CN115783337A - Active taper sleeve for aerial recovery of unmanned aerial vehicle - Google Patents
Active taper sleeve for aerial recovery of unmanned aerial vehicle Download PDFInfo
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- CN115783337A CN115783337A CN202310084734.1A CN202310084734A CN115783337A CN 115783337 A CN115783337 A CN 115783337A CN 202310084734 A CN202310084734 A CN 202310084734A CN 115783337 A CN115783337 A CN 115783337A
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- taper sleeve
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- aerial vehicle
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- 238000011084 recovery Methods 0.000 title claims abstract description 32
- 230000007246 mechanism Effects 0.000 claims abstract description 20
- 230000005540 biological transmission Effects 0.000 claims description 7
- 230000007704 transition Effects 0.000 claims description 4
- 238000004064 recycling Methods 0.000 claims description 3
- 230000008859 change Effects 0.000 abstract description 3
- 230000010355 oscillation Effects 0.000 abstract description 2
- 210000001503 joint Anatomy 0.000 description 5
- 239000007787 solid Substances 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000002401 inhibitory effect Effects 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 230000033001 locomotion Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 230000026058 directional locomotion Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000035484 reaction time Effects 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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Abstract
The invention discloses an active taper sleeve for aerial recovery of an unmanned aerial vehicle, which comprises a taper sleeve body, a fairing, a rudder group and a traction cable, wherein an electromagnet is arranged in a taper opening of the taper sleeve body; the fairing is sleeved outside the tip end of the taper sleeve body; the rudder group comprises a plurality of adjusting rudders which are arranged on the side wall of the fairing in a surrounding manner, and the adjusting rudders are connected with the fairing through a driving mechanism; one end of the traction cable is respectively connected with the tip of the taper sleeve body, the driving mechanism and the electromagnet. When the taper sleeve body bears the air current disturbance, inevitable emergence dislocation is removed, leads to the change of gesture and height, through the directional swing respectively of a plurality of adjustment rudders of actuating mechanism control to change the air current flow direction, make the taper sleeve body implement directional removal, through the amplitude of oscillation and the swing direction of constantly adjusting a plurality of adjustment rudders, thereby no matter how the air current disturbs, the homoenergetic makes the taper sleeve body be in relatively stable state and height, provides the stability basis for unmanned aerial vehicle's recovery.
Description
Technical Field
The invention relates to the technical field of taper sleeves, in particular to an active taper sleeve for aerial recovery of an unmanned aerial vehicle.
Background
The large-scale manned machine can regard as unmanned aerial vehicle's aerial vehicle platform, with the help of the longer dead time of manned machine and voyage, can make unmanned aerial vehicle's operation distance promote by a wide margin, with the help of having the man-machine to lean on preceding deployment, can make unmanned aerial vehicle's operation reaction time shorten greatly. In future operations, the existing large-scale unmanned aerial vehicle can be used as an aerial carrier of the unmanned aerial vehicle, stays at the periphery far away from a defense area of enemy, then releases the unmanned aerial vehicle, executes tasks such as information investigation, operations and the like, and can be recovered for maintenance after the tasks are completed.
In the prior art, the aerial release of the unmanned aerial vehicle is easy to realize, the aerial recovery butt joint technology is mainly embodied in aerial refueling, and a passive taper sleeve is adopted to be in butt joint with an oil receiving machine, so that the recovery of the unmanned aerial vehicle can be implemented by utilizing the passive taper sleeve, but the passive taper sleeve can swing along with wind or oscillate at high and low levels in the air, the recovery difficulty is high, and the recovery success rate is unstable.
Disclosure of Invention
The invention aims to provide an active taper sleeve for aerial recovery of an unmanned aerial vehicle, and solves the technical problem that when the existing passive taper sleeve is used for recovering the unmanned aerial vehicle, swinging or oscillation is easy to occur, and the recovery difficulty is high.
The invention is realized by the following technical scheme:
an active drogue for aerial recovery of an unmanned aerial vehicle, comprising: the taper sleeve comprises a taper sleeve body, wherein an electromagnet is arranged in a taper opening of the taper sleeve body and is used for recovering the unmanned aerial vehicle; the fairing is sleeved outside the tip of the taper sleeve body; the rudder group comprises a plurality of adjusting rudders, the adjusting rudders are arranged on the side wall of the fairing in a surrounding mode and arranged along the radial direction of the taper sleeve body, the adjusting rudders are connected with the fairing through a driving mechanism, and the driving mechanism is used for enabling the adjusting rudders to swing directionally so as to enable the taper sleeve body to move directionally; and one end of the traction cable is connected with the tip end of the taper sleeve body, the driving mechanism and the electromagnet respectively, and the other end of the traction cable is connected with the external environment.
Optionally, the rudder group includes four adjusting rudders, and the four adjusting rudders are arranged in an X shape.
Optionally, the driving mechanism comprises a plurality of servo steering engines, and the plurality of servo steering engines correspond to the plurality of adjusting rudders one by one; the adjusting rudder comprises a connecting portion and a swinging portion, the connecting portion is connected with the side wall of the fairing, the servo steering engine is embedded in the connecting portion correspondingly, the output end of the servo steering engine is connected with a rotating shaft in a transmission mode, the rotating shaft is arranged along the radial extension of the taper sleeve body, and the swinging portion is sleeved in the rotating shaft.
Optionally, the connecting portion is in a streamline plate shape, the plane of the connecting portion is coplanar with the axis of the taper sleeve body, a resistance reducing tip is convexly arranged at a position, close to the tip end of the taper sleeve body, of the connecting portion, where the connecting portion is connected with the fairing, and the windward side of the resistance reducing tip is in streamline transition.
Optionally, the swing portion is in a streamline plate shape, the plane where the swing portion is located is in an initial state and is flush with the plane where the connecting portion is located, and the cross section of the swing portion in the thickness direction is in a droplet shape.
Optionally, one side of the swinging portion close to the tip of the taper sleeve body is provided with an inclined surface, so that the swinging portion is in a trapezoidal plate shape, and the width of one side of the swinging portion far away from the connecting portion is smaller than the width of one side of the swinging portion close to the connecting portion.
Optionally, the conical surface of the taper sleeve body is arranged in a streamline shape, the conical surface of the taper sleeve body is arranged in a hollow manner to form a plurality of guide wings which are distributed annularly, the plane where the guide wings are located is coplanar with the axis of the taper sleeve body, and the guide wings extend from the tip end of the taper sleeve body to the taper opening of the taper sleeve body.
Optionally, a fixing ring is arranged in a cone opening of the cone sleeve body, and an outer ring of the fixing ring is in cross insertion with the inner sides of all the guide wings.
Optionally, the fixing ring is equally divided into a plurality of arc sections, and every two adjacent arc sections are in mortise-tenon connection.
Optionally, the outer ring of the cone opening of the cone sleeve body is annularly provided with a plurality of LED lamp bodies.
Compared with the prior art, the invention has the following advantages and beneficial effects:
according to the active taper sleeve for aerial recovery of the unmanned aerial vehicle, the taper sleeve body and the traction cable are arranged, so that the taper sleeve body is released when the manned aircraft flies, and is connected with the manned aircraft through the traction cable, so that the taper sleeve body flies together with the manned aircraft under the traction action of the manned aircraft; on the basis, the fairing is sleeved outside the tip end of the taper sleeve body, the fairing is used for inhibiting the interference of airflow on the taper sleeve body, and the stability of the taper sleeve body is improved; on the basis, the rudder group is arranged and comprises a plurality of adjusting rudders, the adjusting rudders are connected with the fairing through the driving mechanism, when the taper sleeve body bears airflow disturbance, the dislocation movement inevitably occurs to cause the change of the posture and the height, the driving mechanism controls the adjusting rudders to respectively swing directionally, so that the airflow direction is changed, the taper sleeve body carries out directional movement, and the swinging amplitude and the swinging direction of the adjusting rudders are continuously adjusted, so that the taper sleeve body can be in a relatively stable state and height no matter how the airflow is interfered, and a stable foundation is provided for the recovery of the unmanned aerial vehicle; on this basis, through this internal electro-magnet that sets up at the taper sleeve, after the taper mouth butt joint of unmanned aerial vehicle and taper sleeve body, link unmanned aerial vehicle and taper sleeve body as an organic whole through the electro-magnet to thoroughly implement unmanned aerial vehicle's recovery.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the principles of the invention. In the drawings:
fig. 1 is a schematic view of an active taper sleeve for aerial recovery of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a side view of an active drogue for aerial recovery of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 3 is a front view of an active drogue for aerial recovery of an unmanned aerial vehicle according to an embodiment of the present invention.
Reference numbers and corresponding part names in the figures:
10-taper sleeve body; 11-an electromagnet; 12-guide wings; 13-a fixed ring; 14-an LED lamp body; 20-a fairing; 30-adjusting the rudder; 31-a connecting portion; 311-resistance reducing tip; 32-a swing part; 40-a traction cable; 50-servo steering engine; 51-rotating shaft.
Detailed description of the preferred embodiments
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not meant to limit the present invention.
Example (b): referring to fig. 1 to 3, an embodiment of the present invention provides an active taper sleeve for aerial recycling of an unmanned aerial vehicle, including: the unmanned aerial vehicle recovery device comprises a taper sleeve body 10, wherein an electromagnet 11 is arranged in the taper opening of the taper sleeve body 10 and at the position, close to the tip, of the center of the taper sleeve body and used for recovering the unmanned aerial vehicle; the second comprises a fairing 20, and the fairing 20 is sleeved outside the tip end of the taper sleeve body 10; the third step comprises a rudder group, wherein the rudder group comprises a plurality of adjusting rudders 30, the adjusting rudders 30 are arranged on the side wall of the fairing 20 in a surrounding manner and arranged along the radial direction of the taper sleeve body 10, the adjusting rudders 30 are connected with the fairing 20 through a driving mechanism, and the driving mechanism is used for enabling the adjusting rudders 30 to swing directionally so as to enable the taper sleeve body 10 to move directionally; the fourth is including drawing cable 40, draw cable 40's one end respectively with the pointed end of taper sleeve body 10, actuating mechanism and electromagnet 11 are connected, and the other end is connected with the external environment.
According to the active taper sleeve for aerial recovery of the unmanned aerial vehicle, the taper sleeve body 10 and the traction cable 40 are arranged, so that the taper sleeve body 10 is released when the manned aircraft flies, and is connected with the manned aircraft through the traction cable 40, so that the taper sleeve body 10 flies together with the manned aircraft under the traction action of the manned aircraft; on the basis, the fairing 20 is sleeved outside the tip end of the taper sleeve body 10, the fairing 20 is used for inhibiting the interference of airflow on the taper sleeve body 10, and the stability of the taper sleeve body 10 is improved; on the basis, by arranging the rudder group which comprises the plurality of adjusting rudders 30, the adjusting rudders 30 are connected with the fairing 20 through the driving mechanism, when the taper sleeve body 10 bears airflow disturbance, the inevitable dislocation movement occurs, so that the posture and the height are changed, the driving mechanism is used for controlling the plurality of adjusting rudders 30 to respectively swing directionally, the airflow flow direction is changed, the taper sleeve body is made to move directionally, and the swinging amplitude and the swinging direction of the plurality of adjusting rudders 30 are continuously adjusted, so that the taper sleeve body 10 can be in a relatively stable state and height no matter how the airflow is interfered, and a stability foundation is provided for the recovery of the unmanned aerial vehicle; on this basis, through set up electro-magnet 11 in taper sleeve body 10, after unmanned aerial vehicle docks with the taper of taper sleeve body 10, even as an organic whole with unmanned aerial vehicle and taper sleeve body through electro-magnet 11 to thoroughly implement unmanned aerial vehicle's recovery.
Preferably, the rudder group comprises four adjusting rudders 30, and the four adjusting rudders 30 are arranged in an X shape.
Through setting up four adjustment rudders 30, make whole device can deal with the air current disturbance of each direction, be the X-shaped setting through setting up four adjustment rudders 30, be different from conventional cross setting, can provide bigger lift and adjustment rudders 30 control efficiency to can set up the space for other structures that set up on the taper sleeve body 10 give way, for example GPS antenna etc..
To further limit the specific implementation of the driving mechanism, the driving mechanism includes a plurality of servo steering engines 50, and the plurality of servo steering engines 50 correspond to the plurality of adjustment rudders 30 one by one; the adjusting rudder 30 comprises a connecting portion 31 and a swinging portion 32, the connecting portion 31 is connected with the side wall of the fairing 20, the servo steering engine 50 is embedded in the connecting portion 31 correspondingly, the output end of the servo steering engine 50 is connected with a rotating shaft 51 in a transmission mode, the rotating shaft 51 is arranged along the radial extension of the taper sleeve body 10, and the swinging portion 32 is sleeved on the rotating shaft 51.
Through setting up servo steering wheel 50, utilize servo steering wheel 50's directional swing, the transmission drives pivot 51 directional rotation to drive suit in the directional swing of swing portion 32 on pivot 51, in order to adapt to the air current of different conditions, adjust the state of whole device.
It should be noted that the transmission connection between the servo steering engine 50 and the rotating shaft 51 can be realized by any one of the methods in the prior art, such as gear transmission, coaxial connection, and transmission connection of a speed reducer, as long as the rotating shaft 51 can be driven to rotate by the servo steering engine 50.
For further explanation on the specific structure of the connecting part 31, the connecting part 31 is in a streamline plate shape, the plane of the connecting part 31 is coplanar with the axis of the taper sleeve body 10, a resistance reducing tip 311 is convexly arranged at the connecting part of the connecting part 31, which is close to the tip end of the taper sleeve body 10, and the fairing 20, and the windward side of the resistance reducing tip 311 is in streamline transition.
By arranging the connecting part 31 to be in a streamline plate shape, wind resistance is reduced and turbulence is prevented; by arranging the resistance reducing tip 311, the windward side of the connection part of the connecting part 31 and the fairing 20 is further smoothed, so that the windage is reduced, and the structure of the windward side connection part is prevented from being damaged due to excessive shearing force caused by airflow.
To explain the specific structure of the swing portion 32, the swing portion 32 is a streamlined plate, the plane of the swing portion 32 is flush with the plane of the connecting portion 31 in the initial state, and the cross section of the swing portion 32 in the thickness direction is in the shape of a droplet.
Form smooth transition for connecting portion 31 when reducing windage and air current disturbance through setting up swing portion 32, be the drop shape through the cross-section that sets up swing portion 32 thickness direction, when the directional wobbling in-process of swing portion 32 and after the swing, the outward appearance that all can pass through the drop shape reduces the windage to promote the adaptability to the air current disturbance.
Preferably, in order to further reduce the wind resistance, a side of the swing portion 32 close to the tip of the taper sleeve body 10 is provided with an inclined surface, so that the swing portion 32 has a trapezoidal plate shape, and a width of a side of the swing portion 32 away from the connecting portion 31 is smaller than a width of a side of the swing portion 32 close to the connecting portion 31.
Through the arrangement, on the premise of ensuring the structural performance and the turning performance of the swinging part 32, the wind resistance of the swinging part 32 is further reduced by using hydrodynamics.
In order to further explain the specific structure of the taper sleeve body 10, the conical surface of the taper sleeve body 10 is arranged in a streamline shape, the conical surface of the taper sleeve body 10 is hollowed out to form a plurality of guide wings 12 which are distributed annularly, the plane of the guide wings 12 is coplanar with the axis of the taper sleeve body 10, and the guide wings 12 extend from the tip of the taper sleeve body 10 to the taper mouth of the taper sleeve body 10.
The conical surface through setting up taper sleeve body 10 is streamlined to be the setting, tentatively reduces the windage, through with taper sleeve body 10 fretwork, under the condition of reducing taper sleeve body 10 weight, further utilizes the multi-disc water conservancy diversion wing 12 to carry out the stationary flow.
It should be noted that the specific shape of the guide vane 12 can be adaptively designed according to the actual use condition and the environmental condition.
In order to fix and limit the guide wings 12, a fixing ring 13 is arranged in a conical opening of the taper sleeve body 10, and outer rings of the fixing ring 13 are in cross-shaped insertion connection with the inner sides of all the guide wings 12.
Through setting up solid fixed ring 13, and make the outer loop of solid fixed ring 13 peg graft with the inboard cross of guide vane 12, the mode of utilizing the grafting carries out the structure to guide vane 12 fixed with spacing, prevent that guide vane 12 from taking place the swing when bearing the air current disturbance, buckling or fracture, and, the mode of adopting the cross grafting not only can implement fixedly, can also provide the activity space of certain degree on fixed basis, make solid fixed ring 13 and guide vane 12 not integrated into one piece, when bearing the air current, guide vane 12 inevitable vibration, if adopt integrated into one piece to cause guide vane 12 fracture or cracked, but adopt the mode of grafting can play the buffering effect of similar mortise-tenon joint, can effectively reduce guide vane 12 fracture or cracked possibility.
Similarly, in order to further prevent the fixed ring 13 from breaking or cracking when bearing the airflow, the fixed ring 13 is equally divided into a plurality of arc segments, and every two adjacent arc segments are inserted in mortise and tenon joints.
Preferably, in order to identify the range of the taper sleeve body 10 and facilitate the butt joint, the taper outer ring of the taper sleeve body 10 is annularly provided with a plurality of LED lamp bodies 14.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are merely exemplary embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (10)
1. An active taper sleeve for aerial recovery of an unmanned aerial vehicle, comprising:
the unmanned aerial vehicle recycling device comprises a taper sleeve body (10), wherein an electromagnet (11) is arranged in a taper opening of the taper sleeve body (10) and used for recycling the unmanned aerial vehicle;
the fairing (20) is sleeved outside the tip of the taper sleeve body (10);
the rudder group comprises a plurality of adjusting rudders (30), the adjusting rudders (30) are arranged on the side wall of the fairing (20) in a surrounding mode and are arranged along the radial direction of the taper sleeve body (10), the adjusting rudders (30) are connected with the fairing (20) through driving mechanisms, and the driving mechanisms are used for enabling the adjusting rudders (30) to swing directionally so as to enable the taper sleeve body (10) to move directionally;
and one end of the traction cable (40) is respectively connected with the tip end of the taper sleeve body (10), the driving mechanism and the electromagnet (11), and the other end of the traction cable (40) is connected with the external environment.
2. The active taper sleeve for aerial recovery of unmanned aerial vehicles according to claim 1, wherein the rudder group comprises four adjusting rudders (30), and the four adjusting rudders (30) are arranged in an X shape.
3. The active taper sleeve for aerial recovery of unmanned aerial vehicles according to claim 1 or 2, wherein the driving mechanism comprises a plurality of servo steering engines (50), and the plurality of servo steering engines (50) correspond to the plurality of adjusting rudders (30) one by one;
adjusting rudder (30) include connecting portion (31) and swing portion (32), connecting portion (31) with radome fairing (20) lateral wall is connected, servo steering wheel (50) bury underground in corresponding in connecting portion (31), the output transmission of servo steering wheel (50) is connected with pivot (51), pivot (51) are followed the radial extension of taper sleeve body (10), swing portion (32) suit in pivot (51).
4. The active taper sleeve used for unmanned aerial vehicle aerial recovery according to claim 3, wherein the connecting part (31) is in a streamline plate shape, the plane of the connecting part (31) is coplanar with the axis of the taper sleeve body (10), a resistance reducing tip (311) is convexly arranged on one side of the connecting part (31) close to the tip end of the taper sleeve body (10) and connected with the fairing (20), and the windward side of the resistance reducing tip (311) is in streamline transition.
5. The active taper sleeve for unmanned aerial vehicle aerial recovery according to claim 4, wherein the swinging portion (32) is in a streamline plate shape, the plane of the swinging portion (32) is flush with the plane of the connecting portion (31) in an initial state, and the cross section of the swinging portion (32) in the thickness direction is in a drop shape.
6. The active taper sleeve for unmanned aerial vehicle aerial recovery according to claim 5, wherein one side of the swinging portion (32) close to the tip of the taper sleeve body (10) is provided with an inclined surface, so that the swinging portion (32) is in a trapezoid plate shape, and the width of one side of the swinging portion (32) far away from the connecting portion (31) is smaller than that of one side of the swinging portion (32) close to the connecting portion (31).
7. The active taper sleeve for unmanned aerial vehicle aerial recovery according to claim 1, wherein the conical surface of the taper sleeve body (10) is arranged in a streamline shape, the conical surface of the taper sleeve body (10) is hollowed out to form a plurality of guide wings (12) which are distributed annularly, the plane of the guide wings (12) is coplanar with the axis of the taper sleeve body (10), and the guide wings (12) extend from the tip of the taper sleeve body (10) to the taper opening of the taper sleeve body (10).
8. The active taper sleeve for unmanned aerial vehicle aerial recovery according to claim 7, wherein a fixing ring (13) is arranged in a taper opening of the taper sleeve body (10), and an outer ring of the fixing ring (13) is inserted with an inner cross of all the guide wings (12).
9. The active taper sleeve for unmanned aerial vehicle aerial recovery according to claim 8, wherein the fixing rings (13) are equally divided into a plurality of arc segments, and two adjacent arc segments are in mortise-tenon connection.
10. The active taper sleeve for unmanned aerial vehicle aerial recovery according to claim 1, wherein the outer ring of the taper sleeve body (10) is annularly provided with a plurality of LED lamp bodies (14).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310084734.1A CN115783337A (en) | 2023-02-09 | 2023-02-09 | Active taper sleeve for aerial recovery of unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310084734.1A CN115783337A (en) | 2023-02-09 | 2023-02-09 | Active taper sleeve for aerial recovery of unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN115783337A true CN115783337A (en) | 2023-03-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310084734.1A Pending CN115783337A (en) | 2023-02-09 | 2023-02-09 | Active taper sleeve for aerial recovery of unmanned aerial vehicle |
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| Country | Link |
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| CN (1) | CN115783337A (en) |
Cited By (1)
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| CN117922831A (en) * | 2024-03-25 | 2024-04-26 | 中国空气动力研究与发展中心计算空气动力研究所 | Active control aerial refueling taper sleeve based on flexible control surface and control method |
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Application publication date: 20230314 |