CN113899518B - Airplane test driving system and driving method - Google Patents
Airplane test driving system and driving method Download PDFInfo
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- CN113899518B CN113899518B CN202111497700.2A CN202111497700A CN113899518B CN 113899518 B CN113899518 B CN 113899518B CN 202111497700 A CN202111497700 A CN 202111497700A CN 113899518 B CN113899518 B CN 113899518B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
Abstract
The invention discloses an aircraft test driving system and a driving method, and belongs to the technical field of aircraft testing. The invention can solve the problem that the existing driving system can not transport the experiment module to the designated position.
Description
Technical Field
The invention relates to the technical field of airplane testing, in particular to an airplane test driving system and a driving method.
Background
Aircraft testing is commonly applied to simulation testing of various parameters of dynamic performance and flight characteristics of an aircraft under various environments during aircraft development. The airplane climate environment test is one of important test links in airplane test flight.
The airplane climate environment test is usually carried out in a climate environment laboratory, the climate environment laboratory has typical climate environment capabilities of simulating temperature, humidity, illumination radiation, thunder and lightning, rain, snow fall, freezing rain, solar radiation, icing, low-speed air blowing and the like, and meanwhile the climate environment adaptability verification requirements of large-scale aviation weaponry such as unmanned planes, fighters, scouts and the like can be met. In general, when a climate environment laboratory simulates solar radiation, rain, freezing rain, fog and freezing tests, the test modules of the special environment simulation systems need to be hung at a designated position on the top of the laboratory. At this moment, the experiment module is transported to a specific position by the lifting appliance equipment of the lifting trolley, then the experiment module is grabbed by the lifting appliance grabber, and large-scale self-driven lifting equipment cannot be used due to limited climate environment laboratory field and numerous field equipment.
In the prior art, a driving system is usually additionally arranged, the driving system and a lifting appliance are connected and hung through a rope, the lifting appliance is driven by the driving system to run to reach an appointed area, and then the experimental module is lifted through a lifting appliance gripper. However, due to the flexible connection of the rope, the lifting appliance still moves forward under the action of inertia when the driving system brakes, the experimental module cannot be accurately transported to the designated position under the action of the inertia force, the lifting appliance needs to be adjusted at any time when being operated on site by a worker, other related equipment is easily touched and scratched by the worker during the adjustment process, and even the worker is easily accidentally injured.
Disclosure of Invention
Aiming at the problems, the invention provides an aircraft test driving system and a driving method, which can effectively solve the technical problems that in the prior art, due to the fact that the driving system is connected with a lifting appliance through a rope, an experimental module cannot be transported to a specified position, and the danger of scratch with other equipment is increased.
The invention has the technical scheme that the aircraft test driving system comprises a walking part nested on a top end rail of a laboratory, a transverse fixing frame vertically and fixedly connected with the walking part, a shell fixedly connected with the lower surface of the transverse fixing frame, a ground controller capable of controlling the walking part of the driving system to move, and a navigation device fixed at the front end of the transverse fixing frame, wherein the ground controller is in signal connection with the navigation device and is in electric connection with the walking part; the electromagnetic sleeve device comprises a C-shaped sleeve frame fixedly connected with the transverse fixing frame, two ends of the C-shaped sleeve frame extend outwards to form a sleeve space which can accommodate the external ear of the lifting appliance, one extending end of the C-shaped sleeve frame is fixedly connected with an electromagnetic generating device, the other extending end of the C-shaped sleeve frame is fixedly connected with a locking device, the C-shaped sleeve frame is provided with a pressure sensor which is electrically connected with the locking device, the ground controller is respectively electrically connected with the electromagnetic generating device, the locking device and the pressure sensor and sends a control command, make electromagnetism generating device produce the electromagnetism and adsorb the external ear of hoist, pressure sensor is touched to the external ear of hoist, and pressure sensor gives ground controller with electric signal transmission, and ground controller control locking device inserts in the hoist external ear and locks the hoist external ear.
Further, electromagnetism generating device includes hollow cast iron shell, hollow cast iron shell passes through bolted connection with the extension end of C type cover connection frame, magnetic coil has been cup jointed along the bolt circumference to cast iron shell inside, magnetic coil's one end extends the cast iron shell, magnetic coil's extension end fixedly connected with produces magnetic controller, the inside circuit board that is provided with of magnetism controller, the welding has magnetism generating power and on-off controller on the circuit board, on-off controller and ground controller signal connection, magnetism generating power and on-off controller power connection. Wherein, ground controller control switch controller opens and shuts to for magnetic coil power transmission, magnetic coil circular telegram back can produce magnetic force, this magnetic force can adsorb the external ear of hoist and move pressure sensor and contact with it, and then pressure sensor gives ground controller with trigger signal transmission, and ground controller control locking device takes place the action, makes locking device lock the external ear of hoist. This application changes former rope traction mode into electromagnetic traction mode according to the principle of electricity magnetism, eliminates the influence of iron cable connection inertia to guarantee that the hoist can not reach the thing of accurate positioning and take place because of inertia.
Furthermore, the locking device comprises a locking seat, a worm is connected to the locking seat in a sliding mode, a first driving motor is fixedly connected to the locking seat, an output shaft of the first driving motor is connected with the worm through a gear, and the first driving motor is electrically connected with the ground controller. The locking device is realized through the mode of worm gear, and the gear of the output shaft of first driving motor is equivalent to the worm wheel, can effectively ensure transmission efficiency through this mode, can realize the demand of great doing work.
Further, still including cup jointing the horizontal buffer who cup joints between horizontal mount and C type cover connects the frame, horizontal buffer includes first bolster, second bolster, third bolster, and the one end and the horizontal mount of first bolster cup joint, and the one end and the C type cover of third bolster connect the frame and cup joint, and the other end of first bolster and the other end extension of third bolster are gone into in the second bolster and are left the clearance with second bolster swing joint, are filled with the buffer solution in the clearance. The transverse buffer device can prevent instant linkage force from being extruded to cause linkage part damage when the lifting appliance and the driving system are linked, and the buffer liquid in the gap is generally selected by lubricating oil or gear lubricant, so that on one hand, the first buffer part and the third buffer part enter the inner part of the second buffer part to play a lubricating role, and on the other hand, the lubricating oil and the gear lubricant have a buffering role between the parts.
Further, the ground controller is an MCU chip-level computer formed by integrating a CPU, an RAM, a ROM, a timing counter and various I/O interfaces on one chip. The ground controller is generally selected from controllers already disclosed in the prior art, such as: granted publication No. CN111532802B, patent name: a controller for cargo transportation and transfer device and method in port of arrival is disclosed, which can control the movement of the running part and connect the pressure sensor, the electromagnetic generator and the locking device with electric power and signal so as to realize the linkage of circuit signal.
The walking part comprises a first walking component and a second walking component which are sleeved on a rail at the top end of the laboratory in a front-back mode and have the same structure, the first walking component comprises walking wheels and a walking frame connected with the walking wheels through bearings, the walking wheels are arranged on the inner side of the rail and are in rolling contact with the lower edge of the rail, a second driving motor is fixedly connected onto the walking frame and is electrically connected with a ground controller, the second driving motor is connected with the walking wheels through gears and is used for driving the walking wheels to move, two buffering rolling bodies are fixedly connected onto one side of the walking frame, which is opposite to the rail surface, and are symmetrically arranged on two sides of the walking wheels, rubber patterns are arranged on the outer surfaces of the buffering rolling bodies, and the rubber patterns of the buffering rolling bodies are in contact with the rail surface and can rotate relatively on the rail surface. When the ground controller controls the walking part to stop, the walking wheel cannot stop and brake immediately due to the action of inertia, the buffering rolling body with rubber patterns and the rail surface can generate friction force, and the friction force can be instantly impacted and resisted with the inertia force, so that the displacement error caused by the action of inertia when the driving system moves in place is avoided.
The brake assembly comprises a third driving motor fixedly arranged in the shell, a rotating disc rotatably connected with the center of the transverse fixing frame, and a brake shoe elastically connected with the transverse fixing frame, a first gap is reserved between the brake shoe and the side edge of the track, a lug is arranged on the rotating disc, a second gap is reserved between the rotating disc and the brake shoe, the size of the first gap is equal to that of the second gap, the size of the second gap is smaller than that of the lug, an output shaft of the third driving motor is connected with the rotating disc through a chain, the third driving motor is electrically connected with a ground controller, when braking is needed, the ground controller firstly cuts off the power of the second driving motor, then switches on the power of the third driving motor, the third driving motor drives the rotating disc to rotate through the chain, and the brake shoe is jacked up when the lug passes through the second gap, the brake shoe is contacted with the side edge of the track through the first gap for braking. When the buffering rolling body with the rubber patterns fails, the braking assembly can act to further prevent the driving system from generating displacement difference due to inertia.
Furthermore, fixing columns are symmetrically arranged on the transverse fixing frame along the center surface in the direction towards the track, springs are sleeved on the fixing columns, and the lower surface of the brake shoe is connected to the springs in a clamped mode. The elastic connection mode can stabilize the brake shoe in the vertical direction, and can slowly apply the acting force of the lug on the brake shoe to prevent the brake shoe from being instantly applied to a track to cause locking.
The invention also provides a driving method of the aircraft test driving system, which comprises the following steps:
s1, an operator sends a driving signal to the walking part by controlling the ground controller;
s2, when the electromagnetic sleeving device is close to the outer ear of the lifting appliance, the ground controller sends a signal to control the electromagnetic generating device to generate electromagnetism, the electromagnetism adsorbs the outer ear of the lifting appliance, and the outer side of the outer ear of the lifting appliance touches the pressure sensor on the C-shaped sleeving frame;
s3, converting the pressure signal into an electric signal by the pressure sensor and transmitting the electric signal to the ground controller, and then controlling the locking device to be inserted into and lock the outer ear of the lifting appliance by the ground controller;
s4, locking the outer ear of the lifting appliance by a locking device, driving the walking part to run along the track by a ground controller, and navigating by the navigation device for an airplane test driving system;
and S5, when the aircraft test driving system runs to the navigation specified position of the navigation device, driving the running part to brake through the ground controller.
Compared with the prior art, the invention has the beneficial effects that: according to the aircraft test driving system, the electromagnetic force generated by the electromagnetic sleeving device acts on the outer ear of the lifting appliance in an electromagnetic manner, the outer ear of the lifting appliance is firmly adsorbed on the outer surface of the electromagnetic sleeving device, meanwhile, due to the fact that the pressure sensor is arranged, when the end part of the outer ear of the lifting appliance contacts the pressure sensor, the pressure sensor is triggered to transmit a signal to the ground controller, the ground controller controls the locking device to lock the driving system and the lifting appliance, then accurate guidance is carried out through the navigation device on the driving system, and the driving system runs to the designated position. The invention replaces the rope flexible connection mode in the prior art by the rigid connection mode of electromagnetism and locking, and meanwhile, the rope can be accurately guided by the navigation device to reach the lifting appliance without position deviation in the transportation process, thereby ensuring that the experiment module can be transported to the designated position.
Drawings
FIG. 1 is a flow chart of a driving method of the present invention;
FIG. 2 is a schematic structural diagram of a driving system according to the present invention;
FIG. 3 is a schematic structural diagram of the electromagnetic sleeving apparatus shown in FIG. 2;
FIG. 4 is a schematic structural view of example 2 of the present invention;
FIG. 5 is a schematic view of the lateral cushioning device of FIG. 4;
FIG. 6 is an enlarged view of a portion of A-A of FIG. 2;
fig. 7 is a schematic structural diagram of the electromagnetic socket device according to embodiment 4.
Wherein, 1, a transverse fixing frame, 2, a shell, 3, a navigation device, 4, an electromagnetic sleeve device, 4-1, a C-shaped sleeve frame, 4-2, an electromagnetic generating device, 4-2-1, a cast iron shell, 4-3, a locking device, 4-3-1, a locking seat, 4-3-2, a first driving motor, 5, a pressure sensor, 6, a magnetic coil, 7, a magnetism generating controller, 8, a worm, 9, a transverse buffering device, 9-1, a first buffering device, 9-2, a second buffering device, 9-3, a third buffering device, 10, a traveling wheel, 11, a traveling frame, 12, a second driving motor, 13, a buffering rolling body, 14, a braking component, 14-1, a third driving motor, 14-2, a rotating disc, 14-3, a braking block, 15. lug, 16 spring, 17 bumper pad, 18 shock absorber bumper.
Detailed Description
The following detailed description of the present invention is provided in conjunction with the accompanying drawings, but it should be understood that the scope of the present invention is not limited to the specific embodiments.
In the description of the present invention, it is to be understood that the terms "lateral", "longitudinal", "vertical", "edge", "side end", "upper", "lower", "surface", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing technical solutions of the present invention and simplifying the description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Example 1
As shown in figures 2-3, an aircraft test driving system comprises a running part nested on a top end track of a laboratory, a transverse fixing frame 1 vertically and fixedly connected with the running part, a shell 2 fixedly connected with the lower surface of the transverse fixing frame 1, a ground controller capable of controlling the running part of the driving system to move, a navigation device 3 fixed at the front end of the transverse fixing frame 1, and an electromagnetic socket device 4 with one end parallel to and fixedly connected with the transverse fixing frame 1, wherein the electromagnetic socket device 4 comprises a C-shaped socket frame 4-1 fixedly connected with the transverse fixing frame 1, two ends of the C-shaped socket frame 4-1 extend outwards to form a socket space, the socket space can accommodate an external ear of a lifting appliance, and an extension end of the C-shaped socket frame 4-1 is fixedly connected with an electromagnetic generating device 4-2, the other extension end is fixedly connected with a locking device 4-3, a C-shaped sleeve frame 4-1 is provided with a pressure sensor 5, the pressure sensor 5 is electrically connected with the locking device 4-3, a ground controller is respectively electrically connected with an electromagnetic generation device 4-2, the locking device 4-3 and the pressure sensor 5 and sends a control instruction, so that the electromagnetic generation device 4-2 generates electromagnetism to adsorb the outer ear of the lifting appliance, the outer ear of the lifting appliance touches the pressure sensor 5, the pressure sensor 5 transmits an electric signal to the ground controller, and the ground controller controls the locking device 4-3 to be inserted into the outer ear of the lifting appliance and locks the outer ear of the lifting appliance. The experimental actuating system of aircraft of this embodiment, cup joint device 4 through the electromagnetism and act on the auricle of hoist with the electromagnetic mode of production, firmly adsorb the auricle of hoist at the electromagnetism and cup joint device 4's surface, owing to install pressure sensor 5 simultaneously, when hoist auricle tip contact pressure sensor 5, pressure sensor 5 is triggered then gives ground controller with signal transmission, ground controller control locking device 4-3 with actuating system and hoist locking, then carry out the accurate guidance through navigation head 3 on the actuating system, move actuating system to the assigned position. The rigid connection mode of electromagnetism replaces the mode of rope flexible connection in the prior art, and the accurate guidance of the navigation device 3 is used for reaching the lifting appliance without position deviation in the transportation process, so that the experiment module can be transported to a specified position. The navigation device 3 is a GPS navigation positioning device.
Referring to fig. 3, the electromagnetic generating device 4-2 includes a hollow cast iron housing 4-2-1, the hollow cast iron housing 4-2-1 is connected with an extending end of the C-shaped sleeve frame 4-1 through a bolt, a magnetic coil 6 is sleeved inside the cast iron housing 4-2-1 along the circumference of the bolt, one end of the magnetic coil 6 extends out of the cast iron housing 4-2-1, the extending end of the magnetic coil 6 is fixedly connected with a magnetism generating controller 7, a circuit board is arranged inside the magnetism generating controller 7, a magnetism generating power supply and a switch controller are welded on the circuit board, the switch controller is in signal connection with a ground controller, and the magnetic power supply is electrically connected with the switch controller. The ground controller controls the switch controller to be switched on and switched off, so that the magnetic coil 6 is powered on, the magnetic coil 6 can generate magnetic force after being powered on, the magnetic force can adsorb the external lugs of the lifting appliance to move to the pressure sensor 5 to be contacted with the pressure sensor, the pressure sensor 5 transmits a trigger signal to the ground controller, and the ground controller controls the locking device 4-3 to act, so that the locking device 4-3 locks the external lugs of the lifting appliance. This application changes former rope traction mode into electromagnetic traction mode according to the principle of electricity magnetism, eliminates rope and connects inertial influence to guarantee that the hoist can not reach the thing of accurate positioning and take place because of inertia. The locking device 4-3 comprises a locking seat 4-3-1, a worm 8 is connected to the locking seat 4-3-1 in a sliding mode, the locking seat 4-3-1 is fixedly connected with a first driving motor 4-3-2, an output shaft of the first driving motor 4-3-2 is connected with the worm 8 through a gear, and the first driving motor 4-3-2 is electrically connected with a ground controller. The ground controller is an MCU chip-level computer formed by integrating a CPU, an RAM, a ROM, a timing counter and various I/O interfaces on one chip. The ground controller is generally selected from controllers already disclosed in the prior art, such as: granted publication No. CN111532802B, patent name: a controller related to a cargo transportation and transfer device and a method for arriving at a port can control the action of a walking part, and can connect a pressure sensor 5, an electromagnetic generating device 4-2 and a locking device 4-3 through electric power and signals so as to realize the linkage of circuit signals. The communication mode of the signals is usually wireless communication, and the modules of the wireless communication are also concentrated on the MCU chip, and the wireless communication mode is a mobile network.
Example 2
On the basis of the embodiment 1, referring to fig. 4-5, the aircraft test driving system further includes a transverse buffering device 9 sleeved between the transverse fixing frame 1 and the C-shaped sleeved frame 4-1, the transverse buffering device 9 includes a first buffering device 9-1, a second buffering device 9-2, and a third buffering device 9-3, one end of the first buffering device 9-1 is sleeved with the transverse fixing frame 1, one end of the third buffering device 9-3 is sleeved with the C-shaped sleeved frame 4-1, the other end of the first buffering device 9-1 and the other end of the third buffering device 9-3 extend into the second buffering device 9-2 to be movably connected with the second buffering device 9-2 and leave a gap, and the gap is filled with a buffering liquid. The transverse buffer device 9 can prevent damage of the coupling parts caused by extrusion of instant coupling force when the lifting appliance and the driving system are coupled, and the buffer solution in the gap is generally selected from lubricating oil or gear lubricant, so that on one hand, the first buffer part 9-1 and the third buffer part 9-3 enter the internal parts of the second buffer part 9-2 to play a role in lubricating, and on the other hand, the lubricating oil and the gear lubricant have a buffer pressure effect on all parts. The gap is left to ensure the moving margin of the first buffer member 9-1 and the third buffer member 9-3 in the second buffer member 9-2.
Referring to fig. 6, the running part of the above embodiments 1 and 2 comprises the first running component sleeved on the top end rail of the laboratory in the front-back manner and has the same structure, the first walking assembly comprises walking wheels 10 and a walking frame 11 connected with the walking wheels 10 in a bearing mode, the walking wheels 10 are arranged on the inner side of a track and are in rolling contact with the lower edge of the track, a second driving motor 12 is fixedly connected to the walking frame 11, the second driving motor 12 is electrically connected with a ground controller, the second driving motor 12 is connected with the walking wheels 10 through gears to drive the walking wheels 10 to move, two buffering rolling bodies 13 are fixedly connected to one side, opposite to the rail surface, of the walking frame 11, the two buffering rolling bodies 13 are symmetrically arranged on two sides of the walking wheels 10, rubber patterns are arranged on the outer surfaces of the buffering rolling bodies 13, and the rubber patterns of the buffering rolling bodies 13 are in contact with the rail surface and can rotate relatively on the rail surface. When the ground controller controls the running part to stop, the running wheel 10 cannot stop and brake immediately due to the action of inertia, the buffering rolling body 13 with rubber patterns and the rail surface generate friction force, and the friction force can be immediately and mutually impacted with the inertia force, so that the displacement error caused by the action of inertia when the driving system moves in place is avoided.
Example 3
On the basis of the embodiment 2, referring to fig. 6, the aircraft test driving system further includes a brake assembly 14, the brake assembly 14 includes a third driving motor 14-1 fixedly disposed inside the housing 2, a rotating disc 14-2 rotatably connected to the center of the transverse fixing frame 1, the rotating disc 14-2 is provided with a protrusion 15, and a brake shoe 14-3 elastically connected to the transverse fixing frame 1, and the transverse fixing frame 1 and the brake shoe 14-3 are specifically connected in the following manner: fixing columns are symmetrically arranged on the transverse fixing frame 1 along the direction of the center surface facing the track, springs 16 are sleeved on the fixing columns, and the lower surfaces of the brake shoes 14-3 are clamped on the springs 16. The elastic connection can stabilize the brake shoe 14-3 in the vertical direction on one hand, and can slowly apply the acting force of the lug 15 on the brake shoe 14-3 on the other hand, so that the brake shoe 14-3 is prevented from being instantaneously applied to a rail to cause locking. A first gap is reserved between the brake shoe 14-3 and the side edge of the track, a second gap is reserved between the rotating disc 14-2 and the brake shoe 14-3, the size of the first gap is equal to that of the second gap, the size of the second gap is smaller than the length size of the lug 15, an output shaft of a third driving motor 14-1 is connected with the rotating disc 14-2 through a chain, the third driving motor 14-1 is electrically connected with a ground controller, when braking is needed, the ground controller firstly cuts off the power of the second driving motor 12, then the power supply of the third driving motor 14-1 is switched on, the third driving motor 14-1 drives the rotating disc 14-2 to rotate through the chain, the lug 15 jacks up the brake shoe 14-3 when passing through the second gap, and the brake shoe 14-3 contacts with the side edge of the track to brake through the first gap. The length of the projection 15 may be 5cm, the distance of the second gap may be 3cm, at this time, the projection 15 reaches the second gap under the driving action of the third driving motor 14-1, due to the elastic force of the spring 16, the brake shoe 14-3 will be driven to be gradually jacked by the projection 15, when the brake shoe 14-3 contacts the side edge of the track, the brake shoe 14-3 cannot be jacked, the brake shoe 14-3 transmits the received resistance to the projection 15, the cam 15 further transmits the received resistance to the third driving motor 14-1, at this time, the ground controller stops supplying power to the third driving motor 14-1 due to the received resistance of the output shaft of the third driving motor 14-1, and the third driving motor 14-1 stops working. When the buffering rolling body 13 with the rubber pattern fails, the brake assembly 14 acts to further prevent the driving system from generating displacement difference due to inertia. Meanwhile, a longitudinal damping buffer part 18 is arranged at one end of the transverse fixing frame 1, wherein the damping buffer part 18 can be a damping spring, so that longitudinal vibration in the driving process is further relieved, and the driving stability is further ensured.
Example 4
Referring to fig. 7, on the basis of embodiment 3, a cushion pad 17 is disposed at a position corresponding to the pressure sensor 5 of the C-shaped socket frame 4-1, wherein the cushion pad 17 is made of rubber, and buffers an extrusion force of the spreader vehicle during coupling with the driving system, thereby preventing the pressure sensor 5 from being damaged by the extrusion force.
The driving method of the aircraft test driving system, as shown in fig. 1, includes the following steps:
s1, an operator sends a driving signal to the walking part by controlling the ground controller;
s2, when the electromagnetic sleeving connection device 4 is close to the outer ear of the lifting appliance, the ground controller sends a signal to control the electromagnetic generation device 4-2 to generate electromagnetism, the electromagnetism adsorbs the outer ear of the lifting appliance, and the outer side of the outer ear of the lifting appliance touches the pressure sensor 5 on the C-shaped sleeving connection frame 4-1;
s3, converting the pressure signal into an electric signal by the pressure sensor 5 and transmitting the electric signal to the ground controller, and then controlling the locking device 4-3 to be inserted into and lock the outer ear of the lifting appliance by the ground controller;
s4, locking the outer ear of the lifting appliance by a locking device 4-3, driving the walking part to run along the track by a ground controller, and simultaneously navigating the plane test driving system by a navigation device 3;
and S5, when the aircraft test driving system runs to the navigation specified position of the navigation device 3, driving the running part to brake through the ground controller.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (7)
1. An aircraft test driving system is characterized by comprising a walking part nested on a top end rail of a laboratory, a transverse fixing frame (1) vertically and fixedly connected with the walking part, a shell (2) fixedly connected with the lower surface of the transverse fixing frame (1), a ground controller capable of controlling the walking part of the driving system to move, and a navigation device (3) fixed at the front end of the transverse fixing frame (1), wherein the ground controller is in signal connection with the navigation device (3), and is electrically connected with the walking part;
the lifting appliance is characterized by further comprising an electromagnetic sleeving device (4) with one end parallel to the transverse fixing frame (1) and fixedly connected with the transverse fixing frame (1), wherein the electromagnetic sleeving device (4) comprises a C-shaped sleeving frame (4-1) fixedly connected with the transverse fixing frame (1), two ends of the C-shaped sleeving frame (4-1) extend outwards to form a sleeving space, the sleeving space can accommodate the external ear of a lifting appliance, one extending end of the C-shaped sleeving frame (4-1) is fixedly connected with an electromagnetic generating device (4-2), the other extending end of the C-shaped sleeving frame (4-1) is fixedly connected with a locking device (4-3), a pressure sensor (5) is arranged on the C-shaped sleeving frame (4-1), the pressure sensor (5) is electrically connected with the locking device (4-3), and the ground controller is respectively connected with the electromagnetic generating device (4-2), The locking device (4-3) and the pressure sensor (5) are electrically connected and send a control instruction, so that the electromagnetic generating device (4-2) generates electromagnetism to adsorb the external ear of the lifting appliance, the external ear of the lifting appliance touches the pressure sensor (5), the pressure sensor (5) transmits an electric signal to the ground controller, and the ground controller controls the locking device (4-3) to be inserted into the external ear of the lifting appliance and locks the external ear of the lifting appliance;
the electromagnetic generating device (4-2) comprises a hollow cast iron shell (4-2-1), the hollow cast iron shell (4-2-1) is connected with an extending end of the C-shaped sleeving frame (4-1) through a bolt, a magnetic coil (6) is sleeved inside the cast iron shell (4-2-1) along the circumference of the bolt, one end of the magnetic coil (6) extends out of the cast iron shell (4-2-1), the extending end of the magnetic coil (6) is fixedly connected with a magnetism generating controller (7), a circuit board is arranged inside the magnetism generating controller (7), a magnetism generating power supply and a switch controller are welded on the circuit board, the switch controller is in signal connection with a ground controller, and the magnetism generating power supply is in electric connection with the switch controller;
the locking device (4-3) comprises a locking seat (4-3-1), a worm (8) is connected to the locking seat (4-3-1) in a sliding mode, a first driving motor (4-3-2) is fixedly connected to the locking seat (4-3-1), an output shaft of the first driving motor (4-3-2) is connected with the worm (8) through a gear, and the first driving motor (4-3-2) is electrically connected with a ground controller.
2. The aircraft test driving system according to claim 1, further comprising a transverse buffering device (9) sleeved between the transverse fixing frame (1) and the C-shaped sleeved frame (4-1), wherein the transverse buffering device (9) comprises a first buffering member (9-1), a second buffering member (9-2) and a third buffering member (9-3), one end of the first buffering member (9-1) is sleeved with the transverse fixing frame (1), one end of the third buffering member (9-3) is sleeved with the C-shaped sleeved frame (4-1), the other end of the first buffering member (9-1) and the other end of the third buffering member (9-3) extend into the second buffering member (9-2) to be movably connected with the second buffering member (9-2) and leave a gap, the gap is filled with a buffer solution.
3. An aircraft test driving system according to claim 1, wherein the ground controller is an MCU chip-level computer formed by integrating a CPU, a RAM, a ROM, a timing counter and various I/O interfaces on one chip.
4. The aircraft test driving system according to claim 1, wherein the running part comprises a first running component and a second running component which are sleeved on the top end rail of the laboratory and have the same structure, the first running component comprises running wheels (10) and a running frame (11) connected with the running wheels (10) through bearings, the running wheels (10) are arranged on the inner side of the rail and are in rolling contact with the lower edge of the rail, a second driving motor (12) is fixedly connected to the running frame (11), the second driving motor (12) is electrically connected with a ground controller, the second driving motor (12) is connected with the running wheels (10) through gears to drive the running wheels (10) to move, two buffering rolling bodies (13) are fixedly connected to one surface of the running frame (11) opposite to the rail surface, the two buffering rolling bodies (13) are symmetrically arranged on two sides of the running wheels (10), the outer surface of the buffering rolling body (13) is provided with rubber patterns, and the rubber patterns of the buffering rolling body (13) are in contact with the rail surface and can relatively rotate on the rail surface.
5. An aircraft test driving system according to claim 4, further comprising a brake assembly (14), wherein the brake assembly (14) comprises a third driving motor (14-1) fixedly arranged inside the housing (2), a rotating disc (14-2) rotatably connected with the center of the transverse fixing frame (1), and a brake shoe (14-3) elastically connected with the transverse fixing frame (1), a first gap is reserved between the brake shoe (14-3) and the side edge of the track, a lug (15) is arranged on the rotating disc (14-2), a second gap is reserved between the rotating disc (14-2) and the brake shoe (14-3), the first gap and the second gap have the same size, and the size of the second gap is smaller than the length size of the lug (15), the output shaft of the third driving motor (14-1) is connected with the rotating disc (14-2) through a chain, the third driving motor (14-1) is in electric connection with the ground controller, when braking is needed, the ground controller firstly cuts off the power of the second driving motor (12), then the power of the third driving motor (14-1) is switched on, the third driving motor (14-1) drives the rotating disc (14-2) to rotate through the chain, the lug (15) jacks up the brake shoe (14-3) when passing through the second gap, and the brake shoe (14-3) is in contact braking with the side edge of the track through the first gap.
6. An aircraft test drive system according to claim 5, characterized in that the transverse fixing frame (1) is symmetrically provided with fixing columns along the direction of the central surface facing the track, the fixing columns are sleeved with springs (16), and the lower surfaces of the brake shoes (14-3) are clamped on the springs (16).
7. A method of driving an aircraft test drive system according to any of claims 1 to 6, comprising the steps of:
s1, an operator sends a driving signal to the walking part by controlling the ground controller;
s2, when the electromagnetic sleeving connection device (4) is close to the outer ear of the lifting appliance, the ground controller sends a signal to control the electromagnetic generation device (4-2) to generate electromagnetism, the electromagnetism absorbs the outer ear of the lifting appliance, and the outer side of the outer ear of the lifting appliance touches the pressure sensor (5) on the C-shaped sleeving connection frame (4-1);
s3, converting the pressure signal into an electric signal by the pressure sensor (5) and transmitting the electric signal to the ground controller, and then controlling the locking device (4-3) to be inserted into and lock the outer ear of the lifting appliance by the ground controller;
s4, locking the outer ear of the lifting appliance by a locking device (4-3), driving the walking part to run along the track by a ground controller, and navigating by the navigation device (3) for the aircraft test driving system;
and S5, when the aircraft test driving system runs to the navigation specified position of the navigation device (3), driving the running part to brake through the ground controller.
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| JP2009085912A (en) * | 2007-10-03 | 2009-04-23 | Orion Mach Co Ltd | Environmental testing apparatus |
| CN202785230U (en) * | 2012-07-27 | 2013-03-13 | 宝山钢铁股份有限公司 | Special magnetic hanger for non-magnetic inner cover |
| CN106114904B (en) * | 2016-08-12 | 2018-02-27 | 浙江工业大学 | A kind of brake buffer unit of sun wing plate erecting by overhang |
| CN207618898U (en) * | 2017-11-21 | 2018-07-17 | 武汉力神动力电池系统科技有限公司 | A kind of battery case hanging apparatus |
| JP7033986B2 (en) * | 2018-03-30 | 2022-03-11 | 前田建設工業株式会社 | Model molding equipment for wind tunnel experiments |
| JP2020076608A (en) * | 2018-11-06 | 2020-05-21 | 国立研究開発法人宇宙航空研究開発機構 | Magnetic force support balance device, wind tunnel model, method for controlling magnetic force support balance device, and program |
| CN109399449B (en) * | 2018-11-09 | 2020-05-01 | 中船华南船舶机械有限公司 | Folding arm type lifting appliance for lifting equipment |
| CN209893064U (en) * | 2019-03-11 | 2020-01-03 | 深圳市艾比森光电股份有限公司 | Hoisting device |
| CN213923778U (en) * | 2020-11-23 | 2021-08-10 | 三一海洋重工有限公司 | Remove hoist equipment |
| CN113666242A (en) * | 2021-08-08 | 2021-11-19 | 中国飞机强度研究所 | Modular hoisting method for spray frame in climate environment test |
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