CN113503767A - Full-automatic motion simulation equipment for aircraft cannon - Google Patents
Full-automatic motion simulation equipment for aircraft cannon Download PDFInfo
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- CN113503767A CN113503767A CN202110681086.9A CN202110681086A CN113503767A CN 113503767 A CN113503767 A CN 113503767A CN 202110681086 A CN202110681086 A CN 202110681086A CN 113503767 A CN113503767 A CN 113503767A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
- F41A31/00—Testing arrangements
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/003—Simulators for teaching or training purposes for military purposes and tactics
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Abstract
The invention relates to full-automatic motion simulation equipment for an aviation cannon, which adopts a transmission mechanism of a crown gear cam and an eccentric shaft, transmits power through crown gears, has compact structure and stable operation, and can realize the adjustment of the full travel of the back seat of the aviation cannon; the aircraft gun and the equipment are connected by a coaxial quick-release device, and a power system adopts a constant-torque alternating-current servo motor and a worm and gear speed reducer, so that the aircraft gun motion frequency is continuously adjustable from 0 to 120n/min and the output is stable. The invention fully simulates the shooting movement process of the cannon of the aviation organ, thereby greatly improving the scientific research and technical analysis level; the invention can replace part of live-action test work, greatly improves the scientific research test efficiency and reduces the test cost. The invention can provide a motion simulation platform of the aircraft cannon for teaching, accurately and visually display the motion principle and action relation of the aircraft cannon, and greatly promote the theory and skill promotion of technicians, thereby powerfully ensuring the rapid generation of the combat power of army equipment.
Description
Technical Field
The invention belongs to the field of artillery, and particularly relates to full-automatic motion simulation equipment for an aircraft artillery.
Background
The aircraft cannon has the characteristics of compact structure and high shooting speed, so that the aircraft cannon is widely applied to the field of aviation. However, at present, no equipment can realize the full-automatic simulation of the movement state of the aircraft cannon, so that the following problems exist in the aspects of scientific research and teaching:
in the scientific research technical aspect: the aviation gun can encounter some faults in the production test and the user use process, and the corresponding technical analysis cannot realize fault state simulation positioning due to the fact that no platform for simulating the motion of the aviation gun exists, so that the technical analysis support is insufficient.
Teaching and training: the aviation organ cannon belongs to main combat equipment, knowledge and skill of relevant ordnance guarantee talents promote generation of direct relation combat power, at present, no direct means exists for motion simulation of the aviation organ cannon, the motion principle of the aviation organ cannon cannot be intuitively and rapidly mastered, and teaching and training level is difficult to promote.
Disclosure of Invention
The technical problem solved by the invention is as follows: the invention discloses a full-automatic motion simulation device for an aviation organ cannon, which aims to solve the problem that a motion simulation means is lacked in the aspects of scientific research and technical analysis and teaching training of a certain type of aviation organ cannon.
The technical scheme of the invention is as follows: a full-automatic motion simulation device for an aircraft cannon comprises a cannon mounting frame, a supporting table, a control system, a sliding shaft combination, a control display system, a main transmission case and a power combination;
the artillery mounting frame is positioned on the table surface at one end of the support table, the control system is positioned in the support table, and the main transmission case is positioned on the side surface at the other end of the support table; the gun body of the machine-made gun is positioned on the gun mounting frame, and the gun barrel is connected with one end of the sliding shaft combination;
the main transmission case comprises an eccentric shaft, a locking nut, a crown gear cam and a crown gear sprocket; the crown-shaped tooth chain wheel is connected with one end of the eccentric shaft through a key, and the crown-shaped tooth cam is arranged at the middle eccentric section of the eccentric shaft; the crown-shaped tooth chain wheel can be meshed with the crown-shaped tooth cam so as to drive the crown-shaped tooth cam to rotate; the locking nut is connected with the eccentric shaft, and when the locking nut is screwed or loosened, the crown-tooth cam and the crown-tooth chain wheel can be reliably meshed or separated, so that the adjustable stroke of the aircraft cannon recoil base is realized;
the power combination is positioned below the main transmission case, an output chain wheel of the power combination is connected with a crown-shaped tooth chain wheel of the main transmission case through a roller chain, and the roller chain transmits the rotary motion of the output chain wheel to the crown-shaped tooth chain wheel;
the other end of the sliding shaft combination is connected with the crown-shaped tooth cam, and the rotating motion of the crown-shaped tooth cam can be converted into the axis reciprocating motion of the sliding shaft combination, so that the machine cannon is driven to carry out the axis reciprocating motion;
the control system is used for servo control of the power combination;
the control display system can be used for setting or displaying parameter information of movement displacement, speed and period of the aircraft cannon in real time.
The further technical scheme of the invention is as follows: the sliding shaft combination comprises a quick connection combination, a sliding shaft and a needle bearing combination;
the quick connection combination is used for quickly connecting the mechanical cannon with the sliding shaft;
one end of the sliding shaft is provided with a step surface used for being matched with the quick connection assembly, the other end of the sliding shaft is symmetrically provided with notches along the axis, so that the end is integrally in a convex shape, the convex surface is provided with a through hole, and the axis of the through hole is vertical to the axis of the sliding shaft;
the needle bearing assembly is connected to a convex surface at the other end of the sliding shaft, and the needle bearing assembly is in contact with inner and outer rolling surfaces of the crown-shaped tooth cam to convert the rotary motion of the crown-shaped tooth cam into the linear reciprocating motion of the sliding shaft.
The further technical scheme of the invention is as follows: the needle bearing assembly comprises a needle bearing, a swing arm and a bolt needle bearing;
the number of the needle roller bearings is two, and the number of the swing arms is two; the two needle roller bearings are respectively fixedly connected with one ends of the two swing arms on two sides of the convex surface of the sliding shaft through double-end studs, and the double-end studs penetrate through holes in the convex surface of the sliding shaft;
the two bolt needle roller bearings are fixedly connected with the other ends of the two swing arms respectively, and the two bolt needle roller bearings are not contacted after being fixedly connected.
The further technical scheme of the invention is as follows: the crown-shaped tooth cam is inserted into a gap of the bolt needle roller bearing, the bolt needle roller bearing is directly contacted with an inner rolling surface of the crown-shaped tooth cam, and the needle roller bearing is directly contacted with an outer rolling surface of the crown-shaped tooth cam; the rotary motion of the crown-shaped tooth cam is converted into the linear reciprocating motion of the sliding shaft through the rolling contact of the needle bearing and the bolt needle bearing with the inner and outer rolling surfaces of the crown-shaped tooth cam flange.
The further technical scheme of the invention is as follows: the quick connection assembly comprises a positioning pin, a positioning pin cover, a positioning pin seat, a spring, a gun barrel interface, an interface sleeve, a sliding shaft, a bolt and a first limiting sleeve; a stepped hole is formed in the interface sleeve, the interface sleeve can be sleeved at one end of the sliding shaft, the first limiting sleeve penetrates through the interface sleeve and is sleeved at the end head of one end of the sliding shaft, the bolt penetrates through the first limiting sleeve and the end face of the sliding shaft to connect the interface sleeve and the sliding shaft, and the interface sleeve can rotate around the central shaft of the sliding shaft; one end of the gun tube interface is inserted into the interface sleeve, is connected with the interface sleeve through arc-shaped tooth occlusion after rotating and is positioned through a positioning pin, and the other end of the gun tube interface is connected with an aviation machine gun through threads; the positioning pin is positioned in the positioning holes in the side walls of the interface sleeve and the gun tube interface, the large end of the positioning pin faces downwards, the spring is sleeved on a pin column of the positioning pin, the positioning pin seat is fixedly connected to a pin hole in the side wall of the interface sleeve in a welding mode, and the axes of the positioning pin seat and the pin hole coincide; the upper end of the positioning pin seat is symmetrically provided with convex shoulders along the axis and matched with a boss at the lower part of the positioning pin cover; the positioning pin cover is arranged at the upper end of the positioning pin seat and is connected with the positioning pin through a pin; when the fixing pin cover 22 is pulled upwards and rotated by 90 degrees to make the boss surface of the positioning pin cover contact with the convex shoulder surface of the positioning pin seat, the interface sleeve and the gun barrel interface can be disengaged; when the locating pin cover is rotated to enable the boss of the locating pin cover to sink into the locating pin seat groove, the locating pin can sink into the gun barrel interface hole to achieve the positioning connection of the interface sleeve and the gun barrel interface.
The further technical scheme of the invention is as follows: twelve arc grooves are arranged on the crown-shaped tooth cam, and two crown-shaped teeth are arranged on the crown-shaped tooth chain wheel; when the locking nut is loosened, the crown-shaped tooth cam can slide and is separated from the crown-shaped tooth chain wheel, the crown-shaped tooth cam is rotated, the twelve arc grooves on the crown-shaped tooth cam can be adjusted to be matched with the two crown-shaped teeth on the crown-shaped tooth chain wheel, six gears can be formed, the change of the included angle between the eccentric shaft and the maximum deflection line of the crown-shaped tooth cam can be realized, and the adjustment of the output displacement range of the whole mechanism can be realized.
The further technical scheme of the invention is as follows: the power combination comprises a constant-torque motor, a speed reducer and an output chain wheel; the constant torque motor is connected with the speed reducer, and the output chain wheel is fixedly connected with the speed reducer through a key and positioned by a set screw; the output sprocket is connected to a crown sprocket in the main drive housing by a roller chain which transfers the rotational motion of the output sprocket to the crown sprocket.
The further technical scheme of the invention is as follows: the support assembly is positioned between the quick connection assembly and the needle bearing assembly and is used for supporting the sliding shaft assembly; the linear bearing support device comprises a support seat, a linear bearing and a support plate, wherein the support seat is fixedly connected with the support plate through a bolt, and the linear bearing is arranged in the support seat; one end of the sliding shaft penetrates through the linear bearing, and the sliding shaft can reciprocate in the linear bearing.
The further technical scheme of the invention is as follows: the displacement detection assembly comprises a grating ruler, a first positioning frame and a second positioning frame; one end of the grating ruler is fixedly connected to the side wall of the transmission box main body, the first positioning frame and the second positioning frame are in a two-half type, can be sleeved at the other end of the sliding shaft and are fixed through screws and tacking screws; one end of the first positioning frame rod body is located below the grating ruler, and when the sliding shaft reciprocates, the grating ruler can detect displacement data of the grating ruler in real time and transmit the displacement data to the control system.
The further technical scheme of the invention is as follows: the counting detection combination comprises an induction sheet, a proximity switch and a fixing sheet; the induction sheet is fastened on the end face of the output shaft of the speed reducer through a bolt; the proximity switch is fixedly connected with one end of the fixed piece, the other end of the fixed piece is fixedly connected with the structure main body through a bolt, and the position of the proximity switch is close to the sensing piece on the power combination; the proximity switch can detect the rotation periodic signal of the induction sheet and transmit the rotation periodic signal to the control system.
Effects of the invention
The invention has the technical effects that:
1. the simulation device adopts a transmission mechanism of a crown gear cam and an eccentric shaft, transmits power through crown gears, has compact structure and stable operation, and can realize the adjustment of the full travel of the seat after the aircraft cannon is shut.
2. The aircraft cannon and the simulation device of the invention adopt coaxial quick-release devices, which is convenient for the quick and reliable connection of the aircraft cannon and simultaneously ensures the coaxiality of the connecting piece.
3. The power system adopts a constant-torque alternating-current servo motor and a worm gear speed reducer, so that the continuous adjustability of the cannon movement frequency of the aircraft gun from 0 to 120n/min and the stable output of the full-speed torque domain are realized.
4. In the scientific research technical aspect: the device can fully simulate the shooting movement process of the aircraft cannon, provides a simulation platform for scientific research and fault analysis, and greatly improves the scientific research and technical analysis level; the invention can replace part of live-action test work, thereby greatly improving the scientific research test efficiency and reducing the test cost.
5. Teaching and training: the invention can provide a motion simulation platform of the aircraft cannon for the teaching of army and colleges, accurately and visually display the motion principle and action relation of the aircraft cannon, and greatly promote the theory and skill promotion of ordnance support personnel, thereby powerfully and rapidly generating the fighting capacity of army equipment.
Drawings
FIG. 1 is a front view of the automatic motion simulation device for an aircraft cannon according to the present invention
FIG. 2 is a top view of the automatic motion simulator of the aircraft cannon of FIG. 1
FIG. 3 is a schematic perspective view of the automatic motion simulation device for an aircraft cannon of FIG. 1
FIG. 4 is a schematic structural view of the gun mount of the present invention
FIG. 5 is a schematic structural diagram of the structural body of the present invention
FIG. 6 is a schematic diagram of the structure of the control system
FIG. 7 is a schematic diagram of a displacement detection assembly
FIG. 8 is a schematic view of the support assembly
FIG. 9 is a schematic view of the supporting seat in FIG. 8
FIG. 10 is a schematic view of the structure of the linear bearing of FIG. 8
FIG. 11 is a schematic view of the sliding shaft assembly of the present invention
FIG. 12 is a sectional view of the slide shaft assembly of FIG. 11
FIG. 13 is a schematic view showing the structure of the needle roller bearing of FIG. 11
FIG. 14 is a schematic structural view of the swing arm in FIG. 11
FIG. 15 is a schematic view of the needle bearing with a shaft of FIG. 11
FIG. 16 is a schematic view showing the structure of the sliding shaft of FIG. 12
FIG. 17 is a schematic view of the dowel cover of FIG. 12
FIG. 18 is a schematic view of the dowel seat of FIG. 12
FIG. 19 is a schematic view of the structure of the alignment pin of FIG. 12
FIG. 20 is a schematic view of the interface sleeve of FIG. 12
FIG. 21 is a schematic view of the gun barrel interface of FIG. 12
FIG. 22 is a schematic view of the first stop sleeve of FIG. 12
FIG. 23 is a schematic perspective view of the main transmission case of the present invention
FIG. 24 is a cross-sectional view of FIG. 23
FIG. 25 is a schematic view of the structure of the transmission case body of FIG. 24
FIG. 26 is a schematic structural view of the end cap of FIG. 24
FIG. 27 is a schematic view of the eccentric shaft of FIG. 24
FIG. 28 is a schematic view of the locking nut of FIG. 24
FIG. 29 is a schematic view of the structure of the second stop sleeve of FIG. 24
FIG. 30 is a schematic view of the crown gear cam structure of FIG. 24
FIG. 31 is a schematic view of the crown sprocket shown in FIG. 24
FIG. 32 is a schematic view of the structure of the III stopping sleeve of FIG. 24
FIG. 33 is a schematic view of the structure of the handwheel of FIG. 24
FIG. 34 is a schematic view of the power pack of the present invention
FIG. 35 is a schematic view of the output sprocket of FIG. 34
FIG. 36 is a schematic view of the structure of the counting and detecting assembly of the present invention
In the figure, 1-aircraft cannon, 2-cannon mounting rack, 3-structure main body, 4-control system, 5-support combination, 6-sliding shaft combination, 7-control display system, 8-main transmission case, 9-roller chain, 10-power combination, 11-counting detection combination, 12-displacement detection combination, 13-grating ruler, 14-I positioning rack, 15-II positioning rack, 16-supporting seat, 17-linear bearing, 18-supporting plate, 19-needle bearing, 20-swing arm, 21-bolt needle bearing, 22-positioning pin, 23-positioning pin cover, 24-positioning pin seat, 25-spring, 26-cannon barrel interface, 27-interface sleeve, 28-sliding shaft, 29-bolt, 30-I limit sleeve, 31-transmission box main body, 32-end cover, 33-eccentric shaft, 34-locking nut, 35-II limit sleeve, 36-crown gear cam, 37-crown gear sprocket, 38-III limit sleeve, 39-hand disc, 40-handle, 41-constant torque motor, 42-speed reducer, 43-output sprocket, 44-induction sheet, 45-proximity switch, 46-fixing sheet and 47-quick connection combination
Detailed Description
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
Referring to fig. 1 to 36, an aviation cannon full-automatic motion simulation device comprises a cannon mounting frame 2, a structure body 3, a control system 4, a support combination 5, a sliding shaft combination 6, a control display system 7, a main transmission case 8, a roller chain 9, a power combination 10, a counting detection combination 11 and a displacement detection combination 12; the structure main body 3 is integrally frame-type and provides an installation foundation for each part; the aviation cannon 1 is fixedly connected with the cannon mounting frame 2 through an annular clamping groove and a guide rail on the cannon mounting frame 2; the gun mounting frame 2 is fixedly connected to the top of one end of the structure main body 3 through a bolt; the control system 4 is arranged in the frame of the structure main body 3 and is positioned below the artillery mounting frame; the supporting assembly 5 is fixedly connected to the top of the structure body 3 and is close to the other end of the structure body, the supporting assembly 5 comprises a supporting seat 16, a linear bearing 17 and a supporting plate 18, the supporting seat 16 is fixedly connected with the supporting plate 18 through a bolt, and the linear bearing 17 is installed in the supporting seat 16; one end of the sliding shaft 28 passes through the linear bearing 17, and the sliding shaft 28 can reciprocate in the linear bearing 17; one end of the quick connection combination 47 is connected with one end of the sliding shaft 28, and the other end of the quick connection combination 47 is fixedly connected with the aircraft cannon 1; the needle bearing assembly at the other end of the sliding shaft assembly 6 is clamped on the inner and outer rolling surfaces of the flange of the crown-shaped tooth cam 36 in the main transmission case 8, and the rotary motion of the crown-shaped cam 36 is converted into the linear reciprocating motion of the sliding shaft 28; the main transmission box 8 is fixed on the top of the other end of the structure body 3, the power assembly 10 is arranged in the frame of the structure body 3 and is positioned below the main transmission box 8, the crown-shaped toothed chain wheel 37 in the main transmission box 8 is connected with the output chain wheel 43 in the power assembly 10 through the roller chain 9, and the roller chain 9 can transmit the rotation motion of the output chain wheel 43 to the crown-shaped toothed chain wheel 37; the counting detection combination 11 is fixedly connected to the structure main body 3 and is close to the induction sheet 44 on the power combination, and the proximity switch 45 on the counting detection combination 11 can detect a rotation period signal of the induction sheet 44 and transmit the rotation period signal to the control system 4; the grating ruler 13 at one end of the displacement detection assembly 12 is fixedly connected to the side wall of the transmission box main body 31 of the main transmission box 8, the other end of the displacement detection assembly 12 is fixedly connected to the other end of the sliding shaft 28, and when the sliding shaft 28 reciprocates, the grating ruler 13 detects displacement data in real time and transmits the displacement data to the control system 4; the control display system 7 is positioned at the top of the main transmission box 8, has the functions of starting, stopping, resetting, fault alarming and sudden stopping, and can display parameter information of displacement, speed and period in real time.
Referring to fig. 4, one end of a gun mounting frame 2 is rigidly connected with an aircraft gun 1 through an annular fracture clamping groove; the other end is a rectangular roller groove which can be matched with a guide rail of the aircraft cannon 1 to ensure the upper, lower, left and right limiting and front and back guiding of the aircraft cannon 1 in the movement process.
Referring to fig. 5, the structural body 3 is made of steel by welding, and is integrally frame-shaped and used for mounting and bearing each component.
Referring to fig. 6, the control system 4 includes a driver and a controller; the servo control of the constant-torque motor 41 is realized, and the motion mode programmable function is realized; the touch control display has the functions of starting, stopping, resetting, fault alarming and sudden stopping, can perform the functions of speed, period and manual control of equipment operation, and displays parameter information of displacement, speed and period in real time.
Referring to fig. 7, the displacement detection assembly 12 includes a grating ruler 13, a first positioning frame 14, and a second positioning frame 15; one end of the grating ruler 13 is fastened on the side wall of the transmission case main body 31 through a bolt, the first positioning frame 14 and the second positioning frame 15 are in a two-half type, can be sleeved at the left end of the sliding shaft 28 and are fixed through a screw and a set screw; one end of the first positioning frame 14 is located below the grating ruler 13, and when the sliding shaft 28 reciprocates, the grating ruler 13 can detect the displacement data in real time and transmit the displacement data to the control system 4.
Referring to fig. 8-10, the support assembly 5 includes a support base 16, a linear bearing 17, and a support plate 18; the supporting plate 18 is fixed on the top surface of the structure body 3, the supporting seat 16 is fixed on the supporting plate 18 through a bolt, and the supporting seat 16 is made of steel and used for installing the linear bearing 17; the linear bearing 17 is arranged in a through hole in the middle of the supporting seat 16, and two ends of the linear bearing are positioned through check rings; one end of the slide shaft 28 passes through the linear bearing 17 and can reciprocate in the linear bearing 17.
Reference is made to fig. 11-22; the sliding shaft assembly 6 comprises a quick connection assembly 47, a needle bearing assembly and a sliding shaft 28; the quick connection combination 47 and the needle bearing combination are respectively connected to two ends of the sliding shaft 28;
the sliding shaft 28 is made of steel and is integrally columnar, one end of the sliding shaft is provided with a step for mounting the quick connection combination 47, the other end of the sliding shaft is symmetrically provided with a notch, and a through hole is formed in the direction vertical to the axis; the sliding shaft 28 penetrates through the linear bearing 17 in the support assembly 5 to provide the sliding shaft assembly 6 with bearing and guiding functions; the sliding shaft 28 is used for converting the rotary motion of the crown gear cam 36 in the main transmission case 8 into a linear reciprocating motion and transmitting the linear reciprocating motion to the aircraft cannon 1.
The quick connection assembly comprises a positioning pin 22, a positioning pin cover 23, a positioning pin seat 24, a spring 25, a gun barrel interface 26, an interface sleeve 27, a sliding shaft 28, a bolt 29 and an I-th limiting sleeve 30; a stepped hole is formed in the interface sleeve 27, the interface sleeve 26 can be sleeved at one end of the sliding shaft 28, the first limiting sleeve 30 penetrates through the interface sleeve 27 and is sleeved at one end of the sliding shaft 28, the bolt 29 penetrates through the first limiting sleeve 30 and the end face of the sliding shaft 28 to connect the interface sleeve 27 with the sliding shaft 28, and the interface sleeve 27 can rotate around the central shaft of the sliding shaft 28; one end of the gun tube interface 26 can be inserted into the interface sleeve 27, is connected with the interface sleeve 27 through arc tooth engagement after rotating for 60 degrees and is positioned through the positioning pin 22, and the other end of the gun tube interface 26 is connected with the aircraft gun through threads; the positioning pin 22 is positioned in positioning holes in the side walls of the interface sleeve 27 and the gun barrel interface 26, the large end of the positioning pin 22 faces downwards, the spring 25 is sleeved on the pin column of the positioning pin 22, the positioning pin seat 24 is fixedly connected to the pin hole in the side wall of the interface sleeve 27 in a welding mode, and the axes of the positioning pin seat and the pin hole coincide; the upper end of the positioning pin seat 24 is symmetrically provided with convex shoulders along the axis and matched with a convex platform at the lower part of the positioning pin cover 23; the positioning pin cover 23 is arranged at the upper end of the positioning pin seat 24 and is connected with the positioning pin 22 through a pin; when the fixing pin cover 22 is pulled upwards and rotated by 90 degrees to make the boss surface of the positioning pin cover 22 contact with the shoulder surface of the positioning pin seat 24, the interface sleeve 27 and the gun barrel interface 26 can be disengaged; when the locating pin cover 23 is rotated by 90 degrees, the boss of the locating pin cover 23 sinks into the groove of the locating pin seat 24, and the locating pin 22 can sink into the hole of the gun barrel interface 26 to realize the locating connection between the interface sleeve 27 and the gun barrel interface 26.
The needle bearing assembly comprises a needle bearing 19, a swing arm 20 and a bolt needle bearing 21; one ends of the two needle roller bearings 19 and the two swing arms 20 are fixedly connected to through holes at the other ends of the sliding shafts 28 through studs and nuts, and the two bolt needle roller bearings 21 are fixedly connected with the other ends of the two swing arms 20 respectively; the needle bearing 19 is in direct contact with the outer rolling surface of the crown gear cam 36, the bolt needle bearing 21 is in direct contact with the inner rolling surface of the crown gear cam 36, and the needle bearing combination converts the rotary motion of the crown gear cam 36 into the linear reciprocating motion of the sliding shaft 28 through the rolling contact of the needle bearing 19, the bolt needle bearing 21 and the inner and outer rolling surfaces of the flange of the crown gear cam 36; the swing arm 20 is made of steel and used for mounting the needle bearing 19 and the bolt needle bearing 21;
reference is made to fig. 23-33; the main transmission case 8 comprises a transmission case main body 31, an end cover 32, an eccentric shaft 33, a locking nut 34, a second limiting sleeve 35, a crown gear cam 36, a crown gear chain wheel 37, a third limiting sleeve 38, a hand disc 39 and a handle 40; the eccentric shaft 33 penetrates through symmetrical through holes in the side wall of the main transmission case main body 31, and two ends of the eccentric shaft are respectively connected with the transmission case main body 31 through deep groove ball bearings; the crown gear sprocket 37 is positioned in the transmission case main body 31 and fixedly connected with the eccentric shaft 33 through a key; the crown sprocket 37 is connected with an output sprocket 43 in the power assembly 10 through a roller chain 9, and the roller chain 9 transmits the rotation motion of the output sprocket 43 to the crown sprocket 37; a third limiting sleeve 38 is arranged at the right end of the crown-shaped gear sprocket 37 and is used for simultaneously limiting the crown-shaped gear sprocket 37 and a deep groove ball bearing arranged at the right end of the eccentric shaft 33; the crown gear cam 36 is arranged at the eccentric section of the middle part of the eccentric shaft 33, the left side of the crown gear cam is positioned by the II-th limiting sleeve 35, and the locking nut 34 is fixedly connected with the eccentric shaft 33 through threads and tightly presses the II-th limiting sleeve 35; the crown gear cam 36 is connected with the crown gear sprocket 37 through crown teeth, and the crown gear sprocket 37 directly drives the crown gear cam 36 to rotate through the crown teeth; the end covers 32 are fixedly connected with the side walls of the transmission case main body 31 through bolts respectively and tightly press the deep groove ball bearings at two ends, and are used for limiting the deep groove ball bearings; the hand disc 39 is connected with the right end of the eccentric shaft 33 through a non-return bearing, a key and a retainer ring, and the handle 40 is connected with the hand disc 39 through a bolt, so that the manual unidirectional rotation function is realized;
when the locking nut 34 is loosened, the crown-shaped tooth cam 36 slides leftwards to be separated from the crown-shaped tooth chain wheel 37, the crown-shaped tooth cam 36 is rotated, the twelve arc grooves on the crown-shaped tooth cam 36 can be adjusted to be matched with two crown-shaped teeth on the crown-shaped tooth chain wheel 37, six gears can be formed, the change of the included angle between the eccentric shaft 33 and the maximum eccentric line of the crown-shaped tooth cam 36 is realized, and the adjustment of the output displacement range of the whole cam mechanism is realized;
the transmission case main body 31 is made of steel by welding, and is of a case structure used for bearing and mounting transmission parts; through holes are formed in two symmetrical side walls of the device, and the axes of the through holes are overlapped; two ends of the eccentric shaft 33 are arranged in the through hole through deep groove ball bearings;
the end cap 32 is made of steel and used for limiting the deep groove ball bearing.
The eccentric shaft 33 is made of steel and is integrally multi-step; the eccentric amount exists on the design of the axis of the mounting position of the crown-tooth cam 36 and the mounting axis of the eccentric shaft 33, and is used for adjusting the displacement output by the crown-tooth cam 36.
Referring to fig. 28, a lock nut 34 is used to fasten the ii nd limiter sleeve 35 and the crown gear cam 36.
Referring to fig. 29, the second limit sleeve 35 is made of steel for limiting the crown gear cam 36.
Referring to fig. 30, the crown-shaped tooth cam 36 is made of steel, the crown-shaped tooth at the middle part is meshed with the crown-shaped tooth at the crown-shaped tooth chain wheel 37, the outline is a T-shaped inner rolling surface and an outer rolling surface, and the T-shaped inner rolling surface and the T-shaped outer rolling surface are contacted with the needle bearing 19 and the bolt needle bearing 21 to transmit acting force.
Referring to fig. 31, the crown sprocket 37 is made of steel, and the roller chain 9 rotates the crown sprocket 37 and engages with the crown teeth of the crown cam 36 to rotate the crown cam 36. Referring to fig. 34-35, the power assembly 10 includes a constant torque motor 41, a speed reducer 42, an output sprocket 43, wherein the constant torque motor 41 is connected with the speed reducer 42, the output sprocket 43 is fixed with the speed reducer 42 by a key and is positioned by a set screw; the induction sheet 44 is fastened on the end face of the output shaft of the speed reducer 42 through a bolt; the output chain wheel 43 is connected with the crown-tooth chain wheel 37 in the main transmission case 8 through the roller chain 9, and the roller chain 9 can transmit the rotation motion of the output chain wheel 43 to the crown-tooth chain wheel 37;
referring to fig. 36, the counting detection assembly 11 includes a sensing piece 44, a proximity switch 45, and a fixing piece 46; the proximity switch 45 is fixedly connected to one end of a fixing piece 46 through a nut, the other end of the fixing piece 46 is fixedly connected to the structure main body 3 through a bolt, and the position of the proximity switch is close to the sensing piece 44 on the power assembly; the proximity switch 45 can detect the rotation period signal of the sensing piece 44 and transmit the rotation period signal to the control system 4.
When in work:
the invention adopts an eccentric shaft and a crown gear cam mechanism to simulate the recoil of the aircraft cannon, thereby realizing the full-automatic motion simulation of the aircraft cannon; when the device works, the constant-torque motor 41 and the speed reducer 42 drive the output chain wheel 43 to rotate, the output chain wheel 43 rotates to drive the roller chain 9 to rotate, the roller chain 9 rotates to drive the crown-shaped tooth chain wheel 37 to rotate, the crown-shaped tooth chain wheel 37 drives the crown-shaped tooth cam 36 to rotate through crown-shaped teeth on the crown-shaped tooth chain wheel, and the crown-shaped tooth cam 36 rotates to drive the sliding shaft 28 provided with the needle bearing 19, the bolt needle bearing 21 and the swing arm 19 to do linear reciprocating motion; the other end of the sliding shaft 28 passes through a bolt 29 with an interface sleeve 27 and is fixedly connected with an I-th limiting sleeve 30, the interface sleeve 27 and a gun barrel interface 26 are rotationally engaged by 60 degrees through arc teeth and are positioned through a fixing pin 22, the gun barrel interface 26 and the aviation organ gun 1 are fixedly connected through threads, and therefore the sliding shaft 28 moves to drive the gun barrel of the aviation organ gun 1 to reciprocate, so that the loading of recoil of shooting and the recoil of the aviation organ gun is simulated, and the purpose of simulating the full-automatic movement of the aviation organ gun is realized.
Claims (10)
1. The full-automatic motion simulation equipment for the aircraft cannon is characterized by comprising an artillery mounting rack (2), a support table (3), a control system (4), a sliding shaft combination (6), a control display system (7), a main transmission case (8) and a power combination (10);
the artillery mounting rack (2) is positioned on the table top at one end of the support table (3), the control system (4) is positioned in the support table (3), and the main transmission box (8) is positioned on the side face at the other end of the support table (3); the gun body of the machine gun is positioned on the gun mounting rack (2), and the gun barrel is connected with one end of the sliding shaft combination (6);
the main transmission case (8) comprises an eccentric shaft (33), a locking nut (34), a crown gear cam (36) and a crown gear chain wheel (37); the crown gear chain wheel (37) is connected with one end of the eccentric shaft (33) through a key, and the crown gear cam (36) is arranged at the middle eccentric section of the eccentric shaft (33); the crown gear wheel (37) can be meshed with the crown gear cam (36) so as to drive the crown gear cam (36) to rotate; the locking nut (34) is connected with the eccentric shaft (33), and when the locking nut (34) is screwed or loosened, the crown-shaped tooth cam (36) and the crown-shaped tooth chain wheel (37) can be reliably meshed or separated, so that the adjustable travel of the recoil seat of the aircraft cannon is realized;
the power combination (10) is positioned below the main transmission box (8), an output chain wheel (43) of the power combination (10) is connected with a crown-shaped tooth chain wheel (37) of the main transmission box (8) through a roller chain, and the roller chain transmits the rotary motion of the output chain wheel (43) to the crown-shaped tooth chain wheel (37);
the other end of the sliding shaft assembly (6) is connected with the crown-shaped tooth cam (36), and the rotary motion of the crown-shaped tooth cam (36) can be converted into the axial reciprocating motion of the sliding shaft assembly (6), so that the cannon is driven to carry out the axial reciprocating motion;
the control system (4) is used for servo control of the power combination (10);
the control display system (7) can be used for setting or displaying parameter information of movement displacement, speed and period of the aircraft cannon in real time.
2. The automatic motion simulator for aircraft cannons according to claim 1, characterized in that the sliding shaft assembly (6) comprises a quick connection assembly (47), a sliding shaft (28), a needle bearing assembly;
the quick connection combination (47) is used for quickly connecting the mechanical cannon with the sliding shaft (28);
one end of the sliding shaft (28) is provided with a step surface for being matched with the quick connection assembly (47), the other end of the sliding shaft is symmetrically provided with notches along the axis, so that the end is integrally in a convex shape, the convex surface is provided with a through hole, and the axis of the through hole is vertical to the axis of the sliding shaft (28);
the needle bearing assembly is connected to a convex surface at the other end of the sliding shaft (28), and the needle bearing assembly is in contact with inner and outer rolling surfaces of the crown-shaped tooth cam (36) to convert the rotary motion of the crown-shaped tooth cam (36) into the linear reciprocating motion of the sliding shaft (28).
3. The aircraft cannon full-automatic motion simulation equipment as claimed in claim 2, wherein the needle bearing assembly comprises a needle bearing (19), a swing arm (20), a bolt needle bearing (21);
the number of the needle roller bearings (19) is two, and the number of the swing arms (20) is two; the two needle roller bearings (19) are respectively fixedly connected with one ends of the two swing arms (20) on two sides of the convex surface of the sliding shaft (28) through double-end studs, and the double-end studs penetrate through holes in the convex surface of the sliding shaft;
the number of the bolt needle roller bearings (21) is two, the two bolt needle roller bearings are fixedly connected with the other ends of the two swing arms (20) respectively, and the two bolt needle roller bearings (21) are not in contact after being fixedly connected.
4. The automatic motion simulator for aircraft cannons according to claim 3, characterized in that the crown gear cam (36) is inserted into the gap of the bolt needle bearing (21), the bolt needle bearing (21) is in direct contact with the inner rolling surface of the crown gear cam (36), and the needle bearing (19) is in direct contact with the outer rolling surface of the crown gear cam (36); the rotary motion of the crown-shaped tooth cam (36) is converted into the linear reciprocating motion of the sliding shaft (28) through the rolling contact of the needle roller bearing (19) and the bolt needle roller bearing (21) with the inner and outer rolling surfaces of the flange of the crown-shaped tooth cam (36).
5. The aircraft cannon full-automatic motion simulation equipment as claimed in claim 2, wherein the quick connection assembly (47) comprises a positioning pin (22), a positioning pin cover (23), a positioning pin seat (24), a spring (25), a cannon barrel interface (26), an interface sleeve (27), a sliding shaft (28), a bolt (29) and a first limit sleeve (30); a stepped hole is formed in the interface sleeve (27), the interface sleeve (26) can be sleeved at one end of the sliding shaft (28), the first limiting sleeve (30) penetrates through the interface sleeve (27) and is sleeved at one end of the sliding shaft (28), the bolt (29) penetrates through the first limiting sleeve (30) and the end face of the sliding shaft (28) to connect the interface sleeve (27) with the sliding shaft (28), and the interface sleeve (27) can rotate around the central shaft of the sliding shaft (28); one end of the gun barrel interface (26) is inserted into the interface sleeve (27), is connected with the interface sleeve (27) through arc-shaped tooth engagement after rotating and is positioned through the positioning pin (22), and the other end of the gun barrel interface (26) is connected with the aircraft gun through threads; the positioning pin (22) is positioned in positioning holes in the side walls of the interface sleeve (27) and the gun barrel interface (26), the large end of the positioning pin (22) faces downwards, the spring (25) is sleeved on a pin column of the positioning pin (22), the positioning pin seat (24) is fixedly connected to a pin hole in the side wall of the interface sleeve (27) in a welding mode, and the axes of the positioning pin seat and the positioning pin seat are overlapped; the upper end of the positioning pin seat (24) is symmetrically provided with convex shoulders along the axis and matched with a boss at the lower part of the positioning pin cover (23); the positioning pin cover (23) is arranged at the upper end of the positioning pin seat (24) and is connected with the positioning pin (22) through a pin; when the fixing pin cover 22 is pulled upwards and rotated by 90 degrees to enable the boss surface of the positioning pin cover (22) to be in contact with the shoulder surface of the positioning pin seat (24), the interface sleeve (27) and the gun barrel interface (26) can be disengaged; when the locating pin cover (23) is rotated to enable the boss of the locating pin cover (23) to sink into the groove of the locating pin seat (24), the locating pin (22) can sink into the hole of the gun barrel interface (26) to achieve the locating connection between the interface sleeve (27) and the gun barrel interface (26).
6. The aircraft cannon full-automatic motion simulation device as claimed in claim 1, wherein twelve circular arc grooves are formed on the crown gear cam (36), and two crown teeth are formed on the crown gear sprocket (37); when the locking nut (34) is loosened, the crown-shaped toothed cam (36) can slide and is separated from the crown-shaped toothed chain wheel (37), the crown-shaped toothed cam (36) is rotated, twelve arc grooves on the crown-shaped toothed cam (36) can be adjusted to be matched with two crown teeth on the crown-shaped toothed chain wheel (37), six gears can be formed, the change of the included angle between the eccentric shaft (33) and the maximum eccentric line of the crown-shaped toothed cam (36) can be realized, and the adjustment of the output displacement range of the whole mechanism can be realized.
7. The aircraft cannon full-automatic motion simulation device as claimed in claim 1, wherein the power assembly (10) comprises a constant-torque motor (41), a speed reducer (42), and an output sprocket (43); the constant-torque motor (41) is connected with the speed reducer (42), and the output chain wheel (43) is fixedly connected with the speed reducer (42) through a key and is positioned by a set screw; the output sprocket (43) is connected to a crown sprocket (37) in the main drive housing (8) by a roller chain (9), the roller chain (9) transmitting the rotational movement of the output sprocket (43) to the crown sprocket (37).
8. The automatic motion simulator for aircraft cannons according to claim 2, further comprising a support assembly, located between the quick-connect assembly and the needle bearing assembly, for supporting the sliding shaft assembly; the device comprises a supporting seat (16), a linear bearing (17) and a supporting plate (18), wherein the supporting seat (16) is fixedly connected with the supporting plate (18) through a bolt, and the linear bearing (17) is arranged in the supporting seat (16); one end of the sliding shaft (28) penetrates through the linear bearing (17), and the sliding shaft (28) can reciprocate in the linear bearing (17).
9. The automatic motion simulator for aircraft cannons according to claim 1, further comprising a displacement detection assembly comprising a grating ruler (13), a first positioning frame (14), and a second positioning frame (15); one end of the grating ruler (13) is fixedly connected to the side wall of the transmission case main body (31), the first positioning frame (14) and the second positioning frame (15) are in a two-half type, can be sleeved at the other end of the sliding shaft (28), and are fixed through screws and tacking screws; one end of the rod body of the first positioning frame (14) is positioned below the grating ruler (13), and when the sliding shaft (28) does reciprocating motion, the grating ruler (13) can detect the displacement data in real time and transmit the displacement data to the control system (4).
10. The automatic motion simulator for aircraft cannons according to claim 1, characterized in that it further comprises a counting detection assembly comprising a sensing plate (44), a proximity switch (45), a fixing plate (46); the induction sheet (44) is fastened on the end face of the output shaft of the speed reducer (42) through a bolt; the proximity switch (45) is fixedly connected with one end of a fixed sheet (46), the other end of the fixed sheet (46) is fixedly connected with the structure main body (3) through a bolt, and the position of the proximity switch is close to the sensing sheet (44) on the power assembly; the proximity switch (45) can detect a rotation periodic signal of the induction sheet (44) and transmit the rotation periodic signal to the control system (4).
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| CN202110681086.9A CN113503767B (en) | 2021-06-18 | 2021-06-18 | Full-automatic motion simulation equipment for aircraft cannon |
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| CN202110681086.9A CN113503767B (en) | 2021-06-18 | 2021-06-18 | Full-automatic motion simulation equipment for aircraft cannon |
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| CN114152142A (en) * | 2021-10-24 | 2022-03-08 | 西安昆仑工业（集团）有限责任公司 | Manual locking device and locking method for artillery follow-up system |
| CN114894029A (en) * | 2022-05-28 | 2022-08-12 | 西安昆仑工业（集团）有限责任公司 | Aerogun cannon-shot test equipment |
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| CN113503767B (en) | 2023-03-31 |
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