CN109039417A - A kind of aircraft Tianhuangping pumped storage plant delay parameter measurement method - Google Patents
A kind of aircraft Tianhuangping pumped storage plant delay parameter measurement method Download PDFInfo
- Publication number
- CN109039417A CN109039417A CN201810272811.5A CN201810272811A CN109039417A CN 109039417 A CN109039417 A CN 109039417A CN 201810272811 A CN201810272811 A CN 201810272811A CN 109039417 A CN109039417 A CN 109039417A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- time
- control centre
- moment
- ground control
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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
- 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
- H04B7/18517—Transmission equipment in earth stations
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L7/00—Arrangements for synchronising receiver with transmitter
- H04L7/0008—Synchronisation information channels, e.g. clock distribution lines
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L7/00—Arrangements for synchronising receiver with transmitter
- H04L7/0016—Arrangements for synchronising receiver with transmitter correction of synchronization errors
- H04L7/0033—Correction by delay
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L7/00—Arrangements for synchronising receiver with transmitter
- H04L7/0054—Detection of the synchronisation error by features other than the received signal transition
Landscapes
- 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)
- Electric Clocks (AREA)
- Radio Relay Systems (AREA)
Abstract
A kind of aircraft Tianhuangping pumped storage plant delay parameter measurement method, by during aircraft is via satellite and ground control centre interaction data, record time zero, data starting sending instant, valid data sending instant and the valid data time of reception, and the time of aircraft and ground control centre is carried out by unification by GNSS, to time delay parameter and back time delay parameter before being calculated, can achieve before sending in time to control instruction and the accurate purpose for utilizing back data.Method flow accuracy is high, calculates simply, step is clear.
Description
Technical field
The present invention relates to a kind of aircraft Tianhuangping pumped storage plant delay parameter measurement methods, belong to Space TT&C field.
Background technique
Near space vehicle flight test is since flying distance is remote, mobility strong, ground observing and controlling cloth station is compared with conventional flight
Device has larger difficulty.Space-Based TT & C Technology graduallys mature in recent years, and the Tianhuangping pumped storage plant of close to space vehicle test is applied also gradually
Increase.Near space vehicle undergoes environment complicated, and more there is a phenomenon where that can compare during flight test, device carries TT&C system
When system be related to accident analysis, success criterion, the correctness and accuracy of many data applications such as System Discrimination, be observing and controlling system
It unites vital component part.For Tianhuangping pumped storage plant compared with traditional foundation observing and controlling, system is relative complex, and forwards via satellite,
Distance is remote, and link is long, and time delay is the key parameter of Tianhuangping pumped storage plant time unification, and the acquisition of delay parameter has no standard side at present
Method, often uses manual timing, low precision, and the numerical value measured under different conditions can only substantially be compared.
Summary of the invention
Technical problem solved by the present invention is the delay parameter estimated accuracy for being directed to the prior art is poor, surveys under different conditions
The problem of examination data can only substantially be compared, propose a kind of aircraft Tianhuangping pumped storage plant delay parameter measurement method.
The present invention solves above-mentioned technical problem and is achieved by following technical solution:
A kind of aircraft Tianhuangping pumped storage plant delay parameter measurement method, the specific steps are as follows:
(1) in the departure time for recording aircraft on aircraft；
(2) according to the departure time of the aircraft, aircraft, control centre is carried out in signal transduction process to the ground
The Interruption time difference, aircraft GNSS UTC time the UTC time of time and aircraft GNSS are recorded to ground control centre
It is unified to carry out time delay；
(3) adjustment aircraft antenna attitude and ground control centre antenna attitude, and with fixed frame rate N1 by aircraft
Control centre sends test data to the ground, and record test data starts sending instant aircraft GNSS moment frame count sid_
Air1, while recording ground control centre moment T_at1；
(4) aircraft GNSS moment frame count sid_air2 when the starting of record valid data is sent, while recording ground control
Central instant T_at2 processed, wherein valid data are the test data that ground control centre normally receives；
(5) the ground control centre valid data time of reception, T_gr moment is recorded, and according to step (3), the note of step (4)
Aircraft GNSS moment, ground control centre moment are unified for the UTC time of aircraft GNSS by record value, and calculate back communication
Delay time parameter；
(6) after back communication is stablized, test data, note are sent from ground control centre to aircraft with fixed frame rate N1
Record ground control centre moment T_gt1 when data starting is sent；
(7) ground control centre moment T_gt2 when the starting of record valid data is sent；
(8) the ground control centre valid data time of reception, T_ar moment is recorded, while recording when valid data receive and flying
Row device frame count sid_air3, and according to step (6), step (7) record value by aircraft GNSS moment, ground control centre
Moment is unified for the UTC time of aircraft GNSS, and calculates forward communications delay time parameter.
In the step (2), ground control centre records the UTC time time delay Uniform Formula of time, aircraft GNSS are as follows:
T0=T1- Δ T
In formula, ground command center's moment when T0 is aircraft takeoff, Δ T is the Interruption time difference, and T1 is aircraft
Aircraft GNSS moment when taking off.
The back communication delay parameter include back total delay time Δ Tb, back communication delay Δ Tbc,
Back signal search time Δ Tbs, calculation method are as follows:
Δ Tb=T_gr-T_at1
Δ Tbc=T_gr-T_at2
Δ Tbs=Δ Tb-Δ Tbc；
Wherein, the calculation method of data starting sending instant T_at1, valid data starting sending instant T_at2 are as follows:
T_at1=sid_air1/N1+T0
T_at2=sid_air2/N1+T0.
The forward communications delay time parameter include forward delay total time Δ Tf, forward communications delay time Δ Tfc,
Forward signal search time Δ Tfs, calculation method are as follows:
Δ Tf=T_ar-T_gt1
Δ Tfc=T_ar-T_gt2
Δ Tfs=Δ Tf-Δ Tfc
Wherein, the calculation method of valid data time of reception ground control centre moment T_ar are as follows:
T_ar=(sid_air3/N1+T0).
The advantages of the present invention over the prior art are that:
A kind of aircraft Tianhuangping pumped storage plant delay parameter measurement method provided by the invention, the control of when by broadcasting TV programs by satellite to star and ground
Time processed carries out unification, then by the conversion in test data transmission process to the not sent successful data time, can to it is preceding to
Call duration time and back call duration time carry out complete analysis, improve the measurement accuracy of delay parameter.
Detailed description of the invention
Fig. 1 be invention provide when unite method flow diagram；
Fig. 2 is that the GNSS time benchmark that invention provides and local time reference principle of contrast scheme；
Fig. 3 is the back and forward communications delay time axis corresponding diagram that invention provides；
Specific embodiment
A kind of aircraft Tianhuangping pumped storage plant delay parameter measurement method, as shown in Figure 1, being by by Timing Signal module, letter
Frame is compiled in number branch and isolation module, detection module, time recording module, timing interrupts module, GNSS signal module, acquisition
Module, aircraft antenna attitude discrimination module, aircraft signal transmitting and receiving module, the satellite ground tracking telemetry and command station signal transmitting and receiving with ground
Module, B decoding apparatus module, the measurement method of GNSS signal module cooperation completion delay parameter, steps are as follows for specific method:
(1) Timing Signal of aircraft and ground control station is determined, aircraft is using take off signal, GNSS signal, frame meter
Several and interrupt signal carries out time record, and ground carries out time record, aircraft record by B decoding apparatus time, GNSS signal
Time and surface seismic records time are converted to UTC time and carry out time unification.
Acquisition compiles frame module and carries out data framing and frame count with frame frequency N1.Receive the signal that takes off, aircraft frame count into
Row is reset, and by frame count and frame frequency timing, ground was directly recorded by the GNSS signal time service B decoding apparatus time successor.
(2) as shown in Fig. 2, aircraft is taken off time difference of signal and interrupt signal by Interruption response record, and
The GNSS signal time obtains accurate lift-off zero,take-off zero time T0.The zero point is used for the time unification of aircraft and ground control station.
T0=T1- Δ T
In formula, T0 be lift-off zero,take-off zero accurate UTC time, Δ T be the Interruption time difference, T1 be apart from departure time most
The close corresponding GNSS time of aircraft Interruption.
(3) as shown in figure 3, adjusting aircraft antenna attitude and satellite antenna posture, and with fixed frame rate N1 by flying
Via satellite, tracking telemetry and command station sends test data to device to the ground, and record data start sending instant aircraft frame count sid_air1
(counting corresponds to aircraft data starting sending instant T_at1)；
(4) ground satellite tracking telemetry and command station transceiver module receives, parses and record aircraft back data, and record ground is restored
(counting corresponds to aircraft valid data starting sending instant to the corresponding aircraft frame count sid_air2 of first frame back data
T_at2), while UTC time T_gr at the time of restoring data is recorded.Wherein, by the aircraft test that tracking telemetry and command station is sent to the ground
Data can have the case where preceding N frame data can not lock, and N+1 frame is known as valid data, the delivery time of preceding N frame data at this time
It is also contained in back delay time.
(5) as shown in figure 3, record the ground control centre valid data time of reception, T_gr moment, and according to step (2),
Step (3), aircraft is recorded the time to step (4) and ground control station time unification is UTC time, and calculates back communication and prolong
Slow time parameter, the back communication delay parameter include back total delay time Δ Tb, back communication delay Δ
Tbc, back signal search time Δ Tbs, calculation method are as follows:
Δ Tb=T_gr-T_at1
Δ Tbc=T_gr-T_at2
Δ Tbs=Δ Tb-Δ Tbc；
Wherein, the calculation method of aircraft data starting sending instant T_at1, valid data starting sending instant T_at2
Are as follows:
T_at1=sid_air1/N1+T0
T_at2=sid_air2/N1+T0.
(6) after back communication is stablized, test data is sent from ground control station to aircraft with fixed frame rate, ground is surveyed
Control station record data start sending instant T_gt1；
(7) moment T_gt2 when the starting of ground control station record valid data is sent；
(8) as shown in figure 3, (counting is corresponding by aircraft frame count sid_air3 when aircraft record valid data receive
Aircraft receives valid data moment T_ar).Wherein, the test data sent from ground control station to aircraft can have preceding N
The case where frame data are lost, N+1 frame is known as valid data at this time, and the delivery time of preceding N frame data is also contained in forward delay
In time；
When aircraft being recorded time, ground control station record according to step (2), step (6), step (7), step (8)
Between be unified for UTC time, and calculate forward communications delay time parameter, the forward communications delay time parameter includes preceding to prolonging
Slow total time Δ Tf, forward communications delay time Δ Tfc, forward signal search time Δ Tfs, calculation method are as follows:
Δ Tf=T_ar-T_gt1
Δ Tfc=T_ar-T_gt2
Δ Tfs=Δ Tf-Δ Tfc
Wherein, aircraft receives the calculation method of valid data moment T_ar are as follows:
T_ar=(sid_air3/N1+T0).
The content that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.
Claims (4)
1. a kind of aircraft Tianhuangping pumped storage plant delay parameter measurement method, it is characterised in that steps are as follows:
(1) in the departure time for recording aircraft on aircraft；
(2) according to the departure time of the aircraft, aircraft, control centre carries out the timing in signal transduction process to the ground
The UTC time that break period is poor, aircraft GNSS UTC time records time and aircraft GNSS to ground control centre carries out
Time delay is unified；
(3) adjustment aircraft antenna attitude and ground control centre antenna attitude, and with fixed frame rate N1 from aircraft to ground
Face control centre sends test data, and record test data starts sending instant aircraft GNSS moment frame count sid_air1,
Ground control centre moment T_at1 is recorded simultaneously；
(4) aircraft GNSS moment frame count sid_air2 when the starting of record valid data is sent, while recording in the control of ground
Heart moment T_at2, wherein valid data are the test data that ground control centre normally receives；
(5) the ground control centre valid data time of reception, T_gr moment is recorded, and according to the record value of step (3), step (4)
Aircraft GNSS moment, ground control centre moment are unified for the UTC time of aircraft GNSS, and calculate back communication delay
Time parameter；
(6) after back communication is stablized, test data is sent from ground control centre to aircraft with fixed frame rate N1, records number
Ground control centre moment T_gt1 when being sent according to starting；
(7) ground control centre moment T_gt2 when the starting of record valid data is sent；
(8) the ground control centre valid data time of reception, T_ar moment is recorded, while recording aircraft when valid data receive
Frame count sid_air3, and according to step (6), step (7) record value by aircraft GNSS moment, ground control centre moment
It is unified for the UTC time of aircraft GNSS, and calculates forward communications delay time parameter.
2. a kind of aircraft Tianhuangping pumped storage plant delay parameter measurement method according to claim 1, it is characterised in that: the step
Suddenly in (2), ground control centre records the UTC time time delay Uniform Formula of time, aircraft GNSS are as follows:
T0=T1- Δ T
In formula, ground command center's moment when T0 is aircraft takeoff, Δ T is the Interruption time difference, and T1 is aircraft takeoff
When the aircraft GNSS moment.
3. a kind of aircraft Tianhuangping pumped storage plant delay parameter measurement method according to claim 2, it is characterised in that: described to return
When to communication delay parameter including back total delay time Δ Tb, back communication delay Δ Tbc, back signal search
Between Δ Tbs, calculation method is as follows:
Δ Tb=T_gr-T_at1
Δ Tbc=T_gr-T_at2
Δ Tbs=Δ Tb-Δ Tbc；
Wherein, the calculation method of data starting sending instant T_at1, valid data starting sending instant T_at2 are as follows:
T_at1=sid_air1/N1+T0
T_at2=sid_air2/N1+T0.
4. a kind of aircraft Tianhuangping pumped storage plant delay parameter measurement method according to claim 2, it is characterised in that: before described
To communication delay parameter include forward delay total time Δ Tf, forward communications delay time Δ Tfc, forward signal search for when
Between Δ Tfs, calculation method is as follows:
Δ Tf=T_ar-T_gt1
Δ Tfc=T_ar-T_gt2
Δ Tfs=Δ Tf-Δ Tfc
Wherein, the calculation method of valid data time of reception ground control centre moment T_ar are as follows:
T_ar=(sid_air3/N1+T0).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810272811.5A CN109039417B (en) | 2018-03-29 | 2018-03-29 | Aircraft space-based measurement and control time delay parameter measuring method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810272811.5A CN109039417B (en) | 2018-03-29 | 2018-03-29 | Aircraft space-based measurement and control time delay parameter measuring method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109039417A true CN109039417A (en) | 2018-12-18 |
| CN109039417B CN109039417B (en) | 2021-02-05 |
Family
ID=64629434
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810272811.5A Active CN109039417B (en) | 2018-03-29 | 2018-03-29 | Aircraft space-based measurement and control time delay parameter measuring method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109039417B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110187631A (en) * | 2019-06-25 | 2019-08-30 | 北京临近空间飞行器系统工程研究所 | A kind of time unifying method and system of control system |
| CN110502038A (en) * | 2019-07-23 | 2019-11-26 | 北京控制工程研究所 | The preset high stability control method of antenna in a kind of mobile process |
| CN114448836A (en) * | 2022-01-30 | 2022-05-06 | 北京航天飞行控制中心 | Method and system for measuring time delay of space-ground loop |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2113784A2 (en) * | 2008-04-30 | 2009-11-04 | Honeywell International Inc. | Systems and methods for determining location information using dual filters |
| US7679550B2 (en) * | 2006-02-21 | 2010-03-16 | Garrison James L | System and method for model-base compression of GPS ephemeris |
| CN102882586A (en) * | 2012-10-15 | 2013-01-16 | 北京空间飞行器总体设计部 | Satellite time synchronization system |
| CN104181572A (en) * | 2014-05-22 | 2014-12-03 | 南京理工大学 | Missile-borne inertia/ satellite tight combination navigation method |
| CN107359931A (en) * | 2017-06-30 | 2017-11-17 | 上海卫星工程研究所 | Satellite TT chain circuit transmission time delay measuring method based on gps signal |
-
2018
- 2018-03-29 CN CN201810272811.5A patent/CN109039417B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7679550B2 (en) * | 2006-02-21 | 2010-03-16 | Garrison James L | System and method for model-base compression of GPS ephemeris |
| EP2113784A2 (en) * | 2008-04-30 | 2009-11-04 | Honeywell International Inc. | Systems and methods for determining location information using dual filters |
| CN102882586A (en) * | 2012-10-15 | 2013-01-16 | 北京空间飞行器总体设计部 | Satellite time synchronization system |
| CN104181572A (en) * | 2014-05-22 | 2014-12-03 | 南京理工大学 | Missile-borne inertia/ satellite tight combination navigation method |
| CN107359931A (en) * | 2017-06-30 | 2017-11-17 | 上海卫星工程研究所 | Satellite TT chain circuit transmission time delay measuring method based on gps signal |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110187631A (en) * | 2019-06-25 | 2019-08-30 | 北京临近空间飞行器系统工程研究所 | A kind of time unifying method and system of control system |
| CN110187631B (en) * | 2019-06-25 | 2021-04-13 | 北京临近空间飞行器系统工程研究所 | Time alignment method and system for control system |
| CN110502038A (en) * | 2019-07-23 | 2019-11-26 | 北京控制工程研究所 | The preset high stability control method of antenna in a kind of mobile process |
| CN110502038B (en) * | 2019-07-23 | 2022-04-22 | 北京控制工程研究所 | High-stability control method for antenna presetting in maneuvering process |
| CN114448836A (en) * | 2022-01-30 | 2022-05-06 | 北京航天飞行控制中心 | Method and system for measuring time delay of space-ground loop |
| CN114448836B (en) * | 2022-01-30 | 2024-05-31 | 北京航天飞行控制中心 | Method and system for measuring time delay of heaven and earth loop |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109039417B (en) | 2021-02-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106909071B (en) | A kind of spacecraft synchronization accuracy test macro and method based on pulse per second (PPS) | |
| EP1671151B1 (en) | Method and apparatus for satellite-based relative positioning of moving platforms | |
| CN109039417A (en) | A kind of aircraft Tianhuangping pumped storage plant delay parameter measurement method | |
| US11521441B2 (en) | Automated logging of aircraft OOOI times using mobile device | |
| CN108365905B (en) | A kind of national standard time restoration methods based on satellite common vision data real-time exchange | |
| CN106415299B (en) | System and method for high reliability monitoring of aircraft | |
| CN110412629B (en) | Positioning method and positioning system based on GNSS signal simulation node | |
| CN106093855B (en) | The navigation control method and control system of unmanned plane | |
| CN103278822B (en) | Based on satellite navigation and location system performance evaluation system and the method for HLA platform | |
| EP4198649A1 (en) | Distributed centerless space-based time reference establishing and maintaining system | |
| CN205898998U (en) | Unmanned aerial vehicle's navigation control system | |
| CN110515109B (en) | Method and device for fusing autonomous PNT time based on multiple information sources | |
| CN101989363A (en) | System and method for processing digital air data | |
| CN104297739A (en) | Method for guiding photoelectric tracking equipment in navigation monitoring | |
| CN105137754A (en) | Beidou timing type commanding machine | |
| CN117388881B (en) | Method and system for tracing satellite-borne atomic clock of low-orbit satellite to UTC (k) | |
| CN107991693A (en) | A kind of unmanned plane localization method and system for flight check | |
| CN106772472A (en) | A kind of derivation doppler measurement building method for taking the jump of GNSS receiver clock into account | |
| CN103684729A (en) | Clock synchronization device and method | |
| CN111007555A (en) | General aircraft airborne integrated navigation system and navigation method | |
| CN111352718A (en) | Business scheduling system for ground processing of GNSS multi-system occultation | |
| KR101868506B1 (en) | MLAT Receiving Unit Using Local Clock and Driving Method of the Same | |
| Becker et al. | Enabling air-to-air wideband channel measurements between small unmanned aerial vehicles with optical fibers | |
| KR100903114B1 (en) | Real-time orbit determination systems and method | |
| CN110109155B (en) | Bidirectional time correction method without application software interruption on satellite |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |