CN110260928A - Aircraft telemetry system - Google Patents
Aircraft telemetry system Download PDFInfo
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- CN110260928A CN110260928A CN201910671744.9A CN201910671744A CN110260928A CN 110260928 A CN110260928 A CN 110260928A CN 201910671744 A CN201910671744 A CN 201910671744A CN 110260928 A CN110260928 A CN 110260928A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
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- G—PHYSICS
- G08—SIGNALLING
- G08C—TRANSMISSION SYSTEMS FOR MEASURED VALUES, CONTROL OR SIMILAR SIGNALS
- G08C17/00—Arrangements for transmitting signals characterised by the use of a wireless electrical link
- G08C17/02—Arrangements for transmitting signals characterised by the use of a wireless electrical link using a radio link
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Abstract
The invention discloses a kind of aircraft telemetry systems, are related to the test device technical field of aircraft.The system comprises remote sensing instrument, grounded receiving station and test cables, the remote sensing instrument is located on tested aircraft, and the data acquisition interface of the remote sensing instrument is connect with the data output interface of tested aircraft, the remote sensing instrument is by realizing wire communication between test cable and the grounded receiving station, by the test cable to the remote sensing instrument input test digital signal, simulation signal generator injects plug to the remote sensing instrument input test analog signal by the analog signal on test cable for grounded receiving station；Data transmission is realized by wireless network between the remote sensing instrument and the grounded receiving station, the data that the remote sensing instrument acquires are transferred to by the grounded receiving station by wireless network；Regulated power supply provides working power by the test cable for the remote sensing instrument.The system can complete that the data of aircraft are acquired and are analyzed in real time, substantially reduce the aircraft lead time.
Description
Technical field
The present invention relates to the test macro technical field of aircraft more particularly to a kind of aircraft telemetry systems.
Background technique
Currently, the integrated navigation mode based on satellite and inertia has become the important way of precise guidance.In addition, due to
The time of guided flight vehicle flight is short, and can not carry out contact type measurement in guided flight vehicle work, it is therefore desirable to a kind of
The data of aircraft are acquired and are handled in real time by the device that can obtain guided flight vehicle Flight Condition Data in real time.
Summary of the invention
The technical problem to be solved by the present invention is to how provide a kind of data progress that can be completed in real time to aircraft
Acquisition and analysis, substantially reduce the aircraft telemetry system of aircraft lead time.
In order to solve the above technical problems, the technical solution used in the present invention is: a kind of aircraft telemetry system, special
Sign is: including remote sensing instrument, grounded receiving station and test cable, the remote sensing instrument is located on tested aircraft, and described distant
Survey instrument data acquisition interface connect with the data output interface of tested aircraft, the remote sensing instrument pass through test cable and
Wire communication is realized between the grounded receiving station, grounded receiving station is inputted to the remote sensing instrument by the test cable and surveyed
Digital signal is tried, simulation signal generator injects plug to the remote sensing instrument input test mould by the analog signal on test cable
Quasi- signal；Data transmission is realized by wireless network between the remote sensing instrument and the grounded receiving station, it will by wireless network
The data of the remote sensing instrument acquisition are transferred to the grounded receiving station；Regulated power supply is the telemetering by the test cable
Instrument provides working power.
A further technical solution lies in: the remote sensing instrument includes signal conditioning module and microprocessor module, and environment is adopted
Collection sensor is connect with the signal input part of the signal conditioning module, for acquiring environmental information locating for the remote sensing instrument；
G sensor is connect with the signal input part of the signal conditioning module, is overloaded for judging whether；Cable connection interface with
The signal input part of the signal conditioning module connects, and cable connection interface is used for connecting test cable；The power supply of power module
Input terminates the power output end of the regulated power supply, and the power output end of the power module is through described in power conversion module
Need the power input of power supply module to connect in remote sensing instrument, for providing working power for it, data acquisition interface with it is described
The signal input part of signal condition power supply connects, for acquiring the related data of tested aircraft；The signal conditioning circuit
It is bi-directionally connected with the microprocessor module, the signal conditioning circuit is for handling the signal of input；Acquisition is compiled
Code module connect with the signal output end of the microprocessor module, the data for being exported to the microprocessor module into
Row coded treatment；Transmitter module is connect with the signal output end of the acquisition coding module, transmitting antenna and the transmitter
The signal output end of module connects, for sending wireless signal to the grounded receiving station.
A further technical solution lies in: environment acquisition sensor include shock transducer, vibrating sensor and
Temperature sensor, the shock transducer are connect with the signal input part of the signal conditioning module, for acquiring the telemetering
The impact signal of instrument；The vibrating sensor is connect with the signal input part of the signal conditioning module, described distant for acquiring
Survey the vibration signal of instrument；The temperature sensor is connect with the signal input part of the signal conditioning circuit, described for acquiring
The temperature information of remote sensing instrument.
Preferably, the related data of the tested aircraft of acquisition includes Computer signal on machine, inertia member is believed on machine
Number, steering engine actuator signal, GPS signal and power supply signal.
A further technical solution lies in: the remote sensing instrument further includes human-computer interaction module, the human-computer interaction module with
The microprocessor module is bi-directionally connected, and for input control order and shows the data of output.
A further technical solution lies in: the remote sensing instrument further includes reserved image capture interface, and described image acquisition connects
Mouth is connect with the signal input part of the signal conditioning module, for connecting with image capture module.
A further technical solution lies in: the ground monitoring station includes wireless signal receiving antenna, the wireless signal
Receiving antenna is located on antenna servo driving unit, the output end and radio frequency branch combiner of the wireless signal receiving antenna
Input terminal connection, the output end of the radio frequency branch combiner connect with the signal input part of telemetered signal receiving module；Institute
The signal input part of the signal output end and signal conditioning module of stating telemetered signal receiving module connects, the signal condition mould
Block is bi-directionally connected with Telemetering Data Processing and monitoring host computer, and the monitoring host computer, which is used to analyze the received data, to be handled；It is described
The control output end of monitoring host computer is connect with the control signal of antenna steering platform, and the control signal of the antenna steering platform is defeated
Outlet is connect with the control signal of the antenna servo driving unit；The output end of the signal conditioning module with it is multi-functional
The signal input part of telemetered signal emulator connects, and the output end of the emulator and the signal input part of GPS transmitting module connect
It connects, the signal output end of the GPS transmitting module is connect with the signal input part of GPS transmitting antenna.
A further technical solution lies in: the ground monitoring station further includes cable connection interface, and the cable connection connects
Mouth with test cable for connecting.
A further technical solution lies in: the acquisition coding module includes several signal matching devices, the signal
The input of orchestration terminates analog signal, and the output end of the signal matching device is connect with the signal input part of multichannel recon, institute
The output end for stating recon is connect with the input terminal of analogue amplifier sample-and-hold circuit, and the analogue amplifier sampling is kept
The output end of circuit is connect with the input terminal of A/D conversion module, the output end and control adder circuit of the A/D conversion module
Signal input part connection, the input terminal of the control adder circuit is also connected with digital signal, the control adder circuit
Output end and the signal input part of channel coding module connect, and the output end and pattern of the channel coding module change module
Input terminal connection, the output end of pattern variation module and the input terminal of transmitter module connect；PCM program with it is synchronous
The control output end of code generator and multichannel recon, analogue amplifier sample-and-hold circuit, A/D conversion module, control
The control signal of adder circuit connects.
A further technical solution lies in: the power module includes SFL12S12-25WG power supply chip D2 ,+12V electricity
Source is divided into four tunnels after diode D1, and the first via is grounded through capacitor C1, and the second tunnel is grounded through capacitor C2, and third road is through capacitor
C3 ground connection, the 4th tunnel is connect with 1 foot of the D2；2 feet of the D2 are grounded；The drain electrode of 3 feet and metal-oxide-semiconductor D4 of the D2 connects
It connects；The source electrode of the D4 is grounded；The grid of the D4 is divided into two-way, and the first via meets+12V power supply, the second Lu Jing electricity through resistance R1
Hinder R2 ground connection；6 feet of the D2 are hanging；5 feet of the D2 are grounded；4 feet of the D2 are divided into four tunnels, and the first via is through capacitor C5
Ground connection, the second tunnel are grounded through capacitor C4, and third road is grounded through capacitor C6, and 1 foot of the 4th tunnel and BNX022-01 cake core D3 connect
It connects；3 feet of the D3 are grounded；4 feet of the D3 are grounded；2 feet of the D3 are divided into three tunnels, and the first via is grounded through capacitor C7, the
Two tunnels are grounded through capacitor C8；Third road is the power output end of the D3；One end of pwon signal input part and resistance R5 connect
It connects, the other end of resistance R5 is connect with 1 foot of AQW212EHA opto-coupler chip D7, and 2 feet of GNDISO signal and the D7 connect
It connects；PW1 signal input part is connect through resistance R7 with 3 feet of the D7,4 feet, 5 feet and the 7 feet ground connection of the D7；The D7
6 feet connect through resistance R6 with 4 feet of TPCA8120 type triode chip D6,1 foot, 2 feet and 3 feet of the D6 and+12V
Power supply connection, 4 feet of the D6 are divided into two-way after resistance R4, and the first via is connect with+12V power supply, and the second tunnel is through capacitor C9
Ground connection；The 5-8 foot of the D6 is connect with 1 foot of LMZ14203HTZ type direct current conversion chip D8, and 2 feet of the D8 are through resistance R8
Connect the 5-8 foot of the D6；3 feet of the D8 are hanging；4 feet of the D8 are grounded；The 5 foot meridian capacitor C12 of the D8 are grounded；Institute
6 feet for stating D8 are divided into three tunnels, and the first via is grounded through resistance R10, and the second tunnel is connect through capacitor C11 with one end of capacitor C13, the
Three tunnels are connect through resistance R9 with one end of capacitor C13, and the other end ground connection of the capacitor C13, capacitor C14 and capacitor C13 are simultaneously
Connection；The node of the 7 foot connecting resistance R9 and capacitor C11 of the D8；8 feet of the D8 are grounded.
The beneficial effects of adopting the technical scheme are that being acquired in herein described system by remote sensing instrument
And the information such as flight control system voltage analog and digital quantity are measured, and pass through telemetering transmitting module and telemetering antenna
Telemetry is sent to grounded receiving station in real time；Grounded receiving station is deposited in real time after decoding the telemetered signal received, thing
Decoding, the reduction of telemetered signal are completed by ground software kit afterwards；Meanwhile telemetry system ground software kit is also able to achieve
Various functions test to remote sensing instrument；Test cable is used for the connection of remote sensing instrument and grounded receiving station, is realized by Mz connector
Input of each road analog quantity to the remote sensing instrument；It is connect by Sz connector with grounded receiving station, realizes digital quantity to described distant
The input of instrument is surveyed, to realize the simulation test to remote sensing instrument analog quantity, digital quantity.It can be completed in real time by the system
Data acquisition to tested aircraft, and the data of acquisition are transferred to grounded receiving station and are handled, convenient test, contracting
The short aircraft lead time.
Detailed description of the invention
The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.
Fig. 1 is the functional block diagram of system described in the embodiment of the present invention；
Fig. 2 is the functional block diagram of flight control system in the embodiment of the present invention；
Fig. 3 is the work flow diagram of system described in the embodiment of the present invention；
Fig. 4 is the functional block diagram of remote sensing instrument in system described in the embodiment of the present invention；
Fig. 5 is the RS-422 transceiver module schematic diagram with isolation in system described in the embodiment of the present invention；
Fig. 6 is remote sensing instrument and control system interface circuit functional block diagram in system described in the embodiment of the present invention；
Fig. 7 is the basic theory of constitution block diagram of phase-locked loop in the embodiment of the present invention；
Fig. 8 is the functional block diagram of phase-locked loop phase model pair in the embodiment of the present invention；
Fig. 9 is the functional block diagram that coding module is acquired in the embodiment of the present invention；
Figure 10 is the functional block diagram of grounded receiving station in system described in the embodiment of the present invention；
Figure 11 is the schematic diagram of power circuit in the embodiment of the present invention；
Figure 12 is the schematic diagram of interface circuit in the embodiment of the present invention；
Figure 13 is the schematic diagram of interface circuit in the embodiment of the present invention；
Figure 14 is the schematic diagram of FPGA in the embodiment of the present invention；
Wherein: 1, test cable.
Specific embodiment
With reference to the attached drawing in the embodiment of the present invention, technical solution in the embodiment of the present invention carries out clear, complete
Ground description, it is clear that described embodiment is only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts it is all its
His embodiment, shall fall within the protection scope of the present invention.
In the following description, numerous specific details are set forth in order to facilitate a full understanding of the present invention, but the present invention may be used also
To be implemented using other than the one described here other way, those skilled in the art can be without prejudice in the present invention
Similar popularization is done in the case where culvert, therefore the present invention is not limited by the specific embodiments disclosed below.
As shown in Figure 1, the embodiment of the invention discloses a kind of aircraft telemetry system, including remote sensing instrument, grounded receiving station
With test cable 1, the remote sensing instrument is located on tested aircraft, and the data acquisition interface of the remote sensing instrument and tested
The data output interface of aircraft connects, and the remote sensing instrument is wired by realizing between test cable 1 and the grounded receiving station
Communication, by the test cable 1 to the remote sensing instrument input test digital signal, simulation signal generator passes through for grounded receiving station
Analog signal on test cable 1 injects plug to the remote sensing instrument input test analog signal；The remote sensing instrument is with described
Data transmission is realized by wireless network between the receiving station of face, is transmitted by the data that wireless network acquires the remote sensing instrument
To the grounded receiving station；Regulated power supply provides working power by the test cable for the remote sensing instrument.
The main target of the telemetry system system is, by each state parameter real-time collecting of tested flight control system,
Working status parameter of the aircraft in flight course is analyzed, to improve Flight Vehicle Design and improving the performance of aerocraft system
Foundation is provided, the aircraft lead time is shortened.Machine system receives all kinds of parameter numbers that control system is sent on telemetering aircraft
According to, and data are sent to telemetering ground receiving equipment by telemetering transmiter, parsing reconciliation is aobvious after telemetry ground station receives data
Telemetry.Telemetry system interface is relatively simple, other than machine system is associated with control system on aircraft, with other systems
Onrelevant.Machine and control system interface relationship are as shown in Figure 2 on telemetering aircraft.
Workflow:
Remote sensing instrument is realized by external voltage pulse signal and is switched on, and feeds back booting result information by serial ports after being switched on successfully,
Subsequently into working condition, by the analog signal received, digital signal, environmental parameter it is converted after export through telemetering antenna；
After remote sensing instrument booting, grounded receiving station and remote sensing instrument complete frame synchronization；Grounded receiving station completion is operated to the solution of telemetry
Code, data storage；After the completion of remote sensing instrument work, selection stops deposit；By grounded receiving station software kit to deposit data into
Parsing/reduction after behaviour.Instruction shutdown is received by serial ports 1, remote sensing instrument completes shutdown.Telemetry system groundwork process
Figure is as shown in Figure 3.
As shown in figure 4, the remote sensing instrument includes signal conditioning module and microprocessor module, environment acquire sensor with
The signal input part of the signal conditioning module connects, for acquiring environmental information locating for the remote sensing instrument；G sensor
It connect with the signal input part of the signal conditioning module, is overloaded for judging whether；Cable connection interface and the signal tune
The signal input part connection of module is managed, cable connection interface is used for connecting test cable；The power input of power module terminates institute
The power output end of regulated power supply is stated, the power output end of the power module in remote sensing instrument described in power conversion module through needing
The power input of power supply module is wanted to connect, for providing working power, data acquisition interface and signal condition electricity for it
The signal input part in source connects, for acquiring the related data of tested aircraft；The signal conditioning circuit and micro- place
Reason device module is bi-directionally connected, and the signal conditioning circuit is for handling the signal of input；Acquire coding module and institute
The signal output end connection of microprocessor module is stated, the data for exporting to the microprocessor module carry out coded treatment；
Transmitter module is connect with the signal output end of the acquisition coding module, the signal of transmitting antenna and the transmitter module
Output end connection, for sending wireless signal to the grounded receiving station.
Further, as shown in figure 4, environment acquisition sensor includes shock transducer, vibrating sensor and temperature
Sensor is spent, the shock transducer is connect with the signal input part of the signal conditioning module, for acquiring the remote sensing instrument
Impact signal；The vibrating sensor is connect with the signal input part of the signal conditioning module, for acquiring the telemetering
The vibration signal of instrument；The temperature sensor is connect with the signal input part of the signal conditioning circuit, described distant for acquiring
Survey the temperature information of instrument.
Further, as shown in figure 4, the related data of the tested aircraft of acquisition includes Computer signal on machine, machine
Upper inertia member signal, steering engine actuator signal, GPS signal and power supply signal.Preferably, the remote sensing instrument further includes
Human-computer interaction module, the human-computer interaction module are bi-directionally connected with the microprocessor module, for input control order and are shown
Show the data of output.The remote sensing instrument further includes reserved image capture interface, described image acquisition interface and the signal condition
The signal input part of module connects, for connecting with image capture module.
Telemetry system is only interconnected with tested flight control, the telemetering analog quantity of reception control system transmission,
Telemetering digital quantity and telemetering environmental parameter.Control system passes through RS422 (as shown in Figure 5) serial ports of two-way duplex transceiver insulation
It is connect with remote sensing instrument, 1 tunnel timing I/O signal gives remote sensing instrument (3.3VTTL).It is (maximum that control system component provides 1 road 14V ± 2V
Electric current 3A) it exports to distant.Remote sensing instrument and the physical interface of control system are as shown in fig. 6, control system provides 1 tunnel output switch
Signal is measured to telemetering package, 3.3VTTL, DSP6747 export 1 road 3.3V signal by GPIO and export to telemetering.
Remote sensing instrument and the data of control system transmission include telemetering analog quantity, telemetering digital quantity and telemetering environment parameter, each ginseng
Number is as follows: telemetering analog quantity: the analog quantity of remote sensing instrument measurement is shown in Table 1, and real-time period measuring signal uses frequency 1khz, remaining
Sample frequency 100hz.
1 analog quantity telemetry parameter table of table
Telemetering digital quantity: telemetering digital quantity two are respectively Navigation Control parameter and GPS telemetry parameter, are shown in Table 2 institutes
Show.
2 digital quantity telemetry parameter table of table
Navigation Control parameter word: Navigation Control parameter word is communicated using RS422, full duplex transmission, transceiver insulation, serial ports
FIFO depth is not less than 512 bytes.
Delivery form: baud rate 460800bps.1 start bit, 8 data bit, 1 odd, 1 stop position.First
Byte is passed, then passes high byte.Sending cycle 10ms.About 330 byte of the every frame of Navigation Control parameter.
GPS parameter word: GPS parameter word is communicated using RS422, and full duplex transmission, transceiver insulation, serial ports FIFO depth is not
Less than 1024 bytes.
Delivery form: baud rate 230400bps.1 start bit, 8 data bit, 1 odd, 1 stop position, first
Byte is passed, then passes high byte.About 500 byte of the every frame of sending cycle 100ms, GPS parameter word.
Telemetering environmental parameter: telemetering environmental parameter be control cabinet shock and vibration environmental parameter, by remote sensing instrument it is external two
A shock transducer, vibrating sensor measurement measure respectively, are shown in Table 3.
The environmental parameter of 3 telemetering of table
Carry out the integrated design of measured parameter interface, acquisition and encoding function on telemetering aircraft in machine using FPGA technology,
It may make the coding module to have the characteristics that flexible in programming, integrated level are high, speed is fast, online programmable, acquire the road of encoder
Number and output bit rate can Configuration Onlines.In order to effectively transmit RS-422 communication data bag data, RS-422 serial port is utilized
Free time rationally designs PCM frame structure, before the arrival of next frame data packet, the number that former frame is buffered in single-chip microcontroller
According to the real-time forwarding transmission in insertion PCM serial data stream, realizing more data packets.
Carry out the integration of measured parameter interface, acquisition and encoding function on telemetering aircraft in machine using FPGA technology
Design may make the coding module to have the characteristics that flexible in programming, integrated level are high, speed is fast, online programmable, acquisition coding
The number and output bit rate of device can Configuration Onlines.In order to effectively transmit RS-422 communication data bag data, gone here and there using RS-422
The free time of row mouth rationally designs PCM frame structure, and before the arrival of next frame data packet, former frame is buffered in single-chip microcontroller
In data insertion PCM serial data stream in, realize more data packets real-time forwarding transmit.
Trigger mechanism uses modularized design, and complete machine is made of modules such as modulation module, Linear Power Amplifier and secondary power supplies,
It can satisfy the index request of development.In order to realize the received requirement of Star Simulator signal, the band of Ying Tigao airborne power supply, which carries, to be held
Amount, achievees the purpose that transmit at a distance to increase transmission power；The radiation efficiency of antenna, standing wave, antenna radiation pattern are done more
Kind comparative test, filters out the antenna of superperformance index, reduces the quantity of radio frequency connector to the greatest extent, shortens radio frequency (RF) cable.
Transmitter Locked-return equation
As shown in fig. 7, each component part of phase-locked loop has the transfer function of oneself.Three parts are closed according to composition
System connects, and just constitutes the phase feedback system model of phaselocked loop, as shown in Figure 8.
The phase of input signal is j in system1(t), system be by regulated value voltage controlled oscillator output signal phase
j12It (t), is an automatic control system.
The fundamental equation of loop:
By the transfer function and system phase model of each component part of phaselocked loop, following equation can be obtained:
By above formula both sides to time t differential:
Due to the output function of loop filter are as follows:
Uc(S)=F (s) Ud(s) (3)
According to convolution theorem in Laplace transformation, the product of two function Laplace transformations in complex field, be equal to they when
Convolution integral in domain.Therefore, the time domain table not formula exported are as follows:
F (t)=L- ' [F (s)] in formula.
It can obtain:
If being indicated with differential operator p, have:
Above formula gives the input instantaneous phase j of loop1(t) with phase error je(t) relationship that should meet between, it is retouched
The entire phase-adjusted dynamic process of loop, the i.e. fundamental equation of phaselocked loop are stated.Sinj thereineIt (t) is due to using
Analogue phase detection device and introduce.If using digital phase discriminator, due to phase characteristic be it is linear, expression formula just be je(t)
?.
As shown in figure 9, the acquisition coding module includes several signal matching devices, the input of the signal matching device
Analog signal is terminated, the output end of the signal matching device is connect with the signal input part of multichannel recon, the recon
Output end is connect with the input terminal of analogue amplifier sample-and-hold circuit, the output of the analogue amplifier sample-and-hold circuit
End is connect with the input terminal of A/D conversion module, and the output end of the A/D conversion module and the signal of control adder circuit input
End connection, the input terminal of the control adder circuit are also connected with digital signal, the output end and letter of the control adder circuit
The signal input part of road coding module connects, and the input terminal of output end and pattern the variation module of the channel coding module connects
It connects, the output end of the pattern variation module and the input terminal of transmitter module connect；PCM program and synchronous coding generator
Control output end and multichannel recon, analogue amplifier sample-and-hold circuit, A/D conversion module, control adder circuit
Control signal connection.
Multichannel analog signals are fed to multichannel recon by signal matching device, and the main function of model adaptation is anti-
Only or mitigates the influence of various noises, adjusts level.The effect of recon be in order to be input to the signal of telemetry system into
Row sampling, realizes multiplexing.Sampling hold circuit remains a fixed electricity during using the analogue value sampled
It is flat.It receives signal and is sent to A/D converter, become sequence of binary digits thereafter and be input to control adder circuit.In control phase
Be powered on road in, the special code character that sequence of binary digits is generated with synchronous code generator, and directly input, measured number
Signal is arranged in PCM data sequence according to certain rules.PCM programmer provides all timings of data collection system and control letter
Number.It is made of clock, timely logic, decoding logic etc..It export timing controling signal be fed to multichannel recon,
Sampling hold circuit, A/D converter, control adder circuit etc., make them work by established procedure.Synchronous code generator provides
One group of frame swynchronization code synchronous for data.Above-mentioned data are further change in by channel coding and data encryption etc., form warp
Cross the PCM telemetered signal of the strong antijamming capability of encryption.Finally, code pattern converter these PCM telemetering models are changing into it is suitable
The form of transmission is input to RF transmission system.
Grounded receiving station: grounded receiving station, which belongs to, to be repeatedly used, and technology maturation, aircraft is in launching site and technology
In order to improve detection reliability when position is detected, simple detection antenna can be equipped with and often there is letter in actual use
Number leakage phenomenon, can also directly detect, in technical area and launching site detection process, can be equipped with microcomputer telemetering earth station
(portable) is detected.Fig. 7 is grounded receiving station functional block diagram.
As shown in Figure 10, the ground monitoring station includes wireless signal receiving antenna, the wireless signal receiving antenna position
In on antenna servo driving unit, the output end of the wireless signal receiving antenna and the input terminal of radio frequency branch combiner connect
It connects, the output end of the radio frequency branch combiner is connect with the signal input part of telemetered signal receiving module；The telemetered signal
The signal output end of receiving module and the signal input part of signal conditioning module connect, the signal conditioning module and telemetering number
It is bi-directionally connected according to processing with monitoring host computer, the monitoring host computer, which is used to analyze the received data, to be handled；The monitoring host computer
Control output end is connect with the control signal of antenna steering platform, the control signal output of the antenna steering platform with it is described
The control signal of antenna servo driving unit connects；The output end of the signal conditioning module and multi-functional telemetered signal are imitative
The signal input part of true device connects, and the output end of the emulator is connect with the signal input part of GPS transmitting module, described
The signal output end of GPS transmitting module is connect with the signal input part of GPS transmitting antenna.
This programme uses program-controlled reception mode, and in practical dynamic test, antenna is according to previously given orbital curve value
Cloth station is carried out with track height, to meet Star Simulator reception.Star Simulator receives within the system requirements 150km, and receiving antenna is answered
Height is set up as far as possible, and receiving antenna is axial consistent with orbital flight direction as far as possible, and further increases the gain and spirit of receiving antenna
Sensitivity.
Telemetering transmitting antenna uses Conformal Microstrip Antennas, and antenna is mounted on the back segment of control deck store, is completely disposed in high temperature ring
In border (200 DEG C), therefore, it is anti-that telemetering airborne equipment, transmitting microstrip antenna and corresponding input and output connecting line must carry out heat
Shield design, it is ensured that the normal work of telemetering.Preferably use technological approaches below:
1) installation site of transmitting antenna is remote as far as possible away from engine nozzle position.With increase antenna and combustion gas spout away from
From；
2) micro-strip transmitting antenna left and right side and leading flank increase the reinforcement protection pressing plate of integrated molding；
3) aerial radiation level must have heat-barrier coating, to ensure that antenna is not ablated, the thickness of such microstrip antenna
(containing heat-barrier coating) should be not less than 1mm.
Aerodynamic force heating state and warhead inside and outside wall temperature rise according in design standard, when antenna bears rocket flight
Change over time curve；The design of telemetering antenna burn-out proof uses and using mature and sizing and solidifying technology；Burn-out-proof corrosion test institute
The equipment used includes: " Muffle furnace " and mating temperature control device, antenna-specific test equipment " Anritsu vector network analysis
Instrument ".
Test method: heating " Muffle furnace " makes its temperature rise to 500 DEG C, and telemetering protection antenna is placed in " Muffle furnace ",
Keep 500 DEG C of high temperature 30S, and test result；Heating " Muffle furnace " makes its temperature rise to 700 DEG C, and telemetering protection antenna is placed
In " Muffle furnace ", 700 DEG C of high temperature 12S, and test result are kept.
The data acquisition to tested aircraft can be completed in real time by the system, and the data of acquisition are transmitted
It is handled to grounded receiving station, convenient test, shortens the aircraft lead time.
It is middle in the aircraft telemetry system to be connect using FPGA technology progress measured parameter in specific Project Realization
Mouthful, the integrated design of acquisition and encoding function, may make the coding module have flexible in programming, integrated level are high, speed is fast,
The characteristics of online programmable, the number and output bit rate for acquiring encoder can Configuration Onlines.
In order to effectively transmit RS-422 communication data bag data, using the free time of RS-422 serial port, rationally design
Former frame is buffered in the insertion PCM serial data of the data in single-chip microcontroller before the arrival of next frame data packet by PCM frame structure
In stream, the real-time forwarding transmission of more data packets is realized.Its power circuit is as shown in figure 11, and interface circuit is as illustrated by figs. 12-13；
FPGA plate is as shown in figure 14.
Claims (10)
1. a kind of aircraft telemetry system, it is characterised in that: described distant including remote sensing instrument, grounded receiving station and test cable (1)
It surveys instrument to be located on tested aircraft, and the data output interface of the data acquisition interface of the remote sensing instrument and tested aircraft
Connection, by realizing wire communication between test cable (1) and the grounded receiving station, grounded receiving station passes through the remote sensing instrument
Test cable (1) the Xiang Suoshu remote sensing instrument input test digital signal, simulation signal generator pass through the simulation on test cable (1)
Signal injects plug to the remote sensing instrument input test analog signal；Pass through nothing between the remote sensing instrument and the grounded receiving station
The data that the remote sensing instrument acquires are transferred to the grounded receiving station by wireless network by the transmission of line network implementations data；Surely
Voltage source provides working power by the test cable for the remote sensing instrument.
2. aircraft telemetry system as described in claim 1, it is characterised in that: the remote sensing instrument include signal conditioning module and
Microprocessor module, environment acquisition sensor is connect with the signal input part of the signal conditioning module, described distant for acquiring
Survey environmental information locating for instrument；G sensor is connect with the signal input part of the signal conditioning module, for judging whether
Overload；Cable connection interface is connect with the signal input part of the signal conditioning module, and cable connection interface is used for connecting test
Cable；The power input of power module terminates the power output end of the regulated power supply, the power output end of the power module
The power input of power supply module is needed to connect in remote sensing instrument described in power conversion module, for providing working power for it,
Data acquisition interface is connect with the signal input part of the signal condition power supply, for acquiring the dependency number of tested aircraft
According to；The signal conditioning circuit is bi-directionally connected with the microprocessor module, and the signal conditioning circuit is used for the letter to input
It number is handled；Acquisition coding module is connect with the signal output end of the microprocessor module, for the microprocessor
The data of module output carry out coded treatment；Transmitter module is connect with the signal output end of the acquisition coding module, is emitted
Antenna is connect with the signal output end of the transmitter module, for sending wireless signal to the grounded receiving station.
3. aircraft telemetry system as claimed in claim 2, it is characterised in that: the environment acquisition sensor includes that impact passes
The signal input part of sensor, vibrating sensor and temperature sensor, the shock transducer and the signal conditioning module connects
It connects, for acquiring the impact signal of the remote sensing instrument；The signal input part of the vibrating sensor and the signal conditioning module
Connection, for acquiring the vibration signal of the remote sensing instrument；The signal of the temperature sensor and the signal conditioning circuit inputs
End connection, for acquiring the temperature information of the remote sensing instrument.
4. aircraft telemetry system as claimed in claim 2, it is characterised in that: the related data of the tested aircraft of acquisition
Including inertia member signal, steering engine actuator signal, GPS signal and power supply signal on Computer signal on machine, machine.
5. aircraft telemetry system as claimed in claim 2, it is characterised in that: the remote sensing instrument further includes human-computer interaction mould
Block, the human-computer interaction module are bi-directionally connected with the microprocessor module, for input control order and show the number of output
According to.
6. aircraft telemetry system as claimed in claim 2, it is characterised in that: the remote sensing instrument further includes reserved Image Acquisition
Interface, described image acquisition interface are connect with the signal input part of the signal conditioning module, for connecting with image capture module
It connects.
7. aircraft telemetry system as described in claim 1, it is characterised in that: the ground monitoring station includes that wireless signal connects
Antenna is received, the wireless signal receiving antenna is located on antenna servo driving unit, the output of the wireless signal receiving antenna
End is connect with the input terminal of radio frequency branch combiner, output end and the telemetered signal receiving module of the radio frequency branch combiner
Signal input part connection；The signal output end of the telemetered signal receiving module and the signal input part of signal conditioning module connect
It connects, the signal conditioning module is bi-directionally connected with Telemetering Data Processing and monitoring host computer, and the monitoring host computer is used for received
Data are handled；The control output end of the monitoring host computer is connect with the control signal of antenna steering platform, the antenna behaviour
The control signal output of control platform is connect with the control signal of the antenna servo driving unit；The signal conditioning module
Output end is connect with the signal input part of multi-functional telemetered signal emulator, the output end and GPS transmitting module of the emulator
Signal input part connection, the signal output end of the GPS transmitting module connect with the signal input part of GPS transmitting antenna.
8. aircraft telemetry system as described in claim 1, it is characterised in that: the ground monitoring station further includes cable connection
Interface, the cable connection interface with test cable for connecting.
9. aircraft telemetry system as claimed in claim 2, it is characterised in that: the acquisition coding module includes several letters
Number adaptation, the input of the signal matching device terminate analog signal, the output end and multichannel recon of the signal matching device
Signal input part connection, the output end of the recon is connect with the input terminal of analogue amplifier sample-and-hold circuit, described
The output end of analogue amplifier sample-and-hold circuit is connect with the input terminal of A/D conversion module, the output of the A/D conversion module
It holds and is connect with the signal input part of control adder circuit, the input terminal of the control adder circuit is also connected with digital signal, institute
The signal input part of the output end and channel coding module of stating control adder circuit connects, the output end of the channel coding module
It is connect with the input terminal of pattern variation module, the output end of the pattern variation module and the input terminal of transmitter module connect；
The control output end of PCM program and synchronous coding generator and multichannel recon, analogue amplifier sample-and-hold circuit, A/D turn
The control signal connection for changing the mold block, controlling adder circuit.
10. aircraft telemetry system as claimed in claim 2, it is characterised in that: the power module includes SFL12S12-
25WG power supply chip D2 ,+12V power supply is divided into four tunnels after diode D1, and the first via is grounded through capacitor C1, and the second tunnel is through capacitor
C2 ground connection, third road are grounded through capacitor C3, and the 4th tunnel is connect with 1 foot of the D2；2 feet of the D2 are grounded；3 feet of the D2
It is connect with the drain electrode of metal-oxide-semiconductor D4；The source electrode of the D4 is grounded；The grid of the D4 is divided into two-way, and the first via connects through resistance R1+
12V power supply, the second tunnel are grounded through resistance R2；6 feet of the D2 are hanging；5 feet of the D2 are grounded；4 feet of the D2 are divided into four
Road, the first via are grounded through capacitor C5, and the second tunnel is grounded through capacitor C4, and third road is grounded through capacitor C6, the 4th tunnel and BNX022-01
1 foot of cake core D3 connects；3 feet of the D3 are grounded；4 feet of the D3 are grounded；2 feet of the D3 are divided into three tunnels, the first via
It is grounded through capacitor C7, the second tunnel is grounded through capacitor C8；Third road is the power output end of the D3；Pwon signal input part and electricity
Hinder one end connection of R5, the other end of resistance R5 connect with 1 foot of AQW212EHA opto-coupler chip D7, GNDISO signal with it is described
2 feet of D7 connect；PW1 signal input part is connect through resistance R7 with 3 feet of the D7, and 4 feet, 5 feet and 7 feet of the D7 connect
Ground；6 feet of the D7 are connect through resistance R6 with 4 feet of TPCA8120 type triode chip D6,1 foot, 2 feet and 3 of the D6
Foot is connect with+12V power supply, and 4 feet of the D6 are divided into two-way after resistance R4, and the first via is connect with+12V power supply, the second road warp
Capacitor C9 ground connection；The 5-8 foot of the D6 is connect with 1 foot of LMZ14203HTZ type direct current conversion chip D8, the 2 feet warp of the D8
Resistance R8 connects the 5-8 foot of the D6；3 feet of the D8 are hanging；4 feet of the D8 are grounded；The 5 foot meridian capacitor C12 of the D8 connect
Ground；6 feet of the D8 are divided into three tunnels, and the first via is grounded through resistance R10, and the second tunnel connects through one end of capacitor C11 and capacitor C13
It connects, third road is connect through resistance R9 with one end of capacitor C13, the other end ground connection of the capacitor C13, capacitor C14 and capacitor C13
It is in parallel；The node of the 7 foot connecting resistance R9 and capacitor C11 of the D8；8 feet of the D8 are grounded.
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|---|---|---|---|
| CN201910671744.9A CN110260928A (en) | 2019-07-24 | 2019-07-24 | Aircraft telemetry system |
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|---|---|---|---|
| CN201910671744.9A CN110260928A (en) | 2019-07-24 | 2019-07-24 | Aircraft telemetry system |
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| CN111813087A (en) * | 2020-07-15 | 2020-10-23 | 汪子钦 | A test equipment for simulating the operation of a spacecraft control system and a method of using the same |
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| CN113865446A (en) * | 2021-08-18 | 2021-12-31 | 上海机电工程研究所 | Missile testing and remote measuring integrated testing system and testing method thereof |
| CN114362880A (en) * | 2021-12-08 | 2022-04-15 | 北京机电工程研究所 | A general protocol design method for reconfigurable telemetry acquisition and compilation |
| CN115659707A (en) * | 2022-12-28 | 2023-01-31 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-overload-resistant telemetry model for ballistic target telemetry test and model design method |
| CN115826468A (en) * | 2022-12-09 | 2023-03-21 | 重庆航天工业有限公司 | Comprehensive measurement equipment and method for sub-orbital flight |
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| CN111064532B (en) * | 2019-12-23 | 2022-08-12 | 北京航天益森风洞工程技术有限公司 | Transmission delay test method and system for unmanned platform remote control and remote measurement data system |
| CN111064532A (en) * | 2019-12-23 | 2020-04-24 | 北京航天益森风洞工程技术有限公司 | Transmission delay test method and system for unmanned platform remote control and remote measurement data system |
| CN111505962A (en) * | 2020-04-29 | 2020-08-07 | 河北斐然科技有限公司 | Flight control simulator of high-speed aircraft |
| CN111505962B (en) * | 2020-04-29 | 2023-11-17 | 河北斐然科技有限公司 | High-speed aircraft flight control simulator |
| CN111664740A (en) * | 2020-05-28 | 2020-09-15 | 中国人民解放军32181部队 | Passive microwave communication adapter and system |
| CN111813087A (en) * | 2020-07-15 | 2020-10-23 | 汪子钦 | A test equipment for simulating the operation of a spacecraft control system and a method of using the same |
| CN112179522A (en) * | 2020-09-14 | 2021-01-05 | 中国空气动力研究与发展中心超高速空气动力研究所 | Aircraft surface temperature sensor testing system and testing method |
| CN112965414A (en) * | 2021-02-04 | 2021-06-15 | 北京信息科技大学 | Missile-borne computer, control instruction sending method and storage medium |
| CN113865446A (en) * | 2021-08-18 | 2021-12-31 | 上海机电工程研究所 | Missile testing and remote measuring integrated testing system and testing method thereof |
| CN114362880B (en) * | 2021-12-08 | 2023-11-03 | 北京机电工程研究所 | Reconfigurable telemetry acquisition and editing general protocol design method |
| CN114362880A (en) * | 2021-12-08 | 2022-04-15 | 北京机电工程研究所 | A general protocol design method for reconfigurable telemetry acquisition and compilation |
| CN115826468A (en) * | 2022-12-09 | 2023-03-21 | 重庆航天工业有限公司 | Comprehensive measurement equipment and method for sub-orbital flight |
| CN115659707A (en) * | 2022-12-28 | 2023-01-31 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-overload-resistant telemetry model for ballistic target telemetry test and model design method |
| CN115659707B (en) * | 2022-12-28 | 2023-03-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | High overload resistant telemetry model for ballistic target telemetry test and model design method |
| CN115903633A (en) * | 2023-02-28 | 2023-04-04 | 湖南高至科技有限公司 | Multifunctional measurement and control system of aircraft |
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