CN106081160A - A kind of aircraft housing unit passenger cabin inside and outside differential pressure simulation test device and method - Google Patents
A kind of aircraft housing unit passenger cabin inside and outside differential pressure simulation test device and method Download PDFInfo
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- CN106081160A CN106081160A CN201610595508.XA CN201610595508A CN106081160A CN 106081160 A CN106081160 A CN 106081160A CN 201610595508 A CN201610595508 A CN 201610595508A CN 106081160 A CN106081160 A CN 106081160A
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Abstract
The present invention relates to air equipment detection field, particularly relate to a kind of aircraft housing unit passenger cabin inside and outside differential pressure simulation test device and method.Including simulating chamber in aircraft housing unit, cabin, simulating chamber, air extractor and air intake installation out of my cabin, simulate chamber in described cabin and simulate chamber out of my cabin and lay respectively at the both sides of aircraft housing unit, and it is completely isolated by aircraft housing unit, described air extractor respectively with in cabin simulate chamber and out of my cabin simulation chamber is connected, air intake installation respectively with in cabin simulation chamber and out of my cabin simulate chamber be connected.Achieve the accurate simulation of aircraft housing inside and outside differential pressure；The method utilizing dynamic equilibrium achieves being precisely controlled of blood pressure lowering and rate of pressure rise；Automatically controlling of whole experiment process, it is not necessary to the most on duty.
Description
Technical field
The present invention relates to air equipment detection field, particularly relate to a kind of aircraft housing unit passenger cabin inside and outside differential pressure simulation examination
Experiment device and method.
Background technology
Along with the military and development of civil aircraft process industry, aircraft component especially aircraft is being taken off, is flying, landing
During there is inside and outside housing pressure reduction the requirement of space-environment facility of housing unit more and more higher.Pressure reduction tries
Test, height test, decompression test are that aircraft component must be examined with assembly out of my cabin in especially aircraft housing parts bears cabin
Pilot project, main examination aircraft component whether be resistant to hypobaric, whether can under hypobaric normal work
Make, whether be resistant to air pressure Rapid Variable Design, prevent aircraft component taking off, fly, descent lost efficacy.
The pressure test of current aircraft component, height test, decompression test mainly complete with low pressure test chamber, but low
Pressure box can only be that whole aircraft component is inserted in low pressure test chamber, and aircraft housing unit can not produce in process of the test
Raw pressure reduction, it is impossible to the external and internal pressure that true simulated aircraft is subject at flight course middle shell assembly.At present, domestic also do not have one
Can the device of accurate simulated aircraft housing unit inside and outside differential pressure.
Summary of the invention
The technical problem to be solved is to provide a kind of aircraft housing unit passenger cabin inside and outside differential pressure simulation test dress
Put and method, exist at the inside and outside true pressure suffered by flight course aircraft housing, check flight housing with accurate simulated aircraft
Environmental suitability under real differential pressure action.
For solving above-mentioned technical problem, the technical solution adopted in the present invention is: provide a kind of aircraft housing unit passenger cabin
Inside and outside differential pressure simulation test device, it is special is: simulates chamber in including aircraft housing unit, cabin, simulate chamber, dress of bleeding out of my cabin
Put and air intake installation, simulate chamber in described cabin and simulate chamber out of my cabin and lay respectively at the both sides of aircraft housing unit, and by aircraft shell
Body assembly is completely isolated, described air extractor respectively with in cabin simulate chamber and out of my cabin simulate chamber be connected, air intake installation respectively with cabin
Interior simulation chamber and out of my cabin simulation chamber connect.
Described air extractor includes vacuum pump and two electric control valves D1, D2, and described vacuum pump passes through electric control valve
D1 is connected with simulation chamber in cabin, and vacuum pump is connected with simulation chamber out of my cabin by electric control valve D2.
Described air intake installation includes two electric control valves D3, D4 and two mass flowmenters MFC1, MFC2, motorized adjustment
Valve D3 and mass flowmenter MFC1 respectively with in cabin simulate chamber be connected, electric control valve D4 and mass flowmenter MFC2 respectively with cabin
Outer simulation chamber connects.
Also include respectively with simulate chamber in cabin and simulate chamber two pressure transmitters G1, G2 being connected out of my cabin.
Also include control system, described control system respectively with vacuum pump, electric control valve D1, D2, D3, D4, quality stream
Gauge MFC1, MFC2 and pressure transmitter G1, G2 connect.
Method based on above-mentioned a kind of aircraft housing unit passenger cabin inside and outside differential pressure simulation test device, its special character exists
In: comprise the following steps:
1), opening control, pressure transmitter G1 and G2 simulates chamber and simulates the pressure in chamber out of my cabin in starting to gather cabin
Value；
2) simulating cavity pressure desired value in arranging cabin, in the controls is P1, and simulation cavity pressure desired value is P2 out of my cabin,
Rate of pressure reduction is set to V；
3), after control system starts vacuum pump, electric control valve D1 and D2 increases angle by 0, simulates in cabin
Chamber and out of my cabin simulation chamber start blood pressure lowering；
4), simulate chamber and simulate the force value in chamber out of my cabin in pressure transmitter G1 and G2 continuous collecting cabin, by control be
System computing calculates the rate of pressure change in cycle T, if rate of pressure change subtracts more than V, then corresponding D1 or D2 aperture
Little, if rate of pressure change increases less than V, then corresponding D1 or D2 aperture, control rate of pressure reduction by the regulation of aperture and protect
Hold at V；
5), when in cabin, pressure is down to P1, mass flowmenter MFC1 opens, and simulates chamber and is filled with air, control system in cabin
System uses pid algorithm, and when in cabin, pressure is less than P1, inflation rate is more than rate of pressure reduction, and pressure rises to P1, when in cabin, pressure is big
When P1, inflation rate is less than rate of pressure reduction, and pressure is down to P1, Pressure behaviour so can be kept to maintain P1；
6) pressure simulating chamber, out of my cabin continues with rate of pressure reduction V to P2 blood pressure lowering, when the pressure simulating chamber out of my cabin is down to P2
Time, mass flowmenter MFC2 opens, and is filled with air in cabin, and control system uses pid algorithm, when in cabin, pressure is less than P2,
Inflation rate is more than rate of pressure reduction, and pressure rises to P2, and when in cabin, pressure is more than P2, inflation rate is less than rate of pressure reduction, pressure
It is down to P2, Pressure behaviour so can be kept to maintain P2；
7), after pressure keeps terminating, control system controls D1, D2, MFC1 and MFC2 and closes, and controls D3 and D4 and opens,
Force value in G1 and G2 continuous collecting cabin and out of my cabin, calculates the rate of pressure change in cycle T by control system computing,
If rate of pressure change is more than V, then corresponding D3 or D4 aperture reduces, if rate of pressure change is less than V, then corresponding D3
Or D4 aperture increases, control rate of pressure reduction by the regulation of aperture and be maintained at V；
8), when simulating chamber in cabin and simulating after the force value in chamber rises to atmospheric pressure out of my cabin, control system controls D3 and D4 and closes
Close.
The medicine have the advantages that
1, the accurate simulation of aircraft housing inside and outside differential pressure is achieved；2, the method utilizing dynamic equilibrium achieves blood pressure lowering and liter
Being precisely controlled of pressure speed；3, the automatically controlling of whole experiment process, it is not necessary to the most on duty.
Accompanying drawing explanation
Fig. 1 is the theory diagram of specific embodiment.
Specific embodiment
As it is shown in figure 1, need to be down to 70KPa with pressure in cabin, pressure needs to be down to 37.6KPa out of my cabin, and rate of pressure reduction is
As a example by 10KP/min, concrete grammar is:
1), opening control, in survey room and out of my cabin G1 and the G2 pressure transmitter of pressure starts to gather cabin and cabin
Outer force value；
2) arranging pressure target value in cabin, in the controls is 70KPa, and pressure target value is 37.6KPa out of my cabin, blood pressure lowering
Speed is set to 10KP/min；
3) providing vacuum pump P1 enabling signal, in the controls, after vacuum pump startup, electric control valve D1 and D2 is by 0
Starting to increase angle, annular seal space in cabin and out of my cabin starts blood pressure lowering；
4) force value, in G1 and G2 continuous collecting cabin and out of my cabin, is calculated in cycle 5s by control system computing
Rate of pressure change, if rate of pressure change reduces more than 10KP/min, then corresponding D1 or D2 aperture, if pressure change
Speed is less than 10KP/min, then corresponding D1 or D2 aperture increases, and controls rate of pressure reduction by the regulation of aperture and is maintained at 10KP/
min；
5), when in cabin, pressure is down to 70KPa, mass flowmenter MFC1 opens, and is filled with air in cabin, and control system is adopted
With pid algorithm, when in cabin, pressure is less than 70KPa, inflation rate is more than rate of pressure reduction, and pressure rises to 70KPa, when pressure in cabin
More than inflation rate during 70KPa less than rate of pressure reduction, pressure is down to 70KPa, Pressure behaviour so can be kept to maintain
70KPa；
6), out of my cabin pressure continue with the rate of pressure reduction of 10KP/min to 37.6KPa blood pressure lowering, when out of my cabin, pressure is down to
During 37.6KPa, mass flowmenter MFC2 opens, and is filled with air in cabin, and control system uses pid algorithm, when in cabin, pressure is little
When 37.6KPa, inflation rate is more than rate of pressure reduction, and pressure rises to 37.6KPa, the inflation speed when pressure is more than 37.6KPa in cabin
Rate is less than rate of pressure reduction, and pressure is down to 37.6KPa, Pressure behaviour so can be kept to maintain 37.6KPa；
7), keeping Pressure behaviour balance after 1 hour, control system controls D1 and D2 and completely closes, and controls D3 and D4 electronic
Open with regulation valve, force value in G1 and G2 continuous collecting cabin and out of my cabin, calculated in cycle 5s by control system computing
Rate of pressure change, if rate of pressure change is more than 10KP/min, then corresponding D3 or D4 aperture reduces, if pressure becomes
Change speed to increase less than 10KP/min, then corresponding D3 or D4 aperture, control rate of pressure reduction by the regulation of aperture and be maintained at
10KP/min；
8), after force value in cabin, out of my cabin rises to atmospheric pressure, control system controls D3 and D4 and closes.
According to the GJB150 " the military hardware laboratory environment test method " requirement to low-atmospheric pressure test, Stress control error
For ± 5%, the interior any time point control in 1 hour that in cabin, pressure keeps at pressure in the range of 70KPa ± 3.5KPa, cabin
The interior any time point control in 1 hour that external pressure keeps at pressure, in the range of 37.6KPa ± 1.88KPa, i.e. thinks gas
Pressure pass the test, buck speed, with reference to the requirement of ± 5%, for time in the range of 10KPa/min ± 0.5KPa, i.e. thinks lifting
Pressure speed is qualified.
Claims (8)
1. an aircraft housing unit passenger cabin inside and outside differential pressure simulation test device, it is characterised in that: include aircraft housing unit, cabin
Interior simulation chamber, simulate chamber, air extractor and air intake installation out of my cabin, simulate chamber in described cabin and simulate chamber out of my cabin and lay respectively at aircraft
The both sides of housing unit, and completely isolated by aircraft housing unit, described air extractor simulates chamber and mould out of my cabin with in cabin respectively
Intend chamber connect, air intake installation respectively with in cabin simulate chamber and out of my cabin simulate chamber be connected.
A kind of aircraft housing unit passenger cabin inside and outside differential pressure simulation test device the most according to claim 1, it is characterised in that:
Described air extractor includes vacuum pump and two electric control valves D1, D2, and described vacuum pump is by electric control valve D1 and cabin
Simulation chamber connects, and vacuum pump is connected with simulation chamber out of my cabin by electric control valve D2.
A kind of aircraft housing unit passenger cabin inside and outside differential pressure simulation test device the most according to claim 2, it is characterised in that:
Described air intake installation includes two electric control valves D3, D4 and two mass flowmenters MFC1, MFC2, electric control valve D3 and matter
Amount effusion meter MFC1 respectively with in cabin simulate chamber be connected, electric control valve D4 and mass flowmenter MFC2 respectively with simulate chamber out of my cabin
Connect.
A kind of aircraft housing unit passenger cabin inside and outside differential pressure simulation test device the most according to claim 3, it is characterised in that:
Also include respectively with simulate chamber in cabin and simulate chamber two pressure transmitters G1, G2 being connected out of my cabin.
A kind of aircraft housing unit passenger cabin inside and outside differential pressure simulation test device the most according to claim 4, it is characterised in that:
Also include control system, described control system respectively with vacuum pump, electric control valve D1, D2, D3, D4, mass flowmenter MFC1,
MFC2 and pressure transmitter G1, G2 connect.
A kind of aircraft housing unit passenger cabin inside and outside differential pressure simulation test device the most according to claim 1, it is characterised in that:
Described air intake installation includes two electric control valves D3, D4 and two mass flowmenters MFC1, MFC2, electric control valve D3 and matter
Amount effusion meter MFC1 respectively with in cabin simulate chamber be connected, electric control valve D4 and mass flowmenter MFC2 respectively with simulate chamber out of my cabin
Connect.
A kind of aircraft housing unit passenger cabin inside and outside differential pressure simulation test device the most according to claim 1, it is characterised in that:
Also include respectively with simulate chamber in cabin and simulate chamber two pressure transmitters G1, G2 being connected out of my cabin.
8. method based on a kind of aircraft housing unit passenger cabin inside and outside differential pressure simulation test device described in claim 5, it is special
Levy and be: comprise the following steps:
1), opening control, pressure transmitter G1 and G2 simulates chamber and simulates the force value in chamber out of my cabin in starting to gather cabin；
2) simulating cavity pressure desired value in arranging cabin, in the controls is P1, and simulation cavity pressure desired value is P2 out of my cabin, blood pressure lowering
Speed is set to V；
3), starting after vacuum pump in control system, electric control valve D1 and D2 increases angle by 0, simulate in the cabin in chamber with
Simulation chamber starts blood pressure lowering out of my cabin；
4), simulate chamber and simulate the force value in chamber out of my cabin in pressure transmitter G1 and G2 continuous collecting cabin, transported by control system
Calculate the rate of pressure change calculating in cycle T, if rate of pressure change reduces more than V, then corresponding D1 or D2 aperture, as
Really rate of pressure change is less than V, then corresponding D1 or D2 aperture increases, and controls rate of pressure reduction by the regulation of aperture and is maintained at V；
5) when in cabin, pressure is down to P1, mass flowmenter MFC1 opens, and simulates chamber and be filled with air in cabin, and control system uses
Pid algorithm, when in cabin, pressure is less than P1, inflation rate is more than rate of pressure reduction, and pressure rises to P1, when in cabin, pressure is more than P1
Time, inflation rate is less than rate of pressure reduction, and pressure is down to P1, Pressure behaviour so can be kept to maintain P1；
6) pressure simulating chamber out of my cabin continues with rate of pressure reduction V to P2 blood pressure lowering, when the pressure simulating chamber out of my cabin is down to P2, and quality
Effusion meter MFC2 opens, and is filled with air in cabin, and control system uses pid algorithm, when in cabin, pressure is less than P2, and inflation rate
More than rate of pressure reduction, pressure rises to P2, and when in cabin, pressure is more than P2, inflation rate is less than rate of pressure reduction, and pressure is down to P2, this
Sample can keep Pressure behaviour to maintain P2；
7) after pressure keeps terminating, control system controls D1, D2, MFC1 and MFC2 and closes, and controls D3 and D4 and opens, G1 and G2
Force value in continuous collecting cabin and out of my cabin, calculates the rate of pressure change in cycle T by control system computing, if pressure
Power rate of change is more than V, then corresponding D3 or D4 aperture reduces, if rate of pressure change is opened less than V, then corresponding D3 or D4
Degree increases, and controls rate of pressure reduction by the regulation of aperture and is maintained at V；
8) when simulating chamber in cabin and simulating after the force value in chamber rises to atmospheric pressure out of my cabin, control system controls D3 and D4 closedown.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610595508.XA CN106081160B (en) | 2016-07-26 | 2016-07-26 | A kind of aircraft housing unit cockpit inside and outside differential pressure simulation test device and method |
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|---|---|---|---|
| CN201610595508.XA CN106081160B (en) | 2016-07-26 | 2016-07-26 | A kind of aircraft housing unit cockpit inside and outside differential pressure simulation test device and method |
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| CN106081160A true CN106081160A (en) | 2016-11-09 |
| CN106081160B CN106081160B (en) | 2018-08-03 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021036477A1 (en) * | 2019-08-29 | 2021-03-04 | 南京星合精密智能制造研究院有限公司 | Ground test bench for aircraft oxygen system |
| CN114148544A (en) * | 2021-12-03 | 2022-03-08 | 中国飞行试验研究院 | Gravity center adjusting device and method for airtight-non-airtight cabin of airplane |
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| US20110234426A1 (en) * | 2007-11-29 | 2011-09-29 | Thomas Uhlendorf | Apparatus and method for pressurising an aircraft cabin structure and measuring the amount of leakage of the aircraft cabin structure |
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| US20060252360A1 (en) * | 2005-04-14 | 2006-11-09 | Mitchneck James A | Aircraft cabin pressurization control apparatus |
| US20110234426A1 (en) * | 2007-11-29 | 2011-09-29 | Thomas Uhlendorf | Apparatus and method for pressurising an aircraft cabin structure and measuring the amount of leakage of the aircraft cabin structure |
| US20120196520A1 (en) * | 2009-09-28 | 2012-08-02 | Airbus Operations Gmbh | Regulating system for the cabin pressure of an airplane and method for regulating the cabin pressure of an airplane |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| WO2021036477A1 (en) * | 2019-08-29 | 2021-03-04 | 南京星合精密智能制造研究院有限公司 | Ground test bench for aircraft oxygen system |
| CN114148544A (en) * | 2021-12-03 | 2022-03-08 | 中国飞行试验研究院 | Gravity center adjusting device and method for airtight-non-airtight cabin of airplane |
| CN114148544B (en) * | 2021-12-03 | 2024-02-13 | 中国飞行试验研究院 | Gravity center adjusting device and method for airtight-non-airtight cabin of airplane |
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| CN106081160B (en) | 2018-08-03 |
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