CN110654575A - Satellite load power supply device, method, device, storage medium and thruster - Google Patents
Satellite load power supply device, method, device, storage medium and thruster Download PDFInfo
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Abstract
本发明公开了一种卫星负载供电装置,该装置包括:第一检测单元检测负载当前所需功率;主控单元在当前所需功率大于预设阈值时,切断负载与卫星电源之间的通路,控制储能单元向负载供电;储能单元在当前所需功率小于预设阈值时,接收卫星电源传输的电能,并将满足当前所需功率的电能传输给负载,存储冗余电能。上述装置,可以实现大功率负载在小功率卫星上的多次短时间运行,降低了大功率用电负载对卫星电源功率的要求,并在卫星电源与用电负载之间形成了隔离,有效防止用电设备在开关机及工作过程中对卫星电源系统产生瞬间的冲击及扰动。本发明还提出一种卫星负载供电方法、设备、存储介质及推力器。
The invention discloses a satellite load power supply device, which comprises: a first detection unit detects the current power required by the load; when the current required power is greater than a preset threshold, the main control unit cuts off the path between the load and the satellite power supply, The energy storage unit is controlled to supply power to the load; when the current required power is less than the preset threshold, the energy storage unit receives the electrical energy transmitted by the satellite power supply, and transmits the electrical energy that meets the current required power to the load to store redundant electrical energy. The above device can realize multiple short-time operations of high-power loads on low-power satellites, reduce the power requirements of high-power electrical loads on satellite power supplies, and form isolation between satellite power supplies and electrical loads, effectively preventing the The electrical equipment produces instantaneous impact and disturbance to the satellite power system during the on-off and working process. The invention also provides a satellite load power supply method, equipment, storage medium and thruster.
Description
技术领域technical field
本发明涉及卫星供电技术领域,尤其涉及一种卫星负载供电装置、方法、设备、存储介质及推力器。The invention relates to the technical field of satellite power supply, in particular to a satellite load power supply device, method, equipment, storage medium and thruster.
背景技术Background technique
人造卫星上有许多电子设备,特别是对于一些大功率推力器,如大功率电推力器(功率为几十千瓦的霍尔推力器,功率为千瓦量级的电弧加热推力器),其开关机启动过程中产生的大电流会对卫星电源及星载其它用电设备工作带来影响,为了减少该种影响,很多卫星公司对电推力器充电电流及工作能量级别进行了限制,使得电推力器以牺牲推力器性能为代价来满足此要求;其次,大功率推力器在工作时需消耗大量能量,会对卫星电源供电功率带来极大的负担,为了增加用电需要,必须要增加太阳能电池帆板面积,从而增加了卫星体积重量及成本;另外,电推力器放电工作产生的电磁干扰会对卫星电源系统产生瞬间的冲击及扰动,极大地影响了卫星电源系统的稳定性及工作可靠性。There are many electronic devices on artificial satellites, especially for some high-power thrusters, such as high-power electric thrusters (Hall thrusters with a power of tens of kilowatts, and arc heating thrusters with a power of 1000 kilowatts). The large current generated during the start-up process will affect the operation of the satellite power supply and other on-board electrical equipment. In order to reduce this impact, many satellite companies have limited the charging current and working energy level of the electric thruster. This requirement is met at the expense of the performance of the thruster; secondly, the high-power thruster needs to consume a lot of energy when working, which will bring a great burden to the power supply of the satellite power supply. In order to increase the demand for electricity, it is necessary to increase the solar cell. The area of the windsurfing board increases the volume, weight and cost of the satellite; in addition, the electromagnetic interference generated by the discharge of the electric thruster will have an instant impact and disturbance on the satellite power system, which greatly affects the stability and reliability of the satellite power system. .
上述内容仅用于辅助理解本发明的技术方案,并不代表承认上述内容是现有技术。The above content is only used to assist the understanding of the technical solutions of the present invention, and does not mean that the above content is the prior art.
发明内容SUMMARY OF THE INVENTION
本发明的主要目的在于提供一种卫星负载供电装置、方法、设备、存储介质及推力器,旨在解决现有技术卫星电源供电功率小用电负载所需功率大的技术问题。The main purpose of the present invention is to provide a satellite load power supply device, method, equipment, storage medium and thruster, aiming at solving the technical problem of the prior art that the satellite power supply power is small and the power required by the electric load is large.
为实现上述目的,本发明提供了一种卫星负载供电装置,所述装置包括:In order to achieve the above purpose, the present invention provides a satellite load power supply device, the device includes:
第一检测单元:用于检测负载当前所需功率;The first detection unit: used to detect the current required power of the load;
主控单元:用于在所述当前所需功率大于预设阈值时,切断所述负载与卫星电源之间的通路,控制储能单元向所述负载供电;Main control unit: when the current required power is greater than a preset threshold, cut off the path between the load and the satellite power supply, and control the energy storage unit to supply power to the load;
储能单元:用于在所述当前所需功率小于预设阈值时,接收所述卫星电源传输的电能,并将满足所述当前所需功率的电能传输给所述负载,存储冗余电能。Energy storage unit: when the current required power is less than a preset threshold, receive the electrical energy transmitted by the satellite power supply, and transmit the electrical energy that meets the current required power to the load to store redundant electrical energy.
优选地,所述装置还包括:Preferably, the device further comprises:
第二检测单元,用于检测所述储能单元的当前电量。The second detection unit is used to detect the current power of the energy storage unit.
优选地,所述主控单元还用于控制所述储能单元按照预设时间向所述负载供电;在所述当前电量大于储能单元的阈值电量时,控制所述储能单元接收所述卫星电源传输的电能,并将电能传输给所述负载,不存储所述电能。Preferably, the main control unit is further configured to control the energy storage unit to supply power to the load according to a preset time; when the current electric quantity is greater than the threshold electric quantity of the energy storage unit, control the energy storage unit to receive the The power delivered by the satellite power source is delivered to the load without storing the power.
优选地,所述装置的输入端连接所述卫星电源的输出端,所述装置的输出端连接所述负载的电能输入端。Preferably, the input end of the device is connected to the output end of the satellite power supply, and the output end of the device is connected to the power input end of the load.
此外,为实现上述目的,本发明还提出一种卫星负载供电方法,所述方法包括:In addition, in order to achieve the above purpose, the present invention also proposes a method for supplying power to a satellite load, the method comprising:
检测负载当前所需功率;Detect the current required power of the load;
在当前所需功率大于预设阈值时,切断所述负载与卫星电源之间的通路,控制储能单元向所述负载供电;When the current required power is greater than the preset threshold, cut off the path between the load and the satellite power supply, and control the energy storage unit to supply power to the load;
在所述当前所需功率小于预设阈值时,接收所述卫星电源传输的电能,并将满足所述当前所需功率的电能传输给所述负载,存储冗余电能。When the current required power is less than a preset threshold, the electric power transmitted by the satellite power source is received, and the electric power satisfying the current required power is transmitted to the load, and redundant electric power is stored.
优选地,所述在当前所需功率大于预设阈值时,切断所述负载与卫星电源之间的通路,控制储能单元向所述负载供电的步骤具体包括:Preferably, the step of cutting off the path between the load and the satellite power supply when the current required power is greater than a preset threshold, and controlling the energy storage unit to supply power to the load specifically includes:
在当前所需功率大于预设阈值时,切断所述负载与卫星电源之间的通路,控制所述储能单元按照预设时间向所述负载供电。When the current required power is greater than a preset threshold, the path between the load and the satellite power source is cut off, and the energy storage unit is controlled to supply power to the load according to a preset time.
优选地,所述在所述当前所需功率小于预设阈值时,接收所述卫星电源传输的电能,并将满足所述当前所需功率的电能传输给所述负载,存储冗余电能的步骤之后,所述方法还包括:Preferably, when the current required power is less than a preset threshold, the step of receiving the electric energy transmitted by the satellite power supply, transmitting the electric energy satisfying the current required power to the load, and storing redundant electric energy Afterwards, the method further includes:
检测所述储能单元的当前电量;detecting the current power of the energy storage unit;
在所述当前电量大于储能单元的阈值电量时,控制所述储能单元接收所述卫星电源传输的电能,并将电能传输给所述负载,不存储所述电能。When the current electric energy is greater than the threshold electric energy of the energy storage unit, the energy storage unit is controlled to receive the electric energy transmitted by the satellite power supply, and transmit the electric energy to the load without storing the electric energy.
此外,为实现上述目的,本发明还提出一种设备,所述设备包括:存储器、处理器及存储在所述存储器上并可在所述处理器上运行的卫星负载供电程序,所述卫星负载供电程序配置为实现如上所述的卫星负载供电方法的步骤。In addition, in order to achieve the above object, the present invention also proposes a device, the device includes: a memory, a processor, and a satellite load power supply program stored in the memory and running on the processor, the satellite load The power supply program is configured to implement the steps of the satellite load power supply method as described above.
此外,为实现上述目的,本发明还提出一种存储介质,所述存储介质上存储有卫星负载供电程序,所述卫星负载供电程序被处理器执行时实现如上所述的卫星负载供电方法的步骤。In addition, in order to achieve the above object, the present invention also proposes a storage medium on which a satellite load power supply program is stored, and when the satellite load power supply program is executed by a processor, the steps of the above-mentioned satellite load power supply method are implemented .
此外,为实现上述目的,本发明还提出一种推力器,所述推力器包括如上所述的卫星负载供电装置,或者所述推力器应用如上所述的卫星负载供电方法。In addition, in order to achieve the above objective, the present invention also provides a thruster, which includes the above-mentioned satellite load power supply device, or the above-mentioned satellite load power supply method is applied to the thruster.
本发明公开了一种卫星负载供电装置、方法、设备、存储介质及推力器,该装置包括:第一检测单元:用于检测负载当前所需功率;主控单元:用于在所述当前所需功率大于预设阈值时,切断所述负载与卫星电源之间的通路,控制储能单元向所述负载供电;储能单元:用于在所述当前所需功率小于预设阈值时,接收所述卫星电源传输的电能,并将满足所述当前所需功率的电能传输给所述负载,存储冗余电能。以上述装置作为电源为大功率用电负载供电,可有效降低大功率用电负载对卫星电源功率的要求;避免卫星电源对负载电流及工作能量级别的限制,避免了电推力器以牺牲推力器性能为代价来满足此要求情况的发生。The invention discloses a satellite load power supply device, method, equipment, storage medium and thruster. The device includes: a first detection unit: used to detect the current power required by the load; When the required power is greater than the preset threshold, the path between the load and the satellite power supply is cut off, and the energy storage unit is controlled to supply power to the load; The power transmitted by the satellite power source is transmitted to the load to meet the current required power, and redundant power is stored. Using the above device as a power source to supply power to a high-power electrical load can effectively reduce the power requirements of the high-power electrical load on the satellite power supply; avoid the satellite power supply's restrictions on the load current and working energy level, and avoid sacrificing the thruster for electric thrusters. This requirement occurs at the cost of performance.
附图说明Description of drawings
图1是本发明实施例方案涉及的硬件运行环境的设备的结构示意图;1 is a schematic structural diagram of a device of a hardware operating environment involved in an embodiment of the present invention;
图2为本发明卫星负载供电装置第一实施例的结构框图;Fig. 2 is the structural block diagram of the first embodiment of the satellite load power supply device of the present invention;
图3为本发明卫星负载供电方法第一实施例的流程示意图;FIG. 3 is a schematic flowchart of the first embodiment of the satellite load power supply method according to the present invention;
图4为本发明卫星负载供电装置第二实施例的结构框图;4 is a structural block diagram of a second embodiment of a satellite load power supply device according to the present invention;
图5为本发明卫星负载供电方法第二实施例的流程示意图。FIG. 5 is a schematic flowchart of a second embodiment of a method for powering a satellite load according to the present invention.
本发明目的的实现、功能特点及优点将结合实施例,参照附图做进一步说明。The realization, functional characteristics and advantages of the present invention will be further described with reference to the accompanying drawings in conjunction with the embodiments.
具体实施方式Detailed ways
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。It should be understood that the specific embodiments described herein are only used to explain the present invention, but not to limit the present invention.
参照图1,图1为本发明实施例方案涉及的硬件运行环境的设备结构示意图。Referring to FIG. 1 , FIG. 1 is a schematic diagram of a device structure of a hardware operating environment involved in an embodiment of the present invention.
如图1所示,该设备可以包括:处理器1001,例如中央处理器(Central ProcessingUnit,CPU),通信总线1002、存储器1003。其中,通信总线1002用于实现这些组件之间的连接通信。存储器1003可以是高速的随机存取存储器(Random Access Memory,RAM)存储器,也可以是稳定的非易失性存储器(Non-Volatile Memory,NVM),例如磁盘存储器。存储器1003可选的还可以是独立于前述处理器1001的存储装置。As shown in FIG. 1 , the device may include: a
本领域技术人员可以理解,图1中示出的结构并不构成对设备的限定,可以包括比图示更多或更少的部件,或者组合某些部件,或者不同的部件布置。Those skilled in the art can understand that the structure shown in FIG. 1 does not constitute a limitation on the device, and may include more or less components than those shown, or combine some components, or arrange different components.
如图1所示,作为一种存储介质的存储器1003中可以包括操作系统及卫星负载供电程序。As shown in FIG. 1 , the
在图1所示的设备中,本发明设备中的处理器1001、存储器1003可以设置在设备中,所述设备通过处理器1001调用存储器1003中存储的卫星负载供电程序,并执行本发明实施例提供的卫星负载供电方法。In the device shown in FIG. 1 , the
本发明实施例提供了一种卫星负载供电装置,参照图2,图2为本发明一种卫星负载供电装置第一实施例的结构框图。An embodiment of the present invention provides a satellite load power supply device. Referring to FIG. 2 , FIG. 2 is a structural block diagram of a first embodiment of a satellite load power supply device of the present invention.
所述卫星负载供电装置200包括:第一检测单元201、主控单元203、储能单元204。The satellite load
需要说明的是,所述卫星负载供电装置200的输入端和卫星电源100的输出端连接,所述卫星负载供电装置200的输出端和负载300的输入端连接。所述负载100,可为卫星内全部需要供电的负载单元,也可以为卫星中需要大功率供电的负载单元。在本实施例中,将推力器作为负载进行陈述,所述卫星负载供电装置200可以集成到所述推力器上。It should be noted that the input end of the satellite load
易于理解的是,所述卫星负载供电装置200在卫星电源与用电负载之间形成了隔离,可以有效防止用电设备在开关机及工作过程中对卫星电源系统产生瞬间的冲击及扰动,极大地提升了卫星电源系统的稳定性及工作可靠性。It is easy to understand that the satellite load
所述第一检测单元201:用于检测负载当前所需功率。The first detection unit 201: used to detect the current power required by the load.
需要说明的是,所述第一检测单元201将检测结果发送给所述主控单元203,可以设置所述第一检测单元201为周期性检测、实时监测及触发式检测。本实施例中,以推力器作为负载进行陈述,例如,在推力器启动时,触发所述第一检测单元201对负载当前所需功率进行检测。It should be noted that the
所述主控单元203:用于在所述当前所需功率大于预设阈值时,切断所述负载与卫星电源之间的通路,控制所述储能单元204向所述负载供电;The
需要说明的是,所述预设阈值预先设置并存储在所述主控单元203的存储器中,具体实现中,所述预设阈值可根据实际需求设置。在本实施例中,以推力器作为负载进行陈述,例如:将预设阈值设置为推力器不工作时所需功率,在所述推力器工作时,检测到当前所需功率大于预设阈值,切断推力器和卫星电源的通路,控制所述储能单元204向所述推力器供电,即,推力器工作时,仅由所述储能单元204供电,其余负载仍可由所述卫星电源供电。It should be noted that, the preset threshold value is preset and stored in the memory of the
所述储能单元204:用于在所述当前所需功率小于预设阈值时,接收所述卫星电源100传输的电能,并将满足所述当前所需功率的电能传输给所述负载300,存储冗余电能。The
需要说明的是,所述储能单元在本实施例中为动力锂电池,选用锂电池的理由是,锂电池储能量大,且锂电池较轻,不会给卫星带来额外的重量负担。在具体实施中,所述储能单元可以为大容量化学电池、燃料电池,但不仅局限于所列举储能设备类型,其目的是为卫星负载提供大功率供电,且不影响卫星的体积重量及成本,能满足上述目的储能设备都可以用于本发明。It should be noted that the energy storage unit is a power lithium battery in this embodiment, and the reason for selecting the lithium battery is that the lithium battery has a large energy storage capacity and is light, and will not bring additional weight burden to the satellite. In specific implementation, the energy storage unit can be a large-capacity chemical battery or a fuel cell, but it is not limited to the listed energy storage device types, and its purpose is to provide high-power power supply for the satellite load without affecting the volume, weight and Cost, energy storage devices that can meet the above objectives can be used in the present invention.
需要说明的是,所述卫星负载供电装置200起到了通路作用,并未对原有的卫星电源100向用电负载300供电的电路造成影响,仅存储冗余电能。It should be noted that the satellite load
本实施例装置,可以将卫星电源产生的电能,特别是将在用电负荷较小时刻卫星电源产生的冗余电能储存在储能单元中,达到充分收集卫星电源产生的电能的效果,满足了卫星用电负载大功率用电的需求,避免卫星电源对负载电流及工作能量级别的限制,避免了电推力器以牺牲推力器性能为代价来满足此要求。储能装置在卫星电源与用电负载之间形成了隔离,可以有效防止用电设备在开关机及工作过程中对卫星电源系统产生瞬间冲击及扰动,极大地提升了卫星电源系统的稳定性及工作可靠性。The device of this embodiment can store the electric energy generated by the satellite power supply, especially the redundant electric energy generated by the satellite power supply when the electricity load is small, in the energy storage unit, so as to achieve the effect of fully collecting the electric energy generated by the satellite power supply, and satisfies the The demand for high-power power consumption of satellite power load avoids the limitation of load current and working energy level by satellite power supply, and avoids the need for electric thrusters to meet this requirement at the expense of thruster performance. The energy storage device forms an isolation between the satellite power supply and the electrical load, which can effectively prevent the electrical equipment from causing instantaneous impact and disturbance to the satellite power supply system during the switching and working process, which greatly improves the stability and performance of the satellite power supply system. Work reliability.
基于本发明卫星负载供电装置第一实施例,本发明提供了一种卫星负载供电方法,参照图3,图3为本发明一种卫星负载供电方法第一实施例的流程示意图;Based on the first embodiment of the satellite load power supply device of the present invention, the present invention provides a satellite load power supply method. Referring to FIG. 3 , FIG. 3 is a schematic flowchart of the first embodiment of the satellite load power supply method of the present invention;
步骤S100:检测负载当前所需功率;Step S100: Detecting the current power required by the load;
需要说明的是,本实施例以推力器作为负载进行陈述,例如,所述推力器开始工作,检测到所述推力器当前所需功率。It should be noted that, in this embodiment, the thruster is used as the load. For example, the thruster starts to work, and the current required power of the thruster is detected.
步骤S200:在当前所需功率大于预设阈值时,切断所述负载300与卫星电源100之间的通路,控制储能单元204向所述负载300供电;Step S200: when the current required power is greater than a preset threshold, cut off the path between the
需要说明的是,所述预设阈值可根据实际需求设置。例如:将预设阈值设置为推力器不工作时所需功率,在所述推力器工作时,检测到当前所需功率大于预设阈值,切断推力器和卫星电源的通路,控制所述储能单元204向所述推力器供电,即,推力器工作时,仅由所述储能单元204供电,其余负载仍可由所述卫星电源供电。It should be noted that the preset threshold can be set according to actual requirements. For example, the preset threshold is set as the power required when the thruster is not working, and when the thruster is working, it is detected that the current required power is greater than the preset threshold, the passage between the thruster and the satellite power supply is cut off, and the energy storage is controlled. The
步骤S300:在所述当前所需功率小于预设阈值时,接收所述卫星电源100传输的电能,并将满足所述当前所需功率的电能传输给所述负载200,存储冗余电能。Step S300: When the current required power is less than a preset threshold, receive the electrical energy transmitted by the
需要说明的是,例如:所述推力器暂时不工作,检测到所述推力器当前所需功率小于预设阈值,接收卫星电源100传输的电能,所述卫星负载供电装置200此时作为通路将电能输出给其余负载,并将冗余电能存储。It should be noted that, for example, the thruster does not work temporarily, it is detected that the current required power of the thruster is less than a preset threshold, and the electric energy transmitted by the
本实施例方法,可以将卫星电源产生的电能,特别是将在用电负荷较小时刻卫星电源产生的冗余电能储存在储能单元中,达到充分收集卫星电源产生的电能的效果,满足了卫星用电负载大功率用电的需求,避免卫星电源对负载电流及工作能量级别的限制,避免了电推力器以牺牲推力器性能为代价来满足此要求。The method of this embodiment can store the electric energy generated by the satellite power supply, especially the redundant electric energy generated by the satellite power supply when the power load is small, in the energy storage unit, so as to achieve the effect of fully collecting the electric energy generated by the satellite power supply, and satisfy the The demand for high-power power consumption of satellite power load avoids the limitation of load current and working energy level by satellite power supply, and avoids the need for electric thrusters to meet this requirement at the expense of thruster performance.
基于本发明一种卫星负载供电装置第一实施例,提出本发明一种卫星负载供电装置第二实施例。参照图4,图4为本发明卫星负载供电装置第二实施例的结构框图;Based on the first embodiment of a satellite load power supply device of the present invention, a second embodiment of a satellite load power supply device of the present invention is proposed. Referring to FIG. 4, FIG. 4 is a structural block diagram of the second embodiment of the satellite load power supply device of the present invention;
所述卫星负载供电装置200还包括:第二检测单元202。The satellite load
所述第二检测单元202:用于检测所述储能单元204的当前电量。The second detection unit 202 : used to detect the current power of the
易于理解的是,所述储能单元204的电能存储量有上限,过充过放都会损耗所述储能单元204的使用寿命,因此设置所述第二检测单元202,检测所述储能单元204的当前电量,并将所述当前电量值发送至主控单元203。It is easy to understand that the energy storage capacity of the
所述主控单元203:还用于在所述当前所需功率大于预设阈值时,切断所述负载300与卫星电源100之间的通路,控制所述储能单元204按照预设时间向所述负载300供电。在所述当前电量大于储能单元204的阈值电量时,控制所述储能单元204接收所述卫星电源100传输的电能,并将电能传输给所述负载300,不存储所述电能。The
易于理解的是,出于对所述大功率用电负载的使用寿命及所述储能单元204的使用寿命的考虑,优选的方案是按照预设时间进行工作,本实施例中,以推力器为负载进行陈述。例如:所述推力器启动,需要大功率供电,所述主控单元203切断所述推力器与卫星电源100直接的通路,根据卫星当前所需的推力,规划出所述推力器所需的供电时长为200s,将200s定为预设时间,所述主控单元203根据预设时间,控制所述储能单元204向所述推力器供电。当卫星完成了动作,不再需要供电,预设时间到达,所述主控单元203控制所述储能单元204停止供电。所述推力器当前所需功率降低至预设阈值以下,控制所述储能单元204接收所述卫星电源100传输的电能,并将满足所述当前所需功率的电能传输给所述负载200,存储冗余电能。It is easy to understand that, in consideration of the service life of the high-power electrical load and the service life of the
易于理解的是,所述储能单元204的当前电量达到了阈值电量,则控制所述储能单元204接收所述卫星电源100传输的电能,并将电能传输给所述负载300,不存储所述电能。此时所述装置仅作为通路,不再存储电能,以免过充。It is easy to understand that when the current power of the
本实施例装置,在第一实施例的基础上,按照预设时间向负载供电,解决了卫星电功率小但用电负载需要功率大的矛盾,保障了装置和负载的使用寿命,在卫星电源与用电负载之间形成了隔离,可以有效防止用电设备在开关机及工作过程中对卫星电源系统产生瞬间的冲击及扰动,极大地提升了卫星电源系统的稳定性及工作可靠性。The device of this embodiment, on the basis of the first embodiment, supplies power to the load according to the preset time, which solves the contradiction that the satellite electric power is small but the electric load needs large power, and ensures the service life of the device and the load. Isolation is formed between the electrical loads, which can effectively prevent the electrical equipment from causing instantaneous impact and disturbance to the satellite power system during the switching and working process, which greatly improves the stability and working reliability of the satellite power system.
基于本发明卫星负载供电装置第二实施例,本发明提供了一种卫星负载供电方法,参照图5,图5为本发明一种卫星负载供电方法第二实施例的流程示意图;Based on the second embodiment of the satellite load power supply device of the present invention, the present invention provides a satellite load power supply method. Referring to FIG. 5 , FIG. 5 is a schematic flowchart of the second embodiment of the satellite load power supply method according to the present invention;
所述步骤S200,具体包括:The step S200 specifically includes:
S201:在当前所需功率大于预设阈值时,切断所述负载300与卫星电源100之间的通路,控制所述储能单元204按照预设时间向所述负载300供电。S201: When the current required power is greater than a preset threshold, cut off the path between the
易于理解的是,出于对所述大功率用电负载的使用寿命及所述储能单元的使用寿命的考虑,优选的方案是按照预设时间进行工作,本实施例中,以推力器为负载进行陈述。例如:所述推力器启动,需要大功率供电,所述主控单元203切断所述推力器与卫星电源100直接的通路,根据卫星当前所需的推力,规划出所述推力器所需的供电时长为200s,将200s定为预设时间,所述主控单元203根据预设时间,控制所述储能单元204向所述推力器供电。当卫星完成了动作,不再需要供电,预设时间到达,所述主控单元203控制所述储能单元204停止供电,所述推力器当前所需功率降低至预设阈值以下,回到步骤S300。It is easy to understand that, in consideration of the service life of the high-power electrical load and the service life of the energy storage unit, the preferred solution is to work according to the preset time. load statement. For example, when the thruster starts and needs high-power power supply, the
所述步骤S300之后,所述方法还包括:After the step S300, the method further includes:
步骤S301:检测所述储能单元204的当前电量;Step S301: detecting the current power of the
易于理解的是,检测所述储能单元204的当前电量,并将所述当前电量值发送至主控单元203。It is easy to understand that the current power of the
步骤S302:在所述当前电量大于储能单元的阈值电量时,控制所述储能单元接收所述卫星电源传输的电能,并将电能传输给所述负载,不存储所述电能。Step S302: When the current power is greater than the threshold power of the energy storage unit, control the energy storage unit to receive the power transmitted by the satellite power supply, and transmit the power to the load without storing the power.
需要说明的是,所述储能单元204的当前电量达到了阈值电量,则控制所述储能单元204接收所述卫星电源100传输的电能,并将电能传输给所述负载300,不存储所述电能。此时所述装置仅作为通路,不再存储电能,以免过充。It should be noted that, when the current power of the
本实施例方法,在第一实施例的基础上,按照预设时间向负载供电,解决了卫星电功率小但用电负载需要功率大的矛盾,保障了装置和负载的使用寿命,在卫星电源与用电负载之间形成了隔离,可以有效防止用电设备在开关机及工作过程中对卫星电源系统产生瞬间的冲击及扰动,极大地提升了卫星电源系统的稳定性及工作可靠性。The method of this embodiment, on the basis of the first embodiment, supplies power to the load according to the preset time, solves the contradiction that the satellite electric power is small but the electric load needs large power, and ensures the service life of the device and the load. Isolation is formed between the electrical loads, which can effectively prevent the electrical equipment from causing instantaneous impact and disturbance to the satellite power system during the switching and working process, which greatly improves the stability and working reliability of the satellite power system.
此外,本发明实施例还提出一种存储介质,所述存储介质上存储有卫星负载供电程序,所述卫星负载供电程序被处理器执行时实现如上文所述的卫星负载供电方法的步骤。由于本存储介质采用了上述所有实施例的全部技术方案,因此至少具有上述实施例的技术方案所带来的所有有益效果,在此不再一一赘述。In addition, an embodiment of the present invention further provides a storage medium, where a satellite load power supply program is stored on the storage medium, and when the satellite load power supply program is executed by a processor, the steps of the satellite load power supply method as described above are implemented. Since the storage medium adopts all the technical solutions of all the above-mentioned embodiments, it has at least all the beneficial effects brought by the technical solutions of the above-mentioned embodiments, which will not be repeated here.
本发明还提出一种设备,由于本设备采用了上述所有实施例的全部技术方案,因此至少具有上述实施例的技术方案所带来的所有有益效果,在此不再一一赘述。The present invention also provides a device. Since the device adopts all the technical solutions of the above-mentioned embodiments, it has at least all the beneficial effects brought by the technical solutions of the above-mentioned embodiments, which will not be repeated here.
本发明还提出一种推力器,由于本推力器采用了上述所有实施例的全部技术方案,因此至少具有上述实施例的技术方案所带来的所有有益效果,在此不再一一赘述。The present invention also provides a thruster. Since the thruster adopts all the technical solutions of all the above-mentioned embodiments, it has at least all the beneficial effects brought by the technical solutions of the above-mentioned embodiments, and will not be repeated here.
应当理解的是,以上仅为举例说明,对本发明的技术方案并不构成任何限定,在具体应用中,本领域的技术人员可以根据需要进行设置,本发明对此不做限制。It should be understood that the above are only examples, and do not constitute any limitation to the technical solutions of the present invention. In specific applications, those skilled in the art can make settings as required, which is not limited by the present invention.
需要说明的是,以上所描述的工作流程仅仅是示意性的,并不对本发明的保护范围构成限定,在实际应用中,本领域的技术人员可以根据实际的需要选择其中的部分或者全部来实现本实施例方案的目的,此处不做限制。It should be noted that the above-described workflow is only illustrative, and does not limit the protection scope of the present invention. In practical applications, those skilled in the art can select some or all of them to implement according to actual needs. The purpose of the solution in this embodiment is not limited here.
此外,需要说明的是,在本文中,术语“包括”、“包含”或者其任何其他变体意在涵盖非排他性的包含,从而使得包括一系列要素的过程、方法、物品或者系统不仅包括那些要素,而且还包括没有明确列出的其他要素,或者是还包括为这种过程、方法、物品或者系统所固有的要素。在没有更多限制的情况下,由语句“包括一个……”限定的要素,并不排除在包括该要素的过程、方法、物品或者系统中还存在另外的相同要素。Furthermore, it should be noted that, herein, the terms "comprising", "comprising" or any other variation thereof are intended to encompass non-exclusive inclusion, such that a process, method, article or system comprising a series of elements includes not only those elements, but also other elements not expressly listed or inherent to such a process, method, article or system. Without further limitation, an element qualified by the phrase "comprising a..." does not preclude the presence of additional identical elements in the process, method, article or system that includes the element.
上述本发明实施例序号仅仅为了描述,不代表实施例的优劣。The above-mentioned serial numbers of the embodiments of the present invention are only for description, and do not represent the advantages or disadvantages of the embodiments.
通过以上的实施方式的描述,本领域的技术人员可以清楚地了解到上述实施例方法可借助软件加必需的通用硬件平台的方式来实现,当然也可以通过硬件,但很多情况下前者是更佳的实施方式。基于这样的理解,本发明的技术方案本质上或者说对现有技术做出贡献的部分可以以软件产品的形式体现出来,该计算机软件产品存储在一个存储介质(如只读存储器(Read Only Memory,ROM)/RAM、磁碟、光盘)中,包括若干指令用以使得一台终端设备(可以是手机,计算机,服务器,或者网络设备等)执行本发明各个实施例所述的方法。From the description of the above embodiments, those skilled in the art can clearly understand that the method of the above embodiment can be implemented by means of software plus a necessary general hardware platform, and of course can also be implemented by hardware, but in many cases the former is better implementation. Based on such understanding, the technical solutions of the present invention can be embodied in the form of software products in essence or the parts that make contributions to the prior art, and the computer software products are stored in a storage medium (such as a read-only memory). , ROM)/RAM, magnetic disk, optical disk), including several instructions to make a terminal device (which may be a mobile phone, a computer, a server, or a network device, etc.) execute the methods described in the various embodiments of the present invention.
以上仅为本发明的优选实施例,并非因此限制本发明的专利范围,凡是利用本发明说明书及附图内容所作的等效结构或等效流程变换,或直接或间接运用在其他相关的技术领域,均同理包括在本发明的专利保护范围内。The above are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Any equivalent structure or equivalent process transformation made by using the contents of the description and drawings of the present invention, or directly or indirectly applied in other related technical fields , are similarly included in the scope of patent protection of the present invention.
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Effective date of registration: 20211230 Address after: Room 1012, 10 / F, building 2, haipingyuan, 229 Guyuan Road, high tech Development Zone, Changsha, Hunan 410000 Patentee after: Hunan Hongxing Technology Co.,Ltd. Patentee after: National University of Defense Technology Address before: 518000 unit 01c-1, building B5, Guangming Science Park, China Merchants Group, 3009 Guangming Street, Guangming New District, Shenzhen City, Guangdong Province Patentee before: SHENZHEN XUNTIAN SPACE TECHNOLOGY CO.,LTD. |