CN111912339B - Laser ranging device and method for airplane - Google Patents
Laser ranging device and method for airplane Download PDFInfo
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- CN111912339B CN111912339B CN202010703974.1A CN202010703974A CN111912339B CN 111912339 B CN111912339 B CN 111912339B CN 202010703974 A CN202010703974 A CN 202010703974A CN 111912339 B CN111912339 B CN 111912339B
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- laser
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- shaped target
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- aircraft
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/02—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01G—WEIGHING
- G01G19/00—Weighing apparatus or methods adapted for special purposes not provided for in the preceding groups
- G01G19/02—Weighing apparatus or methods adapted for special purposes not provided for in the preceding groups for weighing wheeled or rolling bodies, e.g. vehicles
- G01G19/07—Weighing apparatus or methods adapted for special purposes not provided for in the preceding groups for weighing wheeled or rolling bodies, e.g. vehicles for weighing aircraft
Abstract
Aircraft laser rangefinder relates to laser rangefinder technical field, especially a device to carrying out the range finding in the aircraft platform formula process of weighing. Two ends of the slide rail are respectively connected with the support legs through transverse plates; the slide rail is arranged in a slide way of the slide block, a thread through hole is arranged on the slide block and communicated with the slide way, and the thread through hole on the slide block is in thread connection with the locking bolt; the laser measuring assembly is connected with the sliding block and comprises a laser ranging sensor module, a laser emitter, an outer shell, a bottom cover and a fixing frame; the outer shell is provided with a cavity with an opening at the lower end, the upper end of the outer shell is provided with two symmetrically distributed strip-shaped through holes, the bottom cover is connected with the opening at the lower end of the outer shell, and one end of the knob penetrates through the through hole on the outer wall of the outer shell to be connected with one end of the worm. The laser measurement assembly accurately positions a connecting line of the axes of the airplane wheels on the left side and the right side of the airplane, then measures the vertical distance between the connecting line of the axes and the axis of the front wheel, and takes the average value of the measured values on the two sides, so that the error caused by the deflection of the front wheel is reduced.
Description
Technical Field
The invention relates to the technical field of laser ranging devices, in particular to a device for ranging in an airplane platform type weighing process.
Background
To ensure the flight safety of an aircraft, the weight and center of gravity of the aircraft must remain within the design envelope at all times. The China civil aviation administration requires that each aviation operator regularly weigh the aircraft operated by the aviation operator, so that the weight and the gravity center of the aircraft continuously meet the airworthiness requirement. The airplane weighing mode generally comprises a jacking mode and an airplane wheel bearing mode. The airplane wheel bearing type is the most commonly used, and the realization mode is as follows: placing a platform scale behind each airplane wheel of the airplane, pushing the airplane onto the platform scale by means of a trailer, wherein the sum of the weights of the platform scales is the total weight of the airplane; and calculating the gravity center position of the airplane through a formula. For some public service aircraft models and small-sized navigation aircraft, in the calculation process, the moment arm value is needed, namely the length data from the axle center of the aircraft wheel to a certain reference point is measured on site. The accuracy of these data directly affects the accuracy of the aircraft center of gravity. However, most airplane design companies only give data to be measured, mainly the horizontal distance between the axle centers of the left and right airplane wheels of the airplane and the axle center of the front wheel or a certain reference point on the airplane body, and no specific measuring method or tool is given. And since the aircraft shock strut is not perpendicular to the ground, the extension of the shock strut affects the value of the wheel wheelbase. In the actual operation process, the position points cannot be accurately projected on the same horizontal plane for measurement by using the traditional measuring methods such as a measuring tape, and when the position points are projected on the ground, large errors exist, so that the accuracy of a calculation result is greatly influenced.
Disclosure of Invention
The invention aims to provide an aircraft laser ranging device and a ranging method aiming at the defects of the prior art, so as to achieve the purpose of accurately measuring the distances between the front and rear wheel distances of an aircraft and the distance between the line connecting two rear wheel axes and a weighing datum point.
The invention provides an aircraft laser ranging device, which comprises a slide rail assembly; the sliding rail assembly comprises a sliding rail, a sliding block, a transverse plate and supporting legs, and two ends of the sliding rail are respectively connected with the supporting legs through the transverse plate; the slide rail is arranged in a slide way of the slide block, a thread through hole is arranged on the slide block and communicated with the slide way, and the thread through hole on the slide block is in thread connection with the locking bolt; the method is characterized in that: the device also comprises a laser measuring component and a T-shaped target; the laser measuring assembly is connected with the sliding block and comprises a laser ranging sensor module, a laser emitter, an outer shell, a bottom cover and a fixing frame; the outer shell is provided with a cavity with an opening at the lower end, the upper end of the outer shell is provided with two symmetrically distributed elongated through holes, the bottom cover is connected with the opening at the lower end of the outer shell, the upper end of the bottom cover is connected with the fixed frame, the fixed frame is fixedly connected with the upper connecting frame and the lower connecting frame from top to bottom in sequence, two sides of the upper connecting frame are respectively provided with a slide way, the lower connecting frame is rotatably connected with the worm, and one end of the knob penetrates through the through hole in the outer wall of the outer shell to be connected with one end of the worm; the fixing frame is rotationally connected with the bidirectional screw rod, two sections of threads of the bidirectional screw rod are respectively positioned in the two slideways of the upper connecting frame, the bidirectional screw rod is fixedly matched with a central hole of the worm wheel, and the worm wheel is meshed with the worm; the fixing frame is hinged with the two laser transmitters respectively, the inner ends of the laser transmitters are connected with the guide pin shaft through the connecting plate, and the outer ends of the laser transmitters are positioned at the position of the rectangular through hole of the outer shell; a guide block provided with a threaded through hole is installed in the slide way of the upper connecting frame, the bidirectional screw rod is in threaded fit with the threaded through hole of the guide block, the guide block is connected with the guide plate, and the guide pin shaft is placed in the elongated guide through hole of the guide plate; a laser ranging sensor module and a lithium battery are arranged in the cavity of the outer shell; the T-shaped target comprises a base and a target sheet, wherein the target sheet is of a T-shaped plate structure, and the lower end of the target sheet is connected with the base.
The support legs comprise an upper support column and a lower support column, the upper end of the upper support column is connected with the transverse plate, the lower end of the upper support column is connected with the threaded sleeve, the lower end of the threaded sleeve is provided with a threaded blind hole, the upper half part of the lower support column is provided with external threads, and the lower support column is in threaded connection with the threaded sleeve.
The upper end of the fixing frame is provided with two groups of ear plates, and each group of ear plates is hinged with the middle position of the laser emitter respectively.
The latter half of above-mentioned shell body is equipped with a battery compartment, installs the lithium cell in the battery compartment.
The upper end walls of the outer shells are respectively provided with a horizontal bubble.
An aircraft ranging method, comprising the steps of:
step 1, placing an aircraft laser ranging device in the middle of two rear wheels of an aircraft, adjusting the angle of a laser emitter by rotating a knob to enable the center point of a cross laser beam emitted by the laser emitter to be located at the position with the same height as the axle center points of the two rear wheels, and enabling the center point of the cross laser beam emitted by the laser emitter to be located at the position of the axle center points of the two rear wheels by adjusting the position of a sliding rail component;
step 4, calculating the average value of the measured values B1 and B2 at two sides, namely the distance B to be measured;
and 5, finding out a weighing reference point in an airplane manual, hanging a plumb at the weighing reference point, placing the front surface of the T-shaped target under the plumb, moving a slide block on a slide rail to enable a laser ranging sensor module of the laser measuring assembly to be aligned with the T-shaped target, fixing the slide block by using a locking bolt, starting the laser ranging sensor module, enabling a measuring laser beam to shoot to the T-shaped target, and recording a measured distance value A.
Compared with the prior art, the invention has the following outstanding beneficial effects:
1. the device can adjust the angles of the two laser transmitters by rotating the knob, so that cross laser beams emitted by the laser transmitters can be aligned to the axle center points of airplane rear wheels with different specifications and models;
2. the T-shaped targets are respectively arranged on two sides of the axle center of the front wheel of the airplane, the connecting line of the axle centers of the wheels on the left side and the right side of the airplane is accurately positioned through the laser measuring assembly, then the vertical distance between the connecting line of the axle centers and the axle center of the front wheel is measured, the average value of the measured values on the two sides is taken, and the error caused by deflection of the front wheel is reduced.
Drawings
Fig. 1 is a schematic structural view of the present invention.
Fig. 2 is a schematic structural diagram of a laser measuring assembly of the present invention.
Fig. 3 is a perspective view of the internal structure of the laser measuring assembly of the present invention.
Fig. 4 is a front view of the internal structure of the laser measuring assembly of the present invention.
Fig. 5 is a schematic structural view of a T-type target portion of the present invention.
Detailed Description
The invention is further described with reference to the drawings and the detailed description.
As shown in fig. 1 to 5, the present invention includes a laser measuring assembly 1, a slide rail assembly 2 and a T-shaped target 3.
As shown in fig. 2 to 4, the laser measuring assembly 1 includes a laser ranging sensor module 103, a laser emitter 115, an outer casing 101, a bottom cover 110, and a fixing frame 111.
The outer shell 101 is provided with a cavity with an opening at the lower end, the upper end of the outer shell 101 is provided with two symmetrically distributed elongated through holes which are communicated with the cavity of the outer shell 101, the bottom cover 110 is in threaded connection with the opening at the lower end of the outer shell 101, the upper end of the bottom cover 110 is fixedly connected with the fixing frame 111, the fixing frame 111 is fixedly connected with the upper connecting frame 113 and the lower connecting frame 112 from top to bottom in sequence, two sides of the upper connecting frame 113 are respectively provided with a slide way, the lower connecting frame 112 is rotatably connected with the worm 116, the outer wall of the outer shell 101 is provided with a through hole, and one end of the knob 102 penetrates through the through hole on the outer wall of the outer shell 101 to be fixedly connected with one end of the worm 116.
The fixing frame 111 is rotatably connected with the bidirectional screw rod 119, a through hole is formed in the joint of the fixing frame 111 and the upper connecting frame 113, two ends of the bidirectional screw rod 119 respectively penetrate through the through hole in the joint of the fixing frame 111 and the upper connecting frame 113 to be rotatably matched with the side wall of the slideway of the upper connecting frame 113, two sections of threads of the bidirectional screw rod 119 are respectively positioned in the two slideways of the upper connecting frame 113, the middle position of the bidirectional screw rod 119 is fixedly matched with a central hole of the worm wheel 117, and the worm wheel 117 is meshed with the worm 116.
Two groups of ear plates 118 are arranged at the upper end of the fixing frame 111, each group of ear plates 118 is hinged with the middle position of the laser emitter 115, the inner end of the laser emitter 115 is vertically and fixedly connected with the connecting plate 122, the outer end of the laser emitter 115 is positioned at the position of the rectangular through hole of the outer shell 101, and the lower end of the connecting plate 122 is fixedly connected with the guide pin shaft 121.
The two slideways of the upper connecting frame 113 are respectively provided with a guide block 120, the side wall of the guide block 120 is attached to the side wall of the slideway, the guide block 120 is provided with a threaded through hole, the bidirectional screw rod 119 is in threaded fit with the threaded through hole of the guide block 120, the upper end of the guide block 120 is fixedly connected with the guide plate 114, and the guide pin shaft 121 is placed in the elongated guide through hole of the guide plate 114.
Be equipped with a notch on the lateral wall of the first half of shell body 101, the notch link up with the cavity of shell body 101 mutually, and laser ranging sensor module 103 passes the notch fixed mounting of shell body 101 in the upper end of mount 111, and the latter half of shell body 101 is equipped with a battery compartment 104, installs lithium cell 105 in the battery compartment 104. The laser beam emitted by the laser ranging sensor module 103 is perpendicular to the plane formed by the laser beams emitted by the two laser emitters 115.
The laser emitter 115, the power switch 107 and the lithium battery 105 are connected through a power supply, the power switch 107 controls the on and off of the laser emitter 115, the circuit is the prior art, and the specific structure of the circuit is not described in detail.
The slide rail assembly 2 comprises slide rails 201, sliders 207, a transverse plate 205 and support legs, two ends of the two slide rails 201 are fixedly connected with the transverse plate 205 respectively, two ends of the transverse plate 205 are provided with one support leg respectively, each support leg comprises an upper support column 204 and a lower support column 202, the upper end of the upper support column 204 is fixedly connected with the transverse plate 205, the lower end of the upper support column 204 is fixedly connected with a threaded sleeve 203, the lower end of the threaded sleeve 203 is provided with a threaded blind hole, the upper half part of the lower support column 202 is provided with an external thread, and the lower support column 202 is in threaded connection with the threaded sleeve 203. By rotating the lower support column 202, the height of the foot can be adjusted.
The slide block 207 is provided with two slide ways, the slide rail 201 is placed in the slide way of the slide block 207, the slide block 207 is provided with a threaded through hole which is communicated with the slide way, the threaded through hole of the slide block 207 is in threaded connection with the locking bolt 206, and the slide block 207 can be fixed on the slide rail 201 by rotating the locking bolt 206.
The laser measuring component 1 is fixedly connected with the sliding block 207, and the laser ranging sensor module 103 is perpendicular to the sliding rail 201.
As shown in fig. 5, the T-shaped target 3 includes a base 302 and a target 301, the target 301 is a T-shaped plate, and the lower end of the target 301 is fixedly connected to the base 302.
The operation flow is as follows: when the device is used, the rotary knob 102 can drive the worm 116 to rotate, the worm 116 drives the bidirectional screw rod 119 to rotate through the worm wheel 117, the bidirectional screw rod 119 drives the two guide blocks 120 to move oppositely in the rotating process, the guide blocks 120 drive the guide plates 114 to move, and the guide plates 114 drive the two laser emitters 115 to synchronously rotate through the guide pin shafts 121 and the connecting plate 122, so that the height of the central point of the cross-shaped laser beam emitted by the laser emitters 115 can be adjusted.
An aircraft ranging method comprising the steps of:
step 1, placing the laser ranging device of the airplane at the middle position of two rear wheels of the airplane, adjusting the angle of the laser emitter 115 by rotating the knob 102, so that the central point of a cross laser beam emitted by the laser emitter 115 is positioned at the position with the same height as the axle center points of the two rear wheels, and adjusting the position of the slide rail component 2, so that the central point of the cross laser beam emitted by the laser emitter 115 is positioned at the axle center points of the two rear wheels.
And 3, placing the T-shaped target 3 on the other side of the front wheel of the airplane, aligning a transverse plate of the T-shaped target 3 with the axis of the front wheel, loosening the locking bolt 206, adjusting the position of the laser measuring component 1 on the slide rail 201, aligning the laser ranging sensor module 103 on the laser measuring component 1 with the T-shaped target 3, adjusting the height of the support leg, keeping the laser measuring component 1 horizontal by observing the horizontal bubble 109, fixing the slide block 207 and the laser measuring component 1 on the slide rail 201 by screwing down the locking bolt 206, starting the laser ranging sensor module 103 to emit a measuring laser beam to irradiate on the T-shaped target 3, and recording the measured distance value B2.
And 4, calculating the average value of the measured values B1 and B2 at two sides, namely the distance B to be measured.
And 5, finding a weighing reference point in an airplane manual, hanging a plumb at the weighing reference point, placing the front surface of the T-shaped target 3 right below the plumb, moving the slide block 207 on the slide rail 201 to enable the laser ranging sensor module 103 of the laser measuring assembly 1 to be aligned with the T-shaped target 3, fixing the slide block 207 by using the locking bolt 206, pressing a measuring button, starting the laser ranging sensor module 103, enabling a measuring laser beam to shoot at the T-shaped target 3, and recording a measured distance value A.
It should be noted that while the invention has been described in detail with respect to specific embodiments thereof, it will be apparent to those skilled in the art that various obvious changes can be made therein without departing from the spirit and scope of the invention.
Claims (6)
1. An aircraft laser ranging device comprises a slide rail component (2); the sliding rail assembly (2) comprises a sliding rail (201), a sliding block (207), a transverse plate (205) and supporting legs, and two ends of the sliding rail (201) are respectively connected with the supporting legs through the transverse plate (205); the sliding rail (201) is arranged in a slideway of the sliding block (207), a threaded through hole which is communicated with the slideway is arranged on the sliding block (207), and the threaded through hole on the sliding block (207) is in threaded connection with the locking bolt (206); the method is characterized in that: the device also comprises a laser measuring component (1) and a T-shaped target (3); the laser measuring assembly (1) is connected with the sliding block (207), and the laser measuring assembly (1) comprises a laser ranging sensor module (103), a laser emitter (115), an outer shell (101), a bottom cover (110) and a fixed frame (111); the outer shell (101) is provided with a cavity with an opening at the lower end, the upper end of the outer shell (101) is provided with two symmetrically distributed elongated through holes, the bottom cover (110) is connected with the opening at the lower end of the outer shell (101), the upper end of the bottom cover (110) is connected with the fixed frame (111), the fixed frame (111) is fixedly connected with the upper connecting frame (113) and the lower connecting frame (112) from top to bottom in sequence, two sides of the upper connecting frame (113) are respectively provided with a slide way, the lower connecting frame (112) is rotatably connected with the worm (116), and one end of the knob (102) penetrates through the through hole in the outer wall of the outer shell (101) and is connected with one end of the worm (116); the fixed frame (111) is rotationally connected with a bidirectional screw rod (119), two sections of threads of the bidirectional screw rod (119) are respectively positioned in two slide ways of the upper connecting frame (113), the bidirectional screw rod (119) is fixedly matched with a central hole of a worm wheel (117), and the worm wheel (117) is meshed with the worm (116); the fixing frame (111) is respectively hinged with the two laser emitters (115), the inner ends of the laser emitters (115) are connected with the guide pin shaft (121) through a connecting plate (122), and the outer ends of the laser emitters are positioned at the position of the rectangular through hole of the outer shell (101); a guide block (120) provided with a threaded through hole is installed in the slide way of the upper connecting frame (113), a bidirectional screw rod (119) is in threaded fit with the threaded through hole of the guide block (120), the guide block (120) is connected with the guide plate (114), and a guide pin shaft (121) is placed in the elongated guide through hole of the guide plate (114); a laser ranging sensor module (103) and a lithium battery (105) are arranged in a cavity of the outer shell (101); the T-shaped target (3) comprises a base (302) and a target sheet (301), the target sheet (301) is of a T-shaped plate structure, and the lower end of the target sheet (301) is connected with the base (302).
2. An aircraft laser ranging device as defined in claim 1 wherein: the supporting legs comprise upper supporting columns (204) and lower supporting columns (202), the upper ends of the upper supporting columns (204) are connected with the transverse plate (205), the lower ends of the upper supporting columns are connected with the threaded sleeves (203), threaded blind holes are formed in the lower ends of the threaded sleeves (203), external threads are formed in the upper half portions of the lower supporting columns (202), and the lower supporting columns (202) are connected with the threaded sleeves (203) in a threaded mode.
3. An aircraft laser ranging device as defined in claim 1 wherein: the upper end of the fixing frame (111) is provided with two groups of ear plates (118), and each group of ear plates (118) is hinged with the middle position of the laser emitter (115) respectively.
4. An aircraft laser ranging device as defined in claim 1 wherein: the lower half part of the outer shell (101) is provided with a battery bin (104), and a lithium battery (105) is installed in the battery bin (104).
5. An aircraft laser ranging device as defined in claim 1 wherein: and horizontal bubbles (109) are respectively arranged on the upper end wall of the outer shell (101).
6. An aircraft ranging method using the apparatus of claim 5, comprising the steps of:
step 1, placing an aircraft laser ranging device in the middle of two rear wheels of an aircraft, adjusting the angle of a laser emitter (115) by rotating a knob (102), so that the center point of a cross laser beam emitted by the laser emitter (115) is located at the position with the same height as the axle center points of the two rear wheels, and adjusting the position of a sliding rail component (2) so that the center point of the cross laser beam emitted by the laser emitter (115) is located at the axle center point positions of the two rear wheels;
step 2, placing a T-shaped target (3) on one side of a front wheel of an airplane, aligning a transverse plate of the T-shaped target (3) with the center of the front wheel, adjusting the position of a laser measuring assembly (1) on a sliding rail (201), aligning a laser ranging sensor module (103) on the laser measuring assembly (1) with the T-shaped target (3), adjusting the height of a supporting leg, keeping the laser measuring assembly (1) horizontal by observing a horizontal bubble (109), fixing a sliding block (207) and the laser measuring assembly (1) on the sliding rail (201) by screwing a locking bolt (206), starting the laser ranging sensor module (103), emitting a measuring laser beam on the T-shaped target (3), and recording a measured distance value B1;
step 3, placing the T-shaped target (3) on the other side of the front wheel of the airplane, aligning a transverse plate of the T-shaped target (3) with the axis of the front wheel, loosening the locking bolt (206), adjusting the position of the laser measuring assembly (1) on the slide rail (201), aligning a laser ranging sensor module (103) on the laser measuring assembly (1) with the T-shaped target (3), adjusting the height of the support leg, keeping the laser measuring assembly (1) horizontal by observing a horizontal bubble (109), fixing the slide block (207) and the laser measuring assembly (1) on the slide rail (201) by screwing the locking bolt (206), starting the laser ranging sensor module (103) to emit a measuring laser beam to the T-shaped target (3), and recording a measured distance value B2;
step 4, calculating the average value of the measured values B1 and B2 at two sides, namely the distance B to be measured;
and 5, finding out a weighing reference point in an airplane manual, hanging a plumb at the weighing reference point, placing the front surface of the T-shaped target (3) right below the plumb, moving a sliding block (207) on a sliding rail (201), aligning a laser ranging sensor module (103) of the laser measuring assembly (1) with the T-shaped target (3), fixing the sliding block (207) by using a locking bolt (206), starting the laser ranging sensor module (103), enabling a measuring laser beam to shoot at the T-shaped target (3), and recording a measured distance value A.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010703974.1A CN111912339B (en) | 2020-07-21 | 2020-07-21 | Laser ranging device and method for airplane |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010703974.1A CN111912339B (en) | 2020-07-21 | 2020-07-21 | Laser ranging device and method for airplane |
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| CN111912339A CN111912339A (en) | 2020-11-10 |
| CN111912339B true CN111912339B (en) | 2022-02-18 |
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| CN112319842B (en) * | 2020-11-27 | 2022-07-15 | 日照山太飞机工程股份有限公司 | Aircraft elevator weight evaluation method |
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| US6802130B2 (en) * | 2002-09-30 | 2004-10-12 | Bridgestone/Firestone North American Tire, Llc | Alignment device for rotating tire laser mapping machine |
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