Unmanned aerial vehicle micro weapon system with intelligent observing and hitting integrated function
阅读说明:本技术 一种具备智能察打一体功能的无人机用微型武器系统 (Unmanned aerial vehicle micro weapon system with intelligent observing and hitting integrated function ) 是由 黄春光 邓宏彬 文颀 李科伟 熊镐 潘振华 王迪 于 2019-08-29 设计创作,主要内容包括:本发明涉及武器系统技术领域,尤其是一种具备智能察打一体功能的无人机用微型武器系统,包括三自由度伺服转台、发射舱、光电火控装置、起落架、微型火箭弹,所述三自有度伺服转台上的俯仰轴两端均分别通过法兰固定安装有一个发射舱,且两个所述发射舱对称设置,所述发射舱内均填充有若干微型火箭弹,所述三自由度伺服转台上的悬臂上悬挂有光电火控装置,所述三自由度伺服转台的撑板上通过螺钉固定安装有起落架。本发明具有微型化、轻量化、低成本化、承载能力高的优点。(The invention relates to the technical field of weapon systems, in particular to a miniature weapon system for an unmanned aerial vehicle with an intelligent observing and shooting integrated function, which comprises a three-degree-of-freedom servo turntable, launching cabins, photoelectric fire control devices, landing gears and miniature rocket projectiles, wherein two ends of a pitching shaft on the three-degree-of-freedom servo turntable are respectively and fixedly provided with one launching cabin through flanges, the two launching cabins are symmetrically arranged, the launching cabins are filled with a plurality of miniature rocket projectiles, a cantilever on the three-degree-of-freedom servo turntable is suspended with the photoelectric fire control devices, and the landing gears are fixedly arranged on supporting plates of the three-degree-of-freedom servo turntable through screws. The invention has the advantages of miniaturization, light weight, low cost and high bearing capacity.)
1. The utility model provides a miniature weapon system for unmanned aerial vehicle that possesses integrative function of intelligent investigation, includes three degree of freedom servo revolving stage (1A), launch cabin (2A), photoelectricity fire control device (3A), undercarriage (4A), miniature rocket projectile (5A), a serial communication port, three degree of freedom servo revolving stage (1A) are including roll axle (17), roll axle (17) are a hollow shaft that has two step faces, first step face of roll axle (17) lower part is from up overlapping in proper order down thrust washer (19a), fagging (1), bearing washer (22), roll-over bearing (21), connecting seat (16), go up thrust washer (19b) down, the second step face of roll axle (17) upper portion is from up overlapping in proper order down and is equipped with organism fixing base (20), flange (34) and silica gel pad (18), just organism fixing base (20), The connecting flange (34) and the silica gel pad (18) are both fixed on a rolling shaft (17) through the compression of a fixing nut, a pair of first deep groove bearings (15) is fixedly installed between the connecting seat (16) and the machine body fixing seat (20), an inner gear ring (14) is fixedly installed on the machine body fixing seat (20) close to the inner part of one side of the supporting plate (1), rolling teeth (31) are fixedly installed on the inner side of the inner gear ring (14), the rolling teeth (31) are meshed with the inner gear ring (14), a rolling motor (26) is arranged under the rolling teeth (31), the rolling teeth (31) are fixedly connected onto an output shaft of the rolling motor (26), the rolling motor (26) is fixedly installed on the lower surface of the supporting plate (1), the supporting plate (1) is fixedly connected with the connecting seat (16) through screws, a conductive sliding ring (11) is arranged under the rolling shaft (17), the head of the conductive slip ring (11) is sleeved in the cavity of the rolling shaft (17);
the lower surface of the supporting plate (1) is fixedly connected with two side plates (2) which are symmetrically arranged through screws, two side plates (2) are fixedly supported through two cross beams (7) and four pull rods (50), a bearing hole position is formed in the bottom of each side plate (2), a pitch gear disc (3) and a cantilever gear disc (10) which are symmetrically arranged are fixedly installed in the bearing hole position through a second deep groove bearing (5), a pitch motor (6) is fixedly installed on each cross beam (7), pitch motor teeth (61) are fixedly installed on an output shaft of each pitch motor (6), the pitch gear discs (3) are meshed with the pitch motor teeth (61), another cantilever motor (64) is fixedly installed on each cross beam (7), the installation direction of each cantilever motor (64) is opposite to that of each pitch motor (6), and cantilever motor teeth (75) are fixedly installed on an output shaft of each cantilever motor (64), the cantilever gear plate (10) is meshed with the cantilever motor teeth (75);
a rotating pitch shaft (8) is inserted into central holes in the pitch gear disc (3) and the cantilever gear disc (10), the pitch shaft (8) is a hollow flat shaft, pins (9) which are correspondingly arranged are inserted into the head end and the tail end of the pitch shaft (8), the two pins respectively block the edges of the pitch gear disc (3) and the cantilever gear disc (10), a main cantilever (61) is sleeved in the central hole of the cantilever gear disc (10), a bearing (53) is arranged between the main cantilever (61) and the pitch shaft (8), four bearings (35) are fixedly arranged between matching surfaces of the main cantilever (61) and the cantilever gear disc (10), a slave cantilever (62) is sleeved in the central hole in the outer side of the pitch gear disc (3), and a bearing (53) is arranged between the slave cantilever (62) and the pitch shaft (8);
pitching axis (8) both ends on three degree of freedom servo revolving stage (1A) are equallyd divide and do not have one through flange (13) fixed mounting and launch cabin (2A), and two launch cabin (2A) symmetry sets up, it has a plurality of miniature rocket bullets (5A) all to fill in launch cabin (2A), cantilever (62) on three degree of freedom servo revolving stage (1A) go up to hang photoelectric fire control device (3A), there are undercarriage (4A) through screw fixed mounting on fagging (1) of three degree of freedom servo revolving stage (1A).
2. The micro weapon system for the unmanned aerial vehicle with the intelligent scouting and punching integrated function according to claim 1, wherein the launching cabin (2A) comprises five launching tubes (71), the front end parts of the five launching tubes (71) are sleeved with front end clamps (28) matched with the front end clamps, the middle parts of the five launching tubes (71) are sleeved with middle clamps (29) matched with the middle clamps, the tail parts of the five launching tubes (71) are sleeved with rear end clamps (30) matched with the rear end clamps, two pull rods (12) symmetrically arranged are fixedly installed on the inner side surface of the front end clamps (28), the inner ends of the two pull rods (12) penetrate through the middle clamps (29) and then are fixedly installed on the rear end clamps (30), and flanges (13) are fixedly installed on the outer plane of the middle clamps (29) through screws.
3. The unmanned aerial vehicle micro-weapon system with an intelligent scouting and striking integrated function as claimed in claim 2, wherein said pull rod (12) is a hollow thin-walled metal tube.
4. The unmanned aerial vehicle micro-weapon system with intelligent scouting and batting integrated function as claimed in claim 2, wherein five said launching tubes (71) are all carbon fiber launching tubes.
5. The micro-weapon system for the unmanned aerial vehicle with the integrated intelligent scouting and punching function as claimed in claim 2, wherein the outer surfaces of the front end card (28), the middle card (29) and the rear end card (30) are respectively fixedly provided with a fixing hoop (70) matched with the outer surfaces of the front end card, the middle card (29) and the rear end card through screws, and the width of the fixing hoop (70) on the middle card (29) is larger than the width of the fixing hoop (70) on the front end card (28) and the rear end card (30).
6. The micro-weapon system for the unmanned aerial vehicle with the intelligent scouting and batting integrated function according to claim 1, wherein the micro-rocket projectile (5A) comprises a tail cover (81), a tail wing (82), a rocket engine (83), a warhead (84) and a fuze cabin (85), the fuze cabin (85) is fixedly installed at the top end of the warhead (84) along the axial direction of the projectile body through screws, the rocket engine (83) is fixedly installed at the bottom end of the warhead (83) along the axial direction of the projectile body through screws, the tail wing (82) is fixedly installed on a tail shell of the rocket engine (83), the tail cover (81) is fixedly installed at the tail of the rocket engine (83), and the tail wing (82) is closely attached to the shell of the rocket engine (83) after being accommodated through the tail cover (81).
7. The micro-weapon system for the unmanned aerial vehicle with the intelligent scouting and batting integrated function according to claim 6, wherein the tail wing (82) comprises a connecting shaft (86), a rolling arc wing (87) and a torsion spring (88), four sections of the rolling arc wing (87) are uniformly arranged on the rocket engine (83) shell in an X shape, the root of each rolling arc wing (87) wing is provided with the connecting shaft (86), the rolling arc wing (87) can be rotatably installed on the connecting shaft (86), each section of the rolling arc wing (87) is fixed on a fixing ring of the rocket engine (83) shell in a hole shaft connection mode, and each connecting shaft (86) is provided with one torsion spring (83) in a compression state.
8. The micro weapon system with the intelligent observing and shooting integrated function for the unmanned aerial vehicle as claimed in claim 1, wherein the photoelectric fire control device (3A) comprises a shell (36), a PCB (37), a visible light module (38) and a laser ranging module (39), the PCB (37) is fixedly installed in the shell (36), the visible light module (38) and the laser ranging module (39) are fixedly installed on the PCB (37), the shell (36) comprises a base layer (36a) and a coating layer (36b), the coating layer (36b) is sprayed on the outer surface of the base layer (36a), the base layer (36a) is sequentially provided with a shielding layer (3601), a glass fiber board heat insulation layer (3602), a carbon fiber board layer (3603) and a ceramic fiber board fire-proof layer (3604) from inside to outside, and the coating layer (36b) is sequentially provided with a wear-resistant layer (3605) and a wear-resistant layer (3604) from inside to outside, A reflective layer (3606).
9. The micro-weapon system for unmanned aerial vehicle with intelligent scouting and batting integrated function as claimed in claim 8, wherein said shielding layer (3601) is an electromagnetic shielding film.
10. The micro-weapon system for unmanned aerial vehicle with intelligent scouting and batting integrated function as claimed in claim 8, wherein said wear layer (3605) is epoxy resin coating.
11. The unmanned aerial vehicle micro-weapon system with intelligent scouting and batting integrated function as claimed in claim 8, wherein said reflective layer (3606) is Al2O3 coating.
12. The micro-weapon system for the unmanned aerial vehicle with the intelligent observing and hitting integrated function according to claim 1, wherein the undercarriage (4A) comprises two connecting rods (1101), the two connecting rods (1101) are arranged in parallel, the micro-weapon system is characterized in that shock absorption wrapping feet (1102) are sleeved at two ends of each connecting rod (1101), two three-way connectors (1103) are sleeved on the connecting rods (1101) between the two corresponding shock absorption wrapping feet (1102), each three-way connector (1103) is arranged close to the corresponding shock absorption wrapping foot (1102), each two corresponding three-way connectors (1103) are provided with bent rods (1104) in a matched mode, and two tail ends of each bent rod (1104) are fixed through screws after being inserted into connecting ports of the corresponding three-way connectors (1103).
13. The unmanned aerial vehicle micro-weapon system with intelligent scouting and batting integrated function as claimed in claim 12, wherein said connecting rods (1101) are all carbon fiber tubes.
14. The unmanned aerial vehicle micro-weapon system with the intelligent scouting and batting integrated function as claimed in claim 12, wherein the shock absorption foot wrap (1102) is a soft rubber sleeve, and the shock absorption foot wrap (1102) is in interference fit with the connecting rod (1101).
15. The micro-weapon system for the unmanned aerial vehicle that possesses integrative function of an intelligence scouting and beating of claim 12, characterized in that, curved bar (1104) is aluminum alloy pipe, curved bar (1104) is including straight spool pipe (1106), circular arc pipe (1107), equal fixed mounting has circular arc pipe (1107) on two tip of straight spool pipe (1106), two screw holes (1105) have been opened along the length axis direction to the centre on straight spool pipe (1106).
Technical Field
The invention relates to the technical field of weapon systems, in particular to a micro weapon system for an unmanned aerial vehicle with an intelligent scouting and batting integrated function.
Background
In recent years, micro rotor unmanned aerial vehicles have the characteristics of small volume, low cost, low requirement on take-off and landing sites, convenience in carrying and use, vertical take-off, landing and hovering capabilities, are receiving more and more attention from military, armed police and special public security combat troops, and are widely used for executing light-weight tasks such as aerial photography reconnaissance and field monitoring.
The micro rotor unmanned aerial vehicle has weak impact resistance and very limited load capacity (generally not more than 5kg), how to achieve high integration, observation and beating integration, follow-up stable aiming and stable launching of a weapon system under the condition of adapting to the platform carrying capacity of the unmanned aerial vehicle, is a difficult point for researching a micro airborne intelligent observation and beating integration weapon system, and mainly comprises the following aspects:
(1) at present, the existing unmanned weapon systems at home and abroad are mainly used for ground unmanned platforms, medium and large-sized fixed wing unmanned aerial vehicles and armed unmanned helicopters, the ground unmanned platform weapon systems have better universality and carry more anti-riot bombs or grenades, the fire striking is carried out in a remote control mode, the ground weapon systems and the carried ammunitions thereof have large volume and weight, and the impact on the platforms when the ammunitions are launched is large, so that the load and impact resistance requirements of the micro rotor unmanned aerial vehicles are difficult to meet; large and medium-sized fixed wing unmanned aerial vehicle and unmanned helicopter airborne weapon system of armed need be directed against specific model special design usually, do not have the commonality, it carries the ammunition and usually is accurate guidance ammunition, carry out accurate guidance through unmanned aerial vehicle's self high accuracy optoelectronic device, realize accurate striking, airborne weapon system and carry the ammunition volume, weight are equally very big, and accurate guidance ammunition is with high costs, be difficult to satisfy microminiature rotor unmanned aerial vehicle's load requirement. Therefore, the overall technology of the low-cost and light-weight weapon system becomes the difficulty of the micro-miniature airborne intelligent surveying and striking integrated weapon system.
(2) For a survey and strike integrated weapon system, the quality of the performance of a photoelectric detection system directly influences the strike precision of the weapon system, the current home and abroad high-precision photoelectric detection system is quite mature in technology, but the photoelectric detection system is high in cost, large in size and weight, is generally used for high-value weapon systems such as medium and large unmanned aerial vehicles and strategic tactical missiles, and is a difficult point for researching a micro airborne intelligent survey and strike integrated weapon system, and how to realize the miniaturization, light weight and low cost of the photoelectric detection system on the basis of the existing research.
(3) The weapon system can receive the influence of unmanned aerial vehicle vibration, gesture and wind-force constantly in the course of the work, leads to weapon system aiming line to change along with unmanned aerial vehicle vibration and gesture, influences aim and strikes the precision. Therefore, how to realize the stability of the aiming line of the weapon system with low cost and low weight becomes the difficulty of the micro-miniature airborne intelligent observing and shooting integrated weapon system.
(4) The traditional lethal and non-lethal ammunition has the advantages of large overload, short firing range, high quality, large volume, single damage mode, high cost of accurately guided ammunition and difficulty in realizing miniaturization, so that the micro ammunition technology suitable for the micro unmanned aerial vehicle-mounted platform is also a difficulty for researching a micro airborne intelligent observing and striking integrated weapon system.
At present, many domestic and foreign units develop research work of a microminiature airborne intelligent investigation and shooting integrated weapon system, most of them adopt a mode of directly fixing ammunition on an unmanned aerial vehicle, are equipped with an infrared or visible light lens for remote control monitoring, and realize ammunition emission through a switch or an ignition signal. For example, an FE15 fire-fighting and fire-extinguishing unmanned aerial vehicle system developed by Washel in China in 2018 adopts a rocket launching tube with the diameter of 67mm and filled with a special fire extinguishing agent to be directly carried below a four-rotor fuselage, and the effective range can reach 40 m. In 2018, the QZU-01 armed unmanned aerial vehicle system jointly developed by Shenzhen light technology and Hunan military industry group also directly fixes the grenade launcher with the bottom of the unmanned aerial vehicle and can continuously launch small-caliber grenades forwards. The mode is also basically adopted internationally, for example, a miniature tactical four-rotor unmanned aerial vehicle which is about to be equipped by a Korean army reported in the Jian's defense period of 14 days in 2018 has the maximum takeoff weight of 9kg, carries 2 bombs of 500g, and attacks the bombs in a bomb projection mode.
In summary, the research on the micro unmanned aerial vehicle-mounted scouting and shooting integrated weapon system at home and abroad is still in the starting stage, and the overall technology of a low-cost and light-weight weapon system, the miniaturization, light-weight and low-cost technology of a photoelectric detection system, the aiming line stabilizing technology, the micro ammunition technology suitable for the micro unmanned aerial vehicle-mounted platform and other key technologies and difficulties are required.
The military requirements of air-to-ground reconnaissance and striking tasks are executed by utilizing a microminiature unmanned aerial vehicle in a complex environment during special operations of land, sea and air and stability maintenance of armed polices and anti-terrorism; aiming at the problem that the existing micro unmanned aerial vehicle cannot realize intelligent observing and shooting based on target locking and tracking; on the basis of the existing follow-up control and image processing technology, unmanned intelligent scouting and shooting technical research based on a rocket projectile and weapon system is developed; the method breaks through the unmanned intelligent observing and printing overall technology, the rapid identification and positioning and locking tracking algorithm under the complex background and the follow-up sight-stabilizing control technology; the effect of fighting of carrying out intelligent investigation and play to ground personnel and vehicle is reached.
Disclosure of Invention
The invention aims to solve the defects of large volume, heavy weight, high cost and poor bearing capacity in the prior art, and provides an unmanned aerial vehicle micro-weapon system with an intelligent scouting and hitting integrated function.
In order to achieve the purpose, the invention adopts the following technical scheme:
the design is a micro weapon system for the unmanned aerial vehicle with the intelligent observing and shooting integrated function, which comprises a three-degree-of-freedom servo turntable, a launching cabin, a photoelectric fire control device, an undercarriage and a micro rocket projectile, wherein the three-degree-of-freedom servo turntable comprises a rolling shaft, the rolling shaft is a hollow shaft with two step surfaces, a first step surface at the lower part of the rolling shaft is sequentially sleeved with a lower thrust washer, a supporting plate, a bearing washer, a rolling bearing, a connecting seat and an upper thrust washer from bottom to top, a second step surface at the upper part of the rolling shaft is sequentially sleeved with a machine body fixing seat, a connecting flange and a silica gel pad from bottom to top, the machine body fixing seat, the connecting flange and the silica gel pad are all pressed and fixed on the rolling shaft through fixing nuts, a pair of first deep groove bearings are fixedly installed between the connecting seat and the machine body fixing seat, and an inner gear ring is fixedly, the inner side of the inner gear ring is fixedly provided with rolling teeth, the rolling teeth are meshed with the inner gear ring, a rolling motor is arranged right below the rolling teeth, the rolling teeth are fixedly connected to an output shaft of the rolling motor, the rolling motor is fixedly arranged on the lower surface of a supporting plate, the supporting plate is fixedly connected with a connecting seat through screws, a conductive sliding ring is arranged right below the rolling shaft, and the head of the conductive sliding ring is sleeved in a cavity of the rolling shaft;
the lower surface of the supporting plate is fixedly connected with two symmetrically-arranged side plates through screws, the two side plates are fixedly supported through two cross beams and four pull rods, the bottoms of the side plates are respectively provided with a bearing hole site, a pitch gear disc and a cantilever gear disc which are symmetrically arranged are fixedly arranged in the bearing hole sites through second deep groove bearings, a pitch motor is fixedly arranged on the cross beam, pitch motor teeth are fixedly arranged on an output shaft of the pitch motor, the pitch gear disc is meshed with the pitch motor teeth, a cantilever motor is fixedly arranged on the other cross beam, the installation direction of the cantilever motor is opposite to that of the pitch motor, cantilever motor teeth are fixedly arranged on an output shaft of the cantilever motor, and the cantilever gear disc is meshed with the cantilever motor teeth;
a rotary pitch shaft is inserted into central holes on the pitch gear disc and the cantilever gear disc, the pitch shaft is a hollow flat shaft, pins which are correspondingly arranged are inserted into the head end and the tail end of the pitch shaft, the two pins respectively block the edges of the pitch gear disc and the cantilever gear disc, a main cantilever is sleeved in the central hole of the cantilever gear disc, a bearing is arranged between the main cantilever and the pitch shaft, four keys are fixedly arranged between matching surfaces of the main cantilever and the cantilever gear disc, a slave cantilever is sleeved in the central hole on the outer side of the pitch gear disc, and a bearing is arranged between the slave cantilever and the pitch shaft;
the two ends of the pitching shaft on the three-degree-of-freedom servo rotary table are respectively and fixedly provided with a launching cabin through flanges, the launching cabins are symmetrically arranged, the launching cabins are filled with a plurality of miniature rocket projectiles, a photoelectric fire control device is suspended on a cantilever on the three-degree-of-freedom servo rotary table, and a supporting plate of the three-degree-of-freedom servo rotary table is fixedly provided with an undercarriage through screws.
Preferably, the launching cabin includes including five launching tubes, five the tip cover is equipped with the front end card of looks adaptation with it before the launching tube, five the launching tube middle part cover is equipped with the well card of looks adaptation with it, five the rear end card of looks adaptation with it is equipped with to the launching tube afterbody cover, fixed mounting has two pull rods that the symmetry set up on the inboard surface of front end card, two fixed mounting is on the rear end card after the inboard end of pull rod passes well card, through screw fixed mounting flange on the outside plane of well card.
Preferably, the pull rod is a hollow thin-wall metal tube.
Preferably, all five of the launching tubes are carbon fiber launching tubes.
Preferably, the outer surfaces of the front end card, the middle card and the rear end card are fixedly provided with fixing hoops matched with the front end card, the middle card and the rear end card through screws, and the width of the fixing hoop on the middle card is larger than that of the fixing hoops on the front end card and the rear end card.
Preferably, miniature rocket projectile includes tail-hood, fin, rocket engine, warhead, fuze cabin, the fuze cabin passes through the screw and installs on warhead top along projectile body axial fixity, the rocket engine passes through the screw and installs in warhead bottom along projectile body axial fixity, fin fixed mounting is on rocket engine afterbody shell, rocket engine afterbody fixed mounting has the tail-hood, the fin is taken in the back through the tail-hood and is hugged closely and set up with rocket engine shell.
Preferably, the tail wing comprises a connecting shaft, a plurality of rolling arc wings and torsion springs, the four sections of rolling arc wings are uniformly arranged on the rocket engine shell in an X shape, the root of each rolling arc wing is provided with the connecting shaft, the rolling arc wings can be rotatably arranged on the connecting shaft, each section of rolling arc wing is fixed on a fixing ring of the rocket engine shell in a hole shaft connection mode, and each connecting shaft is provided with one torsion spring in a compression state.
Preferably, the photoelectric fire control device includes casing, PCB board, visible light module and laser rangefinder module, fixed mounting has the PCB board in the casing, fixed mounting has the module of seeing light and laser rangefinder module on the PCB board, the casing includes basic unit, dope layer, basic unit surface spraying has the dope layer, the basic unit is shielding layer, glass fiber board insulating layer, carbon fiber sheet layer, ceramic fiber board flame retardant coating from inside to outside in proper order, the dope layer is wearing layer, reflector layer from inside to outside in proper order.
Preferably, the shielding layer is an electromagnetic shielding film.
Preferably, the wear-resistant layer is an epoxy resin coating.
Preferably, the reflecting layer is an Al2O3 coating.
Preferably, the undercarriage includes two connecting rods, and two the mutual parallel arrangement of connecting rod, its characterized in that, every the both ends of connecting rod all are equipped with the shock attenuation and wrap up in the foot, per two correspond all the cover is equipped with two tee bend connectors on the shock attenuation wraps up in the connecting rod between the foot, and every tee bend connector all wraps up in the foot setting in the shock attenuation of corresponding, per two correspond all mutually support in the tee bend connector and inserted the knee-beam, all pass through the fix with screw after inserting the connector on the tee bend connector that corresponds for two ends of knee-beam.
Preferably, the connecting rods are all carbon fiber tubes.
Preferably, the damping foot wrapping sleeve is a soft rubber sleeve, and the damping foot wrapping sleeve is in interference fit with the connecting rod.
Preferably, the knee is aluminum alloy tube, the knee includes straight spool, circular arc pipe, equal fixed mounting has circular arc pipe on two extremes of straight spool, the centre department is opened along length axis direction on the straight spool has two screw holes.
The invention provides a micro weapon system for unmanned aerial vehicle with intelligent scouting and batting integrated function, which has the advantages that:
1. the overall structure of the three-degree-of-freedom servo weapon system is designed in a light weight, integrated and modularized manner, the overall weight of the weapon system is reduced to 2kg (no rocket bullets) through a large number of finite element optimization designs and industrial-level mature processes in the design process, meanwhile, the weapon system designed by the scheme is provided with 1 deep groove ball bearing assembly along the radial direction of the rolling shaft, and is provided with 2 thrust bearings along the axial direction, so that the weapon system not only can horizontally rotate 360 degrees along the rolling shaft, but also can bear large tensile force and pressure in the axial direction in the rotating process; in the pitching direction of the weapon system, the pitching shaft and the cantilever shaft are concentrically arranged, the concentricity of the two shafts is ensured through the assembly of the deep groove ball bearings, the two shafts can be caused to rotate mutually without mutual interference, the space is saved, the two motors respectively provide power for the two shafts, and the whole transmission structure is compact, small in size and high in bearing capacity.
2. The high-performance photoelectric fire control system based on the servo platform is researched based on industrial CMOS imaging and laser ranging technology, the moving target recognition rate in the moving background reaches more than 70%, the locking tracking speed reaches more than 15 frames/s, and the integration, the light weight and the low cost of the high-performance high-point detection module are realized.
3. The whole rocket projectile is in a modular design and can be quickly installed without tools. The rocket projectile has small size, light weight and small impact on a platform during launching, and is provided with various warheads such as armor piercing, explosion killing, knocking, lacrimation, fuming and the like.
Drawings
Fig. 1 is a schematic three-dimensional structural diagram of a micro-weapon system for unmanned aerial vehicle with an intelligent scouting and batting integrated function according to the present invention;
fig. 2 is a schematic front structural diagram of a micro-weapon system for unmanned aerial vehicle with an intelligent scouting and batting integrated function according to the present invention;
FIG. 3 is a schematic side view of a micro-weapon system for unmanned aerial vehicle with an intelligent scouting and batting integrated function according to the present invention;
fig. 4 is a schematic top view of a micro-weapon system for unmanned aerial vehicle with an intelligent scouting and batting integrated function according to the present invention;
fig. 5 is a schematic view of an installation structure of a pitching motor and a cantilever motor of a three-degree-of-freedom servo turntable according to the present invention;
fig. 6 is a schematic structural diagram of an upper portion of a three-degree-of-freedom servo turntable according to the present invention;
fig. 7 is a schematic view of an installation structure of a cantilever motor tooth and a cantilever gear plate of a three-degree-of-freedom servo turntable according to the present invention;
fig. 8 is a schematic view of an installation structure of a pitch shaft, a main cantilever, and a cantilever gear plate of a three-degree-of-freedom servo turntable according to the present invention;
fig. 9 is a schematic cross-sectional structure diagram of a three-degree-of-freedom servo turntable according to the present invention;
FIG. 10 is a schematic front view of a multi-connected micro rocket projectile launching capsule according to the present invention;
FIG. 11 is a schematic three-dimensional structure diagram of a multi-connected micro rocket projectile launching capsule according to the present invention;
FIG. 12 is a schematic side view of a multi-gang micro rocket projectile launching capsule according to the present invention;
FIG. 13 is a schematic diagram of an outline structure of a photoelectric fire control device according to the present invention;
fig. 14 is a schematic structural diagram of a visible light module of a photoelectric fire control device according to the present invention;
fig. 15 is a schematic structural view of a laser ranging module of a photoelectric fire control device according to the present invention;
FIG. 16 is a schematic diagram of an internal structure of an electro-optical fire control device according to the present invention;
fig. 17 is a schematic diagram of a basic structure of an electro-optical fire control device according to the present invention;
FIG. 18 is a schematic view of a coating layer structure of an electro-optical fire control device according to the present invention;
fig. 19 is a schematic side structure view of a landing frame for a fire percussion platform of a micro unmanned aerial vehicle according to the present invention;
fig. 20 is a schematic front structural view of a landing frame for a fire percussion platform of a micro unmanned aerial vehicle according to the present invention;
fig. 21 is a schematic top view of a landing frame for a fire striking platform of a micro unmanned aerial vehicle according to the present invention;
FIG. 22 is a schematic view of the overall structure of a miniature rocket projectile according to the present invention;
fig. 23 is a schematic view of an internal structure of a micro rocket projectile according to the present invention;
fig. 24 is a schematic view of a tail mounting structure of a micro rocket projectile according to the present invention.
In the figure: three-degree-of-freedom servo turntable 1A, a launching cabin 2A, a photoelectric fire control device 3A, an undercarriage 4A, a miniature rocket projectile 5A, a supporting plate 1, a side plate 2, a rolling gear disc 3, a second deep groove bearing 5, a pitching motor 6, a cross beam 7, a pitching shaft 8, a pin 9, a cantilever gear disc 10, a conductive sliding ring 11, an inner gear ring 14, a connecting seat 16, a rolling shaft 17, a silica gel pad 18, a lower thrust washer 19a, an upper thrust washer 19b, a machine body fixing seat 20, a rolling bearing 21, a rolling motor 26, a Z-shaped plate 27, a retainer ring 32, a connecting flange 34, a pull rod 50, a bearing 53, a main cantilever 61, a secondary cantilever 62, a cantilever motor 64, a waterproof ring 65, a coaming 66, a connecting rod 1101, a damping wrapping foot 1102, a three-way connector 1103, a bent rod 1104, a screw hole 1105, a linear pipe 1106, a bent pipe 1107, a pull rod 12, a flange 13, a front end, The device comprises a launching tube 71, a tail cover 81, a tail wing 82, a rocket motor 83, a warhead 84, a fuze cabin 85, a connecting shaft 86, a rolling arc wing 87, a torsion spring 88, a shell 36, a base layer 36a, a shielding layer 3601, a glass fiber board heat insulation layer 3602, a carbon fiber board layer 3603, a ceramic fiber board fireproof layer 3603, a paint layer 36b, a wear-resistant layer 3605, a reflecting layer 3606, a PCB 37, a visible light module 38 and a laser ranging module 39.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.
Referring to fig. 1-24, a miniature weapon system for unmanned aerial vehicle with intelligent observing and shooting integrated function comprises a three-degree-of-
The three-degree-of-freedom servo turntable 1A comprises a rolling shaft 17, the rolling shaft 17 is a hollow shaft with two step surfaces, a first step surface at the lower part of the rolling shaft 17 is sequentially sleeved with a lower thrust washer 19a, a supporting plate 1, a bearing washer 22, a rolling bearing 21, a connecting seat 16 and an upper thrust washer 19b from bottom to top, a second step surface at the upper part of the rolling shaft 17 is sequentially sleeved with a machine body fixing seat 20, a connecting flange 34 and a silica gel pad 18 from bottom to top, the machine body fixing seat 20, the connecting flange 34 and the silica gel pad 18 are all tightly fixed on the rolling shaft 17 through fixing nuts, a pair of first deep groove bearings 15 are fixedly arranged between the connecting seat 16 and the machine body fixing seat 20, an inner gear ring 14 is fixedly arranged inside one side of the machine body fixing seat 20 close to the supporting plate 1, rolling teeth 31 are fixedly arranged inside the inner gear ring 14, the rolling teeth 31 are meshed with the inner, the rolling teeth 31 are fixedly connected to the output shaft of the rolling motor 26, the rolling motor 26 is fixedly installed on the lower surface of the supporting plate 1, the supporting plate 1 and the connecting seat 16 are fixedly connected through screws, and when the rolling motor 26 works, the supporting plate 1 and the connecting seat 16 can be driven to rotate around the rolling shaft 17. A
the lower surface of the supporting plate 1 is fixedly connected with two symmetrically arranged
a bearing hole position is formed in the bottom of each
the pitch gear plate 3 and the
Two ends of a pitching
The
two symmetrically arranged
the tail ends of the inner sides of the two
the outer surfaces of the front end card 28, the
The
before the rocket projectile is launched, all the winding
The photoelectric
the
the
The
all the cover is equipped with two three
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.
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