CN207763881U - A kind of Multi-functional probe for measuring rotor downwash - Google Patents
A kind of Multi-functional probe for measuring rotor downwash Download PDFInfo
- Publication number
- CN207763881U CN207763881U CN201820056854.5U CN201820056854U CN207763881U CN 207763881 U CN207763881 U CN 207763881U CN 201820056854 U CN201820056854 U CN 201820056854U CN 207763881 U CN207763881 U CN 207763881U
- Authority
- CN
- China
- Prior art keywords
- pressure
- downwash
- functional probe
- utility
- gyroplane
- Prior art date
- 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.)
- Active
Links
Landscapes
- Indicating Or Recording The Presence, Absence, Or Direction Of Movement (AREA)
Abstract
The utility model belongs to aircraft atmosphere parameter measurement technology, is related to a kind of Multi-functional probe for measuring rotor downwash.There are two the pressure experience hole for being in 90 ° of angles on the Multi-functional probe tube body, one of pressure experience hole is perpendicular to downwash flow direction, another pressure experience hole face downwash flow direction.The utility model increases by two pressure ports in 90 ° of angles on the pressure experience tube body of traditional Multi-functional probe, the measurement of gyroplane rotor downwash speed may be implemented by the pressure difference of holes in flight course, the incoming that can be used for experiencing Multi-functional probe is total, static pressure parameter is modified, to improve the impression precision of air data system.
Description
Technical field
The utility model belongs to aircraft atmosphere parameter measurement technology, is related to a kind of for measuring the more of rotor downwash
Function is popped one's head in.
Background technology
Multi-functional probe is the important component of gyroplane air data system, is installed on gyroplane down side
Pressure signal stagnation pressure and static pressure and can be transferred to atmospheric engine on impression machine, be counted as pressure altitude through atmospheric engine solution, refers to by top
Show the atmospheric parameters such as air speed, true air speed, Mach number, lifting speed, the angle of attack.
For gyroplane in flight, air-flow can be pressed towards obliquely downward, generate downward air-flow below rotor, referred to as descend gas washing
Stream.In flight, pitot is located at below rotor gyroplane, due to there is the influence of rotor downwash, total, static pressure hole of popping one's head in
Fly the horizontal velocity component generated before the existing aircraft of air velocity at place, also there is the vertical velocity component and water that downwash flow generates
Flat velocity component.When aircraft high-speed flight, downwash flow can ignore the measurement of pressure influence, and total, static pressure hole can be accurate
Experience total, the static pressure of fuselage in ground.When gyroplane hovers or flies at low speed, speed total, that downwash flow generates at static pressure hole
Component is affected to static pressure sense to account for principal element.Existing gyroplane air data system is popped one's head in using traditional pressure experience
Impression it is total, that static pressure parameter experiences precision at low speeds is poor.
Utility model content
Technical problem to be solved in the utility model is：A kind of novel Multi-functional probe is provided, rotor can be measured
Downwash flow speed can correct pressure measurement caused by existing gyroplane air data system is influenced by rotor downwash
Error.
The technical solution of the utility model is：A kind of Multi-functional probe for measuring rotor downwash, more work(
Can pop one's head on tube body there are two the pressure experience hole for being in 90 ° of angles, one of pressure experience hole perpendicular to downwash flow direction,
Another pressure experience hole face downwash flow direction.
The utility model has the beneficial effects that：The utility model Multi-functional probe, in the feeling of stress of traditional Multi-functional probe
By two pressure ports in 90 ° of angles are increased on tube body, gyroplane may be implemented by the pressure difference of holes in flight course
The measurement of rotor downwash speed, the incoming that can be used for experiencing Multi-functional probe is total, static pressure parameter is modified, to carry
The impression precision of high air data system.
Description of the drawings
Fig. 1 is the structural schematic diagram of the utility model Multi-functional probe；
Fig. 2 is gyroplane downwash flow flow field figure I；
Fig. 3 is gyroplane downwash flow flow field figure II；
Wherein, 1- pressure experiences hole.
Specific implementation mode
Specific embodiment of the present utility model is described further below in conjunction with the accompanying drawings.
Referring to Fig. 1, is influenced according to the fuselage of gyroplane and rotor airflow influence, Multi-functional probe tube body increase by two and be in
The pressure port of 90 ° of angles, the utility model downwash flow pressure tap trepanning mode are shown in Fig. 1.
Gyroplane floating state flow field is emulated using fluid emulation software (CFD), downwash flow can be obtained
Flow field, Fig. 2, Fig. 3 are gyroplane floating state downwash flow flow field figure.Under this state under one face of tube body pressure port
Airflow direction is washed, another hole is perpendicular to downwash flow direction, and the pressure of holes impression is the stagnation pressure and static pressure of downwash flow, through solution
Calculation can obtain effective downwash flow velocity amplitude.
Claims (1)
1. a kind of Multi-functional probe for measuring rotor downwash, it is characterized in that：Have two on the Multi-functional probe tube body
A is in the pressure experience hole of 90 ° of angles, and one of pressure experience hole is perpendicular to downwash flow direction, another pressure experience hole
Face downwash flow direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820056854.5U CN207763881U (en) | 2018-01-12 | 2018-01-12 | A kind of Multi-functional probe for measuring rotor downwash |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820056854.5U CN207763881U (en) | 2018-01-12 | 2018-01-12 | A kind of Multi-functional probe for measuring rotor downwash |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207763881U true CN207763881U (en) | 2018-08-24 |
Family
ID=63184314
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820056854.5U Active CN207763881U (en) | 2018-01-12 | 2018-01-12 | A kind of Multi-functional probe for measuring rotor downwash |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207763881U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111024298A (en) * | 2019-12-24 | 2020-04-17 | 太原航空仪表有限公司 | Adjustable total pressure probe |
| CN111157759A (en) * | 2019-12-24 | 2020-05-15 | 太原航空仪表有限公司 | Fixed differential pressure type attack angle sensor and use method |
| CN112977869A (en) * | 2021-02-25 | 2021-06-18 | 成都凯天电子股份有限公司 | Helicopter atmospheric data system rotor wing down-wash influence correction method |
| CN113624393A (en) * | 2021-06-22 | 2021-11-09 | 成都凯天电子股份有限公司 | Atmospheric data system and method with rotor downwash effect correction |
-
2018
- 2018-01-12 CN CN201820056854.5U patent/CN207763881U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111024298A (en) * | 2019-12-24 | 2020-04-17 | 太原航空仪表有限公司 | Adjustable total pressure probe |
| CN111157759A (en) * | 2019-12-24 | 2020-05-15 | 太原航空仪表有限公司 | Fixed differential pressure type attack angle sensor and use method |
| CN111024298B (en) * | 2019-12-24 | 2021-10-08 | 太原航空仪表有限公司 | Adjustable total pressure probe |
| CN112977869A (en) * | 2021-02-25 | 2021-06-18 | 成都凯天电子股份有限公司 | Helicopter atmospheric data system rotor wing down-wash influence correction method |
| LU501425A1 (en) * | 2021-02-25 | 2022-09-16 | Chengdu Caic Electronics Co Ltd | Method for correcting affection of rotor downwash with helicopter air data system |
| CN113624393A (en) * | 2021-06-22 | 2021-11-09 | 成都凯天电子股份有限公司 | Atmospheric data system and method with rotor downwash effect correction |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN207763881U (en) | A kind of Multi-functional probe for measuring rotor downwash | |
| CN102749181B (en) | Wind tunnel test method on basis of momentum theory | |
| McCroskey | Measurements of boundary layer transition, separation and streamline direction on rotating blades | |
| CN206407132U (en) | A kind of swept tip boring device for being used to suppress rotor noise | |
| CN205940856U (en) | Pick -up is always pressed in steam deicing | |
| CN105424267B (en) | A kind of probe for gyroplane total pressure measurement | |
| CN108303227A (en) | Aeroelastic effect wind tunnel test half model system and test method | |
| CN105424971B (en) | A kind of probe head of static pressure for the small tachometric survey of gyroplane | |
| CN107132376A (en) | A kind of acquisition methods of aircraft angle of attack fair curve | |
| CN208476493U (en) | Aeroelastic effect wind tunnel test half model system | |
| CN216209247U (en) | Vane type sensor for measuring pneumatic data | |
| CN205246692U (en) | A static pressure probe for little speed measurement of gyroplane | |
| Kleinert et al. | Aeroacoustics of High-Fidelity URANS Simulations of a Model Contra-Rotating Open Rotor with Mounting Pylon | |
| CN113419078B (en) | Wind vane type sensor for measuring pneumatic data | |
| CN113624393B (en) | Atmospheric data system and method with rotor downwash impact correction | |
| JP2807772B2 (en) | Pitot tube probe | |
| Carlson et al. | Sonic‐boom pressure‐field estimation techniques | |
| CN102175886A (en) | Pneumatic helicopter airspeed meter | |
| CN103809464A (en) | Simulation method for influence of shipboard effect of helicopter | |
| CN102323440A (en) | Biaxial airspeed detection system of helicopter | |
| CN207135083U (en) | A kind of analog output modulate circuit for air data computer test | |
| Watson et al. | Experimental Validation of the Unsteady CFD-Generated Airwake of the HMS Queen Elizabeth Aircraft Carrier | |
| Philipsen et al. | An overview of advanced propeller simulation tests in the german dutch wind tunnels (DNW) | |
| ROSS et al. | Dynamic wind tunnel tests on control of forebody vortices with suction | |
| Ehn | Measurements of static stability coefficients of an ogive delta wing model at transonic and supersonic speeds |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |