CN108001709A - A kind of aircraft secondary power systems air inlet measuring device - Google Patents
A kind of aircraft secondary power systems air inlet measuring device Download PDFInfo
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- CN108001709A CN108001709A CN201711083300.0A CN201711083300A CN108001709A CN 108001709 A CN108001709 A CN 108001709A CN 201711083300 A CN201711083300 A CN 201711083300A CN 108001709 A CN108001709 A CN 108001709A
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- Prior art keywords
- inlet
- measuring point
- air inlet
- air intake
- air
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Or Calibration Of Command Recording Devices (AREA)
Abstract
The present invention relates to a kind of aircraft secondary power systems air inlet measuring device, it includes air intake duct, inlet valve, inlet valve executing agency, temperature sensor and pressure sensor.The simulation air inlet road shape is " L " shape, its corner seamlessly transits, Fighter Inlet measuring point (3), auxiliary power unit air inlet measuring point (5), air intake port measuring point (6) are set in the air intake duct (1), and each measuring point averagely arranges some pressure sensors and temperature sensor.The present invention is mainly suitable for the measurement of civil and military aircraft secondary power systems air inlet performance, simulates true installation environment, is conducive to measure real air inlet performance during accessory power system ground experiment, has larger use value.
Description
Technical field
The invention belongs to aircraft secondary power systems technology, is related to a kind of aircraft secondary power systems air inlet measuring device.
Background technology
The auxiliary power unit air inlet measuring device of the prior art can only be measured for auxiliary power unit import, not had
Have and carry out simulation air inlet measurement according to the true environment and inlet valve aperture of aircraft, cause accessory power system ground experiment can not
, there is larger aberrations in property after installing in true reflection installation state.
The content of the invention
The purpose of the present invention is：For it is a kind of it is simple in structure, measurement is accurate, can be moved easily and auxiliary easy to the aircraft of maintenance
Power-assist Force system air inlet measuring device.
Technical scheme：A kind of aircraft secondary power systems air inlet measuring device, it is characterised in that：The aircraft
Accessory power system air inlet measuring device include simulation air intake duct 1, inlet valve executing agency 2, inlet valve 4, pressure sensor and
Temperature sensor；Wherein, the simulation air inlet road shape is " L " shape, its corner seamlessly transits, set in the air intake duct 1
Fighter Inlet measuring point 3, auxiliary power unit air inlet measuring point 5, air intake port measuring point 6；The inlet valve 4 and air intake duct 1
It is bolted；The inlet valve executing agency 2 is a motor, and inlet valve executing agency 2 is connected with inlet valve 4 by drive link
Connect, the charge flow rate of the aperture regulation air intake duct by controlling inlet valve；The Fighter Inlet measuring point 3 is arranged on air intake duct 1
Inlet, air intake port measuring point 6 are arranged on 1 exit of air intake duct, and it is dynamic that auxiliary power unit air inlet measuring point 5 is arranged on auxiliary
At the air inlet of power apparatus；Fighter Inlet measuring point 3, air intake port measuring point 6, auxiliary power unit air inlet measuring point 5 are each flat
Arrange some pressure sensors and temperature sensor.
Beneficial effects of the present invention：The present invention uses the structure similar to aircraft auxiliary power plant gas handling system, approximate
Installation and air inlet environment on analog machine, the charge flow rate of air intake duct are adjusted using inlet valve, in inlet mouth and near exit
Pressure sensor and temperature sensor are evenly arranged, the gas parameter of air intake duct intake and exhaust can be accurately measured, so that convenient
The pressure loss of air intake duct is calculated, the true inlet air conditions of accessory power system are simulated.In auxiliary power unit entrance
Pressure sensor and temperature sensor nearby are evenly arranged, auxiliary power unit inlet induction parameter can be measured；The present invention
The air inlet performance measurement of civilian or military aircraft secondary power systems is applicable to, it is with certain versatility and preferably real
With value.
Brief description of the drawings
Fig. 1 is the structure diagram of the aircraft secondary power systems air inlet measuring device of the present invention；
Wherein, 1- air intake ducts, 2- inlet valves executing agency, 3- Fighter Inlets measuring point, 4- inlet valves, 5- auxiliary powers dress
Put air inlet measuring point, 6- air intake port measuring points.
Embodiment
By embodiment, the present invention is described in further detail below in conjunction with the accompanying drawings.
Referring to Fig. 1, it is the structure diagram of the present invention.A kind of aircraft secondary power systems air inlet measuring device includes
Air intake duct 1, inlet valve executing agency 2, Fighter Inlet measuring point 3, inlet valve 4, auxiliary power unit air inlet measuring point 5, air inlet
Road exports measuring point 6, wherein, inlet valve 4 is bolted with air intake duct 1, and inlet valve executing agency 2 passes through biography with inlet valve 4
Lever connects, and Fighter Inlet measuring point 3 is uniformly fixed on 1 inlet of air intake duct by screw, and air intake port measuring point 6 passes through spiral shell
Nail is uniformly fixed on 1 exit of air intake duct, and auxiliary power unit air inlet measuring point 5 is evenly distributed on auxiliary power unit air inlet
Place, each measuring point respectively arrange four temperature sensors and four pressure sensors.
The inlet valve 4 of the present invention adjusts aperture by inlet valve executing agency 2, according to the air inlet needs of auxiliary power unit
Into the gas of different flow, Fighter Inlet measuring point 3 measures the pressure and temperature of air inlet, and air inlet is truly managed by simulating aircraft
The air intake duct 1 on road, into auxiliary power unit.Air intake port measuring point 6 measures air inlet and passes through the pressure and temperature after air intake duct 1
Degree, the pressure loss and charge flow rate of charge air flow can be calculated using calculation formula.The measurement air inlet of air inlet measuring point 5 enters auxiliary
The pressure and temperature of power-assisting device, it can be determined that the air inlet performance of auxiliary power unit.The air intake duct 1 of the present invention simulates aircraft
It is true that auxiliary power unit air inlet pipeline, inlet valve 4 and inlet valve executing agency 2 can adjust aperture simulation auxiliary power unit
Air inflow, this is the key that can simulate the true installation environment of aircraft.
The full admission amount of the air intake duct 1 of the present invention is 4kg/s, meets the following auxiliary power unit of 300kW equivalent horsepowers
Air inlet demand.Inlet valve executing agency 2 drives inlet valve 4 by motorized adjustment.Fighter Inlet measuring point 3 and air intake port
Measuring point 6 measures the stagnation pressure and total temperature of air inlet, and the pitot loss and inlet air flow of air intake duct can be accurately drawn after calculating
Amount.Air intake duct 1 is designed according to the auxiliary power unit inlet structure of aircraft, simulates true installation environment as far as possible.
A kind of aircraft secondary power systems air inlet measuring device of the present invention, its effect is auxiliary to civil aircraft or military aircraft
There is provided during power-assist Force system ground experiment accurately, close to the air inlet performance measurements of truth.The structure of the present invention is special
Point is suitable for high motor-driven, easy to maintenance ground run environment.
Claims (2)
- A kind of 1. aircraft secondary power systems air inlet measuring device, it is characterised in that：The aircraft secondary power systems air inlet is surveyed Measuring device includes simulation air intake duct (1), inlet valve executing agency (2), inlet valve (4), pressure and temperature sensor；Wherein, institute It is " L " shape to state simulation air inlet road shape, its corner seamlessly transits, and Fighter Inlet measuring point is set in the air intake duct (1) (3), auxiliary power unit air inlet measuring point (5), air intake port measuring point (6)；The inlet valve (4) passes through with air intake duct (1) It is bolted；The inlet valve executing agency (2) is a motor, and inlet valve executing agency (2) passes through drive link with inlet valve (4) Connection, the charge flow rate of the aperture regulation air intake duct by controlling inlet valve；The Fighter Inlet measuring point (3) is arranged on air inlet Road (1) inlet, air intake port measuring point (6) are arranged on air intake duct (1) exit, auxiliary power unit air inlet measuring point (5) It is arranged at the air inlet of auxiliary power unit；Fighter Inlet measuring point (3), air intake port measuring point (6), auxiliary power unit Air inlet measuring point (5) is each averagely to arrange some pressure sensors and temperature sensor.
- 2. aircraft secondary power systems air inlet measuring device according to claim 1, it is characterised in that：In Fighter Inlet Measuring point (3), air intake port measuring point (6), auxiliary power unit air inlet measuring point (5) be each averagely arrange four pressure sensors and Four temperature sensors.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711083300.0A CN108001709A (en) | 2017-11-06 | 2017-11-06 | A kind of aircraft secondary power systems air inlet measuring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711083300.0A CN108001709A (en) | 2017-11-06 | 2017-11-06 | A kind of aircraft secondary power systems air inlet measuring device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108001709A true CN108001709A (en) | 2018-05-08 |
Family
ID=62052144
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711083300.0A Pending CN108001709A (en) | 2017-11-06 | 2017-11-06 | A kind of aircraft secondary power systems air inlet measuring device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108001709A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109459098A (en) * | 2018-09-29 | 2019-03-12 | 中国飞行试验研究院 | A kind of inlet airflow amount real time computation system |
| CN110374763A (en) * | 2019-06-28 | 2019-10-25 | 南京理工大学 | Solid rocket ramjet air intake duct flow adjusts experimental provision |
| CN113063601A (en) * | 2021-03-30 | 2021-07-02 | 大连理工大学 | Aircraft auxiliary power unit jet-nozzle test system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH061297A (en) * | 1992-06-23 | 1994-01-11 | Mitsubishi Heavy Ind Ltd | Air intake device for aircraft |
| CN1081493A (en) * | 1992-07-07 | 1994-02-02 | 迪霍华德公司 | The S shape conduit of turbo-jet aircraft engine |
| US20090154522A1 (en) * | 2007-12-18 | 2009-06-18 | Weston Aerospace Limited | Temperature sensor and method for measuring temperature |
| CN103115747A (en) * | 2012-12-21 | 2013-05-22 | 中国飞行试验研究院 | Large-size composite material air inlet passage measuring rake |
| CN205203420U (en) * | 2015-10-23 | 2016-05-04 | 中国飞行试验研究院 | A APU intake duct for flight test |
-
2017
- 2017-11-06 CN CN201711083300.0A patent/CN108001709A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH061297A (en) * | 1992-06-23 | 1994-01-11 | Mitsubishi Heavy Ind Ltd | Air intake device for aircraft |
| CN1081493A (en) * | 1992-07-07 | 1994-02-02 | 迪霍华德公司 | The S shape conduit of turbo-jet aircraft engine |
| US20090154522A1 (en) * | 2007-12-18 | 2009-06-18 | Weston Aerospace Limited | Temperature sensor and method for measuring temperature |
| CN103115747A (en) * | 2012-12-21 | 2013-05-22 | 中国飞行试验研究院 | Large-size composite material air inlet passage measuring rake |
| CN205203420U (en) * | 2015-10-23 | 2016-05-04 | 中国飞行试验研究院 | A APU intake duct for flight test |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109459098A (en) * | 2018-09-29 | 2019-03-12 | 中国飞行试验研究院 | A kind of inlet airflow amount real time computation system |
| CN110374763A (en) * | 2019-06-28 | 2019-10-25 | 南京理工大学 | Solid rocket ramjet air intake duct flow adjusts experimental provision |
| CN113063601A (en) * | 2021-03-30 | 2021-07-02 | 大连理工大学 | Aircraft auxiliary power unit jet-nozzle test system |
| CN113063601B (en) * | 2021-03-30 | 2022-01-04 | 大连理工大学 | Aircraft auxiliary power unit jet-nozzle test system |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180508 |
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| RJ01 | Rejection of invention patent application after publication |