CN102874418B - Method for improving orbit-transferring safety of inclined orbit satellite - Google Patents
Method for improving orbit-transferring safety of inclined orbit satellite Download PDFInfo
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- CN102874418B CN102874418B CN201210411126.9A CN201210411126A CN102874418B CN 102874418 B CN102874418 B CN 102874418B CN 201210411126 A CN201210411126 A CN 201210411126A CN 102874418 B CN102874418 B CN 102874418B
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Abstract
The invention relates to a method for improving the orbit-transferring safety of an inclined orbit satellite, wherein the problem of energy-source shortage of the inclined orbit satellite in the period of orbit-transferring motorization under the condition of high solar angles is solved through the reasonable adjustment of flight events by considering the condition of solar altitude angles in the designing process of a flight program, and meanwhile, flight-control operation can be simplified. The discharging time of a storage battery in the period of orbit-transferring ignition can be shortened by designing the flight program according to the method, so that the load power in the power-supplying period of the storage battery is reduced, therefore the discharging depth of the storage battery is reduced, the energy-source safety of the satellite is ensured, and a launch window is not limited by solar illumination angles.
Description
Technical field
The present invention relates to a kind of method improving the safety of inclined plane Satellite Orbit Maneuver, the safety of the energy, thermal control during can guaranteeing Satellite Orbit Maneuver, mainly use during inclined plane satellite flies control.
Background technology
General geo-synchronous orbit satellite due to launch enter the orbit after solar elevation lower, between change rail burn period, solar irradiation angle (sunray and the sunray angle between the projection in satellite orbit face) is little, meet the power demands of satellite, therefore the mission program design become during rail generally need not consider the problem of energy deficiency, during common change rail mission program method of designing into: according to change rail strategy, follow the tracks of segmental arc, sequentially arrange earth acquisition and set up the earth to point to attitude, Gyro Calibration under earth sensing attitude, prepare before becoming rail, erect windsurfing and set up firing attitude, kick-in-the-apogee, igniting terminates the TT&C event such as rear state is arranged.
But for inclined plane satellite, launch in Various Seasonal, solar elevation difference is larger.In high sun angle situation, satellite terminates again to recover the earth to igniting and points in the whole time period of attitude from setting up firing attitude, solar irradiation angle (angle of windsurfing normal and sunshine) is comparatively large, and solar wing horsepower output can not meet power satellite demand.When solar elevation reaches more than 70 °, horsepower output is very little, main by storage battery power supply, time of battery discharging is that satellite is set up the time becoming rail firing attitude and again made windsurfing to the time of day after igniting terminates, and bearing power comprises the power of satellite platform equipment and associated heater.According to calculating, in high sun angle situation, according to high rail DESIGN OF SATELLITE FLIGHT method in common, the depth of discharge of storage battery can exceed design value, affects the power supply safety of satellite.If by the design changing satellite, as increased accumulator capacity, or change the launch window of satellite, launch as only selected the season solar elevation is little, then may increase the development cost of satellite, even affect completing of satellite launch task, as networking satellite, possibly cannot avoid and launching in the season of high sun angle.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, the method of inclined plane Satellite Orbit Maneuver safety is improved under providing a kind of high sun angle situation, by the temperature control threshold value of Reasonable adjustment temperature booster, the action opportunity of the fly event such as satellite attitude and perpendicular windsurfing, reduce the depth of discharge of the storage battery become during rail as far as possible, guarantee the energy and the thermal control safety of satellite.
Technical solution of the present invention is: a kind of method improving the safety of inclined plane Satellite Orbit Maneuver, and step is as follows:
(1) calculate the solar elevation θ s of time of ignition t, described solar elevation is the earth and the angle between sun line and orbit plane; If θ s < is y, then the control program that conveniently flies carries out change rail; Otherwise go to step (2), described y=arccos (t bearing power/solar wing exports full power)
(2) according to sending time and the yaw attitude regulation time of setting up firing attitude telecommand, the firing attitude moment is set up in design;
(3) establish the earth under calculating not perpendicular solar array situation point to the solar irradiation angle θ sa0 of attitude moment t0 and establish the solar irradiation angle θ sa1 of firing attitude moment t1; Described solar irradiation angle is the angle of windsurfing normal and sunray;
(4) according to the result of calculation of step (3), if θ sa0 < θ is sa1, then establishes after the earth points to attitude at satellite and carry out perpendicular windsurfing operation immediately; Otherwise, before setting up firing attitude, carry out perpendicular windsurfing operation;
(5) the battery discharging degree of depth X become between rail burn period is calculated, if X > is m, the temperature control threshold value then heightening not area of illumination temperature booster during becoming rail after establishing earth sensing attitude, to the safety value upper limit, turns down the temperature control threshold value of not area of illumination temperature booster to safety value lower limit before setting up firing attitude; Otherwise do not carry out the temperature control adjusting thresholds of temperature booster, described m is the maximum permission depth of discharge of transfer orbit storage battery;
(6) judge to light a fire and terminate rear perigee of orbit height and whether be less than the minimum use requirement for height of earth sensor on satellite, if be less than, then satellite goes out at this cruise attitude proceeding to Direct to the sun before segmental arc is followed the tracks of in observing and controlling; Otherwise go to step (7);
(7) satellite yaw angle Offset and windsurfing corner under design earth sensing attitude: if the solar elevation θ s < (90 ° of-β) calculated in step (1), then arrange yaw angle Offset and be-90 °, windsurfing corner is-90 °; Otherwise, yaw angle Offset keep 0 ° constant, windsurfing follow the tracks of the sun; Described β=arccos (bearing power/solar wing exports full power).
Battery discharging degree of depth X=100%* ((((P1-P0) * T1)/U)/Ah) in described step (5); Wherein, P1 becomes the bearing power between rail burn period; Solar wing horsepower output P0=P*cos (θ sa), P are that solar wing exports full power, and θ sa is the solar irradiation angle of time of ignition; T1 sets up firing attitude terminate to becoming rail igniting and recover the time that the earth points to attitude; U is the bus voltage in storage battery power supply situation; Ah is the specified ampere-hour of storage battery.
Before the igniting of change rail, gas cylinder is heated to more than temperature Tw, Tw=tw+v*T2;
Wherein, tw is gas cylinder temperature requirement value lower limit; V is ignition process gas cylinder temperature descending speed; T2 is for becoming rail point of ignition.
After described step (6) igniting terminates, increase and judge whether the solar elevation of satellite change next time rail time of ignition t exceedes the measurement range of sun sensor, if exceed, establish the earth before then judging to become rail igniting next time again and point to attitude to the nominal time of setting up the time before firing attitude and whether meet satellite gyroscope, if do not meet, then become after rail terminates at this and increase a Gyro Calibration operation.
The present invention's beneficial effect is compared with prior art:
(1) energy security of satellite is the basis that satellite succeeds in sending up and normally works in-orbit.But inclined plane satellite is when launching some season, solar elevation is high, thus cause satellite to the whole time period of igniting end again recovery earth sensing attitude, to need storage battery power supply from setting up firing attitude, if the battery discharging degree of depth exceedes design value, satellite energy security can be affected.The present invention is not when changing the design of satellite (as increased accumulator capacity) or adjustment launch window, by the Reasonable adjustment becoming satellite hot control system temperature control threshold value before and after rail, fly event implements time and order and attitude and windsurfing corner, under just can guaranteeing high solar elevation situation, the energy of satellite and thermal control safety.Reduce the development cost of change design of satellites on the one hand, decrease the restriction to launch window simultaneously, make the launch time of inclined plane satellite more flexible.
(2) time gap between inclined plane satellite each change rail is longer, and there is the invisible segmental arc of observing and controlling, and the safety mode proceeding to Direct to the sun after each time change rail terminates can guarantee the energy and the thermal control safety of satellite.But, if proceed to Direct to the sun safety mode, then before becoming rail next time, need to re-start earth acquisition and set up the observing and controlling operation that the earth points to attitude.The invention provides the yaw attitude by satellite under adjustment earth sensing attitude and windsurfing corner method, on the basis of guaranteeing the satellite energy and thermal control safety, observing and controlling operation can be simplified.
(3) become in rail ignition process, gas cylinder temperature can decline rapidly.If gas cylinder temperature is too low, then can affects propulsion system and normally work.If but gas cylinder temperature is too high, then gas cylinder has the danger of blasting.The present invention is by Reasonable adjustment gas cylinder temperature, and during can ensureing to become rail, the temperature of gas cylinder is in required value scope.
(4) after satellite sets up firing attitude, if do not meet the field range of sun sensor, gyro then can only be used as the gauge reference target of yaw attitude, and the time requirement of Gyro Calibration is more than 40 minutes, if due to the restriction of observing and controlling tracking time, cause Gyro Calibration deficiency of time and make calibration result inaccurate.Time after the present invention is terminated by Appropriate application change rail, this problem can be solved.
Accompanying drawing explanation
Fig. 1 is Satellite Orbit Maneuver process schematic;
Fig. 2 is diagram of circuit of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is further described in detail.
The energy and thermal control are safely the bases of implementing the motor-driven work of Satellite Orbit Maneuver.But, at the inclined plane satellite (55 °, common inclination angle) that some season launches, solar elevation can be very large (if inclination angle is 55 °, then solar elevation is 55 ° (inclination angles)+23.5 ° (angle in ecliptic and equator)=78.5 ° to the maximum), thus cause satellite to terminate again to recover in the time period of earth sensing attitude to igniting from setting up firing attitude, solar irradiation angle (angle of windsurfing normal and sunshine) is larger, solar wing horsepower output can not meet power satellite demand, needs storage battery power supply.But the finite capacity of storage battery, if depth of discharge is excessive, then can affect the power supply safety of satellite.
The invention provides a kind of method, time and the order of Reasonable adjustment temperature booster temperature control threshold value and fly event can be passed through, shorten the discharge time of storage battery to a great extent, reduce bearing power, thus reduce the battery discharging degree of depth, guarantee satellite energy security.
In order to clearer understanding the present invention, first the change rail process of satellite routine is described below, as shown in Figure 1, satellite generally carries out 3-4 change rail, each time change rail process is close, if main difference point is that before becoming rail igniting, satellite has worked in earth sensing attitude, then without the need to carrying out earth acquisition operation.
Satellite, before the igniting of change rail, first catches the earth, and (, perpendicular to the orbit plane flown, positive dirction points to the celestial sphere South Pole for OY axle and pitch axis to set up earth sensing attitude; OZ axle and yaw axis forward point to the earth's core; OX axle and the axis of rolling and OY axle and OZ axle form right-handed helix direction).If satellite has been in the earth and has pointed to attitude, then do not carry out this work.Dead work carry out the igniting such as Gyro Calibration under ground refers to attitude before, perpendicular windsurfing (make windsurfing normal parallel with the X-axis of satellite), (OX axle is positioned at the orbit plane of satellite flight, the working direction of positive dirction sensing satellite to set up firing attitude; OZ axle forward points to the earth's core; OY axle and OZ axle and OX axle form right-handed helix direction).After Satellite Orbit Maneuver igniting terminates, recover the earth and point to attitude.
The present invention becomes on rail process basis in routine, improves the safety of IGSO Satellite Orbit Maneuver through the following steps, is mainly reflected in three aspects:
One, the optimization of the front fly event of rail igniting is become
(1) calculate the solar elevation θ s of time of ignition t, described solar elevation is the angle of sunray vector and orbital plane, if θ s < is y, then the control program that conveniently flies carries out change rail; Otherwise go to step (2); Described y=arccos (t bearing power/solar wing exports full power);
According to the change rail strategy file of satellite, the track of satellite before and after known each change rail igniting.If obtaining time of ignition t sun unit vector at the component of orbital coordinate system according to orbit information is Sox, Soy, Soz, the solar elevation of t is: θ s=arcsin (Soy).Described θ s < y degree is empirical equation, when θ s < y degree, after satellite sets up firing attitude, solar wing horsepower output can meet load needs, storage battery does not discharge or discharges very little, and flight control program can not consider the problem of energy deficiency.
(2) according to sending time and the yaw attitude regulation time of setting up firing attitude telecommand, firing attitude moment t2 is set up in design;
Within t2 minute before turning ignition mode, start the operation of carrying out setting up firing attitude, in high solar elevation situation, in order to reduce discharge time of accumulator, need as far as possible retardation time t2, can set as follows: t2=(transmission set up firing attitude telecommand time+yaw attitude regulation time (containing the attitude stabilization time)) * 2.
(3) establish the earth under calculating not perpendicular solar array situation point to the solar irradiation angle θ sa0 of attitude moment t0 and establish the solar irradiation angle θ sa1 of firing attitude moment t1; Described solar irradiation angle is the angle of windsurfing normal and sunray;
If calculating t0, t1 moment sun unit vector at the component of satellite body system of axes according to track and attitude information is Sbx, Sby, Sbz, the body concrete according to solar array points to and calculates solar irradiation angle, if Orientation of solar panel-X-axis, then solar irradiation angle is: θ sa0=arccos (-Sbx); If Orientation of solar panel-Z axis, then solar irradiation angle is: θ sa1=arccos (-Sbz).
(4) according to the result of calculation of step (3), if θ sa0 < θ is sa1, then establishes after the earth points to attitude at satellite and carry out perpendicular windsurfing operation immediately; Otherwise, before setting up firing attitude, carry out perpendicular windsurfing operation;
(5) the battery discharging degree of depth X become between rail burn period is calculated, if X > is m, the temperature control threshold value then heightening not area of illumination temperature booster during becoming rail after establishing earth sensing attitude, to the safety value upper limit, turns down the temperature control threshold value of not area of illumination temperature booster to safety value lower limit before setting up firing attitude; Otherwise do not carry out the temperature control adjusting thresholds of temperature booster, described m is the maximum permission depth of discharge of transfer orbit storage battery;
Battery discharging degree of depth X=100%* ((((P1-P0) * T1)/U)/Ah); Wherein, P1 becomes the bearing power between rail burn period; Solar wing horsepower output P0=P*cos (θ sa), P are that solar wing exports full power, and θ sa is the solar irradiation angle of time of ignition; T1 sets up firing attitude terminate to becoming rail igniting and recover the time that the earth points to attitude; U is the bus voltage in storage battery power supply situation; Ah is the specified ampere-hour of storage battery.；
Two, the setting that rail terminates rear satellite attitude is become
Arrive before target track at satellite, satellite becomes the cruise attitude that can proceed to Direct to the sun after rail terminates at every turn or under ground refers to attitude, makes solar irradiation angle remain at solar wing export the scope that can meet loading demand by adjusting yaw attitude and windsurfing corner.Attitude according to following method setting satellite can reach the object meeting energy demand and simplify observing and controlling operation simultaneously:
(6) if this change rail is lighted a fire, the perigee of orbit height after terminating is less than the minimum use requirement for height of earth sensor, then satellite goes out at this cruise attitude proceeding to Direct to the sun before segmental arc is followed the tracks of in observing and controlling; Otherwise go to step (7);
(7) satellite yaw angle Offset and windsurfing corner under design earth sensing attitude: if the solar elevation θ s < (90 ° of-β) calculated in step (1), yaw angle Offset is then set and is-90 °, satellite+Y is made to point to the working direction (supposing that X face is by the long-term operation on orbit design conditions of shining for satellite) of satellite, windsurfing corner is-90 °, can guarantee that solar wing horsepower output meets load request; Otherwise, yaw angle Offset keep 0 ° constant, the sun (as solar irradiation angle > β, need adjustment windsurfing corner, this is well known practice in the industry, does not describe in detail) followed the tracks of by windsurfing; Described β=arccos (bearing power/solar wing exports full power).
Three, other security measures
1, become between rail burn period, gas cylinder temperature can decline rapidly, for guaranteeing that gas cylinder temperature is in required value scope, in advance gas cylinder need be heated to certain more than temperature Tw before ignition, Tw=tw+v*T2;
Wherein, tw is gas cylinder temperature requirement value lower limit; V is ignition process gas cylinder temperature descending speed; T2 is for becoming rail point of ignition.
2, when solar elevation exceedes sun sensor measurement range (being generally 60 °), need, by the yaw attitude of gyro to measure satellite, for ensureing the change rail precision of satellite, need to carry out accurate calibration to gyro.The moment of Gyro Calibration is generally arranged in sets up firing attitude and stablizes to setting up in the time period T3 before firing attitude, because Gyro Calibration time General Requirements is more than 40 minutes, if next time becomes the prefiring T3 < of rail 40 minutes, then become after rail terminates at this and increase a Gyro Calibration operation, for using when becoming rail next time.
The inventive method can on the basis of orthodox flight control program in actual application, and the content according to above-mentioned various piece adjusts the corresponding contents flying control program, to reach the object improving Satellite Orbit Maneuver safety.During China's many inclined plane Satellite Orbit Maneuver, the depth of discharge of storage battery during adopting the present invention to greatly reduce change rail, simplify and fly control operation, gas cylinder temperature, within the scope of required value, ensure that the energy and the thermal control safety of Satellite Orbit Maneuver mobile process.
The content be not described in detail in specification sheets of the present invention belongs to the known technology of professional and technical personnel in the field.
Claims (3)
1. improve a method for inclined plane Satellite Orbit Maneuver safety, it is characterized in that step is as follows:
(1) calculate the solar elevation θ s of time of ignition t, described solar elevation is the earth and the angle between sun line and orbit plane; If θ s < is y, then the control program that conveniently flies carries out change rail; Otherwise go to step (2), described y=arccos (t bearing power/solar wing exports full power);
(2) according to sending time and the yaw attitude regulation time of setting up firing attitude telecommand, the firing attitude moment is set up in design;
(3) establish the earth under calculating not perpendicular solar array situation point to the solar irradiation angle θ sa0 of attitude moment t0 and establish the solar irradiation angle θ sa1 of firing attitude moment t1; Described solar irradiation angle is the angle of windsurfing normal and sunray;
(4) according to the result of calculation of step (3), if θ sa0 < θ is sa1, then establishes after the earth points to attitude at satellite and carry out perpendicular windsurfing operation immediately; Otherwise, before setting up firing attitude, carry out perpendicular windsurfing operation;
(5) the battery discharging degree of depth X become between rail burn period is calculated, if X > is m, the temperature control threshold value then heightening not area of illumination temperature booster during becoming rail after establishing earth sensing attitude, to the safety value upper limit, turns down the temperature control threshold value of not area of illumination temperature booster to safety value lower limit before setting up firing attitude; Otherwise do not carry out the temperature control adjusting thresholds of temperature booster, described m is the maximum permission depth of discharge of transfer orbit storage battery; Described battery discharging degree of depth X=100%* ((((P1-P0) * T1)/U)/Ah); Wherein, P1 becomes the bearing power between rail burn period; Solar wing horsepower output P0=P*cos (θ sa), P are that solar wing exports full power, and θ sa is the solar irradiation angle of time of ignition; T1 sets up firing attitude terminate to becoming rail igniting and recover the time that the earth points to attitude; U is the bus voltage in storage battery power supply situation; Ah is the specified ampere-hour of storage battery;
(6) judge to light a fire and terminate rear perigee of orbit height and whether be less than the minimum use requirement for height of earth sensor on satellite, if be less than, then satellite goes out at this cruise attitude proceeding to Direct to the sun before segmental arc is followed the tracks of in observing and controlling; Otherwise go to step (7);
(7) satellite yaw angle Offset and windsurfing corner under design earth sensing attitude: if the solar elevation θ s < (90 ° of-β) calculated in step (1), then arrange yaw angle Offset and be-90 °, windsurfing corner is-90 °; Otherwise, yaw angle Offset keep 0 ° constant, windsurfing follow the tracks of the sun; Described β=arccos (bearing power/solar wing exports full power).
2. a kind of method improving the safety of inclined plane Satellite Orbit Maneuver according to claim 1, is characterized in that: before the igniting of change rail, gas cylinder is heated to more than temperature Tw, Tw=tw+v*T2;
Wherein, tw is gas cylinder temperature requirement value lower limit; V is ignition process gas cylinder temperature descending speed; T2 is for becoming rail point of ignition.
3. a kind of method improving the safety of inclined plane Satellite Orbit Maneuver according to claim 1 and 2, it is characterized in that: after described step (6) igniting terminates, increase and judge whether the solar elevation of satellite change next time rail time of ignition t exceedes the measurement range of sun sensor, if exceed, establish the earth before then judging to become rail igniting next time again and point to attitude to the nominal time of setting up the time before firing attitude and whether meet satellite gyroscope, if do not meet, then become after rail terminates at this and increase a Gyro Calibration operation.
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