CN214138978U - Power system and aircraft adopting same - Google Patents
Power system and aircraft adopting same Download PDFInfo
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- CN214138978U CN214138978U CN202121839550.4U CN202121839550U CN214138978U CN 214138978 U CN214138978 U CN 214138978U CN 202121839550 U CN202121839550 U CN 202121839550U CN 214138978 U CN214138978 U CN 214138978U
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- 230000009467 reduction Effects 0.000 abstract description 2
- 238000001816 cooling Methods 0.000 description 6
- 239000000446 fuel Substances 0.000 description 6
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- 230000008859 change Effects 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
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Abstract
The utility model discloses a driving system and adopt its aircraft, including engine, first motor, second motor and clutch, the pivot of first motor is connected with the crank shaft transmission of engine, and the bent axle and the clutch input of engine are connected, the pivot and the clutch output transmission of second motor are connected. Power system adopt the oil-electricity hybrid mode, both had powerful dynamic performance, had good duration and load-carrying capacity simultaneously again to can reduce fuel-powered oil consumption, energy saving and emission reduction improves the comprehensive ability of aircraft, can switch to the condition of difference, nimble suitability is strong, flight stability is good, the reliability is high.
Description
Technical Field
The utility model relates to an unmanned vehicles technical field especially relates to a driving system and adopt its aircraft.
Background
The power system of the unmanned aerial vehicle usually adopts electric power or fuel power, the electric power system is limited by low energy density of a battery and large weight of the battery, the endurance time is short, the load capacity is small, the efficiency of the fuel power system is low, the power is small, the torsion is small, the emission is high, and the flexibility, the reliability and the controllability of the unmanned aerial vehicle are limited by the singleness of the conventional power system.
SUMMERY OF THE UTILITY MODEL
The utility model discloses the technical problem that will solve and the technical task who provides improve prior art, provide a driving system, it is single to solve driving system in the prior art, is difficult to satisfy the problem of flight flexibility, the nature controlled demand.
For solving the above technical problem, the technical scheme of the utility model is that:
a power system comprises an engine, a first motor, a second motor and a clutch, wherein a rotating shaft of the first motor is in transmission connection with a crankshaft of the engine, the crankshaft of the engine is connected with an input end of the clutch, and a rotating shaft of the second motor is in transmission connection with an output end of the clutch. Power system adopt the oil-electricity hybrid mode, utilize the powerful dynamic characteristic that the motor has, improve the dynamic performance when the condition such as aircraft starting, acceleration, improve the dynamic performance of aircraft to utilize fuel power can improve duration and load-carrying capacity, and can utilize electrode auxiliary drive's mode to reduce the oil consumption of engine, the row falls in the festival, improves the comprehensive ability of aircraft, can carry out nimble switching to the condition of difference, the suitability is stronger.
Further, the rotating shaft of the first motor is in transmission connection with the crankshaft of the engine through a synchronous pulley assembly or a gear assembly. Simple structure, high transmission reliability and good stability.
Furthermore, the rotating shaft of the second motor is in transmission connection with the output end of the clutch through a synchronous pulley assembly or a gear assembly. Simple structure, high transmission reliability and good stability.
Further, a cooling fan is arranged on the engine. The cooling fan is used for cooling the engine, the temperature of the engine is guaranteed to be within a stable preset working temperature range, and working stability is improved.
Further, the clutch output end passes through the transfer assembly to drive at least two rotor assemblies to act simultaneously. Driving system adopt the mode of a plurality of rotor subassembly work of one set of driving system drive, driving system concentrates, compact structure, easy to maintain.
Further, the transfer assembly comprises a gear set, the gear set comprises a power input gear piece and a power output gear piece, the power input gear piece is driven to rotate by the output end of the clutch, the power input gear piece is at least meshed with the two power output gear pieces, and each power output gear piece is in transmission connection with one rotor wing assembly respectively. Simple structure, high transmission efficiency and good stability.
Further, the first motor is used for starting the engine, and the engine drives the first motor to generate power, or the engine and the first motor drive output together, or the first motor rotates along with the idling of the engine. Various working modes can be switched according to conditions, and the flexibility and the applicability are strong.
Furthermore, when the rotating speed of the output end of the clutch driven by the second motor is the same as that of the input end of the clutch driven by the engine, the input end of the clutch is in meshing transmission with the output end of the clutch. The stability of the power switched to the engine drive output is ensured, the conditions of jitter and rapid speed change of the aircraft are avoided, and the flight stability and the control accuracy are improved.
Furthermore, when the engine stops unexpectedly, the input end of the clutch and the output end of the clutch are disconnected for transmission, the second motor drives the output end of the clutch to rotate independently, when the engine breaks down, the second motor is used for continuously maintaining power output, the falling condition of the aircraft is avoided, the safety guarantee is realized by the second motor, and the accidental condition is avoided.
An aircraft comprises the power system, and is good in power performance, long in endurance time and good in loading capacity, and the signals are controlled.
Compared with the prior art, the utility model discloses the advantage lies in:
power system adopt the oil-electricity hybrid mode, both had powerful dynamic performance, had good duration and load-carrying capacity simultaneously again to can reduce fuel-powered oil consumption, energy saving and emission reduction improves the comprehensive ability of aircraft, can carry out the power switch to the condition of difference, nimble suitability is strong, flight stability is good, the reliability is high.
Drawings
FIG. 1 is an overall schematic diagram of a power system;
FIG. 2 is a top structural view of the power system coupled to the rotor assembly;
FIG. 3 is a side view schematic illustration of the powertrain coupled to the transfer assembly;
FIG. 4 is an internal schematic view of the transfer assembly.
In the figure:
the engine 1, the first motor 2, the second motor 3, the clutch 4, the clutch input 41, the clutch output 42, the radiator fan 5, the rotor assembly 6, the transfer assembly 7, the power input gear piece 71 and the power output gear piece 72.
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 embodiment of the utility model discloses a driving system can switch between electronic and fuel power according to the condition, improves flight ability, and continuation of the journey is long, load carrying capacity is big, and power is big, and the flexibility is good.
As shown in fig. 1 to 4, a power system, which is mainly used for an unmanned aerial vehicle, includes an engine 1, a first motor 2, a second motor 3 and a clutch 4, the first motor 2 and the second motor 3 are powered by a battery pack, a rotating shaft of the first motor 2 is in transmission connection with a crankshaft of the engine 1 through a synchronous pulley assembly, the crankshaft of the engine 1 is connected with a clutch input end 41, and a rotating shaft of the second motor 3 is in transmission connection with a clutch output end 42 through a synchronous pulley assembly, so that the structure is compact, the organic combination of electric power and fuel power is realized, the advantages of electric power and fuel power are combined and the respective disadvantages are complemented, the power output performance is improved, the flexible switching can be performed according to the situation, the flexible applicability is strong, and the requirements of various flight conditions are met.
When the aircraft is started, the clutch 4 is in a disconnected state (the clutch input end 41 is in non-transmission connection with the clutch output end 42), the first motor 2 is powered by the battery pack, so that the first motor 2 starts the engine 1 to rotate through the synchronous pulley assembly, then the engine 1 is in an idle state, and then the first motor 2 rotates along with the engine 1 in an idle speed;
then, the second motor 3 is powered by a battery pack, the second motor 3 drives the clutch output end 42 to rotate through a synchronous pulley assembly, and the rotating speed of the clutch output end 42 is the same as that of the input end of the clutch 4 driven by the engine 1;
then, the clutch 4 is switched to the engaged state (the clutch input end 41 and the clutch output end 42 are engaged for transmission), so that the engine 1 drives the clutch output end 42 to rotate at the same time, and at the moment, the second motor 3 rotates along with the engine 1 in an idling mode through a synchronous pulley assembly;
the rotating speed of the engine 1 is increased from an idle speed to a working rotating speed and the working rotating speed is maintained, the first motor 2 synchronously rotates along with the engine 1 through a synchronous pulley component, the state of the first motor 2 is determined by a controller of the first motor, the state comprises three types, namely the engine 1 drives the first motor 2 to generate electricity, the engine 1 and the first motor 2 jointly drive output, and the first motor 2 rotates along with the engine 1 in an idle speed; the second motor 3 is determined by the controller, the state comprises the driving output of the engine 1 and the second motor 3, and the second motor 3 rotates along with the idling of the engine 1.
When the power of the engine is enough to maintain a stable working rotating speed, if the electric power of the battery pack is lower than a preset value at the moment, the first motor 2 carries out a power generation state, the engine 1 drives the first motor 2 to generate power, and the first motor 2 charges the battery pack;
when the power of the engine is not enough to maintain a stable working rotating speed and the electric power of the battery pack is higher than a preset value, the first motor 2 is in a driving state, the engine 1 and the first motor 2 are driven and output together, namely the battery pack supplies power to the first motor 2, the first motor 2 and the engine 1 work in parallel, and the rotating speed is guaranteed to be at the working rotating speed;
when the engine 1 is stopped accidentally, the clutch is switched to a disconnected state, namely the clutch input end 41 and the clutch output end 42 are disconnected for transmission, the second motor 3 drives the clutch output end 42 to rotate independently, the aircraft is maintained in a flying state, the aircraft is prevented from falling, and the safety and reliability of the flying are improved.
In order to improve the stability of the engine, the power system is further provided with a cooling fan 5, the cooling fan 5 is powered by the battery pack, the cooling fan 5 is arranged on the engine 1 to cool the engine, the temperature of the engine is guaranteed to be within a stable preset working temperature range, and the working stability is improved.
In this embodiment, the aircraft adopts many rotor crafts, driving system only set up one set, by the action of a plurality of rotor subassemblies of a set of driving system simultaneous drive 6, specifically, rotor subassembly 6 be provided with four groups, the aircraft is four rotor crafts promptly, clutch output 42 passes through transfer assembly 7 and moves with a plurality of rotor subassemblies of simultaneous drive 6.
As shown in fig. 3, the clutch output end 42 is provided with a front end and a rear end, the front end and the rear end are respectively connected with a first transmission shaft through a coupling, the first transmission shaft is connected to the transfer assembly 7, the transfer assembly 7 includes a gear set, the gear set includes a power input gear 71 and a power output gear 72, the power input gear 71 is in transmission connection with the transmission shaft, that is, the power input gear 71 is driven by the clutch output end 42 to rotate, a bevel gear is arranged on the power input gear 71, a bevel gear matched with the bevel gear on the power input gear 71 is arranged on the power output gear 72, two power output gears 72 are simultaneously engaged on the power input gear 71, and each power output gear 72 is in transmission connection with one rotor assembly 6, power take off gear part 72 be connected through quick detach shaft coupling and the second transmission shaft that sets up in the horn of aircraft, transmission shaft two again with rotor subassembly 6's pivot transmission, thereby realize the action of a plurality of rotor subassemblies of driving system simultaneous drive, and rotor subassembly 6 adopts is the pitch-variable structure, can rotate the in-process at the rotor and carry out pitch change regulation, thereby adjust lift in a flexible way under the unchangeable condition of rotational speed, the realization is controlled aircraft gesture and motion through the mode of pitch-variable, be favorable to increasing the rotor diameter, can effectively improve mobility, wind-resistant ability and flight performance.
The above is only a preferred embodiment of the present invention, and it should be noted that the above preferred embodiment should not be considered as limiting the present invention, and the protection scope of the present invention should be subject to the scope defined by the claims. It will be apparent to those skilled in the art that various modifications and enhancements can be made without departing from the spirit and scope of the invention, and such modifications and enhancements are intended to be within the scope of the invention.
Claims (10)
1. The power system is characterized by comprising an engine (1), a first motor (2), a second motor (3) and a clutch (4), wherein a rotating shaft of the first motor (2) is in transmission connection with a crankshaft of the engine (1), the crankshaft of the engine (1) is connected with a clutch input end (41), and a rotating shaft of the second motor (3) is in transmission connection with a clutch output end (42).
2. The power system according to claim 1, characterized in that the rotating shaft of the first motor (2) is in transmission connection with the crankshaft of the engine (1) through a synchronous pulley assembly or a gear assembly.
3. The power system of claim 1, wherein the rotating shaft of the second motor (3) is in transmission connection with the clutch output end (42) through a synchronous pulley assembly or a gear assembly.
4. A power system according to claim 1, characterized in that a radiator fan (5) is provided on the engine (1).
5. A power system according to any one of claims 1 to 4, characterised in that the clutch output (42) is operable via a transfer assembly (7) to simultaneously drive at least two rotor assemblies (6) into action.
6. The powertrain system according to claim 5, characterized in that the transfer assembly (7) comprises a gear train including a power input gear member (71) and a power output gear member (72), the power input gear member (71) being driven in rotation by the clutch output (42), the power input gear member (71) engaging at least two power output gear members (72), each power output gear member (72) being in driving connection with a respective one of the rotor assemblies (6).
7. The power system of any one of claims 1 to 4, wherein the first motor (2) is used for starting the engine (1), and the engine (1) drives the first motor (2) to generate power, or the engine (1) and the first motor (2) drive output together, and then the first motor (2) rotates along with the engine (1) in an idling mode.
8. A power system according to any one of claims 1 to 4, characterized in that the clutch input (41) is in meshing transmission with the clutch output (42) when the second electric machine (3) drives the clutch (4) output at the same speed as the speed of the clutch (4) input driven by the engine (1).
9. A power system according to any one of claims 1 to 4, characterized in that when the engine (1) is unexpectedly stopped, the clutch input (41) is disconnected from the clutch output (42), and the second electric machine (3) alone drives the clutch output (42) to rotate.
10. An aircraft comprising a power system according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121839550.4U CN214138978U (en) | 2021-08-09 | 2021-08-09 | Power system and aircraft adopting same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121839550.4U CN214138978U (en) | 2021-08-09 | 2021-08-09 | Power system and aircraft adopting same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214138978U true CN214138978U (en) | 2021-09-07 |
Family
ID=77554125
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121839550.4U Active CN214138978U (en) | 2021-08-09 | 2021-08-09 | Power system and aircraft adopting same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214138978U (en) |
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2021
- 2021-08-09 CN CN202121839550.4U patent/CN214138978U/en active Active
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240103 Address after: 201506, 1st Floor, No. 10, Lane 1688, Jiugong Road, Jinshan Industrial Zone, Jinshan District, Shanghai Patentee after: SHANGHAI DONGTING AUTOMATION TECHNOLOGY CO.,LTD. Address before: 610015 China (Sichuan) pilot Free Trade Zone, Chengdu, Sichuan Patentee before: Sichuan fusion Future Aviation Technology Co.,Ltd. |
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| TR01 | Transfer of patent right |