CN102360088A - Air data computer and realization method thereof - Google Patents
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Abstract
The invention discloses an air data computer, which comprises an air pressure sensor assembly and a data signal processor assembly, wherein the air pressure sensor assembly comprises a full pressure sensor, a static pressure sensor and a first microprocessor, the digital signal processing assembly comprises a second microprocessor, and the second microprocessor receives the static pressure data and movable pressure data output by the air pressure sensor assembly and the actual measurement temperature data output by a temperature sensor at time intervals through gating signals for calculating air data. The air data computer has the advantages that the size is small, the weight is light, the power consumption is low, the data processing speed is high, and the low air pressure altitude data hop amplitude is small.
Description
Technical field
The invention belongs to the aviation electronics field, relate to a kind of air data computer system and its implementation in particular.
Background technology
Air data computer is used for the control and the navigation of aircraft flight; Can Total Air Temperature data, Static Air Temperature data, atmosphere static pressure data, atmosphere total head data, barometer altitude data, true air speed data, indicator air speed data, Mach number, airflow direction, rising or falling speed and relative height data be provided to aircraft, these data are referred to as atmosphere data.
Wherein, Total Air Temperature is meant that atmosphere in the aircraft flight is compressed the atmospheric temperature at rear stagnation point place; Undisturbed atmospheric temperature around Static Air Temperature is meant in the aircraft flight; The atmosphere static pressure is that desirable incompressible gas acts on the power on the unit area; The atmosphere dynamic pressure is that desirable incompressible gas acts on the power on the unit area when arriving the stationary point; The atmosphere total head is static pressure and dynamic pressure sum; Barometer altitude is meant the height of aircraft apart from the standard pressure plane, and wherein, the standard pressure plane accurate state of index is that 760mmHg, temperature are that 288.15K, density are the mean sea level of 1.225kg/m3; True air speed is meant the speed of the relative windstream of aircraft; Indicator air speed is meant the value of true air speed naturalization to the sea level, does not promptly consider the variation of atmospheric density with height, all regards static pressure and temperature as constant, equals the static pressure and the temperature of sea level normal atmosphere respectively, through measuring the air speed that dynamic pressure obtains; Mach number is aircraft true air speed and the ratio that belongs to velocity of sound highly; Rising or falling speed is meant the pace of change of barometer altitude p.s.; Relative height is meant aircraft with respect to the barometer altitude on the airport before taking off.
At present, the air data computer of domestic use is mainly produced by 161 factories of group of Air China and 221 factories, and its technology is in confidential state always, and relevant information is unknown.
According to the introduction of National Defense Industry Press in " air data computer system " (Xiao Jiande volume) of publication in 1992, the external air data computer that uses at present is divided into simulation air data computer and digital air data computer.Wherein, the simulation air data computer mainly adopts the mode of mechanical type and mimic channel to realize the measurement to atmosphere data; The Z8002 microprocessor that the numeral air data computer mainly adopts 16 of a slices is realized the measurement to atmosphere data as core component with the mode of digital processing.
Find that according to field trial the air data computer volume and weight of domestic present use is bigger, the amplitude of low latitude barometer altitude data saltus step is bigger, and the time of data processing is longer.
Summary of the invention
The air data computer volume and weight that the objective of the invention is to overcome domestic present use is big, the amplitude of low latitude barometer altitude data saltus step is big, the long shortcoming of time of data processing, and a kind of air data computer and its implementation that modern integrated level is high, the digital circuit collection of fast operation constitutes of utilizing is provided.
The present invention solves the problems of the technologies described above the technical scheme that is adopted: air data computer comprises baroceptor assembly and these two basic functions modules of digital signal processing assembly; Wherein, The baroceptor assembly comprises total head sensor, static pressure transducer and first microprocessor, and first microprocessor can carry out temperature compensation to sampled data; The digital signal processing assembly comprises second microprocessor, and this second microprocessor is through gating signal, and timesharing receives the static pressure data and the dynamic pressure data of baroceptor assembly output, and the observed temperature data of temperature sensor output.
Airflow-direction sensor can be used as user's apolegamy part, can also increase the GPS receiver module on this basis, and this GPS receiver module comprises GPS receiver antenna, high-frequency feed line cable and GPS receiver card.
Ram-air pipe, static tube, temperature sensor and airflow-direction sensor are installed in outside at aircraft; Wherein, Ram-air pipe respectively is connected total head connector and static pressure connector air data computer shell in interior of aircraft through flexible pipe or hard tube with static tube; Guarantee that outside air pressure is transmitted to total head sensor and static pressure transducer, temperature sensor is connected digital signal processing component through lead or cable respectively with airflow-direction sensor.Wherein, ram-air pipe is the metal tube of opening towards the aircraft flight direction, static tube be opening towards the aircraft side or the back metal tube, flexible pipe can adopt proofed sleeve, hard tube can adopt the plastic-aluminum pipe.
The static pressure data of second microprocessor timesharing reception baroceptor assembly output and dynamic pressure data, the observed temperature data of temperature sensor output, the airflow direction data of airflow-direction sensor output; And the airport barometric information of aircraft navigation computing machine output; Utilize mathematical formulae that these data are calculated and handled; Can obtain Total Air Temperature, Static Air Temperature, atmosphere static pressure, atmosphere total head, barometer altitude, true air speed, indicator air speed, rising or falling speed, relative height and airflow direction angle; Again the data-switching that obtains is become the data of RS422 form, send to industrial computer or other needs the cross-linking apparatus of these data through one road RS422 serial line interface.
The present invention compared with prior art has following advantage:
The present invention adopts the digital circuit of modern integrated level height, fast operation; Replace a large amount of simulation discrete devices; The baroceptor part and the processor circuit of air data computer are partly made two basic functions modules, and each functional module is handled with a slice microprocessor, has both improved the real-time of signal Processing; Reduced the amplitude of low latitude barometer altitude data saltus step, reduced again system volume, weight and power consumption, increased the extendability of system.
The present invention reached air data computer the function that will realize; Can export Total Air Temperature data, Static Air Temperature data, atmosphere static pressure data, atmosphere total head data, barometer altitude data, true air speed data, indicator air speed data, rising or falling speed, airflow direction angle-data and relative height data; Wherein the barometer altitude data error is: 0m～1000m is 8m; 1000m～15000m is 1%, and the output data refresh rate is≤50ms, and the volume of whole air data computer system is 187.4mm * 165mm * 34mm; Weight is less than 1kg, and power consumption is less than 10W.
Description of drawings
Fig. 1 is a general structure block diagram of the present invention;
Fig. 2 is an inner structure synoptic diagram of the present invention;
Fig. 3 is the structured flowchart of baroceptor assembly of the present invention;
Fig. 4 is the structured flowchart of digital signal processing assembly of the present invention;
Fig. 5 is a workflow block diagram of the present invention.
Embodiment
Below in conjunction with accompanying drawing and specific embodiment the present invention is made further detailed description.
With reference to Fig. 1, baroceptor assembly and digital signal processor component have constituted two basic functions modules of air data computer of the present invention, are basic configuration of the present invention.Airflow-direction sensor can be used as user's apolegamy part, can also increase the GPS receiver module on this basis, comprises GPS receiving antenna, high-frequency feed line cable and GPS receiver card.
Ram-air pipe, static tube, temperature sensor and airflow-direction sensor are installed in the outside of aircraft; Wherein, Ram-air pipe is the metal tube of opening towards the aircraft flight direction; Static tube be opening towards the aircraft side or the metal tube of back, ram-air pipe and static tube pass through flexible pipe such as proofed sleeve in interior of aircraft, perhaps hard tube such as plastic-aluminum pipe connect total head connector and the static pressure connector on the air data computer shell respectively; Guarantee that outside air pressure is transmitted to total head sensor and static pressure transducer, temperature sensor is connected digital signal processor component through lead or cable respectively with airflow-direction sensor.
Fig. 2 is an air data computer inner structure synoptic diagram of the present invention; Low frequency socket and total head connector, static pressure connector are housed on the air data computer shell; Wherein, the low frequency socket is used for externally fed and test, and can be used as and the outside port that carries out data transmission; A printed board is adorned in air data computer inside, and promptly the air data computer motherboard links to each other with the baroceptor assembly through flat cable.
With reference to Fig. 3, adopted high-precision static pressure transducer and total head sensor in the baroceptor assembly, wherein, static pressure transducer is a gauge pressure transducer, 101.325 * 10
3The data of exporting during handkerchief are near 0, along with the decline output data of air pressure becomes greatly gradually, it are linked to each other output static pressure simulating signal with the static pressure connector; The total head sensor is a differential pressure type absolute pressure sensor, and it imports an end is total head, and the other end is a static pressure; Output data is the dynamic pressure data, and when total head equated with static pressure, dynamic pressure was 0; Then output data is near 0, and along with the difference change of total head and static pressure is big, it is big that output data becomes gradually; Its first input end is connected the static pressure connector, and second input end connects the total head connector, output dynamic pressure simulating signal; The baroceptor assembly also comprises amplifier, multi-way switch and high-precision A/D converter; To static pressure simulating signal and dynamic pressure simulating signal amplify successively, after gating and the A/D conversion; Send into the processor of baroceptor assembly, this processor compares careful calibration and temperature compensation to the sampled data that receives, and the static pressure and the dynamic pressure value that make acquisition are more near true value; And be processed into 32 bit parallel digital signals, export through the parallel port.After becoming decimal number, the static pressure data-switching of baroceptor assembly output equals 101.325 * 10
3Handkerchief deducts static pressure, equals dynamic pressure after the dynamic pressure data-switching of output becomes decimal number.Data lag time≤the 10ms of this baroceptor assembly, precision is 0.25%, possesses temperature compensation and calibration function, power consumption is not more than 1.7W.
With reference to Fig. 4; The RS232 interface that will be connected with industrial computer is as the test interface or the excitation interface of processor module; When the excitation control signal is effective; Can be through the artificial input temp data in the interface of industrial computer, atmosphere static pressure, atmosphere dynamic pressure, airport air pressure and airflow direction; Industrial computer is delivered to the CPU in the processor circuit to these data through the RS232 serial ports, utilizes corresponding mathematical formulae that these data are calculated and handled, and obtains Total Air Temperature, Static Air Temperature, atmosphere static pressure, atmosphere total head, barometer altitude, true air speed, indicator air speed, rising or falling speed, relative height and airflow direction angle; Again the data-switching that obtains is become the data of RS422 form, send to the equipment that needs these data through one road RS422 serial line interface; When excitation control signal when invalid, processor module is read the static pressure data of baroceptor assembly through gating signal S, reads the dynamic pressure data of baroceptor assembly through gating signal P.BUSY is the busy signal of baroceptor assembly, when this signal is " 0 ", allows the outside to read barometric information; When this signal was " 1 ", data-switching was being carried out in expression, does not allow the outside to read barometric information.
The constant-temperature constant-current source circuit provides a stable current source to temperature sensor, and temperature sensor output signal is through after amplifying, and treated device circuit gating is through giving CPU after multi-way switch and the A/D conversion.
When the user had matched airflow-direction sensor, after the left angle of attack, the right angle of attack and the yaw angle signal of airflow-direction sensor output changed through the simulating signal regulator, treated device circuit gating was through giving CPU after multi-way switch and the A/D conversion.
After CPU timesharing in the processor circuit receives the airport barometric information that observed temperature data, airflow direction data (the left angle of attack, the right angle of attack, yaw angle) and the aircraft navigation computing machine of static pressure data and dynamic pressure data, the temperature sensor of baroceptor assembly give; According to mathematical formulae these data are calculated and handled; Obtain Total Air Temperature, Static Air Temperature, atmosphere static pressure, atmosphere total head, barometer altitude, true air speed, indicator air speed, rising or falling speed, relative height and airflow direction angle; Again the data-switching that obtains is become the data of RS422 form, send to the cross-linking apparatus that needs these data through one road RS422 serial line interface.
The parallel expansion interface of the input that is connected with CPU be used for the GPS receiver module in the GPS receiver card be connected; The sea level elevation that records because of the GPS part that communicates with the barometer altitude that air data computer records; Can be through the sea level elevation on the airport that records of comparison GPS and the barometer altitude that air data computer records; Revise the relative height of air data computer output; Further revise barometer altitude through revised relative height again, can either export high-precision barometer altitude and relative height, can possess the positioning function of GPS again thereby air data computer can be expanded to.
When carrying out data processing and calculating, used mathematical formulae has:
1) barometer altitude is calculated formula:
H
P≤11000m，
11000m＜H
P≤20000m，
20000m＜H
P＜32000m，
Wherein, H
PBe barometer altitude, unit is m; P
SBe static pressure, unit is KPa.
2) true air speed computing formula (considering compression of air property):
A) subsonic speed (Ma＜mach one) aircraft in the troposphere (H
P≤when 11000m) flying, P
T=P
s+ P
q
B) subsonic speed (Ma＜mach one) aircraft is at stratosphere (11000m＜H
P≤when 20000m) flying
Wherein, Ma is a Mach number; V is a true air speed, and unit is km/h; P
TBe total head, P
SBe static pressure, P
qBe dynamic pressure, unit is KPa; H
PBe barometer altitude, unit is m.
3) indicator air speed is calculated formula:
To subsonic speed (Ma＜mach one) aircraft
P
T＝P
s+P
q；
Wherein, Ma is a Mach number; V
iBe indicator air speed, unit is km/h; P
TBe total head, P
SBe static pressure, P
qBe dynamic pressure, unit is KPa.
4) rising or falling speed calculates formula:
Wherein, V
HnBe n rising or falling speed constantly, H
Pn, H
Pn-1Be respectively the n moment, n-1 barometer altitude constantly, t
n-t
N-1Be the n moment and n-1 mistiming constantly.
5) relative height computing formula:
H
Relatively=H
P-H
The airport,
Wherein, H
PBe barometer altitude, unit is m; H
The airportBarometer altitude for the airport.
6) Total Air Temperature computing formula:
The actual detection temperature of temperature sensor output is T
p, Total Air Temperature T then
T=T
p/ (1-η)+γ, wherein, η is very little, is compensating factor, and because of between temperature sensor and the aircraft skin heat conduction losses being arranged, the temperature and the actual temperature that cause temperature sensor to record are variant, and this compensating factor is that temperature sensor is intrinsic; γ is the correction term of probe Thermal Anti-ice.
7) Static Air Temperature computing formula:
T
s＝T
T/(1+0.2ηMa
2)，
Wherein, T
sBe Static Air Temperature; T
TBe Total Air Temperature; η is very little, is compensating factor, and because of between temperature sensor and the aircraft skin heat conduction losses being arranged, the temperature and the actual temperature that cause temperature sensor to record are variant, and this compensating factor is that temperature sensor is intrinsic; Ma is a Mach number.
8) Mach number calculates formula:
Mach number Ma is true air speed V and the ratio of velocity of sound a, Ma=V/a={5 [(P
T/ P
S)
1/3.5-1] }
1/2, wherein, P
TBe total head, P
SBe static pressure.
With reference to Fig. 5, the self check of air data computer of the present invention is divided into startup self-detection, cycle self check and is made self check.Wherein, startup self-detection is that the various piece of start back system begins to get into duty, stablizes the back each several part is checked, if certain part breaks down, just externally sends corresponding failure code; If there is not fault, just get into normal operating conditions; The cycle self check is every work a period of time each several part once to be checked, if certain part breaks down, just externally sends corresponding failure code; If there is not fault, follow operate as normal; Made that self check is when receiving outside self-test signal, system gets into the self check state, and when this signal was unsettled, system forwarded normal operating conditions to.
The workflow of air data computer is:
Start back self check is once promptly carried out startup self-detection, if there is fault just to export failure code, whether is not made self check if there is fault to judge, if just continue self check again; If not, with regard to receiving sensor data P
S, P
TWith data such as temperature T s, calculate then and handle, draw barometer altitude H
p, true air speed V, indicator air speed V
iEtc. data, and, after depositing enough n time, these data are averaged,, calculate relative height H then to reduce the amplitude of data saltus step with resulting data storage
n, with these packing data output, behind enough N time of output data bag, then return self check then, promptly carry out the cycle self check.
Wherein, failure code is decided to be approximately, and this air data computer was uploaded in the self check Frame to the navigational computer cycle on the aircraft, and D0, D1, D2 are the failure code position, and this position is 0 expression non-fault, and this position is that 1 expression has fault.Wherein, the D0 position is that Total Air Temperature is gathered fault, and the voltage signal of expression temperature sensor output exceeds bound; The D1 position is that static pressure is gathered fault, and the expression normal condition is read less than the static pressure data; The D2 position is that total head is gathered fault, and the expression normal condition is read less than the dynamic pressure data.
Claims (11)
1. an air data computer comprises baroceptor assembly and digital signal processing assembly, it is characterized in that, said baroceptor assembly comprises total head sensor, static pressure transducer and first microprocessor; Said digital signal processing assembly comprises second microprocessor, and said second microprocessor is through gating signal, and timesharing receives the static pressure data and the dynamic pressure data of baroceptor assembly output, and the observed temperature data of temperature sensor output.
2. air data computer according to claim 1; It is characterized in that; The simulating signal of said static pressure transducer and the output of total head sensor is sent into said first microprocessor, after said first microprocessor is handled after changing through amplification, gating and A/D; Obtain said static pressure data and dynamic pressure data, and through exporting from said baroceptor assembly the parallel port.
3. air data computer according to claim 1; It is characterized in that; Said digital signal processing assembly is connected with airflow-direction sensor; Receive the simulating signal of said airflow-direction sensor input, after simulating signal adjusting, gating and A/D conversion, receive through said gating signal timesharing by said second microprocessor.
4. air data computer according to claim 3 is characterized in that said air data computer also comprises the GPS receiver module, and said GPS receiver module comprises GPS receiving antenna, high-frequency feed line cable and GPS receiver card; Said GPS receiver card is connected with parallel expansion interface in the said digital signal processing assembly.
5. according to the described air data computer of one of aforementioned claim; It is characterized in that; Static pressure connector and total head connector are housed on the shell of said air data computer; Said static pressure transducer connects said static pressure connector, and the first input end of said total head sensor connects said static pressure connector, and second input end connects said total head connector; Said static pressure connector is connected static tube and ram-air pipe with the total head connector respectively through flexible pipe or hard tube, guarantees that outside air pressure is transmitted to said total head sensor and static pressure transducer; Said temperature sensor is connected said digital signal processing assembly through lead or cable respectively with pneumatic sensor.Said static tube, ram-air pipe, temperature sensor and pneumatic sensor are installed in the outside of aircraft.
6. air data computer according to claim 5 is characterized in that said flexible pipe is a proofed sleeve.
7. air data computer according to claim 5 is characterized in that, said hard tube is the plastic-aluminum pipe.
8. according to claim 3 or 4 described air data computers; It is characterized in that; Said digital signal processing assembly is through the external industrial computer of RS232 interface; Said industrial computer sends the excitation control signal to said second microprocessor, when said excitation control signal is effective, through the interface artificial input data of industrial computer; When said excitation control signal is invalid; Said digital signal processing assembly timesharing receives by the said static pressure data of said baroceptor assembly input and dynamic pressure data, the said airflow direction data imported by the said observed temperature data of said temperature sensor input, by said pneumatic sensor; And by the airport barometric information of aircraft navigation computing machine input; Said second microprocessor calculates and handles said data, and said calculating and process result are exported through the serial of RS422 interface.
9. air data computer according to claim 8; It is characterized in that; Said second microprocessor is calculated by said data and processing comprises; Utilize the said static pressure data, dynamic pressure data and the observed temperature data that repeatedly receive, calculate a plurality of barometer altitude data, true air speed data and indicator air speed data, and respectively said a plurality of barometer altitude data, true air speed data and indicator air speed data are averaged.
10. the implementation method of an air data computer is characterized in that, comprises following process:
(1) through static tube and ram-air pipe air pressure is transmitted to static pressure transducer and total head sensor; Said static pressure transducer and total head sensor are exported static pressure simulating signal and dynamic pressure simulating signal respectively; After amplification, gating and A/D conversion, send into first microprocessor, handle through first microprocessor; Obtain static pressure data and dynamic pressure data, and through parallel port output;
(2) second microprocessor timesharing receive said static pressure data and dynamic pressure data; And by the observed temperature data of temperature sensor input; By the airflow direction data of airflow-direction sensor input and the airport barometric information of importing by the aircraft navigation computing machine; Said data are calculated and handled, obtain barometer altitude H
p, true air speed V and indicator air speed V
iAnd storage;
(3) step (2) is repeated n time, then n said barometer altitude H being stored
p, true air speed V and indicator air speed V
iAverage;
(4) utilize the barometer altitude H of gained in the step (3)
pMean value computation relative height H
n
11. method according to claim 10 is characterized in that, the said barometer altitude H that obtains in the sea level elevation on the airport that records through GPS relatively and the step (3)
pAverage, revise the said relative height H that obtains in the step (4)
n, again through revised relative height H
nFurther revise barometer altitude H
p
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