CN105620782B - A kind of aircraft heat management system tests heater power set-up method - Google Patents
A kind of aircraft heat management system tests heater power set-up method Download PDFInfo
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- CN105620782B CN105620782B CN201410591338.9A CN201410591338A CN105620782B CN 105620782 B CN105620782 B CN 105620782B CN 201410591338 A CN201410591338 A CN 201410591338A CN 105620782 B CN105620782 B CN 105620782B
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- power
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- radiator
- management system
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Abstract
The invention belongs to aircraft heat management system experimental technique field, is related to a kind of aircraft heat management system experiment heater power set-up method.The heater power that this method is managed by the means opposite heat tube of experiment on systems test bed carries out successive adjustment, realizes the setting of heater power.In whole process, it is only necessary to which the temperature in experiment and flow parameter are simply calculated, it becomes possible to which the accurate actual power set up needed for heater, it is incomplete to avoid theoretical calculation input parameter, calculates the shortcomings that inaccurate.
Description
Technical field
The invention belongs to aircraft heat management system experimental technique field, is related to a kind of aircraft heat management system experiment heater
Power set-up method.
Background technology
It is the technology studied in recent years that aircraft is carried out integrated using fuel oil heat management system to the heat of full machine Mechatronic Systems
Focus, the key problem of heat management system design are exactly that the heat of Mechatronic Systems subsystems (fuel oil, hydraulic pressure, ring control etc.) is born
Carry section and optimize integrated, fuel oil is played maximum heat sink benefit.After the completion of design, generally require by heat management system
System is tested the whether reasonable of fuel oil heat management system design verified.It is difficult that reproduction is electromechanical each in being tested due to heat management system
The actual configuration of subsystem, therefore generally use heater simulates heat caused by subsystems.The heating work(of heater
The selection of rate value is the difficult point in heat management system experiment, and the heat radiation power that should ensure radiator is required value, is also needed to simultaneously
Consider the thermal loss of heat dissipation subsystem pipeline and annex.In theory, the heating power value of electric heater can lead to superheat calculation
Obtain, but due to being related to the thermodynamic parameter of numerous pipelines and finished product, cause calculating process complexity and accuracy is poor.
The content of the invention
It is an object of the invention to provide a kind of simple to operate, heater in the experiment of aircraft heat management system can be accurately set up
The method of power.
Technical scheme：The set-up method of electric heater capacity, described in a kind of aircraft heat management system experiment
Aircraft heat management system experiment include oil supply loop 13 and heat load simulation system 14, wherein oil supply loop 13 also includes fuel feeding
Pump 1, fuel tank 2, radiator 3, temperature sensor 4, stop valve 5 and engine consumption analogue means 6, wherein heat load simulation system
14 include check valve 7, cooling pump 8, heater 9, flow control valve 10, flowmeter 11 and coolant hold-up tank 12, following steps：
Step 1: firing test device, adjusts the size needed for the fuel flow to experiment in oil supply loop 13, adjusts simultaneously
Save the size needed for coolant rate to experiment in heat load simulation system 14；
Step 2: the power of heater 9 is set to the heat exchange power W that radiator 3 requires；
Step 3: the flow Q, the entrance coolant temperature T of radiator 3 of measurement heat load simulation system 14rIt is cold with exporting
But liquid temperature degree Tc；
Step 4: calculate the actual heat exchange power W of radiator 3r=Q (Tr-Tc), and the heat exchange power required with radiator 3
W is compared, if Wr＜ W, then the power of heater 3 is increased into △ W；
Step 5: repeat step three and step 4, in the actual power W of radiator 3rSoon close to during W, it is necessary to reduce △ W, directly
To the actual heat exchange power W of radiator 3rUntill identical with desired heat exchange power W, at this moment heater power is final rating test
The rated power of obtained heater.
The advantages of the present invention：
The heater power that the present invention is managed by the means opposite heat tube of experiment on systems test bed carries out successive adjustment, realizes
The setting of heater power.In whole process, it is only necessary to the temperature in experiment and flow parameter are simply calculated, with regard to energy
Enough accurate actual powers set up needed for heater, it is incomplete to avoid theoretical calculation input parameter, calculates the shortcomings that inaccurate, this
The heater power set-up method gone out given in invention, method is simple and convenient to operate, workable, suitable for any aircraft
The setting of heater power, versatile in heat management system experiment, has application value.
Brief description of the drawings
Fig. 1 is aircraft heat management system test principle figure in the present invention；
Wherein, 1- oil feed pumps, 2- fuel tanks, 3- radiators, 4- temperature sensors, 5- stop valves, the simulation of 6- engines consumption
Device, 7- check valves, the cold pump of 8- liquid, 9- heaters, 10- flow control valves, 11- flowmeters, 12- coolant hold-up tanks, 13- are supplied
Oil return line, 14- heat load simulation systems.
Embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings, refers to Fig. 1.
Typical aircraft heat management system test principle figure See Figure 1, wherein, the part that top solid line represents is returned for fuel feeding
Road 13, lower dotted line represent for heat load simulation system 14.Fuel system is each to having connected on the pipeline of engine oil
The radiator 3 of subsystem, typical heat sink share four interfaces, and fuel inlet, fuel outlet, cooling liquid inlet, coolant go out
Mouthful.The relatively low fuel oil of temperature coolant higher with entering the temperature of radiator 3 after radiator 3 is entered carries out heat exchange, combustion
Temperature raises after oil absorbs heat entrained in coolant, subsequently enters simulation of engine device 6 and is consumed.Temperature declines
Coolant afterwards reenters heat load simulation system 14 and circulated after the outlet of radiator 3 outflow.Wherein each radiator
All it is connected with a heat load simulation system 14, is not entirely shown in figure.
When it is implemented, its step is as follows：
Step 1: open oil feed pump 1 and engine consumption analogue means 6, adjust fuel flow in oil supply loop 13 to
Size needed for experiment, starting the cold pump 8 of liquid makes coolant starting the cycle in the pipeline of heat load simulation system 14, meanwhile, adjust
Throttle adjustable valve 10, and reads over and take flowmeter 11, ensures coolant rate for experiment desirable value；
Step 2: start heater 9, and the power for adjusting heater 9 is the power W of radiator requirement, is started negative to heat
The coolant carried in simulation system 14 is heated；
Step 3: after system working stability, the entrance coolant temperature T of radiator 3 is readrWith outlet coolant temperature
Tc, and in heat load simulation system 14 coolant flow Q；
Step 4: calculate the actual heat exchange power W of radiator 3r=Q (Tr-Tc), and the heat exchange power required with radiator 3
W is compared, if Wr＜ W, then the power of heater 9 is increased into △ W, usually 500 watts；
Step 5: repeat step three and step 4, the power of heater 9 is stepped up, in the actual power W of radiator 3rIt hurry up
Close to during W, it is necessary to reduce the power of heater 9 each value added △ W, usually 50 watts, until 3 actual heat exchange power of radiator
WrUntill identical with desired heat exchange power W, at this moment the power of heater 3 is the specified work(for the heater that final rating test obtains
Rate.
Claims (1)
1. a kind of aircraft heat management system tests heater power set-up method, it is characterized in that：Described heater power is set up
Method comprises the following steps:
Step 1: firing test device, adjusts the size needed for the fuel flow to experiment in oil supply loop (13), adjusts simultaneously
Size in heat load simulation system (14) needed for coolant rate to experiment；
Step 2: heater (9) power is set to the heat exchange power W of radiator (3) requirement；
Step 3: the flow Q, the entrance coolant temperature T of radiator (3) of measurement heat load simulation system (14)rCooled down with outlet
Liquid temperature degree Tc；
Step 4: calculate radiator (3) actual heat exchange power Wr=Q (Tr-Tc), and the heat exchange power required with radiator (3)
W is compared, if Wr＜ W, then the power of heater (3) is increased into △ W；
Step 5: repeat step three and step 4, in radiator (3) actual power WrSoon close to during W, it is necessary to reduce △ W, until
The actual heat exchange power W of radiator (3)rUntill identical with desired heat exchange power W, at this moment heater power is final rating test
The rated power of obtained heater.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410591338.9A CN105620782B (en) | 2014-10-28 | 2014-10-28 | A kind of aircraft heat management system tests heater power set-up method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410591338.9A CN105620782B (en) | 2014-10-28 | 2014-10-28 | A kind of aircraft heat management system tests heater power set-up method |
Publications (2)
| Publication Number | Publication Date |
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| CN105620782A CN105620782A (en) | 2016-06-01 |
| CN105620782B true CN105620782B (en) | 2018-01-16 |
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| CN201410591338.9A Active CN105620782B (en) | 2014-10-28 | 2014-10-28 | A kind of aircraft heat management system tests heater power set-up method |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1644892A (en) * | 2004-01-20 | 2005-07-27 | 联合工艺公司 | Thermal management system for an aircraft |
| CN201808671U (en) * | 2010-10-15 | 2011-04-27 | 中国飞行试验研究院 | Fuel warming-up device |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2011504834A (en) * | 2007-11-29 | 2011-02-17 | エアバス・オペレーションズ・ゲーエムベーハー | Method and kit for testing a three-phase supply on an aircraft |
| US8826641B2 (en) * | 2008-01-28 | 2014-09-09 | United Technologies Corporation | Thermal management system integrated pylon |
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2014
- 2014-10-28 CN CN201410591338.9A patent/CN105620782B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1644892A (en) * | 2004-01-20 | 2005-07-27 | 联合工艺公司 | Thermal management system for an aircraft |
| CN201808671U (en) * | 2010-10-15 | 2011-04-27 | 中国飞行试验研究院 | Fuel warming-up device |
Non-Patent Citations (1)
| Title |
|---|
| 飞机燃油系统热管理研究;徐志英等;《航空动力学报》;20071130;第22卷(第11期);pp1834-pp1837 * |
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| CN105620782A (en) | 2016-06-01 |
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