CN102081704A - Generation method for ontrack-operation injection data of scientific detecting instrument lunar probe - Google Patents
Generation method for ontrack-operation injection data of scientific detecting instrument lunar probe Download PDFInfo
- Publication number
- CN102081704A CN102081704A CN 201110026942 CN201110026942A CN102081704A CN 102081704 A CN102081704 A CN 102081704A CN 201110026942 CN201110026942 CN 201110026942 CN 201110026942 A CN201110026942 A CN 201110026942A CN 102081704 A CN102081704 A CN 102081704A
- Authority
- CN
- China
- Prior art keywords
- data
- data block
- scientific exploration
- scientific
- exploration instrument
- 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
Images
Landscapes
- Geophysics And Detection Of Objects (AREA)
Abstract
The invention discloses a generation method for the ontrack-operation injection data of a scientific detecting instrument lunar probe, comprising the following steps: 1. carrying out orbit determination on the lunar probe with a USB (Universal Serial Bus) range and velocity measurement method in the mode of very long baseline interferometry (VLBI) combination orbit measurement, providing the view direction motion information of the lunar probe by the USB range and velocity measurement method, and providing the transverse motion information of the lunar probe by VLBI; 2. setting the working parameter of the scientific detecting instrument according to the orbit determination result of the lunar probe; and 3. generating the injection data block of the scientific detecting instrument by the working parameter, and packaging the injection data block into frames. By utilizing the method provided by the invention, the scientific detecting instrument lunar probe can be controlled by sending the injection data to the detecting instrument, and lunar probing operation can be guaranteed to be carried out normally.
Description
Technical field
The present invention relates to method that the instrument of satellite scientific exploration is in orbit controlled, the scientific exploration instrument that particularly a kind of lunar orbiter carries injects the generation method of data in orbit.
Background technology
The moon is the unique natural satellite of the earth, is the celestial body nearest apart from the earth.Therefore, the moon is the important object of human observational study always, also is the preferred object that the mankind carry out survey of deep space.Because it can be human desirable base and preceding post to the outer space development, so realize that moon exploration has extensive and important meaning for various unique resource of human development and utilization that the moon has.At present, started the moon exploration upsurge of a new round in the world, European Space Agency, Japan, India and China all in moonshot in recent years the lunar orbiting exploration device, simultaneously the U.S. has also planned new moon exploration plan.Every month, ball detector all can be carried multiple scientific exploration instrument, in order to the purpose that realizes the moon is carried out scientific exploration.Thereby, how the scientific exploration instrument that carries on the lunar orbiter is control effectively, just become the major issue that moon exploration project need be considered.
At present, the control mode to the earth and lunar orbiter mainly is to finish by detector is sent the method for injecting data.The injection data comprise the effective control information to scientific instrument, and the scientific exploration instrument is finished duty setting in the detection process by reading the control information of injecting data.But in present method, to the orbit determination of detector use usually unified S ripple (Unified S-Band, USB) ranging and range rate method is though this method can realize the work of the orbit determination of detector, but orbit determination accuracy is lower, can not guarantee the orbit determination demand of lunar orbiter fully.On the other hand, lunar orbiter in the process, has only the part-time section can enter the observation segmental arc in orbit every day.The surface work personnel can receive detector signal and detector is controlled in the may observe segmental arc, other times all can't pick-up probe signal or control detector equipment.Therefore, must in the may observe segmental arc, finish control, and guarantee that detection instrument is working properly before entering the observation segmental arc next time lunar orbiter scientific exploration instrument.Yet, mainly at the earth satellite design, number of times is more frequent because earth satellite passes by, or geostationary orbit satellite for present data method for implanting, can realize that instant the transmission inject data, inject with the data of lunar orbiter and require difference to some extent.
So demand providing a kind of method that can more effectively control lunar orbiter urgently.
Summary of the invention
In order to overcome the above-mentioned defective of prior art, the invention provides the generation method that a kind of lunar orbiter scientific exploration instrument injects data in orbit, this method is based on the accurate orbit determination to lunar orbiter, calculates the orbit of lunar orbiter accurately.The orbital data of analysis-by-synthesis detector and menology ground type information, the work program and the device parameter of scientific exploration instrument on the formulation detector.Simultaneously, this method can generate the injection data of control corresponding detector duty in real time according to the scientific exploration demand of scientific exploration instrument on the lunar orbiter, and send on the lunar orbiter and carry out by injecting data, realization is to the adjustment and the setting of scientific exploration Instrument working state, thereby finishes the scientific exploration target of expection.The injection data that send to detector had both comprised the power supply steering order of scientific exploration instrument, also comprised the parameter adjustment data of detection instrument, can realize the flexible control to the scientific exploration instrument.Different detection instruments has different instruction set and parameter setting, need different detection instruments is distinguished in the injection data, thereby guarantee that steering order and parameter that data are injected can send to corresponding detection instrument, guarantee that scientific exploration normally carries out.
This method comprises: a kind of lunar orbiter scientific exploration instrument injects the generation method of data in orbit, comprise step: use USB ranging and range rate method and very long baseline interferometry(VLBI VLBI to unite the mode of surveying rail lunar orbiter is carried out orbit determination, utilize USB ranging and range rate measuring method that the line of vision movable information of lunar orbiter is provided, utilize VLBI that the transverse movement information of lunar orbiter is provided; Utilize the orbit determination result of lunar orbiter to set the running parameter of scientific exploration instrument; And step 3, utilize described running parameter to generate the injection data block of scientific exploration device.
Preferably, generate the Precise Orbit radical that detector moves in the lunar oribt by orbit determination.
Preferably, calculate the running orbit of lunar orbiter, to determine that each scientific exploration instrument is in effective search coverage of moonscape on the lunar orbiter according to the orbit determination result.
Preferably, described running parameter is used to adjust the duty of scientific exploration instrument, and it is determined according to the detection of a target and demand and scientific exploration instrument current working state.
Preferably, described injection data block comprises: inject the data block information head, as the control information of injecting data block; And the injection data content, its running parameter according to the scientific exploration instrument generates.
Preferably, described injection data block information head comprises: scientific exploration instrument and equipment identification information is used to identify the scientific exploration instrument of carrying out described injection data block; Inject the control information of data block data content, be used to indicate order and the data block length that injects between the data block.
Preferably, described frame comprises frame head information and data content two parts, and wherein frame head information is used for identifying injecting data block, and controls injecting data block order and length, and data content comprises described injection data block.
Preferably, inject data block and comprise: device identifier is used to specify to carry out and injects the scientific exploration instrument that data block is instructed; The instruction control preface is used to control one group of data injecting the data block order; Instruction length is used to indicate the byte quantity of secondary top guide of this injection data block and data field; Secondary top guide is an Optional Field, is used for the explanation to the data field content; Data field is the valid data information that the scientific exploration instrument parameter is provided with, and the scientific exploration instrument is just set and revised instrument parameter according to the content in the data field.
Preferably, described frame comprises: Packet Identifier is to be used for identification data to inject a group mark sign indicating number of bag, shows that from then on beginning is the content that data are injected bag, Packet Identifier has uniqueness, promptly injects the content of wrapping in data and the data content identical with Packet Identifier can not occur; The control of bag preface is used for a plurality of data are injected the sequential control sign of wrapping; Packet length indicates the byte quantity of application data and filler code; Application data is described injection data block; Filler code is used for the data content that the polishing data are injected bag, when the length of scientific exploration instrument injection data block does not satisfy requiring of data injection bag, just injects the afterbody interpolation filler code of bag in data.
Use method of the present invention, by introducing a kind of new orbit determination mode, promptly use USB ranging and range rate method and very long baseline interferometry(VLBI VLBI to unite the mode of surveying rail the moon exploration instrument is carried out orbit determination, generate the injection data according to accurate orbit determination result, and will inject data and be sent on the lunar orbiter, can realize scientific exploration instrument that the such satellite sensor of for example CE-1 is carried in rail control, thereby guarantee the normal operation of each scientific exploration instrument.
Description of drawings
Fig. 1 injects the generation method flow diagram of data in orbit for lunar orbiter scientific exploration instrument provided by the invention.
Fig. 2 is the structural representation of injection data block of the present invention;
Fig. 3 will inject data block framing frame structure synoptic diagram afterwards for the present invention.
Embodiment
For making the purpose, technical solutions and advantages of the present invention clearer, below in conjunction with specific embodiment, and with reference to accompanying drawing, the present invention is described in more detail.
With reference to the process flow diagram of Fig. 1, lunar orbiter scientific exploration instrument of the present invention injects data creation method in orbit and mainly comprises step:
Step S101 carries out orbit determination to lunar orbiter.
Lunar orbiter orbit determination is that the lunar orbiter scientific instrument are carried out the most important condition in rail control, have only running orbit and the detector attitude that just can accurately know detector by accurate orbit determination, can guarantee that on the one hand the detecting devices on the detector obtains accurately, reliable detection data; Also can help the surface work personnel to formulate the work program of scientific exploration instrument more accurately on the other hand, guarantee the validity of lunar orbiter work.In the method, use USB (Unified S-Band, unified S ripple) and VLBI (Very Long Baseline Interferometry, very long baseline interferometry(VLBI) to unite the method for surveying rail lunar orbiter is carried out orbit determination.
USB ranging and range rate measuring system only can provide the line of vision movable information of lunar orbiter, and VLBI then can provide the transverse movement information of lunar orbiter.Compare with the radio distance-measuring velocity measuring technique, the VLBI technology has plurality of advantages, for example only needs the descending one way signal of observation, and angle measurement accuracy height, and measuring accuracy do not increase with distance and reduce requires low etc. to the support of antenna.Therefore, the VLBI technology is that the useful of radio distance-measuring velocity measuring technique replenished, and has important effect in lunar orbiter is followed the tracks of.The main source of error of VLBI observation has: the instrumental delay error that the noise error of antenna and receiver, receiving system and signal Processing data system produce, clocking error and the ionosphere and the tropospheric propagation delay error of research station.In order to eliminate the clock correction error of instrumental delay sum of errors research station, what widely adopt at present is that relatively poor VLBI measures, intersect when its measuring principle is detector observation and observe near accurately known extragalactic radio source of the position of detector, eliminate common instrumental delay sum of errors research station clocking error with this, ionosphere and tropospheric atmospheric propagation error also part are eliminated.The survey rail ability of China VLBI is at present: the time delay precision is better than 10ns (1ns=10
-9S), the about 1ps/s (1ps=10 of time delay rate precision
-12S).
The range finding of precision angle and USB by the VLBI technology is positioned at this geometrical constraint of moonscape in conjunction with the lunar surface target, can realize the precision positioning to the lunar surface target.Specific implementation is VLBI single epoch of the precision angle that utilizes in a period of time, or in conjunction with the range observation of USB, the relevant information of utilizing the moon to rotate is carried out comprehensive adjustment processing with the positioning result of single epoch, to obtain the precision positions of lunar surface target in moon spherical coordinate system.
The precision of using USB and VLBI to unite orbit determination significantly is better than the precision of the independent orbit determination of USB, and with respect to the independent orbit determination of USB, perigee orbit prediction precision constantly improves significantly after the associating orbit determination.Associating orbit determination is with respect to the independent orbit determination of USB, and not only precision in the horizontal significantly improves (the lateral attitude precision improves about 70%), and the precision of radial direction equally also improves a lot (the radial position precision improves about 50%).
After orbit determination is finished, will generate the Precise Orbit radical that detector moves in the lunar oribt, inject the important initial conditions that generates as follow-up scientific exploration instrument data.
USB and VLBI associating orbit determination is applied to any lunar exploration satellite, " Chang'e I (CE-1) " lunar exploration satellite for example, and " Chang'e I (CE-1) " lunar exploration satellite is the first step that China moves towards survey of deep space by China's emission.Carry out in the detection mission process at " Chang'e I (CE-1) " satellite, use USB and VLBI dual mode associating orbit determination, finish tracking " Chang'e I (CE-1) " satellite.For satisfying the requirement of measuring rail precision, use the antenna of domestic 4 land stations to form the VLBI net, be respectively two 25m antennas for radio astronomy in Beijing Miyun 50m antenna for radio astronomy, Kunming 40m antenna for radio astronomy and Shanghai and Urumchi.Simultaneously, also use two 25m antennas in Qingdao and Keshen to adopt the USB mode to measure rail.
At " Chang'e I (CE-1) " detector run duration, use above-mentioned 6 antennas to adopt VLBI and USB mode simultaneously the detector orbit to be measured respectively, guaranteed the degree of accuracy of detector orbit determination to the full extent.After antenna receives detector signal, respectively data are handled, COMPREHENSIVE CALCULATING obtains the orbit parameter of detector again, and issues detector orbit determination result with the form of Precise Orbit radical.Comprise six important parameters in the Precise Orbit radical,, be respectively: major semi-axis a, eccentric ratio e, orbit inclination i, right ascension of ascending node Ω, perilune argument ω peace inbreeding point M in order to determine the running orbit of detector.According to these six parameters, use existing ripe satellite orbit computation model, just can calculate the operation attitude and the track of detector accurately, for follow-up work provides basic initial conditions.
Step S103 determines the running parameter of scientific exploration instrument.
The scientific exploration plan is the work program of lunar orbiter scientific exploration instrument.In lunar orbiter process in orbit, the surface work personnel need take all factors into consideration running status, detection data quality and the factors such as flight path and attitude of lunar orbiter, formulate or adjust the detection of a target and the detection demand of lunar orbiter scientific exploration instrument, and export with the form of scientific exploration plan.
The important initial conditions that generates the scientific exploration plan is exactly the orbit determination result of lunar orbiter.After detector orbit determination is finished, just can accurately calculate the running orbit of lunar orbiter, thereby determine the effective search coverage of lunar orbiter at moonscape according to the orbit determination result.Accurate orbit determination result can guarantee the accuracy that search coverage is determined, the survey plan of Zhi Dinging can guarantee the quality of the scientific exploration data obtained on this basis.When generating the scientific exploration plan, except the running orbit that will calculate lunar orbiter, also need comprehensively can consider the terrain information of search coverage moonscape, and the quality of the detection data that obtains before.Effectively definite one side of search coverage is the running orbit according to lunar orbiter, needs the characteristics of each scientific exploration instrument on the reference detector on the other hand, carries out analysis-by-synthesis and determines.Finish after this work, effective search coverage information of lunar orbiter and topography of lunar surface geomorphology information are combined, just can know in the lineament of detector search coverage and the search coverage whether have the important detection of a target, thereby as the initial conditions of formulating the scientific exploration plan.The important detection of a target in the lineament of detector search coverage and the search coverage is an important reference of formulating the scientific exploration plan.The concrete work program of each scientific exploration instrument on the lunar orbiter is formulated or adjusted to these information of surface work personnel analysis-by-synthesis according to the task object and the current working state of engineering.The scientific exploration plan of timely replacement can guarantee the validity and the adaptability of scientific exploration instrument work, improves the quality and the efficient of lunar orbiter work.
The work program of each scientific instrument has been formulated in the scientific exploration plan, is the follow-up basic initial conditions that data generate that injects.
The CCD three linear array stereoscopic cameras that carry with " Chang'e I (CE-1) " satellite are example, and the process that generates the scientific exploration plan is described.The CCD stereoscopic camera is the scientific instruments equipment that is used for taking the moonscape striograph, in " Chang'e I (CE-1) " satellite around-the-moon flight process, the CCD stereoscopic camera need be at the reasonable time photographic images of starting shooting, thereby finishes the task object that obtains moon whole world striograph.The surface work personnel need the information with reference to following several respects when formulating CCD stereoscopic camera scientific exploration plan: (1) " Chang'e I (CE-1) " satellite orbit forecast file, determine the satellite flight track; (2) topography of lunar surface information, the characteristics of analysis CCD stereoscopic camera imaging region; (3) CCD stereoscopic camera view data is analyzed stereoscopic camera duty and camera imaging quality.
By the analysis-by-synthesis to above-mentioned information, the surface work personnel just can formulate the imaging plan of CCD stereoscopic camera according to the task needs, and image is obtained in start in predetermined shooting area.Simultaneously,, also need to adjust CCD stereoscopic camera imaging strategy in good time, guarantee to obtain the quality of image according to the characteristics and the camera imaging quality of shooting area.The content of comprehensive this two aspect just can generate the scientific exploration plan, and survey plan is issued, and makes it to be converted into the injection data of each scientific exploration instrument.
In scientific exploration in the works, the work program or the working strategies of scientific exploration instrument have just been formulated.How to realize detection mission, also need to adjust the running parameter of scientific exploration instrument in conjunction with actual conditions according to survey plan.Setting the running parameter of scientific exploration instrument, is the direct approach of adjusting each scientific exploration Instrument working state.The surface work personnel realize the control to scientific exploration instrument on the lunar orbiter by the running parameter of instrument is set.Therefore, after generating the scientific exploration plan, the surface work personnel need further the work program of instrument to be changed into the running parameter of scientific exploration instrument, with survey plan as basic initial conditions, and, then can derive the running parameter of finishing the scientific exploration instrument that survey plan need set in conjunction with science detection instrument current working state.By the duty that new running parameter just can change the scientific exploration instrument is set, make it to adapt to new task scheduling.
Be example with " Chang'e I " Satellite CCD stereoscopic camera equally, after the survey plan of formulating the CCD stereoscopic camera, need adjust the duty of satellite and obtain the selenograph picture of appointed area according to the requirement of survey plan.On the basis that is adjusted at the survey plan that rests on a scientific basis of CCD stereoscopic camera duty, also need to consider the influence of satellite factor such as longitude and latitude position and the variation of shooting area sun altitude in moon spherical coordinate system, satellite all can have influence on the image quality of CCD stereoscopic camera in the difference of different position of the moon or sun altitude.So, when CCD stereoscopic camera duty is set, need take all factors into consideration the influence of this several respects factor, adjust the switching on and shutting down time and the time shutter of CCD stereoscopic camera according to the variation of actual conditions, make the duty adaptation survey plan of CCD stereoscopic camera and the requirement of image-forming condition, obtain the image of scientific exploration plan appointed area.
By analysis to scientific exploration plan and detection instrument condition of work, the scientific exploration Instrument working parameter that accomplished survey plan need be provided with, and with its important evidence as generation detector injection data.The running parameter of scientific exploration instrument is to generate the direct initial conditions that injects data, just can determine to inject the content of data according to the running parameter of detection instrument.Therefore, determine that the scientific exploration Instrument working parameter is to generate to inject the data most crucial steps.
Step S105 is according to the running parameter generation scientific exploration instrument injection data block of scientific exploration instrument.
The initial conditions that generates scientific exploration instrument injection data block is the device parameter of scientific exploration instrument.After the surface work personnel determine the device parameter of scientific exploration instrument according to the scientific exploration plan, just can enter the stage that the scientific exploration instrument injects data block that generates.
It is the data message that the scientific exploration instrument is directly controlled that the scientific exploration instrument injects data block, it is made up of one group of 16 system data, in data block, comprise the device identification of scientific exploration instrument and the control information of equipment, can realize operation control different scientific exploration instruments.
The scientific exploration instrument injects data block mainly to be made up of two parts, and a part is to inject the data block information head, and another part is that the scientific exploration instrument injects data content.Injecting the data block information head is the control information of injecting data block, injects the data block information head and mainly comprises two parts content: the one, and scientific exploration instrument and equipment identification information is used for illustrating the scientific exploration instrument of carrying out this injection data block; The 2nd, inject the control information of data block data content, be used for indicating order and data block length between the injection data block.Injecting the data block information head is the important component part that data are injected piece, and the scientific exploration instrument obtains relevant injection data by injecting the data block information head, and guarantees to inject the correctness of data read and execution sequence.It is the control information of scientific exploration instrument that the scientific exploration instrument injects data content, injecting data content generates according to the scientific exploration Instrument working parameter, detection instrument carries out inverting with data content wherein after receiving the injection data block, the duty of instrument just can be set according to the content of parameter that obtains, finish the scientific exploration task.
Particularly, with reference to Fig. 2, the scientific exploration instrument injects data block and preferably comprises following components according to field: device identifier; The instruction control preface; Instruction length; Secondary top guide and data field.
Device identifier is to be used for specifying carrying out injecting the scientific exploration instrument that data block is instructed, guarantee that by the interpretation device identifier instrument receives and the correctness of execution command, thereby avoid causing the mutual execution error of injection data between the different scientific exploration instruments.
The instruction control preface is to be used for controlling one group of data injecting the data block order, and different injection data blocks will have no sequential counting, and the scientific exploration instrument is carried out the injection data block of receiving in order.
Instruction length indicates the byte quantity of secondary top guide of this injection data block and data field, is the foundation that the scientific exploration instrument is used for judging content of parameter.
Secondary top guide is the explanation to the data field content, and this partial content has different regulations according to different scientific exploration instruments, and the scientific exploration instrument data that has injects piece does not have secondary top guide.
Data field is the valid data information that the scientific exploration instrument parameter is provided with, and the scientific exploration instrument just can be set and revise according to the content in the data field instrument parameter.
The scientific exploration instrument injects data block and generates according to corresponding standard, and each scientific exploration instrument all has specific device identifier, and each parameter of scientific exploration instrument all has unique order code.After the running parameter of confirming the scientific exploration instrument, just the parameter information of detection instrument is converted into order code according to standard, write the injection data block.With the CCD stereoscopic camera is example, when generating the injection data block, at first will write the device identifier of CCD stereoscopic camera in data block, uses for the CCD stereoscopic camera in order to show this injection data block; Next fills in instruction control preface information, and the ordinal relation between a plurality of injection data blocks is described, carries out in proper order according to this when carrying out the injection data block; Once more, fill in the data field that injects data block, running parameter is converted to order code writes in order in the data field, carry out for the CCD stereoscopic camera and use according to the running parameter of CCD stereoscopic camera; At last, fill in instruction length and secondary top guide information, be used for showing the content character of this injection data block according to content and the length of injecting the data block data field.
So just finished generation of injecting data block of CCD stereoscopic camera,, just generated successively according to this process if the CCD stereoscopic camera has a plurality of injection data blocks.
Step S107 injects the data block framing.
Generate after the injection data block of scientific exploration instrument, need send on the lunar orbiter, could will inject data forwarding by lunar orbiter and give each scientific exploration instrument injecting data block.Therefore after injecting the data block generation, need carry out framing to it and just can send to lunar orbiter, just also need to encapsulate sign and the control information that one deck lunar orbiter can be discerned again to injecting data block, its objective is that the scientific exploration instrument that helps lunar orbiter identification and control to receive injects data block, effectively manage, avoid the mistake of Data Receiving and forwarding injecting data block.
Injection data block behind the framing can be called data and inject bag, mainly is made up of header packet information and data content.Header packet information is to be used for identifying injecting data block on the one hand, is to control injecting data block order and length on the other hand.By reading header packet information, lunar orbiter just can determine that these data inject the type of bag, and guarantees the correctness of order between correctness that packet content reads and a plurality of packet.The data content that data are injected bag is exactly that the scientific exploration instrument that generates injects data block, and it is the control information of scientific exploration instrument.Lunar orbiter receives after data inject bag, wherein scientific exploration instrument is injected data block be transmitted to corresponding scientific exploration instrument, makes it according to the content of injecting data block duty to be set, and finishes the scientific exploration plan.
Particularly, with reference to Fig. 3, the data behind the framing are injected bag and can be comprised according to field: Packet Identifier; The control of bag preface; Packet length; Application data; Filler code.
Wherein Packet Identifier is to be used for identification data to inject a group mark sign indicating number of bag, shows that from then on beginning is the content that data are injected bag, and Packet Identifier has uniqueness, and promptly the content of injecting bag in data the data content identical with Packet Identifier can not occur.
Wrapping preface control is the sequential control sign of a plurality of data being injected bag, can know the sequencing of data injection bag by reading this sign.
Packet length indicates the byte quantity of application data and filler code, and detector injects the data content of bag according to the packet length specified data.
The injection data block of the scientific exploration instrument that application data generates before being exactly is the core content that data are injected bag, and detector will inject data block and be forwarded to each corresponding scientific exploration instrument execution.
Filler code is to be used for the polishing data to inject the data content of bag, and the length of injecting data block when the scientific exploration instrument does not satisfy data when injecting requiring of bag, just injects the afterbody interpolation filler code of bag in data.
Inject after the data block framing, just the injection data can be sent on the lunar orbiter and carry out, make the scientific exploration instrument of lunar orbiter can adjust its duty as requested, thereby finish corresponding scientific exploration task.
The injection data creation method that uses the present invention to propose by the accurate orbit determination to the moon exploration instrument, and utilizes the orbit determination result to generate the injection data, thus realize to lunar orbiter scientific exploration instrument in rail control, support the realization of moon exploration project with this.
Above-described specific embodiment; purpose of the present invention, technical scheme and beneficial effect are further described; institute is understood that; the above only is specific embodiments of the invention; be not limited to the present invention; within the spirit and principles in the present invention all, any modification of being made, be equal to replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (10)
1. a lunar orbiter scientific exploration instrument injects the generation method of data in orbit, comprises step:
Step 1, use USB ranging and range rate method and very long baseline interferometry(VLBI VLBI to unite the mode of surveying rail lunar orbiter is carried out orbit determination, utilize USB ranging and range rate measuring method that the line of vision movable information of lunar orbiter is provided, utilize VLBI that the transverse movement information of lunar orbiter is provided;
Step 2 utilizes the orbit determination result of lunar orbiter to set the running parameter of scientific exploration instrument; And
Step 3 utilizes described running parameter to generate the injection data block of scientific exploration device.
2. method according to claim 1 is characterized in that step 1 further comprises: generate the Precise Orbit radical that detector moves in the lunar oribt by orbit determination.
3. method according to claim 2, it is characterized in that step 1 further comprises: comprise six parameters in the Precise Orbit radical, in order to determine the running orbit of detector, be respectively: major semi-axis a, eccentric ratio e, orbit inclination i, right ascension of ascending node Ω, perilune argument ω peace inbreeding point M, according to described parameter, the operation attitude and the track of calculating detector are to determine the effective search coverage of lunar orbiter at moonscape.
4. method according to claim 1 is characterized in that described running parameter is used to adjust the duty of scientific exploration instrument, and it is determined according to the detection of a target and demand and scientific exploration instrument current working state.
5. method according to claim 1 is characterized in that, described injection data block comprises:
Inject the data block information head, as the control information of injecting data block; And
Inject data content, its running parameter according to the scientific exploration instrument generates.
6. method according to claim 5 is characterized in that, described injection data block information head comprises:
Scientific exploration instrument and equipment identification information is used to identify the scientific exploration instrument of carrying out described injection data block;
Inject the control information of data block data content, be used to indicate the order and and the data block length that inject between the data block.
7. method according to claim 1, it is characterized in that, after step 3, also comprise injection data block encapsulation framing, described frame comprises frame head information and data content two parts, wherein frame head information is used for identifying injecting data block, and controls injecting data block order and length, and data content comprises described injection data block.
8. according to each described method of claim 1-7, it is characterized in that described moon exploration instrument is the lunar exploration satellite.
9. method according to claim 8 is characterized in that, described injection data block comprises:
Device identifier is used to specify to carry out and injects the scientific exploration instrument that data block is instructed;
The instruction control preface is used to control one group of data injecting the data block order;
Instruction length is used to indicate the byte quantity of secondary top guide of this injection data block and data field;
Secondary top guide is an Optional Field, is used for the explanation to the data field content;
Data field is the valid data information that the scientific exploration instrument parameter is provided with, and the scientific exploration instrument is just set and revised instrument parameter according to the content in the data field.
10. method according to claim 9 is characterized in that, described frame comprises:
Packet Identifier is to be used for identification data to inject a group mark sign indicating number of bag, shows that from then on beginning is the content that data are injected bag, and Packet Identifier has uniqueness, and promptly the content of injecting bag in data the data content identical with Packet Identifier can not occur;
The control of bag preface is used for a plurality of data are injected the sequential control sign of wrapping
Packet length indicates the byte quantity of application data and filler code;
Application data is described injection data block;
Filler code is used for the data content that the polishing data are injected bag, when the length of scientific exploration instrument injection data block does not satisfy requiring of data injection bag, just injects the afterbody interpolation filler code of bag in data.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110026942 CN102081704A (en) | 2011-01-25 | 2011-01-25 | Generation method for ontrack-operation injection data of scientific detecting instrument lunar probe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110026942 CN102081704A (en) | 2011-01-25 | 2011-01-25 | Generation method for ontrack-operation injection data of scientific detecting instrument lunar probe |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102081704A true CN102081704A (en) | 2011-06-01 |
Family
ID=44087663
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201110026942 Pending CN102081704A (en) | 2011-01-25 | 2011-01-25 | Generation method for ontrack-operation injection data of scientific detecting instrument lunar probe |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102081704A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103490856A (en) * | 2013-09-16 | 2014-01-01 | 中国科学院上海天文台 | Mark5B-format VLBI data receiving decoding and error correcting system and method used for deep space exploration |
| CN103776427A (en) * | 2014-01-21 | 2014-05-07 | 北京空间机电研究所 | Parameter setting and adjusting method applied to stereo mapping camera |
| CN103984592A (en) * | 2014-05-19 | 2014-08-13 | 上海微小卫星工程中心 | Satellite instruction sequence processing method and device based on multiple tasks |
| CN110244291A (en) * | 2019-07-19 | 2019-09-17 | 北京航天飞行控制中心 | Speed-measuring method and device based on radio signal processing |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101038169A (en) * | 2007-02-13 | 2007-09-19 | 北京空间飞行器总体设计部 | Navigation satellite autonomous navigation system and method based on X-ray pulsar |
-
2011
- 2011-01-25 CN CN 201110026942 patent/CN102081704A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101038169A (en) * | 2007-02-13 | 2007-09-19 | 北京空间飞行器总体设计部 | Navigation satellite autonomous navigation system and method based on X-ray pulsar |
Non-Patent Citations (2)
| Title |
|---|
| 《测绘科学》 20080131 王宏等 USB-VLBI综合确定SMART-1环月探测器轨道 40-42 1-10 第33卷, 第1期 * |
| 《载人航天》 20060630 丁兵 未来空间飞行器测控与通信系统的CCSDS高级在轨系统研究 36-39 5-10 , 第3期 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103490856A (en) * | 2013-09-16 | 2014-01-01 | 中国科学院上海天文台 | Mark5B-format VLBI data receiving decoding and error correcting system and method used for deep space exploration |
| CN103776427A (en) * | 2014-01-21 | 2014-05-07 | 北京空间机电研究所 | Parameter setting and adjusting method applied to stereo mapping camera |
| CN103776427B (en) * | 2014-01-21 | 2015-11-04 | 北京空间机电研究所 | A kind of optimum configurations and method of adjustment being applied to tridimensional mapping camera |
| CN103984592A (en) * | 2014-05-19 | 2014-08-13 | 上海微小卫星工程中心 | Satellite instruction sequence processing method and device based on multiple tasks |
| CN110244291A (en) * | 2019-07-19 | 2019-09-17 | 北京航天飞行控制中心 | Speed-measuring method and device based on radio signal processing |
| CN110244291B (en) * | 2019-07-19 | 2021-06-01 | 北京航天飞行控制中心 | Speed measuring method and device based on radio signal processing |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101968542B (en) | Method for tracking lunar probe by using earth station | |
| CN100565105C (en) | A kind of star-load TDICCD camera calculates and method of adjustment integral time | |
| CN101241011B (en) | High precision positioning and posture-fixing device on laser radar platform and method | |
| Li et al. | The global image of the Moon obtained by the Chang’E-1: Data processing and lunar cartography | |
| CN103033188A (en) | Navigation satellite autonomous time synchronization method based on synthetic aperture observation | |
| CN103674020B (en) | A kind of constellation orientation analogue system and method based on X-ray pulsar | |
| CN105444781B (en) | It is spaceborne to be imaged ground validation method from main boot | |
| CN110275192A (en) | A kind of high-precision point positioning method and device based on smart phone | |
| CN110146906A (en) | Remote time transmission method based on single poor carrier phase observation data | |
| CN105444780B (en) | Spaceborne sweep type optical camera framing verification system and processing method | |
| CN108871348A (en) | Low-orbit satellite autonomous orbit determination method using space-based visible light camera | |
| CN109827541A (en) | A method of improving the more electro-optic theodolite mutual designation precision to cooperate | |
| CN109633701A (en) | GNSS timing receiver system delay calibration method based on punctual lab resources | |
| CN102426017A (en) | Method for determining attitude of carrier relative to geographic coordinate system based on star sensor | |
| CN105823469A (en) | GNSS high precision assisted unmanned plane aerotriangulation method | |
| CN102081704A (en) | Generation method for ontrack-operation injection data of scientific detecting instrument lunar probe | |
| CN110286395A (en) | A kind of dipper system precision calculation method | |
| Ma | Very long baseline interferometry applied to polar motion, relativity and geodesy | |
| CN203857967U (en) | Initial posture field calibration system of combined guidance system | |
| CN110646819A (en) | Low-orbit satellite ephemeris forecasting device and application method | |
| Muellerschoen | Results of an automated GPS tracking system in support of TOPEX/POSEIDON and GPSMet | |
| CN104296726B (en) | Two-sided battle array pushes away sweeps stereo mapping formation method and imaging system | |
| CN105510936B (en) | Spaceborne GNSS associating orbit determination method and device | |
| CN105973203A (en) | Differential GNSS application method in unmanned aerial vehicle aerial photography | |
| CN106814376A (en) | A kind of quick accurate Centimeter Level one-point positioning method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20110601 |