CN114563070B - Weighing and traversing method for airplane - Google Patents
Weighing and traversing method for airplane Download PDFInfo
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- CN114563070B CN114563070B CN202210218527.6A CN202210218527A CN114563070B CN 114563070 B CN114563070 B CN 114563070B CN 202210218527 A CN202210218527 A CN 202210218527A CN 114563070 B CN114563070 B CN 114563070B
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- 238000005303 weighing Methods 0.000 title claims abstract description 141
- 238000000034 method Methods 0.000 title claims abstract description 25
- 230000007246 mechanism Effects 0.000 claims abstract description 66
- 239000010720 hydraulic oil Substances 0.000 claims abstract description 26
- 230000005540 biological transmission Effects 0.000 claims description 29
- 239000003921 oil Substances 0.000 claims description 19
- 230000005484 gravity Effects 0.000 claims description 6
- 238000009434 installation Methods 0.000 claims description 5
- 230000009471 action Effects 0.000 claims description 3
- 230000008878 coupling Effects 0.000 claims description 2
- 238000010168 coupling process Methods 0.000 claims description 2
- 238000005859 coupling reaction Methods 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 230000008569 process Effects 0.000 description 8
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 206010034719 Personality change Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000003340 mental effect Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 230000008685 targeting Effects 0.000 description 1
Classifications
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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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01G—WEIGHING
- G01G21/00—Details of weighing apparatus
- G01G21/02—Arrangements of bearings
- G01G21/08—Bearing mountings or adjusting means therefor
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vehicle Cleaning, Maintenance, Repair, Refitting, And Outriggers (AREA)
Abstract
The invention discloses a weighing and traversing method for an aircraft, which relates to the technical field of aircraft production, and comprises the following steps that a weighing traversing mechanism is required to be moved to an aircraft stopping position; second sliding the device from the opening into the aircraft wheel; thirdly, lifting the aircraft wheel until the aircraft wheel is separated from the ground; fourthly, a manual control valve in the hydraulic oil system is adjusted to a 'hold' gear, and the aircraft is moved to a designated position to finish the sideslip work; fifthly, controlling a lifting mechanism in the weighing assembly to enable the weighing traversing mechanism to perform weighing work on the ground together with the aircraft; and after the weighing work is finished, the weighing and traversing mechanism is moved out in a reverse operation mode, and the whole weighing and traversing work is finished. The invention can conveniently complete the weighing and traversing work of the airplane by using the weighing and traversing device without other equipment, thereby not only damaging the airplane, but also rapidly completing the weighing and traversing work of the airplane.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a weighing and traversing method for an aircraft.
Background
The attitude adjustment process of the aircraft fuselage is an indispensable link in the production and use processes of the aircraft, and in the operations of assembly debugging, field overhaul, aircraft modification, zero calibration of airborne equipment and the like of the aircraft, the aircraft leveling operation is needed, for example, in the assembly process of the aircraft, the attitude adjustment of the aircraft at the aircraft position is needed by multiple stations such as component installation, size measurement and the like, so that the aircraft fuselage is leveled, and because of the need of training, the attitude adjustment operation of the aircraft is needed first before the scenes such as large-motor flight, engine overhaul, targeting training and regular overhaul are carried out, and the like, and the operation of the aircraft attitude adjustment of other application units or sites is also needed.
The traditional aircraft fuselage attitude adjustment process is realized by observing the height information of a fuselage datum point through a level gauge and manually adjusting the attitude by utilizing three hydraulic jacks, in the actual attitude adjustment process, the oil leakage phenomenon of the hydraulic jacks is very common, so that an aircraft berthing site is difficult to clean, the hydraulic jacks often have the damage to-be-repaired conditions such as explosion cylinders and pressure deficiency, the normal assembly work is seriously influenced, the situation of slow pressure release exists in a hydraulic system, the situation that the aircraft attitude changes due to the descending of the height of the jacks after the completion of the aircraft attitude adjustment finally results in the attitude adjustment failure, the aircraft leveling work needs to be carried out for a long time all the year, each aircraft needs to be leveled and overhauled at least 1-3 times, but the attitude adjustment mode needs 60 minutes or more for skilled operators, even more than 90 minutes for the operation unskilled operators, the logistic guarantee efficiency is seriously influenced, and the weight under various inclined attitudes need to be measured and the gravity center offset need to be calculated when the aircraft is subjected to the occasion such as the aircraft refitting and the component overhauling, the whole process is very difficult to calculate the manual operation, and the whole operation is very difficult to be operated.
The publication number is CN211871258U, and the publication day is 20201106's chinese patent discloses an automatic jacking gesture device of aircraft, including the fuselage, locate the aircraft nose of fuselage front end and locate the wing of fuselage middle part left and right sides, be equipped with the front wheel under the aircraft nose, fuselage rear portion left and right sides is equipped with the back wheel that is mutual symmetry, its characterized in that: a laser leveling instrument is arranged on the right side of the machine body; a front receiver is arranged on the side wall of the right side of the machine head; the side walls of the left side and the right side of the middle part of the machine body are provided with a middle receiver adjacent to the wing; a rear receiver is arranged on the right side wall of the rear part of the machine body; the front receiver, the middle receiver and the rear receiver can all receive the laser beams of the laser scanner; a comprehensive control mechanism is arranged at the right front of the machine body; the left side and the right side of the machine head right below the machine body middle part are respectively provided with a servo jacking mechanism, and the servo jacking mechanisms can receive information fed back by the comprehensive control mechanism; the servo jacking mechanism is arranged right below the machine head and is provided with a front jacking device; the left top device is positioned at the left side below the middle part of the machine body, and the right top device is positioned at the right side below the middle part of the machine body; the left top device is connected with the right top device through a fine adjustment plate, and the fine adjustment plate is attached to the lower surface of the machine body. However, in the using process of the device, the servo jacking mechanism is directly contacted with the fuselage and the wings to cause damage easily, the device needs to be carried to the aircraft during use, the labor intensity is increased, the aircraft not only needs to be in the attitude adjustment process, but also needs to be moved, and the device also lacks a moving function. An airplane weighing and traversing method which is convenient and quick is lacking.
Disclosure of Invention
In order to solve the technical problems, the invention provides a weighing and traversing method for an airplane, which comprises the steps that a weighing traversing mechanism is required to be moved to a stop position of the airplane; second, sliding the equipment (weighing and traversing mechanism) from the opening into the airplane wheel; thirdly, lifting the aircraft wheel until the aircraft wheel is separated from the ground; fourthly, a manual control valve in the hydraulic oil system is adjusted to a 'hold' gear, and the aircraft is moved to a designated position to finish the sideslip work; fifthly, controlling a lifting mechanism in the weighing assembly to enable the weighing traversing mechanism and the airplane to be separated from the ground together for weighing; and after the weighing work is finished, the weighing and traversing mechanism is moved out in a reverse operation mode, and the whole weighing and traversing work is finished. The invention can conveniently complete the weighing and traversing work of the airplane by using the weighing and traversing device without other equipment, thereby not only damaging the airplane, but also rapidly completing the weighing and traversing work of the airplane.
The invention aims at realizing the following technical scheme:
The weighing and traversing method for the airplane is characterized by comprising the following steps of:
step one, moving three weighing and transversely moving mechanisms to the vicinity of a front wheel and a rear wheel of an airplane, and sliding the three weighing and transversely moving mechanisms into the positions of the wheels of the airplane from an opening;
step two, adjusting a manual reversing valve in the hydraulic oil system to a weighing traversing gear;
Operating a manual pump in the hydraulic oil system, and enabling the oil cylinder to act until the aircraft wheel is separated from the ground;
Step four, inserting a safety plug pin, and pulling a manual reversing valve in the hydraulic oil system to a 'hold' gear;
fifthly, moving the airplane to a designated position through three weighing and traversing mechanisms to finish traversing work;
Step six, when the aircraft moves to the appointed position, the lifting mechanism in the weighing assembly is controlled by the control cabinet, so that the weighing traversing mechanism and the aircraft are separated from the ground together;
Starting a weighing assembly, enabling a weighing sensor to start working, transmitting data to a control cabinet by the weighing sensor, and displaying all data on the control cabinet after the control cabinet is calculated;
and step eight, after weighing is completed, reversely operating the moving-out weighing and traversing mechanism to complete the whole traversing and weighing work.
Preferably, in the third step, the oil cylinders at two ends of the opening simultaneously extend inwards under the combined action of the manual pump and the manual reversing valve, so that the lifting support, the supporting piece and the sliding block are driven to extend inwards along the sliding rail, and the aircraft wheel is separated from the ground.
Preferably, in the sixth step, the servo motor is started through the control cabinet, and the servo motor drives the transmission belt and the transmission wheel to rotate, so that the transmission shaft rotates to drive the worm wheel screw rod lifter to extend downwards until the support plate at the lower end of the worm wheel screw rod lifter contacts with the ground and the universal wheels on the base leave the ground.
Preferably, in the seventh step, the respective data includes data of a single load cell, resultant force of the weight traversing mechanism and total weight of the aircraft.
Preferably, in the seventh step, the center of gravity calculation is further included.
Preferably, in the eighth step, the control cabinet controls the lifting mechanism in the weighing assembly to enable the universal wheels on the base to be in contact with the ground; then the safety plug pin is pulled out, and a manual reversing valve in the hydraulic oil system is pulled to a zero position gear; operating a manual pump in the hydraulic oil system, and enabling the oil cylinder to act until the aircraft wheel is contacted with the ground; and then the weighing and traversing mechanism slides out of the airplane wheel by utilizing the opening, so that the weighing and traversing mechanism is separated from the airplane wheel.
The utility model provides a sideslip device of weighing for aircraft, includes weighing sideslip mechanism and switch board of setting at aircraft front wheel and aircraft rear wheel, weighing sideslip mechanism includes the base, base lower extreme four corners department is provided with the universal wheel, base one end is provided with the opening that is used for the roll-in or roll-out aircraft wheel, the opening both sides all are provided with the subassembly of lifting that is used for the aircraft wheel to lift, still be provided with the subassembly of weighing that is used for the aircraft to weigh on the base, the switch board links to each other with the subassembly of lifting and the subassembly of weighing.
Preferably, the lifting assembly comprises a lifting support, a supporting piece for supporting the aircraft wheel is arranged on the lifting support, sliding blocks are arranged on the left side and the right side of the lifting support, the sliding blocks are in sliding connection with the sliding rails, the sliding rails are fixedly arranged on the base, the lifting support is connected with the movable end of the telescopic piece, the fixed end of the telescopic piece is connected with the base, and the telescopic piece enables the lifting support to move along the horizontal direction of the sliding rails; the supporting piece adopts a roller, and the roller is rotationally connected with the lifting bracket; the telescopic piece adopts an oil cylinder.
Preferably, the weighing assembly comprises supporting seats arranged at two ends of the base, and the two ends of the supporting seats are respectively provided with a weighing sensor and a lifting mechanism; the supporting seat is also provided with an adjustable support; the lifting mechanism adopts a worm wheel screw rod lifter, the worm wheel screw rod lifter is connected with a transmission shaft, and the transmission shaft is connected with the supporting seat through a coupler; the transmission shaft is provided with a transmission wheel which is connected with the power piece through a transmission belt; lifting appliance interfaces are arranged at four corners of the upper end of the base.
The beneficial effects of this technical scheme are as follows:
The invention provides a weighing and traversing method for an airplane, which comprises the steps that firstly, a weighing traversing mechanism is required to be moved to a stop position of the airplane; second, sliding the equipment (weighing and traversing mechanism) from the opening into the airplane wheel; thirdly, lifting the aircraft wheel until the aircraft wheel is separated from the ground; fourthly, adjusting a manual reversing valve in the hydraulic oil system to a 'hold' gear, and moving the aircraft to a designated position to finish the sideslip work; fifthly, controlling a lifting mechanism in the weighing assembly to enable the weighing traversing mechanism and the airplane to be separated from the ground together for weighing; and after the weighing work is finished, the weighing and traversing mechanism is moved out in a reverse operation mode, and the whole weighing and traversing work is finished. The invention can conveniently complete the weighing and traversing work of the airplane by using the weighing and traversing device without other equipment, thereby not only damaging the airplane, but also rapidly completing the weighing and traversing work of the airplane.
Drawings
The invention will be described in further detail with reference to the drawings and detailed description, wherein:
FIG. 1 is a schematic view of the structure of the initial state of the present invention;
FIG. 2 is a schematic view of the structure of the support of the present invention in a condition of just contacting an aircraft wheel;
FIG. 3 is a schematic view of the structure of the aircraft wheel of the present invention in a ground-off state;
FIG. 4 is a schematic view of the structure of the weighing assembly of the present invention in a state of just contacting the ground;
FIG. 5 is a schematic view of the structure of the device for weighing and traversing of the present invention in a ground-off state with respect to an aircraft;
FIG. 6 is a schematic view of a traversing device for weighing in the present invention;
FIG. 7 is a schematic view of the structure of the weighing and traversing mechanism of the present invention;
FIG. 8 is a schematic view of a base structure according to the present invention;
FIG. 9 is a schematic view of a lifting assembly according to the present invention;
FIG. 10 is a schematic view of a weighing assembly according to the present invention;
FIG. 11 is a schematic diagram of the operation of the hydraulic control system of the present invention;
The marks in the figure: 1. a weighing and traversing mechanism; 1.1, a base; 1.2, universal wheels; 1.3, opening; 1.4, lifting the assembly; 1.41, lifting a bracket; 1.42, support; 1.43, slider; 1.44, sliding rail; 1.45, telescoping pieces; 1.5, a weighing assembly; 1.51, a supporting seat; 1.52, a weighing sensor; 1.53, lifting mechanism; 1.54, an adjustable support; 1.55, a transmission shaft; 1.56, a coupler; 1.57, a driving wheel; 1.58, a driving belt; 1.59, a power piece; 1.6, a lifting appliance interface; 1.7, a safety latch; 2. a control cabinet; 3.1, a hydraulic oil tank; 3.2, a manual pump; 3.3, a filter element; 3.4, a manual reversing valve; 3.5, a throttle valve; 3.6, the throttle valve is attached with a check valve; 3.7, a one-way valve; 3.8, an air filter; 3.9, a pressure gauge; 3.10, an overflow valve; 100. an aircraft.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present invention and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
As shown in fig. 1 to 5, a method for weighing and traversing an aircraft is characterized by comprising the following steps:
Step one, three weighing and transversely moving mechanisms 1 are moved to the vicinity of the front wheels of the aircraft 100 and the rear wheels of the aircraft 100, and the aircraft wheels (the aircraft wheels comprise the front wheels of the aircraft 100 and the rear wheels of the aircraft 100) are slid in from an opening 1.3;
Step two, adjusting a manual reversing valve 3.4 in the hydraulic oil system to a weighing traversing gear;
operating a manual pump 3.2 in the hydraulic oil system, and enabling the oil cylinder to act until the aircraft wheels (the aircraft wheels comprise front wheels of the aircraft 100 and rear wheels of the aircraft 100) are separated from the ground;
Step four, inserting a safety plug pin 1.7, and pulling a manual reversing valve 3.4 in the hydraulic oil system to a 'hold' gear;
Fifthly, moving the aircraft 100 to a designated position through three weighing and traversing mechanisms 1 to finish traversing work;
step six, when the aircraft 100 moves to the designated position, the lifting mechanism 1.53 in the weighing assembly 1.5 is controlled by the control cabinet 2 so that the weighing traversing mechanism 1 and the aircraft 100 are separated from the ground together;
Step seven, starting the weighing assembly 1.5, starting the weighing sensor 1.52 to work, transmitting data to the control cabinet 2 by the weighing sensor 1.52, and displaying each data on the control cabinet 2 after the control cabinet 2 calculates;
and step eight, after weighing is completed, reversely operating the moving-out weighing and traversing mechanism 1 to complete the whole traversing and weighing work.
In the third step, the oil cylinders at the two ends of the opening 1.3 are simultaneously extended inwards under the combined action of the manual pump 3.2 and the manual reversing valve 3.4, so that the lifting support 1.41, the support piece 1.42 and the sliding block 1.43 are driven to extend inwards along the sliding rail 1.44, and the aircraft 100 wheels are separated from the ground.
In the sixth step, the servo motor is started through the control cabinet 2, and drives the transmission belt 1.58 and the transmission wheel 1.57 to rotate, so that the transmission shaft 1.55 rotates to drive the worm wheel screw rod lifter to extend downwards until the support plate at the lower end of the worm wheel screw rod lifter contacts with the ground and the universal wheel 1.2 on the base 1.1 leaves the ground.
In the seventh step, the data include data of a single weighing sensor 1.52, a resultant force of the weighing and traversing mechanisms 1, and a total weight of the aircraft 100, where the resultant force of the weighing and traversing mechanisms 1 is a sum of data of three weighing sensors 1.52 on the single weighing and traversing weighing mechanism, and the total weight of the aircraft 100 is a sum of the weighing and traversing mechanisms 1 at two positions of the front wheel of the aircraft 100 and the rear wheel of the aircraft 100.
In the seventh step, the method further includes center of gravity calculation. The conditions are known: 100 front wheel station of airplane) 100 Left rear wheel station of airplane) Right rear wheel of aircraft 100) ; The weight at each wheel was measured by weighing: weight of front wheel of aircraft 100 ) Weight of aircraft 100 left rear wheel ) Weight of airplane 100 right rear wheel) ; By the gravity center calculation formula: ； obtaining the position of the center of gravity of the aircraft 100 ）。
In the eighth step, the control cabinet 2 controls the lifting mechanism 1.53 in the weighing assembly 1.5 to enable the universal wheels 1.2 on the base 1.1 to be in contact with the ground; then the safety bolt 1.7 is pulled out, and a manual reversing valve 3.4 in the hydraulic oil system is pulled to a zero position gear; operating a manual pump 3.2 in the hydraulic oil system, and enabling the oil cylinder to act until the aircraft wheel is contacted with the ground; the weighing and traversing mechanism 1 is then slid out of the wheel by means of the opening 1.3, and the work of disengaging the wheel is completed.
As shown in fig. 6-10, a weighing and traversing device for an aircraft 100 comprises a weighing and traversing mechanism 1 and a control cabinet 2, wherein the weighing and traversing mechanism 1 and the control cabinet 2 are arranged on a front wheel of the aircraft 100 and a rear wheel of the aircraft 100, the weighing and traversing mechanism 1 is identical in structure and the only difference in size at the front wheel of the aircraft 100 and the rear wheel of the aircraft 100, the weighing and traversing mechanism 1 comprises a base 1.1, the base 1.1 is an aluminum alloy base 1.1, universal wheels 1.2 are arranged at four corners at the lower end of the base 1.1, one end of the base 1.1 is provided with an opening 1.3 for sliding in or out of the aircraft wheels, lifting assemblies 1.4 for lifting the aircraft wheels are arranged on two sides of the opening 1.3, a weighing assembly 1.5 for weighing the aircraft 100 is further arranged on the base 1.1, and the control cabinet 2 is connected with the lifting assemblies 1.4 and the weighing assemblies 1.5.
The lifting assembly 1.4 comprises a lifting support 1.41, a support piece 1.42 for supporting an aircraft 100 wheel is arranged on the lifting support 1.41, sliding blocks 1.43 are arranged on the left side and the right side of the lifting support 1.41, the sliding blocks 1.43 are in sliding connection with sliding rails 1.44, the sliding rails 1.44 are fixedly arranged on a base 1.1, the lifting support 1.41 is connected with the movable end of a telescopic piece 1.45, the fixed end of the telescopic piece 1.45 is connected with the base 1.1, the telescopic piece 1.45 enables the lifting support 1.41 to move along the sliding rails 1.44 in the horizontal direction, a safety bolt fixing hole for plugging a safety bolt 1.7 is formed in the base 1.1, and a second fixing hole corresponding to the safety bolt fixing hole is formed in the lifting support 1.41.
Wherein, the support piece 1.42 adopts the gyro wheel, the gyro wheel is rotated with lifting support 1.41 and is connected.
As shown in FIG. 11, the telescopic part 1.45 adopts an oil cylinder, the base 1.1 is also provided with a hydraulic system installation cavity, the hydraulic system installation cavity is internally provided with a hydraulic oil system, the hydraulic oil system comprises a hydraulic oil tank 3.1, a manual pump 3.2, a filter element 3.3, a manual reversing valve 3.4, a throttle valve 3.5, a throttle valve attached check valve 3.6 and a one-way valve 3.7, the hydraulic oil tank 3.1 is connected with the filter element 3.3 through a pipeline, the other end of the filter element 3.3 is connected with the suction end of the manual pump 3.2, the output end of the manual pump 3.2 is connected with one end of the one-way valve 3.7, the other end of the one-way valve 3.7 is connected with the manual reversing valve 3.4 through an oil pipe and the filter element 3.3, the one-way valve 3.7 is also connected with the hydraulic oil tank 3.1 through a return pipe and an overflow valve 3.10, the rear end of the manual reversing valve 3.4 is connected with a throttle auxiliary check valve 3.6, the rear end of the throttle auxiliary check valve 3.6 is connected with an oil cylinder, a pressure gauge 3.9 is further arranged between the manual reversing valve 3.4 and the throttle auxiliary check valve 3.6, the one-way valve 3.7 is arranged on a bypass of the throttle auxiliary check valve 3.6, the manual reversing valve 3.4 is connected with the hydraulic oil tank 3.1 through an oil return pipe and a throttle valve 3.5, and three gears including a weighing and traversing gear, a zero position gear and a holding gear are arranged on the manual reversing valve 3.4; an air filter 3.8 is further arranged on the hydraulic oil tank 3.1. When the automatic weighing and traversing device is used, after the manual pump 3.2 is started, the manual reversing valve 3.4 is switched to a weighing and traversing gear, so that the oil cylinder is contracted inwards, the oil cylinder drives the lifting support 1.41, the support piece 1.42 and the sliding block 1.43 to extend inwards along the sliding rail 1.44, the aircraft wheel is lifted upwards, and the damage to the aircraft wheel is reduced by adopting the roller type support piece 1.42.
The weighing assembly 1.5 comprises supporting seats 1.51 arranged at two ends of a base 1.1, the supporting seats 1.51 are connected with the base 1.1 through hinges, weighing sensors 1.52 and lifting mechanisms 1.53 are arranged at two ends of the supporting seats 1.51, and the weighing sensors 1.52 are cantilever type weighing sensors 1.52.
The adjustable support 1.54 is arranged on the support seat 1.51, the stress end of the cantilever type weighing sensor 1.52 is located at the upper end of the adjustable support 1.54, the fixed end of the cantilever type weighing sensor 1.52 is fixedly connected with the upper end of the base 1.1, and the cantilever type weighing sensor 1.52 is further connected with the control cabinet 2.
The lifting mechanism 1.53 adopts a worm gear screw lifter, the worm gear screw lifter is connected with the transmission shaft 1.55, the transmission shaft 1.55 is connected with the supporting seat 1.51 through the coupling 1.56, and the lower end of the worm gear screw lifter is provided with a supporting plate.
Wherein, be provided with manual lift interface on the worm wheel lead screw lift. The manual lifting interface can meet the requirements of emergency lifting and manual fine adjustment, and is convenient to operate.
The transmission shaft 1.55 is provided with a transmission wheel 1.57, the transmission wheel 1.57 is connected with a power piece through a transmission belt 1.58, the transmission belt 1.58 adopts a synchronous belt, and the transmission piece 1.59 adopts a servo motor. The servo motor is arranged in a motor accommodating cavity on the base 1.1. During weighing, the servo motor is started through the control cabinet 2, the servo motor drives the transmission shaft 1.55 to rotate through the transmission belt 1.58 and the transmission wheel 1.57, the transmission shaft 1.55 rotates to drive the worm wheel screw rod lifter to extend downwards until the support plate at the lower end of the worm wheel screw rod lifter contacts with the ground and the universal wheel 1.2 on the base 1.1 leaves the ground, then the weighing assembly 1.5 is started, and the cantilever type weighing sensor 1.52 starts to work. The arrangement of the servo motor, the driving belt 1.58 and the driving shaft 1.55 enables the four lifting mechanisms 1.53 on the weighing assembly 1.5 to integrally and synchronously lift, and the worm wheel screw lifter can also realize reliable self-locking.
Wherein lifting appliance interfaces 1.6 are arranged at four corners of the upper end of the base 1.1.
In view of the foregoing, it will be appreciated by those skilled in the art that, after reading the present specification, various other modifications can be made in accordance with the technical scheme and concepts of the present invention without the need for creative mental efforts, and the modifications are within the scope of the present invention.
Claims (4)
1. A weighing and traversing method for an aircraft is characterized in that: the method is realized by using a weighing and traversing device for an airplane, the device comprises a weighing and traversing mechanism and a control cabinet, the weighing and traversing mechanism comprises a base, universal wheels are arranged at four corners of the lower end of the base, and one end of the base is provided with an opening for sliding in or out of the airplane wheels; the base is also provided with a weighing assembly and a hydraulic system installation cavity for weighing the aircraft, and the control cabinet is connected with the lifting assembly and the weighing assembly;
The lifting assembly comprises a lifting support, a supporting piece for supporting an airplane wheel is arranged on the lifting support, sliding blocks are arranged on the left side and the right side of the lifting support, the sliding blocks are in sliding connection with a sliding rail, the sliding rail is fixedly arranged on a base, the lifting support is connected with a movable end of an oil cylinder, a fixed end of the oil cylinder is connected with the base, the oil cylinder enables the lifting support to move along the horizontal direction of the sliding rail, a safety bolt fixing hole for inserting and pulling a safety bolt is formed in the base, and a second fixing hole corresponding to the safety bolt fixing hole is formed in the lifting support;
The hydraulic system is arranged in the hydraulic system installation cavity, the hydraulic system comprises a manual pump and a manual reversing valve, and three gears are arranged on the manual reversing valve, wherein the three gears comprise a weighing traversing gear, a zero position gear and a holding gear;
The weighing assembly comprises supporting seats arranged at two ends of a base, the supporting seats are connected with the base through hinges, weighing sensors and lifting mechanisms are arranged at two ends of the supporting seats, the weighing sensors are further connected with a control cabinet, the lifting mechanisms adopt worm wheel screw rod lifters, the worm wheel screw rod lifters are connected with transmission shafts, the transmission shafts are connected with the supporting seats through couplings, and supporting plates are arranged at the lower ends of the worm wheel screw rod lifters;
the method specifically comprises the following steps:
Step one, moving three weighing and transversely moving mechanisms to the vicinity of a front wheel and a rear wheel of an airplane, and sliding the airplane wheels in from an opening;
step two, adjusting a manual reversing valve in the hydraulic oil system to a weighing traversing gear;
Operating a manual pump in the hydraulic oil system, and enabling oil cylinders at two ends of an opening to extend inwards under the combined action of the manual pump and a manual reversing valve, so that a lifting support, a supporting piece and a sliding block are driven to extend inwards along a sliding rail, and an airplane wheel is separated from the ground;
Step four, inserting a safety plug pin, and pulling a manual reversing valve in the hydraulic oil system to a 'hold' gear;
fifthly, moving the airplane to a designated position through three weighing and traversing mechanisms to finish traversing work;
step six, after the aircraft moves to the appointed position, starting a servo motor through a control cabinet, and enabling the servo motor to drive a transmission belt and a transmission wheel to rotate, so that the transmission shaft rotates to drive a worm wheel screw rod lifter to extend downwards until a support plate at the lower end of the worm wheel screw rod lifter contacts with the ground and universal wheels on a base leave the ground;
Starting a weighing assembly, enabling a weighing sensor to start working, transmitting data to a control cabinet by the weighing sensor, and displaying all data on the control cabinet after the control cabinet is calculated;
and step eight, after weighing is completed, reversely operating the moving-out weighing and traversing mechanism to complete the whole traversing and weighing work.
2. The method of weighing and traversing an aircraft according to claim 1, wherein: the total weight of the aircraft is the sum of the weighing and traversing mechanisms of the front wheel and the rear wheel of the aircraft.
3. The method of weighing and traversing an aircraft according to claim 2, wherein: in the seventh step, the method further comprises center of gravity calculation.
4. A method of weighing and traversing an aircraft as claimed in claim 3, wherein: the control cabinet controls the lifting mechanism in the weighing assembly to enable the universal wheels on the base to be in contact with the ground; then the safety plug pin is pulled out, and a manual reversing valve in the hydraulic oil system is pulled to a zero position gear; operating a manual pump in the hydraulic oil system, and enabling the oil cylinder to act until the aircraft wheel is contacted with the ground; and then the weighing and traversing mechanism slides out of the airplane wheel by utilizing the opening, so that the weighing and traversing mechanism is separated from the airplane wheel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210218527.6A CN114563070B (en) | 2022-03-08 | 2022-03-08 | Weighing and traversing method for airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105444855A (en) * | 2015-11-28 | 2016-03-30 | 沈阳飞机工业（集团）有限公司 | Airplane weight gravity center measurement and adjustment device |
| CN113247293A (en) * | 2021-06-28 | 2021-08-13 | 中国船舶重工集团公司第七一三研究所 | Rodless aircraft tractor of side direction centre gripping |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN204064422U (en) * | 2014-10-21 | 2014-12-31 | 宁波星箭航天机械有限公司 | Weighing machine for aircraft |
| FR3052255B1 (en) * | 2016-06-03 | 2018-07-27 | Airbus | WEIGHING DEVICE AND SYSTEM FOR DETERMINING THE MASS AND CENTER OF GRAVITY OF AN AIRCRAFT |
| CN109443641A (en) * | 2018-12-29 | 2019-03-08 | 中航电测仪器股份有限公司 | A kind of system and method for fast tuning aircraft level |
| CN112146738B (en) * | 2019-06-28 | 2024-04-05 | 西安京东天鸿科技有限公司 | Aircraft weighing method and system |
| US20210114851A1 (en) * | 2019-10-22 | 2021-04-22 | Ken Lock | Aircraft jack and system |
| CN112304408B (en) * | 2020-11-24 | 2022-09-16 | 贵州航天特种车有限责任公司 | Automatic measurement device for weight and gravity center of multi-model airplane |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105444855A (en) * | 2015-11-28 | 2016-03-30 | 沈阳飞机工业（集团）有限公司 | Airplane weight gravity center measurement and adjustment device |
| CN113247293A (en) * | 2021-06-28 | 2021-08-13 | 中国船舶重工集团公司第七一三研究所 | Rodless aircraft tractor of side direction centre gripping |
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