WO2017193228A1 - 电能与力学环境管理多功能结构 - Google Patents

电能与力学环境管理多功能结构 Download PDF

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Publication number
WO2017193228A1
WO2017193228A1 PCT/CN2016/000380 CN2016000380W WO2017193228A1 WO 2017193228 A1 WO2017193228 A1 WO 2017193228A1 CN 2016000380 W CN2016000380 W CN 2016000380W WO 2017193228 A1 WO2017193228 A1 WO 2017193228A1
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WO
WIPO (PCT)
Prior art keywords
frame
power module
elastic
module
lower cover
Prior art date
Application number
PCT/CN2016/000380
Other languages
English (en)
French (fr)
Inventor
李东旭
尹昌平
吴军
李德湛
Original Assignee
国防科学技术大学
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 国防科学技术大学 filed Critical 国防科学技术大学
Priority to EP16901184.8A priority Critical patent/EP3330188B1/en
Publication of WO2017193228A1 publication Critical patent/WO2017193228A1/zh
Priority to US15/855,426 priority patent/US10882641B2/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/425—Power storage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/223—Modular spacecraft systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/228—Damping of high-frequency vibration effects on spacecraft elements, e.g. by using acoustic vibration dampers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
    • B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F7/00—Vibration-dampers; Shock-absorbers
    • F16F7/10—Vibration-dampers; Shock-absorbers using inertia effect
    • F16F7/104—Vibration-dampers; Shock-absorbers using inertia effect the inertia member being resiliently mounted
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M10/00—Secondary cells; Manufacture thereof
    • H01M10/05—Accumulators with non-aqueous electrolyte
    • H01M10/052—Li-accumulators
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M50/00—Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
    • H01M50/20—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders
    • H01M50/271—Lids or covers for the racks or secondary casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
    • F16F15/022—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using dampers and springs in combination
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M10/00—Secondary cells; Manufacture thereof
    • H01M10/42—Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
    • H01M10/48—Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
    • H01M10/482—Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte for several batteries or cells simultaneously or sequentially
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M10/00—Secondary cells; Manufacture thereof
    • H01M10/42—Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
    • H01M10/48—Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
    • H01M10/486—Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte for measuring temperature
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M2220/00—Batteries for particular applications
    • H01M2220/20—Batteries in motive systems, e.g. vehicle, ship, plane
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02E60/10—Energy storage using batteries

Definitions

  • the invention belongs to the multi-disciplinary cross-technology field of materials, mechanics and energy, and particularly relates to a multifunctional structure of electric energy and mechanical environment management.
  • the present invention provides a multi-functional structure for managing electrical energy and mechanical environment, which can effectively solve the above problems.
  • the invention provides a multifunctional structure for electric energy and mechanical environment management, comprising a main structure module, four chargeable/discharge power modules, a vibration damping system and a set of sensor modules;
  • the main structural module comprises a frame (10), an upper cover (11) and a lower cover (12); wherein the overall shape of the frame (10) is in a field configuration with four square cavities.
  • the frame (10) has omnidirectional symmetry about three axes of x, y and z;
  • the lower cover (12) is fixed to the bottom surface of the frame (10);
  • the upper cover (11) is fixed to a top surface of the frame (10);
  • the frame (10), the upper cover (11) and the lower cover (12) constitute a main bearing structure, and has a structure carrying function;
  • the power module includes four power modules I (20), a power module II (21), a power module III (22), and a power module IV (23); each of the power modules is embedded by elastic support. Buried The utility model is disposed in the closed square cavity formed by the frame (10), the upper cover plate (11) and the lower cover plate (12), and only one power supply module is installed in each square cavity; wherein The elastic support comprises an elastic block (30) and an elastic pad (31); in addition, the positive and negative wires of the power module are led out by a strong electric cable and connected to a strong electric connector disposed on the outer side wall of the frame (10) (24) forming a charging and discharging interface; the power module has the functions of multiple charging and multiple discharging, and has the function of consuming vibration energy as a vibrator;
  • an elastic block (30) is disposed between each of the power module and a square cavity wall for accommodating the power module; a bottom surface of each of the power modules and the lower cover (12)
  • An elastic pad (31) is disposed between each of the top surface of the power module and the upper cover (11); an elastic pad (31); the power module and the elastic block (30)
  • the elastic pad (31) constitutes a vibration damping system, corresponding to a "spring-vibrator" model, wherein the elastic block (30) and the elastic pad (31) correspond to elastic support having a certain rigidity and damping
  • the power module is equivalent to a vibrator having a certain mass, and the vibration damping system absorbs energy by deformation of the elastic support on the one hand, and consumes vibration by converting the structural vibration energy into vibrator kinetic energy by the power module as the vibrator. Energy, the combined effect of the two reduces the transmission of vibration in the multi-functional structure and effectively manages the mechanical environment of the power module;
  • the sensor module includes a plurality of temperature sensors and a plurality of acceleration sensors; wherein the temperature sensor is disposed on a cavity and an outer sidewall of the power module for monitoring a temperature of the power module; the acceleration sensor is disposed at An inner wall of the frame (10), an inner wall of the upper cover (11), and an inner wall of the lower cover (12) for measuring the frame (10), the upper cover (11), and The vibration of the lower cover (12) provides a means of detecting and monitoring the internal electrical energy and vibration management of the multifunctional structure.
  • the frame (10) is assembled by two types of hollow square tubes, which are respectively eight borders (10-1) located around and four keels (10-2) at the center;
  • the four keels (10-2) form a cross structure through a cross-shaped joint
  • the eight borders (10-1) are named as the frame I to the frame VIII, respectively, and each of the two frames is first formed into an L-shaped structure through an L-shaped joint, thereby obtaining four L-shaped structures;
  • the four L-shaped structures and the cross structure composed of four keels are combined by a T-joint to form a symmetrical field-shaped frame.
  • the keel (10-2) and the frame (10-1) are all made of carbon fiber composite material, and the layering method is [ ⁇ 45/0/ ⁇ 45] 2S ;
  • the cross-shaped joint, the L-shaped joint and the T-shaped joint are made of a titanium alloy material having a high specific strength and a low thermal expansion coefficient; and the frame is used between the frame (10-1) and the keel (10-2). Adhesive bonding.
  • an L-shaped corner piece (10-3) is bonded with a structural adhesive, and the corner piece (10-3) is made of a polyimide insulating material. It is used to strengthen the joint of the frame (10) and has insulation effect;
  • An insulating sheet (10-4) is bonded to the mounting portion of the acceleration sensor, and the insulating sheet is also made of a polyimide insulating material to insulate the acceleration sensor from the main structural module.
  • the upper cover plate (11) and the lower cover plate (12) are in the form of a sandwich structure composed of an upper skin/core panel/lower skin;
  • the sandwich structure form refers to: an upper skin (11-1), a sandwich panel (11-2), and a lower skin (11-3) in order from top to bottom;
  • the skin (11-1) and the sandwich panel (11-2) are connected by an adhesive, and the thickness of the adhesive layer is controlled in the range of 0.1 mm to 0.2 mm;
  • the sandwich panel (11-2) is connected by an adhesive, and the thickness of the adhesive layer is controlled in a range of 0.1 mm to 0.2 mm;
  • the sandwich panel (11-2) is in the form of a rib mesh, and the upper skin (11-1) and the lower skin (11-3) are both in the form of a panel, and the upper Mongolian
  • the structure and material of the skin (11-1) and the lower skin (11-3) are identical;
  • the upper skin (11-1), the sandwich panel (11-2), and the lower skin (11-3) are both made of a carbon fiber composite material, and the upper skin (11) -1) and the lower skin (11-3) layering method is [0/ ⁇ 45/90/ ⁇ 45] S ; the sandwich panel (11-2) is layered [0/ ⁇ 45/90/0] 2S .
  • the upper cover plate (11) and the lower cover plate (12) are designed with a plurality of regularly arranged circular vent holes for use as a discharge passage for the internal gas of the structure in a process and a vacuum environment;
  • the lower cover (12) is fixed to the bottom surface of the frame (10) by gluing; the upper cover (11) is screwed to the top surface of the frame (10) by screws.
  • the screw mounting holes are located at the four corners, the center position of the frame (10), and the frame and the keel; the screws are made of a titanium alloy material having a small thermal expansion coefficient, and are suitable for a working environment with large temperature difference and severe change.
  • the elastic block (30) and the elastic pad (31) are made of a material made of a polymer elastic material vinyl terminated polydimethylsiloxane, and the chemical molecular structure of the material.
  • a material made of a polymer elastic material vinyl terminated polydimethylsiloxane vinyl terminated polydimethylsiloxane, and the chemical molecular structure of the material.
  • the elastic block (30) and the elastic pad (31) have the functions of structurally supporting the power module, and can also dissipate a part of the vibration energy through self-elastic deformation, and have the function of protecting the power module, and also have the function of
  • the power module is insulated from the main structural module and functions to dissipate heat from the power module.
  • the elastic block (30) and the elastic pad (31) are installed in a pre-pressing manner, and an elastic force is generated by pre-compression to realize elastic constraint support of the power module;
  • the elastic block (30) has a rectangular parallelepiped shape. The two ends are respectively in contact with the inner side of the frame (10) and the outer side of the power module in a surface contact manner, and there is no fixed relationship;
  • the elastic pad (31) has a well-shaped configuration, and one side passes through the adhesive and the upper cover.
  • a structural adhesive is used to bond the limit block (32) for limiting the elastic block (30). Bit so that it does not move and misplace.
  • the power module can adopt a lithium battery
  • a plurality of voltage detecting lines are also drawn inside the power module, and are soldered to the electrical connectors (33) mounted on the outer sidewall of the frame (10) to form a detecting interface for detecting the voltage signal of each power module grading. ;
  • the upper surface of the upper cover plate (11) and the lower surface of the lower cover plate (12) are polished to make the carbon fiber surface of the entire multifunctional structure have electrical conductivity consistency;
  • An annular copper foil (50) is laid on the upper surface of the upper cover (11); a bottom copper foil (51) is laid on the lower surface of the lower cover (12), and the bottom copper foil (51) is a plurality of copper foils of a certain width are spliced to form an integral conductive surface; a U-shaped copper foil (52) is evenly laid on the outer side wall of the frame (10), and the U-shaped copper foil (52) and the upper portion
  • the annular copper foil (50) on the cover plate (11) and the bottom copper foil (51) on the lower cover plate (12) are overlapped to make the electrical energy uniform with the electrical conductivity of the mechanical environment management multifunctional structure;
  • a grounding pile (53) is further mounted on each of the four corners of the annular copper foil (50). One end of the grounding pile (53) is connected to the ground of the power module, and the other end is connected to the external ground through the ground.
  • the pile (53) allows the multifunctional structure to be effectively grounded as a whole.
  • the present invention integrates the power module into the structure by elastic restraint, so that the structure realizes multi-functional heights such as bearing, power supply, vibration reduction, etc., and the structure adopts various lightweight materials such as carbon fiber composite materials.
  • the material and the hollow frame structure effectively reduce the weight of the structure; at the same time, the space occupied by the original power source is saved, and the space available for the payload is increased.
  • the present invention substantially increases the load/mass ratio, load/volume ratio, and function/structural ratio of the system platform.
  • the invention adopts the vibration-damping design considerations such as elastic support, so that it can smoothly pass the harsh vibration mechanical environment assessment of the rocket ascending section to meet the requirements of aerospace applications; at the same time, through material selection, vent structure design and the like, It can withstand environmental assessments such as thermal vacuum and thermal cycling, and adapt to the space vacuum working environment.
  • FIG. 1 is a schematic exploded view of a multi-function structure of electrical energy and mechanical environment management provided by the present invention
  • Figure 2 is a front elevational view of the frame provided by the present invention.
  • Figure 3 is a perspective view of a frame provided by the present invention.
  • FIG. 4 is a schematic structural view of an L-shaped joint provided by the present invention.
  • Figure 5 is a schematic structural view of a cross-shaped joint provided by the present invention.
  • FIG. 6 is a schematic structural view of a T-joint provided by the present invention.
  • Figure 7 is a partial enlarged view of the F area of Figure 3;
  • Figure 8 is a schematic exploded view of the upper cover or the lower cover provided by the present invention at an angle
  • Figure 9 is a schematic exploded view of the upper cover or the lower cover provided by the present invention at another angle;
  • Figure 10 is a schematic structural view of an elastic pad provided by the present invention.
  • Figure 11 is a front elevational view showing the assembled state of the power module according to the present invention.
  • Figure 12 is a perspective view showing the assembled state of the power module according to the present invention.
  • Figure 13 is a front elevational view showing the assembled state of the elastic block provided by the present invention.
  • Figure 14 is a perspective view showing the assembled state of the elastic block provided by the present invention.
  • Figure 15 is a partial enlarged view of the area B in Figure 14;
  • FIG. 17 is a schematic diagram of a mounting position of a temperature sensor and an acceleration sensor provided by the present invention. wherein, WDC represents a temperature sensor; JSDC represents an acceleration sensor;
  • Figure 18 is a top plan view of the multifunctional structure of electrical energy and mechanical environment management provided by the present invention.
  • Figure 19 is a front elevational view of the multi-function structure of the electrical energy and mechanical environment management provided by the present invention.
  • 20 is an overall perspective view of a multifunction structure of electrical energy and mechanical environment management provided by the present invention.
  • Figure 21 is a schematic view of the multi-functional structure provided by the present invention as a spacecraft bulkhead
  • Figure 22 is an acceleration output response diagram of the X-direction of the multi-function structure of the electrical energy and mechanical environment management
  • Figure 23 is an acceleration output response diagram of the Y-direction of the multi-function structure of electrical energy and mechanical environment management.
  • the present invention proposes a multi-functionality of electrical energy and mechanical environment management integrating load carrying, vibration damping, power storage and measurement functions. structure.
  • the power and mechanical environment management multifunctional structure includes a main structural module, four chargeable/discharge power modules, a vibration damping system and a set of sensor modules, which can withstand frequencies. It is a broadband random vibration with a range of 0 to 2000 Hz, a total rms acceleration of 28 g, and an impact load of up to 1600 g, and an acceleration load of 10 g.
  • the main structural module includes a frame 10, an upper cover 11 and a lower cover 12.
  • the lower cover 12 is fixed to the bottom surface of the frame 10.
  • the lower cover 12 is fixed to the bottom surface of the frame 10 by gluing;
  • the upper cover 11 is fixed to the top surface of the frame 10.
  • the upper cover 11 is passed through the screw. It is fixed to the top surface of the frame 10 by screw connection.
  • the screw mounting holes are located at the four corners of the frame 10, the center position, and the frame and the keel.
  • the screws are made of titanium alloy material with small thermal expansion coefficient, which is suitable for large temperature difference and severe change. Work environment.
  • the frame 10, the upper cover 11 and the lower cover 12 constitute a main bearing structure and have a structure carrying function.
  • the overall shape of the frame 10 is in a field configuration with four square cavities, and the frame 10 has an x, The omnidirectional symmetry of the three axes of y and z, wherein the definition of the coordinate system o-xyz is as shown in Figures 2 and 3, the x-axis and the y-axis are in the plane of the frame 10, and the z-axis is perpendicular to the o-xy plane and The right-hand coordinate system is formed with the x-axis and the y-axis.
  • the frame 10 is assembled by two types of hollow square tubes, which are respectively eight borders 10-1 located around and four keels 10-2 at the center; the four keels 10-2 form a cross structure through a cross joint;
  • the root frame 10-1 is named as the frame I to the frame VIII, respectively, and each of the two frames is first formed into an L-shaped structure through an L-shaped joint, thereby obtaining four L-shaped structures; and the four L-shaped structures are composed of four keels
  • the cross structure is combined by a T-joint to form a symmetrical field-shaped frame.
  • the keel 10-2 and the frame 10-1 are made of carbon fiber composite material, and the layering method is [ ⁇ 45/0/ ⁇ 45] 2S ; cross type joint, L type joint and T type The joint is made of titanium alloy material with high specific strength and low thermal expansion coefficient; it is bonded with the frame 10-1 and the keel 10-2 with an adhesive.
  • an L-shaped corner piece 10-3 is also bonded with a structural adhesive, and the corner piece 10-3 is made of a polyimide insulating material for reinforcing the assembly joint of the frame 10 while With insulation.
  • the upper cover 11 and the lower cover 12 are both in the form of a sandwich structure composed of an upper skin/core panel/lower skin;
  • the sandwich structure form refers to: in top-down order, including upper skin 11-1, sandwich panel 11-2 and lower skin 11-3; upper skin 11-1 and sandwich panel 11 -2 is connected by adhesive, and the thickness of the adhesive layer is controlled in the range of 0.1 mm to 0.2 mm; the lower skin 11-3 and the sandwich panel 11-2 are connected by an adhesive, and the adhesive is preferably J47. a film, thereby controlling the thickness of the adhesive layer in a range of 0.1 mm to 0.2 mm;
  • the sandwich panel 11-2 is in the form of a rib grid, and the upper skin 11-1 and the lower skin 11-3 are in the form of a panel, and the upper skin 11-1 and the lower skin 11-3
  • the structural dimensions and materials are identical;
  • the upper skin 11-1, the sandwich panel 11-2 and the lower skin 11-3 are all made of a carbon fiber composite material, and the upper skin 11-1 and the lower skin 11-3 are layered [0]. / ⁇ 45/90/ ⁇ 45] S ; the layering pattern of the sandwich panel 11-2 is [0/ ⁇ 45/90/0] 2S .
  • the upper cover 11 and the lower cover 12 are designed with a plurality of regularly arranged circular vent holes for use as a discharge passage for the internal gas of the structure in a process and a vacuum environment.
  • the power module includes four, and the power module can adopt a lithium battery, and more preferably a solid lithium battery; the four power modules are respectively recorded as a power module I20, a power module II21, a power module III22, and a power module IV23; each power module passes
  • the elastic support is embedded in the closed square cavity formed by the frame 10, the upper cover 11 and the lower cover 12, and only one power module is installed in each square cavity; wherein, the elastic The support comprises an elastic block 30 and an elastic pad 31; in addition, the positive and negative wires of the power module are led out through a strong electric cable, and connected to the high-voltage electrical connector 24 disposed on the outer side wall of the frame 10 to form a charging and discharging interface;
  • the function of multiple charging and multiple discharging has the function of acting as a vibrator to consume vibration energy.
  • a plurality of voltage detecting lines are also drawn inside the power module and soldered to the electrical connectors 33 mounted on the outer side walls of the frame 10 to form a detecting interface for detecting the voltage signal of each power module.
  • the power module can be further connected to an external power management unit, which can realize constant current charging/discharging or constant voltage charging/discharging, and at the same time, the charging/discharging speed can be controlled, thereby effectively realizing the management of electric energy.
  • an elastic block 30 is disposed between the periphery of each power module and the wall of the check box for accommodating the power module; an elastic pad 31 is disposed between the bottom surface of each power module and the lower cover 12, and each An elastic pad 31 is also disposed between the bottom surface of the power module and the upper cover 11; the power module, the elastic block 30 and the elastic pad 31 constitute a vibration damping system, which is equivalent to a "spring-vibrator" model, wherein the elastic block 30 and the elastic pad 31 corresponds to an elastic support with a certain stiffness and damping; the power module is equivalent to a vibrator with a certain quality.
  • the vibration damping system absorbs energy through the deformation of the elastic support, and on the other hand, the vibration energy is converted into the vibration energy of the vibrator by the power module as the vibrator, and the combined effect of the two reduces the vibration.
  • the material used for the elastic block 30 and the elastic pad 31 is a material made of a polymer elastic material vinyl terminated polydimethylsiloxane, and the chemical molecular structure of the material is:
  • the elastic block 30 and the elastic pad 31 not only have the function of supporting the power module, but also can dissipate a part of the vibration energy through self-elastic deformation, and have the function of protecting the power module, and also have electricity.
  • the elastic block 30 has a rectangular parallelepiped shape, and its two ends are respectively in surface contact with the inner side surface of the frame 10 and the outer side surface of the power module, and there is no fixed relationship;
  • the elastic pad 31 has a well-shaped configuration, and one side passes through the adhesive and the upper side.
  • the lower surface of the cover plate 11 and the upper surface of the lower cover 12 are bonded together, and the other surface is only in surface contact with the surface of the power module, and there is no fixed relationship; the elastic block 30 and the elastic after installation
  • the pads 31 are all in a pre-compression state and have a structural support function to enable the power module in the stationary state to maintain a position determination inside the frame 10.
  • a structural adhesive is used to bond the limit block 32 for limiting the elastic block 30.
  • the sensor module includes a plurality of temperature sensors and a plurality of acceleration sensors; wherein the temperature sensors are disposed on the inner and outer sidewalls of the power module for monitoring the temperature of the power module; the acceleration sensor is disposed on the inner wall of the frame 10, the upper cover 11 and The inner wall and the inner wall of the lower cover 12 are used for measuring the vibration of the frame 10, the upper cover 11 and the lower cover 12, and provide detection and monitoring means for the internal electric energy and vibration management of the multifunctional structure.
  • annular copper foil 50 is laid on the upper surface of the upper cover 11, and the four corners of the annular copper foil are also connected to a grounding post 53, one end of the grounding post 53 and the ground of the power module. Connected, the other end is connected to the external ground, such as the system structure of the spacecraft; the bottom surface of the lower cover 12 is covered with the bottom copper foil 51; and the outer side wall of the frame 10 is evenly laid with the U-shaped copper foil 52.
  • the U-shaped copper foil 52 is overlapped with the annular copper foil 50 and the underlying copper foil 51.
  • the present invention integrates the power module into the structure by elastic restraint, so that the structure realizes multi-functional heights such as bearing, power supply, vibration reduction, etc., and the structure adopts various lightweight materials such as carbon fiber composite materials.
  • the material and the hollow frame structure effectively reduce the weight of the structure; at the same time, the space occupied by the original power source is saved, and the space available for the payload is increased.
  • the present invention substantially increases the load/mass ratio, load/volume ratio, and function/structural ratio of the system platform.
  • the invention adopts the vibration-damping design considerations such as elastic support, so that it can smoothly pass the harsh vibration mechanical environment assessment of the rocket ascending section to meet the needs of aerospace applications; at the same time, through material selection and arrangement
  • the design of the pore structure is considered to enable it to withstand environmental assessments such as thermal vacuum and thermal cycling, and to adapt to the space vacuum working environment.
  • the utility model provides a multi-functional structure for electric energy and mechanical environment management, and has various functions such as bearing, vibration damping, power supply, electric storage, data measurement, etc., and is used on a certain type of spacecraft, and has the capability of impact vibration resistance.
  • the multi-function structure will be specifically described below in conjunction with the assembly process flow.
  • Step 1 the frame is assembled.
  • the overall shape and structural composition of the frame are shown in Figures 2 and 3.
  • the frame is assembled by hollow square tube made of M40J/TDE-86 carbon fiber composite material.
  • the outer section of the square tube is 30mm ⁇ 25mm and the wall thickness is 2.5mm.
  • the specific lamination method is shown in Table 1 below. According to the structure, the square tubes that make up the frame can be divided into two categories: the border around and the keel at the center.
  • the frame and the keel are bonded by applying a structural adhesive (J133) to the joint to obtain a frame.
  • J133 structural adhesive
  • the specific combination sequence is as follows: a total of four keels, first through the "ten” type joints to form a "ten” word structure; and a total of eight borders, named as border I ⁇ border VIII, first pass each two through "L "The joints form four "L”-shaped structures, and the four "L”-shaped structures are combined with the "T"-shaped structure composed of four keels through a "T"-type joint to form a symmetrical "field".
  • the font frame has an outer envelope size of 800 mm ⁇ 800 mm ⁇ 25 mm.
  • the three shape joints used are shown in Figures 4-6.
  • a structural adhesive (J133) is also used to bond the "L"-shaped corner pieces at the corners of the frame, a total of eight, and a thickness of 1 mm, as shown in FIG.
  • the upper and lower covers are made.
  • the upper cover and the lower cover are made of the same material, structural size and layup. Their outer envelope dimensions are 800mm ⁇ 800mm ⁇ 5mm, using the "upper skin / sandwich panel / lower skin” sandwich structure, in which the upper and lower skin thickness is 0.96mm
  • the sandwich panel structure is in the form of a composite rib with a thickness of 3 mm, as shown in FIGS. 8 and 9.
  • the upper skin/core panel/lower skin is joined by gluing.
  • J47 film is used as the adhesive.
  • the material system, the thickness of each layer and the lamination method of the upper/lower cover are shown in Table 2 below.
  • a circular vent hole arranged regularly is formed on the surface.
  • the lower cover is bonded to the frame.
  • the lower cover is bonded to the frame in the first step to form a unitary structure.
  • the lower cover is glued to the elastic pad.
  • the elastic pad is made of K216 silicone rubber material, and its structural appearance is in a "well" configuration, as shown in Figure 10.
  • the material system, structural dimensions and performance parameters of the elastic mat are shown in Table 3.
  • Step 5 the power module is installed.
  • the multi-function structure includes a total of four power modules, which are respectively recorded as power modules I, II, III, and IV.
  • two power modules adjacent to each other are connected in series to obtain two sets of power sources of the same output voltage, which are respectively called a primary power source and a backup power source. It is not difficult to know that different numbers of power modules (for example, three or four) can be combined in series to obtain DC voltages of different sizes.
  • the outer envelope size of the power module is 300mm ⁇ 280mm ⁇ 20mm, and the overall shape is shown in Figure 11 and Figure 12. Then, the four power modules are installed in the four square cavities formed by the "Tian" type frame and the cover plate, and the lower bottom surface of the power module is in surface contact with the elastic pad.
  • the overall schematic diagram of the four power modules installed on the frame is shown in Figure 12.
  • the positive and negative wires of the main/backup power supply are slotted from the side and connected to a 5-core high-voltage electrical connector through the C55/0812-18 cable (this embodiment is selected by Airbon, and the model specification is MM-2F2-005-P13-2200-ZLP 5-core high-voltage electrical connector), the strong electric connector is placed on the outer side wall of the frame to form the charging/discharging interface of the main/backup power supply.
  • a set of voltage detection lines is also drawn inside the power module for detecting the voltage signal of each power module.
  • the voltage detection line is connected by a cable and soldered to a 15-core electrical connector (this embodiment uses a 15-core electrical connector manufactured by Guizhou Aerospace Electric Co., Ltd., model number J30JHT15TJSAN01), and the electrical connector is also mounted on the outer wall of the frame. .
  • Step 6 the elastic block is installed.
  • the elastic block is made of K216 silicone rubber material like the elastic pad.
  • the elastic block has a rectangular parallelepiped configuration, and its structure is shown in FIG. 13 and FIG. 14, and the material system, structural size and performance parameters are shown in Table 4.
  • the four sides of the power module are connected by surface contact between the elastic block and the frame.
  • the limit The block is made of T300/E648 fiber fabric laminate paving material and has a size of 10mm ⁇ 5mm ⁇ 2mm for limiting the elastic block.
  • the elastic block After installation, the elastic block is pre-stressed and the power module cannot move inside the frame.
  • the power module is connected to the main bearing structure through an elastic block and an elastic pad to form a vibration damping system.
  • the damping module has two functions: managing the mechanical environment of the internal power module to protect the power module; at the same time, dissipating the vibration energy through the deformation of the elastic material to reduce the transmission of vibration in the structure.
  • the vibration damping principle is as shown in Fig. 16.
  • the power module in the present invention corresponds to the damping element in the figure, that is, the vibrator having the mass m 2
  • the elastic support corresponds to the spring having the stiffness k and the damping coefficient c. Damper.
  • m 1 represents the mass of the entire electrical energy and mechanical management multi-function structure
  • ⁇ represents the natural angular frequency of vibration
  • the mass m 2 of the damping element and the stiffness k of the elastic support are appropriately selected such that k- ⁇ 2 m 2 ⁇ 0, then the vibration of the structure x 1 ⁇ 0, x 2 ⁇ 0, ie the vibration will be borne by the damping element The vibration is attenuated by the damping characteristics of the damping element.
  • Step 7 the sensor is bonded.
  • the sensor includes a temperature sensor and an acceleration sensor for obtaining internal temperature and acceleration signals of the structure, and their specific mounting positions are as shown in FIG. There are 8 temperature sensors and 8 acceleration sensors, the models of which are shown in Table 5.
  • the temperature sensors are numbered WDC01 to WDC08, and the temperature sensors numbered WDC01, WDC03, WDC05, and WDC07 are bonded to the side wall of the outer surface of the power module, and the temperature sensors are numbered WDC02, WDC04, WDC06, and WDC08. Bonded to the inner cavity of the power module.
  • the sensor is connected to the outside through an electrical connector.
  • the head of the temperature sensor is fixed by using GD414 type silicone rubber.
  • the lead of the temperature sensor is taken out from the side of the power module and then goes to the upper surface of the power module, and is connected to a 9-core weak electric power as a detection interface through the C55/0114-26 wire.
  • Connector Guizhou Aerospace Electrician, model J30JH).
  • the accelerometers are numbered JSDC01 ⁇ JSDC08 in the figure.
  • the installation position is located on the inner side wall of the frame and the inner surface of the cover.
  • the acceleration sensor numbered JSDC01 is mounted on the inner side wall of the frame V
  • the acceleration sensor numbered JSDC02 is mounted on the inner side wall of the frame IV
  • the acceleration sensor numbered JSDC03 is mounted on the upper surface of the lower cover plate.
  • the acceleration sensor numbered JSDC04 Mounted on the lower surface of the upper cover, the acceleration sensor numbered JSDC05 is mounted on the inner side wall of the frame I, the acceleration sensor numbered JSDC06 is mounted on the inner side wall of the frame VIII, and the acceleration sensor numbered JSDC07 is mounted on the inner side wall of the frame IV.
  • the acceleration sensor numbered JSDC08 is mounted on the inner side wall of the frame VIII.
  • the upper cover is glued to the elastic pad.
  • the J133 structural adhesive is also used to bond the upper cover and the elastic pad together to form a unitary structure.
  • Step 9 the upper cover is installed.
  • the elastic pad is also pre-pressed, and the power module cannot move inside the frame.
  • step 10 the conductive copper foil and the grounding post are installed.
  • the upper surface of the upper cover and the lower surface of the lower cover are polished; then, the annular copper foil is laid on the upper surface of the upper cover (see FIG. 18), laying the bottom copper foil on the entire lower surface of the lower cover (in this embodiment, the bottom copper foil is formed by splicing a plurality of copper foils of 50 mm width to form an integral conductive surface, see FIG. 19), and in the frame
  • the U-shaped copper foil is uniformly laid on the side wall, and the U-shaped copper foil is overlapped with the annular copper foil and the underlying copper foil (see Fig. 20).
  • the four corners of the annular copper foil are finally connected to a grounding pile (see Figure 20).
  • One end of the grounding pile is connected to the ground of the power module, and the other end is connected to the spacecraft system. Structurally connected.
  • the multi-function structure of electric energy and mechanical environment management of the invention can be used as a structure with a bearing function, which can directly replace the original spacecraft deck and can also be used as a bearing board structure in a spacecraft cabin.
  • the present invention directly replaces one of the original decks of a spacecraft, and a schematic view thereof is shown in FIG.
  • an acceleration response test was conducted under ground conditions.
  • the frame of the present invention was struck by a hammer at point A in the X-axis direction and point B in the Y-axis direction, respectively, and a response signal of the acceleration sensor was acquired by a test computer.
  • the acceleration signals of the acceleration sensor 1 (JSDC01) and 5 (JSDC05) are obtained as shown in FIG. 22 when tapping in the X direction, and the accelerations of the acceleration sensors 2 (JSDC02) and 6 (JSDC06) are obtained when tapping in the Y direction.
  • the signal is shown in Figure 23. As can be seen from FIG. 22 and FIG.
  • the signal peak value of the acceleration sensor 1 is significantly larger than the signal peak value of the acceleration sensor 5
  • the signal peak value of the acceleration sensor 2 is significantly larger than the signal peak value of the acceleration sensor 6, so that it can be concluded that the tapping is generated.
  • the vibration is significantly attenuated after passing through the multi-function structure.
  • the multi-functional structure of electric energy and mechanical environment management provided by the present invention is a structure integrating load bearing, vibration damping, power storage, measurement and the like, and can realize lightweight structure and small volume. Demand.

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Abstract

公开了一种电能与力学环境管理多功能结构，其包括主结构模块、四个可充/放电源模块、减振系统以及传感器模块；主结构模块包括框架（10）、上盖板（11）和下盖板（12）；每个电源模块的四周与用于容纳该电源模块的方格空腔壁之间、每个电源模块的底面与下盖板（12）、以及每个电源模块的顶面与上盖板（11）之间分别设置有弹性垫（31）。该结构通过将电源模块以弹性约束的方式嵌入结构内部实现了承载、供电、减振等多功能高度融为一体以及大幅提高了系统平台的载荷/质量比、载荷/体积比及功能/结构比。

Description

电能与力学环境管理多功能结构
本申请要求以下中国专利申请的优先权：
于2016年05月10日提交中国专利局，申请号为201610307086.1，发明名称为“电能与力学环境管理多功能结构”的中国专利申请，其全部内容通过引用结合在本申请中。
技术领域
本发明属于材料、力学、能源等多学科交叉技术领域，具体涉及一种电能与力学环境管理多功能结构。
背景技术
对于现代航天器结构，急需发展多功能结构技术，把电、热、推进、减振、防护等独立功能单元与结构平台有机融合在一起，以实现结构、功能、电能、材料等的一体化成型，从而消除传统结构大量冗余的重量和体积，实现结构质量的轻量化以及体积的小型化，提高系统平台的载荷/质量比、功能/结构比等，降低研制成本、延长航天器寿命，并增加航天器能力。然而截止目前，尚未见到相关的文献资料报道。
发明内容
针对现有技术的不足，本发明提供一种电能与力学环境管理多功能结构，可有效解决上述问题。
本发明采用的技术方案如下：
本发明提供一种电能与力学环境管理多功能结构，包括一个主结构模块、四个可充/放电源模块、一套减振系统以及一套传感器模块；
所述主结构模块包括框架(10)、上盖板(11)和下盖板(12)；其中，所述框架(10)的整体外形呈田字构型，具有四个方格空腔，所述框架(10)具有关于x、y和z三轴的全方位对称性；所述下盖板(12)固定于所述框架(10)的底面；所述上盖板(11)固定于所述框架(10)的顶面；所述框架(10)、所述上盖板(11)和所述下盖板(12)组成主承力结构，具有结构承载的功能；
所述电源模块包括4个，分别记为电源模块Ⅰ(20)、电源模块Ⅱ(21)、电源模块Ⅲ(22)和电源模块Ⅳ(23)；每个所述电源模块通过弹性支撑以嵌埋方 式设置于框架(10)、上盖板(11)和下盖板(12)所形成的封闭方格空腔内，并且，每个方格空腔内唯一安装1个所述电源模块；其中，弹性支撑包括弹性块(30)和弹性垫(31)；此外，电源模块的正、负极线通过强电电缆引出，连接到设置于所述框架(10)的外侧壁的强电电连接器(24)上形成充放电接口；所述电源模块既具有多次充电与多次放电的功能，又具有充当振子消耗振动能量的功能；
另外，每个所述电源模块的四周与用于容纳该电源模块的方格空腔壁之间设置有弹性块(30)；每个所述电源模块的底面与所述下盖板(12)之间设置有弹性垫(31)，每个所述电源模块的顶面与所述上盖板(11)之间也设置有弹性垫(31)；所述电源模块、所述弹性块(30)和所述弹性垫(31)构成减振系统，相当于“弹簧-振子”模型，其中，所述弹性块(30)和所述弹性垫(31)相当于具有一定刚度和阻尼的弹性支撑；所述电源模块相当于具有一定质量的振子，该减振系统一方面通过弹性支撑的变形吸振耗能，另一方面由作为振子的电源模块将结构振动能量转化为振子动能的方式来消耗振动能量，二者综合作用的结果降低了振动在多功能结构中的传递，并有效管理电源模块的力学环境；
所述传感器模块包括若干个温度传感器和若干个加速度传感器；其中，所述温度传感器设置于所述电源模块的内腔和外侧壁，用于监测所述电源模块的温度；所述加速度传感器设置于所述框架(10)的内壁、所述上盖板(11)的内壁和所述下盖板(12)的内壁，用于测量所述框架(10)、所述上盖板(11)和所述下盖板(12)的振动情况，为多功能结构内部电能与振动管理提供了检测与监控手段。
优选的，所述框架(10)采用两类空心方管连接装配而成，分别是位于四周的八根边框(10-1)和处于中心的四根龙骨(10-2)；
四根龙骨(10-2)通过十字型接头组成十字结构；
八根边框(10-1)分别命名为边框Ⅰ～边框Ⅷ，先将每两根边框通过L型接头组成L型结构，由此得到四个L型结构；
将四个L型结构与由四根龙骨构成的十字结构通过T型接头组合形成一个具有对称性的田字型框架。
优选的，所述龙骨(10-2)和所述边框(10-1)均采用碳纤维复合材料铺层而成，铺层方式为[±45/0/±45]2S；
所述十字型接头、所述L型接头和所述T型接头采用高比强度、低热膨胀系数的钛合金材料制成；其与边框(10-1)、龙骨(10-2)之间采用胶粘剂进行粘接。
优选的，在所述框架(10)的各转角处还采用结构胶粘剂粘接有L型的角片(10-3)，角片(10-3)由聚酰亚胺绝缘材料制作而成，用于对框架(10)装配连接处进行加强，同时具有绝缘作用；
在所述加速度传感器的安装处粘接有绝缘片(10-4)，该绝缘片也由聚酰亚胺绝缘材料制成，能够使加速度传感器与主结构模块之间绝缘。
优选的，所述上盖板(11)和所述下盖板(12)均采用上蒙皮/夹芯格板/下蒙皮构成的夹芯结构形式；
所述夹芯结构形式是指：按自上而下顺序，依次包括上蒙皮(11-1)、夹芯格板(11-2)和下蒙皮(11-3)；所述上蒙皮(11-1)和所述夹芯格板(11-2)之间采用胶粘剂进行连接，控制粘接胶层的厚度在0.1mm～0.2mm的范围；所述下蒙皮(11-3)和所述夹芯格板(11-2)之间采用胶粘剂进行连接，控制粘接胶层的厚度在0.1mm～0.2mm的范围；
其中，夹芯格板(11-2)为筋条网格形式，所述上蒙皮(11-1)和所述下蒙皮(11-3)均为面板形式，并且，所述上蒙皮(11-1)和所述下蒙皮(11-3)的结构尺寸和材料完全相同；
另外，所述上蒙皮(11-1)、所述夹芯格板(11-2)和所述下蒙皮(11-3)均采用碳纤维复合材料制成，所述上蒙皮(11-1)和所述下蒙皮(11-3)铺层方式为[0/±45/90/±45]S；所述夹芯格板(11-2)的铺层方式为[0/±45/90/0]2S。
优选的，所述上盖板(11)和所述下盖板(12)设计有多个规则排列的圆形排气孔，用作工艺过程和真空环境下结构内部气体的排出通道；
另外，所述下盖板(12)通过胶粘方式固定于所述框架(10)的底面；所述上盖板(11)通过螺钉以螺纹连接方式固定于所述框架(10)的顶面，螺钉安装孔位于所述框架(10)的四个角点、中心位置以及边框和龙骨上；螺钉采用热膨胀系数小的钛合金材料制作，适用于温差大且变化剧烈的工作环境。
优选的，所述弹性块(30)和所述弹性垫(31)所采用的材料为由高分子弹性材料乙烯基封端聚二甲基硅氧烷制成的材料，该材料的化学分子结构式为：
Figure PCTCN2016000380-appb-000001
所述弹性块(30)和所述弹性垫(31)既具有结构支撑电源模块的功能，还可通过自身弹性变形达到耗散一部分振动能量的作用，具有保护电源模块的功能，同时还具有使电源模块与主结构模块绝缘及为电源模块散热的功能。
优选的，所述弹性块(30)和弹性垫(31)以预压方式进行安装，通过预压缩产生弹性力来实现对电源模块的弹性约束支撑；所述弹性块(30)呈长方体形状，其两端分别与框架(10)的内侧面和电源模块的外侧面以面接触方式相接，不存在固接关系；所述弹性垫(31)呈井字构型，一面通过胶粘剂与上盖板(11)的下表面和下盖板(12)的上表面粘接在一起，而另一面仅以面接触方式与电源模块的表面相接，也不存在固接关系；安装好后的弹性块(30)和弹性垫(31)均处于预压紧状态，具有结构支撑作用，可使得静止状态下的电源模块在框架(10)内部保持位置确定。
优选的，在框架(10)的内侧，在每个弹性块(30)两侧根部界限处的位置，均采用结构胶粘剂粘接有限位块(32)，用于对弹性块(30)进行限位，使其不发生移动和错位。
优选的，所述电源模块可采用锂电池；
和/或
在所述电源模块的内部还引出若干电压检测线，并焊接到安装于框架(10)外侧壁的电连接器(33)上，形成一个用于检测每个电源模块分级的电压信号的检测接口；
和/或
所述上盖板(11)的上表面和下盖板(12)的下表面均进行了打磨处理，使整个多功能结构的碳纤维表面具有导电一致性；
在所述上盖板(11)的上表面铺贴有环形铜箔(50)；在下盖板(12)的下表面整面铺贴底层铜箔(51)，该底层铜箔(51)由若干一定宽度的铜箔拼接而成，形成一个整体导电面；在所述框架(10)的外侧壁均匀铺贴有U形铜箔(52)，该U形铜箔(52)与所述上盖板(11)上的环形铜箔(50)和下盖板(12)上的底层铜箔(51)进行搭接，使整个电能与力学环境管理多功能结构的导电性一致；
所述环形铜箔(50)的四个角还各安装了一个接地桩(53)，该接地桩(53)的一端与电源模块的地线相连，另一端与外部地相连接，通过该接地桩(53)使得该多功能结构整体有效接地。
本发明提供的电能与力学环境管理多功能结构具有以下优点：
(1)本发明通过将电源模块以弹性约束的方式嵌入结构内部，使该结构实现了承载、供电、减振等多功能高度融为一体，且结构中采用了碳纤维复合材料等多种轻质材料及空心框架结构，有效减轻了结构重量；同时由于省出了原有电源所占空间，增大了有效载荷可利用空间。因此，本发明大幅提高了系统平台的载荷/质量比、载荷/体积比及功能/结构比。
(2)本发明通过采用弹性支撑等减振设计考虑，使之能够顺利通过火箭上升段严酷的振动力学环境考核，满足航天应用的需求；同时，通过材料选择、排气孔结构设计等考虑，使之能够经受热真空、热循环等环境考核，适应太空真空工作环境。
附图说明
图1为本发明提供的电能与力学环境管理多功能结构的分解状态示意图；
图2为本发明提供的框架的正视图；
图3为本发明提供的框架的立体图；
图4为本发明提供的L型接头的结构示意图；
图5为本发明提供的十字型接头的结构示意图；
图6为本发明提供的T型接头的结构示意图；
图7为图3中F区域的局部放大图；
图8为本发明提供的上盖板或下盖板在一个角度下的分解状态示意图；
图9为本发明提供的上盖板或下盖板在另一个角度下的分解状态示意图；
图10为本发明提供的弹性垫的结构示意图；
图11为本发明提供的电源模块的装配状态正视图；
图12为本发明提供的电源模块的装配状态立体图；
图13为本发明提供的弹性块的装配状态正视图；
图14为本发明提供的弹性块的装配状态立体图；
图15为图14中B区域的局部放大图；
图16为本发明提供的等效减振模型示意图；
图17为本发明提供的温度传感器和加速度传感器的安装位置示意图；其中，WDC代表温度传感器；JSDC代表加速度传感器；
图18为本发明提供的电能与力学环境管理多功能结构的顶面正视图；
图19为本发明提供的电能与力学环境管理多功能结构的底面正视图；
图20为本发明提供的电能与力学环境管理多功能结构的整体立体图；
图21为本发明提供的多功能结构作为航天器舱壁的示意图；
图22为电能与力学环境管理多功能结构的X方向的加速度输出响应图；
图23为电能与力学环境管理多功能结构的Y方向的加速度输出响应图。
具体实施方式
为了使本发明所解决的技术问题、技术方案及有益效果更加清楚明白，以下结合附图及实施例，对本发明进行进一步详细说明。应当理解，此处所描述的具体实施例仅用以解释本发明，并不用于限定本发明。
针对结构轻量化与体积小型化的需求，同时兼顾结构减振及充/放电要求，本发明提出了一种集承载、减振、供蓄电与测量功能于一体的电能与力学环境管理多功能结构。
结合图1-图23，本发明提供的电能与力学环境管理多功能结构，包括包括一个主结构模块、四个可充/放电源模块、一套减振系统以及一套传感器模块，可承受频率为0～2000Hz范围、总均方根加速度达28g的宽频带随机振动和高达1600g的冲击载荷，以及10g大小的加速度载荷。
以下对各部分详细介绍：
(一)主结构模块
主结构模块包括框架10、上盖板11和下盖板12。下盖板12固定于框架10的底面，优选的，下盖板12通过胶粘方式固定于框架10的底面；上盖板11固定于框架10的顶面，优选的，上盖板11通过螺钉以螺纹连接方式固定于框架10的顶面，螺钉安装孔位于框架10的四个角点、中心位置以及边框和龙骨上；螺钉采用热膨胀系数小的钛合金材料制作，适用于温差大且变化剧烈的工作环境。框架10、上盖板11和下盖板12组成主承力结构，具有结构承载的功能。
(1)框架
框架10的整体外形呈田字构型，具有四个方格空腔，框架10具有关于x、 y和z三轴的全方位对称性，其中，坐标系o-xyz的定义如图2和图3所示，x轴和y轴位于框架10所在平面内，z轴垂直于o-xy平面并与x轴、y轴构成右手坐标系。
框架10采用两类空心方管连接装配而成，分别是位于四周的八根边框10-1和处于中心的四根龙骨10-2；四根龙骨10-2通过十字型接头组成十字结构；八根边框10-1分别命名为边框Ⅰ～边框Ⅷ，先将每两根边框通过L型接头组成L型结构，由此得到四个L型结构；将四个L型结构与由四根龙骨构成的十字结构通过T型接头组合形成一个具有对称性的田字型框架。
另外，龙骨10-2和边框10-1两类方管均采用碳纤维复合材料铺层而成，铺层方式为[±45/0/±45]2S；十字型接头、L型接头和T型接头采用高比强度、低热膨胀系数的钛合金材料制成；其与边框10-1、龙骨10-2之间采用胶粘剂进行粘接。
在框架10的8个转角处还采用结构胶粘剂粘接有L型的角片10-3，角片10-3由聚酰亚胺绝缘材料制作，用于对框架10装配连接处进行加强，同时具有绝缘作用。
(2)上/下盖板
上盖板11和下盖板12均采用上蒙皮/夹芯格板/下蒙皮构成的夹芯结构形式；
夹芯结构形式是指：按自上而下顺序，依次包括上蒙皮11-1、夹芯格板11-2和下蒙皮11-3；上蒙皮11-1和夹芯格板11-2之间采用胶粘剂进行连接，控制粘接胶层的厚度在0.1mm～0.2mm的范围；下蒙皮11-3和夹芯格板11-2之间采用胶粘剂进行连接，胶粘剂优选为J47胶膜，从而控制粘接胶层的厚度在0.1mm～0.2mm的范围；
其中，夹芯格板11-2为筋条网格形式，上蒙皮11-1和下蒙皮11-3均为面板形式，并且，上蒙皮11-1和下蒙皮11-3的结构尺寸和材料完全相同；
另外，上蒙皮11-1、夹芯格板11-2和下蒙皮11-3均采用碳纤维复合材料制成，上蒙皮11-1和下蒙皮11-3铺层方式为[0/±45/90/±45]S；夹芯格板11-2的铺层方式为[0/±45/90/0]2S。
上盖板11和下盖板12设计有多个规则排列的圆形排气孔，用作工艺过程和真空环境下结构内部气体的排出通道。
(二)可充/放电源模块
电源模块包括4个，电源模块可采用锂电池，更优选可采用固态锂电池；将4个电源模块分别记为电源模块Ⅰ20、电源模块Ⅱ21、电源模块Ⅲ22和电源模块Ⅳ23；每个电源模块通过弹性支撑以嵌埋的方式设置于框架10、上盖板11和下盖板12所形成的封闭方格空腔内，并且，每个方格空腔内唯一安装1个电源模块；其中，弹性支撑包括弹性块30和弹性垫31；此外，电源模块的正、负极线通过强电电缆引出，连接到设置于框架10的外侧壁的强电电连接器24上形成充放电接口；电源模块既具有多次充电与多次放电的功能，又具有充当振子消耗振动能量的功能。
在电源模块内部还引出若干电压检测线，并焊接到安装于框架10外侧壁的电连接器33上，形成一个用于检测每个电源模块分级的电压信号的检测接口。
电源模块还可以进一步连接外置的电源管理单元，可以实现恒流充/放电或恒压充/放电，同时充/放电速度可控，从而有效实现对电能的管理。
(三)减振系统
另外，每个电源模块的四周与用于容纳该电源模块的方格空腔壁之间设置有弹性块30；每个电源模块的底面与下盖板12之间设置有弹性垫31，每个电源模块的底面与上盖板11之间也设置有弹性垫31；电源模块、弹性块30和弹性垫31构成减振系统，相当于“弹簧-振子”模型，其中，弹性块30和弹性垫31相当于具有一定刚度和阻尼的弹性支撑；电源模块相当于具有一定质量的振子。该减振系统一方面通过弹性支撑的变形吸振耗能，另一方面由作为振子的电源模块将结构振动能量转化为振子动能的方式来消耗振动能量，二者综合作用的结果降低了振动在多功能结构中的传递，并有效管理电源模块的力学环境。
弹性块30和弹性垫31所采用的材料为由高分子弹性材料乙烯基封端聚二甲基硅氧烷制成的材料，该材料的化学分子结构式为：
Figure PCTCN2016000380-appb-000002
弹性块30和弹性垫31既具有结构支撑电源模块的功能，还可通过自身弹性变形达到耗散一部分振动能量的作用，具有保护电源模块的功能，同时还具有电 源模块绝缘与散热的功能。
弹性块30呈长方体形状，其两端分别与框架10的内侧面和电源模块的外侧面以面接触方式相接，不存在固接关系；弹性垫31呈井字构型，一面通过胶粘剂与上盖板11的下表面和下盖板12的上表面粘接在一起，而另一面仅以面接触方式与电源模块的表面相接，不存在固接关系；安装好后的弹性块30和弹性垫31均处于预压紧状态，具有结构支撑作用，可使得静止状态下的电源模块在框架10内部保持位置确定。
在框架10的内侧，在每个弹性块30两侧根部界限处的位置，均采用结构胶粘剂粘接有限位块32，用于对弹性块30进行限位。
(四)传感器模块
传感器模块包括若干个温度传感器和若干个加速度传感器；其中，温度传感器设置于电源模块的内腔和外侧壁，用于监测电源模块的温度；加速度传感器设置于框架10的内壁、上盖板11和内壁和下盖板12的内壁，用于测量框架10、上盖板11和下盖板12的振动情况，为多功能结构内部电能与振动管理提供了检测与监控手段。
此外，本发明中，在上盖板11的上表面铺贴有环形铜箔50，环形铜箔的四个角还各连接到一个接地桩53，该接地桩53的一端与电源模块的地线相连，另一端与外部地，例如航天器的系统结构地相连接；在下盖板12的下表面整面铺贴有底层铜箔51；在框架10的外侧壁均匀铺贴有U形铜箔52，该U形铜箔52与环形铜箔50和底层铜箔51进行搭接。
通过采用上述技术方案，形成了一种集承载、减振、供蓄电、测量等功能于一体的电能与力学环境管理多功能结构。
本发明的创新点如下：
(1)本发明通过将电源模块以弹性约束的方式嵌入结构内部，使该结构实现了承载、供电、减振等多功能高度融为一体，且结构中采用了碳纤维复合材料等多种轻质材料及空心框架结构，有效减轻了结构重量；同时由于省出了原有电源所占空间，增大了有效载荷可利用空间。因此，本发明大幅提高了系统平台的载荷/质量比、载荷/体积比及功能/结构比。
(2)本发明通过采用弹性支撑等减振设计考虑，使之能够顺利通过火箭上升段严酷的振动力学环境考核，满足航天应用的需求；同时，通过材料选择、排 气孔结构设计等考虑，使之能够经受热真空、热循环等环境考核，适应太空真空工作环境。
本发明提供的电能与力学环境管理多功能结构，具有承载、减振、供电、蓄电、数据测量等多种功能，用于某型号航天器上，具有抗冲击振动能力。
下面结合装配的工艺流程，对该多功能结构进行具体描述。
第1步，框架装配。
框架的整体外形及结构组成如图2和图3所示。框架采用由M40J/TDE-86碳纤维复合材料铺层制成的空心方管连接装配而成，方管外截面尺寸为30mm×25mm，壁厚为2.5mm，具体铺层方式如下表1所示。按结构形式，组成框架的方管可以分为两类，分别是：位于四周的边框和处于中心的龙骨。
边框、龙骨通过在接头上涂覆结构胶粘剂(J133)粘接而得到框架。具体组合顺序如下：龙骨共计四根，先通过“十”字型接头组成一个“十”字结构；而边框共计有八根，分别命名为边框Ⅰ～边框Ⅷ，先将每两根通过“L”型接头组成四个“L”型结构，再将这四个“L”型结构与由四根龙骨构成的“十”字结构通过“T”型接头组合形成一个具有对称性的“田”字型框架，其外缘包络尺寸为800mm×800mm×25mm。所用的三种形状接头分别如图4-图6所示。
为了对框架装配连接处进行加强，在框架各转角处用结构胶粘剂(J133)还粘接有“L”型的角片，共计8个，厚度为1mm，如图7所示。
表1框架材料体系及铺层方式
Figure PCTCN2016000380-appb-000003
第2步，上、下盖板制作。
上盖板和下盖板的制作材料、结构尺寸及铺层方式完全相同。它们的外缘包络尺寸均为800mm×800mm×5mm，采用“上蒙皮/夹芯格板/下蒙皮”构成的夹芯结构形式，其中上蒙皮和下蒙皮厚度均为0.96mm，夹芯格板结构为复合材料筋条形式，厚度为3mm，如图8和图9所示。上蒙皮/夹芯格板/下蒙皮通过胶粘方式进行连接，为严格控制粘接胶层的厚度(保持在0.1mm～0.2mm的范围)，采用了J47胶膜作为粘接剂。上/下盖板具体采用的材料体系、各层厚度及铺层方式如下表2所示。
表2上/下盖板的材料体系及铺层方式
Figure PCTCN2016000380-appb-000004
上、下盖板制作完成后，在表面打出规则排列的圆形排气孔。
第3步，下盖板与框架粘接。
采用J133结构胶粘剂，将下盖板与第1步中的框架粘接在一起，形成一体结构。
第4步，下盖板与弹性垫胶接。
弹性垫采用K216硅橡胶材料制成，其结构外观呈“井”字构型，如图10所示。弹性垫的材料体系、结构尺寸及性能参数如表3所示。
表3弹性垫的相关参数
Figure PCTCN2016000380-appb-000005
采用J133胶粘剂，将4个弹性垫依次粘接在下盖板上。
第5步，电源模块安装。
该多功能结构共包含有4个电源模块，分别记为电源模块Ⅰ、Ⅱ、Ⅲ、Ⅳ。为确保可靠性，本实施例中，将位置相邻的2个电源模块进行串联，得到两组相同输出电压的电源，分别称为主份电源和备份电源。不难知道，也可以将不同数量的电源模块(例如3个或4个)进行串联组合，从而得到不同大小输出的直流电压。
电源模块的外缘包络尺寸为300mm×280mm×20mm，整体外形如图11和图12所示。然后，将四个电源模块安装于“田”字型框架与盖板所形成的四个方格空腔内，电源模块的下底面与弹性垫以面接触方式进行相接。在框架上安装后的四个电源模块总体示意图如图12所示。
主/备份电源的正极线、负极线从其侧面开槽引出，且通过C55/0812-18电缆分别连接到一个5芯的强电电连接器上(本实施例选用Airbon公司生产、型号规格为MM-2F2-005-P13-2200-ZLP的5芯强电电连接器)，强电电连接器设置在框架的外侧壁上，形成主/备份电源的充放电接口。
在电源模块内部还引出了一组电压检测线，用于检测每个电源模块分级的电压信号。电压检测线通过电缆连接后焊接在一个15芯电连接器上(本实施例选用贵州航天电器公司生产、型号规格为J30JHT15TJSAN01的15芯电连接器)，电连接器同样安装于框架的外侧壁上。
第6步，弹性块安装。
弹性块与弹性垫一样，也采用K216硅橡胶材料制成。弹性块呈长方体构型，其结构如图13和图14所示，而材料体系、结构尺寸及性能参数如表4所示。
表4弹性块的相关参数
组件 材料体系 硬度/A 外形尺寸/mm 厚度/mm
弹性块 K216硅橡胶 35～40 矩形，39×40 24
电源模块的四个侧面均通过弹性块与与框架之间以面接触方式相接，对于每根框架的边框或龙骨，均采用三个并列的弹性块进行连接，共计有3×4×4＝48个，弹性块与电源模块、框架之间均不存在固定连接关系。
在框架的内侧，对应于弹性块两侧根部界限处的位置(具体位置如图15所 示)，还采用J133结构胶粘剂粘接有96个限位块(每个弹性块根部采用两个限位块，共计2×3×4×4＝96个)，如图15所示，限位块采用T300/E648纤维织物层合铺覆材料制作，尺寸为10mm×5mm×2mm，用于对弹性块进行限位。
安装好后，弹性块处于预压紧状态，电源模块在框架内部不能发生移动。
电源模块通过弹性块、弹性垫与主承力结构相接，构成减振系统。减振模块具有两个作用：管理内部电源模块的力学环境，以保护电源模块；同时通过弹性材料的自身变形耗散振动能量，减少振动在结构中的传递。减振原理如图16所示，本发明中的电源模块相当于该图中的减振元件，即具有质量为m2的振子，而弹性支撑相当于刚度为k的弹簧和阻尼系数为c的阻尼器。
系统的传递特性可表达为下式：
Figure PCTCN2016000380-appb-000006
式中m1表示整个电能与力学管理多功能结构的质量，ω表示振动固有角频率。
那么在外界动载荷f1的激励下，结构的输出为：
Figure PCTCN2016000380-appb-000007
因此，适当地选取减振元件的质量m2以及弹性支撑的刚度k，使k-ω2m2→0，那么结构的振动x1→0，x2≠0，即振动将由减振元件承担，通过减振元件的阻尼特性将振动衰减。
第7步，传感器粘接。
传感器包括温度传感器和加速度传感器，是为了获取结构内部温度和加速度信号，它们的具体安装位置如图17所示。共有8个温度传感器和8个加速度传感器，其型号如表5所示。
表5内部传感器的型号及编号
传感器名称 传感器型号 数量 对应的图中编号
温度传感器 MF501 8 WDC01～WDC08
加速度传感器 PCB352A21 8 JSDC01～JSDC08
温度传感器在图中对应的编号为WDC01～WDC08，编号为WDC01、WDC03、WDC05、WDC07的温度传感器粘接在电源模块外表面的侧壁处，而编号为WDC02、WDC04、WDC06、WDC08的温度传感器粘接在电源模块的内腔。传感器通过电连接器与外部连接。使用GD414型硅橡胶将温度传感器头部进行固定，温度传感器的引线从电源模块侧边引出后走电源模块的上表面，并通过C55/0114-26导线连接到一个作为检测接口的9芯弱电电连接器上(贵州航天电器生产，型号为J30JH)。
加速度传感器在图中对应的编号为JSDC01～JSDC08，安装位置位于框架的内侧壁和盖板的内表面，其中框架内侧壁共计6个，上、下盖板的内表面各有1个，具体位置为：编号为JSDC01的加速度传感器安装在边框Ⅴ的内侧壁，编号为JSDC02的加速度传感器安装在边框Ⅳ的内侧壁，编号为JSDC03的加速度传感器安装在下盖板的上表面，编号为JSDC04的加速度传感器安装在上盖板的下表面，编号为JSDC05的加速度传感器安装在边框Ⅰ的内侧壁，编号为JSDC06的加速度传感器安装在边框Ⅷ的内侧壁，编号为JSDC07的加速度传感器安装在边框Ⅳ的内侧壁，编号为JSDC08的加速度传感器安装在边框Ⅷ的内侧壁。安装时，在结构本体的相应位置上，先用J133胶粘接绝缘片，再将加速度传感器通过J133胶粘接在绝缘片上，以保证安装后的加速度传感器的壳体与多功能减振结构的本体完全绝缘。安装后将加速度传感器引线通过C55/0114-26导线连接到一个9芯的电连接器上(贵州航天电器生产，型号为J30JH)。
第8步，上盖板与弹性垫胶接。
同样采用J133结构胶粘剂，将上盖板与弹性垫粘接在一起，形成一体结构。
第9步，上盖板安装。
在框架的四个角点、中心位置以及边框和龙骨上开设安装螺孔，通过材料为钛合金TC-4R的结构安装螺钉及相应的平垫圈和弹簧垫圈，将上盖板紧固在框架上，这样便形成一个完整的电能与力学环境管理多功能结构，其组装好的整体示意图如图20所示。
上盖板安装后，弹性垫也处于预压紧状态，电源模块在框架内部不能发生移动。
第10步，导电铜箔和接地桩安装。
为使整个多功能结构的碳纤维表面具有导电一致性，对上盖板的上表面和下盖板的下表面均进行了打磨处理；然后，在上盖板上表面铺贴环形铜箔(见图 18)，在下盖板下表面整面铺贴底层铜箔(本实施例中，该底层铜箔由若干50mm宽度的铜箔拼接而成，形成一个整体导电面，见图19)，而在框架侧壁均匀铺贴U形铜箔，该U形铜箔与环形铜箔和底层铜箔进行搭接(见图20)。
为使该多功能结构有效接地，最后将环形铜箔的四个角各连接到一个接地桩(见图20)，该接地桩的一端与电源模块的地线相连，另一端与航天器的系统结构地相连接。
本发明所述电能与力学环境管理多功能结构作为一种具有承载功能的结构，既可以直接取代原有的航天器舱板，也可以作为一种航天器舱内的承力板结构。在本实施例中，将本发明直接取代某航天器原有的一个舱板，其示意图如图21所示。
为进一步验证本发明的减振效果，在地面条件下开展加速度响应测试试验。如图17所示，分别在X轴方向上的A点、Y轴方向上的B点利用力锤敲击本发明的边框，通过测试计算机采集得到加速度传感器的响应信号。在X方向上敲击时得到加速度传感器1(JSDC01)和5(JSDC05)的加速度信号如图22所示；而在Y方向上敲击时得到加速度传感器2(JSDC02)和6(JSDC06)的加速度信号如图23所示。从图22和图23中可以看出，加速度传感器1的信号峰值明显大于加速度传感器5信号峰值，加速度传感器2的信号峰值明显大于加速度传感器6信号峰值，因此可以得出结论，敲击所产生的振动经过该多功能结构的传递后有明显衰减。
综上所述，本发明提供的电能与力学环境管理多功能结构，是一种集承载、减振、供蓄电、测量等功能于一体的结构，可实现结构质量的轻量化以及体积的小型化的需求。
以上所述仅是本发明的优选实施方式，应当指出，对于本技术领域的普通技术人员来说，在不脱离本发明原理的前提下，还可以做出若干改进和润饰，这些改进和润饰也应视本发明的保护范围。

Claims (10)

  1. 一种电能与力学环境管理多功能结构，其特征在于，包括一个主结构模块、四个可充/放电源模块、一套减振系统以及一套传感器模块；
    所述主结构模块包括框架(10)、上盖板(11)和下盖板(12)；其中，所述框架(10)的整体外形呈田字构型，具有四个方格空腔，所述框架(10)具有关于x、y和z三轴的全方位对称性；所述下盖板(12)固定于所述框架(10)的底面；所述上盖板(11)固定于所述框架(10)的顶面；所述框架(10)、所述上盖板(11)和所述下盖板(12)组成主承力结构，具有结构承载的功能；
    所述电源模块包括4个，分别记为电源模块Ⅰ(20)、电源模块Ⅱ(21)、电源模块Ⅲ(22)和电源模块Ⅳ(23)；每个所述电源模块通过弹性支撑以嵌埋方式设置于框架(10)、上盖板(11)和下盖板(12)所形成的封闭方格空腔内，并且，每个方格空腔内唯一安装1个所述电源模块；其中，弹性支撑包括弹性块(30)和弹性垫(31)；此外，电源模块的正、负极线通过强电电缆引出，连接到设置于所述框架(10)的外侧壁的强电电连接器(24)上形成充放电接口；所述电源模块既具有多次充电与多次放电的功能，又具有充当振子消耗振动能量的功能；
    另外，每个所述电源模块的四周与用于容纳该电源模块的方格空腔壁之间设置有弹性块(30)；每个所述电源模块的底面与所述下盖板(12)之间设置有弹性垫(31)，每个所述电源模块的顶面与所述上盖板(11)之间也设置有弹性垫(31)；所述电源模块、所述弹性块(30)和所述弹性垫(31)构成减振系统，相当于“弹簧-振子”模型，其中，所述弹性块(30)和所述弹性垫(31)相当于具有一定刚度和阻尼的弹性支撑；所述电源模块相当于具有一定质量的振子，该减振系统一方面通过弹性支撑的变形吸振耗能，另一方面由作为振子的电源模块将结构振动能量转化为振子动能的方式来消耗振动能量，二者综合作用的结果降低了振动在多功能结构中的传递，并有效管理电源模块的力学环境；
    所述传感器模块包括若干个温度传感器和若干个加速度传感器；其中，所述温度传感器设置于所述电源模块的内腔和外侧壁，用于监测所述电源模块的温度；所述加速度传感器设置于所述框架(10)的内壁、所述上盖板(11)的内壁 和所述下盖板(12)的内壁，用于测量所述框架(10)、所述上盖板(11)和所述下盖板(12)的振动情况，为多功能结构内部电能与振动管理提供了检测与监控手段。
  2. 根据权利要求1所述的电能与力学环境管理多功能结构，其特征在于，所述框架(10)采用两类空心方管连接装配而成，分别是位于四周的八根边框(10-1)和处于中心的四根龙骨(10-2)；
    四根龙骨(10-2)通过十字型接头组成十字结构；
    八根边框(10-1)分别命名为边框Ⅰ～边框Ⅷ，先将每两根边框通过L型接头组成L型结构，由此得到四个L型结构；
    将四个L型结构与由四根龙骨构成的十字结构通过T型接头组合形成一个具有对称性的田字型框架。
  3. 根据权利要求2所述的电能与力学环境管理多功能结构，其特征在于，所述龙骨(10-2)和所述边框(10-1)均采用碳纤维复合材料铺层而成，铺层方式为[±45/0/±45]2S；
    所述十字型接头、所述L型接头和所述T型接头采用高比强度、低热膨胀系数的钛合金材料制成；其与边框(10-1)、龙骨(10-2)之间采用胶粘剂进行粘接。
  4. 根据权利要求2所述的电能与力学环境管理多功能结构，其特征在于，在所述框架(10)的各转角处还采用结构胶粘剂粘接有L型的角片(10-3)，角片(10-3)由聚酰亚胺绝缘材料制作而成，用于对框架(10)装配连接处进行加强，同时具有绝缘作用；
    在所述加速度传感器的安装处粘接有绝缘片(10-4)，该绝缘片也由聚酰亚胺绝缘材料制成，能够使加速度传感器与主结构模块之间绝缘。
  5. 根据权利要求1所述的电能与力学环境管理多功能结构，其特征在于，所述上盖板(11)和所述下盖板(12)均采用上蒙皮/夹芯格板/下蒙皮构成的夹芯结构形式；
    所述夹芯结构形式是指：按自上而下顺序，依次包括上蒙皮(11-1)、夹芯格板(11-2)和下蒙皮(11-3)；所述上蒙皮(11-1)和所述夹芯格板(11-2)之间采用胶粘剂进行连接，控制粘接胶层的厚度在0.1mm～0.2mm的范围；所述下 蒙皮(11-3)和所述夹芯格板(11-2)之间采用胶粘剂进行连接，控制粘接胶层的厚度在0.1mm～0.2mm的范围；
    其中，夹芯格板(11-2)为筋条网格形式，所述上蒙皮(11-1)和所述下蒙皮(11-3)均为面板形式，并且，所述上蒙皮(11-1)和所述下蒙皮(11-3)的结构尺寸和材料完全相同；
    另外，所述上蒙皮(11-1)、所述夹芯格板(11-2)和所述下蒙皮(11-3)均采用碳纤维复合材料制成，所述上蒙皮(11-1)和所述下蒙皮(11-3)铺层方式为[0/±45/90/±45]S；所述夹芯格板(11-2)的铺层方式为[0/±45/90/0]2S。
  6. 根据权利要求1所述的电能与力学环境管理多功能结构，其特征在于，所述上盖板(11)和所述下盖板(12)设计有多个规则排列的圆形排气孔，用作工艺过程和真空环境下结构内部气体的排出通道；
    另外，所述下盖板(12)通过胶粘方式固定于所述框架(10)的底面；所述上盖板(11)通过螺钉以螺纹连接方式固定于所述框架(10)的顶面，螺钉安装孔位于所述框架(10)的四个角点、中心位置以及边框和龙骨上；螺钉采用热膨胀系数小的钛合金材料制作，适用于温差大且变化剧烈的工作环境。
  7. 根据权利要求1所述的电能与力学环境管理多功能结构，其特征在于，所述弹性块(30)和所述弹性垫(31)所采用的材料为由高分子弹性材料乙烯基封端聚二甲基硅氧烷制成的材料，该材料的化学分子结构式为：
    Figure PCTCN2016000380-appb-100001
    所述弹性块(30)和所述弹性垫(31)既具有结构支撑电源模块的功能，还可通过自身弹性变形达到耗散一部分振动能量的作用，具有保护电源模块的功能，同时还具有使电源模块与主结构模块绝缘及为电源模块散热的功能。
  8. 根据权利要求1所述的电能与力学环境管理多功能结构，其特征在于，所述弹性块(30)和弹性垫(31)以预压方式进行安装，通过预压缩产生弹性力来实现对电源模块的弹性约束支撑；所述弹性块(30)呈长方体形状，其两端分别与框架(10)的内侧面和电源模块的外侧面以面接触方式相接，不存在固接关 系；所述弹性垫(31)呈井字构型，一面通过胶粘剂与上盖板(11)的下表面和下盖板(12)的上表面粘接在一起，而另一面仅以面接触方式与电源模块的表面相接，也不存在固接关系；安装好后的弹性块(30)和弹性垫(31)均处于预压紧状态，具有结构支撑作用，可使得静止状态下的电源模块在框架(10)内部保持位置确定。
  9. 根据权利要求1所述的电能与力学环境管理多功能结构，其特征在于，在框架(10)的内侧，在每个弹性块(30)两侧根部界限处的位置，均采用结构胶粘剂粘接有限位块(32)，用于对弹性块(30)进行限位，使其不发生移动和错位。
  10. 根据权利要求1-9任一项所述的电能与力学环境管理多功能结构，其特征在于，所述电源模块可采用锂电池；
    和/或
    在所述电源模块的内部还引出若干电压检测线，并焊接到安装于框架(10)外侧壁的电连接器(33)上，形成一个用于检测每个电源模块分级的电压信号的检测接口；
    和/或
    所述上盖板(11)的上表面和下盖板(12)的下表面均进行了打磨处理，使整个多功能结构的碳纤维表面具有导电一致性；
    在所述上盖板(11)的上表面铺贴有环形铜箔(50)；在下盖板(12)的下表面整面铺贴底层铜箔(51)，该底层铜箔(51)由若干一定宽度的铜箔拼接而成，形成一个整体导电面；在所述框架(10)的外侧壁均匀铺贴有U形铜箔(52)，该U形铜箔(52)与所述上盖板(11)上的环形铜箔(50)和下盖板(12)上的底层铜箔(51)进行搭接，使整个电能与力学环境管理多功能结构的导电性一致；
    所述环形铜箔(50)的四个角还各安装了一个接地桩(53)，该接地桩(53)的一端与电源模块的地线相连，另一端与外部地相连接，通过该接地桩(53)使得该多功能结构整体有效接地。
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