CN109387176A - A kind of aircraft rudder surface angle displacement measuring device - Google Patents
A kind of aircraft rudder surface angle displacement measuring device Download PDFInfo
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- CN109387176A CN109387176A CN201710653070.0A CN201710653070A CN109387176A CN 109387176 A CN109387176 A CN 109387176A CN 201710653070 A CN201710653070 A CN 201710653070A CN 109387176 A CN109387176 A CN 109387176A
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- linear movement
- movement pick
- rudder face
- measuring device
- pick
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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
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- General Physics & Mathematics (AREA)
- A Measuring Device Byusing Mechanical Method (AREA)
Abstract
The invention discloses a kind of aircraft rudder surface angle displacement measuring devices, belong to aeronautic measurement field of measuring technique.Described device includes the first linear movement pick-up (2) and the second linear movement pick-up (3), the telescopic end of first linear movement pick-up (2) and the second linear movement pick-up (3) with rudder face (1) hingedly, the fixing end of the first linear movement pick-up (2) and the second linear movement pick-up (3) is hinged with hold-down support.The present invention is without complicated positioning and specialist tools, Fast Installation can be realized in narrow installation space, measurement error caused by installation error caused by more intermediate link and sensor and pivot center difference axis is avoided simultaneously, can realize precise measurement to the angular displacement in larger rudder face stroke range.
Description
Technical field
The invention belongs to aeronautic measurement field of measuring technique, and in particular to a kind of aircraft rudder surface angle displacement measuring device.
Background technique
At present in industrial design field, especially in the verification process of industrial design field, it is related to many angle displacement measurements
Problem is not easy to solve, such as aircraft control surface deflection angle.It is required that real-time measurement moving component angular displacement, for angular displacement sensor
Mounting means and measurement method require it is stringent, for having multiple measurement points and operating condition is different everywhere, when the difference of space, design
And the cost that processed sensor fixture needs to pay is very high, and since the manufacturing and fixing error of fixture will lead to measurement result not
Accurately.The requirement of various operating conditions is able to satisfy without a kind of general device and measurement method at present.
A kind of angle displacement measuring device and measurement side are disclosed in the Chinese patent of Patent No. ZL201310195631.9
Method, including angular displacement sensor, sensor support base, rocker arm, connecting rod, positioning device.When measurement using locating piece and positioning foot rest,
Positioning beam is as positioning device, to position cornual plate on angular displacement sensor and measured piece on the basis of the effective length of rocker arm and connecting rod
Position, and angular displacement sensor, rocker arm, connecting rod, small support are sequentially connected, the angular displacement of measured piece are converted into rocker arm
Angular displacement, so that the angular displacement to measured piece measures.The measuring device and measurement method can effectively measure ground experiment
In rudder face angular displacement, but it is difficult to the rudder face angular displacement during flight control system test and practical flight due to space is limited
With measurement, and implementation steps and intermediate link are more, and connecting rod, the installation gap of rocker arm and error will affect measurement result
Accuracy.
Summary of the invention
To solve the above-mentioned problems, the invention proposes a kind of aircraft rudder surface angle displacement measuring device, it can be achieved that including ground
Interview tests, the measurement of flight control system test and a variety of environment such as practical flight process and the displacement of operating condition lower rudder face angle, structure is simple,
Easy for installation, measurement range is big, precision is high, and functional reliability is high.
Aircraft rudder surface angle displacement measuring device of the present invention, including the first linear movement pick-up and the second linear movement pick-up,
The telescopic end of first linear movement pick-up and the second linear movement pick-up is hinged with rudder face, the first linear movement pick-up and second
The fixing end of linear movement pick-up is hinged with hold-down support.
Preferably, the first linear movement pick-up and the second linear movement pick-up are dragline type linear movement pick-up.
Preferably, the first linear movement pick-up and the second linear movement pick-up are that the redundance containing multiple groups coil is stretched
Contracting rod-type linear movement pick-up.
Preferably, the two o'clock for being articulated with rudder face of first linear movement pick-up and the second linear movement pick-up about
The neutral surface of rudder face is symmetrical.
Preferably, two be articulated on hold-down support of first linear movement pick-up and the second linear movement pick-up
Point is symmetrical about the neutral surface of rudder face.
Preferably, the two o'clock for being articulated with rudder face of first linear movement pick-up and the second linear movement pick-up is formed
Minor arc at 150 °~170 °.
Rudder face angular displacement and the first linear movement pick-up and the second linear movement pick-up be respectively provided with corresponding relationship F (x1) and
F (x2), and F (x1) and F (x2) obeys the cosine law.
The value of rudder face angular displacement can take two linear movement pick-ups after corresponding relationship F (x1) and F (x2) is solved
Weighted average can also take wherein sensor body axis and rudder face center of rotation-sensor telescopic end and rudder face hinge joint
The linear movement pick-up of line closer to 90 degree of that sides passes through the value of angular displacement that solution obtains.
The present invention can realize Fast Installation, simultaneously without complicated positioning and specialist tools in narrow installation space
Measurement error caused by installation error caused by more intermediate link and sensor and pivot center difference axis is avoided, it can be right
Precise measurement is realized in angular displacement in larger rudder face stroke range.
Detailed description of the invention
Fig. 1 is the structural schematic diagram according to a preferred embodiment of aircraft rudder surface angle displacement measuring device of the present invention.
Fig. 2 is the angular displacement deflection situation flowering structure schematic diagram of embodiment illustrated in fig. 1.
Wherein, 1 is rudder face, and 2 be the first linear movement pick-up, and 3 be the second linear movement pick-up, and 101 be the rudder face neutral conductor,
102 be rudder face horizontal line, and 103 be deflection wire, and 201 be the first telescopic end hinge joint, and 202 be the first fixing end hinge joint, and 301 are
Second telescopic end hinge joint, 302 be the second fixing end hinge joint.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
The invention proposes a kind of aircraft rudder surface angle displacement measuring devices, as shown in Figure 1, including the first linear movement pick-up
2 and second linear movement pick-up 3, the telescopic end of the first linear movement pick-up 2 and the second linear movement pick-up 3 is cut with scissors with rudder face 1
It connects, the fixing end of the first linear movement pick-up 2 and the second linear movement pick-up 3 is hinged with hold-down support.
Specifically, the telescopic end of the first linear movement pick-up 2 and rudder face are articulated with the first telescopic end hinge joint 201, first
The fixing end and hold-down support of linear movement pick-up 2 are articulated with the first fixing end hinge joint 202；Second linear movement pick-up 3
Telescopic end and rudder face are articulated with the second telescopic end hinge joint 301, and the fixing end and hold-down support of the second linear movement pick-up 3 are hinged
In the second fixing end hinge joint 302.
With reference to Fig. 2, after rudder face deflects α angle to the left, left side the first telescopic end hinge joint 201 is to close to hold-down support
The telescopic end of first linear movement pick-up 2, i.e., be recovered in the cylinder where its fixing end by direction movement, conversely, right side the
Two telescopic end hinge joints 301 are moved to the direction far from hold-down support, i.e., consolidate the telescopic end of the second linear movement pick-up 3 from it
It is pulled out in cylinder where fixed end.
In the present embodiment, the shown rudder face center of circle is O, radius R, it is to be understood that as shown in Fig. 2, control surface deflection angle
Spend the displacement x existence function relationship of β and the second linear movement pick-up 3, the functional relation is β angle is smaller and the second telescopic end is cut with scissors
Contact 301 closer to rudder face horizontal line when, can be indicated with cosine function, i.e. x=Rcos β.
For this purpose, in the present embodiment, first linear movement pick-up 2 and the second linear movement pick-up 3 are articulated with rudder face
The minor arc that is formed of two o'clock at 150 °~170 °, with reference to Fig. 1 or Fig. 2, make the first telescopic end hinge joint 201 and second flexible as far as possible
Hold hinge joint 301 close to rudder face horizontal line 102, rudder face horizontal line described here refers to perpendicular to the straight of the rudder face neutral conductor 101
Diameter.On the other hand, when control surface deflection angle beta is greater than set angle α, it is preferred to use the range of one of linear movement pick-up
As measured value, reference point of the solution value of not outer linear movement pick-up as rudder face angular displacement, for example, in the present embodiment
α is chosen for 15 °, with reference to Fig. 2, at this point, carrying out control surface deflection angle on the basis of the measured value of second linear movement pick-up on right side
Degree solves, and selection principle is, sensor body axis and rudder face center of rotation-sensor telescopic end and rudder face hinge joint line
The linear movement pick-up of (hereinafter referred to as deflection wire 103) closer 90 degree of that sides, such as the biography of the second linear movement pick-up of right side
Sensor body axis and deflection wire 103 are closer to 90 °.
It is understood that being within the scope of α in rudder face angular displacement, the value of rudder face angular displacement takes two linear movement pick-ups
Weighted average after corresponding relationship F (x1) and F (x2) is solved.When thering is one to break down in two linear movement pick-ups
Afterwards, the value of aircraft rudder surface angular displacement is value of the linear movement pick-up of non-faulting side after solving.
In the present embodiment, the first linear movement pick-up 2 and the second linear movement pick-up 3 are dragline type displacement of the lines sensing
Device, or be the redundance Telescopic shaft type linear movement pick-up containing multiple groups coil.
In the present embodiment, the two o'clock for being articulated with rudder face of first linear movement pick-up 2 and the second linear movement pick-up 3
Neutral surface about rudder face is symmetrical.Similarly, first linear movement pick-up 2 and being articulated with for the second linear movement pick-up 3 are consolidated
The two o'clock determined on support is symmetrical about the neutral surface of rudder face, with reference to Fig. 1 or Fig. 2.
The present invention provides a kind of aircraft rudder surface angle displacement measuring device, it can be achieved that including ground experiment, flight control system examination
The measurement with a variety of environment such as practical flight process and the displacement of operating condition lower rudder face angle is tested, using redundance linear movement pick-up conduct
Measuring tool, converts the measurement of angular displacement to using simple mathematical relationship the measurement of displacement of the lines, and measurement range is big, precision
Height, high reliablity, structure is simple, easy for installation, can be real in narrow installation space without complicated positioning and specialist tools
Existing Fast Installation, while avoiding caused by installation error caused by more intermediate link and sensor and pivot center difference axis
Measurement error can realize precise measurement to the angular displacement in larger rudder face stroke range.
Finally it is noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, those skilled in the art should understand that: it is still
It is possible to modify the technical solutions described in the foregoing embodiments, or part of technical characteristic is equally replaced
It changes；And these are modified or replaceed, the essence for technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution
Mind and range.
Claims (6)
1. a kind of aircraft rudder surface angle displacement measuring device, which is characterized in that including the first linear movement pick-up (2) and the second line position
The telescopic end of displacement sensor (3), the first linear movement pick-up (2) and the second linear movement pick-up (3) with rudder face (1) hingedly,
The fixing end of first linear movement pick-up (2) and the second linear movement pick-up (3) is hinged with hold-down support.
2. aircraft rudder surface angle displacement measuring device as described in claim 1, which is characterized in that the first linear movement pick-up (2)
It is dragline type linear movement pick-up with the second linear movement pick-up (3).
3. aircraft rudder surface angle displacement measuring device as described in claim 1, which is characterized in that the first linear movement pick-up (2)
It is the redundance Telescopic shaft type linear movement pick-up containing multiple groups coil with the second linear movement pick-up (3).
4. aircraft rudder surface angle displacement measuring device as claimed in claim 2 or claim 3, which is characterized in that first displacement of the lines passes
The two o'clock for being articulated with rudder face of sensor (2) and the second linear movement pick-up (3) is symmetrical about the neutral surface of rudder face.
5. aircraft rudder surface angle displacement measuring device as claimed in claim 2 or claim 3, which is characterized in that first displacement of the lines passes
The two o'clock of sensor (2) and the second linear movement pick-up (3) being articulated on hold-down support is symmetrical about the neutral surface of rudder face.
6. aircraft rudder surface angle displacement measuring device as described in claim 1, which is characterized in that first linear movement pick-up
(2) and the minor arc of the two o'clock formation for being articulated with rudder face of the second linear movement pick-up (3) is at 150 °~170 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710653070.0A CN109387176A (en) | 2017-08-02 | 2017-08-02 | A kind of aircraft rudder surface angle displacement measuring device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710653070.0A CN109387176A (en) | 2017-08-02 | 2017-08-02 | A kind of aircraft rudder surface angle displacement measuring device |
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| Publication Number | Publication Date |
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| CN109387176A true CN109387176A (en) | 2019-02-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201710653070.0A Pending CN109387176A (en) | 2017-08-02 | 2017-08-02 | A kind of aircraft rudder surface angle displacement measuring device |
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| CN (1) | CN109387176A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111412880A (en) * | 2020-04-09 | 2020-07-14 | 中国飞机强度研究所 | Real-time monitoring system and method for deflection angle of movable wing surface of airplane |
| CN112947539A (en) * | 2020-12-17 | 2021-06-11 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for compensating control surface nonlinearity caused by linear driver |
-
2017
- 2017-08-02 CN CN201710653070.0A patent/CN109387176A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111412880A (en) * | 2020-04-09 | 2020-07-14 | 中国飞机强度研究所 | Real-time monitoring system and method for deflection angle of movable wing surface of airplane |
| CN111412880B (en) * | 2020-04-09 | 2022-02-22 | 中国飞机强度研究所 | Real-time monitoring system and method for deflection angle of movable wing surface of airplane |
| CN112947539A (en) * | 2020-12-17 | 2021-06-11 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for compensating control surface nonlinearity caused by linear driver |
| CN112947539B (en) * | 2020-12-17 | 2023-07-07 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for compensating control surface nonlinearity caused by linear driver |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190226 |
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| WD01 | Invention patent application deemed withdrawn after publication |