CN104340377B - A kind of baroport correction of the flank shape bulge of light aerocraft - Google Patents
A kind of baroport correction of the flank shape bulge of light aerocraft Download PDFInfo
- Publication number
- CN104340377B CN104340377B CN201310337568.8A CN201310337568A CN104340377B CN 104340377 B CN104340377 B CN 104340377B CN 201310337568 A CN201310337568 A CN 201310337568A CN 104340377 B CN104340377 B CN 104340377B
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- CN
- China
- Prior art keywords
- baroport
- correction
- circle
- flank shape
- fuselage
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Abstract
Aerodynamic Configuration of Aireraft design field of the present invention, particularly relates to the baroport correction of the flank shape bulge of a kind of light aerocraft.The correction of the flank shape bulge of this baroport is: take the midpoint o of the light aerocraft former baroport line of centres, o point is perpendicular to aircraft plane of symmetry direction translation 6mm outside fuselage and generates bulge summit p, the radius circle as 100mm is done at fuselage surface with o for the center of circle, take two end points a of this circle arbitrary diameter projected on circle on fuselage, b, take two end points c of the upper diameter perpendicular with this diameter of this projection circle, d, with a, p, b 3 is circular arc line apb, with c, p, d 3 is circular arc line cpd, the geometric surface that circular arc line cpd generates with circular arc line apb for crestal line sweeping is intersected with fuselage, i.e. generate the correction of the flank shape bulge of this baroport.The correction of the flank shape bulge of this baroport can reduce pressure reduction 150pa at light aerocraft baroport, and when flight speed is 120 joint, indicator air speed is about 4 joints with the reduction amount of the difference absolute value of calibrated airspeed.
Description
Technical field
Aerodynamic Configuration of Aireraft design field of the present invention, particularly relates to the baroport correction of the flank shape drum of a kind of light aerocraft
Bag.
Background technology
The error restriction of aircraft airspeed system is strict by CCAR23.1323 and 1325 clauses.Consider quiet
Pressure systematic error and airspeed system error, when speed is more than 100 joint, indicator air speed needs little with the absolute value of the difference of calibrated airspeed
In 3 joints.Certain light aerocraft pitot static calibrations flight test result shows, under 0 degree of state of wing flap, indicator air speed is less than calibrated air speed 5
To 7 joints, it is unsatisfactory for airworthiness requirement.Therefore, need to consider adjust baroport position or carry out correction of the flank shape in existing baroport position.
Summary of the invention
The technical problem to be solved in the present invention:
Design correction of the flank shape bulge in light aerocraft baroport position so that static pressure measurement position projection, thus reduce instruction
Air speed and the absolute value of the difference of calibrated airspeed, to meet CCAR23 portion code requirement, need not change interior of aircraft structure simultaneously.
Technical scheme:
In conjunction with existing flight test result, by CFD computational analysis, meet in the design of light aerocraft baroport position and make
With the correction of the flank shape bulge required.
The baroport correction of the flank shape bulge of a kind of light aerocraft, the correction of the flank shape bulge of this baroport is: take in the former baroport of light aerocraft
Midpoint o, the o point of heart line is perpendicular to aircraft plane of symmetry direction translation 6mm outside fuselage and generates bulge summit p, exists with o for the center of circle
Fuselage surface does the circle that radius is 100mm, takes two end points a, b of this circle arbitrary diameter projected on circle on fuselage, takes
Two end points c, d of the upper diameter perpendicular with this diameter of this projection circle, are circular arc line apb with a, p, b at 3, with c, p, d tri-
Point is circular arc line cpd, is intersected with fuselage by the geometric surface that circular arc line cpd generates with circular arc line apb for crestal line sweeping, i.e. generates this
Baroport correction of the flank shape bulge.
Beneficial effects of the present invention:
In conjunction with existing flight test result, shown by aerodynamic analysis and CFD Calculation results, this baroport correction of the flank shape drum
Bag can reduce pressure reduction 150pa at light aerocraft baroport, when flight speed is 120 joint, and indicator air speed and the difference of calibrated airspeed
The reduction amount of absolute value is about 4 joints, can meet CCAR23 portion code requirement, and correction of the flank shape bulge planform is the most easily implemented, simultaneously
Interior of aircraft structure need not be changed.
Accompanying drawing explanation
Fig. 1 is baroport correction of the flank shape bulge position view；
Fig. 2 is baroport correction of the flank shape bulge schematic diagram；In figure, 1 is the correction of the flank shape bulge of this baroport, 2 quiet in correction of the flank shape bulge
Pressure hole site, 3 is bulge range circle, and its radius is 100mm, and 4 is former fuselage surface, and 5 is bulge summit, and it is away from former fuselage surface
6mm。
Detailed description of the invention
Add correction of the flank shape bulge in certain light aerocraft baroport position, static pressure measurement point projection can be made, and then reduce this position
Put institute's pressure measurement poor, reach the purpose reducing aircraft indicator air speed with the difference absolute value of calibrated airspeed.The correction of the flank shape bulge of this baroport,
Apex height is 6mm, and bulge range circle radius is 100mm, understands through CFD computational analysis, after adding correction of the flank shape bulge, can make light-duty
The indicator air speed of aircraft is reduced to 1 to 3 joints with the difference absolute value of calibrated airspeed, thus meets CCAR23 portion code requirement.
Claims (1)
1. a baroport correction of the flank shape bulge for light aerocraft, is characterized in that, the correction of the flank shape bulge of this baroport is: take light aerocraft former quiet
Midpoint o, the o point of the pressure hole line of centres is perpendicular to aircraft plane of symmetry direction translation 6mm outside fuselage and generates bulge summit p, with o is
The circle that radius is 100mm is done, at fuselage surface, in the center of circle, takes two end points of this circle arbitrary diameter projected on circle on fuselage
A, b, take two end points c, d of the upper diameter the most perpendicular with this diameter of this projection circle, be circular arc line apb with a, p, b at 3, with c,
P, d 3 are circular arc line cpd, are intersected with fuselage, i.e. by the geometric surface that circular arc line cpd generates with circular arc line apb for crestal line sweeping
Generate the correction of the flank shape bulge of this baroport.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310337568.8A CN104340377B (en) | 2013-08-05 | 2013-08-05 | A kind of baroport correction of the flank shape bulge of light aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310337568.8A CN104340377B (en) | 2013-08-05 | 2013-08-05 | A kind of baroport correction of the flank shape bulge of light aerocraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104340377A CN104340377A (en) | 2015-02-11 |
| CN104340377B true CN104340377B (en) | 2016-09-28 |
Family
ID=52496970
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310337568.8A Expired - Fee Related CN104340377B (en) | 2013-08-05 | 2013-08-05 | A kind of baroport correction of the flank shape bulge of light aerocraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104340377B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3002382A (en) * | 1955-08-16 | 1961-10-03 | North American Aviation Inc | Static pressure error compensator |
| EP2415670A1 (en) * | 2009-03-30 | 2012-02-08 | The Society of Japanese Aerospace Companies | Method of reducing noise of air vehicle, leg structure of air vehicle and air vehicle |
| CN103033334A (en) * | 2012-12-19 | 2013-04-10 | 中国航空工业集团公司沈阳空气动力研究所 | Testing device of flow measurement and control used in aerospace |
| CN202938972U (en) * | 2012-12-04 | 2013-05-15 | 中信海直通用航空维修工程有限公司 | Dynamic-static pressure tester for helicopter out-field maintenance |
| CN203024954U (en) * | 2013-01-09 | 2013-06-26 | 浙江大学 | Frame bent device for flow field test of wind tunnel |
-
2013
- 2013-08-05 CN CN201310337568.8A patent/CN104340377B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3002382A (en) * | 1955-08-16 | 1961-10-03 | North American Aviation Inc | Static pressure error compensator |
| EP2415670A1 (en) * | 2009-03-30 | 2012-02-08 | The Society of Japanese Aerospace Companies | Method of reducing noise of air vehicle, leg structure of air vehicle and air vehicle |
| CN202938972U (en) * | 2012-12-04 | 2013-05-15 | 中信海直通用航空维修工程有限公司 | Dynamic-static pressure tester for helicopter out-field maintenance |
| CN103033334A (en) * | 2012-12-19 | 2013-04-10 | 中国航空工业集团公司沈阳空气动力研究所 | Testing device of flow measurement and control used in aerospace |
| CN203024954U (en) * | 2013-01-09 | 2013-06-26 | 浙江大学 | Frame bent device for flow field test of wind tunnel |
Non-Patent Citations (1)
| Title |
|---|
| 浅析飞机静压孔检查注意事项;刘寿军;《科学与财富》;20120831(第8期);第183页 * |
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| Publication number | Publication date |
|---|---|
| CN104340377A (en) | 2015-02-11 |
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