CN105955075A - Spacecraft in-orbit multifunctional structure integrated management and control system - Google Patents
Spacecraft in-orbit multifunctional structure integrated management and control system Download PDFInfo
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- CN105955075A CN105955075A CN201610305265.1A CN201610305265A CN105955075A CN 105955075 A CN105955075 A CN 105955075A CN 201610305265 A CN201610305265 A CN 201610305265A CN 105955075 A CN105955075 A CN 105955075A
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
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Abstract
A spacecraft in-orbit multifunctional structure integrated management and control system comprises a multifunctional structure unit, a power management unit, a data processing unit, and a discharge load unit. The multifunctional structure unit integrates the bearing, power supply and vibration reduction functions. The power management unit controls charge/discharge operation, detects and adjusts the electrical performance parameters of power modules in real time, and transmits the parameters to the data processing unit. The data processing unit acquires the mechanical/electrical performance parameters of system operation and submits the parameters to a spacecraft platform through a remote sensing and data transmission interface, and the parameters are finally transmitted back to the ground. The discharge load unit consumes power under control of the power management unit. According to the system, a spacecraft structure and a power source are fused in a multifunctional manner, power source charge/discharge management, structure mechanics/electrical performance monitoring, and data management and transmission are integrated together, and the task process from remote control instruction receiving to multifunction implementation and further to state monitoring and data management and transmission can be executed systematically.
Description
Technical field
The invention belongs to spacecraft structure and design technical field, be specifically related to a kind of spacecraft the most multi-functional
Structure composition management and control system.
Background technology
Currently, spacecraft proposes the highest requirement to its payload ratio and available space, to this end,
Multifunction structure technology gradually comes into one's own at space industry and moves towards application.Multifunction structure technology is number
Organically blend be integrated according to the functions such as process, radiation protection, thermal control, electric power storage and spacecraft self structure
Item technology, by using structure, function and the integrated design of material, eliminates bulk redundancy quality and volume,
Thus it is obviously improved the load/mass ratio of spacecraft, load/volume ratio and function/structure ratio.
But, for a concrete multifunction structure, want to realize it spaceborne smooth, normal
Work, needs its operation on orbit process is managed and is controlled, simultaneously need to enter its operation on orbit state
Row monitoring.Therefore, it is badly in need of developing a set of management and control system in-orbit, so that spacecraft multifunction structure to be entered
Row effectively management and control.Up to now, the most do not find about this type of management and control system
Document report or engineer applied precedent.
Summary of the invention
Normally work on spacecraft to realize multifunction structure, the invention provides a kind of spacecraft in-orbit
Multifunction structure integrated management and control system.
The technical scheme is that
A kind of spacecraft multifunction structure integrated management and control system in-orbit, including multifunction structure unit,
Power Management Unit, data processing unit and discharge load unit.Wherein, described multifunction structure unit by
Main structure module, four can charge/discharge source module, vibration insulating system and sensor assembly composition, described power supply
Administrative unit with can be connected by charge/discharge source module, control can charge/discharge source module charging and discharging operation, with
Time detect in real time adjust can each unit for electrical property parameters of charge/discharge source module, and by can each electricity of charge/discharge source module
Performance parameter is transferred to data processing unit, and by self working status parameter telemetry interface by himself
Directly it is submitted to spacecraft platform；Described data processing unit is connected with sensor assembly, passes through sensor die
Block obtains mechanical performance parameter when multifunction structure unit runs and unit for electrical property parameters, and passes through himself
Telemetry interface passes interface with number, and the data of collection are submitted to spacecraft platform, finally passes ground observing and controlling back and puts down
Platform；Described discharge load unit is connected with Power Management Unit, it is possible to consume under the control of Power Management Unit
With the energy of power module.
In the present invention, described main structure module includes framework, upper cover plate and lower cover；Wherein, described framework
Monnolithic case be field word configuration, there are four grid cavitys, described framework has about x, y and z tri-axle
Comprehensive symmetry；Described lower cover is fixed on the bottom surface of described framework；Described upper cover plate is fixed on described frame
The end face of frame；Described framework, upper cover plate and lower cover together form main force support structure, have structural bearing
Function；
Described can include 4 by charge/discharge source module, be designated as respectively can charge/discharge source module I, can discharge charge power supply
Module II, can charge/discharge source module III and can charge/discharge source module IV；Each can pass through bullet by charge/discharge source module
Property supporting construction is arranged at, to be embedded into mode, the closing grid cavity that framework, upper cover plate and lower cover are formed
In, and in each grid cavity in framework, unique installation one can charge/discharge source module；Can discharge charge power supply mould
The positive and negative polar curve of block is drawn by forceful electric power cable, is connected to be arranged at the forceful electric power electricity of the lateral wall of described framework
Discharge and recharge interface is formed on adapter；Described can both have repeatedly charging and multiple discharge by charge/discharge source module
Function, has again the function serving as oscillator consumption vibrational energy.
Each can charge/discharge source module surrounding with for accommodate this can the grid cavity wall of charge/discharge source module
Between be provided with elastomer block.Each can be provided with elasticity between bottom surface and the described lower cover of charge/discharge source module
Pad.Each can be also equipped with cushion between end face and the described upper cover plate of charge/discharge source module.Can charge/discharge
Source module, elastomer block and cushion constitute vibration insulating system, are equivalent to " spring-oscillator " model.Wherein, institute
State elastomer block and described cushion is equivalent to the resilient support with certain rigidity and damping；Described can charge/discharge
Source module is equivalent to the oscillator with certain mass, and on the one hand this vibration insulating system is inhaled by the deformation of resilient support
Shake power consumption, on the other hand by structural vibration energy can be converted into oscillator move by charge/discharge source module as oscillator
The mode of energy consumes vibrational energy, and the result of the two comprehensive function reduces vibration in multifunction structure
Transmission, and effectively management can the mechanical environment of charge/discharge source module；
Described sensor assembly includes several temperature sensors and several acceleration transducers；Wherein, institute
State several temperature sensors be respectively arranged at can the inner chamber of charge/discharge source module and lateral wall, be used for monitoring phase
Should the temperature of charge/discharge source module；Several acceleration transducers described are respectively arranged at the interior of described framework
Wall, the inwall of upper cover plate and the inwall of described lower cover, be used for measuring described framework, upper cover plate and described
The Vibration Condition of lower cover, the electric energy within multifunction structure unit and vibration management provide detection and prison
Control means.
Additionally, described multifunction structure unit also has 2 road light current interface, respectively temperature signal output interfaces
With acceleration signal output interface, they all use weak-current cable to be connected with data processing unit.
In the present invention, two groups can be obtained by can connecting adjacent for position 2 by charge/discharge source module
The power supply of identical output voltage, is called main part power supply and backup battery；Described main part power supply and backup electricity
Source respectively has 1 tunnel discharge and recharge interface, and discharge and recharge interface is forceful electric power interface, and described main part power supply and backup battery are each
Forceful electric power cable is used to be connected with Power Management Unit from by its discharge and recharge interface.
In the present invention, described Power Management Unit includes charging regulator module, electric discharge adjustor module, tune
Reason circuit module and auxiliary source circuit, have charging control, control of discharge, the switching of active/standby part power supply and voltage/
Current detecting conditioning functions；For multifunction structure unit in orbit time charge/discharge management, and utilize
The detection modulate circuit being internally integrated, assists discharge load unit to obtain the lithium battery in multifunction structure unit
Unit for electrical property parameters in orbit.
Described Power Management Unit has 2 tunnel discharge and recharge interfaces and 1 road instruction interface, and 2 tunnel discharge and recharge interfaces are respectively
Being connected to main part power supply and the backup battery of power module, the control of 1 instruction interface reception spacecraft transmission refers to
Order, Power Management Unit controls discharge load unit and discharges main part power supply or backup battery.
In the present invention, described data processing unit includes power module, CPU control module and data acquisition module
Block, data processing unit collection, processes and transmits multifunction structure unit in launching phase and phase in orbit
Between mechanical performance parameter and the unit for electrical property parameters such as voltage, electric current, the vibration obtaining multifunction structure unit is special
Property, the checking structural support energy of multifunction structure unit and basic electric property energy.
In the present invention, described discharge load unit can use any form of load, consumes multifunction structure
The electric energy of unit.As described discharge load unit uses the mode of multichannel heating plate to realize, it is used for consuming many merits
The electric energy of energy construction unit.
In the present invention, described multifunction structure unit can be connected by screw mode and be arranged in spacecraft deck board,
Also can use directly as spacecraft deck board or dividing plate.Described Power Management Unit and data processing unit are all pacified
It is loaded in spacecraft body cabin.Described discharge load unit thermal conductance sticker can be used to be contained on spacecraft bulkhead or
The alternate manner such as be spirally connected is arranged in spacecraft body cabin, and is connected with Power Management Unit by cable.
Further, phase change device, this multifunction structure can be installed on described multifunction structure unit bottom surface
And available dielectric film isolation between phase change device；Described dielectric film uses polyimide material to make；Described phase
Becoming device is by hexadecane fill being made in metal-back, for carrying out multifunction structure unit
Passive thermal control.
By using technique scheme, define a kind of spacecraft multifunction structure integrated management and behaviour in-orbit
Ore-controlling Role, this system can provide power management and observing and controlling interface function, can realize multifunction structure inside electricity
The charge/discharge of source module controls, and can monitor the voltage and current signal of power module, simultaneously also by driving
Dynamic acceleration transducer multifunction structure within and temperature sensor, monitor and analyze its damping behavior with
Thermal characteristics.
Compared with prior art, it is an advantage of the current invention that: by multi-functional fusions such as spacecraft structure and power supplys,
Union power supply charge/discharge management, structural mechanical property monitoring, electrical property monitoring, data management and transmission etc. are
Integrally, it is possible to systematically perform to receive multi-functional realization, again to status monitoring and data pipe from telecommand
The task process such as reason and transmission, and volume is little, lightweight, functional density is high, solves spacecraft internal empty
Between limitation, weight restriction etc. with it, multi-functional, long-life etc. is required the sharp contradiction that day by day improves.
Accompanying drawing explanation
Fig. 1 is the theory diagram of the present invention.
Fig. 2 is the structural representation of multifunction structure unit.
Fig. 3 is the structure composition diagram of Power Management Unit.
Fig. 4 is the structure composition diagram of data processing unit.
Fig. 5 is the annexation figure of discharge load unit.
Fig. 6 is spacecraft of the present invention multifunction structure integrated management in-orbit with control system within spacecraft
A kind of installation site schematic diagram.
Fig. 7 is spacecraft of the present invention multifunction structure integrated management in-orbit with control system within spacecraft
Another kind of installation site schematic diagram.
Label declaration in figure:
1, multifunction structure unit；2, Power Management Unit；3, data processing unit；4, discharge load
Unit；5, framework；6, upper cover plate；7, lower cover；8, can charge/discharge source module I；9, can charge/discharge
Source module II；10, can charge/discharge source module III；11, can charge/discharge source module IV；12, elastomer block；13、
Cushion.
Symbol description in figure:
MFSU multifunction structure unit；BMU Power Management Unit；DPU data process
Unit；DLU discharge load unit；BCR charging regulator module；BDR discharges regulation
Device module；APS auxiliary source circuit.
Detailed description of the invention
In order to make technical problem solved by the invention, technical scheme and beneficial effect clearer, with
Lower combination drawings and Examples, are further elaborated to the present invention.Should be appreciated that described herein
Specific embodiment only in order to explain the present invention, be not intended to limit the present invention.
In order to integrated management and manipulation spacecraft electric energy manage multifunction structure with mechanical environment, the present invention proposes
A kind of spacecraft multifunction structure integrated management and control system in-orbit.
In conjunction with Fig. 1-Fig. 7, spacecraft multifunction structure integrated management and the control system in-orbit that the present invention provides,
Including multifunction structure unit 1, Power Management Unit 2, data processing unit 3 and discharge load unit 4, energy
Enough systematically execution receives multi-functional realization, again to status monitoring and data management and transmission from telecommand
Deng task process.
Hereinafter each ingredient is described in detail:
(1) multifunction structure unit
Described multifunction structure unit 1 is the core of spacecraft multifunction structure integrated management in-orbit and control system
Heart workpiece, has the functions such as structural bearing, vibration damping, power supply and electric power storage, vibration and temperature survey.Fig. 2
For the structural representation of multifunction structure unit 1, including main structure module, four can charge/discharge source module, subtract
Four parts such as vibrating system and sensor assembly.
1, multifunction structure unit
Described multifunction structure unit includes framework 5, upper cover plate 6 and lower cover 7；Lower cover 7 is fixed on framework 5
Bottom surface；Upper cover plate 6 is fixed on the end face of framework 5；Framework 5, in sphere of movements for the elephants configuration, has upper and lower, left and right
And the structural symmetry on fore-and-aft direction.Framework 5 forms main force support structure together with upper cover plate 6, lower cover 7,
There is the function of structural bearing.
Described framework 5 includes the frame being positioned at surrounding and to be positioned at the Os Draconis of lower portion, frame and Os Draconis equal
Use hollow square tube to be linked and packed to form.Described hollow square tube be use carbon fibre composite laying make and
Becoming, its ply sequence is [± 45/0/ ± 45]2S.By cross joint, L-type structure between described hollow square tube
Or the mutual assembly and connection of T connector forms frame and Os Draconis and then forms framework.In order to strengthen hollow square tube
With cross joint, the reliability that is connected between L-type structure and T connector, described cross joint, L
Adhesive is all used to carry out between type structure and T connector with connected hollow square tube bonding.
Described upper cover plate 6, lower cover 7 all use sandwich structure, described upper and lower cover plate all include eyelid covering,
Sandwich panel and lower eyelid covering, upper eyelid covering and lower eyelid covering are respectively paved on the upper and lower surface being fixed on sandwich framework,
Up and down adhesive between eyelid covering and sandwich panel, is all used to be attached, and control the bonded adhesives at adhesive place
The thickness of layer is in the range of 0.1mm～0.2mm, and uses J47 glued membrane as adhesive.Described sandwich panel
Using rib form, sandwich framework is uniform in a plurality of muscle laterally or longitudinally arranged in including frame and frame
Rib.
Additionally, be also equipped with multiple steam vent on upper cover plate 6 and lower cover 7, for use as technical process and vacuum ring
The passing away of internal gas under border.
2, can charge/discharge source module
Described can amount to 4 by charge/discharge source module, be designated as respectively can charge/discharge source module I 8, can discharge charge power supply
Module II 9, can charge/discharge source module III 10 and can charge/discharge source module IV 11；Can adopt by charge/discharge source module
With lithium battery, it is furthermore preferred that solid state lithium battery can be used；Each can charge/discharge source module in the way of being embedded into
It is arranged in the closing grid cavity that framework 5 and upper and lower cover plates 6,7 are formed.Further, in each grid cavity
Unique installation 1 can charge/discharge source module；Can both have repeatedly charging and multiple discharge by charge/discharge source module
Function, has again the function serving as oscillator consumption vibrational energy.
In the present embodiment, adjacent for position 2 can be connected by charge/discharge source module, obtain two groups identical defeated
Go out the power supply of voltage, be called main part power supply and backup battery；Main part power supply and master backup power supply respectively have 1
Road discharge and recharge interface, this discharge and recharge interface is forceful electric power interface, uses forceful electric power cable to be connected with Power Management Unit 2
Connect.
Can also draw some voltage detecting lines inside charge/discharge source module, and be welded to be installed on outside framework 5
On the electric connector of wall, formed one for detect each can the detection of charge/discharge source module tapping voltage signal
Interface.
External Power Management Unit 2 can be connected the most further by charge/discharge source module, it is possible to achieve constant current discharge charge
Electricity or constant voltage charge/discharge, charge/discharge speed simultaneously is controlled, thus effectively realizes the management to electric energy.
3, vibration insulating system
Described discharge charge can be provided with elastic between charge/discharge source module and framework 5, upper cover plate 6 and lower cover 7
Support member.Described elastic supporting member for supporting optical member includes elastomer block 12 and cushion 13, and described elastomer block 12 and cushion 13 are equal
K216 silastic material is used to support.
Each can charge/discharge source module surrounding with for accommodate this can the grid cavity of charge/discharge source module
Elastomer block 12 it is provided with between wall；Each can be provided with elasticity between bottom surface and the lower cover 7 of charge/discharge source module
Pad 13, each can be also equipped with cushion 13 between bottom surface and the upper cover plate 6 of charge/discharge source module；Can discharge charge
Power module, elastomer block 12 and cushion 13 constitute vibration insulating system, are equivalent to " spring-oscillator " model, its
In, elastomer block 12 and cushion 13 are equivalent to the resilient support with certain rigidity and damping；Can discharge charge power supply
Module is equivalent to the oscillator with certain mass.This vibration insulating system is on the one hand by the deformation absorbing of resilient support
On the other hand power consumption, by structural vibration energy being converted into charge/discharge source module oscillator kinetic energy as oscillator
Mode consume vibrational energy, the result of the two comprehensive function reduce vibration in multifunction structure unit
Transmission, and effectively management can the mechanical environment of charge/discharge source module.
Elastomer block 12 and cushion 13 both had structure support can the function of charge/discharge source module, also by from
Body elastic deformation reaches to dissipate the effect of a part of vibrational energy, have protection can the function of charge/discharge source module,
The most also having can the insulation of charge/discharge source module and the function dispelled the heat.
Elastomer block 12 in rectangular shape, its two ends respectively with the medial surface of framework 5 and can charge/discharge source module
Lateral surface connects with the face way of contact, there is not fixed relationship；Cushion 13 is in well word configuration, and one side is passed through
Adhesive bonds together with the lower surface of upper cover plate 6 and the upper surface of lower cover 7, and another side only connects with face
The mode of touching with can the surface of charge/discharge source module connect, there is not fixed relationship；Elastomer block 12 after installing
Be in pre-pressing state with cushion 13, there is structure supporting role, can make filling under resting state/
Discharge source module determines in the internal holding position of framework 5.
In the inner side of framework 5, the position at the root boundary of each elastomer block 12 both sides, all use structure gluing
Agent is bonded with limited block, for carrying out spacing to elastomer block 12.
4, sensor assembly
Described sensor assembly includes multiple temperature sensor and multiple acceleration transducer；Wherein, temperature passes
Sensor be arranged at can the inner chamber of charge/discharge source module and lateral wall, can the temperature of charge/discharge source module for monitoring
Degree；Acceleration transducer is arranged at the inwall of framework 5, the inwall of upper cover plate 6 and the inwall of lower cover 7, is used for
Gage frame 5, upper cover plate 6 and the Vibration Condition of lower cover 7, for multifunction structure unit internal electric energy and vibration
Management provides detection and monitoring means.
(2) Power Management Unit
Power Management Unit 2 is the important composition of spacecraft multifunction structure integrated management in-orbit and control system
Part, it is possible to provide charge/discharge control, master for spacecraft multifunction structure integrated management in-orbit and regulator control system
Stand-by power source controls and detects the functions such as conditioning.Specifically, Power Management Unit 2 receives the remote control of spacecraft platform
Instruction, utilize spacecraft bus power supply and discharge load unit 4, in multifunction structure unit 1 can discharge charge
Power module charges and discharges operation；Meanwhile, detect and nurse one's health can discharge charge power supply mould for Power Management Unit 2
The unit for electrical property parameters (including voltage, current signal) of block, submits to data processing unit 3 and spacecraft, and
Self working status parameter is submitted to spacecraft platform by direct telemetry interface.
With reference to the structure composition diagram that Fig. 3 is Power Management Unit.Power Management Unit Power Management Unit 2 includes
Charging regulator module BCR, electric discharge adjustor module BDR, conditioning circuit module, auxiliary source circuit APS
(being included in modules) is constituted.Charhing unit module BCR mainly by main power circuit, protection circuit,
Sample circuit, charging control and the composition such as power driving circuit and power supply circuits；Electric discharge adjustor module BDR
Mainly it is made up of filter circuit, protection circuit, charge/discharge control circuit and power supply circuits；Conditioning circuit module master
To make to flow through that often to save the electric current of cell consistent to carrying out corresponding compensation between every batteries and ground；Auxiliary
Source circuit APS is helped to have input undervoltage protection, the input defencive function such as overcurrent protection, output over-voltage protection.
(3) data processing unit
It is heavy with another of control system that data processing unit 3 is spacecraft multifunction structure integrated management in-orbit
Wanting ingredient, it obtains bus power supply and the control instruction of 100V DC from spacecraft platform, passes through sensor
With detection modulate circuit obtain multifunction structure unit 1 run time mechanical performance parameter (acceleration signal) with
Can the unit for electrical property parameters (voltage, current signal and temperature signal) of charge/discharge source module, and connect by remote measurement
Mouth (direct remote measurement amount and bus telemetering channel) passes interface with number, the data of collection is submitted to spacecraft and puts down
Platform, finally passes ground observing and controlling platform back.
Fig. 4 is the structure composition diagram of data processing unit, including can charge/discharge source module, CPU control module,
Data acquisition module and four module compositions of optical fiber controller module.Wherein, can the main merit of charge/discharge source module
Can include that the conversion of primary power source interface, instruction interface, secondary power supply, equipment add power-off control, relay shape
State amount remote measurement, Fibre Optical Sensor and acceleration transducer add power-off control etc.；CPU control module major function
It is collection and process, data storage and LVDS data transmission control, the 1553B bus communication control etc. of data
Function；Data acquisition module major function includes acceleration transducer interface, Temperature Quantity input interface, voltage
Amount input interface, multiselect one passage control, signal condition etc.；Optical fiber controller module is used for as optical fiber control
Device provides working power, and by the collection data of RS485 interface optical fiber controller output.Energy of the present invention
Enough realize spacecraft multifunction structure integrated management in-orbit and regulator control system in launching phase and phase in orbit
Between structural behaviour and battery performance be acquired, store, process and the function such as transmission.
In the present embodiment, the component quality grade in data processing unit 3 all uses more than general army, and passes through
Redundancy Design improves equipment dependability, in addition to sensor interface and modulate circuit, equipment add power-off control circuit,
Other circuit all does Redundancy Design.
(4) discharge load unit
Discharge load unit 4 is that spacecraft multifunction structure integrated management in-orbit is born with the electricity consumption in control system
Carrying, it can use any form of load, and main consumption can discharge charge power supply mould inside multifunction structure unit
The electric energy of block.
Fig. 5 is the annexation figure of discharge load unit 4, and it is by Power Management Unit 2 and multifunction structure list
Contact set up by the internal electric source of unit 1, can consume multifunction structure unit 1 under the control of Power Management Unit 2
Internal can the energy of charge/discharge source module.
In the present embodiment, discharge load unit 4 have employed 10 tunnels maturations, the heating of purely resistive load type
Sheet realizes.10 road heating plates are with parallel operation, and the rated power on every road is 62.5W, and its technical specification is joined
Number is as shown in table 1 below.
The technical specification parameter of the internal heating plate of table 1 discharge load unit
| Sequence number | Attribute | Technical specification parameter |
| 1 | Nominal input voltage | 80～105V (direct current DC) |
| 2 | Unit rated power | 625W |
| 3 | Heating plate quantity | 10 tunnels are in parallel |
| 4 | Single channel heating plate rated power | 62.5W |
| 5 | Heating plate type | Purely resistive load |
| 6 | Single channel heating plate resistance | 180±1Ω |
By using technique scheme, define the power supply charge/discharge management of a kind of collection, structural mechanical property prison
The spacecraft multifunction structure integrated management in-orbit that survey, electrical property monitoring, data management and transmission etc. are integrated
With control system.The innovative point of the present invention is as follows:
(1) this system is by multi-functional fusions such as spacecraft structure and power supplys, it is possible to systematically perform to refer to from remote control
Order receives multi-functional realization, arrive the task process such as status monitoring and data management and transmission again；
(2) this system bulk is little, lightweight, functional density is high, solve spacecraft inner space limitation,
The sharp contradiction that the requirements such as multi-functional, long-life are day by day improved by weight restriction etc. with it.
Below in conjunction with present invention connection between assembly technology flow process and each building block of system on spacecraft
Relation, is specifically described with control system this spacecraft multifunction structure integrated management in-orbit.
1st step, multifunction structure unit is installed.
Multifunction structure unit mainly has two kinds at spaceborne mounting means, the most as shown in Figure 6 and Figure 7.
First kind of way is multifunction structure unit to be connected by screw mode be arranged in spacecraft deck board, such as Fig. 6
Shown in；The second way is as new space flight using direct substitution for multifunction structure unit original spacecraft deck board
Device deck board uses, as shown in Figure 7.In addition, it is possible to the dividing plate as spacecraft uses.
In the present embodiment, use the mode (first kind of way) that bolt is spirally connected by described multifunction structure unit
It is installed in spacecraft deck board (referring specifically to Fig. 6).Consider from thermal control design angle, at described multi-functional knot
A kind of phase change device is there is also mounted between structure unit and spacecraft deck board.This phase change device is by by positive 16
The alkane colourless liquid of 18.2 DEG C (a kind of fusing point be) fill is made in board-like metal-back, for many merits
Passive thermal control can be carried out by construction unit 1.Additionally, consider from insulating Design angle, at phase change device with described many
Between the bottom surface of functional architecture unit, additionally use dielectric film and isolate.This dielectric film uses polyimides
Material is made, it is possible to multifunction structure unit is played insulating effect.
2nd step, Power Management Unit is installed and connection.
As shown in Figure 6 and Figure 7, in Power Management Unit is installed on the body cabin of spacecraft.
After installing, the most respectively with 2 forceful electric power cables by 2 tunnel charge/discharge interfaces of Power Management Unit 2
(X04 with X09) is connected to 2 tunnel charge/discharge interfaces (the most corresponding multi-functional solution list of multifunction structure unit
Main part power supply within Yuan and backup battery), to realize can charge/discharge source module in multifunction structure unit
Charging and discharging operation control；Then, will be used for detecting supply voltage in Power Management Unit 2 with cable
Interface is connected to the electric connector of multifunction structure unit, and (this electric connector is mounted to multifunction structure unit
Framework lateral wall, for detect each can the detection interface of charge/discharge source module tapping voltage signal), this electricity
After source voltage input power administrative unit 2, by under the process of modulate circuit therein, form power supply classification electricity
Pressure signal exports to data processing unit 3.
3rd step, data processing unit is installed and connection.
Similarly, data processing unit 3 is also installed in the body cabin of spacecraft, as shown in Figure 6 and Figure 7.
After data processing unit 3 installs, the most respectively with weak-current cable by the temperature of data processing unit 3/add
2 road light current interfaces of rate signal input interface and multifunction structure unit 1 (i.e. temperature signal output interface and
Acceleration signal output interface) couple together；Then, use cable by the supply voltage of data processing unit 3
/ current signal interface and power supply tapping voltage signaling interface output interface corresponding to Power Management Unit 2 are even
Pick up, to obtain supply voltage/current signal and power supply tapping voltage signal.
4th step, discharge load unit is installed and connection.
Discharge load unit 4 can use the alternate manner such as be mounted on spacecraft bulkhead or be spirally connected to be arranged on space flight
In device body cabin.In the present embodiment, discharge load unit is to use 10 road heating plate parallel waies to constitute,
Thus use heat conductive silica gel to be mounted on the bulkhead of spacecraft.
After attachment, by cable, discharge load unit 4 is connected to an interface of Power Management Unit 2
(X03) on.So, discharge load unit inside with multifunction structure unit 1 the most in an indirect way can fill/
Discharge source module sets up contact, and under the control of Power Management Unit 2, consumes multifunction structure unit 1
Internal can the energy of charge/discharge source module.
The above is only the preferred embodiment of the present invention, and protection scope of the present invention is not limited merely to
Stating embodiment, all technical schemes belonged under thinking of the present invention belong to protection scope of the present invention.Should carry
Go out, for those skilled in the art, improvement without departing from the principles of the present invention
And retouching, these improvements and modifications also should be regarded as protection scope of the present invention.
Claims (10)
1. spacecraft multifunction structure integrated management and a control system in-orbit, including multifunction structure unit
(1), Power Management Unit (2), data processing unit (3) and discharge load unit (4), its spy
Levy and be:
Described multifunction structure unit (1) by main structure module, four can charge/discharge source module, vibration insulating system
And sensor assembly composition, described Power Management Unit (2) with can be connected by charge/discharge source module, control can
The charging and discharging operation of charge/discharge source module, simultaneously in real time detection adjust can charge/discharge source module each electrically
Can parameter, and each unit for electrical property parameters of charge/discharge source module will can be transferred to data processing unit (3), and will
Self working status parameter is directly submitted to spacecraft platform by the telemetry interface of himself；At described data
Reason unit (3) is connected with sensor assembly, obtains multifunction structure unit (1) by sensor assembly and transports
Mechanical performance parameter during row and unit for electrical property parameters, and pass interface by the telemetry interface of himself with number, will
The data gathered submit to spacecraft platform, finally pass ground observing and controlling platform back；Described discharge load unit (4)
It is connected with Power Management Unit (2), it is possible under the control of Power Management Unit (2), consume power module
Energy.
Spacecraft the most according to claim 1 multifunction structure integrated management and control system in-orbit, its
It is characterised by:
Described main structure module includes framework (5), upper cover plate (6) and lower cover (7), described framework (5)
Monnolithic case be field word configuration, there are four grid cavitys, described framework (5) has about x, y and z
The comprehensive symmetry of three axles；Described lower cover (7) is fixed on the bottom surface of described framework (5)；On described
Cover plate (6) is fixed on the end face of described framework (5)；Described framework (5), upper cover plate (6) and lower cover
Plate (7) composition main force support structure；
Described can include 4 by charge/discharge source module, be designated as respectively can charge/discharge source module I (8), can fill/
Discharge source module II (9), can charge/discharge source module III (10) and can charge/discharge source module IV (11)；
Each can be arranged at framework (5), upper cover plate (6) by elastic support structure to be embedded into mode by charge/discharge source module
And in the closing grid cavity that formed of lower cover (7), and uniquely pacify in each grid cavity in framework
Filling 1 can charge/discharge source module；Can the positive and negative polar curve of charge/discharge source module be drawn by forceful electric power cable, even
Receive formation discharge and recharge interface on the forceful electric power electric connector of the lateral wall being arranged at described framework；Described can discharge charge
Power module had both had the function of repeatedly charging and multiple discharge, has again and serves as oscillator consumption vibrational energy
Function；
Each can charge/discharge source module surrounding with for accommodate this can be in the grid cavity of charge/discharge source module
Elastomer block (12) it is provided with between wall；Each can charge/discharge source module bottom surface and described lower cover (7) it
Between be provided with cushion (13), each can between end face and the described upper cover plate (6) of charge/discharge source module also
It is provided with cushion (13)；Charge/discharge source module, elastomer block (12) and cushion (13) can constitute and subtract
Vibrating system；
Described sensor assembly includes several temperature sensors and several acceleration transducers；Described some
Individual temperature sensor be respectively arranged at can the inner chamber of charge/discharge source module and lateral wall, be used for monitoring can fill accordingly/
The temperature of discharge source module；Several acceleration transducers described be respectively arranged at described framework (5) inwall,
The inwall of upper cover plate (6) and the inwall of described lower cover (7), be used for measuring described framework (5),
Cover plate (6) and the Vibration Condition of described lower cover (7).
Spacecraft the most according to claim 2 multifunction structure integrated management and control system in-orbit, its
It is characterised by: described multifunction structure unit (1) has 2 road light current interfaces, respectively temperature signal output
Interface and acceleration signal output interface, they all use weak-current cable to be connected with data processing unit (3).
4. according to the spacecraft described in Claims 2 or 3 multifunction structure integrated management and control system in-orbit,
It is characterized in that: adjacent for position 2 can be connected by charge/discharge source module, obtain two groups of identical output electricity
The power supply of pressure, is called main part power supply and backup battery；Described main part power supply and backup battery respectively have 1 tunnel
Discharge and recharge interface, discharge and recharge interface is forceful electric power interface, and described main part power supply and backup battery fill each via it
Electric discharge interface uses forceful electric power cable to be connected with Power Management Unit (2).
Spacecraft the most according to claim 4 multifunction structure integrated management and control system in-orbit, its
It is characterised by: described Power Management Unit (2) includes charging regulator module, electric discharge adjustor module, tune
Reason circuit module and auxiliary source circuit, have charging control, control of discharge, the switching of active/standby part power supply and voltage/
Current detecting conditioning functions；For multifunction structure unit (1) in orbit time charge/discharge management, and
Utilize the detection modulate circuit being internally integrated, assist discharge load unit (4) to obtain multifunction structure unit (1)
In lithium battery unit for electrical property parameters in orbit.
Spacecraft the most according to claim 5 multifunction structure integrated management and control system in-orbit, its
It is characterised by: described Power Management Unit (2) has 2 tunnel discharge and recharge interfaces and 1 road instruction interface, and 2 tunnels are filled
Electric discharge interface is connected respectively to main part power supply and the backup battery of power module, and 1 instruction interface receives spacecraft
The control instruction sent, Power Management Unit (2) control discharge load unit (4) to main part power supply or
Backup battery discharges.
Spacecraft the most according to claim 1 multifunction structure integrated management and control system in-orbit, its
Being characterised by, described data processing unit (3) includes power module, CPU control module and data acquisition module
Block, data processing unit (3) gather, process and transmit multifunction structure unit (1) at launching phase and
Mechanical performance parameter during in orbit and the unit for electrical property parameters such as voltage, electric current, obtain multifunction structure list
The vibration characteristics of unit (1), the structural support energy of checking multifunction structure unit (1) and basic electric property energy.
Spacecraft the most according to claim 1 multifunction structure integrated management and control system in-orbit, its
It is characterised by: described discharge load unit (4) uses the mode of multichannel heating plate to realize, and is used for consuming many merits
The electric energy of energy construction unit.
Spacecraft the most according to claim 1 multifunction structure integrated management and control system in-orbit, its
It is characterised by: described multifunction structure unit (1) mode of being connected by screw is arranged in spacecraft deck board,
Or multifunction structure unit (1) uses directly as spacecraft deck board or dividing plate；
Described Power Management Unit (2) and data processing unit (3) are mounted in spacecraft body cabin；
Described discharge load unit (4) can use thermal conductance sticker to be contained on spacecraft bulkhead or other side such as be spirally connected
Formula is arranged in spacecraft body cabin, and is connected with Power Management Unit (2) by cable.
Spacecraft the most according to claim 9 multifunction structure integrated management and control system in-orbit, its
Be characterised by: on described multifunction structure unit (1) bottom surface install phase change device, this multifunction structure with
Isolate with dielectric film between phase change device；Described dielectric film uses polyimide material to make；Described phase transformation fills
Putting is by hexadecane fill being made in metal-back, for carrying out multifunction structure unit (1)
Passive thermal control.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106886665A (en) * | 2017-04-06 | 2017-06-23 | 中国人民解放军国防科学技术大学 | New ideas space flight multifunction structure ground simulation demonstration and verification system |
| CN110957711A (en) * | 2019-11-14 | 2020-04-03 | 中国空间技术研究院 | Equivalent spacecraft power supply overvoltage protection device for ground test |
| CN114154243A (en) * | 2021-12-03 | 2022-03-08 | 中国人民解放军国防科技大学 | Active and passive comprehensive thermal control design method for aerospace multifunctional structure battery |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1227038A2 (en) * | 2001-01-30 | 2002-07-31 | TRW Inc. | Method for providing power to electric propulsion thrusters |
| US20040261569A1 (en) * | 2003-06-26 | 2004-12-30 | Jacobs Jack H. | Piezodynamic vibration damping system |
| CN102795350A (en) * | 2012-07-06 | 2012-11-28 | 中国航天科技集团公司第五研究院第五一三研究所 | Physical discrete type satellite system structure |
| CN103944629A (en) * | 2014-04-28 | 2014-07-23 | 航天东方红卫星有限公司 | Satellite integrated electronic system |
| CN104460443A (en) * | 2014-11-18 | 2015-03-25 | 上海空间电源研究所 | Fast integration power supply and distribution control device for satellite |
| CN105425874A (en) * | 2015-11-12 | 2016-03-23 | 淮滨县电业局 | Unattended transformer substation information acquisition device |
| CN105947235A (en) * | 2016-05-10 | 2016-09-21 | 国防科学技术大学 | Electric energy and mechanical environment management multifunctional structure |
-
2016
- 2016-05-10 CN CN201610305265.1A patent/CN105955075B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1227038A2 (en) * | 2001-01-30 | 2002-07-31 | TRW Inc. | Method for providing power to electric propulsion thrusters |
| US20040261569A1 (en) * | 2003-06-26 | 2004-12-30 | Jacobs Jack H. | Piezodynamic vibration damping system |
| CN102795350A (en) * | 2012-07-06 | 2012-11-28 | 中国航天科技集团公司第五研究院第五一三研究所 | Physical discrete type satellite system structure |
| CN103944629A (en) * | 2014-04-28 | 2014-07-23 | 航天东方红卫星有限公司 | Satellite integrated electronic system |
| CN104460443A (en) * | 2014-11-18 | 2015-03-25 | 上海空间电源研究所 | Fast integration power supply and distribution control device for satellite |
| CN105425874A (en) * | 2015-11-12 | 2016-03-23 | 淮滨县电业局 | Unattended transformer substation information acquisition device |
| CN105947235A (en) * | 2016-05-10 | 2016-09-21 | 国防科学技术大学 | Electric energy and mechanical environment management multifunctional structure |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106886665A (en) * | 2017-04-06 | 2017-06-23 | 中国人民解放军国防科学技术大学 | New ideas space flight multifunction structure ground simulation demonstration and verification system |
| CN110957711A (en) * | 2019-11-14 | 2020-04-03 | 中国空间技术研究院 | Equivalent spacecraft power supply overvoltage protection device for ground test |
| CN110957711B (en) * | 2019-11-14 | 2022-04-12 | 中国空间技术研究院 | Equivalent spacecraft power supply overvoltage protection device for ground test |
| CN114154243A (en) * | 2021-12-03 | 2022-03-08 | 中国人民解放军国防科技大学 | Active and passive comprehensive thermal control design method for aerospace multifunctional structure battery |
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|---|---|
| CN105955075B (en) | 2017-03-22 |
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