CN111688945A - Unmanned aerial vehicle strutting arrangement - Google Patents
Unmanned aerial vehicle strutting arrangement Download PDFInfo
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- CN111688945A CN111688945A CN201910187927.3A CN201910187927A CN111688945A CN 111688945 A CN111688945 A CN 111688945A CN 201910187927 A CN201910187927 A CN 201910187927A CN 111688945 A CN111688945 A CN 111688945A
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- unmanned aerial
- aerial vehicle
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- fixed
- sliding assembly
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- 238000010586 diagram Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 229920000742 Cotton Polymers 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 208000035473 Communicable disease Diseases 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 210000005069 ears Anatomy 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
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Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Catching Or Destruction (AREA)
Abstract
The present disclosure provides an unmanned aerial vehicle strutting arrangement, unmanned aerial vehicle is including placing strutting arrangement's recess (1), strutting arrangement includes: the unmanned aerial vehicle supporting device comprises a supporting rod (2) used for supporting an unmanned aerial vehicle, a fixing component (3) used for fixing one end of the supporting rod (2) in the groove (1), a spring (4) used for connecting the other end of the supporting rod (2) with the groove (1), and a sliding component (5) sleeved on the supporting rod (2); the stay bar (2) can rotate around the fixing component (3), the sliding component (5) is used for controlling the stay bar (2) to be fixed in the direction vertical to the longitudinal axis of the unmanned aerial vehicle body or releasing the control, and the spring (4) is used for recovering the stay bar into the groove (1). Can realize the supporting role to the unmanned aerial vehicle fuselage before unmanned aerial vehicle takes off, and after unmanned aerial vehicle takes off, can retrieve this strutting arrangement to unmanned aerial vehicle's recess in.
Description
Technical Field
The utility model relates to an aeronautical engineering technical field especially relates to an unmanned aerial vehicle strutting arrangement.
Background
Unmanned aerial vehicles are unmanned aerial vehicles that use wireless remote control or program control to perform specific aviation tasks, and are currently widely used in a plurality of fields such as aerial photography, agriculture, plant protection, miniature autodyne, express transportation, disaster relief, infectious disease monitoring, surveying and mapping, news reporting, and power inspection.
The unmanned aerial vehicle system comprises an unmanned aerial vehicle, a communication station matched with the unmanned aerial vehicle, a take-off (launching) recovery device, an unmanned aerial vehicle transportation, storage and detection device and the like. The takeoff mode aiming at the unmanned aerial vehicle comprises autonomous running takeoff, aerial launching by a mother aircraft, hand throwing takeoff, rocket boosting takeoff and the like, wherein the kinetic energy for the unmanned aerial vehicle to take off is from energy generated by combustion of fuel in a rocket booster in the rocket boosting takeoff mode. The rocket boosting launching mode has the advantages that the occupied area of the whole launching device is small, the cost is low, the influence from the outside is small, the unmanned aerial vehicle can be deployed at a high speed, the use is convenient, the reliability is high, the rapid take-off of the unmanned aerial vehicle can be realized by means of high thrust in a short time of the rocket booster, and the unmanned aerial vehicle is enabled to get rid of the dependence on a runway.
Adopt the unmanned aerial vehicle that rocket boosting takes off often fix on the launcher earlier before taking off, need reserve the supporting mechanism who is connected with the launcher on the unmanned aerial vehicle organism, and this kind of supporting mechanism is outstanding outside the organism usually, and the flight in-process can influence unmanned aerial vehicle's aerodynamic characteristic certainly, and especially more obvious to high-speed unmanned aerial vehicle flight performance's influence.
Disclosure of Invention
One aspect of the present disclosure provides an unmanned aerial vehicle strutting arrangement, unmanned aerial vehicle includes can place strutting arrangement's recess, strutting arrangement includes: the unmanned aerial vehicle supporting device comprises a supporting rod for supporting an unmanned aerial vehicle, a fixing assembly for fixing one end of the supporting rod in the groove, a spring for connecting the other end of the supporting rod with the groove, and a sliding assembly sleeved on the supporting rod; the strut can rotate around the fixing assembly, the sliding assembly is used for controlling the strut to be fixed in the direction perpendicular to the longitudinal axis of the unmanned aerial vehicle body or releasing the control, and the spring is used for recovering the strut into the groove.
Optionally, the fixing assembly comprises a pin, by which the pin is hinged to the stay, the stay being rotatable about the pin axis.
Optionally, the fixing component comprises a fixing part, two lug parts and a stressed spring between the fixing part and the two lug parts, and one end of the stay bar is fixed in the groove through the fixing part.
Optionally, the sliding assembly comprises a movement control assembly which enables the sliding assembly to move along the axial direction of the stay bar, and the sliding assembly controls the stay bar to be fixed in the direction perpendicular to the longitudinal axis of the unmanned aerial vehicle body or releases the control through the movement.
Optionally, the movement control assembly comprises: the rope is fixed on the sliding assembly, the fixing assembly and the unmanned aerial vehicle, and the cutter is used for cutting off the rope;
the rope fixes the position of the sliding assembly, the sliding assembly controls the stay bar to be fixed in the direction perpendicular to the longitudinal axis of the unmanned aerial vehicle body, and when the cutter cuts off the rope, the sliding assembly releases the control.
Optionally, the movement control assembly comprises: the rope is fixed to the sliding assembly at one end, and the unmanned aerial vehicle at the other end, and a cutter is used for cutting off the rope;
the rope fixes the position of the sliding assembly, the sliding assembly controls the stay bar to be fixed in the direction perpendicular to the longitudinal axis of the unmanned aerial vehicle body, and when the cutter cuts off the rope, the sliding assembly releases the control.
Optionally, the sliding assembly is sleeved at the joint of the fixing assembly and the stay bar to control the stay bar to be fixed in the direction perpendicular to the longitudinal axis of the unmanned aerial vehicle body.
Optionally, the drone further comprises an operating flap, the cutter and the cord being disposed within the operating flap.
Optionally, the cutter is connected with a control system of the drone.
Optionally, the support rod is a cylinder, the sliding assembly is a hollow cylinder, and the outer diameter of the support rod is matched with the inner diameter of the sliding assembly.
Drawings
For a more complete understanding of the present disclosure and the advantages thereof, reference is now made to the following descriptions taken in conjunction with the accompanying drawings, in which:
fig. 1 schematically illustrates an unmanned aerial vehicle and an unmanned aerial vehicle support device structure diagram provided by an embodiment of the present disclosure;
fig. 2 schematically illustrates a structural schematic diagram of a supporting device of an unmanned aerial vehicle provided by an embodiment of the present disclosure;
fig. 3 schematically illustrates a connection structure diagram of a fixing assembly and a strut in the supporting device of the unmanned aerial vehicle provided by the embodiment of the disclosure;
fig. 4 schematically shows a structural schematic diagram of a fixing component in the supporting device of the unmanned aerial vehicle provided by the embodiment of the disclosure;
fig. 5 schematically illustrates a structural diagram of a stay bar in a support device of an unmanned aerial vehicle provided by an embodiment of the present disclosure;
fig. 6 schematically shows a structural diagram of a sliding assembly in the support device of the unmanned aerial vehicle provided by the embodiment of the disclosure;
wherein the reference numerals are:
1. a groove; 2. a stay bar; 3. a fixing assembly; 4. a spring; 5. a sliding assembly; 6. a movement control assembly; 7. operating the flap;
201. a single ear; 301. a pin; 302. a fixed part; 303. two ear parts; 304. a stressed spring;
601. a cord; 602. and a cutter.
Detailed Description
Hereinafter, embodiments of the present disclosure will be described with reference to the accompanying drawings. It should be understood that the description is illustrative only and is not intended to limit the scope of the present disclosure. In the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the disclosure. It may be evident, however, that one or more embodiments may be practiced without these specific details. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present disclosure.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. The terms "comprises," "comprising," and the like, as used herein, specify the presence of stated features, steps, operations, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, or components.
All terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art unless otherwise defined. It is noted that the terms used herein should be interpreted as having a meaning that is consistent with the context of this specification and should not be interpreted in an idealized or overly formal sense.
Referring to fig. 1 and 2, the present disclosure provides a drone support device, where the drone includes a groove 1 in which the drone may be placed, and the drone support device includes: the unmanned aerial vehicle supporting device comprises a supporting rod 2 for supporting an unmanned aerial vehicle, a fixing component 3 for fixing one end of the supporting rod 2 in the groove 1, a spring 4 for connecting the other end of the supporting rod 2 with the groove 1, and a sliding component 5 sleeved on the supporting rod 2; the supporting rod 2 can rotate around the fixing component 3, the sliding component 5 is used for controlling the supporting rod 2 to be fixed in a direction perpendicular to the longitudinal axis of the unmanned aerial vehicle body or releasing the control, and the spring 4 is used for recovering the supporting rod into the groove 1.
This unmanned aerial vehicle strutting arrangement's theory of operation does: when unmanned aerial vehicle takes off the preceding needs support, takes out vaulting pole 2 through the pivoted mode from recess 1, rotates to the direction of vaulting pole 2 perpendicular to unmanned aerial vehicle fuselage axis of ordinates to through the control of slip subassembly 5 vaulting pole 2 is fixed in the direction of perpendicular unmanned aerial vehicle fuselage axis of ordinates, makes its one end and unmanned aerial vehicle launcher contact, realizes the supporting role to unmanned aerial vehicle. After the unmanned aerial vehicle takes off, the control is released through the sliding component 5, namely the strut 2 is fixed in the direction vertical to the longitudinal axis of the unmanned aerial vehicle body, so that the strut 2 can rotate around the fixing component 3. Since one end of the stay bar 2 is fixed in the groove 1 through the fixing component 3, and the other end is connected with the groove 1 through the spring 4, at this time, under the action of the spring 4, the stay bar 2 rotates around the fixing component 3, and the stay bar is recovered into the groove 1.
Therefore, the unmanned aerial vehicle strutting arrangement that this disclosed embodiment provided can realize the supporting role to the unmanned aerial vehicle fuselage before unmanned aerial vehicle takes off to after unmanned aerial vehicle takes off, can retrieve this strutting arrangement to in unmanned aerial vehicle's the recess. The problem of the supporting mechanism that adopts among the prior art outstanding outside the organism, lead to the flight in-process to inevitably influence unmanned aerial vehicle's aerodynamic characteristic, influence unmanned aerial vehicle flight performance is solved.
Specifically, referring to fig. 3, the fixing assembly 3 includes a pin 301, and the stay 2 is hinged to the stay 2 through the pin 301, so that the stay 2 can rotate around the axis of the pin 301. And, referring to fig. 4, the fixing assembly 3 includes a fixing portion 302 and a double-supporting ear portion 303, and a force receiving spring 304 between the fixing portion 302 and the double-supporting ear portion 303, and one end of the stay bar 2 is fixed in the groove 1 by the fixing portion 302. As will be understood by those skilled in the art, referring to fig. 5, the stay bar 2 comprises a single lug part 201 which is matched with a double lug part 303 of the fixing component 3, and the hinge joint is realized through the matching of the single lug part 201, the pin 301 and the double lug part 303, so as to realize the process that the stay bar 2 can rotate around the fixing component. The fixing portion 302 may be welded in the recess 1 of the drone.
The sliding assembly 5 comprises a movement control assembly 6 which enables the sliding assembly 5 to move along the axial direction of the stay bar 2, and the sliding assembly 5 controls the stay bar 2 to be fixed in the direction perpendicular to the longitudinal axis of the unmanned aerial vehicle body or releases the control through the movement.
In a possible way, with reference to fig. 2, the movement control assembly 6 comprises a cord 601 co-located on the sliding assembly 5, on the fixed assembly 3 and on the drone, and a cutter 602 for cutting off the cord 601. As shown in fig. 2 and 4, when fixing the cord 601, a ring may be welded to the outer wall of the sliding component 5 and the fixing portion 302 of the fixing component 3, one end of the cord 601 may be fixed to the ring on the outer wall of the sliding component 5, and the cord 601 may pass through the ring on the fixing portion 302, so that the same manner may be adopted for fixing the cord 601 on the drone. The position of the sliding assembly 5 is fixed through the wire rope, so that the sliding assembly 5 controls the stay bar 2 to be fixed in the direction vertical to the longitudinal axis of the unmanned aerial vehicle body, and when the cutter 602 cuts off the wire rope, the sliding assembly 5 releases the control.
In another possible way, the movement control assembly 6 comprises: a string 601 fixed at one end to the sliding assembly 5 and at the other end to the drone, and a cutter 602 for cutting the string. The fixing mode of the rope 601 can also adopt that the rope is fixed on a circular ring welded on a sliding component 5 and the unmanned aerial vehicle, the position of the sliding component 5 is fixed by the rope, the sliding component 5 controls the direction that the stay bar 2 is fixed in the direction vertical to the longitudinal axis of the unmanned aerial vehicle body, and when the cutter 602 cuts off the rope, the sliding component 5 releases the control.
Specifically, as shown in fig. 2, fixing the position of the sliding assembly 5 refers to enabling the sliding assembly 5 to be sleeved at the joint of the fixing assembly 3 and the stay bar 2, and controlling the stay bar 2 to be fixed in the direction perpendicular to the longitudinal axis of the unmanned aerial vehicle body. That is, a part of the sliding component 5 is sleeved on the double-lug portion 303 of the fixing component 3, and a part of the sliding component is sleeved on the stay bar 2, so as to form a fixing function at the hinged position of the stay bar 2 and the fixing component 3, and the stay bar 2 can not rotate around the axis of the pin 301 any more by the sleeved mode. Bracing piece 2 and fixed subassembly 3 are on a straight line this moment, and bracing piece 2 and fixed subassembly 3 all are perpendicular to unmanned aerial vehicle fuselage axis of ordinates.
Before unmanned aerial vehicle takes off, 2 one end of vaulting pole and unmanned aerial vehicle launcher contact realize acting on unmanned aerial vehicle's support, and cotton rope 601 is for fixed state that does not cut off, is fixed in fixed subassembly 3 with sliding assembly 5 and vaulting pole 2's junction, vaulting pole 2, fixed subassembly 3's fixed part 302, two ears 303 and atress spring 304 all are in whole stress state this moment. After the unmanned aerial vehicle takes off, the cutter 602 cuts off the cotton rope, the sliding assembly 5 removes the control, namely the sliding assembly 5 moves towards one end of the supporting rod 2 away from the same fixed assembly 3 along the axis of the supporting rod 2 under the action of the stressed spring 304, when the sliding assembly 5 moves to be only sleeved on the supporting rod 2 and is not sleeved on the fixed assembly 3, the supporting rod 2 rotates along the axis of the pin 301 of the fixed assembly 3 under the action of the spring 4 connected with the groove 1, gradually approaches the groove 1 and is finally recovered into the groove 1, at the moment, the supporting device is in a recovery state, and the pneumatic characteristic and the flight performance of the unmanned aerial vehicle in the flight process cannot be influenced.
It should be noted that the unmanned aerial vehicle further includes an operation flap 7, and the cutter 602 and the cord 601 are disposed in the operation flap 7. As shown in fig. 1, the operating flap may be positioned above the recess 1 to facilitate installation of the cord 601 and cutter 602 by an operator during use. The cutter 602 is connected with a control system of the unmanned aerial vehicle, and after the unmanned aerial vehicle takes off, the control system of the unmanned aerial vehicle sends out an instruction to control the cutter 602 to cut off the cord 601.
In addition, the stay bar 2 is a cylinder, the sliding component 5 is a hollow cylinder (as shown in fig. 6), and the outer diameter of the stay bar 2 is matched with the inner diameter of the sliding component 5. However, the shape of the stay bar and the sliding member is not particularly limited in the embodiments of the present disclosure, and may be, for example, a rectangular parallelepiped or a hollow rectangular parallelepiped.
Those skilled in the art will appreciate that various combinations and/or combinations of features recited in the various embodiments and/or claims of the present disclosure can be made, even if such combinations or combinations are not expressly recited in the present disclosure. In particular, various combinations and/or combinations of the features recited in the various embodiments and/or claims of the present disclosure may be made without departing from the spirit or teaching of the present disclosure. All such combinations and/or associations are within the scope of the present disclosure.
While the disclosure has been shown and described with reference to certain exemplary embodiments thereof, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the disclosure as defined by the appended claims and their equivalents. Accordingly, the scope of the present disclosure should not be limited to the above-described embodiments, but should be defined not only by the appended claims, but also by equivalents thereof.
Claims (10)
1. A drone supporting device, the drone comprising a recess (1) in which the supporting device can be placed, the supporting device comprising: the unmanned aerial vehicle supporting device comprises a supporting rod (2) used for supporting an unmanned aerial vehicle, a fixing component (3) used for fixing one end of the supporting rod (2) in the groove (1), a spring (4) used for connecting the other end of the supporting rod (2) with the groove (1), and a sliding component (5) sleeved on the supporting rod (2);
the stay bar (2) can rotate around the fixing component (3), the sliding component (5) is used for controlling the stay bar (2) to be fixed in the direction vertical to the longitudinal axis of the unmanned aerial vehicle body or releasing the control, and the spring (4) is used for recovering the stay bar into the groove (1).
2. Support device according to claim 1, characterized in that said fixing assembly (3) comprises a pin (301), by means of which pin (301) said stay (2) is hinged, said stay (2) being rotatable about the axis of said pin (301).
3. The support device according to claim 2, characterized in that the fixing component (3) comprises a fixing part (302) and a double-supporting ear part (303), and a force-bearing spring (304) positioned between the fixing part (302) and the double-supporting ear part (303), wherein one end of the stay bar (2) is fixed in the groove (1) through the fixing part (302).
4. The support device according to claim 1, characterized in that the sliding assembly (5) comprises a movement control assembly (6) for moving the sliding assembly (5) along the axial direction of the stay (2), and the sliding assembly (5) controls the stay (2) to be fixed in the direction perpendicular to the longitudinal axis of the unmanned aerial vehicle body or to be released from the control through the movement.
5. The support device according to claim 4, characterized in that the movement control assembly (6) comprises: a cord (601) fixed to the sliding assembly (5), to the fixed assembly (3) and to the drone, and a cutter (602) for cutting the cord (601);
the rope fixes the position of the sliding assembly (5), so that the sliding assembly (5) controls the stay bar (2) to be fixed in the direction vertical to the longitudinal axis of the unmanned aerial vehicle body, and when the cutter (602) cuts off the rope, the sliding assembly (5) releases the control.
6. The support device according to claim 4, characterized in that the movement control assembly (6) comprises: a rope (601) with one end fixed on the sliding component (5) and the other end fixed on the unmanned aerial vehicle, and a cutter (602) for cutting off the rope;
the rope fixes the position of the sliding assembly (5), so that the sliding assembly (5) controls the stay bar (2) to be fixed in the direction vertical to the longitudinal axis of the unmanned aerial vehicle body, and when the cutter (602) cuts off the rope, the sliding assembly (5) releases the control.
7. The support device according to claim 5 or 6, characterized in that the sliding assembly (5) controls the strut (2) to be fixed in a direction perpendicular to the longitudinal axis of the unmanned aerial vehicle fuselage by being sleeved at the joint of the fixing assembly (3) and the strut (2).
8. The support device of claim 5 or 6, wherein the drone further comprises an operating flap (7), the cutter (602) and the cord (601) being disposed within the operating flap (7).
9. The support device of claim 8, wherein the cutter (602) is connected to a control system of the drone.
10. Support device according to claim 1, characterized in that the stay (2) is a cylinder, the sliding assembly (5) is a hollow cylinder, and the outer diameter of the stay (2) and the inner diameter of the sliding assembly (5) are mutually matched.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910187927.3A CN111688945A (en) | 2019-03-12 | 2019-03-12 | Unmanned aerial vehicle strutting arrangement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910187927.3A CN111688945A (en) | 2019-03-12 | 2019-03-12 | Unmanned aerial vehicle strutting arrangement |
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| Publication Number | Publication Date |
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| CN111688945A true CN111688945A (en) | 2020-09-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910187927.3A Pending CN111688945A (en) | 2019-03-12 | 2019-03-12 | Unmanned aerial vehicle strutting arrangement |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115402526A (en) * | 2022-10-11 | 2022-11-29 | 南昌航空大学 | Aircraft power boosting device |
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