Integrated electronic management system for miniature Mars lander

A management system and integrated electronics technology, applied in the field of integrated electronic management systems, can solve the problems of electronic equipment management systems such as weight, volume, and power consumption restrictions, and achieve the effects of low weight, high space utilization, and low power consumption

Active Publication Date: 2013-11-20
SHANGHAI SATELLITE ENG INST
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Problems solved by technology

The weight, volume, and power consumption restrictions of the electronic equipment management system in the lander are more stringent

Method used

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  • Integrated electronic management system for miniature Mars lander
  • Integrated electronic management system for miniature Mars lander

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Embodiment Construction

[0022] The embodiments of the present invention are described in detail below: the present embodiment implements under the premise of the technical solution of the present invention, provides detailed implementation and specific operation process, but protection scope of the present invention is not limited to the following implementation example.

[0023] Such as figure 1 As shown, this embodiment provides an integrated electronic management system for a small Mars lander, including a central management module 3, an internal and external power conversion module 1, a pyrotechnic detonation module 2, a power supply control module 4 and a connector module 5 ,in:

[0024] - The central management module 3 is respectively connected to the internal and external power conversion module 1, the pyrotechnic detonation module 2 and the power supply control module 4 for signal connection, through the lander status sensor data exchanged with the lander's detector platform system, the lan...

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Abstract

The invention discloses an integrated electronic management system for a miniature Mars lander. The function composition of the integrated electronic management system comprises an internal and external electricity conversion module, an initiating explosive device detonation module, a power supply control module, a central management module and a connector assembly module, wherein the internal and external electricity conversion module is used for realizing switching control for an external power supply circuit and an internal power supply circuit of the lander; the initiating explosive device detonation module is used for realizing unlocking control for mechanism expansion, back-stepping braking and the like in the processes of entering, descending and landing of the lander; the power supply control module is used for realizing power supply control for an internal sensor, a communication unit, a heater and the like of the lander; the central management module is used for realizing functions such as program control in the landing process of the lander, internal bus communication, remote measurement signal acquisition, scientific data collection, data nonvolatile storage and the like; and the connector assembly module is used for realizing electrical connection between the management system and other electronic equipment in the lander. The integrated electronic management system has the characteristics of low weight, low power consumption and high space utilization rate, and solves a miniature and integrated design problem of the Mars miniature lander electronic system.

Description

technical field [0001] The invention relates to the technical field of lander managers, in particular to an integrated electronic management system for small Mars landers. Background technique [0002] my country plans to launch an independent Mars probe in 2015 to realize Mars orbit, carry out Mars global remote sensing exploration, and at the same time carry out Mars landing verification missions to verify Mars entering deceleration landing related technologies. Due to the constraints of the launch window and the existing carrying capacity, the Mars Global Remote Sensing Probe has more stringent constraints on weight and power consumption than previous satellite models. The total weight of the detector cannot exceed 2340kg. Among them, the weight of the landing probe cannot exceed 60kg, which is less than one-tenth of the weight of the lightest Mars lander in the United States. The weight, volume, and power consumption restrictions of the electronic equipment management ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B19/04
CPCY02P90/02
Inventor 施伟璜马彦涵牛俊坡朱新波
Owner SHANGHAI SATELLITE ENG INST
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