CN108196090A - A kind of unmanned plane Flush Airdata Sensing System - Google Patents
A kind of unmanned plane Flush Airdata Sensing System Download PDFInfo
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- CN108196090A CN108196090A CN201711448946.4A CN201711448946A CN108196090A CN 108196090 A CN108196090 A CN 108196090A CN 201711448946 A CN201711448946 A CN 201711448946A CN 108196090 A CN108196090 A CN 108196090A
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- unmanned plane
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- differential pressure
- solenoid valve
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P13/00—Indicating or recording presence, absence, or direction, of movement
- G01P13/02—Indicating direction only, e.g. by weather vane
- G01P13/025—Indicating direction only, e.g. by weather vane indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw
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- Aviation & Aerospace Engineering (AREA)
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- General Physics & Mathematics (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
A kind of unmanned plane Flush Airdata Sensing System of the present invention, including solenoid valve, pressure measurement pipeline, absolute pressure sensor, differential pressure pick-up and digital information processing system；One end connection unmanned plane of pressure measurement pipeline, the other end are divided into A roads and B roads, and A drive test pressure pipes are directly connected to absolute pressure sensor；B drive test pressure pipes are connected to solenoid valve, and differential pressure pick-up is reconnected by solenoid valve；The signal that digital information processing system acquisition absolute pressure sensor, differential pressure pick-up transmit resolves signal and is controlled the break-make of solenoid valve.Present system measuring speed range is wide, precision is high, efficient and reliability is high.
Description
Technical field
The present invention relates to Flush Airdata Sensing System technology, more particularly to Flush Airdata Sensing System
Design method belongs to flush airdata sensing system technical field.
Background technology
Flush airdata sensing system (Flush Air Data Sensing, FADS) system, by pressure sensor battle array
Row measure the pressure distribution of aircraft surface, obtain the flights such as static pressure, Mach number, the angle of attack, yaw angle indirectly by special algorithm
Atmosphere data.FADS systems are that aircraft obtains the main path that flight atmosphere data is inputted as flight control, particularly pair
It is particularly important in Flying-wing's unmanned plane.
The design of FADS systems mainly includes three aspects, derivation algorithm, manometric module and solver.Low-speed unmanned aerial vehicle FADS
System design key technological difficulties essentially consist in algorithm and manometric module design, and low-speed unmanned aerial vehicle system flight Mach number is usually
0.03~0.8, particularly in low mach section (Ma≤0.1), Reynolds number is low, and flow field serious interference, surface pressing accurately measures
Difficulty is big.Therefore FADS system design difficulties are very big.In low mach section, since dynamic pressure is low so that unmanned plane surface pressing
Change with flight incoming flow conditions very small, it is desirable that sensor accuracy higher can just pick out the variation of pressure.And in High Mach number
Section, dynamic pressure is big and variation range is wide, then sensor is required to have higher range ability.Therefore existing FADS systems take into account height
The requirement of low mach section flight incoming parameter measurement precision.
Invention content
The technology of the present invention solves the problems, such as：Overcome the shortcomings of existing FADS systems, it is proposed that a kind of unmanned plane is embedded
Airdata sensing system, the unmanned plane during flying incoming atmospheric parameter for meeting 0.03~0.8 range of Mach number measure.
The present invention technical solution be：A kind of unmanned plane Flush Airdata Sensing System including solenoid valve, is surveyed
Pressure pipe road, absolute pressure sensor, differential pressure pick-up and digital information processing system；One end connection unmanned plane of pressure measurement pipeline, it is another
End is divided into A roads and B roads, and A drive test pressure pipes are directly connected to absolute pressure sensor；B drive test pressure pipes are connected to solenoid valve, pass through solenoid valve
Reconnect differential pressure pick-up；The signal that digital information processing system acquisition absolute pressure sensor, differential pressure pick-up transmit, to letter
Number resolved and controlled the break-make of solenoid valve.
The absolute pressure sensor encapsulation is using the box shape packing forms of " single tobacco pipe ", the differential pressure pick-up use
The box shape packing forms of " double tobacco pipes ".
The absolute pressure sensor 9, transducer range be ± 20PSI, precision 0.04%.
The differential pressure pick-up 8, transducer range be ± 1PSI, precision 0.1%.
The digital information processing system uses the digital information processing system of FPGA+DSP frameworks, is responsible for acquisition by FPGA
Sensor signal data is transferred to DSP, and FADS algorithms is recycled to be resolved in DSP, data are returned FPGA after the completion；
FPGA judges that control is turned on and off solenoid valve according to range of Mach numbers.
Using BP neural network technology and CFD technologies, the FADS derivation algorithms based on BP neural network are established；Utilize absolute pressure
The unmanned plane surface pressing data of sensor measurement, which solve, obtains flight free stream Mach number, and the range of Mach number Ma is sentenced
It is disconnected；If Mach number Ma>0.2, then differential pressure pick-up pressure measurement pipeline electromagnetic valve door is closed, DSP utilizes the nothing that absolute pressure sensor measures
Man-machine surface pressing data solve and obtain flight incoming parameter, data returned to FPGA, and export flight and carry out flow parameter measurement knot
Fruit；If Mach number Ma≤0.2, differential pressure pick-up pressure measurement pipeline electromagnetic valve door is opened, DSP utilizes the nothing that differential pressure pick-up measures
Man-machine surface pressing data solve and obtain flight incoming parameter, data returned to FPGA, and export flight and carry out flow parameter measurement knot
Fruit.
The flight incoming parameter includes Mach number, static pressure, the angle of attack and yaw angle.
Encapsulation babinet is further included, encapsulation rear box size is 38.1mm × 38.1mm × 43.18mm.
The present invention compared with prior art the advantages of：
(1) present invention by using the double group sensors of absolute pressure and differential pressure and combine FADS derivation algorithms control solenoid valve according to
Range of Mach numbers selection sensor group measures unmanned plane surface pressing value, effectively solves low mach section and High Mach number section air
DATA REASONING.System accuracy is high, simple in structure, at low cost.
(2) FADS systematic surveys range of Mach numbers 0.03~0.8 of the present invention can meet absolute portions unmanned plane during flying speed
Range is spent, and higher measurement accuracy is respectively provided in low mach section and High Mach number section.
(3) absolute pressure sensor encapsulation of the present invention uses the box shape packing forms of " single tobacco pipe ", and differential pressure pick-up is adopted
With the box shape packing forms of " double tobacco pipes ".Small after encapsulation, structural strength is big.
Description of the drawings
Fig. 1 is the scale diagrams of dummy vehicle in the embodiment of the present invention；
Fig. 2 is scheme of installation of the FADS systems in unmanned plane in the embodiment of the present invention；
Fig. 3 is the system schematic of the present invention；
Fig. 4 is the triplate line connection diagram of the present invention；
Fig. 5 is the differential pressure pick-up encapsulation schematic diagram of the present invention；
Fig. 6 is the absolute pressure sensor encapsulation schematic diagram of the present invention.
Specific embodiment
By taking the unmanned plane of certain Flying-wing as an example, referring to Fig. 1 and Fig. 2, FADS systems are mounted on aircraft interior, P1 to P9
For the pressure measurement pipeline of FADS systems, load cell goes out through pressure-measuring pipe pass mounted on unmanned plane surface, using based on DSP+
The solver acquisition of FPGA frameworks measures P1~P9 pressure measurement point pressures, and it is quiet that pressure data passes through derivation algorithm calculating acquisition in DSP
The flights incoming parameter such as pressure, Mach number, the angle of attack and yaw angle.Specific embodiment is as follows：
(1) in unmanned plane head surface trepanning, aperture 1mm connects pressure measurement pipeline, then is connected by threeway, by pipeline point
For A roads and B roads, A drive test pressure pipes are directly connected to A group absolute pressure sensors；B roads are connected to solenoid valve, and B is reconnected by solenoid valve
The differential pressure pick-up of group, as shown in Figure 3；
(2) absolute pressure sensor 9, transducer range are ± 20PSI (± 137900Pa), and precision is 0.04% (55Pa)；
Differential pressure pick-up 8, transducer range are ± 1PSI (± 6895Pa), and precision is 0.1% (7Pa)；Totally 17 sensors, are divided into
A groups-absolute pressure and B groups-differential pressure, as shown in Figure 4；
(3) digital information processing system using FPGA+DSP frameworks is acquired and resolved, is responsible for acquiring sensor by FPGA
Signal data is transferred to DSP, and FADS algorithms is recycled to be resolved in DSP, data are returned FPGA after the completion.FPGA according to
Range of Mach numbers judges that control is turned on and off pipeline electromagnetic valve；
(4) using BP neural network technology and CFD technologies, the FADS derivation algorithms based on BP neural network are established.Utilize A
The unmanned plane surface pressing data of group sensor measurement, which solve, obtains flight free stream Mach number, and the range of Mach number Ma is carried out
Judge；
(5) if Ma>0.2, then B group measuring pressure of sensor pipeline electromagnetic valves are closed, because differential pressure pick-up measures knot at this time
Fruit may no to scale, if not closing B group measuring pressure of sensor pipelines, sensor unit can be damaged, B groups is caused to sense
Device measures failure.DSP then utilizes the unmanned plane surface pressing data of A group sensor measurements, and pressure data is asked by FADS algorithms
Solution obtains the flights incoming parameters such as Mach number, static pressure, the angle of attack and yaw angle, and data are returned FPGA, is exported and flown by RS422
Incoming parameter measurements；
(6) B group measuring pressure of sensor pipeline electromagnetic valves are then opened, at this time the low A groups sensor of measuring point pressure value in Ma≤0.2
Measuring result error is larger, can not accurately resolve and obtain incoming parameter, and the differential pressure pick-up precision of B groups is high, can accurately measure
Each measuring point of fuselage and the differential pressure data on head.DSP then utilizes the unmanned plane surface pressing data of B group sensor measurements, vertex
It is still measured for absolute pressure sensor, other P2~P9 are measured for differential pressure pick-up, are using vertex P1 pressure as reference, are measured other
The pressure difference of P2~P9 obtains the absolute pressure of other each points by being added with vertex P1, and the pressure precision which obtains is high, very
Be conducive to low mach section pressure measurement.Pressure data solves by FADS algorithms and obtains Mach number, static pressure, the angle of attack and yaw angle
Flights incoming parameter is waited, data are returned into FPGA, flight incoming parameter measurements are exported by RS422；
(7) Mach number measurement range 0.03~0.8, static pressure elevation carrection 0~10km of range, the angle of attack and sideslip angular measurement model
Enclose is -15 °~15 °；
(8) systematic measurement error (3 σ) is respectively：Mach number error≤0.01, static pressure error≤100Pa, angle of attack error≤
1.5°(Ma<0.1) /≤0.5 ° (Ma >=0.1) and sideslip angle error≤1.8 ° (Ma<0.1)/≤0.5°(Ma≥0.1)；
(9) absolute pressure sensor encapsulation uses the box shape packing forms of " single tobacco pipe ", and differential pressure pick-up uses " double cigarettes
The box shape packing forms of bucket ", as shown in Fig. 4 and Fig. 5.It is 38.1mm × 38.1mm × 43.18mm to encapsulate rear box size,
The output pipe of sensor is that internal diameter is 1mm, outer diameter 2mm.
Unspecified part of the present invention belongs to common sense well known to those skilled in the art.
Claims (8)
1. a kind of unmanned plane Flush Airdata Sensing System, it is characterised in that：It is passed including solenoid valve, pressure measurement pipeline, absolute pressure
Sensor, differential pressure pick-up and digital information processing system；One end connection unmanned plane of pressure measurement pipeline, the other end are divided into A roads and B
Road, A drive test pressure pipes are directly connected to absolute pressure sensor；B drive test pressure pipes are connected to solenoid valve, and reconnecting differential pressure by solenoid valve passes
Sensor；The signal that digital information processing system acquisition absolute pressure sensor, differential pressure pick-up transmit, resolves simultaneously signal
Control the break-make of solenoid valve.
2. a kind of unmanned plane Flush Airdata Sensing System according to claim 1, it is characterised in that：The absolute pressure passes
Sensor encapsulation uses the box shape packing forms of " single tobacco pipe ", and the differential pressure pick-up is sealed using the box shape of " double tobacco pipes "
Dress form.
3. a kind of unmanned plane Flush Airdata Sensing System according to claim 1, it is characterised in that：The absolute pressure passes
Sensor 9, transducer range be ± 20PSI, precision 0.04%.
4. a kind of unmanned plane Flush Airdata Sensing System according to claim 1, it is characterised in that：The differential pressure passes
Sensor 8, transducer range be ± 1PSI, precision 0.1%.
5. a kind of unmanned plane Flush Airdata Sensing System according to claim 1, it is characterised in that：The number letter
Number processing system uses the digital information processing system of FPGA+DSP frameworks, is responsible for acquiring sensor signal data transmission by FPGA
To DSP, FADS algorithms is recycled to be resolved in DSP, data are returned into FPGA after the completion；FPGA sentences according to range of Mach numbers
Disconnected control is turned on and off solenoid valve.
6. a kind of unmanned plane Flush Airdata Sensing System according to claim 5, it is characterised in that：Using BP nerves
Network technology and CFD technologies establish the FADS derivation algorithms based on BP neural network；The unmanned plane measured using absolute pressure sensor
Surface pressing data, which solve, obtains flight free stream Mach number, and the range of Mach number Ma is judged；If Mach number Ma>0.2,
Differential pressure pick-up pressure measurement pipeline electromagnetic valve door is then closed, DSP utilizes the unmanned plane surface pressing data that absolute pressure sensor measures, asks
Solution obtains flight incoming parameter, data is returned to FPGA, and export flight incoming parameter measurements；If Mach number Ma≤0.2,
Differential pressure pick-up pressure measurement pipeline electromagnetic valve door is then opened, DSP utilizes the unmanned plane surface pressing data that differential pressure pick-up measures, asks
Solution obtains flight incoming parameter, data is returned to FPGA, and export flight incoming parameter measurements.
7. a kind of unmanned plane Flush Airdata Sensing System according to claim 6, it is characterised in that：The flight comes
It flows parameter and includes Mach number, static pressure, the angle of attack and yaw angle.
8. according to a kind of arbitrary unmanned plane Flush Airdata Sensing Systems of claim 1-5, it is characterised in that：Also wrap
Encapsulation babinet is included, encapsulation rear box size is 38.1mm × 38.1mm × 43.18mm.
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| CN201711448946.4A CN108196090A (en) | 2017-12-27 | 2017-12-27 | A kind of unmanned plane Flush Airdata Sensing System |
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| CN201711448946.4A CN108196090A (en) | 2017-12-27 | 2017-12-27 | A kind of unmanned plane Flush Airdata Sensing System |
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Cited By (3)
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| CN110987285A (en) * | 2019-11-20 | 2020-04-10 | 中国航空工业集团公司沈阳飞机设计研究所 | Full-embedded atmospheric data system for flying wing type airplane |
| CN110987287A (en) * | 2019-11-20 | 2020-04-10 | 中国航空工业集团公司沈阳飞机设计研究所 | Semi-embedded atmospheric data system for flying wing type airplane |
| CN110987284A (en) * | 2019-11-20 | 2020-04-10 | 中国航空工业集团公司沈阳飞机设计研究所 | High-reliability full-embedded atmospheric data system for flying wing type airplane |
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Application publication date: 20180622 |