Unmanned helicopter

An unmanned helicopter comprising a fuselage, three arms are provided on each side of the fuselage respectively, one end of each of said arms is connected with the fuselage, and the other end of each of the arms is used for arranging a rotor having a motor, wherein:

• the six arms are grouped into three groups in turn in the direction of the fuselage:
• a first group, a second group and a third group, the first group of two arms are arranged symmetrically relative to an axis of the fuselage, and when the two arms are completely deployed, each of the arms is at an acute angle relative to a direction of an axis extending outward the fuselage;
• the second group of two arms are arranged symmetrically relative to the same axis of the fuselage, and when the two arms are completely deployed, each of the arms is at an acute angle, a right angle or an obtuse angle relative to the direction of the axis;
• the third group of two arms are arranged symmetrically relative to the same axis of the fuselage, and when the two arms are completely deployed, each of the arms is at an acute angle relative to the direction of the axis extending outward the fuselage;
• the fuselage and each of said arms employ a movable connection respectively, wherein:
• the movable connection of the first group of two arms enables one end of each arm of the first group connected with the fuselage to respectively rotate about a first or second rotation axis at a location of the respective movable connection, wherein a length direction of any arm of the first group of arms and its corresponding first or second rotation axis form an angle r1, 20°<r1<90°, an angle formed by the first or second rotation axis and the horizontal surface of the fuselage is angle a1, 1°<a1<86° or −86°<a1<−1°, meanwhile, a projection line of the first or second rotation axis on the horizontal surface of the fuselage and the direction of the axis extending outward the fuselage form an angle b1, 30°<b1<90°,
• the movable connection of the second group of two arms enables one end of each arm of the second group connected with the fuselage to respectively rotate about a third or fourth rotation axis at the location of the respective movable connection, wherein a length direction of any arm of the second group of arms and its corresponding third or fourth rotation axis form an angle r2, 20°<r2<160°, an angle formed by the third or fourth rotation axis and the horizontal surface of the fuselage is angle a2, 1°<a2<86° or −86°<a2<−1°, wherein a2 and a1 have the same plus or minus sign, meanwhile, a projection line of the third or fourth rotation axis on the horizontal surface of the fuselage and the direction of the axis extending outward the fuselage form an angle b2, 30°<b2<150°,
• the movable connection of the third group of two arms enables one end of each arm of the third group connected with the fuselage to respectively rotate about a fifth or sixth rotation axis at the location of the respective movable connection, wherein a length direction of any arm of the third group of arms and its corresponding fifth or sixth rotation axis form an angle r3, 90°<r3<160°, an angle formed by the fifth or sixth rotation axis and the horizontal surface of the fuselage is angle a3, 1°<a3<86° or −86°<a3<−1°, wherein a3 and a1 have the same plus or minus sign, meanwhile, a projection line of the fifth or sixth rotation axis on the horizontal surface of the fuselage and the direction of the axis extending outward the fuselage form an angle b3, 90°<b3<150°.

An unmanned helicopter comprising a fuselage, four arms are provided on each side of the fuselage respectively, one end of each of said arms is connected with the fuselage, and the other end of each of the arms is used for arranging a rotor having a motor, wherein:

• the eight arms are grouped into four groups in turn in the direction of the fuselage:
• a first group, a second group, a third group and a fourth group, the first group of two arms are arranged symmetrically relative to an axis of the fuselage, and when the two arms are completely deployed, each of the arms is at an acute angle relative to a direction of an axis extending outward the fuselage;
• the second group of two arms are arranged symmetrically relative to the same axis of the fuselage, and when the two arms are completely deployed, each of the arms is at an acute angle, a right angle or an obtuse angle relative to the direction of the axis;
• the third group of two arms are arranged symmetrically relative to the same axis of the fuselage, and when the two arms are completely deployed, each of the arms is at an acute angle, a right angle or an obtuse angle relative to the direction of the axis;
• the fourth group of two arms are arranged symmetrically relative to the same axis of the fuselage, and when the two arms are completely deployed, each of the arms is at an acute angle relative to the direction of the axis extending outward the fuselage;
• the fuselage and each of said arms employ a movable connection respectively, wherein:
• the movable connection of the first group of two arms enables one end of each arm of the first group connected with the fuselage to respectively rotate about a first or second rotation axis at a location of the respective movable connection, wherein a length direction of any arm of the first group of arms and its corresponding first or second rotation axis form an angle r1, 20°<r1<90°, an angle formed by the first or second rotation axis and the horizontal surface of the fuselage is angle a1, 1°<a1<86° or −86°<a1<−1°, meanwhile, a projection line of the first or second rotation axis on the horizontal surface of the fuselage and the direction of the axis extending outward the fuselage form an angle b1, 30°<b1<90°;
• the movable connection of the second group of two arms enables one end of each arm of the second group connected with the fuselage to respectively rotate about a third or fourth rotation axis at the location of the respective movable connection, wherein a length direction of any arm of the second group of arms and its corresponding third or fourth rotation axis form an angle r2, 20°<r2<160°, an angle formed by the third or fourth rotation axis and the horizontal surface of the fuselage is angle a2, 1°<a2<86° or −86°<a2<−1°, wherein a2 and a1 have the same plus or minus sign, and meanwhile, a projection line of the third or fourth rotation axis on the horizontal surface of the fuselage and the direction of the axis extending outward the fuselage form an angle b2, 30°<b2<150°;
• the movable connection of the third group of two arms enables one end of each arm of the third group connected with the fuselage to respectively rotate about a fifth or sixth rotation axis at the location of the respective movable connection, wherein a length direction of any arm of the third group of arms and its corresponding fifth or sixth rotation axis form an angle r3, 20°<r3<160°, an angle formed by the fifth or sixth rotation axis and the horizontal surface of the fuselage is angle a3, 1°<a3<86° or −86°<a3<−1°, wherein a3 and a1 have the same plus or minus sign, and meanwhile, a projection line of the fifth or sixth rotation axis on the horizontal surface of the fuselage and the direction of the axis extending outward the fuselage form an angle b3, 30°<b3<150°;
• the movable connection of the fourth group of two arms enables one end of each arm of the fourth group connected with the fuselage to respectively rotate about a seventh or eighth rotation axis at the location of the respective movable connection, wherein a length direction of any arm of the fourth group of arms and its corresponding seventh or eighth rotation axis form an angle r4, 90°<r4<160°, an angle formed by the seventh or eighth rotation axis and the horizontal surface of the fuselage is angle a4, 1°<a4<86° or −86°<a4<−1°, wherein a4 and a1 have the same plus or minus sign, and meanwhile, a projection line of the seventh or eighth rotation axis on the horizontal surface of the fuselage and the direction of the axis extending outward the fuselage form an angle b4, 90°<b4<150°.