors 10 immediately after and aircraft is carried out
Accelerate or climb, preposition rotor 2 no longer works.
After transition mode terminates, inclining rotary mechanism drives two rearmounted rotors 10 to tilt forward to horizontality, aircraft
Enter fixed-wing pattern；
Under fixed-wing pattern, when aircraft is in climb mode, power supervisor controls two rearmounted rotors 10 all works
Make, when aircraft is in cruising condition, power supervisor controls a rearmounted rotor 10 to work.
Preposition rotor 2 described in present embodiment only uses in more rotor modes and transition mode, need to provide larger push away
Power, to reduce its power in landing, the oar of large-size can be used.Rearmounted rotor is in more rotor modes, transition mode
Worked always with fixed-wing pattern, it is desirable to provide thrust it is smaller, for reduce oar cruise when resistance, rearmounted rotor
Oar diameter is unsuitable excessive.Because the maximum thrust of preposition rotor 2 and rearmounted rotor 10 has big difference, the motor model selected requires
There must be two sets of electric power systems.
The rotor plane of rearmounted rotor 10 described in present embodiment is located at the lower section of horizontal tail 16, the rotor of preposition rotor 2
For plane in the top of wing 1, the rotor diameter of the rearmounted rotor 10 is less than the rotor diameter of preposition rotor 2, rearmounted rotor 10
Between wheelbase be less than wheelbase between preposition rotor 2, and two rearmounted rotors have 10 degree of the upper counterangle, so when in fixation
During the wing pattern cruise only rearmounted work of rotor 10, the intersection point of axis of its thrust line with crossing center of gravity is in aircraft center of gravity
Before at 10mm.Because the presence at the upper counterangle reduces single rearmounted rotor as yawing caused by cruising power,
But a side force component is thus had, the electronic compound rotor aircraft there can be one 1 degree or so of rolling all the time when normaling cruise
Corner flies to offset the side force component.The efficiency of its dynamical system when the single rearmounted rotor of fixed-wing pattern cruises as power
70%~85% is can reach, dynamical system efficiency is higher.
Embodiment two, illustrate present embodiment with reference to Fig. 3 to Fig. 5, present embodiment is embodiment one
The method of work of described electronic compound rotor aircraft：
Aircraft is in more rotor modes when taking off, and power supervisor controls preposition rotor motor 13 and rearmounted rotor motor
24 start work, and inclining rotary mechanism two rearmounted rotors 10 of maintenance make a concerted effort straight up, when upward pulling force is more than gravity to fly
Row device starts to take off, and the flight controller of aircraft controls the appearance of electronic compound rotor aircraft by adjusting the rotating speed of each rotor
State and position.
Take off vertically after certain altitude, i.e.,：The more rotor mode departure time about 10s, into transition mode, inclining rotary mechanism
The drive link mechanism of steering wheel 9 drives rotating shaft 8 to vert, so as to drive rearmounted rotor motor 24 and rearmounted rotor 10 to tilt forward 30
Degree, now the horizontal pull of rearmounted rotor 10 accelerates to aircraft horizontal direction, the component of rearmounted rotor vertical direction power
For keeping the posture of aircraft, the vertical pulling force of rearmounted rotor 10 keeps the appearance of aircraft together with the pulling force of preposition rotor 2
State, aircraft level is maintained to accelerate to stalling speed in this condition；About 15 seconds flight time of transition mode.
After the horizontal velocity of aircraft exceedes stalling speed, transition mode terminates；Power supervisor control driving two
The preposition rotor motor 13 of individual preposition rotor 2 is stopped, while aircraft controls two rearmounted rotor electricity during gliding
Machine 24 is first stopped, and is again started up after the rearmounted rotor 10 of inclining rotary mechanism driving turned forward in 1 second and goes to horizontality
Rearmounted rotor motor 24 works, now into fixed-wing pattern,
Aircraft two rearmounted rotor motors 24 during climbing still work under fixed-wing pattern, are climbing to patrolling
After flying height degree, power supervisor controls rearmounted rotor motor 24 1 to be stopped, and another is as the power to cruise.
After it will reach landing point after electronic compound rotor aircraft has performed task, the electronic compound rotor aircraft first drops
To 100 meters of height, aircraft draws the angle of attack to be decelerated to stalling speed in fixed-wing pattern, after now power supervisor control closes two
Rotor motor 24 is put, inclining rotary mechanism drove two rearmounted rotors 10 to retreat in 1 second and goes to vertical, then startup two simultaneously
Preposition rotor motor 13 and two rearmounted rotor motors 24, now electronic compound rotor aircraft enter more rotor modes, then with
More rotor modes drop to appointed place.
Aircraft described in present embodiment can ensure total constant feelings of battery weight according to different mission requirements
It can be hovered the time by the proportion relation of the supplying cell of rotor motor before and after adjustment so as to obtain different more rotors under condition
With the combination in fixed-wing cruising time.
Aircraft described in present embodiment had both reduced more rotor system deadweights during fixed-wing cruise, while improved again
The utilization rate of dynamical system, while the efficiency of dynamical system when fixed-wing cruises can also be improved so that the endurance of such aircraft
Performance is optimal.
Although above description describe the embodiment of the present invention, it is noted that for those skilled in the art
For, some improvement can also be made under the premise without departing from the principles of the invention, and such as rearmounted tilting rotor is in more rotor modes
Produce downward thrust, verted after back-mounted rotary flapwise during transition mode, these improvement also should be regarded as protection scope of the present invention.
Claims (8)
1. electronic compound rotor aircraft, including fixed-wing component, the fixed-wing component includes wing (1), fuselage (13), shoe
Bar (11), vertical fin (18), horizontal tail (16) and avionics system；The vertical fin (18) is connected with fuselage (3) by tail supporting rod (11), is put down
Tail (16) is symmetrically mounted on above vertical fin (18)；
It is characterized in that in addition to rotating shaft (8), rotor assemblies and inclining rotary mechanism, the rotor assemblies include two preposition rotors (2)
With two rearmounted rotors (10), the preposition rotor (2) and rearmounted rotor (10) respectively by preposition rotor motor (13) and after
Rotor motor (24) driving is put, the preposition rotor motor (13) is symmetrically and fixedly mounted to machine by preposition flight support bar (12)
On the wing (1) of body (3) both sides, rearmounted rotor motor (24) is fixedly mounted on the both ends of rotating shaft (8)；
The rotor plane keep level of the preposition rotor (2)；The rotating shaft (8) is arranged on tail supporting rod by tee pipe fitting (23)
(11) end, the rotor plane of the rearmounted rotor (10) set 10 degree of the upper counterangle；
The avionics system includes power supervisor and two sets of electric power systems, and a set of electric power system supplies for preposition rotor motor (13)
Electricity, another set of electric power system are powered for rearmounted rotor motor (24)；
The inclining rotary mechanism includes inclining rotary mechanism steering wheel (9) and linkage, and the inclining rotary mechanism steering wheel (9) is fixed on vertical fin illiteracy
On skin (25), linkage one end is connected with steering wheel rocking arm (20), and the other end and the rotating shaft (8) of linkage are connected；It is described to incline
Rotation mechanism steering wheel (9) is verted by steering wheel rocking arm (20) drivening rod mechanism drive shaft (8), realizes that latter two puts rotor (10)
Synchronously vert.
2. electronic compound rotor aircraft according to claim 1, it is characterised in that the fixed-wing component also includes inner side
Aileron (4), outer aileron (5), elevator (6) and rudder (7), the inner aileron (4) are symmetrically mounted in wing (1)
Side, outer aileron (5) are symmetrically mounted on the outside of wing (1), and the inner aileron (4) and outer aileron (5) pass through inner side respectively
Aileron steering wheel (14) and outer aileron steering wheel (15) drive control rolling；
The elevator (6) and rudder (7) control wing by elevator steering wheel (17) and rudder steering wheel (19) respectively
Pitching and yaw rotation.
3. electronic compound rotor aircraft according to claim 1, it is characterised in that being located at for the rearmounted rotor (10) is flat
The lower section of tail (16), the rotor plane of preposition rotor (2) is in the top of wing (1), the rotor diameter of the rearmounted rotor (10)
Less than the rotor diameter of preposition rotor (2), the wheelbase between rearmounted rotor (10) is less than the wheelbase between preposition rotor (2).
4. electronic compound rotor aircraft according to claim 1, it is characterised in that the position of centre of gravity of the aircraft is preposition
Between rotor (2) and rearmounted rotor (10), it is 1 that preposition rotor (2), which arrives the ratio between centroidal distance of aircraft with rearmounted rotor (10),：
3。
5. electronic compound rotor aircraft according to claim 1, it is characterised in that the linkage includes connecting rod (21)
With collar connecting rod (22)；The steering wheel rocking arm (20) is connected on inclining rotary mechanism steering wheel (9) and positioned at the side of vertical fin (18), axle
Ring connecting rod (22), which is fixed in rotating shaft (8) and contacted with tee pipe fitting (23), to align, the steering wheel rocking arm (20) and collar connecting rod
(22) it is parallel and pass through connecting rod (21) connect；Inclining rotary mechanism steering wheel (9) passes through steering wheel rocking arm (20), connecting rod (21) and collar connecting rod
(22) rotating shaft (8) and rearmounted rotor (10) synchronous axial system are made.
6. electronic compound rotor aircraft according to claim 1, it is characterised in that when inclining rotary mechanism controls rearmounted rotor
(10) turning forward after turning 90 degrees, the thrust line of rearmounted rotor (10) is with crossing the axis of aircraft center of gravity in same plane, and two
The intersection point of line is in front of center of gravity at 10mm.
7. electronic compound rotor aircraft according to claim 1, it is characterised in that characterized in that, it is electronic multiple to set this
It is more rotor modes when closing rotor aircraft VTOL and hovering, stage die is referred to as by the transition process of more rotors to fixed-wing
Formula, it is fixed-wing pattern when climbing and cruising.
8. electronic compound rotor aircraft according to claim 7, it is characterised in that under more rotor modes, power management
Device controls two preposition rotor motors (13) to drive two preposition rotors (2) respectively, and two rearmounted rotor motors (24) are driven respectively
Dynamic two rearmounted rotor (10) work；
Under transition mode, when accelerating, inclining rotary mechanism controls two rearmounted rotors (10) synchronously to tilt forward 30 degree, in the state
Lower maintenance aircraft level accelerates to stalling speed；
After transition mode terminates, inclining rotary mechanism drives two rearmounted rotors (10) to tilt forward to horizontality, aircraft entrance
Fixed-wing pattern；
Under fixed-wing pattern, when aircraft is in climb mode, power supervisor controls two rearmounted rotors (10) all to work,
When aircraft is in cruising condition, power supervisor controls rearmounted rotor (10) job.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108275263A (en) * | 2018-03-14 | 2018-07-13 | 长沙市云智航科技有限公司 | A kind of manned more rotor flying vehicles |
| CN109131867A (en) * | 2018-07-18 | 2019-01-04 | 深圳筋斗云智能科技有限公司 | Aircraft |
| CN110683046A (en) * | 2018-07-04 | 2020-01-14 | 保时捷股份公司 | Aircraft with a flight control device |
| CN110683059A (en) * | 2018-07-04 | 2020-01-14 | 保时捷股份公司 | Aircraft with a flight control device |
| CN110683050A (en) * | 2018-07-04 | 2020-01-14 | 保时捷股份公司 | Aircraft with a flight control device |
| CN113165732A (en) * | 2018-11-30 | 2021-07-23 | 斯凯卡诺公司 | Aircraft with enhanced pitch control and interchangeable components |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB616227A (en) * | 1946-08-30 | 1949-01-18 | Cierva Autogiro Co Ltd | Improvements in aircraft with sustaining rotors disposed forward and aft of the centre of gravity |
| JP2006051841A (en) * | 2004-08-09 | 2006-02-23 | Ishikawajima Harima Heavy Ind Co Ltd | Small sized flying device |
| US20110303795A1 (en) * | 2009-10-09 | 2011-12-15 | Richard David Oliver | Three-wing, six tilt-propulsion unit, vtol aircraft |
| US20120043413A1 (en) * | 2005-10-18 | 2012-02-23 | Smith Frick A | Apparatus and method for vertical take-off and landing aircraft |
| US20120091257A1 (en) * | 2009-05-27 | 2012-04-19 | Israel Aerospace Industries Ltd. | Air vehicle |
| CN204507265U (en) * | 2015-02-12 | 2015-07-29 | 中电科（德阳广汉）特种飞机系统工程有限公司 | Be with the multi-rotor aerocraft of the fixed-wing that verts |
| CN105438463A (en) * | 2015-11-30 | 2016-03-30 | 珞石（北京）科技有限公司 | Quad tilt-rotor aircraft |
| CN105480416A (en) * | 2016-01-18 | 2016-04-13 | 南京信息工程大学 | Unmanned aerial vehicle with tilted rotors |
| CN105539835A (en) * | 2016-01-18 | 2016-05-04 | 成都纵横自动化技术有限公司 | Composite-wing vertical take-off and landing aircraft |
| CN105752345A (en) * | 2016-03-18 | 2016-07-13 | 西安交通大学 | Large load long duration multifunctional aircraft for operation |
| CN205396533U (en) * | 2016-03-04 | 2016-07-27 | 沈阳上博智拓科技有限公司 | Rotorcraft unmanned aerial vehicle wing and rotorcraft unmanned aerial vehicle that verts vert |
| CN205661659U (en) * | 2016-05-09 | 2016-10-26 | 中国科学院沈阳自动化研究所 | Electronic multiaxis rotor unmanned aerial vehicle system of verting |
-
2017
- 2017-03-20 CN CN201710165753.1A patent/CN107416200B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB616227A (en) * | 1946-08-30 | 1949-01-18 | Cierva Autogiro Co Ltd | Improvements in aircraft with sustaining rotors disposed forward and aft of the centre of gravity |
| JP2006051841A (en) * | 2004-08-09 | 2006-02-23 | Ishikawajima Harima Heavy Ind Co Ltd | Small sized flying device |
| US20120043413A1 (en) * | 2005-10-18 | 2012-02-23 | Smith Frick A | Apparatus and method for vertical take-off and landing aircraft |
| US20120091257A1 (en) * | 2009-05-27 | 2012-04-19 | Israel Aerospace Industries Ltd. | Air vehicle |
| US20110303795A1 (en) * | 2009-10-09 | 2011-12-15 | Richard David Oliver | Three-wing, six tilt-propulsion unit, vtol aircraft |
| CN204507265U (en) * | 2015-02-12 | 2015-07-29 | 中电科（德阳广汉）特种飞机系统工程有限公司 | Be with the multi-rotor aerocraft of the fixed-wing that verts |
| CN105438463A (en) * | 2015-11-30 | 2016-03-30 | 珞石（北京）科技有限公司 | Quad tilt-rotor aircraft |
| CN105480416A (en) * | 2016-01-18 | 2016-04-13 | 南京信息工程大学 | Unmanned aerial vehicle with tilted rotors |
| CN105539835A (en) * | 2016-01-18 | 2016-05-04 | 成都纵横自动化技术有限公司 | Composite-wing vertical take-off and landing aircraft |
| CN205396533U (en) * | 2016-03-04 | 2016-07-27 | 沈阳上博智拓科技有限公司 | Rotorcraft unmanned aerial vehicle wing and rotorcraft unmanned aerial vehicle that verts vert |
| CN105752345A (en) * | 2016-03-18 | 2016-07-13 | 西安交通大学 | Large load long duration multifunctional aircraft for operation |
| CN205661659U (en) * | 2016-05-09 | 2016-10-26 | 中国科学院沈阳自动化研究所 | Electronic multiaxis rotor unmanned aerial vehicle system of verting |
Non-Patent Citations (1)
| Title |
|---|
| 万佳等: "机翼位置对复合式直升机旋翼-机翼干扰的影响", 《北京航空航天大学学报》 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108275263A (en) * | 2018-03-14 | 2018-07-13 | 长沙市云智航科技有限公司 | A kind of manned more rotor flying vehicles |
| CN110683046A (en) * | 2018-07-04 | 2020-01-14 | 保时捷股份公司 | Aircraft with a flight control device |
| CN110683059A (en) * | 2018-07-04 | 2020-01-14 | 保时捷股份公司 | Aircraft with a flight control device |
| CN110683050A (en) * | 2018-07-04 | 2020-01-14 | 保时捷股份公司 | Aircraft with a flight control device |
| CN109131867A (en) * | 2018-07-18 | 2019-01-04 | 深圳筋斗云智能科技有限公司 | Aircraft |
| CN109131867B (en) * | 2018-07-18 | 2023-10-27 | 深圳筋斗云智能科技有限公司 | Aircraft with a plurality of aircraft body |
| CN113165732A (en) * | 2018-11-30 | 2021-07-23 | 斯凯卡诺公司 | Aircraft with enhanced pitch control and interchangeable components |
| CN113165732B (en) * | 2018-11-30 | 2022-10-28 | 斯凯卡诺公司 | Aircraft with enhanced pitch control and interchangeable components |
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| CN107416200B (en) | 2023-03-21 |
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