Multi-rotor luminous aircraft

Abstract

The utility model discloses a multi-rotor luminous aircraft, which comprises an aircraft main body, a plurality of rotors and a night lamp, the plurality of rotors are arranged on the aircraft main body, the aircraft main body is connected with a protective device for protecting the rotors, and the night lamp is arranged on the protective device. Through the arrangement of the connecting rod, the limiting rod, the protruding block and the night lamp, the connecting rod slides on the aircraft body, the distance between the limiting rod and the rotor wing can be adjusted, the situation that the limiting rod makes contact with the rotor wing after being unfolded is prevented, the rotor wing is protected after the limiting rod is unfolded, and the protruding block is used for angle limiting after the limiting rod is unfolded. And the arranged limiting disc is used for limiting and fixing after the limiting rod is unfolded or limiting and fixing when the limiting rod is closed. And through the arranged grooves, the grooves formed in the night lamps are used for driving the night lamps to clamp and abut the rotor wings on the aircraft main body through the grooves when the limiting rods are closed, and the situation that the rotor wings are prone to being damaged when the rotor wings are in the unfolded state is larger than the aircraft main body is prevented.

Description

TECHNICAL FIELD

[0001] The utility model belongs to aircraft device technical field, especially, a kind of multi-rotor night light aircraft. BACKGROUND

[0002] Unmanned aerial vehicle, is using radio remote control equipment and self-provided program control device to operate not to carry person aircraft to fly at night.

[0003] And the light of night light unmanned aerial vehicle is only warning operation, easy to touch object under the condition of night operation, cause unmanned aerial vehicle rotor damage, for this, we need to protect improvement. UTILITY MODEL CONTENT

[0004] The utility model is such realization, a kind of multi-rotor night light aircraft, including aircraft main body, multiple rotors and night light, multiple the rotors are installed on aircraft main body, the protection device for protecting rotor is connected on aircraft main body, the night light is installed on protection device;

[0005] The protection device includes connecting piece, limit rod, the night light is installed on limit rod, limit rod is installed on connecting piece, connecting piece is slidingly connected on aircraft main body, when limit rod is close to aircraft main body by connecting piece, limit rod is folded and clamped on rotor.

[0006] As the utility model is preferred, the connecting piece includes connecting rod, the insert cavity is set up on aircraft main body, the connecting rod is slidingly connected in insert cavity, the limit rod is installed at the position of connecting rod away from aircraft main body.

[0007] As the utility model is preferred, the limit rod includes one number of rod and two number of rods, one number of rod and two number of rods are rotatably connected on connecting rod, the night light is installed at the position of one number of rod and two number of rods away from connecting rod, when one number of rod and two number of rods are close to aircraft main body by connecting rod, the night light is clamped on rotor.

[0008] As the utility model is preferred, recess is set up on night light, the night light is clamped on the side wall of rotor by recess.

[0009] As the utility model is preferred, further including pivot, pivot is rotatably connected on connecting rod, one number of rod and two number of rods are rotatably connected on pivot.

[0010] As the utility model is preferred, the end of connecting rod away from aircraft main body extends protruding block, when one number of rod and two number of rods are rotated to parallel position with protruding block, one number of rod and two number of rods are limited on connecting rod.

[0011] As the utility model discloses, preferably, further include the limit disc, the limit disc is installed on the pivot of aircraft main body, when the first rod, the second rod and the protruding block keep horizontal, the output end of the limit disc is inserted on the connecting rod through the first rod, the second rod and the pivot.

[0012] The utility model discloses a connecting rod, limit rod, protruding block, night light are set up, and the connecting rod is slid on the aircraft main body, can adjust the distance between limit rod and rotor, prevent limit rod from having contact with rotor after opening, and limit rod protects rotor after unfolding, and the protruding block is for angle limit of limit rod after opening.

[0013] The limit disc is set up and is used for the limit fixing of limit rod after unfolding or the limit fixing when limit rod is closed.

[0014] The recess is set up, and the recess set up on the night light is for when limit rod is closed, drives night light to be connected with rotor through the recess and leans on the aircraft main body, prevents the state of rotor from being unfolded and being damaged easily by the aircraft main body. DRAWINGS

[0015] Figure 1 It is the whole structure schematic diagram that the utility model embodiment provides;

[0016] Figure 2 It is the structure schematic diagram of closing that the utility model embodiment provides;

[0017] Figure 3 It is the close -up of A that the utility model embodiment provides;

[0018] Figure 4 It is the structure diagram of night light that the utility model embodiment provides;

[0019] Figure 5 It is the limit disc structure diagram that the utility model embodiment provides.

[0020] In the drawing: 1, aircraft main body;2, rotor;3, night light;4, limit rod;401, first rod;402, second rod;5, connecting rod;6, insert cavity;7, protruding block;8, pivot;9, recess;10, limit disc. SPECIFIC EMBODIMENT

[0021] In order to further understand the utility model content, characteristics and efficacy of the utility model, the following examples are cited, and the following is described in detail with the drawings.

[0022] The structure of the utility model is described in detail below in combination with the drawings.

[0023] As Figures 1 to 5As shown, the utility model embodiment provides a kind of multi-rotor night light aircraft, including aircraft main body 1, multiple rotors 2 and night light 3, multiple rotors 2 are installed on aircraft main body 1, aircraft main body 1 is connected with the protective device for protecting rotor 2, night light 3 is installed on protective device,

[0024] Protective device includes connecting piece, limiting rod 4, night light 3 is installed on limiting rod 4, limiting rod 4 is installed on connecting piece, connecting piece is slidingly connected on aircraft main body 1, when limiting rod 4 is close to aircraft main body 1 by connecting piece, limiting rod 4 is folded and clamped on rotor 2.

[0025] Aircraft main body 1 and multiple rotors 2: multiple rotors 2 are installed on aircraft main body 1, provide the lift required for flight.

[0026] Protective device: for protecting rotor 2, aircraft main body 1 is connected with protective device, to prevent multiple rotors 2 from being damaged externally during flight.

[0027] Night light 3 installation: night light 3 is installed on protective device, can provide visibility in night or low light environment, to improve safety.

[0028] As preferred in the utility model, connecting piece includes connecting rod 5, and the plug cavity 6 is opened in aircraft main body 1, and the connecting rod 5 is slidingly connected in the plug cavity 6, and the limiting rod 4 is installed at the position away from aircraft main body 1 of connecting rod 5.

[0029] Limiting block is provided on aircraft main body 1, for adjusting distance, and the limiting block is inserted on connecting rod 5 after passing through aircraft main body 1.

[0030] Connecting rod 5 can also be driven by gas rod, to facilitate automatic operation.

[0031] Connecting rod 5 and plug cavity 6: connecting piece includes a connecting rod 5, which is slidingly connected in the plug cavity 6 on aircraft main body 1, to facilitate adjusting the position between limiting rod 4 on connecting rod 5 and rotor 2.

[0032] As preferred in the utility model, limiting rod 4 includes a first rod 401 and a second rod 402, and one end of the first rod 401 and the second rod 402 is rotatably connected to the connecting rod 5, and the night light 3 is installed at the position away from the connecting rod 5 of the first rod 401 and the second rod 402, and when the first rod 401 and the second rod 402 are close to the aircraft main body 1 by the connecting rod 5, the night light 3 is clamped on the rotor 2.

[0033] Limiting rod 4 and connecting piece: protective device includes connecting piece and limiting rod 4. Limiting rod 4 is slidingly connected on aircraft main body 1 by connecting piece. When limiting rod 4 is close to aircraft main body 1, it can be folded and clamped on rotor 2, so as to realize closed protection to rotor 2.

[0034] As the utility model preferred, the night lamp 3 is provided with a groove 9, and the night lamp 3 is clamped on the side wall of the rotor 2 through the groove 9.

[0035] As the utility model preferred, the utility model further comprises a rotating shaft 8, the rotating shaft 8 is rotatably connected on the connecting rod 5, and the first rod 401 and the second rod 402 are rotatably connected on the rotating shaft 8.

[0036] As the utility model preferred, the end portion of the connecting rod 5 away from the aircraft body 1 extends a protruding block 7, when the first rod 401 and the second rod 402 are rotated to the parallel position with the protruding block 7, the first rod 401 and the second rod 402 are limited on the connecting rod 5.

[0037] The limiting rod 4 is composed of the first rod 401 and the second rod 402, and the two are rotatably connected on the rotating shaft 8, and the rotating shaft 8 is rotatably connected with the connecting rod 5.

[0038] The protruding block 7 is arranged, when the first rod 401 and the second rod 402 are rotated to be parallel with the protruding block 7 on the rotating shaft 8, the movement position is limited.

[0039] As the utility model preferred, the utility model further comprises a limiting disc 10, the limiting disc 10 is installed on the rotating shaft 8 of the aircraft body 1, when the first rod 401, the second rod 402 and the protruding block 7 are kept horizontal, the output end of the limiting disc 10 is inserted on the connecting rod 5 through the first rod 401, the second rod 402 and the rotating shaft 8.

[0040] The application of the limiting disc 10: the limiting disc 10 is installed on the rotating shaft 8 of the aircraft body 1, and is used for providing additional support, when the first rod 401 and the second rod 402 are horizontal, the output end thereof is inserted on the connecting rod 5 through the rotating shaft 8, the first rod 401 and the second rod 402, so as to limit and enhance the stability of the structure of the first rod 401 and the second rod 402, and the limiting disc 10 is limited on the rotating shaft 8 when the first rod 401 and the second rod 402 are clamped on the rotor 2 after being folded, so as to limit the stability of the structure of the first rod 401 and the second rod 402 when being folded.

[0041] It should be noted that, in this text, relational terms such as first and second and the like can only be used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply that there is any such actual relationship or order between these entities or operations. Moreover, the terms "include", "contain" or any other variants thereof are intended to cover non-exclusive inclusion, so that the process, method, article or equipment including a series of elements not only includes those elements, but also includes other elements not explicitly listed or inherent to such process, method, article or equipment.

[0042] Although the embodiments of the present application have been shown and described, it is to be understood that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present application, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A multi-copter luminous aerial vehicle, characterized by: The utility model provides an aircraft body (1), a plurality of rotors (2) and night lamp (3), a plurality of the rotor (2) is installed on aircraft body (1), be connected with the protection device for protecting the rotor (2) on aircraft body (1), night lamp (3) is installed on the protection device, The protection device includes a connecting piece, a limiting rod (4), the night lamp (3) is installed on the limiting rod (4), the limiting rod (4) is installed on the connecting piece, the connecting piece is slidingly connected on the aircraft body (1), when the limiting rod (4) is close to the aircraft body (1) through the connecting piece, the limiting rod (4) is folded and clamped on the rotor (2).

2. The multi-copter luminous flying vehicle of claim 1, wherein: The connecting piece includes a connecting rod (5), the aircraft body (1) is provided with an insertion cavity (6), the connecting rod (5) is slidingly connected in the insertion cavity (6), the limiting rod (4) is installed at the position away from the aircraft body (1) of the connecting rod (5).

3. A multi-copter luminous flying vehicle as claimed in claim 2, wherein: The limiting rod (4) includes a first rod (401) and a second rod (402), one end of the first rod (401) and the second rod (402) is rotatably connected to the connecting rod (5), the night lamp (3) is installed at the position away from the connecting rod (5) of the first rod (401) and the second rod (402), when the first rod (401) and the second rod (402) are close to the aircraft body (1) through the connecting rod (5), the night lamp (3) is clamped on the rotor (2).

4. A multi-copter luminous flying vehicle as claimed in claim 3, wherein: The night lamp (3) is provided with a groove (9), and the night lamp (3) is clamped on the side wall of the rotor (2) through the groove (9).

5. A multi-copter luminous flying vehicle as claimed in claim 3, wherein: It also includes a rotating shaft (8), the rotating shaft (8) is rotatably connected to the connecting rod (5), and the first rod (401) and the second rod (402) are rotatably connected to the rotating shaft (8).

6. A multi-copter luminous flying vehicle as claimed in claim 5, wherein: The end of the connecting rod (5) away from the aircraft body (1) extends a protrusion (7), when the first rod (401) and the second rod (402) are rotated to the parallel position of the protrusion (7), the first rod (401) and the second rod (402) are limited on the connecting rod (5).

7. A multi-copter luminous flying vehicle as claimed in claim 6, wherein: It also includes a limiting disc (10), the limiting disc (10) is installed on the rotating shaft (8) of the aircraft body (1), when the first rod (401), the second rod (402) and the protrusion (7) are kept horizontal, the output end of the limiting disc (10) is inserted on the connecting rod (5) through the first rod (401), the second rod (402) and the rotating shaft (8).

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