CN111697559A - Space separable power supply system - Google Patents

Space separable power supply system Download PDF

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Publication number
CN111697559A
CN111697559A CN202010688028.4A CN202010688028A CN111697559A CN 111697559 A CN111697559 A CN 111697559A CN 202010688028 A CN202010688028 A CN 202010688028A CN 111697559 A CN111697559 A CN 111697559A
Authority
CN
China
Prior art keywords
power supply
connector
supply system
switching device
electrically connected
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202010688028.4A
Other languages
Chinese (zh)
Inventor
孟剑
赵洪楷
万伟华
李云伟
王京亮
潘志鹏
邹睿
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Guizhou Meiling Power Supply Co Ltd
Original Assignee
Guizhou Meiling Power Supply Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Guizhou Meiling Power Supply Co Ltd filed Critical Guizhou Meiling Power Supply Co Ltd
Priority to CN202010688028.4A priority Critical patent/CN111697559A/en
Publication of CN111697559A publication Critical patent/CN111697559A/en
Pending legal-status Critical Current

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Classifications

    • 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
    • H02J1/00—Circuit arrangements for dc mains or dc distribution networks
    • H02J1/10—Parallel operation of dc sources
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/428—Power distribution and management
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
    • B64G1/446—Thermal solar power generation
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/645—Separators
    • 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
    • H02J1/00—Circuit arrangements for dc mains or dc distribution networks
    • H02J1/10—Parallel operation of dc sources
    • H02J1/109—Scheduling or re-scheduling the operation of the DC sources in a particular order, e.g. connecting or disconnecting the sources in sequential, alternating or in subsets, to meet a given demand
    • 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
    • H02J7/0063—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with circuits adapted for supplying loads from the battery
    • 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
    • H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
    • H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells

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  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Sustainable Energy (AREA)
  • Thermal Sciences (AREA)
  • Sustainable Development (AREA)
  • Charge And Discharge Circuits For Batteries Or The Like (AREA)

Abstract

The application discloses a space separable power supply system in the technical field of aerospace application, which mainly comprises a charging power supply, a power supply source, a switching device, a connector and a power supply center, wherein the charging power supply, the power supply source, the switching device and the connector are positioned in a separating mechanism; the power center is arranged in the main body mechanism, the charging power supply is connected with the switching device, the switching device is connected with the connector and the power supply, and the connector is connected with the power center. The system can realize the functions of supplying power to the aircraft before the separation of the space separation mechanism and independently supplying power after the separation, and is suitable for the aerospace application field.

Description

Space separable power supply system
Technical Field
The invention belongs to the technical field of aerospace application, and particularly relates to a separable power supply system.
Background
With the rapid development of the aerospace field in China, the space aircraft is more and more applied, the aircraft generally comprises a main body mechanism and a separation mechanism, and the aircraft needs a power supply system to provide power in the operation process. And aircraft often experience spatial separation during operation. The separation of the aircraft can bring great changes to the whole power supply system, and meanwhile, in order to keep the separation mechanism to normally operate after separation, a corresponding power supply needs to be provided for the separation mechanism after separation. Under the condition of sufficient energy, the main mechanism and the separating mechanism are simultaneously provided with corresponding power supplies, which is the most direct solution, however, when the main mechanism and the separating mechanism are limited by mass and space volume, the two groups of power supplies are obviously difficult to realize, so an optimized power supply system is needed, and the power supply problem before and after separation can be ensured.
Disclosure of Invention
Aiming at the defects of the prior art, the invention designs a space separable power supply system so as to meet the problem that a group of power supplies can simultaneously ensure power supply before and after separation.
The invention relates to a space separable power supply system, which is matched with a separation mechanism and a main body mechanism of an aircraft for use, and mainly comprises a charging power supply, a switching device, a connector and a power supply center, wherein the charging power supply, the switching device and the connector are positioned in the separation mechanism; the power center is arranged in the main body mechanism, the charging power supply is electrically connected with the switching device, the switching device is respectively electrically connected with the connector and the power supply, and the connector is electrically connected with the power center.
Further, the charging power supply is an independent power supply system formed by combining one or more of a solar cell and a thermoelectric cell. Can generate electric energy in space by itself, and can reduce energy consumption.
Further, the power supply is a power supply system formed by combining one or more of a lithium ion battery, a thermal battery, a lithium carbon fluoride battery and a lithium thionyl chloride battery. The battery is used as a power supply, can work in a low-temperature and high-temperature environment, has the characteristics of high specific energy and specific power, and is suitable for aerospace application.
Further, the switching device is composed of a power supply module, a switching module and an activation module.
Further, when the main body mechanism is not separated from the separating mechanism, the short-circuit point of the switching module and the short-circuit point of the connector are in a parallel connection state, and the power supply module is electrically connected with the connector.
Preferably, when the main body mechanism is separated from the separating mechanism, the switching module and the short contact of the connector are in an open circuit state, the activating module is electrically connected with the power supply, and the power supply module is electrically connected with the power supply.
Further preferably, the connector is a drop connector.
Further, the connector is electrically connected with the power supply center, the connector is detachably connected with the main body mechanism, and the separation mode of the connection part of the connector and the main body mechanism is one or more of mechanical separation and lock ring separation.
The working principle of the invention is as follows: according to the scheme, the separation mechanism and the aircraft are identified in the on-off state through the short-circuit loop of the falling connector, when the falling connector is connected with the aircraft power supply central circuit, the charging power supply of the separation mechanism transmits electric energy to the power supply center through the circuit, and the power supply center transmits the electric energy to the aircraft power equipment; when the separating mechanism leaves the aircraft to independently execute a task, the falling connector falls off and further serves as a starting control signal to enable the switching device to switch, and the charging power supply of the separating mechanism supplies power to the power supply of the separating mechanism so as to meet the power consumption requirement of the separating mechanism; when the separating mechanism returns, the switching device is switched again, the charging power supply is switched to supply power for switching the aircraft and the separating mechanism through state switching, the power utilization requirement of a space separable system during long endurance is met, and the power utilization requirement of high specific power is met.
Due to the adoption of the technical scheme, the invention has the following beneficial effects: the application provides a separable power supply system in space can be before the separation of aircraft for the main part mechanism power supply, for the release mechanism power supply after the separation.
(2) The utility model provides a separable power supply system in space can improve the utilization ratio of power supply system energy, and has that equipment is simple, and is with low costs, is fit for using widely.
Drawings
FIG. 1 is a schematic diagram of a spatially separable power supply system of the present invention;
fig. 2 is a control circuit diagram of a spatially separable power supply system according to the present invention.
Detailed Description
The following is a detailed description of the embodiments of the present invention, but the present invention is not limited to these embodiments, and any modifications or substitutions in the basic spirit of the embodiments are included in the scope of the present invention as claimed in the claims.
Embodiment 1 as shown in fig. 1, a space-separable power supply system is composed of a charging power supply, a power supply source, a switching device, a connector, a power supply center, and the like. The charging power supply, the switching device and the connector are located in the separating mechanism, and the power supply center is located in the main body mechanism. Before the separating mechanism is not separated, a charging power supply positioned in the separating mechanism is connected with the connectors through 1, 2 points in the switching device (as shown in figure 2), and then is connected with a power supply center in the main body mechanism, and the power supply center supplies power to the aircraft by converging electric energy of each connector. When the separating mechanism is separated, the connector is separated from the power center firstly and serves as a starting control signal, then the connector is separated, the short circuit of the connector is disconnected, the light-emitting diode acts, the selector switch is connected from 1 point to 2 point and is converted into 1 point to 3 point connection, and the power supply supplies power to the separating mechanism (as shown in fig. 2). The separating mechanism starts to supply power autonomously, when the separating mechanism is connected with the main mechanism again, the switching device is switched reversely, and the charging power supply of the separating mechanism recovers to supply power to the main mechanism of the aircraft. The separated power supply can independently supply power for a plurality of separating mechanisms at the same time, and is suitable for application in the field of future aerospace.
Wherein, the charging power supply can be a solar battery; the power supply is a lithium carbon fluoride battery, and the separation mode is mechanical separation.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.

Claims (8)

1. A separable power supply system for use with a disconnect mechanism and a main body mechanism of an aircraft, comprising: the power supply system mainly comprises a charging power supply, a switching device, a connector and a power supply center, wherein the charging power supply, the switching device and the connector are positioned in a separating mechanism; the power center is arranged in the main body mechanism, the charging power supply is electrically connected with the switching device, the switching device is respectively electrically connected with the connector and the power supply, and the connector is electrically connected with the power center.
2. A spatially separable power supply system according to claim 1, wherein: the charging power supply is an independent power supply system formed by combining one or more of a solar cell and a thermoelectric cell.
3. A spatially separable power supply system according to claim 2, wherein: the power supply is a power supply system formed by combining one or more of a lithium ion battery, a thermal battery, a lithium carbon fluoride battery and a lithium thionyl chloride battery.
4. The spatially separable power supply system of claim 3, wherein: the switching device consists of a power supply module, a switching module and an activation module.
5. The spatially separable power supply system of claim 4, wherein: when the main body mechanism is not separated from the separating mechanism, the short-circuit point of the switching module and the short-circuit point of the connector are in a parallel connection state, and the power supply module is electrically connected with the connector.
6. The spatially separable power supply system of claim 4, wherein: when the main body mechanism is separated from the separating mechanism, the short-circuit point of the switching module and the connector is in an open circuit state, the activating module is electrically connected with the power supply, and the power supply module is electrically connected with the power supply.
7. A spatially separable power supply system according to claim 5 or 6, characterized in that: the connector is a releasable connector.
8. The spatially separable power supply system of claim 7, wherein the connector is electrically connected to the power supply center, the connector is detachably connected to the main body mechanism, and the connection between the connector and the main body mechanism is separated by one or more of mechanical separation and lock ring separation.
CN202010688028.4A 2020-07-16 2020-07-16 Space separable power supply system Pending CN111697559A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202010688028.4A CN111697559A (en) 2020-07-16 2020-07-16 Space separable power supply system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202010688028.4A CN111697559A (en) 2020-07-16 2020-07-16 Space separable power supply system

Publications (1)

Publication Number Publication Date
CN111697559A true CN111697559A (en) 2020-09-22

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Family Applications (1)

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CN202010688028.4A Pending CN111697559A (en) 2020-07-16 2020-07-16 Space separable power supply system

Country Status (1)

Country Link
CN (1) CN111697559A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113386982A (en) * 2021-02-26 2021-09-14 上海埃依斯航天科技有限公司 Space power supply system for final-stage rail-staying application

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090045292A1 (en) * 2007-08-16 2009-02-19 Maddali Vijay K Engine having power bus fault short circuit control with a disconnection switch
CN101663775A (en) * 2007-03-20 2010-03-03 空中客车营运有限公司 Power regulating device for an aircraft
CN104828252A (en) * 2015-06-02 2015-08-12 冯圣冰 Method for implementing aerial continuous voyage for unmanned aerial vehicle
CN105552973A (en) * 2014-10-28 2016-05-04 南京德朔实业有限公司 Electric energy transmission system and power supply system and charging combination thereof
CN107585309A (en) * 2017-10-26 2018-01-16 无锡同春新能源科技有限公司 To the aerogenerator device people of the wired power supply of electric air unmanned plane
CN109038795A (en) * 2018-07-20 2018-12-18 上海空间电源研究所 For electrically separated interlock protection and soft-switching device and method

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101663775A (en) * 2007-03-20 2010-03-03 空中客车营运有限公司 Power regulating device for an aircraft
US20090045292A1 (en) * 2007-08-16 2009-02-19 Maddali Vijay K Engine having power bus fault short circuit control with a disconnection switch
CN105552973A (en) * 2014-10-28 2016-05-04 南京德朔实业有限公司 Electric energy transmission system and power supply system and charging combination thereof
CN104828252A (en) * 2015-06-02 2015-08-12 冯圣冰 Method for implementing aerial continuous voyage for unmanned aerial vehicle
CN107585309A (en) * 2017-10-26 2018-01-16 无锡同春新能源科技有限公司 To the aerogenerator device people of the wired power supply of electric air unmanned plane
CN109038795A (en) * 2018-07-20 2018-12-18 上海空间电源研究所 For electrically separated interlock protection and soft-switching device and method

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113386982A (en) * 2021-02-26 2021-09-14 上海埃依斯航天科技有限公司 Space power supply system for final-stage rail-staying application

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Application publication date: 20200922