CN107483131A - The double satellite combined channel Markov state method for generating sequence of high-speed aircraft - Google Patents

The double satellite combined channel Markov state method for generating sequence of high-speed aircraft Download PDF

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CN107483131A
CN107483131A CN201710525769.9A CN201710525769A CN107483131A CN 107483131 A CN107483131 A CN 107483131A CN 201710525769 A CN201710525769 A CN 201710525769A CN 107483131 A CN107483131 A CN 107483131A
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msub
mrow
mtd
state
satellite
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CN107483131B (en
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石磊
杨惠婷
刘彦明
李小平
杨敏
白博文
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Xidian University
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    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B17/00—Monitoring; Testing
    • H04B17/30—Monitoring; Testing of propagation channels
    • H04B17/391—Modelling the propagation channel
    • 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
    • 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

Abstract

The invention belongs to TTC＆T Technology field, discloses a kind of double satellite combined channel Markov state method for generating sequence of high-speed aircraft, including：According to land mobile satellite double star channel condition model and plasma sheath set Markov channel condition model, near space high-speed aircraft satellite 1 and the state-transition matrix of the system of aircraft satellite 2 are established respectively；According to the correlation between double satellites, the state-transition matrix of the double satellite relevant links of generation near space high-speed aircraft；According to the state-transition matrix of relevant link, the double satellite united state sequences of generation near space high-speed aircraft；United state sequence is decomposed to obtain the respective status switch of aircraft satellite 1 and aircraft satellite 2.The foundation of multimode Markov state chain can be completed in the case of without measured data, can accurately describe the double satellite channels of hypersonic vehicle under plasma sheath channel effect.

Description

The double satellite combined channel Markov state method for generating sequence of high-speed aircraft
Technical field
The invention belongs to TTC＆T Technology field, more particularly to a kind of double satellite combined channel Ma Erke of high-speed aircraft Husband's status switch production method.
Background technology
With near space utilization and the rapid development of aerospace flight technology, the research of the high hypersonic aircraft of near space into For the focus studied both at home and abroad.Reliable telemetry communication is one of core technology of high-speed aircraft, and high hypersonic aircraft is present High-speed flight and the electromagnetic environment of plasma sheath complexity, this allows for reception signal high speed time-varying, deep fading.When serious Spacecraft TT＆C communication information Transmission can be caused, greatly threatened the flight safety of aircraft.From radio communication angle For, high-speed flight environment and the mismatch of plasma sheath set of environments and existing telemetry communication system are to influence communication quality And one of the main reason for interrupting, therefore deeply recognize and build in communication of the accurate channel model to breaking through high-speed aircraft Disconnected Study on Problems is significant.The current channel model for high-speed aircraft is less, and research all at present is all Rest in the channel model research of " end-to-end ", do not account for improvement result of the multi-platform joint communication to communication quality.It is real On border, from the angle of lifting channel capacity, signal of communication decay can be alleviated using the communication of more low orbit satellite Platform Alliances Influence, be more actual communication plan especially with double satellite platforms.Correlation can be used for reference in terms of channel model research Channel model be land mobile satellite channels, be all the non stationary channel of high-speed mobile, Markov channel model can be used Modeling.Document " E.Lutz, A Markov model for correlated land mobile satellite channels [J] .International Journal of Satellite Communications.1996,14 (4) 333-339. " are based on Aeronautical satellite measured data gives single star Markov channel model and double star combined channel model of land mobile satellite.It is high The main distinction of fast aircraft and channel model for land mobile satellite is existing plasma sheath set of environments.Generally speaking, it is high Had the following disadvantages in terms of fast aircraft Channel Modeling：(1) what traditional single channel channel model was used for reference more is aerial remote reconnaissance letter Road model, the non-stationary problem of channel time-varying is not considered, does not meet aircraft truth, cause established channel model meter It is inaccurate to calculate result, error is big.(2) plasma sheath channel circumstance is directed to, patent " build, and Fang Shui news etc., one kind reenters dynamic by stone Plasma sheath covers Markov channel modeling method, CN：201510513924.6 " construct the Markov of plasma sheath Channel model, but the space transmission channel environment of high-speed aircraft is not considered yet.Therefore, the channel of high-speed aircraft is built at present Mould research can not describe space transmission channel environment and plasma sheath combined influence simultaneously.Although land mobile can be used for reference to defend Star channel, but need consider plasma sheath set of environments influence the satellite channel model of reference is modified, particularly pair The improvement of the state model of combined channel.For near space high-speed aircraft-bis- satellite communication systems, the channel model established Effectively accurate determined by the state model of non stationary channel.Therefore, build in combined channel model process and close the most Key be state model (Markov state sequence) under high-speed aircraft plasma sheath set of environments production method.
In summary, the problem of prior art is present be：Exist at present in terms of high-speed aircraft Channel Modeling and do not consider to believe Road time-varying is non-stationary；The structure of combined channel model is not completed；State model is forbidden in the modeling of high-speed aircraft combined channel Really.
The content of the invention
The problem of existing for prior art, the invention provides a kind of double satellite combined channel Ma Erke of high-speed aircraft Husband's status switch production method.
The present invention is achieved in that a kind of double satellite combined channel Markov state sequence generation sides of high-speed aircraft Method, the double satellite combined channel Markov state method for generating sequence of the high-speed aircraft comprise the following steps：
Step 1, Markov channel status mould is covered according to land mobile satellite double star channel condition model and plasma sheath Type, near space high-speed aircraft-satellite 1 and the state-transition matrix of the system of aircraft-satellite 2 are established respectively；
Step 2, according to the correlation between double satellites, the shape of generation near space high-speed aircraft-bis- satellites relevant link State transfer matrix；
Step 3, according to the state-transition matrix of relevant link, generation near space high-speed aircraft-bis- satellites united state Sequence；
Step 4, united state sequence is decomposed to obtain the respective state of aircraft-satellite 1 and aircraft-satellite 2 Sequence.
Further, the double satellite combined channel Markov state method for generating sequence of the high-speed aircraft include following step Suddenly：
The first step, Markov channel status mould is covered according to land mobile satellite double star channel condition model and plasma sheath Type, the state-transition matrix P of near space high-speed aircraft-system of satellite 1 is established respectivelysat1_plasmaWith near space high-speed flight The state-transition matrix P of the system of device-satellite 2sat2_plasma；
Second step, according to the correlation between double satellites, by the state Ma Er of near space high-speed aircraft-mono- satellite system two The state-transition matrix P of section's husband's modelsat1_plasmaAnd Psat2_plasmaBuild near space high-speed aircraft-bis- satellites relevant link Four state models state-transition matrix Pcorr_tran；
3rd step, utilize the state-transition matrix of the near space high-speed aircraft obtained-bis- satellites relevant link Pcorr_tran, the united state sequence S of the Markov channel model of the double satellites of acquisitiont(t=1,2 ..., n)；
4th step, united state sequence is decomposed to obtain the status switch A of near space high-speed aircraft-satellite 1tWith The status switch B of aircraft-satellite 2t(t=1,2 ..., n).
Further, the first step includes：
(1) according to the elevation angle and azimuth of satellite 1 and satellite 2, two state-transition matrixes of satellite 1 and satellite 2 are chosen Psat1And Psat2, and input two state-transition matrix P of plasma sheathplasma；
(2) state of satellite 1 is shifted into transfer matrix Psat1With the state-transition matrix P of plasma sheathplasmaJoined Close, obtain the state-transition matrix of near space high-speed aircraft-system of satellite 1：
Wherein, b1Represent that satellite 1 is transferred to " bad state " probability, g from " good state "1Represent satellite 1 from " bad state " to " good state " transition probability；
(3) state of satellite 2 is shifted into transfer matrix Psat2With the state-transition matrix P of plasma sheathplasmaJoined Close, obtain the state-transition matrix of near space high-speed aircraft-system of satellite 2：
Wherein, b2Represent that satellite 2 is transferred to " bad state " probability, g from " good state "2Represent satellite 2 from " bad state " to " good state " transition probability
Need further exist for illustrating, in step (2) and step (3), b1、b2、g1And g2It is calculated as follows：
b1=Psat1(1,2)+Pplasma(1,2)-Psat1(1,2)×Pplasma(1,2)
b2=Psat2(1,2)+Pplasma(1,2)-Psat2(1,2)×Pplasma(1,2)
Wherein, Psat1(i,j)、Psat2(i, j) and Pplasma(i, j) is transition transfer matrix P respectivelysat1、Psat2And Pplasma In element, expression is the probability that state j is jumped to from state i, 0≤Psat1(i, j)≤1,0≤Psat2(i, j)≤1 and 0≤ Pplasma(i, j)≤1 andWith
Further, the second step includes：
1) first assume that the channel of two satellites is separate, by near space high-speed aircraft-mono- satellite system state Transfer matrix Psat1_plasmaAnd Psat2_plasmaBring following formula into, derive that near space high-speed aircraft-bis- satellite channels are separate Four state models state-transition matrix Ptran：
WhereinRepresenting matrix multiplication；
2) by four separate state-transition matrix P of channeltranIt is modified using correlation matrix C, obtains near space Four state-transition matrix P of high-speed aircraft-bis- satellites relevant linkcorr_tran：
Wherein x, y, v, w are corrected parameters；
Correlation matrix C computational methods are as follows：
The correlation coefficient ρ inputted between two satellites, obtain initial correction parameter x0, y0, v0, w0If ρ >=0, utilize Lower formula tries to achieve initial correction parameter x0, y0, v0, w0：
If ρ ＜ 0, initial correction parameter x is tried to achieve by lower formula0, y0, v0, w0：
According to the united state second moment ρ of following formula satellite 1,2, correction factor c can be derived
Wherein,
The correction factor c derived is：
Utilize the initial correction parameter x tried to achieve0, y0, v0, w0Following formula is substituted into correction factor c, obtains correlation matrix C：
Further, the 3rd step specifically includes：
Step 1, input the state-transition matrix for the near space high-speed aircraft-bis- satellites relevant link obtained Pcorr_tran, give current state St(St=1,2,3,4)；
Step 2, (0, a 1) uniform random number U is produced, and k=1 is set；
Step 3, test condition：
Meet test condition, then NextState St+1=k；If being unsatisfactory for test condition, k=k+1 continues to repeat to survey Examination, go directly untill meeting condition；
Step 4, by determining the state of next step, and then produce the Markov united state sequence S of double satellitest, t =1,2 ..., n.
Further, the 4th step specifically includes：
1) assume high-speed aircraft-satellite 1 and " the good state " of high-speed aircraft-satellite 2 and " bad state " respectively with 1,2 Represent, the state of high-speed aircraft-bis- satellite channels can be divided into " good-good ", " good-bad ", " bad-good ", " bad-bad " four connection Conjunction state, represented respectively with 1,2,3,4；
2) to united state sequence StDecompose the status switch A of near space high-speed aircraft-satellite 1tAnd flight The status switch B of device-satellite 2t, Rule of judgment：
Work as St=1, then the correspondence of high-speed aircraft-satellite 1 " good state ", i.e. At=1；The correspondence of high-speed aircraft-satellite 2 is " good State ", i.e. Bt=1；
Work as St=2, then the correspondence of high-speed aircraft-satellite 1 " good state ", i.e. At=1；The correspondence of high-speed aircraft-satellite 2 is " bad State ", i.e. Bt=2；
Work as St=3, then the correspondence " bad state " of high-speed aircraft-satellite 1, i.e. At=2；The correspondence of high-speed aircraft-satellite 2 is " good State ", i.e. Bt=1；
Work as St=4, then the correspondence " bad state " of high-speed aircraft-satellite 1, i.e. At=2；The correspondence of high-speed aircraft-satellite 2 is " bad State ", i.e. Bt=2；
Obtained Near Space Flying Vehicles-satellite 1 and the status switch of aircraft-satellite 2.
It is a kind of using the double satellite combined channel Markovs of the high-speed aircraft another object of the present invention is to provide The high hypersonic aircraft of status switch production method.
Advantages of the present invention and good effect are：The present invention can complete multimode Ma Erke in the case of without measured data The foundation of husband's state chain；Influence of the plasma sheath to status switch is considered simultaneously, with existing double star channel condition model Compare, can more accurately describe hypersonic vehicle under the influence of plasma sheath-bis- in the state aspect of non stationary channel defends Star channel.
Status switch production method proposed by the invention is built suitable near space high-speed aircraft repeater satellite channel The generation of state model in mould and space flight reentry vehicle repeater satellite Channel Modeling.
Brief description of the drawings
Fig. 1 is the double satellite combined channel Markov state sequence generation sides of high-speed aircraft provided in an embodiment of the present invention Method flow chart.
Fig. 2 is the state Markov Model state of near space high-speed aircraft provided in an embodiment of the present invention-bis- satellites four Transition diagram.
Fig. 3 is the generation frame for the status switch that united state sequence provided in an embodiment of the present invention resolves into each satellite Figure.
Fig. 4 is that united state status switch provided in an embodiment of the present invention resolves into Near Space Flying Vehicles-satellite 1 and flight The schematic diagram of the status switch of device-satellite 2.
Embodiment
In order to make the purpose , technical scheme and advantage of the present invention be clearer, with reference to embodiments, to the present invention It is further elaborated.It should be appreciated that the specific embodiments described herein are merely illustrative of the present invention, it is not used to Limit the present invention.
The application principle of the present invention is explained in detail below in conjunction with the accompanying drawings.
As shown in figure 1, the double satellite combined channel Markov state sequences of high-speed aircraft provided in an embodiment of the present invention Production method comprises the following steps：
S101：According to land mobile satellite double star channel condition model and plasma sheath set Markov channel status mould Type, near space high-speed aircraft-satellite 1 and the state-transition matrix of the system of aircraft-satellite 2 are established respectively；
S102：According to the correlation between double satellites, the state of generation near space high-speed aircraft-bis- satellites relevant link Transfer matrix；
S103：According to the state-transition matrix of relevant link, generation near space high-speed aircraft-bis- satellites united state sequence Row；
S104：United state sequence is decomposed to obtain the respective state sequence of aircraft-satellite 1 and aircraft-satellite 2 Row.
The application principle of the present invention is further described below in conjunction with the accompanying drawings.
As shown in figure 1, the double satellite combined channel Markov state sequences of high-speed aircraft provided in an embodiment of the present invention Production method, comprise the following steps：
S1 covers Markov channel condition model according to land mobile satellite double star channel condition model and plasma sheath, point The state-transition matrix P of near space high-speed aircraft-system of satellite 1 is not establishedsat1_plasmaWith near space high-speed aircraft-satellite The state-transition matrix P of 2 systemssat2_plasma。
S1.1：It it is 45 ° according to the azimuth of two satellites, the elevation angle of satellite 1 is 25 ° and the elevation angle of satellite 2 is 45 °, is obtained Two state-transition matrixes of satellite 1 and satellite 2With And input two state-transition matrixes of plasma sheath
S1.2：By the state of satellite 1 transfer transfer matrix Psat1With the state-transition matrix P of plasma sheathplasmaJoined Close, obtain the state-transition matrix of near space high-speed aircraft-system of satellite 1：
Wherein, b1Represent to be transferred to " bad state " probability, g from " good state "1Represent from " bad state " to " good state " transfer Probability；B can be obtained using lower formula1And g1:
Therefore
Wherein, Psat1(i, j) and Pplasma(i, j) is transition transfer matrix P respectivelysat1And PplasmaIn element, expression It is the probability that state j is jumped to from state i, 0≤Psat1(i, j)≤1,0≤Pplasma(i, j)≤1 and
S1.3：By the state of satellite 2 transfer transfer matrix Psat2With the state-transition matrix P of plasma sheathplasmaJoined Close, obtain the state-transition matrix near space high-speed aircraft-system of satellite 2：
Wherein, b2Represent to be transferred to " bad state " probability, g from " good state "2Represent from " bad state " to " good state " transfer Probability, b can be obtained using lower formula2And g2：
Therefore
Wherein, Psat2(i, j) is transition transfer matrix Psat2In element, expression is to jump to state j from state i Probability, 0≤Psat2(i, j)≤1, and
S2 is according to the correlation between double satellites, by the state Markov of near space high-speed aircraft-mono- satellite system two The state-transition matrix P of modelsat1_plasmaAnd Psat2_plasmaBuild the four of near space high-speed aircraft-bis- satellites relevant link The state-transition matrix P of state modelcorr_tran。
S2.1：First assume that the channel of two satellites is separate, by near space high-speed aircraft-mono- satellite system shape State transfer matrixWithBring following formula into, Derive the state-transition matrix P of four separate state models of near space high-speed aircraft-bis- satellite channelstran：
S2.2：Satellite has different coefficient correlations between different azimuth and the elevation angle, the azimuth of two satellites here For 45 °, the elevation angle of satellite 1 is 25 ° and the elevation angle of satellite 2 is 45 °, and correlation coefficient ρ=0.1454 of two satellites is, it is necessary to consider Correlation between channel, therefore the four state-transition matrix P by channel independently of each othertranAfter being corrected using correlation matrix C To four state-transition matrix P of near space high-speed aircraft-bis- satellites relevant linkcorr_tran：
Wherein x, y, v, w are corrected parameters；
Need further exist for illustrating, in step S2.2, described correlation matrix C computational methods are as follows：
S2.2.1：The correlation coefficient ρ inputted between two satellites, obtain initial correction parameter x0, y0, v0, w0If ρ >=0, Then initial correction parameter x is tried to achieve using lower formula0, y0, v0, w0：
If ρ ＜ 0, initial correction parameter x is tried to achieve by lower formula0, y0, v0, w0：
S2.2.2：According to the united state second moment ρ of following formula satellite 1,2, correction factor c can be derived, wherein,
The correction factor c derived is：
Utilize the initial correction parameter x tried to achieve0, y0, v0, w0Following formula is substituted into correction factor c, obtains correlation matrix C：
S2.2.3：The initial correction parameter x tried to achieve using S2.2.1 and S2.2.20, y0, v0, w0Following formula is substituted into c, is obtained Correlation matrix C：
The state-transition matrix of the near space high-speed aircraft that S3 is obtained using step S2-bis- satellites relevant link Pcorr_tran, the united state sequence S of the Markov channel model of the double satellites of acquisitiont(t=1,2 ..., n).
S3.1：The state-transition matrix of the near space high-speed aircraft that input step S2 is obtained-bis- satellites relevant link Pcorr_tran, give current state St(St=1,2,3,4)；
S3.2：(0,1) uniform random number U is produced, and k=1 is set；
S3.3：Test condition：
If meeting test condition, NextState St+1=k；If being unsatisfactory for test condition, k=k+1 continues to repeat Step S3.3 is tested, and is gone directly untill meeting condition；
S3.4：The state of next step is determined by S3.3 steps, and then produces the Markov united state sequence of double satellites Arrange St, t=1,2 ..., n.
S4 is decomposed to obtain the status switch A of near space high-speed aircraft-satellite 1 to united state sequencetAnd flight The status switch B of device-satellite 2t(t=1,2 ..., n).
S4.1：Assuming that high-speed aircraft-satellite 1 and " the good state " of high-speed aircraft-satellite 2 and " bad state " are used respectively 1st, 2 represent, the state of high-speed aircraft-bis- satellite channels can be divided into " good-good ", " good-bad ", " bad-good ", " bad-bad " four Individual united state, represent (S with 1,2,3,4 respectivelyt=1,2,3,4), as shown in Figure 2；
S4.2 is as shown in figure 3, to united state sequence StDecompose the state of near space high-speed aircraft-satellite 1 Sequence AtWith the status switch B of aircraft-satellite 2t, Rule of judgment：
Work as St=1, then the correspondence of high-speed aircraft-satellite 1 " good state ", i.e. At=1；The correspondence of high-speed aircraft-satellite 2 is " good State ", i.e. Bt=1；
Work as St=2, then the correspondence of high-speed aircraft-satellite 1 " good state ", i.e. At=1；The correspondence of high-speed aircraft-satellite 2 is " bad State ", i.e. Bt=2；
Work as St=3, then the correspondence " bad state " of high-speed aircraft-satellite 1, i.e. At=2；The correspondence of high-speed aircraft-satellite 2 is " good State ", i.e. Bt=1；
Work as St=4, then the correspondence " bad state " of high-speed aircraft-satellite 1, i.e. At=2；The correspondence of high-speed aircraft-satellite 2 is " bad State ", i.e. Bt=2；
Obtained Near Space Flying Vehicles-satellite 1 and the status switch of aircraft-satellite 2 is as shown in Figure 4.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention All any modification, equivalent and improvement made within refreshing and principle etc., should be included in the scope of the protection.

Claims (7)

  1. A kind of 1. double satellite combined channel Markov state method for generating sequence of high-speed aircraft, it is characterised in that the height The double satellite combined channel Markov state method for generating sequence of fast aircraft comprise the following steps：
    Step 1, Markov channel condition model is covered according to land mobile satellite double star channel condition model and plasma sheath, Near space high-speed aircraft-satellite 1 and the state-transition matrix of the system of aircraft-satellite 2 are established respectively；
    Step 2, according to the correlation between double satellites, the state of generation near space high-speed aircraft-bis- satellites relevant link turns Move matrix；
    Step 3, according to the state-transition matrix of relevant link, generation near space high-speed aircraft-bis- satellites united state sequence Row；
    Step 4, united state sequence is decomposed to obtain the respective state sequence of aircraft-satellite 1 and aircraft-satellite 2 Row.
  2. 2. the double satellite combined channel Markov state method for generating sequence of high-speed aircraft as claimed in claim 1, it is special Sign is that the double satellite combined channel Markov state method for generating sequence of the high-speed aircraft comprise the following steps：
    The first step, Markov channel condition model is covered according to land mobile satellite double star channel condition model and plasma sheath, The state-transition matrix P of near space high-speed aircraft-system of satellite 1 is established respectivelysat1_plasmaWith near space high-speed aircraft-defend The state-transition matrix P of the system of star 2sat2_plasma；
    Second step, according to the correlation between double satellites, by the state Markov of near space high-speed aircraft-mono- satellite system two The state-transition matrix P of modelsat1_plasmaAnd Psat2_plasmaBuild the four of near space high-speed aircraft-bis- satellites relevant link The state-transition matrix P of state modelcorr_tran；
    3rd step, utilize the state-transition matrix P of the near space high-speed aircraft obtained-bis- satellites relevant linkcorr_tran, obtain Take the united state sequence S of the Markov channel model of double satellitest(t=1,2 ..., n)；
    4th step, united state sequence is decomposed to obtain the status switch A of near space high-speed aircraft-satellite 1tAnd flight The status switch B of device-satellite 2t(t=1,2 ..., n).
  3. 3. the double satellite combined channel Markov state method for generating sequence of high-speed aircraft as claimed in claim 2, it is special Sign is that the first step includes：
    (1) according to the elevation angle and azimuth of satellite 1 and satellite 2, two state-transition matrix P of satellite 1 and satellite 2 are chosensat1With Psat2, and input two state-transition matrix P of plasma sheathplasma；
    (2) state of satellite 1 is shifted into transfer matrix Psat1With the state-transition matrix P of plasma sheathplasmaCombined, obtained The state-transition matrix of near space high-speed aircraft-system of satellite 1：
    <mrow> <msub> <mi>P</mi> <mrow> <mi>s</mi> <mi>a</mi> <mi>t</mi> <mn>1</mn> <mo>_</mo> <mi>p</mi> <mi>l</mi> <mi>a</mi> <mi>s</mi> <mi>m</mi> <mi>a</mi> </mrow> </msub> <mo>=</mo> <mfenced open = "[" close = "]"> <mtable> <mtr> <mtd> <mrow> <mn>1</mn> <mo>-</mo> <msub> <mi>b</mi> <mn>1</mn> </msub> </mrow> </mtd> <mtd> <msub> <mi>b</mi> <mn>1</mn> </msub> </mtd> </mtr> <mtr> <mtd> <msub> <mi>g</mi> <mn>1</mn> </msub> </mtd> <mtd> <mrow> <mn>1</mn> <mo>-</mo> <msub> <mi>g</mi> <mn>1</mn> </msub> </mrow> </mtd> </mtr> </mtable> </mfenced> </mrow>
    Wherein, b1Represent that satellite 1 is transferred to " bad state " probability, g from " good state "1Represent satellite 1 from " bad state " to " good shape State " transition probability；
    (3) state of satellite 2 is shifted into transfer matrix Psat2With the state-transition matrix P of plasma sheathplasmaCombined, obtained The state-transition matrix of near space high-speed aircraft-system of satellite 2：
    <mrow> <msub> <mi>P</mi> <mrow> <mi>s</mi> <mi>a</mi> <mi>t</mi> <mn>2</mn> <mo>_</mo> <mi>p</mi> <mi>l</mi> <mi>a</mi> <mi>s</mi> <mi>m</mi> <mi>a</mi> </mrow> </msub> <mo>=</mo> <mfenced open = "[" close = "]"> <mtable> <mtr> <mtd> <mrow> <mn>1</mn> <mo>-</mo> <msub> <mi>b</mi> <mn>2</mn> </msub> </mrow> </mtd> <mtd> <msub> <mi>b</mi> <mn>2</mn> </msub> </mtd> </mtr> <mtr> <mtd> <msub> <mi>g</mi> <mn>2</mn> </msub> </mtd> <mtd> <mrow> <mn>1</mn> <mo>-</mo> <msub> <mi>g</mi> <mn>2</mn> </msub> </mrow> </mtd> </mtr> </mtable> </mfenced> </mrow>
    Wherein, b2Represent that satellite 2 is transferred to " bad state " probability, g from " good state "2Represent satellite 2 from " bad state " to " good shape State " transition probability
    Need further exist for illustrating, in step (2) and step (3), b1、b2、g1And g2It is calculated as follows：
    b1=Psat1(1,2)+Pplasma(1,2)-Psat1(1,2)×Pplasma(1,2)
    b2=Psat2(1,2)+Pplasma(1,2)-Psat2(1,2)×Pplasma(1,2)
    <mrow> <msub> <mi>g</mi> <mn>1</mn> </msub> <mo>=</mo> <mfrac> <mrow> <msub> <mi>P</mi> <mrow> <mi>s</mi> <mi>a</mi> <mi>t</mi> <mn>1</mn> </mrow> </msub> <mrow> <mo>(</mo> <mn>2</mn> <mo>,</mo> <mn>1</mn> <mo>)</mo> </mrow> <mo>&amp;times;</mo> <msub> <mi>P</mi> <mrow> <mi>p</mi> <mi>l</mi> <mi>a</mi> <mi>s</mi> <mi>m</mi> <mi>a</mi> </mrow> </msub> <mrow> <mo>(</mo> <mn>2</mn> <mo>,</mo> <mn>1</mn> <mo>)</mo> </mrow> <mo>&amp;times;</mo> <msub> <mi>b</mi> <mn>1</mn> </msub> </mrow> <mrow> <msub> <mi>P</mi> <mrow> <mi>s</mi> <mi>a</mi> <mi>t</mi> <mn>1</mn> </mrow> </msub> <mrow> <mo>(</mo> <mn>1</mn> <mo>,</mo> <mn>2</mn> <mo>)</mo> </mrow> <mo>&amp;times;</mo> <msub> <mi>P</mi> <mrow> <mi>p</mi> <mi>l</mi> <mi>a</mi> <mi>s</mi> <mi>m</mi> <mi>a</mi> </mrow> </msub> <mrow> <mo>(</mo> <mn>1</mn> <mo>,</mo> <mn>2</mn> <mo>)</mo> </mrow> <mo>+</mo> <msub> <mi>P</mi> <mrow> <mi>s</mi> <mi>a</mi> <mi>t</mi> <mn>1</mn> </mrow> </msub> <mrow> <mo>(</mo> <mn>1</mn> <mo>,</mo> <mn>2</mn> <mo>)</mo> </mrow> <mo>&amp;times;</mo> <msub> <mi>P</mi> <mrow> <mi>p</mi> <mi>l</mi> <mi>a</mi> <mi>s</mi> <mi>m</mi> <mi>a</mi> </mrow> </msub> <mrow> <mo>(</mo> <mn>2</mn> <mo>,</mo> <mn>1</mn> <mo>)</mo> </mrow> <mo>+</mo> <msub> <mi>P</mi> <mrow> <mi>s</mi> <mi>a</mi> <mi>t</mi> <mn>1</mn> </mrow> </msub> <mrow> <mo>(</mo> <mn>2</mn> <mo>,</mo> <mn>1</mn> <mo>)</mo> </mrow> <mo>&amp;times;</mo> <msub> <mi>P</mi> <mrow> <mi>p</mi> <mi>l</mi> <mi>a</mi> <mi>s</mi> <mi>m</mi> <mi>a</mi> </mrow> </msub> <mrow> <mo>(</mo> <mn>1</mn> <mo>,</mo> <mn>2</mn> <mo>)</mo> </mrow> </mrow> </mfrac> </mrow>
    <mrow> <msub> <mi>g</mi> <mn>2</mn> </msub> <mo>=</mo> <mfrac> <mrow> <msub> <mi>P</mi> <mrow> <mi>s</mi> <mi>a</mi> <mi>t</mi> <mn>2</mn> </mrow> </msub> <mrow> <mo>(</mo> <mn>2</mn> <mo>,</mo> <mn>1</mn> <mo>)</mo> </mrow> <mo>&amp;times;</mo> <msub> <mi>P</mi> <mrow> <mi>p</mi> <mi>l</mi> <mi>a</mi> <mi>s</mi> <mi>m</mi> <mi>a</mi> </mrow> </msub> <mrow> <mo>(</mo> <mn>2</mn> <mo>,</mo> <mn>1</mn> <mo>)</mo> </mrow> <mo>&amp;times;</mo> <msub> <mi>b</mi> <mn>2</mn> </msub> </mrow> <mrow> <msub> <mi>P</mi> <mrow> <mi>s</mi> <mi>a</mi> <mi>t</mi> <mn>2</mn> </mrow> </msub> <mrow> <mo>(</mo> <mn>1</mn> <mo>,</mo> <mn>2</mn> <mo>)</mo> </mrow> <mo>&amp;times;</mo> <msub> <mi>P</mi> <mrow> <mi>p</mi> <mi>l</mi> <mi>a</mi> <mi>s</mi> <mi>m</mi> <mi>a</mi> </mrow> </msub> <mrow> <mo>(</mo> <mn>1</mn> <mo>,</mo> <mn>2</mn> <mo>)</mo> </mrow> <mo>+</mo> <msub> <mi>P</mi> <mrow> <mi>s</mi> <mi>a</mi> <mi>t</mi> <mn>2</mn> </mrow> </msub> <mrow> <mo>(</mo> <mn>1</mn> <mo>,</mo> <mn>2</mn> <mo>)</mo> </mrow> <mo>&amp;times;</mo> <msub> <mi>P</mi> <mrow> <mi>p</mi> <mi>l</mi> <mi>a</mi> <mi>s</mi> <mi>m</mi> <mi>a</mi> </mrow> </msub> <mrow> <mo>(</mo> <mn>2</mn> <mo>,</mo> <mn>1</mn> <mo>)</mo> </mrow> <mo>+</mo> <msub> <mi>P</mi> <mrow> <mi>s</mi> <mi>a</mi> <mi>t</mi> <mn>2</mn> </mrow> </msub> <mrow> <mo>(</mo> <mn>2</mn> <mo>,</mo> <mn>1</mn> <mo>)</mo> </mrow> <mo>&amp;times;</mo> <msub> <mi>P</mi> <mrow> <mi>p</mi> <mi>l</mi> <mi>a</mi> <mi>s</mi> <mi>m</mi> <mi>a</mi> </mrow> </msub> <mrow> <mo>(</mo> <mn>1</mn> <mo>,</mo> <mn>2</mn> <mo>)</mo> </mrow> </mrow> </mfrac> </mrow>
    Wherein, Psat1(i,j)、Psat2(i, j) and Pplasma(i, j) is transition transfer matrix P respectivelysat1、Psat2And PplasmaIn Element, expression is the probability that state j is jumped to from state i, 0≤Psat1(i, j)≤1,0≤Psat2(i, j)≤1 and 0≤ Pplasma(i, j)≤1 andWith
  4. 4. the double satellite combined channel Markov state method for generating sequence of high-speed aircraft as claimed in claim 2, it is special Sign is that the second step includes：
    1) channel for first assuming two satellites is separate, and near space high-speed aircraft-mono- satellite system state is shifted Matrix Psat1_plasmaAnd Psat2_plasmaBring following formula into, derive four of near space high-speed aircraft-bis- satellite channels independently of each other The state-transition matrix P of state modeltran：
    <mfenced open = "" close = ""> <mtable> <mtr> <mtd> <mrow> <msub> <mi>P</mi> <mrow> <mi>t</mi> <mi>r</mi> <mi>a</mi> <mi>n</mi> </mrow> </msub> <mo>=</mo> <msub> <mi>P</mi> <mrow> <mi>s</mi> <mi>a</mi> <mi>t</mi> <mn>1</mn> <mo>_</mo> <mi>p</mi> <mi>l</mi> <mi>a</mi> <mi>s</mi> <mi>m</mi> <mi>a</mi> </mrow> </msub> <mo>&amp;CircleTimes;</mo> <msub> <mi>P</mi> <mrow> <mi>s</mi> <mi>a</mi> <mi>t</mi> <mn>2</mn> <mo>_</mo> <mi>p</mi> <mi>l</mi> <mi>a</mi> <mi>s</mi> <mi>m</mi> <mi>a</mi> </mrow> </msub> </mrow> </mtd> </mtr> <mtr> <mtd> <mrow> <mo>=</mo> <mfenced open = "[" close = "]"> <mtable> <mtr> <mtd> <mrow> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>b</mi> <mn>1</mn> </msub> <mo>)</mo> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>b</mi> <mn>2</mn> </msub> <mo>)</mo> </mrow> </mtd> <mtd> <mrow> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>b</mi> <mn>1</mn> </msub> <mo>)</mo> <msub> <mi>b</mi> <mn>2</mn> </msub> </mrow> </mtd> <mtd> <mrow> <msub> <mi>b</mi> <mn>1</mn> </msub> <mrow> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>b</mi> <mn>2</mn> </msub> <mo>)</mo> </mrow> </mrow> </mtd> <mtd> <mrow> <msub> <mi>b</mi> <mn>1</mn> </msub> <msub> <mi>b</mi> <mn>2</mn> </msub> </mrow> </mtd> </mtr> <mtr> <mtd> <mrow> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>b</mi> <mn>1</mn> </msub> <mo>)</mo> <msub> <mi>g</mi> <mn>2</mn> </msub> </mrow> </mtd> <mtd> <mrow> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>b</mi> <mn>1</mn> </msub> <mo>)</mo> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>g</mi> <mn>2</mn> </msub> <mo>)</mo> </mrow> </mtd> <mtd> <mrow> <msub> <mi>b</mi> <mn>1</mn> </msub> <msub> <mi>g</mi> <mn>2</mn> </msub> </mrow> </mtd> <mtd> <mrow> <msub> <mi>b</mi> <mn>1</mn> </msub> <mrow> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>g</mi> <mn>2</mn> </msub> <mo>)</mo> </mrow> </mrow> </mtd> </mtr> <mtr> <mtd> <mrow> <msub> <mi>g</mi> <mn>1</mn> </msub> <mrow> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>b</mi> <mn>2</mn> </msub> <mo>)</mo> </mrow> </mrow> </mtd> <mtd> <mrow> <msub> <mi>g</mi> <mn>1</mn> </msub> <msub> <mi>b</mi> <mn>2</mn> </msub> </mrow> </mtd> <mtd> <mrow> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>g</mi> <mn>1</mn> </msub> <mo>)</mo> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>b</mi> <mn>2</mn> </msub> <mo>)</mo> </mrow> </mtd> <mtd> <mrow> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>g</mi> <mn>1</mn> </msub> <mo>)</mo> <msub> <mi>b</mi> <mn>2</mn> </msub> </mrow> </mtd> </mtr> <mtr> <mtd> <mrow> <msub> <mi>g</mi> <mn>1</mn> </msub> <msub> <mi>g</mi> <mn>2</mn> </msub> </mrow> </mtd> <mtd> <mrow> <msub> <mi>g</mi> <mn>1</mn> </msub> <mrow> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>g</mi> <mn>2</mn> </msub> <mo>)</mo> </mrow> </mrow> </mtd> <mtd> <mrow> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>b</mi> <mn>1</mn> </msub> <mo>)</mo> <msub> <mi>g</mi> <mn>2</mn> </msub> </mrow> </mtd> <mtd> <mrow> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>g</mi> <mn>1</mn> </msub> <mo>)</mo> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>g</mi> <mn>2</mn> </msub> <mo>)</mo> </mrow> </mtd> </mtr> </mtable> </mfenced> </mrow> </mtd> </mtr> </mtable> </mfenced>
    WhereinRepresenting matrix multiplication；
    2) by four separate state-transition matrix P of channeltranIt is modified using correlation matrix C, obtains near space and fly at a high speed Four state-transition matrix P of row device-bis- satellites relevant linkcorr_tran：
    <mrow> <msub> <mi>P</mi> <mrow> <mi>c</mi> <mi>o</mi> <mi>r</mi> <mi>r</mi> <mo>_</mo> <mi>t</mi> <mi>r</mi> <mi>a</mi> <mi>n</mi> </mrow> </msub> <mo>=</mo> <msub> <mi>P</mi> <mrow> <mi>t</mi> <mi>r</mi> <mi>a</mi> <mi>n</mi> </mrow> </msub> <mo>+</mo> <mi>C</mi> <mo>=</mo> <msub> <mi>P</mi> <mrow> <mi>t</mi> <mi>r</mi> <mi>a</mi> <mi>n</mi> </mrow> </msub> <mo>+</mo> <mfenced open = "[" close = "]"> <mtable> <mtr> <mtd> <mi>x</mi> </mtd> <mtd> <mrow> <mo>-</mo> <mi>x</mi> </mrow> </mtd> <mtd> <mi>x</mi> </mtd> <mtd> <mrow> <mo>-</mo> <mi>x</mi> </mrow> </mtd> </mtr> <mtr> <mtd> <mi>y</mi> </mtd> <mtd> <mrow> <mo>-</mo> <mi>y</mi> </mrow> </mtd> <mtd> <mi>y</mi> </mtd> <mtd> <mrow> <mo>-</mo> <mi>y</mi> </mrow> </mtd> </mtr> <mtr> <mtd> <mi>v</mi> </mtd> <mtd> <mrow> <mo>-</mo> <mi>v</mi> </mrow> </mtd> <mtd> <mi>v</mi> </mtd> <mtd> <mrow> <mo>-</mo> <mi>v</mi> </mrow> </mtd> </mtr> <mtr> <mtd> <mi>w</mi> </mtd> <mtd> <mrow> <mo>-</mo> <mi>w</mi> </mrow> </mtd> <mtd> <mi>w</mi> </mtd> <mtd> <mrow> <mo>-</mo> <mi>w</mi> </mrow> </mtd> </mtr> </mtable> </mfenced> </mrow>
    Wherein x, y, v, w are corrected parameters；
    Correlation matrix C computational methods are as follows：
    The correlation coefficient ρ inputted between two satellites, obtain initial correction parameter x0, y0, v0, w0If ρ >=0, lower formula is utilized Try to achieve initial correction parameter x0, y0, v0, w0：
    <mrow> <mfenced open = "{" close = ""> <mtable> <mtr> <mtd> <msub> <mi>x</mi> <mn>0</mn> </msub> <mo>=</mo> <msub> <mi>x</mi> <mi>max</mi> </msub> <mo>=</mo> <mi>min</mi> <mo>{</mo> <msub> <mi>g</mi> <mn>1</mn> </msub> <mo>,</mo> <msub> <mi>g</mi> <mn>2</mn> </msub> <mo>}</mo> <mo>-</mo> <msub> <mi>g</mi> <mn>1</mn> </msub> <msub> <mi>g</mi> <mn>2</mn> </msub> </mtd> </mtr> <mtr> <mtd> <mrow> <msub> <mi>y</mi> <mn>0</mn> </msub> <mo>=</mo> <msub> <mi>y</mi> <mi>max</mi> </msub> <mo>=</mo> <msub> <mi>g</mi> <mn>1</mn> </msub> <msub> <mi>b</mi> <mn>2</mn> </msub> </mrow> </mtd> </mtr> <mtr> <mtd> <msub> <mi>v</mi> <mn>0</mn> </msub> <mo>=</mo> <msub> <mi>v</mi> <mi>max</mi> </msub> <mo>=</mo> <msub> <mi>b</mi> <mn>1</mn> </msub> <msub> <mi>g</mi> <mn>2</mn> </msub> </mtd> </mtr> <mtr> <mtd> <msub> <mi>w</mi> <mn>0</mn> </msub> <mo>=</mo> <msub> <mi>w</mi> <mi>max</mi> </msub> <mo>=</mo> <mi>min</mi> <mo>{</mo> <msub> <mi>b</mi> <mn>1</mn> </msub> <mo>,</mo> <msub> <mi>b</mi> <mn>2</mn> </msub> <mo>}</mo> <mo>-</mo> <msub> <mi>b</mi> <mn>1</mn> </msub> <msub> <mi>b</mi> <mn>2</mn> </msub> </mtd> </mtr> </mtable> </mfenced> <mo>;</mo> </mrow>
    If ρ ＜ 0, initial correction parameter x is tried to achieve by lower formula0, y0, v0, w0：
    <mrow> <mfenced open = "{" close = ""> <mtable> <mtr> <mtd> <msub> <mi>x</mi> <mn>0</mn> </msub> <mo>=</mo> <msub> <mi>x</mi> <mrow> <mi>m</mi> <mi>i</mi> <mi>n</mi> </mrow> </msub> <mo>=</mo> <mo>-</mo> <msub> <mi>g</mi> <mn>1</mn> </msub> <msub> <mi>g</mi> <mn>2</mn> </msub> </mtd> </mtr> <mtr> <mtd> <mrow> <msub> <mi>y</mi> <mn>0</mn> </msub> <mo>=</mo> <msub> <mi>y</mi> <mrow> <mi>m</mi> <mi>i</mi> <mi>n</mi> </mrow> </msub> <mo>=</mo> <msub> <mi>g</mi> <mn>1</mn> </msub> <msub> <mi>b</mi> <mn>2</mn> </msub> <mo>-</mo> <mi>m</mi> <mi>i</mi> <mi>n</mi> <mo>{</mo> <msub> <mi>g</mi> <mn>1</mn> </msub> <mo>,</mo> <msub> <mi>b</mi> <mn>2</mn> </msub> <mo>}</mo> </mrow> </mtd> </mtr> <mtr> <mtd> <msub> <mi>v</mi> <mn>0</mn> </msub> <mo>=</mo> <msub> <mi>v</mi> <mi>min</mi> </msub> <mo>=</mo> <msub> <mi>b</mi> <mn>1</mn> </msub> <msub> <mi>g</mi> <mn>2</mn> </msub> <mo>-</mo> <mi>m</mi> <mi>i</mi> <mi>n</mi> <mo>{</mo> <msub> <mi>b</mi> <mn>1</mn> </msub> <mo>,</mo> <msub> <mi>g</mi> <mn>2</mn> </msub> <mo>}</mo> </mtd> </mtr> <mtr> <mtd> <msub> <mi>w</mi> <mn>0</mn> </msub> <mo>=</mo> <msub> <mi>w</mi> <mrow> <mi>m</mi> <mi>i</mi> <mi>n</mi> </mrow> </msub> <mo>=</mo> <mo>-</mo> <msub> <mi>b</mi> <mn>1</mn> </msub> <msub> <mi>b</mi> <mn>2</mn> </msub> </mtd> </mtr> </mtable> </mfenced> <mo>;</mo> </mrow>
    According to the united state second moment ρ of following formula satellite 1,2, correction factor c can be derived
    Wherein,
    The correction factor c derived is：
    <mrow> <mi>c</mi> <mo>=</mo> <mfrac> <mrow> <mi>&amp;rho;</mi> <mo>&amp;CenterDot;</mo> <msqrt> <mrow> <msub> <mi>g</mi> <mn>1</mn> </msub> <msub> <mi>b</mi> <mn>1</mn> </msub> <msub> <mi>g</mi> <mn>2</mn> </msub> <msub> <mi>b</mi> <mn>2</mn> </msub> </mrow> </msqrt> <mo>&amp;CenterDot;</mo> <mrow> <mo>(</mo> <mn>1</mn> <mo>-</mo> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>g</mi> <mn>1</mn> </msub> <mo>-</mo> <msub> <mi>b</mi> <mn>1</mn> </msub> <mo>)</mo> </mrow> <mrow> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>g</mi> <mn>2</mn> </msub> <mo>-</mo> <msub> <mi>b</mi> <mn>2</mn> </msub> <mo>)</mo> </mrow> <mo>)</mo> </mrow> <mrow> <mo>(</mo> <msub> <mi>g</mi> <mn>1</mn> </msub> <msub> <mi>g</mi> <mn>2</mn> </msub> <msub> <mi>w</mi> <mn>0</mn> </msub> <mo>+</mo> <msub> <mi>g</mi> <mn>1</mn> </msub> <msub> <mi>b</mi> <mn>2</mn> </msub> <msub> <mi>v</mi> <mn>0</mn> </msub> <mo>+</mo> <msub> <mi>b</mi> <mn>1</mn> </msub> <msub> <mi>g</mi> <mn>2</mn> </msub> <msub> <mi>y</mi> <mn>0</mn> </msub> <mo>+</mo> <msub> <mi>b</mi> <mn>1</mn> </msub> <msub> <mi>b</mi> <mn>2</mn> </msub> <msub> <mi>x</mi> <mn>0</mn> </msub> <mo>)</mo> <mo>-</mo> <mi>&amp;rho;</mi> <mo>&amp;CenterDot;</mo> <msqrt> <mrow> <msub> <mi>g</mi> <mn>1</mn> </msub> <msub> <mi>b</mi> <mn>1</mn> </msub> <msub> <mi>g</mi> <mn>2</mn> </msub> <msub> <mi>b</mi> <mn>2</mn> </msub> </mrow> </msqrt> <mo>&amp;CenterDot;</mo> <mo>(</mo> <msub> <mi>y</mi> <mn>0</mn> </msub> <mo>-</mo> <msub> <mi>x</mi> <mn>0</mn> </msub> <mo>+</mo> <msub> <mi>v</mi> <mn>0</mn> </msub> <mo>-</mo> <msub> <mi>w</mi> <mn>0</mn> </msub> <mo>)</mo> </mrow> </mfrac> <mo>,</mo> <mn>0</mn> <mo>&amp;le;</mo> <mi>c</mi> <mo>&amp;le;</mo> <mn>1</mn> <mo>;</mo> </mrow>
    Utilize the initial correction parameter x tried to achieve0, y0, v0, w0Following formula is substituted into correction factor c, obtains correlation matrix C：
    <mrow> <mi>C</mi> <mo>=</mo> <mi>c</mi> <mfenced open = "[" close = "]"> <mtable> <mtr> <mtd> <msub> <mi>x</mi> <mn>0</mn> </msub> </mtd> <mtd> <mrow> <mo>-</mo> <msub> <mi>x</mi> <mn>0</mn> </msub> </mrow> </mtd> <mtd> <msub> <mi>x</mi> <mn>0</mn> </msub> </mtd> <mtd> <mrow> <mo>-</mo> <msub> <mi>x</mi> <mn>0</mn> </msub> </mrow> </mtd> </mtr> <mtr> <mtd> <msub> <mi>y</mi> <mn>0</mn> </msub> </mtd> <mtd> <mrow> <mo>-</mo> <msub> <mi>y</mi> <mn>0</mn> </msub> </mrow> </mtd> <mtd> <msub> <mi>y</mi> <mn>0</mn> </msub> </mtd> <mtd> <mrow> <mo>-</mo> <msub> <mi>y</mi> <mn>0</mn> </msub> </mrow> </mtd> </mtr> <mtr> <mtd> <msub> <mi>v</mi> <mn>0</mn> </msub> </mtd> <mtd> <mrow> <mo>-</mo> <msub> <mi>v</mi> <mn>0</mn> </msub> </mrow> </mtd> <mtd> <msub> <mi>v</mi> <mn>0</mn> </msub> </mtd> <mtd> <mrow> <mo>-</mo> <msub> <mi>v</mi> <mn>0</mn> </msub> </mrow> </mtd> </mtr> <mtr> <mtd> <msub> <mi>w</mi> <mn>0</mn> </msub> </mtd> <mtd> <mrow> <mo>-</mo> <msub> <mi>w</mi> <mn>0</mn> </msub> </mrow> </mtd> <mtd> <msub> <mi>w</mi> <mn>0</mn> </msub> </mtd> <mtd> <mrow> <mo>-</mo> <msub> <mi>w</mi> <mn>0</mn> </msub> </mrow> </mtd> </mtr> </mtable> </mfenced> <mo>=</mo> <mfenced open = "[" close = "]"> <mtable> <mtr> <mtd> <mi>x</mi> </mtd> <mtd> <mrow> <mo>-</mo> <mi>x</mi> </mrow> </mtd> <mtd> <mi>x</mi> </mtd> <mtd> <mrow> <mo>-</mo> <mi>x</mi> </mrow> </mtd> </mtr> <mtr> <mtd> <mi>y</mi> </mtd> <mtd> <mrow> <mo>-</mo> <mi>y</mi> </mrow> </mtd> <mtd> <mi>y</mi> </mtd> <mtd> <mrow> <mo>-</mo> <mi>y</mi> </mrow> </mtd> </mtr> <mtr> <mtd> <mi>v</mi> </mtd> <mtd> <mrow> <mo>-</mo> <mi>v</mi> </mrow> </mtd> <mtd> <mi>v</mi> </mtd> <mtd> <mrow> <mo>-</mo> <mi>v</mi> </mrow> </mtd> </mtr> <mtr> <mtd> <mi>w</mi> </mtd> <mtd> <mrow> <mo>-</mo> <mi>w</mi> </mrow> </mtd> <mtd> <mi>w</mi> </mtd> <mtd> <mrow> <mo>-</mo> <mi>w</mi> </mrow> </mtd> </mtr> </mtable> </mfenced> <mo>.</mo> </mrow>
  5. 5. the double satellite combined channel Markov state method for generating sequence of high-speed aircraft as claimed in claim 2, it is special Sign is that the 3rd step specifically includes：
    Step 1, input the state-transition matrix P for the near space high-speed aircraft-bis- satellites relevant link obtainedcorr_tran, give Determine current state St(St=1,2,3,4)；
    Step 2, (0, a 1) uniform random number U is produced, and k=1 is set；
    Step 3, test condition：
    <mrow> <mi>U</mi> <mo>&amp;le;</mo> <munderover> <mo>&amp;Sigma;</mo> <mrow> <mi>j</mi> <mo>=</mo> <mn>1</mn> </mrow> <mi>k</mi> </munderover> <msub> <mi>P</mi> <mrow> <mi>c</mi> <mi>o</mi> <mi>r</mi> <mi>r</mi> <mo>_</mo> <mi>t</mi> <mi>r</mi> <mi>a</mi> <mi>n</mi> </mrow> </msub> <mrow> <mo>(</mo> <msub> <mi>S</mi> <mi>t</mi> </msub> <mo>,</mo> <mi>j</mi> <mo>)</mo> </mrow> <mo>;</mo> </mrow>
    Meet test condition, then NextState St+1=k；If being unsatisfactory for test condition, k=k+1 continues retest, directly Untill condition is met；
    Step 4, by determining the state of next step, and then produce the Markov united state sequence S of double satellitest, t=1, 2,...,n。
  6. 6. the double satellite combined channel Markov state method for generating sequence of high-speed aircraft as claimed in claim 2, it is special Sign is that the 4th step specifically includes：
    1) assume high-speed aircraft-satellite 1 and " the good state " of high-speed aircraft-satellite 2 and " bad state " respectively with 1,2 tables Show, the state of high-speed aircraft-bis- satellite channels can be divided into " good-good ", " good-bad ", " bad-good ", " bad-bad " four joints State, represented respectively with 1,2,3,4；
    2) to united state sequence StDecompose the status switch A of near space high-speed aircraft-satellite 1tWith aircraft-defend The status switch B of star 2t, Rule of judgment：
    Work as St=1, then the correspondence of high-speed aircraft-satellite 1 " good state ", i.e. At=1；The correspondence of high-speed aircraft-satellite 2 " good shape State ", i.e. Bt=1；
    Work as St=2, then the correspondence of high-speed aircraft-satellite 1 " good state ", i.e. At=1；Correspondence " the bad shape of high-speed aircraft-satellite 2 State ", i.e. Bt=2；
    Work as St=3, then the correspondence " bad state " of high-speed aircraft-satellite 1, i.e. At=2；The correspondence of high-speed aircraft-satellite 2 " good shape State ", i.e. Bt=1；
    Work as St=4, then the correspondence " bad state " of high-speed aircraft-satellite 1, i.e. At=2；Correspondence " the bad shape of high-speed aircraft-satellite 2 State ", i.e. Bt=2；
    Obtained Near Space Flying Vehicles-satellite 1 and the status switch of aircraft-satellite 2.
  7. 7. a kind of usage right requires the double satellite combined channel Markov state sequences of high-speed aircraft described in 1~6 any one The high hypersonic aircraft of row production method.
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