CN215794512U - Small-size fixed wing unmanned aerial vehicle launches recovery integrated device - Google Patents
Small-size fixed wing unmanned aerial vehicle launches recovery integrated device Download PDFInfo
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- CN215794512U CN215794512U CN202122475142.1U CN202122475142U CN215794512U CN 215794512 U CN215794512 U CN 215794512U CN 202122475142 U CN202122475142 U CN 202122475142U CN 215794512 U CN215794512 U CN 215794512U
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Abstract
The application discloses a small-sized fixed wing unmanned aerial vehicle ejection and recovery integrated device, which comprises a rotary base mechanism; the ejection rail arm is hinged with the rotary base mechanism, and an ejection rail is arranged along the length direction; the ejection cylinder mechanism is fixedly connected with the ejection rail arm; the telescopic arm mechanism is connected with the ejection track arm; the cantilever seat is arranged at the top end of the telescopic arm mechanism; the bearing trolley is arranged on the ejection track and is connected with the ejection cylinder mechanism through a traction rope; one end of the vertical rope is detachably connected with the bearing trolley, and the other end of the vertical rope is connected with the cantilever mechanism and penetrates through the cantilever mechanism; the ejection cylinder mechanism stretches and retracts to drive the bearing trolley to move along the ejection track. During ejection, the rotary base mechanism is rotated, the front end of the ejection rail arm is adjusted to be declined, the unmanned aerial vehicle can be installed manually, the operation is easy, and the unmanned aerial vehicle is convenient to apply to various operating environments; when retrieving, utilize the cylinder mechanism that launches as buffer, provide effectual buffering for unmanned aerial vehicle's string rope retrieves, simplified the system, improved technical stability and reliability.
Description
Technical Field
The application relates to the technical field of unmanned aerial vehicle take-off and landing support systems, in particular to a small-sized fixed-wing unmanned aerial vehicle catapulting and recovering integrated device.
Background
In the unmanned aerial vehicle field, take off and retrieve two links that are essential in the fixed wing unmanned aerial vehicle application process.
Taking off: the take-off mode of the fixed-wing unmanned aerial vehicle mainly comprises running take-off, rocket boosting take-off, catapult take-off, manual throwing and flying and the like. Large unmanned aerial vehicles generally need to run through a runway for takeoff, medium and small fixed-wing unmanned aerial vehicles mostly adopt rocket boosting or catapult takeoff, and the manual throwing mode is mainly applied to small and miniature unmanned aerial vehicles with smaller weight.
And (3) recovering: the large unmanned aerial vehicle generally adopts runway to descend and retrieve, also can assist through arresting cable, drogue to shorten the aircraft and descend to retrieve the length requirement to the runway.
For the small and miniature unmanned aerial vehicle which is thrown and takes off manually, the mode of parachuting or direct ground landing is mostly adopted.
For medium and small unmanned aerial vehicles, the existing recovery modes mainly include sliding running and landing, parachuting, rope hanging recovery, net collision recovery and the like.
The small-sized fixed wing unmanned machine has the structural characteristics of relatively high body strength and strong overload bearing capacity, and is convenient for quick operation, and mostly adopts application modes of catapult takeoff and vertical rope recovery.
At present, a catapult takeoff and vertical rope recovery system of a small unmanned aerial vehicle mainly comprises a catapult track, a vertical rope hanging arm and an aircraft crane, and three different devices of the catapult track, the vertical rope hanging arm and the aircraft crane are generally arranged on the same or a plurality of bearing chassis.
During catapult-assisted take-off operation, because the catapult track is arranged on the vehicle carrying chassis and extends obliquely upwards to form a certain height, the catapult track is inconvenient for manual operation, and therefore an airplane needs to be hoisted to a bearing trolley on the upper part of the catapult track through an airplane crane;
when the airplane is recovered, the special vertical rope hanging arm is unfolded upwards and hangs a vertical rope, the airplane in flight is hung with the suspended vertical rope through a wing hook, and the vertical rope is buffered through a connecting rubber rope or a spring, so that the recovery operation is realized.
The existing catapult-assisted take-off and vertical rope recovery system is composed of three independent devices, namely a catapult track, a vertical rope hanging arm and an airplane crane, so that the whole system is heavy in weight, large in occupied area and space, too complex in system operation and inconvenient to apply in various scenes such as vehicle-mounted scenes and carrier-borne scenes.
SUMMERY OF THE UTILITY MODEL
For solving the not enough of prior art existence, this application provides a high integrated recovery unit that launches, and the purpose is for small-size fixed wing unmanned aerial vehicle's launch take-off and the rope recovery operation that hangs down, provides a strong adaptability, area occupation space is little, light in weight, easy and simple to handle's launch recovery integrated device.
The technical scheme of the application is as follows:
the application provides a small-size fixed wing unmanned aerial vehicle launches recovery integrated device, include:
a rotating base mechanism; the ejection rail arm is hinged with the rotary base mechanism and is provided with an ejection rail along the length direction; the ejection cylinder mechanism is fixedly connected with the ejection rail arm; the telescopic arm mechanism is connected with the ejection rail arm; the cantilever mechanism is arranged at the top end of the telescopic arm mechanism; the bearing trolley is arranged on the ejection track and is connected with the ejection cylinder mechanism through a traction rope; the ejection cylinder mechanism stretches and retracts to drive the bearing trolley to move along the ejection track; one end of the vertical rope is detachably connected with the bearing trolley, and the other end of the vertical rope is connected with the cantilever mechanism and penetrates through the cantilever mechanism.
Further, the ejection cylinder mechanism comprises a fixed part fixedly arranged on the ejection rail arm and a reciprocating part connected with the fixed part; the fixed part, the reciprocating motion part and the ejection rail arm are symmetrically provided with ejection pulley blocks, the ejection pulley blocks are wound and connected with the traction ropes, the traction ropes are fixedly connected with the bearing trolley, and two ends of the traction ropes are respectively fixedly connected with the reciprocating motion part of the ejection cylinder mechanism.
Further, the fixed part is set as a piston rod, the piston rod is fixedly connected with the ejection rail arm, and the reciprocating part is set as a reciprocating cylinder barrel.
Further, the telescopic arm mechanism comprises at least one telescopic arm which can be telescopic along the length direction; a first hollow cavity and a second hollow cavity are arranged in the ejection rail arm; the telescopic boom mechanism is arranged in the first hollow cavity chamber to form a telescopic boom mechanism; the ejection cylinder mechanism is arranged in the second hollow cavity; the ejection rail arm is provided with the vertical rope guide wheel.
Furthermore, the telescopic arm mechanism comprises a first telescopic arm, a second telescopic arm and a third telescopic arm, the first telescopic arm and the ejection rail arm, the first telescopic arm, the second telescopic arm and the third telescopic arm are in telescopic sliding connection, and can be unlocked or locked through a pin pulling mechanism and a cylinder pin, the third telescopic arm can be sleeved in the second telescopic arm, and the second telescopic arm can be sleeved in the first telescopic arm; the first telescopic arm can be sleeved into the ejection rail arm; the top end of the third telescopic arm is fixedly connected with a cantilever seat; the lower part of the tail end of the third telescopic arm is provided with the vertical rope guide wheel.
Furthermore, the cantilever mechanism comprises a cantilever rod, a cantilever hydraulic cylinder and a rope hanging guide wheel arranged at the tail end of the cantilever rod, the cantilever rod is hinged with the cantilever seat, the cantilever hydraulic cylinder is respectively hinged with the cantilever rod and the cantilever seat, and the cantilever hydraulic cylinder drives the cantilever rod to fold or unfold.
Furthermore, a connecting and supporting assembly is arranged between the cantilever rod and the cantilever seat, and comprises a first connecting frame hinged with the cantilever seat, a second connecting frame hinged with the cantilever rod and a pin shaft arranged between the first connecting frame and the second connecting frame; the cylinder barrel of the cantilever hydraulic cylinder is hinged with the cantilever seat, and the piston rod of the cantilever hydraulic cylinder is hinged with the pin shaft.
Furthermore, the rotary base mechanism comprises a rotary disc, a base support arranged at the upper part of the rotary disc, and a vertical hydraulic mechanism arranged between the base support and the ejection rail arm; two ends of the erecting hydraulic mechanism are respectively hinged with the base support and the ejection rail arm; the ejection rail arm can be tilted relative to the base support angle, and the ejection rail arm can rotate along with the rotary disk.
Furthermore, a damper is fixedly arranged in the ejection rail arm, the damper is a linear stroke elastic damper, ejection pulley blocks are symmetrically arranged on two sides of the stroke end of the damper, the traction rope is pulled by a reciprocating motion part of the ejection cylinder mechanism, and the damper passes through the ejection pulley blocks to drive the traction rope, so that the bearing trolley is driven to move.
Furthermore, the ejection pulley block comprises a guide pulley, a movable pulley and pulleys, the guide pulley is connected with the ejection rail arm, the pulleys are arranged on two sides of the fixed portion of the ejection cylinder mechanism and two sides of the stroke end of the damper, and the movable pulleys are arranged on two sides of two ends of the reciprocating portion of the ejection cylinder mechanism.
The beneficial effect that this application reached does:
through the small-size fixed wing unmanned aerial vehicle launches recovery integrated device that this application embodiment provided, including rotating base mechanism, with erect the articulated rail arm that launches of hydraulic mechanism and rotating base mechanism, launch the rail arm and set up along length direction and launch the track, still include with launch rail arm fixed connection launch cylinder mechanism, with launch the telescopic boom mechanism that the rail arm is connected, set up cantilever seat, bearing trolley and the rope that hangs down on telescopic boom mechanism top. The bearing trolley is arranged on the ejection track and is connected with the ejection cylinder mechanism through a traction rope; one end of the vertical rope is detachably connected with the bearing trolley, and the other end of the vertical rope passes through the vertical rope guide wheel of the cantilever mechanism and is led out; the ejection cylinder mechanism stretches and retracts to drive the bearing trolley to move along the ejection track. Before launching, rotatory rotating base mechanism makes launch the arm rotation to appropriate direction, launches the rail arm front end and has a down dip through erecting hydraulic pressure mechanism adjustment, owing to reduced the height, unmanned aerial vehicle can be installed to the manual work, saves the hoist and mount operation, changes in the operation, has made things convenient for the use under the various operation environment. When retrieving, hang the rope with the couple, the impact force of aircraft is through hanging down the rope and transmitting to the bearing trolley, and the bearing trolley passes through the haulage rope and uses ejection cylinder mechanism to utilize ejection cylinder mechanism as elastic damping device, retrieve for unmanned aerial vehicle's string rope and provide effectual buffering, replaced materials such as rubber rope, spring, the system can furthest's simplification and optimization, has improved technical stability and reliability.
Through technical innovation, this application has realized the integration with many sets of independent equipment such as the necessary bearing trolley of current unmanned aerial vehicle ejection recovery system, recovery arm, loop wheel machine, solves a series of problems such as different equipment mutual interference, operation complicacy, maintenance inconvenience, and the at utmost has realized the lightweight of system, has reduced the manufacturing cost of system, has simplified operation and maintenance.
The technical scheme that this application adopted furthest has reduced volume, weight and the area that launches recovery system, and the on-vehicle installation of both being convenient for is used, satisfies equipment transition operation demand, also is favorable to carrier-borne installation, deployment, provides the assurance for narrow, the unmanned aerial vehicle of hiding the environment such as small-size naval vessel, island reef, jungle, building uses.
This application uses launch rail arm gyration back front end decline to launch backward, embeds flexible arm mechanism and regard as the innovation technique of retrieving buffering damping with launching cylinder mechanism, for the application under all-round, full scene, the various operation environment of small-size fixed wing unmanned aerial vehicle, provides very convenient, reliable guarantee.
Drawings
Fig. 1 is a schematic view of the overall structure of an embodiment of the present application in a storage and transportation mode (vehicle-mounted installation).
Fig. 2 is a schematic view of the overall structure in the ejection operation mode (vehicle-mounted installation) according to an embodiment of the present application.
Fig. 3 is a schematic view of the overall structure (vehicle-mounted installation) in the hanging rope recovery operation mode according to the embodiment of the present application.
Fig. 4 is a schematic overall structure diagram of an embodiment of the present application.
Fig. 5 is a schematic overall structure diagram (a side plate on one side of the ejection rail arm is hidden) of an embodiment of the application.
In the figure, 100, a rotary base mechanism; 110. a rotary disk; 120. a base support; 130. erecting a hydraulic mechanism; 200. ejecting a rail arm; 210. ejecting the track; 220. a hauling rope; 230. a first guide pulley; 240. A second guide pulley; 250. a pulley; 260. a movable pulley; 300. an ejection cylinder mechanism; 400. a telescopic arm mechanism; 410. a first telescopic arm; 420. a second telescopic arm; 430. a third telescopic arm; 440. a cantilever mount; 500. a cantilever mechanism; 510. a cantilever bar; 520. a cantilever hydraulic cylinder; 530. connecting the support component; 531. a first connecting frame; 532. a second link frame; 533. a pin shaft; 540. a vertical rope guide wheel; 600. carrying a trolley; 700. a hanging rope; 800. an unmanned aerial vehicle; 900. a damper.
Detailed Description
The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are 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 construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
It will be understood that when an element is referred to as being "mounted on" another element, it can be directly on the other element or intervening elements may also be present. When a component is referred to as being "disposed on" another component, it can be directly on the other component or intervening components may also be present. When an element is referred to as being "secured to" another element, it can be directly secured to the other element or intervening elements may also be present.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein in the description of the present application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application.
The utility model provides a small unmanned aerial vehicle launches recovery integrated device will launch and the integration of recovery system on same equipment, saves hoisting machine and constructs and retrieve the davit. During ejection, the rotary base mechanism 100 is rotated to drive the ejection rail arm 200, the telescopic arm mechanism 400 and the cantilever mechanism 500 to rotate together, the cantilever mechanism 500 lands on the ground and supports the ground, the trolley is adjusted to one end, close to the telescopic arm mechanism 400, of the ejection rail arm 200, the unmanned aerial vehicle 800 can be installed on the trolley manually, the hoisting mechanism is not needed, the cost is saved, and the size, the weight and the floor area are reduced.
The traction rope 220 is connected with the trolley, the traction rope 220 is connected with the ejection power in a closed-loop connection mode, the connection between the vertical rope 700 and the trolley is increased during recovery, the ejection power can provide power for ejection of the airplane in an ejection link, and elastic buffering force can be provided for airplane recovery in a recovery link.
The following describes in detail a small unmanned aerial vehicle catapulting and recovering integrated device according to an embodiment of the present application with reference to fig. 1 to 5.
The small unmanned aerial vehicle catapulting and recovering integrated device is divided into different modes when in use, and as shown in figures 1-3, the integrated device is respectively in a storage and transportation mode, a catapulting operation mode and a vertical rope recovery operation mode.
The utility model provides a small-size unmanned aerial vehicle launches recovery integrated device mainly comprises rotating base mechanism 100, launches the arm 200, launches cylinder mechanism 300, telescopic boom mechanism 400, cantilever mechanism 500, attenuator 900, bearing trolley 600 and hangs down rope 700 etc..
As shown in fig. 2, the rotating base mechanism 100 can rotate in a horizontal direction, and includes a rotating disk 110, a base support 120 disposed on an upper portion of the rotating disk 110, and a raising hydraulic mechanism 130 disposed between the base support 120 and an ejection rail arm 200. The erecting hydraulic mechanism 130 is used to adjust the vertical angle of the ejector rail arm 200. The erecting hydraulic mechanism 130 is hinged to the base support 120 and the ejection rail arm 200, specifically, the erecting hydraulic mechanism 130 may be a hydraulic cylinder, a piston rod of the hydraulic cylinder is connected to the ejection rail arm 200, a cylinder barrel of the hydraulic cylinder is connected to the base support 120, and the base support 120 is fixed to the rotary disc 110. The bottom of the rotating disk 110 may be attached to a carrying chassis of the device to be connected, the ejection rail arm 200 may be angularly pitched relative to the base support 120, and the ejection rail arm 200 may rotate with the rotating disk 110.
Specifically, the bearing chassis can be vehicle-mounted, is convenient to transport and use, and can also be fixedly arranged on corresponding equipment of a ship, and the purpose of the application is not influenced when the bearing chassis is specifically installed.
The ejection rail arm 200 is provided with an ejection rail 210 along the length direction, and a plurality of groups of guide pulleys are symmetrically arranged on the inner sides of the side walls of the two sides of the ejection rail arm 200.
As shown in fig. 4 to 5, a mounting hole for mounting the ejection pulley block is formed on the side wall of the ejection rail arm 200, and the guide pulley is mounted on the inner wall of the side wall. The guide pulleys include a first guide pulley 230 and a second guide pulley 240, the first guide pulley 230 is installed at both front and rear ends of the side wall of the ejection rail arm 200, the second guide pulley 240 is installed near the damper 900 and the ejection cylinder mechanism 300, and the diameter of the first guide pulley 230 is greater than that of the second guide pulley 240.
A first hollow chamber and a second hollow chamber are formed in the ejection rail arm 200, the second hollow chamber is arranged at the lower part of the first hollow chamber, the telescopic arm mechanism 400 is installed in the first hollow chamber, and the ejection cylinder mechanism 300 and the damper 900 are fixedly installed in the second hollow chamber. The damper 900 is a linear stroke elastic damper.
The pulley 250 and the movable pulley 260 are symmetrically installed on two sides of the ejection cylinder mechanism 300, the pulley 250 is symmetrically installed on two sides of the damper 900, specifically, the pulley 250 is installed on two sides of the fixing portion of the ejection cylinder mechanism 300, the movable pulley 260 is installed on two sides of two ends of the reciprocating portion of the ejection cylinder mechanism 300, and the pulley 250 is installed at the stroke end of the damper 900.
Two ends of the pulling rope 220 are respectively fixedly connected with the reciprocating part of the ejection cylinder mechanism 300, and the reciprocating part of the ejection cylinder mechanism 300 stretches and retracts to drive the bearing trolley 600 to slide along the ejection track 210 through the pulling rope.
As shown in fig. 5, two sides of the bottom of the carrying trolley 600 are respectively fixedly connected with a pulling rope 220, one end of the pulling rope 220 is sequentially wound around a first guide pulley 230 and a second guide pulley 240 at the front end of the side wall of the ejection rail arm 200, a pulley 250 at the stroke end of a damper 900, and a movable pulley 260 on the reciprocating part of the ejection cylinder mechanism 300, and finally is fixedly connected with the reciprocating part of the ejection cylinder mechanism 300, wherein the pulling rope is wound between the pulley 250 at the stroke end of the damper 900 and the movable pulley 260 on the reciprocating part of the ejection cylinder mechanism 300 for multiple times in a reciprocating manner, and the specific number of times is subject to the requirement of increasing range magnification; the other end of the pulling rope 220 is sequentially wound around the first guide pulley 230 and the second guide pulley 240 at the rear end of the side wall of the ejection rail arm 200, the movable pulley 260 at the reciprocating part of the ejection cylinder mechanism 300, the pulley 250 at the fixing part of the ejection cylinder mechanism 300, and finally connected and fixed with the reciprocating part of the ejection cylinder mechanism 300, wherein the pulling rope is wound between the pulley 250 at the fixing part of the ejection cylinder mechanism 300 and the movable pulley 260 at the reciprocating part of the ejection cylinder mechanism 300 in a reciprocating manner for multiple turns, the specific number of turns is consistent with the number of turns of the other end of the pulling rope between the pulley 250 at the stroke end of the damper 900 and the movable pulley 260 at the reciprocating part of the ejection cylinder mechanism 300, and the winding manner is symmetrical.
In this embodiment, the fixed portion of the ejection cylinder mechanism 300 is a piston rod, the reciprocating portion is a reciprocating cylinder, when the reciprocating cylinder of the ejection cylinder mechanism 300 reciprocates, the movable pulley 260 reciprocates along with the reciprocating cylinder, and the traction power is generated by the traction rope 220 to form an ejection stroke, when the device is ejected and recovered, the pneumatic control performance of the reciprocating cylinder is superior to that of the piston rod, because the impact force is large when the airplane is ejected and recovered, and the cylinder pressure needs to be regulated and controlled at any time, such an installation and connection mode is favorable for stably exerting the technical performance of the device.
In order to enlarge the length of the running section of the carrying trolley 600, the pulley 250 and the movable pulley 260 are preferably paired by adopting a plurality of pulley combinations and are used symmetrically front and back.
The telescopic arm mechanism 400 includes at least one telescopic arm that can be extended and retracted inside and outside. When the unmanned aerial vehicle 800 needs to be recovered, the telescopic arm mechanism 400 extends out of the ejection rail arm 200.
As shown in fig. 3, in this embodiment, the telescopic arm mechanism 400 includes a first telescopic arm 410, a second telescopic arm 420 and a third telescopic arm 430, the first telescopic arm 410 and the ejection rail arm 200, the first telescopic arm 410, the second telescopic arm 420 and the third telescopic arm 430 are in telescopic sliding connection, and can be unlocked or locked by a pin pulling mechanism and a cylinder pin, the third telescopic arm 430 can be sleeved in the second telescopic arm 420, the second telescopic arm 420 can be sleeved in the first telescopic arm 410, and the first telescopic arm 410 can be sleeved in the ejection rail arm 200; in order to facilitate connection with the boom mechanism 500, a boom base 440 is fixedly connected to a top end of the third telescopic arm 430, and a rope guide wheel 540 is disposed on a lower wall of the third telescopic arm 430.
As shown in fig. 3 to 4, the boom mechanism 500 is hinged to the boom base 440 and is connected to the telescopic boom mechanism 400 through a boom cylinder 520, and the boom cylinder 520 is used for adjusting an extending angle of the boom 510.
The boom mechanism 500 comprises a boom rod 510, a boom cylinder 520 and a rope guide wheel 540 arranged on the boom rod 510, the boom rod 510 is hinged with a boom seat 440, the boom cylinder 520 is respectively hinged with the boom rod 510 and the boom seat 440, and the boom cylinder 520 drives the boom rod 510 to move.
Specifically, in this embodiment, a connection support assembly 530 is disposed between the cantilever bar 510 and the cantilever base 440, and the connection support assembly 530 includes a first connection frame 531 hinged to the cantilever base 440, a second connection frame 532 hinged to the cantilever bar 510, and a pin 533 disposed between the first connection frame 531 and the second connection frame 532. The cylinder barrel of boom cylinder 520 is fixed to boom base 440, and the piston rod of boom cylinder 520 is fixed to pin 533. Connection supporting component 530 has two effects, the effect is firstly used for the action of linkage cantilever pole 510 at cantilever seat 440, the effect is secondly when unmanned aerial vehicle 800 launches the takeoff, launch rail arm 200 counter rotation, connection supporting component 530 contacts ground and forms the outrigger, it has the space that has the decline to launch rail arm 200 front end, unmanned aerial vehicle 800 launches the takeoff backward from the front end that launches rail arm 200, this ground loading launches unmanned aerial vehicle 800's mode, the hoist and mount operation of aircraft has been avoided, make unmanned aerial vehicle 800 launch the takeoff and easily operate, the manual work is placed and can be realized, greatly made things convenient for the use under the various operational environment. Of course, it should be noted that, when the unmanned aerial vehicle 800 takes off and launches, the declination angle of the launching rail arm 200 may be adjustable, or may be placed in parallel to launch, and is not limited to be placed on the ground to launch, or may be placed on a certain device or platform to take off and launch horizontally or at various angles, which does not affect the protection scope of the present application.
The functional mechanism of each main part is as follows:
1. rotary base mechanism 100:
the swivel base mechanism 100 is used to carry all the equipment and may be mounted on a vehicle, trailer chassis or on a ship deck. The rotary base mechanism 100 is connected with the bearing chassis through a rotary disc 110, and the direction and angle adjustment of the ejection and recovery operation of the whole device are realized through the self-rotation of the rotary base mechanism 100 and the erecting hydraulic mechanism 130. Devices such as air pumps, hydraulic pumps, motors or motors may be integrated into the pivoting base mechanism 100 or the chassis of the vehicle or trailer.
The rotary base mechanism 100 is hinged with the rear part of the ejection rail arm 200 and is connected with the ejection rail arm 200 through the erecting hydraulic mechanism 130, and different operation states of the device, such as horizontal, declination, erecting and the like, can be realized through the extension and retraction of the erecting hydraulic mechanism 130.
2. Ejection rail arm 200:
the ejection rail arm 200 is a main body for bearing the ejection rail 210, the bearing trolley 600, the ejection pulley block, the traction rope 220, the ejection cylinder mechanism 300 and the damper 900.
The ejection rail arm 200 restrains the carrier vehicle 600 through the ejection rail 210, and the carrier vehicle 600 is restrained by the ejection rail 210 and can only move linearly back and forth along the ejection rail 210.
The ejection cylinder mechanism 300 is connected with the bearing trolley 600 through the traction rope 220 and the ejection pulley block, and the ejection cylinder mechanism 300 is used for providing power for the running of the bearing trolley 600 in the ejection process; in the recovery process, the elastic damping device is used for providing elastic damping for recovering the hanging rope through the traction rope 220 and the bearing trolley 600.
In the ejection process, the traction rope 220 is used for transmitting the acting force of the ejection cylinder mechanism 300 to the bearing trolley 600 and providing traction force for the bearing trolley 600 through the guidance of the ejection pulley block; in the recovery process, the pulling rope 220 is used for transmitting the elastic damping acting force of the ejection cylinder mechanism 300 to the bearing trolley 600, and the trolley 600 provides elastic damping force for the vertical rope 700 to absorb the impact energy of the airplane after the airplane hangs the rope.
The ejection rail arm 200 can realize different operation states such as horizontal, declination and erection through the extension and retraction of the erection hydraulic mechanism 130, and the ejection rail arm 200 is linked with the telescopic arm mechanism 400 in the processes of horizontal rotation and vertical pitching.
The ejection rail arm 200 can carry a telescopic arm mechanism 400, and the telescopic arm mechanism 400 is arranged inside the ejection rail arm 200, and the action mechanism of the telescopic arm mechanism is the same as that of a telescopic suspension arm.
3. The carrying trolley 600:
the carrier vehicle 600 is used for carrying and fixing the unmanned aerial vehicle 800, and the carrier vehicle 600 is connected with the ejection track 210 and pulls the carrier vehicle 600 to run along the ejection track 210 through the traction rope 220. The carrier vehicle 600 is provided with locking and unlocking devices of the drone 800. Before launching, unmanned aerial vehicle 800 is locked on bearing trolley 600, when launching with higher speed, haulage rope 220 is from the reverse tractive bearing trolley 600 in rear portion, bearing trolley 600 starts, accelerate and unblock unmanned aerial vehicle 800, it is terminal to launch the stroke, the cylinder receives the stroke restriction, stop the action, and through haulage rope pulling bearing trolley 600 speed reduction, unmanned aerial vehicle 800 breaks away from bearing trolley 600 and begins the autonomous flight, under the inertial action, bearing trolley 600 stretches out the action through haulage rope 220 pulling attenuator 900, attenuator 900 is through the reverse tractive of haulage rope 220, cause the retardation to bearing trolley 600, bearing trolley 600 slows down, stop.
4. Ejection pulley block:
the ejection pulley block comprises a guide pulley, a pulley 250 and a movable pulley 260.
The guide pulley plays a role in guiding and restraining the traction rope 220. The guide pulleys include a first guide pulley 230 and a second guide pulley 240. In order to ensure that the traction rope 220 is not detached from the cable when the corresponding portion is turned, it is preferable that the first guide pulley 230 and the second guide pulley 240 are deep groove pulleys, and the ejection pulley block is provided with a traction rope detachment prevention member.
The pulleys 250 installed at both sides of the fixing portion of the eject cylinder mechanism 300 are used as fixed pulleys; the pulley 250 installed at the stroke end of the damper 900 is normally used as a fixed pulley, but at the rear stage of the ejection action, under the impact pulling action of the carrying trolley 600, the pulley is pulled out together with the stroke end of the damper 900, and can be temporarily converted into a movable pulley for use, so that the damping and buffering effects are achieved.
The movable pulleys 260 are installed at both sides of the movable portion of the ejection pneumatic mechanism and operate together with the cylinder.
5. Telescopic arm mechanism 400:
the telescopic arm mechanism 400 is used to increase the suspension height of the boom mechanism 500 and the drop line 700 so as to provide a sufficient space for airplane recovery.
In the storage and transportation mode of the device, the telescopic arm mechanism 400 is retracted and the ejection rail arm 200 is kept horizontal or the default non-operational state angle of the device.
In the ejection operation mode of the device, the telescopic arm mechanism 400 is retracted, the front end of the ejection rail arm 200 is lowered and tilted to a certain angle, and the airplane is loaded on the bearing trolley 600 at the front end of the ejection rail arm 200 and is ejected backwards along the ejection rail arm 200 to take off.
In the rope-lowering recovery operation mode of the device, the launch rail arm 200 is set to the raising state by the raising hydraulic mechanism 130, the boom state is set by the extendable boom mechanism 400 being extended, the boom mechanism 500 is deployed by the boom cylinder 520, and the rope 700 is lowered by the rope-lowering guide wheel 540.
6. Cantilever mechanism 500:
the cantilever mechanism 500 is used for outwards choosing out the rope 700 that hangs down, makes the rope 700 that hangs down keep away from telescopic boom mechanism 400 to reserve sufficient space for the impact gyration, the swing of rolling after the rope is hung to unmanned aerial vehicle 800, avoid colliding with telescopic boom mechanism 400, interfere.
In the storage, transportation and ejection mode, the cantilever mechanism 500 is in a folded and retracted state.
In the recovery operation mode, the boom mechanism 500 is hydraulically operated by the boom to extend the boom outward, and the droop rope 700 is suspended by the droop rope guide 540.
The vertical rope guide wheel 540 is used for guiding and restraining the vertical rope 700. Preferably, the vertical rope guide 540 mounted on the boom 510 is provided with a retainer for holding the vertical rope 700 along with the boom mechanism 500 without any cable off-line.
7. The carrying trolley 600:
as a carrier of the unmanned aerial vehicle 800, the carrier vehicle 600 is used for carrying the operation of the unmanned aerial vehicle 800 on the ejection rail arm 200, the rear end of the ejection rail arm 200 serves as an ejection departure end, in the ejection process, the carrier vehicle 600 is pulled by the traction rope 220 to rush from the front end of the ejection rail arm 200 to the rear end of the ejection rail arm 200 along the ejection rail 210, and the carrier vehicle decelerates and stops at the rear end to throw the aircraft away.
8. The vertical rope 700:
rope 700 that hangs down is used for unmanned aerial vehicle 800 to retrieve, and under retrieving the operation mode, cantilever mechanism 500 outwards expandes cantilever bar 510 through cantilever hydraulic cylinder 520, hangs down rope 700 through the rope guide wheel 540 that hangs down, and unmanned aerial vehicle 800 hangs down rope 700 and locking through the couple that sets up on unmanned aerial vehicle 800 after the rope 700 contact that hangs down, realizes retrieving the operation. Under the recovery operation mode, the top of the rope 700 that will hang is connected with the dolly, can hang on the dolly through the mode of couple or buckle, and the tail end of the rope 700 that hangs down is fixed subaerial, perhaps stretches out a connecting rod on carrying the car, will hang down the tail end of rope 700 and be connected with the connecting rod that stretches out.
The front end of the cantilever bar 510, the end of the third telescopic arm 430 and the end of the launch rail arm 200 are respectively provided with a plumb line guide wheel 540 for guiding and restraining the plumb line 700.
The action mechanism of each main part is as follows:
1. catapult take-off of the unmanned plane 800:
as shown in fig. 2, the telescopic arm mechanism 400 does not extend out of the ejection rail arm 200, the ejection rail arm 200 transversely rotates to a proper direction, the ejection rail arm 200 is linked with the telescopic arm mechanism 400, the ejection rail arm 200 forms a declination operation state through the extension and retraction of the vertical hydraulic mechanism 130, in order to play a role of stable support, the connection support component 530 can be in contact with the ground, the bearing trolley 600 is adjusted to an ejection initial position, and the unmanned aerial vehicle 800 is mounted and locked on the bearing trolley 600. Wherein, the ejection initial position is the front end of the ejection rail arm 200.
The ejection rail 210 is in a predetermined direction and angle by adjusting the rotary disk 110 of the rotary base mechanism 100 and the erecting hydraulic mechanism 130.
By adjusting the extension length of the telescopic arm mechanism 400, the ejection elevation angle can be appropriately adjusted while the connection support 530 is kept in contact with the ground and plays a role of stable support.
The drone 800 is started, the engine power is increased and set to take-off state.
The carrier vehicle 600 loosens the brake, and meanwhile, the reciprocating cylinder barrel of the ejection cylinder mechanism 300 is controlled to move forwards according to the speed and mode set by the equipment, the unmanned aerial vehicle 800 performs ejection takeoff, and the unmanned aerial vehicle 800 automatically breaks away from the carrier vehicle 600 and enters an autonomous flight state to complete ejection.
2. Returning the ejection system:
the reciprocating cylinder barrel of the ejection cylinder mechanism 300 is operated to run reversely, the carrying trolley 600 is pulled back to the ejection initial position through the traction rope 220, the carrying trolley 600 is braked and locked, and the carrying trolley enters the state to be ejected again.
3. Unmanned aerial vehicle retrieves:
as shown in fig. 3, the ejector rail is erected, the telescopic arm mechanism 400 is extended, the boom shaft 510 of the boom mechanism 500 is unfolded and fixed, and the boom 700 is wound around the boom guide roller 540 of the boom shaft 510. One end of the plumb line 700 is hooked to the load-bearing trolley 600 by passing around the plumb line guide wheel 540 on the first telescopic arm 410 and the plumb line guide wheel 540 at the rear end of the launch rail arm 200, and the other end hangs down.
The rotary disk 110 and the vertical hydraulic mechanism 130 are adjusted, the vertical rope 700 hung under the cantilever rod 510 is hung on the return channel of the unmanned aerial vehicle 800 according to a proper height, and the side surfaces of the ejection rail arm 200, the telescopic arm mechanism 400 and the cantilever rod 510 face the return direction of the unmanned aerial vehicle 800.
When the reciprocating cylinder of the ejection cylinder mechanism 300 is operated to move, the carrying trolley 600 is pulled to the ejection starting position through the pulling rope 220, the ejection cylinder mechanism maintains proper air pressure, and in this state, when the hanging rope 700 pulls the carrying trolley 600 to move towards the ejection direction, the ejection cylinder mechanism 300 generates elastic damping on the hanging rope 700 through the carrying trolley 600.
Operation unmanned aerial vehicle 800 hits according to retrieving the height and hangs down to rope 700, and unmanned aerial vehicle 800 catches on through the hawser hasp and hangs down rope 700, hangs down rope 700 pulling bearing trolley 600 and produces elastic damping, hangs the impact that produces behind the rope and plays cushioning effect to unmanned aerial vehicle 800, through absorbing impact energy, prevents that unmanned aerial vehicle 800 from receiving the impact damage. After the unmanned aerial vehicle 800 is stable, the rotary base mechanism 100, the vertical hydraulic mechanism 130, the telescopic arm mechanism 400, the cantilever rod 510 and the like are operated, the unmanned aerial vehicle 800 is placed to a preset position through adjusting the direction, the height, the posture and the angle, and the recovery is completed.
4. Returning, storing and transporting:
as shown in fig. 1, the reciprocating cylinder of the ejection cylinder mechanism 300 is controlled to stop the carrier vehicle 600 at the ejection end of the ejection rail arm 200, the telescopic arm mechanism 400 retracts into the ejection rail arm 200, and the rotary base mechanism 100 and the erecting hydraulic mechanism 130 are operated to return the ejection and recovery integrated device to a proper storage and transportation state.
The above-described embodiments of the present application do not limit the scope of the present application. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present application shall be included in the scope of the claims of the present application.
Claims (10)
1. The utility model provides a small-size fixed wing unmanned aerial vehicle launches recovery integrated device which characterized in that includes:
a rotating base mechanism (100);
the ejection rail arm (200) is hinged with the rotary base mechanism (100) and is provided with an ejection rail (210) along the length direction;
the ejection cylinder mechanism (300) is fixedly connected with the ejection rail arm (200);
the telescopic arm mechanism (400) is connected with the ejection rail arm (200);
the cantilever mechanism (500) is arranged at the top end of the telescopic arm mechanism (400);
the bearing trolley (600) is arranged on the ejection track (210), and the bearing trolley (600) is connected with the ejection cylinder mechanism (300) through a traction rope (220); the ejection cylinder mechanism (300) stretches and retracts to drive the bearing trolley (600) to move along the ejection track (210);
one end of the vertical rope (700) is detachably connected with the bearing trolley (600), and the other end of the vertical rope is connected with the cantilever mechanism (500) and penetrates through the cantilever mechanism (500).
2. The integrated device for launch and recovery of a small-sized fixed wing drone of claim 1, wherein the launch cylinder mechanism (300) comprises a fixed part fixed to the launch rail arm (200) and a reciprocating part connected to the fixed part;
the ejection pulley block is symmetrically arranged on the fixed portion, the reciprocating motion portion and the ejection rail arm (200), the traction rope (220) is connected to the ejection pulley block in a winding mode, the traction rope (220) is fixedly connected with the bearing trolley (600), and two ends of the traction rope (220) are fixedly connected with the reciprocating motion portion of the ejection cylinder mechanism (300).
3. The integrated device for catapulting and recycling of small-sized fixed wing unmanned aerial vehicles according to claim 2, wherein the fixed part is provided as a piston rod, the piston rod is fixedly connected with the catapulting rail arm (200), and the reciprocating part is provided as a reciprocating cylinder.
4. The integrated catapult-recovery device for small fixed-wing uavs as claimed in claim 1, wherein said telescopic arm mechanism (400) comprises at least one telescopic arm that can be extended and retracted in a length direction;
a first hollow cavity and a second hollow cavity are arranged in the ejection rail arm (200); the telescopic arm mechanism (400) is arranged in the first hollow chamber, and the ejection cylinder mechanism (300) is arranged in the second hollow chamber;
the ejection rail arm (200) is provided with a vertical rope guide wheel (540).
5. The integrated device for launch and recovery of a small-sized fixed wing unmanned aerial vehicle as claimed in claim 4, wherein the telescopic arm mechanism (400) comprises a first telescopic arm (410), a second telescopic arm (420) and a third telescopic arm (430), the first telescopic arm (410) and the launch rail arm (200), the first telescopic arm (410), the second telescopic arm (420) and the third telescopic arm (430) are in telescopic sliding connection, and can be unlocked or locked through a pin pulling mechanism and a cylinder pin, the third telescopic arm (430) can be sleeved in the second telescopic arm (420), the second telescopic arm (420) can be sleeved in the first telescopic arm (410), and the first telescopic arm (410) can be sleeved in the launch rail arm (200); the top end of the third telescopic arm (430) is fixedly connected with a cantilever seat (440); the lower part of the third telescopic arm (430) can be provided with the rope hanging guide wheel (540).
6. The integrated catapulting and recovery device for small-sized fixed wing uavs according to claim 5, wherein the boom mechanism (500) comprises a boom rod (510), a boom cylinder (520) and the rope guide wheel (540) disposed on the boom rod (510), the boom rod (510) is hinged to the boom base (440), the boom cylinder (520) is hinged to the boom rod (510) and the boom base (440), and the boom cylinder (520) drives the boom rod (510) to fold or unfold.
7. The integrated catapult-recovery device for small fixed-wing drones as claimed in claim 6, wherein a connecting support assembly (530) is disposed between the cantilever bar (510) and the cantilever base (440), the connecting support assembly (530) comprises a first connecting frame (531) hinged to the cantilever base (440), a second connecting frame (532) hinged to the cantilever bar (510), and a pin (533) disposed between the first connecting frame (531) and the second connecting frame (532); the cylinder barrel of the cantilever hydraulic cylinder (520) is hinged to the cantilever base (440), and the piston rod of the cantilever hydraulic cylinder (520) is hinged to the pin shaft (533).
8. The integrated catapult-recovery device for small fixed-wing uavs according to claim 1, wherein the rotating base mechanism (100) comprises a rotating disc (110), a base support (120) disposed on the upper portion of the rotating disc (110), and a vertical hydraulic mechanism (130) disposed between the base support (120) and the catapult rail arm (200); the erecting hydraulic mechanism (130) is hinged with the base support (120) and the ejection rail arm (200) respectively; the ejection rail arm (200) is angularly tiltable relative to the base support (120), and the ejection rail arm (200) is rotatable with the rotating disk (110).
9. The integrated device for launch and recovery of a small-sized fixed-wing unmanned aerial vehicle as claimed in claim 2, wherein a damper (900) is further fixedly arranged in the launch rail arm (200), the damper (900) is a linear travel elastic damper, the launch pulley blocks are symmetrically arranged on two sides of a travel end of the damper (900), the reciprocating part of the launch cylinder mechanism (300) pulls the traction rope (220), and the traction rope (220) is driven through the launch pulley blocks of the damper (900), so that the carrying trolley (600) is driven to move.
10. The integrated device for catapulting and recycling of small-sized fixed wing unmanned aerial vehicle as claimed in claim 9, wherein the catapult pulley block comprises a guide pulley, a movable pulley (260) and a pulley (250), the guide pulley is connected with the catapult rail arm (200), the pulley (250) is arranged on two sides of the fixed part of the catapult cylinder mechanism (300) and two sides of the stroke end of the damper (900), and the movable pulley (260) is arranged on two sides of two ends of the reciprocating part of the catapult cylinder mechanism (300).
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| CN202122475142.1U CN215794512U (en) | 2021-10-14 | 2021-10-14 | Small-size fixed wing unmanned aerial vehicle launches recovery integrated device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113815881A (en) * | 2021-10-14 | 2021-12-21 | 青岛启航弹射科技有限公司 | Small-size fixed wing unmanned aerial vehicle launches recovery integrated device |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113815881A (en) * | 2021-10-14 | 2021-12-21 | 青岛启航弹射科技有限公司 | Small-size fixed wing unmanned aerial vehicle launches recovery integrated device |
| CN113815881B (en) * | 2021-10-14 | 2024-08-27 | 青岛启航弹射科技有限公司 | Small-size fixed wing unmanned aerial vehicle catapult recovery integrated device |
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