CN103963967B - Multiple bladed rotors tandem aircraft - Google Patents
Multiple bladed rotors tandem aircraft Download PDFInfo
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- CN103963967B CN103963967B CN201410182199.4A CN201410182199A CN103963967B CN 103963967 B CN103963967 B CN 103963967B CN 201410182199 A CN201410182199 A CN 201410182199A CN 103963967 B CN103963967 B CN 103963967B
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Abstract
Multiple bladed rotors tandem aircraft, it relates to aircraft and model plane field, solves the big inefficient problem of existing aircraft size. comprise take body center as multiple connecting arm of angularly distributing of the center of circle and multiple driving unit, unit is driven to comprise the first of series connection form and rotation axis parallel, 2nd coaxial rotor system, the rotor up and down of coaxial rotor system is that aerodynamic configuration is identical or close, sense of rotation is contrary, rotation conllinear, the positive and negative rotor that the number of blade is identical, the first of same driving unit, the number of blade of the upper rotor of the 2nd coaxial rotor system is different, the number of blade of the upper rotor of adjacent two the first coaxial rotor system (the 2nd coaxial rotor system) driving unit is different, the Plane of rotation of upper rotor of adjacent two the first coaxial rotor system driving unit not in same plane and the Plane of rotation of lower rotor also not in same plane. keeping under big working load prerequisite, size reduces 10% to 30%, efficiency height.
Description
Technical field
The present invention relates to aircraft and model plane technical field, it is specifically related to one kind of multiple bladed rotors tandem aircraft.
Background technology
There is the rotor class aircraft of the function such as VTOL and hovering, not only play an important role in military field, in disaster field relief, the fields such as dangerous environment is detected, traffic monitoring or aerial photographing also show huge applications potentiality, have been subject to extensive concern.
Current multi-rotor aerocraft mainly contains the structure formations such as four rotors, six rotors, eight rotors, is characterized in being changed rotor lift and level of torque by the rotating speed size of multiple rotor, it is achieved the change of attitude of flight vehicle and motion. Structure, all adopting and arrange multiple rotor in same plane, namely its Plane of rotation is in same plane, or multiple sets of coaxial rotors, and on it, rotor and upper rotor Plane of rotation are in same plane, and lower rotor and lower rotor Plane of rotation are in same plane. The Chinese patent of publication number to be the Chinese patent of CN101823556A and publication number be CN101823555A all discloses a kind of has the 12 rotor aircraft that rotor Plane of rotation has pitch angle, it is possible to realize the decoupling zero of motion and attitude. Above-mentioned aircraft limitation structurally is, when aircraft is in order to carry bigger load, certainly will be installed the rotor of more how identical size or select the larger sized rotor with greater lift. The former, when rotor quantity is more, as being more than or equal to 6, for avoiding the mutual interference between rotor, aircraft size certainly will increase, and the latter makes aircraft size increase equally.
Summary of the invention
In order to solve, the size that existing multi-rotor aerocraft exists is big, the problem of inefficiency, the multiple bladed rotors tandem aircraft that the present invention provides a kind of and keeps big working load, structure is more compact.
The present invention is that the technical scheme that technical solution problem adopts is as follows:
Multiple bladed rotors tandem aircraft, comprise supporter, aviation electronics system in supporter, energy source and load, take-off and landing device bottom supporter, taking body center as multiple connecting arms that the center of circle is angularly distributed on supporter, one_to_one corresponding installs multiple driving unit on the connecting arm;
Described driving unit comprises connecting the first coaxial rotor system and the 2nd coaxial rotor system that form is installed on the connecting arm and rotation is parallel to each other, and the first coaxial rotor system and the 2nd coaxial rotor system of all driving unit are distributed in circumferentially same respectively, about two rotors that described first coaxial rotor system and the 2nd coaxial rotor system include two drive-motor and be arranged on respectively on drive-motor, upper rotor is that aerodynamic configuration is identical or close with lower rotor, sense of rotation is contrary, rotation conllinear, the positive and negative rotor that the number of blade is identical, the upper rotor of the first coaxial rotor system of same driving unit is different from the number of blade of the upper rotor of the 2nd coaxial rotor system, the number of blade of the number of blade difference of the upper rotor of adjacent two the first coaxial rotor system driving unit and the upper rotor of the 2nd coaxial rotor system is also different,
The Plane of rotation of upper rotor of adjacent two the first coaxial rotor system driving unit not in same plane and the Plane of rotation of lower rotor also not in same plane, be separated by one the Plane of rotation of the upper rotor driving two of unit the first coaxial rotor system driving unit in same plane and the Plane of rotation of the upper rotor of the 2nd coaxial rotor system also in same plane, be separated by one the Plane of rotation of the lower rotor driving two of unit the first coaxial rotor system driving unit in same plane and the Plane of rotation of the lower rotor of the 2nd coaxial rotor system also in same plane, two Plane of rotations of two Plane of rotations of the rotor up and down of the first coaxial rotor system of same driving unit and the rotor up and down of the 2nd coaxial rotor system are parallel to each other each other,
Distance D between the rotor rotation of the first coaxial rotor system of same driving unit and the rotor rotation of the 2nd coaxial rotor system1Meet: 1.4R1��D1��1.8R1; Distance D between the rotor rotation of adjacent two the first coaxial rotor system driving unit2Meet: 1.4R2��D2��1.8R2; Distance D between the rotor rotation of adjacent two the 2nd coaxial rotor system driving unit3Meet: 1.4R3��D3��1.8R3; R1��R2��R3It is the maximum radius of rotor.
The number of described driving unit is 6,8,10 or 12.
The blade number of described upper rotor is 2,3,4 or 5.
When described driving unit is six, it is divided into identical two group, often three in group drive the blade number of the blade number difference of the upper rotor of the first coaxial rotor system of unit and the upper rotor of the 2nd coaxial rotor system also different, or, being divided into identical three group, often two in group drive the blade number of the blade number difference of the upper rotor of the first coaxial rotor system of unit and the upper rotor of the 2nd coaxial rotor system also different.
Described six drive cell-average to be divided into identical two group, often three in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 2, 3, or often three in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, 3, or often three in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, 4, or often three in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 3, 4,
Described six drive cell-average to be divided into identical three group, often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 3, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 3, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 3, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 4.
When described driving unit is eight, it is divided into identical two group, often four in group drive the blade number of the blade number difference of the upper rotor of the first coaxial rotor system of unit and the upper rotor of the 2nd coaxial rotor system also different, or, being divided into identical four group, often two in group drive the blade number of the blade number difference of the upper rotor of the first coaxial rotor system of unit and the upper rotor of the 2nd coaxial rotor system also different.
Described eight drive cell-average to be divided into identical two group, often four in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2,3,4,5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5,2,3,4, or often four in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2,3,5,4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4,2,3,5;
Described eight drive cell-average to be divided into identical four group, often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 3, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 3, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 3, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 4.
When described driving unit is ten, being divided into identical five group, often two in group drive the blade number of the blade number difference of the upper rotor of the first coaxial rotor system of unit and the upper rotor of the 2nd coaxial rotor system also different;
Described ten drive cell-average to be divided into identical five group, often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 3, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 3, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 3, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 4.
When described driving unit is 12, it is divided into identical three group, often four in group drive the blade number of the blade number difference of the upper rotor of the first coaxial rotor system of unit and the upper rotor of the 2nd coaxial rotor system also different, or, it is divided into identical four group, often three in group drive the blade number of the blade number difference of the upper rotor of the first coaxial rotor system of unit and the upper rotor of the 2nd coaxial rotor system also different, or, it is divided into identical six group, often two in group drive the blade number of the blade number difference of the upper rotor of the first coaxial rotor system of unit and the upper rotor of the 2nd coaxial rotor system also different.
Described 12 drive cell-average to be divided into identical three group, often four in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2,3,4,5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5,2,3,4, or often four in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2,3,5,4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4,2,3,5;
12 drive cell-averages be divided into identical four group, often three in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 2, 3, or often three in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, 3, or often three in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, 4, or often three in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 3, 4,
Described 12 drive cell-average to be divided into identical six group, often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 3, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 3, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 3, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 4.
The useful effect of the present invention is as follows:
1, when keeping big working load, aircraft does more compacter than by the aircraft that prior art is known. The size of aircraft can be advantageously made to reduce 10% to 30% by this measure.
2, by each turning axle spacing driving unit first coaxial rotor system and the 2nd coaxial rotor system of reasonable disposition, each can be made to drive unit whole work efficiency rotor more single than two higher.
3, each drives the first coaxial rotor system of unit and the number of blade of the 2nd coaxial rotor system to adopt 2,3,4 or 5 respectively, compared with the rotor structure adopting the identical number of blade, can improve and between rotor, disturb the impact on rotor aeroperformance, it is to increase the aeroperformance that many rotors work simultaneously.
Accompanying drawing explanation
Fig. 1 is the vertical view of the multiple bladed rotors tandem aircraft of the present invention shown in embodiment two.
Fig. 2 is the axis side view of the multiple bladed rotors tandem aircraft of the present invention shown in embodiment two.
Fig. 3 is the frontview of the multiple bladed rotors tandem aircraft of the present invention shown in embodiment two.
In figure: 1, supporter, 2, take-off and landing device, 201, support, 202, cylinder, 3, connecting arm, 4, drive unit, 401, the first coaxial rotor system, 402, the 2nd coaxial rotor system, 403, upper rotor, 404, lower rotor, 901, the first plane, 902, the 2nd plane, the 903, the 3rd plane, the 904, the 4th plane.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail.
The multiple bladed rotors tandem aircraft of the present invention, comprise supporter 1, aviation electronics system, energy source, load, take-off and landing device 2, multiple connecting arm 3 and multiple driving unit 4, aviation electronics system, it is inner that energy source and load are installed in supporter 1, take-off and landing device 2 is arranged on bottom supporter 1, multiple connecting arm 3 is angularly distributed on supporter 1 taking body center (supporter 1 center) as the center of circle, multiple driving unit 4 one_to_one corresponding is arranged on multiple connecting arm 3, each connecting arm 3 is provided with one and drives unit 4, the quantity of connecting arm 3 is identical with driving the quantity of unit 4, the number driving unit 4 can be 6, 8, 10 or 12, take-off and landing device 2 comprises two and becomes the support 201 of ladder structure and the cylinder 202 of two certain lengths, two round pipe 202 correspondences are arranged on two supports, 201 times ends, two support 201 upper end symmetries are arranged on bottom supporter 1.
The rotation of drive unit 4 to comprise the first coaxial rotor system 401 that the form of connecting is arranged on connecting arm 3 and the 2nd coaxial rotor system 402, first coaxial rotor system 401 and the 2nd coaxial rotor system 402 is parallel to each other. First coaxial rotor system 401 of all driving unit 4 is distributed in circumferentially same, and the 2nd coaxial rotor system 402 of all driving unit 4 is distributed in circumferentially same. First coaxial rotor system 401 and the 2nd coaxial rotor system 402 include two drive-motor and the upper rotor 403 being arranged on drive-motor respectively and lower rotor 404, upper rotor 403 is the positive and negative rotor that aerodynamic configuration is identical or close, sense of rotation contrary, rotation conllinear, the number of blade are identical with lower rotor 404, and the blade number of upper rotor 403 (lower rotor 404) is 2,3,4 or 5. The upper rotor 403 (lower rotor 404) of the first coaxial rotor system 401 of same driving unit 4 is different from the number of blade of the upper rotor 403 (lower rotor 404) of the 2nd coaxial rotor system 402. The number of blade of the number of blade difference of the upper rotor 403 (lower rotor 404) of adjacent two the first coaxial rotor system 401 driving unit 4 and the upper rotor 403 (lower rotor 404) of the 2nd coaxial rotor system 402 is also different.
The Plane of rotation of upper rotor 403 of adjacent two the first coaxial rotor system 401 driving unit 4 not in same plane and the Plane of rotation of lower rotor 404 also not in same plane. Be separated by one the Plane of rotation of the upper rotor 403 driving two of unit 4 the first coaxial rotor system 401 driving unit 4 in same plane and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 also in same plane. Be separated by one the Plane of rotation of the lower rotor 404 driving two of unit 4 the first coaxial rotor system 401 driving unit 4 in same plane and the Plane of rotation of the lower rotor 404 of the 2nd coaxial rotor system 402 also in same plane. The Plane of rotation of the upper rotor 403 of the first coaxial rotor system 401 of same driving unit 4 and the Plane of rotation of lower rotor 404 are parallel to each other and separated by a distance and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 and the Plane of rotation of lower rotor 404 are also parallel to each other and separated by a distance. The Plane of rotation of the Plane of rotation of the upper rotor 403 of the first coaxial rotor system 401 of same driving unit 4 and the upper rotor 403 of the 2nd coaxial rotor system 402 is parallel to each other and the Plane of rotation of lower rotor 404 of the first coaxial rotor system 401 and the Plane of rotation of the lower rotor 404 of the 2nd coaxial rotor system 402 are also parallel to each other.
Distance D between the rotor rotation of the first coaxial rotor system 401 of same driving unit 4 and the rotor rotation of the 2nd coaxial rotor system 4021Meet: 1.4R1��D1��1.8R1; Distance D between the rotor rotation of adjacent two the first coaxial rotor system 401 driving unit 42Meet: 1.4R2��D2��1.8R2; Distance D between the rotor rotation of adjacent two the 2nd coaxial rotor system 402 driving unit 43Meet: 1.4R3��D3��1.8R3; R1��R2��R3It is the maximum radius of rotor.
Embodiment one,
The multiple bladed rotors tandem aircraft of the present invention, comprise supporter 1, aviation electronics system, energy source, load, take-off and landing device 2, six connecting arms 3 and six driving unit 4, aviation electronics system, it is inner that energy source and load are installed in supporter 1, take-off and landing device 2 is arranged on bottom supporter 1, six connecting arms 3 are angularly distributed in supporter 1 on as the center of circle according to 60 �� taking body center (supporter 1 center), six drive unit 4 one_to_one corresponding to be arranged on six connecting arms 3, each connecting arm 3 is provided with one and drives unit 4, it is separated by two and drives two of unit 4 to drive the rotation of unit 4 on longitudinal plane of symmetry of aircraft, take-off and landing device 2 comprises two and becomes the support 201 of ladder structure and the cylinder 202 of two certain lengths, two round pipe 202 correspondence bondings or mechanical parts are connected to two supports, 201 times ends, two support 201 upper ends are arranged on bottom supporter 1 by screw symmetry.
The rotation of drive unit 4 to comprise the first coaxial rotor system 401 that the form of connecting is arranged on connecting arm 3 and the 2nd coaxial rotor system 402, first coaxial rotor system 401 and the 2nd coaxial rotor system 402 is parallel to each other. Six to drive six the first coaxial rotor system 401 of unit 4 to be distributed in same circumferentially and near supporter 1, these six drive six the 2nd coaxial rotor system 402 of unit 4 be distributed in circumferentially same and away from supporter 1. First coaxial rotor system 401 and the 2nd coaxial rotor system 402 include two drive-motor and the upper rotor 403 being arranged on drive-motor respectively and lower rotor 404, upper rotor 403 is the positive and negative rotor that aerodynamic configuration is identical or close, sense of rotation contrary, rotation conllinear, the number of blade are identical with lower rotor 404, and the blade number of upper rotor 403 (lower rotor 404) can be 2,3,4 or 5. The upper rotor 403 (lower rotor 404) of the first coaxial rotor system 401 of same driving unit 4 is different from the number of blade of the upper rotor 403 (lower rotor 404) of the 2nd coaxial rotor system 402. The number of blade of the number of blade difference of the upper rotor 403 (lower rotor 404) of adjacent two the first coaxial rotor system 401 driving unit 4 and the upper rotor 403 (lower rotor 404) of the 2nd coaxial rotor system 402 is also different.
The Plane of rotation of upper rotor 403 of adjacent two the first coaxial rotor system 401 driving unit 4 not in same plane and the Plane of rotation of lower rotor 404 also not in same plane. be separated by one the Plane of rotation of the upper rotor 403 driving two of unit 4 the first coaxial rotor system 401 driving unit 4 in same plane and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 also in same plane, be separated by one the Plane of rotation of the lower rotor 404 driving two of unit 4 the first coaxial rotor system 401 driving unit 4 in same plane and the Plane of rotation of the lower rotor 404 of the 2nd coaxial rotor system 402 also in same plane: first, 3rd, 5th drive the Plane of rotation of upper rotor 403 of the first coaxial rotor system 401 of unit 4 in same plane and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 also in same plane, first, 3rd, 5th drive the Plane of rotation of lower rotor 404 of the first coaxial rotor system 401 of unit 4 in same plane and the Plane of rotation of the lower rotor 404 of the 2nd coaxial rotor system 402 also in same plane, 2nd, 4th, 6th drive the Plane of rotation of upper rotor 403 of the first coaxial rotor system 401 of unit 4 in same plane and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 also in same plane, 2nd, 4th, 6th drive the Plane of rotation of lower rotor 404 of the first coaxial rotor system 401 of unit 4 in same plane and the Plane of rotation of the lower rotor 404 of the 2nd coaxial rotor system 402 also in same plane. each drive unit 4 the first coaxial rotor system 401 the Plane of rotation of upper rotor 403 and the Plane of rotation of lower rotor 404 is parallel to each other and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 and the Plane of rotation of lower rotor 404 are also parallel to each other. each drives the Plane of rotation of upper rotor 403 of the first coaxial rotor system 401 of unit 4 and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 is parallel to each other and the Plane of rotation of the Plane of rotation of lower rotor 404 of the first coaxial rotor system 401 and the lower rotor 404 of the 2nd coaxial rotor system 402 is also parallel to each other.
Each drives the distance D between the rotor rotation of the first coaxial rotor system 401 of unit 4 and the rotor rotation of the 2nd coaxial rotor system 4021Meet: 1.4R1��D1��1.8R1; Distance D between the rotor rotation of adjacent two the first coaxial rotor system 401 driving unit 42Meet: 1.4R2��D2��1.8R2; Distance D between the rotor rotation of adjacent two the 2nd coaxial rotor system 402 driving unit 43Meet: 1.4R3��D3��1.8R3; R1��R2��R3It is the maximum radius of rotor.
Six drive unit 4 to be divided into identical two group, often three in group drive the blade number of the blade number difference of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 and the upper rotor 403 of the 2nd coaxial rotor system 402 also different, and often three in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 3, 4, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 4, 2, 3, or often three in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 3, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 2, 3, or often three in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 4, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 2, 4, or often three in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 3, 4, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 3, 4.
Six drive unit 4 to be divided into identical three group, often two in group drive the blade number of the blade number difference of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 and the upper rotor 403 of the 2nd coaxial rotor system 402 also different, often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 3, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 3, 2, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 4, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 4, 2, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 2, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 3, 4, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 4, 3, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 3, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 3, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 4, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 4.
Embodiment two,
The multiple bladed rotors tandem aircraft of the present invention, comprise supporter 1, aviation electronics system, energy source, load, take-off and landing device 2, eight connecting arms 3 and eight driving unit 4, as shown in Figure 2, it is inner that aviation electronics system, energy source and load are installed in supporter 1, take-off and landing device 2 is arranged on bottom supporter 1, eight connecting arms 3 taking body center (supporter 1 center) as the center of circle according to 45��Angularly it is distributed on supporter 1, eight drive unit 4 one_to_one corresponding to be arranged on eight connecting arms 3, each connecting arm 3 is provided with one and drives unit 4, it is separated by three and drives two of unit 4 to drive the rotation of unit 4 on longitudinal plane of symmetry of aircraft, take-off and landing device 2 comprises two and becomes the support 201 of ladder structure and the cylinder 202 of two certain lengths, two round pipe 202 correspondence bondings or mechanical parts are connected to two supports, 201 times ends, and two support 201 upper ends are arranged on bottom supporter 1 by screw symmetry.
The rotation of drive unit 4 to comprise the first coaxial rotor system 401 that the form of connecting is arranged on connecting arm 3 and the 2nd coaxial rotor system 402, first coaxial rotor system 401 and the 2nd coaxial rotor system 402 is parallel to each other. As shown in Figure 1, eight to drive eight the first coaxial rotor system 401 of unit 4 to be distributed in same circumferentially and near supporter 1, these eight drive eight the 2nd coaxial rotor system 402 of unit 4 be distributed in circumferentially same and away from supporter 1. First coaxial rotor system 401 and the 2nd coaxial rotor system 402 include two drive-motor and the upper rotor 403 being arranged on drive-motor respectively and lower rotor 404, upper rotor 403 is the positive and negative rotor that aerodynamic configuration is identical or close, sense of rotation contrary, rotation conllinear, the number of blade are identical with lower rotor 404, and the blade number of upper rotor 403 (lower rotor 404) can be 2,3,4 or 5. The upper rotor 403 (lower rotor 404) of the first coaxial rotor system 401 of same driving unit 4 is different from the number of blade of the upper rotor 403 (lower rotor 404) of the 2nd coaxial rotor system 402. The number of blade of the number of blade difference of the upper rotor 403 (lower rotor 404) of adjacent two the first coaxial rotor system 401 driving unit 4 and the upper rotor 403 (lower rotor 404) of the 2nd coaxial rotor system 402 is also different.
The Plane of rotation of upper rotor 403 of adjacent two the first coaxial rotor system 401 driving unit 4 not in same plane and the Plane of rotation of lower rotor 404 also not in same plane. be separated by one the Plane of rotation of the upper rotor 403 driving two of unit 4 the first coaxial rotor system 401 driving unit 4 in same plane and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 also in same plane, be separated by one the Plane of rotation of the lower rotor 404 driving two of unit 4 the first coaxial rotor system 401 driving unit 4 in same plane and the Plane of rotation of the lower rotor 404 of the 2nd coaxial rotor system 402 also in same plane: as shown in Figure 3, first, 3rd, 5th, 7th drive that the Plane of rotation of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 is upper in same plane (the first plane 901) and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 also in same plane (the 2nd plane 902), first, 3rd, 5th, 7th drive that the Plane of rotation of the lower rotor 404 of the first coaxial rotor system 401 of unit 4 is upper in same plane (the 3rd plane 903) and the Plane of rotation of the lower rotor 404 of the 2nd coaxial rotor system 402 also in same plane (the 4th plane 904), 2nd, 4th, 6th, 8th drive that the Plane of rotation of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 is upper in same plane (the 2nd plane 902) and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 also in same plane (the first plane 901), 2nd, 4th, 6th, 8th drive that the Plane of rotation of the lower rotor 404 of the first coaxial rotor system 401 of unit 4 is upper in same plane (the 4th plane 904) and the Plane of rotation of the lower rotor 404 of the 2nd coaxial rotor system 402 also in same plane (the 3rd plane 903). each drive unit 4 the first coaxial rotor system 401 the Plane of rotation of upper rotor 403 and the Plane of rotation of lower rotor 404 is parallel to each other and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 and the Plane of rotation of lower rotor 404 are also parallel to each other. each drives the Plane of rotation of upper rotor 403 of the first coaxial rotor system 401 of unit 4 and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 is parallel to each other and the Plane of rotation of the Plane of rotation of lower rotor 404 of the first coaxial rotor system 401 and the lower rotor 404 of the 2nd coaxial rotor system 402 is also parallel to each other.
Each drives the distance D between the rotor rotation of the first coaxial rotor system 401 of unit 4 and the rotor rotation of the 2nd coaxial rotor system 4021Meet: 1.4R1��D1��1.8R1; Distance D between the rotor rotation of adjacent two the first coaxial rotor system 401 driving unit 42Meet: 1.4R2��D2��1.8R2; Distance D between the rotor rotation of adjacent two the 2nd coaxial rotor system 402 driving unit 43Meet: 1.4R3��D3��1.8R3; R1��R2��R3It is the maximum radius of rotor.
Eight drive unit 4 to be divided into identical two group, often four in group drive the blade number of the blade number difference of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 and the upper rotor 403 of the 2nd coaxial rotor system 402 also different, often four in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 3, 4, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 2, 3, 4, or often four in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 3, 5, 4, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 4, 2, 3, 5.
Eight drive unit 4 to be divided into identical four group, often two in group drive the blade number of the blade number difference of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 and the upper rotor 403 of the 2nd coaxial rotor system 402 also different, often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 3, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 3, 2, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 4, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 4, 2, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 2, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 3, 4, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 4, 3, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 3, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 3, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 4, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 4.
Embodiment three,
The multiple bladed rotors tandem aircraft of the present invention, comprise supporter 1, aviation electronics system, energy source, load, take-off and landing device 2, ten connecting arms 3 and ten driving unit 4, aviation electronics system, it is inner that energy source and load are installed in supporter 1, take-off and landing device 2 is arranged on bottom supporter 1, ten connecting arms 3 are angularly distributed in supporter 1 on as the center of circle according to 36 �� taking body center (supporter 1 center), ten drive unit 4 one_to_one corresponding to be arranged on ten connecting arms 3, each connecting arm 3 is provided with one and drives unit 4, it is separated by four and drives two of unit 4 to drive the rotation of unit 4 on longitudinal plane of symmetry of aircraft, take-off and landing device 2 comprises two and becomes the support 201 of ladder structure and the cylinder 202 of two certain lengths, two round pipe 202 correspondence bondings or mechanical parts are connected to two supports, 201 times ends, two support 201 upper ends are arranged on bottom supporter 1 by screw symmetry.
The rotation of drive unit 4 to comprise the first coaxial rotor system 401 that the form of connecting is arranged on connecting arm 3 and the 2nd coaxial rotor system 402, first coaxial rotor system 401 and the 2nd coaxial rotor system 402 is parallel to each other. Ten drive unit 4 ten the first coaxial rotor system 401 be distributed in same circumferentially and near supporter 1, ten drive unit 4 ten the 2nd coaxial rotor system 402 be distributed in circumferentially same and away from supporter 1. First coaxial rotor system 401 and the 2nd coaxial rotor system 402 include two drive-motor and the upper rotor 403 being arranged on drive-motor respectively and lower rotor 404, upper rotor 403 is the positive and negative rotor that aerodynamic configuration is identical or close, sense of rotation contrary, rotation conllinear, the number of blade are identical with lower rotor 404, and the blade number of upper rotor 403 (lower rotor 404) can be 2,3,4 or 5. The upper rotor 403 (lower rotor 404) of the first coaxial rotor system 401 of same driving unit 4 is different from the number of blade of the upper rotor 403 (lower rotor 404) of the 2nd coaxial rotor system 402. The number of blade of the number of blade difference of the upper rotor 403 (lower rotor 404) of adjacent two the first coaxial rotor system 401 driving unit 4 and the upper rotor 403 (lower rotor 404) of the 2nd coaxial rotor system 402 is also different.
The Plane of rotation of upper rotor 403 of adjacent two the first coaxial rotor system 401 driving unit 4 not in same plane and the Plane of rotation of lower rotor 404 also not in same plane. be separated by one the Plane of rotation of the upper rotor 403 driving two of unit 4 the first coaxial rotor system 401 driving unit 4 in same plane and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 also in same plane, the Plane of rotation of the lower rotor 404 of two the first coaxial rotor system 401 driving unit 4 driving unit 4 of being separated by same plane and the Plane of rotation of the lower rotor 404 of the 2nd coaxial rotor system 402 also in same plane: first, 3rd, 5th, 7th, 9th drive the Plane of rotation of upper rotor 403 of the first coaxial rotor system 401 of unit 4 in same plane and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 also in same plane, first, 3rd, 5th, 7th, 9th drive the Plane of rotation of lower rotor 404 of the first coaxial rotor system 401 of unit 4 in same plane and the Plane of rotation of the lower rotor 404 of the 2nd coaxial rotor system 402 also in same plane, the 2nd, 4th, 6th, 8th, tenth drive the Plane of rotation of upper rotor 403 of the first coaxial rotor system 401 of unit 4 in same plane and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 also in same plane, the 2nd, 4th, 6th, 8th, tenth drive the Plane of rotation of lower rotor 404 of the first coaxial rotor system 401 of unit 4 in same plane and the Plane of rotation of the lower rotor 404 of the 2nd coaxial rotor system 402 also in same plane. each drive unit 4 the first coaxial rotor system 401 the Plane of rotation of upper rotor 403 and the Plane of rotation of lower rotor 404 is parallel to each other and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 and the Plane of rotation of lower rotor 404 are also parallel to each other. each drives the Plane of rotation of upper rotor 403 of the first coaxial rotor system 401 of unit 4 and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 is parallel to each other and the Plane of rotation of the Plane of rotation of lower rotor 404 of the first coaxial rotor system 401 and the lower rotor 404 of the 2nd coaxial rotor system 402 is also parallel to each other.
Each drives the distance D between the rotor rotation of the first coaxial rotor system 401 of unit 4 and the rotor rotation of the 2nd coaxial rotor system 4021Meet: 1.4R1��D1��1.8R1; Distance D between the rotor rotation of adjacent two the first coaxial rotor system 401 driving unit 42Meet: 1.4R2��D2��1.8R2; Distance D between the rotor rotation of adjacent two the 2nd coaxial rotor system 402 driving unit 43Meet: 1.4R3��D3��1.8R3; R1��R2��R3It is the maximum radius of rotor.
Ten drive unit 4 to be divided into identical five group, and often two in group drive the blade number of the blade number difference of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 and the upper rotor 403 of the 2nd coaxial rotor system 402 also different, often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 3, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 3, 2, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 4, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 4, 2, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system of unit 4 to be respectively 2, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 2, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 3, 4, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 4, 3, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 3, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 3, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 4, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 4.
Embodiment four,
The multiple bladed rotors tandem aircraft of the present invention, comprise supporter 1, aviation electronics system, energy source, load, take-off and landing device 2, 12 connecting arms 3 and 12 driving unit 4, aviation electronics system, it is inner that energy source and load are installed in supporter 1, take-off and landing device 2 is arranged on bottom supporter 1, 12 connecting arms 3 are angularly distributed in supporter 1 on as the center of circle according to 30 �� taking body center (supporter 1 center), 12 drive unit 4 one_to_one corresponding to be arranged on 12 connecting arms 3, each connecting arm 3 is provided with one and drives unit 4, it is separated by five and drives two of unit 4 to drive the rotation of unit 4 on longitudinal plane of symmetry of aircraft, take-off and landing device 2 comprises two and becomes the support 201 of ladder structure and the cylinder 202 of two certain lengths, two round pipe 202 correspondence bondings or mechanical parts are connected to two supports, 201 times ends, two support 201 upper ends are arranged on bottom supporter 1 by screw symmetry.
The rotation of drive unit 4 to comprise the first coaxial rotor system 401 that the form of connecting is arranged on connecting arm 3 and the 2nd coaxial rotor system 402, first coaxial rotor system 401 and the 2nd coaxial rotor system 402 is parallel to each other. 12 drive unit 4 12 the first coaxial rotor system 401 be distributed in same circumferentially and near supporter 1,12 drive unit 4 12 the 2nd coaxial rotor system 402 be distributed in circumferentially same and away from supporter 1. First coaxial rotor system 401 and the 2nd coaxial rotor system 402 include two drive-motor and the upper rotor 403 being arranged on drive-motor respectively and lower rotor 404, upper rotor 403 is the positive and negative rotor that aerodynamic configuration is identical or close, sense of rotation contrary, rotation conllinear, the number of blade are identical with lower rotor 404, and the blade number of upper rotor 403 (lower rotor 404) can be 2,3,4 or 5. The upper rotor 403 (lower rotor 404) of the first coaxial rotor system 401 of same driving unit 4 is different from the number of blade of the upper rotor 403 (lower rotor 404) of the 2nd coaxial rotor system 402. The number of blade of the number of blade difference of the upper rotor 403 (lower rotor 404) of adjacent two the first coaxial rotor system 401 driving unit 4 and the upper rotor 403 (lower rotor 404) of the 2nd coaxial rotor system 402 is also different.
The Plane of rotation of upper rotor 403 of adjacent two the first coaxial rotor system 401 driving unit 4 not in same plane and the Plane of rotation of lower rotor 404 also not in same plane. be separated by one the Plane of rotation of the upper rotor 403 driving two of unit 4 the first coaxial rotor system 401 driving unit 4 in same plane and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 also in same plane, the Plane of rotation of the lower rotor 404 of two the first coaxial rotor system 401 driving unit 4 driving unit 4 of being separated by same plane and the Plane of rotation of the lower rotor 404 of the 2nd coaxial rotor system 402 also in same plane: first, 3rd, 5th, 7th, 9th, 11 drive the Plane of rotation of upper rotor 403 of the first coaxial rotor system 401 of unit 4 in same plane and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 also in same plane, first, 3rd, 5th, 7th, 9th, 11 drive the Plane of rotation of lower rotor 404 of the first coaxial rotor system 401 of unit 4 in same plane and the Plane of rotation of the lower rotor 404 of the 2nd coaxial rotor system 402 also in same plane, the 2nd, 4th, 6th, 8th, tenth, 12 drive the Plane of rotation of upper rotor 403 of the first coaxial rotor system 401 of unit 4 in same plane and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 also in same plane, the 2nd, 4th, 6th, 8th, tenth, 12 drive the Plane of rotation of lower rotor 404 of the first coaxial rotor system 401 of unit 4 in same plane and the Plane of rotation of the lower rotor 404 of the 2nd coaxial rotor system 402 also in same plane. each drive unit 4 the first coaxial rotor system 401 the Plane of rotation of upper rotor 403 and the Plane of rotation of lower rotor 404 is parallel to each other and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 and the Plane of rotation of lower rotor 404 are also parallel to each other. each drives the Plane of rotation of upper rotor 403 of the first coaxial rotor system 401 of unit 4 and the Plane of rotation of the upper rotor 403 of the 2nd coaxial rotor system 402 is parallel to each other and the Plane of rotation of the Plane of rotation of lower rotor 404 of the first coaxial rotor system 401 and the lower rotor 404 of the 2nd coaxial rotor system 402 is also parallel to each other.
Each drives the distance D between the rotor rotation of the first coaxial rotor system 401 of unit 4 and the rotor rotation of the 2nd coaxial rotor system 4021Meet: 1.4R1��D1��1.8R1; Distance D between the rotor rotation of adjacent two the first coaxial rotor system 401 driving unit 42Meet: 1.4R2��D2��1.8R2; Distance D between the rotor rotation of adjacent two the 2nd coaxial rotor system 402 driving unit 43Meet: 1.4R3��D3��1.8R3; R1��R2��R3It is the maximum radius of rotor.
12 drive unit 4 to be divided into identical three group, often four in group drive the blade number of the blade number difference of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 and the upper rotor 403 of the 2nd coaxial rotor system 402 also different, often four in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 3, 4, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 2, 3, 4, or often four in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 3, 5, 4, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 4, 2, 3, 5.
12 drive unit 4 to be divided into identical four group, often three in group drive the blade number of the blade number difference of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 and the upper rotor 403 of the 2nd coaxial rotor system 402 also different, and often three in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 3, 4, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 4, 2, 3, or often three in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 3, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 2, 3, or often three in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 4, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 2, 4, or often three in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 3, 4, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 3, 4.
12 drive unit 4 to be divided into identical six group, often two in group drive the blade number of the blade number difference of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 and the upper rotor 403 of the 2nd coaxial rotor system 402 also different, often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 3, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 3, 2, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 4, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 4, 2, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 2, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 2, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 3, 4, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 4, 3, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 3, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 3, or often two in group drive the blade number of the upper rotor 403 of the first coaxial rotor system 401 of unit 4 to be respectively 4, 5, the blade number of the upper rotor 403 of the 2nd simultaneously corresponding coaxial rotor system 402 is respectively 5, 4.
Claims (6)
1. many kinds of bladed rotors tandem aircraft, comprise supporter, aviation electronics system in supporter, energy source and load, take-off and landing device bottom supporter, taking body center as multiple connecting arms that the center of circle is angularly distributed on supporter, one_to_one corresponding installs multiple driving unit on the connecting arm;
It is characterized in that, described driving unit comprises connecting the first coaxial rotor system and the 2nd coaxial rotor system that form is installed on the connecting arm and rotation is parallel to each other, and the first coaxial rotor system and the 2nd coaxial rotor system of all driving unit are distributed in circumferentially same respectively, about two rotors that described first coaxial rotor system and the 2nd coaxial rotor system include two drive-motor and be arranged on respectively on drive-motor, upper rotor is that aerodynamic configuration is identical or close with lower rotor, sense of rotation is contrary, rotation conllinear, the positive and negative rotor that the number of blade is identical, the upper rotor of the first coaxial rotor system of same driving unit is different from the number of blade of the upper rotor of the 2nd coaxial rotor system, the number of blade of the number of blade difference of the upper rotor of adjacent two the first coaxial rotor system driving unit and the upper rotor of the 2nd coaxial rotor system is also different,
The Plane of rotation of upper rotor of adjacent two the first coaxial rotor system driving unit not in same plane and the Plane of rotation of lower rotor also not in same plane, be separated by one the Plane of rotation of the upper rotor driving two of unit the first coaxial rotor system driving unit in same plane and the Plane of rotation of the upper rotor of the 2nd coaxial rotor system also in same plane, be separated by one the Plane of rotation of the lower rotor driving two of unit the first coaxial rotor system driving unit in same plane and the Plane of rotation of the lower rotor of the 2nd coaxial rotor system also in same plane, two Plane of rotations of two Plane of rotations of the rotor up and down of the first coaxial rotor system of same driving unit and the rotor up and down of the 2nd coaxial rotor system are parallel to each other each other,
Distance D between the rotor rotation of the first coaxial rotor system of same driving unit and the rotor rotation of the 2nd coaxial rotor system1Meet: 1.4R1��D1��1.8R1; Distance D between the rotor rotation of adjacent two the first coaxial rotor system driving unit2Meet: 1.4R2��D2��1.8R2; Distance D between the rotor rotation of adjacent two the 2nd coaxial rotor system driving unit3Meet: 1.4R3��D3��1.8R3; R1��R2��R3It is the maximum radius of rotor;
The number of described driving unit is 6,8,10 or 12;
When described driving unit is six, it is divided into identical two group, often three in group drive the blade number of the blade number difference of the upper rotor of the first coaxial rotor system of unit and the upper rotor of the 2nd coaxial rotor system also different, or, being divided into identical three group, often two in group drive the blade number of the blade number difference of the upper rotor of the first coaxial rotor system of unit and the upper rotor of the 2nd coaxial rotor system also different;
When described driving unit is eight, it is divided into identical two group, often four in group drive the blade number of the blade number difference of the upper rotor of the first coaxial rotor system of unit and the upper rotor of the 2nd coaxial rotor system also different, or, being divided into identical four group, often two in group drive the blade number of the blade number difference of the upper rotor of the first coaxial rotor system of unit and the upper rotor of the 2nd coaxial rotor system also different;
When described driving unit is ten, being divided into identical five group, often two in group drive the blade number of the blade number difference of the upper rotor of the first coaxial rotor system of unit and the upper rotor of the 2nd coaxial rotor system also different;
When described driving unit is 12, it is divided into identical three group, often four in group drive the blade number of the blade number difference of the upper rotor of the first coaxial rotor system of unit and the upper rotor of the 2nd coaxial rotor system also different, or, it is divided into identical four group, often three in group drive the blade number of the blade number difference of the upper rotor of the first coaxial rotor system of unit and the upper rotor of the 2nd coaxial rotor system also different, or, it is divided into identical six group, often two in group drive the blade number of the blade number difference of the upper rotor of the first coaxial rotor system of unit and the upper rotor of the 2nd coaxial rotor system also different.
2. multiple bladed rotors tandem aircraft according to claim 1, it is characterised in that, the blade number of described upper rotor is 2,3,4 or 5.
3. multiple bladed rotors tandem aircraft according to claim 1, it is characterised in that, described six drive cell-average to be divided into identical two group, and often three in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 2, 3, or often three in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, 3, or often three in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, 4, or often three in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 3, 4,
Described six drive cell-average to be divided into identical three group, often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 3, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 3, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 3, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 4.
4. multiple bladed rotors tandem aircraft according to claim 1, it is characterized in that, described eight drive cell-average to be divided into identical two group, often four in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, 3, 4, or often four in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, 5, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 2, 3, 5,
Described eight drive cell-average to be divided into identical four group, often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 3, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 3, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 3, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 4.
5. multiple bladed rotors tandem aircraft according to claim 1, it is characterized in that, described ten drive cell-average to be divided into identical five group, often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 3, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 3, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 3, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 4.
6. multiple bladed rotors tandem aircraft according to claim 1, it is characterized in that, described 12 drive cell-average to be divided into identical three group, often four in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, 3, 4, or often four in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, 5, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 2, 3, 5,
12 drive cell-averages be divided into identical four group, often three in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 2, 3, or often three in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, 3, or often three in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, 4, or often three in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 3, 4,
Described 12 drive cell-average to be divided into identical six group, often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 3, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 3, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 2, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 2, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 4, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 4, 3, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 3, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 3, or often two in group drive the blade number of the upper rotor of the first coaxial rotor system of unit to be respectively 4, 5, the blade number of the upper rotor of the 2nd simultaneously corresponding coaxial rotor system is respectively 5, 4.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1807185A (en) * | 2006-02-23 | 2006-07-26 | 上海交通大学 | Articulated type double-rotor flying robot |
| CN201367115Y (en) * | 2008-11-17 | 2009-12-23 | 西安智澜科技发展有限公司 | Foldable four-axis multi-rotor wing aerocraft |
| CN102514711A (en) * | 2011-12-02 | 2012-06-27 | 叶洪新 | Multi-rotor fuel-electric hybrid aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1807185A (en) * | 2006-02-23 | 2006-07-26 | 上海交通大学 | Articulated type double-rotor flying robot |
| CN201367115Y (en) * | 2008-11-17 | 2009-12-23 | 西安智澜科技发展有限公司 | Foldable four-axis multi-rotor wing aerocraft |
| CN102514711A (en) * | 2011-12-02 | 2012-06-27 | 叶洪新 | Multi-rotor fuel-electric hybrid aircraft |
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