CN113353283A - Installation design method for aircraft control surface position sensor - Google Patents
Installation design method for aircraft control surface position sensor Download PDFInfo
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- CN113353283A CN113353283A CN202010135726.1A CN202010135726A CN113353283A CN 113353283 A CN113353283 A CN 113353283A CN 202010135726 A CN202010135726 A CN 202010135726A CN 113353283 A CN113353283 A CN 113353283A
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
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Abstract
The method for installing and designing the position sensor of the airplane control surface comprises the steps of forming different triangular relations with the intersection point of a suspension point of the airplane control surface, the intersection point of a fixed end of the position sensor and the maximum vertical deflection angle of the airplane control surface through different intersection points of movable ends of the position sensor, reflecting the length and the size of an installation angle of a rocker arm of the position sensor according to the triangular relations, and selecting the optimal intersection point position of the movable ends of the position sensor by calculating and comparing the linearity errors of the position sensor formed by different lengths of the rocker arm of the position sensor and different sizes of the installation angle.
Description
Technical Field
The invention belongs to the field of airplane design, and particularly relates to an installation design method of an airplane control surface position sensor.
Background
In modern aircraft design, fly-by-wire flight control systems have become the mainstream development trend of aircraft flight control systems. One problem that has to be considered by adopting the fly-by-wire system is the measurement of the position of the control surface of the airplane, because the measurement result of the position of the control surface is used for providing the position indication of the control surface of the airplane and the unhooking judgment of an actuator for a pilot, the measurement accuracy of a position sensor directly influences the judgment of the pilot on the position of the control surface of the airplane and also influences the detection result of the fly-by-wire system on the system fault of the fly-by-wire system.
The control surface position sensor is used for extending or retracting movement along with the up-and-down deflection of the control surface of the airplane, and the angle of the up-deflection or the down-deflection of the control surface of the airplane is calculated by measuring the extending or retracting stroke of an iron core in the position sensor. The measurement error of the position sensor mainly comprises three parts, namely a position sensor installation design error, a self measurement error and an electronic circuit demodulation error. The self-measuring error of the position sensor is limited by the process level, at present, domestic manufacturers can achieve 1% -1.5% of FS (full travel), and foreign known manufacturers, such as position sensors produced by the United states Honeywell company, can achieve 0.7% of FS. For the demodulation error of the position sensor, the current domestic and foreign levels are equivalent, and are approximately 0.7% FS. The error of the installation design of the position sensor is limited by the personal ability and experience of a designer, so that the error range of the installation design of the position sensor is large. For this technical field, no system installation design method or specification has been described.
Disclosure of Invention
The application aims to solve the problem that the installation design of the rudder surface position sensor in the traditional design is limited by experience and capability of designers, so that the measurement error of the position sensor is artificially increased, and the measurement precision of the position sensor is reduced, and provides an installation design method of the aircraft rudder surface position sensor.
A method for installing and designing an airplane control surface position sensor, wherein an airplane control surface is hinged on a suspension arm of a fixed wing back beam of an airplane through a suspension point, two ends of the position sensor are hinged on a girder of the airplane control surface and the fixed wing back beam, the position of the suspension point of the airplane control surface and the maximum vertical deflection angle of the airplane control surface are known, the connection intersection point of the fixed end of the position sensor and the fixed wing back beam is known, and the intersection point of the airplane control surface and the movable end of the position sensor is designed, which is characterized in that different triangle relations are formed respectively with the intersection point of the suspension point of the airplane control surface and the fixed end of the position sensor and the maximum vertical deflection angle of the airplane control surface through different intersection points of the movable end of the position sensor, the length and the size of the installation angle of the position sensor are reflected through the triangle relations, and the linearity errors of the position sensor formed by comparing different lengths of rocker arms of the position sensor and different sizes of the installation angles are calculated, thereby selecting the optimal position of the intersection point of the movable ends of the position sensor.
The optimal design method is that the airplane control surface is in a neutral position, a design plane is established in design software and is perpendicular to the airplane control surface rotating shaft, and the airplane control surface suspension point, the position sensor fixed end connecting intersection point and the position sensor movable end intersection point are displayed on the design plane.
Preferably, different triangular relationships are formed on the above-mentioned design plane: 1) connecting a fixed end of a position sensor with a connection intersection point and an airplane control surface suspension point, taking the distance between the two points as the diameter to make a first circle, preselecting a point in the first circle near a girder of the airplane control surface as a movable end connection intersection point of the position sensor, taking the length between the preselected movable end intersection point of the position sensor and the airplane control surface suspension point as the length of a rocker arm of the position sensor, taking the airplane control surface suspension point as the center of a circle, and taking the length of the rocker arm of the position sensor as the radius to make a second circle; 2) constructing a first triangle by taking the aircraft control surface suspension point, the intersection point of the preselected position sensor movable end and the intersection point of the position sensor fixed end as vertexes, wherein the length between the intersection point of the preselected position sensor movable end and the intersection point of the position sensor fixed end is the neutral length of the position sensor, and in the first triangle, the included angle between the intersection point of the preselected position sensor movable end and the intersection point of the aircraft control surface suspension point and the position sensor fixed end is the position sensor installation angle; 3) taking an aircraft control surface suspension point as a center to form a first straight line, wherein an included angle between an intersection point of the straight line and a preselected movable end of the position sensor and a connecting line of the aircraft control surface suspension point is equal to the maximum downward deflection angle of an aircraft control surface, an intersection point of the straight line and a second circle is a movable end downward deflection limit point of the position sensor, the length between the movable end downward deflection limit point of the position sensor and an intersection point of a fixed end of the position sensor is the minimum shortened length of the position sensor, and a second triangle is constructed by taking the control surface suspension point, the movable end downward deflection limit point of the position sensor and the preselected movable end intersection point of the position sensor as vertexes; constructing a third triangle by taking the lower limit point of the movable end of the position sensor, the intersection point of the movable end of the preselected position sensor and the intersection point of the fixed end of the position sensor as vertexes; 4) taking the suspension point of the airplane control surface as a center to form a second straight line, wherein an included angle between the intersection point of the straight line and the preselected movable end of the position sensor and the connection line of the suspension point of the airplane control surface is equal to the maximum upper deflection angle of the airplane control surface, the intersection point of the straight line and a second circle is an upper deflection limit point of the movable end of the position sensor, the length between the upper deflection limit point of the movable end of the position sensor and the intersection point of the fixed end of the position sensor is the maximum extension length of the position sensor, and a fourth triangle is constructed by taking the upper deflection limit point of the movable end of the position sensor, the intersection point of the preselected movable end of the position sensor and the intersection point of the fixed end of the position sensor as vertexes; 5) defining the difference between the maximum extension length of the position sensor and the neutral length of the position sensor as the extension stroke of the position sensor, defining the difference between the neutral length of the position sensor and the shortest retraction length of the position sensor as the retraction stroke of the position sensor, defining the ratio between the extension stroke of the position sensor and the maximum upward deflection angle of the control surface as the extension gradient of the position sensor, defining the ratio between the retraction stroke of the position sensor and the maximum downward deflection angle of the control surface as the retraction gradient of the position sensor, and defining the difference between the extension gradient of the position sensor and the retraction gradient of the position sensor as the linearity error of the position sensor;
preferably reflecting the size of the rocker arm and the installation angle of the position sensor by a triangular relation, taking the length of the rocker arm of the position sensor and the installation angle of the position sensor as basic variables, and respectively calculating the length of a preselected position sensor from a movable end intersection point to a lower limit point of a movable end of the position sensor, the length of a preselected position sensor from a movable end intersection point to a fixed end intersection point of the position sensor, the length of the preselected position sensor from the lower limit point of the movable end of the position sensor to the fixed end intersection point of the position sensor and the length of the preselected position sensor from an upper limit point of the movable end of the position sensor to a fixed end intersection point of the position sensor in a first triangle, a second triangle, a third triangle and a fourth triangle; the influence of the rocker arm on the linearity error of the position sensor and the installation angle of the position sensor is determined by changing the size of the rocker arm of the position sensor, and the length and the installation angle of the rocker arm of the position sensor corresponding to the minimum value of the linearity error of the position sensor are selected by comparison, so that the position of the intersection point of the movable end of the position sensor is determined.
Compared with the traditional installation design method of the aircraft control surface position sensor, the method has the following advantages: 1) the invention describes the installation design flow of the control surface position sensor in detail, and the design basis is sufficient. The selection of the installation angle of the position sensor and the length of the rocker arm is obtained through theoretical calculation and simulation analysis, and the selection of numerical values according to personal experience in the traditional design is broken through. 2) Compared with the traditional installation design method of the control surface position sensor, the method can effectively reduce the installation design error of the control surface position sensor and improve the measurement precision of the control surface position sensor.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
FIG. 1 is a schematic illustration of an aircraft control surface position sensor installation.
FIG. 2 is a schematic diagram of an aircraft control surface position sensor design.
The numbering in the figures illustrates: the plane comprises an airplane control surface 1, suspension points 2, a movable end intersection point 3, a suspension support arm 4, a position sensor 5, a fixed end intersection point 6, a fixed wing rear beam 7, a first circle 8, a second circle 9, a first auxiliary straight line 10 and a second auxiliary straight line 11.
Detailed Description
Referring to the attached drawings, the installation and design method of the aircraft control surface position sensor comprises the steps that an aircraft control surface 1 is hinged to a suspension arm 4 of a fixed wing back beam of an aircraft through a suspension point 2, two ends of a position sensor 5 are hinged to a crossbeam of the aircraft control surface 1 and the fixed wing back beam 7, the position of the suspension point 2 of the aircraft control surface and the maximum vertical deflection angle of the aircraft control surface are known, a fixed end intersection point 6 of the position sensor 5 and the fixed wing back beam is known, a movable end intersection point 3 of the aircraft control surface 1 and the position sensor 5 needs to be accurately designed, different movable end intersection points 3 of the position sensor are pre-selected, different triangular relations are formed respectively with the fixed end intersection point 6 of the aircraft control surface suspension point 2 and the position sensor and the maximum vertical deflection angle of the aircraft control surface, the length and the installation angle of a position sensor rocker arm are reflected in the triangular relations, and calculating the linearity error of the position sensor formed by comparing different rocker arm lengths and different installation angles of the position sensor, thereby selecting the optimal position of the intersection point of the movable end of the position sensor.
Taking the installation design of the left aileron position sensor of a certain airplane as an example for explanation, the specific design process is as follows:
in a CATIA tool of airplane three-dimensional design software, an aileron is positioned at a neutral position, a design plane is established and is perpendicular to an aileron rotating shaft, and an intersection point of the design plane and the aileron rotating shaft is an aileron suspension point H. The intersection point F of the fixed end of the position sensor 5 is marked on the design plane, and the point is 25mm away from the plane of the fixed wing back beam and 35mm away from the vertical distance of the lower edge of the fixed wing back beam.
Different triangular relationships are formed on the above design planes: 1) the fixed end of the connecting position sensor is connected with an intersection point F and a left aileron suspension point H, the distance between the two points is taken as a diameter to be taken as a first circle 8, a point is preselected in the first circle 8 near the left aileron crossbeam to be taken as a movable end intersection point M of the connecting position sensor, the length between the preselected movable end intersection point M of the position sensor and the left aileron suspension point H is taken as a rocker arm length r of the position sensor, the left aileron suspension point H is taken as a circle center, and the rocker arm length r of the position sensor is taken as a radius to be taken as a second circle 9; 2) constructing a first triangle delta FMH by taking a left aileron suspension point H, a preselected position sensor movable end intersection point M and a position sensor fixed end intersection point F as vertexes, wherein the length of the F between the preselected position sensor movable end intersection point M and the position sensor fixed end intersection point is the position sensor neutral length, and in the first triangle delta FMH, an included angle FMH between the preselected position sensor movable end intersection point M and the left aileron suspension point H and the position sensor fixed end intersection point F is a position sensor installation angle phi; 3) a first auxiliary straight line 10 is made by taking a left aileron suspension point H as a center, an included angle between a connecting line of a cross point M of the straight line and a preselected position sensor movable end and the left aileron suspension point H is equal to the maximum downward deflection angle alpha of the left aileron, an intersection point of the straight line and a second circle 9 is a position sensor movable end downward deflection limit point A, the length between the position sensor movable end downward deflection limit point A and a position sensor fixed end cross point F is the minimum shortening length of the position sensor, and a second triangle delta AHM is constructed by taking a control surface suspension point H, the position sensor movable end downward deflection limit point A and the preselected position sensor movable end cross point M as vertexes; constructing a third triangle delta AMF by taking a lower deflection limit point A of the movable end of the position sensor, a preselected intersection point M of the movable end of the position sensor and an intersection point F of the fixed end of the position sensor as vertexes; 4) a second auxiliary straight line is made by taking the hanging point H of the left aileron as the center, the included angle between the connecting line of the intersection point M of the straight line and the preselected movable end of the position sensor and the hanging point H of the left aileron is equal to the maximum upper deflection angle beta of the left aileron, the intersection point of the straight line and a second circle is the upper deflection limit point B of the movable end of the position sensor, the length between the upper deflection limit point B of the movable end of the position sensor and the intersection point F of the fixed end of the position sensor is the maximum extension length of the position sensor, and a fourth triangle delta BMF is constructed by taking the upper deflection limit point B of the movable end of the position sensor, the preselected movable end intersection point M of the position sensor and the intersection point F of the fixed end of the position sensor as vertexes; 5) the difference between the maximum extension length of the position sensor and the neutral length of the position sensor is defined as the extension stroke of the position sensor, the difference between the neutral length of the position sensor and the shortest retraction length of the position sensor is defined as the retraction stroke of the position sensor, the ratio between the extension stroke of the position sensor and the maximum upward deflection angle of the control surface is defined as the extension gradient of the position sensor, the ratio between the retraction stroke of the position sensor and the maximum downward deflection angle of the control surface is defined as the retraction gradient of the position sensor, and the difference between the extension gradient of the position sensor and the retraction gradient of the position sensor is defined as the linearity error epsilon of the position sensor.
The method comprises the steps of reflecting the length r and the mounting angle phi of a rocker arm of a position sensor by a triangular relation, taking the length r and the mounting angle phi of the rocker arm of the position sensor as basic variables, and respectively calculating the length AM of a preselected position sensor movable end intersection point M to a position sensor movable end lower deflection limit point A, the length FM of the preselected position sensor movable end intersection point M to a position sensor fixed end intersection point F, the length AF of the position sensor movable end lower deflection limit point A to the position sensor fixed end intersection point F and the length BF of the position sensor movable end upper deflection limit point B to the position sensor fixed end intersection point F in a first triangle delta FMH, a second triangle delta AHM, a third triangle delta AMF and a fourth triangle delta BMF; the influence of the rocker arm r on the linearity error epsilon of the position sensor and the installation angle phi of the position sensor is determined by changing the size of the rocker arm r of the position sensor, and the calculation result is as follows:
when the rocker arm r of the position sensor is 55mm, the installation angle phi is 1.587rad, and the linearity error epsilon is 0.0238;
when the rocker arm r of the position sensor is equal to 60mm, the installation angle phi is equal to 1.583rad, and the linearity error epsilon is equal to 0.0457;
when the rocker arm r of the position sensor is 65mm, the installation angle phi is 1.583rad, and the linearity error epsilon is 0.0087;
when the rocker arm r of the position sensor is 70mm, the installation angle phi is 1.583rad, and the linearity error epsilon is 0.0356;
when the rocker arm r of the position sensor is 75mm, the installation angle phi is 1.580rad, and the linearity error epsilon is 0.0244;
when the rocker arm r of the position sensor is 80mm, the installation angle phi is 1.580rad, and the linearity error epsilon is 0.0278;
when the rocker arm r of the position sensor is 85mm, the installation angle phi is 1.577rad, and the linearity error epsilon is 0.039;
by comparison, when the length r of the rocker arm of the position sensor is selected to be 65mm, the installation angle phi of the position sensor is 1.583rad to be 90.75 degrees, at the moment, the linearity error epsilon is minimum 0.0087, and finally, in a design plane, the coordinate value of the point M under the state that the length r of the rocker arm of the position sensor is 65mm and the installation angle phi of the position sensor is 1.583rad to be 90.75 degrees is taken as the design value of the intersection point of the movable end of the position sensor.
Claims (4)
1. A method for installing and designing an airplane control surface position sensor, wherein an airplane control surface is hinged on a suspension arm of a fixed wing back beam of an airplane through a suspension point, two ends of the position sensor are hinged on a girder of the airplane control surface and the fixed wing back beam, the position of the suspension point of the airplane control surface and the maximum vertical deflection angle of the airplane control surface are known, the connection intersection point of the fixed end of the position sensor and the fixed wing back beam is known, and the intersection point of the airplane control surface and the movable end of the position sensor is designed, which is characterized in that different triangle relations are formed respectively with the intersection point of the suspension point of the airplane control surface and the fixed end of the position sensor and the maximum vertical deflection angle of the airplane control surface through different intersection points of the movable end of the position sensor, the length and the size of the installation angle of the position sensor are reflected through the triangle relations, and the linearity errors of the position sensor formed by comparing different lengths of rocker arms of the position sensor and different sizes of the installation angles are calculated, thereby selecting the optimal position of the intersection point of the movable ends of the position sensor.
2. The installation and design method of the aircraft control surface position sensor according to claim 1, characterized in that the aircraft control surface is in a neutral position, a design plane is established in the design software, the plane is perpendicular to the aircraft control surface rotating shaft, and the suspension point of the aircraft control surface, the connection intersection point of the fixed end of the position sensor and the intersection point of the movable end of the position sensor are all displayed on the design plane.
3. An aircraft control surface position sensor installation design method as claimed in claim 2, characterized in that different triangular relationships are formed on the design plane: 1) connecting a fixed end of a position sensor with a connection intersection point and an airplane control surface suspension point, taking the distance between the two points as the diameter to make a first circle, preselecting a point in the first circle near a girder of the airplane control surface as a movable end connection intersection point of the position sensor, taking the length between the preselected movable end intersection point of the position sensor and the airplane control surface suspension point as the length of a rocker arm of the position sensor, taking the airplane control surface suspension point as the center of a circle, and taking the length of the rocker arm of the position sensor as the radius to make a second circle; 2) constructing a first triangle by taking the aircraft control surface suspension point, the intersection point of the preselected position sensor movable end and the intersection point of the position sensor fixed end as vertexes, wherein the length between the intersection point of the preselected position sensor movable end and the intersection point of the position sensor fixed end is the neutral length of the position sensor, and in the first triangle, the included angle between the intersection point of the preselected position sensor movable end and the intersection point of the aircraft control surface suspension point and the position sensor fixed end is the position sensor installation angle; 3) taking an aircraft control surface suspension point as a center to form a first straight line, wherein an included angle between an intersection point of the straight line and a preselected movable end of the position sensor and a connecting line of the aircraft control surface suspension point is equal to the maximum downward deflection angle of an aircraft control surface, an intersection point of the straight line and a second circle is a movable end downward deflection limit point of the position sensor, the length between the movable end downward deflection limit point of the position sensor and an intersection point of a fixed end of the position sensor is the minimum shortened length of the position sensor, and a second triangle is constructed by taking the control surface suspension point, the movable end downward deflection limit point of the position sensor and the preselected movable end intersection point of the position sensor as vertexes; constructing a third triangle by taking the lower limit point of the movable end of the position sensor, the intersection point of the movable end of the preselected position sensor and the intersection point of the fixed end of the position sensor as vertexes; 4) taking the suspension point of the airplane control surface as a center to form a second straight line, wherein an included angle between the intersection point of the straight line and the preselected movable end of the position sensor and the connection line of the suspension point of the airplane control surface is equal to the maximum upper deflection angle of the airplane control surface, the intersection point of the straight line and a second circle is an upper deflection limit point of the movable end of the position sensor, the length between the upper deflection limit point of the movable end of the position sensor and the intersection point of the fixed end of the position sensor is the maximum extension length of the position sensor, and a fourth triangle is constructed by taking the upper deflection limit point of the movable end of the position sensor, the intersection point of the preselected movable end of the position sensor and the intersection point of the fixed end of the position sensor as vertexes; 5) the difference between the maximum extension length of the position sensor and the neutral length of the position sensor is defined as the extension stroke of the position sensor, the difference between the neutral length of the position sensor and the shortest retraction length of the position sensor is defined as the retraction stroke of the position sensor, the ratio between the extension stroke of the position sensor and the maximum upward deflection angle of the control surface is defined as the extension gradient of the position sensor, the ratio between the retraction stroke of the position sensor and the maximum downward deflection angle of the control surface is defined as the retraction gradient of the position sensor, and the difference between the extension gradient of the position sensor and the retraction gradient of the position sensor is defined as the linearity error of the position sensor.
4. The aircraft control surface position sensor installation design method of claim 3, characterized in that the size of the position sensor rocker arm length and the installation angle is reflected in a triangular relation, the length of the position sensor rocker arm length and the installation angle of the position sensor are taken as basic variables, and in a first triangle, a second triangle, a third triangle and a fourth triangle, the length of a preselected position sensor movable end intersection point to a position sensor movable end lower limit point, the length of the preselected position sensor movable end intersection point to a position sensor fixed end intersection point, the length of the position sensor movable end lower limit point to a position sensor fixed end intersection point and the length of the position sensor movable end upper limit point to a position sensor fixed end intersection point are respectively calculated; the influence of the rocker arm on the linearity error of the position sensor and the installation angle of the position sensor is determined by changing the size of the rocker arm of the position sensor, and the length and the installation angle of the rocker arm of the position sensor corresponding to the minimum value of the linearity error of the position sensor are selected by comparison, so that the position of the intersection point of the movable end of the position sensor is determined.
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| CN202010135726.1A CN113353283A (en) | 2020-03-02 | 2020-03-02 | Installation design method for aircraft control surface position sensor |
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| CN202010135726.1A CN113353283A (en) | 2020-03-02 | 2020-03-02 | Installation design method for aircraft control surface position sensor |
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| CN106767647A (en) * | 2015-11-24 | 2017-05-31 | 中航贵州飞机有限责任公司 | A kind of deflection angle of airplane control surface degree measurement apparatus |
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| CN110803298A (en) * | 2019-10-18 | 2020-02-18 | 中航通飞华南飞机工业有限公司 | Device and method for determining neutral position of control surface of airplane |
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