CN203616154U - Aircraft steering engine temperature testing device - Google Patents
Aircraft steering engine temperature testing device Download PDFInfo
- Publication number
- CN203616154U CN203616154U CN201320798904.4U CN201320798904U CN203616154U CN 203616154 U CN203616154 U CN 203616154U CN 201320798904 U CN201320798904 U CN 201320798904U CN 203616154 U CN203616154 U CN 203616154U
- Authority
- CN
- China
- Prior art keywords
- temperature
- environment case
- environmental cabinet
- testing device
- steering engine
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- 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.)
- Expired - Lifetime
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 40
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims abstract description 48
- 230000007613 environmental effect Effects 0.000 claims abstract description 46
- 229910052757 nitrogen Inorganic materials 0.000 claims abstract description 24
- 239000007788 liquid Substances 0.000 claims abstract description 23
- 239000007789 gas Substances 0.000 claims description 24
- 230000008676 import Effects 0.000 claims description 6
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 abstract description 4
- 238000000034 method Methods 0.000 abstract description 2
- 238000005057 refrigeration Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 3
- 238000002474 experimental method Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
Images
Abstract
The utility model discloses a aircraft steering engine temperature testing device which belongs to the aircraft steering engine testing technique, and relates to the improvement of the aircraft steering engine temperature testing device. The aircraft steering engine temperature testing device is characterized by comprising a control and display system (3), a first liquid nitrogen tank (4), a second liquid nitrogen tank (5), a two-position three-way valve (6), a temperature control box (7) and n environmental boxes. The aircraft steering engine temperature testing device can rapidly adjust the temperature inside the environment boxes, and can simulate the low-temperature environment below minus 60 DEG C; and the aircraft steering engine temperature testing device provided with the plurality of environmental boxes greatly increases the aircraft steering engine temperature test efficiency, and realizes the purpose of integral test on the steering engine of the whole flight control system.
Description
Technical field
The utility model belongs to aircraft steering wheel experimental technique, relates to the improvement to aircraft steering wheel temperature testing device.
Background technology
The system principle diagram of current a kind of aircraft steering wheel temperature testing device is referring to Fig. 1, and it is made up of refrigeration machine 1, environmental cabinet 2 and control and display system 3.The gas outlet of refrigeration machine 1 is communicated with the air intake opening of environmental cabinet 2 by pipeline, the interior band having heaters of environmental cabinet 2 and fan, the heater control signal input end of environmental cabinet 2 is connected with the heater control signal output terminal of control and display system 3 by wire, the fan control signal input end of environmental cabinet 2 is connected with the fan control signal output terminal of control and display system 3 by wire, and the control signal input end of refrigeration machine 1 is connected with the refrigeration machine control signal output terminal of control and display system 3 by wire.Its principle of work is: when test, aircraft steering wheel is positioned in environmental cabinet, connects after the fluid pressure line and control cables of steering wheel, close the chamber door of environmental cabinet.Start-up temperature test unit, arranges environment temperature.Control and display system 3 are selected the well heater work in refrigeration machine 1 or environmental cabinet according to the temperature setting, and fan is for stirring the air in environmental cabinet 2, and the temperature of assurance environmental cabinet 2 inside is even, consistent.When temperature in environmental cabinet reaches setting value, start to carry out steering wheel test.Its shortcoming is: the first, the interior thermoregulator time of environmental cabinet 2 long, can not simulate the low temperature environment that exceedes-60 ℃.Adopt the surrounding air of refrigeration as cold air source, can not simulate the low temperature environment lower than-60 ℃; Meanwhile, the time that reaches design temperature is long, and temperature regulates efficiency low, and cannot carry out verification experimental verification to alternating temperature process.The second, only have an environmental cabinet, limited by the quantity of test steering wheel, test efficiency is low.Three, owing to only having an environmental cabinet, finite capacity cannot carry out bulk testing to the steering wheel of whole flight control system simultaneously.
Summary of the invention
The purpose of this utility model is: propose temperature in the rapid adjusting ambient case of a kind of energy, can simulate and exceed the low temperature environment of-60 ℃, have the aircraft steering wheel temperature testing device of multiple environmental cabinets, to improve the efficiency of aircraft steering wheel humid test, and realize and the steering wheel of whole flight control system is carried out to bulk testing simultaneously.
The technical solution of the utility model is: a kind of aircraft steering wheel temperature testing device, is characterized in that: aircraft steering wheel temperature testing device forms by controlling with display system 3, the first liquid nitrogen container 4, the second liquid nitrogen container 5, two-position three-way valve 6, temperature control box 7 and n environmental cabinet, the outlet of the first liquid nitrogen container 4 is communicated with the first import of two-position three-way valve 6 by pipeline, the outlet of the second liquid nitrogen container 5 is communicated with the second import of two-position three-way valve 6 by pipeline, the outlet of two-position three-way valve 6 is communicated with the air intake opening 7a of temperature control box 7 by pipeline, temperature control box 7 is with having heaters and fan, the heater control signal input end 7b of temperature control box 7 is connected with the heater control signal output terminal 3a of control and display system 3 by wire, the fan control signal input end 7c of temperature control box 7 is connected with the fan control signal output terminal 3b of control and display system 3 by wire, n environmental cabinet is first environment case 8
1, second environment case 8
2to n environmental cabinet 8
n, the natural number that n is 2～30, the gas outlet 7e of temperature control box 7 by pipeline respectively with first environment case 8
1air intake opening, second environment case 8
2air intake opening to the n environmental cabinet 8
nair intake opening be communicated with, first environment case 8
1gas outlet, second environment case 8
2gas outlet to the n environmental cabinet 8
ngas outlet be communicated with the gas returning port 7d of temperature control box 7 by pipeline, at first environment case 8
1, second environment case 8
2to n environmental cabinet 8
ntemperature sensor is inside installed respectively, first environment case 8
1the signal output part of temperature sensor, second environment case 8
2signal output part to the n environmental cabinet 8 of temperature sensor
nthe signal output part of temperature sensor by wire respectively with the first environment case 8 of control and display system 3
1the signal input part 3c1 of temperature sensor, second environment case 8
2signal input part 3c2 to the n environmental cabinet 8 of temperature sensor
nthe signal input part 3cn of temperature sensor connects.
The utility model has the advantages that: proposed temperature in the rapid adjusting ambient case of a kind of energy, can simulate and exceed the low temperature environment of-60 ℃, there is the aircraft steering wheel temperature testing device of multiple environmental cabinets, greatly improve the efficiency of aircraft steering wheel humid test, and realized and the steering wheel of whole flight control system has been carried out to bulk testing simultaneously.Evidence, an embodiment of the present utility model, the quantity n=21 of environmental cabinet, its test efficiency has improved more than 20 times than current test unit.
Accompanying drawing explanation
Fig. 1 is the system principle diagram of current a kind of aircraft steering wheel temperature testing device.
Fig. 2 is system principle diagram of the present utility model.
Embodiment
Below the utility model is described in further details.Referring to Fig. 2, a kind of aircraft steering wheel temperature testing device, is characterized in that: aircraft steering wheel temperature testing device forms by controlling with display system 3, the first liquid nitrogen container 4, the second liquid nitrogen container 5, two-position three-way valve 6, temperature control box 7 and n environmental cabinet, the outlet of the first liquid nitrogen container 4 is communicated with the first import of two-position three-way valve 6 by pipeline, the outlet of the second liquid nitrogen container 5 is communicated with the second import of two-position three-way valve 6 by pipeline, the outlet of two-position three-way valve 6 is communicated with the air intake opening 7a of temperature control box 7 by pipeline, temperature control box 7 is with having heaters and fan, the heater control signal input end 7b of temperature control box 7 is connected with the heater control signal output terminal 3a of control and display system 3 by wire, the fan control signal input end 7c of temperature control box 7 is connected with the fan control signal output terminal 3b of control and display system 3 by wire, n environmental cabinet is first environment case 8
1, second environment case 8
2to n environmental cabinet 8
n, the natural number that n is 2～30, the gas outlet 7e of temperature control box 7 by pipeline respectively with first environment case 8
1air intake opening, second environment case 8
2air intake opening to the n environmental cabinet 8
nair intake opening be communicated with, first environment case 8
1gas outlet, second environment case 8
2gas outlet to the n environmental cabinet 8
ngas outlet be communicated with the gas returning port 7d of temperature control box 7 by pipeline, at first environment case 8
1, second environment case 8
2to n environmental cabinet 8
ntemperature sensor is inside installed respectively, first environment case 8
1the signal output part of temperature sensor, second environment case 8
2signal output part to the n environmental cabinet 8 of temperature sensor
nthe signal output part of temperature sensor by wire respectively with the first environment case 8 of control and display system 3
1the signal input part 3c1 of temperature sensor, second environment case 8
2signal input part 3c2 to the n environmental cabinet 8 of temperature sensor
nthe signal input part 3cn of temperature sensor connects.
Principle of work of the present utility model is: when test, n steering wheel is arranged on respectively in n environmental cabinet, the natural number that n is 2～30, connects fluid pressure line and steering wheel control cables.Start-up temperature test unit, set test temperature, while doing low temperature test, two-position three-way valve 6 is connected the first liquid nitrogen container 4, open the valve of the first liquid nitrogen container 4, low temperature nitrogen enters temperature control box 7, after passing through fan mixes with the gas of gas returning port 7d, gas outlet 7e by temperature control box 7 is blown into entered environment case at a high speed by fan, reaches the object of the temperature inside the box that controls environment by gas flow temperature.After reaching requirement, the temperature in n environmental cabinet starts steering wheel test.While doing high temperature experiment, the well heater work in temperature control box 7, after passing through fan mixes with the gas of gas returning port 7d, is blown into entered environment case by the gas outlet 7e of temperature control box 7 at a high speed by fan, reaches the object of the temperature inside the box that controls environment by gas flow temperature.After reaching requirement, the temperature in n environmental cabinet starts steering wheel test.The object that two liquid nitrogen containers are set is to increase liquid nitrogen deposit.After the liquid nitrogen in the first liquid nitrogen container 4 exhausts, close the valve of the first liquid nitrogen container 4, open the valve of the second liquid nitrogen container 5, two-position three-way valve 6 is connected the second liquid nitrogen container 5 and is proceeded test.
In an embodiment of the present utility model, n=21.
Claims (1)
1. an aircraft steering wheel temperature testing device, is characterized in that: aircraft steering wheel temperature testing device is by controlling and display system (3), the first liquid nitrogen container (4), the second liquid nitrogen container (5), two-position three-way valve (6), temperature control box (7) and n environmental cabinet form, the outlet of the first liquid nitrogen container (4) is communicated with the first import of two-position three-way valve (6) by pipeline, the outlet of the second liquid nitrogen container (5) is communicated with the second import of two-position three-way valve (6) by pipeline, the outlet of two-position three-way valve (6) is communicated with the air intake opening (7a) of temperature control box (7) by pipeline, temperature control box (7) band having heaters and fan, the heater control signal input end (7b) of temperature control box (7) is connected with the heater control signal output terminal (3a) of control and display system (3) by wire, the fan control signal input end (7c) of temperature control box (7) is connected with the fan control signal output terminal (3b) of control and display system (3) by wire, n environmental cabinet is first environment case (8
1), second environment case (8
2) to n environmental cabinet (8
n), the natural number that n is 2～30, the gas outlet (7e) of temperature control box (7) by pipeline respectively with first environment case (8
1) air intake opening, second environment case (8
2) air intake opening to the n environmental cabinet (8
n) air intake opening be communicated with, first environment case (8
1) gas outlet, second environment case (8
2) gas outlet to the n environmental cabinet (8
n) gas outlet be communicated with the gas returning port (7d) of temperature control box (7) by pipeline, at first environment case (8
1), second environment case (8
2) to n environmental cabinet (8
n) in temperature sensor is installed respectively, first environment case (8
1) signal output part, the second environment case (8 of temperature sensor
2) signal output part to the n environmental cabinet (8 of temperature sensor
n) temperature sensor signal output part by wire respectively with the first environment case (8 of control and display system (3)
1) signal input part (3c1), the second environment case (8 of temperature sensor
2) signal input part (3c2) of temperature sensor is to n environmental cabinet (8
n) temperature sensor signal input part (3cn) connect.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320798904.4U CN203616154U (en) | 2013-12-04 | 2013-12-04 | Aircraft steering engine temperature testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320798904.4U CN203616154U (en) | 2013-12-04 | 2013-12-04 | Aircraft steering engine temperature testing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203616154U true CN203616154U (en) | 2014-05-28 |
Family
ID=50768788
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320798904.4U Expired - Lifetime CN203616154U (en) | 2013-12-04 | 2013-12-04 | Aircraft steering engine temperature testing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203616154U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106644466A (en) * | 2016-12-12 | 2017-05-10 | 西北工业大学 | Simulation testing device used for air vehicle rudder transmission mechanism |
| CN110749464A (en) * | 2019-10-30 | 2020-02-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Steering engine performance test method |
-
2013
- 2013-12-04 CN CN201320798904.4U patent/CN203616154U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106644466A (en) * | 2016-12-12 | 2017-05-10 | 西北工业大学 | Simulation testing device used for air vehicle rudder transmission mechanism |
| CN106644466B (en) * | 2016-12-12 | 2019-02-01 | 西北工业大学 | A kind of simulating test device for aircraft rudder transmission mechanism |
| CN110749464A (en) * | 2019-10-30 | 2020-02-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Steering engine performance test method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140528 |