CN107640330B - Unmanned aerial vehicle jettison device - Google Patents
Unmanned aerial vehicle jettison device Download PDFInfo
- Publication number
- CN107640330B CN107640330B CN201710833746.4A CN201710833746A CN107640330B CN 107640330 B CN107640330 B CN 107640330B CN 201710833746 A CN201710833746 A CN 201710833746A CN 107640330 B CN107640330 B CN 107640330B
- Authority
- CN
- China
- Prior art keywords
- lock
- initial
- elastic rope
- block
- bracket
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Landscapes
- Forklifts And Lifting Vehicles (AREA)
- Toys (AREA)
Abstract
The invention discloses an unmanned aerial vehicle ejection device, which comprises a guide rail, a bracket pulley and an initial elastic rope, and further comprises: a fixed base fixed on the ground; the initial baffle is arranged on the fixed base, and the first end of the initial elastic rope penetrates through the through hole on the initial baffle and is fixedly connected to the fixed base; the initial driving assembly is arranged on the bracket pulley and is connected with the second end of the initial elastic rope, and the initial baffle can separate the initial elastic rope from the bracket pulley; the starting end of the relay elastic rope is positioned in the middle of the guide rail; the top lock is connected with the relay elastic rope and is clamped on the fixed base; the locking device is arranged on the bracket pulley and can lock the top lock; and the disengaging device can disengage the top lock from the fixed base after the locking device locks the top lock. The invention replaces the initial elastic rope with the relay elastic rope to pull the rear half stroke of the bracket pulley, thereby avoiding the situation that the pulling force is greatly reduced.
Description
Technical Field
The invention relates to the technical field of aviation equipment, in particular to an unmanned aerial vehicle ejection device.
Background
The launching of the unmanned aerial vehicle has direct influence on indexes such as battlefield viability, reusability, regional adaptability and use flexibility of the unmanned aerial vehicle system, and is one of the most difficult and critical stages in use. At present, unmanned aerial vehicles have various launching modes, such as ground running takeoff, rocket boosting launching, gas/liquid/electromagnetic launching, vertical takeoff, elastic launching and other launching methods.
The elastic ejection adopts the rubber band as a power source, the equipment development and use cost is low, the adaptability is strong, the device is suitable for the emission of small unmanned aerial vehicles, and the device is an emission mode adopted by most civil unmanned aerial vehicles at present.
The elastic ejection mainly depends on the elasticity of a rubber rope to drive the ejection bracket and the unmanned aerial vehicle to move on the guide rail in an accelerated manner, and when the unmanned aerial vehicle reaches a certain speed at the end point of the guide rail, the unmanned aerial vehicle releases to take off to finish the launching. The elastic rope (hereinafter, referred to as elastic rope for short) of the rubber band is adopted by considering the nonlinear relation between the tension of the rubber material and the stretching length, namely the tension is not greatly increased when the stretching amount is increased after the rubber rope is stretched, and the characteristic of the trend of constant force can fully utilize the length of the guide rail, so that the elastic rope can effectively do work in the whole process of the pulley movement. However, in the practical use of the rubber rope, it is difficult to achieve the ideal constant force characteristic, and the actual measurement shows that the tensile force of the rubber rope continuously increases with the increase of the stretching length, and on the contrary, in the latter half of the pulley pulled by the rubber rope, the tensile force is greatly reduced, and the guide rail stroke is wasted.
The invention aims to solve the technical problem of how to recover the rear half-way pulling force of a bracket pulley by using an elastic rope as a driving element, ensure the take-off speed required by flight power under the condition of not increasing the maximum pulling force due to the limitation of overload strength, reduce the length of a launching guide rail so as to reduce the overall scale of a launching frame and bring convenience to storage, transportation, spreading and use.
Therefore, how to recover the rear half-stroke tension of the bracket pulley when the elastic rope is used as a driving element, so that the takeoff speed required by flight power is ensured under the condition that the maximum tension is not increased due to the limitation of overload strength, and the length of the launching guide rail is reduced, so that the overall scale of the launching cradle is urgently needed to be solved by the technical problem of the technical personnel in the field.
Disclosure of Invention
In view of the above, the present invention provides an unmanned aerial vehicle ejection device, which can recover the tension of the rear half of a carriage pulley when an elastic rope is used as a driving element, so that the takeoff speed required by flight power is ensured under the condition that the maximum tension is not increased due to the limitation of overload strength, and the length of a launching guide rail is reduced, so that the overall scale of a launching frame is reduced.
In order to achieve the above object, the present invention provides the following solutions:
an unmanned aerial vehicle ejection device, comprising a guide rail, a carrier block and an initial elastic rope in a stretched state, wherein the initial elastic rope can pull the carrier block to move on the guide rail, the unmanned aerial vehicle ejection device further comprising:
the fixed base is fixed on the ground;
the initial baffle is arranged on the fixed base, the first end of the initial elastic rope is connected with the fixed base, and the initial elastic rope penetrates through a through hole formed in the initial baffle;
the initial driving assembly is mounted on the bracket trolley and connected with the second end of the initial elastic rope, and the initial baffle can separate the initial elastic rope from the bracket trolley when contacting with the initial driving assembly;
the initial stretching state of the relay elastic rope is consistent with that of the initial elastic rope, the elastic coefficient of the relay elastic rope is consistent with that of the initial elastic rope, and the starting end of the relay elastic rope is positioned in the middle of the guide rail;
the top lock is connected with the first end of the relay elastic rope and is clamped on the fixed base;
the locking device is arranged on the bracket tackle and can lock the top lock;
and the disengaging device can disengage the top lock from the fixed base after the top lock is clamped by the clamping and locking device, and the initial baffle plate is contacted with the initial driving assembly to separate the initial elastic rope from the bracket pulley after the top lock is disengaged from the fixed base.
Preferably, in the above-mentioned unmanned aerial vehicle ejection device, the initial driving assembly includes:
the pull plates are arranged at four corners of the front end surface of the bracket sliding trolley, and the space between the upper pull plate and the lower pull plate can allow the initial baffle to pass through;
the pull plate guide shaft is arranged on the reverse side of the pull plate, and the reverse side of the pull plate is the side, facing the bracket pulley, of the pull plate;
the pull block is provided with an installation through hole, the pull block is slidably installed on the pull plate guide shaft through the installation through hole, and the reverse side of the pull block is connected with the second end of the initial elastic rope.
Preferably, in above-mentioned unmanned aerial vehicle jettison device, still include and establish the top lock card fixing device on unable adjustment base, fixing device includes:
the fixing pile is fixed on the fixing base;
the inclined block is installed at the bottom end of the fixing pile, and the right-angle bottom end of the inclined block is connected with the fixing base through a first compression spring;
the retaining shaft is slidably connected with the top lock, a first guide hole is formed in the top of the fixing pile, the retaining shaft can be slidably mounted in the first guide hole, the bottom end of the retaining shaft is fixed with the inclined surface of the inclined block, and the separating device can extrude the inclined block to separate the top lock from the retaining shaft in a sliding mode.
Preferably, in the above-mentioned unmanned aerial vehicle ejection device, the top lock includes:
the lock seat is provided with a second guide hole, the top end of the baffle shaft penetrates through the second guide hole, the lock seat is pressed at the top end of the fixing pile, the thickness of the lock seat is smaller than the height of the inclined block, and the first end of the relay elastic rope is connected with the lock seat;
the lock head is arranged on the lock seat, and the locking device can lock the lock head.
Preferably, in the unmanned aerial vehicle ejection device, a sliding linear bearing or a rolling linear bearing is mounted in the first guide hole and the second guide hole.
Preferably, in the unmanned aerial vehicle ejection device, the top lock further comprises a lock rod;
one end of the lock rod is connected with the lock head, the other end of the lock rod is connected with the lock seat, and the length of the lock rod is larger than the length of the bottom edge of the inclined block along the direction of the guide rail.
Preferably, in the above-mentioned drone launcher, the latch device includes:
the cross section of each clamping block is triangular, the inclined surfaces of the 2 clamping blocks are arranged face to face, the first right-angle surface of each clamping block is arranged in parallel with the corresponding guide rail, and the distance value between the clamping blocks is gradually increased along the direction from the clamping blocks to the lock head;
the second compression spring is connected with the clamping blocks, the second compression spring can enable the 2 clamping blocks to be close to each other, and the lock head can push the clamping blocks open and is clamped on the second right-angle surfaces of the clamping blocks along the clamping grooves.
Preferably, in the above-mentioned drone launcher, the latch device further comprises:
a fixture block guide sleeve arranged on the bracket pulley;
and when the clamping blocks move mutually under the action of the lock head, the clamping block guide shaft can slide in the clamping block guide sleeve.
Preferably, in the above unmanned aerial vehicle ejection device, the cross section of the lock head along the direction of the guide rail is trapezoidal, the width of the lock head gradually decreases along the direction from the lock head to the fixture block, and the trapezoidal inner angle of the lock head is the same as the inner angle of the fixture block.
Preferably, in the above-mentioned unmanned aerial vehicle ejection device, the disengaging device includes:
a press roll bracket mounted on the carriage block;
and the compression roller is arranged on the compression roller bracket and can press down the inclined block, so that the blocking shaft can be separated from the lock seat.
According to the technical scheme, when the unmanned aerial vehicle ejection device disclosed by the invention is used, the initial elastic rope in a pre-stretching state drives the initial driving assembly to move, and the initial driving assembly is arranged on the bracket pulley, so that the initial elastic rope drives the bracket pulley to move; after the top lock is clamped on the clamping and locking device of the bracket pulley, the top lock is separated from the fixed base by the separation device, and then the initial baffle is contacted with the initial driving assembly to separate the initial elastic rope from the bracket pulley, so that the relay elastic rope in the stretching state can be contracted to continuously drive the bracket pulley to move along the guide rail. The starting end of the relay elastic rope is positioned in the middle of the guide rail, namely the relay elastic rope continuously drives the bracket pulley to run for the other half stroke of the guide rail through the relay elastic rope after the initial elastic rope drives the bracket pulley to run for half of the stroke of the guide rail. The invention discloses an unmanned aerial vehicle ejection device, which enables a bracket pulley bearing an unmanned aerial vehicle to slide along a guide rail from the starting point of a launching frame in an accelerating way under the driving of an initial elastic rope, when the pretension of the initial elastic rope is reduced in the midway of the movement of the bracket pulley to a stroke, a relay elastic rope is switched to replace the initial elastic rope to pull the bracket pulley to run, the initial elastic rope is separated from the bracket pulley, the relay elastic rope has the same initial pretension as the initial elastic rope, and the bracket pulley is continuously pulled to advance in an accelerating way until the end point of the guide rail, so that the ejection is finished. The rear half stroke of the bracket pulley is pulled by replacing the initial elastic rope with the relay elastic rope, so that the situations that the pulling force is greatly reduced and the guide rail stroke is wasted are avoided. The technical problem of the rear half-way pulling force of the bracket pulley is recovered, so that the takeoff speed required by flight power is ensured under the condition that the maximum pulling force is not increased due to the limitation of overload strength, the length of the launching guide rail is reduced, the overall scale of the launching rack is reduced, and convenience is brought to storage, transportation, spreading and use.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic structural diagram of an unmanned aerial vehicle ejection device provided by the invention.
Wherein, in fig. 1:
the device comprises a guide rail 1, a bracket pulley 2, an initial elastic rope 3, a fixed base 4, an initial baffle 5, an initial driving assembly 6, a relay elastic rope 7, an ejector lock 8, a latch device 9, a disengaging device 10, a pulling plate 601, a pulling plate guide shaft 602, a pulling block 603, a fixing device 11, a fixed pile 1101, an inclined block 1102, a baffle shaft 1103, a first compression spring 1104, a lock seat 801, a lock head 802, a lock rod 803, a fixture block 901, a second compression spring 902, a fixture block guide sleeve 903, a fixture block guide shaft 904, a compression roller bracket 1001 and a compression roller 1002.
Detailed Description
In order to make the technical solutions of the present invention better understood, the present invention will be further described in detail with reference to the accompanying drawings and specific embodiments.
Example one
As shown in fig. 1, the invention discloses an unmanned aerial vehicle ejection device, wherein the unmanned aerial vehicle ejection device comprises a guide rail 1, a bracket pulley 2, an initial elastic rope 3, a fixed base 4, an initial baffle 5, an initial driving assembly 6, a relay elastic rope 7, a top lock 8, a locking device 9 and a disengaging device 10.
The initial bungee cord 3 is in tension and is able to pull the carriage trolley 2 to move on the guide rail 1. The tension of the initial elastic rope 3 in the first half stroke of the guide rail 1 is basically not changed along with the change of the length, namely the tension value tends to be stable in the first half stroke of the guide rail 1.
The fixed base 4 is fixed on the ground and is positioned between the two guide rails 1.
The initial baffle 5 is arranged on the fixed base 4, and the first end of the initial elastic rope 3 is connected with the fixed base 4 and passes through a through hole arranged on the initial baffle 5.
The initial driving assembly 6 is fixedly installed on the bracket pulley 2 and connected with the second end of the initial elastic rope 3, and when the initial baffle 5 is in contact with the initial driving assembly 6, the initial baffle 5 can separate the initial elastic rope 3 from the bracket pulley 2.
The relay elastic rope 7 is the same as the initial elastic rope 3, namely the initial stretching state of the relay elastic rope 7 is the same as the initial state of the initial elastic rope 3, the elastic coefficient of the relay elastic rope 7 is the same as the elastic coefficient of the initial elastic rope 3, the starting end of the relay elastic rope 7 is positioned in the middle of the guide rail 1, and the relay elastic rope 7 replaces the initial elastic rope 3 to drive the rear half stroke of the bracket pulley 2 on the guide rail 1.
The top lock 8 is connected with the first end of the relay elastic rope 7, and the top lock 8 is clamped on the fixed base 4. A latch device 9 is mounted on the carriage block 2, and the latch device 9 can latch the top lock 8. After the locking device 9 locks the top lock 8, the disengaging device 10 can disengage the top lock 8 from the fixed base 4, so that the relay elastic rope 7 can drive the bracket pulley 2 to move. And when the top lock 8 is separated from the fixed base 4, the initial baffle 5 is contacted with the initial driving assembly 6, so that the initial elastic rope 3 is separated from the bracket pulley 2.
When the unmanned aerial vehicle ejection device disclosed by the invention is used, the initial elastic rope 3 in a pre-stretching state drives the initial driving assembly 6 to move, and the initial driving assembly 6 is arranged on the bracket pulley 2, so that the initial elastic rope 3 drives the bracket pulley 2 to move; after the top lock 8 is clamped on the clamping lock device 9 of the bracket pulley 2, the separation device 10 separates the top lock 8 from the fixed base 4, and then the initial baffle 5 contacts with the initial driving component 6 to separate the initial elastic rope 3 from the bracket pulley 2, so that the relay elastic rope 7 in the stretching state can be contracted to continue to drive the bracket pulley 2 to move along the guide rail 1. Because the starting end of the relay elastic rope 7 is located in the middle of the guide rail 1, namely, after the initial elastic rope 3 drives the bracket pulley 2 to run for half of the travel of the guide rail 1, the relay elastic rope 7 continuously drives the bracket pulley 2 to run for the other half of the travel of the guide rail 1. The invention discloses an unmanned aerial vehicle ejection device, which enables a bracket pulley 2 bearing an unmanned aerial vehicle to slide along a guide rail 1 from the starting point of a launcher in an accelerating manner under the driving of an initial elastic rope 3, when the bracket pulley 2 moves to the midway of a stroke and the pretension of the initial elastic rope 3 is reduced, a relay elastic rope 7 is switched to replace the initial elastic rope 3 to pull the bracket pulley 2 to run, the initial elastic rope 3 is separated from the bracket pulley 2, the relay elastic rope 7 has the same initial pretension as the initial elastic rope 3, and the bracket pulley 2 is continuously pulled to move forward in an accelerating manner until the end point of the guide rail 1, so that the ejection is completed. The relay elastic rope 7 replaces the initial elastic rope 3 to pull the rear half stroke of the bracket pulley 2, so that the situation that the pulling force is greatly reduced and the stroke of the guide rail 1 is wasted is avoided. The technical problem of the rear half-way tension of the bracket pulley 2 is recovered, so that the takeoff speed required by flight power is ensured under the condition that the maximum tension is not increased due to the limitation of overload strength, the length of the launching guide rail 1 is reduced, the overall scale of the launching frame is reduced, and convenience is brought to storage, transportation, spreading and use.
Example two
In the second embodiment provided by the present invention, the structure of the ejection device for an unmanned aerial vehicle in this embodiment is similar to that of the ejection device for an unmanned aerial vehicle in the first embodiment, and the same parts are not repeated, and only differences are introduced.
In this embodiment, it is whole to be symmetrical overall arrangement to disclose unmanned aerial vehicle jettison device. The 2 basic configurations of bracket coaster include roof and curb plate, and the inner space that forms has certain height for arrange initial drive assembly 6, kayser device 9 and disengaging device 10, its roof upper portion space arranges concrete bearing structure according to different grade type unmanned aerial vehicle's transmission demand, and the coaster is built the skeleton by the roof beam section bar, is equipped with panel and accomplishes, and its material is steel or aluminium.
In the present embodiment, it is specifically disclosed that the initial drive assembly 6 includes a pulling plate 601, a pulling plate guide shaft 602, and a pulling block 603.
Wherein, the pulling plates 601 are installed at four corners of the front end surface of the bracket pulley 2, the space between the upper pulling plate 601 and the lower pulling plate 601 can allow the initial baffle 5 to pass through, and the front end surface of the bracket pulley 2 refers to the surface of the bracket pulley 2 facing the fixed base 4. The pulling plate guide shaft 602 is installed on the reverse side of the pulling plate 601, which is the side of the pulling plate 601 facing the carriage block 2. The pull block 603 is provided with a mounting through hole, the pull block 603 is slidably mounted on the pull plate guide shaft 602 through the mounting through hole, and the reverse side of the pull block 603 is connected with the second end of the initial elastic rope 3. When the bracket pulley 2 moves to the position where the initial baffle 5 contacts the pull block 603, the initial baffle 5 blocks the pull block 603, so that the pull block 603 falls off from the pull plate guide shaft 602, and since the reverse side of the pull block 603 is connected with the second end of the initial elastic rope 3, the initial baffle 5 is connected with the first end of the initial elastic rope 3, so that the initial elastic rope 3 is separated from the bracket pulley 2. Specifically, the initial baffle 5 is an inverted L-plate.
It should be noted that the pulling plate 601 may be disposed at any position where the strength of the boundary between the top plate and the side plate of the carriage 2 (i.e. the front end surface of the carriage 2) is high, and may be disposed at the middle or rear end of the carriage 2, or even outside the side plate of the carriage 2, as long as the carriage does not interfere with other components during the traveling process. The pulling plate 601 is connected with the pulley by welding or bolts, if triangular reinforcing ribs can be added on the outer side of the pulley by the pulling plate 601, the pulling plate 601 is made of steel or aluminum. Correspondingly, the pull block 603, the pull plate guide shaft 602 and the initial baffle 5 are arranged according to the inner or outer position of the pull plate 601, the pull plate guide shaft 602 is connected with the pull plate 601 by bolts or nuts, the pull plate guide shaft 602 is perpendicular to the pull plate 601 during assembly and adjustment, the pull plate guide shaft 602 forms large clearance fit in a mounting through hole formed in the pull block 603, the pull block 603 can freely move under the constraint of the two pull plate guide shafts 602, the pull plate guide shaft 602 is made of smooth steel columns, and the pull block 603 is made of aluminum materials. If the pulling plate 601 is arranged on the outer side of the bracket pulley 2, the initial baffle 5 is fixed on the base on the outer side of the guide rail 1, the cantilever faces the inner side, a round hole is formed in the cantilever of the initial baffle 5 and used for penetrating through the initial elastic rope 3, buffer rubber can be pasted at the impact part of the initial baffle 5 and the pulling block 603, and the baffle is made of a steel plate or an aluminum plate and is fixed on the base through bolts.
Further, the invention discloses an unmanned aerial vehicle ejection device, which further comprises a fixing device 11 for clamping the top lock 8 on the fixing base 4.
The particular fixture 11 includes a spud 1101, a ramp 1102, and a stop shaft 1103. The spud 1101 is 2 inverted L-shaped blocks, the cantilevers of the L-shaped blocks are arranged face to face, and the spud 1101 is fixed on the fixed base 4. The inclined block 1102 is installed at the bottom end of the cantilever with the inclined surface of the inclined block 1102 facing the carriage pulley 2 in the initial state, and the right-angled bottom end of the inclined block 1102 is connected with the stationary base 4 by a first compression spring 1104. The blocking shaft 1103 can be slidably connected with the top lock 8, the top of the fixing pile 1101 is provided with a first guide hole, the blocking shaft 1103 can be slidably mounted in the first guide hole, the bottom end of the blocking shaft 1103 is fixed with the inclined surface of the inclined block 1102, and the disengaging device 10 can slidably disengage the top lock 8 from the blocking shaft 1103 by extruding the inclined block 1102. Specifically, the inclined block 1102 moves downward under the pressing action of the disengaging device 10, and drives the blocking shaft 1103 to slide away from the top lock 8.
Further, the present invention discloses that the top lock 8 comprises a lock housing 801 and a lock head 802. Wherein, the lock seat 801 is provided with a second guide hole, the top end of the stop shaft 1103 passes through the second guide hole, and the lock seat 801 is pressed on the top end of the fixing pile 1101, the thickness of the lock seat 801 is smaller than the height of the inclined block 1102, and the first end of the relay elastic rope 7 is connected with the lock seat 801. The lock head 802 is mounted on the lock housing 801 and the latch device 9 is capable of locking the lock head 802.
The invention also discloses that the top lock 8 further comprises a lock rod 803. One end of the lock rod 803 is connected with the lock head 802, the other end of the lock rod 803 is connected with the lock seat 801, and the length of the lock rod 803 is greater than the length of the bottom edge of the inclined block 1102 along the direction of the guide rail 1, so that when the lock head 802 is clamped in the locking device 9, the bracket pulley 2 does not interfere with the fixing pile 1101.
In order to make the blocking shaft 1103 smoothly come out under the action of the disengaging device 10, the invention discloses that a sliding linear bearing or a rolling linear bearing is installed in the first guide hole and the second guide hole.
In this embodiment, the lock head 802, the lock rod 803 and the lock seat 801 are of an integral structure and made of steel. The stop shaft 1103 is a steel light column, and is fitted in the through hole of the inclined block 1102, and the lower end of the stop shaft is fixed by a nut, so that the stop shaft 1103 can be conveniently replaced and disassembled. The length of the lock bar 803 is greater than the length of the bottom edge of the inclined block 1102 along the direction of the guide rail 1, and the height of the inclined block 1102 is greater than the thickness of the lock base 801. After assembly, each matched part is finely adjusted, the bracket pulley 2 is manually pushed, so that the top lock 8 is smoothly pushed into the clamping and locking device 9, the disengaging device 10 presses the inclined block 1102, and the time sequence connection is accurate.
The invention specifically discloses that the latch device 9 comprises a second compression spring 902 and 2 blocks 901. The cross section of the fixture block 901 is triangular, the inclined surfaces of 2 fixture blocks 901 are arranged face to face, the first right-angle surface of the fixture block 901 is arranged parallel to the guide rail 1, and the distance between the fixture blocks 901 is gradually increased along the direction from the fixture block 901 to the lock head 802. The second compression spring 902 is connected with the fixture block 901, and the second compression spring 902 can enable the 2 fixture blocks 901 to approach each other, and the lock head 802 can eject the fixture block 901 and is clamped on a second right-angle surface of the fixture block 901 along the fixture groove.
Further, the invention discloses that the locking device 9 further comprises a fixture block guide sleeve 903 and a fixture block guide shaft 904. Wherein, the fixture block guide 903 is installed on the bracket pulley 2, the fixture block guide shaft 904 is installed on the fixture block 901, and when the fixture block 901 moves mutually under the action of the lock head 802, the fixture block guide shaft 904 can slide in the fixture block guide 903.
The cross section of the lock head 802 along the direction of the guide rail 1 is trapezoidal, the width of the lock head 802 is gradually reduced along the direction from the lock head 802 to the fixture block 901, the inner angle of the trapezoid of the lock head 802 is the same as the inner angle of the fixture block 901, the smooth finish of the inclined surface of the lock head 802 is improved, and hardening treatment is performed.
The fixture block 901 is made of steel, the working inclined plane and the inner groove have certain smoothness and are subjected to hardening treatment such as quenching treatment, the included angle between the two inclined planes is 30-60 degrees, and lubricating grease is coated on the surface of the inner groove. The cartridge guide shaft 904 is a steel optical shaft, and the external threads at the end are screwed into the internal threads on the side surface of the cartridge 901. The cartridge guide shaft 904 is fixedly connected to the underside of the top plate of the carrier block 2 by means of a collar or flange, and is internally provided with a sliding or ball linear bearing which is axially movably engaged with the guide shaft. The second cable pressing spring has smaller rigidity, so that the fixture block 901 cannot be separated due to vibration in the process that the top lock 8 pulls the bracket pulley 2 to move forwards, and the fixture block 901 can just clamp the lock head 802. The inner grooves of the two latch blocks 901 form a large clearance fit with the lock rod 803, and the lock rod 803 can freely move in the grooves of the latch blocks 901 along the direction of the guide rail 1.
It should be noted that the latch device 9 and the top lock 8 may be provided in the form of a snap connection.
Further, the present invention discloses that the detaching means 10 includes a pressure roller holder 1001 and a pressure roller 1002. Wherein, the pressure roller bracket 1001 is installed on the carriage 2 and is a rectangular frame, and the pressure roller 1002 is installed on the pressure roller bracket 1001. The pressure roller 1002 can press down the inclined block 1102 so that the blocking shaft 1103 can be disengaged from the latch base 801. The distance between the cantilevers of the L-shaped blocks is larger than the length of the compression roller bracket 1001 and the compression roller 1002, that is, the compression roller bracket 1001 and the compression roller 1002 can pass between the cantilevers of the L-shaped blocks along with the carriage block 2 after the lock housing 801 and the fixing pile 1101 are disengaged.
It is also possible to provide the roller holder 1001 in an L-shape and the spud 1101 in an inverted L-shape so that the roller holder 1001 can pass smoothly under the spud 1101.
When the unmanned aerial vehicle ejection device disclosed by the invention is used, the initial elastic rope 3 in a pre-stretching state drives the pull block 603 to move, and the pull block 603 is clamped on the pull plate 601, and the pull plate 601 is arranged on the bracket pulley 2, so that the initial elastic rope 3 drives the bracket pulley 2 to move. When the bracket pulley 2 moves forward and touches the top lock 8, the side inclined surface of the lock head 802 and the inner inclined surface of the fixture block 901 generate impact contact, under the action of the inertia force of the bracket pulley 2 and the residual tension of the initial elastic rope 3, the top lock 8 resists the pressure of the second compression spring 902 to push the fixture block 901 open towards two sides until the lock head 802 completely crosses the narrow-edge bayonet formed by the two fixture blocks 901, the second compression spring 902 rebounds the fixture block 901, and at the moment, the inner groove at the inclined surface of the fixture block 901 surrounds the lock rod 803 and forms sliding fit, so as to bear the offset load moment generated by the relay elastic rope 7 when the baffle shaft 1103 is pulled away from the lock seat 801; following this operation, the pressing roller 1002 fixed to the carriage pulley 2 via the pressing roller bracket 1001 reaches the inclined block 1102, the carriage pulley 2 moves forward, the pressing roller 1002 presses the inclined surface to move downward, and the stopper shaft 1103 is finally pulled out from the lock seat 801. At this time, the top lock 8 drawn by the relay elastic rope 7 is not restrained by the fixing pile 1101 any more, but is clamped by the narrow edge of the clamping block 901 on the bracket pulley 2, so that continuous force butt joint is realized. At the end of the continuous force action, the bracket pulley 2 reaches the initial baffle 5 fixed on the base, the cross arm of the initial baffle 5 passes through the gap of the pull plate 601 in front of the pulley and stops the pull block 603, while the bracket pulley 2 is separated from the pull block 603 connected with the initial elastic rope 3, and under the traction of the relay elastic rope 7, the bracket pulley 2 continues to move forward through the butt joint force transmission of the top lock 8 and the fixture block 901. The invention discloses an unmanned aerial vehicle ejection device, which enables a bracket pulley 2 bearing an unmanned aerial vehicle to slide along a guide rail 1 from the starting point of a launcher in an accelerating manner under the driving of an initial elastic rope 3, when the bracket pulley 2 moves to the midway of a stroke and the pretension of the initial elastic rope 3 is reduced, a relay elastic rope 7 is switched to replace the initial elastic rope 3 to pull the bracket pulley 2 to run, the initial elastic rope 3 is separated from the bracket pulley 2, the relay elastic rope 7 has the same initial pretension as the initial elastic rope 3, and the bracket pulley 2 is continuously pulled to move forward in an accelerating manner until the end point of the guide rail 1, so that the ejection is completed. The rear half stroke of the pulley is pulled by the relay elastic rope 7 instead of the initial elastic rope 3, so that the situations that the pulling force is greatly reduced and the stroke of the guide rail 1 is wasted are avoided. The technical problem of the rear half-way tension of the bracket pulley 2 is recovered, so that the takeoff speed required by flight power is ensured under the condition that the maximum tension is not increased due to the limitation of overload strength, the length of the launching guide rail 1 is reduced, the overall scale of the launching frame is reduced, and convenience is brought to storage, transportation, spreading and use.
The terms "first", "second", and the like in the present invention are used for descriptive distinction and have no other special meaning.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and inventive features disclosed herein.
Claims (10)
1. An unmanned aerial vehicle jettison device, includes guide rail (1), bracket coaster (2) and is in tensile state initial stretch cord (3), wherein, initial stretch cord (3) can pull bracket coaster (2) and move on guide rail (1), its characterized in that still includes:
the fixed base (4), the said fixed base (4) is fixed on the ground;
the initial baffle (5) is installed on the fixed base (4), the first end of the initial elastic rope (3) is connected with the fixed base (4), and the initial elastic rope (3) penetrates through a through hole formed in the initial baffle (5);
an initial driving assembly (6), wherein the initial driving assembly (6) is installed on the bracket pulley (2) and connected with the second end of the initial elastic rope (3), and the initial baffle (5) can separate the initial elastic rope (3) from the bracket pulley (2) when being contacted with the initial driving assembly (6);
the relay elastic rope (7) is in the same initial stretching state as the initial elastic rope (3), the elastic coefficient of the relay elastic rope (7) is in the same elastic coefficient as the initial elastic rope (3), and the starting end of the relay elastic rope (7) is positioned in the middle of the guide rail (1);
the top lock (8), the top lock (8) is connected with the first end of the relay elastic rope (7), and the top lock (8) is clamped on the fixed base (4);
the locking device (9), the locking device (9) is installed on the bracket pulley (2), and the locking device (9) can lock the top lock (8);
the disengaging device (10) can disengage the top lock (8) from the fixed base (4) after the top lock (8) is clamped by the clamping and locking device (9), and the initial baffle (5) can be in contact with the initial driving assembly (6) to separate the initial elastic rope (3) from the bracket pulley (2) after the top lock (8) is disengaged from the fixed base (4).
2. The drone ejector as claimed in claim 1, wherein the initial drive assembly (6) comprises:
pull plates (601), wherein the pull plates (601) are installed at four corners of the front end surface of the bracket pulley (2), and a space between the upper pull plate and the lower pull plate (601) can allow the initial baffle (5) to pass through;
the pull plate guide shaft (602), the pull plate guide shaft (602) is installed on the reverse side of the pull plate (601), and the reverse side of the pull plate (601) is the side of the pull plate (601) facing the bracket pulley (2);
the pull block (603) is provided with an installation through hole, the pull block (603) is slidably installed on the pull plate guide shaft (602) through the installation through hole, and the reverse side of the pull block (603) is connected with the second end of the initial elastic rope (3).
3. The unmanned aerial vehicle ejection device of claim 2, further comprising a fixing device (11) for clipping the top lock (8) to the fixing base (4), wherein the fixing device (11) comprises:
a spud pile (1101), said spud pile (1101) being fixed on said fixed base (4);
the inclined block (1102), the inclined block (1102) is installed at the bottom end of the fixing pile (1101), and the right-angled bottom end of the inclined block (1102) is connected with the fixing base (4) through a first compression spring (1104);
keep off axle (1103), keep off axle (1103) slidable connection top lock (8), just first guide hole has been seted up at the top of spud pile (1101), keep off axle (1103) can slidable mounting in first guide hole, the bottom of keeping off axle (1103) with the inclined plane of sloping block (1102) is fixed, disengaging gear (10) can be through the extrusion sloping block (1102) will top lock (8) with keep off axle (1103) slide and break away from.
4. The drone ejector as claimed in claim 3, characterized in that the top lock (8) comprises:
the lock base (801) is provided with a second guide hole, the top end of the baffle shaft (1103) penetrates through the second guide hole, the lock base (801) is arranged at the top end of the fixing pile (1101) in a pressing mode, the thickness of the lock base (801) is smaller than the height of the inclined block (1102), and the first end of the relay elastic rope (7) is connected with the lock base (801);
a lock head (802), wherein the lock head (802) is installed on the lock seat (801), and the locking device (9) can lock the lock head (802).
5. The unmanned aerial vehicle ejection device of claim 4, wherein the first guide hole and the second guide hole have a sliding linear bearing or a rolling linear bearing mounted therein.
6. The drone ejector of claim 4 or 5, wherein the top lock (8) further comprises a lock bar (803);
one end of the lock rod (803) is connected with the lock head (802), the other end of the lock rod (803) is connected with the lock seat (801), and the length of the lock rod (803) is greater than the length of the bottom edge of the inclined block (1102) along the direction of the guide rail (1).
7. The drone ejector as claimed in claim 4 or 5, characterized in that the latch means (9) comprise:
the cross section of each clamping block (901) is triangular, the inclined surfaces of the 2 clamping blocks (901) are arranged in a face-to-face mode, the first right-angle surface of each clamping block (901) is arranged in parallel with the corresponding guide rail (1), and the distance between the clamping blocks (901) is gradually increased along the direction from each clamping block (901) to the corresponding lock head (802);
the second compression spring (902) is connected with the clamping block (901), the second compression spring (902) can enable 2 clamping blocks (901) to approach each other, and the lock head (802) can push the clamping block (901) open and is clamped on a second right-angle surface of the clamping block (901) along the clamping groove.
8. The drone ejector as claimed in claim 7, characterized in that the latch device (9) further comprises:
a fixture block guide sleeve (903) installed on the bracket pulley (2);
and a fixture block guide shaft (904) mounted on the fixture block (901), wherein when the fixture block (901) moves mutually under the action of the lock head (802), the fixture block guide shaft (904) can slide in the fixture block guide sleeve (903).
9. The unmanned aerial vehicle ejection device of claim 7, wherein the cross section of the locking head (802) along the direction of the guide rail (1) is trapezoidal, the width of the locking head (802) is gradually reduced along the direction from the locking head (802) to the fixture block (901), and the trapezoidal internal angle of the locking head (802) is the same as the internal angle of the fixture block (901).
10. The drone ejector as claimed in claim 4, characterized in that the disengaging means (10) comprise:
a platen roller supporter (1001) installed on the carriage block (2);
a compression roller (1002) mounted on the compression roller bracket (1001), wherein the compression roller (1002) can press down the inclined block (1102) so that the blocking shaft (1103) can be disengaged from the lock seat (801), and the disengaging device (10) can pass through the fixing pile (1101) along with the bracket pulley (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710833746.4A CN107640330B (en) | 2017-09-15 | 2017-09-15 | Unmanned aerial vehicle jettison device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710833746.4A CN107640330B (en) | 2017-09-15 | 2017-09-15 | Unmanned aerial vehicle jettison device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107640330A CN107640330A (en) | 2018-01-30 |
| CN107640330B true CN107640330B (en) | 2020-01-14 |
Family
ID=61111458
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710833746.4A Expired - Fee Related CN107640330B (en) | 2017-09-15 | 2017-09-15 | Unmanned aerial vehicle jettison device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107640330B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109436364B (en) * | 2018-10-22 | 2021-10-15 | 南京航空航天大学 | Device and method for continuous launching of unmanned aerial vehicle |
| CN110316397A (en) * | 2019-07-22 | 2019-10-11 | 西安探索鹰航空科技有限公司 | A kind of unmanned aerial vehicle ejecting device and takeoff method being detached from based on principle of inertia |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6851647B1 (en) * | 2003-04-03 | 2005-02-08 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Portable catapult launcher for small aircraft |
| CN201694394U (en) * | 2010-06-18 | 2011-01-05 | 北京朗天博泰科技有限公司 | Catapult-launching device |
| CN202130573U (en) * | 2011-01-27 | 2012-02-01 | 深圳市鸣鑫实业有限公司 | Light portable takeoff ejecting rack for small-sized individual soldier unmanned plane |
| CN102616383B (en) * | 2012-04-19 | 2014-08-13 | 哈尔滨工业大学 | Multi-stage catapult-launching device |
| CN203793657U (en) * | 2014-04-16 | 2014-08-27 | 武汉智能鸟无人机有限公司 | Take-off assisting device for fixed-wing unmanned aerial vehicle |
| CN203832760U (en) * | 2014-04-25 | 2014-09-17 | 北京中量安测科技有限公司 | Catapulting system for small size unmanned aerial vehicle |
| CN205273882U (en) * | 2015-12-08 | 2016-06-01 | 广州南方测绘仪器有限公司 | Small -size fixed wing uavs launching cradle |
-
2017
- 2017-09-15 CN CN201710833746.4A patent/CN107640330B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN107640330A (en) | 2018-01-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107640330B (en) | Unmanned aerial vehicle jettison device | |
| WO2018121745A1 (en) | Unlocking device, locking device, battery replacement mobile platform and fast battery replacement system | |
| CN203079644U (en) | Hydraulic gliding device | |
| CN112960383A (en) | Battery module sliding cabinet-entering carrier | |
| CN107941081B (en) | Quick loading device of hand formula section of thick bamboo bullet | |
| CN111731501A (en) | Pulley bracket integrated device for unmanned aerial vehicle ejection | |
| US20210094593A1 (en) | Startup stage protection device for experiment of emu train coupler | |
| CN112572508A (en) | Guide wheel device for railway vehicle, bogie and railway vehicle | |
| CN105967108A (en) | Forward-moving type forklift storage battery unhooking device | |
| CN112026668A (en) | Vehicle-mounted electronic equipment | |
| CN213776162U (en) | Vehicle frame braking device | |
| CN113734457A (en) | Ejector | |
| CN111637791B (en) | Rocket loading system and method | |
| US20220348439A1 (en) | Brake device | |
| CN216424776U (en) | Launcher for unmanned aerial vehicle detection | |
| CN102471037A (en) | Releasable step locking system | |
| US5373952A (en) | Pneumatic shock absorber in compound trolley conveyor | |
| CN114475239B (en) | Auxiliary driving device for road vehicle | |
| CN219946019U (en) | Frock is dismantled to damaged coupling buffer | |
| CN217598592U (en) | Mining portable car arrester | |
| CN202089082U (en) | Rail clamping device | |
| CN214827053U (en) | Battery module sliding cabinet-entering carrier | |
| CN213106441U (en) | Motorcycle clamp | |
| CN211106951U (en) | Connecting device | |
| CN219216853U (en) | Loading device of mineral water bucket |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200114 Termination date: 20210915 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |