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A satellite on-orbit reconfiguration framework system and method

A frame system and micro-satellite technology, applied in the field of aerospace, can solve problems such as weak software adaptability and inability to effectively meet demand changes in the late stage of satellite development or in orbit, and achieve the effect of meeting demand changes and improving software adaptability

Active Publication Date: 2018-05-25
AEROSPACE DONGFANGHONG DEV LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0010] The purpose of the embodiments of the present invention is to provide a satellite on-orbit reconfiguration framework system to solve the problem that the software in the prior art has weak adaptability and cannot effectively meet the needs of the satellite in the later stage of development or during the orbit.

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  • A satellite on-orbit reconfiguration framework system and method
  • A satellite on-orbit reconfiguration framework system and method
  • A satellite on-orbit reconfiguration framework system and method

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Embodiment 1

[0041] Such as figure 1 Shown is the satellite on-orbit reconstruction framework system provided by the embodiment of the present invention, the system includes an application layer, a system interface layer and a port driver layer, wherein:

[0042] The application layer includes a plurality of application layer modules, and each application layer module has a standardized external interface; the specific interface includes: an initialization interface, a module instruction processing interface and a module main program interface; wherein: the initialization interface is responsible for initializing the module; instruction processing The interface is responsible for processing the relevant instructions of the module; the main program of the module completes the actual function of the module.

[0043] The port driver layer includes a plurality of external software and hardware interface modules, each external software and hardware interface module has a standardized external i...

Embodiment 2

[0052] The satellite on-orbit reconfiguration framework method provided by the second embodiment of the present invention is based on the satellite on-orbit reconfiguration framework system, and the system includes an application layer, a system interface layer and a port driver layer, wherein:

[0053] The application layer includes a plurality of application layer modules, the application layer modules can be used to complete various specific functions of the on-board software, and each application layer module has a standardized external interface;

[0054] The system interface layer includes a core scheduling layer, a data exchange layer, a first interface form and a second interface form; wherein: the first interface form stores the standardized external interface address and each parameter address of each application layer module; the second The second interface form stores the standardized external interface address of each port driver layer module; the core scheduling l...

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Abstract

The present invention is applicable to the aerospace field, and provides a system and method for micro-satellite on-orbit reconfiguration framework. The system includes an application layer, a system interface layer, and a port driver layer. The system interface layer includes a core scheduling layer, a data exchange layer, and a layer, the first interface form and the second interface form; the core scheduling layer calls and runs the corresponding application layer module in the application layer through the first interface form; the data exchange layer inputs the external data of the application layer through the second interface form The output request is forwarded to the corresponding port driver layer interface module. Because in the embodiment of the present invention, the address of the corresponding application layer module or port driver layer module can be called, modified or adjusted through the first and second interface forms, the software can be reconfigured on the track, the adaptability of the software can be significantly improved, and the Demand changes in the late stage of satellite development or during orbit.

Description

technical field [0001] The invention belongs to the aerospace field, and in particular relates to an on-orbit reconfiguration framework system and method for a tiny satellite. Background technique [0002] In the current micro-satellite research and development model, on-board software is developed in accordance with software engineering requirements, and together with the entire satellite, it is tested, launched, and in-orbit as a whole. Currently, satellite on-orbit mission updates are implemented through code annotations, and the main implementation methods include: [0003] 1. Note on the software code as a whole [0004] During the operation of the satellite in orbit, the ground will inject the modified and recompiled entire software code onto the satellite through the high-speed uplink channel, and jump the current software operation to the above-mentioned software operation through instructions, and the original software will be discarded. [0005] 2. Use the hook f...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F8/35
Inventor 刘宽俊薛力军寇义民潘乐尚华于小龙何峰庄武祥黄宇栋张莹
Owner AEROSPACE DONGFANGHONG DEV LTD
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