CN211893665U

CN211893665U - Novel unmanned aerial vehicle machine carries power generation system

Info

Publication number: CN211893665U
Application number: CN201921844526.2U
Authority: CN
Inventors: 孙伟
Original assignee: Hebei Chunbo Aviation Technology Co ltd
Current assignee: Hebei Chunbo Aviation Technology Co ltd
Priority date: 2019-10-30
Filing date: 2019-10-30
Publication date: 2020-11-10
Anticipated expiration: 2029-10-30

Abstract

The utility model discloses a novel unmanned aerial vehicle machine carries power generation system in the technical field of unmanned aerial vehicle machine carries power generation, including fuel engine, the left end swing joint engine crankshaft of fuel engine, the left end face of fuel engine sets up mounting structure, the output of fuel engine connects the screw, the left end of engine crankshaft connects machine carries control system, machine carries control system through throttle control output connection fuel engine, fuel engine passes through engine crankshaft swing joint generator, reduces machine carries power reserve volume, reaches the weight reduction purpose, and for oil-electricity hybrid power unmanned aerial vehicle, the generator can directly supply power, lightens weight from aspects such as complete machine overall layout, through two aspects subtract heavy and optimize the organism, can load task equipment or more load fuel under the same gross weight, increase the time of flight, or increase the load capacity, under the condition of reducing the weight of fuel oil, the time and the range of the flight can be increased.

Description

Novel unmanned aerial vehicle machine carries power generation system

Technical Field

The utility model relates to an unmanned aerial vehicle machine carries the electricity generation technical field, specifically is a novel unmanned aerial vehicle machine carries power generation system.

Background

The existing airplane is a pure-oil-drive or pure-electric-drive type flight power system, and a few unmanned planes such as a vertical take-off and landing unmanned plane are used together, but the insufficient electric quantity seriously restricts the time, range and task carrying capacity of the unmanned plane. The utility model discloses power generation system uses the shaft of oil-driven engine to drive the electricity generation simultaneously at the unmanned aerial vehicle flight stage, for the power supply of airborne battery or electronic propulsion system, can have certain improvement to the time of endurance, the journey of flight to alleviate the weight of battery from the complete machine, alleviate aircraft complete machine weight, make the aircraft have bigger equipment carrying capacity under the same condition; the prior art is a storage lithium battery power supply system, and has high cost, heavy weight and limited power storage capacity. Therefore, more and better batteries have to be added due to power requirement, the weight of the airplane is greatly increased, the endurance of the airplane is influenced, the airplane enters into vicious circle, and the navigation quality of the airplane is also influenced. The invention has the characteristic of synergy and high efficiency, and improves the navigation time and the navigation range. Therefore, a novel unmanned aerial vehicle airborne power generation system is provided.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a novel unmanned aerial vehicle machine carries power generation system to solve the problem that proposes in the above-mentioned background art.

In order to achieve the above object, the utility model provides a following technical scheme: a novel unmanned aerial vehicle airborne power generation system comprises a fuel engine, wherein the left end of the fuel engine is movably connected with an engine crankshaft, the left end surface of the fuel engine is provided with a mounting structure, the output end of the fuel engine is connected with a propeller, the left end of the engine crankshaft is connected with an airborne control system, the airborne control system is connected with a fuel engine through the control output of an accelerator, the fuel engine is movably connected with a generator through an engine crankshaft, a bearing is arranged at the joint of a rotor at the output end of the generator and the engine crankshaft, the electrical output of the generator is connected with a power supply manager, the two-way electrical output of the power supply manager is connected with an onboard control system, the power supply manager is electrically connected with the airborne power supply, the power supply manager is electrically connected with the electrical system for the airborne equipment, and the airborne power supply is electrically connected with the electrical system for the airborne equipment.

Furthermore, the power manager comprises a battery sensor electrically connected with the onboard power supply, the battery sensor is electrically connected with the main control unit, and the main control unit is electrically connected with the onboard control system.

Further, the generator is a three-phase brushless alternating current motor, and the output power of the generator is 4000w-4500 r/min.

Further, the diameter of the generator is 175mm, the thickness of the generator is 63mm, and the no-load voltage of the generator is 10v-1000 r/min.

Furthermore, mounting structure is including fixing the fixed plate at fuel engine left end face, and the outer wall of fixed plate evenly sets up the screw hole, and the screw hole is totally four groups.

Compared with the prior art, the beneficial effects of the utility model are that:

1. the reserve capacity of the airborne power supply is reduced, and the purpose of weight reduction is achieved;

2. for the oil-electricity hybrid power unmanned aerial vehicle, the generator can directly supply power, the weight is reduced from the aspects of overall layout and the like of the whole unmanned aerial vehicle, and the unmanned aerial vehicle optimizes the unmanned aerial vehicle body by reducing the weight in two aspects;

3. under the same total takeoff weight, mission equipment or more fuel oil can be loaded, and the time and the range of flight are increased or the load capacity is increased;

4. under the condition of reducing the weight of fuel oil, the time and the range of the flight can be increased.

Drawings

FIG. 1 is a schematic structural view of the present invention;

fig. 2 is a schematic diagram of the present invention.

In the figure: 1. a fuel-powered engine; 2. an engine crankshaft; 3. an onboard control system; 4. a mounting structure; 5. a propeller; 6. a power manager; 7. a generator; 8. an onboard power supply; 9. and the airborne equipment uses the electric system.

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.

The utility model provides a technical scheme: a novel unmanned aerial vehicle airborne power generation system, please refer to fig. 1, comprises a fuel engine 1, wherein the left end of the fuel engine 1 is movably connected with an engine crankshaft 2, the left end surface of the fuel engine 1 is provided with a mounting structure 4, the output end of the fuel engine 1 is connected with a propeller 5, the left end of the engine crankshaft 2 is connected with an airborne control system 3, and the airborne control system 3 can be remotely controlled, such as a common robot which can be remotely controlled in life, so that a worker can conveniently control the airborne control system 3 indoors to operate an unmanned aerial vehicle;

referring to fig. 1 and 2, an onboard control system 3 is connected with a fuel engine 1 through an accelerator control output, the fuel engine 1 is movably connected with a generator 7 through an engine crankshaft 2, a bearing is arranged at the joint of a rotor at the output end of the generator 7 and the engine crankshaft 2, when the unmanned aerial vehicle runs, the fuel engine 1 is controlled by the onboard control system 3 through an accelerator, the fuel engine 1 can drive the propeller 5 to rotate during running so that the unmanned aerial vehicle takes off, the fuel engine 1 is connected with the generator 7 through the engine crankshaft 2 at the rear part during rotating motion, thereby driving the rotor of the generator 7 to rotate, and a larger margin is left when the fuel engine 1 rotates, so that only a small amount of energy is needed when the generator 7 is driven, thereby utilizing the little kinetic energy of the fuel engine 1 to be converted into electric energy for storage or direct use;

referring to fig. 1 and 2, the generator 7 is electrically connected to the power manager 6, the power manager 6 is electrically connected to the onboard control system 3 in a bidirectional manner, and the power manager 6 is electrically connected to the onboard power supply 8, so that when the fuel engine 1 drives the generator 7 to operate, the electric quantity can be stored in the onboard power supply 8, the power manager 6 is electrically connected to the onboard equipment power utilization system 9, the onboard power supply 8 is electrically connected to the onboard equipment power utilization system 9, and the operating state of the generator 7 can be conveniently adjusted by the power manager 6 in different states of the generator 7;

the power supply manager 6 comprises a battery sensor electrically connected with the airborne power supply 8, the battery sensor is electrically connected with the main control unit, the main control unit is electrically connected with the airborne control system 3, and under the condition of normal battery charging and discharging, if the battery sensor detects that the battery in the airborne power supply 8 is in an undercharging state, the main control unit can correspondingly increase the working voltage of the generator 7, improve the charging efficiency of the generator 7 and carry out quick charging;

when the battery electric quantity in the onboard power supply 8 is in a saturated state, the voltage of the generator is correspondingly reduced, so that the generator 7 is in an idle state, unnecessary overcharge on the battery is avoided, the consumed torque is reduced, the fuel consumption can be reduced, the charging state is kept in a safe level range, the battery works in a benign interval, and the service life of the battery is prolonged.

The generator 7 is a three-phase brushless alternating current motor, and the output power of the generator 7 is 4000w-4500 r/min.

The diameter of the generator 7 is 175mm, the thickness of the generator 7 is 63mm, and the no-load voltage of the generator 7 is 10v-1000 r/min.

Mounting structure 4 evenly sets up the screw hole including fixing the fixed plate at 1 left end face of fuel engine, the outer wall of fixed plate, and the screw hole is total four groups, and mounting structure 4 can be convenient through the screw hole install fuel engine and use on unmanned aerial vehicle.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides a novel unmanned aerial vehicle machine carries power generation system, includes fuel engine (1), its characterized in that: the left end of the fuel engine (1) is movably connected with an engine crankshaft (2), the left end face of the fuel engine (1) is provided with a mounting structure (4), the output end of the fuel engine (1) is connected with a propeller (5), the left end of the engine crankshaft (2) is connected with an airborne control system (3), the airborne control system (3) is connected with the fuel engine (1) through throttle control output, the fuel engine (1) is movably connected with a generator (7) through the engine crankshaft (2), a bearing is arranged at the joint of the rotor at the output end of the generator (7) and the engine crankshaft (2), the generator (7) is electrically connected with a power supply manager (6), the power supply manager (6) is electrically connected with the airborne control system (3) in a two-way manner, the power supply manager (6) is electrically connected with an airborne power supply (8), the power supply manager (6) is electrically connected with the electrical system (9) for the airborne equipment in an output mode, and the airborne power supply (8) is electrically connected with the electrical system (9) for the airborne equipment in an output mode.

2. The novel airborne power generation system of unmanned aerial vehicle of claim 1, characterized in that: the power supply manager (6) comprises a battery sensor electrically connected with the airborne power supply (8), the battery sensor is electrically connected with the main control unit, and the main control unit is electrically connected with the airborne control system (3).

3. The novel airborne power generation system of unmanned aerial vehicle of claim 1, characterized in that: the generator (7) is a three-phase brushless alternating current motor, and the output power of the generator (7) is 4000w-4500 r/min.

4. The novel airborne power generation system of unmanned aerial vehicle of claim 1, characterized in that: the diameter of the generator (7) is 175mm, the thickness of the generator (7) is 63mm, and the no-load voltage of the generator (7) is 10v-1000 r/min.

5. The novel airborne power generation system of unmanned aerial vehicle of claim 1, characterized in that: the mounting structure (4) comprises a fixing plate block fixed on the left end face of the fuel engine (1), threaded holes are uniformly formed in the outer wall of the fixing plate block, and the number of the threaded holes is four.