CN107065904A - Gasoline and electric hybrid aircraft balance control system - Google Patents
Gasoline and electric hybrid aircraft balance control system Download PDFInfo
- Publication number
- CN107065904A CN107065904A CN201710142036.7A CN201710142036A CN107065904A CN 107065904 A CN107065904 A CN 107065904A CN 201710142036 A CN201710142036 A CN 201710142036A CN 107065904 A CN107065904 A CN 107065904A
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- motor
- power
- sensor
- control unit
- maincenter
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
- G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
- G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
- G05D1/0816—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft to ensure stability
Abstract
The invention discloses a kind of gasoline and electric hybrid aircraft balance control system, including：Data processing maincenter, sensing maincenter, the first control unit, the second control unit, petrol engine, motor, wireless transport module；Sensing maincenter includes：First power sensor, multiple second power sensors, multiple state sensors；The quantity of motor is four or more even number, and the quantity of motor is identical with the quantity of the second power sensor；First power sensor is used for the engine power for monitoring petrol engine；Second power sensor is used for the rotating speed for monitoring motor；State sensor is used to obtain attitude data；Petrol engine is used in the vertical direction and provides climbing power；Motor is used to provide locomotivity and flight balance power.The structure of the invention is novel, and petrol engine, the motor division of labor are clear and definite, and the live load of motor is retarded, from the cruising time and navigation stability for integrally lifting the aircraft that need to be controlled.
Description
Technical field
The invention is related to balance control system technical field, more particularly to a kind of gasoline and electric hybrid flight
Device balance control system.
Background technology
Power is provided using petrol engine or motor more than existing aircraft, when providing power using petrol engine,
When needing to set oil storage chamber in aircraft, and motor offer power being provided, then need to set battery in aircraft；Also may be used
Gasoline and electric hybrid are selected according to demand.
But when existing use gasoline and electric power mixing provide power, petrol engine can not often be carried out with motor and cooperateed with
Work, is typically only capable to take the pattern of alternation, divides the work not clear and definite enough, asking for motor Work overload often occurs
Topic, is not sufficiently stable and the problem of cruising time is shorter so as to aircraft performance occur.
The content of the invention
The purpose of the invention is to provide a kind of gasoline and electric hybrid aircraft balance control system, structure
Novelty, petrol engine, the motor division of labor are clear and definite, and the live load of motor is retarded, from integrally lifting the aircraft that need to control
Cruising time and navigation stability.
The above-mentioned purpose of the invention is achieved by the following technical programs.
A kind of gasoline and electric hybrid aircraft balance control system, including：Data processing maincenter, sensing maincenter,
First control unit, the second control unit, petrol engine, motor, wireless transport module；
The sensing maincenter includes：First power sensor, multiple second power sensors, multiple state sensors；
The quantity of the motor is four or more even number, and the quantity of the motor is passed with second power
The quantity of sensor is identical；
First power sensor is used for the engine power for monitoring the petrol engine；
Second power sensor is used for the rotating speed for monitoring the motor；
The state sensor is used to obtain attitude data；
The petrol engine is used in the vertical direction and provides climbing power；
The motor is used to provide locomotivity and flight balance power；
The wireless transport module is used for the control instruction for receiving external control devices transmission；
The data processing maincenter obtains the poised state of aircraft itself according to the attitude data, and with reference to the control
System instruction controls the engine power of the petrol engine by first control unit, is controlled by described second
Unit controls the rotating speed of the motor, and then the petrol engine is monitored by first power sensor, leads to
Cross second power sensor to monitor the motor, to confirm the result after control.
The data processing maincenter of the invention is used to carry out Data Management Analysis；The sensing maincenter utilizes sensing
Device is monitored to the posture of aircraft and motion state that need to be controlled, obtains the attitude data, and by the appearance
State data feedback gives the data processing maincenter；The data processing maincenter is according to the attitude data and described is wirelessly transferred
The control instruction that module is received, controls the petrol engine by first control unit, passes through described second
Control unit controls the motor；And then first power sensor is monitored to the petrol engine again, pass through described
Two power sensors are monitored to the motor, so as to which the operational data after control is fed back into the data processing maincenter；And it is described
Petrol engine is used in the vertical direction and provides climbing power, so as to mainly undertake the weight of aircraft itself；And the motor
For providing locomotivity and flight balance power, so as to coordinate the petrol engine to adjust the state of aircraft；Present invention wound
Make structure novel, the petrol engine, the motor division of labor are clear and definite, and the live load of the motor is retarded, from entirety
Lift cruising time and the navigation stability for the aircraft that need to be controlled.
Specifically, the attitude data includes：Shift state data, the velocity of displacement of vertical direction, the position of horizontal direction
Move speed；
Entered according to the velocity of displacement of the shift state data, the velocity of displacement of the vertical direction, the horizontal direction
Row binding analysis, you can the poised state and current mobile status of aircraft itself are obtained, to be preferably balanced
Regulation and control.
Specifically, the data processing maincenter respectively with first power sensor, first control unit, described
Second control unit, the wireless transport module, multiple second power sensors, multiple state sensor connections；
The data processing maincenter for reception instruction, is received as the core component of the data processing of the invention
Data, data analysis and instruction are sent, and technical support is provided for the running of the invention.
Specifically, second control unit includes multiple the second electricity tune connected one to one with the motor, described
Second electricity, which is adjusted to be pivoted with the Data processing, to be connect；
The running that data processing maincenter control second electricity is adjusted, the motor is made by the described second electricity regulation and control
Running, to adjust the rotating speed of the motor.
Specifically, first control unit includes：First electricity is adjusted, steering wheel；
The data processing maincenter, first electricity are adjusted, the steering wheel；
The steering wheel is used for the throttle for controlling the petrol engine；
The running that data processing maincenter control first electricity is adjusted, and then the running of the steering wheel is controlled, so as to control
The throttle of the petrol engine is made, to adjust the engine power of the petrol engine.
Specifically, the external control devices includes the one or more in remote control, mobile phone, tablet personal computer；
So that user remotely can be controlled to aircraft, the external control devices can also be had from other
The equipment for instructing output function and wireless transmission function.
Preferably, the state sensor includes nine axle attitude transducers and velocity sensor；
The nine axles attitude transducer, which can be monitored, obtains the current its own shape of aircraft, and the velocity sensor energy
The current translational speed of aircraft is enough learnt, the translational speed includes rate travel and moving direction, works as with reference to aircraft
The current translational speed of preceding its own shape, aircraft results in shift state data in the attitude data, institute
State velocity of displacement, the velocity of displacement of the horizontal direction of vertical direction.
Compared with prior art, the invention beneficial effect is：
1st, the structure of the invention is novel, and petrol engine, the motor division of labor are clear and definite, and the live load of motor is subtracted
It is slow, from the cruising time and navigation stability for integrally lifting the aircraft that need to be controlled.
2nd, second electricity of the invention is adjusted connects one to one with motor so that the second electricity, which is adjusted, can be accurately controlled electricity
The running of machine, to ensure the steady of aircraft.
Brief description of the drawings
Fig. 1 is the gasoline of embodiment 1 and the structured flowchart of electric hybrid aircraft balance control system.
In figure：1st, data processing maincenter；2nd, maincenter is sensed；201st, the first power sensor；202nd, the second power sensor；
203rd, state sensor；3rd, the first control unit；301st, the first electricity is adjusted；302nd, steering wheel；4th, the second control unit；401st, the second electricity
Adjust；5th, petrol engine；6th, motor；7th, wireless transport module.
Embodiment
Clear, complete description is carried out to the technical scheme of each embodiment of the invention below with reference to accompanying drawing, it is clear that
Described embodiment is only a part of embodiment of the invention, rather than whole embodiments.Based on present invention wound
The embodiment made, those of ordinary skill in the art's all other implementation resulting on the premise of creative work is not made
Example, belongs to the scope that the invention is protected.
, it is necessary to explanation in the description of the invention, term " " center ", " on ", " under ", it is "left", "right", " perpendicular
Directly ", the orientation or position relationship of the instruction such as " level ", " interior ", " outer " are, based on orientation shown in the drawings or position relationship, to be only
Described for the ease of description the invention and simplifying, rather than to indicate or imply that signified device or element must have specific
Orientation, with specific azimuth configuration and operation, therefore it is not intended that limitation to the invention.In addition, term " the
One ", " second ", " the 3rd " are only used for describing purpose, and it is not intended that indicating or implying relative importance.
, it is necessary to which explanation, unless otherwise clearly defined and limited, term " are pacified in the description of the invention
Dress ", " connected ", " connection " should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or integratedly
Connection；Can be mechanical connection or electrical connection；Can be joined directly together, can also be indirectly connected to by intermediary,
It can be the connection of two element internals.For the ordinary skill in the art, above-mentioned art can be understood with concrete condition
Concrete meaning of the language in the invention.
The invention is described in further detail below by specific embodiment and with reference to accompanying drawing.
Embodiment 1
As shown in figure 1, a kind of gasoline and electric hybrid aircraft balance control system, including：Data processing maincenter
1st, sensing maincenter 2, the first control unit 3, the second control unit 4, petrol engine 5, motor 6, wireless transport module 7；Sensing
Maincenter 2 includes：First power sensor 201, multiple second power sensors 202, multiple state sensors 203；The number of motor 6
The even number for four or more is measured, the quantity of motor 6 is identical with the quantity of the second power sensor 202；First power
Sensor 201 is used for the engine power for monitoring petrol engine 5；Second power sensor 202 is used to monitor turning for motor 6
Speed；State sensor 203 is used to obtain attitude data；Petrol engine 5 is used in the vertical direction and provides climbing power；Motor 6
For providing locomotivity；Wireless transport module 7 is used for the control instruction for receiving external control devices transmission；Data processing maincenter 1
The poised state of aircraft itself is obtained according to attitude data, and combines control instruction gasoline is controlled by the first control unit 3
The engine power of engine 5, by the rotating speed of the controlled motor 6 of the second control unit 4, and then passes through the first power sensor
201 pairs of petrol engines 5 are monitored, and motor 6 is monitored by the second power sensor 202, to confirm the result after control；
The data processing maincenter 1 of the invention is used to carry out Data Management Analysis；Sensing maincenter 2 is using sensor to needing
The posture and motion state for the aircraft being controlled are monitored, and obtain attitude data, and attitude data is fed back into number
According to processing maincenter 1；The control instruction that data processing maincenter 1 is received according to attitude data and wireless transport module 7, passes through
One control unit 3 controls petrol engine 5, passes through the controlled motor 6 of the second control unit 4；And then the first power sensor 201 again
Petrol engine 5 is monitored, motor 6 monitored by the second power sensor 202, so as to which the operational data after control is fed back
Data processing maincenter 1；And petrol engine 5 is used in the vertical direction and provides climbing power, so as to mainly undertake aircraft itself
Weight；And motor 6 is used to provide locomotivity and flight balance power, so as to coordinate petrol engine 5 to adjust the shape of aircraft
State, is flown or held stationary；The invention structure is novel, and petrol engine 5, motor 6 are divided the work clearly, the work of motor 6
Make that load is retarded, from the cruising time and navigation stability for integrally lifting the aircraft that need to be controlled；
Wherein, data processing maincenter 1 is the module with data processing chip, and microcomputer, single-chip microcomputer etc. is set
It is standby.
Preferably due to which the quantity of motor 6 is four or more even number, motor 6 is uniformly arranged on flight
On device, consequently facilitating regulating and controlling by multiple motors 6 to the stability of aircraft.
In the present embodiment, attitude data includes：Shift state data, the velocity of displacement of vertical direction, the position of horizontal direction
Move speed；
Analysis is combined according to the velocity of displacement of shift state data, the velocity of displacement of vertical direction, horizontal direction, i.e.,
The poised state and current mobile status of aircraft itself can be obtained, to be preferably balanced regulation and control.
In the present embodiment, data processing maincenter 1 is controlled with the first power sensor 201, the first control unit 3, second respectively
Unit 4 processed, wireless transport module 7, multiple second power sensors 202, multiple state sensors 203 are connected；
Data processing maincenter 1 for reception instruction, receives number as the core component of the data processing of the invention
Sent according to, data analysis and instruction, technical support is provided for the running of the invention.
In the present embodiment, the second control unit 4 includes multiple the second electricity connected one to one with motor 6 and adjusts 401, second
Electricity adjusts 401 to be connected with data processing maincenter 1；
The electricity of the control of data processing maincenter 1 second adjusts 401 running, and the running of 401 controlled motors 6 is adjusted by the second electricity, with
Just the rotating speed of motor 6 is adjusted；And the second electricity adjusts 401 to be connected one to one with motor 6 so that the second electricity tune 401 can be accurately
The running of controlled motor 6, to ensure the steady of aircraft.
In the present embodiment, the first control unit 3 includes：First electricity adjusts 301, steering wheel 302；The electricity of data processing maincenter 1, first
Adjust 301, steering wheel 302；Steering wheel 302 is used for the throttle for controlling petrol engine 5；
The electricity of the control of data processing maincenter 1 first adjusts 301 running, and then controls the running of steering wheel 302, so as to control gasoline
The throttle of engine 5, to adjust the engine power of petrol engine 5.
In the present embodiment, external control devices includes the one or more in remote control, mobile phone, tablet personal computer；
So that user remotely can be controlled to aircraft, external control devices can also have instruction from other
The equipment of output function and wireless transmission function.
In the present embodiment, state sensor 203 includes nine axle attitude transducers and velocity sensor；
Nine axle attitude transducers, which can be monitored, obtains the current its own shape of aircraft, and velocity sensor can learn winged
The current translational speed of row device, translational speed include rate travel and moving direction, with reference to the current its own shape of aircraft,
The current translational speed of aircraft results in shift state data, the velocity of displacement of vertical direction, level in attitude data
The velocity of displacement in direction.
Finally it should be noted that：Above example is only to the technical scheme for illustrating the invention, rather than its limitations；
Although the invention is described in detail with reference to the foregoing embodiments, it will be understood by those within the art that：
It can still modify to the technical scheme described in previous embodiment, or to which part or all technical characteristic
Carry out equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from the invention embodiment
Technical scheme.
Claims (7)
1. a kind of gasoline and electric hybrid aircraft balance control system, it is characterised in that the control system includes：Number
According to processing maincenter, sensing maincenter, the first control unit, the second control unit, petrol engine, motor, wireless transport module；
The sensing maincenter includes：First power sensor, multiple second power sensors, multiple state sensors；
The quantity of the motor is four or more even number, the quantity of the motor and second power sensor
Quantity it is identical；
First power sensor is used for the engine power for monitoring the petrol engine；
Second power sensor is used for the rotating speed for monitoring the motor；
The state sensor is used to obtain attitude data；
The wireless transport module is used for the control instruction for receiving external control devices transmission；
The petrol engine is used in the vertical direction and provides climbing power；
The motor is used to provide locomotivity and flight balance power；
The data processing maincenter obtains the poised state of aircraft itself according to the attitude data, and refers to reference to the control
The engine power that the petrol engine is controlled by first control unit is made, passes through second control unit
The rotating speed of the motor is controlled, and then the petrol engine is monitored by first power sensor, passes through institute
State the second power sensor to monitor the motor, to confirm the result after control.
2. gasoline according to claim 1 and electric hybrid aircraft balance control system, it is characterised in that described
Attitude data includes：Shift state data, the velocity of displacement of vertical direction, the velocity of displacement of horizontal direction.
3. gasoline according to claim 1 and electric hybrid aircraft balance control system, it is characterised in that described
Data processing maincenter respectively with first power sensor, first control unit, second control unit, the nothing
Line transport module, multiple second power sensors, multiple state sensor connections.
4. gasoline according to claim 1 and electric hybrid aircraft balance control system, it is characterised in that described
Second control unit is adjusted including the second electricity that the multiple and motor connects one to one, at the second electricity tune and the data
Reason maincenter is connected.
5. gasoline according to claim 1 and electric hybrid aircraft balance control system, it is characterised in that described
First control unit includes：First electricity is adjusted, steering wheel；
The data processing maincenter, first electricity are adjusted, the steering wheel；
The steering wheel is used for the throttle for controlling the petrol engine.
6. gasoline according to claim 1 and electric hybrid aircraft balance control system, it is characterised in that described
External control devices includes the one or more in remote control, mobile phone, tablet personal computer.
7. gasoline according to claim 1 and electric hybrid aircraft balance control system, it is characterised in that described
State sensor includes nine axle attitude transducers and velocity sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710142036.7A CN107065904A (en) | 2017-03-10 | 2017-03-10 | Gasoline and electric hybrid aircraft balance control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710142036.7A CN107065904A (en) | 2017-03-10 | 2017-03-10 | Gasoline and electric hybrid aircraft balance control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107065904A true CN107065904A (en) | 2017-08-18 |
Family
ID=59621563
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710142036.7A Pending CN107065904A (en) | 2017-03-10 | 2017-03-10 | Gasoline and electric hybrid aircraft balance control system |
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| CN (1) | CN107065904A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201159160Y (en) * | 2008-02-22 | 2008-12-03 | 新疆派犨泰克石油科技有限责任公司 | Air pumping controller |
| CN105129079A (en) * | 2015-09-29 | 2015-12-09 | 郝建新 | Hybrid power long-endurance multi-shaft air vehicle |
| CN204956916U (en) * | 2015-09-29 | 2016-01-13 | 郝建新 | Multiaxis aircraft during long boat of hybrid |
| CN105398570A (en) * | 2015-11-26 | 2016-03-16 | 北京浩恒征途航空科技有限公司 | Oil-operated multi- rotor aerocraft |
| CN105539828A (en) * | 2015-12-08 | 2016-05-04 | 陈蜀乔 | Petrol-electric hybrid multi-rotor aerial vehicle capable of self electricity generation |
| CN106155072A (en) * | 2016-07-21 | 2016-11-23 | 张健雄 | A kind of small aircraft automated driving system and method |
| CN205787031U (en) * | 2016-06-02 | 2016-12-07 | 杭州摩恩电机有限公司 | A kind of easy servomotor velocity-measuring system |
-
2017
- 2017-03-10 CN CN201710142036.7A patent/CN107065904A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201159160Y (en) * | 2008-02-22 | 2008-12-03 | 新疆派犨泰克石油科技有限责任公司 | Air pumping controller |
| CN105129079A (en) * | 2015-09-29 | 2015-12-09 | 郝建新 | Hybrid power long-endurance multi-shaft air vehicle |
| CN204956916U (en) * | 2015-09-29 | 2016-01-13 | 郝建新 | Multiaxis aircraft during long boat of hybrid |
| CN105398570A (en) * | 2015-11-26 | 2016-03-16 | 北京浩恒征途航空科技有限公司 | Oil-operated multi- rotor aerocraft |
| CN105539828A (en) * | 2015-12-08 | 2016-05-04 | 陈蜀乔 | Petrol-electric hybrid multi-rotor aerial vehicle capable of self electricity generation |
| CN205787031U (en) * | 2016-06-02 | 2016-12-07 | 杭州摩恩电机有限公司 | A kind of easy servomotor velocity-measuring system |
| CN106155072A (en) * | 2016-07-21 | 2016-11-23 | 张健雄 | A kind of small aircraft automated driving system and method |
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Legal Events
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information | ||
| CB03 | Change of inventor or designer information |
Inventor after: Hao Gang Inventor after: Zhang Wuyun Inventor after: Deng Qing Inventor after: Yang Zhonghao Inventor after: Fu Bingxiang Inventor after: Wang Shaozhi Inventor after: Ming Junan Inventor after: Shi Xiaomei Inventor before: Hao Gang Inventor before: Fu Bingxiang Inventor before: Zhang Wuyun Inventor before: Shi Xiaomei Inventor before: Wang Shaozhi Inventor before: Ming Junan Inventor before: Deng Qing |
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170818 |