CN108202876B - Guarantor type unmanned aerial vehicle launches draw gear - Google Patents
Guarantor type unmanned aerial vehicle launches draw gear Download PDFInfo
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- CN108202876B CN108202876B CN201611163749.3A CN201611163749A CN108202876B CN 108202876 B CN108202876 B CN 108202876B CN 201611163749 A CN201611163749 A CN 201611163749A CN 108202876 B CN108202876 B CN 108202876B
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- 230000000087 stabilizing effect Effects 0.000 claims abstract description 13
- 230000033001 locomotion Effects 0.000 claims abstract description 11
- 230000000694 effects Effects 0.000 abstract description 5
- 230000005484 gravity Effects 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 5
- 210000000245 forearm Anatomy 0.000 description 3
- 230000006641 stabilisation Effects 0.000 description 3
- 238000011105 stabilization Methods 0.000 description 3
- 101000606504 Drosophila melanogaster Tyrosine-protein kinase-like otk Proteins 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000011982 device technology Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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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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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention provides a shape-preserving unmanned aerial vehicle ejection traction device, when an unmanned aerial vehicle is fixed on a stable support module, the unmanned aerial vehicle can be automatically closed at a preset position of the traction device under the action of gravity due to the existence of an emission angle under the rotation of the stable support module, so that the effect of stabilizing the unmanned aerial vehicle is completed, and at the moment, a spring lock pin is pulled up and locked in a concave lock groove at a corresponding position on the body; when the unmanned aerial vehicle is ejected, the spring lock pin can also generate a thrust consistent with the movement direction of the traction device to push the unmanned aerial vehicle and the traction device to move together; stop motion behind draw gear motion to slide rail front end buffer, continue the motion under the effect of inertial force at unmanned aerial vehicle to promote draw gear's stable support module and rotate the rocking arm and revolute the rotation of axes, stable support module expands to the outside respectively, removes the fixed to unmanned aerial vehicle, and unmanned aerial vehicle accomplishes and leaves the rail action of taking off.
Description
Technical Field
The invention relates to an aviation mechanical device technology, in particular to a shape-preserving unmanned aerial vehicle ejection traction device.
Background
Currently, unmanned aerial vehicles have been widely used in many fields such as tactical reconnaissance, target positioning, target damage assessment, electronic countermeasure, communication relay, and the like. The on-site launching preparation time of the maritime reconnaissance and striking unmanned aerial vehicle is short, and strict requirements are also met on a launching site and a launching mode. Therefore, a safe and reliable catapult-launching device must be used. The ejection and emission mode is divided into pneumatic ejection or rubber band ejection according to a power source. No matter which mode is adopted, the aircraft needs to be pulled by the traction device, the aircraft is guaranteed to be boosted and slide in an accelerated mode along the track, the requirement on the off-track speed is finally met, and the catapult-assisted take-off process is completed. The traction device needs to complete the key tasks of statically locking the airplane, stabilizing the airplane on the rail and quickly disengaging from the rail under the traction of the catapult.
In the prior art, structures such as an externally hung launching sliding block of a fuselage are mostly adopted during catapult takeoff of an unmanned aerial vehicle, and launching takeoff action is completed in a mode of pushing the externally hung sliding block through a boosting device, but the connection mode usually needs a corresponding force transmission structure in the fuselage, so that normal layout of a fuselage mechanism or a wing structure is influenced, and sometimes conflict occurs with an internal oil tank or other task load arrangement. In addition, the airframe hanging object influences the flow field distribution of airflow on the surface of the wing to a certain extent, so that external interference and resistance are introduced in the flying process of the airplane after launching and lifting off, and the flying performance of the unmanned aerial vehicle is influenced. The invention provides a nondestructive launching traction device for guaranteeing the pneumatic appearance of an unmanned aerial vehicle, and solves the problem that the pneumatic characteristic of the unmanned aerial vehicle is influenced when an externally-hung launching slider is arranged on the surface of the unmanned aerial vehicle in the existing unmanned aerial vehicle launching process.
Disclosure of Invention
The invention relates to a shape-preserving unmanned aerial vehicle ejection traction device which comprises an ejection launcher, a traction device, a stable structure module, a traction tackle module, a first rotating rocker arm, a fixed oblique arm, a second rotating rocker arm, a spring lock pin, a slide rail, a horizontal pulley and a vertical pulley. The slide rail sets up on launching cradle, pull the coaster module and pass through horizontal pulley under draw gear's traction, reciprocal linear motion is along the slide rail to perpendicular pulley, stable structure module sets up a left side, right side two parts just are used for jointly bearing unmanned aerial vehicle, fixed forearm sets up two and is fixed in the slope of pulling coaster module both sides and about the vertical symmetry of unmanned aerial vehicle through the connecting rod, first rotation rocking arm sets up two and sets up respectively in the fixed forearm up end that corresponds and along rotation axis rotation and with the stable structure module fixed connection who corresponds, the second rotates the rocking arm and sets up two and sets up respectively in the fixed forearm down end that corresponds and just along rotation axis rotation and with the stable structure module fixed connection who corresponds, the spring lockpin sets up two and is located respectively about stable structure module on two parts and match with the spill locked groove on the unmanned aerial vehicle fuselage.
By adopting the device, the stable structure module is provided with a left part and a right part, and each part comprises a first connecting rod, a second connecting rod, a third connecting rod, a fourth connecting rod, a fifth connecting rod, a wing shape-preserving supporting seat and a fuselage stable supporting bracket; fuselage outrigger bracket is fixed in first rotation rocking arm, first connecting rod is fixed in fuselage outrigger bracket upper portion, the third connecting rod is fixed in first rotation rocking arm upper end and constitutes triangle-shaped with first connecting rod, the second connecting rod is fixed in fuselage outrigger bracket lower part and forms triangle-shaped support with first connecting rod, the fourth connecting rod is fixed in first rotation rocking arm lower extreme and forms triangle-shaped support with the third connecting rod, fifth connecting rod and second rotation rocking arm fixed connection just form triangle-shaped support with the third connecting rod, wing shape-preserving supporting seat sets up on the nodical interior cavity appearance and the unmanned aerial vehicle wing front end appearance of first connecting rod and third connecting rod and wing shape-preserving supporting seat identical.
By adopting the device, the inner side of the lower end of the second rotating rocker arm is provided with the cam, and the side wall of the traction tackle module is provided with the wedge-shaped stop block matched with the cam; when the traction sheave module is stationary, the wedge shaped stop blocks rotation of the second rotary rocker arm.
Compared with the existing unmanned aerial vehicle ejection traction device adopting a bolt type mode of fixing the externally hung launching sliding block, the traction device can ensure that the unmanned aerial vehicle is statically locked by utilizing the appearance characteristics of the unmanned aerial vehicle under the condition that the pneumatic appearance of the unmanned aerial vehicle is not influenced; stabilizing the unmanned aerial vehicle on the track; and guarantee that the jettison device actuates and pulls unmanned aerial vehicle and slide at the launching track is quick accurate to accomplish the process of taking off from the orbit. The device is convenient for operation of operators, and the device structure only adopts a metal mechanism, so that the reliability is high.
The invention is further described below with reference to the accompanying drawings.
Drawings
Fig. 1 is a schematic view of the present invention with ejector and drone installation examples.
Figure 2 is a schematic view of the apparatus of the present invention.
Figure 3 is a schematic view of the upper half of the stabilization module of the apparatus of the present invention.
Fig. 4 is a schematic view of the traction sheave module of the lower half of the apparatus of the present invention.
FIG. 5 is a schematic view of the structure of the stabilizing module of the device of the present invention.
Fig. 6 is a schematic view of the traction sheave of the apparatus of the present invention and the connection of the stabilization module to the traction sheave module.
Figure 7 is a schematic view of the traction sheave locking arrangement of the present invention.
Fig. 8 is a schematic view of the connection of the tackle locking structure and the slide rail according to the invention.
Detailed Description
Fig. 1 schematically shows an overall schematic diagram of an ejection and traction device of a unmanned aerial vehicle according to an embodiment of the invention. The stable supporting part on the traction device 3 is respectively installed on the guide rail of the catapult 2 together with the wing and the rear part of the body on the unmanned aerial vehicle.
The upper partial stabilization module 4 and the lower partial traction sheave module 5 of the traction device 3 in fig. 2.
Fig. 3 schematically shows the structure of the stabilizing support module 4.
Fig. 4 shows schematically the structure of the traction sheave module 5.
Fig. 5, 6 and 7 schematically show the structural components of the stabilizing support 4. The stable structure module 4 consists of a first connecting rod 7, a second connecting rod 8, a third connecting rod 9, a fourth connecting rod 10, a fifth connecting rod 16, a wing shape-preserving supporting seat 6 and a fuselage stable supporting bracket 11, and the stable structure module and the wing shape-preserving supporting seat form a stable truss structure together by adopting a welding process.
The utility model provides a guarantor type unmanned aerial vehicle launches draw gear, includes launch launcher 2, draw gear 3, stable structure module 4, pulls coaster module 5, first rocking arm 12 that rotates, fixed sloping arm 13, second rocking arm 14 that rotates, spring lock pin 15, slide rail 20, horizontal pulley 21, vertical pulley 22. The slide rail 20 is fixed on the launching cradle 2, and the launching cradle 2 inclines upwards by a certain angle; the traction tackle module 5 makes reciprocating linear motion along the slide rail 20 through a horizontal pulley 21 and a vertical pulley 22 under the traction of the traction device 3, and hooks for fixing a traction rope of the traction device 3 are arranged at the front and the back of the traction tackle module 5; the stabilizing structure module 4 is provided with a left part and a right part, and each part is used for bearing the unmanned aerial vehicle; two fixed oblique arms 13 are arranged, are fixed on two sides of the traction tackle module 5 through connecting rods and are longitudinally and symmetrically inclined relative to the unmanned aerial vehicle, and the inclination angle range of the fixed oblique arms 13 is [5 degrees, 15 degrees ]; the two first rotating rocker arms 12 are respectively arranged on the upper end surfaces of the corresponding fixed oblique arms 13, the first rotating rocker arms 12 can rotate on the upper end surfaces of the fixed oblique arms 13 by taking the central axis of the first rotating rocker arms 12 as a rotating shaft, and the first rotating rocker arms 12 are fixedly connected with the corresponding stable structure modules 4; the two second rotating rocker arms 14 are respectively arranged on the lower end faces of the corresponding fixed inclined arms 13, the second rotating rocker arms 14 rotate on the lower end faces of the fixed inclined arms 13 by taking the central axes of the second rotating rocker arms 14 as rotating axes, and the second rotating rocker arms 14 are fixedly connected with the corresponding stable structure modules 4; spring lock pin 15 sets up two and is located respectively and stabilizes on the structure module 4 left and right sides two parts and match with the spill locked groove on the unmanned aerial vehicle fuselage. The central axis of the fixed oblique arm 13 is parallel to the rotating axes of the first rotating rocker arm 12 and the second rotating rocker arm 14. The second swing arm 14 rotates in a flat key manner together with the first swing arm 12.
The stable structure module 4 is provided with a left part and a right part, and each part comprises a first connecting rod 7, a second connecting rod 8, a third connecting rod 9, a fourth connecting rod 10, a fifth connecting rod 16, a wing shape-keeping supporting seat 6 and a fuselage stable supporting bracket 11. The fuselage stabilizing support bracket 11 is fixed on the first rotating rocker arm 12, the fuselage stabilizing support brackets 11 on the left side and the right side are respectively provided with a half groove, the two half grooves form a groove, and the shape of the groove is matched with that of the fuselage of the unmanned aerial vehicle; the first connecting rod 7 is fixed on the upper part of the stable supporting bracket 11 of the machine body; the third connecting rod 9 is fixed at the upper end of the first rotating rocker arm 12 and is parallel to a triangle formed by the first connecting rod 7 relative to the sliding rail 20; the second connecting rod 8 is fixed at the lower part of the stable supporting bracket 11 of the machine body and forms a triangular bracket with the first connecting rod 7; the fourth connecting rod 10 is fixed at the lower end of the first rotating rocker arm 12 and forms a triangular bracket with the third connecting rod 9; the fifth connecting rod 16 is fixedly connected with the second rotary rocker 14 through a connecting lug 17 and a bolt, and forms a triangular bracket with the third connecting rod 9; wing shape-preserving supporting seat 6 is arranged on the intersection point of first connecting rod 7 and third connecting rod 9, and the appearance of the inner cavity of wing shape-preserving supporting seat 6 is identical with the appearance of the front end of the wing of the unmanned aerial vehicle.
In fig. 8, the bottom of the second rotating rocker arm 14 is provided with a characteristic cam 18, the characteristic cam 18 is matched with a wedge-shaped stop 19 on a slide rail 20, after the traction device 3 retracts to a preset position at the rear end of the slide rail, the cam 18 rotates around the first rotating rocker arm 12 and the second rotating rocker arm 14 under the action of an inclined surface of the wedge-shaped stop 19 to play a locking function when the engine is started before an ejection instruction, and after the traction device leaves an initial position under the traction of the ejector, the cam 18 leaves the wedge-shaped stop 19, and the locking function is released.
After unmanned aerial vehicle fixes on the stable supporting module 4, owing to there is the launch angle, so unmanned aerial vehicle can rotate at the stable supporting module 4 under the effect of gravity and automatic closure in draw gear's preset position down to accomplish stable unmanned aerial vehicle's effect, at this moment with spring locking pin 15 pull-up and lock in the concave locked groove of the relevant position on the fuselage. When the unmanned aerial vehicle launches, the spring lock pin 15 can also generate a thrust force which is consistent along the movement direction of the traction device, and the unmanned aerial vehicle is pushed to move together with the traction device. Stop motion behind draw gear motion to slide rail front end buffer, thereby at unmanned aerial vehicle continuation motion under the effect of inertial force, promote draw gear stable support module 4 and make first rotation rocking arm 12 revolute the rotation of axes, stable support module expandes to the outside, removes the fixed to unmanned aerial vehicle, and unmanned aerial vehicle accomplishes and takes off the action from the rail.
Claims (7)
1. An environment-friendly unmanned aerial vehicle ejection traction device is characterized by comprising an ejection launcher (2), a traction device (3), a stable structure module (4), a traction tackle module (5), a first rotating rocker arm (12), a fixed oblique arm (13), a second rotating rocker arm (14), a spring lock pin (15), a slide rail (20), a horizontal pulley (21) and a vertical pulley (22); wherein
The slide rail (20) is arranged on the ejection launching rack (2),
the traction tackle module (5) does reciprocating linear motion along the slide rail (20) through a horizontal pulley (21) and a vertical pulley (22) under the traction of the traction device (3),
the stabilizing structure module (4) is provided with a left part and a right part, each part is used for bearing the unmanned aerial vehicle,
two fixed oblique arms (13) are arranged and fixed on two sides of the traction tackle module (5) through connecting rods and are longitudinally and symmetrically inclined relative to the unmanned aerial vehicle,
the first rotating rocker arms (12) are provided with two and are respectively arranged on the upper end surfaces of the corresponding fixed oblique arms (13), rotate along the rotating shaft and are fixedly connected with the corresponding stable structure modules (4),
the two second rotating rocker arms (14) are respectively arranged on the lower end surfaces of the corresponding fixed oblique arms (13), rotate along the rotating shaft and are fixedly connected with the corresponding stable structure modules (4),
spring lock round pin (15) set up two and lie in respectively and stabilize on the structure module (4) left and right sides two parts and match with the spill locked groove on the unmanned aerial vehicle fuselage.
2. The shape-preserving unmanned aerial vehicle ejection traction device as claimed in claim 1, wherein the stabilizing structure module (4) is provided with a left part and a right part, and each part comprises a first connecting rod (7), a second connecting rod (8), a third connecting rod (9), a fourth connecting rod (10), a fifth connecting rod (16), a wing shape-preserving supporting seat (6) and a fuselage stabilizing and supporting bracket (11); wherein
The stable supporting bracket (11) of the machine body is fixed on a first rotating rocker arm (12),
the first connecting rod (7) is fixed on the upper part of the stable supporting bracket (11) of the machine body,
the third connecting rod (9) is fixed at the upper end of the first rotating rocker arm (12), a triangle formed by the third connecting rod (9) and the first connecting rod (7) is parallel to the sliding rail (20),
the second connecting rod (8) is fixed at the lower part of the stable supporting bracket (11) of the machine body and forms a triangular bracket with the first connecting rod (7),
the fourth connecting rod (10) is fixed at the lower end of the first rotating rocker arm (12) and forms a triangular bracket with the third connecting rod (9),
the fifth connecting rod (16) is fixedly connected with the second rotating rocker arm (14) and forms a triangular bracket with the third connecting rod (9),
the wing shape-preserving supporting seat (6) is arranged on the intersection point of the first connecting rod (7) and the third connecting rod (9), and the appearance of the inner cavity of the wing shape-preserving supporting seat (6) is identical to that of the front end of the wing of the unmanned aerial vehicle.
3. The shape-preserving unmanned aerial vehicle ejection traction device as claimed in claim 1 or 2, wherein a cam (18) is arranged on the inner side of the lower end of the second rotating rocker arm (14), and a wedge-shaped stop block (19) matched with the cam (18) is arranged on the side wall of the sliding rail (20); when the traction sheave module (5) is at rest, the wedge stop (19) prevents the second pivoting arm (14) from pivoting.
4. The shape-preserving unmanned aerial vehicle catapult-traction device as claimed in claim 1 or 2, wherein the center axis of the fixed oblique arm (13) is parallel to the rotation axes of the first swing arm (12) and the second swing arm (14).
5. The shape-preserving unmanned aerial vehicle ejection traction device as claimed in claim 1 or 2, wherein hooks for fixing a traction rope of the traction device (3) are arranged at the front and the back of the traction tackle module (5).
6. The shape-preserving unmanned aerial vehicle catapult traction device as claimed in claim 2, wherein the fifth connecting rod (16) is fixedly connected with the second rotary rocker arm (14) through a connecting lug (17) and a bolt.
7. The shape-preserving unmanned aerial vehicle catapult-traction device as claimed in claim 2, wherein the angle of inclination of the fixed oblique arm (13) is in the range of [5 °,15 ° ].
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611163749.3A CN108202876B (en) | 2016-12-16 | 2016-12-16 | Guarantor type unmanned aerial vehicle launches draw gear |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611163749.3A CN108202876B (en) | 2016-12-16 | 2016-12-16 | Guarantor type unmanned aerial vehicle launches draw gear |
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| Publication Number | Publication Date |
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| CN108202876A CN108202876A (en) | 2018-06-26 |
| CN108202876B true CN108202876B (en) | 2021-03-26 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201611163749.3A Active CN108202876B (en) | 2016-12-16 | 2016-12-16 | Guarantor type unmanned aerial vehicle launches draw gear |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108910073B (en) * | 2018-08-03 | 2020-05-29 | 北京迈凯飞科技有限公司 | Unmanned aerial vehicle ejection rack launching trolley and unmanned aerial vehicle launching method |
| CN109229414B (en) * | 2018-10-17 | 2021-08-13 | 杭州木书科技有限公司 | Small and miniature unmanned aerial vehicle combat launching device |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7165745B2 (en) * | 2003-01-17 | 2007-01-23 | The Insitu Group, Inc. | Methods and apparatuses for launching unmanned aircraft, including releasably gripping aircraft during launch and braking subsequent grip motion |
| US6851647B1 (en) * | 2003-04-03 | 2005-02-08 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Portable catapult launcher for small aircraft |
| CN103466099B (en) * | 2013-09-22 | 2015-09-16 | 河南省寰宇测绘科技发展有限公司 | Unmanned measuring machine high speed ejection frame |
| CN104803006B (en) * | 2015-04-27 | 2016-08-31 | 西北工业大学 | A kind of unmanned aerial vehicle ejecting launching apparatus |
| CN105711851A (en) * | 2016-01-25 | 2016-06-29 | 中国人民解放军国防科学技术大学 | Electric and light-weight catapult with multiple strands of rubber strings for small unmanned aerial vehicle |
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Effective date of registration: 20180918 Address after: No. 29, Qinhuai District, Qinhuai District, Nanjing, Jiangsu Applicant after: Nanjing University of Aeronautics and Astronautics Applicant after: Nanjing long sky Technology Co., Ltd. Applicant after: Nanjing Pukou high tech Industrial Development Zone Management Committee Address before: No. 29, Yu Dao Street, Nanjing, Jiangsu Province Applicant before: Nanjing University of Aeronautics and Astronautics |
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