阅读说明：本技术 卫星座充系统 (Satellite seat charging system ) 是由 徐骏 蒋志杰 张科科 付碧红 陈宏宇 于 2020-05-15 设计创作，主要内容包括：本发明提供了一种卫星座充系统,包括卫星电源系统、运载电源系统、地面电源系统及接触式星载连接系统,接触式星载连接系统使卫星电源系统与运载电源系统之间电连接；卫星电源系统、运载电源系统及地面电源系统被配置为依次连接的第一座充状态,第一座充状态包括：地面电源系统为运载电源系统供电,运载电源系统为卫星电源系统供电,接触式星载连接系统处于导通状态；卫星电源系统及运载电源系统还被配置为相互连接的第二座充状态,第二座充状态包括：运载电源系统为卫星电源系统供电,接触式星载连接系统处于导通状态；卫星电源系统还被配置为自供电状态,自供电状态包括：卫星的太阳能阵列为卫星电源系统供电,接触式星载连接系统处于断开状态。(The invention provides a satellite base charging system which comprises a satellite power supply system, a carrying power supply system, a ground power supply system and a contact type satellite-borne connection system, wherein the contact type satellite-borne connection system enables the satellite power supply system and the carrying power supply system to be electrically connected; the satellite power supply system, the carrying power supply system and the ground power supply system are configured to be connected in sequence in a first seat charging state, and the first seat charging state comprises the following steps: the ground power supply system supplies power to the carrying power supply system, the carrying power supply system supplies power to the satellite power supply system, and the contact type satellite-borne connection system is in a conducting state; the satellite power system and the carrier power system are further configured to a second charging state of interconnection, the second charging state comprising: the carrying power supply system supplies power to the satellite power supply system, and the contact type satellite-borne connection system is in a conducting state; the satellite power system is further configured in a self-powered state including: the solar array of the satellite supplies power to the satellite power system, and the contact type satellite-borne connection system is in a disconnected state.)

1. A satellite base charging system is characterized by comprising a satellite power supply system, a carrying power supply system, a ground power supply system and a contact type satellite-borne connection system, wherein:

the contact type satellite-borne connection system is used for electrically connecting the satellite power supply system and the carrying power supply system;

the satellite power system, the carrier power system and the ground power system are configured as a first charging state connected in sequence, and the first charging state comprises: the ground power supply system supplies power to the carrying power supply system, the carrying power supply system supplies power to the satellite power supply system, and the contact type satellite-borne connection system is in a conducting state;

the satellite power system and the onboard power system are further configured to a second seated charging state of interconnection, the second seated charging state comprising: the carrying power supply system supplies power to the satellite power supply system, and the contact type satellite-borne connection system is in a conducting state;

the satellite power system is further configured in a self-powered state comprising: the solar array of the satellite supplies power to the satellite power supply system, and the contact type satellite-borne connection system is in a disconnected state.

2. A satellite seating charge system as claimed in claim 1, wherein the launch vehicle includes a release mechanism, wherein:

the release mechanism is configured to an attached state, the attached state comprising: the satellite is fixed on the release mechanism;

the release mechanism is further configured to a release state, the release state comprising: the satellite disengages the release mechanism;

the contact type satellite-borne connection system comprises a first connection device and a second connection device, wherein the first connection device is fixed on the surface of the satellite, and the second connection device is fixed on the surface of the release mechanism;

the attachment state further includes: the first connecting device is in compression joint with the second connecting device;

the release state further comprises: the first connecting device is disconnected from the second connecting device.

3. A satellite seat filling system according to claim 2, wherein the release mechanism comprises a locking device, a pyrotechnic device, and a resilient device, wherein:

the locking device is used for fixing the satellite to the release mechanism;

the initiating explosive device is used for destroying the locking device to enable the locking device to lose effectiveness;

the elastic device is used for providing pushing force for pushing the satellite away from the release mechanism.

4. A satellite seat filling system as defined in claim 3, wherein the first connecting means and the second connecting means each comprise a compact structure, wherein:

the compact structure comprises side lugs and a connecting piece, the two side lugs are used for fixing the compact structure on the surface of the satellite or the surface of the release mechanism, and the connecting piece protrudes between the two side lugs to provide an electrically connected hardware passage;

the side ear has a hole in the center for inserting a fixing bolt.

5. A satellite seat charging system as recited in claim 4, wherein said second connecting means further comprises a spring secured to said compact structure, wherein:

the reed is of a U-shaped structure, the outer wall of one side of the U-shaped structure is welded on the connecting piece of the pressing block structure of the second connecting device, and the outer wall of the other side of the U-shaped structure is in press connection with the connecting piece of the pressing block structure of the first connecting device;

the height of the reed is 5mm in the attached state, and the height of the reed is 7mm in the released state.

6. A satellite charger system as claimed in claim 2, wherein said first connecting means is plural in number, said second connecting means is plural in number, and one of said first connecting means corresponds to one of said second connecting means to form an interface, wherein:

the plurality of interfaces comprise a power supply positive line interface, a power supply return line interface and a plurality of data interfaces;

the power supply positive line interface and the power supply return line interface are used for providing a loop for a satellite seat charging system;

the data interface is used for receiving and transmitting the satellite test data in a downlink mode and receiving and transmitting the ground test instruction in an uplink mode.

7. A satellite desk charging system as recited in claim 6, wherein the satellite desk charging system comprises a first cable assembly, a second cable assembly, a third cable assembly, and a fourth cable assembly, wherein:

the first cable assembly establishes an electrical connection between the satellite power system and the first connection device;

the second cable assembly establishes an electrical connection between the second connection device and the onboard power system;

the third cable assembly establishes an electrical connection inside the onboard power system;

the fourth cable assembly establishes an electrical connection between the onboard power system and the surface power system.

8. A satellite seat charging system as recited in claim 7, wherein said third cable assembly is further coupled to a protection diode, wherein:

the anode of the protection diode is coupled to the ground power supply system, and the cathode of the protection diode is coupled to the satellite power supply system.

9. A satellite base charging system as set forth in claim 8, wherein said satellite power system comprises a MOS transistor, a first diode, a rc filter circuit, a battery, a second diode, and a switch, wherein:

the second diode is connected with the anode of the storage battery after being connected with the switch in parallel,

one end of the resistance-capacitance filter circuit is connected with the cathode of the storage battery, and the other end of the resistance-capacitance filter circuit is connected with the anode of the second diode;

the cathode of the first diode is connected with the anode of the second diode, the anode of the first diode is connected with one end of the source and drain of the MOS tube, and the other end of the source and drain of the MOS tube is connected with the cathode of the storage battery;

the anode of the first diode is also connected with the cathode of the protection diode.

10. A satellite base charging system as claimed in claim 9, wherein said satellite power system is further connected to said solar array, said solar array having an anode connected to a cathode of a third diode, said third diode having an anode connected to a cathode of said first diode, said solar array having a cathode connected to a cathode of said battery;

the interface also includes a ground analog array port and a ground array loop port.

Technical Field

The invention relates to the technical field of satellite power supply, in particular to a satellite seat charging system.

Background

Before the launch of the launch vehicle, the satellite is electrically disconnected from the ground system, and the electrical connection plug on the surface of the satellite is unplugged (hereinafter, simply referred to as unplugging). In the process, an operator needs to climb up the launching tower to enter the rocket fairing to operate, the process is complex, and certain risk is realized.

In the whole satellite testing link, the satellite is supplied with power jointly by an external power supply and a storage battery, and the external power supply is connected with the whole satellite through disconnection and insertion. Although the power supply mode is convenient for ground test, the satellite is completely surrounded by the fairing after the satellite and rocket combination is installed and covered, and in the test process of the launching tower, the plugging and unplugging of the take-off and plugging requires personnel to enter the rocket fairing, so that the process is complicated and has risks. If meet small-size solid rocket, there is not operating space at all in the radome fairing, gets to the tradition and takes the bottleneck for the design of inserting.

Disclosure of Invention

The invention aims to provide a satellite seat charging system to solve the problem that the existing satellite whole satellite testing link is connected with an external power supply to cause the possibility of disconnection and connection.

In order to solve the technical problem, the invention provides a satellite seat charging system, which comprises a satellite power supply system, a carrying power supply system, a ground power supply system and a contact type satellite-borne connection system, wherein:

the contact type satellite-borne connection system is used for electrically connecting the satellite power supply system and the carrying power supply system;

the satellite power system, the carrier power system and the ground power system are configured as a first charging state connected in sequence, and the first charging state comprises: the ground power supply system supplies power to the carrying power supply system, the carrying power supply system supplies power to the satellite power supply system, and the contact type satellite-borne connection system is in a conducting state;

the satellite power system and the onboard power system are further configured to a second seated charging state of interconnection, the second seated charging state comprising: the carrying power supply system supplies power to the satellite power supply system, and the contact type satellite-borne connection system is in a conducting state;

the satellite power system is further configured in a self-powered state comprising: the solar array of the satellite supplies power to the satellite power supply system, and the contact type satellite-borne connection system is in a disconnected state.

Optionally, in the satellite charging system, the launch vehicle includes a release mechanism, wherein:

the release mechanism is configured to an attached state, the attached state comprising: the satellite is fixed on the release mechanism;

the release mechanism is further configured to a release state, the release state comprising: the satellite disengages the release mechanism;

the contact type satellite-borne connection system comprises a first connection device and a second connection device, wherein the first connection device is fixed on the surface of the satellite, and the second connection device is fixed on the surface of the release mechanism;

the attachment state further includes: the first connecting device is in compression joint with the second connecting device;

the release state further comprises: the first connecting device is disconnected from the second connecting device.

Optionally, in the satellite seat charging system, the release mechanism includes a locking device, an initiating explosive device, and an elastic device, wherein:

the locking device is used for fixing the satellite to the release mechanism;

the initiating explosive device is used for destroying the locking device to enable the locking device to lose effectiveness;

the elastic device is used for providing pushing force for pushing the satellite away from the release mechanism.

Optionally, in the satellite seat charging system, the first connecting device and the second connecting device each include a compact structure, wherein:

the compact structure comprises side lugs and a connecting piece, the two side lugs are used for fixing the compact structure on the surface of the satellite or the surface of the release mechanism, and the connecting piece protrudes between the two side lugs to provide an electrically connected hardware passage;

the side ear has a hole in the center for inserting a fixing bolt.

Optionally, in the satellite seat charging system, the second connecting device further includes a spring fixed to the pressing block structure, wherein:

the reed is of a U-shaped structure, the outer wall of one side of the U-shaped structure is welded on the connecting piece of the pressing block structure of the second connecting device, and the outer wall of the other side of the U-shaped structure is in press connection with the connecting piece of the pressing block structure of the first connecting device;

the height of the reed is 5mm in the attached state, and the height of the reed is 7mm in the released state.

Optionally, in the satellite charger system, the number of the first connection devices is multiple, the number of the second connection devices is multiple, and one first connection device corresponds to one second connection device to form an interface, where:

the plurality of interfaces comprise a power supply positive line interface, a power supply return line interface and a plurality of data interfaces;

the power supply positive line interface and the power supply return line interface are used for providing a loop for a satellite seat charging system;

the data interface is used for receiving and transmitting the satellite test data in a downlink mode and receiving and transmitting the ground test instruction in an uplink mode.

Optionally, in the satellite seat charging system, the satellite seat charging system includes a first cable assembly, a second cable assembly, a third cable assembly, and a fourth cable assembly, where:

the first cable assembly establishes an electrical connection between the satellite power system and the first connection device;

the second cable assembly establishes an electrical connection between the second connection device and the onboard power system;

the third cable assembly establishes an electrical connection inside the onboard power system;

the fourth cable assembly establishes an electrical connection between the onboard power system and the surface power system.

Optionally, in the satellite seat charging system, the third cable assembly is further coupled to a protection diode, wherein:

the anode of the protection diode is coupled to the ground power supply system, and the cathode of the protection diode is coupled to the satellite power supply system.

Optionally, in the satellite base charging system, the satellite power supply system includes an MOS transistor, a first diode, a resistance-capacitance filter circuit, a storage battery, a second diode, and a switch, where:

the second diode is connected with the anode of the storage battery after being connected with the switch in parallel,

one end of the resistance-capacitance filter circuit is connected with the cathode of the storage battery, and the other end of the resistance-capacitance filter circuit is connected with the anode of the second diode;

the cathode of the first diode is connected with the anode of the second diode, the anode of the first diode is connected with one end of the source and drain of the MOS tube, and the other end of the source and drain of the MOS tube is connected with the cathode of the storage battery;

the anode of the first diode is also connected with the cathode of the protection diode.

Optionally, in the satellite base charging system, the satellite power supply system is further connected to the solar array, an anode of the solar array is connected to a cathode of a third diode, an anode of the third diode is connected to a cathode of the first diode, and a cathode of the solar array is connected to a cathode of the storage battery;

the interface also includes a ground analog array port and a ground array loop port.

In the satellite seat charging system provided by the invention, in the ground test stage, a satellite power supply system, a carrying power supply system and a ground power supply system are configured to be in a first seat charging state which is connected in sequence, the ground power supply system supplies power to the carrying power supply system, the carrying power supply system supplies power to the satellite power supply system, a contact type satellite-borne connection system is in a conducting state, before launching or when a satellite and a carrying are not separated, the satellite power supply system and the carrying power supply system are further configured to be in a second seat charging state which are connected with each other, the carrying power supply system supplies power to the satellite power supply system, the contact type satellite-borne connection system is in the conducting state, after the satellite is separated from the carrying after launching, the satellite power supply system is further configured to be in a self-powered state: the solar array of the satellite supplies power to the satellite power supply system, the contact type satellite-borne connection system is in a disconnected state, the design scheme of a satellite surface contact type electrical connection mode (hereinafter referred to as a seat charging system) is realized, the limitation of the traditional pulling-out and plugging-out operation is eliminated, and the convenience of satellite-rocket electrical connection is improved while the workload is reduced.

The invention provides a satellite seat charging system capable of supplying power and testing a satellite without depending on disconnection and insertion, and a carrier power supply system in a carrier rocket provides electrical connection for the satellite. Before launching, the fourth cable assembly connected with the ground power supply system is pulled out by the carrying power supply system, the satellite is separated from the carrier rocket after launching, and the contact type satellite-borne connection system can be automatically disconnected, so that the personnel operation can be greatly reduced, and the safety and the reliability are further improved.

Drawings

Fig. 1 is a schematic diagram of a satellite seating and charging system according to an embodiment of the invention;

FIG. 2 is a schematic diagram of a compact configuration according to an embodiment of the present invention;

FIG. 3 is a schematic view of a reed structure according to one embodiment of the invention;

FIG. 4 is a schematic structural diagram of a compact structure and a spring plate according to an embodiment of the present invention;

FIG. 5 is a schematic structural diagram of a satellite power system according to an embodiment of the invention;

shown in the figure: 10-a satellite; 11-satellite power supply system; 20-a launch vehicle; 21-a release mechanism; 22-a patch plug; 30-a ground power system; 40-contact satellite-borne connection system; 41-briquetting structure; 42-reed; 43-first connecting means; 44-second connecting means; 51-a first cable assembly; 52-a second cable assembly; 53-a third cable assembly; 54-a fourth cable assembly; 61-ground analog array port; 62-ground array loop port; 63-solar arrays; 64-seat charging positive line; 65-seat charging and returning line.

Detailed Description

The satellite seating and charging system provided by the invention is further described in detail with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims. It is to be noted that the drawings are in a very simplified form and are not to precise scale, which is merely for the purpose of facilitating and distinctly claiming the embodiments of the present invention.

The invention provides a satellite seat charging system, which aims to solve the problem of possible disconnection and connection caused by connection of an existing satellite whole satellite testing link and an external power supply.

In order to realize the idea, the invention provides a satellite seat charging system, which comprises a satellite power supply system, a carrying power supply system, a ground power supply system and a contact type satellite-borne connection system, wherein: the contact type satellite-borne connection system is used for electrically connecting the satellite power supply system and the carrying power supply system; the satellite power system, the carrier power system and the ground power system are configured as a first charging state connected in sequence, and the first charging state comprises: the ground power supply system supplies power to the carrying power supply system, the carrying power supply system supplies power to the satellite power supply system, and the contact type satellite-borne connection system is in a conducting state; the satellite power system and the onboard power system are further configured to a second seated charging state of interconnection, the second seated charging state comprising: the carrying power supply system supplies power to the satellite power supply system, and the contact type satellite-borne connection system is in a conducting state; the satellite power system is further configured in a self-powered state comprising: the solar array of the satellite supplies power to the satellite power supply system, and the contact type satellite-borne connection system is in a disconnected state.

< example one >

In the present embodiment, as shown in fig. 1 to 5, the satellite charging system includes a satellite power system 11, a carrying power system (not shown), a ground power system 30 and a contact satellite-borne connection system 40, wherein: the contact type satellite-borne connection system 40 is used for electrically connecting the satellite power supply system 11 with the carrier power supply system; the satellite power system 11, the carrier power system, and the ground power system 30 are configured as a first charging state connected in sequence, where the first charging state includes: the ground power system 30 supplies power to the carrying power system, the carrying power system supplies power to the satellite power system 11, and the contact type satellite-borne connection system 40 is in a conducting state; the satellite power system 11 and the onboard power system are further configured to a second charging state of interconnection, the second charging state comprising: the carrying power supply system supplies power to the satellite power supply system 11, and the contact type satellite-borne connection system 40 is in a conducting state; the satellite power system 11 is also configured in a self-powered state, which includes: the solar array 63 of the satellite 10 supplies power to the satellite power system 11, and the contact satellite-borne connection system 40 is in a disconnected state.

As shown in fig. 1, in the satellite seating and charging system, the launch vehicle 20 includes a release mechanism 21, in which: the release mechanism 21 is configured in an attached state comprising: the satellite 10 is fixed on the release mechanism 21; the release mechanism 21 is further configured to a release state, which includes: the satellite 10 disengages the release mechanism 21; the contact type satellite-borne connection system 40 comprises a first connection device 43 and a second connection device 44, wherein the first connection device 43 is fixed on the surface of the satellite 10, and the second connection device 44 is fixed on the surface of the release mechanism 21; the attachment state further includes: the first connecting device 43 is in pressure conduction with the second connecting device 44; the release state further comprises: said first connecting means 43 are disconnected from said second connecting means 44.

Specifically, in the satellite seat charging system, the release mechanism 21 includes a locking device, an initiating explosive device and an elastic device, wherein: the locking device is used for fixing the satellite 10 to the release mechanism 21; the initiating explosive device is used for destroying the locking device to enable the locking device to lose effectiveness; the elastic means are intended to provide a pushing force that pushes the satellite 10 away from the release mechanism 21.

As shown in fig. 2, in the satellite seat inflation system, the first connecting device 43 and the second connecting device 44 each include a compact structure 41, wherein: the compact structure 41 includes side ears and a connecting member, the two side ears are used for fixing the compact structure 41 on the surface of the satellite 10 or the surface of the release mechanism 21, and the connecting member protrudes between the two side ears to provide a hardware path for electrical connection; the side ear has a hole in the center for inserting a fixing bolt.

As shown in fig. 3, in the satellite seat inflation system, the second connecting device 44 further includes a spring plate 42 fixed to the compact structure 41, wherein: the spring plate 42 is of a U-shaped structure, one outer wall of the U-shaped structure is welded on the connecting piece of the pressing block structure 41 of the second connecting device 44, and the other outer wall of the U-shaped structure is pressed on the connecting piece of the pressing block structure 41 of the first connecting device 43; in the attached state, the height of the spring 42 is 5mm, and in the released state, the height of the spring 42 is 7 mm.

Further, in the satellite base charging system, the number of the first connecting devices 43 is plural, the number of the second connecting devices 44 is plural, and one first connecting device 43 corresponds to one second connecting device 44 to form one interface, so that plural interfaces are formed, for example, 4, 6, or 8 interfaces are formed, where: the plurality of interfaces include a power supply positive line interface (i.e., the charging positive line 64 shown in fig. 5), a power supply return line interface (i.e., the charging positive line 65 shown in fig. 5), and a plurality of data interfaces; the power supply positive line interface and the power supply return line interface are used for providing a loop for a satellite seat charging system; the data interface is used for receiving and transmitting the satellite test data in a downlink mode and receiving and transmitting the ground test instruction in an uplink mode.

As shown in fig. 1, in the satellite seat charging system, the satellite seat charging system includes a first cable assembly 51, a second cable assembly 52, a third cable assembly 53 and a fourth cable assembly 54, wherein: the first cable assembly 51 establishes an electrical connection between the satellite power system 11 and the first connection device 43; the second cable assembly 52 establishes an electrical connection between the second connecting device 44 and the onboard power system; the third cable assembly 53 establishes electrical connections inside the onboard power system; the fourth cable assembly 54 establishes an electrical connection between the onboard power system and the surface power system 30.

As shown in fig. 5, in the satellite seat charging system, the third cable assembly 53 is further coupled to a protection diode D4, wherein: the anode of the protection diode D4 is coupled to the ground power system 30, and the cathode of the protection diode D4 is coupled to the satellite power system 11. The satellite power system 11 includes a MOS transistor Q1, a first diode D1, a resistance-capacitance filter circuit, a battery V1, a second diode D2, and a switch K1, wherein: the second diode D2 is connected with the switch K1 in parallel and then is connected with the anode of the storage battery V1, one end of the resistance-capacitance filter circuit is connected with the cathode of the storage battery V1, and the other end of the resistance-capacitance filter circuit is connected with the anode of the second diode D2; the cathode of the first diode D1 is connected with the anode of the second diode D2, the anode of the first diode D1 is connected with one end of the source drain of the MOS tube Q1, and the other end of the drain of the MOS source Q1 is connected with the cathode of the storage battery V1; the anode of the first diode D1 is also connected to the cathode of the protection diode D4.

Specifically, in the satellite base charging system, the satellite power system 11 is further connected to the solar array 63, the anode of the solar array 63 is connected to the cathode of a third diode D3, the anode of the third diode D3 is connected to the cathode of the first diode D1, and the cathode of the solar array 63 is connected to the cathode of the battery V1; the interface also includes a ground analog array port 61 and a ground array loop line port 62.

In the satellite seat charging system provided by the present invention, in the ground test stage, the satellite power system 11, the carrier power system and the ground power system 30 are configured to be connected in sequence in a first seat charging state, the ground power system 30 supplies power to the carrier power system, the carrier power system supplies power to the satellite power system 11, the contact satellite-borne connection system 40 is in a conducting state, before transmission or when the satellite and the carrier are not separated during transmission, the satellite power system 11 and the carrier power system are further configured to be connected in a second seat charging state, the carrier power system supplies power to the satellite power system 11, the contact satellite-borne connection system 40 is in a conducting state, and after the satellite and the carrier are separated after transmission, the satellite power system 11 is further configured to be in a self-powered state, wherein the self-powered state includes: the solar array 63 of the satellite supplies power to the satellite power supply system 11, the contact type satellite-borne connection system 40 is in a disconnected state, the design scheme of a satellite surface contact type electrical connection mode (hereinafter referred to as a seat charging system) is achieved, the limitation of the traditional pulling-out and plugging-out operation is eliminated, and the convenience of satellite-rocket electrical connection is improved while the workload is reduced.

The invention provides a satellite seat charging system which can supply power and test for a satellite without depending on disconnection and insertion, and a carrier power supply system in a carrier rocket 20 provides electrical connection for the satellite. Before launching, the fourth cable assembly 54 connected with the ground power supply system 30 is pulled out by the carrier power supply system on the ground, after launching, the satellite is separated from the carrier rocket 20, and the contact type satellite-borne connection system 40 can be automatically disconnected, so that the personnel operation can be greatly reduced, and the safety and the reliability are further improved.

In the invention, in order to save the operation that an operator climbs up the launching tower to enter the fairing to pull out and remove the insertion, the contact connection is used for realizing the electrical conduction, and after the operation enters the track, the initiating explosive device of the release mechanism 21 is detonated, and the satellite 10 is released, namely the connection is disconnected. After the satellite 10 is mounted on the launch vehicle 20, it is necessary to perform testing and temporary state checking, and at this time, it is necessary to supply power to the entire satellite by an external power supply, and to perform both downlink reception of satellite data and uplink transmission of instructions. By combining the requirements, a seat charging system design scheme based on a pressing block structure and a carrying inner cable is provided. Furthermore, enough safety distance is reserved among a plurality of briquetting structures, physical contact is avoided, the risk of electricity crosstalk among the briquetting structures is avoided, and the safety of seat charging is further guaranteed.

In one embodiment of the invention, the satellite seat charging system mainly realizes the power supply and signal access by the spring plate 42, the pressing block structure 41 and the connecting cable assembly. The compact structure 41 is made of copper to ensure good electrical conductivity. The spring 42 is made of stainless steel to provide both elasticity and electrical conductivity. The principle of the whole satellite seat charging system is shown in fig. 1, which mainly includes: a cable 51 connected with a pressure block (satellite end) inside the satellite 10, a pressure block arranged on the surface of the satellite 10, a pressure block and connecting reed 42 arranged on the surface of a carrying releasing mechanism 21, a cable 52 connected with a pressure block (carrying end) inside the carrier rocket 20, a switching cable 53 inside the carrier rocket, and a cable 54 connected with a ground power supply system (star front end/energy front end) of the carrier rocket 20. The third cable assembly 53 is a standard adapter cable, and the contacts are adapted correspondingly to each other, so as to meet the requirements of different satellite models.

In one embodiment of the present invention, the connection between compacts is as shown in fig. 4. The number of the pressing block structures can be determined by self according to the requirements of power supply and data interfaces so as to adapt to different models, and the minimum requirement is 6 groups, namely two groups of power supply and four groups of data. According to the minimum requirement of the satellite tower test, the interface of the seat charging can be divided into a power supply interface and a data interface. The power supply interface comprises a power supply positive line and a power supply return line, the data interface comprises a data downlink interface and a command uplink interface, and for example, the RS422 data interface comprises a TX +, TX-, RX + and RX-four interfaces. Different interface paths can be used according to different satellite models.

Since the seat charger involves power supply and it is a critical path for testing and energy replenishment after satellite installation, reliability and safety design is required.

In one embodiment of the present invention, the present charging system is the minimum composition, and comprises twelve pressing blocks, wherein six pressing blocks are provided with spring plates 42, the spring plates 42 are mounted on the pressing blocks by welding, the pressing blocks are also mounted at the same positions outside the satellite structure, when the satellite is mounted on the release mechanism 21, the spring plates 42 are pressed, and thus the electrical connection between the satellite and the ground system can be realized. The height of the reeds 42 is about 7mm, and the height of the reeds 42 on the two sides is about 5mm after the reeds 42 are compressed, so that the reeds 42 can be guaranteed to be compressed, and damage to the reeds 42 due to over stress is avoided.

In one embodiment of the present invention, to ensure the safety of power supply, a protection diode D4 is added to the charging positive line 64 at the satellite power system side, as shown in fig. 3. Before launching, the fourth cable assembly 54 is pulled out by the carrier, but the satellite power supply system 11 is in a power-on state for the satellite storage battery V1, when the carrier rocket 20 is launched, the tail flame may melt the connection end of the third cable assembly 53 and the fourth cable assembly 54, and short circuits occur between the interfaces of the connection end, so that the internal electricity of the satellite cannot be conducted reversely due to the reverse cut-off characteristic of the protection diode D4, thereby ensuring the safety of power supply. The same is true when the redundant objects such as space debris contact the exposed pressure block on the surface of the satellite during the on-orbit operation of the satellite.

In summary, the above embodiments have described the satellite seat-charging system in detail, but it goes without saying that the present invention includes but is not limited to the configurations listed in the above embodiments, and any modifications based on the configurations provided by the above embodiments are within the scope of the present invention. One skilled in the art can take the contents of the above embodiments to take a counter-measure.

The above description is only for the purpose of describing the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention, and any variations and modifications made by those skilled in the art based on the above disclosure are within the scope of the appended claims.