CN111903213B - Measuring profile of nose airspeed head - Google Patents
Measuring profile of nose airspeed head Download PDFInfo
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- CN111903213B CN111903213B CN200710081190.4A CN200710081190A CN111903213B CN 111903213 B CN111903213 B CN 111903213B CN 200710081190 A CN200710081190 A CN 200710081190A CN 111903213 B CN111903213 B CN 111903213B
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Abstract
The invention belongs to the technology of atmospheric parameter measurement, and relates to improvement of a nose airspeed head. The measuring device comprises a streamline-shaped rotating surface [1] positioned at the front end of the airspeed head and a second cylindrical surface [4] positioned at the rear end of the airspeed head, and is characterized in that a first cylindrical surface [2] and a conical surface [3] are sequentially arranged between the streamline-shaped rotating surface [1] and the second cylindrical surface [4], the streamline-shaped rotating surface [1], the first cylindrical surface [2], the conical surface [3] and the second cylindrical surface [4] are mutually connected to form a measuring profile of the airspeed head, and an attack angle measuring hole is formed in the conical surface [3 ]. The invention increases the function of measuring the attack angle on the basis of meeting the dynamic and static pressure measurement requirements, and has the capability of compensating the static pressure position error with high precision and full range.
Description
Technical Field
The invention belongs to the technology of atmospheric parameter measurement, and relates to improvement of a nose airspeed head.
Background
Airspeedtubes are a very important measurement tool on aircraft. The measuring profile of the existing aircraft nose airspeed head consists of a streamline-shaped rotating surface 1 positioned at the front end of the airspeed head and a cylindrical surface 4 positioned at the rear end of the airspeed head, and the measuring profile can only measure dynamic and static pressure parameters and cannot measure attack angle parameters. Special attack angle parameter measuring devices are required to be additionally arranged. When the pitot tube is mounted at a certain position on the aircraft, the static pressure sensed by the pitot tube is disturbed by the aircraft around the flow field, and is different from the atmospheric static pressure at the flight altitude, which is not the true static pressure, and the difference is usually called as static pressure position error or position error for short. The static pressure position error is different along with the installation position of the airspeed head and the appearance of the airplane, and changes along with the Mach number and the attack angle, so that larger errors of height measurement, speed measurement and the like are caused, and the static pressure position error increasingly becomes a serious problem influencing the safety, the economy and the tactical technical performance of the airplane. The profile of the streamline-shaped rotating surface 1 in the existing measuring profile has poor capability of compensating static pressure position errors, and the requirements of high precision and full-range compensation are difficult to meet.
Disclosure of Invention
The purpose of the invention is: the aircraft nose airspeed head measurement molded surface which can simultaneously measure dynamic and static pressure parameters and attack angle parameters and has high-precision full-range static pressure position error compensation capability is provided so as to meet the development requirements of a certain novel aircraft.
The technical scheme of the invention is as follows: a measuring profile of a nose airspeed head comprises a streamline rotating surface 1 positioned at the front end of the airspeed head and a second cylindrical surface 4 positioned at the rear end of the airspeed head, wherein a static pressure measuring hole is formed in the surface of the streamline rotating surface 1, and a total pressure measuring hole is formed in the front end of the streamline rotating surface 1, and the measuring profile is characterized in that a first cylindrical surface 2 and a conical surface 3 are sequentially arranged between the streamline rotating surface 1 and the second cylindrical surface 4, the streamline rotating surface 1, the first cylindrical surface 2, the conical surface 3 and the second cylindrical surface 4 are mutually connected to form the measuring profile of the airspeed head, the rear end surface of the streamline rotating surface 1 is smoothly connected with the front end surface of the first cylindrical surface 2, the diameter of the rear end surface of the first cylindrical surface 2 is equal to the diameter of the small end of the conical surface 3 and is connected with the small diameter end, the rear end surface of the conical surface 3 is a large diameter end, the diameter of the end surface is equal to the diameter of the second cylindrical surface 4 and is connected, an attack angle measuring hole is formed in the conical surface 3;
setting: the axial distance from the cone tip point A of the streamline rotating surface 1 to the vertical section where the static pressure measuring hole is located is X0; the axial distance from the conical tip point A of the streamline rotating surface 1 to the vertical section where the maximum radius R0 of the streamline rotating surface 1 is located is L; the axial distance from the vertical section where the maximum radius R0 of the streamline rotating surface 1 is located to the connecting surface of the streamline rotating surface 1 and the first cylindrical surface 2 is L1, the axial length of the first cylindrical surface 2 is L2, and the radius of the first cylindrical surface is R2; the axial length of the conical surface 3 is L3; the axial length of the second cylindrical surface 4 is L4, and its radius is R3; then:
(1)L＝50～130mm；L1＝40～100mm；L2＝40～100mm；L3＝15～70mm；L4＝300～500mm；R0＝8～20mm；R2＝8～16mm；R3＝15～30mm；X0＝15～130mm；
(2) the generatrix equation of the streamlined rotating surface 1 is as follows: taking the cone cusp point A as an origin, taking the axis of the streamline rotating surface 1 as an X axis of a horizontal coordinate, and taking a straight line passing through the point A and perpendicular to the X axis as an R axis, the generatrix equation of the streamline rotating surface 1 is as follows:
when X is less than or equal to L:
when L < X ≦ L + L1:
in the formulas (1) and (2), X is the abscissa of any point on the generatrix of the streamlined rotating surface 1, and R is the ordinate of any point on the generatrix of the streamlined rotating surface 1.
The invention has the advantages that: the function of measuring the attack angle is added on the basis of meeting the dynamic and static pressure measurement requirements, and the static pressure position error compensation capability with high precision and full range is realized. Wind tunnel tests and test flight tests prove that the residual static pressure position error completely meets the tolerance requirement specified by GJB1623 general Specification for designing and installing static pressure systems, and the residual error of an attack angle meets the requirement of a novel airplane.
Drawings
Fig. 1 is a schematic structural view of the present invention.
Detailed Description
The present invention is described in further detail below. Referring to fig. 1, the measuring profile of the aircraft nose airspeed head comprises a streamline-shaped rotating surface 1 positioned at the front end of the airspeed head and a second cylindrical surface 4 positioned at the rear end of the airspeed head, wherein a static pressure measuring hole is formed in the surface of the streamline-shaped rotating surface 1, and a total pressure measuring hole is formed in the front end of the streamline-shaped rotating surface 1. The device is characterized in that a first cylindrical surface 2 and a conical surface 3 are sequentially arranged between a streamline-shaped rotating surface 1 and a second cylindrical surface 4, the streamline-shaped rotating surface 1, the first cylindrical surface 2, the conical surface 3 and the second cylindrical surface 4 are connected with each other to form a measuring molded surface of the airspeed tube, the rear end surface of the streamline-shaped rotating surface 1 is smoothly connected with the front end surface of the first cylindrical surface 2, the diameter of the rear end surface of the first cylindrical surface 2 is equal to the diameter of the small end of the conical surface 3 and is connected with the small diameter end, the rear end surface of the conical surface 3 is a large diameter end, the diameter of the end surface is equal to the diameter of the second cylindrical surface 4 and is connected with the front end surface of the second cylindrical surface 4, and an attack angle measuring hole is formed in the conical.
The two angle of attack survey holes are located two vertexes on the upper and lower of the axial middle section of the conical surface 3, the axis of the angle of attack survey hole is the normal of the two vertexes, and the diameter d of the angle of attack survey hole is 0.8-1.4 mm.
The axial distance from the cone tip point A of the streamline rotating surface 1 to the vertical section where the static pressure measuring hole is located is X0; the axial distance from the conical tip point A of the streamline rotating surface 1 to the vertical section where the maximum radius R0 of the streamline rotating surface 1 is located is L; the axial distance from the vertical section where the maximum radius R0 of the streamline rotating surface 1 is located to the connecting surface of the streamline rotating surface 1 and the first cylindrical surface 2 is L1, the axial length of the first cylindrical surface 2 is L2, and the radius of the first cylindrical surface is R2; the axial length of the conical surface 3 is L3; the axial length of the second cylindrical surface 4 is L4, and its radius is R3; then:
(1)L＝50～130mm；L1＝40～100mm；L2＝40～100mm；L3＝15～70mm；L4＝300～500mm；R0＝8～20mm；R2＝8～16mm；R3＝15～30mm；X0＝15～130mm；
(2) the generatrix equation of the streamlined rotating surface 1 is as follows: taking the cone cusp point A as an origin, taking the axis of the streamline rotating surface 1 as an X axis of a horizontal coordinate, and taking a straight line passing through the point A and perpendicular to the X axis as an R axis, the generatrix equation of the streamline rotating surface 1 is as follows:
when X is less than or equal to L:
when L < X ≦ L + L1:
in the above formulas (1) and (2), X is the abscissa of any point on the generatrix of the streamlined rotating surface 1, and R is the ordinate of any point on the generatrix of the streamlined rotating surface 1. The test flight of the airspeed head with the streamline-shaped rotating surface 1 bus in cooperation with a certain airplane proves that the compensation effect is satisfactory.
Examples are given.
In one embodiment of the invention, L ═ 125 mm; l1 ═ 70 mm; l2 ═ 77 mm; l3 ═ 38 mm; l4 ═ 410 mm; r0 ═ 14 mm; r2 ═ 12.8 mm; r3 ═ 22 mm; x0 ═ 66 mm.
Claims (3)
1. A measuring profile of a nose airspeed head comprises a streamline rotating surface [1] positioned at the front end of the airspeed head and a second cylindrical surface [4] positioned at the rear end of the airspeed head, wherein a static pressure measuring hole is formed in the surface of the streamline rotating surface [1], a total pressure measuring hole is formed in the front end of the streamline rotating surface [1], the measuring profile is characterized in that a first cylindrical surface [2] and a conical surface [3] are sequentially arranged between the streamline rotating surface [1] and the second cylindrical surface [4], the streamline rotating surface [1], the first cylindrical surface [2], the conical surface [3] and the second cylindrical surface [4] are mutually connected to form the measuring profile of the airspeed head, the rear end surface of the streamline rotating surface [1] is smoothly connected with the front end surface of the first cylindrical surface [2], the rear end surface of the first cylindrical surface [2] is equal to the small end diameter of the conical surface [3] and is connected with the small diameter end, the rear end face of the conical surface [3] is a large-diameter end, the diameter of the end face is equal to that of the second cylindrical surface [4] and is connected with the front end face of the second cylindrical surface [4], and an attack angle measuring hole is formed in the conical surface [3 ];
setting: the axial distance from the cone tip point A of the streamline-shaped rotating surface [1] to the vertical section where the static pressure measuring hole is located is X0; the axial distance from the conical tip point A of the streamline-shaped rotating surface [1] to the vertical section where the maximum radius R0 of the streamline-shaped rotating surface [1] is positioned is L; the axial distance from the vertical section where the maximum radius R0 of the streamline rotating surface [1] is located to the connecting surface of the streamline rotating surface [1] and the first cylindrical surface [2] is L1, the axial length of the first cylindrical surface [2] is L2, and the radius of the first cylindrical surface is R2; the axial length of the conical surface [3] is L3; the axial length of the second cylindrical surface [4] is L4, and the radius of the second cylindrical surface is R3; then:
(1)L＝50～130mm；L1＝40～100mm；L2＝40～100mm；L3＝15～70mm；L4＝300～500mm；R0＝8～20mm；R2＝8～16mm；R3＝15～30mm；X0＝15～130mm；
(2) the generatrix equation of the streamline rotation surface [1] is as follows: taking the cone cusp point A as an original point, taking the axis of the streamline rotating surface [1] as an X axis of a horizontal coordinate, and taking a straight line which passes through the point A and is vertical to the X axis as an R axis, the generatrix equation of the streamline rotating surface [1] is as follows:
when X is less than or equal to L:
when L < X ≦ L + L1:
in the formulas (1) and (2), X is the abscissa of any point on the generatrix of the streamline rotation surface [1], and R is the ordinate of any point on the generatrix of the streamline rotation surface [1 ].
2. The measuring profile of the aircraft nose airspeed head as claimed in claim 1, wherein the angle of attack measuring hole has two, locate two summits on the upper and lower of the axial middle section of the conical surface [3], the axis of the angle of attack measuring hole is the normal of the two summits, the diameter d of the angle of attack measuring hole is 0.8-1.4 mm.
3. The measurement profile of an aircraft nose pitot tube as claimed in claim 1 or claim 2, wherein L is 125 mm; l1 ═ 70 mm; l2 ═ 77 mm; l3 ═ 38 mm; l4 ═ 410 mm; r0 ═ 14 mm; r2 ═ 12.8 mm; r3 ═ 22 mm; x0 ═ 66 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200710081190.4A CN111903213B (en) | 2007-04-23 | 2007-04-23 | Measuring profile of nose airspeed head |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200710081190.4A CN111903213B (en) | 2007-04-23 | 2007-04-23 | Measuring profile of nose airspeed head |
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| Publication Number | Publication Date |
|---|---|
| CN111903213B true CN111903213B (en) | 2012-09-12 |
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| CN200710081190.4A Active CN111903213B (en) | 2007-04-23 | 2007-04-23 | Measuring profile of nose airspeed head |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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2007
- 2007-04-23 CN CN200710081190.4A patent/CN111903213B/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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