CN206177602U - Aircraft heat exchanger test equipment - Google Patents
Aircraft heat exchanger test equipment Download PDFInfo
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- CN206177602U CN206177602U CN201621112259.6U CN201621112259U CN206177602U CN 206177602 U CN206177602 U CN 206177602U CN 201621112259 U CN201621112259 U CN 201621112259U CN 206177602 U CN206177602 U CN 206177602U
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Abstract
The utility model discloses an aircraft heat exchanger test equipment, include: gas source device for provide the test required compressed air, with the pressure environment under the simulated aircraft heat exchanger operating condition, air supply voltage regulator device, through the pipeline with gas source device connects, is used for reducing compressed air pulsating nature and fluctuation, loss of pressure testing arrangement, through the pipeline with air supply voltage regulator device connects, is used for the test heat exchanger's loss of pressure. Because gas source device with air supply voltage regulator device has been disposed between the loss of pressure testing arrangement, so can guarantee to get into in test procedure loss of pressure testing arrangement's compressed air satisfies the required flow of test and the requirement of pressure, and then guarantees that the test result is accurate reliable.
Description
Technical field
This utility model is related to aerospace field, and in particular to a kind of test equipment of airborne vehicle, more specifically, relates to
And a kind of airplane heat exchanger test equipment.
Background technology
The heat exchanger of air condition of civil aircraft is mainly used in plane environmental control system and air supply system, is control
The pressure of compressed air, flow, temperature, humidity, the critical elements of flow direction.At present, the heat exchanger of air condition category of number big absolutely
Formula, single-pass cross-current type, air-air heat exchanger are stuck up in plate, material is aluminum.Heat exchanger of air condition operationally, its hot-flow flue
Gas from engine thermal bleed stream, the gas of cold air duct is from ram-air.Two-way air-flow cross flow one carries out heat biography
Pass so as to the gas flow temperature of hot-flow flue be reduced.Hot-flow flue or cold air duct air-flow all have certain pressure, cold and hot friendship
The stress and mechanical stress for changing generation easily causes heat converter structure damage, causes leakage exceeded, and whole heat can be made when serious
Exchanger is damaged.Therefore, after heat exchanger operation a period of time, need to pull down the cleaning that carries out for 2 times offing normal and overhaul, offing normal
Cleaning needs the pressure and traffic environment test for simulating aircraft air-conditioning system after the completion of overhauling.
But, at present the country still carries out stress test work without standard, unified special pressure testing tool, and tests
Job demand meets requirements of the handbook CMM21-50-14 to stress test, and producing stress test has a code requirement and above-mentioned pressure
Can target-seeking contradiction without specification with traffic environment test equipment, it is not easy to ensure the concordance that aircraft air condition pressure heat exchanger is tested
With conjunction standardization.For this purpose, the Chinese utility model patent of Application No. CN201320521740.0 discloses a kind of aircraft air condition
Pressure heat exchanger testing tool, including：One pond, contains test fluid for accommodating heat exchanger of air condition to be tested；A pair
Blanking cover, for the fluid inlet and outlet of matching connection heat exchanger of air condition to be tested, and one is provided with interface tube；One trunk airduct,
The interface tube is connected to, to provide the compressed gas of predetermined pressure, and control valve and pressure is provided with the trunk airduct
Force test device；One relief port, is equiped with earial drainage valve, and is disposed on a blanking cover or trunk airduct.It is pointed out that
The source of the gas requirement carried out to airplane heat exchanger needed for stress test is very harsh, it usually needs pulsating nature and undulatory property are minimum
Source of the gas can just obtain accurate measurement data.And in aircraft air condition pressure heat exchanger testing tool disclosed in above-mentioned patent, in advance
The compressed gas of constant-pressure send into heat exchanger by trunk airduct, and a control valve is provided only with trunk airduct to control
The flow velocity or flow of source of the gas, it is difficult to ensure that the pulsating nature and undulatory property of source of the gas meet test request in test process, causes test
It is difficult to smoothly complete.
For this reason, it is necessary to a kind of new airplane heat exchanger test equipment is designed, to overcome the problems referred to above.
Utility model content
Technical problem to be solved in the utility model is, for aircraft air condition pressure heat exchanger disclosed in prior art
The compressed gas of predetermined pressure send into heat exchanger by trunk airduct in testing tool, and a control is provided only with trunk airduct
Valve processed controlling the flow velocity or flow of source of the gas, it is difficult to ensure that in test process the pulsating nature and undulatory property of source of the gas meet test will
Ask, cause to test the problem for being difficult to smoothly complete, there is provided a kind of airplane heat exchanger test equipment, and it can accurately control gas
Body flow and pressure, effectively reduce the pulsating nature and undulatory property of source of the gas, it is ensured that eventually enter into the gas flow and pressure of test device
The stable scope required in test of power.
This utility model solves the technical scheme that its technical problem adopted：
This utility model provides a kind of airplane heat exchanger test equipment, including：
Compressed air source unit, for provide test needed for compressed air, to simulate airplane heat exchanger working condition under pressure
Force environment；
Source of the gas stable-pressure device, is connected by pipeline with the compressed air source unit, for reduce the compressed air pulsating nature and
Undulatory property；
Pressure loss test device, is connected by pipeline with the source of the gas stable-pressure device, for testing the heat exchanger
The pressure loss.
In the airplane heat exchanger test equipment that this utility model is provided, the pressure loss test device includes：With
In the cold end test device for testing the heat exchanger cold end pressure loss, and for testing heat exchanger hot junction pressure
The hot junction test device of loss.
This utility model provide airplane heat exchanger test equipment in, also including test control device, at the same with institute
The communication connection of source of the gas stable-pressure device, the cold end test device and the hot junction test device is stated, for steady to the source of the gas
Pressure device, the cold end test device and the hot junction test device send control signal and receive from the source of the gas voltage stabilizing
The feedback signal of device, the cold end test device and the hot junction test device.
In the airplane heat exchanger test equipment that this utility model is provided, the source of the gas stable-pressure device includes：By pipe
The variable frequency pump that road is connected with the compressed air source unit, while the frequency conversion communicated to connect with the variable frequency pump and the test control device
Device, while the air accumulator being connected with the cold end test device, hot junction test device and the variable frequency pump pipeline, and be configured in
The 3rd pressure transmitter on the air accumulator outlet pipe.
In the airplane heat exchanger test equipment that this utility model is provided, the cold end test device includes：With it is described
First mass flowmenter of air accumulator pipeline connection, the first electric control valve being connected with the first mass flowmenter pipeline,
The steady air current room being connected with the cold side conduits of first electric control valve and the heat exchanger simultaneously, and it is configured in institute
State the first temperature sensor on the outlet pipe of steady air current room and first pressure transmitter.
In the airplane heat exchanger test equipment that this utility model is provided, the hot junction test device includes：With it is described
Air accumulator pipeline connection the second mass flowmenter, while with second mass flowmenter and the end tube of the heat exchanger
Second electric control valve of road connection, and the second temperature sensor being configured on the second electric control valve outlet pipe
With second pressure transmitter.
In the airplane heat exchanger test equipment that this utility model is provided, the test control device includes：
PLC control modules, communicate to connect the converter, first pressure transmitter, second pressure transmitter, the 3rd pressure
Transmitter, the first temperature sensor, second temperature sensor, the first mass flowmenter, the second mass flowmenter, the first electric adjustable
Section valve and the second electric control valve, for sending pressure regulation drive signal to the converter, to first electric adjustable
Section valve and the second electric control valve transmitted traffic adjust drive signal, receive from the first pressure transmitter, second pressure
The pressure feedback signal of transmitter and the 3rd pressure transmitter, reception are sensed from first temperature sensor and second temperature
The temperature feedback signal of device and reception are from first mass flowmenter and the flow feedback signal of the second mass flowmenter；
Touching type operation screen, electrically connects with the PLC control modules, including for showing the pressure feedback signal, temperature
The data display unit of degree feedback signal and flow feedback signal, and for defeated for the instruction of user input test condition parameters
Enter unit.
In the airplane heat exchanger test equipment that this utility model is provided, the gas stream of the source of the gas stable-pressure device output
Measure as 0~240LB/MIN, pressure value is 0.8MPA.
In the airplane heat exchanger test equipment that this utility model is provided, the filtering accuracy of the source of the gas stable-pressure device is
5μm。
Implement the airplane heat exchanger test equipment that this utility model is provided, following beneficial effect can be reached：This practicality
The airplane heat exchanger test equipment of new offer includes：Compressed air source unit, the compressed air needed for for providing test, to simulate
Pressure environment under airplane heat exchanger working condition；Source of the gas stable-pressure device, is connected by pipeline with the compressed air source unit, is used for
Reduce the compressed air pulsating nature and undulatory property；Pressure loss test device, is connected by pipeline with the source of the gas stable-pressure device
Connect, for testing the pressure loss of the heat exchanger.Because the compressed air source unit and the pressure loss test device it
Between be configured with source of the gas stable-pressure device, it is possible to ensure that the compression into the pressure loss test device in test process is empty
Fullness caused by stagnant QI tests enough the requirement of required flow and pressure, and then ensures test result accurately and reliably.
Description of the drawings
Fig. 1 is the general block diagram that this utility model preferably applies example；
Fig. 2 is the more detailed block diagram that this utility model preferably applies example.
The drawing reference numeral explanation of specific embodiment：
| Compressed air source unit | 1 | Source of the gas stable-pressure device | 2 |
| Pressure loss test device | 3 | Testing control module | 4 |
| Variable frequency pump | 21 | Converter | 22 |
| Air accumulator | 23 | 3rd pressure transmitter | 24 |
| Cold end test device | 31 | Hot junction test device | 32 |
| PLC control modules | 41 | Touching type operation screen | 42 |
| First mass flowmenter pipe | 311 | First electric control valve | 312 |
| Steady air current room | 313 | First temperature sensor | 314 |
| First pressure transmitter | 315 | Second mass flowmenter pipe | 321 |
| Second electric control valve | 322 | Second temperature sensor | 323 |
| Second pressure transmitter | 324 |
Specific embodiment
In order to be more clearly understood to technical characteristic of the present utility model, purpose and effect, accompanying drawing is now compareed detailed
Illustrate specific embodiment of the present utility model.
As shown in figure 1, a kind of preferred embodiment of the airplane heat exchanger test equipment provided for this utility model, described
Airplane heat exchanger test equipment includes compressed air source unit 1, source of the gas stable-pressure device 2, pressure loss test device 3 and testing and control
Device 4.
Wherein, the pipeline of source of the gas stable-pressure device 2 is connected to the compressed air source unit 1 and the pressure loss test device 3
Between, it is possible thereby to ensure that the compressed air into the pressure loss test device 3 in test process is met needed for test
Flow and pressure requirement, and then ensure test result accurately and reliably.
In addition, the test control device 4, at the same with the source of the gas stable-pressure device 2 and the pressure loss test device 3
Communication connection, thus, during test, user can pass through the test control device 4 and set the required compressed gas of test
The flow of body and the size of pressure, will also be understood that in test process the flow of compressed gas, pressure and temperature in each device
Real-time size, so as to realize the intelligentized control method of test process.
It is noted that the airplane heat exchanger generally has two parts of hot channel and cold pipeline, and for heat
The test condition of the pressure loss of pipeline and cold pipeline is different, for example, the gas flow of required compressed air, test interface
Difference.Therefore, the test condition different with cold pipeline in order to meet hot channel, in the present embodiment, the pressure loss test
Device 3 is specifically divided into cold end test device 31 and hot junction test device 32.
The effect of the compressed air source unit 1 is to provide the compressed air needed for test, so as to simulate airplane heat exchanger work
Pressure environment under state.
The source of the gas stable-pressure device 2, referring to Fig. 2 (dotted line represents communication connection in figure, and solid line represents that pipeline connects), passes through
Pipeline is connected with the compressed air source unit 1, can play a part of to reduce the compressed air pulsating nature and undulatory property.Specifically,
The source of the gas stable-pressure device 2 includes the variable frequency pump 21 being connected with the compressed air source unit 1 by pipeline, at the same with the variable frequency pump 21
With the test control device 4 communication connection converter 22, while with the cold end test device 31, hot junction test device 32
With the pipeline of the variable frequency pump 21 connection air accumulator 23, and be configured on the outlet pipe of the air accumulator 23 with the test
3rd pressure transmitter 24 of the communication connection of control device 4.In test process, user can pass through the test control device
The running parameter of the 4 setting converters 22 to reach the purpose for adjusting the working condition of variable frequency pump 21, so as to will be from the gas
The flow value and pressure value of the compressed air of source device 1 is adjusted to required scope, and in the present embodiment, flow value is 0~
240LB/MIN, pressure value is 0.8MPA.3rd pressure transmitter 24 is by the real-time pressure value of the compressed air for measuring
Signal is fed back in the test control device 4, so as to facilitate user to export in source of the gas stable-pressure device 2 described in the monitor in real time of distal end
The compressed air pressure value.In order that the aridity and cleanliness factor of the compressed air reach the requirement needed for test,
Exsiccator and filter are also configured with the air accumulator 23 of the source of the gas stable-pressure device 2, the filtering accuracy of the filter is 5
μm。
Referring to Fig. 2 (dotted line represents communication connection in figure, and solid line represents that pipeline connects), the pressure loss test device 3,
It is connected with the source of the gas stable-pressure device 2 by pipeline, its role is to test the pressure loss of the heat exchanger.The present embodiment
In, the test condition different with cold pipeline in order to meet hot channel, the pressure loss test device 3 is configured for testing institute
State the cold end test device 31 of the heat exchanger cold end pressure loss and for testing the heat exchanger hot junction pressure loss
Hot junction test device 32.Wherein, the cold end test device 31 includes the first quality stream being connected with the pipeline of the air accumulator 23
Gauge 311, the first electric control valve 312 being connected with the pipeline of the first mass flowmenter 311, while electronic with described first
The steady air current room 313 of the cold side conduits connection of regulating valve 312 and the heat exchanger, and it is configured in the steady air current room
The first temperature sensor 314 and first pressure transmitter 315 on 313 outlet pipes.The hot junction test device 32 include with
Second mass flowmenter 321 of the pipeline of the air accumulator 23 connection, while handing over second mass flowmenter 321 and the heat
Second electric control valve 322 of the hot side conduit connection of parallel operation, and it is configured in the outlet pipe of the second electric control valve 322
On second temperature sensor 323 and second pressure transmitter 324.
Referring to Fig. 2 (dotted line represents communication connection in figure, and solid line represents that pipeline connects), the test control device 4 includes
PLC control modules 41 and the touching type operation screen 42 electrically connected with the PLC control modules.Wherein, the PLC control modules 41
Communicate to connect the converter 22, first pressure transmitter 315, second pressure transmitter 324, the 3rd pressure transmitter 24,
One temperature sensor 314, second temperature sensor 323, the first mass flowmenter 311, the second mass flowmenter 321, first are electric
The electric control valve 322 of dynamic regulating valve 312 and second, its role is to send pressure and adjust to drive to the converter 22 believe
Number, to the transmitted traffic of 312 and second electric control valve of the first electric control valve 322 adjust drive signal, receive from institute
First pressure transmitter 315, the pressure feedback signal of the pressure transmitter 24 of second pressure transmitter 324 and the 3rd are stated, is received and
Temperature feedback signal and reception from first temperature sensor 314 and second temperature sensor 323 is from described first
The flow feedback signal of the mass flowmenter 321 of mass flowmenter 311 and second.The touching type operation screen 42 is included for showing
The data display unit of the pressure feedback signal, temperature feedback signal and flow feedback signal, and for supplying user input
The instruction input unit of test condition parameters.Therefore, in test process, user can be in the finger in the touching type operation screen 42
Make and conditional parameter needed for test process keyed in input block, for example, can be input into first electric control valve 312, the
The flow/pressure of two electric control valves 322 and converter 22 adjusts drive signal (relevant operating parameter), the PLC controls
It is electronic that flow/pressure regulation drive signal is accordingly reached down first electric control valve 312, second by module 41
Regulating valve 322 or converter 22, so as to realize Based Intelligent Control.In addition, the PLC control modules 41 can be received from described
One pressure transmitter 315, the pressure feedback signal of second pressure transmitter 324 and the 3rd pressure transmitter 24, from described
The temperature feedback signal of one temperature sensor 314 and second temperature sensor 323 and from first mass flowmenter 311
With the flow feedback signal of the second mass flowmenter 321, and the data display unit transmitted into the touching type operation screen 42,
So as to realize monitor in real time of the user to each device in test process.In addition, different with cold pipeline in order to meet hot channel
Test condition, contains test system (the i.e. hot junction of two sets of different regulation compression gas flows in the test control device 4
Test system and cold end test system).
Implement the airplane heat exchanger test equipment that this utility model is provided, have the advantages that：
1st, the airplane heat exchanger test equipment includes compressed air source unit 1, source of the gas stable-pressure device 2, pressure loss test dress
Put 3 and test control device 4.Wherein, the source of the gas stable-pressure device 2 is connected to the compressed air source unit 1 and the pressure loss
Between test device 3, it is possible thereby to ensure that the compressed air into the pressure loss test device 3 in test process meets
The requirement of flow and pressure needed for test, and then ensure test result accurately and reliably.
2nd, the test control device 4, while logical with the source of the gas stable-pressure device 2 and the pressure loss test device 3
Letter connection, thus, during test, user can set the compressed gas needed for test by the test control device 4
Flow and pressure size, will also be understood that the reality of the flow of compressed gas, pressure and temperature in each device in test process
Shi great little, so as to realize the intelligentized control method of test process.
3rd, the pressure loss test device 3 is configured for testing the cold end survey of the heat exchanger cold end pressure loss
Trial assembly puts 31 and for testing the hot junction test device 32 of the heat exchanger hot junction pressure loss, correspondingly the test control
Test system (i.e. hot junction test system and the cold end test of two sets of different regulation compression gas flows is contained in device processed 4
System).Thus, the hot channel of the airplane heat exchanger test condition different with cold pipeline can be met.
Embodiment of the present utility model is described above in conjunction with accompanying drawing, but this utility model is not limited to
The specific embodiment stated, above-mentioned specific embodiment be only it is schematic, rather than restricted, this area it is common
Technical staff under enlightenment of the present utility model, without departing from this utility model objective and scope of the claimed protection situation
Under, many forms can be also made, these are belonged within protection of the present utility model.
Claims (9)
1. a kind of airplane heat exchanger test equipment, it is characterised in that include：
Compressed air source unit (1), for provide test needed for compressed air, to simulate airplane heat exchanger working condition under pressure
Environment；
Source of the gas stable-pressure device (2), is connected by pipeline with the compressed air source unit (1), for reducing the compressed air pulsating nature
And undulatory property；
Pressure loss test device (3), is connected, for testing the heat exchange by pipeline with the source of the gas stable-pressure device (2)
The pressure loss of device.
2. airplane heat exchanger test equipment according to claim 1, it is characterised in that the pressure loss test device
(3) include：For testing the cold end test device (31) of the heat exchanger cold end pressure loss, and for testing the heat
The hot junction test device (32) of the exchanger hot junction pressure loss.
3. airplane heat exchanger test equipment according to claim 2, it is characterised in that also including test control device
(4), while logical with the source of the gas stable-pressure device (2), the cold end test device (31) and the hot junction test device (32)
Letter connection, for the source of the gas stable-pressure device (2), the cold end test device (31) and the hot junction test device (32)
Send control signal and receive and survey from the source of the gas stable-pressure device (2), the cold end test device (31) and the hot junction
The feedback signal of (32) is put in trial assembly.
4. airplane heat exchanger test equipment according to claim 3, it is characterised in that the source of the gas stable-pressure device (2)
Including：The variable frequency pump (21) being connected with the compressed air source unit (1) by pipeline, at the same with the variable frequency pump (21) and the test
Control device (4) communication connection converter (22), while with the cold end test device (31), hot junction test device (32) and
The air accumulator (23) of variable frequency pump (21) the pipeline connection, and the 3rd pressure being configured on the air accumulator (23) outlet pipe
Power transmitter (24).
5. airplane heat exchanger test equipment according to claim 4, it is characterised in that the cold end test device (31)
Including：The first mass flowmenter (311) being connected with the air accumulator (23) pipeline, with first mass flowmenter (311)
First electric control valve (312) of pipeline connection, while cold with first electric control valve (312) and the heat exchanger
The steady air current room (313) of end pipe road connection, and the first temperature being configured on steady air current room (313) outlet pipe
Sensor (314) and first pressure transmitter (315).
6. airplane heat exchanger test equipment according to claim 5, it is characterised in that the hot junction test device (32)
Including：The second mass flowmenter (321) being connected with the air accumulator (23) pipeline, at the same with second mass flowmenter
(321) and the heat exchanger hot side conduit connection the second electric control valve (322), and to be configured in described second electronic
Second temperature sensor (323) and second pressure transmitter (324) on regulating valve (322) outlet pipe.
7. airplane heat exchanger test equipment according to claim 6, it is characterised in that the test control device (4)
Including：
PLC control modules (41), communicate to connect the converter (22), first pressure transmitter (315), second pressure transmitter
(324), the 3rd pressure transmitter (24), the first temperature sensor (314), second temperature sensor (323), the first mass flow
Meter (311), the second mass flowmenter (321), the first electric control valve (312) and the second electric control valve (322), for
The converter (22) send pressure adjust drive signal, to first electric control valve (312) and the second electric control valve
(322) transmitted traffic adjusts drive signal, receives from the first pressure transmitter (315), second pressure transmitter (324)
With the pressure feedback signal of the 3rd pressure transmitter (24), reception from first temperature sensor (314) and second temperature
The temperature feedback signal of sensor (323) and reception are from first mass flowmenter (311) and the second mass flowmenter
(321) flow feedback signal；
Touching type operation screen (42), electrically connects with the PLC control modules, including for showing the pressure feedback signal, temperature
The data display unit of degree feedback signal and flow feedback signal, and for defeated for the instruction of user input test condition parameters
Enter unit.
8. airplane heat exchanger test equipment according to claim 1, it is characterised in that the source of the gas stable-pressure device (2)
The gas flow of output is 0~240LB/MIN, and pressure value is 0.8MPA.
9. airplane heat exchanger test equipment according to claim 1, it is characterised in that the source of the gas stable-pressure device (2)
Filtering accuracy be 5 μm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621112259.6U CN206177602U (en) | 2016-10-11 | 2016-10-11 | Aircraft heat exchanger test equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621112259.6U CN206177602U (en) | 2016-10-11 | 2016-10-11 | Aircraft heat exchanger test equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206177602U true CN206177602U (en) | 2017-05-17 |
Family
ID=58677377
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621112259.6U Active CN206177602U (en) | 2016-10-11 | 2016-10-11 | Aircraft heat exchanger test equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206177602U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112504719A (en) * | 2020-12-28 | 2021-03-16 | 成都成发泰达航空科技有限公司 | Comprehensive detection system for aviation heat exchanger |
| CN113702081A (en) * | 2021-08-27 | 2021-11-26 | 欧伏电气股份有限公司 | Heat exchange core testing method, electronic equipment, system and storage medium |
| CN114577504A (en) * | 2022-05-07 | 2022-06-03 | 中国飞机强度研究所 | Anti-freezing pressure adjusting system for aircraft test and adjusting method thereof |
-
2016
- 2016-10-11 CN CN201621112259.6U patent/CN206177602U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112504719A (en) * | 2020-12-28 | 2021-03-16 | 成都成发泰达航空科技有限公司 | Comprehensive detection system for aviation heat exchanger |
| CN112504719B (en) * | 2020-12-28 | 2021-09-14 | 成都成发泰达航空科技有限公司 | Comprehensive detection system for aviation heat exchanger |
| CN113702081A (en) * | 2021-08-27 | 2021-11-26 | 欧伏电气股份有限公司 | Heat exchange core testing method, electronic equipment, system and storage medium |
| CN113702081B (en) * | 2021-08-27 | 2024-03-29 | 欧伏电气股份有限公司 | Heat exchange core testing method, electronic equipment, system and storage medium |
| CN114577504A (en) * | 2022-05-07 | 2022-06-03 | 中国飞机强度研究所 | Anti-freezing pressure adjusting system for aircraft test and adjusting method thereof |
| CN114577504B (en) * | 2022-05-07 | 2022-07-12 | 中国飞机强度研究所 | Anti-freezing pressure adjusting system for aircraft test and adjusting method thereof |
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Legal Events
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|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20211215 Address after: 510470 Room 301, No. 2, Lane 2, Fenghe feng'an street, Renhe Town, Baiyun District, Guangzhou, Guangdong Province (Airport Baiyun) Patentee after: Xiaoyi Aviation Technology (Guangzhou) Co.,Ltd. Address before: 518000 room 2619, block a, Qunxing Plaza, Huaqiang North Street, Futian District, Shenzhen, Guangdong Patentee before: SHENZHEN ARMSTRONG AVIATION TECHNOLOGY CO.,LTD. |
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| TR01 | Transfer of patent right |