CN209192233U - A kind of redundance power supply system for unmanned plane - Google Patents
A kind of redundance power supply system for unmanned plane Download PDFInfo
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- CN209192233U CN209192233U CN201821941431.8U CN201821941431U CN209192233U CN 209192233 U CN209192233 U CN 209192233U CN 201821941431 U CN201821941431 U CN 201821941431U CN 209192233 U CN209192233 U CN 209192233U
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- battery
- control
- unmanned plane
- battery case
- redundance
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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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
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- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The utility model discloses a kind of redundance power supply systems for unmanned plane, including unmanned plane main body, unmanned plane bottom part body both ends are symmetrically arranged with shock bracket, control cabinet is fixed between the shock bracket, one end of the control cabinet side is hinged with the first door-plate, the other end of the control cabinet side is hinged with the second door-plate, locking slot corresponding with tapered end is offered among the second door-plate avris, it is equipped with inside the control cabinet and flies control redundance power-supply controller, the first battery case and third battery case are provided with below the winged control redundance power-supply controller, a kind of redundance power supply system for unmanned plane of the utility model, by by winged control battery, VTOL battery and cruise battery and winged control redundance power-supply controller are electrically connected, it is powered by flying control redundance power-supply controller to different supply ports, When the electricity of VTOL battery depletes, the cruise battery meeting position Xiang Chuiqi powers, therefore will not influence entirety.
Description
Technical field
The utility model relates to a kind of power supply system, in particular to a kind of redundance power supply system for unmanned plane belongs to
In unmanned plane equipment technical field.
Background technique
Unmanned plane is the not manned aircraft using radio robot and the presetting apparatus provided for oneself manipulation.Nothing on machine
Cockpit, but the equipment such as automatic pilot, presetting apparatus are installed.On ground, naval vessels or machine tool remote control station personnel pass through
The equipment such as radar track it, are positioned, are remotely controlled, telemetering and Digital Transmission.It can be under wireless remotecontrol as conventional airplane one
Sample takes off or is launched with booster rocket, can also be taken to by machine tool it is aerial launch flight, when recycling, can with conventional airplane
Process the same mode automatic Landing in land can also be recycled by remote control parachute or block.
Existing unmanned plane power supply system flies control battery: the high-capacity battery being separately provided by three pieces of battery compositions；It hangs down
Straight landing battery: the low-capacity batteries of high-discharge-rate；Cruise battery: the high-capacity battery of place point multiplying power.Because of three blocks of electricity
The case where interface in pond is different, is easy to appear wrong plug, and three pieces of batteries are separately provided, and can not carry out the mutual of electricity with other batteries
It mends, influences unmanned plane and integrally use.Therefore we make improvement to this, propose a kind of redundance power supply system for unmanned plane
System.
Utility model content
The purpose of this utility model is to provide a kind of redundance power supply systems for unmanned plane, to solve above-mentioned background
The problem of traditional unmanned plane battery interface proposed in technology is easy wrong plug, and fuselage is influenced vulnerable to battery capacity.
To achieve the above object, the utility model provides the following technical solutions: a kind of redundance power supply for unmanned plane
System, including unmanned plane main body, unmanned plane bottom part body both ends are symmetrically arranged with shock bracket, between the shock bracket
It is fixed with control cabinet, one end of the control cabinet side is hinged with the first door-plate, is equipped with tapered end among the first door-plate avris,
The other end of the control cabinet side is hinged with the second door-plate, and lock corresponding with tapered end is offered among the second door-plate avris
Tight slot is equipped with inside the control cabinet and flies control redundance power-supply controller, and the winged control redundance power-supply controller lower section is set
It is equipped with the first battery case and third battery case, the second battery case is equipped between the third battery case and the first battery case, it is described
It is connected with respectively inside first battery case, the second battery case and third battery case and flies control battery, VTOL battery and cruise electricity
Pond is electrically connected between the winged control battery, VTOL battery and cruise battery and winged control redundance power-supply controller, described
Fly one end at the top of control redundance power-supply controller and is provided with winged control supply port, data radio station supply port and steering engine feeder ear
Mouthful.
As a kind of optimal technical scheme of the utility model, the winged control redundance power-supply controller and winged control feeder ear
It is electrically connected between mouth, data radio station supply port and steering engine supply port.
As a kind of optimal technical scheme of the utility model, first battery case, the second battery case and third battery
Groove top portion is pasted with tag along sort.
As a kind of optimal technical scheme of the utility model, it is bolted between the control cabinet and shock bracket
Connection.
As a kind of optimal technical scheme of the utility model, the control cabinet bottom is evenly distributed with radiating fin.
As a kind of optimal technical scheme of the utility model, the winged control redundance power-supply controller uses GL-RC-
003 type product.
Compared with prior art, the utility model has the beneficial effects that the utility model is a kind of for the extra of unmanned plane
Spend power supply system, have battery interface will not wrong plug, the advantages of battery capacity can be complementary to one another use, specifically using
In, it compares with traditional power supply system, the utility model passes through winged control battery, VTOL battery and cruise battery
It is electrically connected with winged control redundance power-supply controller, is powered by flying control redundance power-supply controller to different supply ports, when
The electricity of VTOL battery depletes, the cruise battery meeting position Xiang Chuiqi power supply, therefore will not influence entirety, and using effect is good.
Detailed description of the invention
Fig. 1 is the utility model overall structure diagram；
Fig. 2 is the power supply system flow diagram of the utility model；
In figure: 1, the first battery case；2, fly control battery；3, tag along sort；4, fly control redundance power-supply controller；5, second
Battery case；6, VTOL battery；7, third battery case；8, cruise battery；9, unmanned plane main body；10, the first door-plate；11, it locks
Head；12, shock bracket；13, the second door-plate；14, locking slot；15, control cabinet；16, fly control supply port；17, data radio station supplies
Electric port；18, steering engine supply port.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
Every other embodiment obtained, fall within the protection scope of the utility model.
The utility model provides a kind of redundance power supply system for unmanned plane, including unmanned plane referring to FIG. 1-2,
Main body 9, the 9 bottom both ends of unmanned plane main body are symmetrically arranged with shock bracket 12, are fixed with control between the shock bracket 12
Case 15 processed, one end of 15 side of control cabinet are hinged with the first door-plate 10, are equipped with tapered end among 10 avris of the first door-plate
11, the other end of 15 side of control cabinet is hinged with the second door-plate 13, offers and locks among 13 avris of the second door-plate
First 11 corresponding locking slot 14 is equipped with inside the control cabinet 15 and flies control redundance power-supply controller 4, the winged control redundance
Be provided with the first battery case 1 and third battery case 7 below power-supply controller 4, the third battery case 7 and the first battery case 1 it
Between be equipped with the second battery case 5, be connected with winged control respectively inside first battery case 1, the second battery case 5 and third battery case 7
Battery 2, VTOL battery 6 and cruise battery 8, the winged control battery 2, VTOL battery 6 and cruise battery 8 and winged control are more
It is electrically connected between redundant electrical pow er supply controller 4, described winged 4 top one end of control redundance power-supply controller, which is provided with, flies control feeder ear
Mouth 16, data radio station supply port 17 and steering engine supply port 18.
Preferably, the winged control redundance power-supply controller 4 with fly control supply port 16, data radio station supply port 17 and
It is electrically connected between steering engine supply port 18, convenient for being grouped control to each port electricity consumption.
Preferably, first battery case 1, the second battery case 5 and 7 top of third battery case are pasted with tag along sort 3,
The case where battery variety is separated fixation, prevents wrong plug.
Preferably, it is bolted to connection between the control cabinet 15 and shock bracket 12, when reducing unmanned plane landing
The vibration of generation endangers.
Preferably, 15 bottom of control cabinet is evenly distributed with radiating fin, prevents the battery inside control cabinet 15 from working
When the high temperature that generates influence the use of unmanned plane.
Preferably, the winged control redundance power-supply controller 4 uses GL-RC-003 type product, low in energy consumption, transmission range
Far, strong antijamming capability.
When specifically used, a kind of redundance power supply system for unmanned plane of the utility model has battery interface will not
The advantages of wrong plug, battery capacity can be complementary to one another use, by winged control battery 2, VTOL battery 6 and cruise battery 8 and flies
Control redundance power-supply controller 4 is electrically connected, and is powered by flying control redundance power-supply controller 4 to different supply ports, when vertical
The electricity of straight landing battery 6 depletes, the cruise meeting of battery 8 position Xiang Chuiqi power supply, therefore will not influence entirety, flies control redundance and supplies
One group of battery that electric controller 4 can automatically select ceiling voltage carries out priority power supply, and tag along sort 3 to classify between battery
It is clear, control cabinet 15 is protected using the first door-plate 10 and the second door-plate 13, using effect is good, strong applicability, is worth carrying out extensive
It promotes.
In the description of the present invention, it should be understood that term " coaxial ", " bottom ", " one end ", " top ", " in
The orientation of the instructions such as portion ", " other end ", "upper", " side ", " top ", "inner", " front ", " center ", " both ends " or position are closed
System is to be based on the orientation or positional relationship shown in the drawings, and is merely for convenience of describing the present invention and simplifying the description, rather than
The device or element of indication or suggestion meaning must have a particular orientation, be constructed and operated in a specific orientation, therefore cannot
It is construed as a limitation of the present invention.
In addition, term " first ", " second ", " third ", " the 4th " are used for description purposes only, and should not be understood as instruction or
It implies relative importance or implicitly indicates the quantity of indicated technical characteristic, define " first ", " second ", " the as a result,
Three ", the feature of " the 4th " can explicitly or implicitly include at least one of the features.
In the present invention unless specifically defined or limited otherwise, term " installation ", " setting ", " connection ", " Gu
Calmly ", the terms such as " being screwed on " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integral；
It can be mechanical connection, be also possible to be electrically connected；It can be directly connected, can also indirectly connected through an intermediary, it can be with
It is the interaction relationship of the connection or two elements inside two elements, unless otherwise restricted clearly, for this field
For those of ordinary skill, the concrete meaning of above-mentioned term in the present invention can be understood as the case may be.
While there has been shown and described that the embodiments of the present invention, for the ordinary skill in the art,
It is understood that these embodiments can be carried out with a variety of variations in the case where not departing from the principles of the present invention and spirit, repaired
Change, replacement and variant, the scope of the utility model is defined by the appended claims and the equivalents thereof.
Claims (6)
1. a kind of redundance power supply system for unmanned plane, including unmanned plane main body (9), which is characterized in that the unmanned plane
Main body (9) bottom both ends are symmetrically arranged with shock bracket (12), are fixed with control cabinet (15), institute between the shock bracket (12)
The one end for stating control cabinet (15) side is hinged with the first door-plate (10), and tapered end is equipped among the first door-plate (10) avris
(11), the other end of control cabinet (15) side is hinged with the second door-plate (13), is opened among the second door-plate (13) avris
Equipped with locking slot (14) corresponding with tapered end (11), it is equipped with inside the control cabinet (15) and flies control redundance power-supply controller
(4), it is provided with the first battery case (1) and third battery case (7) below the winged control redundance power-supply controller (4), described the
The second battery case (5) are equipped between three battery cases (7) and the first battery case (1), first battery case (1), the second battery case
(5) and inside third battery case (7) it is connected with respectively and flies control battery (2), VTOL battery (6) and cruise battery (8), it is described
Fly control battery (2), VTOL battery (6) and cruise battery (8) and flies electrically to connect between control redundance power-supply controller (4)
It connects, one end, which is provided with, at the top of the winged control redundance power-supply controller (4) flies control supply port (16), data radio station supply port
(17) and steering engine supply port (18).
2. a kind of redundance power supply system for unmanned plane according to claim 1, it is characterised in that: the winged control is more
Redundant electrical pow er supply controller (4) and fly control supply port (16), data radio station supply port (17) and steering engine supply port (18) it
Between be electrically connected.
3. a kind of redundance power supply system for unmanned plane according to claim 1, it is characterised in that: first electricity
Tag along sort (3) are pasted at the top of pond slot (1), the second battery case (5) and third battery case (7).
4. a kind of redundance power supply system for unmanned plane according to claim 1, it is characterised in that: the control cabinet
(15) it is bolted to connection between shock bracket (12).
5. a kind of redundance power supply system for unmanned plane according to claim 1, it is characterised in that: the control cabinet
(15) bottom is evenly distributed with radiating fin.
6. a kind of redundance power supply system for unmanned plane according to claim 1, it is characterised in that: the winged control is more
Redundant electrical pow er supply controller (4) uses GL-RC-003 type product.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821941431.8U CN209192233U (en) | 2018-11-23 | 2018-11-23 | A kind of redundance power supply system for unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821941431.8U CN209192233U (en) | 2018-11-23 | 2018-11-23 | A kind of redundance power supply system for unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209192233U true CN209192233U (en) | 2019-08-02 |
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ID=67425674
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821941431.8U Active CN209192233U (en) | 2018-11-23 | 2018-11-23 | A kind of redundance power supply system for unmanned plane |
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| CN (1) | CN209192233U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112644717A (en) * | 2019-10-09 | 2021-04-13 | 肇庆凌飞航空科技有限公司 | One-way parallel electric composite wing aircraft double-power-supply system |
-
2018
- 2018-11-23 CN CN201821941431.8U patent/CN209192233U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112644717A (en) * | 2019-10-09 | 2021-04-13 | 肇庆凌飞航空科技有限公司 | One-way parallel electric composite wing aircraft double-power-supply system |
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