CN112623277B - Orbital transfer method for quickly arriving circular orbit targets with different surfaces in space - Google Patents
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Abstract
The invention relates to a track transfer method for quickly arriving a spatial different-surface circular track target, which innovatively designs a virtual track and optimizes the virtual track to obtain the optimal intersection phase and intersection time of the spatial target; the optimal time and the phase of the service aircraft entering the elliptic transfer orbit are obtained by reversely deducing the optimal rendezvous phase and the rendezvous time; obtaining the track phase adjustment amplitude and the adjustment time of the service aircraft according to the initial position of the service aircraft and the phase of the service aircraft entering the elliptic transfer track; and adjusting the amplitude and the adjusting time according to the track phase of the service aircraft to obtain the parking waiting time of the service aircraft on the initial track. Therefore, the service aircraft orbital transfer strategy can be calculated.
Description
Technical Field
The invention belongs to the technical field of on-orbit service and maintenance of a spacecraft.
Background
The in-orbit service and maintenance are one of leading-edge hotspots of the aerospace technology, the service aircraft performs service operations such as close-range observation, module replacement, fuel filling, auxiliary orbit transfer and the like after approaching a space target satellite, and can realize the in-orbit fault recovery of the target satellite and prolong the service life, thereby continuously exerting the in-orbit application value and generating great economic benefit. In order to implement service operation on a spatial target satellite, one of the preconditions is that the target satellite arrives near the target satellite, close-range detailed observation is implemented on the target satellite, geometric characteristics, spatial attitude and the like of the target satellite are found out, and required observation input is provided for the service operation.
The service aircraft can reach the vicinity of the target satellite only through the orbital transfer maneuver, before orbital transfer, the service aircraft and the target satellite are usually located in different orbital planes, and the service aircraft and the target satellite are located in circular orbits, so that the method has very important practical significance for fast arriving orbital transfer strategy research of an out-of-plane circular orbit space target.
The existing research on the orbital transfer strategy is developed for a common-rail-surface space target, and for a different-rail-surface space target, a Lambert orbital transfer mode is adopted, which generally requires a service aircraft to carry a large amount of orbital transfer fuel. It is necessary to provide a novel time-saving and fuel-saving orbital transfer strategy aiming at the task of quickly arriving a circular orbit target with different spatial surfaces, and orbital transfer times, orbital transfer time and orbital transfer speed increment required by a service aircraft for realizing the arrival observation of a target satellite are given through the orbital transfer strategy.
At present, no published literature report and patent of the method for designing the orbital transfer strategy of the space different-plane circular orbit target satellite, which is the same as the patent, exists at home and abroad.
Disclosure of Invention
The technical problem solved by the invention is as follows: a service aircraft is an orbital transfer strategy for quickly and fuel-efficiently arriving space target satellites in different circular orbital planes.
The technical scheme of the invention is as follows: a rail changing method for quickly arriving a space out-of-plane circular orbit target is realized by the following steps:
s1, setting a virtual service aircraft and an initial orbit element thereof, wherein the orbit of the virtual service aircraft is the same as the orbit of the target aircraft in height but not on the same orbit plane;
s2, calculating the phase P of the space virtual service aircraft when the virtual service aircraft meets the target aircraft by using the virtual service aircraft orbitsAnd phase P of the target aircraftt；
S3, calculating the time T of the target aircraft from the initial position to the intersection phase according to the initial phase of the target aircraft and the phase of the target aircraft at the intersection calculated in S2t；
S4, calculating the actual service space vehicle on the ellipse transfer orbit according to the semimajor axis of the actual space vehicle orbit and the semimajor axis of the target vehicle orbitWhen flying, the combination of the time T used in S3tDetermining the time T when the actual service aircraft of the space enters the elliptic transfer orbitb(ii) a And according to the phase P in S2sCalculating the phase P of the actual service space aircraft on the initial orbit at the moment of entering the ellipse transfer orbitb；
S5, according to the phase P calculated in S4bTime TbAnd initial phase P in initial orbit element of virtual service aircraft in S1siCalculating the track phase adjustment amplitude value P before the practical space service aircraft enters the ellipse transfer trackA；
S6, calculating the orbit motion period of the space practical service aircraft on the initial orbit according to the orbit semimajor axis of the space practical service aircraft, and combining the orbit phase adjustment amplitude P in S5ACalculating the required speed increment D for adjusting the track phase of the space actual service aircraftvpAnd time T for phase adjustmentADetermining the parking waiting time T of the actual service aircraft in the space on the initial orbitw；
S7, calculating the orbital transfer speed increment D required by the actual service spacecraft in the space to enter the elliptic transfer orbit according to the semimajor axis of the actual spacecraft orbit in the space and the semimajor axis of the target spacecraft orbitve；
S8, according to the parameters calculated by S4-S7, the space practical service aircraft can rapidly arrive at the intersection with the space target aircraft at the far place of the oval transfer orbit according to the strategy that the space practical service aircraft waits for the initial orbit parking, then enters the phase modulation orbit, and enters the oval transfer orbit after the phase modulation is finished.
Preferably, the semi-major axis of the orbit of the virtual service aircraft in S1 is the same as the semi-major axis of the target aircraft, and the eccentricity, the inclination, the ascent crossing right ascension, the argument of the perigee, and the phase are the same as the corresponding parameters of the orbit of the space actual service aircraft.
Preferably, the phase of the space virtual service aircraft and the phase of the target aircraft at the time of the crossing in S2 are determined by:
s21, initializing the nearest relative distance R between the virtual service aircraft and the space targetmin；
S22, assuming that the virtual service aircraft and the space target arrive at the remote place of the transfer orbit at the same time, the phase of the virtual service aircraft is PsThe phase of the target aircraft is PtThe phase search interval value is PReso，Ps、Pt、PResoAll values of (1) are [0,2 pi ]]；
S23, maintaining initial phase P of virtual service aircraftsiIs constant, let the initial phase P of the target aircrafttiStarting from 0, according to PResoThe step length of the step is gradually increased until the upper boundary of the value range is reached;
s24, changing the phase P of the virtual serversiValue, let PsiStarting from 0, according to PResoThe step length of the step is gradually increased until the upper boundary of the value range is reached; each time P is changedsiThe value executes once step S23;
each step in the above-mentioned S23, S24 loop calculates the relative distance R between the virtual service aircraft and the target aircrafttemp(ii) a When R istempLess than RminInstant Rmin＝Rtemp、Pt＝Pti、Ps＝Psi；
S25, reducing phase search interval value PResoSetting up PsiHas a value range of [ Ps-PReso,Ps+PReso]，PtiHas an initial value of [ Pt-PReso,Pt+PReso](ii) a Re-executing S23, S24 until PResoDecrease to a specified value;
p obtained after the end of the cyclesI.e. the orbital phase, P, of the virtual service aircraft at arrivaltThe orbital phase to reach the spatial target is the cross-phase.
Preferably, the virtual service aircraft is at a closest relative distance R to the space targetminIs at least greater than 2at(ii) a A is describedtThe semi-major axis in the initial orbit element for the virtual service aircraft.
Preferably, the phase search interval value is PResoInitiation ofThe value ranges from 0.05 pi to 0.2 pi.
Preferably, the phase search interval value P is decreased in S25ResoTo reduce to PResoThe initial value is (0.05-0.5).
Preferably, the actual space service aircraft applies a speed increment D in the opposite direction to the track phase adjustment in the first track maneuver at the beginning and the end of the track phase adjustmentvp。
Preferably, the space real service vehicle applies 1 speed increment D in the speed direction at the beginning of the track phasingvpApplying 1 speed increment D in the opposite direction of speed at the end of track phasingvp。
Preferably, the speed increments of the space actual service aircraft in the speed direction and the speed reverse direction at the beginning of the track phase adjustment are respectively calculated, and the direction with the smaller speed increment in the speed direction and the speed reverse direction is taken as the space for the design service aircraft to apply the speed increment at the beginning of the track phase adjustment.
Preferably, the specific implementation manner in S8 is: the actual service aircraft in the space performs 2 orbital maneuvers, and the purpose of the 1 st orbital maneuver is to pass through the parking waiting time T from the initial orbitwEntering a phase-modulated track, and changing the track speed by an increment of DvpAt a time TbFinishing phase modulation according to track-changing speed increment DveAnd performing orbital maneuver for the 2 nd time to enter the elliptical transfer orbit, and realizing rapid arrival and intersection with the space target aircraft at the far place of the elliptical transfer orbit.
Compared with the prior art, the invention has the beneficial effects that:
(1) the service aircraft provided by the invention can realize the orbital transfer intersection which can quickly reach the space out-of-plane target and save fuel for the orbital transfer strategy of the space target satellite in the out-of-plane circular orbit to reach the intersection;
(2) the invention innovatively designs a virtual track, and optimizes the virtual track to obtain the optimal rendezvous phase and rendezvous time of a space target; the optimal time and the phase of the service aircraft entering the elliptic transfer orbit are obtained by reversely deducing the optimal rendezvous phase and the rendezvous time; obtaining the track phase adjustment amplitude and the adjustment time of the service aircraft according to the initial position of the service aircraft and the phase of the service aircraft entering the elliptic transfer track; and adjusting the amplitude and the adjusting time according to the track phase of the service aircraft to obtain the parking waiting time of the service aircraft on the initial track. Calculating a service aircraft orbital transfer strategy according to the data;
(3) the invention provides a calculation method of orbital transfer time and orbital transfer speed increment for serving the aircraft for 2 times of orbital transfer, the algorithm is simple and reliable, and the serving aircraft can quickly arrive at a space out-of-plane target by performing 2 times of orbital transfer maneuvers.
Drawings
FIG. 1 is a schematic view of an initial orbital configuration of a service vehicle and a target satellite;
FIG. 2 is a schematic diagram of the configurations of an elliptical transfer orbit of a service aircraft, an initial orbit of the service aircraft and an initial orbit of a target satellite;
FIG. 3 is a schematic diagram of a configuration of a virtual service aircraft orbit, a service aircraft initial orbit, and a target satellite initial orbit.
Detailed Description
The invention is further explained below with reference to the drawings and examples.
A track change strategy for quickly arriving a space out-of-plane circular track target is implemented by the following steps:
(1) computing orbital phases of a service vehicle to a space target at arrival
The service aircraft and the space target are not on the same orbital plane, and the orbital configuration schematic diagrams of the service aircraft and the space target are shown in fig. 1.
Setting the orbit element of the service aircraft at the initial moment as a semi-major axis asEccentricity esAngle of inclination isThe right ascension channel omegasArgument of near place omegasPhase PsiThe spatial target track element is a semimajor axis atEccentricity etAngle of inclination itThe right ascension channel omegatArgument of near place omegatPhase Pti。
In order to reach the space out-of-plane target, the service aircraft should enter the elliptical transfer orbit from the initial orbit of the service aircraft, and the near point of the transfer orbit is positioned at the initial orbit of the service aircraft and the far point is positioned at the orbit of the space out-of-plane target. If the initial orbit height of the service aircraft is higher than the spatial non-coplanar target orbit, the far point of the transfer orbit is positioned on the initial orbit of the service aircraft, and the near point is positioned on the spatial non-coplanar target orbit. In the following description of the invention, the case that the initial orbit height of the service aircraft is lower than the space out-of-plane target orbit is described, and the related orbital transfer strategy design method is suitable for the case that the initial orbit height of the service aircraft is higher than the space out-of-plane target orbit. The elliptical transfer orbit is shown in fig. 2.
In order to achieve the arrival of the space target, it is necessary that the service vehicle arrives at the remote location of the transfer track while the space out-of-plane target also arrives at that point. The phase when the space out-of-plane target reaches this point is taken as the rendezvous phase.
The phases of the virtual service aircraft and the space target when arriving at the remote place of the transfer orbit at the same time are calculated, and the specific description is as follows:
(1.1) setting initial value
Setting a virtual service aircraft, wherein the initial orbit element of the virtual service aircraft is taken as a semi-major axis atEccentricity esAngle of inclination isThe right ascension channel omegasArgument of near place omegasPhase Psi. Setting the nearest relative distance R of the virtual service aircraft and the space targetminIs 1 very large number, and generally takes a value greater than 2atFor example, taking the value 1e 16.
(1.2) setting 1 larger phase search interval value
Assuming that the virtual service aircraft and the space target arrive at the remote place of the transfer orbit at the same time, the phase of the virtual service aircraft is PsWith a spatial target phase of PtThe phase search interval value is PReso，Ps、Pt、PResoAll values of (1) are [0,2 pi ]]. Will PResoThe initial value of (a) is set to be 1 or more number within a value range, and generally ranges from 0.05 pi to 0.2 pi, for example, 0.1 pi.
(1.3) finding the optimum phase search Interval value
(1.3.1) holding PsiIs not changed, letPtiStarting from 0, according to PResoStep-by-step increase of (1) until reaching an upper boundary of the value range, each step increasing PReso。
(1.3.2) when P istiAfter having increased to the upper boundary of the range of values, let PsiStarting from 0, according to PResoStep-by-step increase of (1) until reaching an upper boundary of the value range, each step increasing PResoRepeat (1.3.1), and so on until PsiHas increased to a value bounded on the scale.
The relative distance between the virtual service aircraft and the space target is recorded as RtempCalculating R for each step in the cycletemp. When R istempLess than RminInstant Rmin＝Rtemp、Pt＝Pti、Ps＝Psi。
(1.4) changing the phase search Interval value
Reducing phase search interval value PResoThe value is reduced to (0.05-0.5), for example, to 1/10. Setting PsiHas a value range of [ Ps-PReso,Ps+PReso]，PtiHas an initial value of [ Pt-PReso,Pt+PReso]。
(1.5) circular search
Cycling according to steps 1.3 and 1.4 until PResoReduced to a specified value, e.g. 10-5rad。
(1.6) recording the track phases of the serving aircraft on both the arrival of the space object
P obtained after the end of the cyclesI.e. the orbital phase, P, of the service aircraft at arrivaltThe orbital phase to reach the spatial target is the cross-phase.
(2) Calculating the time taken for a space target (i.e. a target aircraft) to reach the rendezvous phase from an initial position
Time-lapse T for spatial target to reach intersection phase from initial positiontCalculated as follows:
μEis the earth's gravitational constant.
(3) Calculating the time when the actual service aircraft (also called service aircraft) in the space enters the ellipse transfer orbit
T when service aircraft flies on elliptical transfer orbittransCalculated as follows:
the time when the service aircraft enters the elliptical transfer orbit is calculated according to the following formula:
Tb＝Tt-Ttrans
the phase of the service aircraft on its initial orbit at the moment of entering the elliptical transfer orbit is calculated as follows:
Pb＝Ps-π
(4) calculating track phase adjustment amplitude before service aircraft enters ellipse transfer track
Servicing aircraft to be at TbThe moment reaches the phase P of its initial trackbAnd phase adjustment is required to be carried out through orbital maneuver, and the phase adjustment amplitude is as follows:
(5) calculating the velocity increment and time required for the track phase adjustment of the service aircraft
The orbital motion period of the service vehicle on its initial orbit is:
the increment of speed required for the track phase adjustment of the service aircraft is
In the formula
The time taken for the track phase adjustment of the service vehicle is
Calculating the parking waiting time of a service aircraft on its initial trajectory
Tw＝Tb-TA
(6) Calculating the orbital transfer speed increment required by the service aircraft to enter the elliptical transfer orbit
(7) Generating a tracking strategy for a service aircraft
The service aircraft carries out 2 orbital maneuvers, wherein the 1 st orbital maneuver aims to enter a phase modulation orbit from an initial operation orbit, and the 2 nd orbital maneuver aims to finish the phase modulation and enter an elliptic transfer orbit, so that the variable orbit strategy is as follows:
1 st orbital maneuver time TwChange of track speed increment Dvp。
2 nd orbital maneuver time TbChange of track speed increment Dve-Dvp。
The service vehicle applies 1 speed increment D in the speed direction at the beginning of the track phasingvpApplying 1 speed increment D in the opposite direction of speed at the end of track phasingvp. More preferably, the speed increment D of the space real service aircraft in the speed direction and the speed reverse direction at the beginning of the track phase adjustment is calculated respectivelyvpTaking the direction of the smaller velocity increment asThe space is such that the design service aircraft applies a velocity increment at the beginning of the track phasing in a direction opposite to the beginning.
Examples
At an initial time (denoted as time 0), the service aircraft orbit element semi-major axis as12378.137km, eccentricity esIs 0, inclination angle is40 degrees and the right ascension channel omega of the rising pointsIs 100.25 DEG, argument of perigee omegasIs 0 DEG and phase PsiIs 5 degrees, and the semi-major axis a of the orbit element of the space target satellitet30378.137km, eccentricity etIs 0, inclination angle it10 DEG, right ascension angle omegatIs 250.25 DEG, argument of perigee omegatIs 0 DEG and phase PtiAt 60 °, the calculation process of the orbital transfer strategy for the service aircraft to quickly arrive at the space target satellite is as follows:
(1) computing orbital phases of a service vehicle to a space target at arrival
Setting an initial value according to the orbit elements of the service aircraft and the space target satellite at the initial moment, and recording the initial orbit element of the virtual service aircraft as a semi-major axis atEccentricity esAngle of inclination isThe right ascension channel omegasArgument of near place omegasPhase Psi. Virtual service aircraft, space target's nearest relative distance RminInitial value of 1016And m is selected. The orbital configuration of the service vehicle, the space target satellite, the virtual service vehicle is shown in figure 3.
Setting a phase search interval value to PResoThe initial value is 0.1 pi rad, and the minimum relative distance 2985km can be obtained when the virtual service aircraft and the space target satellite are searched according to the method listed in the technical scheme under the search interval and the respective phases are 2.91rad and 6.70rad respectively; reducing search interval PResoThe value is 0.01 pi rad, and the searching is continued, so that the minimum relative distance 327km can be obtained when the respective phases of the virtual service aircraft and the space target satellite are respectively 3.04rad and 6.73 rad; continuing to reduce the search interval PResoValue until it is reduced to 0.00001rad, a virtual service flight can be obtainedThe minimum relative distance of 64m can be obtained when the respective phases of the satellite and the space target satellite are 3.03rad and 6.72rad, respectively, which is the orbital phase of the virtual service aircraft to the space target when the space target arrives.
(2) Calculating the time spent by the space target from the initial position to the intersection phase
The time taken for the spatial object to reach the rendezvous phase from the initial position is 47607 s.
(3) Calculating the time for the service aircraft to enter the elliptical transfer orbit
The time when the service aircraft enters the elliptical transfer orbit is 32053 s. The phase of the service aircraft on its initial orbit at the moment of entering the elliptical transfer orbit is 6.17 rad.
(4) Calculating track phase adjustment amplitude before service aircraft enters ellipse transfer track
In order for the service aircraft to reach 6.17rad of its initial orbit at time 32053s, it needs to be phased by orbital maneuver, with a phase adjustment amplitude of-2.33 rad.
(5) Calculating the velocity increment and time required for the track phase adjustment of the service aircraft
The service aircraft begins the 1 st orbital phasing maneuver at 13263s at a speed increment of 515m/s, and after 18791s the 2 nd orbital phasing maneuver is performed at a speed increment of-515 m/s.
(6) Calculating the orbital transfer speed increment required by the service aircraft to enter the elliptical transfer orbit
The orbital transfer speed increment required for the service aircraft to enter the elliptical transfer orbit is 1089 m/s. Since the maneuver of the service aircraft for the 2 nd orbit phase adjustment and the maneuver of entering the elliptical transfer orbit are simultaneously carried out, the sum of the maneuver and the maneuver is equal to 574 m/s.
(7) Generating a tracking strategy for a service aircraft
The service aircraft carries out 2 orbital maneuvers, wherein the 1 st orbital maneuver aims to enter a phase modulation orbit from an initial operation orbit, and the 2 nd orbital maneuver aims to finish the phase modulation and enter an elliptic transfer orbit, so that the variable orbit strategy is as follows:
track change time 13263s, track change speed increment 515m/s for 1 st time.
Track make time 2 32054s, change track speed increment 574 m/s.
The service aircraft arrives at the space target satellite at 47607 s.
The invention has not been described in detail in part in the common general knowledge of a person skilled in the art.
Claims (10)
1. A rail changing method for quickly arriving a space non-coplanar circular orbit target is characterized by being realized by the following modes:
s1, setting a virtual service aircraft and an initial orbit element thereof, wherein the orbit of the virtual service aircraft is the same as the orbit of the target aircraft in height but not on the same orbit plane;
s2, calculating the phase P of the space virtual service aircraft when the virtual service aircraft meets the target aircraft by using the virtual service aircraft orbitsAnd phase P of the target aircraftt；
S3, calculating the time T of the target aircraft from the initial position to the intersection phase according to the initial phase of the target aircraft and the phase of the target aircraft at the intersection calculated in S2t；
S4, calculating flight time of the space actual service aircraft on the ellipse transfer orbit according to the semimajor axis of the space actual aircraft orbit and the semimajor axis of the target aircraft orbit, and combining the flight time T in the S3tDetermining the time T when the actual service aircraft of the space enters the elliptic transfer orbitb(ii) a And according to the phase P in S2sCalculating the phase P of the actual service space aircraft on the initial orbit at the moment of entering the ellipse transfer orbitb；
S5, according to the phase P calculated in S4bTime TbAnd initial phase P in initial orbit element of virtual service aircraft in S1siCalculating the track phase adjustment amplitude value P before the practical space service aircraft enters the ellipse transfer trackA；
S6, calculating the orbit semimajor axis of the space actual service aircraft according to the orbit semimajor axis of the space actual service aircraftThe period of the orbital motion on the initial orbit is combined with the orbit phase adjustment amplitude P in S5ACalculating the required speed increment D for adjusting the track phase of the space actual service aircraftvpAnd time T for phase adjustmentADetermining the parking waiting time T of the actual service aircraft in the space on the initial orbitw；
S7, calculating the orbital transfer speed increment D required by the actual service spacecraft in the space to enter the elliptic transfer orbit according to the semimajor axis of the actual spacecraft orbit in the space and the semimajor axis of the target spacecraft orbitve；
S8, according to the parameters calculated by S4-S7, the space practical service aircraft can rapidly arrive at the intersection with the space target aircraft at the far place of the oval transfer orbit according to the strategy that the space practical service aircraft waits for the initial orbit parking, then enters the phase modulation orbit, and enters the oval transfer orbit after the phase modulation is finished.
2. The method of claim 1, wherein: the orbit semi-major axis of the virtual service aircraft in the S1 is the same as the target aircraft semi-major axis, and the eccentricity, the inclination angle, the ascension point right ascension, the argument of the perigee and the phase position are the same as the corresponding parameters of the space actual service aircraft orbit.
3. The method of claim 1, wherein: determining the phase of the space virtual service aircraft and the phase of the target aircraft at the meeting in S2 by:
s21, initializing the nearest relative distance R between the virtual service aircraft and the space targetmin；
S22, assuming that the virtual service aircraft and the space target arrive at the remote place of the transfer orbit at the same time, the phase of the virtual service aircraft is PsThe phase of the target aircraft is PtThe phase search interval value is PReso，Ps、Pt、PResoAll values of (1) are [0,2 pi ]]；
S23, maintaining initial phase P of virtual service aircraftsiIs constant, let the initial phase P of the target aircrafttiValue of (A)Starting from 0, according to PResoThe step length of the step is gradually increased until the upper boundary of the value range is reached;
s24, changing the phase P of the virtual serversiValue, let PsiStarting from 0, according to PResoThe step length of the step is gradually increased until the upper boundary of the value range is reached; each time P is changedsiThe value executes once step S23;
each step in the above-mentioned S23, S24 loop calculates the relative distance R between the virtual service aircraft and the target aircrafttemp(ii) a When R istempLess than RminInstant Rmin＝Rtemp、Pt＝Pti、Ps＝Psi；
S25, reducing phase search interval value PResoSetting up PsiHas a value range of [ Ps-PReso,Ps+PReso]，PtiHas an initial value of [ Pt-PReso,Pt+PReso](ii) a Re-executing S23, S24 until PResoDecrease to a specified value;
p obtained after the end of the cyclesI.e. the orbital phase, P, of the virtual service aircraft at arrivaltThe orbital phase to reach the spatial target is the cross-phase.
4. A method of orbital transfer according to claim 3, characterized in that: closest relative distance R of virtual service aircraft to space targetminIs at least greater than 2at(ii) a A is describedtThe semi-major axis in the initial orbit element for the virtual service aircraft.
5. A method of orbital transfer according to claim 3, characterized in that: phase search interval value PResoThe initial value range of (A) is 0.05 pi-0.2 pi.
6. A method of orbital transfer according to claim 3, characterized in that: decreasing the phase search interval value P in S25ResoTo reduce to PResoThe initial value is (0.05-0.5).
7. The method of claim 1, wherein: in the first orbit maneuver process of the space practical service aircraft, the speed increment D in the opposite direction is applied at the beginning of the orbit phase adjustment and at the end of the orbit phase adjustmentvp。
8. The method of claim 7, wherein: the space practical service aircraft applies 1 time of speed increment D along the speed direction at the beginning of track phase adjustmentvpApplying 1 speed increment D in the opposite direction of speed at the end of track phasingvp。
9. The method of claim 7, wherein: and respectively calculating the speed increment of the space actual service aircraft along the speed direction and the speed opposite direction when the track phase adjustment is started, and taking the direction with the smaller speed increment of the speed increment and the speed increment as the space to enable the design service aircraft to apply the speed increment when the track phase adjustment is started.
10. The method of claim 1, wherein: the specific implementation manner in S8 is: the actual service aircraft in the space performs 2 orbital maneuvers, and the purpose of the 1 st orbital maneuver is to pass through the parking waiting time T from the initial orbitwEntering a phase-modulated track, and changing the track speed by an increment of DvpAt a time TbFinishing phase modulation according to track-changing speed increment DveAnd performing orbital maneuver for the 2 nd time to enter the elliptical transfer orbit, and realizing rapid arrival and intersection with the space target aircraft at the far place of the elliptical transfer orbit.
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