CN218949505U

CN218949505U - Zero calibration device for aircraft rudder

Info

Publication number: CN218949505U
Application number: CN202222592491.6U
Authority: CN
Inventors: 盛国超; 刘心; 何利华; 王奎顺
Original assignee: Shanghai Aircraft Customer Service Co ltd; Commercial Aircraft Corp of China Ltd
Current assignee: Shanghai Aircraft Customer Service Co ltd; Commercial Aircraft Corp of China Ltd
Priority date: 2022-09-29
Filing date: 2022-09-29
Publication date: 2023-05-02
Anticipated expiration: 2032-09-29

Abstract

The utility model provides a zero calibration device for an aircraft rudder, which comprises a positioning clamping part and a measuring part, wherein the positioning clamping part comprises a clamping part with a C-shaped cross section, the clamping part comprises an opening part, a containing part and a reference surface formed on the inner side surface of the containing part, and the rear edge part of the aircraft rudder can be inserted into the clamping part through the opening part and firmly clamped in the containing part, so that the reference surface is fully attached to a positioning plane; the measuring component is arranged in an opening on the positioning and clamping component, measuring light rays emitted by the laser transmitters on the measuring component penetrate through the lower opening and are emitted downwards, when the aircraft rudder is firmly clamped in the positioning and clamping component, the position of the rear edge part of the aircraft rudder is changed by adjusting a hinge connected with the front edge of the aircraft rudder, and the calibrated measuring light rays can be positioned in a target area of a plane for measuring the fuselage to realize zero calibration of the rudder.

Description

Zero calibration device for aircraft rudder

Technical Field

The utility model relates to the field of manufacturing, assembly and maintenance of aircrafts, in particular to a zero calibration device for an aircraft rudder.

Background

An aircraft rudder generally refers to a movable airfoil component mounted on the vertical tail of an aircraft for heading manipulation of the aircraft. The rudder is typically attached to the rear of the vertical stabilizer of the tail wing of the aircraft by a hinge. The pilot can control the course of the airplane by operating the left and right deflection of the pilot through the pedals. For example, when the rudder turns left, the airflow will act on it to create a moment to the right of the tail to turn the aircraft nose to the left, thereby changing the heading of the aircraft. It can be said that the yaw direction and yaw angle of the rudder of the aircraft will directly influence the actual heading and angle of the aircraft during flight. Therefore, after the aircraft rudder is mounted on the aircraft vertical stabilizer, it is often necessary to mechanically zero the aircraft rudder before it can be used to accurately steer the heading of the aircraft.

As shown in fig. 1, the aircraft rudder 1 comprises a locating plane 11 extending in its longitudinal direction on the right side of its trailing edge portion 14 and a leading edge (not shown) which is hinged to the vertical stabilizer of the aircraft tail. When the aircraft rudder 1 is initially installed behind the vertical stabilizer, it is located above the fuselage measurement plane 12. When the aircraft rudder 1 is in the mechanical null position, the plane in which the aircraft rudder positioning plane 11 lies intersects the target area 13 on the fuselage measurement plane 12 and the right-hand side line 15 of its rear part 14 is at a distance from the target area 13 on the fuselage measurement plane 12.

However, after the conventional aircraft, such as the rudder of an aircraft, is initially installed, the conventional aircraft is usually only subjected to simple human eye detection adjustment or is put into use without adjustment, and the conventional aircraft is completely dependent on manual judgment of whether the aircraft rudder 1 is in a mechanical zero position or not and is installed in place, so that the manual detection result is extremely susceptible to factors such as external environment and individual difference, and the like, thereby causing the situations of yaw of the aircraft, increasing the difficulty of flight tasks of pilots and causing poor user experience.

Disclosure of Invention

Therefore, the technical problem to be solved by the utility model is to overcome the defects that the zero calibration scheme of the existing aircraft rudder cannot accurately and effectively calibrate the aircraft rudder, and the like, and provide a novel zero calibration device for the aircraft rudder.

In particular, the utility model provides a zero calibration device for an aircraft rudder comprising a locating plane located to the right of its trailing edge portion and extending in the longitudinal direction of the aircraft rudder and mounted above the fuselage measurement plane of the aircraft by means of a hinge arranged between its leading edge and the aircraft vertical stabilizer, characterized in that it comprises:

a positioning clamping member including a clamping portion having a C-shaped cross section, the clamping portion including an opening portion facing an insertion direction of the aircraft rudder and a receiving portion for receiving the aircraft rudder, a longitudinally extending reference surface being formed on an inner side surface of the receiving portion, wherein a trailing edge portion of the aircraft rudder can be inserted into the clamping portion through the opening portion and firmly clamped in the receiving portion so that the reference surface is sufficiently fitted to the positioning plane;

a measuring part mounted on the positioning and clamping part, the measuring part comprising a laser emitter, the measuring light emitted by the laser emitter is emitted downwards through an opening arranged on the bottom wall of the positioning and clamping part,

wherein the collimated measuring ray is configured parallel to a right side line of a trailing edge portion of the aircraft rudder and is located on an extension of the reference plane; and, in addition, the processing unit,

wherein when the aircraft rudder is firmly clamped in the positioning clamping member, the position of the trailing edge portion of the aircraft rudder is changed by adjusting the hinge connected to the leading edge of the aircraft rudder, thereby changing the positions of the positioning clamping member and the measuring member, whereby the collimated measuring light is located in the target area of the fuselage measuring plane.

According to one embodiment of the utility model, the zero calibration device further comprises an L-shaped calibration block for calibrating the measuring light before zero calibration of the rudder of the aircraft, the longitudinal section of the L-shaped calibration block being insertable into the clamping part through the opening and being firmly clamped in the receiving part, wherein a fitting surface is formed on a side of the longitudinal section of the L-shaped calibration block facing the positioning plane, the fitting surface being shaped to conform to the positioning plane such that the fitting surface substantially fits the positioning plane when the L-shaped calibration block is inserted into the clamping part.

According to another embodiment of the utility model, the alignment surface is formed at the same side of the transverse section of the L-shaped alignment block as the abutment surface, the alignment surface being provided with groove graduations configured as side lines extending parallel to the longitudinal direction of the abutment surface, wherein the measuring light emitted by the measuring means can be brought to fall into the groove graduations by adjusting the measuring means, whereby the measuring light is aligned.

According to still another embodiment of the present utility model, the sidewall of the positioning and clamping member is formed with a through groove extending longitudinally, and a pre-tightening spring is provided between the measuring member and a bottom surface of the groove, the pre-tightening spring being configured to be capable of pressing the measuring member by a spring restoring force, thereby mounting the measuring member on the positioning and clamping member in cooperation with an inner wall surface of the positioning and clamping member.

According to a further embodiment of the utility model, the positioning and clamping part further comprises a first threaded through hole extending transversely and located on different sides of the pretensioning spring and an adjusting bolt extending through the first threaded through hole, the adjusting bolt being pressed against the measuring part, so that the angular offset of the measuring part is adjusted in cooperation with the pretensioning spring to enable measuring light emitted by the measuring part to fall into the groove graduation marks.

According to yet another embodiment of the present utility model, there are a plurality of first threaded through holes, and the plurality of first threaded through holes are opened on different sides of the positioning and clamping member; the adjusting bolts correspondingly comprise a plurality of adjusting bolts, and each adjusting bolt is pressed against the measuring component from different directions through the corresponding first threaded through hole, so that the angle offset of the measuring component in different directions is adjusted.

According to yet another embodiment of the utility model, the measuring component further comprises a mounting block for holding the laser transmitter, wherein the mounting block comprises a longitudinally extending through hole and a transversely extending second threaded through hole, wherein the through hole is configured to receive the laser transmitter, and a stop screw is passed through the second threaded through hole to press the laser transmitter against the second threaded through hole to firmly hold the measuring component in the mounting block.

According to a further embodiment of the utility model, the clamping part is further provided with a third threaded through hole, through which a locking bolt is passed for fixedly locking the aircraft rudder to the positioning clamping part.

According to a further embodiment of the utility model, the clamping part is further provided with an adjusting part, which is configured to be able to pass through the clamping part of the positioning clamping part such that its end is pressed against the positioning plane of the rudder of the aircraft, in order to ensure a sufficient fit of the reference plane with the positioning plane.

According to another embodiment of the utility model, the outer surface of the side wall of the positioning and clamping component is further provided with a longitudinally extending middle surface marking line, and the middle surface marking line is positioned on the extending surface of the datum plane.

According to another embodiment of the utility model, the positioning and clamping member is made of a metallic material and has been surface treated.

On the basis of conforming to the common knowledge in the field, the above preferred conditions can be arbitrarily combined to obtain the preferred examples of the utility model.

The positive progress effect of the above embodiment of the utility model is that: the zero calibration device can easily limit the gesture of the aircraft rudder, zero calibrate the aircraft rudder and keep the aircraft rudder at a mechanical zero position, and has the advantages of strong practicability, simple structure and zero calibration operation and wide application range.

Drawings

FIG. 1 is a schematic view of an aircraft rudder initially installed behind a vertical stabilizer of an aircraft tail;

FIG. 2 is a schematic view of a zero calibration device for an aircraft rudder according to a preferred embodiment of the utility model;

FIG. 3 is a partial cross-sectional view of the zero calibration device of FIG. 2;

FIG. 4 is a schematic illustration of an L-shaped calibration block for calibrating measurement light prior to aircraft rudder zero calibration in accordance with a preferred embodiment of the present utility model;

FIG. 5 is an assembled schematic view of the calibration of the measuring light in the zero calibration device of FIG. 2 using the L-shaped calibration block of FIG. 4;

FIG. 6 is an assembled schematic view of an aircraft rudder zero calibration after measurement light calibration using the zero calibration device of FIG. 2;

wherein reference numerals are as follows:

1-an aircraft rudder; 11-positioning plane; 12-a fuselage measurement plane; 13-target region; 14-trailing edge portion; 15-a right edge line of the trailing edge portion; 2-positioning the clamping member; 21-a clamping part; 22-opening parts; 23-a housing; 24-datum plane; 25-an adjustment member; 26-mid-plane identification line; 27-adjusting bolts; 3-measuring means; 31-a laser emitter; 32-mounting blocks; 33-a set screw; 34-grooves; 35-pre-tightening a spring; 36-a first threaded through hole; a 4-L shaped calibration block; 41-a conforming surface; 42-a calibration surface; 43-groove graduation line.

Detailed Description

For the purposes of clarity, technical solutions and advantages of the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings, which show various embodiments according to the present application. It should be understood that the described embodiments are only some, but not all, of the embodiments of the present application. All other embodiments, which can be made by one of ordinary skill in the art without undue burden on the person of ordinary skill in the art based on the embodiments described herein, are intended to be within the scope of the present application.

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs; the terminology used in the description of the application herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application; the terms "comprising," "having," "with," and the like in the description of the present application and in the claims and drawings described above are used for open ended terms. Thus, an apparatus that "comprises," "has," or "has" one or more elements, but is not limited to having only one or more elements. The terms first, second and the like in the description and in the claims or in the above-described figures, are used for distinguishing between different objects and not necessarily for describing a particular sequential or chronological order. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present application, unless otherwise indicated, the meaning of "a plurality" is two or more.

In the description of the present application, it should be understood that directional terms, such as "upper", "lower", "below", "longitudinal", "transverse", "bottom", etc., are used for convenience of description of the present application and for simplification of the description based on the azimuth or the positional relationship shown in the drawings, and do not indicate or imply that the apparatus or element to be referred to must have a specific azimuth, be configured and operated in a specific azimuth, and thus should not be construed as limiting the present application.

In the description of the present application, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "attached," "fixedly secured" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art as the case may be.

Reference in the specification to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment may be included in at least one embodiment of the application. The appearances of such phrases in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. Those of skill in the art will explicitly and implicitly understand that the embodiments described herein may be combined with other embodiments.

As noted above, it should be emphasized that the term "comprises/comprising" when used in this specification is taken to specify the presence of stated features or components, but does not preclude the presence or addition of one or more other features, components or groups of features, components. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.

The term "and/or" in this application is merely an association relation describing an associated object, and indicates that three relations may exist, for example, a and/or B may indicate: a exists alone, A and B exist together, and B exists alone. In this application, the character "/" generally indicates that the associated object is an or relationship.

After the aircraft has performed rudder inspection and maintenance tasks on the airlines, mechanical zeroing is required during installation of the aircraft rudder 1. When the aircraft rudder 1 is reinstalled, after the aircraft rudder 1 is connected with the vertical stabilizer rear edge cabin hinge joint, mechanical zeroing of the aircraft rudder 1 is needed, and the attitude of the aircraft rudder 1 is limited, so that the aircraft rudder 1 is in a mechanical zero position and kept.

Therefore, the utility model provides a novel zero calibration device for the aircraft rudder 1, and the zero calibration device can conveniently, quickly and accurately calibrate the zero of the aircraft rudder 1. In particular, fig. 2 shows a zero calibration device for an aircraft rudder 1 according to a preferred embodiment of the utility model. As shown in fig. 2, the zero calibration device comprises a positioning clamping member 2 and a measuring member 3 mounted on the positioning clamping member 2. The positioning and clamping member 2 serves to clamp the trailing edge portion 14 of the aircraft rudder 1 and to bring the reference surface 24 on the inside of the positioning and clamping member 2 into full abutment with the positioning plane 11. The laser transmitter 31 in the measuring part 3 is capable of transmitting measuring light downwards, wherein the collimated measuring light is arranged parallel to the right-hand line of the trailing edge portion of the aircraft rudder and is located on the extension of the reference plane. When the aircraft rudder 1 is clamped in the positioning clamping member 2, the deflection of the aircraft rudder 1 is adjusted, the positions of the positioning clamping member 2 and the measuring member 3 can be changed, thereby enabling the calibrated measuring light to be located in the target area 13 of the fuselage measuring plane 12 for zero calibration.

Specifically, as shown in fig. 2 and 3, the positioning and clamping member 2 includes a clamping portion 21 having a C-shaped cross section, the clamping portion 21 including an opening portion 22 toward the insertion direction of the aircraft rudder 1, a housing portion 23 for housing the aircraft rudder 1, and a reference surface 24 formed on an inner side surface of the housing portion 23 and extending longitudinally, wherein the trailing edge portion 14 of the aircraft rudder 1 can be inserted into the clamping portion 21 through the opening portion 22 and firmly clamped to the housing portion 23 such that the reference surface 24 sufficiently conforms to the positioning plane 11. Preferably, the end of the clamping part 21 remote from the opening part 22 is provided with a third threaded through hole, by means of which the aircraft rudder 1 can be fixedly locked to the positioning clamping part 2 by means of a locking bolt. The positioning and clamping part 2 adopts an integrated design, and the integrated design can effectively improve the system precision of the zeroing tool and avoid errors caused by assembly. Preferably, the positioning and clamping part 2 is made of metal material and is subjected to surface treatment to meet the rust-proof requirement

Preferably, an adjusting member 25 is further provided at the clamping portion 21, which adjusting member 25 is configured to be able to pass through the clamping portion 21 such that its end portion directly abuts against the left side surface of the aircraft rudder 1 (i.e. the side of the aircraft rudder 1 opposite to the positioning plane), thereby abutting against the positioning plane 11 of the aircraft rudder 1, so that it is possible to ensure that the reference plane 24 and the positioning plane 11 are sufficiently fitted by adjusting the distance of the adjusting member 25 from the reference plane 24. Preferably, the adjusting member 25 is 2 rudder adjusting bolts mounted to the clamping portion 21 and passing through threaded through holes in the clamping portion, and the rudder adjusting bolts are screwed into the rudder adjusting bolts to press against the aircraft rudder 1, thereby ensuring that the reference surface 24 is sufficiently fitted to the positioning plane 11.

The measuring part 3 is mounted in a mounting cavity on the positioning and clamping part 2, wherein the upper end of the mounting cavity is open and the bottom has an opening extending in the longitudinal direction of the positioning and clamping part 2 through the bottom wall of the positioning and clamping part 2, the size of the opening being slightly smaller than the size of the measuring part 3. The measuring part 3 comprises a laser emitter 31 capable of emitting measuring light, which measuring light emitted by the laser emitter 31 is emitted downwards through an opening provided in the bottom of the installation cavity. Preferably, when the aircraft rudder 1 is clamped to the positioning clamping member 2, the longitudinal direction of the positioning clamping member is the same as the longitudinal direction of the aircraft rudder 1.

As shown in fig. 2 and 3, the side wall of the positioning and holding member is formed with a through groove 34 extending longitudinally, and a pre-tightening spring 35 is provided between the measuring member 3 and the groove 34, the pre-tightening spring 35 being configured to be capable of pressing the measuring member 3 by a spring restoring force, thereby mounting the measuring member 3 on the positioning and holding member 2 in cooperation with the inner wall surface of the positioning and holding member 2. In particular, the side walls of the mounting cavity further comprise a longitudinally extending through groove 34. Another exemplary embodiment of the positioning clamp 2 further comprises a first threaded through hole 36 extending transversely on different sides of the pretensioning spring 35 and an adjusting bolt 27, the adjusting bolt 27 being configured to be able to press the measuring part 3 through the first threaded through hole 36, and to calibrate the measuring light by adjusting the angular offset of the measuring part 3 in cooperation with the pretensioning spring 35. The adjusting bolt 27 cooperates with the pre-tightening spring 35 to provide a certain damping, and performs an angular offset and a position adjustment on the measuring light emitted from the laser emitter 31, thereby calibrating the measuring light.

Illustratively, the first threaded through holes 36 are configured in a plurality, the plurality of first threaded through holes 36 having different directions and being located on different sides of the positioning clamp member 2. The adjusting bolts 27 are correspondingly configured in a plurality, each adjusting bolt 27 is respectively pressed against the measuring part 3 from different directions through a corresponding first threaded through hole 36, and the angular offset of the measuring part 3 is adjusted by being matched with the adjusting bolts 27 and/or the pre-tightening springs 35 in different directions. The outer surface of the side wall of the positioning and clamping part 2 is also provided with a longitudinally extending median marking line 26, and the median marking line 26 is positioned on the extension surface of the reference surface 24.

As another example, as shown in fig. 3, the measuring component 3 further comprises a mounting block 32 for clamping the fixed, laser transmitter 31, wherein the mounting block 32 comprises a longitudinally extending through hole and a transversely extending second threaded through hole, the through hole being configured to be able to receive the laser transmitter 31, the stop screw 33 being arranged to press the laser transmitter 31 through the second threaded through hole to clamp the laser transmitter 31 in the mounting block 32. Preferably, the laser transmitter 31 is cylindrical and is disposed in a through hole of the mounting block 32. The 2 set screws pass through the second threaded through holes in the mounting block 32 from 2 directions, respectively, against and hold the laser transmitter 31 in the mounting block 32, thereby mounting the laser transmitter 31 in the mounting block 32 of the measuring part 3.

Fig. 4 shows an L-shaped calibration block 4 for calibrating measuring light before the zero calibration of the aircraft rudder 1. As shown in fig. 4, an abutment surface 41 is formed at one side of the longitudinal section of the L-shaped calibration block 4, and the abutment surface 41 is shaped to conform to the positioning plane 11 such that the abutment surface 41 is sufficiently abutted with the positioning plane 11 when the L-shaped calibration block 4 is inserted into the clamping portion. Specifically, when the longitudinal section of the L-shaped calibration block 4 is inserted into the holding portion 21 through the opening portion 22 and is firmly held in the accommodating portion 23, the side thereof facing the positioning plane 11 is formed with the fitting surface 41. The shape of the fitting surface 41 is configured to be consistent with the positioning plane 11, and parameters such as surface roughness, flatness, etc. are consistent with the positioning plane 11. At the same side of the lateral section of the L-shaped calibration block 4 as the abutment surface 41, a calibration surface 42 is formed, which calibration surface 42 is provided with groove graduations 43, which groove graduations 43 are configured as side lines extending parallel to the longitudinal direction of the abutment surface 41, wherein by adjusting the measuring part 3 measuring light rays emitted by the measuring part 3 can be made to fall into the groove graduations 43, whereby the measuring light rays are calibrated.

In fig. 4, the direction perpendicular to the paper surface is the left-right direction, the right side of the longitudinal section of the L-shaped calibration block 4 is provided with an abutment surface 41, the right side of the transverse section of the L-shaped calibration block 4 is provided with a calibration surface 42, the calibration surface 42 is coplanar with the abutment surface 41 and a groove graduation line 43 is provided thereon, and the groove graduation line 43 is configured to be parallel to a side line of the abutment surface 41 extending in the longitudinal direction. Preferably, the longitudinal direction of the L-shaped calibration block 4 is the same as the longitudinal direction of the rudder of the aircraft.

Fig. 5 shows an assembly of the use of an L-shaped calibration block 4 for calibrating measuring light. As shown in fig. 5, when the L-shaped calibration block 4 is used to calibrate the measuring light, the longitudinal section portion of the L-shaped calibration block 4 is inserted into the holding portion 21 through the opening portion 22 and is firmly held in the accommodating portion 23. At this time, an abutting surface 41 is formed on the side of the longitudinal section of the L-shaped calibration block 4 facing the positioning plane 11, the abutting surface 41 abutting against the positioning plane 11, and the transverse section portion of the L-shaped calibration block 4 and the calibration surface 42 thereon are located below the measuring member 3. On different sides of the measuring part 3, adjusting bolts 27 are arranged in different directions for adjusting the angle and position of the measuring part 3, and the collimated measuring light falls on groove graduation marks 43 below the L-shaped collimating block 4.

The process of calibrating the measuring light using the L-shaped calibration block 4 includes: the L-shaped calibration block 4 is inserted into the clamping portion 21 through the opening 22 of the positioning clamping member 2, with the abutment surface 41 of the L-shaped calibration block 4 in the receiving portion 23 and in abutment with the datum surface 24, thereby ensuring that the datum surface of the grooved graduation marks 43 of the L-shaped calibration block 4 is substantially coplanar with the datum surface 24 of the positioning clamping member. By positioning the adjustment member 25 on the clamping member 2, the abutment surface 41 of the L-shaped calibration block 4 can be made substantially abutting, i.e. coplanar, with the reference surface 24, with the longitudinally extending edge of the abutment surface 41 being parallel to the mid-plane reference line 26. After the L-shaped calibration block 4 is fixed and adjusted, the angle and the position of the measuring light are adjusted by fine adjustment of the adjusting bolts 27 in different directions, so that the measuring light emitted by the measuring component 3 is exactly captured by the groove score line on the L-shaped calibration block 4. Because the L-shaped calibration block 4 adopts an integrated design, machining precision is guaranteed easily, and groove scribing is guaranteed to be coplanar with the attaching surface 41 and parallel to the side line of the attaching surface 41 extending longitudinally, so that an effective calibration measurement light effect can be achieved.

Subsequently, as shown in fig. 6, the aircraft rudder 1 is zero calibrated using the zero calibration device after the measurement light calibration. The zero calibration procedure for the aircraft rudder 1 using the zero calibration device comprises: the measurement light calibration is zeroed mechanically with the aircraft rudder 1. Specifically, the process of measuring light calibration includes: clamping the L-shaped calibration block 4 to the clamping portion 21 of the positioning clamping member 2, with the fitting surface 41 of the L-shaped calibration block 4 in the receiving portion 23 and fitting with the reference surface 24; initially adjusting the measuring light of the measuring part 3 to be located on the alignment surface 42 of the L-shaped alignment block 4; and then the adjusting bolts 27 in different directions are matched with the pre-tightening springs 35 arranged in the grooves 34 of the positioning and clamping components 2, the positions and angles of measuring light rays of the measuring components are adjusted, the measuring light rays penetrate through groove graduation marks 43 of the L-shaped calibration block 4, and at the moment, the measuring light rays are calibrated, and the measuring light rays are parallel to the middle plane marking lines 26 and are located on the plane where the reference planes 24 are located.

Specifically, the aircraft rudder 1 mechanical change positioning process includes: after the light to be measured is calibrated, the L-shaped calibration block 4 is detached from the clamping and positioning component 2; then clamping the aircraft rudder 1 to the clamping part 21 of the positioning clamping part 2, so that the aircraft rudder 1 is positioned above the fuselage measurement plane 12, and fully fitting the reference plane 24 and the positioning plane 11 by using the adjusting part 25 to keep consistent; adjusting the angle and position of the measuring light using the adjusting bolt 27, ensuring that the measuring light is located on the extension of the locating plane 11 and parallel to the right side line 15 of the trailing edge portion 14; when the aircraft rudder 1 is firmly clamped in the positioning clamping member 2, the position of the trailing edge portion 14 of the aircraft rudder 1 is changed by adjusting the hinge connected to the leading edge of the aircraft rudder 1, so that the positions of the positioning clamping member 2 and the measuring member 3 are also adjusted accordingly, so that the measuring light is located in the target area 13 on the fuselage measuring plane 12, thereby completing the mechanical zero calibration of the aircraft rudder 1.

The zero calibration device provided by the utility model can effectively realize zero calibration of the rudder 1 of the aircraft, has high accuracy, few operation steps, simple structure and good economic benefit, and can be widely applied to mechanical zero adjustment of the rudder in the installation procedure of the rudder 1 of the aircraft after the aircraft performs the rudder checking and maintaining tasks on the airlines.

While specific embodiments of the utility model have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and the scope of the utility model is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the principles and spirit of the utility model, but such changes and modifications fall within the scope of the utility model.

Claims

1. A zero calibration device for an aircraft rudder comprising a locating plane located to the right of its trailing portion and extending longitudinally of the aircraft rudder and mounted above a fuselage measurement plane of the aircraft by a hinge provided between its leading edge and an aircraft vertical stabilizer, characterized in that it comprises:

a positioning and clamping member including a clamping portion having a C-shaped cross section, the clamping portion including an opening portion toward an insertion direction of the aircraft rudder and a receiving portion for receiving the aircraft rudder, a longitudinally extending reference surface being formed on an inner side surface of the receiving portion, wherein a trailing edge portion of the aircraft rudder can be inserted into the clamping portion through the opening portion and firmly clamped in the receiving portion such that the reference surface is sufficiently fitted to the positioning plane;

the measuring component is arranged on the positioning and clamping component and comprises a laser emitter, measuring light emitted by the laser emitter is downwards emitted through an opening arranged on the bottom wall of the positioning and clamping component,

wherein the collimated measuring ray is configured parallel to a right-hand line of the trailing edge portion of the aircraft rudder and is located on an extension of the reference plane; and, in addition, the processing unit,

wherein when the aircraft rudder is firmly clamped in the positioning clamping member, the position of the trailing edge portion of the aircraft rudder is changed by adjusting the hinge connected to the leading edge of the aircraft rudder, thereby changing the positions of the positioning clamping member and the measuring member, thereby causing the collimated measuring light to lie within the target area of the fuselage measuring plane.

2. The zero calibration device according to claim 1, further comprising an L-shaped calibration block for calibrating measuring light prior to zero calibration of an aircraft rudder, a longitudinal section of the L-shaped calibration block being insertable into the clamping portion through the opening and securely clamped in the receiving portion, wherein an abutment surface is formed on a side of the longitudinal section of the L-shaped calibration block facing a positioning surface, the abutment surface being shaped to conform to the positioning plane such that the abutment surface substantially abuts the positioning plane when the L-shaped calibration block is inserted into the clamping portion.

3. A zero calibration device according to claim 2, characterized in that a calibration surface is formed at the same side of the lateral section of the L-shaped calibration block as the abutment surface, which calibration surface is provided with groove graduations configured as side lines extending parallel to the longitudinal direction of the abutment surface, wherein the measuring light rays emitted by the measuring means can be caused to fall into the groove graduations by adjusting the measuring means, whereby the measuring light rays are calibrated.

4. A zero calibration device according to claim 3, characterized in that the side wall of the positioning clamp member is formed with a longitudinally extending through recess, and that a pre-tension spring is provided between the measuring member and the recess, the pre-tension spring being configured to be able to press the measuring member by means of a spring restoring force, thereby mounting the measuring member on the positioning clamp member in cooperation with the inner wall surface of the positioning clamp member.

5. The zero calibration device of claim 4, wherein the positioning clamp member further comprises a first laterally extending threaded through hole on a different side of the preload spring and an adjustment bolt extending through the first threaded through hole, the adjustment bolt pressing against the measurement member to adjust an angular offset of the measurement member in cooperation with the preload spring to cause measurement light from the measurement member to fall into the groove graduation mark.

6. The zero calibration device of claim 5, wherein there are a plurality of said first threaded through holes and a plurality of said first threaded through holes are open on different sides of said locating clamp member; the adjusting bolts are correspondingly arranged in a plurality, and each adjusting bolt is respectively pressed against the measuring component from different directions through the corresponding first threaded through hole, so that the angle offset of the measuring component in different directions is adjusted.

7. The zero calibration device of claim 5, wherein the measurement component further comprises a mounting block for clamping the laser transmitter, wherein the mounting block comprises a longitudinally extending through bore and a transversely extending second threaded through bore, wherein the through bore is configured to receive the laser transmitter, and a set screw is passed through the second threaded through bore to press against the laser transmitter to securely clamp the measurement component in the mounting block.

8. The zero calibration device of claim 1, wherein a third threaded through hole is further provided in the clamp portion through which a locking bolt passes to fixedly lock the aircraft rudder to the locating clamp member.

9. The zero calibration device of claim 1, wherein the clamping portion is further provided with an adjustment member configured to pass through the clamping portion of the positioning clamping member such that an end thereof is pressed against a positioning plane of the aircraft rudder to ensure that the reference plane is sufficiently conformed to the positioning plane.

10. The zero calibration device of claim 1, wherein the positioning clamp member further has a longitudinally extending mid-plane indicator line on an outer surface of the sidewall, the mid-plane indicator line being located on an extended surface of the datum plane.

11. The zero calibration device of claim 1, wherein the positioning clamp member is made of a metallic material and has been surface treated.