阅读说明：本技术 卫星用星地太阳电池阵供电一体化设计系统及方法 (Satellite-ground solar cell array power supply integrated design system and method ) 是由 陈占胜 张朋松 王益军 邵陈懋 陈华 赵美玲 孙伟 于 2021-07-29 设计创作，主要内容包括：本发明提供了一种卫星用星地太阳电池阵供电一体化设计系统及方法,涉及卫星的供配电安全技术领域,该方法包括：卫星太阳电池阵、地面模拟阵、星表支架、星表功能插座、星表复合功能电缆、星表保护插头、电源控制器、脱分插脐带电缆以及功率传输电缆；其中,星表功能插座包括星表功能插座A、星表功能插座B以及星表功能插座C；均安装在星表支架上。本发明能够对于优化卫星电源控制器供电设计方案,提高太阳电池阵装星后测的试手段,优化卫星脱分插脐带电缆信号传输,降低电源控制器、低频电缆网重量,提高供配电安全性等有益效果。(The invention provides a satellite-ground solar cell array power supply integrated design system and method, and relates to the technical field of satellite power supply and distribution safety, wherein the method comprises the following steps: the system comprises a satellite solar cell array, a ground analog array, a star watch bracket, a star watch functional socket, a star watch composite functional cable, a star watch protective plug, a power supply controller, a disconnecting and plugging umbilical cable and a power transmission cable; the star watch functional socket comprises a star watch functional socket A, a star watch functional socket B and a star watch functional socket C; are all arranged on the star watch bracket. The invention has the advantages of optimizing the power supply design scheme of the satellite power supply controller, improving the test section of the solar cell array after satellite mounting, optimizing the signal transmission of the satellite de-distribution plugging umbilical cable, reducing the weight of the power supply controller and the low-frequency cable network, improving the power supply and distribution safety and the like.)

1. The utility model provides a satellite is with integration design system of star ground solar cell array power supply which characterized in that includes:

the system comprises a satellite solar cell array, a ground analog array, a star watch bracket, a star watch functional socket, a star watch composite functional cable, a star watch protective plug, a power supply controller, a disconnecting and plugging umbilical cable and a power transmission cable;

the star watch functional socket comprises a star watch functional socket A, a star watch functional socket B and a star watch functional socket C; the meter function socket A, the star meter function socket B and the star meter function socket C are all arranged on the star meter bracket;

the star watch composite functional cable is used for connecting star watch functional sockets; the star watch protection plug is used for protecting the star watch functional socket;

the satellite solar cell array is connected to the star watch functional socket A through a power transmission cable, the ground simulation array is connected to the star watch functional socket B through the power transmission cable, and the power supply controller is connected to the star watch functional socket C through the power transmission cable.

2. The satellite-earth solar cell array power supply integrated design system for the satellite according to claim 1, wherein the star-earth composite function cable can only realize the connection between a star-earth function socket A and a star-earth function socket C or between a star-earth function socket B and a star-earth function socket C at the same time, and the power supply of the satellite solar cell array and the ground analog array is switched through the star-earth composite function cable; when the star watch functional socket A is connected with the star watch functional socket C, the star watch protection plug realizes the protection of the star watch functional socket B; and the star watch functional socket B is connected with the star watch functional socket C in a time-sharing manner, and the star watch protection plug realizes the protection of the star watch functional socket A.

3. The satellite-earth solar cell array power supply integrated design system as claimed in claim 1, wherein the star watch functional socket and the star watch protection plug are power connectors meeting aerospace requirements.

4. The integrated design system for supplying power to the satellite earth and satellite solar battery array according to claim 1, wherein a star catalogue operation port is reserved according to the size of a star catalogue support during the design of the satellite, and is used for star catalogue operation during satellite testing and launching.

5. The satellite-earth solar cell array power supply integrated design system as claimed in claim 1, wherein the ground-earth pseudo-solar cell array can be directly connected with a star-watch function socket A to supply power to the power supply controller, or can be connected with a star-watch function socket C through a separate umbilical cable, and is connected to the star-watch function socket A through a star-watch composite function cable to supply power to the power supply controller.

6. The satellite-earth solar cell array power supply integrated design system for the satellite according to claim 1, wherein the setting of the number of the star table functional sockets can be set according to actual requirements of the satellite solar cell array, and safety needs to be considered in the design of positive lines and negative lines of the star table functional sockets;

the connector types and the contact arrangement of the star watch functional socket B and the star watch functional socket C are the same, the connector types of the star watch functional socket A are different from those of the star watch functional socket B and the star watch functional socket C, and the star watch functional socket A, the star watch functional socket B and the star watch functional socket C are all hole type sockets.

7. The integrated design system for supplying power to the satellite earth solar battery array is characterized in that the star surface protection plug is a pin type air plug and is subjected to potting treatment by GD414 or GD414C glue for spaceflight.

8. The integrated design system for supplying power to the satellite-earth solar cell array is characterized in that the star watch function socket A, the star watch function socket B and the star watch function socket C adopt J36A-52ZKL, J36A-62ZKL and J36A-74ZKL connectors, and the types of the star watch function socket A and the star watch function socket B are different from the type of the star watch function socket C.

9. The integrated design system for satellite-earth solar battery array power supply according to claim 1, wherein the ground is provided with a ground star watch protection plug and an indicator lamp, and the ground star watch protection plug and the indicator lamp are on after the star watch functional socket a, the star watch functional socket B and the star watch functional socket C are connected with the star watch composite functional cable.

10. A satellite-earth solar cell array power supply integrated design method, based on the satellite-earth solar cell array power supply integrated design system as claimed in any one of claims 1 to 9, comprising:

step S1: designing the number of the star watch functional sockets according to the number of the satellite power points, wherein the positive line and the negative line of the star watch functional sockets are designed to meet the isolation requirement;

step S2: designing a power cable for connecting a satellite solar cell array to a star catalogue functional socket A;

step S3: designing a power cable for connecting the power controller to the star catalogue functional socket C;

step S4: designing a power cable which is connected to the star watch functional socket B through an umbilical cord separation and insertion cable; the star watch functional socket A is completely the same as the star watch functional socket B; the ground analog array is directly connected to a power cable of the star watch functional socket C;

step S5: designing a star watch composite function cable, wherein a star watch composite function cable connector is matched with a star watch function socket C and a star watch function socket A;

step S6: designing a star surface protection plug, wherein the star surface protection plug is a needle type hollow plug, is subjected to potting treatment by GD414 or GD414C glue for spaceflight, and is matched with a star surface functional socket A or a star surface functional socket B;

step S7: respectively installing a star watch functional socket A, a star watch functional socket B and a star watch functional socket C on a star watch bracket;

step S8: when the ground analog array supplies power, the connection between the star table functional socket B and the star table functional socket C is completed through the star table composite functional cable, so that the ground analog array supplies power to the on-satellite power supply controller, and meanwhile, a star table protective plug is plugged into the star table functional socket A, so that the protection of the star table functional socket A is realized;

step S9: when the satellite solar cell array supplies power, the connection between the star watch functional socket A and the star watch functional socket C is completed through the star watch composite functional cable, so that the power supply of the satellite solar cell array to the star power supply controller is realized, and meanwhile, a star watch protection plug is plugged into the star watch functional socket B, so that the protection of the star watch functional socket B is realized.

Technical Field

The invention relates to the technical field of satellite power supply and distribution safety, in particular to a satellite earth solar battery array power supply integrated design system and method.

Background

The current satellite power supply mode is that the solar cell array power supply and the ground simulation array power supply are separately arranged, on one hand, the satellite solar cell array is connected to the power supply controller through a power cable, and on the other hand, the ground simulation array is connected to the power supply controller through a separate-plug satellite umbilical cable. The power supply controller is internally provided with a solar cell array power supply interface and a ground analog array power supply interface, the power supply interface is complex, no corresponding power supply isolation measure is provided, and the weight is heavier. Because the separate-plug cable is exposed on the surface of the satellite after the satellite and the arrow are separated, the satellite can be in short circuit when the satellite and the arrow are separated or after the satellite and the arrow are separated, and the analysis of the emission loss of a certain satellite clearly indicates that the separate-plug umbilical cable of the satellite can be one of the reasons for short circuit of the whole satellite bus and further satellite failure.

When the satellite solar cell array supplies power, the power output of the solar cell array is directly connected to the power supply controller through the driving mechanism, and the solar cell array cannot be tested after the solar cell array is assembled and connected in the power supply mode; when the ground simulation array supplies power, the ground simulation array power is connected to the power control through the separation and insertion cable, the power supply mode increases the complexity of the separation and insertion cable design, increases the weight, has potential safety hazards of power supply and distribution when the separation and insertion is carried out, and meanwhile, the number of power supply power contacts is large, more separation and insertion resources are occupied, and the test requirements of other systems or single units cannot be met. With increasingly strict constraint conditions of satellite design, the weight, test and other resources are increasingly tense, the safety requirement is enhanced, and the design of light weight, integration, testability and high safety becomes a necessity of satellite design.

In the existing related patents related to spacecraft energy balance design, the invention patent with the publication number of CN104269915A discloses a multi-solar-array unified regulation control method, which teaches a multi-solar-array unified regulation control method but does not relate to power supply integrated design; the invention patent with the publication number of CN108802534A discloses a method for testing the performance of a transmission channel of a solar array driving mechanism, which teaches a method for testing the performance of the transmission channel of the solar array driving mechanism and focuses on the introduction of the test method; the invention with the publication number of CN107329493A discloses a double-wing sun array sun-facing directional driving device applied to a networking small satellite, and teaches the double-wing sun array sun-facing directional driving device, and does not relate to power supply integration.

Disclosure of Invention

Aiming at the defects in the prior art, the invention provides a satellite-ground solar cell array power supply integrated design system and method.

According to the satellite-ground solar cell array power supply integrated design system and method provided by the invention, the scheme is as follows:

in a first aspect, a satellite-ground solar cell array power supply integrated design system is provided, the system includes:

the system comprises a satellite solar cell array, a ground analog array, a star watch bracket, a star watch functional socket, a star watch composite functional cable, a star watch protective plug, a power supply controller, an umbilical cord add-drop cable and a power transmission cable;

the star watch functional socket comprises a star watch functional socket A, a star watch functional socket B and a star watch functional socket C; the meter function socket A, the star meter function socket B and the star meter function socket C are all arranged on the star meter bracket;

the star watch composite functional cable is used for connecting star watch functional sockets; the star watch protection plug is used for protecting the star watch functional socket;

the satellite solar cell array is connected to the star watch functional socket A through a power transmission cable, the ground simulation array is connected to the star watch functional socket B through the power transmission cable, and the power supply controller is connected to the star watch functional socket C through the power transmission cable.

Preferably, the star watch composite function cable can only realize the connection of the star watch function socket A and the star watch function socket C or the connection of the star watch function socket B and the star watch function socket C at the same time, and the power supply of the satellite solar cell array and the ground analog array realizes the switching through the star watch composite function cable; when the star watch functional socket A is connected with the star watch functional socket C, the star watch protection plug realizes the protection of the star watch functional socket B; and the star watch functional socket B is connected with the star watch functional socket C in a time-sharing manner, and the star watch protection plug realizes the protection of the star watch functional socket A.

Preferably, the star watch functional socket and the star watch protection plug are power type connectors meeting the aerospace requirement.

Preferably, a star catalogue operation port is reserved according to the size of a star catalogue support during satellite design and is used for star catalogue operation during satellite testing and launching.

Preferably, the ground pseudomorphic array can be directly connected with the star watch functional socket A to supply power to the power supply controller, or can be connected with the star watch functional socket C through a de-plugging umbilical cable and connected to the star watch functional socket A through a star watch composite functional cable to supply power to the power supply controller.

Preferably, the setting of the number of the star watch functional sockets can be set according to the actual requirements of the satellite solar cell array, and the safety of the design of the positive line and the negative line of the star watch functional sockets needs to be considered;

the connector types and the contact arrangement of the star watch functional socket B and the star watch functional socket C are the same, the connector types of the star watch functional socket A are different from those of the star watch functional socket B and the star watch functional socket C, and the star watch functional socket A, the star watch functional socket B and the star watch functional socket C are all hole type sockets.

Preferably, the star surface protection plug is a pin type hollow plug and is subjected to potting treatment by GD414 or GD414C glue for spaceflight.

Preferably, the star watch function socket A, the star watch function socket B and the star watch function socket C are selected from J36A-52ZKL, J36A-62ZKL and J36A-74ZKL connectors, and the types of the star watch function socket A and the star watch function socket B are different from the type of the star watch function socket C.

Preferably, a ground star watch protection plug is required to be provided with an indicator lamp, and the ground star watch protection plug is provided with the indicator lamp when the star watch functional socket A, the star watch functional socket B and the star watch functional socket C are connected with the star watch composite functional cable.

In a second aspect, a satellite-ground solar cell array power supply integrated design method is provided, and the method includes:

step S1: designing the number of the star watch functional sockets according to the number of the satellite power points, wherein the positive line and the negative line of the star watch functional sockets are designed to meet the isolation requirement;

step S2: designing a power cable for connecting a satellite solar cell array to a star catalogue functional socket A;

step S3: designing a power cable for connecting the power controller to the star catalogue functional socket C;

step S4: designing a power cable which is connected to the star watch functional socket B through an umbilical cord separation and insertion cable; the star watch functional socket A is completely the same as the star watch functional socket B; the ground analog array is directly connected to a power cable of the star watch functional socket C;

step S5: designing a star watch composite function cable, wherein a star watch composite function cable connector is matched with a star watch function socket C and a star watch function socket A;

step S6: designing a star surface protection plug, wherein the star surface composite plug is a needle type hollow plug, is subjected to potting treatment by GD414 or GD414C glue for spaceflight, and is matched with a star surface functional socket A or a star surface functional socket B;

step S7: respectively installing a star watch functional socket A, a star watch functional socket B and a star watch functional socket C on a star watch bracket;

step S8: when the ground analog array supplies power, the connection between the star table functional socket B and the star table functional socket C is completed through the star table composite functional cable, so that the ground analog array supplies power to the on-satellite power supply controller, and meanwhile, a star table protective plug is plugged into the star table functional socket A, so that the protection of the star table functional socket A is realized;

step S9: when the satellite solar cell array supplies power, the connection between the star watch functional socket A and the star watch functional socket C is completed through the star watch composite functional cable, so that the power supply of the satellite solar cell array to the star power supply controller is realized, and meanwhile, a star watch protection plug is plugged into the star watch functional socket B, so that the protection of the star watch functional socket B is realized.

Compared with the prior art, the invention has the following beneficial effects:

1. the invention improves the test section of the solar cell array after the satellite is assembled for optimizing the power supply design scheme of the satellite power supply controller;

2. the invention optimizes the signal transmission of the satellite separation plugging umbilical cable, reduces the weight of the power supply controller and the low-frequency cable network, improves the power supply and distribution safety and the like.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

FIG. 1 is a schematic block diagram of a power supply access method for an original satellite solar cell array and a ground simulation array;

FIG. 2 is a schematic block diagram of an optimized method for implementing a power supply path of a solar cell array according to the present invention;

FIG. 3 is a schematic block diagram of a first method for implementing a power supply path of a ground analog array according to the present invention;

fig. 4 is a schematic block diagram of a second ground analog array power supply path implementation method after optimization.

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.

The embodiment of the invention provides a satellite-ground solar battery array power supply integrated design system, which specifically comprises: the system comprises a satellite solar cell array, a ground analog array, a star watch bracket, a star watch functional socket, a star watch composite functional cable, a star watch protective plug, a power supply controller, an umbilical cord add-drop cable and a power transmission cable;

the star watch functional socket comprises a star watch functional socket A, a star watch functional socket B and a star watch functional socket C; the meter function socket A, the star meter function socket B and the star meter function socket C are all arranged on the star meter bracket; the star watch compound function cable comprises 1 star watch compound function cable and 1 star watch protection plug.

The star watch composite functional cable is used for connecting the star watch functional sockets; the star watch protection plug is used for protecting the star watch functional socket;

the satellite solar cell array is connected to the star watch functional socket A through a power transmission cable, the ground simulation array is connected to the star watch functional socket B through the power transmission cable, and the power supply controller is connected to the star watch functional socket C through the power transmission cable.

The star watch composite functional cable can only realize the connection of a star watch functional socket A and a star watch functional socket C or the connection of a star watch functional socket B and the star watch functional socket C at the same time, and the power supply of the satellite solar cell array and the ground analog array realizes the switching through the star watch composite functional cable; when the star watch functional socket A is connected with the star watch functional socket C, the star watch protection plug realizes the protection of the star watch functional socket B; and the star watch functional socket B is connected with the star watch functional socket C in a time-sharing manner, and the star watch protection plug realizes the protection of the star watch functional socket A.

The star watch functional socket and the star watch protection plug are power type connectors meeting the aerospace requirement, and preferably series power type connectors such as J36A and J6W are selected.

A star watch operation port is reserved according to the size of a star watch support during satellite design and is used for star watch operation during satellite testing and launching.

The ground pseudo-array can be directly connected with the star watch functional socket A to actually supply power to the power supply controller, or can be connected with the star watch functional socket C through a disconnecting and plugging umbilical cable and connected to the star watch functional socket A through a star watch composite functional cable to realize power supply to the power supply controller.

The quantity of the star watch functional sockets can be set according to the actual requirements of the satellite solar cell array, and the safety of the positive line and the negative line of the star watch functional sockets needs to be considered in design;

the connector types and the contact arrangement of the star watch functional socket B and the star watch functional socket C are completely consistent, the connector types of the star watch functional socket A are different from those of the star watch functional socket B and the star watch functional socket C, and the star watch functional socket A, the star watch functional socket B and the star watch functional socket C are all hole type sockets.

The star surface protection plug is a pin type hollow plug and is encapsulated by GD414 or GD414C glue for spaceflight.

And a ground star watch protection plug is required to be provided with an indicator lamp, and the indicator lamp is on when the star watch functional socket A, the star watch functional socket B and the star watch functional socket C are connected with the star watch composite functional cable.

The star watch support is arranged on a satellite instrument board, the star watch support is made of 2A14T651, the star watch functional socket and the star watch protection plug are power type connectors meeting the aerospace requirement, and J36A series power type connectors are preferably selected.

After the satellite solar cell array is assembled, the solar cell array electrical performance can be tested through the star watch functional socket A.

When the satellite is designed, a star watch operation port is reserved according to the size of the cable support and is used for star watch operation during satellite testing and launching.

The rocket fairing is designed to be provided with an operation opening for star catalogue operation of the launching tower of the launching field.

The invention also provides a satellite-ground solar cell array power supply integrated design method, which comprises the following steps:

step S1: designing the number of the star watch functional sockets according to the number of the satellite power points, wherein the positive line and the negative line of the star watch functional sockets are designed to meet the isolation requirement;

the star watch functional socket A, the star watch functional socket B and the star watch functional socket C are connectors J36A-52ZKL, J36A-62ZKL and J36A-74ZKL, and the types of the star watch functional socket A and the star watch functional socket B are different from the type of the star watch functional socket C.

Step S2: designing a power cable for connecting a satellite solar cell array to a star catalogue functional socket A;

step S3: designing a power cable for connecting the power controller to the star catalogue functional socket C;

step S4: designing a power cable which is connected to the star watch functional socket B through an umbilical cord separation and insertion cable; the star watch functional socket A is completely the same as the star watch functional socket B; the ground analog array is directly connected to a power cable of the star watch functional socket C;

step S5: designing a star watch composite function cable, wherein a star watch composite function cable connector is matched with a star watch function socket C and a star watch function socket A (a star watch function socket B);

step S6: designing a star surface protection plug, wherein the star surface composite plug is a needle type hollow plug, is subjected to potting treatment by GD414 or GD414C glue for spaceflight, and is matched with a star surface functional socket A (a star surface functional socket B);

step S7: respectively installing a star watch functional socket A, a star watch functional socket B and a star watch functional socket C on a star watch bracket;

step S8: when the ground analog array supplies power, the connection between the star table functional socket B and the star table functional socket C is completed through the star table composite functional cable, so that the ground analog array supplies power to the on-satellite power supply controller, and meanwhile, a star table protective plug is plugged into the star table functional socket A, so that the protection of the star table functional socket A is realized;

step S9: when the satellite solar cell array supplies power, the connection between the star watch functional socket A and the star watch functional socket C is completed through the star watch composite functional cable, so that the power supply of the satellite solar cell array to the star power supply controller is realized, and meanwhile, a star watch protection plug is plugged into the star watch functional socket B, so that the protection of the star watch functional socket B is realized.

Next, the present invention will be described in more detail.

As shown in fig. 1, the power supply method for the original satellite solar cell array and the ground simulation array is that the satellite solar cell array is directly connected to a power supply controller; the ground analog array power supply is connected to the power supply controller through the add-drop, and generally, the ground analog array power supply occupies an add-drop contact, so that the problems of add-drop, add-drop resource waste, weight increase, signal interference of other systems caused by high-power long-distance transmission and the like are caused; the power supply controller needs to be provided with a solar battery array and a ground simulation array power plug at the same time, so that the problems of contact waste, weight increase, unreasonable structural layout and the like of the power supply controller are caused.

A satellite-ground solar cell array power supply integrated design system and method comprises the following steps: the system comprises a satellite solar cell array, a ground simulation array, a star watch bracket, a star watch functional socket, a star watch composite functional cable, a star watch protective plug, a power supply controller, an umbilical cord add-drop cable and a power transmission cable;

referring to fig. 2, the solar cell array power supply implementation manner: the satellite solar battery array is connected to the star watch functional socket A through a power transmission cable, the star watch functional socket A is connected with the star watch functional socket C through a star watch composite functional cable in a switching mode, then the solar battery array power is input to the power supply controller, and at the moment, the star watch functional socket B is protected through a star watch protection plug.

Referring to fig. 3, a power supply method 1 of the ground analog array power supply system: the ground analog array power supply system is connected to the star watch functional socket B through a separation and insertion umbilical cable, the switching between the star watch functional socket B and the star watch functional socket C is achieved through a star watch composite functional cable, then the ground analog array power is input to the power supply controller, and at the moment, the protection of the star watch functional socket A is achieved through a star watch protection plug.

Referring to fig. 4, a ground analog array power supply system power supply method 2: the ground analog array power supply system is directly connected to the star watch functional socket C, the ground analog array power is input to the power supply controller, and the star watch functional socket A is protected through the star watch protection plug.

In the state of fig. 2, the satellite solar cell array is provided with satellites, and the electrical performance inspection of the satellite-provided solar cell array can be realized through the star watch functional socket a.

In the states of fig. 2 and fig. 3, the correctness of cable connection can be checked by plugging an indicator lamp into a star watch plug arranged on the ground, and the same applies in the state of fig. 4.

The star watch functional socket A and the star watch functional socket B are only connected with one functional socket and a star watch composite functional cable at the same time, and the other functional socket is connected with a star watch protection plug, so that the state that a star watch connector is exposed in space does not exist in any state, and the problem of satellite failure caused by the fact that an umbilical cable is exposed when a satellite is disconnected and plugged is completely solved.

The embodiment of the invention provides a satellite-ground solar cell array power supply integrated design system and method, aiming at optimizing a power supply design scheme of a satellite power supply controller, improving a test means after a solar cell array is assembled into a satellite, optimizing satellite de-plugging signal transmission, reducing the weight of the power supply controller and a low-frequency cable network, improving power supply and distribution safety and the like.

Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, units provided by the present invention as pure computer readable program code, the system and its various devices, modules, units provided by the present invention can be fully implemented by logically programming method steps in such a manner as to implement the same functions in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system and various devices, modules and units thereof provided by the invention can be regarded as a hardware component, and the devices, modules and units included in the system for realizing various functions can also be regarded as structures in the hardware component; means, modules, units for performing the various functions may also be regarded as structures within both software modules and hardware components for performing the method.

The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.