CN107757876A - A kind of aircraft - Google Patents
A kind of aircraft Download PDFInfo
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- CN107757876A CN107757876A CN201711000229.5A CN201711000229A CN107757876A CN 107757876 A CN107757876 A CN 107757876A CN 201711000229 A CN201711000229 A CN 201711000229A CN 107757876 A CN107757876 A CN 107757876A
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- 230000001105 regulatory effect Effects 0.000 claims abstract description 25
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Abstract
The present invention relates to technical field of aircraft design, provide a kind of aircraft, including fuselage, preceding wing, wing afterwards, first power packages and the second power packages, wing mutually staggers with preceding wing on x-axis direction and z-axis direction afterwards, first power packages and the second power packages are symmetrical arranged along the y-axis direction, preceding pitching regulating device is provided with preceding wing, rear pitching regulating device is provided with wing afterwards, the preceding pitching regulating device and rear pitching regulating device cooperate, for adjusting rolling movement of the aircraft around x-axis and the elevating movement around y-axis, so that aircraft can switch state of flight vertically or horizontally in flight course.No matter how the load of aircraft institute band arranges, machine gravity is with respect to any one direction of x, y, z all between above-mentioned forward and backward wing and forward and backward pitching regulating device, its handling and stability can be improved, and the adaptability to different loads, suitable for the uneven mission payload of distribution of weight.
Description
Technical field
The present invention relates to technical field of aircraft design, more particularly to a kind of aircraft.
Background technology
Unmanned vehicle has the advantage such as small volume, low cost, easy to use, low to environmental requirement and extensive because of it
Applied to logistics transportation, high-tension bus-bar, oil-gas pipeline inspection, geological prospecting, environmental monitoring, the fire prevention of deep woods, precision agriculture, frontier defense
In the fields such as patrol.Unmanned vehicle can be divided into fixed-wing and the major class of rotor two：Fixed Wing AirVehicle load-carrying is big, energy of continuing a journey
Power is strong, but needs sliding race landing, higher to SITE AND SPACE REQUIREMENTS；Gyroplane can VTOL, any hovering, not by place and
Space limits, but load-carrying is small, and endurance is weak.Therefore, fixed-wing is combined with rotor technology is to solve VTOL simultaneously, appoint
Meaning hovering, heavy－duty, a kind of trend of long continuation of the journey.
Prior art provides the aircraft that a variety of more rotors are combined with fixed-wing, such as：The first is using deflectable
Rotor, in VTOL, propeller disk is horizontally oriented, produce lift, lifting aircraft；Turn to put down rotation of verting when flying
The wing, making rotor card vertical, so as to produce thrust, promote aircraft horizontal flight, this aircraft layout structure is complicated, due to
Gyroscopic effect, it is difficult to maximize, very high to structural requirement, flight control system is complicated.Second is to fly two with flat using VTOL
Set system, the rotor lifting of use level card during VTOL, put down horizontal card when flying rotor stalling and vertical card
Rotor works, and promotes aircraft to put down and flies, and this layout all some motor and propellers when hovering and being flat winged leave unused, and cause
The increase of invalid load and resistance, load and endurance substantially reduce.The third is X-type wing vertical landing cloth
Office, this layout is simple, but a vertical aerofoil leaves unused after turning flat and flying, and causes lift-drag ratio to substantially reduce, endurance subtracts significantly
It is small.4th kind is flying wing type vertical landing layout, the requirement of the flight stability of this layout to unmanned plane position of centre of gravity
It is excessively harsh, the installation of mission payload is not easy to, can not more adapt to variously-shaped in the logistics transportation and object of distribution of weight
Carrying.Therefore, the technical problem that although prior art solves VTOL, arbitrarily hovered, but the shortcomings that following also be present：
Complicated mechanical rotation design, causes potential safety hazard and technical costs increase；The power to be left unused during cruise and aerofoil increase
Cruise drag, so as to seriously reduce load-carrying and endurance；It is excessively harsh to center of gravity status requirement, it is not easy to mission payload
Placement.Except above mentioned problem, aircraft is in load transportation, due to the shape of its Dead Weight Cargo and not knowing for position of centre of gravity
Property so that aircraft also faces another question, that is, any change of the aircraft center of gravity brought by goods influences
The smooth flight of aircraft.Accordingly, it is desirable to provide a kind of technical scheme is to solve the above problems.
The content of the invention
The technical problems to be solved by the invention are to provide a kind of aircraft simple in construction, and suitable for distribution of weight not
Uniform mission payload.
Technical scheme is used by the present invention solves above-mentioned technical problem：
A kind of aircraft, including fuselage, preceding wing, rear wing, the first power packages and the second power packages are provided, before described
Wing is respectively fixed on the fuselage with the rear wing, and the rear wing is with the preceding wing in x-axis direction and z-axis side
Mutually stagger upwards；First power packages and second power packages are symmetrical arranged along the y-axis direction, for being carried for aircraft
For power；Preceding pitching regulating device is provided with the preceding wing, rear pitching regulating device is provided with the rear wing, it is described
Preceding pitching regulating device and the rear pitching regulating device cooperate, for adjusting aircraft around the rolling movement of x-axis and around y
The elevating movement of axle.
As the improvement of above-mentioned technical proposal, the preceding wing includes machine before wing and second before first symmetrically
The wing, it is described after wing include after symmetrical first wing after wing and second, wing after wing and first before described first
Positioned at the same side of the fuselage, wing is located at the opposite side of fuselage after wing and described second before described second.
As the further improvement of above-mentioned technical proposal, the preceding wing and it is described after wing be parallel to each other and along y-axis side
To extension.
As the further improvement of above-mentioned technical proposal, before the preceding pitching regulating device includes first before rudder face and second
Rudder face, the first preceding rudder face is arranged on the rear edge of the described first preceding wing and wing can rotated before described first, described
Second preceding rudder face the rear edge that the described second preceding wing is set and can before described second wing rotation, first front rudder
Rudder face is symmetrical before face and described second；Rudder face after rudder face and second, described after pitching regulating device includes first after described
Rudder face sets the rear edge of wing after first in the rear after first, and wing can be rotated after described first, after described second
Rudder face is arranged on the rear edge of wing after described second, and wing can be rotated after described second, rudder face and institute after described first
Rudder face is symmetrical after stating second；Before described first before rudder face, described second after rudder face, described first after rudder face and described second
Rudder face moves independently of each other.
As the further improvement of above-mentioned technical proposal, first power packages include the first front propeller device and first
Rear screw shaft device, the first front propeller device are correspondingly arranged at the front of rudder face before described first, spiral shell after described first
Rotation oar device is correspondingly arranged at the front of rudder face after described first；Second power packages include the second front propeller device and the
Two rear screw shaft devices, the second front propeller device are correspondingly arranged at the front of rudder face before described second, after described second
Propeller set is correspondingly arranged at the front of rudder face after described second；The first front propeller device, first rear screw
Oar device, the second front propeller device and the second rear screw shaft device rotate around x-axis.
As the further improvement of above-mentioned technical proposal, the first front propeller device and first rear screw shaft dress
The steering put is identical, and the second front propeller device is identical with the steering of the second rear screw shaft device, also, described
Steering and the spiral shell after the second front propeller device, described second of one front propeller device, the first rear screw shaft device
The steering for revolving oar device is opposite.
As the further improvement of above-mentioned technical proposal, the first front propeller device, first rear screw shaft dress
Put, the second front propeller device and the second rear screw shaft device move independently of each other.
As the further improvement of above-mentioned technical proposal, the first front propeller device and first rear screw shaft dress
Put and be synchronized with the movement；The second front propeller device and the second rear screw shaft device are synchronized with the movement.
As the further improvement of above-mentioned technical proposal, before first power packages include one or two or multiple first
Propeller set, first power packages include one or two or multiple first rear screw shaft devices, second power packages
Including one or two or multiple second front propeller devices, after second power packages include one or two or multiple second
Propeller set, second power packages and first power packages are symmetrical.
As the further improvement of above-mentioned technical proposal, the fuselage is connected in the preceding wing and the rear wing
Portion so that aircraft is integrally in I-shaped.
As the further improvement of above-mentioned technical proposal, the fuselage includes the first housing and the second housing, and described first
One end of the body connection preceding wing and the rear wing, the second housing connection preceding wing and the rear wing
The other end.
The beneficial effects of the invention are as follows：
The invention provides a kind of aircraft, including fuselage, preceding wing, rear wing, the first power packages and the second power packages,
Preceding wing is respectively fixed on fuselage with rear wing, and rear wing and preceding wing are mutually wrong on x-axis direction and z-axis direction
Open；First power packages and the second power packages are symmetrical arranged along the y-axis direction, for providing power for the flight of aircraft；Preceding wing
On be provided with preceding pitching regulating device, rear pitching regulating device is provided with rear wing, the preceding pitching regulating device and rear pitching
Adjusting means cooperates, for adjusting rolling maneuver of the aircraft around x-axis and the pitching motion around y-axis so that aircraft can
Diverter shaft flies nonstop to row or level flight condition in flight course.Above-mentioned preceding wing, rear wing, the first power packages and the second power
The setting of group make it that no matter how the load of aircraft institute band arranges that machine gravity can all be located with respect to any one direction of x, y, z
Between above-mentioned forward and backward wing and above-mentioned forward and backward pitching regulating device, its handling and stability can be improved, and to difference
The adaptability of load, suitable for the uneven mission payload of distribution of weight.
Brief description of the drawings
Technical scheme in order to illustrate the embodiments of the present invention more clearly, make required in being described below to embodiment
Accompanying drawing briefly describes：
Fig. 1 is the dimensional structure diagram of first embodiment of the invention；
Fig. 2 is the front view of embodiment described in Fig. 1；
Fig. 3 is Fig. 2 left view；
Fig. 4 is Fig. 2 top view；
Fig. 5 is the dimensional structure diagram of undercarriage in first embodiment of the invention；
Fig. 6 is the dimensional structure diagram of second embodiment of the invention；
Fig. 7 is the front view of embodiment described in Fig. 6；
Fig. 8 is Fig. 7 left view；
Fig. 9 is the dimensional structure diagram of third embodiment of the invention；
Figure 10 is the front view of embodiment described in Fig. 9；
Figure 11 is Fig. 9 left view.
Embodiment
Carried out below with reference to the design of embodiment and accompanying drawing to the present invention, concrete structure and caused technique effect clear
Chu, it is fully described by, to be completely understood by the purpose of the present invention, feature and effect.Obviously, described embodiment is this hair
Bright part of the embodiment, rather than whole embodiments, based on embodiments of the invention, those skilled in the art is not paying
The other embodiment obtained on the premise of creative work, belongs to the scope of protection of the invention.In addition, it is related in patent
All connection/annexations, not singly refer to component and directly connect, and refer to can according to specific implementation situation, by addition or
Couple auxiliary is reduced, to form more excellent draw bail.The orientation such as upper and lower, left and right involved by the present invention describe
For the mutual alignment relation of each part of the present invention in accompanying drawing.Each technical characteristic in the present invention, not
Can be with combination of interactions on the premise of conflicting conflict.
Fig. 1~5 respectively illustrate dimensional structure diagram, front view, left view, the vertical view of first embodiment of the invention
The structural representation of figure and undercarriage；Referring to Fig. 1~5, the right angle in the upper right corner is sat in x-axis, y-axis and z-axis reference chart
Mark system.As schemed, in the present embodiment, aircraft includes preceding wing 100, rear wing 200, the first power packages 300, the second power packages
400 and fuselage 500.Preceding wing 100 is each attached on fuselage 500 with rear wing 200, and the two is parallel to each other and prolonged along the y-axis direction
Stretch, fuselage 500 connects the middle part of preceding wing 100 and the middle part of rear wing 200 so that aircraft is integrally in I-shaped.
Wing 200 is L with the relative distance of preceding wing 100 in the direction of the x axis afterwards, rear wing 200 in the z-axis direction with it is preceding
The relative distance of wing 100 is D, and L, D are not zero, and rear wing 200 and preceding wing 100 are homogeneous on x-axis direction and z-axis direction
Mutually stagger, interfered with reducing, and lift can be provided simultaneously, so as to reduce whole wing area, increase lift-drag ratio, increase
Heavy－duty and endurance, L, D big I are rationally set according to the overall structure of aerocraft real.In the present embodiment,
Fuselage includes front fuselage 510 and back body 520, and preceding wing 100 is fixed on the bottom of front fuselage 510, and rear wing 200 is solid
The top of back body 520 is scheduled on, when aircraft is in the posture of horizontal flight, fuselage is horizontal, and rear wing 200 is higher than
Preceding wing 100, for the head of front fuselage 510 to bottom deflection, the afterbody of back body 520 is to top deflection so that overall in stream
Line style fuselage.Preceding wing 100 effectively produces lift and controling power with rear wing 200, compared with conventional in layout, can reduce each
The area of wing, reduce wing chord length, so that aspect ratio increases, induced drag reduces, lift-drag ratio improves, and then improve and carry
Weight and endurance.
In the specific implementation, preceding wing 100 can be also fixed on to the top of the front end of fuselage 500, rear wing 200 as needed
It is fixed on the bottom of the rear end of fuselage 500 so that when aircraft is in the posture of horizontal flight, rear wing 200 is less than preceding wing
100, its effect is identical with such scheme.
Preceding pitching regulating device is provided with preceding wing 100, rear pitching regulating device is provided with rear wing 200, before this
Pitching regulating device and rear pitching regulating device are used to adjust aircraft in flight around the rolling maneuver of x-axis and bowing around y-axis
Face upward action.
In the present embodiment, wing 120 before wing 110 and second before preceding wing 100 includes first, wing 110 before first
With second before wing 120 it is symmetrical relative to fuselage 500, and extend in the y-direction.Wing 210 and the after wing 200 includes first afterwards
Wing 220 after two, wing 220 is symmetrical relative to fuselage 500 after wing 210 and second after first, and extends in the y-direction.Specifically
During implementation, wing 210 can also be with y-axis at an angle after wing 110 and first before first, the He of wing 120 before same second
After second wing 220 can also with y-axis at an angle, before only needing first before wing 110 and second wing 120 relative to fuselage
500 is symmetrical, and wing 220 is symmetrical relative to fuselage 500 after wing 210 and second after first.
Rudder face 140 before rudder face 130 and second before front rudder face includes first, wing before rudder face 130 is arranged on first before first
110 rear edge, and wing 110 can be rotated in the y-direction before first；Rudder face 140 is arranged on wing 120 before second before second
Edge afterwards, and wing 120 can be rotated in the y-direction before second；The relative fuselage 500 of rudder face 140 before rudder face 130 and second before first
Symmetrically.
Rudder face 240 after rudder face 230 and second after rudder face includes first afterwards, wing after rudder face 230 is arranged on first after first
210 rear edge, and wing 210 can be rotated in the y-direction after first；Rudder face 240 is arranged on wing 220 after second after second
Edge afterwards, and wing 220 can be rotated in the y-direction after second；After first after rudder face 230 and second rudder face 240 relative to fuselage
500 is symmetrical.
The phase of rudder face 240 4 after rudder face 230 and second after rudder face 140, first before rudder face 130, second before above-mentioned first
Mutual self-movement, does not interfere with each other.
Aircraft around x-axis rolling moment by first before rudder face 140, before rudder face 230 and second after rudder face 130, first
Rudder face 240 is realized with respect to the deflection angle difference of wing after two, by controlling the differential seat angle to control aircraft to be rolled around x-axis
Transhipment is dynamic.No matter how the center of gravity of load-carrying changes, and aircraft center of gravity is all in rudder face 230 and after rudder face 130, first before first
Any position before two after rudder face 140, second between 240 two groups of rudder faces of rudder face, couple moment preserving, for controlling the PID of rolling
(Proportion Integration Differentiation:PID) fly control parameter without adjustment, subtract significantly
Light flight control system burden, increases flight stability.
Aircraft around y-axis pitching moment by first before rudder face 230, after rudder face 140 and first before rudder face 130, second
Rudder face 240 is realized with respect to the deflection angle difference of wing after two, by controlling the differential seat angle to control aircraft to be bowed around y-axis
Face upward motion.No matter how the center of gravity of load-carrying changes, and aircraft center of gravity is all in rudder face 140 and before rudder face 130, second before first
Any position after one after rudder face 230, second between 240 two groups of rudder faces of rudder face, couple moment preserving, for controlling the PID of rolling
Fly control parameter without adjustment, mitigate flight control system burden significantly, increase flight stability.
First power packages 300 and the second power packages 400 are used to provide power, and the difference for passing through the two for the flight of aircraft
Speed control aircraft carries out yawing rotation around z-axis.First power packages 300 include spiral shell after the first front propeller device 310 and first
Oar device 320 is revolved, the second power packages 400 include the second front propeller device 410 and the second rear screw shaft device 420.
The position of rudder face 130 is arranged on the front of wing 110 before first before first front propeller device 310 corresponding first,
And rotated around x-axis so that the first front propeller device 310 is located at the front of rudder face 130 before first, when the first front propeller device
During 310 rotation, it rotates rudder face 130 before the air-flow formed flows backwards through first, therefore, no matter aircraft is in state of flight also
Floating state, have enough air-flows flow through first before rudder face 130, so as to ensure control of the rudder face 130 to aircraft before first
System.
The position of rudder face 230 is arranged on the front of wing 210 after first after first rear screw shaft device 320 corresponding first,
And rotated around x-axis so that the first rear screw shaft device 320 is located at the front of rudder face 230 after first, when the first rear screw shaft device
During 320 rotation, it rotates rudder face 230 after the air-flow formed flows backwards through first, therefore, no matter aircraft is in state of flight also
Floating state, have enough air-flows flow through first after rudder face 230, so as to ensure control of the rudder face 230 to aircraft after first
System.
The position of rudder face 140 is arranged on the front of wing 120 before second before second front propeller device 410 corresponding second,
And rotated around x-axis so that the second front propeller device 410 is located at the front of rudder face 140 before second, when the second front propeller device
During 410 rotation, it rotates rudder face 140 before the air-flow formed flows backwards through second, therefore, no matter aircraft is in state of flight also
Floating state, have enough air-flows flow through second before rudder face 140, so as to ensure control of the rudder face 140 to aircraft before second
System.
Second rear screw shaft device 420 is correspondingly arranged at the front of rudder face after described second；So that the second rear screw shaft fills
420 fronts for being located at rudder face 240 after second are put, when the second rear screw shaft device 420 rotates, it rotates the air-flow formed backward
Rudder face 240 after flowing through second, therefore, no matter aircraft is in state of flight or floating state, there are enough air-flows to flow through
Rudder face 240 after second, so as to ensure control of the rudder face 240 to aircraft after second.
Above-mentioned the first front propeller device 310, the first rear screw shaft device 320, the second front propeller device 410 and
Two 420 4 sets of rear screw shaft device propellers are located at before wing, even if ensureing aircraft under static state, wing also can
Produce lift；Also, aforementioned four rudder face is located at edge after wing so that before four sets of propellers are located at rudder face, ensures that aircraft is in office
Under what posture, as long as propeller is in rotary state, rudder face just has enough air-flows by ensureing enough effect control aircrafts.
Spiral shell after first front propeller device 310, the first rear screw shaft device 320, the second front propeller device 410 and second
Rotation oar 420 4 sets of propeller sets of device are driven respectively by four drive devices so that four work independently from each other, mutually not shadow
Ring, redundancy can be improved, so as to lift security.Wherein, the first front propeller device 310 and the first rear screw shaft device 320
Steering it is identical, the second front propeller device 410 is identical with the steering of the second rear screw shaft device 420, also, spiral before first
Steering and the second front propeller device 410 the and the second rear screw shaft device of oar device 310, the first rear screw shaft device 320
420 steering is advantageous to aircraft on the contrary, so as to offset the unnecessary rolling moment in x-axis direction caused by power motor
Stabilized flight.When it is implemented, also can only set two sets of drive devices to be driven, wherein, first driving means pass through machinery
The first front propeller of device linkage driving device 310 and the first rear screw shaft device 320 rotate simultaneously, and the second drive device passes through
The second front propeller of mechanical device linkage driving device 410 and the second rear screw shaft device 420 rotate simultaneously, first driving means
It is opposite with the output speed of the second drive device.
In the present embodiment, the first power packages 300 include a first front propeller device 310 and the first rear screw dress
320 are put, the second power packages 400 include a second front propeller device 410 and a second rear screw shaft device 420, are having
In body implementation process, the quantity of propeller set can be arranged as required to, for example, the first power packages 300 may include one or two
Individual or multiple first front propeller devices 310 and one or two or multiple first rear screw shaft devices 320, accordingly, second
Power packages 400 be provided with second front propeller 410 device equal with the quantity of the first propeller set 310 and with the first rear screw
The second equal rear screw shaft device 420 of the quantity of oar device 320, and make the first power packages and the second power packages symmetrical.
Above-mentioned first power packages and the second power packages are provided by being placed in the propeller set in front of wing for aircraft
Propulsive force, in the specific implementation, the first power packages and the second power packages can also be placed in embedded propeller among wing,
The ducted fan or vector jet engine of embedded wing, to produce propulsive force.
Aircraft is filled around the yawing of z-axis by the first front propeller device 310, the first rear screw shaft of aircraft side
Put 320 to realize with the second front propeller device 410 of aircraft opposite side, the speed discrepancy of the second rear screw shaft device 420, pass through
The speed discrepancy is controlled so as to control aircraft to carry out yawing rotation around z-axis.No matter how the center of gravity of load-carrying changes, aircraft center of gravity
All in the first front propeller device 310, the first rear screw shaft device 320 and the second front propeller device 410, the second rear screw
Any position between 420 liang of propellers of oar device, couple moment preserving, the PID for controlling rolling fly control parameter without adjusting,
Mitigate flight control system burden significantly, increase flight stability.Also settable fixed fin and vertical rudder face, make to fly on fuselage
Row device has static stability on the yaw direction around z-axis.
Autonomous operation is realized by independent navigation and automatic control system.Three sets of burdensome systems built in automatic control system,
Flight reliability and security is substantially improved, automatic control system coordinates aforementioned four propeller simultaneously and four rudder faces are jointly complete
Controlled into flight, no matter how fuselage internal load arranges relative any one direction of x, y, z, and machine gravity can all be in above-mentioned four
Cover between propeller set and aforementioned four rudder face, its handling and stability, and the adaptability to different loads can be improved.
The aircraft of the present embodiment also includes undercarriage 600, as shown in figure 5, undercarriage 600 is arranged on the rear end of fuselage
520 bottoms, and can be rotated relative to fuselage 500, undercarriage can also be arranged on other positions.The undercarriage 600 is used in aircraft
Aircraft fuselage is supported during vertical state, it is easy to the vertical landing of aircraft on vertical vertical and ground, or for flying
Row device carries out sliding race landing in Horizontal Take-off and Landing.
Fig. 6~8 respectively illustrate dimensional structure diagram, front view and the left view of second embodiment of the invention, please
Referring concurrently to Fig. 6~8, the present embodiment is that the structure of fuselage is different from the difference of one embodiment, is specially：The present embodiment
In, fuselage 500 is the vertical stabilizer that both ends connect the preceding middle part of wing 100 and the middle part of rear wing 200 respectively so that aircraft is overall
In I-shaped.The fuselage can mitigate fuselage weight and resistance, and when aircraft is in level flight condition, fuselage 500 is inclination
Relative distance D be present in the relatively preceding wing 100 in z-axis direction in state, rear wing 200.Others set with above-mentioned first
Embodiment is identical, does not repeat herein.
Fig. 9~11 respectively illustrate dimensional structure diagram, front view and the left view of third embodiment of the invention, please
Referring concurrently to Fig. 9~11, the present embodiment is that the structure of fuselage is different from the difference of one embodiment, is specially：This
In embodiment, preceding wing 100 and rear wing 200 equal length, before first before wing 110 and second wing 120 relative to preceding machine
The middle part of the wing 100 is symmetrical, and wing 220 is symmetrical relative to the middle part of rear wing after wing 210 and second after first.Fuselage 500 wraps
The first housing 530 and the second housing 540 are included, the first housing 530 connects same one end of preceding wing 100 and rear wing 200, and second
Body 540 connects the other end of preceding wing 100 and rear wing 200 so that and aircraft is in integrally hollow, in the present embodiment,
One body 510 and the second housing 520 are vertical stabilizer, so that wing box structure is integrally formed in aircraft, can mitigate fuselage
Weight and resistance, and can play stabilization to preceding wing and rear wing.When aircraft is in level flight condition, the first machine
Body 530 and the second housing 540 are heeling condition, and rear wing 200 has relative distance D in the relatively preceding wing 100 in z-axis direction.
Others setting is identical with above-mentioned one embodiment, does not repeat herein.
The flight course of aircraft approximately as：
Vertical takeoff process：Ground is stood on vertically using itself tail structure (settable undercarriage is supported), is started
Above-mentioned four groups of power motors make aforementioned four propeller while worked, and increase rotating speed, when pulling force straight up is enough
Wait, aircraft, which is realized, to take off vertically；
Vertical hovering process：Such as disturbed by wind, aircraft by after rudder face 130, first before first rudder face 230 it is inclined
The Differential Control of the deflection angle of rudder face 240 realizes the roll stabilization in x-axis direction after rudder face 140, second before gyration and second,
Ensure that the rotation around x-axis does not occur for aircraft；Pass through the deflection angle and first of rudder face 140 before rudder face 130, second before first
The Differential Control of the deflection angle of rudder face 240 realizes that the pitching in y-axis direction is stable after rudder face 230, second afterwards, that is, keeps fuselage to begin
Eventually straight up, do not topple over；Pass through spiral before the first front propeller device 310, the first rear screw shaft device 320 and second
Oar device 410, the speed discrepancy of the second rear screw shaft device 420 realize that the driftage in z-axis direction is stable, i.e., aircraft will not be around z-axis
Swing or rotate.
Vertical hovering is transformed into level cruise process：Rudder face 140 is upward from current location before rudder face 130, second before first
Deflection with the lift of wing 100 before reducing, while after first after rudder face 230, second rudder face 240 from current location deflect down with
The lift of wing 200 after increase, so as to produce nose-down pitching moment, fuselage is deflected around y-axis, bow to bow and lie prone, until horizontality.
During fuselage rotates, as fuselage rotates, the thrust direction of aforementioned four propeller is also by switching to forward, progressively exist upwards
Horizontal direction accelerates, and completes vertical turn and equals winged process.
Cruise process：Aircraft around x-axis rolling moment by first before the front rudder of rudder face 230 and second after rudder face 130, first
Rudder face 240 is realized with respect to the deflection angle difference of wing behind face 140, second；Aircraft around y-axis pitching moment by first before rudder face
130th, rudder face 240 is realized with respect to the deflection angle difference of wing after rudder face 230, second after rudder face 140 and first before second；Aircraft
Around z-axis yawing by aircraft side the first front propeller device 310, the first rear screw shaft device 320 and aircraft
The second front propeller of opposite side device 410, the speed discrepancy of the second rear screw shaft device 420 are realized.In the event of air-dry disturb, also by
Aircraft is retracted expecting state by same mechanism.
Level cruise is transformed into vertical hovering process：Level cruise process is transformed on the contrary, first with above-mentioned vertical hovering
Rudder face 140 deflects down before preceding rudder face 130 and second, and rudder face 240 upward deflects after rudder face 230 and second after first, makes fuselage
Deflected around y-axis, new line is steeved, and this process horizontal velocity is gradually reduced, and the thrust of aforementioned four propeller is progressively turned by level
For vertically upward, until aircraft reaches vertical state.
Vertical drop process：Under vertical floating state, while the rotating speed of aforementioned four propeller is reduced, it is perpendicular so as to reduce
Straight upward pulling force, when pulling force is less than gravity, aircraft declines, and supported grounding is provided by aircraft tail structure or undercarriage
Landing.
Horizontal Take-off and Landing process：Aircraft can be placed horizontally at ground, use conventional aircraft as traditional aircraft
Undercarriage, pass through aforementioned four propeller and accelerate sliding to run landing.
Presently preferred embodiments of the present invention is above are only, but the present invention is not restricted to the embodiment, is familiar with this area
Technical staff can also make a variety of equivalent variations or replacement on the premise of without prejudice to spirit of the invention, these equivalent deformations
Or replace and be all contained in the application claim limited range.
Claims (11)
- A kind of 1. aircraft, it is characterised in that：Including fuselage, preceding wing, rear wing, the first power packages and the second power packages, institute Wing is respectively fixed on the fuselage with the rear wing before stating, and the rear wing is with the preceding wing in x-axis direction and z Mutually stagger on direction of principal axis；First power packages and second power packages are symmetrical arranged along the y-axis direction, for for flight Device provides power；Preceding pitching regulating device is provided with the preceding wing, rear pitching regulating device is provided with the rear wing, The preceding pitching regulating device and the rear pitching regulating device cooperate, for adjusting rolling movement of the aircraft around x-axis With the elevating movement around y-axis.
- 2. aircraft according to claim 1, it is characterised in that：The preceding wing includes wing before symmetrical first With second before wing, it is described after wing include after symmetrical first wing after wing and second, before described first wing and Wing is located at the same side of the fuselage after first, and wing is located at the another of fuselage after wing and described second before described second Side.
- 3. aircraft according to claim 2, it is characterised in that：The preceding wing and it is described after wing be parallel to each other and edge Y-axis direction extends.
- 4. aircraft according to claim 2, it is characterised in that：The preceding pitching regulating device include first before rudder face and Rudder face before second, the first preceding rudder face are arranged on the rear edge of the described first preceding wing and wing can turned before relatively described first It is dynamic, the second preceding rudder face be arranged on the rear edge of the described second preceding wing and can the wing rotation before described second, described the Rudder face is symmetrical before rudder face and described second before one；Rudder after rudder face and second after pitching regulating device includes first after described Face, rudder face sets the rear edge of wing after first in the rear after described first, and wing can be rotated after described first, described Rudder face is arranged on the rear edge of wing after described second after second, and wing can be rotated after described second, rudder after described first Rudder face is symmetrical behind face and described second；Rudder face and described after rudder face, described first before rudder face, described second before described first Rudder face moves independently of each other after second.
- 5. aircraft according to claim 4, it is characterised in that：First power packages include the first front propeller device With the first rear screw shaft device, the first front propeller device is correspondingly arranged at the front of rudder face before described first, and described One rear screw shaft device is correspondingly arranged at the front of rudder face after described first；Second power packages fill including the second front propeller Put with the second rear screw shaft device, the second front propeller device is correspondingly arranged at the front of rudder face before described second, described Second rear screw shaft device is correspondingly arranged at the front of rudder face after described second；The first front propeller device, described first Rear screw shaft device, the second front propeller device and the second rear screw shaft device rotate around x-axis.
- 6. aircraft according to claim 4, it is characterised in that：Spiral shell after the first front propeller device and described first The steering of rotation oar device is identical, and the second front propeller device is identical with the steering of the second rear screw shaft device, also, The first front propeller device, steering and the second front propeller device of the first rear screw shaft device, described the The steering of two rear screw shaft devices is opposite.
- 7. aircraft according to claim 6, it is characterised in that：Spiral shell after the first front propeller device, described first Rotation oar device, the second front propeller device and the second rear screw shaft device move independently of each other.
- 8. aircraft according to claim 6, it is characterised in that：Spiral shell after the first front propeller device and described first Rotation oar device is synchronized with the movement；The second front propeller device and the second rear screw shaft device are synchronized with the movement.
- 9. the aircraft according to any one of claim 5~8, it is characterised in that：First power packages include one Or two or more first front propeller devices, first power packages include one or two or multiple first rear screw shafts fill Put, second power packages include one or two or multiple second front propeller devices, and second power packages include one Or two or more second rear screw shaft devices, second power packages and first power packages are symmetrical.
- 10. aircraft according to claim 1, it is characterised in that：The fuselage connects the preceding wing and the rear machine The middle part of the wing so that aircraft is integrally in I-shaped.
- 11. aircraft according to claim 1, it is characterised in that：The fuselage includes the first housing and the second housing, institute State the first housing connect the preceding wing and it is described after wing one end, the second housing connect the preceding wing and it is described after The other end of wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711000229.5A CN107757876A (en) | 2017-10-24 | 2017-10-24 | A kind of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711000229.5A CN107757876A (en) | 2017-10-24 | 2017-10-24 | A kind of aircraft |
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| Publication Number | Publication Date |
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| CN107757876A true CN107757876A (en) | 2018-03-06 |
Family
ID=61269935
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711000229.5A Pending CN107757876A (en) | 2017-10-24 | 2017-10-24 | A kind of aircraft |
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| CN (1) | CN107757876A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639344A (en) * | 2018-06-27 | 2018-10-12 | 深圳市雷凌广通技术研发有限公司 | Unmanned aerial vehicle that equilibrium is good |
| EP4151525A1 (en) * | 2021-09-21 | 2023-03-22 | Textron Innovations Inc. | Convertible staggerwing aircraft having optimized hover power |
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| EP4151525A1 (en) * | 2021-09-21 | 2023-03-22 | Textron Innovations Inc. | Convertible staggerwing aircraft having optimized hover power |
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