CN104062110B - Aircraft liquid cold pipe-line system flow ground scaling method - Google Patents

Aircraft liquid cold pipe-line system flow ground scaling method Download PDF

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CN104062110B
CN104062110B CN201410259552.4A CN201410259552A CN104062110B CN 104062110 B CN104062110 B CN 104062110B CN 201410259552 A CN201410259552 A CN 201410259552A CN 104062110 B CN104062110 B CN 104062110B
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pipeline
flow
aircraft
temperature
rotation platform
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CN104062110A (en
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施红
赵颖杰
蔡玉飞
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Jiangsu University of Science and Technology
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Abstract

The invention discloses a kind of aircraft liquid cold pipe-line system flow ground scaling method, belong to aircraft liquid pipeline system field of measuring technique.The principle that the method utilizes the reducer pipe in aircraft liquid cooling system pipeline or elbow to produce pressure reduction carries out on ground demarcating thus obtains the flow of liquid cooling system pipeline.Fluid circulation system, parameter measurement system and data collecting system that the caliberating device that described method uses by rotation platform and is installed on rotation platform form；Acceleration that wherein rotation platform is awing subject in order to simulate pipe-line system, the pressure and temperature effect of tube fluid.This method can be implemented in the demarcation of the aircraft liquid cooling system piping flow carried out on ground under flight load function, has simple in construction, little to original pipeline system destruction, controllability good, safety advantages of higher.

Description

Aircraft liquid cold pipe-line system flow ground scaling method
Art
The present invention relates to a kind of aircraft liquid cold pipe-line system flow ground scaling method, belong to aircraft liquid line and measure skill Art field.
Background technology
In recent years, aircraft equipment there occurs huge change, and the application of air environment is more and more extensive, electronic compartment heat Load sharply increases, and thermic load produced by it increases to tens kilowatts from original several kilowatts.These electronic device works Time, on the one hand in addition to launching a small amount of power, the input power of 70%～90% is all transformed to heat；On the other hand, Along with electronic device is to integrated, the trend of miniaturization, electronic device power increases, packaging density increases, volume-diminished, The heat flow density causing electronic equipment steeply rises.If these heats can not be cooled down in time, electronics will be directly affected and set Standby normal work, even causes the destruction of electronic equipment.Therefore, air environment under heat density high-power, high is solved Cooling is a problem the most crucial in Special Aircraft environmental Kuznets Curves, is also a Special Aircraft important guarantor completing mission Card.But, traditional air cooling faces various problems: be first that electromotor is not provided that excessive amount of air entrainment；Secondly, air Cooling line is difficult to arrange in electronic equipment internal；It addition, air can not meet high heat flux heat exchange as cooling medium Requirement.And liquid is big more than air due to its coefficient of heat transfer and specific heat, liquid-cooling system has higher cooling effectiveness and steady Fixed ability to work.Therefore, liquid-cooling system becomes inevitable for the electronic equipment dissipating heat of modern high performance aircraft.
The key property parameter of liquid cooling system is in addition to temperature and pressure, and the flow of refrigerating fluid is also an important design Parameter, its acquisition is mainly measured by experiment.Traditional liquid flow measuring method has a lot, but is implemented with one aboard , there is leakage, by many unfavorable factors such as flight operating mode restrictions, it is therefore necessary to find the measurement of a kind of safe and feasible in fixed difficulty And scaling method.
The research of Domestic Aircraft liquid cooling system is at the early-stage, and technology is not perfect, and the liquid flow measuring method related to is also Seldom, the test equipment volume that ground experiment uses is difficult to more greatly implement aboard, and the most external relevant report is the fewest And the Cost Problems of equipment also can be related to when coming into operation.
In view of the foregoing, it is an object of the invention to provide a kind of simple in construction, aircraft liquid cooling system stream easy for installation The measuring method of amount, and be modified demarcating, for aircraft liquid cooling system flow to the flow of liquid cryogen by correction factor method Measure and calculate and Technical Reference is provided.
Summary of the invention
Goal of the invention: it is an object of the invention to, in order to realize the measurement of piping flow parameter in airborne liquid cooling system, carry For a kind of simple in construction, original structure is destroyed little aircraft liquid cold pipe-line system flow ground scaling method.
For achieving the above object, the present invention adopts the following technical scheme that
A kind of aircraft liquid cold pipe-line system flow ground scaling method of the present invention, the ground installation of use, including rotating Platform and the flow calibration blood circulation being installed on described rotation platform, wherein,
Described rotation platform includes turntable, motor and converter, and turntable described in described motor-driven rotates, described change Frequently device is connected with motor, for controlling the rotating speed of motor；
Described flow calibration blood circulation includes fluid circulation system, parameter measurement system and data collecting system, wherein,
Described fluid circulation system includes water tank, pump, heater, filter, test section, imported valve and outlet valve； Described water tank, pump, filter, heater, imported valve, test section and outlet valve are sequentially connected by pipeline, described water tank Outlet is connected with described pump by pipeline, and described outlet valve is connected with the water return outlet of water tank by pipeline；
Described parameter measurement system includes effusion meter, temperature sensor and pressure transducer, described effusion meter, temperature sensing Device and pressure transducer are respectively arranged in before and after described test section on the pipeline of position；
Described data collecting system includes computer and the data acquisition module being connected with described parameter measurement system.
The a kind of of the present invention uses aircraft liquid cold pipe-line system flow ground scaling method, comprises the following steps:
Utilize the flight load that rotation platform simulation liquid pipeline system is suffered awing, wherein rotated by regulation The rotating speed of platform realizes different magnitudes of load, obtains loading direction by the arranged direction of test section；
Described flow calibration blood circulation is installed on turntable, to realize measuring real time record and the preservation of parameter.
Further, comprise the following steps: realize liquid temperature different in test section by the power of regulation heater Degree；Pressure different in described fluid circulation system pipeline is realized by the aperture of regulation outlet valve.
Further, comprise the following steps: choose the variable diameters in aircraft liquid pipeline system or elbow pipeline as examination Testing part, the demarcation carried out testpieces under different acceleration, pressure and temperature by ground flow rating test platform is obtained The discharge characteristic of testpieces.
Further, comprise the following steps:
When carrying out flow calibration experiment, the centrifugal force direction of test section position is considered as the heading of aircraft；
The acceleration a of calibration experiment accomplishes+6g from-6g, is spaced apart 1g；Temperature T according to the operating temperature of coolant from Low temperature accomplishes maximum temperature, is spaced 5 DEG C；Pressure reduction P to 50kPa, is spaced apart 5kPa from 0；
Recording the flow under different acceleration, temperature and pressure, set up data on flows storehouse, the flow of testpieces is ternary Function: Q=f (ai,Tj,Pk)；
The then flow function of pipeline during real aircraft:
f(am,Tp,Pq)=f (ai+α,Tj+β,Pk+ γ),
Wherein, α, beta, gamma is a dimensionless, am,Tp,PqIt is respectively the acceleration that the measurement during real aircraft draws Degree, temperature and pressure reduction, ai,Tj,pkFor some point in experiment parameter, this point and am,Tp,PqClosest, i.e.
(am-ai)2+(Tp-Tj)2+(Pq-Pk)2≤(am-ai')2+(Tp-Tj')2+(Pq-Pk')2,
In formula: ai',Tj',pk' it is any one point in experiment；
Utilize the Taylor expansion of three element complex:
f ( a i + α , T j + β , P k + γ ) = f ( a i , T j , P k ) + 1 1 ! ( h ∂ ∂ a + k ∂ ∂ T + l ∂ ∂ P ) f ( a i , T j , P k ) + 1 2 ! ( h ∂ ∂ a + k ∂ ∂ T + l ∂ ∂ P ) 2 f ( a i , T j , P k ) + 1 3 ! ( h ∂ ∂ a + k ∂ ∂ T + l ∂ ∂ P ) 3 f ( a i , T j , P k ) + .... + 1 n ! ( h ∂ ∂ a + k ∂ ∂ T + l ∂ ∂ P ) n f ( a i , T j , P k )
Take 2 on the right of formula, as increase precision can increase successively the right item number, therefore,
Q = f ( a i , T j , P k ) + ( h ∂ ∂ a + k ∂ ∂ T + l ∂ ∂ P ) f ( a i , T j , P k ) ,
Wherein:
Said process obtains the discharge characteristic under testpieces full working scope.
Beneficial effects of the present invention:
The method is suitably applied the flow calibration of aircraft liquid pipeline system, measures with other aircraft liquid line flow Method is compared, have simple and reliable, original structure is destroyed the advantage such as little.This device is in order to realize liquid line at flight course In be subject to acceleration, temperature and pressure load, this device has that compact conformation, controllability be good, safety advantages of higher.
Accompanying drawing explanation
Fig. 1 is the structure principle chart of the present invention；
Fig. 2 is the side view of the present invention；
Wherein, 1 water tank, 2 pumps, 3 filters, 4 heaters, 5 effusion meters, 6 pressure transducers, 7 imported valves, 8 outlet valves Door, 9 temperature sensors, 10 test sections, 11 data acquisition modules, 12 computers, 13 turntables, 14 bearings, 15 motor, 16 frequency conversions Device, 17 protection wire gauzes, 18 belts.
Detailed description of the invention
Purpose and technical scheme for making the embodiment of the present invention are clearer, attached below in conjunction with the embodiment of the present invention Figure, is clearly and completely described the technical scheme of the embodiment of the present invention.Obviously, described embodiment is the present invention A part of embodiment rather than whole embodiments.Based on described embodiments of the invention, those of ordinary skill in the art The every other embodiment obtained on the premise of without creative work, broadly falls into the scope of protection of the invention.
Those skilled in the art of the present technique are appreciated that unless otherwise defined, and all terms used herein (include technology art Language and scientific terminology) have with the those of ordinary skill in art of the present invention be commonly understood by identical meaning.Also should Being understood by, those terms defined in such as general dictionary should be understood that the meaning having with the context of prior art The meaning that justice is consistent, and unless defined as here, will not explain by idealization or the most formal implication.
The implication of heretofore described "and/or" refers to respective individualism or both simultaneous situations are all wrapped Including including.
The implication of heretofore described " inside and outside " refers to relative to equipment itself, the side within sensing equipment To for interior, otherwise it is outward, rather than the specific restriction to assembly of the invention mechanism.
When the implication of heretofore described " left and right " refers to reader just to accompanying drawing, the left side of reader is a left side, The right of reader is the right side, rather than the specific restriction to assembly of the invention mechanism.
The implication of heretofore described " connection " can be being directly connected between parts can also be to pass through between parts Being indirectly connected with of other parts.
Embodiment:
A kind of flight load of the present invention is got off the plane liquid cold pipe-line system flow ground scaling method, is come by ground experiment The flow of pipeline during demarcating original reducer pipe in liquid cooling system or elbow thus obtaining practical flight.Traditional differential pressure Formula flow measuring meter has the straight length of certain length before and after needing to increase restricting element in pipeline and require restricting element.So And, installing throttling arrangement on the pipeline of liquid cooling system additional can affect the flow resistance characteristic of whole system, refers to from the technology of liquid cooling system Mark, it can be seen that the inlet pressure of radar component is about 800kPa, configures a restricting element and may produce 40kPa, even more The big pressure loss, impacts the performance of system, and system may be caused time serious to circulate；In addition throttling arrangement is installed additional Add the probability of refrigerating fluid leakage.Meanwhile, on aircraft, the pipe arrangement of liquid cooling system typically obeys other critical pieces Configuration therefore its pipeline elbow is more, it is impossible to the length requirement of straight length before and after guarantee throttling element.Therefore, the stream of aircraft refrigeration liquid Amount can be used for reference differential pressure type flow instrument and measure the principle of fluid flow, is produced by reducer pipe original in pipe-line system or elbow Differential pressure principle, carries out ground calibration experiment to it, obtains outflow along with pressure reduction, temperature, the delta data storehouse of acceleration.Entering During the experiment of row flow calibration, the centrifugal force direction of test section position is considered as the heading of aircraft.
The acceleration a of calibration experiment accomplishes+6g from-6g, is spaced apart 1g；Temperature T according to the operating temperature of coolant from Low temperature accomplishes maximum temperature, is spaced 5 DEG C；Pressure reduction P to 50kPa, is spaced apart 5kPa from 0.Record different acceleration, temperature and Flow under pressure, sets up data on flows storehouse.
From said process, the flow of testpieces is three element complex: Q=f (ai,Tj,Pk)。
Then during real aircraft, the flow of pipeline can be written as such function:
f(am,Tp,Pq)=f (ai+α,Tj+β,Pk+γ)
Wherein, α, beta, gamma is a dimensionless, am,Tp,PqIt is respectively the acceleration that the measurement during real aircraft draws Degree, temperature and pressure reduction, ai,Tj,pkFor some point in experiment parameter, this point and am,Tp,PqClosest i.e.,
(am-ai)2+(Tp-Tj)2+(Pq-Pk)2≤(am-ai')2+(Tp-Tj')2+(Pq-Pk')2
In formula: ai',Tj',pk' it is any one point in experiment.
Utilize the Taylor expansion of three element complex:
f ( a i + α , T j + β , P k + γ ) = f ( a i , T j , P k ) + 1 1 ! ( h ∂ ∂ a + k ∂ ∂ T + l ∂ ∂ P ) f ( a i , T j , P k ) + 1 2 ! ( h ∂ ∂ a + k ∂ ∂ T + l ∂ ∂ P ) 2 f ( a i , T j , P k ) + 1 3 ! ( h ∂ ∂ a + k ∂ ∂ T + l ∂ ∂ P ) 3 f ( a i , T j , P k ) + .... + 1 n ! ( h ∂ ∂ a + k ∂ ∂ T + l ∂ ∂ P ) n f ( a i , T j , P k )
Take 2 on the right of formula, as increase precision can increase successively the right item number, therefore,
Q = f ( a i , T j , P k ) + ( h ∂ ∂ a + k ∂ ∂ T + l ∂ ∂ P ) f ( a i , T j , P k )
Wherein:
Said process can obtain the discharge characteristic under testpieces full working scope.
A kind of flight load of the present invention is got off the plane liquid cold pipe-line system flow ground caliberating device, as it is shown in figure 1, mainly It is in order to the cold pipeline of simulated aircraft liquid load subjected to and overpressure and variations in temperature in flight course, and by this dress Put the reducer pipe in pipe-line system cold to aircraft liquid or elbow is demarcated.
This device is made up of rotation platform and the flow calibration blood circulation that is installed on rotation platform.
Above-mentioned rotation platform is made up of turntable 13, motor 15, converter 16.
Above-mentioned flow calibration blood circulation is made up of fluid circulation system, parameter measurement system and data collecting system.
Aforesaid liquid blood circulation is by water tank 1, pump 2, heater 4, filter 3, test section 10, imported valve 7, outlet valve Door 8 composition.Wherein water tank 1 outlet by pipeline successively with pump 2, filter 3, heater 4, imported valve 7, test section 10, Outlet valve 8 is connected, and outlet valve 8 is connected with the water return outlet of water tank 1 by pipeline.
The high speed rotating of above-mentioned rotation platform needs whole platform structure firm, stable, and therefore platform is mainly built by cement Become.As in figure 2 it is shown, motor 15 and converter 16 are all bolted on ground, turntable 13 is by bearing 14, belt 18 It is connected with motor 15.Motor 15 is by belt 18 band dynamic bearing high speed rotating, and then the turntable 13 being connected with bearing 14 is high Speed rotates.Motor 15 is connected with converter 16, and the rotating speed of motor 15 is controlled by converter 16 and regulated.Due to turntable 13 High speed rotating, experiment has certain danger, therefore at the peripheral protection wire gauze increasing by 2 meters high of whole experiment porch 17, injure experimenter by a crashing object to prevent the object on rotation platform from flying away from rotation platform in rotary course and damage peripheral structure.
Circulating water is flowed through filter 3 after the inner extraction of water tank 1 filtered by pump 2, after heat through heater 4, then enter Enter test section 10, finally by pipeline reflow tank, form a circulation.Effusion meter 5, temperature are installed before and after test section Degree sensor 9, pressure transducer 6.The parameter of sensor measurement saves the data in computer 12 by data acquisition module 11 On.Process of the test is realized the different rotating speeds of turntable by converter 16.Regulation imported valve 7 and the phase para-position of outlet valve 8 Putting and can realize pressure different in test section 10, the power of regulation heater 4 can realize temperature different in test section 10.Above-mentioned In regulation can realize acceleration that pipeline is subject in flight course and pipe, temperature and pressure changes.
This device is suitably applied the flow calibration of aircraft liquid pipeline system, measures with other aircraft liquid line flow Method is compared, have simple and reliable, original structure is destroyed the advantage such as little.
Although as it has been described above, represented and described the present invention with reference to specific preferred embodiment, but it must not be explained For the restriction to the present invention self.Under the spirit and scope of the present invention premise defined without departing from claims, can be right Various changes can be made in the form and details for it.

Claims (3)

1. an aircraft liquid cold pipe-line system flow ground scaling method, the method based on device include rotation platform and installation Flow calibration blood circulation on described rotation platform, wherein,
Described rotation platform includes turntable, motor and converter, and turntable described in described motor-driven rotates, described converter It is connected with motor, for controlling the rotating speed of motor；
Described flow calibration blood circulation includes fluid circulation system, parameter measurement system and data collecting system, wherein,
Described fluid circulation system includes water tank, pump, heater, filter, test section, imported valve and outlet valve；Described Water tank, pump, filter, heater, imported valve, test section and outlet valve are sequentially connected by pipeline, described water tank water outlet Mouth is connected with described pump by pipeline, and described outlet valve is connected with the water return outlet of water tank by pipeline；
Described parameter measurement system includes effusion meter, temperature sensor and pressure transducer, described effusion meter, temperature sensor and Pressure transducer is respectively arranged in before and after described test section on the pipeline of position；
Described data collecting system includes computer and the data acquisition module being connected with described parameter measurement system；Its feature exists In, described scaling method comprises the following steps:
Utilize the flight load that rotation platform simulation liquid pipeline system is suffered awing, wherein by regulation rotation platform Rotating speed realize different magnitudes of load, obtain loading direction by the arranged direction of test section；
Described flow calibration blood circulation is installed on turntable, to realize measuring real time record and the preservation of parameter；
Further comprising the steps of:
When carrying out flow calibration experiment, the centrifugal force direction of test section position is considered as the heading of aircraft；
The acceleration a of calibration experiment accomplishes+6g from-6g, is spaced apart 1g；Temperature T according to the operating temperature of coolant from lowest temperature Degree accomplishes maximum temperature, is spaced 5 DEG C；Pressure reduction P to 50kPa, is spaced apart 5kPa from 0；
Recording the flow under different acceleration, temperature and pressure, set up data on flows storehouse, the flow of testpieces is ternary letter Number: Q=f (ai,Tj,Pk)；
The then flow function of pipeline during real aircraft:
f(am,Tp,Pq)=f (ai+α,Tj+β,Pk+ γ),
Wherein, α, beta, gamma is a dimensionless, am,Tp,PqBe respectively acceleration that the measurement during real aircraft draws, Temperature and pressure reduction, ai,Tj,pkFor some point in experiment parameter, this point and am,Tp,PqClosest, it may be assumed that
(am-ai)2+(Tp-Tj)2+(Pq-Pk)2≤(am-ai')2+(Tp-Tj')2+(Pq-Pk')2,
In formula: ai',Tj',pk' it is any one point in experiment；
Utilize the Taylor expansion of three element complex:
f ( a i + h , T j + k , P k + l ) = f ( a i , T j , P k ) + 1 1 ! ( h ∂ ∂ a + k ∂ ∂ T + l ∂ ∂ P ) f ( a i , T j , P k ) + 1 2 ! ( h ∂ ∂ a + k ∂ ∂ T + l ∂ ∂ P ) 2 f ( a i , T j , P k ) + 1 3 ! ( h ∂ ∂ a + k ∂ ∂ T + l ∂ ∂ P ) 3 f ( a i , T j , P k ) + ... · + 1 n ! ( h ∂ ∂ a + k ∂ ∂ T + l ∂ ∂ P ) n f ( a i , T j , P k )
Take 2 on the right of formula, as increase precision can increase successively the right item number, therefore,
Q = f ( a i , T j , P k ) + ( h ∂ ∂ a + k ∂ ∂ T + l ∂ ∂ P ) f ( a i , T j , P k ) ,
Wherein:
k ∂ ∂ T f ( a i , T j , P k ) = ( T p - T j ) f i , j + 1 , k - f i , j , k Δ T | ( a i , T j , p k )
l ∂ ∂ P f ( a i , T j , P k ) = ( P q - P k ) f i , j , k + 1 - f i , j , k Δ P | ( a i , T j , p k )
Said process obtains the discharge characteristic under testpieces full working scope.
Aircraft liquid cold pipe-line system flow ground the most according to claim 1 scaling method, it is characterised in that include following Step: realize temperature of liquid different in test section by the power of regulation heater；By regulating the aperture of outlet valve Realize pressure different in described fluid circulation system pipeline.
Aircraft liquid cold pipe-line system flow ground the most according to claim 1 scaling method, it is characterised in that include following Step: choose the variable diameters in aircraft liquid pipeline system or elbow pipeline as testpieces, by ground flow rating test Platform carries out the demarcation under different acceleration, pressure and temperature to obtain the discharge characteristic of testpieces to testpieces.
CN201410259552.4A 2014-06-11 2014-06-11 Aircraft liquid cold pipe-line system flow ground scaling method Expired - Fee Related CN104062110B (en)

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CN112432797B (en) * 2020-08-31 2023-08-22 扬州船用电子仪器研究所(中国船舶重工集团公司第七二三研究所) Multifunctional universal integrated liquid cooling equipment comprehensive test system

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