CN215155708U - Rotor type vertical take-off and landing unmanned aerial vehicle wire harness structure - Google Patents
Rotor type vertical take-off and landing unmanned aerial vehicle wire harness structure Download PDFInfo
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- CN215155708U CN215155708U CN202120304544.2U CN202120304544U CN215155708U CN 215155708 U CN215155708 U CN 215155708U CN 202120304544 U CN202120304544 U CN 202120304544U CN 215155708 U CN215155708 U CN 215155708U
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Abstract
The utility model discloses a rotor type vertical take-off and landing unmanned aerial vehicle wiring harness structure, which comprises a power supply system, a control system and a rotor system, wherein the power supply system is also connected with an engine and a generator through wiring harnesses, an RCU controller is connected in the wiring harnesses of the power supply system and the generator, and the rotor system is connected with the control system through wiring harnesses; the power supply system comprises a main storage battery and a low-voltage storage battery; the control system comprises a flight control computer, an altimeter, a data receiving and transmitting combination and a combined navigation device; the rotor system comprises a tilting rotor steering engine, a right rotary wing motor, a right aileron steering engine, a left rotor steering engine, a left rotary wing motor, a left aileron steering engine, a left V tail steering engine and a right V tail steering engine. The utility model discloses, separately lay wire with power and other signals, avoid signal transmission to disturb, chooseing for use of electric wire, protective material, electric connector etc. satisfy unmanned aerial vehicle electric wire netting design standard.
Description
Technical Field
The utility model relates to an aviation electric connector technique and electric wire, cable, pencil technical field especially relate to rotor formula VTOL unmanned aerial vehicle pencil structure.
Background
Aiming at high drift objects (or flying objects with low airspeed), monitoring and verification are carried out by using photoelectric observation equipment, and then, a laser weapon is used for striking. Because the detected relative speed of the hit object is low, the unmanned aerial vehicle platform must have low-speed flight capability or hovering capability, and the existing unmanned aerial vehicle platforms cannot meet the requirement, so that an unmanned aerial vehicle capable of vertically taking off and landing and hovering in the air needs to be developed, and the cable design of the tilting wing type vertically taking off and landing unmanned aerial vehicle is a vital part of the development project;
in order to realize that unmanned aerial vehicle can realize the wing formula VTOL that inclines to and strike the function of the lower flight thing of airspeed, need this unmanned aerial vehicle pencil of rational design in order to ensure to realize this unmanned aerial vehicle's basic function, and realize its platform index demand.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving current unmanned aerial vehicle and not having low-speed flight ability or the ability of hovering, and the unmanned aerial vehicle's that can hover rotor formula VTOL unmanned aerial vehicle pencil structure is being proposed and can be VTOL.
In order to achieve the above purpose, the utility model adopts the following technical scheme: the wiring harness structure of the rotary wing type vertical take-off and landing unmanned aerial vehicle comprises a power supply system, a control system and a rotary wing system, wherein the power supply system is also connected with an engine and a generator through wiring harnesses;
the power supply system comprises a main storage battery and a low-voltage storage battery;
the control system comprises a flight control computer, an altimeter, a data receiving and transmitting combination and a combined navigation device;
the rotor wing system comprises a tilting rotor wing steering engine, a right rotor wing motor, a right aileron steering engine, a left rotor wing motor, a left aileron steering engine, a left V tail steering engine and a right V tail steering engine;
power supply system, control system all set up the back fuselage position at unmanned aerial vehicle, and distribute about power supply system and the control system.
As a further description of the above technical solution:
the control system is connected with a ground wire harness, and the tail end of the ground wire harness is arranged at the tail wing of the unmanned aerial vehicle.
As a further description of the above technical solution:
the low-voltage battery comprises a 28V power module.
As a further description of the above technical solution:
the control system is connected with a central adapter socket through a wire harness, the central adapter socket is arranged at the middle body position of the unmanned aerial vehicle, and the right rotor steering engine, the right rotary wing motor, the right aileron steering engine, the left rotor steering engine, the left rotary wing motor and the left aileron steering engine are all connected with the central adapter socket through the wire harness.
As a further description of the above technical solution:
the engine and the generator are connected and arranged at the front body position of the unmanned aerial vehicle.
As a further description of the above technical solution:
all the wires and cables of the unmanned aerial vehicle wire harness are seamless lapped and PI composite material insulated light wires and cables according with AS22759/83,/86,/91 specifications.
As a further description of the above technical solution:
the unmanned aerial vehicle pencil that adopts the cover to prevent ripples cover protection, and prevents that ripples cover and electric connector casing are connected and are realized ground connection.
The utility model discloses following beneficial effect has:
1. compared with the prior art, this rotor formula VTOL unmanned aerial vehicle pencil structure separately lays wire with power and other signals, avoids signal transmission to disturb, and the chooseing for use of electric wire, protective material, electric connector etc. satisfy unmanned aerial vehicle electric wire netting design standard.
Drawings
Fig. 1 is a schematic diagram of the overall harness distribution of the harness structure of the rotary wing type vertical take-off and landing unmanned aerial vehicle provided by the utility model;
fig. 2 is a schematic diagram of the local wiring harness distribution of the power supply and control system of the wiring harness structure of the rotary wing type vertical take-off and landing unmanned aerial vehicle provided by the utility model;
fig. 3 is a schematic diagram of the distribution of the harness on the left side of the body of the harness structure of the rotary wing type vertical take-off and landing unmanned aerial vehicle provided by the utility model;
fig. 4 is a schematic diagram of the distribution of the harness on the right side of the body of the harness structure of the rotary wing type vertical take-off and landing unmanned aerial vehicle provided by the utility model;
fig. 5 is the utility model provides a rotor system pencil distribution schematic diagram of rotor formula VTOL unmanned aerial vehicle pencil structure.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention; the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance, and furthermore, unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Referring to fig. 1-5, the utility model provides a rotor type VTOL unmanned aerial vehicle pencil structure: the system comprises a power supply system 14, a control system 15 and a rotor system, wherein the power supply system is also connected with an engine 1 and a generator 2 through a wiring harness, an RCU controller 3 is connected in the wiring harness of the power supply system and the generator, and the rotor system is connected with the control system through the wiring harness;
the power supply system includes a main battery 16 and a low-voltage battery 17;
the control system comprises a flight control computer 22, an altimeter 21, a data receiving and transmitting combination 20 and a combined navigation device 18;
the rotor wing system comprises a tilting rotor wing steering engine 13, a right rotor wing steering engine 8, a right rotary wing motor 7, a right aileron steering engine 6, a left rotary wing steering engine 9, a left rotary wing motor 10, a left aileron steering engine 11, a left V tail steering engine 4 and a right V tail steering engine 5;
power supply system, control system all set up the back fuselage position at unmanned aerial vehicle, and distribute about power supply system and the control system.
The control system is connected with a grounding wire harness, the tail end of the grounding wire harness is arranged at the empennage of the unmanned aerial vehicle, the low-voltage storage battery comprises a 28V power module 19, the control system is connected with a central adapter socket 12 through the wire harness, the central adapter socket 12 is arranged at the middle body position of the unmanned aerial vehicle, the right rotor steering engine, the right rotor motor, the right aileron steering engine, the left rotor motor and the left aileron steering engine are all connected with the central adapter socket through the wire harness, and the engine and the generator are connected and arranged at the front body position of the unmanned aerial vehicle;
all wires and cables of the adopted unmanned aerial vehicle wire harness adopt seamless lapping and PI composite material insulating light wires and cables according with AS22759/83,/86 and/91 specifications, the adopted unmanned aerial vehicle wire harness is protected by a wave-proof sleeve, and the wave-proof sleeve is connected with an electric connector shell to realize grounding;
fuselage left side pencil (blue), fuselage right side pencil (red) and rotor system pencil (purple), the left side pencil is mainly to fly accuse, the relevant line of link and task system, and the right side pencil is mainly the relevant line of energy rotor system, and rotor system pencil is mainly the line of rotor motor and rotor steering wheel to flying pipe computer.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications and variations can be made in the embodiments or in part of the technical features of the embodiments without departing from the spirit and the scope of the invention.
Claims (7)
1. Rotor formula VTOL unmanned aerial vehicle pencil structure, its characterized in that: the system comprises a power supply system, a control system and a rotor system, wherein the power supply system is also connected with an engine and a generator through a wiring harness, an RCU controller is connected in the wiring harness of the power supply system and the generator, and the rotor system is connected with the control system through the wiring harness;
the power supply system comprises a main storage battery and a low-voltage storage battery;
the control system comprises a flight control computer, an altimeter, a data receiving and transmitting combination and a combined navigation device;
the rotor wing system comprises a tilting rotor wing steering engine, a right rotor wing motor, a right aileron steering engine, a left rotor wing motor, a left aileron steering engine, a left V tail steering engine and a right V tail steering engine;
power supply system, control system all set up the back fuselage position at unmanned aerial vehicle, and distribute about power supply system and the control system.
2. The harness structure of a rotary-wing VTOL UAV according to claim 1, wherein: the control system is connected with a ground wire harness, and the tail end of the ground wire harness is arranged at the tail wing of the unmanned aerial vehicle.
3. The harness structure of a rotary-wing VTOL UAV according to claim 1, wherein: the low-voltage battery comprises a 28V power module.
4. The harness structure of a rotary-wing VTOL UAV according to claim 1, wherein: the control system is connected with a central adapter socket through a wire harness, the central adapter socket is arranged at the middle body position of the unmanned aerial vehicle, and the right rotor steering engine, the right rotary wing motor, the right aileron steering engine, the left rotor steering engine, the left rotary wing motor and the left aileron steering engine are all connected with the central adapter socket through the wire harness.
5. The harness structure of a rotary-wing VTOL UAV according to claim 1, wherein: the engine and the generator are connected and arranged at the front body position of the unmanned aerial vehicle.
6. The harness structure of a rotary-wing VTOL UAV according to any one of claims 1-5, wherein: all the wires and cables of the unmanned aerial vehicle wire harness are seamless lapped and PI composite material insulated light wires and cables according with AS22759/83,/86,/91 specifications.
7. The harness structure of a rotary-wing VTOL UAV according to claim 6, wherein: the unmanned aerial vehicle pencil that adopts the cover to prevent ripples cover protection, and prevents that ripples cover and electric connector casing are connected and are realized ground connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120304544.2U CN215155708U (en) | 2021-02-03 | 2021-02-03 | Rotor type vertical take-off and landing unmanned aerial vehicle wire harness structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120304544.2U CN215155708U (en) | 2021-02-03 | 2021-02-03 | Rotor type vertical take-off and landing unmanned aerial vehicle wire harness structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215155708U true CN215155708U (en) | 2021-12-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120304544.2U Active CN215155708U (en) | 2021-02-03 | 2021-02-03 | Rotor type vertical take-off and landing unmanned aerial vehicle wire harness structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215155708U (en) |
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2021
- 2021-02-03 CN CN202120304544.2U patent/CN215155708U/en active Active
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