CN109059936A - Based on the installation modified Mars Approach phase optical guidance data calculation method of matrix - Google Patents
Based on the installation modified Mars Approach phase optical guidance data calculation method of matrix Download PDFInfo
- Publication number
- CN109059936A CN109059936A CN201810745817.XA CN201810745817A CN109059936A CN 109059936 A CN109059936 A CN 109059936A CN 201810745817 A CN201810745817 A CN 201810745817A CN 109059936 A CN109059936 A CN 109059936A
- Authority
- CN
- China
- Prior art keywords
- mars
- navigation
- matrix
- calculation method
- optical
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
- G01C21/24—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 specially adapted for cosmonautical navigation
Landscapes
- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- Automation & Control Theory (AREA)
- General Physics & Mathematics (AREA)
- Investigating Or Analysing Materials By Optical Means (AREA)
Abstract
The present invention provides one kind based on the installation modified Mars Approach phase optical guidance data calculation method of matrix, comprising the following steps: step 1: Mars probes adjust detector posture during close to Mars, and optical navigation sensor is made to be directed toward Mars；Step 2: Mars, phobos, Deimos is imaged in optical navigation sensor；Step 3: being handled navigation picture using central point extractive technique, determines navigation target source center, obtains direction of visual lines of the navigation target source relative to Mars probes.The present invention can meet the following mars exploration independent navigation mission requirements, provide good technological means for the navigation of deep space probe high-precision independent.
Description
Technical field
The present invention relates to a kind of Mars Approach phase optical guidance data calculation methods, and in particular, to one kind is based on installation
The modified Mars Approach phase optical guidance data calculation method of matrix.
Background technique
Mars exploration operation flight distance is remote, the duration is long, and detected object and detection environment exist a large amount of unknown and not
Certainty, radionavigational precision and real-time are reduced with the increase of distance between detector and earth station, and there are because
The problems such as navigation data caused by communication blind district is discontinuous can not fully meet the special mission phase of mars exploration (as braking is caught
Obtain section) navigation needs.For this purpose, needing to carry out Mars Optical autonomous navigation technique study.
Summary of the invention
For the defects in the prior art, it is close based on the installation modified Mars of matrix that the object of the present invention is to provide one kind
Section optical guidance data calculation method, can meet the following mars exploration independent navigation mission requirements, be that deep space probe is high-precision
Degree independent navigation provides good technological means.
According to an aspect of the present invention, it provides a kind of based on the installation modified Mars Approach phase optical guidance data of matrix
Calculation method, which comprises the following steps:
Step 1: Mars probes adjust detector posture, are directed toward optical navigation sensor during close to Mars
Mars；
Step 2: Mars, phobos, Deimos is imaged in optical navigation sensor；
Step 3: being handled navigation picture using central point extractive technique, determines navigation target source center, and acquisition is led
Navigate direction of visual lines of the target source relative to Mars probes；
Step 4: adjustment Mars probes posture continues tracking observation Mars, phobos, Deimos, obtains observation letter
Breath；
Step 5: estimated in real time in conjunction with celestial body ephemeris, detector posture, dynamics of orbits model using Navigation algorithm
Count the position and speed information of Mars probes.
Preferably, the optical navigation sensor carries out installation matrix amendment by infusing number.
Preferably, the optical navigation sensor is switched on work in cruise section at 10,000,000 kilometers to 100,000 kilometers of Mars
Make.
Preferably, the star chart of the optical navigation sensor shooting independently carries out navigation calculation by spaceborne computer.
Preferably, the optical navigation sensor can be handled captured background star chart, extract posture letter
Breath.
Compared with prior art, the present invention is with following the utility model has the advantages that the present invention makes full use of the nature in cosmic space
Resource realizes continuous autonomous, the real-time high-precision navigation of Mars Approach phase, solves ground based radio navigation method and connect in Mars
The problems such as communication delay, loss near procedure and tracking blind area, the following mars exploration critical stage independent navigation can be met and appointed
Business demand provides good technological means for the navigation of deep space probe high-precision independent.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is that the present invention is based on the flow charts of the installation modified Mars Approach phase optical guidance data calculation method of matrix.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection scope.
As shown in Figure 1, including the present invention is based on the modified Mars Approach phase optical guidance data calculation method of matrix is installed
Following steps:
Step 1: Mars probes adjust detector posture, are directed toward optical navigation sensor during close to Mars
Mars；
Step 2: Mars, phobos, Deimos is imaged in optical navigation sensor；
Step 3: being handled navigation picture using central point extractive technique, determines navigation target source (Mars, Martian satellite
One, Deimos) center, obtain direction of visual lines of the navigation target source relative to Mars probes；
Step 4: adjustment Mars probes posture continues tracking observation Mars, phobos, Deimos, obtains observation letter
Breath；Observational equation is obtained by Mars and Martian satellite sight information, is represented by formula (1)
Z=h (X (t), t)+v (t) (1)
In formula: Z is observed quantity；X is quantity of state；H is measurement equation；V is observation noise.
Step 5: according to detector stress condition, Mars stage section dynamics of orbits model, i.e. state equation are established:
In formula: F is system equation；X is quantity of state；ω is system noise.
Consider that detector in capture section stress condition, has:
In formula: a0For Mars two-body gravitational acceleration；aiFor point mass perturbation acceleration caused by i-th big celestial body, N is
Big celestial body quantity；For Mars gravitational field J2Perturbation acceleration caused by；aRFor perturbation acceleration caused by solar light pressure.
Step 6: united state equation and observational equation, and celestial body ephemeris, detector posture are combined, using Navigation
Algorithm, the position and speed information of real-time estimation Mars probes.
Optical navigation sensor can carry out installation matrix amendment by infusing number, further increase Mars Approach phase device glazing
Learn independent navigation precision.Specifically, when carrying out navigation data resolving, installation matrix and the spy of optical navigation sensor are needed
Posture information of the device device relative to day heart inertial system is surveyed, installation matrix amendment can be carried out by infusing number on device.
Optical navigation sensor is switched on work in cruise section at 10,000,000 kilometers to 100,000 kilometers of Mars, effectively makes up
The deficiencies of continuity of the ground based radio navigation in Mars Approach phase, real-time, independence, it can be used as device upper rail recursion
Backup orbit determination means.
The star chart of optical navigation sensor shooting independently carries out navigation calculation by spaceborne computer, is completely independent of ground
Face station, independence are strong.
Optical navigation sensor can be handled captured background star chart, obtain detector position, speed letter
While breath, it can extract detector posture information.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring substantive content of the invention.
Claims (5)
1. one kind based on installation the modified Mars Approach phase optical guidance data calculation method of matrix, which is characterized in that including with
Lower step:
Step 1: Mars probes adjust detector posture during close to Mars, and optical navigation sensor is made to be directed toward fire
Star；
Step 2: Mars, phobos, Deimos is imaged in optical navigation sensor；
Step 3: being handled navigation picture using central point extractive technique, determines navigation target source center, obtains navigation mesh
Direction of visual lines of the mark source relative to Mars probes；
Step 4: adjustment Mars probes posture continues tracking observation Mars, phobos, Deimos, obtains observation information；
Step 5: in conjunction with celestial body ephemeris, detector posture, dynamics of orbits model, using Navigation algorithm, real-time estimation fire
The position and speed information of star detector.
2. according to claim 1 be based on the installation modified Mars Approach phase optical guidance data calculation method of matrix,
It is characterized in that, the optical navigation sensor carries out installation matrix amendment by infusing number.
3. according to claim 1 be based on the installation modified Mars Approach phase optical guidance data calculation method of matrix,
It is characterized in that, the optical navigation sensor is switched on work in cruise section at 10,000,000 kilometers to 100,000 kilometers of Mars.
4. according to claim 1 be based on the installation modified Mars Approach phase optical guidance data calculation method of matrix,
It is characterized in that, the star chart of the optical navigation sensor shooting independently carries out navigation calculation by spaceborne computer.
5. according to claim 1 be based on the installation modified Mars Approach phase optical guidance data calculation method of matrix,
It is characterized in that, the optical navigation sensor can be handled captured background star chart, extract posture information.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810745817.XA CN109059936A (en) | 2018-07-09 | 2018-07-09 | Based on the installation modified Mars Approach phase optical guidance data calculation method of matrix |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810745817.XA CN109059936A (en) | 2018-07-09 | 2018-07-09 | Based on the installation modified Mars Approach phase optical guidance data calculation method of matrix |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109059936A true CN109059936A (en) | 2018-12-21 |
Family
ID=64819690
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810745817.XA Pending CN109059936A (en) | 2018-07-09 | 2018-07-09 | Based on the installation modified Mars Approach phase optical guidance data calculation method of matrix |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109059936A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110672105A (en) * | 2019-11-22 | 2020-01-10 | 北京理工大学 | High-precision collaborative optical navigation method for small celestial body approaching section double detectors |
| CN111220179A (en) * | 2020-02-21 | 2020-06-02 | 上海航天控制技术研究所 | Inertial reference space-time accurate alignment method of optical navigation sensor |
| CN111426333A (en) * | 2020-02-25 | 2020-07-17 | 上海航天控制技术研究所 | Mars navigation sensor image centroid accurate correction method based on geometric method |
| CN111538019A (en) * | 2020-03-31 | 2020-08-14 | 上海卫星工程研究所 | Auxiliary laser indicator beacon and autonomous navigation measurement system for deep space impact detection |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102168981A (en) * | 2011-01-13 | 2011-08-31 | 北京航空航天大学 | Independent celestial navigation method for Mars capturing section of deep space probe |
| CN103279127A (en) * | 2013-05-22 | 2013-09-04 | 上海新跃仪表厂 | Autonomous control method for GEO (Geosynchronous) orbit satellite by using angle information only |
| CN104764449A (en) * | 2015-04-23 | 2015-07-08 | 北京航空航天大学 | Ephemeris correction-based autonomous celestial navigation method for deep space probe in capturing stage |
| 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 |
| CN107806887A (en) * | 2017-09-22 | 2018-03-16 | 上海卫星工程研究所 | Mars navigation sensor alignment error In-flight calibration method |
-
2018
- 2018-07-09 CN CN201810745817.XA patent/CN109059936A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102168981A (en) * | 2011-01-13 | 2011-08-31 | 北京航空航天大学 | Independent celestial navigation method for Mars capturing section of deep space probe |
| CN103279127A (en) * | 2013-05-22 | 2013-09-04 | 上海新跃仪表厂 | Autonomous control method for GEO (Geosynchronous) orbit satellite by using angle information only |
| CN104764449A (en) * | 2015-04-23 | 2015-07-08 | 北京航空航天大学 | Ephemeris correction-based autonomous celestial navigation method for deep space probe in capturing stage |
| 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 |
| CN107806887A (en) * | 2017-09-22 | 2018-03-16 | 上海卫星工程研究所 | Mars navigation sensor alignment error In-flight calibration method |
Non-Patent Citations (2)
| Title |
|---|
| 王大轶 等: ""深空探测自主导航与控制技术综述"", 《空间控制技术与应用》 * |
| 袁勇 等: ""基于星敏感器测量数据的自主导航算法修正策略"", 《第九届中国卫星导航学术年会论文集-S04卫星轨道与钟差》 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110672105A (en) * | 2019-11-22 | 2020-01-10 | 北京理工大学 | High-precision collaborative optical navigation method for small celestial body approaching section double detectors |
| CN110672105B (en) * | 2019-11-22 | 2021-04-20 | 北京理工大学 | High-precision collaborative optical navigation method for small celestial body approaching section double detectors |
| CN111220179A (en) * | 2020-02-21 | 2020-06-02 | 上海航天控制技术研究所 | Inertial reference space-time accurate alignment method of optical navigation sensor |
| CN111220179B (en) * | 2020-02-21 | 2021-07-13 | 上海航天控制技术研究所 | Inertial reference space-time accurate alignment method of optical navigation sensor |
| CN111426333A (en) * | 2020-02-25 | 2020-07-17 | 上海航天控制技术研究所 | Mars navigation sensor image centroid accurate correction method based on geometric method |
| CN111426333B (en) * | 2020-02-25 | 2022-03-04 | 上海航天控制技术研究所 | Mars navigation sensor image centroid accurate correction method based on geometric method |
| CN111538019A (en) * | 2020-03-31 | 2020-08-14 | 上海卫星工程研究所 | Auxiliary laser indicator beacon and autonomous navigation measurement system for deep space impact detection |
| CN111538019B (en) * | 2020-03-31 | 2023-07-14 | 上海卫星工程研究所 | Auxiliary laser indication beacon and autonomous navigation measurement system for deep space impact detection |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109059936A (en) | Based on the installation modified Mars Approach phase optical guidance data calculation method of matrix | |
| CN104165640B (en) | Near-space missile-borne strap-down inertial navigation system transfer alignment method based on star sensor | |
| CN106595674B (en) | HEO satellite formation flying autonomous navigation method based on star sensor and inter-satellite link | |
| CN102168981B (en) | Independent celestial navigation method for Mars capturing section of deep space probe | |
| CN103063217B (en) | Deep space detector astronomy/radio combination navigation method based on ephemeris correction | |
| CN103472503B (en) | Sonde and upper air wind finding method based on INS | |
| CN105160125B (en) | A kind of simulating analysis of star sensor quaternary number | |
| Zurek et al. | Application of MAVEN accelerometer and attitude control data to Mars atmospheric characterization | |
| CN106643741B (en) | Satellite relative minor planet vision autonomous navigation method | |
| CN105716615A (en) | Method for autonomously navigating Mars probes | |
| CN104296752B (en) | Autonomous spacecraft navigation system with combination of astronomical angle measurement and speed measurement, and navigation method of autonomous spacecraft navigation system | |
| CN105203101A (en) | Deep space explorer acquisition phase celestial navigation method based on target object ephemeris correction | |
| CN104764449A (en) | Ephemeris correction-based autonomous celestial navigation method for deep space probe in capturing stage | |
| CN104360362A (en) | Method and system for positioning observed object via aircraft | |
| CN110162098A (en) | A kind of mining unmanned plane | |
| CN103542853A (en) | Absolute navigation filtering method capable of estimating drifting of accelerometer | |
| US8538606B2 (en) | Systems, methods, and apparatus for sensing flight direction of a spacecraft | |
| Smith et al. | Operational constraint analysis of terrain relative navigation for landing applications | |
| CN106767840A (en) | Mars exploration Approach phase combines autonomous navigation method | |
| Scott et al. | Toward microsatellite based space situational awareness | |
| CN104567868B (en) | Method based on the INS airborne long endurance celestial navigation systems corrected | |
| EP3430799A2 (en) | Image data capturing arrangement | |
| CN106996779A (en) | Ultraviolet sensors systematic error on-orbit calibration method based on GNSS | |
| CN103256932B (en) | Replacement and extrapolation combined navigation method | |
| CN105387861A (en) | Multi-object observation autonomous navigation system adopting large dynamic faint target imaging sensor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181221 |
|
| RJ01 | Rejection of invention patent application after publication |