An automatic lifting and attitude adjustment device for aircraft

Abstract

An automatic lifting and attitude adjustment device for an aircraft comprises a fuselage, a nose arranged at the front end of the fuselage, and wings arranged at the left and right sides of the middle part of the fuselage, a front wheel is arranged just below the nose, and symmetrical rear wheels are arranged on the left and right sides of the rear part of the fuselage, a laser leveler is arranged on the right side of the fuselage; a front receiver is arranged on the right side wall of the nose; a middle receiver adjacent to the wing is arranged on the left and right side walls of the middle part of the fuselage; a rear receiver is arranged on the right side wall of the rear part of the fuselage; the front receiver, the middle receiver and the rear receiver can all receive the laser beam of the laser leveler. The automatic lifting and attitude adjustment device for an aircraft of the present invention can not only reduce the manpower required in the process of aircraft attitude adjustment to the greatest extent, but also obtain accurate data results after the attitude adjustment is completed, effectively ensure the quality of attitude adjustment, and effectively avoid the situation where attitude adjustment fails due to the instability of the jack hydraulic system.

Description

Technical Field

[0001] The invention relates to an automatic lifting and attitude adjusting device for an aircraft. Background Art

[0002] The aircraft fuselage attitude adjustment process is an indispensable part of the aircraft production and use process. Aircraft leveling work is required in aircraft assembly and commissioning, field maintenance, aircraft modification, and zero-position calibration of airborne equipment. For example, in the aircraft assembly process, multiple processes and multiple workstations involving component installation and dimension measurement all require the aircraft at that position to be attitude adjusted so as to level the aircraft fuselage. Due to some training needs, the aircraft must be attitude adjusted before large maneuver flights, engine maintenance, target shooting training, regular maintenance, and other scenarios. At the same time, other application units or sites also require aircraft attitude adjustment.

[0003] The traditional aircraft fuselage attitude adjustment process is to observe the fuselage reference point height information through a level and use three hydraulic jacks to manually adjust the attitude. In the actual attitude adjustment process, oil leakage of the hydraulic jack is very common, which makes it difficult to clean the aircraft parking site, and the hydraulic jacks often have cylinder explosions, pressure loss and other damages to be repaired, which seriously affects the normal assembly work. Due to the slow pressure relief of the hydraulic system, the aircraft attitude will change due to the decrease in the jack height after the aircraft attitude adjustment is completed, which eventually leads to the failure of the attitude adjustment. The aircraft leveling work needs to be carried out all year round. Each aircraft needs to be leveled and inspected at least 1-3 times a year. However, this attitude adjustment method takes about 60 minutes even for skilled operators, and even more than 90 minutes for unskilled operators, which seriously affects the efficiency of logistics support. In addition, if the aircraft is modified, parts are repaired and replaced, and weighing is required, the weight of the aircraft in various tilted attitudes needs to be measured and the center of gravity offset needs to be calculated. The whole process is manual operation, which is difficult to operate and complex to calculate, and the efficiency is extremely low.

[0004] In the traditional aircraft attitude adjustment process, surveyors are required to perform manual measurements with a ruler, and then observers stand at the observation position to perform visual observations with a level. The staff operating the jack operates the jack and changes the horizontal angle of the aircraft based on the information of the observer's violation. The entire attitude adjustment process not only involves a large amount of manpower, but also the accuracy of the data results obtained through manual operation is limited, and it is impossible to obtain accurate measurement results, making it difficult to ensure the quality of the aircraft's attitude adjustment. Summary of the invention

[0005] The present invention aims to solve the existing technical problem by providing an automatic lifting and attitude adjustment device for an aircraft, which can not only reduce the manpower required in the aircraft attitude adjustment process to the greatest extent, but also obtain accurate data results after the attitude adjustment is completed, effectively ensure the attitude adjustment quality, and effectively avoid the attitude adjustment failure caused by the instability of the jack hydraulic system.

[0006] The technical solution adopted by the present invention to solve the above technical problems is:

[0007] The invention discloses an automatic lifting and attitude adjustment device for an aircraft, comprising a fuselage, a nose arranged at the front end of the fuselage, and wings arranged at the left and right sides of the middle part of the fuselage, a front wheel is arranged just below the nose, and rear wheels symmetrical to each other are arranged at the left and right sides of the rear part of the fuselage, and the device is characterized in that: a laser leveling instrument is arranged on the right side of the fuselage; a front receiver is arranged on the right side wall of the nose; a middle receiver adjacent to the wing is arranged on the left and right side walls of the middle part of the fuselage; a rear receiver is arranged on the right side wall of the rear part of the fuselage; the front receiver, the middle receiver and The rear receivers can all receive the laser beam of the laser leveler; an integrated control mechanism is provided at the right front of the fuselage; servo lifting mechanisms are provided on both sides of the left and right sides directly below the nose and directly below the middle of the fuselage, and the servo lifting mechanisms can receive information fed back by the integrated control mechanism; the servo lifting mechanism located directly below the nose is provided with a front lifting device; the left lifting device is located on the left side of the lower middle of the fuselage, and the right lifting device is located on the right side of the lower middle of the fuselage; the left lifting device and the right lifting device are connected through a fine-tuning plate, and the fine-tuning plate fits against the lower surface of the fuselage.

[0008] The servo lifting mechanism includes a lifting bracket plate; a laser leveler bracket seat is provided at the lower end of the laser leveler; a plurality of extension plates evenly distributed in a circumference are provided on the outer peripheral surfaces of the lifting bracket plate and the leveler bracket seat; a displacement fastening device is provided at the end of the extension plate; a driving box is provided on the lower surface of the lifting bracket plate; a servo motor is provided on the upper surface of one side of the lifting bracket plate; a first through hole coaxial with the motor shaft of the servo motor is provided on the lifting bracket plate, and the first through hole is connected with the interior of the driving box; the lower end of the motor shaft of the servo motor passes downward through the first through hole and is provided with a first transmission wheel; a lifting cylinder is provided on the central upper surface of the lifting bracket plate; a A movable hole; a screw rod is provided in the lifting cylinder; a second through hole coaxial with the screw rod is provided on the lifting bracket plate; a rotating shaft is provided at the center of the lower surface of the screw rod; the lower end of the rotating shaft passes through the second through hole and is provided with a second transmission wheel located in the driving box; the second transmission wheel is connected to the first transmission wheel by a conveyor belt; a lifting sleeve meshing with the screw rod is provided outside the screw rod; symmetrical lifting grooves are provided on the inner walls on the left and right sides of the lifting cylinder; limit blocks matching the lifting grooves are provided on the left and right sides of the lifting sleeve; a plurality of support rods evenly distributed in a circle are provided on the upper surface of the lifting sleeve; the upper ends of the support rods pass through the movable hole upward, and the upper ends of the support rods are connected by a lifting plate located directly above the screw rod.

[0009] The front jacking device includes a front jacking rod arranged at the center of the upper surface of the jacking plate, and a jacking head is provided on the upper end of the front jacking rod; the left jacking device includes a left jacking rod arranged at the center of the upper surface of the jacking plate; the right jacking device includes a right jacking rod arranged at the center of the upper surface of the jacking plate; the upper ends of the left jacking rod and the right jacking rod are connected through a fine-tuning plate; the fine-tuning plate is U-shaped, and the fine-tuning plate itself forms an upper jacking groove, and the groove wall of the upper jacking groove is in contact with the outer wall of the fuselage; an embedding hole is provided on both sides of the jacking head and the bottom of the upper jacking groove; a laser locator and a weighing sensor matching them are provided in the embedding hole; a distance measuring sensor is provided on the lower surface of the jacking bracket plate.

[0010] A measuring electric cylinder is provided on the upper surface of the leveling instrument bracket; the displacement fastening device includes a hinged plate arranged at the upper end of the lifting cylinder and the upper end of the measuring electric cylinder; a plurality of hinged rods evenly distributed in a circle are hinged on the outer edge of the hinged plate; a fastening plate is hinged on the end of the extension plate; the lower end of the hinged rod is hinged to the fastening plate; a lifting hole is provided on the extension plate; a pulley seat is provided in the lifting hole, and the outer wall of the pulley seat does not contact the inner wall of the lifting hole; the upper end of the pulley seat is fixed to the hinged rod through a connecting plate; a pulley is provided on the lower surface of the pulley seat; a fastening screw hole is provided on the fastening plate; a screw is screwed in the fastening screw hole; the upper end of the screw passes upward to the outside of the fastening screw hole and is provided with a handwheel; the lower end of the screw passes downward to the outside of the fastening screw hole and is provided with an anti-slip foot pad.

[0011] The anti-slip foot pad is made of rubber.

[0012] The integrated control mechanism comprises a moving seat, and moving wheels are arranged at the four corners of the lower surface of the moving seat; an integrated control box is arranged above the moving seat; an integrated display console is arranged on the upper surface of the integrated control box; a heavy-load connector is arranged inside the integrated control box; the heavy-load connector is connected to the servo lifting mechanism and the laser leveler through a plurality of power lines and a plurality of signal lines.

[0013] The movable seat is provided with a take-up device for winding up the power line and the signal line; the take-up device includes a take-up frame arranged on the movable seat; the take-up frame is provided with a plurality of fixed shafts evenly distributed longitudinally; the fixed shaft is provided with a plurality of take-up wheels evenly distributed transversely, and the take-up wheels can rotate around the fixed shaft.

[0014] The integrated display console is provided with a system alarm and a reset button.

[0015] The integrated control mechanism is connected to a UPS power supply.

[0016] The front receiver, the middle receiver and the rear receiver are all provided with a conducting line; and a patch is provided on the upper end of the conducting line.

[0017] The beneficial effects of the present invention are:

[0018] Compared with the prior art, the automatic lifting and attitude adjustment device for an aircraft using the structure of the present invention can directly drive the front lifting device, the left lifting device and the right lifting device to move upward and adjust the aircraft attitude through the servo lifting mechanism, and the laser beam emitted by the laser leveling instrument can be automatically received by the front receiver, the middle receiver and the rear receiver, and there is no need to manually control the laser leveling instrument and the front lifting device, the left lifting device and the right lifting device, which effectively avoids the participation of a large amount of manpower and effectively simplifies the aircraft attitude adjustment process. The servo lifting mechanism is driven by a servo motor and drives the front lifting device, the left lifting device and the right lifting device. During the entire lifting process, there is no need to use a hydraulic jack. It can effectively prevent the hydraulic jack from having frequent oil leakage, unstable pressure, low reliability and easy damage during use due to poor hydraulic sealing. It can also effectively prevent the hydraulic system from slowly releasing pressure, which may cause the aircraft attitude to change due to the drop in the jack height after the aircraft attitude adjustment is completed, making the attitude adjustment invalid. The entire attitude adjustment process of the aircraft is controlled by the integrated control mechanism, and the integrated display console will record all data in the attitude adjustment process in real time, and completely digitize all the processes, so that each step in the aircraft attitude adjustment process can be clearly understood, effectively avoiding the situation where the data in the attitude adjustment process is judged by manual visual inspection and perception, resulting in inaccurate data results. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a structural schematic diagram of an angle of the automatic lifting and attitude adjustment device for an aircraft of the present invention;

[0020] Figure 2 It is a structural schematic diagram of another angle of the automatic lifting and attitude adjustment device for an aircraft of the present invention;

[0021] Figure 3 It is a schematic diagram of the structure of the front receiver;

[0022] Figure 4 It is a schematic diagram of the structure of the front top device;

[0023] Figure 5 It is a structural schematic diagram when the left top device and the right top device cooperate;

[0024] Figure 6 It is a schematic diagram of the structure of the laser leveling instrument;

[0025] Figure 7 It is a schematic diagram of the structure of the integrated control mechanism;

[0026] Figure 8 It is a structural diagram of the servo lifting mechanism;

[0027] Fig. 9 It is a cross-sectional schematic diagram of the servo lifting mechanism. DETAILED DESCRIPTION

[0028] The present invention is further described in detail below with reference to the accompanying drawings and specific embodiments:

[0029] See also Figures 1 to 9 The present invention provides an automatic lifting and attitude adjustment device for an aircraft, comprising a fuselage 1, a nose 2 arranged at the front end of the fuselage 1, and wings 3 arranged at the left and right sides of the middle part of the fuselage 1, a front wheel 4 is arranged just below the nose 2, and rear wheels 5 are arranged symmetrically on the left and right sides of the rear part of the fuselage 1, a laser leveler 6 is arranged on the right side of the fuselage 1; a front receiver 7 is arranged on the right side wall of the nose 2; a middle receiver 8 adjacent to the wing 3 is arranged on the left and right side walls of the middle part of the fuselage 1; a rear receiver 9 is arranged on the right side wall of the rear part of the fuselage 1; the front receiver 7, the middle receiver 8 and the rear receiver 9 are all capable of Receives the laser beam of the laser leveler 6; an integrated control mechanism 10 is provided at the front right of the fuselage 1; servo lifting mechanisms 11 are provided on both sides of the left and right sides directly below the head 2 and directly below the middle of the fuselage 1, and the servo lifting mechanism 11 can receive the information fed back by the integrated control mechanism 10; the servo lifting mechanism 11 located directly below the head 2 is provided with a front lifting device 12; the left lifting device 13 is located on the left side of the lower middle part of the fuselage 1, and the right lifting device 14 is located on the right side of the lower middle part of the fuselage 1; the left lifting device 13 and the right lifting device 14 are connected through a fine-tuning plate 15, and the fine-tuning plate 15 is in contact with the lower surface of the fuselage 1.

[0030] The servo lifting mechanism 11 includes a lifting bracket plate 16; a laser leveler bracket seat 17 is provided at the lower end of the laser leveler 6; a plurality of extension plates 18 evenly distributed in a circumference are provided on the outer circumference of the lifting bracket plate 16 and the laser leveler bracket seat 17; a displacement fastening device is provided at the end of the extension plate 18; a driving box 19 is provided on the lower surface of the lifting bracket plate 16; a servo motor 20 is provided on the upper surface of one side of the lifting bracket plate 16; a first through hole 21 coaxial with the motor shaft 2001 of the servo motor 20 is provided on the lifting bracket plate 16, and the first through hole 21 is connected with the inside of the driving box 19; the lower end of the motor shaft 2001 of the servo motor 20 passes downward through the first through hole 21 and is provided with a first transmission wheel 22; a lifting cylinder 23 is provided on the central upper surface of the lifting bracket plate 16; the upper surface of the lifting cylinder 23 is provided with a movable hole connected with its internal space 24; a threaded rod 25 is provided in the lifting cylinder 23; a second through hole 26 coaxial with the threaded rod 25 is provided in the lifting bracket plate 16; a rotating shaft 27 is provided at the center of the lower surface of the threaded rod 25; the lower end of the rotating shaft 27 passes through the second through hole 26 and is provided with a second transmission wheel 28 located in the driving box 19; the second transmission wheel 28 is connected to the first transmission wheel 22 by a conveyor belt 29; a lifting sleeve 30 meshing with the threaded rod 25 is provided on the outer sleeve; mutually symmetrical lifting grooves 31 are provided on the inner walls on the left and right sides of the lifting cylinder 23; limit blocks 32 matching the lifting grooves 31 are provided on the left and right sides of the lifting sleeve 30; a plurality of support rods 33 evenly distributed in a circle are provided on the upper surface of the lifting sleeve 30; the upper ends of the support rods 33 pass through the movable holes 24 upward, and the upper ends of the support rods 33 are connected by a lifting plate 34 located just above the threaded rod 25.

[0031] The front jacking device 12 includes a front jacking rod 35 arranged at the center of the upper surface of the jacking plate 34, and a jacking head 36 is provided at the upper end of the front jacking rod 35; the left jacking device 13 includes a left jacking rod 37 arranged at the center of the upper surface of the jacking plate 34; the right jacking device 14 includes a right jacking rod 38 arranged at the center of the upper surface of the jacking plate 34; the upper end of the left jacking rod 37 and the upper end of the right jacking rod 38 are connected through the fine-tuning plate 15; the fine-tuning plate 15 is U-shaped, and the fine-tuning plate 15 itself forms an upper jacking groove 39, and the groove wall of the upper jacking groove 39 is in contact with the outer wall of the fuselage 1; the jacking head 36 and the upper jacking groove 39 are both provided with an embedded hole on the left and right sides of the groove bottom; a laser locator and a weighing sensor matching them are provided in the embedded hole; a distance measuring sensor is provided on the lower surface of the jacking bracket plate 16.

[0032] A measuring electric cylinder 40 is provided on the upper surface of the leveling instrument support seat 17; the displacement fastening device includes a hinged plate 41 provided on the upper end of the lifting cylinder 23 and the upper end of the measuring electric cylinder 40; a plurality of hinged rods 42 evenly distributed in a circumference are hingedly connected to the outer edge of the hinged plate 41; a fastening plate 43 is hingedly connected to the end of the extension plate 18; the lower end of the hinged rod 42 is hingedly connected to the fastening plate 43; a lifting hole 44 is provided on the extension plate 18; a pulley seat 45 is provided in the lifting hole 44, The outer wall of the pulley seat 45 does not contact the inner wall of the lifting hole 44; the upper end of the pulley seat 45 is fixed to the hinge rod 42 through a connecting plate 46; a pulley 47 is provided on the lower surface of the pulley seat 45; a fastening screw hole 48 is provided on the fastening plate 43; a screw rod 49 is screwed to the fastening screw hole 48; the upper end of the screw rod 49 passes upward to the outside of the fastening screw hole 48 and is provided with a hand wheel 50; the lower end of the screw rod 49 passes downward to the outside of the fastening screw hole 48 and is provided with an anti-slip foot pad 51.

[0033] The anti-skid pad 51 is made of rubber.

[0034] The integrated control mechanism 10 includes a moving seat 52, and moving wheels 53 are provided at the four corners of the lower surface of the moving seat 52; an integrated control box 54 is provided above the moving seat 52; an integrated display console 55 is provided on the upper surface of the integrated control box 54; a heavy-duty connector is provided in the integrated control box 54; the heavy-duty connector is connected to the servo lifting mechanism 11 and the laser leveler 6 through a plurality of power lines and a plurality of signal lines.

[0035] The movable seat 52 is provided with a take-up device for winding up the power line and the signal line; the take-up device includes a take-up frame 56 arranged on the movable seat 52; the take-up frame 56 is provided with a plurality of fixed shafts 57 evenly distributed in the longitudinal direction; the fixed shaft 57 is provided with a plurality of take-up wheels 58 evenly distributed in the transverse direction, and the take-up wheels 58 can rotate around the fixed shaft 57 as the center.

[0036] The integrated display console 55 is provided with a system alarm and a reset button.

[0037] The integrated control mechanism 10 is connected to a UPS power supply.

[0038] The front receiver 7 , the middle receiver 8 and the rear receiver 9 are all provided with a conducting wire 59 ; a patch 60 is provided at the upper end of the conducting wire 59 .

[0039] The method of use of the present invention is as follows:

[0040] Before adjusting the aircraft attitude, first find the reference point located at the nose 2, and attach the front receiver 7 to the reference point through the patch 60, then find the reference points located on the left and right sides of the middle of the fuselage 1, and attach the middle receiver 8 to the corresponding reference point through the patch 60, then find the reference point located at the rear of the fuselage 1, and attach the rear receiver 9 to the corresponding reference point through the patch 60. When all the receivers are placed at the correct reference point, the laser leveler 6 can be moved. When the laser leveler 6 is moved to the actual required position, the measuring electric cylinder 40, the front receiver 7, the middle receiver 8, the rear receiver 9 of the laser leveler 6 are connected to the integrated control box 54 of the integrated control mechanism 10 through several power lines or several signal lines, and then the front top device 12, the left top device 13 and the right top device 14 are connected. 14 is moved to the actually required position under the fuselage 1. When the laser leveler 6, the front top device 12, the left top device 13 and the right top device 14 need to be moved, it can be achieved through the displacement fastening device. The pulley 47 of the displacement fastening device can be used to drive the leveler bracket seat 17 to move, and the pulley 47 of the displacement fastening device can also be used to drive the lifting bracket plate 16 to move. When the laser leveler 6, the front top device 12, the left top device 13 and the right top device 14 are all moved to their respective actually required positions, the hand wheel 50 can be rotated to make the screw 49 move downward along the trajectory of the fastening screw hole 48. When the screw 49 moves downward, the anti-slip foot pad 51 moves downward accordingly, the leveler bracket seat 17 and the lifting bracket plate 16 will both rise, and the pulley 47 will be separated from the ground, thereby realizing the fixation between the leveler bracket seat 17 and the lifting bracket plate 16 and the ground.

[0041] One end of the hinged rod 42 is hinged to the outer edge of the hinged plate 41, and the other end of the hinged rod 42 is hinged to the fastening plate 43 at the end of the extension plate 18. Therefore, the hinged rod 42, the extension plate 18 and the lifting cylinder 23 can enclose a right-angled triangle structure, and the hinged rod 42, the extension plate 18 and the measuring electric cylinder 40 can also enclose a right-angled triangle structure, thereby effectively ensuring the strength of the servo lifting mechanism 11 and the laser leveler 6, and effectively ensuring the stability of the servo lifting mechanism 11 when driving the front lifting device 12, the left lifting device 13, and the right lifting device 14 to lift the aircraft. The hinged connection in the components included in the displacement fastening device can enable the components to automatically achieve fine-tuning when fastening is achieved, effectively avoiding the situation where the rigid fit between the components is damaged once excessive force is applied. After the front lifting device 12, the left lifting device 13 and the right lifting device 14 are moved to the actual required position, the servo lifting mechanism 11 can be connected to the integrated control box 54 of the integrated control mechanism 10 through cables.

[0042] When the front top device 12, the left top device 13, the right top device 14 and the laser leveler 6 are in the actual required positions, the integrated control box 54 can be started, and then the corresponding instructions are inputted into the integrated display console 55 on the upper side of the integrated control box 54 to start the automatic leveling, automatic posture adjustment, weight measurement, center of gravity detection and other operations, and then according to the specific posture, the height information that each reference point on the fuselage 1 should actually reach is inputted. After all the information is accurately inputted, the front top device 12, the left top device 13 and the right top device 14 can be driven to move upwards through the servo top lifting mechanism 11. When the servo top lifting mechanism 11 starts to run, the motor shaft 2001 of the servo motor 20 drives The first transmission wheel 22 rotates, and at this time, the first transmission wheel 22 drives the second transmission wheel 28 to rotate through the conveyor belt 29. When the second transmission wheel 28 rotates, the second transmission wheel 28 drives the screw rod 25 to rotate around the second through hole 26 through the rotating shaft 27, and the outer sleeve of the screw rod 25 is provided with a jacking sleeve 30 engaged with it; and the left and right sides of the jacking sleeve 30 are provided with limit blocks 32 matching the jacking slide groove 31. Under the restriction of the limit blocks 32, the jacking sleeve 30 will convert the rotation force of the screw rod 25 into a longitudinal movement force. When the jacking sleeve 30 moves upward stably driven by the screw rod 25, the jacking sleeve 30 will drive the jacking plate 34 to move upward through the support rod 33.

[0043] The front jacking rod 35 of the front jacking device 12, the left jacking rod 37 of the left jacking device 13, and the right jacking rod 38 of the right jacking device 14 are all arranged on the upper surface of the jacking plate 34. When the jacking plate 34 drives the front jacking rod 35 to move upward, the upper end of the front jacking rod 35 will accurately find the top socket position on the machine head 2 through the laser locator, and then determine the reliable contact between the top head 36 and the top socket through the weighing sensor, and establish the original point of the top head. Then, the upper end of the left jacking rod 37 and the upper end of the right jacking rod 38 can be driven to move upward at the same time through the jacking plate 34. At this time, the fine-tuning plate 15 will gradually approach the lower surface of the fuselage 1, and finally through The laser locators on the left and right sides of the upper top groove 39 on the fine-tuning plate 15 accurately find the top socket position, and then the weighing sensor is used to determine the reliable contact between the groove wall of the upper top groove 39 and the top sockets on the left and right sides of the fuselage 1, and the original point of the fine-tuning plate 15 is established. During the process of the top head 36 and the fine-tuning plate 15 jacking the aircraft, the front wheels 4 and the rear wheels 5 of the aircraft leave the ground. At this time, the three original points have been established. At the same time, the distance between the jacking bracket plate 16 of the servo jacking mechanism 11 and the ground can be observed through the distance measuring sensor, which effectively prevents the servo jacking mechanism 11 from deforming or the ground from collapsing and causing safety accidents.

[0044] Then, the front receiver 7, the middle receiver 8, the rear receiver 9 and the laser leveler 6 can be used to adjust the aircraft fuselage 1 to a horizontal state. First, the balance of the left and right wings 3 is adjusted through the middle receiver 8 on the left and right sides of the fuselage 1, and then the front and rear balance between the nose 2 and the rear of the fuselage 1 is adjusted through the front receiver 7 and the rear receiver 9. When adjusting the balance of the left and right wings 3, the measuring electric cylinder 40 can be started, and the electric cylinder rod of the measuring electric cylinder 40 will move upward to realize the increase in the height of the laser leveler 6. The transmitting end on the upper side of the laser leveler 6 will form a laser horizontal plane 61 formed by the laser beam when it is running. At this time, the laser horizontal plane 61 It will gradually move upwards and gradually approach the height of the middle receiver 8. First, the laser horizontal plane 61 will first contact the middle receiver 8 with a lower height on one side. At this time, the measuring electric cylinder 40 continues to control the laser horizontal plane 61 formed by the transmitting end of the laser leveler 6 to rise. When the laser horizontal plane 61 contacts the middle receiver 8 with a higher height on the other side, the measuring electric cylinder 40 no longer controls the laser leveler 6 to rise. Then, the measuring electric cylinder 40 controls the laser horizontal plane 61 formed by the transmitting end of the laser leveler 6 to fall, so that the laser horizontal plane 61 moves to between the horizontal planes formed by the middle receivers 8 on the left and right sides. At this moment, the measuring electric cylinder 40 stops running and the laser horizontal plane 61 remains stationary.

[0045] Then the servo lifting mechanism 11 located just below the left lifting device 13 and the servo lifting mechanism 11 located just below the right lifting device 14 can be started. At this moment, the left lifting rod 37 moves upward or downward, and the left part of the fine-tuning plate 15 gradually pushes the left part of the fuselage 1 upward or drives the left part of the fuselage to move downward, and the middle receiver 8 on the reference point attached to the left part of the fuselage 1 moves upward or downward accordingly. When the right lifting rod 38 moves upward or downward, the right part of the fine-tuning plate 15 gradually pushes the right part of the fuselage 1 upward or drives the right part of the fuselage to move downward. At this time, the middle receiver 8 on the reference point attached to the right part of the fuselage 1 moves upward or downward accordingly. Since the laser horizontal plane 61 is located at the middle receivers 8 on the left and right sides, Between the horizontal planes formed by each of them, the servo jacking mechanism 11 can be used to control the left jacking rod 37 to move up and the right jacking rod 38 to move down synchronously, or the servo jacking mechanism 11 can be used to control the left jacking rod 37 to move down and the right jacking rod 38 to move up synchronously, so as to realize that the middle receivers 8 at different heights on the left and right sides are synchronously close to the laser horizontal plane 61. When the horizontal planes formed by the middle receivers 8 on the left and right sides coincide with the laser horizontal plane 61, the servo jacking mechanism 11 arranged under the left jacking device 13 and the servo jacking mechanism 11 arranged under the right jacking device 14 all stop running. At this time, the balance adjustment of the wings 3 on the left and right sides of the aircraft fuselage 1 is completed.

[0046] When the balance adjustment of the left and right wings of the aircraft fuselage 1 is completed, the front and rear balance between the nose 2 and the rear of the fuselage 1 can be adjusted. At this time, the measuring electric cylinder 40 is started again, and the height of the transmitting end on the upper side of the laser leveler 6 is adjusted by using the measuring electric cylinder 40. During the upward movement of the laser horizontal plane 61 formed by the transmitting end of the laser leveler 6, it will first contact the front receiver 7 or the rear receiver 9 at a lower point. After the contact, the laser horizontal plane 61 continues to move upward, and then the laser horizontal plane 61 will contact the rear receiver 9 or the front receiver 7 at a higher point. After this contact, the measuring electric cylinder 40 will stop controlling the upward movement of the transmitting end of the laser leveler 6, and start controlling the downward movement of the transmitting end of the laser leveler 6, so that the laser horizontal plane 61 formed by the transmitting end of the laser leveler 6 moves to between the horizontal plane formed by the front receiver 7 and the horizontal plane formed by the rear receiver 9. At this time, the operation of the measuring electric cylinder 40 is stopped to keep the laser horizontal plane 61 stationary.

[0047] Then, the servo lifting mechanism 11 located directly below the front lifting device 12 is started. At this time, the servo lifting mechanism 11 controls the front lifting rod 35 to move up or down. When the front lifting rod 35 moves up or down, the position of the machine head 2 will move up or down accordingly. When the machine head 2 moves up, the rear part of the fuselage 1 will move down, and when the machine head 2 moves down, the rear part of the fuselage 1 will move up. After each adjustment of the position of the machine head 2, the height of the sending end of the laser leveling instrument 6 can be adjusted again by using the measuring electric cylinder according to the current state. However, after each height adjustment, the laser horizontal plane is always at the water level formed by the front receiver 7. After the laser horizontal plane 61 is adjusted once, the servo lifting mechanism 11 is used to drive the front lifting device 12 to move up or down, and the height of the front receiver 7 and the rear receiver 9 is adjusted again. After continuous adjustment, the laser horizontal plane 61 is finally made to gradually approach the horizontal plane position of the middle receiver 8, and then the front receiver 7, the rear receiver 9 and the middle receiver 8 on the left and right sides are all in the same horizontal plane, completing the front and rear balance adjustment between the nose 2 and the rear of the fuselage 1, thereby completing the overall attitude adjustment of the aircraft.

[0048] The integrated display console 55 is provided with a system alarm and a reset button. During the aircraft attitude adjustment process, a certain adjustment threshold is set to prevent operation errors caused by inaccurate data due to unexpected situations of related sensors. When the threshold is triggered, the system alarm will alarm immediately. At this time, the working conditions of each sensor should be rechecked. If they are working normally, the fine-tuning program can continue to run after resetting the alarm. Otherwise, the lifting reset button should be pressed after resetting the alarm. After the aircraft lands, the cause can be found. In principle, once a servo fault is triggered, the system stops running. If the aircraft is in the jacking state, it will continue to be maintained until the reset is manually triggered, the aircraft is lifted and reset, and the aircraft lands again.

[0049] In summary, the present invention can directly drive the front top device 12, the left top device 13 and the right top device 14 to move upward and level the aircraft attitude through the servo top mechanism, and the laser beam emitted by the laser leveler 6 can be automatically received by the front receiver 7, the middle receiver 8 and the rear receiver 9, and there is no need to manually control the laser leveler 6 and the front top device 12, the left top device 13 and the right top device 14, which effectively avoids the participation of a large amount of manpower and effectively simplifies the aircraft attitude adjustment process. The servo top mechanism 11 is driven by the servo motor 20 and drives the front top device 12, the left top device 13 and the right top device 14. During the entire top process, there is no need to use hydraulic The jack can effectively prevent the hydraulic jack from having frequent oil leakage, unstable pressure, low reliability and easy damage during use due to poor hydraulic sealing. It can also effectively prevent the hydraulic system from slowly releasing pressure, resulting in the change of the aircraft attitude due to the decrease of the jack height after the aircraft attitude adjustment is completed, making the attitude adjustment invalid. The entire attitude adjustment process of the aircraft is controlled by the integrated control mechanism 10, and the integrated display console 55 will record all data in the attitude adjustment process in real time, and completely digitize all processes, so that each step of the aircraft attitude adjustment process can be clearly understood, effectively avoiding the situation where the data in the attitude adjustment process is judged by manual visual inspection and perception, resulting in inaccurate data results.

[0050] The anti-skid foot pad 51 is made of rubber. The presence of the anti-skid foot pad 51 can not only play a buffering effect and effectively prevent damage to the ground, but also increase the friction between itself and the ground, further improving the stability of the displacement fastening device after being fastened to the ground.

[0051] A take-up device for taking up the power line and the signal line is provided on the movable seat 52, and the take-up device includes a take-up frame 56 arranged on the movable seat 52, and a plurality of fixed shafts 57 uniformly distributed in the longitudinal direction are provided on the take-up frame 56, and a plurality of take-up wheels 58 uniformly distributed in the transverse direction are provided on the fixed shaft 57. The take-up wheel 58 can rotate around the fixed shaft 57 as the center. When laying the power line or the signal line, the power line or the signal line can pass through the take-up wheel. When a part of the power line or the signal line is fixed on the take-up wheel 58, the power line and the signal line can be quickly taken up by rotating the take-up wheel 58.

[0052] The integrated control mechanism 10 is connected to a UPS power supply, and the independent UPS power supply can perform subsequent operations after an emergency power outage occurs.

[0053] By adopting the automatic lifting and attitude adjustment device for aircraft of the present invention, the number of necessary operators can be reduced from 6-7 to 1-2; the attitude adjustment time can be reduced from 40-90 minutes to less than 20 minutes, thereby effectively improving the aircraft attitude adjustment efficiency; and the aircraft center of gravity measurement time can be reduced from 1-3 hours to less than 30 minutes, thereby effectively improving the aircraft center of gravity measurement efficiency.

Claims

1. An automatic lifting and attitude adjustment device for an aircraft, comprising a fuselage, a nose arranged at the front end of the fuselage, and wings arranged at the left and right sides of the middle of the fuselage, a front wheel is arranged just below the nose, and rear wheels are arranged symmetrically on the left and right sides of the rear of the fuselage, characterized in that: A laser leveler is arranged on the right side of the fuselage; a front receiver is arranged on the right side wall of the nose; a middle receiver adjacent to the wing is arranged on the left and right side walls of the middle part of the fuselage; a rear receiver is arranged on the right side wall of the rear part of the fuselage; the front receiver, the middle receiver and the rear receiver can all receive the laser beam of the laser leveler; an integrated control mechanism is arranged on the right front of the fuselage; servo lifting mechanisms are arranged on the left and right sides of the nose and the middle part of the fuselage, and the servo lifting mechanisms can receive information fed back by the integrated control mechanism; The servo jacking mechanism located directly below the machine head is provided with a front jacking device; the left jacking device is located on the left side below the middle of the fuselage, and the right jacking device is located on the right side below the middle of the fuselage; the left jacking device and the right jacking device are connected through a fine-tuning plate, and the fine-tuning plate is in contact with the lower surface of the fuselage; the servo jacking mechanism includes a jacking bracket plate; a laser leveler bracket seat is provided at the lower end of the laser leveler; a plurality of extension plates evenly distributed in a circle are provided on the outer peripheral surfaces of the jacking bracket plate and the leveler bracket seat; a displacement fastening device is provided at the end of the extension plate; a driving box is provided on the lower surface of the jacking bracket plate; A servo motor is provided on the upper surface of one side of the lifting bracket plate; a first through hole coaxial with the motor shaft of the servo motor is provided on the lifting bracket plate, and the first through hole is connected with the inside of the driving box; the lower end of the motor shaft of the servo motor passes downward through the first through hole and is provided with a first transmission wheel; a lifting cylinder is provided on the central upper surface of the lifting bracket plate; a movable hole connected with the internal space thereof is provided on the upper surface of the lifting cylinder; a screw rod is provided in the lifting cylinder; a second through hole coaxial with the screw rod is provided on the lifting bracket plate; a rotating shaft is provided at the center of the lower surface of the screw rod; the lower end of the rotating shaft passes through the second A second transmission wheel is perforated and provided in the driving box; the second transmission wheel is connected to the first transmission wheel by a conveyor belt; the outer sleeve of the screw rod is provided with a lifting sleeve meshing with it; the inner walls on the left and right sides of the lifting cylinder are provided with mutually symmetrical lifting grooves; the left and right sides of the lifting sleeve are provided with limit blocks matching the lifting grooves; the upper surface of the lifting sleeve is provided with a plurality of support rods evenly distributed in a circle; the upper ends of the support rods pass upward through movable holes, and the upper ends of the support rods are connected by a lifting plate located just above the screw rod; the integrated control mechanism is connected to a UPS power supply.

2. The automatic lifting and attitude adjustment device for an aircraft according to claim 1, characterized in that: The front jacking device includes a front jacking rod arranged at the center of the upper surface of the jacking plate, and a jacking head is provided on the upper end of the front jacking rod; the left jacking device includes a left jacking rod arranged at the center of the upper surface of the jacking plate; the right jacking device includes a right jacking rod arranged at the center of the upper surface of the jacking plate; the upper ends of the left jacking rod and the right jacking rod are connected through a fine-tuning plate; the fine-tuning plate is U-shaped, and the fine-tuning plate itself forms an upper jacking groove, and the groove wall of the upper jacking groove is in contact with the outer wall of the fuselage; an embedding hole is provided on both sides of the jacking head and the bottom of the upper jacking groove; a laser locator and a weighing sensor matching them are provided in the embedding hole; a distance measuring sensor is provided on the lower surface of the jacking bracket plate.

3. The automatic lifting and attitude adjustment device for an aircraft according to claim 1, characterized in that: A measuring electric cylinder is provided on the upper surface of the leveling instrument bracket; the displacement fastening device includes a hinged plate arranged at the upper end of the lifting cylinder and the upper end of the measuring electric cylinder; a plurality of hinged rods evenly distributed in a circle are hinged on the outer edge of the hinged plate; a fastening plate is hinged on the end of the extension plate; the lower end of the hinged rod is hinged to the fastening plate; a lifting hole is provided on the extension plate; a pulley seat is provided in the lifting hole, and the outer wall of the pulley seat does not contact the inner wall of the lifting hole; the upper end of the pulley seat is fixed to the hinged rod through a connecting plate; a pulley is provided on the lower surface of the pulley seat; a fastening screw hole is provided on the fastening plate; a screw is screwed in the fastening screw hole; the upper end of the screw passes upward to the outside of the fastening screw hole and is provided with a handwheel; the lower end of the screw passes downward to the outside of the fastening screw hole and is provided with an anti-slip foot pad.

4. The automatic lifting and attitude adjustment device for an aircraft according to claim 3, characterized in that: The anti-skid foot pad is made of rubber.

5. The automatic lifting and attitude adjustment device for an aircraft according to claim 3, characterized in that: The integrated control mechanism comprises a moving seat, and moving wheels are arranged at the four corners of the lower surface of the moving seat; an integrated control box is arranged above the moving seat; an integrated display console is arranged on the upper surface of the integrated control box; a heavy-load connector is arranged inside the integrated control box; the heavy-load connector is connected to the servo lifting mechanism and the measuring electric cylinder of the laser leveler through a number of power lines and a number of signal lines.

6. The automatic lifting and attitude adjustment device for an aircraft according to claim 5, characterized in that: The movable seat is provided with a take-up device for winding up the power line and the signal line; the take-up device includes a take-up frame arranged on the movable seat; the take-up frame is provided with a plurality of fixed shafts evenly distributed longitudinally; the fixed shaft is provided with a plurality of take-up wheels evenly distributed transversely, and the take-up wheels can rotate around the fixed shaft.

7. The automatic lifting and attitude adjustment device for an aircraft according to claim 5, characterized in that: The integrated display console is provided with a system alarm and a reset button.

8. The automatic lifting and attitude adjustment device for an aircraft according to claim 1, characterized in that: The front receiver, the middle receiver and the rear receiver are all provided with a conducting line; and a patch is provided on the upper end of the conducting line.

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