CN211108051U - Detachable unmanned aerial vehicle bearing structure, fly device and fly recovery system - Google Patents
Detachable unmanned aerial vehicle bearing structure, fly device and fly recovery system Download PDFInfo
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- CN211108051U CN211108051U CN201921888886.2U CN201921888886U CN211108051U CN 211108051 U CN211108051 U CN 211108051U CN 201921888886 U CN201921888886 U CN 201921888886U CN 211108051 U CN211108051 U CN 211108051U
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Abstract
The utility model provides a detachable unmanned aerial vehicle bearing structure, fly off the device and fly off recovery system, should fly off recovery system and include that unmanned aerial vehicle flies device and recovery unit. The flying device comprises a flying tractor, a flying trailer and a detachable unmanned aerial vehicle supporting structure; the recovery device comprises a recovery tractor, a recovery trailer and a shock absorption piece. The utility model provides a close on space solar energy unmanned aerial vehicle's ground and fly away the recovery problem, this system has that simple structure is reliable, convenient to detach and change, and local damage can be restoreed very fast, characteristics such as interchangeability is good between each part.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field especially relates to a detachable unmanned aerial vehicle bearing structure, fly device and fly recovery system.
Background
With the continuous development of unmanned aerial vehicle technology, unmanned aerial vehicle plays an increasingly greater role in our life. The near space solar unmanned aerial vehicle runs at a height of 20km from the earth surface, and can theoretically realize permanent endurance by means of solar power supply. Because the size of the solar unmanned aerial vehicle in the near space is large, the flight speed is low, and the requirement on the weight is very high. Conventional solar drones are all provided with an undercarriage structure which is useful for the drone only during the takeoff and landing phases, belonging to the "dead weight" during the whole flight phase. For a solar unmanned aerial vehicle flying in a month-crossing or even year-crossing manner, the elimination of the undercarriage structure has a very positive influence on the comprehensive performance of the system.
SUMMERY OF THE UTILITY MODEL
In view of this, the main object of the present invention is to provide a detachable unmanned aerial vehicle supporting structure, a flying device and a flying recovery system, so as to at least partially solve at least one of the above mentioned technical problems.
In order to achieve the above object, as an aspect of the utility model provides a detachable unmanned aerial vehicle bearing structure, including main tributary vaulting pole, preforming, auxiliary stay pole and actuating mechanism, wherein:
one end of the main supporting rod is rotatably connected to a supporting support, and the other end of the main supporting rod is provided with a U-shaped groove with an upward opening and used for horizontally limiting an unmanned aerial vehicle butt-joint piece arranged in the U-shaped groove;
the upper limiting part is arranged above the U-shaped groove and matched with the U-shaped groove to vertically limit the unmanned aerial vehicle butt joint part;
one end of the auxiliary supporting rod is movably connected with the main supporting rod through the connecting part of the pressing sheet to form linkage;
the force application end of the driving mechanism is connected with the main support rod and provides a rotary driving force for the main support rod;
wherein, make preforming and auxiliary stay produce the interlock through the rotation of main tributary vaulting pole, and make the last spacing portion of preforming removes from U type recess top, realizes the horizontal spacing and the vertical spacing of removing to unmanned aerial vehicle butt joint spare.
As another aspect of the utility model, still provide a detachable unmanned aerial vehicle bearing structure, including main tributary vaulting pole, preforming, vice bracing piece and fixed establishment, wherein:
one end of the main supporting rod is rotatably connected to a supporting support, and the other end of the main supporting rod is provided with an L-shaped groove with an upward opening and used for carrying out unidirectional horizontal limiting on an unmanned aerial vehicle butt-joint piece arranged in the L-shaped groove;
the pressing piece comprises an upper limiting part and a connecting part, the upper limiting part is arranged above the L-shaped groove and is matched with the L-shaped groove to vertically limit the unmanned aerial vehicle butt joint part;
one end of the auxiliary supporting rod is movably connected with the main supporting rod through the connecting part of the pressing sheet to form linkage;
the force application end of the fixing mechanism is connected with the main support rod and provides fixing acting force for the main support rod, the connecting part of the pressing sheet and the auxiliary support rod which form linkage;
wherein, through the spacing antiport of one-way level is followed to unmanned aerial vehicle butt joint spare, realizes the horizontal spacing and the vertical spacing of unmanned aerial vehicle butt joint spare and relieves.
As a further aspect of the utility model, still provide an unmanned aerial vehicle device of flying, including flying the tractor, flying trailer and a plurality of support element, wherein:
the flying tractor is connected with the flying trailer and is used for providing traction force for the flying trailer;
the flying trailer can reach the ground clearance speed of the unmanned aerial vehicle under the traction of the flying tractor;
a plurality of supporting element include respectively as above-mentioned detachable unmanned aerial vehicle bearing structure, along unmanned aerial vehicle's balanced atress position set up in fly between trailer and the unmanned aerial vehicle fly after the trailer reaches unmanned aerial vehicle's terrain clearance, unmanned aerial vehicle bearing structure is through the spacing removal to the unmanned aerial vehicle butt joint piece, and the completion is right unmanned aerial vehicle flies.
As a further aspect of the present invention, there is also provided an unmanned aerial vehicle flying recovery system, comprising a recovery device and the unmanned aerial vehicle flying device as described above;
recovery unit is including retrieving tractor, retrieving trailer and damper, wherein:
the recovery tractor is connected with the recovery trailer and is used for providing traction force for the recovery trailer;
the recovery trailer is used for keeping the movement consistent with the horizontal speed and the course of the unmanned aerial vehicle under the traction of the recovery tractor so as to enable the gliding unmanned aerial vehicle to land;
the shock attenuation piece sets up on retrieving the trailer for to descending unmanned aerial vehicle carries out the shock attenuation.
According to the technical scheme, the utility model discloses at least, one of them or one of them part of following beneficial effect has:
the utility model discloses a design detachable unmanned aerial vehicle bearing structure, fly off the device and fly off recovery system and replace the undercarriage structure on the traditional technique, realize taking off and landing stage's auxiliary action, cancel the undercarriage structure, the effectual structure dead weight that reduces solar energy unmanned aerial vehicle has improved the comprehensive performance of its system;
the utility model realizes the tasks of flying and recovering the unmanned aerial vehicle by adopting the ground unmanned aerial vehicle flying and recovering system, has lower requirements on the take-off and landing runway of the unmanned aerial vehicle, and can realize the flying and recovering of the unmanned aerial vehicle on the narrower runway;
the utility model has the advantages of maintain simply, the system is simple reliable, be convenient for observe, dismantle and change, and local damage should be able to restore very fast, interchangeability is good between each part.
Drawings
Fig. 1 is a schematic view of an unmanned aerial vehicle flying apparatus according to an embodiment of the present invention;
fig. 2 is a schematic view of an unmanned aerial vehicle recovery device according to an embodiment of the present invention;
fig. 3 is a schematic view of a detachable drone support structure of a first form of embodiment of the present invention;
fig. 4 is a schematic diagram of a first form of detachable unmanned aerial vehicle support structure cutting completion status of an embodiment of the present invention;
figure 5 is a side view of a detachable drone support structure cut completion state of a first form of an embodiment of the present invention;
fig. 6 is a schematic structural view of a front main support rod according to an embodiment of the present invention;
figure 7 is a schematic view of a detachable drone support structure of a second form of embodiment of the present invention;
figure 8 is a side view of a detachable drone supporting structure of a second form of embodiment of the present invention;
fig. 9 is a schematic structural view of a rear main support rod according to an embodiment of the present invention;
FIG. 10 is a schematic view of an embodiment of the present invention showing a structure of a secondary support rod;
fig. 11 is a schematic structural view of a diagonal member according to an embodiment of the present invention;
figure 12 is a side view of a wafer structure according to an embodiment of the present invention;
fig. 13 is the utility model discloses unmanned aerial vehicle reserves interface structure schematic diagram.
In the above drawings, the reference numerals are as follows:
1. a tractor; 2. a front support unit; 3. a triangular trailer; 4. an unmanned aerial vehicle; 5. a rear support unit; 7. a platform trailer; 6. a lifting platform; 8. a shock-absorbing air bag; 11. a docking interface; 12. a front main support bar; 13. a spring; 14. a spring support; 15. tabletting; 151. a limiting part; 152. a connecting portion; 16. exploding the bolt; 17. an auxiliary support rod; 18. a diagonal member; 19. a support base; 20. a diagonal draw bar support; 21. the back main support rod.
Detailed Description
It should also be noted that directional terms, such as "upper", "lower", "front", "rear", "left", "right", etc., used in the embodiments are only directions referring to the drawings, and are not intended to limit the protection scope of the present invention. Throughout the drawings, like elements are represented by like or similar reference numerals. Conventional structures or constructions will be omitted when they may obscure the understanding of the present invention.
And the shapes and sizes of the respective components in the drawings do not reflect actual sizes and proportions, but merely illustrate the contents of the embodiments of the present invention. Furthermore, in the claims, any reference signs placed between parentheses shall not be construed as limiting the claim.
Furthermore, the word "comprising" does not exclude the presence of elements or steps not listed in a claim. The word "a" or "an" preceding an element does not exclude the presence of a plurality of such elements.
As one aspect of the present invention, an embodiment of the present invention provides an unmanned aerial vehicle flying recovery system, which includes a recovery device and an unmanned aerial vehicle flying device;
recovery unit is including retrieving tractor, retrieving trailer and damper, wherein:
the recovery tractor is connected with the recovery trailer and is used for providing traction force for the recovery trailer;
the recovery trailer is used for keeping the movement consistent with the horizontal speed and the course of the unmanned aerial vehicle under the traction of the recovery tractor so as to enable the gliding unmanned aerial vehicle to land;
the shock attenuation piece sets up on retrieving the trailer for carry out the shock attenuation to the unmanned aerial vehicle that descends.
As another aspect of the utility model, the embodiment of the utility model provides an foretell unmanned aerial vehicle device of flying, including flying the tractor, flying trailer and a plurality of support element, wherein:
the flying tractor is connected with the flying trailer and is used for providing traction force for the flying trailer;
the flying trailer can reach the ground clearance speed of the unmanned aerial vehicle under the traction of the flying tractor;
a plurality of supporting element include detachable unmanned aerial vehicle bearing structure respectively, set up between flying trailer and unmanned aerial vehicle along unmanned aerial vehicle's balanced atress position, after flying the trailer and reach unmanned aerial vehicle's terrain clearance, unmanned aerial vehicle bearing structure is through the spacing removal to unmanned aerial vehicle, accomplishes and fly to unmanned aerial vehicle.
The utility model discloses an in some embodiments, unmanned aerial vehicle device of flying still includes a plurality of lift platforms, sets up in the support element and flies between the trailer one-to-one for adjust unmanned aerial vehicle's height.
The utility model discloses an in the embodiment, the quantity of supporting element can add and make up according to actual conditions with setting up the position, can but not confine to, and the quantity of supporting element is 3, is the back supporting element of 1 preceding supporting element and two symmetries respectively, is isosceles triangle and distributes as long as can play stable supporting role can.
Wherein, in some embodiments of the present invention, the front supporting unit comprises a detachable unmanned aerial vehicle supporting structure of a first form, the detachable unmanned aerial vehicle supporting structure of the first form comprises a main supporting rod, a pressing sheet, an auxiliary supporting rod and a driving mechanism, wherein:
one end of the main support rod is rotatably connected to a support, and the other end of the main support rod is provided with a U-shaped groove with an upward opening and used for horizontally limiting an unmanned aerial vehicle butt joint piece arranged in the U-shaped groove;
the pressing piece comprises an upper limiting part and a connecting part, the upper limiting part is arranged above the U-shaped groove and is matched with the U-shaped groove to vertically limit the unmanned aerial vehicle butt joint part;
one end of the auxiliary supporting rod is movably connected with the main supporting rod through a connecting part of the pressing sheet to form linkage;
the force application end of the driving mechanism is connected with the main support rod and provides a rotary driving force for the main support rod;
wherein, the rotation through the main tributary vaulting pole makes preforming and auxiliary stay produce the interlock, and makes the last spacing portion of preforming removes from U type recess top, realizes the horizontal spacing and the vertical spacing of removing to unmanned aerial vehicle butt joint spare.
It can be understood that unmanned aerial vehicle interfacing part is the interfacing part between unmanned aerial vehicle bearing structure and the unmanned aerial vehicle promptly, and it can be fixed in unmanned aerial vehicle on, fix unmanned aerial vehicle and spacing on unmanned aerial vehicle bearing structure through unmanned aerial vehicle interfacing part.
In some embodiments of the present invention, the driving mechanism includes a spring and an inclined pull rod respectively disposed on both sides of the main support rod, wherein:
one end of the spring is connected with the spring support, and the other end of the spring is connected with the main support rod;
one end of the diagonal draw bar is connected with the diagonal draw bar support, and the other end of the diagonal draw bar is connected with the main support bar through an explosive bolt;
the connection between the diagonal draw bar and the main support bar is cut off by controlling the explosive bolt, and the main support bar is driven to rotate under the action of the spring.
The utility model discloses an in some embodiments, the detachable unmanned aerial vehicle bearing structure of back supporting unit including second form, the detachable unmanned aerial vehicle bearing structure of second form includes main tributary vaulting pole, preforming, vice bracing piece and fixed establishment, wherein:
one end of the main supporting rod is rotatably connected to a supporting support, and the other end of the main supporting rod is provided with an L-shaped groove with an upward opening and used for carrying out one-way horizontal limiting on an unmanned docking piece arranged in the L-shaped groove;
the pressing piece comprises an upper limiting part and a connecting part, the upper limiting part is arranged above the L-shaped groove and is matched with the L-shaped groove to vertically limit the unmanned aerial vehicle butt-joint piece;
one end of the auxiliary supporting rod is movably connected with the main supporting rod through a connecting part of the pressing sheet to form linkage;
the force application end of the fixing mechanism is connected with the main support rod and provides fixing acting force for the main support rod, the connecting part of the pressing sheet and the auxiliary support rod which are linked;
wherein, follow the spacing reverse movement of one-way level through the unmanned aerial vehicle butt joint spare, realize the horizontal spacing and the vertical spacing of unmanned aerial vehicle butt joint spare and relieve.
In some embodiments of the present invention, the securing mechanism comprises a diagonal draw bar; one end of the diagonal draw bar is connected with the diagonal draw bar support, and the other end of the diagonal draw bar is connected with the main support rod.
In some embodiments of the present invention, the other end of the auxiliary support rod is rotatably connected to the support base; the auxiliary support rod, the connecting part of the pressing sheet, the main support rod and the support form four-connecting-rod linkage;
the utility model discloses an in some embodiments, the preforming sets up to the Z type, and the last horizontal pole is upper limit portion, and the bottom end rail is connecting portion, the both ends of connecting portion respectively with main tributary vaulting pole and vice bracing piece swing joint.
The utility model discloses an in the embodiment, the detachable unmanned aerial vehicle bearing structure of first form and the detachable unmanned aerial vehicle bearing structure of second form, the structure is similar, convenient to detach and change, and interchangeability is good between each part.
Of course, in the utility model discloses an in other embodiments, the unmanned aerial vehicle bearing structure of second form can also be chooseed for use to the supporting element, and the unmanned aerial vehicle bearing structure of first form can also be chooseed for use to the back supporting element, and is not particularly restricted. Only when the number of the detachable unmanned aerial vehicle supporting structures in the first form is more than two, explosive bolts need to be controlled to simultaneously occur when the unmanned aerial vehicle supporting structures are cut off; and preferably at least comprises a first form of drone support structure to ensure that the drone can be reliably secured to the drone flying apparatus.
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in detail with reference to the accompanying drawings.
Examples
The embodiment of the utility model provides a flying recovery system of a near space solar unmanned aerial vehicle, which consists of an unmanned aerial vehicle flying device and a recovery device;
fig. 1 is a schematic view of an unmanned aerial vehicle flying device according to an embodiment of the present invention, and as shown in fig. 1, the unmanned aerial vehicle flying device is composed of a tractor 1, a triangular trailer 3, a lifting platform 6, a front support unit 2, a rear support unit 5, and the like; wherein, the triangle trailer 3 is used as a flying trailer;
more specifically, the triangular trailer 3 is mechanically connected with the tractor 1, the triangular trailer 3 is pulled to move by the tractor 1, and three lifting platforms 6 are arranged on the triangular trailer 3 to adjust the height of the unmanned aerial vehicle 4, so that the unmanned aerial vehicle 4 is prevented from colliding with the tractor 1 in front when flying;
preceding support element 2 and back support element 5 and lift platform 6 between carry out mechanical fixed connection, unmanned aerial vehicle 4 is connected with preceding support element 2, back support element 5 through the butt joint interface 11 (being unmanned aerial vehicle butt joint spare) that reserves.
Fig. 3 is a schematic view of a detachable drone support structure of a first form of embodiment of the present invention; fig. 4 is a schematic diagram of a first form of detachable unmanned aerial vehicle support structure cutting completion status of an embodiment of the present invention; figure 5 is a side view of a detachable drone support structure cut completion state of a first form of an embodiment of the present invention; fig. 6 is a schematic structural view of a front main support rod according to an embodiment of the present invention; FIG. 10 is a schematic view of an embodiment of the present invention showing a structure of a secondary support rod; fig. 11 is a schematic structural view of a diagonal member according to an embodiment of the present invention; figure 12 is a side view of a wafer structure according to an embodiment of the present invention; fig. 13 is the utility model discloses unmanned aerial vehicle reserves interface structure schematic diagram.
As shown in fig. 3 to 6 and fig. 10 to 13, in the embodiment of the present invention, the front support unit 2 is composed of a front main support rod 12, a pressing plate 15, an auxiliary support rod 17, a diagonal member 18, an explosion bolt 16, a spring 13, a spring support 14, a support 19, and a diagonal member support 20;
the front main support rod 12 of the front support unit 2 is a main support structure and is connected with the support 19 through a pin; the auxiliary support rod 17 is also connected with the support 19 through a pin;
the front main supporting rod 12 and the auxiliary supporting rod 17 are connected through a pressing piece 15 in a pin connection mode, and the front main supporting rod, the auxiliary supporting rod and the auxiliary supporting rod can rotate mutually;
the pressing piece 15 comprises an upper limiting part 151 and a connecting part 152, wherein the upper limiting part 151 is arranged above the U-shaped groove and is matched with the U-shaped groove to vertically limit the unmanned aerial vehicle butt joint part;
namely, the docking interface 11 of the unmanned aerial vehicle 4 is pressed in a reserved C-shaped groove (namely a U-shaped groove) on the front main supporting rod 12 through a pressing sheet 15, the C-shaped groove structure can limit the forward and backward movement of the unmanned aerial vehicle 4, and the vertical direction is limited through the pressing sheet 15;
two interfaces are reserved on the front main support rod 12, the rear side interface is connected with a diagonal draw bar 18 through an explosive bolt 16, and the other side of the diagonal draw bar 18 is in pin connection with a diagonal draw bar support 20; the front side interface of the front main support rod 12 is connected with a spring support 14 through a spring 13; after the cutting instruction is sent, the explosive bolt 16 finishes cutting, the inclined pull rod 18 is separated from the front main support rod 12, at the moment, the front support unit 2 tilts forward under the action of the spring 13, the pressing sheet 15 is separated from the butt joint interface 11 of the unmanned aerial vehicle 4, and the unmanned aerial vehicle is completely flown.
More specifically, in the embodiment of the present invention, fig. 7 is a schematic view of a detachable unmanned aerial vehicle supporting structure of a second form of the embodiment of the present invention; figure 8 is a side view of a detachable drone supporting structure of a second form of embodiment of the present invention; fig. 9 is a schematic structural view of the rear main support rod according to the embodiment of the present invention.
As shown in fig. 7-9 and fig. 10-13, the rear end support unit 5 is composed of a rear main support bar 21, a pressing sheet 15, an auxiliary support bar 17, a diagonal member 18, a support 19, a diagonal member support 20, and the like;
the rear main support rod 21 of the rear end support unit is a main support structure, the auxiliary support rod 17 is connected with the rear main support rod 21 through a pressing piece 15, and the connection mode is pin connection;
the rear main supporting rod 21, the auxiliary supporting rod 17 and the supporting support 19 are connected through pins;
an interface is reserved on the rear main support rod 21 and is connected with the diagonal draw bar 18 through a pin, and the other side of the diagonal draw bar 18 is connected with the diagonal draw bar support 20 through a pin, so that the rear end support system is fixed and cannot tilt and rotate back and forth;
in "L" type recess of reserving is pressed on back main support pole 21 through preforming 15 to unmanned aerial vehicle 4's butt joint interface 11, this "L" groove structure only carries on spacingly to unmanned aerial vehicle 4's backward removal, and it is spacing not to carry on to the removal, and wherein vertical direction carries on spacingly through preforming 15.
Wherein, fig. 2 is a schematic view of the recovery device of the unmanned aerial vehicle according to the embodiment of the present invention, as shown in fig. 2, the recovery device is composed of a tractor 1, a platform trailer 7, a damping air bag 8, and the like; wherein, the platform trailer 7 is used as a recovery trailer, and the damping air bag 8 is used as a damping part;
when unmanned aerial vehicle 4 accomplished the predetermined task and navigated back and approach ground, pull unmanned aerial vehicle recovery unit through tractor 1 and move to make unmanned aerial vehicle 4 aim at the central line of shock attenuation gasbag 8, keep tractor 1 unanimous with unmanned aerial vehicle 4's horizontal velocity, the course is unanimous, make unmanned aerial vehicle 4 slowly descend on shock attenuation gasbag 8, accomplish unmanned aerial vehicle 4's safety recovery.
Wherein, in the embodiment of the utility model provides an in, unmanned aerial vehicle is let to fly and is retrieved the concrete implementation description as follows:
when the unmanned aerial vehicle flying device carries the unmanned aerial vehicle 4 to slide at a high speed, a power system of the unmanned aerial vehicle 4 starts to work, when the ground clearance of the unmanned aerial vehicle 4 is reached, an explosion bolt of the front supporting unit 2 is cut off through remote control, the front supporting unit 2 tilts forward, front end release is completed, meanwhile, a rear end interface of the unmanned aerial vehicle 4 is also separated from the rear supporting unit 5, and flying of the unmanned aerial vehicle 4 is completed;
when unmanned aerial vehicle 4 accomplished the predetermined task and navigated back and approach ground, pull recovery unit through tractor 1 and move to make unmanned aerial vehicle 4 aim at the central line of shock attenuation gasbag 8, keep tractor 1 unanimous, the course unanimous with unmanned aerial vehicle 4's horizontal velocity, make unmanned aerial vehicle slowly descend on shock attenuation gasbag 8, accomplish unmanned aerial vehicle 4's safety recovery.
According to the above embodiment, the utility model provides a close on space solar energy unmanned aerial vehicle's ground and fly away the recovery problem, this system has and maintains simply, and the system is simple reliable, be convenient for observe, dismantle and change, and local damage can be restoreed very fast, characteristics such as interchangeability is good between each part.
The system for recovering flying of the solar unmanned aerial vehicle in the near space is not limited to be applied to the solar unmanned aerial vehicle, but also can be applied to other unmanned aerial vehicles of various types, target drone and the like.
In addition, unless steps are specifically described or must occur in sequence, the order of the steps is not limited to that listed above and may be changed or rearranged as desired by the desired design. The embodiments described above may be mixed and matched with each other or with other embodiments based on design and reliability considerations, i.e., technical features in different embodiments may be freely combined to form further embodiments.
Similarly, it should be appreciated that in the foregoing description of exemplary embodiments of the invention, various features of the invention are sometimes grouped together in a single embodiment, figure, or description thereof for the purpose of streamlining the disclosure and aiding in the understanding of one or more of the various inventive aspects. However, the method of the present invention should not be interpreted as reflecting an intention that: rather, the invention as claimed requires more features than are expressly recited in each claim. Rather, as the following claims reflect, inventive aspects lie in less than all features of a single foregoing disclosed embodiment. Thus, the claims following the detailed description are hereby expressly incorporated into this detailed description, with each claim standing on its own as a separate embodiment of this invention.
The above-mentioned embodiments, further detailed description of the objects, technical solutions and advantages of the present invention, it should be understood that the above-mentioned embodiments are only specific embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (10)
1. The utility model provides a detachable unmanned aerial vehicle bearing structure, its characterized in that includes main bracing piece, preforming, vice bracing piece and actuating mechanism, wherein:
one end of the main supporting rod is rotatably connected to a supporting support, and the other end of the main supporting rod is provided with a U-shaped groove with an upward opening and used for horizontally limiting an unmanned aerial vehicle butt-joint piece arranged in the U-shaped groove;
the upper limiting part is arranged above the U-shaped groove and matched with the U-shaped groove to vertically limit the unmanned aerial vehicle butt joint part;
one end of the auxiliary supporting rod is movably connected with the main supporting rod through the connecting part of the pressing sheet to form linkage;
the force application end of the driving mechanism is connected with the main support rod and provides a rotary driving force for the main support rod;
wherein, make preforming and auxiliary stay produce the interlock through the rotation of main tributary vaulting pole, and make the last spacing portion of preforming removes from U type recess top, realizes the horizontal spacing and the vertical spacing of removing to unmanned aerial vehicle butt joint spare.
2. The detachable unmanned aerial vehicle support structure of claim 1, wherein the driving mechanism comprises a spring and a diagonal draw bar respectively disposed on two sides of the main support bar, wherein:
one end of the spring is connected with the spring support, and the other end of the spring is connected with the main support rod;
one end of the diagonal draw bar is connected with the diagonal draw bar support, and the other end of the diagonal draw bar is connected with the main support rod through an explosive bolt;
the connection between the diagonal draw bar and the main support bar is cut off by controlling the explosive bolt, and the main support bar is driven to rotate under the action of the spring.
3. The utility model provides a detachable unmanned aerial vehicle bearing structure, its characterized in that includes main bracing piece, preforming, vice bracing piece and fixed establishment, wherein:
one end of the main supporting rod is rotatably connected to a supporting support, and the other end of the main supporting rod is provided with an L-shaped groove with an upward opening and used for carrying out unidirectional horizontal limiting on an unmanned aerial vehicle butt-joint piece arranged in the L-shaped groove;
the pressing piece comprises an upper limiting part and a connecting part, the upper limiting part is arranged above the L-shaped groove and is matched with the L-shaped groove to vertically limit the unmanned aerial vehicle butt joint part;
one end of the auxiliary supporting rod is movably connected with the main supporting rod through the connecting part of the pressing sheet to form linkage;
the force application end of the fixing mechanism is connected with the main support rod and provides fixing acting force for the main support rod, the connecting part of the pressing sheet and the auxiliary support rod which form linkage;
wherein, through the spacing antiport of one-way level is followed to unmanned aerial vehicle butt joint spare, realizes the horizontal spacing and the vertical spacing of unmanned aerial vehicle butt joint spare and relieves.
4. The detachable drone supporting structure of claim 3, wherein the securing mechanism includes a diagonal draw bar; one end of the diagonal draw bar is connected with the diagonal draw bar support, and the other end of the diagonal draw bar is connected with the main support rod.
5. The detachable unmanned aerial vehicle support structure of claim 1 or 3, wherein the other end of the secondary support rod is rotatably connected with the support pedestal; the auxiliary support rod, the connecting part of the pressing sheet, the main support rod and the support form four-connecting-rod linkage;
the preforming sets up to the Z type, goes up the horizontal pole and is upper limit portion, and the lower horizontal pole is connecting portion, the both ends of connecting portion respectively with main tributary vaulting pole and vice bracing piece swing joint.
6. The utility model provides an unmanned aerial vehicle device of flying, its characterized in that, including the tractor of flying, the trailer and a plurality of support element of flying, wherein:
the flying tractor is connected with the flying trailer and is used for providing traction force for the flying trailer;
the flying trailer can reach the ground clearance speed of the unmanned aerial vehicle under the traction of the flying tractor;
a plurality of supporting units, include the detachable unmanned aerial vehicle bearing structure of claim 1 or 3 respectively, set up between the trailer of flying away and unmanned aerial vehicle along unmanned aerial vehicle's balanced atress position, after the trailer of flying away reaches unmanned aerial vehicle's ground clearance, unmanned aerial vehicle bearing structure accomplishes through removing the spacing to unmanned aerial vehicle butt joint spare, and the completion is right unmanned aerial vehicle flies away.
7. The unmanned aerial vehicle device that flies of claim 6, wherein the number of the support units is 3, and the support units are respectively 1 front support unit and two symmetrical rear support units, and are distributed in an isosceles triangle; the front support unit comprising the drone support structure of claim 1 and the rear support unit comprising the drone support structure of claim 3;
unmanned aerial vehicle device of flying still includes a plurality of lift platforms, set up in one-to-one in between support element and the trailer of flying for adjust unmanned aerial vehicle's height.
8. An unmanned aerial vehicle flying recovery system, comprising recovery means and unmanned aerial vehicle flying means as claimed in claim 6 or 7;
recovery unit is including retrieving tractor, retrieving trailer and damper, wherein:
the recovery tractor is connected with the recovery trailer and is used for providing traction force for the recovery trailer;
the recovery trailer is used for keeping the movement consistent with the horizontal speed and the course of the unmanned aerial vehicle under the traction of the recovery tractor so as to enable the gliding unmanned aerial vehicle to land;
the shock attenuation piece sets up on retrieving the trailer for to descending unmanned aerial vehicle carries out the shock attenuation.
9. The unmanned aerial vehicle recovery system that flies of claim 8, wherein the trailer that flies is a triangular trailer; the recovery trailer is a platform trailer.
10. The unmanned aerial vehicle recovery system that flies of claim 8, wherein the shock absorber is a shock absorbing air bag.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201921888886.2U CN211108051U (en) | 2019-11-04 | 2019-11-04 | Detachable unmanned aerial vehicle bearing structure, fly device and fly recovery system |
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| CN201921888886.2U CN211108051U (en) | 2019-11-04 | 2019-11-04 | Detachable unmanned aerial vehicle bearing structure, fly device and fly recovery system |
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| CN211108051U true CN211108051U (en) | 2020-07-28 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110667874A (en) * | 2019-11-04 | 2020-01-10 | 中国科学院工程热物理研究所 | Detachable unmanned aerial vehicle bearing structure, fly device and fly recovery system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110667874A (en) * | 2019-11-04 | 2020-01-10 | 中国科学院工程热物理研究所 | Detachable unmanned aerial vehicle bearing structure, fly device and fly recovery system |
| CN110667874B (en) * | 2019-11-04 | 2024-06-14 | 中国科学院工程热物理研究所 | Detachable unmanned aerial vehicle bearing structure, put and fly device and put and fly recovery system |
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Granted publication date: 20200728 Effective date of abandoning: 20240614 |