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CN-224225330-U - Tandem double-rotor structure and unmanned helicopter

CN224225330UCN 224225330 UCN224225330 UCN 224225330UCN-224225330-U

Abstract

The utility model provides a tandem double-rotor structure which comprises a first rotor wing assembly and a second rotor wing assembly, wherein the first rotor wing assembly is arranged at the front end of an unmanned helicopter body, the second rotor wing assembly is arranged at the rear end of the unmanned helicopter body, the bottom ends of rotor wing shafts of the first rotor wing assembly and the second rotor wing assembly are respectively connected with corresponding mounting seats, the mounting seats are connected with the unmanned helicopter body, and the mounting seats have preset forward tilting angles relative to the unmanned helicopter body. According to the utility model, by means of simultaneously inclining the front rotor wing and the rear rotor wing forwards by a certain angle, the plane body can be kept as horizontal as possible when the unmanned helicopter flies forwards at a high speed, and only the front paddle disc and the rear paddle disc incline forwards to generate forward propulsion component force, so that the windward area of the plane body can be kept to be minimum, the resistance of the plane body during the front flight can be reduced, the windward area of the paddle discs can be smaller, the forward flight resistance can be further reduced, the aerodynamic performance of the unmanned helicopter is improved, and the applicability of the unmanned helicopter is improved.

Inventors

  • WAN DAN

Assignees

  • 湘潭创航新材料科技有限公司

Dates

Publication Date
20260512
Application Date
20250514

Claims (8)

  1. 1. The tandem double-rotor structure is characterized by comprising a first rotor assembly and a second rotor assembly, wherein the first rotor assembly is arranged at the front end of an unmanned helicopter body, and the second rotor assembly is arranged at the rear end of the unmanned helicopter body; The first rotor wing assembly and the second rotor wing assembly comprise blades, a rotor wing head, a rotor wing shaft, a periodical pitch control module and a mounting seat; The rotor shaft bottom of first rotor subassembly the second rotor subassembly respectively with correspond the mount pad is connected, the mount pad with the fuselage is connected, the mount pad for the fuselage has the angle of prearranging, so that first rotor subassembly the whole second rotor subassembly for the fuselage has the angle of prearranging, thereby the oar dish that the paddle constitutes has the angle of prearranging for the fuselage.
  2. 2. The tandem twin rotor structure of claim 1, wherein said first rotor assembly and said second rotor assembly each have the same rake angle with respect to said fuselage.
  3. 3. The tandem twin rotor structure according to claim 1, wherein the rotor shaft lengths of the first rotor assembly and the second rotor assembly are set to be identical, or, The rotor shaft lengths of the first rotor assembly and the second rotor assembly are set to be different.
  4. 4. The tandem twin rotor structure of claim 1, wherein the mounting base includes a base body and a plurality of connectors disposed on both sides of the base body, the base body being connected to the bottom end of the rotor shaft, the connectors being connected to the front or rear end of the fuselage.
  5. 5. The tandem twin rotor structure of claim 4, wherein each of the connectors is formed by a pair of clips, one of the clips being integrally or fixedly connected with the housing and simultaneously detachably connected with the other clip, the front and rear ends of the fuselage being provided with connecting shafts, the clips being engaged with the connecting shafts, the connecting shafts having a predetermined rake angle with respect to the fuselage.
  6. 6. The tandem twin rotor structure of claim 1, wherein the forward and aft ends of the fuselage are each provided with a universal coupling for connecting and synchronizing rotation of the drive structure in the mount with the drive shaft in the fuselage.
  7. 7. The tandem twin rotor structure of any one of claims 1-6, wherein the forward tilt angles of the first rotor assembly and the second rotor assembly are each set to 5-10 °.
  8. 8. An unmanned helicopter comprising a fuselage and a tandem twin rotor structure as claimed in any one of claims 1 to 6.

Description

Tandem double-rotor structure and unmanned helicopter Technical Field The utility model relates to the technical field of unmanned helicopters, in particular to a tandem double-rotor wing structure and an unmanned helicopter. Background In recent years, with the progress of technologies in various fields, particularly the progress of technologies such as flight control, unmanned helicopters have been rapidly developed, and have been increasingly focused. In the field of unmanned helicopters, dual rotors are commonly used, which can be divided into tandem, and coaxial. The two rotors are distributed on two sides of the fuselage, so that the forward flight resistance is high and the rotors are rarely used. The coaxial rotor is characterized in that two rotors with opposite rotation directions are arranged on the upper side and the lower side of a rotor shaft, the two rotor disks are completely overlapped, the upper rotor and the lower rotor are in pneumatic mutual interference, and meanwhile, a complex operating mechanism and a special hub increase waste resistance and reduce forward flight efficiency. The tandem type helicopter is an unmanned helicopter double-rotor structure which is applied more at present, a rotor is respectively arranged in front of and behind a helicopter body, two rotors of the helicopter are identical and opposite in rotation direction, and the rotor disks of the two rotors are overlapped to a certain extent and synchronous in rotation phase. Therefore, in order to prevent the two pairs of rotors from rubbing against each other, the rotation of the rotors requires phase synchronization, which requires a synchronizing shaft penetrating the fuselage, which also increases the structural complexity and weight. In the related art, the scheme that the front and back of the two pairs of rotary wings are arranged is also adopted, the two pairs of rotary wings can be staggered in height, so that even if the rotation phases of the two pairs of rotary wings are not synchronous, the two pairs of rotary wings cannot scratch each other, and compared with the traditional scheme, a synchronous shaft is not required to be arranged, and the lifting effect is brought. With further updating and iteration of unmanned helicopter technology, the aerodynamic performance requirements of unmanned helicopters are higher and higher, and therefore further improvements are needed. Disclosure of utility model The utility model aims to provide a longitudinal double-rotor wing structure which is arranged in a front-back high-low mode and is inclined forwards and a scheme of an unmanned helicopter aiming at the defects in the background technology, so that the unmanned helicopter has better aerodynamic performance. In order to achieve the above object, the present utility model provides a tandem double rotor structure, comprising a first rotor assembly and a second rotor assembly, wherein the first rotor assembly is arranged at the front end of an unmanned helicopter body, and the second rotor assembly is arranged at the rear end of the unmanned helicopter body; The first rotor wing assembly and the second rotor wing assembly comprise blades, a rotor wing head, a rotor wing shaft, a periodical pitch control module and a mounting seat; The rotor shaft bottom of first rotor subassembly the second rotor subassembly respectively with correspond the mount pad is connected, the mount pad with the fuselage is connected, the mount pad for the fuselage has the angle of prearranging, so that first rotor subassembly the whole second rotor subassembly for the fuselage has the angle of prearranging, thereby the oar dish that the paddle constitutes has the angle of prearranging for the fuselage. Further, the first rotor assembly and the second rotor assembly each have the same forward tilt angle with respect to the fuselage. Further, the rotor shaft lengths of the first rotor assembly and the second rotor assembly are set to be the same, or, The rotor shaft lengths of the first rotor assembly and the second rotor assembly are set to be different. Further, the mount pad includes the pedestal and sets up a plurality of connectors of pedestal both sides, the pedestal with the bottom of rotor shaft is connected, the connector with the front end or the rear end of fuselage are connected. Further, each connector is composed of a pair of hoops, one of the hoops is integrally or fixedly connected with the base body, the other hoop is detachably connected with the other hoop, connecting shafts are arranged at the front end and the rear end of the machine body, the hoops are clamped with the connecting shafts, and the connecting shafts have preset forward tilting angles relative to the machine body. Further, the front end and the rear end of the machine body are respectively provided with a universal coupling, and the universal couplings are used for enabling the transmission structure in the mounting seat to be connected with the transmissi