Driving device assembly with multiple drive devices and application thereof
The present invention relates to a drive device assembly having a plurality of drive devices and an aircraft for which drive devices and loads can be increased unlimitedly. The drive devices are arranged in a triangle so as to form a triangular drive device module. In a preferred assembling method, the spatial distances between adjacent drive devices are equal; a drive device module arranged in a triangle is taken as a basis, and is mapped and arranged and assembled towards the spatial direction so as to form a drive device assembly constituted by the multiple drive devices. The present application improves the aircraft, especially in terms of the traditional structure layout of the aircraft driven by multiple drive devices, such that the drive devices in the drive system can be increased unlimitedly, thus improving the flight performance and loading capacity of the aircraft.
1. An aircraft comprising:
a plurality of rotors;
a plurality of movable connectors, each of the plurality of rotors coupled to at least one other of the plurality of rotors by one of the plurality of movable connectors to form a movable skeleton of the aircraft,
wherein the movable skeleton is configured to collapse through movement of the movable connectors and the plurality of rotors are distributed as follows:
three of the rotors form a triangular unit by way of at least two of the plurality of movable connectors, the three rotors are located at vertices of the triangular unit, and other rotors are distributed outside the triangular unit and at intersection points of three groups of parallel lines,
wherein each group of parallel lines comprise an equidistant line in parallel with a side of the triangular unit and a line where the side is located, spacing of each group of parallel lines is a height length of a corresponding side of the triangular unit and a number of the rotors is greater than or equal to 3, 4, 5, 6, 7, 8, 9, 10, 15, 24 or 30; and
a plurality of wings, each of the plurality of wings rotatably connected to the movable skeleton of the aircraft through one or more of the movable connectors, the plurality of wings distributed across the movable skeleton and configured to be rotated to adjust an angle of attack during flight of the aircraft such that the plurality of wings result in pitch and roll forces being applied to the aircraft during flight of the aircraft based on the rotation of the plurality of wings, wherein one or more of the wings is additionally configured to a second state to serve as a landing support device for the aircraft.
2. The aircraft according to claim 1 , wherein the plurality of rotors are powered by one or more batteries and/or engine.
3. The aircraft according to claim 1 , wherein the aircraft is assembled in a form of module groups, and the module groups comprises: a rotor unit; a connecting cabin unit; and an auxiliary unit.
4. The aircraft according to claim 1 , further comprising a fuselage for carrying a load.
5. The aircraft according to claim 4 , wherein the aircraft is assembled in a form of module groups, and the module groups comprises: a rotor unit; a connecting cabin unit; and an auxiliary unit.
6. The aircraft according to claim 1 , wherein the triangular unit is an equilateral triangle.
7. The aircraft according to claim 6 , wherein the plurality of rotors are distributed to form the triangular unit,
the triangular unit and one or more additional triangular units are mapped and arranged towards a spatial direction so as to be combined such that the aircraft is constituted by multiple rotors, and
the number of the rotors in the aircraft is N, wherein N≥3.
8. The aircraft according to claim 7 , wherein the plurality of rotors include:
the three of the rotors that form the triangular unit, with vertices A, B, and C, the triangular unit being a first triangular unit and being arranged as an equilateral triangle,
a side BC of the triangular unit that includes vertices B and C are part of a second triangular unit with the vertices B, C, and vertex D, the second triangular unit arranged as an equilateral triangle, the first triangular unit and the second triangular unit forming a first diamond unit that includes the three of the rotors and a fourth rotor,
wherein the aircraft further includes a second diamond unit configured in the same manner as the first diamond unit, the second diamond unit sharing one or more vertices with the first diamond unit such that the second diamond unit also includes one or more of the three of the rotors and the fourth rotor.