CN110048760A - A kind of antenna in-orbit autonomous management method of the double antenna without the fixed satellite of direction over the ground - Google Patents
A kind of antenna in-orbit autonomous management method of the double antenna without the fixed satellite of direction over the ground Download PDFInfo
- Publication number
- CN110048760A CN110048760A CN201910219160.8A CN201910219160A CN110048760A CN 110048760 A CN110048760 A CN 110048760A CN 201910219160 A CN201910219160 A CN 201910219160A CN 110048760 A CN110048760 A CN 110048760A
- Authority
- CN
- China
- Prior art keywords
- antenna
- satellite
- duty
- ground
- passes
- 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.)
- Granted
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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/03—Cooperating elements; Interaction or communication between different cooperating elements or between cooperating elements and receivers
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18519—Operations control, administration or maintenance
Landscapes
- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- Computer Networks & Wireless Communication (AREA)
- Aviation & Aerospace Engineering (AREA)
- Signal Processing (AREA)
- Automation & Control Theory (AREA)
- Radio Relay Systems (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
Abstract
The present invention relates to a kind of double antennas without the fixed in-orbit autonomous management method of antenna for being directed toward satellite over the ground: at the time of being ahead of satellite and correspond to by visible segmental arc immigration the first preset time period of moment in grounded receiving station, it controls satellite and stops posture scanning, and the attitude of satellite is maintained to three axis of the inertia direction for stopping the scanning moment, later, it is directed toward according to in-orbit antenna when lagging behind at the time of the first preset time period of current time corresponds to independently estimated in real time and determines that criterion selects and record quasi- number on duty to pass antenna channels with centroid of satellite-grounded receiving station line angle information and preset standard antenna on duty；After entering in the specified visible segmental arc in grounded receiving station in satellite, antenna channels record is passed according to number on duty quasi- in following first preset time period, determine that number on duty passes antenna channels and corresponding number passes segmental arc and carries out number over the ground and passes, until satellite leaves the visible segmental arc in grounded receiving station.It then automatically controls satellite and restores posture scanning.
Description
Technical field
The present invention relates to satellite data transmission antenna it is in-orbit it is autonomous preferably and implementation method, be suitable for various tracks, many attitude
Passing under control model without the fixed number over the ground for being directed toward satellite over the ground, is especially suitable for carrying out inertia observation to any space in universe
In low rail space science satellite over the ground number pass.
Background technique
The satellite main task that number passes over the ground is when satellite enters ground data station range of receiving (visible segmental arc), by root
According to the load that requires that treated and platform data after radio-frequency modulations, wave duct component of seeing off amplification, and passed by number and passed under antennas
Ground data station.After satellite goes out ground data station range of receiving, stopping sends data to the ground.Therefore satellite is needed to cross ground
When data station, number passes antenna beam and is directed toward within the tracking range of receiving in ground data receiving antenna on star.
The number over the ground of current satellite in orbit passes to be substantially to be completed by common antenna.Such as remote sensing, communication tradition are over the ground
Orientation or side-sway satellite over the ground, have it is fixed to ground, can be passed by number antenna to ground installation combine antenna be directed toward weave control,
Increasing antenna velocity of wave angle is motor-driven to specially the mode of number biography posture realizes that number biography antenna beam direction ground connects on star over the ground
It receives in following range.And other on-fixeds are directed toward satellite over the ground, such as certain scientific observation satellites, then are usually by interrupting director
It is engaged in and motor-driven to specially number passes posture realization over the ground.
But for having continuous observation or monitoring any direction satellite of demand or simultaneously there are a variety of different gesture stabilities
The satellite of directing mode, is on the one hand difficult to find that fixed direction over the ground, and midway is not on the other hand allowed to deviate observation posture again
It carries out special number over the ground to pass, the number biography antenna beam for just having to be used in combination the realization total space on star by multiple antenna covers
Lid.
And in terms of the specific implementation that number passes over the ground, current satellite in orbit, which is substantially, passes channel by infusing number on ground
The switching on and shutting down time completes data transmission work over the ground.And antenna beam can be realized over the ground due to only using a secondary number biography antenna
The direction of face range of receiving, usually number pass the time that the channel switch machine time is the visible segmental arc in satellite disengaging grounded receiving station,
Ground control is easy.
But the case where antenna joint realizes wave cover is passed for more secondary numbers, the same time there can only be common antenna channel work
Make, and the direction over the ground of antenna beam is directly related with the posture of satellite at that time, therefore counts have to when passing specific implementation over the ground
The direction over the ground of antenna beam is calculated according to the installation direction of the attitude of satellite and antenna, and condition over the ground is selected from multiple antenna
Preferably used as antenna on duty.And for inertia be directed toward etc. it is non-be directed toward satellite over the ground, satellite is once passing by segmental arc
Posture is also changing always over the ground, thus the wave beam of the primary in the course of transit same antenna might not be constantly in ground receiver with
Within the scope of track, it is possible to will appear the switching of antenna on duty.By taking the number of two secondary half space coverings passes antenna combination method as an example, root
According to theory analysis and simulation calculation, it is once in the course of transit at most likely to occur the switching of two secondary antennas.In this case, it counts over the ground
The implementation of biography controls, and not only needs preferred antenna on duty, also accurately to calculate the switching on and shutting down time (segmental arc of passing by of antenna on duty
Internal antenna wave beam disengaging ground receiver following range time) and antenna switch time.And for ground control is implemented,
At least to shift to an earlier date a rail to complete to infuse in accurate estimated and instruction, it is long-term to run difficulty and larger workload.
It is in-orbit by independently determining and controlling especially for posture on star, and the satellite under a kind of attitude control mode
The inertia that can change to axis variation or orientation axes spin direction is directed toward indefinite satellite, and ground is difficult the satellite by shifting to an earlier date several rails
Posture telemetry Accurate Estimation goes out to meet the posture over the ground of antenna beam ground receiver tracking accuracy requirement and posture change of passing by
Change process may result in number and pass loss of data.And the mode that several rails stop posture scanning in advance can lose a large amount of observation
Time.
In these cases, it is directed toward satellite over the ground for without fixation, the in-orbit autonomous management method of antenna is needed preferably to count
It passes antenna and carries out several biographies.
Summary of the invention
Technology of the invention solves the problems, such as: overcome the deficiencies in the prior art, is directed toward satellite over the ground for without fixation, proposes
A kind of even numbers passes the in-orbit autonomous management method of antenna, make satellite it is in office mean to observation/monitoring task work status under it is in-orbit
It is autonomous to complete to pass under data are timely and effective.
Technical Solving of the invention is: a kind of antenna in-orbit autonomous management of the double antenna without the fixed satellite of direction over the ground
Method, the double antenna pass antenna time-sharing multiplex channel realization data transmission system without fixed two number of the passing of satelline of being directed toward over the ground
Total space wave cover is swept when satellite operation is directed toward indefinite posture in the inertia that orientation axes change or orientation axes spin changes
When retouching under mode, it is achieved by the steps of the in-orbit autonomous management that number passes antenna channels:
(1.1), using satellite by the immigration moment in the visible segmental arc in grounded receiving station as starting point, be ahead of the starting point
At the time of one preset time period corresponds to, control satellite stops posture scanning, and the attitude of satellite is maintained at and stops the scanning moment
Three axis of inertia is directed toward, and later, each execution period executes step (1.2)；
(1.2), in-orbit independently to estimate in real time when lagging behind at the time of the first preset time period of current time corresponds to, some day
Line is directed toward and centroid of satellite-grounded receiving station line angle information, according to angle information and preset standard antenna criterion on duty
It selects and records quasi- number biography antenna channels on duty；
(1.3), after entering in the specified visible segmental arc in grounded receiving station in satellite, according to following first preset time period
Interior standard number on duty passes antenna channels record, determines that number passes segmental arc and number on duty passes antenna channels, and carry out number over the ground and pass:
(1.4), satellite controls satellite Autonomous and restores scanning mould by the departure moment in the visible segmental arc in grounded receiving station
Formula.
The step (1.3) determines that number passes segmental arc and number on duty passes antenna channels according to following principle:
(1.3.1), selected antenna number pass in segmental arc, and it is default to cannot be less than first with the number biography antenna duration surely on duty
Period；
(1.3.2), selected significant figure pass segmental arc, do not include satellite departure the moment before with surely it is on duty number pass antennas continue when
Between number on duty less than continuous two sections of standards before the segmental arc and departure of the second preset time period pass the antenna channels duration add up to it is small
In the segmental arc of the second preset time period；
(1.3.3), a satellite pass by during number biography, and at most number of progress passes antenna channels and switches；
First preset time period is determined according to following condition:
(1.1.1), the hardware being switched on again greater than number biography antenna channels shutdown implement constrained time interval requirement；
(1.1.2), stop the scanning required attitude stabilization time greater than satellite；
(1.1.3), under the premise of the condition that meets (1.1.1) and condition (1.1.2), selection as far as possible compared with fractional value, with
Shorten the time for stopping scanning.
The second preset time period Criterion of Selecting are as follows:
(1.3.2a) is less than satellite can be averaged the 1/3 of visible arc-segment time with single grounded receiving station；
(1.3.2b) is greater than the hardware that number biography antenna channels shutdown is switched on again and implements constrained time interval requirement.
It is real as follows when satellite operation is under inertial orientation three-axis stabilization mode and astronomic orientation slowly rotation mode
Now number passes the in-orbit autonomous management of antenna channels:
On star it is in-orbit independently to lagging behind at the time of current time third preset time period corresponds to when, a certain antenna be directed toward with
Centroid of satellite-grounded receiving station line angle information is estimated in real time, and only selects the satellite of selected grounded receiving station can
See in segmental arc that same number passes antennas and continuously meets quasi- antenna criterion duration longest segmental arc on duty as number biography segmental arcs on duty,
And it selects corresponding quasi- number biography antenna channels on duty to carry out number over the ground and passes.
The third preset time period is chosen for the specified visible arc-segment time of grounded receiving station single longest and adds default surplus.
The surplus is selected 1~3 minute.
The standard antenna selection criterion on duty are as follows:
(a), when certain count pass antenna be directed toward with centroid of satellite-grounded receiving station line angle be located at [0,89 °) when, selection should
Number passes antenna as quasi- antenna on duty；
(b), when certain count pass antenna be directed toward with centroid of satellite-grounded receiving station line angle be located at (91 °, л] when, selection is another
One number passes antenna as quasi- antenna on duty；
(c), it is located in [89 °, 91 °] range when certain counts to pass antenna and be directed toward with centroid of satellite-grounded receiving station line angle
When, maintain former quasi- antenna on duty constant.
The double antenna passes through software certainly without the fixed in-orbit autonomous management method of antenna for being directed toward satellite over the ground on satellite
Main realization.
Compared with the prior art, the invention has the advantages that:
(1), the present invention realizes in-orbit certainly without the fixed satellite total space timesharing of direction over the ground covering double antenna Data transfer system
Main number on duty passes channel and preferably uses with implementation, can effectively improve the autonomous management ability of satellite, guarantees that data are timely on star
Lower biography ground simultaneously reduces the long-term operation amount in ground.
(2), the present invention proposes that the satellite measured based on limited pre-set time single antenna in the visible segmental arc in grounded receiving station is referred to
Segmental arc preferred method is passed to antenna channels sum number is passed with centroid of satellite-grounded receiving station line angle predictive information number on duty,
And based on satellite operation mode gesture stability type characteristic propose it is different preferably and implementation method, solve various gesture stabilities
It is in-orbit certainly without the biography antenna channels of number over the ground under the fixed direction of the posture over the ground long-term continuous observation of satellite/monitoring demand under mode
It is main preferably and implementation issue.
(3), the present invention is based on the posture phases over the ground of satellite under inertial orientation three-axis stabilization mode and astronomic orientation slowly rotation mode
To the characteristics of accurately predicting is easy to, proposes and only select list in the visible segmental arc of single grounded receiving station satellite under such operating mode
The continuous segmental arc of antenna longest carry out number pass antenna channels preferably with implement criterion, in improve data transfer system use reliability
While, realize the visible segmental arc effective rate of utilization of satellite earth receiving station under such operating mode not less than 75%.
(4), the present invention is based on satellite under inertia direction non-directional scan pattern, posture is difficult to the characteristics of accurately predicting over the ground,
Propose under such operating mode using pass by stop sweeping and based on shorter lead estimate information carry out number pass antenna channels it is excellent
Select and allow the switching of most secondary antennas preferably and using criterion is implemented, guarantee data on star and pass at present, and guarantee to observe
Task is continuous.
Detailed description of the invention
Fig. 1 is that hard X ray of the embodiment of the present invention adjusts telescope (HXMT) satellite even numbers biography antenna channels switching principle figure；
Fig. 2 is that the number biography antenna that hard X ray of the embodiment of the present invention adjusts under the area telescope (HXMT) satellite little Tian mode exists
Rail manages independently design flow diagram.
Fig. 3 is that hard X ray of the embodiment of the present invention adjusts number telescope (HXMT) satellite positioning mode and toured the heavens under mode
Pass the in-orbit autonomous management design flow diagram of antenna.
Specific embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in detail.
Currently, double antenna includes that two mutually isostructural numbers pass antenna without the fixed satellite that is directed toward over the ground, two numbers pass antenna
Celestial body two sides, each hemispherical wave beam of antenna radiation pattern are installed in 180 °.Two number of the passing of satelline passes antenna channels and realizes number
According to Transmission system total space wave cover.
In order to complete multiple-task, general double antenna is divided into following two without the fixed operating mode for being directed toward satellite over the ground
Class:
(1), the first kind: non-directional is directed toward there are the inertia of orientation axes variation and the variation of orientation axes spin direction and scans mould
Formula；
(2), the second class: stable inertial orientation mode is directed toward to long-term three axis of inertia point, native to this world Celestial Objects are determined
Slowly mode is revolved to and around the astronomic orientation that celestial body single shaft at the uniform velocity rotates.
The present invention determines that number passes the in-orbit autonomous management method of antenna by different operating modes.
1, number passes the in-orbit autonomous management method of antenna under first kind operating mode
When satellite operation is directed toward indefinite posture scan pattern in the inertia that orientation axes change or orientation axes spin changes
When lower, it is achieved by the steps of the in-orbit autonomous management that number passes antenna channels:
(1.1), using satellite by the immigration moment in the visible segmental arc in grounded receiving station as starting point, be ahead of the starting point
At the time of one preset time period P1 is corresponded to, control satellite stops posture scanning, and the attitude of satellite is maintained at the stopping scanning moment
Three axis of inertia be directed toward, later, each executions period execution step (1.2)；
(1.2), in-orbit independently estimate in real time lags behind current time tkWhen the first preset time period P1 moment, a certain antenna
Direction and centroid of satellite-grounded receiving station line angle information are selected according to angle information and preset standard antenna criterion on duty
It selects and records quasi- number on duty and pass antenna channels；
(1.3), after satellite enters in the visible segmental arc in grounded receiving station, according to subsequent preset first preset time period
Quasi- number on duty passes antenna channels record in P1, according to following principle, determines that number passes segmental arc and number on duty passes antenna channels, and carry out
Number passes over the ground:
(1.3.1), selected antenna number pass in segmental arc, and it is default to cannot be less than first with the number biography antenna duration surely on duty
Period P1；
(1.3.2), selected significant figure pass segmental arc, do not include satellite departure the moment before with surely it is on duty number pass antenna channels hold
The continuous time passes the antenna channels duration less than continuous two sections of standards number on duty before the segmental arc and departure of the second preset time period P2
Total segmental arc less than the second preset time period P2；
(1.3.3), a satellite pass by during number biography, and at most number of progress passes antenna channels and switches；
(1.4), satellite restores scan pattern by the departure moment in the visible segmental arc in grounded receiving station, satellite Autonomous.
The first preset time period P1 is determined according to following condition:
(1.1.1), the hardware being switched on again greater than number biography antenna channels shutdown implement constrained time interval requirement；
(1.1.2), stop the scanning required attitude stabilization time greater than satellite；
(1.1.3), under the premise of the condition that meets (1.1.1) and condition (1.1.2), selection as far as possible compared with fractional value, with
Shorten the time for stopping scanning.
The second preset time period P2 Criterion of Selecting are as follows:
(1.3.2a) is less than list grounded receiving station used in satellite and is averaged the 1/3 of visible arc-segment time；
(1.3.2b) is greater than the hardware that number biography antenna channels shutdown is switched on again and implements constrained time interval requirement.
2, number passes the in-orbit autonomous management method of antenna under the second class operating mode
(native to this world Celestial Objects are determined when satellite operation revolves mode in inertial orientation three-axis stabilization mode and astronomic orientation slowly
At the uniform velocity rotate to and around star orientation axis) under when, be achieved by the steps of the in-orbit autonomous managements that number passes antenna channels:
It is in-orbit on star independently antenna a certain when lagging behind the third preset time period P3 moment at current time to be directed toward and satellite
Mass center-grounded receiving station line angle information is estimated in real time, and only selects the satellite visible arc of selected grounded receiving station
Same number biography antennas continuously meet quasi- antenna criterion duration longest segmental arc on duty as number biography segmental arcs on duty in section, and select
Selecting corresponding quasi- number biography antenna channels progress on duty, number passes over the ground.
The third preset time period P3 be chosen for satellite can the visible arc-segment time of menu grounded receiving station longest add it is default
Surplus；The surplus is selected 1~3 minute.
Number passes quasi- day line options on duty in the in-orbit autonomous management method of antenna under the above-mentioned first kind and the second class operating mode
Criterion are as follows:
(a), when certain count pass antenna be directed toward with centroid of satellite-grounded receiving station line angle be located at [0,89 °) when, selection should
Number passes antenna as quasi- antenna on duty；
(b), when certain count pass antenna be directed toward with centroid of satellite-grounded receiving station line angle be located at (91 °, л] when, selection is another
One number passes antenna as quasi- antenna on duty；
(c), it is located in [89 °, 91 °] range when certain counts to pass antenna and be directed toward with centroid of satellite-grounded receiving station line angle
When, maintain former quasi- antenna on duty constant.
Embodiment:
In conjunction with attached drawing 1~3, the present invention is carried out by hard X-ray Modulation Telescope (HXMT) satellite embodiment further
Explanation.
1. the data transmission system over the ground of total space covering
(1) antenna is selected and is installed: passing antenna using the identical orientation number of two auxiliary structures, every slave antenna directional diagram is
Hemispheric beam, two antennas are outside along axis, are mounted on celestial body two sides in 180 °, realize data transmission system by two antenna arrays
Total space wave cover.
(2) number passes channel composition and switching principle: two numbers pass antenna channels composition and switching principle is as shown in Figure 1.Number passes
Antenna channels are by 2 identical traveling wave tube assemblies (the first travelling-wave tubes component, the second traveling wave tube assembly), waveguide switch, 2 pairs
Identical number passes antenna (number passes antenna A, B) equipment composition such as composition and high frequency cable net.2 traveling wave tube assemblies are in-orbit
Cold standby realizes number on duty using switching or the setting of waveguide switch state by the first travelling-wave tubes component, the second traveling wave tube assembly
Pass the switching of antenna channels.
2. number passes the in-orbit autonomous switching approach of antenna and determines
In view of in-orbit row is put, switching is complicated, and in-orbit autonomous management uses shape based on the traveling wave tube assembly that real-time detection arrives
State, by waveguide switch it is straight-through/antenna that uses of crossing condition setting selection actual needs.In Fig. 1, first wave tube assembly and
Two traveling wave tube assemblies are mutually backups, and fixing 1 under normal circumstances, in running order (usual main part working condition is the first traveling wave
Tube assembly work), traveling wave tube assembly, waveguide switch and number pass antenna A or number passes antenna B and constitutes the first number and passes antenna channels and the
Two numbers pass antenna channels.
By taking the state of the first travelling-wave tubes component operation as an example, waveguide switch is set as pass-through state, passes antenna A using number,
I.e. first number passes antenna channels；Waveguide switch is set as crossing condition, passes antenna B using number, i.e., the second number passes antenna channels.
3. determining that number passes the instruction that channel autonomous management uses and sends sequence
Instruction sequence includes booting, switching and shutdown three classes instruction sequence
(1), 3 kinds of antenna power-on instruction sequences on duty, realize different situations under it is on duty number pass antenna channels selections and open
Machine number passes: antenna power-on instruction sequence A (waveguide switch is set as straight-through) on duty, antenna power-on instruction sequence B on duty (open by waveguide
Pass is set as intersecting), antenna power-on instruction sequence C on duty (waveguide switch be arranged state keep)；
(2), 2 kinds of antenna switching command sequences realize that two numbers pass the switching sum number biography of antenna channels: antenna switching command sequence
Column A (waveguide switch is switched to pass-through state by intersecting), (waveguide switch is switched to intersection by pass-through state to antenna switching command sequence B
State)；
(3), a kind of number passes channel power-down sequence, realizes that stopping number passing.
4. the satellite operation mode for pair needing to implement number biography is classified, and it is in-orbit from being responsible for determine that corresponding number passes antenna
Manage principle
(1) HXMT satellite needs to carry out data transmission under three kinds of observation modes, three kinds of observation modes and its gesture stability
Mode is respectively:
(a) tour the heavens mode: Direct to the sun spins at a slow speed gesture stability mode；
(b) fixed point mode: inertial orientation three-axis stabilization gesture stability mode；
(c) area little Tian mode: small angle rotation shuttle-scanning gesture stability mode.
The attitudes vibration of mode of touring the heavens in three kinds of operating modes and fixed point mode is stablized, and posture is easy to accurate pre- to satellite over the ground
It surveys.The area Er little Tian mode needs two axis rotating around satellite to be rotated, and direction of rotation often changes, it is difficult to accurate prediction
Satellite posture over the ground, thus be divided into two classes and carry out number and pass the design of antenna optimum principles.
(2) number passes the in-orbit autonomous management principle of antenna and determines:
(a) mode of touring the heavens and fixed point mode keep original gesture stability mode, and only using selected grounded receiving station satellite can
See the continuously available longest segmental arc of the same antenna in segmental arc, and selects respective counts to pass antenna channels and carry out number biography over the ground；
(b) area little Tian mode shifts to an earlier date the first preset time period before satellite enters the visible segmental arc in ground data station and stops sweeping holding
Inertial orientation three-axis stabilization continues former scanning mode out when visible segmental arc.It is continuous without using the same antenna in the visible segmental arc of satellite
It can stop sweeping the segmental arc of the first preset time period of lead and less than the departure frontal arc of the second preset time period with the immigration moment is less than
Section and two different antennae continuously available times are total less than most latter two different antennae before the departure of the second preset time period
Segmental arc, and primary in the course of transit at most only one secondary antenna switching of progress.
5. determining quasi- line options judgment criterion in day on duty
The standard antenna selection criterion on duty determined according to attitude prediction precision on star is as follows, and judgment threshold in-orbit can be modified:
(1) when number pass antenna A be directed toward with centroid of satellite-grounded receiving station line angle be located at [0,89 °) when, select number pass
Antenna A is as quasi- antenna on duty；
(2) when number pass antenna A be directed toward with centroid of satellite-grounded receiving station line angle be located at (91 °, л] when, select number pass
Antenna B is as quasi- antenna on duty；
(3) when number, which passes antenna A direction, to be located in [89 °, 91 °] range with centroid of satellite-grounded receiving station line angle,
Maintain former quasi- antenna on duty constant.
6. the number of fixed point and mode of touring the heavens passes the in-orbit autonomous management method of antenna
Flow chart is shown in Fig. 2, detailed process are as follows:
(1) number when control system independently estimates+15 minutes current times (third preset time period) in real time on star passes day
Line A is directed toward the angle with each grounded receiving station line of centroid of satellite-.
Third preset time period numerical value is chosen for the visible arc-segment time of satellite list grounded receiving station longest and adds more than 1~3 minute
Amount.Longest visible segmental arc in HXMT satellite list grounded receiving station is 12 minutes, and third preset time period is determined as 15 minutes.
(2) upper note number passes mission bit stream before m- third preset time period when into grounded receiving station on ground, comprising: into ground
Face receiving station time T0；Grounded receiving station time T1 out；The grounded receiving station that this circle uses；Play-back command parameter.
(3) since the T0- third preset time period moment, when data handling subsystem independently judges work locating for satellite on star
Mode is to be transferred to respective counts when pinpointing or tour the heavens mode and pass the in-orbit autonomous management determining program of antenna.
A. continuous collecting number passes antenna A direction and grounded receiving station binding clip angle information used in centroid of satellite-this circle, according to
Quasi- line options judgment criterion in day on duty judges quasi- antenna channels on duty and records, and stops to the T1- third preset time period moment；
B. it is selected in complete quasi- antenna channels variation array on duty during crossing grounded receiving station from the satellite of preservation same
Continuously longest segmental arc selects corresponding quasi- number on duty as number biography segmental arc (being assumed to be T0+x1~T0+x2 period) to antenna channels
The number on duty that antenna channels are passed as actual use passes antenna channels；
C. on the T0+x1 moment, star according to the use state of current travelling-wave tubes component and the setting state of waveguide switch from
It is main to send corresponding antenna power-on instruction sequence on duty；
D. number is independently sent on the T0+x2 moment, star passes channel power-down sequence.
7. the number of the area little Tian mode passes the in-orbit autonomous management method of antenna
Flow chart is shown in Fig. 3, detailed process are as follows:
(1) number when control system independently estimates+70 seconds current times (the first preset time period) in real time on star passes antenna A
It is directed toward the angle with each grounded receiving station line of centroid of satellite-.
First preset time period numerical value, which is chosen, is greater than the hardware implementation institute that the shutdown of HXMT satellite data transmission antenna channels is switched on again
The 1 minute time interval requirement of constraint, and be greater than satellite and stop needed for scanning the maximum attitude stabilization time 1 minute, and to the greatest extent may be used
It can be shortened and stop sweep time, determine that the first preset time period is 70 seconds.
(2) upper note number passes mission bit stream, packet before 15 minutes m- (third preset time period) when into grounded receiving station on ground
It includes: into grounded receiving station time T0；Grounded receiving station time T1 out；The grounded receiving station that this circle uses；Play-back command parameter.
It is matched to pass the in-orbit autonomous management method of antenna with the number for the mode that pinpoints and tour the heavens, it is minimum that the time is infused on surface instruction
Lead is unified for third preset time period, and note Timing Advance is greater than the requirement of the first preset time period in satisfaction.
(3) since the T0- third preset time period moment, when data handling subsystem independently judges work locating for satellite on star
When mode is the area little Tian mode, it is transferred to respective counts and passes the in-orbit autonomous management determining program of antenna.
A. " stopping scanning " instruction is independently sent on T0- the first preset time period moment star, and starts continuous collecting number
Antenna A direction and grounded receiving station binding clip angle information used in centroid of satellite-this circle are passed, while being sentenced according to quasi- day line options on duty
Disconnected criterion judges quasi- antenna channels on duty and records；
B. at the T0 moment, judge the standard of 70 seconds (the first preset time periods) having saved antenna channels array record on duty
Whether it is the same antenna, if the same antenna, is then selected as antenna channels on duty, and directly send out the antenna booting on duty at the T0 moment
Instruction sequence, and it is transferred to step f；Otherwise record changes moment (being assumed to be the T0+y1a moment) and continues to execute step c；
Whether the standard antenna on duty c. recorded during the T0+y1a moment judges T0+y1a~T0+y1a+69 is identical, if not
Together, then record second occurs (being assumed to be T0+y2a) at the time of quasi- antenna on duty variation, and by third standard day bank on duty
Duan Zuowei antenna segmental arc on duty uses, and send out on duty antenna power up sequences at the T0+y2a moment, then sends out number biography channel at the T1 moment
Power-down sequence terminates this number biography, and is transferred to step k；Otherwise using second standard antenna segmental arc on duty as antenna segmental arc on duty
It uses, sends out antenna power up sequences on duty at the T0+y1a moment, and continue to execute step d；
D. judge whether the standard antenna on duty of current record is identical as previous moment, it is identical, continue to judge, when T1
It carves, number is independently sent out on star and passes channel power-down sequence, terminate this number biography, and be transferred to step k；Otherwise it records and occurs standard for the second time and work as
(it is assumed to be T0+y2b) at the time of class's antenna variation, and continues to execute step e；
E. there is at the time of quasi- antenna on duty variation (T0+y2b) whether there are also 3 minutes away from departure (T1) in judgement second
The time of (the second preset time period), if sending out number less than 3 minutes at the T0+y2b moment and passing channel power-down sequence, and terminated this
Number passes, and is transferred to step k；Otherwise it is used using the quasi- antenna segmental arc on duty of third as antenna segmental arc on duty, at the T0+y2b moment
It sends out day line cutting machine sequence on duty, and sends out number at the T1 moment and pass channel power-down sequence, terminate this number biography, and be transferred to step k；
Second preset time period, which is chosen, to be greater than required by the hardware implementation that the shutdown of HXMT satellite data transmission antenna channels is switched on again
1 minute time interval, and be less than satellite can be averaged with single grounded receiving station visible segmental arc 10 minutes 1/3, be determined as 3 points
Clock.
F. judge whether the standard antenna on duty of current record is identical as previous moment, it is identical, continue to judge, when T1
It carves, number is independently sent out on star and passes channel power-down sequence, terminate this number biography, and be transferred to step k；Otherwise record variation the moment (assuming that
For the T0+y1b moment) and continue to execute step g；
G. judging to occur for the first time at the time of quasi- antenna on duty variation (T0+y1b), whether there are also 3 minutes away from departure (T1)
Time, if sending out number less than 3 minutes at the T0+y1b moment and passing channel power-down sequence, and terminated this number biography, and be transferred to step k；It is no
Then continue to execute step h；
Whether the standard antenna on duty h. recorded during the T0+y1b moment judges T0+y1b~T0+y1b+69 is identical, if phase
Together, then it is used using second standard antenna segmental arc on duty as antenna segmental arc on duty, sends out number biography antenna switching at the T0+y1b moment and refer to
Sequence is enabled, and continues to execute step i；Otherwise number is sent out at the T0+y1b moment and pass channel power-down sequence, and record second and standard occur
T0+y2d at the time of antenna on duty changes, and it is transferred to step j；
I. judge whether the standard antenna on duty of current record is identical as previous moment, it is identical, continue to judge, when T1
It carves, number is independently sent out on star and passes channel power-down sequence, terminate this number biography, and be transferred to step k；Otherwise judge that occurring standard for the second time works as
At the time of class's antenna variation (T0+y2c), and number is sent out at the T0+y2c moment and passes channel power-down sequence, terminate this number biography, and be transferred to
Step k；
J. there is at the time of quasi- antenna on duty variation (T0+y2d) whether there are also 3 minutes away from departure (T1) in judgement second
Time, if being transferred to step k less than 3 minutes；Otherwise it is used using the quasi- antenna segmental arc on duty of third as antenna segmental arc on duty,
It sends out antenna power-on instruction sequence on duty at the T0+y2d moment, and sends out number at the T1 moment and pass channel power-down sequence, terminate this number biography,
And it is transferred to step k；
K. " starting scanning " instruction is independently sent on T1 moment star, this number biography terminates, restores original scanning and observe appearance
State.
In conclusion the present invention on star number pass the in-orbit autonomous managements of antenna by way of can save satellite and ground interaction when
Between, number is carried out on the basis of real-time attitude on star and passes estimating of being directed toward over the ground of antennas, and completes antenna on duty within a very short time
Channel is preferably controlled with implementation, while guaranteeing that number passes time control precision, is reduced observation time to greatest extent and is damaged
It loses, also greatly reduces the difficulty and workload that ground is runed for a long time.
Unspecified part of the present invention belongs to technology and knowledge well known to those skilled in the art.
Claims (9)
1. a kind of double antenna is without the fixed in-orbit autonomous management method of antenna for being directed toward satellite over the ground, the double antenna without it is fixed over the ground
It is directed toward two number of the passing of satelline and passes antenna time-sharing multiplex channel realization data transmission system total space wave cover, it is characterised in that
When satellite operation orientation axes change or orientation axes spin variation inertia be directed toward under indefinite posture scan pattern when, pass through
Following steps realize that number passes the in-orbit autonomous management of antenna channels:
(1.1), using satellite by the immigration moment in the visible segmental arc in grounded receiving station as starting point, it is pre- to be ahead of the starting point first
If the period corresponds to, control satellite stops posture scanning, and the attitude of satellite is maintained to the inertia for stopping the scanning moment
Three axis are directed toward, and later, each execution period executes step (1.2)；
(1.2), in-orbit independently to estimate in real time when lagging behind at the time of the first preset time period of current time corresponds to, a certain antenna refers to
To with centroid of satellite-grounded receiving station line angle information, selected according to angle information and preset standard antenna criterion on duty
And it records quasi- number on duty and passes antenna channels；
(1.3), after entering in the specified visible segmental arc in grounded receiving station in satellite, according to quasi- in following first preset time period
Number on duty passes antenna channels record, determines that number passes segmental arc and number on duty passes antenna channels, and carry out number over the ground and pass:
(1.4), satellite controls satellite Autonomous and restores scan pattern by the departure moment in the visible segmental arc in grounded receiving station.
2. a kind of antenna in-orbit autonomous management method of the double antenna according to claim 1 without the fixed satellite of direction over the ground,
The step (1.3) determines that number passes segmental arc and number on duty passes antenna channels according to following principle:
(1.3.1), selected antenna number pass in segmental arc, cannot be less than the first preset time with the number biography antenna duration surely on duty
Section；
(1.3.2), selected significant figure pass segmental arc, do not include satellite departure the moment before with surely it is on duty number pass the antenna duration it is small
It is total less than that continuous two sections of standards before the segmental arc and departure of the second preset time period number on duty passes the antenna channels duration
The segmental arc of two preset time periods；
(1.3.3), a satellite pass by during number biography, and at most number of progress passes antenna channels and switches.
3. a kind of antenna in-orbit autonomous management method of the double antenna according to claim 1 without the fixed satellite of direction over the ground,
It is characterized in that first preset time period is determined according to following condition:
(1.1.1), the hardware being switched on again greater than number biography antenna channels shutdown implement constrained time interval requirement；
(1.1.2), stop the scanning required attitude stabilization time greater than satellite；
(1.1.3), under the premise of the condition that meets (1.1.1) and condition (1.1.2), selection is compared with fractional value as far as possible, to shorten
Stop the time of scanning.
4. a kind of antenna in-orbit autonomous management method of the double antenna according to claim 1 without the fixed satellite of direction over the ground,
It is characterized in that the second preset time period Criterion of Selecting are as follows:
(1.3.2a) is less than satellite can be averaged the 1/3 of visible arc-segment time with single grounded receiving station；
(1.3.2b) is greater than the hardware that number biography antenna channels shutdown is switched on again and implements constrained time interval requirement.
5. a kind of double antenna is without the fixed in-orbit autonomous management method of antenna for being directed toward satellite over the ground, it is characterised in that work as satellite operation
When under inertial orientation three-axis stabilization mode and astronomic orientation slowly rotation mode, be achieved by the steps of number pass antenna channels
Rail autonomous management:
On star it is in-orbit independently to lagging behind at the time of current time third preset time period corresponds to when, a certain antenna is directed toward and satellite
Mass center-grounded receiving station line angle information is estimated in real time, and only selects the satellite visible arc of selected grounded receiving station
Same number biography antennas continuously meet quasi- antenna criterion duration longest segmental arc on duty as number biography segmental arcs on duty in section, and select
Selecting corresponding quasi- number biography antenna channels progress on duty, number passes over the ground.
6. a kind of antenna in-orbit autonomous management method of the double antenna according to claim 5 without the fixed satellite of direction over the ground,
It is characterized in that the third preset time period be chosen for the specified visible arc-segment time of grounded receiving station single longest add it is default remaining
Amount.
7. a kind of antenna in-orbit autonomous management method of the double antenna according to claim 5 without the fixed satellite of direction over the ground,
It is characterized in that the surplus is selected 1~3 minute.
8. a kind of double antenna is without the fixed in-orbit autonomous management of antenna for being directed toward satellite over the ground according to claim 1 or described in 5
Method, it is characterised in that the standard antenna selection criterion on duty are as follows:
(a), when certain count pass antenna be directed toward with centroid of satellite-grounded receiving station line angle be located at [0,89 °) when, select the number
Antenna is passed as quasi- antenna on duty；
(b), when certain count pass antenna be directed toward with centroid of satellite-grounded receiving station line angle be located at (91 °, л] when, select another
Number passes antenna as quasi- antenna on duty；
(c), when certain, which counts biography antenna direction, is located in [89 °, 91 °] range with centroid of satellite-grounded receiving station line angle, dimension
It is constant to hold former quasi- antenna on duty.
9. a kind of double antenna is without the fixed in-orbit autonomous management of antenna for being directed toward satellite over the ground according to claim 1 or described in 5
Method, it is characterised in that independently realized on satellite by software.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910219160.8A CN110048760B (en) | 2019-03-21 | 2019-03-21 | Antenna on-orbit autonomous management method for double-antenna non-fixed earth-pointing satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910219160.8A CN110048760B (en) | 2019-03-21 | 2019-03-21 | Antenna on-orbit autonomous management method for double-antenna non-fixed earth-pointing satellite |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110048760A true CN110048760A (en) | 2019-07-23 |
| CN110048760B CN110048760B (en) | 2021-06-11 |
Family
ID=67273926
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910219160.8A Active CN110048760B (en) | 2019-03-21 | 2019-03-21 | Antenna on-orbit autonomous management method for double-antenna non-fixed earth-pointing satellite |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110048760B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115473570A (en) * | 2022-09-14 | 2022-12-13 | 国家卫星海洋应用中心 | Satellite observation data playback method, device and apparatus |
| CN117544214A (en) * | 2023-05-23 | 2024-02-09 | 国家卫星海洋应用中心 | Satellite earth data transmission method, device, equipment and readable storage medium |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101697010A (en) * | 2009-10-27 | 2010-04-21 | 电子科技大学 | Method for constructing multifunctional linear array three-dimensional synthetic aperture radar (SAR) system |
| TW201218513A (en) * | 2010-06-08 | 2012-05-01 | Echostar Technologies Llc | Antenna orientation determination |
| WO2014144920A2 (en) * | 2013-03-15 | 2014-09-18 | Maxtena, Inc. | Method and apparatus for establishing communications with a satellite |
| CN105180926A (en) * | 2015-09-21 | 2015-12-23 | 中国科学院国家天文台 | Method for judging synchronous orbit space object attitude stabilization mode |
| CN107154532A (en) * | 2017-04-17 | 2017-09-12 | 北京臻迪科技股份有限公司 | A kind of multiple antennas control method, control system and smart machine |
| CN108616809A (en) * | 2018-04-12 | 2018-10-02 | 新华三技术有限公司 | A kind of antenna element selection method and device |
-
2019
- 2019-03-21 CN CN201910219160.8A patent/CN110048760B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101697010A (en) * | 2009-10-27 | 2010-04-21 | 电子科技大学 | Method for constructing multifunctional linear array three-dimensional synthetic aperture radar (SAR) system |
| TW201218513A (en) * | 2010-06-08 | 2012-05-01 | Echostar Technologies Llc | Antenna orientation determination |
| WO2014144920A2 (en) * | 2013-03-15 | 2014-09-18 | Maxtena, Inc. | Method and apparatus for establishing communications with a satellite |
| CN105180926A (en) * | 2015-09-21 | 2015-12-23 | 中国科学院国家天文台 | Method for judging synchronous orbit space object attitude stabilization mode |
| CN107154532A (en) * | 2017-04-17 | 2017-09-12 | 北京臻迪科技股份有限公司 | A kind of multiple antennas control method, control system and smart machine |
| CN108616809A (en) * | 2018-04-12 | 2018-10-02 | 新华三技术有限公司 | A kind of antenna element selection method and device |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115473570A (en) * | 2022-09-14 | 2022-12-13 | 国家卫星海洋应用中心 | Satellite observation data playback method, device and apparatus |
| CN115473570B (en) * | 2022-09-14 | 2023-10-24 | 国家卫星海洋应用中心 | Satellite observation data playback method, device and apparatus |
| CN117544214A (en) * | 2023-05-23 | 2024-02-09 | 国家卫星海洋应用中心 | Satellite earth data transmission method, device, equipment and readable storage medium |
| CN117544214B (en) * | 2023-05-23 | 2024-05-24 | 国家卫星海洋应用中心 | Satellite earth data transmission method, device, equipment and readable storage medium |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110048760B (en) | 2021-06-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Busch et al. | UWE-3, in-orbit performance and lessons learned of a modular and flexible satellite bus for future pico-satellite formations | |
| CN110048760A (en) | A kind of antenna in-orbit autonomous management method of the double antenna without the fixed satellite of direction over the ground | |
| US5227802A (en) | Satellite system cell management | |
| CN112580906A (en) | Satellite remote sensing task planning and ground resource scheduling combined solving method | |
| CN111338367B (en) | Method for determining middle track under double-pulse control of same track for eccentricity freezing | |
| CN109639341B (en) | Method for autonomously accessing low-orbit broadcast satellite without ephemeris | |
| CN112465296A (en) | Dynamic task re-planning method for agile satellite | |
| CN110299938B (en) | Ground measurement and control resource scheduling method suitable for low-earth orbit satellite | |
| CN108199763B (en) | Repeater satellite method for scheduling task and system | |
| EP3978371B1 (en) | Satellite constellation forming system, satellite constellation formimg method | |
| CN106933121B (en) | The spot beam anternma control method of task based access control spatial and temporal distributions characteristic | |
| Sun et al. | Adaptive node and power simultaneous scheduling strategy for target tracking in distributed multiple radar systems | |
| Yang et al. | Problem A of 9th China trajectory optimization competition: Results found at NUAA | |
| CN110535523A (en) | A kind of method that trunk subscriber terminal independently switches tracking relay satellite | |
| CN114926021B (en) | Satellite time sequence optimal task planning method based on integration of imaging segmentation and planning | |
| Smith et al. | Mission control for the 48-satellite Globalstar constellation | |
| EP3978372A1 (en) | Satellite constellation formation system, satellite constellation formation method, satellite constellation, deorbiting method, debris collection method, and ground device | |
| KR100618655B1 (en) | Apparatus and method for automated station keeping of geostationary satellite | |
| US11888519B1 (en) | Optical communication satellite cross-connect | |
| CN116208236B (en) | SAR satellite constellation task planning method | |
| Bokulic et al. | Recovery of a spacecraft from Sun-safe mode using a fanbeam antenna | |
| CN114035912B (en) | Autonomous running method of agile satellite data transmission element task sequence | |
| Lin | Mission planning for electromagnetism environment monitors satellite based on heuristic tabu search algorithm | |
| Rao et al. | Designing An On‐board Macro Executor For Payload (MEP) For Optimized Payload Operations Of Earth Observation Satellites | |
| Miller | Pioneer Venus 1978 mission support |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |