CN105955075B - Spacecraft in-orbit multifunctional structure integrated management and control system - Google Patents
Spacecraft in-orbit multifunctional structure integrated management and control system Download PDFInfo
- Publication number
- CN105955075B CN105955075B CN201610305265.1A CN201610305265A CN105955075B CN 105955075 B CN105955075 B CN 105955075B CN 201610305265 A CN201610305265 A CN 201610305265A CN 105955075 B CN105955075 B CN 105955075B
- Authority
- CN
- China
- Prior art keywords
- charge
- discharge
- unit
- source module
- spacecraft
- 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.)
- Active
Links
Classifications
-
- 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
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, and in particular to a kind of in-orbit multifunction structure of spacecraft is comprehensive
Close management and control system.
Background technology
Currently, spacecraft proposes higher and higher requirement to its payload ratio and using space, for this purpose, multi-functional
Structure technology is gradually taken seriously in space industry and moves towards application.Multifunction structure technology be data processing, radiation protection,
The functions such as thermal control, electric power storage and spacecraft self structure organically blend a technology being integrated, by using structure, function and material
The integrated design of material, eliminates bulk redundancy quality and volume, so as to be obviously improved load/mass ratio, the load/body of spacecraft
Product ratio and function/structure ratio.
However, for a specific multifunction structure, wanting to realize which, in spaceborne smooth, normal work, needs
Its operation on orbit process is managed and is controlled, while needing to be monitored its operation on orbit state.Therefore, it is badly in need of grinding
A set of in-orbit management and control system are made, so that effectively management and control are carried out to spacecraft multifunction structure.Up to now, in state
The inside and outside document report or engineer applied precedent having not found with regard to such management with control system.
The content of the invention
In order to realize multifunction structure normal work on spacecraft, the invention provides a kind of spacecraft is in-orbit multi-functional
Structure composition management and control system.
The technical scheme is that：
A kind of in-orbit multifunction structure integrated management of spacecraft and control system, including multifunction structure unit, power supply pipe
Reason unit, data processing unit and discharge load unit.Wherein, the multifunction structure unit by main structure module, four can
Charge/discharge source module, vibration insulating system and sensor assembly composition, the PMU with can charge/discharge source module connect
Connect, control can charge/discharge source module charging and discharging operation, while real-time detection adjustment can charge/discharge source module each electricity
Performance parameter, and by can each unit for electrical property parameters of charge/discharge source module be transferred to data processing unit, and by itself working condition
Parameter is directly submitted to spacecraft platform by the telemetry interface of its own；The data processing unit is connected with sensor assembly
Connect, the mechanical performance parameter and unit for electrical property parameters when multifunction structure unit runs is obtained by sensor assembly, and passes through which
The telemetry interface of itself passes interface with number, and the data of collection are submitted to spacecraft platform, ground observing and controlling platform is finally passed back；Institute
State discharge load unit to be connected with PMU, the energy of power module can be consumed under the control of PMU
Amount.
In the present invention, the main structure module includes framework, upper cover plate and lower cover；Wherein, the framework is overall outer
Shape is in field word configuration, and with four grid cavitys, the framework is with the comprehensive symmetry with regard to tri- axle of x, y and z；Under described
Cover plate is fixed on the bottom surface of the framework；The upper cover plate is fixed on the top surface of the framework；The framework, upper cover plate and lower cover
Plate together constitutes main force support structure, the function with structural bearing；
It is described can charge/discharge source module include 4, be designated as respectively can charge/discharge source module I, can charge/discharge source module
IIth, can charge/discharge source module III and can charge/discharge source module IV；Each can charge/discharge source module by elastic support structure with
It is embedded into mode to be arranged in the closing grid cavity formed by framework, upper cover plate and lower cover, and each grid in framework
In cavity, unique installation one can charge/discharge source module；Can the positive and negative polar curve of charge/discharge source module drawn by forceful electric power cable,
It is connected to formation charge and discharge electrical interface on the forceful electric power electric connector of the lateral wall for being arranged at the framework；It is described can discharge charge power supply mould
Block had both had a function of repeatedly charging with multiple discharge, and with serving as oscillator and consume the function of vibrational energy.
Each can charge/discharge source module surrounding and can be between the grid cavity wall of charge/discharge source module for accommodating this
It is provided with elastomer block.Each can charge/discharge source module bottom surface and the lower cover between be provided with cushion.Each can fill/
Cushion is also equipped between the top surface and the upper cover plate of electric discharge source module.Can charge/discharge source module, elastomer block and cushion
Vibration insulating system is constituted, equivalent to " spring-oscillator " model.Wherein, the elastomer block and the cushion are equivalent to certain
Rigidity and the resilient support of damping；It is described can charge/discharge source module equivalent to the oscillator with certain mass, the vibration insulating system one
Deformation absorbing power consumption of the aspect by resilient support, on the other hand by as oscillator can charge/discharge source module by structural vibration
Energy is converted into the mode of oscillator kinetic energy to consume vibrational energy, and the result of the two comprehensive function reduces vibration in multi-functional knot
Transmission in structure, and effectively management can charge/discharge source module mechanical environment；
The sensor assembly includes several temperature sensors and several acceleration transducers；Wherein, it is described some
Individual temperature sensor be respectively arranged at can charge/discharge source module inner chamber and lateral wall, accordingly can discharge charge power supply mould for monitoring
The temperature of block；Described several acceleration transducers are respectively arranged at the inwall of the framework, the inwall of upper cover plate and described
The inwall of lower cover, for measuring the Vibration Condition of the framework, upper cover plate and the lower cover, is in multifunction structure unit
The electric energy in portion provides detection and monitoring means with vibration management.
Additionally, the multifunction structure unit also has 2 road light current interfaces, respectively temperature signal output interface and acceleration
Degree signal output interface, they are connected with data processing unit using weak-current cable.
In the present invention, can by by position adjacent 2 can charge/discharge source module connected, obtain two groups it is identical
The power supply of output voltage, is referred to as main part power supply and backup battery；Main part power supply and backup battery respectively have 1 tunnel charge and discharge
Electrical interface, charge and discharge electrical interface are forceful electric power interface, and main part power supply and backup battery adopt strong each via its charge and discharge electrical interface
Electrical cables are connected with PMU.
In the present invention, the PMU includes charging regulator module, electric discharge adjustor module, modulate circuit mould
Block and auxiliary source circuit, with charge control, control of discharge, the switching of active/standby part power supply and voltage/current detection conditioning functions；
Charge/discharge management during for multifunction structure unit in orbit, and using the detection modulate circuit being internally integrated, assist
Lithium battery in discharge load unit acquisition multifunction structure unit unit for electrical property parameters in orbit.
The PMU has 2 tunnel charge and discharge electrical interfaces and 1 road instruction interface, and 2 tunnel charge and discharge electrical interfaces connect respectively
To the control instruction that main part power supply and backup battery of power module, 1 instruction interface reception spacecraft send, power management list
Unit's control discharge load unit discharges to main part power supply or backup battery.
In the present invention, the data processing unit includes power module, CPU control modules and data acquisition module, data
Processing unit collection, process and transmit multifunction structure unit in launching phase and in orbit during mechanical performance parameter and
The unit for electrical property parameters such as voltage, electric current, obtain vibration characteristics, the structure of checking multifunction structure unit of multifunction structure unit
Support performance and basic electric property energy.
In the present invention, the discharge load unit can adopt any form of load, consume multifunction structure unit
Electric energy.As the discharge load unit is realized by the way of multichannel heating plate, for consuming the electric energy of multifunction structure unit.
In the present invention, the multifunction structure unit can be connected by screw mode in spacecraft deck board, also may be used
Use directly as spacecraft deck board or dividing plate.The PMU and data processing unit are mounted on spacecraft body
In cabin.The discharge load unit can be mounted on spacecraft bulkhead or is spirally connected etc. alternate manner and be arranged on space flight using thermal conductivity sticker
In device body cabin, and it is connected with PMU by cable.
Further, phase change device can be installed on the multifunction structure unit bottom surface, the multifunction structure and phase transformation
Dielectric film isolation is can use between device；The dielectric film is made using polyimide material；The phase change device is by will just
Hexadecane is filling to be made in metal-back, for carrying out passive thermal control to multifunction structure unit.
By adopting above-mentioned technical proposal, a kind of in-orbit multifunction structure integrated management of spacecraft is defined with manipulation system
System, the system can provide power management and observing and controlling interface function, be capable of achieving the charging to multifunction structure internal electric source module/put
Electric control, can monitor the voltage and current signal of power module, while can also pass through to drive the acceleration inside multifunction structure
Sensor and temperature sensor, monitor and analyze its damping behavior and 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, and current collection
Source charge/discharge management, structural mechanical property monitoring, electrical property monitoring, data management and transmission etc. are integrated, and systematically can hold
Row receives multi-functional realization from telecommand, again to task process such as status monitoring and data management and transmission, and small volume,
Lightweight, functional density is high, and solving spacecraft inner space limitation, weight restriction etc. will to multi-functional, long-life etc. with which
Seek the sharp contradiction for increasingly improving.
Description of the drawings
Fig. 1 is the theory diagram of the present invention.
Structural representations of the Fig. 2 for multifunction structure unit.
Structure composition figures of the Fig. 3 for PMU.
Structure composition figures of the Fig. 4 for data processing unit.
Annexation figures of the Fig. 5 for discharge load unit.
Fig. 6 is a kind of peace of the in-orbit multifunction structure integrated management of spacecraft of the present invention with control system inside spacecraft
Holding position schematic diagram.
Fig. 7 is the in-orbit multifunction structure integrated management of spacecraft of the present invention and another kind of the control system inside spacecraft
Schematic view of the mounting position.
Label declaration in figure：
1st, multifunction structure unit；2nd, PMU；3rd, data processing unit；4th, discharge load unit；5th, framework；
6th, upper cover plate；7th, lower cover；8th, can charge/discharge source module I；9th, can charge/discharge source module II；10th, can charge/discharge source module
III；11st, can charge/discharge source module IV；12nd, elastomer block；13rd, cushion.
Symbol description in figure：
MFSU multifunction structure units；BMU PMUs；DPU data processing units；
DLU discharge load units；BCR charging regulator modules；BDR electric discharge adjustor modules；APS auxiliary sources
Circuit.
Specific embodiment
In order that technical problem solved by the invention, technical scheme and beneficial effect become more apparent, below in conjunction with
Drawings and Examples, the present invention will be described in further detail.It should be appreciated that specific embodiment described herein only to
The present invention is explained, is 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 one kind
The in-orbit multifunction structure integrated management of spacecraft and control system.
The in-orbit multifunction structure integrated management of spacecraft provided with reference to Fig. 1-Fig. 7, the present invention and control system, including it is many
Functional architecture unit 1, PMU 2, data processing unit 3 and discharge load unit 4, systematically can perform from remote control
Command reception to multi-functional realization, arrive the task process such as status monitoring and data management and transmission again.
Hereinafter each part is described in detail：
(1) multifunction structure unit
The multifunction structure unit 1 is the core work of the in-orbit multifunction structure integrated management of spacecraft and control system
Part, with functions such as structural bearing, vibration damping, power supply and electric power storage, vibration and temperature surveys.Fig. 2 is multifunction structure unit 1
Structural representation, including main structure module, four can four portions such as charge/discharge source module, vibration insulating system and sensor assembly
Point.
1st, multifunction structure unit
The multifunction structure unit includes framework 5, upper cover plate 6 and lower cover 7；Lower cover 7 is fixed on the bottom of framework 5
Face；Upper cover plate 6 is fixed on the top surface of framework 5；Framework 5 is in sphere of movements for the elephants configuration, the structure with upper and lower, left and right and on fore-and-aft direction
Symmetry.Framework 5 constitutes main force support structure together with upper cover plate 6, lower cover 7, the function with structural bearing.
The framework 5 includes that the frame positioned at surrounding and the keel positioned at lower portion, frame and keel are adopted
Hollow square tube is linked and packed and forms.The hollow square tube is made using carbon fibre composite laying, its ply sequence
For [± 45/0/ ± 45]2S.Pass through cross type joint, the L-type structure or T connector mutually company of assembling between the hollow square tube
Connect to form frame and keel and then form framework.In order to strengthen hollow square tube and cross type joint, L-type structure and T-shaped connect
The reliability connected between head, between the cross type joint, L-type structure and T connector and connected hollow square tube
Bonding is carried out using adhesive.
The upper cover plate 6, lower cover 7 adopt sandwich structure, the upper and lower cover plate to include upper covering, sandwich panel
With lower covering, upper covering and lower covering be respectively paved and be fixed on the upper and lower surface of sandwich framework, upper and lower covering and sandwich panel
Between be attached using adhesive, and control adhesive place bonding glue-line thickness 0.1mm～0.2mm scope
It is interior, and using J47 glued membranes as adhesive.The sandwich panel adopts rib form, sandwich framework to include frame and frame
It is interior uniform in a plurality of rib for laterally or longitudinally arranging.
Additionally, multiple steam vents are also equipped with upper cover plate 6 and lower cover 7, under technical process and vacuum environment
The passing away of portion's gas.
2nd, can charge/discharge source module
It is described can charge/discharge source module amount to 4, be designated as respectively can charge/discharge source module I 8, can charge/discharge source module
II 9, can charge/discharge source module III 10 and can charge/discharge source module IV 11；Can charge/discharge source module can adopt lithium battery, it is more excellent
Choosing, solid state lithium battery can be adopted；Each can charge/discharge source module framework 5 and upper and lower cover plates 6,7 are arranged in the way of being embedded into
In the closing grid cavity for being formed.Also, unique installation 1 can charge/discharge source module in each grid cavity；Can discharge charge
Power module had both had a function of repeatedly charging with multiple discharge, and with serving as oscillator and consume the function of vibrational energy.
In the present embodiment, by position adjacent 2 can charge/discharge source module connected, obtain two groups it is identical output electricity
The power supply of pressure, is referred to as main part power supply and backup battery；Main part power supply and master backup power supply respectively have 1 tunnel charge and discharge electrical interface,
The charge and discharge electrical interface is forceful electric power interface, is connected with PMU 2 using forceful electric power cable.
Some voltage detecting lines can also being drawn inside charge/discharge source module, and be welded to and be installed on 5 lateral wall of framework
On electric connector, formed one be used for detect each can charge/discharge source module tapping voltage signal detection interface.
Can charge/discharge source module also further connect external PMU 2, it is possible to achieve constant current charge/discharge or
Constant pressure charge/discharge, while charge/discharge speed is controllable, so as to effectively realize the management to electric energy.
3rd, vibration insulating system
The discharge charge can be provided with elastic supporting member for supporting optical member between charge/discharge source module and framework 5, upper cover plate 6 and lower cover 7.
The elastic supporting member for supporting optical member includes that elastomer block 12 and cushion 13, the elastomer block 12 and cushion 13 adopt K216 silicon rubber materials
Material is supported.
Each can charge/discharge source module surrounding with for accommodate this can charge/discharge source module grid cavity wall it
Between be provided with elastomer block 12；Each can charge/discharge source module bottom surface and lower cover 7 between be provided with cushion 13, each can
Cushion 13 is also equipped between the bottom surface of charge/discharge source module and upper cover plate 6；Can charge/discharge source module, elastomer block 12 and bullet
Property pad 13 constitute vibration insulating system, equivalent to " spring-oscillator " model, wherein, elastomer block 12 and cushion 13 are equivalent to one
Determine the resilient support of rigidity and damping；Can charge/discharge source module equivalent to the oscillator with certain mass.One side of the vibration insulating system
Deformation absorbing power consumption of the face by resilient support, on the other hand by as oscillator can charge/discharge source module by structural vibration energy
Amount is converted into the mode of oscillator kinetic energy to consume vibrational energy, and the result of the two comprehensive function reduces vibration in multifunction structure
Transmission in unit, and effectively management can charge/discharge source module mechanical environment.
Elastomer block 12 and cushion 13 both have structural support can charge/discharge source module function, can also pass through itself bullet
Property deformation reach the effect of a part of vibrational energy that dissipates, with protection can charge/discharge source module function, while also with can
The function that charge/discharge source module insulate with radiating.
Elastomer block 12 is in rectangular shape, its two ends respectively with the medial surface of framework 5 and can charge/discharge source module outside
Face is connected with the face way of contact, there is no fixed relationship；Cushion 13 is in well word configuration, simultaneously by adhesive and upper cover plate 6
Lower surface and the upper surface of lower cover 7 bond together, and another side only with the face way of contact with can charge/discharge source module
Surface connects, and there is no fixed relationship；Elastomer block 12 and cushion 13 after installing is in pre-pressing state, with structure
Supporting role, can cause under inactive state can charge/discharge source module 5 inside holding position of framework determine.
In the inner side of framework 5, the position at each 12 both sides root boundary of elastomer block, using sqtructural adhesive bonding
Limited location block, it is spacing for carrying out to elastomer block 12.
4th, sensor assembly
The sensor assembly includes multiple temperature sensors and multiple acceleration transducers；Wherein, temperature sensor sets
Be placed in can charge/discharge source module inner chamber and lateral wall, for monitoring can charge/discharge source module temperature；Acceleration transducer
The inwall of the inwall, the inwall of upper cover plate 6 and lower cover 7 of framework 5 is arranged at, for gage frame 5, upper cover plate 6 and lower cover 7
Vibration Condition, be that multifunction structure unit internal electric energy and vibration management are provided and detected and monitoring means.
(2) PMU
PMU 2 is the important component part of the in-orbit multifunction structure integrated management of spacecraft and control system,
Charge/discharge control, main power supply control and inspection can be provided for the in-orbit multifunction structure integrated management of spacecraft and regulator control system
Survey the functions such as conditioning.Specifically, PMU 2 receives the telecommand of spacecraft platform, using spacecraft bus power supply
With discharge load unit 4, to multifunction structure unit 1 in can charge/discharge source module charge and discharge operation；Meanwhile,
PMU 2 detect and nurse one's health can charge/discharge source module unit for electrical property parameters (include voltage, current signal), submit to
Data processing unit 3 and spacecraft, and itself working status parameter is submitted to spacecraft platform by direct telemetry interface.
With reference to the structure composition figure that Fig. 3 is PMU.PMU PMU 2 includes charging and adjusts
Section device module BCR, electric discharge adjustor module BDR, conditioning circuit module, auxiliary source circuit APS (being included in modules) structure
Into.Charhing unit module BCR mainly by main power circuit, protection circuit, sample circuit, charge control and power driving circuit with
And the composition such as power supply circuits；Adjustor module BDR is mainly by filter circuit, protection circuit, charge/discharge control circuit and power supply for electric discharge
Circuit is constituted；Conditioning circuit module mainly to carry out between every batteries and ground it is corresponding compensate, make to flow through every section cell
Electric current it is consistent；Auxiliary source circuit APS has the defencive functions such as input undervoltage protection, input overcurrent protection, output over-voltage protection.
(3) data processing unit
Data processing unit 3 is another important composition of the in-orbit multifunction structure integrated management of spacecraft and control system
Part, which obtains the bus power supply and control instruction of 100V DC from spacecraft platform, is obtained by sensor and detection modulate circuit
Take multifunction structure unit 1 run when mechanical performance parameter (acceleration signal) with can charge/discharge source module electrical property ginseng
Number (voltage, current signal and temperature signal), and connect with number biography by telemetry interface (direct remote measurement amount and bus telemetering channel)
Mouthful, the data of collection are submitted to into spacecraft platform, ground observing and controlling platform is finally passed back.
Structure composition figures of the Fig. 4 for data processing unit, including can charge/discharge source module, CPU control modules, data adopt
Four module compositions of collection module and optical fiber controller module.Wherein, can charge/discharge source module major function include that primary power source connects
Mouth, instruction interface, secondary power supply conversion, equipment add power-off control, relay status amount remote measurement, Fibre Optical Sensor and acceleration to pass
Sensor adds power-off control etc.；CPU control module major functions are the collection of data and process, data storage and LVDS data is activations
The functions such as control, the control of 1553B bus communications；Data acquisition module major function includes acceleration transducer interface, Temperature Quantity
Input interface, voltage input interface, one passage control of multiselect, signal condition etc.；Optical fiber controller module is used for as optical fiber control
Device processed provides working power, and the gathered data exported by RS485 interfaces optical fiber controller.It is right that the present invention can be realized
The structural behaviour and electricity of the in-orbit multifunction structure integrated management of the spacecraft and regulator control system period in launching phase and in orbit
Pond performance data such as is acquired, stores, processes and transmits at the function.
In the present embodiment, the component quality grade in data processing unit 3 adopts more than general army, and is set by redundancy
Meter improves equipment dependability, and in addition to sensor interface and modulate circuit, equipment add power-off control circuit, other circuits all do redundancy
Design.
(4) discharge load unit
Discharge load unit 4 is the use electric loading in the in-orbit multifunction structure integrated management of spacecraft and control system, its
Can adopt any form of load, it is main consume inside multifunction structure unit can charge/discharge source module electric energy.
Annexation figures of the Fig. 5 for discharge load unit 4, which passes through PMU 2 with multifunction structure unit 1
Internal electric source sets up contact, can be under the control of PMU 2, and consuming can discharge charge power supply inside multifunction structure unit 1
The energy of module.
In the present embodiment, discharge load unit 4 employs 10 tunnels maturation, purely resistive load type heating plate reality
It is existing.With parallel operation, the rated power per road is 62.5W to 10 road heating plates, and its technical indicator parameter is as shown in table 1 below.
The technical indicator parameter of heating plate inside 1 discharge load unit of table
| Sequence number | Attribute | Technical indicator 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 sheet type | Purely resistive load |
| 6 | Single channel heating plate resistance | 180±1Ω |
By adopting above-mentioned technical proposal, a kind of power supply charge/discharge management of collection, structural mechanical property monitoring, electricity are defined
The in-orbit multifunction structure integrated management of spacecraft and control system that performance monitoring, data management and transmission etc. are integrated.This
Bright innovative point is as follows：
(1) the multi-functional fusions such as spacecraft structure and power supply can systematically be performed from telecommand and be received by the system
To multi-functional realization, the task process such as status monitoring and data management and transmission is arrived again；
(2) system bulk is little, lightweight, functional density is high, solves spacecraft inner space limitation, weight and limits etc.
Sharp contradiction for increasingly improving is required to multi-functional, long-life etc. with which.
With reference to annexation of the present invention on spacecraft between assembly technology flow process and each building block of system,
The in-orbit multifunction structure integrated management of the spacecraft is specifically described with control system.
1st step, multifunction structure unit are installed.
Multifunction structure unit mainly has two kinds in spaceborne mounting means, respectively as shown in Figure 6 and Figure 7.First
The mode of kind is that multifunction structure unit is connected by screw mode in spacecraft deck board, as shown in Figure 6；Second side
Formula is that multifunction structure unit directly replaces original spacecraft deck board use as new spacecraft deck board, as shown in Figure 7.This
Outward, also can use as the dividing plate of spacecraft.
In the present embodiment, by the way of bolt is spirally connected, the multifunction structure unit is installed on boat by (first kind of way)
In its device deck board (referring specifically to Fig. 6).Consider from thermal control design angle, the multifunction structure unit and spacecraft deck board it
Between there is also mounted a kind of phase change device.The phase change device is by by hexadecane (a kind of fusing point is 18.2 DEG C of colourless liquid)
It is filling to make in board-like metal-back, for carrying out passive thermal control to multifunction structure unit 1.Additionally, from insulating Design
Angle considers, between the bottom surface of phase change device and the multifunction structure unit, additionally uses dielectric film and isolated.This is exhausted
Velum is made using polyimide material, can play insulating effect to multifunction structure unit.
2nd step, PMU are installed and connection.
As shown in Figure 6 and Figure 7, PMU is installed in the body cabin of spacecraft.
After installing, first respectively with 2 forceful electric power cables by 2 tunnel charge/discharge interfaces of PMU 2 (X04 and
X09) be connected to multifunction structure unit 2 tunnel charge/discharge interfaces (respectively correspond to it is multi-functional solution unit inside main part power supply and
Backup battery), with realize in multifunction structure unit can charge/discharge source module charging and discharging operational control；Then, use
Cable will be used for detecting that the interface of supply voltage is connected to the electric connector of multifunction structure unit and (is somebody's turn to do on PMU 2
Electric connector is mounted to multifunction structure unit framework lateral wall, for detecting that each can charge/discharge source module tapping voltage
The detection interface of signal), after the supply voltage input power administrative unit 2, by under the process of its internal modulate circuit, formed
Power supply tapping voltage signal output is to data processing unit 3.
3rd step, data processing unit are 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 is installed, first respectively with weak-current cable by the temperature/acceleration of data processing unit 3
2 road light current interfaces (i.e. temperature signal output interface and the acceleration signal output of signal input interface and multifunction structure unit 1
Interface) couple together；Then, the supply voltage of data processing unit 3/current signal interface and power supply are classified using cable
Voltage signal interface is coupled together to the corresponding output interface of PMU 2, with obtain supply voltage/current signal and
Power supply tapping voltage signal.
4th step, discharge load unit are installed and connection.
Discharge load unit 4 can wait alternate manner installed in spacecraft body using being mounted on spacecraft bulkhead or being spirally connected
In cabin.In the present embodiment, discharge load unit is constituted using 10 road heating plate parallel ways, thus will using heat conductive silica gel
Which is mounted on the bulkhead of spacecraft.
After attachment is finished, discharge load unit 4 is connected to by cable for an interface (X03) of PMU 2
On.So, discharge load unit just in an indirect way with the inside of multifunction structure unit 1 can charge/discharge source module set up
Contact, and under the control of PMU 2, consume inside multifunction structure unit 1 can charge/discharge source module energy.
The above is only the preferred embodiment of the present invention, and protection scope of the present invention is not limited merely to above-mentioned enforcement
Example, all technical schemes belonged under thinking of the present invention belong to protection scope of the present invention.Should propose, for the art
Those of ordinary skill for, improvements and modifications without departing from the principles of the present invention, these improvements and modifications should also be regarded
For protection scope of the present invention.
Claims (9)
1. a kind of in-orbit multifunction structure integrated management of spacecraft and control system, including multifunction structure unit (1), power supply pipe
Reason unit (2), data processing unit (3) and discharge load unit (4), it is characterised in that：
The multifunction structure unit (1) by main structure module, four can charge/discharge source module, vibration insulating system and sensor
Module constitute, the PMU (2) with can charge/discharge source module be connected, control can charge/discharge source module charging with
Discharge operation, at the same real-time detection adjustment can charge/discharge source module each unit for electrical property parameters, and by can charge/discharge source module
Each unit for electrical property parameters is transferred to data processing unit (3), and itself working status parameter is straight by the telemetry interface of its own
Connect and be submitted to spacecraft platform；The data processing unit (3) is connected with sensor assembly, obtains many work(by sensor assembly
Mechanical performance parameter and unit for electrical property parameters when energy construction unit (1) runs, and connect with number biography by the telemetry interface of its own
Mouthful, the data of collection are submitted to into spacecraft platform, ground observing and controlling platform is finally passed back；The discharge load unit (4) and electricity
Source control unit (2) connects, and the energy of power module can be consumed under the control of PMU (2)；
The main structure module includes framework (5), upper cover plate (6) and lower cover (7), and the monnolithic case of the framework (5) is in field
Word configuration, with four grid cavitys, the framework (5) is with the comprehensive symmetry with regard to tri- axle of x, y and z；The lower cover
Plate (7) is fixed on the bottom surface of the framework (5)；The upper cover plate (6) is fixed on the top surface of the framework (5)；The framework
(5), upper cover plate (6) and lower cover (7) composition main force support structure；
It is described can charge/discharge source module include 4, be designated as respectively can charge/discharge source module I (8), can charge/discharge source module II
(9), can charge/discharge source module III (10) and can charge/discharge source module IV (11)；Each can charge/discharge source module by elasticity
Supporting construction is arranged in the closing grid cavity formed by framework (5), upper cover plate (6) and lower cover (7) with being embedded into mode,
And unique installation 1 can charge/discharge source module in each the grid cavity in framework；Can charge/discharge source module positive and negative polar curve
Drawn by forceful electric power cable, be connected to formation charge and discharge electrical interface on the forceful electric power electric connector of the lateral wall for being arranged at the framework；
It is described can charge/discharge source module both there is the function of repeatedly charging with multiple discharge, have again and serve as oscillator and consume vibrational energy
Function；
Each can charge/discharge source module surrounding and can set between the grid cavity inner wall of charge/discharge source module for accommodating this
It is equipped with elastomer block (12)；Each can charge/discharge source module bottom surface and the lower cover (7) between be provided with cushion (13),
Each can charge/discharge source module top surface and the upper cover plate (6) between be also equipped with cushion (13)；Elastomer block (12) and bullet
Property pad (13) constitute vibration insulating system；
The sensor assembly includes several temperature sensors and several acceleration transducers；Described several TEMPs
Device be respectively arranged at can charge/discharge source module inner chamber and lateral wall, for monitor accordingly can charge/discharge source module temperature；
Described several acceleration transducers are respectively arranged at the inwall of the framework (5), the inwall of upper cover plate (6) and the lower cover
The inwall of plate (7), for measuring the Vibration Condition of the framework (5), upper cover plate (6) and the lower cover (7).
2. the in-orbit multifunction structure integrated management of spacecraft according to claim 1 and control system, it is characterised in that：Institute
Multifunction structure unit (1) is stated with 2 road light current interfaces, respectively temperature signal output interface and acceleration signal output connects
Mouthful, they are connected with data processing unit (3) using weak-current cable.
3. the in-orbit multifunction structure integrated management of spacecraft according to claim 1 and 2 and control system, its feature exist
In：By position adjacent 2 can charge/discharge source module connected, obtain the power supply of two groups of identical output voltages, be referred to as
Main part power supply and backup battery；Main part power supply and backup battery respectively have 1 tunnel charge and discharge electrical interface, and charge and discharge electrical interface is forceful electric power
Interface, main part power supply and backup battery are each via its charge and discharge electrical interface using forceful electric power cable and PMU (2)
It is connected.
4. the in-orbit multifunction structure integrated management of spacecraft according to claim 3 and control system, it is characterised in that：Institute
PMU (2) is stated including charging regulator module, electric discharge adjustor module, conditioning circuit module and auxiliary source circuit,
With charge control, control of discharge, the switching of active/standby part power supply and voltage/current detection conditioning functions；For multifunction structure list
First (1) in orbit when charge/discharge management, and using the detection modulate circuit being internally integrated, assist discharge load unit
(4) unit for electrical property parameters in orbit of the lithium battery in acquisition multifunction structure unit (1).
5. the in-orbit multifunction structure integrated management of spacecraft according to claim 4 and control system, it is characterised in that：Institute
PMU (2) is stated with 2 tunnel charge and discharge electrical interfaces and 1 road instruction interface, 2 tunnel charge and discharge electrical interfaces are connected respectively to power supply mould
Main part power supply of block and backup battery, 1 instruction interface receive the control instruction that spacecraft sends, PMU (2) control
Discharge load unit (4) processed is discharged to main part power supply or backup battery.
6. the in-orbit multifunction structure integrated management of spacecraft according to claim 1 and control system, it is characterised in that institute
Data processing unit (3) is stated including power module, CPU control modules and data acquisition module, data processing unit (3) collection,
The mechanical performance parameter and voltage, electric current of process and transmission multifunction structure unit (1) period in launching phase and in orbit
Deng unit for electrical property parameters, vibration characteristics, the structural support of checking multifunction structure unit (1) of multifunction structure unit (1) are obtained
Performance and basic electric property energy.
7. the in-orbit multifunction structure integrated management of spacecraft according to claim 1 and control system, it is characterised in that：Institute
State discharge load unit (4) to realize by the way of multichannel heating plate, for consuming the electric energy of multifunction structure unit.
8. the in-orbit multifunction structure integrated management of spacecraft according to claim 1 and control system, it is characterised in that：Institute
State multifunction structure unit (1) and mode is connected by screw in spacecraft deck board, or multifunction structure unit (1) is straight
Connect and use as spacecraft deck board or dividing plate；
The PMU (2) and data processing unit (3) are mounted in spacecraft body cabin；
The discharge load unit (4) is mounted on spacecraft bulkhead or using space flight is arranged on by the way of being spirally connected using thermal conductivity sticker
In device body cabin, and it is connected with PMU (2) by cable.
9. the in-orbit multifunction structure integrated management of spacecraft according to claim 8 and control system, it is characterised in that：
Phase change device is installed on multifunction structure unit (1) bottom surface, between the multifunction structure and phase change device with dielectric film every
From；The dielectric film is made using polyimide material；The phase change device be by by hexadecane filling in metal-back
And make, for carrying out passive thermal control to multifunction structure unit (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610305265.1A CN105955075B (en) | 2016-05-10 | 2016-05-10 | Spacecraft in-orbit multifunctional structure integrated management and control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610305265.1A CN105955075B (en) | 2016-05-10 | 2016-05-10 | Spacecraft in-orbit multifunctional structure integrated management and control system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105955075A CN105955075A (en) | 2016-09-21 |
| CN105955075B true CN105955075B (en) | 2017-03-22 |
Family
ID=56914078
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610305265.1A Active CN105955075B (en) | 2016-05-10 | 2016-05-10 | Spacecraft in-orbit multifunctional structure integrated management and control system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105955075B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106886665B (en) * | 2017-04-06 | 2018-01-19 | 中国人民解放军国防科学技术大学 | Space flight multifunction structure ground simulation demonstration and verification system |
| 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 |
Citations (5)
| 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 |
| 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 |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040261569A1 (en) * | 2003-06-26 | 2004-12-30 | Jacobs Jack H. | Piezodynamic vibration damping system |
| CN102795350B (en) * | 2012-07-06 | 2014-08-13 | 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 |
-
2016
- 2016-05-10 CN CN201610305265.1A patent/CN105955075B/en active Active
Patent Citations (5)
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105955075A (en) | 2016-09-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105947235B (en) | Electric energy and mechanical environment management multifunctional structure | |
| CN103235270B (en) | Reliability testing device for star power system of lunar probe | |
| CN108270230A (en) | A kind of distributed energy storage system | |
| CN202166676U (en) | Novel power battery simulation device | |
| CN105955075B (en) | Spacecraft in-orbit multifunctional structure integrated management and control system | |
| CN104617633A (en) | Intelligent battery, electricity transfer bus system and balanced charging and discharging method | |
| US9831045B2 (en) | Structural supercapacitor usable in a mechanical structure | |
| CN106814332A (en) | A kind of multifunction structure lithium battery interior voltage detecting system | |
| WO2013098923A1 (en) | Cell system | |
| CN104201787A (en) | Mobile energy-storage power plant battery management system based on Calman filtering algorithm | |
| CN205429773U (en) | 270V machine carries high voltage direct current start power | |
| CN105905316B (en) | Multi-functional bulkhead structure for microsatellite system | |
| CN202319955U (en) | Discrete cell management system | |
| CN202582591U (en) | Atmosphere data system automatic detection device | |
| CN106891762B (en) | A kind of accumulator of electric car replaces dead battery method in safeguarding | |
| CN109760819A (en) | A kind of structure battery component of aircraft and aircraft | |
| CN110146319B (en) | Cube-carried structure health monitoring experimental device and method | |
| CN104065250A (en) | Extensible platform of power supply controller | |
| KR20210117854A (en) | Energy storage system for solar generation | |
| CN106799973A (en) | The super charging pile of integrated form | |
| Thangaraj et al. | Energy storage options for wireless sensors powered by aircraft specific thermoelectric energy harvester | |
| CN106654086A (en) | Multifunctional structure battery for aircraft | |
| CN208655720U (en) | A kind of energy storage device | |
| CN109786653A (en) | A kind of function laying of structure battery and structure battery | |
| CN112688004B (en) | Cell type aerospace multifunctional structure lithium battery |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |