Multi-Rotor Passenger-Carrying Aircraft with Foldable Aircraft Arm

Abstract

A multi-rotor passenger-carrying aircraft with foldable aircraft arm is disclosed, including an aircraft body, a fixing mechanism, a connector and an aircraft arm. The fixing mechanism is fastened on the aircraft body, an end of the aircraft arm is articulated to the fixing mechanism, the fixing mechanism is provided with at least one first mounting hole, and the aircraft arm is provided with at least one second mounting hole. When the aircraft arm is in a folded state, one end of the connector is removably attached to the fixing mechanism through a first fastener, and the other end of the connector is removably attached to the aircraft arm through a second fastener, so that the fixing mechanism is kept to be at a first angle with the aircraft arm. When the aircraft arm is in a working state, a third fastener is adapted to pass through both the first and second mounting holes to cause the fixing mechanism to be fixedly connected to the aircraft arm and kept at a second angle with the aircraft arm. The above multi-rotor passenger-carrying aircraft with foldable aircraft arm can change the angle between the aircraft arm and the fixing mechanism to achieve switching of the aircraft arm between the folded state and the working state, which is convenient for transportation and storage.

Claims

1. A multi-rotor passenger-carrying aircraft with foldable aircraft arm, comprising: an aircraft body, a fixing mechanism, a connector having opposing first and second connector ends, and an aircraft arm, wherein an end of the aircraft arm is articulated to the fixing mechanism and the fixing mechanism is fastened to the aircraft body and includes a first mounting hole, and the aircraft arm includes a second mounting hole; wherein when the aircraft arm is in a folded state, the first connector end is removably attached to the fixing mechanism with a first fastener, and the second connector end is removably attached to the aircraft arm with a second fastener, so that the fixing mechanism is maintained at a first angle relative to the aircraft arm; and when the aircraft arm is in a working state, a third fastener is adapted to pass through both the first and second mounting holes to cause the fixing mechanism to be fixedly connected to the aircraft arm and maintained at a second angle relative to the aircraft arm.

2. The multi-rotor passenger-carrying aircraft of claim 1, wherein the first connector end includes a third mounting hole, and the first fastener is adapted to pass through the first and third mounting holes to attach a first end of the fastener to the fixing mechanism; and the second connector end includes a fourth mounting hole, and the second fastener is adapted to pass through the second and fourth mounting holes to attach a second end of the fastener to the aircraft arm.

3. The multi-rotor passenger-carrying aircraft of claim 1, wherein the fixing mechanism includes first and second fasteners disposed on the aircraft body and spaced apart relative to each other, a rotation shaft is connected between the first and second fasteners, and an end of the aircraft arm is articulated to the rotation shaft.

4. The multi-rotor passenger-carrying aircraft of claim 3, wherein the fixing mechanism includes mounting holes respectively arranged on the first and second fasteners.

5. The multi-rotor passenger-carrying aircraft of claim 1, wherein an end of the aircraft arm includes a sleeve, two lugs are arranged at a bottom of the sleeve and are spaced apart from each other, and the aircraft arm includes mounting holes respectively arranged on the lugs.

6. The multi-rotor passenger-carrying aircraft of claim 1, wherein the first fastener is selected from the group consisting of a pin, rivet and bolt.

7. The multi-rotor passenger-carrying aircraft of claim 1, wherein the second fastener is selected from the group consisting of a pin, rivet and bolt.

8. The multi-rotor passenger-carrying aircraft of claim 1, wherein the third fastener is selected from the group consisting of a pin, rivet and bolt.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0015] FIG. 1 is a first schematic diagram of a multi-rotor passenger-carrying aircraft with foldable aircraft arm in a wording state according to one embodiment of the present disclosure.

[0016] FIG. 2 is a second schematic diagram of a multi-rotor passenger-carrying aircraft with foldable aircraft arm in a wording state according to one embodiment of the present disclosure.

[0017] FIG. 3 is a first schematic diagram of a multi-rotor passenger-carrying aircraft with foldable aircraft arm in a folded state according to one embodiment of the present disclosure.

[0018] FIG. 4 a second schematic diagram of a multi-rotor passenger-carrying aircraft with foldable aircraft arm in a folded state according to one embodiment of the present disclosure.

[0019] Description of reference signs:

[0020] 1 fixing mechanism, 2 connector, 3 aircraft arm, 4 sleeve, 10 first fastener, 10a first mounting hole, 11 second fastener, 12 rotation shaft, 40a second mounting hole, and 100 aircraft body.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0021] In the following description of embodiments, reference is made to the accompanying drawings which form a part hereof, and in which it is shown by way of illustration specific embodiments of the disclosure that can be practiced It is to be understood that other embodiments can be used and structural changes can be made without departing from the scope of the disclosed embodiments.

[0022] As shown in FIGS. 1-4, a multi-rotor passenger-carrying aircraft with foldable aircraft arm is provided. The multi-rotor passenger-carrying aircraft with foldable aircraft arm includes an aircraft body 100, a fixing mechanism 1, a connector 2 and an aircraft arm 3, wherein the fixing mechanism 1 is fastened on the aircraft body 100, an end of the aircraft arm 3 is articulated to the fixing mechanism 1, the fixing mechanism 1 is provided with at least one first mounting hole 10a, the aircraft arm 3 is provided with at least one second mounting hole 40a; wherein when the aircraft arm 3 is in a folded state, one end of the connector 2 is removably attached to the fixing mechanism 1 through a first fastener, and the other end of the connector 2 is removably attached to the aircraft arm 3 through a second fastener, so that the fixing mechanism 1 is kept to be at a first angle with the aircraft arm 3; and wherein when the aircraft arm 3 is in a working state, a third fastener is adapted to pass through both the first and second mounting holes 10a, 40a, to cause the fixing mechanism 1 being kept to be at a second angle with the aircraft arm 3. For the above multi-rotor passenger-carrying aircraft with foldable aircraft arm, the aircraft arm 3 is articulated to the fixing mechanism 1 that the angle between the aircraft arm 3 and the fixing mechanism 1 is adjustable, to achieve switching of the aircraft arm 3 between the folded state and the working state. During the transportation and storage of the aircraft, the space occupied by the aircraft can be effectively reduced by mounting the connector 2 through the first and second fasteners to keep a first angle between the fixing mechanism 1 and the aircraft arm 3; and when the aircraft is to be used, the connector 2 is removed, and the fixing mechanism 1 is attached to the aircraft arm 3 through the third fastener, to keep a second angle between the fixing mechanism 1 and the aircraft arm 3. In this way, the aircraft is simple in structure and easy in installation.

[0023] In the embodiment, one end of the connector 2 is provided with a third mounting hole, and the first fastener is adapted to pass through both the first mounting hole 10a and the third mounting hole to cause the end of the fastener 2 is attached to the fixing mechanism 1; and the other end of the connector 2 is provided with a fourth mounting hole, and the second fastener is adapted to pass through both the second mounting hole 40a and the fourth mounting hole to cause the other end of the fastener 2 is attached to the aircraft arm 3. In this way, on additional opening is required, which reduces the manufacturing cost.

[0024] As shown in FIG. 4, the fixing mechanism 1 includes a first fastener 10 and a second fastener 11, the first fastener 10 and the second fastener 11 are arranged on the aircraft body 100 and spaced apart from each other, a rotation shaft 12 is connected between the first fastener 10 and the second fastener 11, and an end of the aircraft arm 3 is articulated to the rotation shaft 12. The aircraft arm 3 is articulated to the fixing mechanism 1 through a pin. In this way, the operation is reliable and the structure is easy to disassemble.

[0025] In the embodiment, the fixing mechanism is provided with two mounting holes 10a correspondingly arranged on the first fastener and the second fastener 10, 11 respectively. The first fastener is a pin. An end of the aircraft arm 3 is provided with a sleeve 4, two lugs are arranged on the bottom of the sleeve 4 and spaced apart from each other, and the aircraft arm is provided with two second mounting holes 40a correspondingly arranged on the two lugs respectively. The second fastener is a pin. During the transportation and storage of the aircraft, one end of the connector 2 is fastened on the fixing mechanism 1 through the pin, and the other end of the connector 2 is fastened on the aircraft arm 3 through the pin, which is easy to disassemble. The third fastener is a rivet. When the aircraft is to be used, the connector 2 is removed, and the fixing mechanism 1 is attached to the aircraft arm 3 through the rivet, with a reliable connection.

[0026] It can be understood that in other embodiments, the first fastener may be a rivet, bolt or any other suitable fastener, the second fastener may be a rivet, bolt or any other suitable fastener, and the third fastener may be a pin, bolt or any other suitable fastener, according to the actual conditions.

[0027] Technical features of the above embodiments can be combined arbitrarily. For simplify and clarity, not all of the possible combinations of the technical features of the above embodiments are described, however, these combinations should be considered within the scope of the description provided that there is no contradiction therebetween.

[0028] The above are preferred embodiments of the present disclosure described in detail, and should not be deemed as limitations to the scope of the present disclosure. It should be noted that variations and improvements will become apparent to those skilled in the art to which the present disclosure pertains without departing from its spirit and scope. Therefore, the scope of the present disclosure is defined by the appended claims.