CN117429651A - Unmanned aerial vehicle catapulting device suitable for marine environment - Google Patents
Unmanned aerial vehicle catapulting device suitable for marine environment Download PDFInfo
- Publication number
- CN117429651A CN117429651A CN202311546927.0A CN202311546927A CN117429651A CN 117429651 A CN117429651 A CN 117429651A CN 202311546927 A CN202311546927 A CN 202311546927A CN 117429651 A CN117429651 A CN 117429651A
- Authority
- CN
- China
- Prior art keywords
- limiting
- driving
- cylinder body
- sliding block
- chamber
- 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.)
- Granted
Links
- 238000013016 damping Methods 0.000 claims description 15
- 238000007789 sealing Methods 0.000 claims description 11
- 230000000149 penetrating effect Effects 0.000 claims description 7
- 238000009434 installation Methods 0.000 claims description 5
- 230000005307 ferromagnetism Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 4
- 239000012530 fluid Substances 0.000 description 10
- 230000002349 favourable effect Effects 0.000 description 8
- 230000033001 locomotion Effects 0.000 description 8
- 125000006850 spacer group Chemical group 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 239000013535 sea water Substances 0.000 description 2
- 229910001030 Iron–nickel alloy Inorganic materials 0.000 description 1
- 239000004677 Nylon Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 229920001778 nylon Polymers 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Actuator (AREA)
Abstract
The application relates to the field of unmanned aerial vehicle ejectors, in particular to an unmanned aerial vehicle ejection device suitable for a marine environment, which comprises a pulley bracket, a limiting assembly and a driving assembly; the limiting assembly comprises a limiting cylinder body, a limiting sliding block, a limiting spring and a limiting pin, wherein the limiting cylinder body is arranged on the ejection guide rail, the limiting sliding block is in sliding fit with the limiting cylinder body along the length direction of the ejection guide rail, one end of the limiting spring is arranged on the limiting sliding block, the other end of the limiting spring is arranged on the limiting cylinder body, the axis of the limiting spring is arranged along the sliding direction of the limiting sliding block, the limiting pin is arranged on the limiting sliding block, and after the pulley bracket falls down, the limiting pin is positioned at the top of the pulley bracket; the driving assembly is used for driving the limit sliding block to move in a sliding mode. The application has the effect that makes the coaster bracket be difficult for the resilience after falling down, reduces the condition of striking between coaster bracket and the unmanned aerial vehicle.
Description
Technical Field
The application relates to the field of unmanned aerial vehicle ejectors, in particular to an unmanned aerial vehicle ejection device suitable for marine environments.
Background
With the increasing maturity of unmanned aerial vehicle technology, unmanned aerial vehicles are gradually being applied to scan, detect or search for the ocean of comparatively complicated environment.
In the related art, an unmanned aerial vehicle generally needs to take off through an ejection device so as to obtain a sufficient initial speed in a short distance, thereby stably lifting off. For example, the Chinese patent application publication No. CN 102372091A discloses an ejection frame of a vehicle-mounted unmanned aerial vehicle, which consists of an ejection guide rail, an air accumulator and a pulley device, wherein the air accumulator is fixed on the outer side of the ejection guide rail, and an air outlet of the air accumulator is communicated with an air transmission pipeline extending from the interior of the ejection guide rail; the kinetic energy accelerator is arranged in the ejection guide rail, the bottom of the pulley device is connected with the kinetic energy accelerator, the other end of the gas transmission pipeline is connected with the kinetic energy accelerator, and the pulley device is of a parallelogram structure in an ejection state.
According to the invention, the kinetic energy accelerator is driven to slide along the ejection guide rail by high-pressure gas of the air accumulator, so that the parallelogram pulley device, namely the pulley bracket, slides, and the unmanned aerial vehicle placed on the pulley bracket obtains enough initial speed to stably lift off.
Aiming at the related technology, the parallelogram pulley bracket falls down after the unmanned aerial vehicle takes off, the fallen pulley bracket easily impacts the ejection guide rail and rebounds, and the rebounded pulley bracket easily impacts with the unmanned aerial vehicle to influence the take-off stability of the unmanned aerial vehicle.
Disclosure of Invention
In order to enable the tackle bracket not to rebound easily after falling down, the condition that collision occurs between the tackle bracket and the unmanned aerial vehicle is reduced, and the application provides an unmanned aerial vehicle catapulting device suitable for marine environment.
The application provides an unmanned aerial vehicle catapulting device suitable for marine environment adopts following technical scheme:
an unmanned aerial vehicle catapulting device suitable for marine environment comprises a pulley bracket, a limiting component and a driving component;
the limiting assembly comprises a limiting cylinder body, a limiting sliding block, a limiting spring and a limiting pin, wherein the limiting cylinder body is arranged on the ejection guide rail, the limiting sliding block is in sliding fit with the limiting cylinder body along the length direction of the ejection guide rail, one end of the limiting spring is arranged on the limiting sliding block, the other end of the limiting spring is arranged on the limiting cylinder body, the axis of the limiting spring is arranged along the sliding direction of the limiting sliding block, the limiting pin is arranged on the limiting sliding block, and after the pulley bracket falls down, the limiting pin is positioned at the top of the pulley bracket; the driving assembly is used for driving the limit sliding block to move in a sliding mode.
Through adopting above-mentioned technical scheme, coaster bracket is fallen the back, and drive assembly drive limit slider is along catapulting guide's length direction sliding motion for limit slider drives the spacer pin and stretches out along catapulting guide's length direction, and the spacer pin after stretching out is located the top of coaster bracket, thereby makes the coaster bracket be difficult to kick-back, has reduced the condition that takes place the striking between coaster bracket and the unmanned aerial vehicle. After the unmanned aerial vehicle takes off, the limiting sliding block and the limiting pin retract under the action of the limiting spring, so that the limiting pin does not limit the movement of the pulley bracket any more, and the unmanned aerial vehicle can be repeatedly ejected through the ejection device.
Optionally, the drive assembly includes drive cylinder body, drive slider, drive spring and drive plate, the drive cylinder body is installed in ejection guide rail, the drive slider slides along ejection guide rail's length direction and drive cylinder body and cooperates, one of them end of drive spring is installed in the drive slider, the other end of drive spring is installed in the drive cylinder body, the axis of drive spring sets up along the slip direction of drive slider, the drive plate is installed in the drive slider, during the drive slider sliding motion, the drive slider drives spacing slider sliding motion.
Through adopting above-mentioned technical scheme, unmanned aerial vehicle breaks away from the coaster bracket and takes off the back, coaster bracket striking drive plate for actuating spring discovers deformation, and then absorbs coaster bracket's impact force, is favorable to reducing the emergence of the condition that coaster bracket striking drive back along catapulting slide rail is kick-backed, thereby is favorable to further reducing the condition that takes place the striking between coaster bracket and the unmanned aerial vehicle. In addition, after the pulley bracket hits the driving plate, the driving plate drives the driving sliding block to slide, so that the limiting sliding block slides, dependence on a driving source is reduced, and the marine environment with complex conditions is convenient to adapt. Meanwhile, the driving slide block drives the limiting slide block to move, so that the limiting spring deforms, and the situation of collision between the pulley bracket and the unmanned aerial vehicle is reduced further.
Optionally, a limiting chamber is formed in the limiting cylinder body, and the limiting sliding block is in tight fit with the inner wall of the limiting chamber and is in sliding fit with the limiting chamber; the driving sliding block is in tight fit with the inner wall of the driving cavity and is in sliding fit with the driving cavity; the limiting cavity is communicated with the driving cavity, and oil is filled in the limiting cavity and the driving cavity.
Through adopting above-mentioned technical scheme, when driving slider sliding motion, the driving slider drives spacing slider sliding motion through spacing cavity and the fluid that fills in the driving cavity, is favorable to controlling catapulting device's volume, reduces the emergence of the condition that is difficult to the time of going up to use because of mechanical parts is corroded by sea water or rainwater for a long time.
Optionally, a damping plate is arranged in the limiting cavity or the driving cavity, and the damping plate is fixedly arranged on the inner wall of the limiting cavity or the inner wall of the driving cavity; the damping plate is provided with a plurality of through holes in a penetrating way.
Through adopting above-mentioned technical scheme, when driving slider sliding motion, the interior fluid of drive slider promotion drive chamber is towards spacing cavity flow for fluid passes the damping board through a plurality of through-holes, has increased the damping that fluid flows, is favorable to reducing the emergence of the condition that the sled bracket striking drive back was followed ejection slide rail and is kick-backed, thereby is favorable to further reducing the condition that takes place the striking between sled bracket and the unmanned aerial vehicle.
Optionally, a check hole is formed in the driving cylinder body, and the limiting cavity and the driving cavity are both communicated with the check hole;
the driving cylinder body is provided with a non-return opening and closing piece, and the non-return opening and closing piece comprises a non-return rubber plug, an adjusting rod and an adjusting seat; the check rubber plug is arranged in the check hole, the diameter size of one end of the check rubber plug is smaller than that of the other end of the check rubber plug, the smaller end of the check rubber plug faces the driving cavity, the larger end of the check rubber plug is in tight fit with the inner wall of the check hole, and the larger end of the check rubber plug is provided with an annular groove;
one end of the adjusting rod is arranged on the check rubber plug, the other end of the adjusting rod penetrates through the driving cylinder body and is in sliding fit with the driving cylinder body, the adjusting seat is arranged on the driving cylinder body, and one end of the adjusting rod penetrating through the driving cylinder body penetrates through the adjusting seat and is in threaded fit with the adjusting seat.
Through adopting above-mentioned technical scheme, when the fluid in the drive chamber flows towards spacing cavity under the effect of drive slider, the fluid passes through the non return hole and gets into in the spacing cavity. When the oil passes through the check hole, one end of the check rubber plug with larger diameter is retracted through the annular groove under the action of the oil, so that the oil passes through the check hole. After the fluid passes through the check hole, the great one end of check plug diameter size supports close fit in the inner wall of check hole for the fluid is difficult to backward flow to in the drive chamber, is favorable to guaranteeing the position stability of spacing slider and spacer pin.
After the unmanned aerial vehicle takes off, rotate and adjust the pole and make the non return plug keep away from the check hole for fluid in the spacing cavity flows back to in the drive cavity under spacing spring and spacing slider's effect, and then makes the spacer pin retract, thereby is favorable to repeatedly catapulting unmanned aerial vehicle through catapulting device.
Optionally, a sealing rubber cushion is arranged between the adjusting seat and the driving cylinder body, one side of the sealing rubber cushion is in tight fit with the driving cylinder body, and the other side of the sealing rubber cushion is in tight fit with the adjusting seat; the adjusting seat is arranged on the driving cylinder body through a plurality of fastening bolts, and the fastening bolts are circumferentially distributed around the axis of the adjusting seat.
Through adopting above-mentioned technical scheme, a plurality of fastening bolts make the both sides of sealed cushion support tight fit respectively in drive cylinder body and regulating seat, and then make the difficult self-limiting chamber of fluid and reveal in the drive chamber to be favorable to guaranteeing the leakproofness of spacing chamber and drive chamber.
Optionally, the ejection guide rail is provided with an ejection guide groove, the ejection guide groove extends to one end of the ejection guide rail along the length direction of the ejection guide rail, and the pulley bracket is in sliding fit with the ejection guide groove; the limiting cylinder body is fixedly arranged on the driving cylinder body, the driving cylinder body is fixedly provided with a mounting sliding block, and the mounting sliding block is in sliding fit with the ejection guide groove; the ejection guide rail is provided with a connecting cover, and the connecting cover is used for fixedly arranging the mounting sliding block on the ejection guide rail.
Through adopting above-mentioned technical scheme, when needing to launch unmanned aerial vehicle, make installation slider and ejection guide slot cooperation that slides, and then make drive cylinder body and spacing cylinder body all install in ejection guide rail, convenient and fast. After the driving cylinder body and the limiting cylinder body slide to the appointed position, the installation sliding block is fixedly arranged on the ejection guide rail through the connecting cover, and then the driving cylinder body and the limiting cylinder body are fixedly arranged at the appointed position, so that the driving cylinder body and the limiting cylinder body are favorably reduced from being deviated under the impact action of the pulley bracket, and the rebound of the pulley bracket is conveniently and effectively reduced.
Optionally, the connection cover is mounted on the ejection rail through a first bolt, and the connection cover is mounted on the mounting slider through a second bolt.
Through adopting above-mentioned technical scheme, the connecting cover makes installation slider and ejection guide rail interconnect, has not only increased the stability of junction between installation slider and the ejection guide rail, still makes ejection guide rail keep stable when coaster bracket catapult slides, reduces ejection guide rail and leads to the rigidity to descend because of the influence of ejection guide slot, is difficult to ensure the emergence of the condition of ejection guide rail straightness.
Optionally, the pulley bracket has ferromagnetism, the driving cylinder body is provided with a magnet, and when the pulley bracket falls down, the pulley bracket is adsorbed on the magnet.
Through adopting above-mentioned technical scheme, the coaster bracket is after falling down, and magnet adsorbs the coaster bracket for the coaster bracket is difficult to the resilience, has reduced the condition that takes place the striking between coaster bracket and the unmanned aerial vehicle.
Optionally, the magnet has seted up the butt caulking groove, the locking piece is installed through locking bolt to the drive cylinder body, the locking piece grafting is mated in butt caulking groove and in each inner wall of butt caulking groove in the tight fit.
By adopting the technical scheme, the locking block is in butt fit with the butt caulking groove, so that the magnet is fixedly arranged on the driving cylinder body. When the magnet needs to be replaced, the locking bolt is only required to be rotated to remove the locking block and replace the magnet, so that the occurrence of the conditions that the magnet is demagnetized under the condition of long-term impact and strong sunlight of the pulley bracket is reduced, and the service life of the ejection device is prolonged.
In summary, the present application includes at least one of the following beneficial technical effects:
1. after the pulley bracket falls down, the driving assembly drives the limiting slide block to slide along the length direction of the ejection guide rail, so that the limiting slide block drives the limiting pin to extend along the length direction of the ejection guide rail, and the extending limiting pin is positioned at the top of the pulley bracket, so that the pulley bracket is difficult to rebound, and the collision between the pulley bracket and the unmanned aerial vehicle is reduced. After the unmanned aerial vehicle takes off, the limiting sliding block and the limiting pin retract under the action of the limiting spring, so that the limiting pin does not limit the movement of the pulley bracket any more, and the unmanned aerial vehicle can be repeatedly ejected through the ejection device.
2. When the driving slide block slides, the driving slide block drives the limiting slide block to slide through the limiting cavity and the oil filled in the driving cavity, so that the volume of the ejection device is controlled, and the situation that the mechanical part is difficult to use for a long time due to corrosion of seawater or rainwater is reduced.
3. When the driving slide block slides, the driving slide block pushes the oil in the driving cavity to flow towards the limiting cavity, so that the oil passes through the damping plate through a plurality of through holes, the damping of the oil flow is increased, the rebound of the ejection slide rail along the ejection slide rail after the impact driving of the pulley bracket is reduced, and the impact between the pulley bracket and the unmanned aerial vehicle is further reduced.
Drawings
Fig. 1 is an overall schematic diagram of the overall structure of an embodiment of the present application.
FIG. 2 is an overall schematic of a pneumatic assembly and carriage of an embodiment of the present application.
FIG. 3 is a schematic cross-sectional view of a drive assembly and a stop assembly according to an embodiment of the present application.
Fig. 4 is a schematic view of a partial explosion of the overall structure of an embodiment of the present application.
Fig. 5 is an enlarged schematic view of a portion a of fig. 3.
Reference numerals illustrate: 1. an ejector rail; 11. ejection guide grooves; 12. ejecting an accelerating piece; 13. a connection cover; 131. a first bolt; 132. a second bolt; 2. a pneumatic assembly; 21. a gas storage tank; 22. an electromagnetic valve; 23. ejecting the catheter; 24. ejecting a piston rod; 25. a safety valve; 3. a sled carriage; 31. a bracket base plate; 32. a bracket link; 33. a bracket top plate; 4. a drive assembly; 41. a driving cylinder; 411. a drive chamber; 412. a damping plate; 413. a check hole; 414. installing a caulking groove; 415. a locking block; 42. driving a sliding block; 421. a first rubber ring; 422. a drive link; 43. a driving plate; 44. a drive spring; 45. installing a sliding block; 46. a non-return opening and closing member; 461. a non-return rubber plug; 462. an adjusting rod; 463. an adjusting seat; 464. a Grignard ring for the shaft; 465. a fastening bolt; 466. sealing rubber cushion; 5. a limit component; 51. a limit cylinder body; 511. a spacing chamber; 52. a limit sliding block; 521. a second rubber ring; 53. a limiting pin; 54. a limit spring; 6. a magnet; 61. abutting against the caulking groove.
Detailed Description
The present application is described in further detail below in conjunction with figures 1-5.
The embodiment of the application discloses unmanned aerial vehicle catapulting device suitable for marine environment. Referring to fig. 1, an unmanned aerial vehicle ejection device suitable for marine environments includes an ejection rail 1, a pneumatic assembly 2, a carriage bracket 3, a driving assembly 4, and a limit assembly 5.
Referring to fig. 1 and 2, the pneumatic assembly 2 includes an air reservoir 21, a solenoid valve 22, an ejector conduit 23, and an ejector piston rod 24. The gas holder 21 is ellipsoidal setting, and gas holder 21 fixed mounting is in the bottom of catapulting guide rail 1, and the axis of gas holder 21 sets up along the length direction of catapulting guide rail 1 to guarantee the portability of unmanned aerial vehicle catapulting device suitable for marine environment. The gas outlet of gas holder 21 communicates in the input of solenoid valve 22, and the output of solenoid valve 22 is connected with safety valve 25, and safety valve 25 selects the ball valve in this application embodiment. A safety valve 25 is connected to the ejector conduit 23 and a solenoid valve 22 is arranged near one end of the ejector rail 1. The ejection chamber is arranged in the ejection conduit 23, extends to two ends of the ejection conduit 23 along the length direction of the ejection conduit 23, and is communicated with the output end of the electromagnetic valve 22, so that the air flow entering the ejection chamber can be regulated by the electromagnetic valve 22, and the stability of the air flow is ensured.
Referring to fig. 2, one end of the ejector piston rod 24 is slidably fitted in the ejector chamber, and the ejector piston rod 24 is tightly fitted to the inner wall of the ejector chamber, so that the ejector piston rod 24 is slidably driven by the gas in the gas tank 21.
Referring to fig. 1 and 2, the ejector rail 1 is provided with an ejector guide groove 11, and the ejector guide groove 11 extends along the length of the ejector rail 1 to an end of the ejector rail 1 away from the solenoid valve 22. The ejection guide groove 11 is slidably matched with the ejection accelerator 12, and the ejection accelerator 12 is fixedly arranged on the ejection piston rod 24 through an ejection connecting block so as to drive the ejection accelerator 12 to slide along the ejection guide groove 11 through the ejection piston rod 24.
Referring to fig. 2, the sled carriage 3 includes a carriage bottom plate 31, a carriage link 32, and a carriage top plate 33. The bracket bottom plate 31 is rectangular, and the bottom of the bracket bottom plate 31 is fixedly arranged on the ejection accelerating element 12 so as to drive the bracket bottom plate 31 to move along the length direction of the ejection guide rail 1 through the ejection accelerating element 12. The bracket links 32 are provided in four, and the four bracket links 32 are provided near the corners of the bracket bottom plate 31, respectively. One end of the bracket link 32 is hinged to the top of the bracket base 31 so as to rotatably reset the bracket link 32. The other end of the bracket connecting rod 32 is hinged to the top of the bracket top plate 33, and the bracket bottom plate 31, the bracket top plate 33 and each bracket connecting rod 32 are arranged in a parallelogram shape, so that the bracket top plate 33 falls down after the unmanned aerial vehicle takes off, and the occurrence of the condition that the bracket top plate 33 impacts the unmanned aerial vehicle is reduced.
Referring to fig. 1 and 3, a drive assembly 4 is provided near one end of the ejector rail 1, the drive assembly 4 comprising a drive cylinder 41, a drive slide 42, a drive plate 43 and a drive spring 44. The driving cylinder 41 is arranged in a cuboid shape, the bottom of the driving cylinder 41 is fixedly provided with a mounting sliding block 45, and the mounting sliding block 45 is in sliding fit with the ejection guide groove 11 so as to conveniently mount the driving cylinder 41 on the ejection guide rail 1 and conveniently adjust the mounting position of the driving cylinder 41.
Referring to fig. 4, one end of the ejector rail 1 is mounted with a connection cover 13 by a first bolt 131, and the connection cover 13 is disposed close to the driving cylinder 41. The connection cover 13 is mounted to the mounting slider 45 by the second bolt 132 so as to lock the position of the mounting slider 45 and to facilitate the disassembly or the mounting of the connection cover 13.
Referring to fig. 3, a driving chamber 411 is opened inside the driving cylinder 41, and the inside of the driving chamber 411 is filled with oil. The driving slider 42 is disposed in the driving chamber 411, and the driving slider 42 is slidably engaged with the driving chamber 411, and the driving slider 42 is tightly engaged with the inner wall of the driving chamber 411 through two first rubber rings 421, so as to reduce oil leakage.
Referring to fig. 3, a driving link 422 is fixedly installed at one side of the driving slider 42, the driving link 422 is disposed along a length direction of the ejection slide rail, and the driving link 422 is penetrated through the driving cylinder 41 and slidably engaged with the driving cylinder 41. One end of the driving connecting rod 422 penetrating through the driving cylinder 41 is fixedly provided with a driving connecting plate, the driving plate 43 is mounted at the bottom of the driving connecting plate through bolts, and the material of the driving plate 43 is nylon so as to increase the wear resistance of the driving plate 43 and facilitate replacement of the driving plate 43. The driving plate 43 is slidably fitted in the ejection guide groove 11 so as to ensure stability when the driving plate 43 moves.
Referring to fig. 3, the driving spring 44 is sleeved on the driving link 422, one end of the driving spring 44 is fixedly installed on the driving slider 42, the other end of the driving spring 44 is fixedly installed on the inner wall of the driving chamber 411, and the axis of the driving spring 44 is arranged along the sliding direction of the driving slider 42, so as to reset the driving slider 42 and absorb impact load.
Referring to fig. 3, a damping plate 412 is disposed in the driving chamber 411, and the damping plate 412 is fixedly installed to an inner wall of the driving chamber 411. The damping plate 412 has a plurality of through holes formed therethrough so as to increase damping of the oil flow through the plurality of through holes when the driving slider 42 pushes the oil flow, thereby further absorbing impact load.
Referring to fig. 3 and 5, a circular check hole 413 is opened in the driving cylinder 41, and the check hole 413 communicates with the driving chamber 411. The driving cylinder 41 is provided with a check opening and closing member 46, and the check opening and closing member 46 includes a check rubber plug 461, an adjusting lever 462, and an adjusting seat 463. The check rubber stopper 461 is arranged in a truncated cone shape, namely, the diameter size of one end of the check rubber stopper 461 is smaller than that of the other end of the check rubber stopper 461. The check rubber stopper 461 is disposed in the check hole 413, and the larger diameter end of the check rubber stopper 461 is tightly matched with the inner wall of the check hole 413, so that oil is difficult to enter the driving chamber 411 from the check hole 413.
Referring to fig. 5, an annular groove is formed at one end of the check rubber stopper 461 with larger diameter, the annular groove is connected in an end-to-end closing manner and is coaxially arranged with the check rubber stopper 461, so that oil in the driving chamber 411 can squeeze the check rubber stopper 461, the check rubber stopper 461 is deformed through the annular groove, and oil in the driving chamber 411 can conveniently pass through the check hole 413 from the driving chamber 411.
Referring to fig. 5, an adjusting hole is opened at the outer circumferential surface of the driving cylinder 41, and the adjusting hole communicates with the check hole 413. One end of the check rubber plug 461 provided with an annular groove is coaxially and fixedly connected with a sliding rod which is in sliding fit with the adjusting hole. The slide bar is coaxially and fixedly sleeved with a shaft gray ring, and the shaft gray ring is in tight fit with the inner wall of the adjusting hole and is in sliding fit with the adjusting hole so as to ensure the tightness of the adjusting hole.
Referring to fig. 5, an adjusting rod 462 is fixedly connected to one end of the sliding rod, which is far away from the check rubber plug 461, the adjusting rod 462 is penetrated through the adjusting hole, and a gap is provided between the outer circumferential surface of the adjusting rod 462 and the inner wall of the adjusting hole. The adjustment seat 463 is provided near the adjustment hole, and the adjustment seat 463 is mounted on the outer peripheral surface of the drive cylinder 41 by a plurality of fastening bolts 465, and the plurality of fastening bolts 465 are uniformly distributed around the axial line circumference of the adjustment seat 463. A sealing rubber gasket 466 is arranged between the adjusting seat 463 and the outer peripheral surface of the driving cylinder 41, one side of the sealing rubber gasket 466 is in tight fit with the driving cylinder 41, and the other side of the sealing rubber gasket 466 is in tight fit with the adjusting seat 463, so that oil leaking from the adjusting hole is reduced through the sealing rubber gasket 466.
Referring to fig. 5, one end of the adjusting rod 462 penetrating through the adjusting hole penetrates through the adjusting seat 463 and is in threaded fit with the adjusting seat 463, and a knob is fixedly mounted at one end of the adjusting rod 462 penetrating through the adjusting seat 463, so that an operator can rotate the adjusting rod 462 conveniently.
Referring to fig. 3, a limit assembly 5 is disposed at the top of the driving cylinder 41, and the limit assembly 5 includes a limit cylinder 51, a limit slider 52, a limit pin 53, and a limit spring 54. The limit cylinder 51 is fixedly mounted on the top of the drive cylinder 41, and the drive cylinder 41 and the limit cylinder 51 are arranged in a form of a back table, i.e. a table top is arranged on the top of the drive cylinder 41.
Referring to fig. 3, a limiting chamber 511 is provided inside the limiting cylinder 51, the limiting chamber 511 is communicated with the check hole 413, and oil is filled inside the limiting chamber 511. The limiting slide block 52 is arranged in the limiting chamber 511, the limiting slide block 52 is in sliding fit with the limiting chamber 511, and the limiting slide block 52 is in tight fit with the inner wall of the limiting chamber 511 through the second rubber ring 521, so that the occurrence of oil leakage is reduced.
Referring to fig. 3, a limit link is fixedly installed at one side of the limit slider 52, the limit link is disposed along the length direction of the ejection slide rail, and the limit link penetrates through the limit cylinder 51 and is slidably engaged with the limit cylinder 51. The limiting pin 53 is fixedly arranged at one end of the limiting connecting rod penetrating through the limiting rod body, a gap is formed between the limiting pin 53 and the table top of the driving cylinder 41, and one end, far away from the limiting connecting rod, of the limiting pin 53 is arranged in an arc shape, so that smooth extension of the limiting pin 53 is ensured.
Referring to fig. 3, a limit spring 54 is sleeved on the limit link, one end of the limit spring 54 is fixedly mounted on the limit slider 52, the other end of the limit spring 54 is fixedly mounted on the inner wall of the limit chamber 511, and the axis of the limit spring 54 is arranged along the sliding direction of the limit slider 52, so that the limit pin 53 is retracted and reset through the elasticity of the limit spring 54.
Referring to fig. 1 and 3, the carrier top plate 33 has ferromagnetism, and in the embodiment of the present application, the material of the carrier top plate 33 is selected to be nickel-iron alloy. The mounting caulking groove 414 is formed in the table top of the driving cylinder 41, and the magnet 6 is embedded in the mounting caulking groove 414, so that the bracket top plate 33 is adsorbed by the magnet 6, and the rebound of the bracket top plate 33 is reduced. The magnet 6 is provided with the abutting caulking groove 61, the driving cylinder 41 is provided with the locking block 415 through the locking bolt, the locking block 415 is in plug-in fit with the abutting caulking groove 61 and is in tight fit with each inner wall of the abutting caulking groove 61, and the locking block 415 is in tight fit with the magnet 6, so that the demagnetized magnet 6 is replaced.
The implementation principle of the unmanned aerial vehicle ejection device suitable for the marine environment is as follows: the ejector rail 1 is set and fixed obliquely, and then the solenoid valve 22 is opened. After the electromagnetic valve 22 is opened, the gas in the gas storage tank 21 enters the ejection guide pipe 23 to drive the ejection piston rod 24 to move, so that the ejection piston rod 24 drives the bracket bottom plate 31 to slide along the ejection sliding rail through the ejection accelerator 12.
After the ejection accelerator 12 slides along the ejection slide rail and impacts the driving plate 43, the bracket top plate 33 continues to move with the unmanned aerial vehicle under the action of inertia and gradually falls down and is far away from the unmanned aerial vehicle, so that the unmanned aerial vehicle obtains the initial speed required for taking off.
After the carrier top plate 33 falls down, it moves in a direction approaching the magnet 6 and is attracted and fixed by the magnet 6, so that it is difficult for the carrier top plate 33 to rebound after striking the drive cylinder 41. During the falling of the carrier top plate 33, the driving plate 43 causes the driving slider 42 to push the oil in the driving chamber 411 into the limiting chamber 511 through the check hole 413. After the oil enters the limiting chamber 511, the limiting slide block 52 drives the limiting connecting rod to slide, and when the bracket top plate 33 is adsorbed on the magnet 6, the limiting pin 53 extends out to the top plate of the bracket top plate 33, so that the bracket top plate 33 is more difficult to rebound after impacting the driving cylinder 41, the bracket top plate 33, namely the pulley bracket 3, is difficult to rebound, and the impact between the pulley bracket 3 and the unmanned aerial vehicle is reduced.
The foregoing are all preferred embodiments of the present application, and are not intended to limit the scope of the present application in any way, therefore: all equivalent changes in structure, shape and principle of this application should be covered in the protection scope of this application.
Claims (10)
1. Unmanned aerial vehicle catapulting device suitable for marine environment, its characterized in that: comprises a pulley bracket (3), a limiting component (5) and a driving component (4);
the limiting assembly (5) comprises a limiting cylinder body (51), a limiting sliding block (52), a limiting spring (54) and a limiting pin (53), wherein the limiting cylinder body (51) is installed on the ejection guide rail (1), the limiting sliding block (52) is in sliding fit with the limiting cylinder body (51) along the length direction of the ejection guide rail (1), one end of the limiting spring (54) is installed on the limiting sliding block (52), the other end of the limiting spring (54) is installed on the limiting cylinder body (51), the axis of the limiting spring (54) is arranged along the sliding direction of the limiting sliding block (52), the limiting pin (53) is installed on the limiting sliding block (52), and after the pulley bracket (3) falls down, the limiting pin (53) is located at the top of the pulley bracket (3); the driving assembly (4) is used for driving the limit sliding block (52) to move in a sliding mode.
2. The unmanned aerial vehicle ejection device suitable for marine environments according to claim 1, wherein: the driving assembly (4) comprises a driving cylinder body (41), a driving sliding block (42), a driving spring (44) and a driving plate (43), wherein the driving cylinder body (41) is installed on the ejection guide rail (1), the driving sliding block (42) is in sliding fit with the driving cylinder body (41) along the length direction of the ejection guide rail (1), one end of the driving spring (44) is installed on the driving sliding block (42), the other end of the driving spring (44) is installed on the driving cylinder body (41), the axis of the driving spring (44) is arranged along the sliding direction of the driving sliding block (42), the driving plate (43) is installed on the driving sliding block (42), and when the driving sliding block (42) moves in a sliding mode, the driving sliding block (42) drives the limiting sliding block (52) to move in a sliding mode.
3. The unmanned aerial vehicle ejection device suitable for marine environments according to claim 2, wherein: a limiting chamber (511) is formed in the limiting cylinder body (51), and the limiting sliding block (52) is in tight fit with the inner wall of the limiting chamber (511) and is in sliding fit with the limiting chamber (511); a driving chamber (411) is formed in the driving cylinder body (41), and the driving sliding block (42) is in tight fit with the inner wall of the driving chamber (411) and is in sliding fit with the driving chamber (411); the limiting chamber (511) is communicated with the driving chamber (411), and oil is filled in both the limiting chamber (511) and the driving chamber (411).
4. The unmanned aerial vehicle ejection device suitable for use in a marine environment of claim 3, wherein: a damping plate (412) is arranged in the limiting chamber (511) or the driving chamber (411), and the damping plate (412) is fixedly arranged on the inner wall of the limiting chamber (511) or the inner wall of the driving chamber (411); the damping plate (412) is provided with a plurality of through holes.
5. The unmanned aerial vehicle ejection device suitable for use in a marine environment of claim 3, wherein: a check hole (413) is formed in the driving cylinder body (41), and the limiting chamber (511) and the driving chamber (411) are communicated with the check hole (413);
the driving cylinder body (41) is provided with a non-return opening and closing piece (46), and the non-return opening and closing piece (46) comprises a non-return rubber plug (461), an adjusting rod (462) and an adjusting seat (463); the check rubber plug (461) is arranged in the check hole (413), the diameter size of one end of the check rubber plug (461) is smaller than that of the other end of the check rubber plug (461), the smaller diameter end of the check rubber plug (461) is arranged towards the driving chamber (411), the larger diameter end of the check rubber plug (461) is in tight fit with the inner wall of the check hole (413), and the larger diameter end of the check rubber plug (461) is provided with an annular groove;
one end of the adjusting rod (462) is installed on the check rubber plug (461), the other end of the adjusting rod (462) penetrates through the driving cylinder body (41) and is in sliding fit with the driving cylinder body (41), the adjusting seat (463) is installed on the driving cylinder body (41), and one end of the adjusting rod (462) penetrating through the driving cylinder body (41) penetrates through the adjusting seat (463) and is in threaded fit with the adjusting seat (463).
6. The unmanned aerial vehicle ejection device suitable for marine environments of claim 5, wherein: a sealing rubber cushion (466) is arranged between the adjusting seat (463) and the driving cylinder body (41), one side of the sealing rubber cushion (466) is in tight fit with the driving cylinder body (41), and the other side of the sealing rubber cushion (466) is in tight fit with the adjusting seat (463); the adjusting seat (463) is mounted on the driving cylinder body (41) through a plurality of fastening bolts (465), and the fastening bolts (465) are circumferentially distributed around the axis of the adjusting seat (463).
7. The unmanned aerial vehicle ejection device suitable for use in a marine environment of claim 3, wherein: the ejection guide rail (1) is provided with an ejection guide groove (11), the ejection guide groove (11) extends to one end of the ejection guide rail (1) along the length direction of the ejection guide rail (1), and the pulley bracket (3) is in sliding fit with the ejection guide groove (11); the limiting cylinder body (51) is fixedly arranged on the driving cylinder body (41), the driving cylinder body (41) is fixedly provided with a mounting sliding block (45), and the mounting sliding block (45) is in sliding fit with the ejection guide groove (11); the ejector rail (1) is provided with a connecting cover (13), and the connecting cover (13) is used for fixedly arranging an installation sliding block (45) on the ejector rail (1).
8. The unmanned aerial vehicle ejection device suitable for use in a marine environment of claim 7, wherein: the connecting cover (13) is mounted on the ejection guide rail (1) through a first bolt (131), and the connecting cover (13) is mounted on the mounting sliding block (45) through a second bolt (132).
9. The unmanned aerial vehicle ejection device suitable for marine environments according to claim 2, wherein: the pulley bracket (3) has ferromagnetism, the magnet (6) is arranged on the driving cylinder body (41), and when the pulley bracket (3) falls down, the pulley bracket (3) is adsorbed on the magnet (6).
10. The unmanned aerial vehicle ejection device suitable for use in a marine environment of claim 9, wherein: the magnet (6) is provided with an abutting caulking groove (61), the driving cylinder body (41) is provided with a locking block (415) through a locking bolt, and the locking block (415) is in plug-in fit with the abutting caulking groove (61) and is in tight fit with each inner wall of the abutting caulking groove (61).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311546927.0A CN117429651B (en) | 2023-11-17 | 2023-11-17 | Unmanned aerial vehicle catapulting device suitable for marine environment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311546927.0A CN117429651B (en) | 2023-11-17 | 2023-11-17 | Unmanned aerial vehicle catapulting device suitable for marine environment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117429651A true CN117429651A (en) | 2024-01-23 |
| CN117429651B CN117429651B (en) | 2024-03-19 |
Family
ID=89558228
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311546927.0A Active CN117429651B (en) | 2023-11-17 | 2023-11-17 | Unmanned aerial vehicle catapulting device suitable for marine environment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117429651B (en) |
Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100096496A1 (en) * | 2008-10-20 | 2010-04-22 | Aai Corporation | Sliding frame aircraft launcher and related method |
| CN201761645U (en) * | 2010-08-27 | 2011-03-16 | 广州天海翔航空科技有限公司 | Vehicle-mounted unmanned aircraft ejecting frame |
| CN102372091A (en) * | 2010-08-27 | 2012-03-14 | 广州天海翔航空科技有限公司 | Launching cradle for vehicle-mounted unmanned aerial vehicle |
| CN205738139U (en) * | 2016-06-07 | 2016-11-30 | 广州天海翔航空科技有限公司 | A kind of plateau unmanned aircraft ejecting frame |
| CN107089345A (en) * | 2017-04-11 | 2017-08-25 | 西安君晖航空科技有限公司 | A kind of unmanned aerial vehicle ejecting frame dolly tripping mechanism |
| CN207029576U (en) * | 2017-04-11 | 2018-02-23 | 西安君晖航空科技有限公司 | A kind of unmanned aerial vehicle ejecting frame dolly tripping mechanism |
| CN109436364A (en) * | 2018-10-22 | 2019-03-08 | 南京航空航天大学 | A kind of device and method continuously emitted for unmanned plane |
| CN209776830U (en) * | 2019-03-28 | 2019-12-13 | 河南机电职业学院 | Vehicle-mounted take-off device of unmanned aerial vehicle with parallelogram structure |
| CN210761355U (en) * | 2019-09-25 | 2020-06-16 | 广州天海翔航空科技有限公司 | General type unmanned aerial vehicle launching cradle |
| CN111994579A (en) * | 2020-08-10 | 2020-11-27 | 广东原点智能技术有限公司 | Engine cylinder block transportation subassembly that slides |
| RU205857U1 (en) * | 2021-04-16 | 2021-08-11 | Федеральное государственное бюджетное военное образовательное учреждение высшего образования "Черноморское высшее военно-морское ордена Красной Звезды училище имени П.С. Нахимова" Министерства обороны Российской Федерации (г. Севастополь) | SHIP TAKE-OFF AND LANDING DEVICE FOR UNMANNED AIRCRAFT TYPE SHORT AND MEDIUM RANGE |
| CN113479340A (en) * | 2021-07-23 | 2021-10-08 | 航天时代飞鹏有限公司 | Unmanned aerial vehicle ejection method |
| CN214729763U (en) * | 2021-06-08 | 2021-11-16 | 深圳化骨龙科技有限公司 | A jettison device for unmanned aerial vehicle assists takes off |
| CN114760786A (en) * | 2022-04-14 | 2022-07-15 | 湖北航天技术研究院总体设计所 | Dense bee colony load honeycomb firework type installation mechanism and release device |
| CN115675908A (en) * | 2022-11-02 | 2023-02-03 | 河南工业职业技术学院 | Launching mechanism of pneumatic track ejection aircraft |
| CN116639255A (en) * | 2023-05-31 | 2023-08-25 | 中国人民解放军国防科技大学 | Aircraft transmitting system and aircraft |
-
2023
- 2023-11-17 CN CN202311546927.0A patent/CN117429651B/en active Active
Patent Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100096496A1 (en) * | 2008-10-20 | 2010-04-22 | Aai Corporation | Sliding frame aircraft launcher and related method |
| CN201761645U (en) * | 2010-08-27 | 2011-03-16 | 广州天海翔航空科技有限公司 | Vehicle-mounted unmanned aircraft ejecting frame |
| CN102372091A (en) * | 2010-08-27 | 2012-03-14 | 广州天海翔航空科技有限公司 | Launching cradle for vehicle-mounted unmanned aerial vehicle |
| CN205738139U (en) * | 2016-06-07 | 2016-11-30 | 广州天海翔航空科技有限公司 | A kind of plateau unmanned aircraft ejecting frame |
| CN107089345A (en) * | 2017-04-11 | 2017-08-25 | 西安君晖航空科技有限公司 | A kind of unmanned aerial vehicle ejecting frame dolly tripping mechanism |
| CN207029576U (en) * | 2017-04-11 | 2018-02-23 | 西安君晖航空科技有限公司 | A kind of unmanned aerial vehicle ejecting frame dolly tripping mechanism |
| CN109436364A (en) * | 2018-10-22 | 2019-03-08 | 南京航空航天大学 | A kind of device and method continuously emitted for unmanned plane |
| CN209776830U (en) * | 2019-03-28 | 2019-12-13 | 河南机电职业学院 | Vehicle-mounted take-off device of unmanned aerial vehicle with parallelogram structure |
| CN210761355U (en) * | 2019-09-25 | 2020-06-16 | 广州天海翔航空科技有限公司 | General type unmanned aerial vehicle launching cradle |
| CN111994579A (en) * | 2020-08-10 | 2020-11-27 | 广东原点智能技术有限公司 | Engine cylinder block transportation subassembly that slides |
| RU205857U1 (en) * | 2021-04-16 | 2021-08-11 | Федеральное государственное бюджетное военное образовательное учреждение высшего образования "Черноморское высшее военно-морское ордена Красной Звезды училище имени П.С. Нахимова" Министерства обороны Российской Федерации (г. Севастополь) | SHIP TAKE-OFF AND LANDING DEVICE FOR UNMANNED AIRCRAFT TYPE SHORT AND MEDIUM RANGE |
| CN214729763U (en) * | 2021-06-08 | 2021-11-16 | 深圳化骨龙科技有限公司 | A jettison device for unmanned aerial vehicle assists takes off |
| CN113479340A (en) * | 2021-07-23 | 2021-10-08 | 航天时代飞鹏有限公司 | Unmanned aerial vehicle ejection method |
| CN114760786A (en) * | 2022-04-14 | 2022-07-15 | 湖北航天技术研究院总体设计所 | Dense bee colony load honeycomb firework type installation mechanism and release device |
| CN115675908A (en) * | 2022-11-02 | 2023-02-03 | 河南工业职业技术学院 | Launching mechanism of pneumatic track ejection aircraft |
| CN116639255A (en) * | 2023-05-31 | 2023-08-25 | 中国人民解放军国防科技大学 | Aircraft transmitting system and aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117429651B (en) | 2024-03-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102094926B (en) | Potential energy storage type protruding undercarriage buffer | |
| US7559398B2 (en) | Lifting device | |
| CN111609073B (en) | Aircraft landing gear buffer | |
| CN117429651B (en) | Unmanned aerial vehicle catapulting device suitable for marine environment | |
| CN213451090U (en) | Multi-stage linkage telescopic gas-liquid driving device | |
| CN110542348A (en) | Pressure-release reverse buffer and method for reversing recoil of buffer | |
| CN105673761A (en) | Hydraulic buffer with multi-stage damping throttles and hydraulic buffering method | |
| CN204878500U (en) | Hydraulic absorber of multistage damping throttle | |
| CN202451495U (en) | Pneumatic cylinder applied to automobile crash test | |
| US3052328A (en) | Hydraulic decelerating device | |
| CN108006148B (en) | Four-gear ultra-strong impact resistant automobile energy storage shock absorber | |
| CN218583887U (en) | Recoil buffering device for ejection | |
| US20020184997A1 (en) | Double acting cylinder with integral end position volume chambers | |
| CN202545417U (en) | Floating buffer plunger structure | |
| CN113790232B (en) | Water vat buffer | |
| CN215980553U (en) | Water vat buffer | |
| CN219570713U (en) | High-energy oil pressure buffer | |
| CN218953903U (en) | Flow-adjustable buffer | |
| CN215984197U (en) | High-energy-level emission and multi-level braking test system | |
| EP2202477B1 (en) | Watertight loading device for spearguns | |
| CN220337356U (en) | Damping-adjustable single-arm front fork shock absorber | |
| CN217764669U (en) | Air pressure reinforcing device based on air cannon | |
| CN115388288B (en) | Sensor fixing device | |
| CN115848547B (en) | Front fork damping mechanism based on electric vehicle buffering | |
| RU112967U1 (en) | VEHICLE SHOCK ABSORBER |
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 |