CN117595912A - Aircraft random access and time synchronization fusion design method - Google Patents

Aircraft random access and time synchronization fusion design method Download PDF

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Publication number
CN117595912A
CN117595912A CN202311370009.7A CN202311370009A CN117595912A CN 117595912 A CN117595912 A CN 117595912A CN 202311370009 A CN202311370009 A CN 202311370009A CN 117595912 A CN117595912 A CN 117595912A
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China
Prior art keywords
aircraft
user
time
target
target aircraft
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朱向鹏
卢樟健
边朗
田野
张亢
王瑛
严涛
周泉
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Xian Institute of Space Radio Technology
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Xian Institute of Space Radio Technology
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Priority to CN202311370009.7A priority Critical patent/CN117595912A/en
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    • 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
    • H04B7/18502—Airborne stations
    • H04B7/18506—Communications with or from aircraft, i.e. aeronautical mobile service
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04W—WIRELESS COMMUNICATION NETWORKS
    • H04W56/00—Synchronisation arrangements
    • H04W56/001—Synchronization between nodes
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04W—WIRELESS COMMUNICATION NETWORKS
    • H04W74/00—Wireless channel access
    • H04W74/08—Non-scheduled access, e.g. ALOHA
    • H04W74/0833—Random access procedures, e.g. with 4-step access
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
    • Y02D30/00—Reducing energy consumption in communication networks
    • Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks

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  • Engineering & Computer Science (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Signal Processing (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Physics & Mathematics (AREA)
  • Radar Systems Or Details Thereof (AREA)

Abstract

The invention relates to a method for designing synchronous fusion of random access and time of an aircraft, which can simultaneously realize the requirements of random access and high-precision measurement, and can meet the capability of low-speed communication of a user spacecraft and a target spacecraft when a clock difference is calculated by using a bidirectional measurement distance result to adjust the time reference of the user spacecraft to be synchronous with Beidou. The invention can meet the time synchronization scene of the multi-user spacecraft, uses the burst signal to scan in different spaces, realizes the broadcasting, random access and high-precision measurement capability of the navigation message, can meet the capability of simultaneous access and time synchronization of multiple users, and changes the condition that the random access process and the time synchronization process are designed according to two stages in the past.

Description

Aircraft random access and time synchronization fusion design method
Technical Field
The invention belongs to the technical field of communication and measurement, and relates to a method for synchronously fusing aircraft random access and time.
Background
At present, the communication navigation integrated technology is developed rapidly, and the integration of the communication and navigation fields is required to be completed technically. When communication and navigation are integrated in a wide airspace, the problems of two technical aspects of random access and time synchronization are required to be faced. According to the prior solution, the random access process and the time synchronization are independently solved.
The random access technology is a special technology in the communication field and is a problem which is primarily solved when a user terminal accesses a communication network. Time synchronization is a problem to be solved in the time-frequency and measurement fields. Patent CN109150284A discloses a multi-scene access method of a measurement and control communication system, which aims at solving the problem that the measurement and control means of the existing planned access cannot adapt to the measurement and control requirements of a future aerospace system. When the application scene is a multi-beam full airspace scanning access mode, the spacecraft continuously transmits telemetry signals, the measurement and control communication system calls scanning beams to perform full airspace target search, the received telemetry signals are identified, and when the spacecraft is a cooperative spacecraft, remote control signals are transmitted to the spacecraft, and the method needs an omnidirectional antenna to assist. This patent is representative of the field of random access technology.
Time synchronization is a problem to be solved in the time-frequency and measurement fields. The patent CN110793528A 'a time synchronization self-adaptive networking method based on GNSS satellite common view' provides a time synchronization self-adaptive networking method based on GNSS satellite common view, and high-precision time wireless comparison among nodes is realized through GNSS satellite common view, so that the problem of high-precision time comparison among nodes in a time network is solved; and a plurality of comparison reference points are selected in a self-adaptive manner among nodes in the network, so that the problem of self-monitoring and judging of the synchronous performance integrity of each node is solved. The patent addresses the problem of time synchronization under co-vision conditions and is now widely used.
According to the prior art approach, the user aircraft time synchronization link and the random access are respectively designed. The method can be used for realizing the purpose of scanning airspace on a large scale for the target aircraft, and has the advantages of large service range, long scanning period, uncontrollable access time and the like, and the independent design of access along with time synchronization can not meet the use requirements in the fields of moon and deep space.
Disclosure of Invention
The invention solves the technical problems that: the method for designing the fusion of the random access and the time synchronization of the aircraft is provided to overcome the defects of the prior art, realize the two processes of the random access and the time synchronization and provide space-time reference and communication access service for the aircraft of the ground and lunar space user.
The solution of the invention is as follows:
a method for designing synchronous fusion of aircraft random access and time includes:
dividing a service airspace into a plurality of wave positions according to a service space by a target aircraft to realize complete coverage;
dividing a working time slot into a receiving time slot and a transmitting time slot by a target aircraft; in the transmitting time slot, the target aircraft switches to the second wave position after the first wave position broadcasts the complete navigation message and access capability information according to the wave position information, updates the navigation message and the access capability information according to the second wave position information and broadcasts, and so on until all wave positions are switched to the receiving time slot after scanning is finished;
the user aircraft divides the working time slot into a receiving time slot and a transmitting time slot; in the receiving time slot, the user aircraft receives the navigation message and the access capability information of the target aircraft, then calculates the position of the target aircraft and determines the access capability of the target aircraft, and determines and adjusts the antenna pointing direction under the condition that the target aircraft has the access capability; continuously sending an access application and self-position information to a target aircraft in a transmitting time slot;
receiving at a receiving slot by a target aircraftThe method comprises the steps of acquiring user aircraft information applied for access by a signal transmitted by a user aircraft, and measuring a pseudo range T of the user aircraft applied for access A And allocating communication resources thereto, the pseudo-range T being determined when transmitting time slots A And the communication resource is used as a receipt signal to be sent to the corresponding user aircraft, so that the user aircraft can be accessed along with meeting;
receiving receipt signals of the target aircraft by the user aircraft in a receiving time slot, and analyzing pseudo-range T through the receipt signals A Measuring a pseudo-range T of a target aircraft using a local time reference B And according to the bidirectional pseudo-range measurement result, performing bidirectional time comparison and calculation, unifying the time reference of the user aircraft to the time reference of the target aircraft, and realizing time synchronization of the user aircraft and the target aircraft.
Preferably, in the initial stage, the user aircraft is preloaded with ephemeris information of the target aircraft, so that the position of the target aircraft can be roughly determined, the user aircraft determines the pointing direction of the receiving antenna according to the position of the target aircraft, and the attitude of the antenna is adjusted to point to the target aircraft and is in a normally-received state.
Preferably, the user aircraft performs bidirectional time comparison and calculation according to the bidirectional pseudo-range measurement result, and the user aircraft time reference is unified to the target aircraft time reference in the following manner:
the user aircraft will resolve the pseudorange T A And measured target aircraft pseudorange T B Carrying out normalization treatment;
determining the orbit position of the user spacecraft by using a liasion positioning method;
obtaining clock differences of the user aircraft and the target aircraft;
the user aircraft uses the clock skew to unify the time reference to the target aircraft time reference.
Preferably, the user aircraft resolves the pseudorange T A And target aircraft pseudorange T measured using local time reference B The expression is as follows:
wherein:
T AB (t 1 )：t 1 at moment, a pseudo range T of a user aircraft applying for access, which is measured by a target aircraft A ；
T BA (t 2 )：t 2 Time of day, a target aircraft pseudorange T measured by a user aircraft using a local time reference B ；
Target aircraft at t 2 Three-dimensional position vector of moment;
user aircraft at t 1 Three-dimensional position vector of moment;
δ A (t 2 ): target aircraft at t 2 Clock difference of time;
δ B (t 1 ): user aircraft at t 1 Clock difference of time;
δ rel-AB ，δ rel-BA : satellite clock periodic relativistic effects;
time delay of a receiving end of a user aircraft;
delay of a transmitting end of the target aircraft;
user flyingDelay of the transmitter transmitting end;
time delay of a receiving end of the target aircraft;
ε AB and epsilon BA Is random noise.
Preferably, the user aircraft will resolve the pseudorange T A And measured target aircraft pseudorange T B Normalization processing is performed in the following manner:
resolving a pseudorange T for a user aircraft A And target aircraft pseudorange T measured using local time reference B Normalized to t 0 (t 0 ≤t 2 ＜t 1 ) Then
T AB (t 0 )：t 0 At moment, the target aircraft measures the obtained pseudo-range normalized value of the user aircraft applied for access;
T BA (t 0 )：t 2 at the moment, the user aircraft uses a target aircraft pseudo-range normalized value measured by a local time reference;
dT AB : target aircraft at t 1 The relative clock difference of the moments;
dT BA : user aircraft at t 1 The relative clock difference of the moments;
c: light velocity;
target aircraft at t 0 Three-dimensional position vector of moment;
user aircraft at t 0 Three-dimensional position vector of moment;
δ A (t 0 ): target aircraft at t 0 Clock difference of time;
δ B (t 0 ): user aircraft at t 0 Clock difference of time.
Preferably, the orbit position of the user spacecraft is determined by using a liasion positioning methodThe formula of (2) is as follows:
preferably, the clock rate of the user aircraft and the target aircraft is obtained using the following formula
Preferably, the user aircraft adjusts the local time of 1pps by using the clock difference, unifies the time reference to the target aircraft time reference, and synchronizes the Beidou time with the target aircraft.
Preferably, the transmitting time slot and the receiving time slot of the target aircraft adopt the same signal structure, and each time slot has 1 frame of data in communication.
Preferably, the random access channel multiplexing of the target aircraft and the user aircraft adopts an SDMA+CDMA mode.
Compared with the prior art, the invention has the beneficial effects that:
(1) The invention provides a method for simultaneously carrying out time synchronization and random access, which can simultaneously realize the requirements of random access and high-precision measurement, and can meet the capability of low-speed communication of a user spacecraft and a target spacecraft when a clock difference is calculated by using a bidirectional measurement distance result to adjust the time reference of the user spacecraft to be synchronous to Beidou.
(2) The invention can meet the time synchronization scene of the multi-user spacecraft, uses burst signals to scan in different ground and moon spaces, realizes the broadcasting, random access and high-precision measurement capability of navigation messages, can meet the capability of simultaneous access and time synchronization of multiple users, and changes the condition that bidirectional time comparison can only be carried out under common view in the past.
Drawings
FIG. 1 is a schematic illustration of the locations of a target aircraft and a user aircraft;
FIG. 2 is a schematic diagram of a communication interaction of a target aircraft with a user aircraft;
FIG. 3 is a transmit-receive slot design;
FIG. 4 is a random access signal design;
fig. 5 is a time synchronization simulation result.
Detailed Description
The invention is further elucidated below in connection with the accompanying drawings.
If the target aircraft is deployed at the Lagrangian point, a space-time reference and access communication service may be provided for the lunar aircraft user aircraft. The target aircraft can provide a Beidou time reference and adopts a beam scanning mode to serve the whole terrestrial month space. The user aircraft needs the target aircraft to provide a time reference, and meanwhile needs to apply for access service of the target aircraft, and communication channel resources are used. However, the target aircraft has the defects of large service range, long scanning period, uncontrollable access time and the like, and the invention designs a random access and time synchronization fusion design method, so that the requirements of communication channel resources and high-precision time synchronization can be simultaneously obtained.
The target aircraft is deployed at the Lagrangian point, and the target aircraft can provide space-time reference and access communication services for the user aircraft. The target aircraft scans according to different wave positions, a wave position diagram of the scanning is shown in fig. 1, and N wave positions are scanned altogether. Mode of operation of a target aircraftThe operation is performed in a mode of training of two modes of a receiving operation time slot and a transmitting operation time slot, as shown in fig. 3. During the transmit time slot, the target aircraft is operating in a transmit signal state. During the receive time slot, the target aircraft is operating in a state of receiving a signal. The duration of the transmit time slot and the duration of the receive time slot are T respectively S Second. FIG. 2 is a schematic diagram of a target aircraft communicating with a user aircraft.
The transmit and receive slots use the same signal structure. The effective length of the signal is 2s, the communication content of each time slot is 1 frame of data, and SDMA+CDMA mode is adopted along with multiplexing of the access channels.
Channel multiplexing: sdma+cdma;
duplex mode: time Division Duplexing (TDD), transmit time slot 2s;
the signal frame structure is shown in fig. 4, the synchronization section and the fine heel section are not modulated data, the synchronization section is 400ms, the fine heel section is 212ms, wherein the synchronization section comprises a preamble section and a capturing section, and the preamble section of the synchronization head is 200ms single carrier data.
The data segment of the target aircraft- & gtuser aircraft transmission signal comprises the broadcasted navigation information and the accessed receipt information. The data segment of the signal transmitted from the user aircraft to the target aircraft comprises links for applying access and pseudo-range measurement values, and the two links are realized in a same-frequency time division mode.
The aircraft random access and time synchronization fusion design specifically comprises four steps:
(1) The target aircraft broadcasts navigation message broadcasting and access capability information:
the target aircraft is divided into a plurality of wave positions according to the service range, so that complete coverage is realized, and all user aircraft can be ensured to establish links with the target aircraft.
The target aircraft has the same time reference as the Beidou, and divides the working time slot into a receiving time slot and a transmitting time slot. The target aircraft continues to switch between transmit and receive time slots. The transmit and receive durations require that the entire terrestrial month space wave position be scanned. In the transmitting time slot, the target aircraft continuously broadcasts the navigation message according to the wave position, after one wave position broadcasts the complete navigation message and the access capability information, updates the message and the access capability information after switching the next wave position, and broadcasts the message until the wave position is switched to the receiving time slot after scanning is finished.
(2) Service application
The user aircraft divides the working time slots into receive time slots and transmit time slots. The user aircraft is always operating in the receiving state when the service application is accessed. The user aircraft loads ephemeris information of the target aircraft, the time reference error established by the user aircraft is in the second level, and the user aircraft can roughly determine the position of the target aircraft. According to the position of the target aircraft, the user aircraft determines the pointing direction of the receiving antenna, and the user aircraft adjusts the attitude of the antenna to point to the target aircraft and is in a normally-received state.
The user aircraft receives the navigation message and the access capability information of the target aircraft. The user aircraft calculates the position of the target aircraft after receiving the navigation message, and meanwhile, the user aircraft determines the access capability of the target aircraft, adjusts more accurate antenna pointing under the condition of having the access capability, and simultaneously sends an access application to the target aircraft, and simultaneously sends the position of the user aircraft to the target aircraft. The user aircraft continuously transmits the self position and application information, and the transmitting state is up to a complete transmitting time slot.
(3) Service application response receipt
The target aircraft receives signals transmitted by the user aircraft in a receiving time slot, and measures a pseudo range T of the user according to the user aircraft information acquired by the application information A While transmitting the pseudorange measurements and allocating communication resources for responding to the response piece. The target aircraft waits for the transmit time slot to send a receipt signal to the target aircraft.
(4) Bidirectional time alignment
User flyThe vehicle measures the pseudo-range T of the target vehicle using a local time reference B . User aircraft resolving pseudoranges T through receipt signals A And performing bidirectional time comparison and calculation according to the bidirectional pseudo-range measurement result.
The two-way alignment solution is implemented on the user aircraft. The target aircraft can provide the time reference and satellite ephemeris of Beidou, and the target aircraft receives the navigation message and analyzes the information content, and when receiving the confirmation information of the self access receipt, the user aircraft extracts the bi-directional measurement pseudo-range, wherein T is as follows AB (T) represents a measured pseudorange received at time T of the user aircraft transmitting signal to the target aircraft, T BA And (t) represents the measured pseudo-range received by the target aircraft at the moment of the t of the user aircraft transmitting the signal.
The target aircraft and the user aircraft adopt a satellite bidirectional measurement mode, the two satellites mutually send signals to measure the distance, and the relative clock difference and the inter-satellite distance measurement result are obtained by exchanging measurement data and resolving, so that most of system errors and correlation errors affecting the inter-satellite distance measurement can be eliminated. It is difficult for two satellites to transmit and receive ranging data simultaneously. For time alignment, it is necessary to normalize the bi-directional pseudoranges to the same epoch.
The link measurements for the target aircraft and the user aircraft may be expressed as follows:
in the above formula:
T AB (t 1 ): target aircraft t for transmitting signals by user aircraft 1 Measuring pseudo-range received at the moment;
T BA (t 2 ): target aircraft transmitting signal user aircraft t 2 Measuring pseudo-range received at the moment;
target aircraft at t 1 Three-dimensional position vector of moment;
user aircraft at t 2 Three-dimensional position vector of moment;
δ A (t 1 ): target aircraft at t 1 Clock difference of time;
δ B (t 2 ): user aircraft at t 2 Clock difference of time;
δ rel-AB ，δ rel-BA : satellite clock periodic relativistic effects;
time delay of a receiving end of a user aircraft;
delay of a transmitting end of the target aircraft;
time delay of a transmitting end of the user aircraft;
time delay of a receiving end of the target aircraft;
ε AB and epsilon BA Is random noise.
Correcting and compensating relativistic effect error and receiving and transmitting time delay, and correcting and compensating t 1 And t 2 The measured ranging value needs to be reduced to t 0 (t 0 ≤t 2 ＜t 1 ) The link measurements may be expressed as follows:
will T AB (t 0 ) And T BA (t 0 ) And adding, namely eliminating satellite clock error information, wherein the satellite clock error information only contains constraint on satellite orbit parameters, obtaining a distance measurement value, and determining the orbit position of the user spacecraft by using a liasion positioning method.
Will T AB (t 0 ) And T BA (t 0 ) The difference can be made, so that satellite orbit information can be eliminated, and the method is directly used for measuring clock difference:
and adjusting the local time of 1pps of the user aircraft by using the clock difference information, so as to realize synchronization with the Beidou of the target aircraft. The result of time synchronization by using the above synchronization method is shown in fig. 5, the time synchronization achieves higher precision, and the user aircraft also achieves the purpose of access.
The random access and time synchronization fusion method provided by the invention can be used not only in lunar space, but also in near-earth space. The method can be used not only in the time division mode but also in the frequency division mode. The design can meet the requirements of access communication and high-precision measurement of the multi-user access target aircraft, and greatly optimizes the access and time synchronization flow.
The invention realizes the space-time reference of moon space and the capability of communication access service with low cost by the designed signal system design and link establishment method, and provides technical support for moon detection and deep space detection in China.
Although the present invention has been described in terms of the preferred embodiments, it is not intended to be limited to the embodiments, and any person skilled in the art can make any possible variations and modifications to the technical solution of the present invention by using the methods and technical matters disclosed above without departing from the spirit and scope of the present invention, so any simple modifications, equivalent variations and modifications to the embodiments described above according to the technical matters of the present invention are within the scope of the technical matters of the present invention.

Claims (10)

1. The aircraft random access and time synchronization fusion design method is characterized by comprising the following steps of:
dividing a service airspace into a plurality of wave positions according to a service space by a target aircraft to realize complete coverage;
dividing a working time slot into a receiving time slot and a transmitting time slot by a target aircraft; in the transmitting time slot, the target aircraft switches to the second wave position after the first wave position broadcasts the complete navigation message and access capability information according to the wave position information, updates the navigation message and the access capability information according to the second wave position information and broadcasts, and so on until all wave positions are switched to the receiving time slot after scanning is finished;
the user aircraft divides the working time slot into a receiving time slot and a transmitting time slot; in the receiving time slot, the user aircraft receives the navigation message and the access capability information of the target aircraft, then calculates the position of the target aircraft and determines the access capability of the target aircraft, and determines and adjusts the antenna pointing direction under the condition that the target aircraft has the access capability; continuously sending an access application and self-position information to a target aircraft in a transmitting time slot;
the target aircraft receives signals transmitted by the user aircraft in a receiving time slot, acquires information of the user aircraft applying for access, and measures a pseudo range T of the user aircraft applying for access A And allocating communication resources thereto, the pseudo-range T being determined when transmitting time slots A And the communication resource is used as a receipt signal to be sent to the corresponding user aircraft, so that the user aircraft is met at any timeAccessing;
receiving receipt signals of the target aircraft by the user aircraft in a receiving time slot, and analyzing pseudo-range T through the receipt signals A Measuring a pseudo-range T of a target aircraft using a local time reference B And according to the bidirectional pseudo-range measurement result, performing bidirectional time comparison and calculation, unifying the time reference of the user aircraft to the time reference of the target aircraft, and realizing time synchronization of the user aircraft and the target aircraft.
2. The aircraft random access and time synchronization fusion design method according to claim 1, wherein initially, the user aircraft is preloaded with ephemeris information of the target aircraft, the position of the target aircraft can be roughly determined, the user aircraft determines the pointing direction of the receiving antenna according to the position of the target aircraft, and the attitude of the antenna is adjusted to point to the target aircraft and is in a normally-received state.
3. The aircraft random access and time synchronization fusion design method according to claim 1, wherein the user aircraft performs bidirectional time comparison and calculation according to the bidirectional pseudo-range measurement result, and the manner of unifying the user aircraft time reference to the target aircraft time reference is as follows:
the user aircraft will resolve the pseudorange T A And measured target aircraft pseudorange T B Carrying out normalization treatment;
determining the orbit position of the user spacecraft by using a liasion positioning method;
obtaining clock differences of the user aircraft and the target aircraft;
the user aircraft uses the clock skew to unify the time reference to the target aircraft time reference.
4. A method for fusion design of aircraft random access and time synchronization according to claim 3, wherein the user aircraft resolves the pseudo range T A And target aircraft pseudorange T measured using local time reference B The expression is as follows:
wherein:
T AB (t 1 )：t 1 at moment, a pseudo range T of a user aircraft applying for access, which is measured by a target aircraft A ；
T BA (t 2 )：t 2 Time of day, a target aircraft pseudorange T measured by a user aircraft using a local time reference B ；
Target aircraft at t 2 Three-dimensional position vector of moment;
user aircraft at t 1 Three-dimensional position vector of moment;
δ A (t 2 ): target aircraft at t 2 Clock difference of time;
δ B (t 1 ): user aircraft at t 1 Clock difference of time;
δ rel-AB ，δ rel-BA : satellite clock periodic relativistic effects;
time delay of a receiving end of a user aircraft;
target aircraftTime delay of a transmitting end;
time delay of a transmitting end of the user aircraft;
time delay of a receiving end of the target aircraft;
ε AB and epsilon BA Is random noise.
5. The aircraft random access and time synchronization fusion design method according to claim 4, wherein the user aircraft analyzes the pseudo range T A And measured target aircraft pseudorange T B Normalization processing is performed in the following manner:
resolving a pseudorange T for a user aircraft A And target aircraft pseudorange T measured using local time reference B Normalized to t 0 (t 0 ≤t 2 ＜t 1 ) Then
T AB (t 0 )：t 0 At moment, the target aircraft measures the obtained pseudo-range normalized value of the user aircraft applied for access;
T BA (t 0 )：t 2 at the moment, the user aircraft uses a target aircraft pseudo-range normalized value measured by a local time reference;
dT AB : target aircraft at t 1 The relative clock difference of the moments;
dT BA : user aircraft at t 1 Time of dayIs a relative clock difference of (2);
c: light velocity;
target aircraft at t 0 Three-dimensional position vector of moment;
user aircraft at t 0 Three-dimensional position vector of moment;
δ A (t 0 ): target aircraft at t 0 Clock difference of time;
δ B (t 0 ): user aircraft at t 0 Clock difference of time.
6. The aircraft random access and time synchronization fusion design method according to claim 5, wherein the orbit position of the user spacecraft is determined by using a liasion positioning methodThe formula of (2) is as follows:
7. the aircraft random access and time synchronization fusion design method according to claim 6, wherein the clock differences of the user aircraft and the target aircraft are obtained by using the following formula
8. The aircraft random access and time synchronization fusion design method according to claim 7, wherein the user aircraft adjusts the local 1pps moment by using the clock difference, unifies a time reference to a target aircraft time reference, and synchronizes the Beidou time with the target aircraft.
9. The aircraft random access and time synchronization fusion design method according to claim 1, wherein the transmitting time slot and the receiving time slot of the target aircraft adopt the same signal structure, and the communication content of each time slot is 1 frame of data.
10. The aircraft random access and time synchronization fusion design method according to claim 1, wherein random access channel multiplexing of the target aircraft and the user aircraft adopts an SDMA+CDMA mode.
CN202311370009.7A 2023-10-20 2023-10-20 Aircraft random access and time synchronization fusion design method Pending CN117595912A (en)

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