CN103412569A - Mars capture process autonomous management method - Google Patents
Mars capture process autonomous management method Download PDFInfo
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- CN103412569A CN103412569A CN2013102916446A CN201310291644A CN103412569A CN 103412569 A CN103412569 A CN 103412569A CN 2013102916446 A CN2013102916446 A CN 2013102916446A CN 201310291644 A CN201310291644 A CN 201310291644A CN 103412569 A CN103412569 A CN 103412569A
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Abstract
The invention discloses a Mars capture process autonomous management method which comprises a Mars detector rover Mars capture former management series, a Mars detector Mars capture process management series and a Mars detector Mars capture later management series which are used for managing an attitude control subsystem, a power supply subsystem, an integrated electronic subsystem and a measurement and control data transmission subsystem. Through the rational planning of detector management events before capture, in the capture and after the capture, through the multidisciplinary design optimization of energy, communication, attitude, lighting and the like, a completed capture process autonomous management series is established, and the autonomous management of the detector capture process is realized.
Description
Technical field
The present invention relates to spacecraft autonomous management method, be specifically related to a kind of autonomous management method in Mars probes Mars acquisition procedure.
Background technology
The section of catching is that entirely fire shifts a most key link in flight course, and acquisition procedure has determined the success or failure of mars exploration task.The section of catching is defined as detector to be affected ball and starts to the flight course of igniting till end of braking from entering Mars.After nineteen ninety, in the mars exploration task that completes earth escape, failed has 5 times, and the section of catching has accounted for 4 times.The section of catching ground observing and controlling time delay is large, control accuracy requires high and chance is unique, and ground observing and controlling is difficult to meet detector in the requirement of target acquistion section to navigation accuracy and real-time, the most urgent to autonomous demand for control.Yet target acquistion section space environment X factor is many, device carries resource-constrained, adaptability, independence and the fault-tolerance of detector navigational system all proposed to challenge.Need to formulate for above-mentioned situation the method for an applicable mars exploration acquisition procedure autonomous management.
Summary of the invention
For the technical matters existed in above-mentioned prior art, the invention provides a kind of Mars acquisition procedure autonomous management method, realize that Mars probes complete Mars and catch task.
For achieving the above object, the technical solution adopted in the present invention is as follows:
A kind of Mars acquisition procedure autonomous management method comprises:
Mars probes Mars is caught front supervisory sequence, Mars probes Mars acquisition procedure supervisory sequence, Mars probes Mars and is caught rear supervisory sequence, for rail control subsystem, power subsystem, integrated electronics subsystem, observing and controlling data transmission subsystem are managed, specific as follows:
Described Mars probes Mars is caught front supervisory sequence: number passes data end of transmission empty storage space over the ground, stop load data collecting-caught first 3 to 5 days, ground system for the first time upper annotate adjust parameter-detector controls attitude and power system according to most recent parameters, approach capture point-caught first 1 to 2 day, ground system for the second time upper annotate adjust parameter-detector controls attitude and power system according to most recent parameters, afterwards in closure detector except catch control other required electronic equipments-communicate the antenna switching, by high-gain aerial switch to low-gain antenna-start the inertial navigation combination, set up firing attitude-adjust the sun wing and point to,
Described Mars probes Mars acquisition procedure supervisory sequence is: the instruction sequence that the rail control subsystem is uploaded according to ground, and start the rail control engine and carry out retarding braking, until meet cut-off condition, close the rail control engine and finish; Power subsystem is load supplying by the electric discharge regulator; The observing and controlling data transmission subsystem by low-gain antenna to underground biography real-time telemetry parameter; The integrated electronics subsystem is controlled the sun wing and is kept fixing;
Described Mars probes Mars is caught rear supervisory sequence: catch the sun-adjust detector and point to attitude, set up firing attitude-by low-gain antenna switch to high-gain aerial-open before catching the electronic equipment of closing-restart that load data is collected and management.
The present invention by before catching, acquisition procedure and catch after the detector Admin Events make rational planning for, Multidisciplinary Optimization by aspects such as the detector energy, communication, attitude, illumination, set up complete acquisition procedure autonomous management sequence, thereby realize the autonomous management of detector acquisition procedure.
The accompanying drawing explanation
Fig. 1 is that flight course figure is caught in the Mars probes braking;
Fig. 2 is Mars probes braking acquisition procedure autonomous management task sequence schematic diagram.
Embodiment
The present invention is further detailed explanation below in conjunction with accompanying drawing.
As shown in Figure 1, the Mars probes section of catching is defined as detector affects ball and starts to the flight course of igniting till end of braking from entering Mars.Braking is caught front detector along the flight of the hyperbolic orbit with areocentric, and dotted line is to catch the motor-driven track of braking orbit, and braking is caught rear detector and entered the ring fire elliptical orbit.In Fig. 1-V speed increment direction while being depicted as retrofiring.
As shown in Figure 2, Mars probes braking acquisition procedure autonomous management task sequence comprises: Mars probes Mars is caught front supervisory sequence, Mars probes Mars acquisition procedure supervisory sequence, Mars probes Mars is caught rear supervisory sequence, and three supervisory sequences are for the regulatory requirement to rail control subsystem, power subsystem, integrated electronics subsystem, observing and controlling data transmission subsystem.
Mars probes Mars is caught front supervisory sequence: number passes data end of transmission empty storage space over the ground, stop load data collecting-caught first 3 to 5 days, ground system for the first time upper annotate adjust parameter-detector controls attitude and power system according to most recent parameters, approach capture point-caught first 1 to 2 day, ground system for the second time upper annotate adjust parameter-detector controls attitude and power system according to most recent parameters, afterwards in closure detector except catch control other required electronic equipments-communicate the antenna switching, by high-gain aerial switch to low-gain antenna-start the inertial navigation combination, set up firing attitude-adjust the sun wing and point to.
Mars probes Mars acquisition procedure supervisory sequence is: the instruction sequence that the rail control subsystem is uploaded according to ground, and start the rail control engine and carry out retarding braking, until meet cut-off condition, close the rail control engine and finish; Power subsystem is load supplying by the electric discharge regulator; Tracking-telemetry and command subsystem by low-gain antenna to underground biography real-time telemetry parameter; The integrated electronics subsystem is controlled the sun wing and is kept fixing.
Mars probes Mars is caught rear supervisory sequence: catch the sun-adjust detector and point to attitude, set up firing attitude-by low-gain antenna switch to high-gain aerial-open before catching the electronic equipment of closing-restart that load data is collected and management.
Claims (1)
1. Mars acquisition procedure autonomous management method is characterized in that: comprising:
Mars probes Mars is caught front supervisory sequence, Mars probes Mars acquisition procedure supervisory sequence, Mars probes Mars and is caught rear supervisory sequence, for rail control subsystem, power subsystem, integrated electronics subsystem, observing and controlling data transmission subsystem are managed, specific as follows:
Described Mars probes Mars is caught front supervisory sequence: number passes data end of transmission empty storage space over the ground, stop load data collecting-caught first 3 to 5 days, ground system for the first time upper annotate adjust parameter-detector controls attitude and power system according to most recent parameters, approach capture point-caught first 1 to 2 day, ground system for the second time upper annotate adjust parameter-detector controls attitude and power system according to most recent parameters, afterwards in closure detector except catch control other required electronic equipments-communicate the antenna switching, by high-gain aerial switch to low-gain antenna-start the inertial navigation combination, set up firing attitude-adjust the sun wing and point to,
Described Mars probes Mars acquisition procedure supervisory sequence is: the instruction sequence that the rail control subsystem is uploaded according to ground, and start the rail control engine and carry out retarding braking, until meet cut-off condition, close the rail control engine and finish; Power subsystem is load supplying by the electric discharge regulator; The observing and controlling data transmission subsystem by low-gain antenna to underground biography real-time telemetry parameter; The integrated electronics subsystem is controlled the sun wing and is kept fixing;
Described Mars probes Mars is caught rear supervisory sequence: catch the sun-adjust detector and point to attitude, set up firing attitude-by low-gain antenna switch to high-gain aerial-open before catching the electronic equipment of closing-restart that load data is collected and management.
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105509750A (en) * | 2015-11-27 | 2016-04-20 | 上海卫星工程研究所 | Astronomical velocity measurement and ground radio combined Mars acquisition phase navigation method |
| CN106292332A (en) * | 2016-09-08 | 2017-01-04 | 上海卫星工程研究所 | Detachable detector based on drag measurement pneumatic capture method of guidance |
| CN106773671A (en) * | 2016-11-21 | 2017-05-31 | 上海卫星工程研究所 | Deep space probe MDO methods stage by stage |
| CN107831809A (en) * | 2017-09-25 | 2018-03-23 | 上海卫星工程研究所 | Method is managed independently in thermal control suitable for mars exploration |
| CN111301719A (en) * | 2020-03-04 | 2020-06-19 | 上海航天控制技术研究所 | Autonomous planning and executing method suitable for Mars detection flight control task |
| CN111319794A (en) * | 2020-02-25 | 2020-06-23 | 上海航天控制技术研究所 | Propelling autonomous fault processing method suitable for Mars detection brake capture period |
| CN111319791A (en) * | 2020-02-28 | 2020-06-23 | 上海航天控制技术研究所 | Attitude control mode management method suitable for Mars detection |
| CN111414002A (en) * | 2020-02-26 | 2020-07-14 | 上海航天控制技术研究所 | Mars detector secondary braking capture control method based on Newton iteration |
| CN111891402A (en) * | 2020-06-30 | 2020-11-06 | 上海航天控制技术研究所 | Mars detection ground antenna pointing recovery method based on autonomous maneuvering |
| CN114526647A (en) * | 2022-04-24 | 2022-05-24 | 北京宇航系统工程研究所 | Precise control method for launch orbit of carrier rocket running fire |
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105509750A (en) * | 2015-11-27 | 2016-04-20 | 上海卫星工程研究所 | Astronomical velocity measurement and ground radio combined Mars acquisition phase navigation method |
| WO2017088352A1 (en) * | 2015-11-27 | 2017-06-01 | 上海卫星工程研究所 | Astronomical velocity measurement and ground radio based mars capture phase navigation method |
| CN106292332A (en) * | 2016-09-08 | 2017-01-04 | 上海卫星工程研究所 | Detachable detector based on drag measurement pneumatic capture method of guidance |
| CN106773671A (en) * | 2016-11-21 | 2017-05-31 | 上海卫星工程研究所 | Deep space probe MDO methods stage by stage |
| CN106773671B (en) * | 2016-11-21 | 2019-08-23 | 上海卫星工程研究所 | Deep space probe MDO method stage by stage |
| CN107831809A (en) * | 2017-09-25 | 2018-03-23 | 上海卫星工程研究所 | Method is managed independently in thermal control suitable for mars exploration |
| CN111319794B (en) * | 2020-02-25 | 2021-10-01 | 上海航天控制技术研究所 | Propelling autonomous fault processing method suitable for Mars detection brake capture period |
| CN111319794A (en) * | 2020-02-25 | 2020-06-23 | 上海航天控制技术研究所 | Propelling autonomous fault processing method suitable for Mars detection brake capture period |
| CN111414002A (en) * | 2020-02-26 | 2020-07-14 | 上海航天控制技术研究所 | Mars detector secondary braking capture control method based on Newton iteration |
| CN111414002B (en) * | 2020-02-26 | 2023-06-06 | 上海航天控制技术研究所 | Mars detector secondary braking capturing control method based on Newton iteration |
| CN111319791A (en) * | 2020-02-28 | 2020-06-23 | 上海航天控制技术研究所 | Attitude control mode management method suitable for Mars detection |
| CN111301719B (en) * | 2020-03-04 | 2021-04-13 | 上海航天控制技术研究所 | Autonomous planning and executing method suitable for Mars detection flight control task |
| CN111301719A (en) * | 2020-03-04 | 2020-06-19 | 上海航天控制技术研究所 | Autonomous planning and executing method suitable for Mars detection flight control task |
| CN111891402A (en) * | 2020-06-30 | 2020-11-06 | 上海航天控制技术研究所 | Mars detection ground antenna pointing recovery method based on autonomous maneuvering |
| CN111891402B (en) * | 2020-06-30 | 2022-03-04 | 上海航天控制技术研究所 | Mars detection ground antenna pointing recovery method based on autonomous maneuvering |
| CN114526647A (en) * | 2022-04-24 | 2022-05-24 | 北京宇航系统工程研究所 | Precise control method for launch orbit of carrier rocket running fire |
| CN114526647B (en) * | 2022-04-24 | 2022-07-15 | 北京宇航系统工程研究所 | Precise control method for launch orbit of carrier rocket running fire |
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