CN207902764U - A kind of unmanned plane landing system - Google Patents
A kind of unmanned plane landing system Download PDFInfo
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- CN207902764U CN207902764U CN201721874670.1U CN201721874670U CN207902764U CN 207902764 U CN207902764 U CN 207902764U CN 201721874670 U CN201721874670 U CN 201721874670U CN 207902764 U CN207902764 U CN 207902764U
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- unmanned plane
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Abstract
The utility model provides a kind of unmanned plane landing system, belongs to unmanned plane landing technical field.The unmanned plane landing system includes that pneumatic ejection mechanism, rocket assist trigger mechanism and day hook recovering mechanism, it is characterized in that, it further include carried and transported mechanism, the carried and transported mechanism includes the transport vehicle with tablet trailer and three turntables being arranged on the tablet trailer, and the pneumatic ejection mechanism, rocket assist trigger mechanism and day hook recovering mechanism and respectively connect with the tablet trailer by a turntable.Unmanned plane landing system provided by the utility model had not only facilitated the transport that pneumatic ejection mechanism, rocket assist trigger mechanism and day hook recovering mechanism, but also can be in a manner of arbitrary combination landing as needed.
Description
Technical field
The utility model is related to a kind of unmanned plane landing systems, belong to unmanned plane landing field.
Background technology
In recent years, no matter unmanned plane field in China's all has a great development from type or performance, in small drone
In landing modes of taking off, relatively conventional has rato, catapult-assisted take-off, day hook recycling etc. several, these types of distance of zero mark hair
The landing mode penetrate, quickly recycled have it is efficient, easy to operate, takeoff speed is fast, it is small to aircraft damage, to place no requirement (NR)
The advantages that.
However, since the corresponding operating mechanism of several landing modes is complicated at present, body is heavy, cause transport opposite
Inconvenience, manufacture, cost declining it is higher.
Invention content
In view of this, the purpose of this utility model is to provide a kind of unmanned plane landing system, pneumatic ejection machine had both been facilitated
Structure, rocket assist trigger mechanism and day hook the transport of recovering mechanism, and can be in a manner of arbitrary combination landing as needed.
What the above-mentioned purpose of the utility model was mainly achieved by following technical solution：
A kind of unmanned plane landing system, including pneumatic ejection mechanism, rocket assist trigger mechanism and day hook recovering mechanism,
It is characterized in that, further includes carried and transported mechanism, the carried and transported mechanism includes the transport vehicle with tablet trailer and is arranged in institute
Three turntables on tablet trailer are stated, the pneumatic ejection mechanism, rocket assist trigger mechanism and day hook recovering mechanism and respectively pass through
One turntable is connect with the tablet trailer.
In an alternative embodiment, the rocket assist trigger mechanism is located at the tail portion of the tablet trailer.
In an alternative embodiment, the carried and transported mechanism further includes multigroup leveling supporting legs, the leveling supporting legs peace
On the chassis of the transport vehicle and the tablet trailer, the levelness for adjusting the tablet trailer.
Further include the power supply mechanism being arranged on the tablet trailer in an alternative embodiment, for described pneumatic
Ejection mechanism, rocket assist trigger mechanism and day hook recovering mechanism power supply.
In an alternative embodiment, the pneumatic ejection mechanism includes supporting table, folds ejector rail, angular adjustment hydraulic pressure
Cylinder, ejection cylinder and shot trolley, the angular adjustment hydraulic cylinder are fixedly connected with the turntable, the supporting table and described turn
Platform is fixedly connected, and is used to support the folding ejector rail, and the folding ejector rail is connect with the angular adjustment hydraulic cylinder,
And angle is adjusted by the angular adjustment hydraulic cylinder, the shot trolley is connect with the piston of the ejection cylinder, described
It launches and folds ejector rail movement described in the promotion lower edge of cylinder.
In an alternative embodiment, the supporting table includes lower supporting table and upper supporting table, the lower supporting table with it is described
Turntable is fixedly connected, and the angular adjustment hydraulic cylinder is fixedly connected by the lower supporting table with the turntable, the upper support
Platform is rotatablely connected with the lower supporting table, is used to support the folding ejector rail, the upper supporting table and the rotation of lower supporting table
Connection.
In an alternative embodiment, the upper supporting table and lower supporting table are triangular prism structure, the lower supporting table
One side is fixedly connected with the turntable, and the one side of the upper supporting table is fixedly connected with the folding ejector rail.
In an alternative embodiment, the rocket assist trigger mechanism includes support frame and is fixed on the support frame
Front arm lodging component, two groups of rear support adjusting parts and rocket bracket installation and adjustment component, the support frame and the turntable
Connection, the front arm lodging component and two groups of rear support adjusting parts are arranged in triangle, and front arm lodging component position
In on the perpendicular bisector of line for supporting adjusting part described in two groups, the rear support component is used to support the left and right machine of unmanned plane
The wing, the front arm lodging component are used to support the head of unmanned plane, and the rocket bracket installation and adjustment component is for fixed fire
Arrow, so that the conehead of the other end of rocket and unmanned aerial vehicle body connects, when the rocket launching, the front arm lodging component
It lodges under thrust, so that unmanned plane takes off.
In an alternative embodiment, the day hooks recovering mechanism and includes expansion hydraulic cylinder, folding support arm and stop rope, institute
It states expansion hydraulic cylinder to be fixedly connected with the turntable, the folding support arm is connect with the expansion hydraulic cylinder, passes through the exhibition
It opens hydraulic cylinder expansion or folds, the rope that blocks is fixed on the folding support arm, when the folding support arm is unfolded, institute
It states and blocks rope with the folding support upper-arm circumference at polygonized structure, for blocking unmanned plane.
The utility model compared with prior art the advantages of be：
Specifically, it in the utility model embodiment, can both be taken off to unmanned plane by pneumatic ejection mechanism 2,
It can be taken off to unmanned plane by rocket assist trigger mechanism 3, other two machines can be adjusted before taking off by turntable
The position of structure is allowed to not interfere with trigger mechanism used；The utility model embodiment is by by rocket assist trigger mechanism 3
It is arranged in the tail portion of tablet trailer, the thermal current generated when can be to avoid rocket launching does harm to the accidental injury of other Liang Ge mechanisms；
In other embodiment, it can also need to adjust the installation site and sequence of each mechanism according to using, the utility model is not construed as limiting.
Description of the drawings
Fig. 1 is a kind of unmanned plane landing system structure diagram that the utility model embodiment provides；
Fig. 2 is the pneumatic ejection mechanism structure schematic diagram of one kind that the utility model embodiment provides；
Fig. 3 is a kind of rocket assist trigger mechanism structural schematic diagram that the utility model embodiment provides；
Fig. 4 is a kind of day hook recovering mechanism structural schematic diagram that the utility model embodiment provides.
Specific implementation mode
Further detailed description is done to the utility model with reference to the accompanying drawings and examples：
Referring to Fig. 1, the utility model embodiment provides a kind of unmanned plane landing system, including pneumatic ejection mechanism 2, fire
Arrow launch assist mechanism 3 and day hook recovering mechanism 4, further include carried and transported mechanism, and carried and transported mechanism 1 includes band tablet trailer
Transport vehicle 1 and the preceding turntable 6, intermediate station 7 and the rear turntable 8 that are arranged on the tablet trailer, pneumatic ejection mechanism 2 be fixed on
On intermediate station 7, rocket assist trigger mechanism 3 and day hook recovering mechanism 4, rocket assist trigger mechanism 3 are fixed in rear turntable 8,
It is hooked before recovering mechanism 4 is fixed on turntable 6.
Specifically, it in the utility model embodiment, can both be taken off to unmanned plane by pneumatic ejection mechanism 2,
It can be taken off to unmanned plane by rocket assist trigger mechanism 3, other two machines can be adjusted before taking off by turntable
The position of structure is allowed to not interfere with trigger mechanism used；The utility model embodiment is by by rocket assist trigger mechanism 3
It is arranged in the tail portion of tablet trailer, the thermal current generated when can be to avoid rocket launching does harm to the accidental injury of other Liang Ge mechanisms；
In other embodiment, it can also need to adjust the installation site and sequence of each mechanism according to using, the utility model is not construed as limiting.
The utility model embodiment provide a kind of unmanned plane landing system whole system, by by pneumatic ejection mechanism,
Rocket assist trigger mechanism and day hook recovering mechanism and are integrated in carried and transported mechanism, realize the convenience in transport of each mechanism, pass through
Turntable adjust each mechanism position avoid taking off landing when each mechanism interference and revolving table position can be adjusted according to wind direction, it is real
Do not have to now smoothly take off and recycle in the case of moving carried and transported mechanism, the system operatio is simple and fast, can be as needed
Arbitrary combination landing mode.
Referring to Fig. 1, the carried and transported mechanism further includes 6 pairs of leveling supporting legs 5, and leveling supporting legs 5 are symmetrically mounted on described
The bottom of transport vehicle, the levelness for adjusting the tablet trailer make vehicle body uniform force in launch reclaim, and are transmitted back to
The impact force for receiving moment passes to ground by supporting leg, effectively solves moment larger impact and is damaged caused by equipment.Referring to figure
1, the unmanned plane landing system further includes the power supply mechanism 22 being arranged on the tablet trailer, for the pneumatic bomb
It penetrates mechanism 2, rocket assist trigger mechanism 3 and day and hooks the power supply of recovering mechanism 4.By the way that the power supply system of each mechanism is integrated into one
Body saves system space, easily facilitates transport.
Referring to Fig. 2, the pneumatic ejection mechanism 2 include supporting table 24, fold ejector rail 9, angular adjustment hydraulic cylinder 10,
Ejection cylinder (be placed in and fold in ejector rail 9, be not shown in figure) and shot trolley 12, angular adjustment hydraulic cylinder 10 and intermediate station
7 are fixedly connected, and supporting table 24 is fixedly connected with intermediate station 7, are used to support and fold ejector rail 9, fold ejector rail 9 and angle
It adjusts hydraulic cylinder 10 to connect, and level angle, shot trolley 12 and the ejection cylinder is adjusted by angular adjustment hydraulic cylinder 10
Piston connection, it is described ejection cylinder promotion lower edge fold ejector rail 9 move；When ejection, unmanned plane is supported on ejection
On trolley 12, shot trolley 12 is connect by cable wire with the piston of ejection cylinder, the instantaneous quickly movement in the case where ejection cylinder pushes
Unmanned plane is set to take off；Pneumatic ejection can adjust launch angle according to hydraulic cylinder, and high degree of automation, pneumatic ejection can be more multiple
Zero length lauuch is realized in the case of miscellaneous.
Referring to Fig. 2, in an alternative embodiment, supporting table 24 includes lower supporting table 241 and upper supporting table 242, lower support
Platform 241 is fixedly connected with intermediate station 7, and angular adjustment hydraulic cylinder 10 is fixedly connected by lower supporting table 241 with intermediate station 7, upper branch
It supports platform 242 to be rotatablely connected with lower supporting table 241, is used to support and folds 241 turns of ejector rail 9, upper supporting table 242 and lower supporting table
Dynamic connection；The structure had not only ensured that gentle support folded ejector rail, but also convenient for adjusting guide rail angle.
Referring to Fig. 2, lower supporting table 241 and upper supporting table 242 are triangular prism structure in an alternative embodiment, lower support
The one side of platform 241 is fixedly connected with intermediate station 7, and the one side of upper supporting table 242 is fixedly connected with ejector rail 9 is folded.
Referring to Fig. 3, rocket assist trigger mechanism 3 includes support frame 23 and the front arm lodging group being fixed on support frame 23
14, two groups of rear support adjusting parts 15 of part and rocket bracket installation and adjustment component 16, support frame 23 is connect with rear turntable 8, preceding to shake
Arm lodging component 14 and two groups of rear support adjusting parts 15 are arranged in triangle, and front arm lodging component 14 is located at two groups of support tune
On the perpendicular bisector for saving the line of component 15,15 component of rear support is used to support the left and right wing of unmanned plane, front arm lodging component
14 are used to support the head of unmanned plane, rocket bracket installation and adjustment component 16 for fixing rocket so that the other end of rocket with
The conehead of unmanned aerial vehicle body connects, and when the rocket launching, front arm lodging component 14 lodges under thrust, so that nothing
It is man-machine to take off.The radiation pattern makes unmanned plane fast implement zero length lauuch, and unmanned plane can be made to reach certain speed, is suitble to
When pneumatically rate request is not achieved in ejection when plateau is taken off, the mode that rocket assist can be used emits.
Referring to Fig. 4, the day hooks recovering mechanism 4 and includes expansion hydraulic cylinder 19, folding support arm 20 and stop rope 21, expansion
Hydraulic cylinder 19 is fixedly connected with preceding turntable 6, and folding support arm 20 is connect with expansion hydraulic cylinder 19, is unfolded by the way that hydraulic cylinder 19 is unfolded
Or fold, it blocks rope 21 and is fixed on folding support arm 20, when folding support arm 20 is unfolded, block rope 21 and folding support arm
20 surround polygonized structure, for blocking unmanned plane.The recycling of this skyhook effectively solves to can not achieve wheeled landing on no road road surface
The problem of the unmanned damage of body body and recycling difficulty caused by being recycled with no road road surface or roughness pavement parachuting.It is this below
One specific embodiment of utility model：
A kind of a variety of landing systems of unmanned plane, including carried and transported mechanism, pneumatic ejection mechanism 2, rocket assist transmitter
Structure 3, day hook recovering mechanism 4 and form.The carried and transported mechanism include 1, six leveling supporting legs 5 of transport vehicle with tablet trailer,
Preceding turntable 6, intermediate station 7 and rear turntable 8, pneumatic ejection mechanism 2 include folding ejector rail 9, launch angle adjusting hydraulic cylinder 11
And shot trolley 12, it includes three sections of guide rails to fold ejector rail 9, is connected by two corners 10 between three sections of guide rails, realizes and fold,
Shot trolley 12 is equipped with trolley card slot 13.Rocket assist trigger mechanism 3 includes front arm lodging 14, two groups of rear support tune of component
Save component 15 and rocket installation and adjustment component 16, front arm lodging component include rocking arm and the safety plug being arranged on rocking arm 17 and
Shear pin 18.Skyhook recovering mechanism 4 is including expansion hydraulic cylinder 19, folding support arm 20 and blocks rope 21.When whole system works,
Transport vehicle is parked in behind launch site, six leveling supporting legs 5 are stretched out into leveling vehicles itself, by turntable before adjusting 6 by skyhook machine
4 support arm 20 of structure is rotated by 90 ° to instantaneous needle, then is adjusted intermediate station 7 and ensured that space is not sent out with day hook mechanism 4 when pneumatic catapult-assisted take-off
Raw interference can also be taken off adjusting the guarantee of turntable angle in the absence of interference according to wind direction, artificial after adjustment angle
Pneumatic ejection folded ammunition is penetrated guide rail 9 along corner 10 to be unfolded in same level, shot trolley 12 is slided into 9 bottom of guide rail, is led to
The launch angle that launch angle is adjusted to 10 ° or so by 11 stroke of angular adjustment hydraulic cylinder is overregulated, by aircraft wing fixed block
It is matched with 13 mechanism of card slot of launching trolley, start unmanned vehicle engine after ready starts when revolution reaches certain value
Switching cylinder, unmanned plane take off.Rato can also be used according to the difference of environment, by 3 points of difference of unmanned aerial vehicle body
It is located on the front arm lodging mechanism 14 and two rear support regulating mechanisms 15 of rocket assist frame, rocket one end is located at fire
The other end is connected with unmanned aerial vehicle body conehead in arrow rest frame installation and adjustment mechanism 16, and unmanned vehicle engine is lighted a fire to maximum and is turned
After number, safety plug 17, rocket firing are extracted, shear pin 18 is cut front arm lodging mechanism 14 and dumps forward nobody by rocket thrust
Machine takes off, and when recycling, support arm 20 was unfolded by hydraulic cylinder 19, and aircraft will hit obstruction rope 21 with certain speed, pass through damping
Aircraft is buffered, by blow-down pulley by aircraft along under, completion is taken off landing.
The best specific implementation mode of the above, only the utility model, but the scope of protection of the utility model is not
It is confined to this, any one skilled in the art within the technical scope disclosed by the utility model, can readily occur in
Change or replacement, should be covered within the scope of the utility model.
The content not being described in detail in the utility model specification belongs to the known technology of professional and technical personnel in the field.
Claims (9)
1. a kind of unmanned plane landing system, including pneumatic ejection mechanism, rocket assist trigger mechanism and day hook recovering mechanism, special
Sign is, further includes carried and transported mechanism, and the carried and transported mechanism includes the transport vehicle with tablet trailer and is arranged described
Three turntables on tablet trailer, the pneumatic ejection mechanism, rocket assist trigger mechanism and day hook recovering mechanism and respectively pass through one
A turntable is connect with the tablet trailer.
2. unmanned plane landing system according to claim 1, which is characterized in that the rocket assist trigger mechanism is located at institute
State the tail portion of tablet trailer.
3. unmanned plane landing system according to claim 1, which is characterized in that the carried and transported mechanism further includes multigroup
Leveling supporting legs, the leveling supporting legs are mounted on the chassis and the tablet trailer of the transport vehicle, described flat for adjusting
The levelness of plate trailer.
4. unmanned plane landing system according to claim 1, which is characterized in that further include being arranged on the tablet trailer
Power supply mechanism, for the pneumatic ejection mechanism, rocket assist trigger mechanism and day hook recovering mechanism power supply.
5. unmanned plane landing system according to claim 1, which is characterized in that the pneumatic ejection mechanism includes support
Platform folds ejector rail, angular adjustment hydraulic cylinder, ejection cylinder and shot trolley, the angular adjustment hydraulic cylinder with described turn
Platform is fixedly connected, and the supporting table is fixedly connected with the turntable, is used to support the folding ejector rail, the folding ejection
Guide rail is connect with the angular adjustment hydraulic cylinder, and by the angular adjustment hydraulic cylinder adjust angle, the shot trolley with
The piston connection of the ejection cylinder folds ejector rail movement described in the promotion lower edge of the ejection cylinder.
6. unmanned plane landing system according to claim 5, which is characterized in that the supporting table includes lower supporting table and upper
Supporting table, the lower supporting table are fixedly connected with the turntable, and the angular adjustment hydraulic cylinder passes through the lower supporting table and institute
It states turntable to be fixedly connected, the upper supporting table is rotatablely connected with the lower supporting table, is used to support the folding ejector rail, institute
State supporting table and the rotation connection of lower supporting table.
7. unmanned plane landing system according to claim 6, which is characterized in that the upper supporting table and lower supporting table are
The one side of triangular prism structure, the lower supporting table is fixedly connected with the turntable, the one side of the upper supporting table with it is described
Ejector rail is folded to be fixedly connected.
8. unmanned plane landing system according to claim 1, which is characterized in that the rocket assist trigger mechanism includes branch
Support frame and front arm lodging component, two groups of rear support adjusting parts and the rocket bracket installation and adjustment being fixed on the support frame
Component, the support frame are connect with the turntable, and the front arm lodging component is set with two groups of rear support adjusting parts in triangle
It sets, and front arm lodging component is located on the perpendicular bisector of the line of support adjusting part described in two groups, the rear support group
Part is used to support the left and right wing of unmanned plane, and the front arm lodging component is used to support the head of unmanned plane, the rocket support
Frame installation and adjustment component is for fixing rocket, so that the conehead of the other end of rocket and unmanned aerial vehicle body connects, when the rocket
When transmitting, the front arm lodging component lodges under thrust, so that unmanned plane takes off.
9. unmanned plane landing system according to claim 1, which is characterized in that it includes developping solution that the day, which hooks recovering mechanism,
Cylinder pressure, folding support arm and stop rope, the expansion hydraulic cylinder is fixedly connected with the turntable, the folding support arm with it is described
Hydraulic cylinder connection is unfolded, is unfolded by the expansion hydraulic cylinder or is folded, the obstruction rope is fixed on the folding support arm,
When the folding support arm is unfolded, the obstruction rope and the folding support upper-arm circumference are at polygonized structure, for blocking nobody
Machine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721874670.1U CN207902764U (en) | 2017-12-28 | 2017-12-28 | A kind of unmanned plane landing system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721874670.1U CN207902764U (en) | 2017-12-28 | 2017-12-28 | A kind of unmanned plane landing system |
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| CN207902764U true CN207902764U (en) | 2018-09-25 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110316398A (en) * | 2019-08-02 | 2019-10-11 | 西安探索鹰航空科技有限公司 | A kind of unmanned plane takes off and recycles institutional operation vehicle |
| CN110963065A (en) * | 2019-12-23 | 2020-04-07 | 太原理工大学 | Emergency guarantee robot for polar unmanned aerial vehicle |
| CN115489749A (en) * | 2022-11-16 | 2022-12-20 | 成都航空职业技术学院 | Fixed wing unmanned aerial vehicle launches take-off and land integrated system |
-
2017
- 2017-12-28 CN CN201721874670.1U patent/CN207902764U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110316398A (en) * | 2019-08-02 | 2019-10-11 | 西安探索鹰航空科技有限公司 | A kind of unmanned plane takes off and recycles institutional operation vehicle |
| CN110963065A (en) * | 2019-12-23 | 2020-04-07 | 太原理工大学 | Emergency guarantee robot for polar unmanned aerial vehicle |
| CN115489749A (en) * | 2022-11-16 | 2022-12-20 | 成都航空职业技术学院 | Fixed wing unmanned aerial vehicle launches take-off and land integrated system |
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