Wireless self-energized power-on system of space equipment and use method of wireless self-energized power-on system

Abstract

The invention provides a wireless self-energized power-on system for space equipment and a use method thereof, and relates to the aerospace power supply control technology, the system comprises an interface module, and a solar charging network, a lithium battery charging network and a load network which are electrically connected with the interface module, the interface module is used for controlling connection states of contacts of all networks according to working conditions; the solar charging network comprises a solar cell and a solar charger which are electrically connected, and an anode contact of the solar charger is led out to the interface module; the lithium battery charging network comprises a lithium battery and a voltameter. Positive and negative electrode contacts of the lithium battery are led out to the interface module. A positive contact of the load network is led to the interface module; and negative electrode nodes of the solar charging network, the lithium battery charging network and the load network are all protected and grounded. The scheme can meet different working condition requirements of space equipment.

Description

Technical Field

[0001] The present invention relates to the field of aerospace power supply control technology, and in particular to a wireless self-powered power-on system for space equipment and a method for using the system. Background Art

[0002] Accelerometers used to measure the flexible parameters of large flexible components in space, such as flexible solar wings and large antennas, are sensitive to impacts, so they need to be powered on during the rocket launch phase. Large flexible equipment often involves space deployment, which makes laying cables for sensors arranged on them complicated and unreliable. Therefore, a wireless self-powered design is ideal.

[0003] In the related technology, traditional self-powered systems often need to charge devices through cables and cannot achieve long-term storage of electrical energy, which makes it difficult for existing wireless self-powered systems to meet complex working conditions.

[0004] Based on this, there is an urgent need for a wireless self-powered power-on system for space equipment and a method of using the system to solve the above-mentioned technical problems. Summary of the invention

[0005] The embodiment of the present invention provides a wireless self-powered power-on system for space equipment and a method of using the system, which can achieve long-term storage of electricity and meet the requirements of various complex working conditions.

[0006] In a first aspect, an embodiment of the present invention provides a wireless self-powered power-on system for space equipment, including an interface module and a solar charging network, a lithium battery charging network and a load network electrically connected to the interface module respectively, wherein:

[0007] The interface module includes a plurality of predefined contacts, and the interface module is used to control the connection status of the contacts of all networks according to working conditions;

[0008] The solar charging network includes electrically connected solar cells and a solar charger, wherein the positive contact of the solar charger is led to an interface module;

[0009] The lithium battery charging network includes a lithium battery and a fuel gauge, wherein the fuel gauge is used to evaluate the power level of the lithium battery and monitor the charge and discharge, and the positive and negative contacts of the lithium battery are both led to the interface module;

[0010] The load network includes an electrically connected secondary power supply and an information processing unit, and the positive contact of the load network is led to the interface module;

[0011] The negative nodes of the solar charging network, the lithium battery charging network and the load network are all protectively grounded.

[0012] In a second aspect, an embodiment of the present invention further provides a method for using a wireless self-powered power-on system for space equipment, including:

[0013] Determining the operating conditions of the space equipment; the operating conditions include ground storage conditions, ground test conditions, and on-orbit operating conditions;

[0014] When the space equipment is in a ground storage condition, the solar charging network, the lithium battery charging network and the load network are disconnected by using the interface module, so that the self-powered system is in a power-off storage state;

[0015] When the space device is in a ground test condition, the solar charging network, the lithium battery charging network and the load network are first connected using the interface module so that each network is in an independent test state;

[0016] When the space device is in an on-orbit operating condition, the solar charging network, the lithium battery charging network and the load network are connected for a second time using the interface module, so that the solar charging network and the lithium battery charging network can be used to self-power the load network.

[0017] The embodiment of the present invention provides a wireless self-powered power-on system for space equipment and a method for using the system. The system includes a solar charging network, a lithium battery charging network, a load network, and an interface module. The three discrete networks lead their respective contacts to the interface module for connection, and then adjust the interface module according to different working conditions to make it in a corresponding connection relationship to meet different mission requirements. The system uses a flexible and configurable power-on interface module to implement a power-on method for different working conditions, meeting various requirements such as long-term storage that requires power off on the ground, independent charging of ground batteries, ground load testing, and power-on in orbit. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0019] Figure 1 is a schematic diagram of a power supply network structure provided by an embodiment of the present invention;

[0020] Figure 2 It is a schematic diagram of an interface module configuration method provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0022] As mentioned above, existing designs often only implement wireless communication, and the power supply is remotely controlled by cable connection. This method is not suitable for the cable-free requirements of space equipment. At the same time, existing designs are also difficult to meet the needs of power outages and long-term storage.

[0023] Based on this, the concept of the present invention is to adopt a power supply network with a flexible and configurable interface module and three groups of independently designed power supply networks to realize a power-on method for different working conditions to meet the needs of practical applications.

[0024] The specific implementation of the above concept is described below.

[0025] Please refer to Figure 1 The embodiment of the present invention provides a wireless self-powered power-on system for space equipment, the system comprising an interface module and a solar charging network, a lithium battery charging network and a load network electrically connected to the interface module respectively, wherein:

[0026] The interface module includes a plurality of predefined contacts, and the interface module is used to control the connection status of the contacts of all networks according to working conditions;

[0027] The solar charging network includes electrically connected solar cells and a solar charger, and the positive contact of the solar charger is led to the interface module;

[0028] The lithium battery charging network includes a lithium battery and a fuel gauge. The fuel gauge is used to evaluate the lithium battery charge and monitor the charge and discharge. The positive and negative contacts of the lithium battery are both connected to the interface module.

[0029] The load network includes an electrically connected secondary power supply and an information processing unit, and the positive contact of the load network is led to the interface module;

[0030] The negative nodes of the solar charging network, lithium battery charging network and load network are all protected by grounding.

[0031] In the embodiment of the present invention, the three discrete networks are connected by leading their respective contacts to the interface module, and then the interface module is adjusted according to different working conditions to be in a corresponding connection relationship to meet different task requirements. The system uses a flexible and configurable power-on interface module to implement power-on methods for different working conditions, meeting various requirements such as long-term storage that requires power off on the ground, independent charging of ground batteries, ground load testing, and power-on in orbit.

[0032] Combine the following Figure 1 and Figure 2 Describe the specific configuration scheme of the interface module under different working conditions.

[0033] In an embodiment of the present invention, the method for realizing flexible power-on is mainly realized by configuring the interface modules. These modules can be connected to the contacts of the device and configure the connection status of the contacts according to the power-on conditions. Based on this, the definition of each contact of the device is shown in Table 1 below.

[0034] Table 1

[0035]

[0036]

[0037] like Figure 1 As shown, it includes three discrete networks, namely solar charging network, lithium battery charging network and load network. The solar cell realizes the photoelectric conversion function, and the charging voltage of 4.2V is realized through the charging chip. The output voltage is connected to the CHARGE+ contact of the interface module. The charging current is not more than 800mA, and its return line is the GND ground plane. When the system is stored on the ground for a long time, the positive and negative charging terminals output by the solar cell and the positive and negative terminals of the lithium-ion battery are disconnected, that is, the other two networks are not charged by default.

[0038] The lithium battery charging network includes lithium batteries and a fuel gauge. The lithium battery leads the positive electrode PACK+ and the negative electrode PACK- to the interface module. The fuel gauge is used to evaluate the power of the lithium battery. In order to monitor the charging and discharging of the lithium battery under self-powered conditions, the BQM+ of the fuel gauge needs to be connected to PACK+, and the BQMGND needs to be connected to PACK-. When the system is stored on the ground for a long time, the fuel gauge and the lithium battery are open-circuited, and the lithium battery is disconnected from the outside, that is, it is not charged and does not supply power to the load, so as to ensure that the lithium battery has sufficient power.

[0039] The load power supply network mainly includes secondary power supply and information processing unit. When the system is stored on the ground for a long time, this part of the network is disconnected, that is, it is not powered by lithium batteries or solar energy.

[0040] In the embodiment of the present invention, when the space equipment is in the on-orbit self-powered working condition, the configuration scheme is that PACK+, CHARGE+, LOAD+, and BQM+ are short-circuited as the positive terminal, and PACK- and BQMGND are short-circuited as the negative terminal. That is to say, the positive contact of the lithium battery, the positive contact of the solar charger, the positive contact of the load, and the positive contact of the power meter are short-circuited through the interface module, and the negative contact of the lithium battery and the negative contact of the power meter are short-circuited through the interface module, so as to use the solar charger to charge the load and the lithium battery, that is, Figure 2 The first configuration is shown in Figure 1.

[0041] In an embodiment of the present invention, when the space equipment is in a ground test condition, for the lithium battery charging network, it is necessary to use an external lithium battery charging dedicated equipment for independent charging, and only PACK+ and PACK- need to be led out. That is to say, the positive contact of the lithium battery is connected to the positive pole of the charging device through the interface module, and the negative contact of the lithium battery is connected to the negative pole of the charging device through the interface module, so as to charge the lithium battery independently.

[0042] For the load network, after the positive pole LOAD+ and negative pole GND of the load are led out to the interface module, an external DC regulated power supply can be used for power supply, that is, the positive pole contact of the load network is connected to the positive pole of the DC regulated power supply through the interface module, and the negative pole contact of the load network is connected to the negative pole of the DC regulated power supply through the interface module, so as to perform independent power supply test on the load network. This configuration state can meet long-term test and calibration work, and does not consume lithium battery power and will not affect the lithium battery charging network. It is safe and reliable.

[0043] For the solar charging network, the positive contact of the solar charging network is connected to the positive pole of the detection equipment through the interface module, and the negative contact of the solar charging network is connected to the negative pole of the detection equipment through the interface module to perform open circuit voltage test and short circuit current test on the solar charging network.

[0044] The above system can realize independent and flexible configuration of the product's internal solar charging network, lithium battery charging network, and load independent power supply network without interfering with each other, which is convenient for ground testing and verification of the product. At the same time, it can realize power-off storage of self-powered products, which is convenient for long-term preservation, and provide space cable-free products with power supply needs that meet various working conditions, which is simple and reliable.

[0045] An embodiment of the present invention provides a method for using a wireless self-powered power-on system for a space device, which is applied to the wireless self-powered power-on system for a space device mentioned in any of the above embodiments, and the method includes:

[0046] Determining the operating conditions of the space equipment; the operating conditions include ground storage conditions, ground test conditions, and on-orbit operating conditions;

[0047] When the space equipment is in a ground storage condition, the solar charging network, the lithium battery charging network and the load network are disconnected by using the interface module, so that the self-powered system is in a power-off storage state;

[0048] When the space device is in a ground test condition, the solar charging network, the lithium battery charging network and the load network are first connected using the interface module so that each network is in an independent test state;

[0049] When the space device is in an on-orbit operating condition, the solar charging network, the lithium battery charging network and the load network are connected for a second time using the interface module, so that the solar charging network and the lithium battery charging network can be used to self-power the load network.

[0050] In an embodiment of the present invention, the first connection includes: using an interface module to connect the positive and negative contacts of a lithium battery to a charging device to independently charge the lithium battery; using an interface module to connect the positive and negative contacts of a load network to a test device to test the load network; using an interface module to connect the positive and negative contacts of a solar charging network to a detection device to perform line detection on the solar charging network.

[0051] In an embodiment of the present invention, the second connection includes: using the interface module to short-circuit the positive contact of the lithium battery, the positive contact of the solar charger, the positive contact of the load and the positive contact of the power meter, and short-circuit the negative contact of the lithium battery and the negative contact of the power meter.

[0052] Specifically, the self-powered process includes the following steps: when the solar charging network receives light, determine whether the load network needs external power supply. If so, provide the charging current generated by the solar charging network to the load network, otherwise provide the charging current to the lithium battery for charging; determine whether the charging current is greater than the current required by the load. If so, transfer the remaining charging current to the lithium battery for charging, otherwise maintain it unchanged to only provide it to the load network; when the solar charging network does not receive light, provide the charging current generated by the lithium battery to the load network.

[0053] It should be noted that, in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the statement "comprise a ..." do not exclude the presence of other identical factors in the process, method, article or device including the elements.

[0054] A person of ordinary skill in the art can understand that all or part of the steps of implementing the above method embodiments can be completed by hardware related to program instructions, and the aforementioned program can be stored in a computer-readable storage medium. When the program is executed, it executes the steps of the above method embodiments; and the aforementioned storage medium includes: ROM, RAM, magnetic disk or optical disk, etc., various media that can store program codes.

[0055] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A wireless self-powered power supply system for space equipment, characterized in that: It includes an interface module and a solar charging network, a lithium battery charging network and a load network electrically connected to the interface module respectively, wherein: The interface module includes a plurality of predefined contacts, and the interface module is used to control the connection status of the contacts of all networks according to working conditions; The solar charging network includes electrically connected solar cells and a solar charger, wherein the positive contact of the solar charger is led to an interface module; The lithium battery charging network includes a lithium battery and a fuel gauge, wherein the fuel gauge is used to evaluate the power of the lithium battery and monitor the charge and discharge, and the positive and negative contacts of the lithium battery are both led to the interface module; The load network includes an electrically connected secondary power supply and an information processing unit, and the positive contact of the load network is led to the interface module; The negative nodes of the solar charging network, the lithium battery charging network and the load network are all protectively grounded.

2. The system according to claim 1, characterized in that When the space equipment is in ground storage condition: The contact points of the solar charging network, the lithium battery charging network and the load network inside the interface module are all open circuited.

3. The system according to claim 1, characterized in that When the space equipment is in an on-orbit self-powered condition: The positive contact of the lithium battery, the positive contact of the solar charger, the positive contact of the load and the positive contact of the fuel gauge are short-circuited through the interface module, and the negative contact of the lithium battery and the negative contact of the fuel gauge are short-circuited through the interface module, so as to use the solar charger to charge the load and the lithium battery.

4. The system according to claim 3, characterized in that The charging current of the solar charger is no more than 800mA.

5. The system according to claim 1, characterized in that When the space equipment is in ground test condition: The positive electrode contact of the lithium battery is connected to the positive electrode of the charging device through the interface module, and the negative electrode contact of the lithium battery is connected to the negative electrode of the charging device through the interface module, so as to charge the lithium battery independently; The positive contact of the load network is connected to the positive electrode of the DC regulated power supply through the interface module, and the negative contact of the load network is connected to the negative electrode of the DC regulated power supply through the interface module, so as to perform an independent power supply test on the load network; The positive contact of the solar charging network is connected to the positive pole of the detection device through the interface module, and the negative contact of the solar charging network is connected to the negative pole of the detection device through the interface module to perform open circuit voltage test and short circuit current test on the solar charging network.

6. The system according to claim 1, characterized in that Each contact point of the solar charging network, the lithium battery charging network and the load network includes at least two pins.

7. A method for using a wireless self-powered power-on system for space equipment, characterized in that: The wireless self-powered power-on system for space equipment as claimed in claim 1 is used to implement the method, comprising the following steps: Determining the operating conditions of the space equipment; the operating conditions include ground storage conditions, ground test conditions, and on-orbit operating conditions; When the space equipment is in a ground storage condition, the solar charging network, the lithium battery charging network and the load network are disconnected by using the interface module, so that the self-powered system is in a power-off storage state; When the space device is in a ground test condition, the solar charging network, the lithium battery charging network and the load network are first connected using the interface module so that each network is in an independent test state; When the space device is in an on-orbit operating condition, the solar charging network, the lithium battery charging network and the load network are connected for a second time using the interface module, so that the solar charging network and the lithium battery charging network can be used to self-power the load network.

8. The method according to claim 7, characterized in that The first connection includes: Use the interface module to connect the positive and negative contacts of the lithium battery to the charging device to charge the lithium battery independently; Connecting the positive and negative contacts of the load network to the test equipment using the interface module to test the load network; The positive and negative contacts of the solar charging network are connected to the detection equipment by using the interface module to perform line detection on the solar charging network.

9. The method according to claim 8, characterized in that The second connection includes: The interface module is used to short-circuit the positive contact of the lithium battery, the positive contact of the solar charger, the positive contact of the load, and the positive contact of the fuel meter, and to short-circuit the negative contact of the lithium battery and the negative contact of the fuel meter.

10. The method according to claim 9, characterized in that The method of using the solar charging network and the lithium battery charging network to self-power the load network includes: When the solar charging network receives light, it determines whether the load network needs external power supply. If so, the charging current generated by the solar charging network is provided to the load network, otherwise, the charging current is provided to the lithium battery for charging; Determine whether the charging current is greater than the current required by the load. If so, transfer the remaining charging current to the lithium battery for charging. Otherwise, keep providing it only to the load network; When the solar charging network is not exposed to sunlight, the charging current generated by the lithium battery is provided to the load network.

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