CN102128946A - Side sliding sensor of air-pressure helicopter - Google Patents
Side sliding sensor of air-pressure helicopter Download PDFInfo
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- CN102128946A CN102128946A CN 201010623595 CN201010623595A CN102128946A CN 102128946 A CN102128946 A CN 102128946A CN 201010623595 CN201010623595 CN 201010623595 CN 201010623595 A CN201010623595 A CN 201010623595A CN 102128946 A CN102128946 A CN 102128946A
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- helicopter
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- sensor
- barometer
- side sliding
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Abstract
The invention provides a side sliding sensor of an air-pressure helicopter, belonging to the technical field of an aerospace sensor. The side sliding sensor of the air-pressure helicopter is characterized by comprising a left air-pressure pipe, a left barometer, a right air-pressure pipe, a right barometer and a micro processor, wherein the side sliding sensor of the air-pressure helicopter is arranged below the helicopter; when the helicopter is in side sliding, the air flow speed difference on two sides of the sensor causes the air pressure to change, and the micro processor can measure the air pressure change circumstances on two sides of the sensor by comparing the measuring values of the barometers on the left and right sides, thereby calculating the size of the side sliding speed by a lookup method. The side sliding sensor in the invention considers and avoids the influence of complicated flowing fields of the helicopter through the pre-measured practical data table, and can precisely measure the side sliding angle of the helicopter.
Description
Technical field
The present invention is the sensor that is used to measure the helicopter slipspeed, can measure the slipspeed of helicopter accurately, reliably.Be mainly used in technical fields such as Aero-Space, helicopter and unmanned plane.
Background technology
Sideslip is an important offline mode of helicopter, shows as the crabbing of helicopter.It is very important for the safe flight of helicopter to measure slipspeed exactly.For example in the turning process, need to eliminate and break away to realize coordinate turn.Yet because helicopter flight speed is low, the flow field is complicated, so there is not effective yaw angle measuring method at present.
The present invention detects the draught head of helicopter sideslip process middle machine body both sides, and measures slipspeed by two barometer sensors.Because the present invention will be installed in the fuselage below, so avoided the direct impact of rotor purling.In addition, because the present invention adopts look-up table to measure slipspeed, thereby counted and avoided the influence of complex flowfield.Flight the invention has the advantages that: in light weight, volume is little, measures accurately, and is simple in structure, the reliability height; In addition,, can be installed in the below of helicopter (especially depopulated helicopter) easily, can not impact flight because this sensor bulk is little
Summary of the invention
The object of the present invention is to provide a kind of with the sensor of measuring the helicopter slipspeed.
The invention is characterized in, contain: shell, left side pneumatic tube, left side barometer, right side pneumatic tube, right side barometer and microprocessor, wherein:
Vapour-pressure type helicopter sideslip sensor is installed in the helicopter below, when breakking away appearred in helicopter, under the effect of sideslip air-flow, a sensor side down with the wind stopped owing to the sideslip air-flow forms the stationary point before pneumatic tube, a leeward side is because air velocity increases, and it is poor that air velocity appears in the sensor both sides; According to bernoulli principle, the air velocity variation can cause air pressure change, therefore:
A sensor side air pressure down with the wind raises, and a leeward side air pressure reduces; Microprocessor is by contrast left side barometer and the barometrical measured value in right side, air pressure change situation that can the survey sensor both sides, and then can calculate the size of slipspeed;
Because the flow field of different helicopters, different installation sites there are differences, so before using the present invention, need experimentize; According to actual conditions, measure the corresponding tables of slipspeed and left and right sides air pressure difference; At helicopter in-flight, microprocessor can obtain the slipspeed of helicopter according to the left and right sides barometer difference of actual measurement by tabling look-up.
The invention has the advantages that: measure accurately, simple in structure, the reliability height, in light weight, cheap.Be fit to helicopter, especially depopulated helicopter is installed and used.
Description of drawings
The scheme of installation of Fig. 1 vapour-pressure type helicopter sideslip sensor on helicopter.
Fig. 2 is the structural representation of vapour-pressure type helicopter sideslip sensor.
Among the figure, 1. helicopter, 2. shell, 3. left side pneumatic tube, 4. left side barometer, 5. right side pneumatic tube, 6. right side barometer, 6. microprocessor.
Embodiment
Vapour-pressure type helicopter sideslip sensor mainly is made up of shell (2), left side pneumatic tube (3), left side barometer (4), right side pneumatic tube (5), right side barometer (6) and microprocessor (7).
Vapour-pressure type helicopter sideslip sensor is installed in helicopter (1) below.Left side pneumatic tube (3), left side barometer (4), right side pneumatic tube (5), right side barometer (6) and microprocessor (7) are all along the axis arranged of shell (2) therein.When breakking away appearred in helicopter (1), under the effect of sideslip air-flow, it is poor that vapour-pressure type helicopter sideslip sensor both sides produce slipspeed.According to bernoulli principle as can be known, the air velocity variation can cause air pressure change:
Wherein, p
A left sideAnd V
A left sideBe air pressure and the air velocity in the left side pneumatic tube (3), p
RightAnd V
RightBe air pressure and the air velocity in the right side pneumatic tube (5), ρ is an atmospheric density, and C is a constant.
The side of facining the wind at vapour-pressure type helicopter sideslip sensor stops owing to the sideslip air-flow forms the stationary point before pneumatic tube, and air pressure raises; The sideslip air-flow increases a leeward side air velocity, and air pressure reduces.Microprocessor (7) can be measured the air pressure change situation of vapour-pressure type helicopter sideslip sensor (2) both sides, and then can calculate the size of helicopter (1) slipspeed by the measured value of contrast left side barometer (4) and right side barometer (6).
Because the flow field of different helicopters and different installation sites there are differences, so before using the present invention, need experimentize.According to actual conditions, measure the corresponding tables of slipspeed and left and right sides air pressure difference.At helicopter (1) in-flight, microprocessor (7) can obtain the slipspeed of helicopter (1) according to the left and right sides barometer difference of actual measurement by tabling look-up.
Claims (1)
1. vapour-pressure type helicopter sideslip sensor is characterized in that, contains: shell, left side pneumatic tube, left side barometer, right side pneumatic tube, right side barometer and microprocessor, wherein:
Vapour-pressure type helicopter sideslip sensor is installed in the helicopter below, when breakking away appears in helicopter, under the effect of sideslip air-flow, a sensor side down with the wind stops owing to the sideslip air-flow forms the stationary point before pneumatic tube, a leeward side is because air flow velocity increase under the effect of breakking away, it is poor that air velocity appears in the sensor both sides, therefore:
A sensor side air pressure down with the wind raises, and a leeward side air pressure reduces; Microprocessor is by contrast left side barometer and the barometrical measured value in right side, air pressure change situation that can the survey sensor both sides, and then can calculate the size of slipspeed;
Because the flow field of different helicopters, different installation sites there are differences, so before using the present invention, need experimentize; According to actual conditions, measure the corresponding tables of slipspeed and left and right sides air pressure difference; At helicopter in-flight, microprocessor can obtain the slipspeed of helicopter according to the left and right sides barometer difference of actual measurement by tabling look-up.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010623595 CN102128946A (en) | 2010-12-30 | 2010-12-30 | Side sliding sensor of air-pressure helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010623595 CN102128946A (en) | 2010-12-30 | 2010-12-30 | Side sliding sensor of air-pressure helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102128946A true CN102128946A (en) | 2011-07-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010623595 Pending CN102128946A (en) | 2010-12-30 | 2010-12-30 | Side sliding sensor of air-pressure helicopter |
Country Status (1)
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| CN (1) | CN102128946A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6073084A (en) * | 1997-03-03 | 2000-06-06 | Aerospatiale Societe Nationale Industrielle | Process and device for verifying the consistency of the measurements from an angle-of-attack probe |
| US6101429A (en) * | 1998-04-07 | 2000-08-08 | Tao Of Systems Integration, Inc. | Broad-range, multi-directional aircraft airspeed measuring system |
| US6772976B1 (en) * | 2002-04-10 | 2004-08-10 | Honeywell International, Inc. | Sensor for measuring wind angle |
| CN101750514A (en) * | 2010-01-27 | 2010-06-23 | 中国科学院光电研究院 | Wind speed and direction real-time measuring method and device of high-altitude sky-parking aircraft |
| CN101923101A (en) * | 2010-05-12 | 2010-12-22 | 西安交通大学 | Digital crosswind sensor for monitoring wind speed and wind direction of crosswind |
-
2010
- 2010-12-30 CN CN 201010623595 patent/CN102128946A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6073084A (en) * | 1997-03-03 | 2000-06-06 | Aerospatiale Societe Nationale Industrielle | Process and device for verifying the consistency of the measurements from an angle-of-attack probe |
| US6101429A (en) * | 1998-04-07 | 2000-08-08 | Tao Of Systems Integration, Inc. | Broad-range, multi-directional aircraft airspeed measuring system |
| US6772976B1 (en) * | 2002-04-10 | 2004-08-10 | Honeywell International, Inc. | Sensor for measuring wind angle |
| CN101750514A (en) * | 2010-01-27 | 2010-06-23 | 中国科学院光电研究院 | Wind speed and direction real-time measuring method and device of high-altitude sky-parking aircraft |
| CN101923101A (en) * | 2010-05-12 | 2010-12-22 | 西安交通大学 | Digital crosswind sensor for monitoring wind speed and wind direction of crosswind |
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Application publication date: 20110720 |