CN221262523U - Satellite battery temperature control power supply device - Google Patents

Satellite battery temperature control power supply device Download PDF

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Publication number
CN221262523U
CN221262523U CN202323009037.4U CN202323009037U CN221262523U CN 221262523 U CN221262523 U CN 221262523U CN 202323009037 U CN202323009037 U CN 202323009037U CN 221262523 U CN221262523 U CN 221262523U
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CN
China
Prior art keywords
battery
power supply
temperature control
push rod
temperature
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Active
Application number
CN202323009037.4U
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Chinese (zh)
Inventor
兰利东
尹中开
熊瀛
王治中
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Beijing Zero Heavy Aerospace Technology Co ltd
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Beijing Zero Heavy Aerospace Technology Co ltd
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Priority to CN202323009037.4U priority Critical patent/CN221262523U/en
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  • Battery Mounting, Suspending (AREA)

Abstract

The utility model relates to the field of power supply, and discloses a satellite battery temperature control power supply device, which solves the problems that along with the development of a space satellite, an energy storage battery adopted by the satellite becomes the main stream, the battery device mainly comprises a battery core, a structure fixing piece, a confluence piece and the like, the traditional scheme often lacks of control and prevention of temperature control on the power supply, the state of temperature control in a battery pack is easily ignored, the power supply current is unstable, and the service time is shortened.

Description

Satellite battery temperature control power supply device
Technical Field
The utility model relates to the field of power sources, in particular to a satellite battery temperature control power source device.
Background
The satellite battery temperature control power supply device is a device for controlling and managing the temperature of a satellite battery, and the main function of the satellite battery temperature control power supply device is to monitor and adjust the temperature of the battery, so that the battery can work in a safe and stable temperature range.
Along with the development of space satellite, the energy storage battery that the satellite adopted becomes mainstream, and battery device mainly contains electric core, structure mounting, conflux piece etc. and constitutes, and traditional scheme often lacks to the control of power control by temperature change, ignores the state of the inside control by temperature change of group battery easily, leads to power supply current unstable, and live time shortens.
Disclosure of utility model
The utility model aims to provide a satellite battery temperature control power supply device which is used for working, so that the problems that the traditional scheme often lacks of control and prevention of power supply temperature control, and the state of temperature control in a battery pack is easily ignored, so that the power supply current is unstable and the service time is shortened are solved.
In order to achieve the above purpose, the present utility model provides the following technical solutions: the satellite battery temperature control power supply device comprises a shell, a temperature control support frame arranged on the inner side of the shell, a first hole arranged on the inner side of the temperature control support frame, a battery arranged on the inner side of the first hole, a top plate arranged above the shell, a base arranged below the shell, a temperature control mechanism arranged below the battery, and a limiting mechanism arranged on the inner side of the temperature control support frame;
The temperature control mechanism comprises an insulating plate arranged below the battery, an integrated circuit board is arranged on the left side of the insulating plate, a heating chip is fixedly connected to the front side of the temperature control support frame, a temperature measuring chip is arranged on the right side of the heating chip, and a filler is filled between the first hole and the battery.
Preferably, the integrated circuit board is connected with the heating chip through a wire, and the integrated circuit board is connected with the temperature measuring chip through a wire.
Preferably, the temperature control supporting frame is made of magnesium alloy materials.
Preferably, the stop gear is including setting up the first connecting plate in control by temperature change support frame top, the inside of first connecting plate is provided with the threaded rod, the inner wall intercommunication of first hole has first recess, the inboard of first recess is provided with first push rod, the inboard of first push rod is provided with the second recess, the left end fixedly connected with splint of first push rod, the top inner wall intercommunication of first recess has the second hole, be provided with the second push rod between first connecting plate and the control by temperature change support frame, the right-hand member fixedly connected with spring of first push rod.
Preferably, the threaded rod is rotationally connected with the first connecting plate, the threaded rod is in threaded connection with the temperature control supporting frame, and the outer side face of the first connecting plate is attached to the inner side face of the shell.
Preferably, the left-view appearance structure of the second push rod is trapezoidal, the connection mode of the second push rod and the first connecting plate is fixed connection, and the matching mode of the second push rod and the second groove is clearance fit.
Preferably, the left-view appearance structure of the clamping plate is trapezoidal, and the clamping plate is in clearance fit with the first groove.
1. According to the satellite battery temperature control power supply device, the temperature control mechanism is arranged, so that the temperature measurement chip transmits signals to the integrated circuit board when detecting that the temperature changes, the integrated circuit board starts the heating chip through signal processing to control the temperature, and the filler is filled outside the battery to enable the heat conduction effect to be better.
2. According to the satellite battery temperature control power supply device, the limiting mechanism is arranged, so that the limiting mechanism can be driven to move downwards by rotating, the limiting mechanism is clung to the outer side of the battery, the shaking of the battery is prevented, the filling agent is prevented from being squeezed and broken and not contacting with the battery, the heat conduction effect is reduced, and the purpose of preventing the heat conduction effect from being reduced is achieved.
Drawings
FIG. 1 is a schematic overall perspective view of the present utility model;
FIG. 2 is a schematic view of a front cross-sectional structure of the present utility model;
FIG. 3 is a schematic view of a left-hand cross-sectional structure of the present utility model;
FIG. 4 is a schematic view of the structure of FIG. 3A according to the present utility model;
fig. 5 is a schematic diagram of the structure of fig. 2B according to the present utility model.
In the figure: 1. a housing; 2. a temperature control support frame; 3. a first hole; 4. a battery; 5. a top plate; 6. a base; 7. a temperature control mechanism; 8. a limiting mechanism; 701. an insulating plate; 702. an integrated circuit board; 703. heating the chip; 704. a temperature measuring chip; 705. a filler; 801. a first connection plate; 802. a threaded rod; 803. a first groove; 804. a first push rod; 805. a second groove; 806. a clamping plate; 807. a second hole; 808. a second push rod; 809. and (3) a spring.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Referring to fig. 1-5, the present utility model provides the following technical solutions: the satellite battery temperature control power supply device comprises a shell 1, a temperature control support frame 2 arranged on the inner side of the shell 1, a first hole 3 arranged on the inner side of the temperature control support frame 2, a battery 4 arranged on the inner side of the first hole 3, a top plate 5 arranged above the shell 1, a base 6 arranged below the shell 1, a temperature control mechanism 7 arranged below the battery 4, and a limit mechanism 8 arranged on the inner side of the temperature control support frame 2;
The temperature control mechanism 7 comprises an insulating plate 701 arranged below the battery 4, an integrated circuit board 702 is arranged on the left side of the insulating plate 701, the temperature control support frame 2 is made of magnesium alloy materials, the heat conduction effect is better, a heating chip 703 is fixedly connected to the front side of the temperature control support frame 2, the integrated circuit board 702 is connected with the heating chip 703 through a wire, the integrated circuit board 702 is connected with a temperature measuring chip 704 through a wire, signals can be transmitted, the temperature measuring chip 704 is arranged on the right side of the heating chip 703, and a filler 705 is filled between the first hole 3 and the battery 4.
The limiting mechanism 8 comprises a first connecting plate 801 arranged above the temperature control supporting frame 2, a threaded rod 802 is arranged in the first connecting plate 801, the threaded rod 802 is in threaded connection with the temperature control supporting frame 2, the outer side face of the first connecting plate 801 is attached to the inner side face of the shell 1, the threaded rod 802 can drive the first connecting plate 801 to move up and down, the inner wall of the first hole 3 is communicated with a first groove 803, a first push rod 804 is arranged on the inner side of the first groove 803, a second groove 805 is arranged on the inner side of the first push rod 804, a clamping plate 806 is fixedly connected to the left end of the first push rod 804, a second hole 807 is communicated to the inner wall of the upper side of the first groove 803, a second push rod 808 is arranged between the first connecting plate 801 and the temperature control supporting frame 2, a spring 809 is fixedly connected to the right end of the first push rod 804, the shape of the left-view appearance structure of the second push rod 808 is trapezoid, the second push rod 808 is fixedly connected with the inner side face of the first connecting plate 801, the second push rod 808 is matched with the second groove 805 is in a clearance fit with the second groove 805, the second groove 803 is matched with the battery 803 in the clearance fit to the middle of the groove 803, and the battery 803 is matched with the first groove 803 in the clearance fit to the clearance, and the battery 803 is matched with the groove 803 in the clearance, and the battery 803 is matched with the groove is in the clearance groove 803 is matched with the groove 803, and the groove is matched with the shape with the battery 803 is 4.
When the temperature needs to be controlled, the temperature measuring chip 704 detects that the temperature changes and transmits signals to the integrated circuit board 702, the integrated circuit board 702 starts the signal processing on the heating chip 703 to control the temperature, the filler 705 is filled at the outer side of the battery 4 to enable the heat conduction effect to be better, and compared with the prior art, the temperature of the battery 4 can be controlled, so that the purposes of preventing unstable power supply current and shortening the service time are achieved.
When the battery 4 is placed into the inner side of the first hole 3, the threaded rod 802 is rotated to drive the first connecting plate 801 to move downwards, and then the second push rod 808 is driven to move downwards, so that the second push rod 808 passes through the inner side of the second hole 807, the first push rod 804 is pushed to move towards the center direction of the battery 4, the inner side surface of the clamping plate 806 is tightly attached to the outer side surface of the battery 4, the shaking of the battery 4 is prevented, the filling agent 705 is prevented from being squeezed to be broken and not contacted with the battery 4, the heat conduction effect is reduced, and the aim of preventing the heat conduction effect from being reduced is fulfilled.
It is noted that in this document, relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Although embodiments of the present utility model have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.

Claims (7)

1. The utility model provides a satellite battery control by temperature change power supply unit, including shell (1), set up at the inboard control by temperature change support frame (2) of shell (1), set up at the inboard first hole (3) of control by temperature change support frame (2), set up battery (4) of first hole (3) inboard, set up roof (5) in shell (1) top, set up base (6) in shell (1) below, its characterized in that: a temperature control mechanism (7) is arranged below the battery (4), and a limiting mechanism (8) is arranged on the inner side of the temperature control support frame (2);
The temperature control mechanism (7) comprises an insulating plate (701) arranged below the battery (4), an integrated circuit board (702) is arranged on the left side of the insulating plate (701), a heating chip (703) is fixedly connected to the front side of the temperature control support frame (2), a temperature measuring chip (704) is arranged on the right side of the heating chip (703), and a filler (705) is filled between the first hole (3) and the battery (4).
2. The satellite battery temperature controlled power supply device of claim 1, wherein: the integrated circuit board (702) is connected with the heating chip (703) through a wire, and the integrated circuit board (702) is connected with the temperature measuring chip (704) through a wire.
3. The satellite battery temperature controlled power supply device of claim 1, wherein: the temperature control supporting frame (2) is made of magnesium alloy materials.
4. The satellite battery temperature controlled power supply device of claim 1, wherein: stop gear (8) is including setting up first connecting plate (801) in control by temperature change support frame (2) top, the inside of first connecting plate (801) is provided with threaded rod (802), the inner wall intercommunication of first hole (3) has first recess (803), the inboard of first recess (803) is provided with first push rod (804), the inboard of first push rod (804) is provided with second recess (805), the left end fixedly connected with splint (806) of first push rod (804), the top inner wall intercommunication of first recess (803) has second hole (807), be provided with second push rod (808) between first connecting plate (801) and the control by temperature change support frame (2), the right-hand member fixedly connected with spring (809) of first push rod (804).
5. The satellite battery temperature controlled power supply apparatus of claim 4, wherein: the threaded rod (802) is rotationally connected with the first connecting plate (801), the threaded rod (802) is in threaded connection with the temperature control support frame (2), and the outer side face of the first connecting plate (801) is attached to the inner side face of the shell (1).
6. The satellite battery temperature controlled power supply apparatus of claim 4, wherein: the left-view appearance structure of the second push rod (808) is trapezoid, the connection mode of the second push rod (808) and the first connecting plate (801) is fixed connection, and the matching mode of the second push rod (808) and the second groove (805) is clearance fit.
7. The satellite battery temperature controlled power supply apparatus of claim 4, wherein: the left-view appearance structure of the clamping plate (806) is trapezoid, and the clamping plate (806) is in clearance fit with the first groove (803).
CN202323009037.4U 2023-11-08 2023-11-08 Satellite battery temperature control power supply device Active CN221262523U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202323009037.4U CN221262523U (en) 2023-11-08 2023-11-08 Satellite battery temperature control power supply device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202323009037.4U CN221262523U (en) 2023-11-08 2023-11-08 Satellite battery temperature control power supply device

Publications (1)

Publication Number Publication Date
CN221262523U true CN221262523U (en) 2024-07-02

Family

ID=91630601

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202323009037.4U Active CN221262523U (en) 2023-11-08 2023-11-08 Satellite battery temperature control power supply device

Country Status (1)

Country Link
CN (1) CN221262523U (en)

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