CN103852101B - Aircraft airspeed system lag time measurement apparatus - Google Patents
Aircraft airspeed system lag time measurement apparatus Download PDFInfo
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- CN103852101B CN103852101B CN201410058015.3A CN201410058015A CN103852101B CN 103852101 B CN103852101 B CN 103852101B CN 201410058015 A CN201410058015 A CN 201410058015A CN 103852101 B CN103852101 B CN 103852101B
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Abstract
The present invention provides the measurement apparatus of a kind of lag time for measuring pressure transmission systems, including: data input module；It is connected to the pressure source of data input module outfan；For being connected to the first pressure transducer of the outfan of pressure source, the outfan of the first pressure transducer is for being connected to the input of pressure transmission systems, and pressure transmission systems includes pressure piping；Acquisition module time delay for the outfan of the outfan and the first pressure transducer that are connected to pressure transmission systems, the pressure-time curve table of the input of the outfan output pressure transmission system of the first pressure transducer, the pressure-time curve table of the outfan of the outfan output pressure transmission system of pressure transmission systems；Time delay, acquisition module gathered the input of pressure transmission systems and the pressure-time curve table of outfan, and compared pressure-time curve table, thus obtaining the lag time of pressure transmission systems.
Description
Technical field
The present invention relates to the measurement apparatus of the lag time of a kind of pressure transmission systems, particularly relate to the measurement apparatus of a kind of aircraft airspeed system lag time, can the hysteresis index of pressure piping in survey aircraft airspeed system, also can measure the lag time of the airspeed system comprising pressure probe, pressure piping, air data computer.
Background technology
Aircraft needs when flight to obtain height, and air speed, rising or falling speed, the data of Mach number etc., these data are obtained by air data system.Tradition air data system is made up of pitot-static pressure sensor, pitot-static pressure pipeline and air data computer.Pitot-static pressure sensor is arranged on engine body exterior, it is mainly used in accurately collecting the total head (stagnation pressure) of air-flow and static pressure, pitot hole is used for collecting the total head of air-flow, pitot hole is arranged in pitot-static pressure sensor just to airflow direction, when air flow to pitot hole, being obstructed completely, flow velocity is zero, thus obtains the total head of air-flow.Baroport is used for collecting the static pressure of air-flow, and baroport is positioned at around fuselage does not have the place of turbulent flow, and static pressure enters air data computer through static line.Air data computer is resolved by total head and the static pressure that pitot-static pressure sensor and pitot-static pressure pipeline are collected, and obtains the important parameter of aircraft such as height, air speed, rising or falling speed, Mach number etc..The defect of traditional air data system is also fairly obvious, first pitot-static pressure pipeline exists pressure retarded, if the change of aircraft current pressure is very fast, there will be flight indicator air speed or highly lag behind real aircraft air speed or height, for airline carriers of passengers, this situation major effect ground starting heats, during owing to taking off, stagnation pressure change is very fast, and takeoff speed and ground run distance are had direct impact by the sluggishness of pipeline.
So, for the Airworthiness Certification of aircraft, FAA(Federal Aviation management board) promulgate and be directed to the amendment 25-109 that the airplane airworthiness of 25 requires: airplane in transportation category air speed instruction system requirements.Amendment clearly increases the new demand that air speed is sluggish in 1323 clauses: guarantee that the impact of air speed instruction system delay does not result in obvious air speed instruction deviation (in period of taking off), or obvious error when stop distance (taking off or accelerate-).
FAAAC25-7A advises, by the regulation of 25.1323 (G) taking off or accelerate-stop distance time, owing to the delay of airspeed system causes that aircraft indicator air speed lags behind true empty-running speed more than 3 joints or owing to postponing to cause that real aircraft ground run distance increases above 100 feet to be exactly obvious.This just requires, allows for obtaining its airspeed system lag time accurately according to 25 aircrafts carrying out Airworthiness Certification.
Current civil aircraft main engine plants carry out the lag time measuring method of aircraft airspeed system: before test, near the pitot-static pressure of aircraft is popped one's head in, install test total-pressure probe additional pop one's head in, directly the measurement result of the total-pressure probe probe installed additional is drawn, it is thus possible to real-time survey aircraft currently true stagnation pressure, additionally install passenger cabin high-speed camera head additional at aircraft cockpit, shooting driving cabin air speed display, the Data Source of air speed display is popped one's head in the pitot-static pressure of aircraft.During test, make aircraft carry out sliding race test according to normal takeoff procedure, the total-pressure probe probe installed additional is carried out total pressure measurement with aircraft pitot-static pressure probe simultaneously.After test, the air speed value of the numerical value of the total-pressure probe installed additional with photographic head shooting is contrasted, obtaining airspeed system lag time, the total-pressure probe namely installed additional obtains the time of data and the time difference of the time of the data of cockpit display display pitot-static pressure probe.But the method needs aircraft carries out test repacking, for instance installing total-pressure probe probe and passenger cabin high-speed camera head additional, and to carry out sliding race on runway, experimentation cost is big, and test requirements document is high, and the required condition of test is harsh.
Summary of the invention
The technical problem to be solved in the present invention is that low cost obtains accurate aircraft airspeed system lag time.
For this, it is provided that the measurement apparatus of a kind of lag time for measuring pressure transmission systems, described measurement apparatus includes: data input module；Input is connected to the pressure source of described data input module outfan, and described pressure source forms predetermined pressure according to the data inputted in described data input module；Input is connected to the first pressure transducer of the outfan of described pressure source, and the outfan of described first pressure transducer is for being connected to the input of described pressure transmission systems, and described pressure transmission systems includes pressure piping；And input is used for being connected to acquisition module time delay of the outfan of the outfan of described pressure transmission systems and the first pressure transducer；Wherein said first pressure transducer detects the pressure-time curve table of the input of described pressure transmission systems, the pressure-time curve table of the outfan of the outfan output pressure transmission system of described pressure transmission systems；Described data input module, described pressure source, described first pressure transducer, described pressure transmission systems and described time delay acquisition module swashed and passed to formation pressure transmission systems test access；In pressure transmission systems test access, the input of the described pressure transmission systems of described acquisition module collection time delay and the pressure-time curve table of outfan, and compare the input of pressure transmission systems and the pressure-time curve table of outfan, thus obtaining the lag time of pressure transmission systems.
The measurement apparatus of the lag time according to above-mentioned pressure transmission systems, it is preferred that, described pressure transmission systems is the tested airspeed system of aircraft, and described data input module is flying quality input module.
The measurement apparatus of the lag time according to above-mentioned pressure transmission systems, preferably, described tested airspeed system includes tested aircraft pressure probe and tested air computer, described pressure piping includes tested pressure piping, the pressure-time curve table of the outfan of pressure transmission systems described in described air computer export.
The measurement apparatus of the lag time according to above-mentioned pressure transmission systems, preferably, also include for being connected to the ARINC bus acquisition module between described tested air computer and described time delay acquisition module, for the output data of described air data computer are acquired decoding.
The measurement apparatus of the lag time according to above-mentioned pressure transmission systems, it is preferred that, also include:
Input is connected to the air chamber of described pressure source outfan；Input is connected to the second pressure transducer of described air chamber outfan, the outfan of described second pressure transducer for be connected to pressure piping input and described time delay acquisition module input；Input is for being connected to the 3rd pressure transducer of outfan of described pressure piping, and the outfan of the 3rd pressure transducer is for being connected to the input of acquisition module described time delay；The volume of described air chamber is more than the internal volume of described pressure piping, and the Step Pressure can preset to pressure piping output；Described second pressure transducer detects the pressure-time curve table of the input of described pressure piping, and described 3rd pressure transducer detects the pressure-time curve table of the outfan of described pressure piping；Described data input module, described pressure source, described air chamber, described second pressure transducer, described pressure piping, described 3rd pressure transducer and described time delay acquisition module swashed and passed to formation pressure piping test access；In pressure piping test access, the input of the described pressure piping of described acquisition module collection time delay and the pressure-time curve table of outfan, and the relatively pressure-time curve table of described input and outfan, thus obtaining the lag time of pressure piping.
The measurement apparatus of the lag time according to above-mentioned pressure transmission systems, preferably, a controllable valve is had between described air chamber and the second pressure transducer, for isolating the gas communication between air chamber and pressure piping, by controlling pressure source, to make the valve both sides of Guan Bi reach required Step Pressure poor, and valve is formed at the input of described pressure piping after opening has the Step Pressure that required Step Pressure is poor.
The measurement apparatus of the lag time according to above-mentioned pressure transmission systems, it is preferred that, the volume of the described air chamber described pressure piping internal volume more than or equal to 100 times.
The measurement apparatus of the lag time according to above-mentioned pressure transmission systems, it is preferred that acquisition module output described time delay in the pressure-time curve table of the outfan of pressure piping at the hysteresis index that lag time is described pressure piping at 63.2% place of Step Pressure pressure reduction.
The measurement apparatus of the lag time according to above-mentioned pressure transmission systems, it is preferred that, the hysteresis index that numerical value is described pressure piping of 1/5th of the lag time of the described pressure transmission systems of described acquisition module output time delay.
Know-why according to the present invention, also provides for the measurement apparatus of the lag time of a kind of pressure piping for measuring in pressure transmission systems, and described measurement apparatus includes: data input module；Input is connected to the pressure source of described data input module outfan；Input is connected to the air chamber of described pressure source outfan；Input is connected to the first pressure transducer of described air chamber outfan, and the outfan of described first pressure transducer is for being connected to the input of described pressure piping；Input is for being connected to the second pressure transducer of the outfan of described pressure piping；Input is connected to the outfan of described first pressure transducer and acquisition module time delay of the outfan of described second pressure transducer；The volume of described air chamber is more than the internal volume of described pressure piping, and the Step Pressure can preset to the output of described pressure piping；Described first pressure transducer detects the pressure-time curve table of the input of described pressure piping, and described second pressure transducer detects the pressure-time curve table of the outfan of described pressure piping；Described data input module, described pressure source, described air chamber, described first pressure transducer, described pressure piping, described second pressure transducer and described time delay acquisition module swashed and passed to formation pressure piping test access；The input of the described pressure piping of described acquisition module collection time delay and the pressure-time curve table of outfan, and compare the pressure-time curve table of input and outfan, thus obtaining the lag time of described pressure piping.
The measurement apparatus of the lag time according to above-mentioned pressure piping, it is preferred that, described pressure transmission systems is the tested airspeed system of aircraft, and described pressure piping includes tested pressure piping, and described data input module is flying quality input module.
The measurement apparatus of the lag time according to above-mentioned pressure piping, preferably, a controllable valve is had between described air chamber and the first pressure transducer, for isolating the gas communication between air chamber and pressure piping, by controlling pressure source, to make the valve both sides of Guan Bi reach required Step Pressure poor, and valve is formed at the input of described pressure piping after opening has the Step Pressure that required Step Pressure is poor.
The measurement apparatus of the lag time according to above-mentioned pressure piping, it is preferred that, the volume of the described air chamber described pressure piping internal volume more than or equal to 100 times.
The measurement apparatus of the lag time according to above-mentioned pressure piping, it is preferred that acquisition module output described time delay in the pressure-time curve table of the outfan of pressure piping at the hysteresis index that lag time is described pressure piping at 63.2% place of Step Pressure pressure reduction.
The measurement apparatus of the lag time according to above-mentioned pressure piping, it is preferred that, the lag time that numerical value is described pressure transmission systems of 5 times of the hysteresis index of the described pressure piping of described acquisition module output time delay.
Accompanying drawing explanation
Fig. 1 is the schematic block diagram according to the first embodiment of the present invention；
Fig. 2 is schematic block diagram according to the second embodiment of the present invention；
Fig. 3 is schematic block diagram according to the third embodiment of the invention；
Fig. 4 shows the pressure of the pressure piping outfan that Step Pressure and described Step Pressure produced by the air chamber in embodiments of the invention are formed.
Detailed description of the invention
As it is shown in figure 1, tested airspeed system is the device of a part for aircraft itself.Tested pressure piping by the pressure conduction at tested aircraft pressure probe place to tested air computer, by COMPUTER DETECTION and the pressure-time curve table calculating aircraft pressure probe.
As it is shown in figure 1, the figure shows the module map of the airspeed system lag time measurement apparatus of the present invention.This measurement apparatus include flying quality input module, pressure source, air chamber, pressure transducer 1, pressure transducer 2, pressure transducer 3, ARINC bus acquisition module and time delay acquisition module.This measurement apparatus can be connected to the tested airspeed system of aircraft and tested pressure piping, is swashed the logical hysteresis index that can be used to measure airspeed system lag time and pressure piping respectively according to different paths.
As in figure 2 it is shown, this figure black line partially illustrates the measurement apparatus of the present invention for measuring the module map of airspeed system lag time.Flying quality input module is connected to pressure source, pressure source is connected to pressure transducer 1, pressure transducer 1 and ARINC bus acquisition module are connected to acquisition module time delay, the path 20 being constructed such that is for measuring airspeed system lag time, now, tested airspeed system is connected between pressure transducer 1 and ARINC bus acquisition module.
As it is shown on figure 3, this figure black line partially illustrates the measurement apparatus of the present invention for measuring the module map of the hysteresis index of pressure piping.Flying quality input module is connected to pressure source, pressure source is connected to air chamber, air chamber is connected to pressure transducer 2, pressure transducer 2 and pressure transducer 3 are connected to acquisition module time delay, the path 30 being constructed such that is for measuring the hysteresis index of pressure piping, now, tested pressure piping is connected between pressure transducer 2 and pressure transducer 3.
The module of measurement apparatus
Flying quality input module can will be converted to control signal with the aircraft altitude of optional frequency collection, speed data pressure source is controlled on aircraft, makes pressure source according to the target stagnation pressure set, static pressure force value size, pressure change rate output stagnation pressure and static pressure.The flying quality input module being arranged on pressure source upstream can according to the air speed of artificial setting, altitude information, it is automatically converted to the treatable pressure controling signal of pressure source, enabling pressure source to export desirable pressure, thus pressure source simulation produces to be equal to the pressure change output of flying quality.The air chamber being arranged in pressure piping measurement path 30 is the volume gas tank more than the pressure piping internal volume of system under test (SUT), for instance, the volume of air chamber is more than or equal to the pressure piping internal volume of 100 times of systems under test (SUT).Air chamber and pressure source can produce to export close to the pressure of ideal step pressure jointly.Pressure transducer 1 is for measuring the pressure of the input of tested airspeed system, and pressure transducer 2 is for measuring the pressure of tested pressure piping input, and pressure transducer 3 is for measuring the pressure of tested pressure piping outfan.Owing to air data computer is that (ARINC is the bus protocol that aviation field is conventional by ARINC bus, AeronauticalRadioIncorporated) output data, so test device also sets up the ARINC bus acquisition module output data to air data computer is acquired decoding, acquisition module is for recording the data of the bus output of tested air computer.Time delay, acquisition module was for gathering the input of tested pressure piping or tested airspeed system and the pressure-time curve of outfan, and compare, obtaining the time delay of any point in pressure change overall process, namely same force value occurs in the time difference of input and outfan.
In fig. 2, pressure transducer 1 and tested aircraft pressure probe are respectively used to measure in real time the input pressure value of tested pressure piping, and the input pressure value that pressure probe obtains is transferred to air computer by pressure piping.In figure 3, pressure transducer 2 and 3 is respectively used to measure in real time input pressure value and the output pressure value of tested pressure piping.
Using this device, it may be achieved carry out pressure retarded measure of time test in ground simulation, it is not necessary to carry out test repacking and sliding race or flight test aboard, can save substantial amounts of experimentation cost, and this measurement device precision is high, error is little, it is ensured that the accuracy of measurement.Secondly, sliding for the real aircraft flying quality run or fly can be processed by this device, true aircraft flight ambient pressure variations situation is simulated according to aircraft flight data, ensure the verity of this measurement device result, 3rd, this test device also can produce Step Pressure input, is used for measuring pipeline hysteresis index.Hysteresis index is that reflection pressure conducts the parameter of fast slow characteristic in pipeline, total lag time of pressure piping substantially hysteresis index of 5 times.
Airspeed system test access 20 shown in Fig. 2 and the pressure piping test access 30 shown in Fig. 3 are described by the examples below.
When airspeed system being carried out lag time and measuring, first as shown in Figure 2 the tested airspeed system of aircraft is connected to this test device, tested airspeed system includes pitot-static pressure probe (i.e. tested aircraft pressure probe in figure), aircraft pitot-static pressure pipeline (i.e. tested pressure piping in figure), aircraft air data computer (i.e. tested air computer in figure), it is consequently formed from flying quality input module, pressure source, pressure transducer 1, tested aircraft pressure probe, tested pressure piping, tested air computer, ARINC bus acquisition module, to time delay acquisition module and pressure transducer 1 be additionally also attached to the airspeed system test access 20 of acquisition module time delay, as shown in Figure 2.Then, practical flight data (with the flying quality in the aircraft flight stage of 4HZ frequency collection on such as aircraft) are inputted flying quality input module with spreadsheet format, start test device, tested airspeed system test access 20 is activated, as shown in Figure 2, time delay, acquisition module will after measurement terminates, the pressure-time curve of the tested airspeed system input and output side that output is obtained by pressure transducer 1 and air computer respectively, operator can input any time or any air speed in test, can obtain this moment or the time delay at air speed place.
When pressure piping being carried out hysteresis index and measuring, first aircraft pressure piping is connected to this test device, be consequently formed from flying quality input module, pressure source, air chamber, pressure transducer 2, tested pressure piping, pressure transducer 3, to time delay acquisition module and pressure transducer 2 be additionally also attached to the pressure piping test access 30 of acquisition module time delay, as shown in Figure 3.Initial pressure value and Step Pressure value being input to flying quality input module, starts test device, tested pressure piping test access 30 is activated, as it is shown on figure 3, test device can pass through the Step Pressure that air chamber is preset to the output of tested pressure piping.Time delay, acquisition module was after measurement terminates, export the pressure-time curve of the input and output side that tested pressure piping is obtained respectively by pressure transducer 2 and pressure transducer 3, and export the hysteresis index value of this tested pressure piping simultaneously, it is preferred that this hysteresis index value be outfan pressure-time curve in time delay of initial pressure value and 63.2% place of the pressure reduction of Step Pressure value.
In path 30 shown in Fig. 3, pressure input data have two, initial pressure value and Step Pressure value.First inputting initial pressure value, namely initial pressure value is the starting point of Step Pressure.An electronically controlled valve is had between air chamber and pressure transducer 2, for isolating the gas communication between air chamber and pressure piping, by controlling pressure source, to make the valve both sides of Guan Bi reach required Step Pressure poor, and valve is formed at the input of described pressure piping after opening has the Step Pressure that required Step Pressure is poor.Such as before the test begins, tested pressure piping is filled with a relatively low pressure (in order to understand conveniently, assume it is the pressure of 1 kPa, as shown in Figure 4, actually not necessarily these data, it is possibly even zero), then in air chamber, it is filled with higher pressure (also assumes that the pressure of 3 kPas, as shown in Figure 4), isolate with electronically controlled valve between pressure source and air chamber, this valve can be opened by computer moment, then at the input of tested pressure piping moment defined and there is a pressure differential (this is assumed to be 2 kPas, Step Pressure as shown in Figure 4).Owing to the volume of air chamber is far longer than the internal volume of tested pressure piping, so after the pressure balance of final air chamber and tested pressure piping, the pressure in whole system can also keep above-mentioned bigger pressure substantially.Finally, for the Step Pressure shown in Fig. 4, time delay, acquisition module was after measurement terminates, export the pressure-time curve (in Fig. 4 shown in input Step Pressure curve) of the input that tested pressure piping is obtained by pressure transducer 2 and pressure transducer 3 respectively and the pressure-time curve (in Fig. 4 shown in output end pressure curve) of outfan, and export the hysteresis index value of this tested pressure piping simultaneously.In the pressure-time curve of outfan, time or time difference at initial pressure value and 63.2% place of the pressure differential of Step Pressure value are the most accurate hysteresis index.Total lag time T is substantially equal to this hysteresis index t of 5 times.
Thus, path 20 shown in Fig. 2 can test the lag time of the complete airspeed system of aircraft, can be used for verifying the requirement whether aircraft meets FAA airworthiness regulation.Path 30 shown in Fig. 3 can test the hysteresis index of aircraft pressure piping, can be used for studying the lag characteristic of physics pipeline.
The relation of total lag time T and hysteresis index t it is appreciated that, namely in from the above
T=5t.
Above-mentioned exemplary embodiment illustrates an embodiment in the technical scheme solving the technical problem to be solved in the present invention.Under the example of this embodiment, other equivalence meeting the principle of the invention broadly falls in the scope of protection of the invention with similar means.Principles of the invention is, it is not necessary to aircraft carries out test repacking, tests the input of tested pressure piping and the time m-pressure curve of outfan at test site, obtains the lag time of airspeed system and the hysteresis index of pressure piping.Such as, learning from the above, two tests of the lag time of airspeed system and the hysteresis index of pressure piping can complete in the airspeed system test access 20 shown in Fig. 2, it is also possible to completes in the pressure piping test access 30 shown in Fig. 3.This is also within scope of invention.
Claims (15)
1., for measuring a measurement apparatus for the lag time of pressure transmission systems, described measurement apparatus includes:
Data input module；
Input is connected to the pressure source of described data input module outfan, and described pressure source forms predetermined pressure according to the data inputted in described data input module；
Input is connected to the first pressure transducer of the outfan of described pressure source, and the outfan of described first pressure transducer is for being connected to the input of described pressure transmission systems, and described pressure transmission systems includes pressure piping；And
Input is used for being connected to acquisition module time delay of the outfan of the outfan of described pressure transmission systems and the first pressure transducer；Wherein said first pressure transducer detects the pressure-time curve table of the input of described pressure transmission systems, the pressure-time curve table of the outfan of the outfan output pressure transmission system of described pressure transmission systems；Described data input module, described pressure source, described first pressure transducer, described pressure transmission systems and described time delay acquisition module swashed and passed to formation pressure transmission systems test access (20)；
In pressure transmission systems test access (20), the input of the described pressure transmission systems of described acquisition module collection time delay and the pressure-time curve table of outfan, and compare the input of pressure transmission systems and the pressure-time curve table of outfan, thus obtaining the lag time of pressure transmission systems.
2. the measurement apparatus of the lag time for measuring pressure transmission systems as claimed in claim 1, it is characterised in that described pressure transmission systems is the tested airspeed system of aircraft, and described data input module is flying quality input module.
3. the measurement apparatus of the lag time for measuring pressure transmission systems as claimed in claim 2, it is characterized in that, described tested airspeed system includes tested aircraft pressure probe and tested air computer, described pressure piping includes tested pressure piping, the pressure-time curve table of the outfan of pressure transmission systems described in described air computer export.
4. the measurement apparatus of the lag time for measuring pressure transmission systems as claimed in claim 3, it is characterized in that, also include for being connected to the ARINC bus acquisition module between described air computer and described time delay acquisition module, for the output data of described air computer are acquired decoding.
5. the measurement apparatus of the lag time for measuring pressure transmission systems as described in any one in claim 1-4, it is characterised in that also include:
Input is connected to the air chamber of described pressure source outfan；
Input is connected to the second pressure transducer of described air chamber outfan, the outfan of described second pressure transducer for be connected to described pressure piping input and described time delay acquisition module input；
Input is for being connected to the 3rd pressure transducer of outfan of described pressure piping, and the outfan of the 3rd pressure transducer is for being connected to the input of acquisition module described time delay；
The volume of described air chamber is more than the internal volume of described pressure piping, and the Step Pressure can preset to the output of described pressure piping；
Described second pressure transducer detects the pressure-time curve table of the input of described pressure piping, and described 3rd pressure transducer (3) detects the pressure-time curve table of the outfan of described pressure piping；
Described data input module, described pressure source, described air chamber, described second pressure transducer, described pressure piping, described 3rd pressure transducer and described time delay acquisition module swashed and passed to formation pressure piping test access (30)；
In pressure piping test access (30), the input of the described pressure piping of described acquisition module collection time delay and the pressure-time curve table of outfan, and the relatively pressure-time curve table of described input and outfan, thus obtaining the lag time of described pressure piping.
6. the measurement apparatus of the lag time for measuring pressure transmission systems as claimed in claim 5, it is characterized in that, a controllable valve is had between described air chamber and the second pressure transducer, for isolating the gas communication between described air chamber and described pressure piping, by controlling pressure source, to make the valve both sides of Guan Bi reach required Step Pressure poor, and valve is formed at the input of described pressure piping after opening has the Step Pressure that required Step Pressure is poor.
7. the measurement apparatus of the lag time for measuring pressure transmission systems as claimed in claim 6, it is characterised in that the volume of the described air chamber described pressure piping internal volume more than or equal to 100 times.
8. the measurement apparatus of the lag time for measuring pressure transmission systems as claimed in claim 7, it is characterized in that, acquisition module output described time delay in the pressure-time curve table of the outfan of described pressure piping at the hysteresis index that lag time is described pressure piping at 63.2% place of Step Pressure pressure reduction.
9. the measurement apparatus of the lag time for measuring pressure transmission systems as described in any one in claim 1-4, it is characterized in that, the hysteresis index that numerical value is described pressure piping of 1/5th of the lag time of the described pressure transmission systems of described acquisition module output time delay.
10., for measuring a measurement apparatus for the lag time of the pressure piping in pressure transmission systems, described measurement apparatus includes:
Data input module；
Input is connected to the pressure source of described data input module outfan；
Input is connected to the air chamber of described pressure source outfan；
Input is connected to the first pressure transducer of described air chamber outfan, and the outfan of described first pressure transducer is for being connected to the input of described pressure piping；
Input is for being connected to the second pressure transducer of the outfan of described pressure piping；
Input is connected to the outfan of described first pressure transducer and acquisition module time delay of the outfan of described second pressure transducer；
The volume of described air chamber is more than the internal volume of described pressure piping, and the Step Pressure can preset to the output of described pressure piping；
Described first pressure transducer detects the pressure-time curve table of the input of described pressure piping, and described second pressure transducer detects the pressure-time curve table of the outfan of described pressure piping；
Described data input module, described pressure source, described air chamber, described first pressure transducer, described pressure piping, described second pressure transducer and described time delay acquisition module swashed and passed to formation pressure piping test access (30)；
The input of the described pressure piping of described acquisition module collection time delay and the pressure-time curve table of outfan, and compare the pressure-time curve table of input and outfan, thus obtaining the lag time of described pressure piping.
11. the measurement apparatus of the lag time of pressure piping as claimed in claim 10, it is characterized in that, described pressure transmission systems is the tested airspeed system of aircraft, and described pressure piping includes tested pressure piping, and described data input module is flying quality input module.
12. the measurement apparatus of the lag time of pressure piping as claimed in claim 11, it is characterized in that, a controllable valve is had between described air chamber and the first pressure transducer, for isolating the gas communication between air chamber and pressure piping, by controlling pressure source, to make the valve both sides of Guan Bi reach required Step Pressure poor, and valve is formed at the input of described pressure piping after opening has the Step Pressure that required Step Pressure is poor.
13. the measurement apparatus of the lag time of pressure piping as claimed in claim 12, it is characterised in that the volume of the described air chamber described pressure piping internal volume more than or equal to 100 times.
14. the measurement apparatus of the lag time of the pressure piping as described in claim 10-13 any one, it is characterized in that, acquisition module output described time delay in the pressure-time curve table of the outfan of pressure piping at the hysteresis index that lag time is described pressure piping at 63.2% place of Step Pressure pressure reduction.
15. the measurement apparatus of the lag time of pressure piping as claimed in claim 14, it is characterised in that the lag time that numerical value is described pressure transmission systems of 5 times of the hysteresis index of the described pressure piping of described acquisition module output time delay.
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| US10768201B2 (en) * | 2017-06-12 | 2020-09-08 | The Boeing Company | System for estimating airspeed of an aircraft based on a drag model |
| CN109088786B (en) * | 2018-06-26 | 2022-03-08 | 中国直升机设计研究所 | Method for testing network delay of helicopter simulator |
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| JPH07117431B2 (en) * | 1990-07-21 | 1995-12-18 | 株式会社日立製作所 | Monitoring device |
| JPH07243875A (en) * | 1994-03-02 | 1995-09-19 | Mitsubishi Electric Corp | Apparatus and method for measuring device |
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| CN102360088A (en) * | 2011-09-09 | 2012-02-22 | 陕西长岭电子科技有限责任公司 | Air data computer and realization method thereof |
| CN103148887A (en) * | 2013-01-30 | 2013-06-12 | 哈尔滨工业大学 | Multi-module real-time monitoring system and method for achieving data simultaneous storage using the same |
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