CN107483131B - Method for generating high-speed aircraft double-satellite combined channel Markov state sequence - Google Patents

Method for generating high-speed aircraft double-satellite combined channel Markov state sequence Download PDF

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CN107483131B
CN107483131B CN201710525769.9A CN201710525769A CN107483131B CN 107483131 B CN107483131 B CN 107483131B CN 201710525769 A CN201710525769 A CN 201710525769A CN 107483131 B CN107483131 B CN 107483131B
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speed aircraft
aircraft
plasma
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CN107483131A (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
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Abstract

The invention belongs to the technical field of measurement and control communication, and discloses a method for generating a Markov state sequence of a dual-satellite joint channel of a high-speed aircraft, which comprises the following steps: respectively establishing state transition matrixes of a near-space high-speed aircraft-satellite 1 system and an aircraft-satellite 2 system according to a terrestrial mobile satellite double-satellite channel state model and a plasma sheath Markov channel state model; generating a state transition matrix of a near space high-speed aircraft-double satellite related link according to the correlation between the double satellites; generating a near space high-speed aircraft-double satellite combined state sequence according to the state transition matrix of the relevant link; and decomposing the combined state sequence to obtain the respective state sequences of the aircraft-satellite 1 and the aircraft-satellite 2. The establishment of the multi-state Markov state chain can be completed under the condition of no measured data, and the hypersonic aircraft-double satellite channel under the influence of the plasma sheath channel can be accurately described.

Description

Method for generating high-speed aircraft double-satellite combined channel Markov state sequence
Technical Field
The invention belongs to the technical field of measurement and control communication, and particularly relates to a method for generating a Markov state sequence of a double-satellite combined channel of a high-speed aircraft.
Background
With the development and utilization of near space and the rapid development of aerospace technology, the research of near space high-ultrasonic aircrafts becomes a hot spot of domestic and foreign research. Reliable measurement and control communication is one of core technologies of high-speed aircrafts, and the high-speed ultrasonic aircrafts have high-speed flight and a complex electromagnetic environment of a plasma sheath, so that received signals are time-varying at high speed and are faded deeply. And in severe cases, the transmission of the measurement and control communication information of the aircraft is interrupted, and the flight safety of the aircraft is greatly threatened. From the perspective of wireless communication, the mismatch between the high-speed flight environment and the plasma sheath environment and the existing measurement and control communication system is one of the main reasons for influencing communication quality and interruption, so that the deep knowledge and construction of an accurate channel model are of great significance for the research of breaking through the communication interruption problem of a high-speed aircraft. Currently, channel models for high-speed aircraft are few, and all current researches are in end-to-end channel model researches, and the improvement effect of multi-platform joint communication on communication quality is not considered. In fact, from the perspective of improving channel capacity, the effect of communication signal attenuation can be alleviated by using multiple low-orbit satellite platforms for joint communication, and particularly, the adoption of a dual-satellite platform is a relatively practical communication scheme. The channel model which can be used for reference in the research aspect of the channel model is a land mobile satellite channel, is a non-stationary channel moving at a high speed, and can be modeled by a Markov channel model. The documents "E.Lutz, A Markov model for corrected land mobile Satellite channels [ J ]. International Journal of Satellite communications.1996,14(4) -. The main difference between high speed aircraft and terrestrial mobile satellite channel models is the presence of a plasma sheath environment. In summary, the following disadvantages exist in the aspect of channel modeling of high-speed aircraft: (1) the traditional single-channel model mostly refers to an aviation remote measurement channel model, does not consider the problem of channel time variation and non-stationarity, does not accord with the real situation of an aircraft, and causes the calculation result of the established channel model to be inaccurate and the error to be large. (2) Aiming at the plasma sheath channel environment, the patent' Stone Lei, Square hydrology, etc., a reentry dynamic plasma sheath Markov channel modeling method, CN: 201510513924.6 "constructed a markov channel model of plasma sheath, but still did not take into account the spatial transmission channel environment of high speed aircraft. Therefore, current channel modeling studies for high speed aircraft cannot simultaneously describe the combined effects of spatial transmission channel environment and plasma sheath. Although the terrestrial mobile satellite channel can be used for reference, the influence of the plasma sheath environment needs to be considered to modify the used satellite channel model, particularly the state model of the joint channel. For the near space high speed aircraft-double satellite communication system, the effectiveness and accuracy of the established channel model are determined by a state model of a non-stationary channel. Therefore, the most important method in constructing the joint channel model is the generation method of the state model (Markov state sequence) in the plasma sheath environment of the high-speed aircraft.
In summary, the problems of the prior art are as follows: in the aspect of channel modeling of the existing high-speed aircraft, channel time-varying non-stationarity is not considered; the construction of the joint channel model is not completed; the state model in the joint channel modeling of the high-speed aircraft is inaccurate.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a method for generating a dual-satellite joint channel Markov state sequence of a high-speed aircraft.
The invention is realized in such a way that a method for generating a dual-satellite joint channel Markov state sequence of a high-speed aircraft comprises the following steps:
respectively establishing state transition matrixes of a near space high-speed aircraft-satellite 1 system and an aircraft-satellite 2 system according to a terrestrial mobile satellite double-satellite channel state model and a plasma sheath Markov channel state model;
generating a state transition matrix of a near space high-speed aircraft-double satellite related link according to the correlation between the double satellites;
generating a near-space high-speed aircraft-double-satellite combined state sequence according to the state transition matrix of the relevant link;
and fourthly, decomposing the combined state sequence to obtain respective state sequences of the aircraft-satellite 1 and the aircraft-satellite 2.
Further, the method for generating the Markov state sequence of the dual-satellite joint channel of the high-speed aircraft comprises the following steps:
firstly, respectively establishing a state transition matrix P of a near-space high-speed aircraft-satellite 1 system according to a terrestrial mobile satellite two-satellite channel state model and a plasma sheath Markov channel state modelsat1_plasmaAnd state transition matrix P of near space high speed aircraft-satellite 2 systemsat2_plasma；
Secondly, according to the correlation between the double satellites, a state transition matrix P of a two-state Markov model of a near space high-speed aircraft-single satellite systemsat1_plasmaAnd Psat2_plasmaState transition matrix P for constructing four-state model of near space high-speed aircraft-double satellite related linkcorr_tran；
Thirdly, using the solved state transition matrix P of the near space high-speed aircraft-double satellite related linkcorr_tranObtaining a joint state sequence S of a Markov channel model for the two satellitest(t＝1,2,...,n)；
Fourthly, decomposing the combined state sequence to obtain a state sequence A of the near space high-speed aircraft-satellite 1tAnd the aircraft-satellite 2 state sequence Bt(t＝1,2,...,n)。
Further, the first step includes:
(1) selecting a two-state transition matrix P of the satellite 1 and the satellite 2 according to the elevation angle and the azimuth angle of the satellite 1 and the satellite 2sat1And Psat2And input into a two-state transition matrix P of the plasma sheathplasma；
(2) Transferring satellite 1 state to a matrix Psat1State transition matrix P with plasma sheathplasmaAnd (3) combining to obtain a state transition matrix of the near-space high-speed aircraft-satellite 1 system:
Figure BDA0001338473460000031
wherein, b1Representing the probability of the satellite 1 transitioning from "good state" to "bad state", g1Indicating that the satellite 1 goes from "bad state" to "goodState "transition probability;
(3) transferring satellite 2 state to matrix Psat2State transition matrix P with plasma sheathplasmaAnd (3) combining to obtain a state transition matrix of the near space high-speed aircraft-satellite 2 system:
Figure BDA0001338473460000041
wherein, b2Representing the probability of the satellite 2 transitioning from "good state" to "bad state", g2Representing the probability of the satellite 2 transitioning from "bad state" to "good state
Further, in the step (2) and the step (3), b1、b2、g1And g2The calculation is 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)
Figure BDA0001338473460000042
Figure BDA0001338473460000043
wherein, Psat1(i,j)、Psat2(i, j) and Pplasma(i, j) are transition matrices P, respectivelysat1、Psat2And PplasmaIs the probability of jumping from state i to state j, 0 ≦ Psat1(i,j)≤1，0≤Psat2(i, j) is less than or equal to 1 and P is less than or equal to 0plasma(i, j) is less than or equal to 1 and
Figure BDA0001338473460000044
and
Figure BDA0001338473460000045
further, the second step includes:
1) firstly, assuming that the channels of two satellites are mutually independent, a near space high-speed aircraft-single satellite system state transfer matrix P is formedsat1_plasmaAnd Psat2_plasmaSubstituting the following formula to derive a state transition matrix P of a four-state model of the near space high-speed aircraft-double satellite channel mutually independenttran：
Figure BDA0001338473460000051
Wherein
Figure BDA0001338473460000052
Representing a matrix multiplication;
2) four-state transition matrix P for mutually independent channelstranThe four-state transition matrix P of the near space high-speed aircraft-double satellite correlation link is obtained by utilizing the correlation matrix C for correctioncorr_tran：
Figure BDA0001338473460000053
Wherein x, y, v, w are correction parameters;
the correlation matrix C is calculated as follows:
inputting a correlation coefficient rho between two satellites to obtain an initial correction parameter x0，y0，v0，w0If rho is not less than 0, the initial correction parameter x is obtained by the following formula0，y0，v0，w0：
Figure BDA0001338473460000054
If rho is less than 0, the initial correction parameter x is obtained by the following formula0，y0，v0，w0：
Figure BDA0001338473460000055
From the joint state secondary moment ρ of the satellites 1,2 of the formula, the correction factor c can be derived
Wherein the content of the first and second substances,
Figure BDA0001338473460000056
the derived correction factor c is:
Figure BDA0001338473460000061
using the derived initial correction parameter x0，y0，v0，w0And substituting the correction coefficient C into the following formula to obtain a correlation matrix C:
Figure BDA0001338473460000062
further, the third step specifically includes:
step one, inputting the state transition matrix P of the near space high-speed aircraft-double satellite related linkcorr_tranGiven the current state St(St＝1,2,3,4)；
Step two, generating a (0,1) uniformly distributed random number U, and setting k to be 1;
step three, testing conditions:
Figure BDA0001338473460000063
if the test condition is satisfied, the next state St+1K is; if the test condition is not met, continuing to repeat the test until the test condition is met;
step four, the state of the next step is determined, and then a Markov combined state sequence S of the double satellites is generatedt，t＝1,2,...,n。
Further, the fourth step specifically includes:
1) assuming that the good state and the bad state of the high-speed aircraft-satellite 1 and the high-speed aircraft-satellite 2 are respectively represented by 1 and 2, the state of the high-speed aircraft-double-satellite channel can be divided into four joint states of good-good, good-bad, bad-good and bad-bad, which are respectively represented by 1,2,3 and 4;
2) for a sequence of associated states StDecomposition into a state sequence A of a near-space high-speed aircraft-satellite 1tAnd the aircraft-satellite 2 state sequence BtAnd judging the conditions:
when S istIf 1, the high-speed aircraft satellite 1 corresponds to a "good state", i.e. at1 is ═ 1; high speed aircraft-satellite 2 corresponds to a "good state", i.e. Bt＝1；
When S istAt 2, the high-speed aircraft satellite 1 corresponds to a "good state", i.e. at1 is ═ 1; high speed aircraft-satellite 2 corresponds to a "bad state", i.e. Bt＝2；
When S istIf 3, the high-speed aircraft satellite 1 corresponds to a "bad state", i.e. at2; high speed aircraft-satellite 2 corresponds to a "good state", i.e. Bt＝1；
When S istIf 4, the high-speed aircraft satellite 1 corresponds to a "bad state", i.e. at2; high speed aircraft-satellite 2 corresponds to a "bad state", i.e. Bt＝2；
The obtained state sequences of the near space vehicle-satellite 1 and the vehicle-satellite 2.
Another object of the present invention is to provide a high-speed ultrasonic aircraft using the method for generating a two-satellite joint channel markov state sequence of a high-speed aircraft.
The invention has the advantages and positive effects that: the invention can complete the establishment of the multi-state Markov state chain under the condition of no actual measurement data; meanwhile, the influence of the plasma sheath on the state sequence is considered, and compared with the existing two-satellite channel state model, the hypersonic aircraft-two-satellite channel under the influence of the plasma sheath can be more accurately described in terms of the state of a non-stationary channel.
The state sequence generation method provided by the invention is suitable for the generation of the state model in the relay satellite channel modeling of the high-speed aircraft in the near space and the relay satellite channel modeling of the space reentry aircraft.
Drawings
Fig. 1 is a flowchart of a method for generating a two-satellite joint channel markov state sequence of a high-speed aircraft according to an embodiment of the present invention.
Fig. 2 is a schematic diagram of state transition of a near-space high-speed aircraft-dual-satellite four-state markov model according to an embodiment of the present invention.
Fig. 3 is a block diagram of the generation of the joint state sequence decomposed into state sequences for each satellite according to an embodiment of the present invention.
Fig. 4 is a schematic diagram of the decomposition of the joint state sequence provided by the embodiment of the present invention into the state sequences of the near-space vehicle-satellite 1 and the vehicle-satellite 2.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the following embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The following detailed description of the principles of the invention is provided in connection with the accompanying drawings.
As shown in fig. 1, a method for generating a dual-satellite joint channel markov state sequence of a high-speed aircraft according to an embodiment of the present invention includes the following steps:
s101: respectively establishing state transition matrixes of a near-space high-speed aircraft-satellite 1 system and an aircraft-satellite 2 system according to a terrestrial mobile satellite double-satellite channel state model and a plasma sheath Markov channel state model;
s102: generating a state transition matrix of a near space high-speed aircraft-double satellite related link according to the correlation between the double satellites;
s103: generating a near space high-speed aircraft-double satellite combined state sequence according to the state transition matrix of the relevant link;
s104: and decomposing the combined state sequence to obtain the respective state sequences of the aircraft-satellite 1 and the aircraft-satellite 2.
The application of the principles of the present invention will now be described in further detail with reference to the accompanying drawings.
As shown in fig. 1, a method for generating a dual-satellite joint channel markov state sequence of a high-speed aircraft according to an embodiment of the present invention includes the following steps:
s1, respectively establishing a state transition matrix P of the near-space high-speed aircraft-satellite 1 system according to the two-satellite channel state model and the plasma sheath Markov channel state model of the land mobile satellitesat1_plasmaAnd state transition matrix P of near space high speed aircraft-satellite 2 systemsat2_plasma。
S1.1: obtaining two state transition matrixes of the satellite 1 and the satellite 2 according to the fact that the azimuth angles of the two satellites are 45 degrees, the elevation angle of the satellite 1 is 25 degrees and the elevation angle of the satellite 2 is 45 degrees
Figure BDA0001338473460000091
And
Figure BDA0001338473460000092
and input into a two-state transition matrix of the plasma sheath
Figure BDA0001338473460000093
S1.2: transferring satellite 1 state to a matrix Psat1State transition matrix P with plasma sheathplasmaAnd (3) combining to obtain a state transition matrix of the near-space high-speed aircraft-satellite 1 system:
Figure BDA0001338473460000094
wherein, b1Representing the probability of a transition from "good state" to "bad state", g1Represents the transition probability from "bad state" to "good state"; b can be obtained by the following formula1And g1:
Figure BDA0001338473460000099
Figure BDA0001338473460000095
Thus, it is possible to provide
Figure BDA0001338473460000096
Wherein, Psat1(i, j) and Pplasma(i, j) are transition matrices P, respectivelysat1And PplasmaIs the probability of jumping from state i to state j, 0 ≦ Psat1(i,j)≤1，0≤Pplasma(i, j) is less than or equal to 1 and
Figure BDA0001338473460000097
s1.3: transferring satellite 2 state to matrix Psat2State transition matrix P with plasma sheathplasmaAnd combining to obtain a state transition matrix of the near space high-speed aircraft-satellite 2 system:
Figure BDA0001338473460000098
wherein, b2Representing the probability of a transition from "good state" to "bad state", g2B is obtained by expressing the probability of transition from "bad state" to "good state" using the following formula2And g2：
Figure BDA0001338473460000107
Figure BDA0001338473460000101
Thus, it is possible to provide
Figure BDA0001338473460000102
Wherein, Psat2(i, j) is the transition matrix Psat2Is the probability of jumping from state i to state j, 0 ≦ Psat2(i, j) is less than or equal to 1, and
Figure BDA0001338473460000103
s2 state transition matrix P of two-state Markov model of near space high speed aircraft-single satellite system based on correlation between two satellitessat1_plasmaAnd Psat2_plasmaState transition matrix P for constructing four-state model of near space high-speed aircraft-double satellite related linkcorr_tran。
S2.1: firstly, assuming that the channels of two satellites are mutually independent, the state of a near space high-speed aircraft-single satellite system is transferred to a matrix
Figure BDA0001338473460000104
And
Figure BDA0001338473460000105
substituting the following formula to derive a state transition matrix P of a four-state model of the near space high-speed aircraft-double satellite channel mutually independenttran：
Figure BDA0001338473460000106
S2.2: different correlation coefficients exist between different azimuth angles and elevation angles of the satellites, wherein the azimuth angles of the two satellites are 45 degrees, the elevation angle of the satellite 1 is 25 degrees, the elevation angle of the satellite 2 is 45 degrees, the correlation coefficient rho of the two satellites is 0.1454, correlation between channels needs to be considered, and therefore a four-state transition matrix P with mutually independent channels is formedtranObtaining a four-state transition matrix P of the near space high-speed aircraft-double satellite correlation link after correction by using the correlation matrix Ccorr_tran：
Figure BDA0001338473460000111
Wherein x, y, v, w are correction parameters;
it should be further noted that, in step S2.2, the method for calculating the correlation matrix C is as follows:
s2.2.1: inputting a correlation coefficient rho between two satellites to obtain an initial correction parameter x0，y0，v0，w0If rho is not less than 0, the initial correction parameter x is obtained by the following formula0，y0，v0，w0：
Figure BDA0001338473460000112
If rho is less than 0, the initial correction parameter x is obtained by the following formula0，y0，v0，w0：
Figure BDA0001338473460000113
S2.2.2: the correction factor c can be derived from the joint state secondary moment p of the satellites 1,2, where,
Figure BDA0001338473460000114
the derived correction factor c is:
Figure BDA0001338473460000115
using the derived initial correction parameter x0，y0，v0，w0And substituting the correction coefficient C into the following formula to obtain a correlation matrix C:
Figure BDA0001338473460000121
s2.2.3: initial correction parameter x obtained by S2.2.1 and S2.2.20，y0，v0，w0And C is substituted into the following formula to obtain a correlation matrix C:
Figure BDA0001338473460000122
s3 utilizes the state transition matrix P of the near space high speed aircraft-double satellite related link obtained in the step S2corr_tranObtaining a joint state sequence S of a Markov channel model for the two satellitest(t＝1,2,...,n)。
S3.1: inputting the state transition matrix P of the near space high speed aircraft-double satellite correlation link obtained in the step S2corr_tranGiven the current state St(St＝1,2,3,4)；
S3.2: generating a (0,1) uniformly distributed random number U, and setting k to be 1;
s3.3: and (3) testing conditions are as follows:
Figure BDA0001338473460000123
if the test condition is satisfied, the next state St+1K is; if the test condition is not met, continuing to repeat the step S3.3 until the test condition is met;
s3.4: determining the state of the next step through the step S3.3, and further generating a Markov combined state sequence S of the double satellitest，t＝1,2,...,n。
S4 decomposing the combined state sequence to obtain a state sequence A of the near-space high-speed aircraft-satellite 1tAnd the aircraft-satellite 2 state sequence Bt(t＝1,2,...,n)。
S4.1: assuming that the good state and the bad state of the high-speed aircraft-satellite 1 and the high-speed aircraft-satellite 2 are respectively represented by 1 and 2, the state of the high-speed aircraft-double-satellite channel can be divided into four combined states of good-good, good-bad, bad-good and bad-bad, which are respectively represented by 1,2 and 2,3.4 represents (S)t1,2,3,4), as shown in fig. 2;
s4.2 As shown in FIG. 3, for the association State sequence StDecomposition into a state sequence A of a near-space high-speed aircraft-satellite 1tAnd the aircraft-satellite 2 state sequence BtAnd judging the conditions:
when S istIf 1, the high-speed aircraft satellite 1 corresponds to a "good state", i.e. at1 is ═ 1; high speed aircraft-satellite 2 corresponds to a "good state", i.e. Bt＝1；
When S istAt 2, the high-speed aircraft satellite 1 corresponds to a "good state", i.e. at1 is ═ 1; high speed aircraft-satellite 2 corresponds to a "bad state", i.e. Bt＝2；
When S istIf 3, the high-speed aircraft satellite 1 corresponds to a "bad state", i.e. at2; high speed aircraft-satellite 2 corresponds to a "good state", i.e. Bt＝1；
When S istIf 4, the high-speed aircraft satellite 1 corresponds to a "bad state", i.e. at2; high speed aircraft-satellite 2 corresponds to a "bad state", i.e. Bt＝2；
The resulting sequence of states for the near space vehicle-satellite 1 and the vehicle-satellite 2 is shown in fig. 4.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.

Claims (3)

1. A method for generating a dual-satellite joint channel Markov state sequence of a high-speed aircraft is characterized by comprising the following steps of:
respectively establishing state transition matrixes of a near space high-speed aircraft-satellite 1 system and an aircraft-satellite 2 system according to a terrestrial mobile satellite double-satellite channel state model and a plasma sheath Markov channel state model;
generating a state transition matrix of a near space high-speed aircraft-double satellite related link according to the correlation between the double satellites;
generating a near-space high-speed aircraft-double-satellite combined state sequence according to the state transition matrix of the relevant link;
decomposing the combined state sequence to obtain respective state sequences of the aircraft-satellite 1 and the aircraft-satellite 2;
the method for generating the Markov state sequence of the double-satellite joint channel of the high-speed aircraft comprises the following steps:
firstly, respectively establishing a state transition matrix P of a near-space high-speed aircraft-satellite 1 system according to a terrestrial mobile satellite two-satellite channel state model and a plasma sheath Markov channel state modelsat1_plasmaAnd state transition matrix P of near space high speed aircraft-satellite 2 systemsat2_plasma；
Secondly, according to the correlation between the double satellites, a state transition matrix P of a two-state Markov model of a near space high-speed aircraft-single satellite systemsat1_plasmaAnd Psat2_plasmaState transition matrix P for constructing four-state model of near space high-speed aircraft-double satellite related linkcorr_tran；
Thirdly, using the solved state transition matrix P of the near space high-speed aircraft-double satellite related linkcorr_tranObtaining a joint state sequence S of a Markov channel model for the two satellitestWherein t is 1, 2.. times.n;
fourthly, decomposing the combined state sequence to obtain a state sequence A of the near space high-speed aircraft-satellite 1tAnd the aircraft-satellite 2 state sequence BtWherein t is 1, 2.. times.n;
the first step comprises:
(1) selecting a two-state transition matrix P of the satellite 1 and the satellite 2 according to the elevation angle and the azimuth angle of the satellite 1 and the satellite 2sat1And Psat2And input into a two-state transition matrix P of the plasma sheathplasma；
(2) Transferring satellite 1 state to matrix Psat1State transition matrix P with plasma sheathplasmaAnd (3) combining to obtain a state transition matrix of the near-space high-speed aircraft-satellite 1 system:
Figure FDA0003048263220000021
wherein, b1Representing the probability of the satellite 1 transitioning from "good state" to "bad state", g1Represents the probability of the satellite 1 transitioning from the "bad state" to the "good state";
(3) transferring satellite 2 state to matrix Psat2State transition matrix P with plasma sheathplasmaAnd (3) combining to obtain a state transition matrix of the near space high-speed aircraft-satellite 2 system:
Figure FDA0003048263220000022
wherein, b2Representing the probability of the satellite 2 transitioning from "good state" to "bad state", g2Represents the probability of the satellite 2 transitioning from "bad state" to "good state";
further, in the step (2) and the step (3), b1、b2、g1And g2The calculation is 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)
Figure FDA0003048263220000023
Figure FDA0003048263220000024
wherein, Psat1(i,j)、Psat2(i, j) and Pplasma(i, j) are respectively a state transition matrix Psat1、Psat2And PplasmaIs the probability of jumping from state i to state j, 0 ≦ Psat1(i,j)≤1，0≤Psat2(i, j) is less than or equal to 1 and P is less than or equal to 0plasma(i, j) is less than or equal to 1 and
Figure FDA0003048263220000025
and
Figure FDA0003048263220000026
wherein i is 1,2, j is 1, 2;
the second step includes:
1) firstly, assuming that the channels of two satellites are mutually independent, a near space high-speed aircraft-single satellite system state transfer matrix P is formedsat1_plasmaAnd Psat2_plasmaSubstituting the following formula to derive a state transition matrix P of a four-state model of the near space high-speed aircraft-double satellite channel mutually independenttran：
Figure FDA0003048263220000031
Wherein
Figure FDA0003048263220000032
Representing a matrix multiplication;
2) four-state transition matrix P for mutually independent channelstranThe four-state transition matrix P of the near space high-speed aircraft-double satellite correlation link is obtained by utilizing the correlation matrix C for correctioncorr_tran：
Figure FDA0003048263220000033
Wherein x, y, v, w are correction parameters;
the correlation matrix C is calculated as follows:
inputting a correlation coefficient rho between two satellites to obtain an initial correction parameter x0，y0，v0，w0If rho is not less than 0, the initial correction parameter x is obtained by the following formula0，y0，v0，w0：
Figure FDA0003048263220000034
If rho is less than 0, the initial correction parameter x is obtained by the following formula0，y0，v0，w0：
Figure FDA0003048263220000035
According to the second moment rho of the joint state of the satellites 1 and 2, a correction coefficient c can be deduced; wherein the content of the first and second substances,
Figure FDA0003048263220000041
the derived correction factor c is:
Figure FDA0003048263220000042
using the derived initial correction parameter x0，y0，v0，w0And substituting the correction coefficient C into the following formula to obtain a correlation matrix C:
Figure FDA0003048263220000043
2. the high-speed aircraft two-satellite joint channel markov state sequence generating method of claim 1, wherein the third step specifically comprises:
step one, inputting the state transition matrix P of the near space high-speed aircraft-double satellite related linkcorr_tranGiven the current state StIn which S ist＝1,2,3,4；
Step two, generating a (0,1) uniformly distributed random number U, and setting k to be 1;
step three, testing conditions:
Figure FDA0003048263220000044
if the test condition is satisfied, the next state St+1K is; if the test condition is not met, continuing to repeat the test until the test condition is met;
step four, the state of the next step is determined, and then a Markov combined state sequence S of the double satellites is generatedt，t＝1,2,...,n。
3. The high-speed aircraft two-satellite joint channel markov state sequence generating method of claim 1 wherein said fourth step specifically comprises:
1) assuming that the good state and the bad state of the high-speed aircraft-satellite 1 and the high-speed aircraft-satellite 2 are respectively represented by 1 and 2, the state of the high-speed aircraft-double-satellite channel can be divided into four joint states of good-good, good-bad, bad-good and bad-bad, which are respectively represented by 1,2,3 and 4;
2) for a sequence of associated states StDecomposition into a state sequence A of a near-space high-speed aircraft-satellite 1tAnd the aircraft-satellite 2 state sequence BtAnd judging the conditions:
when S istIf 1, the high-speed aircraft satellite 1 corresponds to a "good state", i.e. at1 is ═ 1; high speed aircraft-satellite 2 corresponds to a "good state", i.e. Bt＝1；
When S istAt 2, the high-speed aircraft satellite 1 corresponds to a "good state", i.e. at1 is ═ 1; high speed aircraft-satellite 2 corresponding bad shapeState ", i.e. Bt＝2；
When S istIf 3, the high-speed aircraft satellite 1 corresponds to a "bad state", i.e. at2; high speed aircraft-satellite 2 corresponds to a "good state", i.e. Bt＝1；
When S istIf 4, the high-speed aircraft satellite 1 corresponds to a "bad state", i.e. at2; high speed aircraft-satellite 2 corresponds to a "bad state", i.e. Bt＝2；
The obtained state sequences of the near space vehicle-satellite 1 and the vehicle-satellite 2.
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