CN113483738A - Aircraft horizontal adjustment method, aircraft horizontal measurement device and aircraft horizontal measurement method - Google Patents
Aircraft horizontal adjustment method, aircraft horizontal measurement device and aircraft horizontal measurement method Download PDFInfo
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- CN113483738A CN113483738A CN202110708464.8A CN202110708464A CN113483738A CN 113483738 A CN113483738 A CN 113483738A CN 202110708464 A CN202110708464 A CN 202110708464A CN 113483738 A CN113483738 A CN 113483738A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C9/00—Measuring inclination, e.g. by clinometers, by levels
- G01C9/18—Measuring inclination, e.g. by clinometers, by levels by using liquids
- G01C9/24—Measuring inclination, e.g. by clinometers, by levels by using liquids in closed containers partially filled with liquid so as to leave a gas bubble
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C9/00—Measuring inclination, e.g. by clinometers, by levels
- G01C9/005—Measuring inclination, e.g. by clinometers, by levels specially adapted for use in aircraft
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C9/00—Measuring inclination, e.g. by clinometers, by levels
- G01C9/02—Details
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Abstract
The invention discloses an aircraft leveling method, an aircraft leveling device and an aircraft leveling method, wherein the aircraft leveling device comprises a longitudinal leveling mechanism and a transverse leveling mechanism, the longitudinal leveling mechanism comprises a laser level meter, the laser level meter comprises a shell, a display and a laser emission point, the display is arranged in the shell, the laser emission point is arranged on the side wall of the shell, the shell is also provided with a vertical measuring scale, the lower end of the shell is detachably connected with a scale turntable, the scale turntable is provided with a turntable knob, the lower end of the scale turntable is provided with a joint, the joint is provided with a first knob and a second knob, the first knob and the second knob adjust the inclination angle of the shell, the lower end of the joint is provided with a telescopic support rod, the support rod is sleeved with a third knob, the lower end of the support rod is provided with a connecting piece, the connecting piece is provided with a bubble, and the lower end of the connecting piece is provided with a triangular bracket; horizontal level measurement mechanism includes sucking disc subassembly, locating component and measures and erects the chi, and the locating component both sides link to each other with the sucking disc subassembly, and the locating component middle part links to each other with measuring perpendicular chi.
Description
Technical Field
The invention relates to the technical field of aircraft measurement, in particular to an aircraft leveling method, an aircraft leveling device and an aircraft leveling method.
Background
Before the aircraft is on the air, the aircraft needs to carry out installation and calibration work on certain important finished products in a horizontal state, so that the accuracy of indexes such as target shooting precision, radar scanning range and landing attitude of the aircraft in the flying process is guaranteed. The method for leveling the aircraft at the present stage still stays in the middle and later period of the last century, and completely cannot keep up with the development requirement of the era.
The traditional aircraft longitudinal leveling method and the mainly used tool are mutually perpendicular rigid T-shaped rulers, wherein the longer side of the T-shaped ruler is provided with scale marks, and the end part of the other side of the T-shaped ruler is of a sharp point structure. The traditional horizontal leveling method of the aircraft and the mainly used tool are a vertical ruler with scales.
When the rigid T-square is used for measuring the horizontal point, an operator firstly needs to fix the T-square on the T-square support and level the T-square support, then the operator contacts the sharp point structure of the horizontal part of the T-square with the horizontal measuring point on the machine body, and finally the other operator uses the level meter to read. The T-square has larger size and is heavier, and the T-square support does not have the requirement of fixed inspection, so that on one hand, the leveling process of the T-square support is time-consuming and labor-consuming, and the inconvenience of the T-square support is more remarkable when the T-square support is used in an external field; on the other hand, the accuracy of the t-square bracket is gradually reduced due to long-term use on a business trip.
When the vertical ruler is used for measuring the horizontal point, an operator needs to contact one end of the vertical ruler with the horizontal measuring point on the lower surface of the wing, then the other end of the vertical ruler naturally sags under the action of gravity, and the other person uses the level meter to read the vertical ruler. The vertical ruler is held by an operator, so that the problem of vertical ruler jitter inevitably occurs, and horizontal measuring points on the left wing and the right wing are adjusted by adopting a traditional method, so that on one hand, the measured result has large errors, and the accuracy of the measured result is seriously influenced; on the other hand, the number of operators is large, and the cost is increased when the field is out of business.
Disclosure of Invention
In order to solve the technical problems, the invention provides an aircraft horizontal adjusting method, an aircraft horizontal measuring device and an aircraft horizontal measuring method.
The purpose of the invention is realized by the following technical scheme:
an aircraft leveling device, characterized in that: the device comprises a longitudinal horizontal measuring mechanism and a transverse horizontal measuring mechanism, wherein the longitudinal horizontal measuring mechanism is used for measuring the longitudinal horizontal of the aircraft, and the transverse horizontal measuring mechanism is used for measuring the transverse horizontal of the aircraft; the longitudinal leveling mechanism comprises a laser level meter, the laser level meter comprises a shell, a display and a laser emission point, the display is arranged in the shell, the laser emission point is arranged on the side wall of the shell, a vertical measuring scale is further arranged on the shell, the lower end of the shell is detachably connected with a scale turntable, a turntable knob is arranged on the scale turntable, a joint is arranged at the lower end of the scale turntable, a first knob and a second knob are arranged on the joint and used for adjusting the inclination angle of the shell, a telescopic supporting rod is arranged at the lower end of the joint, a third knob is sleeved on the supporting rod, a connecting piece is arranged at the lower end of the supporting rod, a water bubble is arranged on the connecting piece, and a triangular support is arranged at the lower end of the connecting piece; horizontal level measurement mechanism includes sucking disc subassembly, locating component and measures and erects the chi, the locating component both sides link to each other with the sucking disc subassembly, the locating component middle part links to each other with measuring perpendicular chi.
Preferably, the shell is provided with a vertical measuring scale hanging nail, and the vertical measuring scale is hung on the vertical measuring scale hanging nail.
Preferably, the triangular support comprises three auxiliary supports, and a fourth knob is sleeved on each auxiliary support.
Preferably, the positioning assembly comprises a positioning support, positioning plates are arranged on two sides of the positioning support, the middle of the positioning support is hinged to the measuring vertical ruler, the positioning plates are connected with the sucker connecting pieces on the sucker assembly, and suckers are arranged at the ends, far away from the positioning assembly, of the sucker connecting pieces.
Preferably, the spine part at the upper end of the measuring vertical ruler is flush with the upper surface of the positioning plate.
The aircraft leveling method is characterized by comprising an aircraft longitudinal leveling method and an aircraft transverse leveling method,
the longitudinal leveling method comprises the following steps:
step A1, moving the supporting rod to enable the distance between the supporting rod and the aircraft body to be 1m, and fixing the laser level meter on the supporting rod;
step A2, opening the triangular support, and adjusting the angle and the height of the triangular support through a fourth knob to enable the bubbles to be in the middle of the green area;
step A3, adjusting the first knob and the second knob to enable the data displayed by the display to be 0.00, then rotating the shell by 90 degrees, and adjusting the first knob and the second knob again to enable the data displayed by the display to be 0.00;
step A4, turning on a switch of the laser level meter, and adjusting the height of the supporting rod through a third knob to enable laser spots emitted by the laser emitting point to reach a horizontal measuring point on the aircraft body;
step A5, opening a vertical measuring ruler, keeping the vertical measuring ruler in a vertical state by means of gravity, and reading scales on the vertical measuring ruler by an operator through a level gauge so as to determine a numerical value;
the transverse level measurement method comprises the following steps:
step B1, adjusting a positioning component on the transverse horizontal measuring mechanism to ensure that a spine part at the upper end of the measuring vertical ruler coincides with a horizontal measuring point on the lower surface of the aircraft wing, and then slightly pushing the sucker component upwards to enable the sucker component to be tightly adsorbed on the lower surface of the wing;
and step B2, after the vertical ruler to be measured stops swinging, an operator reads the scales on the vertical ruler to be measured through the level gauge so as to determine the numerical value.
Preferably, in step a3, the housing is rotated 90 ° to the left or the housing is rotated 90 ° to the right.
Preferably, in step a5, in order to ensure that the reading does not generate large error, the operator should read at least 3 times, respectivelya 1、a 2、……a nCalculating the average valueAThen, there are:A=
in step B2, in order to ensure that the reading does not generate large error, the operator should read at least 3 times, respectivelyb 1、b 2、……b nCalculating the average valueBThen, there are:
。
an aircraft leveling method, comprising the steps of:
step C1, measuring two measuring points of the aircraft body by using a longitudinal horizontal measuring method, respectively reading scale values of vertical measuring scales corresponding to the two measuring points, and recording the values as left 2 and left 3;
and C2, calculating the difference value between the left 2 and the left 3, and comparing the size relation between the difference value between the left 2 and the left 3 and A +/-delta, wherein: a represents a design theoretical value, delta represents an allowable error range, and if A < - > delta > is less than or equal to left 2 < - > and left 3 is less than or equal to A < + >, the transverse horizontal state of the measuring points on the left wing and the right wing is adjusted; if left 2-left 3 is more than A +/delta or left 2-left 3 is less than A + -delta, the fuselage does not reach the longitudinal horizontal state, the jacks and brackets at the frame STA (C) and the frame STA (D) are continuously adjusted until A-delta is less than or equal to left 2-left 3 is less than or equal to A +/delta, namely the longitudinal horizontal adjustment of the fuselage of the airplane is completed;
step C3, measuring two measuring points of the aircraft wing by using a transverse horizontal measuring method, respectively reading measuring vertical scale values corresponding to the two measuring points, and recording the values as left 4 and right 4;
step C4, calculating a difference value between the left 4 and the right 4, and comparing the size relationship between the difference value between the left 4 and the right 4 and B +/-lambda, wherein B represents a design theoretical value, lambda represents an allowable error range, and if B < - > lambda is less than or equal to the left 4 and less than or equal to the right 4, B < + > lambda is proved to have reached the longitudinal and transverse horizontal states; if left 4-right 4 > B +/lambda or left 4-right 4 < B-lambda, it indicates that the aircraft has not reached the horizontal state, the jacks and brackets at the STA (C) and STA (D) frames should be adjusted continuously until B-lambda ≦ left 4-right 4 ≦ B +/lambda is satisfied, then the readings of left 2 and left 3 of the aircraft body are checked again and the jacks and brackets at the STA (C) and STA (D) frames are adjusted until A-delta ≦ left 2-left 3 ≦ A +/delta.
Preferably, the horizontal level of the aircraft can be adjusted firstly and then the longitudinal level of the aircraft can be adjusted when the aircraft is adjusted horizontally.
The beneficial effects of this technical scheme are as follows:
the invention provides an aircraft horizontal measuring device, which comprises a mechanism for measuring the longitudinal level of an aircraft, a mechanism for measuring the transverse level of the aircraft and a combined measuring method.
The invention provides an aircraft horizontal measuring device, wherein the vertical measuring scale and the vertical measuring scale are both made of CrWMn materials, and the CrWMn materials are good materials for the vertical measuring tape and the vertical measuring scale which need to be folded and unfolded repeatedly, and have the characteristics of small deformation, high wear resistance and good toughness.
The invention provides the aircraft leveling device, when the aircraft leveling device is not used, the transverse leveling mechanism and the longitudinal leveling mechanism are placed in a suitcase, and the outfield is convenient to use and manage.
Drawings
The invention will be described in further detail with reference to the following description taken in conjunction with the accompanying drawings and detailed description, in which:
FIG. 1 is a general schematic view of a longitudinal leveling mechanism according to the present invention;
FIG. 2 is a partial enlarged view of a key part in the longitudinal leveling mechanism according to the present invention;
FIG. 3 is a schematic view of a vertical leveling scenario;
FIG. 4 is an overall schematic view of the lateral leveling mechanism of the present invention;
FIG. 5 is a partial enlarged view of a key part in the lateral leveling mechanism according to the present invention;
FIG. 6 is a schematic view of a lateral leveling scenario;
FIG. 7 is a flow chart of an aircraft leveling method.
The labels in the figure are: 1. a display; 2. a housing; 3. a vertical measuring scale hanging nail; 4. a scale dial; 5. a dial knob; 6. a first knob; 7. a laser emission point; 8. a laser level; 9. a support bar; 10. a third knob; 11. soaking in water; 12. a sub-mount; 13. a fourth knob; 14. a fuselage leveling point; 15. a laser beam; 16. a vertical measuring scale; 17. the line of sight of the human eye; 18. a level gauge; 19. a triangular bracket; 20. a suitcase; 21. a second knob; 22. a sucker component; 23. a positioning assembly; 24. measuring a vertical ruler; 25. positioning the bracket; 26. positioning a plate; 27. a suction cup connecting piece; 28. a suction cup; 29. a spine part.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.
Example 1
As shown in fig. 1, 2, 4 and 5, an aircraft leveling device includes a longitudinal leveling mechanism for measuring a measurement of a longitudinal level of an aircraft and a lateral leveling mechanism for measuring a measurement of a lateral level of the aircraft; the longitudinal horizontal measuring mechanism comprises a laser level meter 8, the laser level meter 8 comprises a shell 2, a display 1 and a laser emission point 7, the display 1 is arranged in the shell 2, the laser emitting point 7 is arranged on the side wall of the shell 2, the shell 2 is also provided with a vertical measuring scale 16, the lower end of the shell 2 is detachably connected with the scale turntable 4, a dial knob 5 is arranged on the scale dial 4, a joint is arranged at the lower end of the scale dial 4, the joint is provided with a first knob 6 and a second knob 21, the first knob 6 and the second knob 21 are used for adjusting the inclination angle of the shell 2, a telescopic supporting rod 9 is arranged at the lower end of the joint, a third knob 10 is sleeved on the supporting rod 9, the lower end of the support rod 9 is provided with a connecting piece, the connecting piece is provided with a bubble 11, and the lower end of the connecting piece is provided with a triangular bracket 19; horizontal leveling mechanism includes sucking disc subassembly 22, locating component 23 and measures vertical ruler 24, locating component 23 both sides link to each other with sucking disc subassembly 22, locating component 23 middle part links to each other with measuring vertical ruler 24, be provided with vertical dipperstick suspension nail 3 on the shell 2, vertical dipperstick 16 hangs on vertical dipperstick suspension nail 3, tripod 19 includes three auxiliary support 12, and the cover is equipped with fourth knob 13 on the auxiliary support 12, locating component 23 includes locating support 25, the locating support 25 both sides are provided with locating plate 26, locating support 25 middle part is articulated with measuring vertical ruler 24, locating plate 26 links to each other with sucking disc connecting piece 27 on the sucking disc subassembly 22, sucking disc connecting piece 27 keeps away from locating component 23 end and is provided with sucking disc 28. The spike 29 at the upper end of the measuring vertical ruler 24 is flush with the upper surface of the positioning plate 26.
As shown in fig. 3 and 6, an aircraft leveling method includes an aircraft longitudinal leveling method and an aircraft transverse leveling method,
the longitudinal leveling method comprises the following steps:
step A1, moving the support rod 9 to enable the distance between the support rod 9 and the aircraft fuselage to be 1m, and fixing the laser level meter 8 on the support rod 9;
step A2, opening the triangular support 19, and adjusting the angle and the height of the triangular support 19 through the fourth knob 13 to enable the bubbles to be in the middle of the green area;
step A3, adjusting the first knob 6 and the second knob 21 to enable the data displayed by the display 1 to be 0.00, then rotating the shell 2 by 90 degrees, and adjusting the first knob 6 and the second knob 21 again to enable the data displayed by the display 1 to be 0.00;
step A4, turning on a switch of the laser level meter 8, and adjusting the height of the supporting rod 9 through a third knob 10 to enable laser spots emitted by the laser emitting point 7 to reach a horizontal measuring point on the aircraft body;
step A5, opening the vertical measuring ruler 16, keeping the vertical measuring ruler 16 in a vertical state by means of gravity, and reading scales on the vertical measuring ruler 16 by an operator through the level gauge 18 so as to determine a numerical value;
the transverse level measurement method comprises the following steps:
step B1, adjusting the positioning component 23 on the transverse horizontal measuring mechanism to ensure that the spine part 29 at the upper end of the measuring vertical ruler 24 is superposed with the horizontal measuring point on the lower surface of the aircraft wing, and then slightly pushing the sucker component 22 upwards to ensure that the sucker component 22 is tightly adsorbed with the lower surface of the wing;
in step B2, after the vertical ruler 24 to be measured stops swinging, the operator reads the scale on the vertical ruler 24 to be measured by the level 18, thereby determining the numerical value.
Preferably, in step a3, housing 2 is rotated 90 ° to the left or housing 2 is rotated 90 ° to the right.
Preferably, in step a5, in order to ensure that the reading does not generate large error, the operator should read at least 3 times, respectivelya 1、a 2、……a nIf the average value A is calculated, then: a =
In step B2, in order to ensure that the reading does not generate large error, the operator should read at least 3 times, respectivelyb 1、b 2、……b nIf the average value B is calculated, then:
。
as shown in fig. 7, an aircraft leveling method includes the following steps:
step C1, measuring two measuring points of the aircraft body by using a longitudinal horizontal measuring method, respectively reading scale values of a vertical measuring scale 16 corresponding to the two measuring points, and recording the scale values as left 2 and left 3;
and C2, calculating the difference value between the left 2 and the left 3, and comparing the size relation between the difference value between the left 2 and the left 3 and A +/-delta, wherein: a represents a design theoretical value, delta represents an allowable error range, delta is 1-3mm, and if A < - > delta is less than or equal to left 2 < - > left 3 < A < + > delta >, the transverse horizontal state of a measuring point on the left wing and the transverse horizontal state of a measuring point on the right wing are adjusted; if left 2-left 3 is more than A +/delta or left 2-left 3 is less than A + -delta, the fuselage does not reach the longitudinal horizontal state, the jacks and brackets at the frame STA (C) and the frame STA (D) are continuously adjusted until A-delta is less than or equal to left 2-left 3 is less than or equal to A +/delta, namely the longitudinal horizontal adjustment of the fuselage of the airplane is completed;
step C3, measuring two measuring points of the aircraft wing by using a transverse horizontal measuring method, respectively reading the scale values of the measuring vertical ruler 24 corresponding to the two measuring points, and recording the values as left 4 and right 4;
step C4, calculating a difference value between the left 4 and the right 4, and comparing the size relationship between the difference value between the left 4 and the right 4 and B +/-lambda, wherein B represents a design theoretical value, lambda represents an allowable error range, and lambda is 1-3mm, if B < - > lambda is less than or equal to the left 4 and the right 4 is less than or equal to B < + >, the airplane is proved to have reached the longitudinal and transverse horizontal states; if left 4-right 4 > B +/lambda or left 4-right 4 < B-lambda, it indicates that the aircraft has not reached the horizontal state, the jacks and brackets at the STA (C) and STA (D) frames should be adjusted continuously until B-lambda ≦ left 4-right 4 ≦ B +/lambda is satisfied, then the readings of left 2 and left 3 of the aircraft body are checked again and the jacks and brackets at the STA (C) and STA (D) frames are adjusted until A-delta ≦ left 2-left 3 ≦ A +/delta.
Example 2
The difference from the embodiment is that the aircraft horizontal adjusting method adopts the steps of firstly adjusting the horizontal level of the aircraft and then adjusting the longitudinal level of the aircraft. The aircraft leveling method comprises the following steps:
step C1, measuring two measuring points of the aircraft wing by using a transverse horizontal measuring method, respectively reading the scale values of the measuring vertical ruler 24 corresponding to the two measuring points, and recording the values as left 4 and right 4;
c2, calculating a difference value between the left side 4 and the right side 4, and comparing the size relationship between the difference value between the left side 4 and the right side 4 and B +/-lambda, wherein B represents a design theoretical value, lambda represents an allowable error range, and if B < - > lambda is less than or equal to the left side 4 and the right side 4 is less than or equal to B < + >, then adjusting the longitudinal horizontal state of the measuring points on the left wing and the right wing; if left 4-right 4 > B +/λ or left 4-right 4 < B- λ, it means that the aircraft has not reached the horizontal state, the jacks and brackets at the STA (C) frame and STA (D) frame should be adjusted continuously until B- λ ≦ left 4-right 4 ≦ B +/λ is satisfied;
step C3, measuring two measuring points of the aircraft body by using a longitudinal horizontal measuring method, respectively reading scale values of a vertical measuring scale 16 corresponding to the two measuring points, and recording the scale values as left 2 and left 3;
and C4, calculating the difference value between the left 2 and the left 3, and comparing the size relation between the difference value between the left 2 and the left 3 and A +/-delta, wherein: a represents a design theoretical value, delta represents an allowable error range, and if A < - > delta > is less than or equal to left 2 < - > and left 3 is less than or equal to A < + > delta, the airplane is proved to have reached a longitudinal and transverse horizontal state; if left 2-left 3 > A +/delta or left 2-left 3 < A-delta, it indicates that the fuselage has not reached the longitudinal horizontal state, the jacks and brackets at the frame STA (C) and STA (D) should be adjusted continuously until A-delta ≦ left 2-left 3 ≦ A +/delta is satisfied, then the left 4 and right 4 readings of the fuselage are checked again and the jacks and brackets at the frame STA (C) and STA (D) are adjusted until B-lambda ≦ left 4-right 4 ≦ B +/lambda is satisfied.
The invention provides an aircraft horizontal measuring device, which comprises a mechanism for measuring the longitudinal level of an aircraft, a mechanism for measuring the transverse level of the aircraft and a combined measuring method.
The vertical measuring scale 16 and the vertical measuring scale 24 are both made of CrWMn materials, and the CrWMn materials are good materials for the vertical measuring tape and the vertical measuring scale 24 which need to be folded and unfolded for many times, and have the characteristics of small deformation, high wear resistance and good toughness. When not in use, the transverse horizontal measuring mechanism and the longitudinal horizontal measuring mechanism are placed in the suitcase 20, and the outfield is convenient to use and manage.
In summary, after reading the present disclosure, those skilled in the art should make various other modifications without creative efforts according to the technical solutions and concepts of the present disclosure, which are within the protection scope of the present disclosure.
Claims (10)
1. An aircraft leveling device, characterized in that: the device comprises a longitudinal horizontal measuring mechanism and a transverse horizontal measuring mechanism, wherein the longitudinal horizontal measuring mechanism is used for measuring the longitudinal horizontal of the aircraft, and the transverse horizontal measuring mechanism is used for measuring the transverse horizontal of the aircraft; the vertical horizontal measuring mechanism comprises a laser level meter (8), the laser level meter (8) comprises a shell (2), a display (1) and a laser emission point (7), the display (1) is arranged in the shell (2), the laser emission point (7) is arranged on the side wall of the shell (2), a vertical measuring scale (16) is further arranged on the shell (2), the lower end of the shell (2) is detachably connected with a scale turntable (4), a turntable knob (5) is arranged on the scale turntable (4), a joint is arranged at the lower end of the scale turntable (4), a first knob (6) and a second knob (21) are arranged on the joint, the first knob (6) and the second knob (21) are used for adjusting the inclination angle of the shell (2), a telescopic supporting rod (9) is arranged at the lower end of the joint, and a third knob (10) is sleeved on the supporting rod (9), the lower end of the supporting rod (9) is provided with a connecting piece, the connecting piece is provided with a bubble (11), and the lower end of the connecting piece is provided with a triangular bracket (19); horizontal level measurement mechanism includes sucking disc subassembly (22), locating component (23) and measures vertical ruler (24), locating component (23) both sides link to each other with sucking disc subassembly (22), locating component (23) middle part links to each other with measuring vertical ruler (24).
2. An aircraft leveling device according to claim 1 wherein: the casing (2) is provided with a vertical measuring scale hanging nail (3), and the vertical measuring scale (16) is hung on the vertical measuring scale hanging nail (3).
3. An aircraft leveling device according to claim 1 wherein: the triangular support (19) comprises three auxiliary supports (12), and a fourth knob (13) is sleeved on each auxiliary support (12).
4. An aircraft leveling device according to claim 1 wherein: locating component (23) is including locating support (25), locating support (25) both sides are provided with locating plate (26), locating support (25) middle part is articulated with measuring vertical ruler (24), locating plate (26) link to each other with sucking disc connecting piece (27) on sucking disc subassembly (22), locating component (23) end is kept away from in sucking disc connecting piece (27) is provided with sucking disc (28).
5. An aircraft leveling device according to claim 1 wherein: and a spine part (29) at the upper end of the measuring vertical ruler (24) is flush with the upper surface of the positioning plate (26).
6. The aircraft leveling method is characterized by comprising an aircraft longitudinal leveling method and an aircraft transverse leveling method,
the longitudinal leveling method comprises the following steps:
step A1, moving the supporting rod (9) to enable the distance between the supporting rod (9) and the aircraft body to be 1m, and fixing the laser level meter (8) on the supporting rod (9);
step A2, opening the triangular support (19), and adjusting the angle and the height of the triangular support (19) through a fourth knob (13) to enable the bubbles to be located in the middle of the green area;
step A3, adjusting the first knob (6) and the second knob (21) to enable the data displayed by the display (1) to be 0.00, then rotating the shell (2) by 90 degrees, and adjusting the first knob (6) and the second knob (21) again to enable the data displayed by the display (1) to be 0.00;
step A4, turning on a switch of a laser level meter (8), and adjusting the height of a supporting rod (9) through a third knob (10) to enable a laser spot emitted by a laser emission point (7) to reach a horizontal measurement point on the fuselage of the aircraft;
step A5, opening the vertical measuring scale (16), keeping the vertical measuring scale (16) in a vertical state by means of gravity, and reading scales on the vertical measuring scale (16) by an operator through a level gauge (18) so as to determine a numerical value;
the transverse level measurement method comprises the following steps:
step B1, adjusting a positioning component (23) on the transverse horizontal measuring mechanism to ensure that a spine part (29) at the upper end of the measuring vertical ruler (24) is superposed with a horizontal measuring point on the lower surface of the aircraft wing, and then slightly pushing the sucker component (22) upwards to ensure that the sucker component (22) is tightly adsorbed on the lower surface of the wing;
and step B2, after the vertical ruler (24) to be measured stops swinging, an operator reads the scales on the vertical ruler (24) to be measured through the level gauge (18) so as to determine the numerical value.
7. An aircraft leveling method according to claim 6 wherein: in the step A3, the shell (2) rotates 90 degrees to the left or the shell (2) rotates 90 degrees to the right.
8. An aircraft leveling method according to claim 6 wherein: in step a5, in order to ensure that the reading does not generate large errors, the operator should read at least 3 times, respectivelya 1、a 2、……a nIf the average value A is calculated, then: a =
In step B2, in order to ensure that the reading does not generate large error, the operator should read at least 3 times, respectivelyb 1、b 2、……b nIf the average value B is calculated, then:
。
9. an aircraft leveling method, comprising the steps of:
step C1, measuring two measuring points of the aircraft body by using a longitudinal horizontal measuring method, respectively reading scale values of a vertical measuring scale (16) corresponding to the two measuring points, and recording the scale values as left 2 and left 3;
and C2, calculating the difference value between the left 2 and the left 3, and comparing the size relation between the difference value between the left 2 and the left 3 and A +/-delta, wherein: a represents a design theoretical value, delta represents an allowable error range, and if A < - > delta > is less than or equal to left 2 < - > and left 3 is less than or equal to A < + >, the transverse horizontal state of the measuring points on the left wing and the right wing is adjusted; if left 2-left 3 is more than A +/delta or left 2-left 3 is less than A + -delta, the fuselage does not reach the longitudinal horizontal state, the jacks and brackets at the frame STA (C) and the frame STA (D) are continuously adjusted until A-delta is less than or equal to left 2-left 3 is less than or equal to A +/delta, namely the longitudinal horizontal adjustment of the fuselage of the airplane is completed;
step C3, measuring two measuring points of the aircraft wing by using a transverse horizontal measuring method, respectively reading scale values of a measuring vertical ruler (24) corresponding to the two measuring points, and recording the scale values as left 4 and right 4;
step C4, calculating a difference value between the left 4 and the right 4, and comparing the size relationship between the difference value between the left 4 and the right 4 and B +/-lambda, wherein B represents a design theoretical value, lambda represents an allowable error range, and if B < - > lambda is less than or equal to the left 4 and less than or equal to the right 4, B < + > lambda is proved to have reached the longitudinal and transverse horizontal states; if left 4-right 4 > B +/lambda or left 4-right 4 < B-lambda, it indicates that the aircraft has not reached the horizontal state, the jacks and brackets at the STA (C) and STA (D) frames should be adjusted continuously until B-lambda ≦ left 4-right 4 ≦ B +/lambda is satisfied, then the readings of left 2 and left 3 of the aircraft body are checked again and the jacks and brackets at the STA (C) and STA (D) frames are adjusted until A-delta ≦ left 2-left 3 ≦ A +/delta.
10. An aircraft leveling method according to claim 9 wherein: the aircraft horizontal adjusting method can also adjust the horizontal level of the aircraft firstly and then adjust the longitudinal level of the aircraft.
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