CN108910073B - Unmanned aerial vehicle ejection rack launching trolley and unmanned aerial vehicle launching method - Google Patents
Unmanned aerial vehicle ejection rack launching trolley and unmanned aerial vehicle launching method Download PDFInfo
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- CN108910073B CN108910073B CN201810882219.7A CN201810882219A CN108910073B CN 108910073 B CN108910073 B CN 108910073B CN 201810882219 A CN201810882219 A CN 201810882219A CN 108910073 B CN108910073 B CN 108910073B
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- 238000009434 installation Methods 0.000 claims description 3
- 238000009825 accumulation Methods 0.000 claims description 2
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
- B64F1/06—Ground or aircraft-carrier-deck installations for launching aircraft using catapults
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/70—Launching or landing using catapults, tracks or rails
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Abstract
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle ejection rack launching trolley and an unmanned aerial vehicle launching method, and aims to solve the technical problem that a propeller is damaged due to the fact that the propeller hits the launching trolley when the unmanned aerial vehicle leaves the rack in the prior art. The swing arm fixing seat assembly comprises a front swing arm support plate, a rear swing arm support plate, a swing arm fixing seat assembly and an opening device; the top of the front swing arm support plate is clamped with a front ejection shaft of the unmanned aerial vehicle; the top of the rear swing arm support plate is clamped with a rear ejection shaft of the unmanned aerial vehicle; the swing arm fixing seat assembly is rotatably connected with the front swing arm support plate and the rear swing arm support plate and is used for enabling the front swing arm support plate and the rear swing arm support plate to be located on the same plane; and the opening device acts on the front swing arm support plate and is used for driving the front swing arm support plate, the rear swing arm support plate and the swing arm fixing seat assembly to overturn outwards. The technical scheme provided by the invention effectively solves the technical problem that the propeller is damaged due to the fact that the propeller hits the launching trolley when the existing unmanned aerial vehicle leaves the frame.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle ejection rack launching trolley and an unmanned aerial vehicle launching method.
Background
The unmanned aerial vehicle ejection rack common use mode commonly used at present has pneumatic ejection, and the rubber band launches etc. wherein pneumatic ejection rack is released in the twinkling of an eye by cylinder high-pressure gas, promotes the piston rod and pops out, and the piston rod drives unmanned aerial vehicle and releases the cylinder together and make unmanned aerial vehicle obtain certain speed of taking off, and rubber band class ejection rack is by the elasticity of rubber band or spring, stimulates dolly and unmanned aerial vehicle, makes unmanned aerial vehicle obtain certain speed of taking off.
The unmanned aerial vehicle is divided into an oil-driven mode and an electric mode, and is divided into a propeller forward-pulling type mode and a propeller backward-pushing type mode.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle ejection rack launching trolley and an unmanned aerial vehicle launching method, which are used for solving the technical problem that a propeller is damaged due to the fact that the propeller hits the launching trolley when an unmanned aerial vehicle leaves the rack in the prior art.
In order to alleviate the technical problems, the technical scheme provided by the invention is as follows:
the utility model provides an unmanned aerial vehicle launching cradle launch vehicle, includes the support group that forms by two support bodys of parallel arrangement, the support body includes:
the device comprises a front swing arm support plate, a rear swing arm support plate, a swing arm fixing seat assembly and an opening device;
the top of the front swing arm support plate is provided with a first notch, and the opening of the first notch faces forwards and is used for clamping a front ejection shaft of the unmanned aerial vehicle;
the top of the rear swing arm support plate is provided with a second notch, and the opening of the second notch faces backwards and is used for clamping a rear ejection shaft of the unmanned aerial vehicle;
the swing arm fixing seat assembly is rotatably connected with the front swing arm support plate and the rear swing arm support plate and is used for enabling the front swing arm support plate and the rear swing arm support plate to be located on the same plane;
the opening device acts on the front swing arm support plate and is used for driving the front swing arm support plate, the rear swing arm support plate and the swing arm fixing seat assembly to turn outwards.
Further, in the present invention,
the swing arm fixing seat assembly comprises a front fixing seat and a rear fixing seat, and the front fixing seat is used for fixing a front side base angle of the front swing arm support plate; the rear fixing seat is used for fixing the lower part of the rear swing arm support plate and the rear bottom angle of the front swing arm support plate.
Further, in the present invention,
the front fixed seat comprises a front base and a front rotating part;
the front base is provided with two side plates which are spaced and are opened at the outer side to form a rotating space;
the lower part of the front rotating part extends into the rotating space and is connected with the front base through a first shaft, and the upper part of the front rotating part is connected with the front swing arm support plate;
further, in the present invention,
the rear fixing seat comprises a rear base and a rear rotating part;
the rear base is provided with two side plates which are spaced and have openings at the outer sides to form a rotating space, and the rear side of the rear base is provided with a groove for accommodating the bottom of the rear swing arm support plate;
the lower part of the rear rotating part extends into the rotating space and is connected with the rear base through a second shaft, and the upper part of the rear rotating part is connected with the rear swing arm supporting plate and the rear bottom angle of the front swing arm supporting plate.
Further, in the present invention,
the front swing arm support plate comprises a front vertical plate, a transverse plate and an inclined plate which are arranged in a triangular shape;
the connecting position of the front vertical plate and the transverse plate forms a front bottom angle of the front swing arm supporting plate, and the transverse plate and the inclined plate form a rear bottom angle of the front swing arm supporting plate.
Further, in the present invention,
the inclined plate is provided with a rear swing arm support plate fixing block, and the rear swing arm support plate fixing block is used for fixing a rear swing arm support plate in a laid-down state.
Further, in the present invention,
two opposite top beads are arranged in the rear swing arm support plate fixing block, and a necking is formed by the two top beads so as to fix the rear swing arm support plate.
Further, in the present invention,
the opening device comprises a rotating shaft and at least one torsion spring arranged on the rotating shaft;
one end of the rotating shaft extends into the front fixing seat to connect the front base and the front rotating part, and the other end of the rotating shaft extends into the rear fixing seat to connect the rear base and the rear rotating part;
one side of the torsion spring abuts against the transverse plate of the front swing arm support plate and is in a force storage state in the takeoff process of the unmanned aerial vehicle so as to drive the front swing arm support plate to turn outwards.
Further, in the present invention,
the launching trolley also comprises a plane supporting frame, and the plane supporting frame comprises a front anti-collision pad, a swing arm anti-collision pad and a locking rod device;
the front anti-collision pad is arranged at the front end of the plane support frame and used for preventing the launching trolley from directly impacting brake rubber arranged on the launching rack in the process of sliding on the launching rack;
the swing arm anti-collision pads are arranged on two sides of the plane support frame and used for preventing the support body from being damaged due to collision in the outward overturning process;
the locking rod device is arranged at the rear part of the plane support frame, is clamped into the locking mechanism of the ejection frame when the launching trolley is in a non-launching state so as to prevent the launching trolley from popping out, and is separated from the locking mechanism in the launching process of the launching trolley.
An unmanned aerial vehicle launching method, comprising:
locking the locking bar device;
laying down the rear swing arm support plate and enabling the rear swing arm support plate to be clamped into the rear swing arm support plate fixing block;
clamping a front ejection shaft at the bottom of the unmanned aerial vehicle to a first notch at the top of the front swing arm support plate;
the rear swing arm support plate in the laid state is pulled up, and a rear ejection shaft at the bottom of the unmanned aerial vehicle is clamped to a second notch of the rear swing arm support plate;
the bottom of the rear swing arm support plate is clamped into a bottom groove of the rear base, so that the front swing arm support plate and the rear swing arm support plate are prevented from turning outwards;
the traction rubber of the ejection frame stores force, the lock rod device is opened to release the launching trolley, and the launching trolley slides on the ejection frame rail until the front anti-collision pad at the front end of the launching trolley impacts the brake rubber of the launching trolley and stops sliding;
the unmanned aerial vehicle continues to slide under the action of inertia force, and a rear ejection shaft at the bottom of the unmanned aerial vehicle pulls forwards and opens a rear swing arm support plate to be bound in a rear fixing seat;
the opening device drives the front swing arm support plate and the rear swing arm support plate to outwards turn around the mounting shaft of the opening device, so that the unmanned aerial vehicle can take off smoothly.
By combining the technical scheme, the invention has the following beneficial effects:
the support body of the launching trolley of the unmanned aerial vehicle ejection rack comprises a front swing arm support plate, a rear swing arm support plate, a swing arm fixing seat assembly and an opening device; the top of the front swing arm support plate is provided with a first notch, and the opening of the first notch faces forwards and is used for clamping a front ejection shaft of the unmanned aerial vehicle; the top of the rear swing arm support plate is provided with a second notch, and the opening of the second notch faces backwards and is used for clamping a rear ejection shaft of the unmanned aerial vehicle; preceding swing arm support top and back swing arm support top have formed unmanned aerial vehicle's fulcrum.
In the launching process of the unmanned aerial vehicle, the launching trolley stops moving after being subjected to the reaction force of brake rubber at the front end of the launching trolley, the unmanned aerial vehicle continues to slide under the action of inertia force, and a rear ejection shaft at the bottom of the unmanned aerial vehicle pulls forwards and opens a rear swing arm support plate; the opening device acts on the front swing arm support plate to drive the front swing arm support plate, the rear swing arm support plate and the swing arm fixing seat assembly to overturn outwards, so that the technical problem that when an existing unmanned aerial vehicle leaves the frame, a propeller hits a launching trolley to cause damage to the propeller is effectively solved.
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, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic view of the overall structure of an unmanned aerial vehicle ejection rack launch vehicle provided by an embodiment of the invention;
fig. 2 is an enlarged structural view of a front fixing seat in the launch trolley of the launch rack of the unmanned aerial vehicle provided by the embodiment of the invention;
fig. 3 is an enlarged structural view of a rear fixing seat in the launch trolley of the unmanned aerial vehicle launch stand provided by the embodiment of the invention;
fig. 4 is a schematic structural view of a front swing arm support plate in the launch vehicle of the launch frame of the unmanned aerial vehicle provided by the embodiment of the invention;
fig. 5 is a schematic structural view of a rear swing arm support plate in the launch vehicle of the launch stand of the unmanned aerial vehicle provided by the embodiment of the invention;
fig. 6 is a schematic structural diagram of an open state of an unmanned aerial vehicle ejection rack launch vehicle provided in an embodiment of the present invention.
Icon: 100-a front swing arm support plate; 200-a rear swing arm support plate; 400-opening the device; 500-plane support frame; 110-a first notch; 210-a second notch; 310-front fixed seat; 320-rear fixed seat; 312-front rotating part; 321-a rear base; 322-rear rotating part; 323-grooves; 101-front riser; 102-a transverse plate; 103-a sloping plate; 104-a rear swing arm support plate fixing block; 410-a rotating shaft; 420-torsion spring; 510-front crash pad; 520-swing arm crash pad; 530-locking bar means.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. 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 invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., 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, but 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 invention. 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.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Embodiment 1 and embodiment 2 are described in detail below with reference to the accompanying drawings:
fig. 1 is a schematic view of the overall structure of an unmanned aerial vehicle ejection rack launch vehicle provided by an embodiment of the invention; fig. 2 is an enlarged structural view of a front fixing seat in the launch trolley of the launch rack of the unmanned aerial vehicle provided by the embodiment of the invention; fig. 3 is an enlarged structural view of a rear fixing seat in the launch trolley of the unmanned aerial vehicle launch stand provided by the embodiment of the invention; fig. 4 is a schematic structural view of a front swing arm support plate in the launch vehicle of the launch frame of the unmanned aerial vehicle provided by the embodiment of the invention; fig. 5 is a schematic structural view of a rear swing arm support plate in the launch vehicle of the launch stand of the unmanned aerial vehicle provided by the embodiment of the invention; fig. 6 is a schematic structural diagram of an open state of an unmanned aerial vehicle ejection rack launch vehicle provided in an embodiment of the present invention.
Example 1
This embodiment provides an unmanned aerial vehicle launching cradle launch vehicle, includes the support group that forms by two support bodys of parallel arrangement, and the support body includes:
a front swing arm brace 100, a rear swing arm brace 200, a swing arm mount assembly, and an opening device 400;
the top of the front swing arm support plate 100 is provided with a first notch 110, and the opening of the first notch 110 faces forwards and is used for clamping a front ejection shaft of the unmanned aerial vehicle;
a second notch 210 is formed in the top of the rear swing arm support plate 200, and the opening of the second notch 210 faces backwards and is used for clamping a rear ejection shaft of the unmanned aerial vehicle;
the swing arm fixing seat assembly is rotatably connected with the front swing arm support plate 100 and the rear swing arm support plate 200 and is used for enabling the front swing arm support plate 100 and the rear swing arm support plate 200 to be located on the same plane;
the opening device 400 acts on the front swing arm support plate 100 and is used for driving the front swing arm support plate 100, the rear swing arm support plate 200 and the swing arm fixing seat assembly to turn outwards.
In the launching process of the unmanned aerial vehicle, the launching trolley stops moving after being subjected to the reaction force of the brake rubber at the front end of the launching trolley, the unmanned aerial vehicle continues to slide under the action of inertia force, and the rear ejection shaft at the bottom of the unmanned aerial vehicle pulls forwards and opens the rear swing arm support plate 200; opening device 400 acts on preceding swing arm extension board 100, and the swing arm extension board 100, back swing arm extension board 200 and swing arm stationary base subassembly are to the outside upset to the technical problem that the screw damaged is caused to the transmission dolly is hit to the screw when effectively having avoided current unmanned aerial vehicle to leave the frame.
In an alternative to this embodiment, it is preferable that,
the swing arm fixing seat assembly comprises a front fixing seat 310 and a rear fixing seat 320, wherein the front fixing seat 310 is used for fixing a front bottom corner of the front swing arm support plate 100; rear mount 320 is used to mount the lower portion of rear swing arm plate 200 and the rear bottom corner of front swing arm plate 100. The above-mentioned fixing may be a rotational connection, for example: the front fixing seat 310 is connected with a front bottom angle of the front swing arm support plate 100 through a shaft, and the front fixing seat 310 and the front swing arm support plate 100 can relatively rotate around an axis. For example, the rear fixing seat 320 is connected with the lower part of the rear swing arm support plate 200 through a shaft, the rear fixing seat 320 is connected with the rear bottom corner of the front swing arm support plate 100 through a shaft, and the axes of the two connecting shafts are parallel to each other.
In an alternative to this embodiment, it is preferable that,
the front fixing base 310 includes a front base and a front rotating portion 312; the front base is provided with two side plates which are spaced and are opened at the outer side to form a rotating space; the lower portion of the front rotary part 312 extends into the rotation space and is connected to the front base through a first shaft, and the upper portion of the front rotary part 312 is connected to the front swing arm stay 100.
In an alternative to this embodiment, it is preferable that,
the rear fixing base 320 includes a rear base 321 and a rear rotating portion 322;
the rear base 321 has two side plates spaced apart and opened at the outer side to form a rotation space, and the rear side of the rear base 321 has a recess 323 for receiving the bottom of the rear swing arm support 200.
The lower portion of the rear rotation portion 322 extends into the rotation space and is connected to the rear base 321 via a second shaft, and the upper portion of the rear rotation portion 322 is connected to the rear bottom corners of the rear swing arm stay 200 and the front swing arm stay 100.
In an alternative to this embodiment, it is preferable that,
the front swing arm support plate 100 comprises a front vertical plate 101, a transverse plate 102 and a sloping plate 103 which are arranged in a triangular shape;
the connecting position of the front riser 101 and the cross plate 102 forms a front bottom angle of the front swing arm brace 100, and the cross plate 102 and the sloping plate 103 form a rear bottom angle of the front swing arm brace 100.
In an alternative to this embodiment, it is preferable that,
the inclined plate 103 is provided with a rear swing arm support plate fixing block 104, and the rear swing arm support plate fixing block 104 is used for fixing the rear swing arm support plate 200 in a laid-down state.
In an alternative to this embodiment, it is preferable that,
two opposite top beads are arranged in the rear swing arm support plate fixing block 104, and the two top beads form a necking so as to fix the rear swing arm support plate 200.
In an alternative to this embodiment, it is preferable that,
at least one through hole is formed in the rear swing arm support plate 200, and the top beads extend into the through hole to position the rear swing arm support plate 200 when the rear swing arm support plate 200 is in a laid-down state.
In an alternative to this embodiment, it is preferable that,
the opening means 400 includes a rotating shaft 410 and at least one torsion spring 420 mounted on the rotating shaft 410;
one end of the rotating shaft 410 extends into the front fixing base 310 to connect the front base and the front rotating part 312, and the other end of the rotating shaft 410 extends into the rear fixing base 320 to connect the rear base 321 and the rear rotating part 322;
the torsion spring 420 abuts against the transverse plate 102 of the front swing arm support plate 100 on one side and is in a power accumulation state in the takeoff process of the unmanned aerial vehicle so as to drive the front swing arm support plate 100 to turn outwards.
In an alternative to this embodiment, it is preferable that,
the launch vehicle further comprises a plane support frame 500, wherein the plane support frame 500 comprises a front anti-collision pad 510, a swing arm anti-collision pad 520 and a locking rod device 530;
the front anti-collision pad 510 is arranged at the front end of the plane support frame 500 and is used for preventing the launching trolley from directly impacting brake rubber arranged on the launching rack in the process of sliding on the launching rack;
the swing arm anti-collision pads 520 are arranged on two sides of the plane support frame 500 and are used for preventing the support body from being damaged due to collision in the process of turning outwards;
the locking rod device 530 is arranged at the rear part of the plane support frame 500, is clamped into the locking mechanism of the ejection frame when the launch vehicle is in the non-launch state so as to prevent the launch vehicle from ejecting, and is separated from the locking mechanism in the launch process of the launch vehicle.
It should be added that, in order to increase the flexibility of rotation and avoid the locking, a bearing is provided on each revolute pair.
Example 2
The embodiment provides an unmanned aerial vehicle launching method, which comprises the following steps:
s1; a locking bar means 530;
s2; laying down the rear swing arm support plate 200 and clamping the rear swing arm support plate 200 into the rear swing arm support plate fixing block 104;
s3; clamping a front ejection shaft at the bottom of the unmanned aerial vehicle to a first notch 110 at the top of the front swing arm support plate 100;
s4; the rear swing arm support plate 200 in the laid state is pulled up, and a rear ejection shaft at the bottom of the unmanned aerial vehicle is clamped to a second notch 210 of the rear swing arm support plate 200;
s5; the bottom of the rear swing arm support plate 200 is clamped into a bottom groove 323 of the rear base 321, so that the front swing arm support plate 100 and the rear swing arm support plate 200 are prevented from turning outwards;
s6; the traction rubber of the ejection rack accumulates force, the locking rod device 530 is opened to release the launch vehicle, and the launch vehicle slides on the ejection rack rail until the front anti-collision pad 510 at the front end of the launch vehicle collides with the brake rubber of the launch vehicle and stops sliding;
s7; the unmanned aerial vehicle continues to slide under the action of inertia force, and a rear ejection shaft at the bottom of the unmanned aerial vehicle pulls forwards and opens the constraint of the rear swing arm support plate 200 in the rear fixing seat 320;
s8; the opening device 400 drives the front swing arm support plate 100 and the rear swing arm support plate 200 to outwards turn around the installation shaft of the opening device 400, so that the unmanned aerial vehicle can take off smoothly.
The launch vehicle firstly locks the locking rod device 530; then the rear swing arm support plate 200 is laid down and the rear swing arm support plate 200 is clamped into the rear swing arm support plate fixing block 104; then, clamping the bottom front ejection shaft of the unmanned aerial vehicle to the top first notch 110 of the front swing arm support plate 100; then, the rear swing arm support plate 200 in the laid state is pulled up, and a rear ejection shaft at the bottom of the unmanned aerial vehicle is clamped to a second notch 210 of the rear swing arm support plate 200; then, the bottom of the rear swing arm support plate 200 is clamped into a bottom groove 323 of the rear base 321, so that the front swing arm support plate 100 and the rear swing arm support plate 200 are prevented from turning outwards; then the traction rubber of the ejection rack accumulates force, the lock rod device 530 is opened to release the launch vehicle, and the launch vehicle slides on the ejection rack rail until the front anti-collision pad 510 at the front end of the launch vehicle collides with the brake rubber of the launch vehicle and stops sliding; then the unmanned aerial vehicle continues to slide under the action of inertia force, and a rear ejection shaft at the bottom of the unmanned aerial vehicle pulls forwards and opens the constraint of the rear swing arm support plate 200 in the rear fixing seat 320; finally, the opening device 400 drives the front swing arm support plate 100 and the rear swing arm support plate 200 to outwards turn around the installation shaft of the opening device 400, so that the unmanned aerial vehicle can take off smoothly. Because in the unmanned aerial vehicle transmission process, preceding swing arm extension board 100, back swing arm extension board 200 and swing arm fixed seat subassembly overturn to the outside to effectively avoided current unmanned aerial vehicle to beat the technical problem that the transmission dolly leads to the screw to damage when leaving the frame.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (8)
1. The utility model provides an unmanned aerial vehicle launching cradle launch vehicle which characterized in that includes the support group that forms by two support bodys of parallel arrangement, the support body includes:
a front swing arm support plate (100), a rear swing arm support plate (200), a swing arm fixing seat assembly and an opening device (400);
the top of the front swing arm support plate (100) is provided with a first notch (110), and an opening of the first notch (110) faces forwards and is used for clamping a front ejection shaft of the unmanned aerial vehicle;
a second notch (210) is formed in the top of the rear swing arm support plate (200), and an opening of the second notch (210) faces backwards and is used for being clamped with a rear ejection shaft of the unmanned aerial vehicle;
the swing arm fixing seat assembly is rotatably connected with the front swing arm support plate (100) and the rear swing arm support plate (200) and is used for enabling the front swing arm support plate (100) and the rear swing arm support plate (200) to be located on the same plane;
the opening device (400) acts on the front swing arm support plate (100) and is used for driving the front swing arm support plate (100), the rear swing arm support plate (200) and the swing arm fixing seat assembly to incline outwards;
the front swing arm support plate (100) comprises a front vertical plate (101), a transverse plate (102) and a sloping plate (103) which are arranged in a triangular shape;
the connecting position of the front vertical plate (101) and the transverse plate (102) forms a front bottom corner of the front swing arm support plate (100), and the transverse plate (102) and the inclined plate (103) form a rear bottom corner of the front swing arm support plate (100);
a rear swing arm support plate fixing block (104) is arranged on the inclined plate (103), and the rear swing arm support plate fixing block (104) is used for fixing a rear swing arm support plate (200) in a laid-down state.
2. The unmanned aerial vehicle ejector launcher emitter carriage of claim 1,
the swing arm fixing seat assembly comprises a front fixing seat (310) and a rear fixing seat (320), wherein the front fixing seat (310) is used for fixing a front bottom angle of the front swing arm support plate (100); the rear fixing seat (320) is used for fixing the lower part of the rear swing arm support plate (200) and the rear bottom angle of the front swing arm support plate (100).
3. The unmanned aerial vehicle ejector launcher emitter carriage of claim 2,
the front fixed seat (310) comprises a front base and a front rotating part (312);
the front base is provided with two side plates which are spaced and are opened at the outer side to form a rotating space;
the lower part of the front rotating part (312) extends into the rotating space and is connected with the front base through a first shaft, and the upper part of the front rotating part (312) is connected with the front swing arm support plate (100).
4. The unmanned aerial vehicle ejector launcher emitter carriage of claim 3,
the rear fixing seat (320) comprises a rear base (321) and a rear rotating part (322);
the rear base (321) is provided with two side plates which are spaced and open at the outer side to form a rotating space, and the rear side of the rear base (321) is provided with a groove for accommodating the bottom of the rear swing arm support plate (200);
the lower part of the rear rotating part (322) extends into the rotating space and is connected with the rear base (321) through a second shaft, and the upper part of the rear rotating part (322) is connected with the rear swing arm support plate (200) and the rear bottom corner of the front swing arm support plate (100).
5. The unmanned aerial vehicle ejector launcher emitter carriage of claim 1,
two opposite top beads are arranged in the rear swing arm support plate fixing block (104), and a necking is formed by the two top beads so as to fix the rear swing arm support plate (200).
6. The unmanned aerial vehicle ejector launcher emitter carriage of claim 4,
the opening device (400) comprises a rotating shaft (410) and at least one torsion spring (420) mounted on the rotating shaft (410);
one end of the rotating shaft (410) extends into the front fixed seat (310) to connect the front base and the front rotating part (312), and the other end of the rotating shaft (410) extends into the rear fixed seat (320) to connect the rear base (321) and the rear rotating part (322);
one side of the torsion spring (420) abuts against a transverse plate (102) of the front swing arm support plate (100) and is in a force accumulation state in the takeoff process of the unmanned aerial vehicle so as to drive the front swing arm support plate (100) to turn outwards.
7. The unmanned aerial vehicle ejector launcher launch vehicle of claim 1, wherein said launch vehicle further comprises a planar support frame (500), said planar support frame (500) comprising a front crash pad (510), a swing arm crash pad (520), and a locking bar arrangement (530);
the front anti-collision pad (510) is arranged at the front end of the plane support frame (500) and is used for preventing the launching trolley from directly impacting brake rubber arranged on the launching rack in the sliding process on the launching rack;
the swing arm anti-collision pads (520) are arranged on two sides of the plane support frame (500) and used for preventing the support body from being damaged due to collision in the process of turning outwards;
the locking rod device (530) is arranged at the rear part of the plane support frame (500), is clamped into a locking mechanism of the ejection frame when the launch vehicle is in a non-launch state to prevent the launch vehicle from being ejected, and is separated from the locking mechanism in the launch process of the launch vehicle.
8. A method of launching an unmanned aerial vehicle using the unmanned aerial vehicle launcher launching trolley of claim 1, comprising:
a locking bar means (530);
laying down a rear swing arm support plate (200) and enabling the rear swing arm support plate (200) to be clamped into the rear swing arm support plate fixing block (104);
clamping a front ejection shaft at the bottom of the unmanned aerial vehicle to a first notch (110) at the top of a front swing arm support plate (100);
the rear swing arm support plate (200) in a laid state is pulled up, and a rear ejection shaft at the bottom of the unmanned aerial vehicle is clamped to a second notch (210) of the rear swing arm support plate (200);
the bottom of the rear swing arm support plate (200) is clamped into a bottom groove of a rear base (321), so that the front swing arm support plate (100) and the rear swing arm support plate (200) are prevented from turning outwards;
the traction rubber of the ejection rack accumulates force, the lock rod device (530) is opened to release the launching trolley, and the launching trolley slides on the ejection rack rail until the front anti-collision pad (510) at the front end of the launching trolley impacts the brake rubber of the launching trolley and then stops sliding;
the unmanned aerial vehicle continues to slide under the action of inertia force, and a rear ejection shaft at the bottom of the unmanned aerial vehicle pulls forwards and opens the constraint of the rear swing arm support plate (200) in the rear fixed seat (320);
the opening device (400) drives the front swing arm support plate (100) and the rear swing arm support plate (200) to outwards turn around the installation shaft of the opening device (400), so that the unmanned aerial vehicle can take off smoothly.
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| CN110395402B (en) * | 2019-06-26 | 2023-08-11 | 北京晶品特装科技股份有限公司 | Low-disturbance unmanned aerial vehicle ejection frame separating mechanism and separating method |
| CN110758762B (en) * | 2019-11-12 | 2021-05-25 | 航天时代飞鸿技术有限公司 | Unmanned aerial vehicle ejection locking releasing device and method |
| CN112455708B (en) * | 2020-11-26 | 2022-06-14 | 中国船舶工业系统工程研究院 | Pulley bracket device for ejection of fixed-wing unmanned aerial vehicle |
| US11787561B2 (en) * | 2021-04-20 | 2023-10-17 | Insitu, Inc. | Adapter assemblies for aircraft and launchers for deploying aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204568070U (en) * | 2015-03-26 | 2015-08-19 | 北京大白科技有限公司 | The two chain stay releasing mechanism of a kind of unmanned aerial vehicle ejecting frame |
| CN106081150A (en) * | 2016-08-04 | 2016-11-09 | 湖南航天机电设备与特种材料研究所 | One launches supporting mechanism and ejection system thereof |
| AU2016250386A1 (en) * | 2003-01-17 | 2016-11-17 | Insitu, Inc. | Methods and apparatuses for capturing and recovering unmanned aircraft, including a cleat for capturing aircraft on a line |
| CN207157568U (en) * | 2017-07-12 | 2018-03-30 | 北京盈想东方科技股份有限公司 | New unmanned target drone ejector |
| CN108202876A (en) * | 2016-12-16 | 2018-06-26 | 南京航空航天大学 | A kind of guarantor's type unmanned aerial vehicle ejecting draft gear |
-
2018
- 2018-08-03 CN CN201810882219.7A patent/CN108910073B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU2016250386A1 (en) * | 2003-01-17 | 2016-11-17 | Insitu, Inc. | Methods and apparatuses for capturing and recovering unmanned aircraft, including a cleat for capturing aircraft on a line |
| CN204568070U (en) * | 2015-03-26 | 2015-08-19 | 北京大白科技有限公司 | The two chain stay releasing mechanism of a kind of unmanned aerial vehicle ejecting frame |
| CN106081150A (en) * | 2016-08-04 | 2016-11-09 | 湖南航天机电设备与特种材料研究所 | One launches supporting mechanism and ejection system thereof |
| CN108202876A (en) * | 2016-12-16 | 2018-06-26 | 南京航空航天大学 | A kind of guarantor's type unmanned aerial vehicle ejecting draft gear |
| CN207157568U (en) * | 2017-07-12 | 2018-03-30 | 北京盈想东方科技股份有限公司 | New unmanned target drone ejector |
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