CN205750521U - A kind of detection equipment for military cockpit pressure regulating system - Google Patents
A kind of detection equipment for military cockpit pressure regulating system Download PDFInfo
- Publication number
- CN205750521U CN205750521U CN201620670217.8U CN201620670217U CN205750521U CN 205750521 U CN205750521 U CN 205750521U CN 201620670217 U CN201620670217 U CN 201620670217U CN 205750521 U CN205750521 U CN 205750521U
- Authority
- CN
- China
- Prior art keywords
- cabin
- pressure
- valve
- circuit
- test
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
This utility model relates to the detection equipment of military cockpit pressure regulating system, described detection equipment includes supply module, power supply test module, car simulation cabin, out of my cabin atmospheric simulation cabin, input module, display module and control unit, and this device possesses that volume is little, it is mobile, easy of use to be easy to, reliability is high, automaticity advantages of higher.The detection equipment that this utility model relates to, has taken into full account cockpit pressure regulating system each influence factor in a line or wild environment are safeguarded, it is adaptable to carry out the troubleshooting operation of cockpit pressure regulating system in a line or wild environment.
Description
Technical field
This utility model relates to a kind of detection equipment for military cockpit pressure regulating system, is especially adapted for use in
Under external field environment, for the seat being made up of department enclosures such as cockpit pressure controller, exhaust valve for cabin and cabin safety valves
Cabin pressure regulating system carries out the detection equipment detected.
Background technology
According to statistics, the defective proportion of military aircraft environmental control system is higher, and along with the increase of aircraft Years Of Service, ring control
The probability of system jam has the trend being gradually increased.Cockpit pressure regulating system is the important composition portion of aircraft environmental control system
/ mono-, its Main Function is from the air pressure of bleed subsystem according to flight altitude control, to ensure passenger cabin internal gas pressure
Value, pressure reduction, pressure change rate meet requirement, thus provide a good comfortable manipulation environment for pilot, meet pilot
Psychological need.
Analysis further to fault understands, the cockpit pressure controller in cockpit pressure regulating system, exhaust valve for cabin
Bigger ratio is occupied with the probability of malfunction of the parts such as cabin safety valve.And cockpit pressure controller be cockpit pressure regulation system
The controlling organization of system, exhaust valve for cabin is the actuator of cockpit pressure regulating system, and cabin safety valve is cockpit pressure
Safety guarantee mechanism, they play conclusive effect to the regulation of cockpit pressure, and its common phenomenon of the failure is usually seat
Cabin overbottom pressure overproof (wherein overbottom pressure refers to the difference of the outer atmospheric pressure of cockpit pressure and passenger cabin), pressure change rate are overproof, and (pressure becomes
Rate refers to the rate of change of the aircraft cabin pressure caused because aircraft rises or falls, when rate of change is bigger, and pilot
Tympanum pressure at both sides does not reaches balance, will form pressure reduction inside and outside tympanum, makes people feel under the weather, pain even tympanum
Rupture), the reaction of pilot is usually " clamp lug " phenomenon, then there will be " swings of elevation rate table " etc. and show in terms of instrument display
As, these problems all drastically influence pilot the mental status and physically and mentally healthy, involve the energy of pilot, govern and fly
The stable performance of office staff's operating aircraft performance, becomes one of major reason of induction aviation accident.
It is reported, the most not be applicable to the detection of the cockpit pressure regulating system used external field environment in prior art
Device, it is impossible to meet the service requirements in outfield when military cockpit pressure regulating system breaks down.
Utility model content
The technical problems to be solved in the utility model is to provide a kind of inspection for military cockpit pressure regulating system
Measurement equipment, it is capable of cockpit pressure controller, exhaust valve for cabin and seat in military cockpit pressure regulating system
Qualitative and the quantitative test of the parts such as cabin safety valve, quickly the trouble unit of location aircraft cabin pressure regulation system, full
The needs of foot cockpit pressure regulating system outfield troubleshooting.
A kind of detection equipment for military cockpit pressure regulating system that the utility model proposes, specifically includes:
Supply module, the alternating current power supply needed for providing for detection equipment and DC source；
Power supply test module, to voltage, electric current and the frequency of described alternating current power supply and the voltage of described DC source and
Electric current is tested, and is attached by circuit with described supply module；
Car simulation cabin, for the supply of simulated aircraft passenger cabin with through pressure controlled closed environment；
Atmospheric simulation cabin out of my cabin, for the simulated aircraft air pressure out of my cabin when differing heights flight, atmospheric simulation cabin out of my cabin
Connect with car simulation cabin by connecting gas circuit, and connecting, in gas circuit, valve is set；
Input module, for interacting with detection equipment, typing information, selection test event；
Display module, function menu, operation indicating and test result；
Control unit, for detecting the Control & data acquisition of equipment, respectively with described supply module, power supply test mould
Block, car simulation cabin, out of my cabin atmospheric simulation cabin, input module and display module are attached by circuit.
Preferably, the connection gas circuit between car simulation cabin and out of my cabin atmospheric simulation cabin is two, and two connect in gas circuit
It is respectively provided with valve.
Preferably, two connect the electromagnetic valve that valve is 3-position 4-way arranged in gas circuit.
Preferably, car simulation cabin and out of my cabin atmospheric simulation cabin are formed by nacelle and hatch door, set between nacelle and hatch door
Put silicone rubber O-ring, hatch door is respectively provided with observation window.
Preferably, car simulation cabin is made up of car simulation room, pneumatic supply and the first pressure transducer；Wherein pneumatic supply by
Source of the gas, the first air filter, first flow valve, the first electromagnetic valve, effusion meter composition, in addition to effusion meter is in parallel with simple gas circuit, its
Its each parts is sequentially connected with by gas circuit, and first flow valve, the first electromagnetic valve, effusion meter are entered with control unit by circuit respectively
Row connects；First pressure transducer is arranged in car simulation room, is attached with control unit by circuit.
Preferably, source of the gas is air compressor or air bottle, specifically optionally can make according to the equipment situation in outfield
With air compressor or air bottle.
Preferably, the first electromagnetic valve in car simulation cabin is two-bit triplet electromagnetic valve.
Preferably, atmospheric simulation cabin is made up of atmospheric simulation room out of my cabin, negative pressure source and the second pressure transducer out of my cabin；Wherein
Negative pressure source is formed by negative pressure branch road and air branch circuit parallel connection；Negative pressure props up route vacuum pump, second flow valve, the second electromagnetic valve group
Becoming, each parts are sequentially connected with by gas circuit, and second flow valve and the second electromagnetic valve are carried out even by circuit and control unit respectively
Connect；Arranging the second air filter on air branch road, the second air filter is connected with the second electromagnetic valve by gas circuit；Second pressure transducer is installed
In atmospheric simulation room out of my cabin, it is attached with control unit by circuit.
Preferably, the second electromagnetic valve is two-bit triplet electromagnetic valve.
Preferably, power supply test module uses test and shows two-in-one instrument, and the result of power supply test is directly at this
Show in instrument.
Accompanying drawing explanation
Fig. 1 is the structure principle chart of military cockpit pressure regulating system detection equipment, and the solid line in figure represents detection
Circuit between each building block of device interior connects, and dotted line represents the gas circuit between the detection each building block of device interior even
Connect.
Fig. 2 is the structure principle chart in car simulation cabin and atmospheric simulation cabin out of my cabin.
Detailed description of the invention
Below as a example by the cockpit pressure regulating system of aircraft, in conjunction with accompanying drawing, introduce concrete reality of the present utility model
Execute mode.
The cockpit pressure regulating system of this type aircraft is mainly by cockpit pressure controller, exhaust valve for cabin and cabin safety
The parts compositions such as valve.Cockpit pressure controller is the controlling organization of cockpit pressure regulating system, and exhaust valve for cabin is passenger cabin
The actuator of pressure regulating system, by cockpit pressure controller according to cockpit pressure adjustment law, by adjusting passenger cabin aerofluxus
The aperture of valve is automatically adjusted cockpit pressure and pressure change rate.Cabin safety valve is that the safety of cockpit pressure regulating system is protected
Barrier mechanism, emergent inflatable and deflatable for passenger cabin, prevent because passenger cabin overbottom pressure and negative pressure exceed setting and damage cockpit structure.
During work, bleed air system the air carried enters passenger cabin, when cockpit pressure exceedes setting, by cockpit pressure controller
Control exhaust valve for cabin, by increasing valve opening, and then reduce cockpit pressure；Otherwise, by reducing valve opening, and then
Increase cockpit pressure.
Cockpit pressure is regulated and is divided into three phases by cockpit pressure regulating system: the free ventilating stage in low latitude, absolute pressure
Regulation stage and residual compression regulation stage.
(1) the free ventilating stage in low latitude
0～H1In altitude range, exhaust valve for cabin is in normally open position, it is ensured that passenger cabin is constantly in ventilation state,
Cockpit pressure Changing Pattern is identical with height change rule with air pressure, but owing to exhaust valve for cabin exists certain flow resistance,
So cockpit pressure exceeds a fixing difference than atmospheric pressure out of my cabin always, i.e. there is certain overbottom pressure in passenger cabin.
(2) the absolute pressure regulation stage
When flying height is positioned at H1～H2In altitude range, enter the absolute pressure regulation stage, adjust according to pressure Rule adjusting
Whole cockpit pressure.In this stage, when the force value that cockpit pressure specifies higher than current flight height, by cockpit pressure controller
In absolute pressure governor motion control exhaust valve for cabin aperture increase so that cockpit pressure returns to setting；Work as seat
During the force value that cabin pressure specifies less than current flight height, then by the absolute pressure adjustment structure control in cockpit pressure controller
The aperture of exhaust valve for cabin processed reduces so that cockpit pressure returns to setting.In this stage, due to passenger cabin overbottom pressure (i.e. seat
The difference of cabin pressure atmospheric pressure outer with passenger cabin) less than setting A, the overbottom pressure controlling organization in cockpit pressure controller does not acts as
With.
(3) the residual compression regulation stage
When flying height is more than or equal to H2Time, the overbottom pressure such as entrance residual compression regulates the stage, cockpit pressure holding.On these rank
Section, when passenger cabin overbottom pressure exceedes setting A constantly, the overbottom pressure controlling organization in cockpit pressure controller is started working, and absolute pressure
Power governor motion no longer plays regulation effect.By the overbottom pressure controlling organization in cockpit pressure controller, control passenger cabin aerofluxus and live
The aperture of door increases so that passenger cabin overbottom pressure reduces, and returns to setting A；When passenger cabin overbottom pressure is less than setting A, control seat
The aperture of cabin exhaust valve reduces so that passenger cabin overbottom pressure raises, and returns to setting A.
The analysis found that, the most common failure of the cockpit pressure regulating system of this type aircraft includes:
(1) system power supply is undesirable, causes parts cisco unity malfunction or damage, so that affecting the normal of system
Work；
(2) draw because of cockpit pressure controller, cabin pressure regulator exhaust valve for cabin or cabin safety valve fault
" amount of leakage is overproof " risen；
(3) draw because of cockpit pressure controller, cabin pressure regulator exhaust valve for cabin or cabin safety valve fault
" overbottom pressure is overproof " risen；
(4) in case of emergency " passenger cabin cannot fast aeration or venting " caused because of cabin safety valve fault.
By further analyzing, for above most common failure, needs are test following items during detection:
(1) test of the voltage and current of the voltage of alternating current power supply, electric current and frequency and DC source；
(2) two airtight boiler-plates are built, analog capsule cabin and out of my cabin air respectively, and seat can be controlled by program
The ginseng such as atmospheric pressure, passenger cabin overbottom pressure, elevation rate under cabin boiler-plate pressure, out of my cabin atmospheric simulation cabin pressure, and certain height
Number, thus realize the simulation of the various working condition to cockpit pressure regulating system；
(3) cockpit pressure regulating system is operated in low latitude free ventilating stage passenger cabin overbottom pressure, and is operated in absolute pressure
Regulation stage and residual compression regulation stage passenger cabin overbottom pressure, the test of cockpit pressure grade；
(4) analog capsule cabin pressure controller breaks down and quits work, the work to the overbottom pressure limiter of cabin safety valve
Test as situation；
(5) simulated aircraft generation emergency, is capable of emergency decompression to cabin safety valve and tests.
For the most common failure of military cockpit pressure regulating system with project need to be detected, the utility model proposes
Plant the detection equipment for military cockpit pressure regulating system, specifically include supply module, power supply test module, passenger cabin mould
Intending cabin, out of my cabin atmospheric simulation cabin, input module, display module and control unit, its composition and annexation are as shown in Figure 1.
(1) supply module, the alternating current power supply needed for providing for detection equipment and DC source, the power supply used by equipment under test
Also it is to be provided by this supply module.In the present embodiment, alternating current (the i.e. city that input power is 220V 50Hz of equipment is detected
Electricity), it is mainly in view of civil power and the most all can take, the most convenient；For detection equipment using the equipment of civil power can be direct
Use, and for detection equipment uses DC installation and the alternating-current installation/AC installation of other power specifications, then need through conversion
For using again, this supply module is also provided with power conversion unit, the civil power of 220V can be converted to 28V, 24V and 5V
Power supply used by the equipment under tests such as unidirectional current.
(2) power supply test module, the voltage of alternating current power supply, electric current and the frequency that supply module is provided and DC source
Voltage and current test, be attached by circuit with supply module.In the present embodiment, specifically 220V (is i.e. examined
The input power of measurement equipment) voltage of alternating current power supply, electric current and frequency, and the voltage of 28V, 24V and 5V DC source and electricity
The aircraft airborne power supply of stream equal-specification is tested, and its object is to: when unit under test breaks down, first pass through power supply
The problem that test module row is brought because power supply is undesirable except aircraft airborne power supply.In order to simplify detection equipment line and
The complexity of system, the power supply test module in the present embodiment uses test and shows two-in-one instrument, the knot of power supply test
Fruit directly shows on the LED display curtain of described instrument.DC source and alternating current power supply respectively use a test and show
Show that two-in-one instrument carries out test and the display of power parameter.
(3) car simulation cabin, for the supply of simulated aircraft passenger cabin with through pressure controlled closed environment.Car simulation
Cabin is made up of car simulation room 2, pneumatic supply and the first pressure transducer 4.Wherein car simulation room 2 is made up of nacelle and hatch door,
Nacelle is square, it is simple to processing, and makes full use of space；Observation window is set on hatch door, it is simple to observe quilt in passenger cabin simulating chamber 2
The situation of measurement equipment；The Guan Bi degree of tightness of hatch door can regulate, and arranges sealing ring, thus ensure car simulation between nacelle and hatch door
The sealing of room 2.Wherein pneumatic supply is by source of the gas the 31, first air filter 32, first flow valve the 33, first electromagnetic valve 34,35 groups of effusion meter
Become, (when purpose is need not measurement of discharge, effusion meter is isolated, to improve flow except effusion meter 35 is in parallel with independent gas circuit
The life-span of meter, and ensure its measuring accuracy) outward, other each parts are sequentially connected with by gas circuit, the most as shown in Figure 2；First-class
Amount valve the 33, first electromagnetic valve 34, effusion meter 35 are attached with control unit by circuit respectively；Source of the gas 31 compresses for air
Machine, if outfield is not equipped with air compressor, it is possible to use air bottle；First electromagnetic valve 34 is two-bit triplet electromagnetic valve.The
One pressure transducer 4 is arranged in car simulation room 2, experiences the pressure of car simulation room 2, pressure transducer 4 by circuit with
Control unit is attached.
(4) atmospheric simulation cabin out of my cabin, for the simulated aircraft air pressure out of my cabin when differing heights flight.Atmospheric simulation out of my cabin
Cabin is made up of atmospheric simulation room 5 out of my cabin, negative pressure source and the second pressure transducer 7.The structure of atmospheric simulation room 5 and seat the most out of my cabin
The structure of cabin simulating chamber 2 is identical.Wherein negative pressure source is formed by negative pressure branch road and air branch circuit parallel connection；Negative pressure props up route vacuum pump
61, second flow valve the 62, second electromagnetic valve 63 forms, and each parts are sequentially connected with by gas circuit, second flow valve 62 and the second electricity
Magnet valve 63 is attached with control unit by circuit respectively；Second air filter 64, the second air filter 64 and are set on air branch road
Two electromagnetic valves 63 connect, and the second electromagnetic valve 63 is connected with atmospheric simulation room 5 out of my cabin, in order to realize equipment under test by gas circuit again
Whole-process automatic test, the second electromagnetic valve 63 selects two-bit triplet electromagnetic valve；The composition of negative pressure source and annexation are concrete also such as Fig. 2
Shown in.Pressure transducer 7 is arranged on out of my cabin in atmospheric simulation room 5, experiences the pressure of atmospheric simulation room 5 out of my cabin, by circuit with
Control unit is attached.The room of atmospheric simulation out of my cabin 5 in atmospheric simulation cabin is by connecting the seat of gas circuit and car simulation cabin out of my cabin
Cabin simulating chamber 2 connects, and arranges valve connecting in gas circuit, and valve can control to connect the break-make of gas circuit, thus realizes tested
The test of equipment difference test event.This connection gas circuit is two, and two connection gas circuits are respectively provided with valve, and this valve is specially
The electromagnetic valve 1 of 3-position 4-way, the type of electromagnetic valve 1 is concrete as shown in Figure 2.
For the ease of arranging and using, car simulation room 2 and out of my cabin atmospheric simulation room 5 use mode setting up and down, and
Out of my cabin, the bottom of atmospheric simulation room 5 is provided with the universal caster wheel of brake, in order to detect the shifting of equipment in line
Dynamic.
(5) input module, for interacting with detection equipment, typing information, selection test event.In the present embodiment
Input module is specially the matrix keyboard of 4 × 4, in keyboard in addition to the numeral keys such as 0～9 is set, be also provided with key, lower key,
Key used substantially by acknowledgement key and return key etc..Input module uses the goods shelf products of standard, while meeting input requirements, also may be used
To reduce the cost of detection equipment.
(6) display module, function menu, operation indicating and test result.In order to reach wieldy purpose, aobvious
Showing that module uses the dot matrix type liquid crystal display that can show Chinese, operator can carry out detection behaviour according to the operation indicating of display
Make.Display module in the present embodiment is specially the liquid crystal display of 192 × 64, and this display is digital liquid crystal display,
It is easy to and controls the part control that is connected and shows, and possess that volume is little, low in energy consumption, display quality high.
(7) control unit, for detecting the Control & data acquisition of equipment, respectively with supply module, power supply test module,
Car simulation cabin, out of my cabin atmospheric simulation cabin, input module and display module are attached by circuit.
Control unit in the present embodiment uses the single-chip microcomputer with 60K byte program memorizer, its dependable performance, just
Display in Chinese prompt information；And with EEPROM, the storage of convenient detection data and reading.Control unit uses with light
The RS485 bus of electric isolution and power supply test module, first pressure transducer the 4, second pressure transducer 7, effusion meter 35, first
Flow valve 33, second flow valve the 62, first electromagnetic valve the 34, second electromagnetic valve 63, the electromagnetic valve 1 of 3-position 4-way communicate.Adopt
It is the noise jamming in order to reduce power supply with Phototube Coupling, improves stability and the accuracy of detection of system；RS485 bus is used to enter
Row communication, then be to suppress common mode disturbances, improves the detection sensitivity etc. during signal transmission.
Detection equipment in the present embodiment employs substantial amounts of electromagnetic valve, its object is to realize equipment under test and is controlling list
Switch freely between multiple test event under the control of unit, thus realize testing the automatization of overall process, improve the effect of test
Rate.
In order to more clearly introduce military cockpit pressure regulating system outfield the detection composition of equipment, the company of each parts
Connecing relation, below in conjunction with the process of test, brief description once detects the using method of equipment.
Embodiment 1:
Passenger cabin overbottom pressure test under cabin safety valve isolation, under differing heights
Before detection, first connect detection equipment and cockpit pressure controller, exhaust valve for cabin and cabin safety valve etc.
Equipment under test.Main connection includes: tested cockpit pressure controller and tested exhaust valve for cabin are placed on car simulation room 2
In, tested cockpit pressure controller and tested exhaust valve for cabin respectively with detection equipment supply module by circuit carry out company
Connect, be attached by circuit between tested cockpit pressure controller and tested exhaust valve for cabin, and by tested passenger cabin aerofluxus
Valve is attached with " two left being connected in gas circuit between car simulation room 2 and out of my cabin atmospheric simulation room 5 " by gas circuit；Quilt
Survey cabin safety valve to be placed on out of my cabin in atmospheric simulation room 5, tested cabin safety valve is entered with supply module by circuit
Row connects, and is carried out with " two right wings being connected in gas circuit between car simulation room 2 and out of my cabin atmospheric simulation room 5 " even by gas circuit
Connect.
After completing the connection of detection equipment and equipment under test, give alternating current (the i.e. city of detection supply of equipment 220V 50Hz
Electricity), then select equipment under test and test event by the matrix keyboard of 4 × 4, and start detection.
By control unit by car simulation room 2 and two 3-position 4-ways connected in gas circuits between atmospheric simulation room 5 out of my cabin
Electromagnetic valve 1 switched to the left position in Fig. 2 by neutral position, i.e. connect car simulation room 2 He by tested exhaust valve for cabin
Atmospheric simulation room 5 out of my cabin, and disconnect the connection of tested cabin safety valve and car simulation room 2.Be equivalent to isolate tested passenger cabin
Safety valve, the overbottom pressure of passenger cabin when detecting tested cockpit pressure controller and the work of tested exhaust valve for cabin.Isolation is surveyed
Examination, can be used for being accurately positioned fault part.Second electromagnetic valve 63 switches to right position, connection negative pressure branch road and out of my cabin atmospheric simulation room 5,
Control unit, according to the height set, builds the subnormal ambient of atmospheric simulation room 5 out of my cabin, out of my cabin the pressure of atmospheric simulation room 5 with
The atmospheric pressure of corresponding flying height is consistent.
First electromagnetic valve 34 switches to left position, adjusts flow valve 34 and regulates the size of air demand, by the source of the gas of pneumatic supply
31, air filter 32, flow valve 33 and electromagnetic valve 34, supply to car simulation room 2.Control unit is according to the height set, to tested
Cockpit pressure controller sends control signal, tested cockpit pressure controller and then the pressure according to car simulation room 2, adjusts quilt
Survey the aperture of exhaust valve for cabin, the gas in car simulation room 2 through tested exhaust valve for cabin, out of my cabin atmospheric simulation room 5, the
Two electromagnetic valves 63, second flow valve 62 and vacuum pump 61 drain into air.Treat the pressure of car simulation room 2 and atmospheric simulation room 5 out of my cabin
After power is stable, is measured the pressure of car simulation room 2 by pressure transducer 4, and measure air mould out of my cabin by pressure transducer 7
Intend the pressure of room 5, and calculated overbottom pressure by control unit, on display module, then show corresponding overbottom pressure numerical value.
After having tested, by control unit, the second electromagnetic valve 63 is connected air branch road, by atmospheric simulation room 5 out of my cabin
Subnormal ambient reverts to normal pressure, in order to open the hatch door of atmospheric simulation room out of my cabin.
Embodiment 2:
Passenger cabin overbottom pressure test under cabin safety valve access state, under differing heights
The gas circuit of this test and the method for attachment of circuit are substantially the same manner as Example 1, main difference is that: by controlling
Unit is by car simulation room 2 and the electromagnetic valve 1 of two 3-position 4-ways connected in gas circuits switches to figure between atmospheric simulation room 5 out of my cabin
Neutral position in 2, accesses detection equipment by tested cabin safety valve, tests under all measured piece access states, and passenger cabin exists
Overbottom pressure under differing heights.
Embodiment 3:
Exhaust valve for cabin leakage test
The gas circuit of this test and the method for attachment of circuit are same as in Example 1, main difference is that: at a certain simulation height
Under degree, electromagnetic valve 33 is switched to right position, effusion meter 35 is accessed gas circuit, after the pressure stability of car simulation room 2, by stream
Whether gauge 35 can record under present level the amount of leakage of tested exhaust valve for cabin beyond requiring.
Embodiment 4:
Passenger cabin emergency pressure relief performance test
The gas circuit of this test and the method for attachment of circuit are substantially the same manner as Example 1, main difference is that: by controlling
Unit is by car simulation room 2 and the electromagnetic valve 1 of two 3-position 4-ways connected in gas circuits switches to figure between atmospheric simulation room 5 out of my cabin
Right position in 2, accesses detection equipment by tested cabin safety valve；By control unit, the second electromagnetic valve 63 is connected air to prop up
Road.
Under a certain simulated altitude, by control unit control pneumatic supply to car simulation room 2 voltage supply, reach for pressure pressure
Cabin safety valve opens pressure, and whether the emergency pressure relief performance of test cabin safety valve meets requirement.
The test of other test event, similar with the test mode in above-described embodiment, it is only necessary to adjust three according to demand
The position of individual valve core of the electromagnetic valve, builds the pressure of corresponding car simulation room 2 and atmospheric simulation room 5 out of my cabin, then tests
?.
This detection equipment is possible not only to realize the test to cockpit pressure regulating system, but also can analog demenstration passenger cabin
The various duties of pressure regulating system, are used for equipping the purposes such as teaching.
The detection equipment for military cockpit pressure regulating system involved by this utility model, can be applicable to multiple
The detection of the cockpit pressure regulating system of model aircraft, as long as its cockpit pressure regulating system is by cockpit pressure controller, passenger cabin
The department enclosure such as exhaust valve and cabin safety valve forms；Closing two for cockpit pressure controller and exhaust valve for cabin is
The cockpit pressure regulating system of one, this detection equipment is equally applicable, only in equipment under test and the detection gas circuit of equipment and circuit
The mode of connection carries out accommodation.
Claims (10)
1. the detection equipment for military cockpit pressure regulating system, it is characterised in that including:
Supply module, the alternating current power supply needed for providing for detection equipment and DC source；
Power supply test module, voltage, electric current and frequency and the voltage and current of described DC source to described alternating current power supply
Test, be attached by circuit with described supply module；
Car simulation cabin, for the supply of simulated aircraft passenger cabin with through pressure controlled closed environment；
Atmospheric simulation cabin out of my cabin, for the simulated aircraft air pressure out of my cabin when differing heights flight, atmospheric simulation cabin is passed through out of my cabin
Connect gas circuit to connect with car simulation cabin, and connecting, in gas circuit, valve is set；
Input module, for interacting with detection equipment, typing information, selection test event；
Display module, function menu, operation indicating and test result；
Control unit, for detecting the Control & data acquisition of equipment, respectively with described supply module, power supply test module,
Car simulation cabin, out of my cabin atmospheric simulation cabin, input module and display module are attached by circuit.
Detect equipment the most as claimed in claim 1, it is characterised in that described car simulation cabin and described atmospheric simulation cabin out of my cabin
Between connection gas circuit be two, two connect in gas circuits and are respectively provided with valve.
Detect equipment the most as claimed in claim 2, it is characterised in that two connect the valve arranged in gas circuit is 3-position 4-way
Electromagnetic valve (1).
Detect equipment the most as claimed in claim 1, it is characterised in that described car simulation cabin and described atmospheric simulation cabin out of my cabin
Formed by nacelle and hatch door, silicone rubber O-ring is set between nacelle and hatch door, hatch door is respectively provided with observation window.
5. the detection equipment as described in claims 1 to 3 is arbitrary, it is characterised in that described car simulation cabin is by car simulation room
(2), pneumatic supply and the first pressure transducer (4) composition；Wherein pneumatic supply is by source of the gas (31), the first air filter (32), first flow
Valve (33), the first electromagnetic valve (34), effusion meter (35) form, in addition to effusion meter (35) is in parallel with independent gas circuit, and other each portion
Part is sequentially connected with by gas circuit, and first flow valve (33), the first electromagnetic valve (34), effusion meter (35) are respectively by circuit and control
Unit is attached；First pressure transducer (4) is arranged in car simulation room (2), is carried out even by circuit and control unit
Connect.
Detect equipment the most as claimed in claim 5, it is characterised in that described source of the gas (31) is air compressor or air bottle.
Detect equipment the most as claimed in claim 5, it is characterised in that described first electromagnetic valve (34) is two-bit triplet electromagnetism
Valve.
8. the detection equipment as described in claims 1 to 3 is arbitrary, it is characterised in that the described cabin of atmospheric simulation out of my cabin is by the biggest
Gas simulating chamber (5), negative pressure source and the second pressure transducer (7) composition；Wherein negative pressure source is by negative pressure branch road and air branch circuit parallel connection
Form；Negative pressure props up route vacuum pump (61), second flow valve (62), the second electromagnetic valve (63) composition, and each parts are depended on by gas circuit
Secondary connection, second flow valve (62) and the second electromagnetic valve (63) are attached with control unit by circuit respectively；Air branch road
On the second air filter (64) is set, the second air filter (64) is connected with the second electromagnetic valve (63) by gas circuit；Second pressure transducer (7)
It is arranged on out of my cabin in atmospheric simulation room (5), is attached with control unit by circuit.
Detect equipment the most as claimed in claim 8, it is characterised in that described second electromagnetic valve (52) is two-bit triplet electromagnetism
Valve.
Detect equipment the most as claimed in claim 1, it is characterised in that described power supply test module uses test and display two
The instrument of unification, the result of power supply test directly shows in described instrument.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620670217.8U CN205750521U (en) | 2016-06-29 | 2016-06-29 | A kind of detection equipment for military cockpit pressure regulating system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620670217.8U CN205750521U (en) | 2016-06-29 | 2016-06-29 | A kind of detection equipment for military cockpit pressure regulating system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205750521U true CN205750521U (en) | 2016-11-30 |
Family
ID=57381979
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620670217.8U Active CN205750521U (en) | 2016-06-29 | 2016-06-29 | A kind of detection equipment for military cockpit pressure regulating system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205750521U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106249731A (en) * | 2016-06-29 | 2016-12-21 | 赵红军 | A kind of military cockpit pressure regulating system outfield detection device |
| CN107608336A (en) * | 2017-09-18 | 2018-01-19 | 沈阳飞机工业（集团）有限公司 | A kind of cabin pressure regulator ground experiment control device |
-
2016
- 2016-06-29 CN CN201620670217.8U patent/CN205750521U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106249731A (en) * | 2016-06-29 | 2016-12-21 | 赵红军 | A kind of military cockpit pressure regulating system outfield detection device |
| CN107608336A (en) * | 2017-09-18 | 2018-01-19 | 沈阳飞机工业（集团）有限公司 | A kind of cabin pressure regulator ground experiment control device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106249731A (en) | A kind of military cockpit pressure regulating system outfield detection device | |
| US5544842A (en) | Apparatus and method for the conversion of a three crew member aircraft cockpit to a two crew member aircraft cockpit | |
| CA2477025C (en) | Instrumentation and control circuit having multiple, dissimilar sources for supplying warnings, indications and controls, and an integrated cabin pressure control system valve incorporating the same | |
| EP0080849A2 (en) | Enclosure pressurisation control system | |
| CN205750521U (en) | A kind of detection equipment for military cockpit pressure regulating system | |
| US5480109A (en) | System for preventing the automatic opening of an improperly closed and locked aircraft door | |
| EP2214791B1 (en) | Test equipment and method for testing an aircraft oxygen system control device | |
| CN106772008B (en) | Pressure-controllable SF6 gas density relay signal simulation tester | |
| US11603206B2 (en) | Cabin pressure control system with all-electric OFV, using dis-similar manual control that performs cabin altitude hold function | |
| CN105352735A (en) | Engine plateau air inlet simulation device | |
| KR100470120B1 (en) | Cabin pressure control system, method of controlling the actual pressure inside a cabin and outflow valve | |
| CN103344499B (en) | Passenger plane fuselage pressure and tightness test equipment | |
| CN106005476B (en) | Electronic type supplies oxygen antiacceleration regulator ground detector and detection method | |
| CN104460659B (en) | A kind of military cockpit air handling system outfield detection method | |
| US7008314B2 (en) | Aircraft modular cabin pressure regulator | |
| CN205906232U (en) | Electronic type oxygen suppliment antiacceleration regulator ground test instrument | |
| CN203486150U (en) | Air leakage tester | |
| BR102018074609A2 (en) | AIR CONDITIONING SYSTEM FOR AN AIRCRAFT | |
| CN109580120A (en) | A kind of monitoring method of undercarriage buffer | |
| CN205854539U (en) | Sealed compartment | |
| CN106081160A (en) | A kind of aircraft housing unit passenger cabin inside and outside differential pressure simulation test device and method | |
| RU2438734C1 (en) | Tester amd method of testing aircraft oxygen feed system control device | |
| CN108341074B (en) | 2600M Temperature Regulator Calibrator | |
| CN108279134A (en) | Universal on-board oxygen equipment simulating experimental rig | |
| CN212624457U (en) | Atmospheric data tester for teaching |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190725 Address after: 264000 13th Floor, Building B3, No. 7 Tongshi South Road, Zhifu District, Yantai City, Shandong Province Patentee after: Shandong Shoujinghui Photoelectric Technology Co., Ltd. Address before: 264007 equipment department, 91213 Laishan airport, Laishan District, Yantai, Shandong Patentee before: Zhao Hongjun |