CN110940296A - Hypersonic aircraft rudder deflection angle measuring method - Google Patents
Hypersonic aircraft rudder deflection angle measuring method Download PDFInfo
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- CN110940296A CN110940296A CN201911043342.0A CN201911043342A CN110940296A CN 110940296 A CN110940296 A CN 110940296A CN 201911043342 A CN201911043342 A CN 201911043342A CN 110940296 A CN110940296 A CN 110940296A
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- deflection angle
- rotation
- control surface
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/26—Measuring arrangements characterised by the use of optical techniques for measuring angles or tapers; for testing the alignment of axes
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/22—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring angles or tapers; for testing the alignment of axes
Abstract
The invention discloses a method suitable for measuring rudder deflection angle of a hypersonic aircraft, which is characterized by comprising the following steps: firstly, a portable three-dimensional measuring device is used for measuring an included angle between the front and the back of rotation of the same plane on a control surface, then an equation set containing the deflection angle of the control surface as an unknown number is established through the geometrical relation between the front and the back of rotation of the measured plane, and the deflection angle of the control surface can be obtained by solving the equation set. The method aims at finally providing the deflection angle of the control surface of the hypersonic aircraft with a measurable plane, is simple and clear in the provided measuring method, portable in used equipment, free of special tools, and suitable for calibrating the deflection angle of the control surface of the hypersonic aircraft during final assembly and debugging in an outfield.
Description
Technical Field
The invention relates to a hypersonic aircraft rudder deflection angle measuring method, and belongs to the field of aerospace aircraft design.
Background
The hypersonic aircraft needs to measure a control surface deflection angle in the installation and debugging processes, and is used for control surface installation quality inspection, steering engine polarity detection and the like. However, in order to prevent problems caused by pneumatic heating, the exposed size of the rudder shaft of the aircraft is extremely short and is shielded or not exposed; the axis of the rudder shaft is difficult to find; the thickness of the control surface is changed along the spanwise direction and the chord length, and the upper surface and the lower surface are not parallel or vertical to the control axis even if the upper surface and the lower surface are planes, so that the upper surface and the lower surface cannot be directly used for measuring and determining the deflection angle of the control surface. Generally, a complex tool is adopted for measuring the rudder deflection angle, but during the general assembly of an aircraft and even the debugging of an external field, the rudder deflection angle needs to be simply and quickly measured, and the rudder deflection angle is calibrated.
Disclosure of Invention
The technical problem solved by the invention is as follows: the method is suitable for measuring the rudder surface rudder deflection angle of the hypersonic aircraft, simple equipment can be used for conveniently and quickly measuring the rudder deflection angle, and the rudder deflection angle is calibrated.
The technical scheme of the invention is as follows: a hypersonic aircraft rudder deflection angle measuring method is realized by the following steps: fixing an aircraft body or a control surface supporting seat, and measuring and drawing the spatial position of a certain measuring plane on a control surface before and after rotation by using a measuring instrument to obtain the rotation angle theta of the measuring plane before and after rotation; and establishing an equation set containing the deflection angle of the control surface as an unknown number through the geometrical relation of the measurement planes before and after rotation, and solving the equation set to obtain the deflection angle of the control surface.
Further, the system of equations is as follows:
r1＝cos(δ)*R1-sin(δ)*R3
r2＝R2
r3＝sin(δ)*R1+cos(δ)*R3
in the formula, the normal vector of the measurement plane after deflection is represented by R ═ R in the global coordinate system 0XYZ and the local coordinate system oxyz, respectively1,R2,R3]And r ═ r1,r2,r3](ii) a Delta is the control plane deflection angle.
Further, measuring and drawing the space position of the measuring plane before and after rotation by using a portable flexible arm three-coordinate measuring instrument or a laser scanning measuring instrument; and then determining the included angle theta between the front and the back of the rotation of the measuring plane.
Further, the measuring plane cannot be perpendicular to the rudder axis.
Further, the measuring plane is preferably a plane on the windward side.
Furthermore, the measuring point positions are marked on the measuring plane, and the spatial positions of the plane are obtained by picking up the measuring points before and after rotation.
Preferably, the measuring plane is parallel to the rudder shaft or the extension line of the rudder shaft, and the measured included angle theta between the front and the rear of the rotation is the rudder deflection angle delta.
Compared with the prior art, the invention has the beneficial effects that:
the method aims at finally providing the deflection angle of the control surface of the hypersonic aircraft with a measurable plane, is simple and clear in the provided measuring method, portable in used equipment, free of special tools, and suitable for the requirement of quickly calibrating the deflection angle of the control surface during final assembly of the hypersonic aircraft and debugging in an outfield.
Drawings
FIG. 1 is a schematic view of the measurement of the deflection angle of the control surface according to the present invention.
Detailed Description
The invention is further illustrated by the following examples.
The aircraft body or the control surface supporting seat is fixed, the portable flexible arm three-coordinate measuring instrument or a laser scanning measuring instrument (short for measuring instrument) is used for mapping the spatial position of the same plane (called as a measuring plane) on the control surface before and after rotation, and the rotation angle theta of the measuring plane before and after rotation is obtained through internal post-processing software of the measuring instrument. And establishing an equation set containing the deflection angle of the control surface as an unknown number through the geometrical relation of the measurement planes before and after rotation, and solving the equation set to obtain the deflection angle of the control surface.
For a clearer understanding of the invention, reference will first be made to the relevant symbols in fig. 1: a global coordinate system OXYZ; a rudder shaft 1; rudder shaft axis 2; initial control surface position 3; the position of the control surface is 4 after rotation; a measuring plane 5 corresponding to the initial position of the control surface; a corresponding measuring plane 6 after the control surface rotates; a measuring point 7 on the plane 5; a measuring point 8 on the plane 6; (the number of the measuring points on each plane is large, only a few of which are marked in the figureStem) local position vector r corresponding to the initial position plane 5a(ii) a Local position vector r corresponding to rotating rear plane 6b
The plane perpendicular to the rudder axis cannot be taken as a measuring plane. For the deflected front and rear control surfaces 3, 4 in the figure, the upper surface of the control surface is selected as the measuring plane. The control plane is only illustrated in the figure, and other partial planes may be used in practice. The angle theta of the upper surface is measured at different positions 5, 6. In order to improve the measurement accuracy: (1) selecting a plane with a larger size as much as possible; (2) the flatness of the measuring plane can be properly improved in the design and processing stages; (3) the same measuring points are adopted for multiple measurements as much as possible, measuring point positions 7 and 8 can be marked on the plane to be measured, and the marked measuring points are picked up each time so as to establish the spatial position of the plane; (4) a measuring instrument with high measuring precision is adopted as much as possible. The accuracy of the measurement of the control plane deflection angle depends on these four factors.
The deflection angle delta of the control surface can be calculated by using the rotation angle theta before and after the rotation of the measuring plane. The solution is derived as follows:
for the measurement plane, a global coordinate system 0XYZ and a local coordinate system oxyz are respectively defined, wherein the global coordinate system 0XYZ is fixedly connected with the ground, and the local coordinate system oxyz is fixedly connected to the control surface and rotates along with the control surface. Without loss of generality, for the convenience of identification, the global coordinate system 0XYZ is determined according to the initial position of the control surface: the Y axis points to the inside of the machine body along the direction of the rudder axis, the X axis points to the front of the machine body, the Z axis is vertical to the rudder surface, and the X, Y and Z are right-hand coordinate systems. The local coordinate system oxyz is initially oriented in the same global coordinate system and moves with the rudder surface deflection. The normal vector of the deflected measurement plane is respectively counted as R ═ R in the global coordinate system 0XYZ and the local coordinate system oxyz1,R2,R3]And r ═ r1,r2,r3]. R can be calculated according to a control surface design drawing or a digital analog, namely r1,r2,r3Are known.
For the control plane deflection angle δ, R and R have the following correspondence:
r＝Ly·R (1)
the euler angle is used to express the transformation relation of two coordinate systems,then
Then (1) is unfolded
r1＝cos(δ)*R1-sin(δ)*R3(2)
r2＝R2(3)
r3＝sin(δ)*R1+cos(δ)*R3(4)
And an included angle theta between the front and back rotation of the plane to be measured, namely an included angle theta between the position vectors before and after rotation. Since the local coordinate system of the initial position coincides with the global coordinate system, and there is no deformation in the rotation process of the control surface, the position vector of the initial position of the measurement plane in the global coordinate system is equal to the position vector r in the local coordinate system, then:
the equations (2) - (5) form an equation set, and the unknown number R can be obtained by solving the equation set1,R2,R3And delta, namely obtaining the rudder deflection angle delta.
The schematic diagram does not show an actual control surface, other forms are possible, any plane which is not perpendicular to the plane of the control shaft can be used as a measuring plane, and in order to improve the measuring precision, a plane on the windward side of the control surface is generally selected as the measuring plane.
In particular, if the measuring plane is parallel to the rudder axis or the extension of the rudder axis, the measured angle between the front and rear of the rotation is the rudder deflection angle, i.e. the rudder deflection angle
δ＝θ (6)
The portable flexible arm three-coordinate measuring instrument or the laser scanning measuring instrument and the computer can be portable, the rudder deflection angle can be conveniently calibrated in various occasions, and the device is particularly suitable for the external field environment.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications, equivalent variations and modifications made to the above embodiment according to the technical spirit of the present invention still fall within the scope of the technical solution of the present invention.
Claims (7)
1. A hypersonic aircraft rudder deflection angle measuring method is characterized by being achieved through the following mode: fixing an aircraft body or a control surface supporting seat, and measuring and drawing the spatial position of a certain measuring plane on a control surface before and after rotation by using a measuring instrument to obtain the rotation angle theta of the measuring plane before and after rotation; and establishing an equation set containing the deflection angle of the control surface as an unknown number through the geometrical relation of the measurement planes before and after rotation, and solving the equation set to obtain the deflection angle of the control surface.
2. The method of claim 1, wherein: the system of equations is as follows:
r1＝cos(δ)*R1-sin(δ)*R3
r2＝R2
r3＝sin(δ)*R1+cos(δ)*R3
in the formula, the normal vector of the measurement plane after deflection is represented by R ═ R in the global coordinate system 0XYZ and the local coordinate system oxyz, respectively1,R2,R3]And r ═ r1,r2,r3](ii) a Delta is the control plane deflection angle.
3. The method of claim 1, wherein: measuring and drawing the spatial position of the measurement plane before and after rotation by using a portable flexible arm three-coordinate measuring instrument or a laser scanning measuring instrument; and then determining the included angle theta between the front and the back of the rotation of the measuring plane.
4. The method of claim 1, wherein: the measuring plane cannot be perpendicular to the rudder axis.
5. The method of claim 1, wherein: the measuring plane is preferably a plane on the windward side.
6. The method of claim 3, wherein: the measuring point positions are marked on the measuring plane, and the spatial positions of the plane are obtained by picking up the measuring points before and after rotation.
7. The method of claim 1, wherein: preferably, the measuring plane is parallel to the rudder shaft or the extension line of the rudder shaft, and the measured included angle theta between the front and the rear of the rotation is the rudder deflection angle delta.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112947534A (en) * | 2021-04-23 | 2021-06-11 | 成都凯天通导科技有限公司 | Adaptive pseudo-spectral method trajectory optimization method for depression section of hypersonic aircraft |
| CN113295134A (en) * | 2021-06-08 | 2021-08-24 | 北京普利永华科技发展有限公司 | Method for measuring rotating angle of rotating shaft unrelated airplane control surface |
| CN114261525A (en) * | 2021-12-30 | 2022-04-01 | 中国航天空气动力技术研究院 | Control surface deflection control and measurement system and method |
| CN114417578A (en) * | 2021-12-30 | 2022-04-29 | 中国航天空气动力技术研究院 | Deflection angle accurate positioning method and system of control surface automatic deflection mechanism |
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2019
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| KR101625509B1 (en) * | 2014-12-30 | 2016-05-30 | 국방과학연구소 | Roll angle estimation method of rotating craft |
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| CN108759798A (en) * | 2018-06-20 | 2018-11-06 | 上海卫星工程研究所 | A kind of implementation method of high-precision spacecraft precision measure |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112947534A (en) * | 2021-04-23 | 2021-06-11 | 成都凯天通导科技有限公司 | Adaptive pseudo-spectral method trajectory optimization method for depression section of hypersonic aircraft |
| CN112947534B (en) * | 2021-04-23 | 2023-05-30 | 成都凯天通导科技有限公司 | Hypersonic aircraft hold-down section self-adaptive pseudo-spectrum method track optimization method |
| CN113295134A (en) * | 2021-06-08 | 2021-08-24 | 北京普利永华科技发展有限公司 | Method for measuring rotating angle of rotating shaft unrelated airplane control surface |
| CN114261525A (en) * | 2021-12-30 | 2022-04-01 | 中国航天空气动力技术研究院 | Control surface deflection control and measurement system and method |
| CN114417578A (en) * | 2021-12-30 | 2022-04-29 | 中国航天空气动力技术研究院 | Deflection angle accurate positioning method and system of control surface automatic deflection mechanism |
| CN114261525B (en) * | 2021-12-30 | 2023-11-03 | 中国航天空气动力技术研究院 | Control surface deflection control and measurement system and method |
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