CN207440293U - Satellite navigation orbit determination receiver - Google Patents
Satellite navigation orbit determination receiver Download PDFInfo
- Publication number
- CN207440293U CN207440293U CN201721523426.0U CN201721523426U CN207440293U CN 207440293 U CN207440293 U CN 207440293U CN 201721523426 U CN201721523426 U CN 201721523426U CN 207440293 U CN207440293 U CN 207440293U
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- China
- Prior art keywords
- navigation module
- receiver
- orbit determination
- main body
- navigation
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Abstract
The utility model provides a kind of satellite navigation orbit determination receiver, including receiver main body B, the receiver main body B includes the first navigation module and the second navigation module, first navigation module and the second navigation module structure are identical, first navigation module includes radiofrequency signal processing unit, digital signal processing unit and external interface unit, GPS orbit determination reception antenna is connected by preamplifier with the input terminal of first navigation module and the second navigation module, constant-temperature crystal oscillator is connected respectively with first navigation module and the second navigation module, the output terminal of first navigation module and the second navigation module passes through external interface unit and gyro, house keeping computer transmits data.This orbit determination receiver achievees the purpose that simplify design using standardization, modularized design；Working method by two-shipper cold standby and the framework using multiple antennas realize and continuous, accurately positioning are kept in the case where satellite rotates.
Description
Technical field
The utility model is related to space industry more particularly to a kind of satellite navigation orbit determination receivers.
Background technology
The support for being required for space and temporal information with load application in orbit of spacecraft, satellite navigation connect
Receipts machine provides high accuracy three-dimensional position and speed and temporal information for spacecraft, while can provide hardware time service synchronization
Pulse.In the prior art, time of system, position, speed are provided by obtaining GPS/BD navigation signals using orbit determination receiver
The orbit determination information such as degree, the navigation informations such as accurate position, posture are provided for experimental satellite.It is but existing to use orbit determination receiver not
The characteristics of AEROSPACE APPLICATION can be directed to well and the experience for combining previous practical flight project, it is impossible to meet AEROSPACE APPLICATION
High reliability demand.
The content of the invention
The utility model will solve more than technical problem, provide it is a kind of can keep continuous to satellite, accurate positionin is determined
Rail receiver.
In order to solve the above technical problems, the technical solution adopted in the utility model is：
A kind of orbit determination receiver, including receiver main body B, the receiver main body B includes the first navigation module and second
Navigation module, first navigation module and the second navigation module structure are identical, and first navigation module includes radiofrequency signal
Processing unit, digital signal processing unit and external interface unit, GPS orbit determination reception antenna pass through preamplifier and described the
The input terminal of one navigation module and the second navigation module is connected, and constant-temperature crystal oscillator navigates respectively with first navigation module and second
Module is connected, and the output terminal of first navigation module and the second navigation module passes through external interface unit and gyro, Star Service meter
Calculation machine transmits data.
Further, two-shipper cold standby working method also can be used in this orbit determination receiver, including receiver main body B and reception
Machine main body A, receiver main body A and receiver main body B external interfaces are completely the same, the receiver main body A and receiver main body B
Switching on and shutting down controlled by house keeping computer by power module；Under normal circumstances, receiver main body A is constantly in start
State, and house keeping computer is sent to while data, real time positioning data, synchronous pulse per second (PPS) quasi-periodic will be observed, receive owner
Body B is initially off-mode, work of starting shooting in the case where receiver main body A breaks down as backup；The reception owner
Body A and receiver main body B switches antenna by switching selection control.
Further, the external interface unit includes radio frequency interface, power supply interface, RS422 interfaces, CAN interface
With PPS interfaces, radio frequency interface is connected with GPS orbit determination reception antennas, and first navigation module and the second navigation module lead to respectively
CAN interface and house keeping computer bi-directional transfer of data are crossed, the gyro passes through RS422 interface transmission datas to the first navigation
Module and the second navigation module, first navigation module and the second navigation module are passed synchronization pulse by PPS interfaces
House keeping computer is sent to, power satellite module is the first navigation module, the second navigation module and constant-temperature crystal oscillator by power supply interface
Power supply.
Further, the radiofrequency signal processing unit includes low-noise amplifier and TCXO analog signal processing circuits.
Radiofrequency signal processing unit carries out the navigation signal of GPS L1 frequency ranges and BD2 B1 frequency ranges down coversion, digital quantization processing, is
Digital signal processing unit provides digitized intermediate frequency GPS/BD2 navigation signals.
Further, the TCXO analog signal processing circuits include power splitter, GNSS receiver and tuner, institute
It states Z antennas with the input terminal of low-noise amplifier to be connected, the input of the output terminal and power splitter of the low-noise amplifier
End is connected, and the input terminal of the output terminal of the power splitter respectively with GNSS receiver and tuner is connected, constant-temperature crystal oscillator with
GNSS receiver is connected with the input terminal of tuner, and the GNSS receiver and tuner export intermediate frequency data at digital signal
Manage unit.
Further, the digital signal processing unit handles for navigation signal and carries out positioning calculation, is positioned
As a result, its main control chip is Zynq7000 chips, the main control chip is electrically connected respectively with CAN bus, FLASH and SDRAM, institute
Main control chip is stated by radio-frequency front-end interface data, the main control chip transmits synchronization pulse using RS422 level.
Further, the data that the main control chip receives include sampled clock signal and intermediate frequency digital sampled data.
Further, this orbit determination receiver uses double antenna, and+Z antennas pass through preamplifier and the first navigation module phase
Even ,-Z antennas are connected by preamplifier with the second navigation module, and first navigation module and the second navigation module use
Identical external clock input circuit.
Further, this orbit determination receiver is supported using single pcb board structure in structure by the reinforcing of screw and aluminum
Frame connects, and in the support frame both ends installation locking mechanism, top installation press strip, total is connect by radio-frequency cable, plate grade
Plug-in unit is attached with satellite Integrated Electronic System.
Further, shielding case is increased in the periphery of this orbit determination receiver, increase pylon on shielding case leads with first/second
It is physically contacted to radiate by heat-conducting silicone grease between the core devices of model plane block, the pcb board is designed using whole plate paving copper,
Enhance the heat-conductive characteristic of circuit board, and pass through mechanical interface and pass on shell and shielding case.
Compared with the prior art, orbit determination receiver described in the utility model has the advantage that：
（1）This orbit determination receiver is using standardization, modularized design, and on the premise of assurance function, use is as few as possible
Component and circuit reach expected function, achieve the purpose that simplify design.
（2）For the work characteristics of satellite, using the framework of multiple antennas when this orbit determination receiver designs, realize in satellite
Continuous, accurately positioning is kept in the case of rotation.
（3）This orbit determination receiver uses the working method of two-shipper cold standby, by observation data, real time positioning data, synchronization
It is sent to house keeping computer pulse per second (PPS) quasi-periodic, realizes the consecutive tracking to satellite.
Description of the drawings
Fig. 1 is the schematic diagram of receiver B；
Fig. 2 is orbit determination receiver system schematic diagram；
Fig. 3 is the circuit diagram of radiofrequency signal processing unit；
Fig. 4 is the schematic diagram of digital signal processing unit；
Fig. 5 is external clock input circuit figure；
Fig. 6 is first/second navigation module internal clocking switching circuit figure.
Specific embodiment
It elaborates below in conjunction with the accompanying drawings to specific embodiment of the utility model.
As shown in Figure 1, a kind of orbit determination receiver, including receiver main body B, the receiver main body B includes the first navigation
Module and the second navigation module, the first navigation module and the second navigation module structure are identical, this orbit determination receiver is containing there are two lead
Model plane block, each navigation module are an individual satellite navigation and location systems, and to ensure the uniformity of measurement data, two are led
Model plane block has been carried out with clock processing.First navigation module includes radiofrequency signal processing unit, digital signal processing unit and outside
Interface unit, the input terminal phase that GPS orbit determination reception antenna passes through preamplifier and the first navigation module and the second navigation module
Even, constant-temperature crystal oscillator is connected respectively with first navigation module and the second navigation module, the first navigation module and the second navigation mould
The output terminal of block transmits data by external interface unit and gyro, house keeping computer.
As shown in Fig. 2, two-shipper cold standby working method also can be used in this orbit determination receiver, including receiver main body B and connect
Receipts machine main body A.The first radiofrequency signal processing unit and the second radiofrequency signal processing unit in receiver main body A is with receiving owner
Radiofrequency signal processing unit in body B is identical.Receiver main body A and receiver main body B external interfaces are completely the same, the reception
The switching on and shutting down of machine main body A and receiver main body B are controlled by house keeping computer by power module；Under normal circumstances, connect
Receipts machine main body A is constantly in open state, and sends with observing data, real time positioning data, synchronous pulse per second (PPS) quasi-periodic
To house keeping computer, receiver main body B is initially off-mode, in the case where receiver main body A breaks down as backup
Start work；The receiver main body A and receiver main body B switch antenna by switching selection control.
As shown in figure 3, radiofrequency signal processing unit includes low-noise amplifier and TCXO analog signal processing circuits, TCXO
Analog signal processing circuit includes power splitter, GNSS receiver and tuner, the input of Z antennas and low-noise amplifier
End is connected, and the output terminal of low-noise amplifier is connected with the input terminal of power splitter, the output terminal of power splitter respectively with
GNSS receiver is connected with the input terminal of tuner, frequency reference source of the constant-temperature crystal oscillator as orbit determination receiver, is received with GNSS
Device is connected with the input terminal of tuner, and GNSS receiver and tuner export intermediate frequency data to digital signal processing unit.Radio frequency
Signal processing unit carries out the navigation signal of GPS L1 frequency ranges and BD2 B1 frequency ranges down coversion, digital quantization processing, for number
Signal processing unit provides digitized intermediate frequency GPS/BD2 navigation signals.There are two radiofrequency signal processing is single for this orbit determination receiver
Member possesses to day two groups of reception antenna input processing functions over the ground, to ensure that satellite consecutive tracking and can carry under rotation status
It is influenced for observing data, while ionospheric error can be eliminated by L1, B1 dual-frequency point processing function.
As shown in figure 4, the main control chip of the digital signal processing unit is Zynq7000 chips, the main control chip point
Be not electrically connected with CAN bus, FLASH and SDRAM, the main control chip by radio-frequency front-end interface sampled clock signal and
Intermediate frequency digital sampled data, the main control chip transmit synchronization pulse using RS422 level.Digital signal processing unit leads to
Cross acquisition radiofrequency signal processing unit output digital intermediate frequency data flow complete to the capture and tracking of GPS/BD2 navigation signals,
And the signal to receiving, which is handled and calculated, obtains dependent observation data progress positioning calculation, is completed by CAN bus
The transmission operation of data.
External interface unit includes radio frequency interface, power supply interface, RS422 interfaces, CAN interface and PPS interfaces, radio frequency
Interface is connected with GPS orbit determination reception antennas, for drawing integrated electronics cabinet.First navigation module and the second navigation module difference
By CAN interface and house keeping computer bi-directional transfer of data, CAN interface rate is 500Kbps, and number is observed in transmission
According to, location data, indirect instruction and injection data.Gyro passes through RS422 interface transmission datas to the first navigation module and second
Navigation module, and merge with GPS data and reach ground under packing.First navigation module and the second navigation module pass through PPS interfaces
Synchronization pulse is transmitted to house keeping computer, power satellite module by power supply interface is the first navigation module, second leads
Model plane block and constant-temperature crystal oscillator power supply.
Spacecraft in orbit when, have an attitudes vibration, in the case of single antenna, have the situation of delocalization.For
Attitudes vibration is tackled, this orbit determination receiver uses double antenna, and+Z antennas are connected by preamplifier with the first navigation module ,-Z
Antenna is connected by preamplifier with the second navigation module, this orbit determination receiver scheme is with section of state day into ripe navigation module
Based on be designed, individual module can only handle the B1C of 12 passage L1C and 12 passages.Therefore receiver employs double
Module designs.As shown in figure 5, to cause the measurement data of two module outputs consistent, the first navigation module and the second navigation mould
Block uses identical external clock input circuit.Fig. 6 is navigation module internal clocking switching figure, and capacitance C16 and C19 can only be welded
One.When capacitance C19 is welded, the clock source of navigation module is external clock, when capacitance C16 is welded, when being carried for navigation module
Clock.
This orbit determination receiver, using single pcb board structure, is connected in structure by screw with the reinforcing brace frame of aluminum,
The support frame both ends installation locking mechanism, top installation press strip, total pass through radio-frequency cable, plate grade connector and satellite
Integrated Electronic System is attached.Increase shielding case in the periphery of receiver, increase pylon on shielding case and navigate with first/second
It is physically contacted to radiate by heat-conducting silicone grease between the core devices of module, the pcb board is increased using whole plate paving copper design
The heat-conductive characteristic of strong circuit board, and pass through mechanical interface and pass to shell and shielding case, it is transmitted to eventually by mechanical interface comprehensive
It closes on electronic shell.
The present embodiment course of work is：Orbit determination receiver receives GPS L1/BD2 B1 satellite navigation signals by antenna, should
Signal enters radiofrequency signal processing unit by low-noise amplifier.Signal will be put inside radiofrequency signal processing unit
Greatly, digital medium-frequency signal is exported to digital signal processing unit after a series of processing such as filtering and down coversion.Digital Signal Processing
Unit will carry out signal relevant treatment to digital medium-frequency signal, while the work such as capture, tracking and positioning calculation for completing signal.
The data content of the navigation module of first navigation module/second output includes two categories below：
A, data are observed
Including L1 C/A codes pseudorange, B1 C/A codes pseudorange, L1 carrier phases, B1 carrier phases, L1 carrier-to-noise ratios, B1 carrier-to-noise ratios
Deng；Receiver start and synchronized tracking is to after aeronautical satellite, i.e., export to house keeping computer to day over the ground two aerial positions
Observation data.
B, real time positioning data and synchronous pulse per second (PPS)（1PPS）
Include time, position and speed under WGS-84 coordinate systems etc.；Receiver is started shooting and synchronized tracking is to 4 or 4
After more than nautical star, after positioning calculation generates location information, send real time positioning data to house keeping computer and can use
Pulse per second (PPS), location data is with lock-out pulse（1PPS）House keeping computer is sent to together, it can be by lock-out pulse and fixed in real time
Temporal information in the data of position obtains current time.
Finally by time, position, speed and original observed quantity（Pseudorange and carrier phase）Etc. data pass through CAN interface
It sends, and by synchronizing clock signals（1PPS）It is sent to house keeping computer.
The above content is the explanations of the preferred embodiment to the invention, those skilled in the art can be helped more to fill
Ground is divided to understand the technical solution of the invention.But these embodiments are merely illustrative, it is impossible to assert the invention
Specific embodiment be only limitted to the explanations of these embodiments.The invention person of an ordinary skill in the technical field is come
It says, without departing from the concept of the premise of the invention, several simple deductions and conversion can also be made, should be all considered as belonging to
The protection domain of the invention.
Claims (10)
1. a kind of satellite navigation orbit determination receiver, it is characterised in that：Including receiver main body B, the receiver main body B includes the
One navigation module and the second navigation module, first navigation module and the second navigation module structure are identical, first navigation
Module includes radiofrequency signal processing unit, digital signal processing unit and external interface unit, and GPS orbit determination reception antennas pass through preceding
The input terminal that amplifier is put with first navigation module and the second navigation module is connected, and constant-temperature crystal oscillator is led respectively with described first
Model plane block and the second navigation module are connected, and the output terminal of first navigation module and the second navigation module passes through external interface list
Member and gyro, house keeping computer transmission data.
2. orbit determination receiver according to claim 1, it is characterised in that：The orbit determination receiver uses two-shipper cold standby work
Make mode, including receiver main body B and receiver main body A, receiver main body A is consistent with receiver main body B external interfaces, described
The switching on and shutting down of receiver main body A and receiver main body B are controlled by house keeping computer by power module；Normal condition
Under, receiver main body A is constantly in open state, and receiver main body B is initially off-mode, is receiving owner as backup
Body A starts shooting work in the case of breaking down；The receiver main body A and receiver main body B are cut by switching selection control
Change antenna.
3. orbit determination receiver according to claim 1, it is characterised in that：The external interface unit include radio frequency interface,
Power supply interface, RS422 interfaces, CAN interface and PPS interfaces, radio frequency interface are connected with GPS orbit determination reception antennas, and described
One navigation module and the second navigation module pass through CAN interface and house keeping computer bi-directional transfer of data, the gyro respectively
By RS422 interface transmission datas to the first navigation module and the second navigation module, first navigation module and the second navigation
Synchronization pulse is transmitted to house keeping computer by module by PPS interfaces, and power satellite module is first by power supply interface
Navigation module, the second navigation module and constant-temperature crystal oscillator power supply.
4. orbit determination receiver as claimed in any of claims 1 to 3, it is characterised in that：The radiofrequency signal processing
Unit includes low-noise amplifier and TCXO analog signal processing circuits.
5. orbit determination receiver according to claim 4, it is characterised in that：The TCXO analog signal processing circuits include work(
Rate separator, GNSS receiver and tuner, Z antennas are connected with the input terminal of low-noise amplifier, the low-noise amplifier
Output terminal be connected with the input terminal of power splitter, the output terminal of the power splitter respectively with GNSS receiver and tuning
The input terminal of device is connected, and constant-temperature crystal oscillator is connected with the input terminal of GNSS receiver and tuner, the GNSS receiver and tuning
Device exports intermediate frequency data to digital signal processing unit.
6. orbit determination receiver according to claim 4, it is characterised in that：The main control chip of the digital signal processing unit
For Zynq7000 chips, the main control chip is electrically connected respectively with CAN bus, FLASH and SDRAM, and the main control chip passes through
Radio-frequency front-end interface data, the main control chip transmit synchronization pulse using RS422 level.
7. orbit determination receiver according to claim 6, it is characterised in that：The data that the main control chip receives include sampling
Clock signal and intermediate frequency digital sampled data.
8. orbit determination receiver according to claim 1 or 2, it is characterised in that：The orbit determination receiver uses double antenna ,+Z
Antenna is connected by preamplifier with the first navigation module, and-Z antennas are connected by preamplifier with the second navigation module,
First navigation module and the second navigation module use identical external clock input circuit.
9. orbit determination receiver according to claim 1 or 2, it is characterised in that：The orbit determination receiver uses in structure
Single pcb board structure is connected by screw with the reinforcing brace frame of aluminum, on the support frame both ends installation locking mechanism, top
Press strip is installed, total is attached by radio-frequency cable, plate grade connector and satellite Integrated Electronic System.
10. orbit determination receiver according to claim 9, it is characterised in that：The periphery of the orbit determination receiver increases shielding
It covers, increases on shielding case and be physically contacted between pylon and the core devices of first/second navigation module by heat-conducting silicone grease
Radiate, the pcb board enhances the heat-conductive characteristic of circuit board using whole plate paving copper design, and pass through mechanical interface pass to it is outer
On shell and shielding case.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2017211099861 | 2017-08-31 | ||
| CN201721109986 | 2017-08-31 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207440293U true CN207440293U (en) | 2018-06-01 |
Family
ID=62289421
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721523426.0U Expired - Fee Related CN207440293U (en) | 2017-08-31 | 2017-11-15 | Satellite navigation orbit determination receiver |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207440293U (en) |
-
2017
- 2017-11-15 CN CN201721523426.0U patent/CN207440293U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180601 Termination date: 20181115 |