CN104590555A - Electrodynamic multi-rotor helicopter - Google Patents
Electrodynamic multi-rotor helicopter Download PDFInfo
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- CN104590555A CN104590555A CN201510043472.XA CN201510043472A CN104590555A CN 104590555 A CN104590555 A CN 104590555A CN 201510043472 A CN201510043472 A CN 201510043472A CN 104590555 A CN104590555 A CN 104590555A
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- 230000007613 environmental effect Effects 0.000 description 1
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- 239000002917 insecticide Substances 0.000 description 1
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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
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- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention belongs to the field of general aircrafts, and particularly relates to an electrodynamic multi-rotor helicopter. The electrodynamic multi-rotor helicopter comprises a fuselage, power rotors, a rotor support arm, a undercarriage, an electric supply system and a flight control system, wherein even power rotors are arranged above the fuselage, each power rotor is installed on the upper part of the fuselage through the rotor support arm, the undercarriage is arranged at the lower part of the fuselage, the electric supply system and the flight control system are respectively installed in a battery cabin and a cockpit in the fuselage; the structures of the power rotors are the same, and the power rotor comprises a screw propeller, a drive motor and fairings; the drive motor is installed on the fuselage through the rotor support arm, the screw propeller is connected with the output end of the drive motor, and fairings are respectively arranged at the lower end of the drive motor and the upper end of the drive motor above the screw propeller. The helicopter disclosed by the invention is compact in structure, flexible in movement, and large in lift-weight ratio, and has the advantages of being strong in adaptability, safe and reliable, economical, environment-friendly, simple in control, and low in maintenance charge.
Description
Technical field
The invention belongs to all purpose aircraft field, specifically a kind of Electronmotive Force multirotor helicopter.
Background technology
Having can the function such as vertical takeoff and landing and hovering, especially can to obtain at numerous areas at the helicopter of low-latitude flying and apply more and more widely.Up to now, the helicopter with this kind of function has single-rotor helicopter, twin-rotor helicopter, tilt rotor helicopter type.But, these helicopters are due to the restriction of power system and drive system structure, the restriction of rotary wing changing pitch system mechanism and Jiang Pan pitch system mechanism, and keep the tail-rotor needed for balance or the restriction of tail gear, not only noise large, handle complicated, rise that anharmonic ratio is low, daily attention costly, also there is fuel oil pollution, and larger rotor easily causes the problems such as safety hazard to surrounding environment and ground staff.
Summary of the invention
In order to solve the problems referred to above that existing helicopter exists, the object of the present invention is to provide a kind of Electronmotive Force multirotor helicopter.
The object of the invention is to be achieved through the following technical solutions:
The present invention includes fuselage, power rotor, flight support arm, alighting gear, electric power supply system and flight control system, wherein the top of fuselage is along the circumferential direction evenly equipped with even number power rotor, each described power rotor is arranged on the top of fuselage respectively by flight support arm, the bottom of described fuselage is provided with alighting gear, and described electric power supply system and flight control system are installed in battery flat in fuselage, driving compartment respectively; Described power rotor is arranged with the horizontal axis Mirror Symmetry of fuselage working direction, and the described power rotor quantity of the horizontal axis left and right sides of described fuselage working direction is identical; Each described power rotor structure is identical, include screw propeller, drive motor and fairing, this drive motor is arranged on fuselage by described flight support arm, described screw propeller is connected with the mouth of drive motor, and lower end and the drive motor upper end be positioned at above screw propeller of described drive motor are all provided with fairing.
The present invention includes fuselage power rotor, flight support arm, alighting gear, electric power supply system and flight control system, wherein the top of fuselage is provided with even number power rotor, each described power rotor is arranged on the top of fuselage respectively by flight support arm, the bottom of described fuselage is provided with alighting gear, and described electric power supply system and flight control system are installed in battery flat in fuselage, driving compartment respectively; The power rotor quantity of the horizontal axis left and right sides of described fuselage working direction is identical, and arranges with the horizontal axis Mirror Symmetry of fuselage working direction; Each described power rotor structure is identical, include screw propeller, drive motor and fairing, this drive motor is arranged on fuselage by described flight support arm, described screw propeller is connected with the mouth of drive motor, and lower end and the drive motor upper end be positioned at above screw propeller of described drive motor are all provided with fairing.
Wherein: the hand of rotation of the screw propeller in adjacent two described power rotors is contrary, lift upwards, respectively by respective described drive motor Direct driver; The center of the power rotor group that each described power rotor forms all is positioned at above the center of gravity of fuselage; Described screw propeller is wheeled helical oar, comprise propeller hub, blade and culvert type annular ring, this propeller hub is connected with the mouth of described drive motor, and blade is multiple, along the circumferential direction uniform, blade root and the described propeller hub of each described blade are affixed, and the inwall of blade tip and described culvert type annular ring is affixed; The side projection of described fuselage is zhou duicheng tuxing, and axis of symmetry is the horizontal axis of described fuselage working direction; Each described flight support arm is stationary structure, is namely all fixed on fuselage; Or be accordion structure, be namely connected collapsibly with described fuselage, each described flight support arm all can upwards fold; Described alighting gear is slide-type, roller type or air-cushion type.
Advantage of the present invention and good effect are:
1. owing to present invention employs many rotors scheme, namely by the rotative speed of screw propeller in each power rotor of adjustment, just the control of Electronmotive Force multirotor helicopter flight attitude and flying speed can be realized, comparatively conventional helicopters, has deducted reducing gearbox system, machine driven system, pitch changing actuator, oar dish leaning device, movement connecting mechanism, tail-rotor or empennage isoequilibrium device; Therefore, volume is little, lightweight, load-carrying large, is not only easy to produce, cheap, and safeguard also simpler, expense is lower, handles simpler, applies safer.
2. because the screw propeller of power rotor of the present invention have employed wheeled helical oar, both the induced drag of blade tip inside can effectively have been reduced, reduce impulsive noise, improve dynamic efficiency, simultaneously, due to the cantilever beam structure of free rotor is changed into wheeled construction, each blade tip of screw propeller has been unified into one by culvert type annular ring, overcome the pneumatic distortion of blade tip, inhibit the formation of tip vortex, thus effectively improve the rotating speed of screw propeller, and the flying speed of raising helicopter, the flying power of enhancing helicopter are had great importance.
3. owing to present invention employs many rotors scheme and wheeled helical oar, effectively improve lift efficiency, thus, achieve the full driven by power of light helicopter, comparatively conventional helicopters more environmental protection, field of application will be more extensive, can be used for traffic patrolling, frontier defense patrol, forest patrol, security monitoring, medical aid, power engineering, explores in the air, the condition of a disaster supervision, to take photo by plane and agricultural is sowed seeds, industry-by-industry and the field such as to spray insecticide.
Accompanying drawing explanation
Figure 1A is the structural front view of the embodiment of the present invention one;
Figure 1B is the right elevation of Figure 1A;
Fig. 1 C is the birds-eye view of Figure 1B;
Fig. 2 A is the structural front view of the embodiment of the present invention two;
Fig. 2 B is the lateral plan of Fig. 2 A;
Fig. 2 C is the birds-eye view of Fig. 2 A;
Fig. 3 A is the structural front view of the embodiment of the present invention three;
Fig. 3 B is the right elevation of Fig. 3 A;
Fig. 3 C is the birds-eye view of Fig. 3 B;
Fig. 4 A is the structural front view of the embodiment of the present invention four;
Fig. 4 B is the lateral plan of Fig. 4 A;
Fig. 4 C is the birds-eye view of Fig. 4 A;
Fig. 5 A is the structural front view of power rotor of the present invention;
Fig. 5 B is the birds-eye view of Fig. 5 A;
Fig. 6 A is the front sectional view of screw propeller in Fig. 5 A;
Fig. 6 B is the birds-eye view of Fig. 6 A;
Wherein: 1 is fuselage, 2 is power rotor, and 3 is flight support arm, and 4 is alighting gear, and 5 is screw propeller, and 6 is drive motor, and 7 is fairing, and 8 is propeller hub, and 9 is blade, and 10 is circular cowling.
Detailed description of the invention
Below in conjunction with accompanying drawing, the invention will be further described.
The present invention includes fuselage 1, power rotor 2, flight support arm 3, alighting gear 4, electric power supply system and flight control system, wherein the side projection of fuselage 1 is zhou duicheng tuxing, axis of symmetry is the horizontal axis of fuselage 1 working direction, the profile of fuselage 1 can be spherical, oval, rectangle or cylindrical, but is not limited to these shapes.The top of fuselage 1 is provided with even number power rotor 2, and each power rotor 2 is arranged on the top of fuselage 1 respectively by flight support arm 3, and the bottom of fuselage 1 is provided with alighting gear 4, and alighting gear 4 can be slide-type, roller type or air-cushion type, depending on type or needs.Be provided with driving compartment, battery flat and carrying cabin in fuselage 1, electric power supply system is installed in battery flat, and flight control system is installed in driving compartment, and carrying can install equipment needed for aerial mission or passenger seat etc. in cabin.
Embodiment one
As shown in Figure 1A, Figure 1B and Fig. 1 C, the Electronmotive Force multirotor helicopter of the present embodiment comprises fuselage 1, power rotor 2, flight support arm 3, alighting gear 4, electric power supply system and flight control system.
Fuselage 1 entirety of the present embodiment is in stream line pattern, side projection and horizontal projection are ellipse, driving compartment, carrying cabin and battery flat is provided with along horizontal axis (the i.e. transverse direction) direction of working direction in fuselage 1, battery flat is located at the postmedian below carrying cabin, electric power supply system is placed in battery flat, and flight control system is placed in driving compartment.
Above fuselage 1, be along the circumferential direction evenly equipped with four power rotors 2, the horizontal axis of fuselage 1 working direction each side have two power rotors 2, arrange with the horizontal axis Mirror Symmetry of fuselage 1 working direction; Each power rotor 2 is positioned at sustained height, and is parallel to horizontal surface.Each power rotor 2 is all by the fixing main truss on the fuselage 1 of flight support arm 3, and namely power rotor 2 is arranged on the outer end of flight support arm 3, the inner of flight support arm 3 and the main truss of fuselage 1 affixed.Flight support arm 3 can be stationary structure (being namely all fixed on fuselage 1), also can be accordion structure (be namely connected collapsibly with fuselage 1, each flight support arm 3 can upwards fold), but is not limited to this two kinds of versions.Angle between the flight support arm 3 of adjacent two power rotors 2 is 90 °, and in the projection of horizontal surface, the flight support arm 3 of each power rotor 2 is 45 ° with the angle of the horizontal axis of fuselage 1 working direction.The geometric configuration of each power rotor 2 is identical, scantling of structure is identical, physical parameter is identical, electric property is identical.The alighting gear 4 of the present embodiment is slide-type, is installed on the left and right sides of fuselage 1 bottom.
Four power rotor 2 structures are identical, as shown in Fig. 5 A, Fig. 5 B, include screw propeller 5, drive motor 6 and fairing 7, this drive motor 6 is on the fuselage 1 affixed by flight support arm 3, screw propeller 5 is arranged in the rotating shaft of drive motor 6 mouth, is all provided with fairing 7 in the lower end of drive motor 6 and drive motor 6 upper end be positioned at above screw propeller 5.The hand of rotation of the screw propeller 5 in two adjacent power rotors 2 is contrary, lift upwards, respectively by respective drive motor 6 Direct driver.Above the center of gravity being centrally located at fuselage 1 of the power rotor group that four power rotors 2 form.
Screw propeller 5 can be wheeled helical oar, existing traditional free style screw propeller (namely only having propeller hub and blade) or culvert type propeller (namely adding duct outside free style screw propeller), the screw propeller 5 of the present embodiment is wheeled helical oar, as shown in Fig. 6 A, Fig. 6 B, comprise propeller hub 8, blade 9 and culvert type annular ring 10, this propeller hub 8 is connected with the mouth of drive motor 6, blade 9 is multiple (the present embodiment is six), along the circumferential direction uniform, blade root and the propeller hub 8 of each blade 9 are affixed, and the inwall of blade tip and culvert type annular ring 10 is affixed.
Embodiment two
As shown in Fig. 2 A, Fig. 2 B and Fig. 2 C, the difference of the present embodiment and embodiment one is, the fuselage 1 of the present embodiment is spherical, double driving compartment of attending a banquet is provided with in fuselage 1, bottom is provided with battery flat, and electric power supply system is placed in battery flat, and flight control system is placed in driving compartment.Other are all identical with embodiment one.
Embodiment three
As shown in Fig. 3 A, Fig. 3 B and Fig. 3 C, the Electronmotive Force multirotor helicopter of the present embodiment comprises fuselage 1, power rotor 2, flight support arm 3, alighting gear 4, electric power supply system and flight control system.
Fuselage 1 entirety of the present embodiment is in stream line pattern, side projection and horizontal projection be journey rectangle all substantially, driving compartment, carrying cabin and battery flat is provided with along horizontal axis (i.e. the line of centers in the rectangle length direction) direction of working direction in fuselage 1, battery flat is located at below carrying cabin, electric power supply system is placed in battery flat, and flight control system is placed in driving compartment.
Six power rotors 2 are provided with above fuselage 1, power rotor 2 is arranged at the left and right sides of the horizontal axis of fuselage 1 working direction between two symmetrically, namely fuselage 1 working direction horizontal axis each side have three power rotors 2, arrange with the horizontal axis Mirror Symmetry of fuselage 1 working direction.Each power rotor 2 is positioned at sustained height, and is parallel to horizontal surface.Each power rotor 2 is all by the fixing main truss on the fuselage 1 of flight support arm 3, and namely power rotor 2 is arranged on the outer end of flight support arm 3, the inner of flight support arm 3 and the main truss of fuselage 1 affixed.Flight support arm 3 can be stationary structure (being namely all fixed on fuselage 1), also can be accordion structure (be namely connected collapsibly with fuselage 1, each flight support arm 3 can upwards fold), but is not limited to this two kinds of versions.The geometric configuration of each power rotor 2 is identical, scantling of structure is identical, physical parameter is identical, electric property is identical.The alighting gear 4 of the present embodiment is front three-point roller type, and front-wheel is installed on the front lower place of fuselage 1, and two trailing wheels are installed on the arranged on left and right sides of fuselage 1 back lower place.
Six power rotor 2 structures are identical, as shown in Fig. 5 A, Fig. 5 B, include screw propeller 5, drive motor 6 and fairing 7, this drive motor 6 is on the fuselage 1 affixed by flight support arm 3, screw propeller 5 is arranged in the rotating shaft of drive motor 6 mouth, is all provided with fairing 7 in the lower end of drive motor 6 and drive motor 6 upper end be positioned at above screw propeller 5.The hand of rotation of the screw propeller 5 in two power rotors 2 of adjacent (comprise homonymy is adjacent and opposite side is symmetrical) is contrary, lift upwards, respectively by respective drive motor 6 Direct driver.Above the center of gravity being centrally located at fuselage 1 of the power rotor group that six power rotors 2 form.
Screw propeller 5 can be wheeled helical oar, existing traditional free style screw propeller (namely only having propeller hub and blade) or culvert type propeller (namely adding duct outside free style screw propeller), the screw propeller 5 of the present embodiment is wheeled helical oar, as shown in Fig. 6 A, Fig. 6 B, comprise propeller hub 8, blade 9 and culvert type annular ring 10, this propeller hub 8 is connected with the mouth of drive motor 6, blade 9 is multiple (the present embodiment is six), along the circumferential direction uniform, blade root and the propeller hub 8 of each blade 9 are affixed, and the inwall of blade tip and culvert type annular ring 10 is affixed.
Embodiment four
As shown in Fig. 4 A, Fig. 4 B and Fig. 4 C, the Electronmotive Force multirotor helicopter of the present embodiment comprises fuselage 1, power rotor 2, flight support arm 3, alighting gear 4, electric power supply system and flight control system.
The fuselage 1 of the present embodiment is cylindrical, and be provided with driving compartment, carrying cabin and battery flat in fuselage 1, battery flat is located at the middle bottom in fuselage 1, and electric power supply system is placed in battery flat, and flight control system is placed in driving compartment.
Above fuselage 1, be along the circumferential direction evenly equipped with eight power rotors 2, the horizontal axis of fuselage 1 working direction each side have four power rotors 2, and to arrange with the horizontal axis Mirror Symmetry of fuselage 1 working direction.Each power rotor 2 is positioned at sustained height, and is parallel to horizontal surface.Each power rotor 2 is all by the fixing main truss on the fuselage 1 of flight support arm 3, and namely power rotor 2 is arranged on the outer end of flight support arm 3, the inner of flight support arm 3 and the main truss of fuselage 1 affixed.Flight support arm 3 can be stationary structure (being namely all fixed on fuselage 1), also can be accordion structure (be namely connected collapsibly with fuselage 1, each flight support arm 3 can upwards fold), but is not limited to this two kinds of versions.Angle between the flight support arm 3 of adjacent two power rotors 2 is 45 °.The geometric configuration of each power rotor 2 is identical, scantling of structure is identical, physical parameter is identical, electric property is identical.The alighting gear 4 of the present embodiment is slide-type, is installed on the left and right sides of fuselage 1 bottom.
Eight power rotor 2 structures are identical, as shown in Fig. 5 A, Fig. 5 B, include screw propeller 5, drive motor 6 and fairing 7, this drive motor 6 is on the fuselage 1 affixed by flight support arm 3, screw propeller 5 is arranged in the rotating shaft of drive motor 6 mouth, is all provided with fairing 7 in the lower end of drive motor 6 and drive motor 6 upper end be positioned at above screw propeller 5.The hand of rotation of the screw propeller 5 in two adjacent power rotors 2 is contrary, lift upwards, respectively by respective drive motor 6 Direct driver.Above the center of gravity being centrally located at fuselage 1 of the power rotor group that eight power rotors 2 form.
Screw propeller 5 can be wheeled helical oar, existing traditional free style screw propeller (namely only having propeller hub and blade) or culvert type propeller (namely adding duct outside free style screw propeller), the screw propeller 5 of the present embodiment is wheeled helical oar, as shown in Fig. 6 A, Fig. 6 B, comprise propeller hub 8, blade 9 and culvert type annular ring 10, this propeller hub 8 is connected with the mouth of drive motor 6, blade 9 is multiple (the present embodiment is six), along the circumferential direction uniform, blade root and the propeller hub 8 of each blade 9 are affixed, and the inwall of blade tip and culvert type annular ring 10 is affixed.
Principle of work of the present invention is:
The present invention has good flying power and level speed, can on any ground level having additional space vertical takeoff and landing, by adjusting the rotative speed of screw propeller 5 in each power rotor 2, just can realize the control of flight attitude of the present invention and flying speed, hovering, driftage, front and back flight, pitching flying can be carried out and put down flight attitudes such as flying.
1. the realization of Electronmotive Force four-rotor helicopter flight attitude:
For embodiment one, two.
If the center of gravity of helicopter is the origin of coordinates, by initial point upwards, X-axis points to helicopter working direction perpendicular to Z axis to Z axis, and Y-axis is determined by right-hand rule; Four power rotors 2 of the helicopter working direction left and right sides lay respectively in four quadrants of system of axes XY plane.
When in four power rotors 2, the rotative speed of screw propeller 5 increases or reduces simultaneously simultaneously, during the gravity of making a concerted effort to be greater than or less than helicopter on Z axis of the lift of generation, helicopter can rise along Z-direction or decline, and realize vertical takeoff and landing;
When in four power rotors 2, the rotative speed of screw propeller 5 is identical, the lift of generation on Z axis make a concerted effort equal with the gravity of helicopter time, helicopter can realize hovering at desired height;
When being arranged in one, the rotative speed of (before working direction) two power rotor 2 screw propellers 5 of four-quadrant is when being greater than or less than the rotative speed of (after working direction) two power rotor 2 screw propellers 5 being arranged in two, three quadrants, helicopter can along Y-axis rolling, realizes movable, pitching flying, frontly flies or retreat;
When being arranged in one, the rotative speed of (on the left of working direction) two power rotor 2 screw propellers 5 of two quadrant be greater than or less than be arranged in three, the rotative speed of (on the right side of working direction) two power rotor 2 screw propellers 5 of four-quadrant time, helicopter along X-axis rolling, can realize sway;
Be arranged in two when the rotative speed of (a pair linea angulata) two power rotor 2 screw propellers 5 being arranged in one, three quadrants is greater than or less than, the rotative speed of (another diagonal line) two power rotor 2 screw propellers 5 of four-quadrant time, helicopter along Z axis rolling, can realize left and right driftage.
2. the realization of Electronmotive Force six heligyro flight attitude:
For embodiment three.
If the center of gravity of helicopter is the origin of coordinates, by initial point upwards, X-axis points to helicopter working direction perpendicular to Z axis to Z axis, and Y-axis is determined by right-hand rule; Two power rotors 2 in the middle of the helicopter working direction left and right sides are positioned in the Y-axis of X-axis both sides, and other four power rotors lay respectively in four quadrants of system of axes XY plane.
When in six power rotors 2, the rotative speed of screw propeller 5 increases or reduces simultaneously simultaneously, during the gravity of making a concerted effort to be greater than or less than helicopter on Z axis of the lift of generation, helicopter can rise along Z-direction or decline, and realize vertical takeoff and landing;
When in six power rotors 2, the rotative speed of screw propeller 5 is identical, the lift of generation on Z axis make a concerted effort equal with the gravity of helicopter time, helicopter can realize hovering at desired height;
When the rotative speed being arranged in Y-axis two power rotor 2 screw propellers 5 is constant, and be arranged in one, the rotative speed of (before working direction) two power rotor 2 screw propellers 5 of four-quadrant is when being greater than or less than the rotative speed of (after working direction) two power rotor 2 screw propellers 5 being arranged in two, three quadrants, helicopter can along Y-axis rolling, realizes movable, pitching flying, frontly flies or retreat;
When being arranged in one, on the rotative speed of two power rotor 2 screw propellers 5 of two quadrant and X-axis left Y-axis, the rotative speed of power rotor 2 screw propeller 5 is greater than or less than and is arranged in three, on the rotative speed of two power rotor 2 screw propellers 5 of four-quadrant and X-axis right Y-axis during the rotative speed of power rotor 2 screw propeller 5, helicopter along X-axis rolling, can realize sway;
When being arranged in one, two, three, the rotative speed of four power rotor 2 screw propellers 5 of four-quadrant is constant, and regulate the rotative speed of two power rotor 2 screw propellers 5 be arranged in Y-axis, make its rotating speed different, helicopter along Z axis rolling, can realize left and right driftage.
3. the realization of Electronmotive Force eight heligyro flight attitude:
For embodiment four.
If the center of gravity of helicopter is the origin of coordinates, by initial point upwards, X-axis points to helicopter working direction perpendicular to Z axis to Z axis, and Y-axis is determined by right-hand rule; Eight power rotors lay respectively in four quadrants of system of axes XY plane.
When in eight power rotors 2, the rotative speed of screw propeller 5 increases or reduces simultaneously simultaneously, during the gravity of making a concerted effort to be greater than or less than helicopter on Z axis of the lift of generation, helicopter can rise along Z-direction or decline, and realize vertical takeoff and landing;
When in eight power rotors 2, the rotative speed of screw propeller 5 is identical, the lift of generation on Z axis make a concerted effort equal with the gravity of helicopter time, helicopter can realize hovering at desired height;
When being arranged in one, the rotative speed of four power rotor 2 screw propellers 5 of four-quadrant (before working direction) is when being greater than or less than the rotative speed of four power rotor 2 screw propellers 5 being arranged in two, three quadrants (before working direction), helicopter can along Y-axis rolling, realizes movable, pitching flying, frontly flies or retreat;
When being arranged in one, the rotative speed of four power rotor 2 screw propellers 5 of two quadrant (on the left of working direction) be greater than or less than be arranged in three, the rotative speed of four power rotor 2 screw propellers 5 of four-quadrant (on the left of working direction) time, helicopter along X-axis rolling, can realize sway;
When being positioned at one, in two quadrant and in two power rotors 2 of Y-axis screw propeller 5 rotative speed and be positioned at three, four-quadrant is interior and rotative speed that is screw propeller 5 in two power rotors 2 of close Y-axis is constant, and adjustment is positioned at one, in two quadrant and in two power rotors 2 of X-axis screw propeller 5 rotative speed and be positioned at three, the rotative speed of screw propeller 5 in four-quadrant and in two power rotors 2 of X-axis, be located at one, in two quadrant and in two power rotors 2 of X-axis screw propeller 5 rotative speed be positioned at three, four-quadrant is interior and rotative speed that is screw propeller 5 in two power rotors 2 of close X-axis is different, helicopter can along Z axis rolling, realize left and right driftage.
Claims (8)
1. an Electronmotive Force multirotor helicopter, it is characterized in that: comprise fuselage (1), power rotor (2), flight support arm (3), alighting gear (4), electric power supply system and flight control system, wherein the top of fuselage (1) is along the circumferential direction evenly equipped with even number power rotor (2), each described power rotor (2) is arranged on the top of fuselage (1) respectively by flight support arm (3), the bottom of described fuselage (1) is provided with alighting gear (4), described electric power supply system and flight control system are installed on the battery flat in fuselage (1) respectively, in driving compartment, described power rotor (2) is arranged with the horizontal axis Mirror Symmetry of fuselage (1) working direction, and described power rotor (2) quantity of the horizontal axis left and right sides of described fuselage (1) working direction is identical, each described power rotor (2) structure is identical, include screw propeller (5), drive motor (6) and fairing (7), this drive motor (6) is arranged on fuselage (1) by described flight support arm (3), described screw propeller (5) is connected with the mouth of drive motor (6), and lower end and drive motor (6) upper end be positioned at above screw propeller (5) of described drive motor (6) are all provided with fairing (7).
2. an Electronmotive Force multirotor helicopter, it is characterized in that: comprise fuselage (1) power rotor (2), flight support arm (3), alighting gear (4), electric power supply system and flight control system, wherein the top of fuselage (1) is provided with even number power rotor (2), each described power rotor (2) is arranged on the top of fuselage (1) respectively by flight support arm (3), the bottom of described fuselage (1) is provided with alighting gear (4), described electric power supply system and flight control system are installed on the battery flat in fuselage (1) respectively, in driving compartment, power rotor (2) quantity of the horizontal axis left and right sides of described fuselage (1) working direction is identical, and arranges with the horizontal axis Mirror Symmetry of fuselage (1) working direction, each described power rotor (2) structure is identical, include screw propeller (5), drive motor (6) and fairing (7), this drive motor (6) is arranged on fuselage (1) by described flight support arm (3), described screw propeller (5) is connected with the mouth of drive motor (6), and lower end and drive motor (6) upper end be positioned at above screw propeller (5) of described drive motor (6) are all provided with fairing (7).
3. by the Electronmotive Force multirotor helicopter described in claim 1 or 2, it is characterized in that: the hand of rotation of the screw propeller (5) in adjacent two described power rotors (2) is contrary, lift upwards, respectively by respective described drive motor (6) Direct driver.
4., by the Electronmotive Force multirotor helicopter described in claim 1 or 2, it is characterized in that: the center of the power rotor group that each described power rotor (2) forms all is positioned at above the center of gravity of fuselage (1).
5. by the Electronmotive Force multirotor helicopter described in claim 1 or 2, it is characterized in that: described screw propeller (5) is wheeled helical oar, comprise propeller hub (8), blade (9) and culvert type annular ring (10), this propeller hub (8) is connected with the mouth of described drive motor (6), blade (9) is for multiple, along the circumferential direction uniform, blade root and the described propeller hub (8) of each described blade (9) are affixed, and the inwall of blade tip and described culvert type annular ring (10) is affixed.
6., by the Electronmotive Force multirotor helicopter described in claim 1 or 2, it is characterized in that: the side projection of described fuselage (1) is zhou duicheng tuxing, and axis of symmetry is the horizontal axis of described fuselage (1) working direction.
7., by the Electronmotive Force multirotor helicopter described in claim 1 or 2, it is characterized in that: each described flight support arm (3) is stationary structure, is namely all fixed on fuselage (1); Or be accordion structure, be namely connected collapsibly with described fuselage (1), each described flight support arm (3) all can upwards fold.
8. by Electronmotive Force multirotor helicopter described in claim 1 or 2, it is characterized in that: described alighting gear (4) is slide-type, roller type or air-cushion type.
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