CN107985614A - Vehicle-mounted flight control system and automobile - Google Patents
Vehicle-mounted flight control system and automobile Download PDFInfo
- Publication number
- CN107985614A CN107985614A CN201711194660.8A CN201711194660A CN107985614A CN 107985614 A CN107985614 A CN 107985614A CN 201711194660 A CN201711194660 A CN 201711194660A CN 107985614 A CN107985614 A CN 107985614A
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- Prior art keywords
- converter
- aircraft
- storage battery
- vehicle
- control system
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D41/00—Power installations for auxiliary purposes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/14—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries for charging batteries from dynamo-electric generators driven at varying speed, e.g. on vehicle
- H02J7/1415—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries for charging batteries from dynamo-electric generators driven at varying speed, e.g. on vehicle with a generator driven by a prime mover other than the motor of a vehicle
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Power Engineering (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The present invention proposes a kind of vehicle-mounted flight control system and automobile, is related to automobile technical field.The system includes power supply unit, DC dc converter and storage battery bag, which is electrically connected with power supply unit and storage battery bag, and the DC dc converter and storage battery bag are connected with aircraft electrical；Storage battery bag provides power supply for the aircraft, and determines whether startup DC dc converter according to the working status of itself；The DC dc converter provides power supply, and charge to storage battery bag after the output voltage of power supply unit is changed after determining to start into aircraft.Energy source of the system using automobile as aircraft, extends the application field of aircraft, is powered by storage battery bag and DC dc converter duplex feeding system for aircraft, adds energy redundancy, improve reliability.
Description
Technical field
The present invention relates to automobile technical field, in particular to a kind of vehicle-mounted flight control system and automobile.
Background technology
With the rapid development of China's automobile industry, automobile serves not only as the vehicles of all trades and professions and widely uses,
At the same time in some particular applications, it is also used as a carrying platform, for different industries people provide operating space,
Electric system guarantee etc..Unmanned plane is as a kind of flight equipment being widely used at present, it is widely used in taking photo by plane, resource is visited
The fields such as survey, the disaster relief, military affairs, social security.It may require that there is long cruising time ability in some special occasions, in this situation
Under, how to solve the problems, such as that its power source just becomes a stubborn problem.
The power source of unmanned plane is mainly solved using following several method at present：One kind is to use energy density bigger
Ternary lithium battery or increase battery pack capacity, so as to extend the hang time；Another kind is to use solar cell, at nobody
Solar panel is arranged on the wing or fuselage of machine, and energy source is provided using solar cell.The first scheme in above-mentioned
The cruising ability of unmanned plane can be increased to a certain extent, but increase battery inclusion quantity or the battery using energy density higher
While can increase the weight of fuselage, the battery of energy higher is also limited be subject to battery self-energy density and can not accomplished more
Height, so cruising ability can only improve limited numerical value；Above-mentioned middle second scheme is adapted to the high-altitude flight in no cloud cover,
And the electricity conversion of the solar panel of batch generally below 20%, is influenced, solar energy by conversion ratio at present
Battery plate suqare, which wants sufficiently large, could effectively utilize solar energy, therefore require the effective very big using area of flight equipment, fit
Together in large-scale flight equipment.
Therefore, the power source of flight equipment how is solved, improves the cruising ability of flight equipment, is all this all the time
The emphasis of field technology personnel concern.
The content of the invention
It is an object of the invention to provide a kind of vehicle-mounted flight control system and automobile, to solve the above problems.
To achieve these goals, the technical solution that the embodiment of the present invention uses is as follows：
In a first aspect, the present invention proposes a kind of vehicle-mounted flight control system, applied to automobile, the vehicle-mounted aircraft control
System processed includes：Power supply unit, DC-DC converter and storage battery bag, the DC-DC converter supply Denso with described
Put and the storage battery bag is electrically connected, the DC-DC converter is connected with mono- aircraft electricals of storage battery Bao Junyu；
The storage battery bag is used to provide power supply for the aircraft；The storage battery bag is additionally operable to be determined according to the working status of itself
Whether the DC-DC converter is started；The DC-DC converter is used for after determining to start, and Denso is supplied by described
The output voltage put changed after into the aircraft provide power supply, and to the storage battery bag charge.
Further, the storage battery bag includes battery and battery management system, the battery and the battery management system
System, the DC-DC converter and the aircraft are electrically connected, and the battery management system becomes with the DC-DC
Parallel operation is electrically connected；The battery management system is used for the remaining capacity for calculating the battery, and in the remaining capacity of the battery
When meeting preset condition, control signal is sent to the DC-DC converter to start the DC-DC converter.
Further, the battery management system be used to gathering in real time the voltage signal of the battery, current signal and
Temperature signal, and according to the remaining capacity of the voltage signal, current signal and the temperature signal calculating battery.
Further, the DC-DC converter includes the first control interface and the second control interface, first control
Interface processed and second control interface are electrically connected with the battery management system；The control signal includes the first control and believes
Number and second control signal, first control interface be used to receive the first control signal, second control interface is used
In receiving the second control signal, the DC-DC converter is according to the first control signal and second control signal
To determine startup.
Further, the automobile is equipped with aircraft storage cabin, for storing the aircraft, the vehicle-mounted aircraft
Control system further includes actuating mechanism controls device, and the actuating mechanism controls device communicates with a remote control transmitter, for root
The control instruction sent according to the remote control transmitter controls the landing of the aircraft and the opening and closing in aircraft storage cabin.
Further, the actuating mechanism controls device includes controller, receiver and performs load, the reception
Device, perform load and the DC-DC converter is electrically connected with the controller, it is described perform load with it is described directly
Stream-DC converter, the storage battery bag are electrically connected.
Further, the vehicle-mounted flight control system further includes Vehicular display device, and the Vehicular display device, direct current-
DC converter, controller and the storage battery bag are connected by CAN bus between any two, and the Vehicular display device is used to show
Show the status information of the DC-DC converter, controller and the storage battery bag.
Further, the power supply unit includes generator, and the generator is electrically connected with the DC-DC converter
Connect.
Further, the power supply unit further includes Vehicular accumulator cell, the Vehicular accumulator cell and the generator, described
DC-DC converter is electrically connected.
Second aspect, the present invention also propose a kind of automobile, and the automobile includes vehicle-mounted flight control system, described vehicle-mounted
Flight control system includes：Power supply unit, DC-DC converter and storage battery bag, the DC-DC converter and institute
State power supply unit and the storage battery bag is electrically connected, the DC-DC converter and the storage battery Bao Junyu mono- fly
Device is electrically connected；The storage battery bag is used to provide power supply for the aircraft；The storage battery bag is additionally operable to the work according to itself
Determine whether to start the DC-DC converter as state；The DC-DC converter is used for after determining to start, will
The output voltage of the power supply unit changed after into the aircraft provide power supply, and to the storage battery bag charge.
Compared with the prior art, the invention has the advantages that：
In vehicle-mounted flight control system provided by the invention, the energy source using automobile as aircraft, is greatly improved
In the cruising time of aircraft, it the application field of aircraft is extended, can meet the particular fields such as security monitoring, search, the disaster relief
Close.The vehicle-mounted flight control system provides duplex feeding system, i.e. storage battery bag and DC-dc conversion for aircraft
Device, ensure that voltage and power demand, increase energy redundancy, improve reliability.Specifically, when the battery in storage battery bag
When remaining capacity is insufficient, battery management system can send control signal to control DC-DC to become according to the remaining capacity of battery
Parallel operation starts, and DC-DC converter is after determining to start, the voltage or Vehicular accumulator cell that can export automobile current generator
Voltage be continuously after being changed the charging of storage battery bag and and provide energy source to aircraft, when storage battery bag and direct current-
When any one in DC converter breaks down, another can stand alone as aircraft and provide power supply.Wherein, the direct current-
The startup of DC converter ensure that with closing by two paths of signals (i.e. first control signal and second control signal) confirmation and be
The security of system control, it also avoid because personnel's maloperation causes damage equipment.
Further, which realizes the lifting control of aircraft by actuating mechanism controls device
System, aircraft store the open and close controlling in cabin, use interlocking pattern between each executing agency, the same time only allows a set of mechanism to move
Make, avoid operator's maloperation from causing equipment damage.
In addition, in the vehicle-mounted flight control system, Vehicular display device, DC-DC converter and the storage battery bag
By CAN bus mutual transmission state information, fault message and control information etc., and shown by Vehicular display device,
When detecting mistake or failure, to remind operating personnel in time.
To enable the above objects, features and advantages of the present invention to become apparent, preferred embodiment cited below particularly, and coordinate
Appended attached drawing, is described in detail below.
Brief description of the drawings
In order to illustrate the technical solution of the embodiments of the present invention more clearly, below will be to needed in the embodiment attached
Figure is briefly described, it will be appreciated that the following drawings illustrate only certain embodiments of the present invention, therefore be not construed as pair
The restriction of scope, for those of ordinary skill in the art, without creative efforts, can also be according to this
A little attached drawings obtain other relevant attached drawings.
Fig. 1 shows the composition schematic diagram for the vehicle-mounted flight control system that the embodiment of the present invention is provided.
Fig. 2 shows the connection diagram of power supply unit and DC-DC converter.
Fig. 3 shows the circuit diagram of DC-DC converter.
Fig. 4 shows the control principle schematic diagram of controller.
Icon：The vehicle-mounted flight control systems of 100-；200- aircraft；300- remote control transmitters；110- power supply units；
120- DC-DC converters；130- storage battery bags；140- Vehicular display devices；150- actuating mechanism controls devices；111- generates electricity
Machine；112- Vehicular accumulator cells；131- battery management systems；132- batteries；151- controllers；152- receivers；153- performs negative
Carry.
Embodiment
Below in conjunction with attached drawing in the embodiment of the present invention, the technical solution in the embodiment of the present invention is carried out clear, complete
Ground describes, it is clear that described embodiment is only part of the embodiment of the present invention, instead of all the embodiments.Usually exist
The component of the embodiment of the present invention described and illustrated in attached drawing can be arranged and designed with a variety of configurations herein.Cause
This, the detailed description of the embodiment of the present invention to providing in the accompanying drawings is not intended to limit claimed invention below
Scope, but it is merely representative of the selected embodiment of the present invention.Based on the embodiment of the present invention, those skilled in the art are not doing
Go out all other embodiments obtained on the premise of creative work, belong to the scope of protection of the invention.
It should be noted that：Similar label and letter represents similar terms in following attached drawing, therefore, once a certain Xiang Yi
It is defined, then it further need not be defined and explained in subsequent attached drawing in a attached drawing.Meanwhile the present invention's
In description, term " first ", " second " etc. are only used for distinguishing description, and it is not intended that instruction or hint relative importance.
Fig. 1 is refer to, the composition schematic diagram of the vehicle-mounted flight control system 100 provided by the embodiment of the present invention.Institute
State vehicle-mounted flight control system 100 to can be applicable on automobile, the automobile is equipped with aircraft storage cabin, flies for storing
Device 200.The vehicle-mounted flight control system 100 can be that aircraft 200 provides energy source, increase flies using automobile as platform
The cruising ability of row device 200；The vehicle-mounted flight control system 100 can also control the landing of aircraft 200 and aircraft to receive
Receive the opening and closing in cabin, wherein, the landing of aircraft 200 is by controlling aircraft operation platform to be realized to predetermined position.
As shown in Figure 1, the vehicle-mounted flight control system 100 includes power supply unit 110, DC-DC converter 120
And storage battery bag 130, the DC-DC converter 120 are electrically connected with the power supply unit 110 and the storage battery bag 130
Connect, the DC-DC converter 120 and the storage battery bag 130 are electrically connected with aircraft 200.Preferably, the flight
Device 200 is connected with the DC-DC converter 120 and the storage battery bag 130 using cable.
The storage battery bag 130 is used to provide power supply for the aircraft 200.Specifically, in the present embodiment, the storage
Battery pack 130 includes battery 132 and battery management system 131, the battery 132 and the battery management system 131, described straight
Stream-DC converter 120 and the aircraft 200 are electrically connected, and the battery management system 131 becomes with the DC-DC
Parallel operation 120 is electrically connected.The aircraft 200 obtains the energy by battery 132.
The storage battery bag 130 is additionally operable to be determined whether to start the DC-dc conversion according to the working status of itself
Device 120.In the present embodiment, the battery management system 131 is used to upon actuation, calculate the remaining capacity of the battery 132,
And (remaining capacity of i.e. above-mentioned working status characterization battery 132 is low when the remaining capacity of the battery 132 meets preset condition
In given threshold), control signal is sent to the DC-DC converter 120 to start the DC-DC converter 120.
For example, the battery management system 131 is believed by gathering the voltage signal, current signal and temperature of the battery 132 in real time
Number, and the remaining capacity of the battery 132 is calculated according to the voltage signal, current signal and the temperature signal, so
When DC-DC converter 120 can be in different conditions according to the remaining capacity of battery 132, using different charge and discharge controls
Strategy, so as to ensure that battery 132 can be stablized, constantly power.
It is to be understood that storage battery bag 130 of the present invention determines whether that starting DC-DC converter 120 is not limited to that, example
Such as, can also be in the following ways：The self-test first upon actuation of battery management system 131, that is, detect whether itself faulty, such as
Fruit has, then does not start DC-DC converter 120, and reporting fault information；If without failure, direct current-straight is directly initiated
Current converter 120, the energy is provided by DC-DC converter 120 and storage battery bag 130 for aircraft 200 jointly.
The DC-DC converter 120 be used for determine start after, by the output voltage of the power supply unit 110 into
Go and provide power supply after changing into the aircraft 200, and charge to the storage battery bag 130.
As shown in Fig. 2, the connection diagram for the power supply unit 110 and the DC-DC converter 120.It is described
Power supply unit 110 includes generator 111 and Vehicular accumulator cell 112, the generator 111 and the DC-DC converter 120
It is electrically connected, the Vehicular accumulator cell 112 is electrically connected with the generator 111, the DC-DC converter 120.It is preferred that
Ground, the Vehicular accumulator cell 112 are 12v lead-acid accumulators.
In the present embodiment, it (is the power supply unit 110 to drive generator 111 to produce voltage using automobile engine
Output voltage), the voltage that the generator 111 produces not only is exported to DC-DC converter 120, but also to be institute
The charging accumulation of energy of Vehicular accumulator cell 112 is stated, to ensure the normal work of automobile itself.When the remaining capacity in storage battery bag 130 not
When foot and the failure of generator 111, then aircraft 200 can not obtain energy, in order to ensure the normal work of aircraft 200,
At this time voltage output temporarily can be provided to DC-DC converter 120 instead of generator 111 by the Vehicular accumulator cell 112.It is described
The energy of generator 111 or Vehicular accumulator cell 112 can be continuously flight by DC-DC converter 120 by BOOST conversion
Device 200 and battery 132 provide energy source.
It should be noted that in the present embodiment, the vehicle-mounted flight control system 100 is due to including storage battery bag
130 and 120 duplex feeding system of DC-DC converter, therefore the energy source of aircraft 200 can be by DC-dc conversion
Either one in device 120 and storage battery bag 130 provides or DC-DC converter 120 and storage battery bag 130 carry jointly
For not limiting this, power supply strategy can be adjusted according to being actually needed；, can be by when wherein electric power system breaks down all the way
In addition electric power system stands alone as aircraft 200 and provides power supply all the way.
Further, as shown in figure 3, circuit diagram for the DC-DC converter 120.The DC-DC
First input interface A1 of converter 120 is electrically connected with one end of generator 111, the cathode of Vehicular accumulator cell 112, the second input
Interface A2 is electrically connected with the other end of generator 111, the anode of Vehicular accumulator cell 112；The DC-DC converter 120
First output interface B1 is electrically connected with the cathode of battery 132, and the second output interface B2 is electrically connected with the anode of battery 132.
The DC-DC converter 120 further include the first control interface C1 and the second control interface (CANH_1 and
CANL_1), the first control interface C1 and second control interface (CANH_1 and CANL_1) with the battery management
System 131 is electrically connected.Wherein, the first control interface C1 and the battery management system 131 are that to be connected using rigid line (be a little
To the connection mode of point), and high level signal is effective, second control interface (CANH_1 and CANL_1) and the cell tube
Reason system 131 is connected by CAN bus.
In the present embodiment, the control signal transmitted by the battery management system 131 includes first control signal and the
Two control signals, the first control interface C1 are used to receive the first control signal, the second control interface (CANH_1
And CANL_1) be used to receive the second control signal, first control of the DC-DC converter 120 according to reception
Signal processed and second control signal determine startup.It is readily appreciated that ground, above-mentioned first control signal is hard signal, such as electricity
Ordinary mail number, the signal are effective when being high level；Above-mentioned second control signal is software signal (or communication signal), for example, number
According to message etc., which is transmitted by CAN communication agreement in CAN bus, is received by DC-DC converter 120.
Therefore, the embodiment of the present invention confirms as a result of simple two-way signal (i.e. first control signal and second control signal)
Mode, i.e., the situation that described DC-DC converter 120 is only received in first control signal and second control signal
Under, it can just start, avoid, when operating personnel's maloperation, causing damage to system.
Further, the vehicle-mounted flight control system 100 that the embodiment of the present invention is provided further includes actuating mechanism controls
Device 150, the actuating mechanism controls device 150 communicates with a remote control transmitter 300, for according to the remote control transmitter
300 control instructions sent control the landing of the aircraft 200 and the opening and closing in aircraft storage cabin.
In the present embodiment, the actuating mechanism controls device 150 includes controller 151, receiver 152 and performs negative
153 are carried, the receiver 152, execution load 153 and the DC-DC converter 120 are electric with the controller 151
Connection, the execution load 153 are electrically connected with the DC-DC converter 120, the storage battery bag 130.Specifically,
It is described that to perform load 153 be electrically connected with the battery 132 in the storage battery bag 130, i.e., it is described perform load 153 with it is described winged
As row device 200, also by one of offer power supply in the DC-DC converter 120 and the storage battery bag 130, or
Person provides power supply jointly by the DC-DC converter 120 and the storage battery bag 130.In the present embodiment, the execution
Load 153 is preferably motor.
As shown in figure 4, the control principle drawing for the controller 151.When receiver 152 receive operating personnel pass through it is distant
Control transmitter 300 send control instruction after, which is converted to mechanism control signal by controller 151, by H bridges after
The rotating of electric appliance (Q1, Q2, Q3, Q4) driving actuating motor M and it is spacing come control the lifting of aircraft operation platform and
Aircraft stores the action of cabin door, so as to fulfill the landing of aircraft 200 and the opening and closing in aircraft storage cabin.Example
Such as, when relay Q1, Q3 connection, relay Q2, Q4 access failure, actuating motor M is rotated forward, then is realized on aircraft operation platform
Rise, aircraft storage cabin is opened；When relay Q1, Q3 access failure, when relay Q2, Q4 are connected, then realize that aircraft operation is put down
Platform declines, and aircraft storage cabin is closed.
Further, in the present embodiment, the vehicle-mounted flight control system 100 further includes Vehicular display device 140, institute
Vehicular display device 140, DC-DC converter 120, controller 151 and the storage battery bag 130 is stated between any two to pass through
CAN bus connects, and the Vehicular display device 140 is used to show the DC-DC converter 120 and the storage battery bag 130
Status information.In the present embodiment, the DC-DC converter 120, controller 151, battery management system 131 pass through
CAN bus transmits respective status information, and is shown by Vehicular display device 140, is carried for the display and warning of whole system
Information source is supplied.For example, operating personnel can understand DC-dc conversion in time by the display content of Vehicular display device 140
Whether device 120, actuating mechanism controls device 150, storage battery bag 130 break down, and ensure whole vehicle-mounted flight control system
100 normal operation.
In the present embodiment, the Vehicular display device 140 also with 200 wireless communication of aircraft, when aircraft 200 is held
During row shooting task, the content of shooting can be shown on the Vehicular display device 140.
In conclusion vehicle-mounted flight control system provided in an embodiment of the present invention and automobile, the vehicle-mounted aircraft control
System processed includes：Power supply unit, DC-DC converter and storage battery bag, the DC-DC converter supply Denso with described
Put and the storage battery bag is electrically connected, the DC-DC converter is connected with mono- aircraft electricals of storage battery Bao Junyu；
The storage battery bag is used to provide power supply for the aircraft；The storage battery bag is additionally operable to be determined according to the working status of itself
Whether the DC-DC converter is started；The DC-DC converter is used for after determining to start, and Denso is supplied by described
The output voltage put changed after into the aircraft provide power supply, and to the storage battery bag charge.The vehicle-mounted aircraft
Energy source of the control system using automobile as aircraft, greatly improves the cruising time of aircraft, extends aircraft
Application field, can meet the special occasions such as security monitoring, search, the disaster relief；The vehicle-mounted flight control system provides two-way
Electric power system, i.e. storage battery bag and DC-DC converter, ensure that voltage and power demand, increase energy redundancy, improve
Reliability.When any one in storage battery bag and DC-DC converter breaks down, another can stand alone as aircraft
Power supply is provided.Further, the vehicle-mounted flight control system further includes actuating mechanism controls device, executing agency's control
Device processed communicates with remote control transmitter, and the control instruction for being sent according to the remote control transmitter controls rising for the aircraft
Drop and the aircraft store the opening and closing in cabin, use interlocking pattern between each executing agency, the same time only allows a set of machine
Structure acts, and avoids operating personnel's maloperation from causing equipment damage.
It should be noted that herein, the relational terms of such as " first " and " second " or the like are used merely to one
A entity or operation are distinguished with another entity or operation, without necessarily requiring or implying these entities or operate it
Between there are any actual relationship or order.Moreover, term " comprising ", "comprising" or its any other variant are intended to
Cover non-exclusive inclusion, so that process, method, article or equipment including a series of elements not only include those
Key element, but also including other elements that are not explicitly listed, or further include as this process, method, article or set
Standby intrinsic key element.In the absence of more restrictions, the key element limited by sentence "including a ...", it is not excluded that
Also there are other identical element in the process, method, article or apparatus that includes the element.
The foregoing is only a preferred embodiment of the present invention, is not intended to limit the invention, for the skill of this area
For art personnel, the invention may be variously modified and varied.Within the spirit and principles of the invention, that is made any repaiies
Change, equivalent substitution, improvement etc., should all be included in the protection scope of the present invention.It should be noted that：Similar label and letter exists
Similar terms is represented in following attached drawing, therefore, once being defined in a certain Xiang Yi attached drawing, is then not required in subsequent attached drawing
It is further defined and is explained.
Claims (10)
- A kind of 1. vehicle-mounted flight control system, applied to automobile, it is characterised in that the vehicle-mounted flight control system bag Include：Power supply unit, DC-DC converter and storage battery bag, the DC-DC converter and the power supply unit and described Storage battery bag is electrically connected, and the DC-DC converter is connected with mono- aircraft electricals of storage battery Bao Junyu；The storage battery bag is used to provide power supply for the aircraft；The storage battery bag is additionally operable to be determined whether to start the DC-DC converter according to the working status of itself；The DC-DC converter is used for after determining to start, and is after the output voltage of the power supply unit is changed The aircraft provides power supply, and charges to the storage battery bag.
- 2. vehicle-mounted flight control system as claimed in claim 1, it is characterised in that the storage battery bag includes battery and electricity Pond management system, the battery are electrically connected with the battery management system, the DC-DC converter and the aircraft Connect, the battery management system is electrically connected with the DC-DC converter；The battery management system is used for the remaining capacity for calculating the battery, and meets to preset in the remaining capacity of the battery During condition, control signal is sent to the DC-DC converter to start the DC-DC converter.
- 3. vehicle-mounted flight control system as claimed in claim 2, it is characterised in that the battery management system is used for real-time The voltage signal, current signal and temperature signal of the battery are gathered, and according to the voltage signal, current signal and institute State the remaining capacity that temperature signal calculates the battery.
- 4. vehicle-mounted flight control system as claimed in claim 2, it is characterised in that the DC-DC converter includes First control interface and the second control interface, first control interface and second control interface with the battery management System is electrically connected；The control signal includes first control signal and second control signal, and first control interface is used to receiving described the One control signal, second control interface are used to receive the second control signal, and the DC-DC converter is according to institute First control signal and second control signal are stated to determine startup.
- 5. vehicle-mounted flight control system as claimed in claim 1, the automobile is equipped with aircraft storage cabin, for storing The aircraft, it is characterised in that the vehicle-mounted flight control system further includes actuating mechanism controls device, the execution machine Structure control device communicates with a remote control transmitter, and the control instruction for being sent according to the remote control transmitter controls the flight The landing of device and the opening and closing in aircraft storage cabin.
- 6. vehicle-mounted flight control system as claimed in claim 5, it is characterised in that the actuating mechanism controls device includes Controller, receiver and perform load, the receiver, perform load and the DC-DC converter with it is described Controller is electrically connected, and the execution load is electrically connected with the DC-DC converter, the storage battery bag.
- 7. vehicle-mounted flight control system as claimed in claim 1, it is characterised in that the vehicle-mounted flight control system is also Including Vehicular display device, the Vehicular display device, DC-DC converter and the storage battery bag pass through CAN between any two Bus connects, and the Vehicular display device is used for the status information for showing the DC-DC converter and the storage battery bag.
- 8. vehicle-mounted flight control system as claimed in claim 1, it is characterised in that the power supply unit includes generator, The generator is electrically connected with the DC-DC converter.
- 9. vehicle-mounted flight control system as claimed in claim 8, it is characterised in that the power supply unit further includes vehicle-mounted storage Battery, the Vehicular accumulator cell are electrically connected with the generator, the DC-DC converter.
- 10. a kind of automobile, it is characterised in that including the vehicle-mounted flight control system of claim 1-9 any one of them.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711194660.8A CN107985614A (en) | 2017-11-24 | 2017-11-24 | Vehicle-mounted flight control system and automobile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711194660.8A CN107985614A (en) | 2017-11-24 | 2017-11-24 | Vehicle-mounted flight control system and automobile |
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| CN107985614A true CN107985614A (en) | 2018-05-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711194660.8A Pending CN107985614A (en) | 2017-11-24 | 2017-11-24 | Vehicle-mounted flight control system and automobile |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109725259A (en) * | 2019-01-25 | 2019-05-07 | 格林美股份有限公司 | An electric forklift power monitoring system and method |
| CN112946477A (en) * | 2021-02-04 | 2021-06-11 | 深圳市蜉飞科技有限公司 | Method, device, equipment and medium for determining remaining battery power of unmanned aerial vehicle device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105006862A (en) * | 2015-07-31 | 2015-10-28 | 深圳前海探鹿科技有限公司 | Vehicle-mounted unmanned aerial vehicle charging device |
| CN105015784A (en) * | 2015-05-26 | 2015-11-04 | 陶文英 | Design method and system for realizing long-endurance flight of multi-rotor aircraft |
| CN204992697U (en) * | 2015-09-14 | 2016-01-20 | 山东农业大学 | Battery -powered many rotor crafts charger of live that needs car |
| CN106004626A (en) * | 2016-06-14 | 2016-10-12 | 郭永 | Vehicle-mounted multifunctional platform of unmanned aerial vehicle |
| CN106340916A (en) * | 2016-09-05 | 2017-01-18 | 北京新能源汽车股份有限公司 | Automobile charging method, charging device, charging system and automobile |
| US20170225802A1 (en) * | 2014-10-13 | 2017-08-10 | Systems Engineering Associates Corporation | Systems and methods for deployment and operation of vertical take-off and landing (vtol) unmanned aerial vehicles |
-
2017
- 2017-11-24 CN CN201711194660.8A patent/CN107985614A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20170225802A1 (en) * | 2014-10-13 | 2017-08-10 | Systems Engineering Associates Corporation | Systems and methods for deployment and operation of vertical take-off and landing (vtol) unmanned aerial vehicles |
| CN105015784A (en) * | 2015-05-26 | 2015-11-04 | 陶文英 | Design method and system for realizing long-endurance flight of multi-rotor aircraft |
| CN105006862A (en) * | 2015-07-31 | 2015-10-28 | 深圳前海探鹿科技有限公司 | Vehicle-mounted unmanned aerial vehicle charging device |
| CN204992697U (en) * | 2015-09-14 | 2016-01-20 | 山东农业大学 | Battery -powered many rotor crafts charger of live that needs car |
| CN106004626A (en) * | 2016-06-14 | 2016-10-12 | 郭永 | Vehicle-mounted multifunctional platform of unmanned aerial vehicle |
| CN106340916A (en) * | 2016-09-05 | 2017-01-18 | 北京新能源汽车股份有限公司 | Automobile charging method, charging device, charging system and automobile |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109725259A (en) * | 2019-01-25 | 2019-05-07 | 格林美股份有限公司 | An electric forklift power monitoring system and method |
| CN112946477A (en) * | 2021-02-04 | 2021-06-11 | 深圳市蜉飞科技有限公司 | Method, device, equipment and medium for determining remaining battery power of unmanned aerial vehicle device |
| CN112946477B (en) * | 2021-02-04 | 2022-03-08 | 深圳市蜉飞科技有限公司 | Method, device, equipment and medium for determining remaining battery power of unmanned aerial vehicle device |
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