CN112678199A - A collapsible debugging bracket car for fixed wing unmanned aerial vehicle - Google Patents
A collapsible debugging bracket car for fixed wing unmanned aerial vehicle Download PDFInfo
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- CN112678199A CN112678199A CN202110072570.1A CN202110072570A CN112678199A CN 112678199 A CN112678199 A CN 112678199A CN 202110072570 A CN202110072570 A CN 202110072570A CN 112678199 A CN112678199 A CN 112678199A
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Abstract
The invention relates to a foldable debugging bracket vehicle for a fixed-wing unmanned aerial vehicle, wherein the bottom of a main frame assembly is provided with a trundle mounting assembly, the front end of the main frame assembly is provided with a front supporting assembly, the rear end of the main frame assembly is provided with a rear supporting assembly, and the main frame assembly, the front supporting assembly and the rear supporting assembly are provided with inclined supports; the front end of the main frame component is provided with a traction rod. Has the following advantages: all structural parts all adopt and to weld the aluminium alloy, accomplished whole no magnetization, can not produce the influence to the operation of airborne equipment in the use, and aluminium alloy is easily purchased, processing moreover, whole low in manufacturing cost is honest and clean. Simple structure, easily operation, mechanism intensity is high, supports stably, safety, is applicable to the structure equipment, the debugging and the short distance transportation of all kinds of small and medium-size unmanned aerial vehicle. Selecting proper caster wheels and adjusting the wheel track of the left caster wheel and the right caster wheel according to different paved road surfaces; can realize quick expansion and folding to highly the wholeization after folding accounts for the space minimum, realizes piling up the transportation.
Description
Technical Field
The invention belongs to the technical field of structural design, and relates to a foldable debugging bracket vehicle for a fixed-wing unmanned aerial vehicle.
Background
Fixed wing unmanned aerial vehicle need do preparation work such as organism equipment, system antithetical couplet debugging, short-distance transportation before taking off, need can bear the workstation of aircraft organism, makes operating personnel can accomplish preparation work before taking off smoothly. Therefore, it is necessary to develop a process device which integrates the functions of machine body assembly, debugging and short-distance transportation.
The existing common method is to manufacture a wooden debugging bracket vehicle which has heavy structure and large volume and occupies large space during transportation.
Chinese invention patent CN105059719A discloses an internal structure of a small unmanned aerial vehicle packing case, which is a design combining a packing case and a debugging bracket. The design is that a bracket with two states is arranged in the packing box, wherein one state is that the bracket is completely arranged in the packing box, and all parts of the airplane are fixed by a mechanism and a binding belt for storage and transportation; the other state is that the bracket extends out of the packing box, and the bracket can be used as a debugging bracket. The scheme has ingenious structure, but has the defects that the airplane can not be transferred by using a bracket after the butt joint is completed, and only can be manually moved, so that the airplane is limited to a dozen kilograms-level small unmanned aerial vehicle.
Chinese invention patent CN108502206A discloses a multipurpose double-layer unmanned aerial vehicle fuselage transportation bracket. This design adopts double-deck frame construction, and operating personnel uses manual hydraulic pump drive lifting unit to move to change the bracket gesture, can accomplish unmanned aerial vehicle altitude mixture control, every single move gesture and adjust, and can carry out the undercarriage and receive and release the test. The design has high structural strength and convenient operation, and is suitable for finishing the specific test action of the medium-large-sized sliding-off and landing unmanned aerial vehicle; but has disadvantages of complicated structure and high manufacturing cost.
Disclosure of Invention
Technical problem to be solved
In order to avoid the defects of the prior art, the invention provides the foldable debugging bracket vehicle for the fixed-wing unmanned aerial vehicle, and solves the problems that the debugging bracket vehicle is complex in structure, high in manufacturing cost, large in occupied space during transportation and incapable of transferring the unmanned aerial vehicle. The invention provides a non-magnetic, foldable and universal unmanned aerial vehicle debugging bracket vehicle. Under the expansion state, the organism supports firmly, and it is convenient, reliable to remove, and it is minimum to account for the space under fold condition, can pile up and place, makes things convenient for long-distance transport to can accomplish fast and expand, fold, saved manpower and time.
Technical scheme
A foldable debugging bracket vehicle for a fixed-wing unmanned aerial vehicle is characterized by comprising a main frame component 1, a front support component 2, a rear support component 3, an inclined support 4, a caster wheel mounting component 5 and a traction rod 6; the bottom of the main frame component 1 is provided with a caster wheel mounting component 5, the front end is provided with a front support component 2, the rear end is provided with a rear support component 3, and the main frame component 1, the front support component 2 and the rear support component 3 are provided with inclined supports 4; the front end of the main frame component 1 is provided with a traction rod 6; the inclined strut 4 is connected with the main frame assembly 1 through a rotatable shaft and connected with the front support assembly 2 and the rear support assembly 3 through a detachable pin shaft, so that the inclined strut 4 can be folded onto the main frame assembly 1; the front support assembly 2 and the rear support assembly 3 are connected with the main frame assembly 1 through rotatable shafts.
The main frame subassembly is welded into "day" style of calligraphy frame by three stull and two erects to prop, puts the thing board and is located the main frame inboard, and the frame four corners is equipped with the pivot support, and fore-and-after stull is equipped with truckle telescope tube, is equipped with four through-holes that are used for the round pin axle on the erectting of both sides.
The front supporting assembly and the rear supporting assembly form a frame by two vertical supports and two transverse supports, and through holes are formed in the side faces of the vertical supports.
The inclined strut 4 is connected with a through hole on the side surface of the vertical strut of the main frame component 1 in a rotatable shaft manner, and is connected with through holes on the two sides of the vertical strut of the main frame component 1, the front strut component 2 and the rear strut component 3 in a detachable pin shaft manner, so that the inclined strut 4 can be folded onto the main frame component 1; the vertical supports of the front supporting component 2 and the rear supporting component 3 are connected with the rotating shaft supports at four corners of the main frame component 1 through rotatable shaft connection.
The upper end of the caster wheel mounting component 5 is provided with a caster wheel mounting plate 5-4 which is inserted into the caster wheel telescopic sleeve 1 of the main frame component 1, and the first quick-release pin 7 is fixedly positioned through holes on the main frame component 1 and the caster wheel mounting plate 5-4.
And the hole positions connected by the pin shafts are provided with quick-release pin sleeves.
The upper end of the front support component 2 is provided with a front support block 2-1 which is matched with the characteristic structure of the placed airplane body.
The upper end of the rear supporting component 3 is provided with a rear supporting block 3-1 which is matched with the characteristic structure of the plane body.
The two vertical supports of the main frame component 1 are provided with limiting pieces 1-7, the installation positions of the limiting pieces do not interfere with the inclined supports 4, and the front support component 2 and the rear support component 3 are clamped when the front support component 2 and the rear support component 3 are folded.
The main structure adopts an aluminum profile.
Collapsible unmanned aerial vehicle debugging bracket car structure includes: the main frame subassembly, preceding supporting component, back supporting component, 4 bracing, 4 truckle subassemblies, traction rod. The main frame assembly is a main body of the bracket vehicle, and 4 caster assemblies are inserted into a sleeve at the bottom of the main frame and are positioned by quick release pins; the front support assembly and the rear support assembly are respectively arranged in the front rotating shaft support and the rear rotating shaft support of the main frame through the perforated pins, and the front support assembly and the rear support assembly can rotate backwards and forwards by 90 degrees around the perforated pins; one side of each inclined support is arranged on the side edge of the frame of the main frame through a pin with a hole and can rotate around the pin with the hole, and the other side of each inclined support is connected with the front support and the rear support through quick-release pins to form a triangular stable structure; the traction rod is connected with a traction rod connecting seat fixed at the front part of the main frame through a quick-release pin and can rotate around the quick-release pin; all the main body structures of the components adopt weldable aluminum profiles, the whole components are nonmagnetic, the operation of airborne equipment cannot be influenced in use, and the components can be disassembled and disassembled quickly.
The main frame assembly includes: 4 pivot supports, 3 studdles, 2 erects to prop, 2 put the thing board, 4 quick-release pin bushes, 2 truckle telescopic tube, 4 spacing pieces, the traction lever connecting seat, 2 tying up the area, 4 sheets of rubber. The 4 rotating shaft supports are positioned at four corners and welded with the 3 cross braces and the 2 vertical braces to form a frame shaped like a Chinese character 'ri', and rotating shaft holes of the front and rear groups of rotating shaft supports are coaxial; 2 caster telescopic sleeves are welded on the bottom surface of the rotating shaft support respectively in front and at the back, and 4 through holes are manufactured as pin shaft holes by taking the through holes on the bottom surface of the rotating shaft support as positioning holes; 4 through holes are respectively formed in the vertical braces at the two sides, and the quick-release pin sleeves are welded in the 4 through holes close to the middle cross brace in an inlaid mode; the object placing plate is arranged at the inner side of the main frame to form an object placing space; 4 limiting pieces are respectively arranged on the vertical supports at the outer sides of the main frame; the draw bar connecting seat is arranged at the central position of the outer side of the cross brace at the front end of the main frame; 2 binding belts are fastened on the object placing plate; 4 rubber sheets are respectively attached to the bottom surfaces of the caster telescopic sleeves.
The front support assembly includes: 2 supporting shoes, 2 vertical braces, 2 stull, 2 quick-release cotter way, 4 rectangle handles. 2 vertical braces and 2 transverse braces are welded into a stable frame; 2 through holes are respectively formed in the upper part and the lower part of each side surface of the 2 vertical braces, two holes in the same position are coaxial, and a quick-release pin bush is welded in an upper hole in an inlaid manner; rounding the right angle of the single side of the vertical support by taking the lower hole as an axis; 2 supporting blocks are arranged at the upper parts of the vertical struts, and are manufactured according to the characteristic structure of the airplane to limit the course and the unfolding freedom degree of the airplane; 4 rectangle handles are installed on 2 studdles, and two liang collineations are with erectting to prop fillet direction homonymy.
The back supporting component comprises: 2 supporting shoes, 2 long erects to prop, 2 short erects to prop, 2 studders, 2 quick-release cotter ways, 4 rectangle handles. The short vertical braces and the transverse braces are welded into a stable frame, 2 through holes are respectively formed in the upper side and the lower side of the side surfaces of the 2 long vertical braces, the two holes are coaxial at the same position, and quick-release pin sleeves are welded in the upper holes in an embedded mode; rounding the right angle of the single side of the long vertical support by taking the lower hole as an axis; 2 supporting blocks are arranged at the upper parts of the vertical struts, and the supporting blocks are used for manufacturing a supporting machine body according to the local appearance of the airplane; 4 rectangle handles are installed on 2 studdles, and two liang collineations are with erectting to prop fillet direction homonymy.
The bracing is rectangle stock structure, and both ends system through-hole divide into 2 groups, and every group is 2, and a set of is connected with preceding supporting component in main frame subassembly both sides, and another group is connected with back supporting component in main frame subassembly both sides, preceding, back supporting component perpendicular to main frame when bracket car uses.
The caster wheel mounting assembly comprises: the truckle, truckle adapter, shock attenuation piece, truckle mounting panel, quick-release pin. The truckle is installed in truckle adapter bottom surface, passes the through-hole of truckle mounting panel through the cylindricality structure above the truckle adapter and uses quick-release pin joint, places the shock attenuation piece between truckle adapter and the truckle mounting panel, makes a set of equidistance through-hole on the truckle mounting panel and is used for adjusting the wheel base of truckle about the bracket car.
The draw bar is a long rod structure, one end of the draw bar is provided with a through hole, the other end of the draw bar is provided with a handle, and the draw bar is arranged on a draw bar connecting seat of the main frame through a quick-release pin.
Advantageous effects
The invention provides a foldable debugging bracket vehicle for a fixed-wing unmanned aerial vehicle, which is characterized in that a caster wheel mounting assembly is arranged at the bottom of a main frame assembly, a front support assembly is arranged at the front end of the main frame assembly, a rear support assembly is arranged at the rear end of the main frame assembly, and inclined supports are arranged on the main frame assembly, the front support assembly and the rear support assembly as well as the rear support assembly; the front end of the main frame component is provided with a traction rod; compared with the prior art, the invention has the following advantages:
according to the foldable debugging bracket vehicle for the fixed-wing unmanned aerial vehicle, all structural parts are made of weldable aluminum profiles, the integral non-magnetization is realized, the operation of airborne equipment is not influenced in the use process, the aluminum profiles are easy to purchase and process, and the integral manufacturing cost is low.
Simple structure, easily operation, mechanism intensity is high, supports stably, safety, is applicable to the structure equipment, the debugging and the short distance transportation of all kinds of small and medium-size unmanned aerial vehicle.
The self-usability and the easy transportation of the bracket vehicle are fully considered, and firstly, the proper caster wheels can be selected according to different paved road surfaces and the wheel track of the left caster wheel and the right caster wheel can be adjusted to ensure the moving safety of the airplane; secondly, by adopting a foldable structure and a quick-assembly and quick-disassembly design, the foldable bicycle can be unfolded and folded quickly, is highly integrated after being folded, occupies small space and realizes stacking and transportation.
Drawings
FIG. 1 is a schematic diagram of a foldable debugging carrier vehicle structure for a fixed wing drone
FIG. 2 is a schematic view of a main frame assembly
FIG. 3 is a schematic view of a front support assembly
FIG. 4 is a schematic view of the rear support assembly
FIG. 5 is a schematic view of a caster wheel mounting assembly
FIG. 6 is a schematic view of the folding process
FIG. 7 is a schematic front view of a folded state
FIG. 8 is a reverse side view of a folded state
Description of reference numerals: 1 main frame component, 2 front support component, 3 rear support component, 4 diagonal support, 5 caster wheel mounting component, 6 draw bar, 7 first quick-release pin, 8 first group of pin shafts with holes and matched split pin, 9 second group of pin shafts with holes and matched split pin, 10 second quick-release pin, 11 third quick-release pin, 1-1 rotating shaft support, 1-2 cross support, 1-3 vertical support, 1-4 object placing plate, 1-5 quick-release pin sleeve, 1-6 caster wheel telescopic sleeve, 1-7 spacing piece, 1-8 draw bar connecting seat, 1-9 binding belt, 1-10 rubber piece, 1-A first connecting hole, 1-B second connecting hole, 1-C third connecting hole, 1-D fourth connecting hole, 1-E fifth connecting hole, 2-1 support block, 2-2 front support vertical support, 2-3 front support cross brace, 2-4 front support quick release pin bushings, 2-5 rectangular handles, 2-A front support first connecting hole, 2-B front support second connecting hole, 3-1 rear support block, 3-2 long vertical braces, 3-3 short vertical braces, 3-4 rear support cross braces, 3-5 rear support quick release pin bushings, 3-6 rear support rectangular handles, 3-A rear support first connecting hole, 3-B rear support second connecting hole, 5-1 caster, 5-2 caster adapter, 5-3 shock absorbing sheet, 5-4 caster mounting plates, 5-5 fourth quick release pins, 5-A caster first connecting hole, and 5-B caster second connecting hole.
Detailed Description
The invention will now be further described with reference to the following examples and drawings:
referring to fig. 1 to 8, the present embodiment is a foldable debugging bracket vehicle for a fixed wing drone, which is composed of a main frame assembly 1, a front support assembly 2, a rear support assembly 3, an inclined support 4, a caster wheel mounting assembly 5, and a drawbar 6.
In the embodiment, the main frame assembly 1 is a main body of the bracket vehicle, and the caster wheel mounting plates 5-4 of the caster wheel mounting assembly 5 are inserted into the caster wheel telescopic sleeves 1-6 of the main frame assembly 1 and are positioned by the first quick-release pins 7; the front support assembly 2 is inserted into two rotating shaft supports 1-1 at the front part of the main frame assembly 1, is positioned by a first group of pin shafts with holes and a matched cotter pin 8, and can only rotate towards one side of the inclined support 4; the rear support component 3 is inserted into two rotating shaft supports 1-1 at the rear part of the main frame component 1, positioned by a first group of pin shafts with holes and matched cotter pins 8 and can only rotate towards one side of the inclined strut 4; one side of the inclined support 4 is connected with the side surface of the main frame 1 through a second group of pin shafts with holes and matched cotter pins 9 and can rotate around the pin shafts with holes 9, and the other side of the inclined support is connected with the front support component 2 and the rear support component 3 through a second quick-release pin 10 to form a triangular stable support; the draw bar 6 is connected with draw bar connecting seats 1-8 at the front part of the main frame assembly 1 through a third quick release pin 11 and can rotate around the third quick release pin 11. All the main body structures of the components adopt weldable aluminum profiles, the whole components are nonmagnetic, the operation of airborne equipment cannot be influenced in use, and the components can be disassembled and disassembled quickly.
4 rotating shaft supports 1-1 in the main frame group are positioned at four corners and are welded with 3 cross braces 1-2 and 2 vertical braces 1-3 to form a frame shaped like a Chinese character 'ri', at the moment, first holes 1-A of front and rear two groups of rotating shaft supports 1-1 are coaxial, 2 caster telescopic sleeves 1-6 are respectively welded with the bottom surfaces of the rotating shaft supports 1-1 to form a whole front and rear parts, and through holes are manufactured in the caster telescopic sleeves 1-6 by taking second holes 1-B of the rotating shaft supports 1-1 as positioning holes to position caster assemblies 5. 2 groups of third holes 1-C and fourth holes 1-D are arranged on the vertical braces 1-3, the axle center distance between the third holes 1-C and the fourth holes 1-D in each group is equal to the axle center distance between two holes on the inclined brace 4, and quick-release pin sleeves are welded at the fourth holes 1-D in a splicing manner; 2 object placing plates 1-4 are arranged at the inner side of the frame to form an object placing space, 2 binding belts 1-9 are arranged through the object placing plates 1-4, and the traction rods can be bound at the bottom of the main frame when the bracket vehicle is folded; 4 limiting pieces 1-7 are respectively arranged at the outer sides of the vertical supports 1-3, the installation positions are selected to ensure that the limiting pieces do not interfere with the inclined supports 4, the material is spring steel, the front support assembly 2 and the rear support assembly 3 can be clamped in a folding manner on the bracket vehicle, and the folding integral fastening is ensured; the traction rod connecting seats 1-8 are arranged at the central positions of the outer sides of the front end crossbars 1-2 and are used for connecting traction rods 6 and 4 rubber sheets which are respectively attached to the bottom surfaces of the caster telescopic sleeves, and the traction rods play a role in protection when a plurality of bracket vehicles are folded, stacked and placed and transported.
In the front support assembly, 2 front support vertical supports 2-2 and 2 front support transverse supports 2-3 are welded into a stable frame; the front support vertical support 2-2 is respectively provided with a front support first hole 2-A and a front support second hole 2-B, the two front support first holes 2-A and the two front support second holes 2-B are respectively coaxial, and the front support first holes 2-A are welded with the quick-release pin sleeves in a splicing manner; the single-side right angle of the vertical support 2-2 is rounded by taking the axle center of the front support second hole 2-B as an axis, and the radius of the right angle is equal to the distance between the axle center of the rotating shaft hole of the rotating shaft support 1-1 and the bottom surface of the through groove; two end surface areas of the front support second hole 2-B are in clearance fit with the through groove of the rotating shaft support 1-1 by adopting a base hole system, the thickness tolerance of the two end surface areas of the front support second hole 2-B is f7, and the opening width tolerance of the through groove of the rotating shaft support 1-1 is H8, so that the front support assembly 2 is ensured to be smoothly inserted into the rotating shaft support 1-1 and can rotate flexibly; 2 support blocks 2-1 are arranged at the upper parts of the front support vertical supports 2-2, the support blocks are manufactured according to the characteristic structure of the supported machine body, the heading and the unfolding freedom degree of the machine body can be limited, and the bracket vehicle can be used among different types of airplanes by replacing different support blocks; 4 rectangular handles 2-5 are arranged on 2-3 front support cross braces, are collinear in pairs and are positioned at the same side of the fillet direction of the vertical support, and the size of the inner space of the rectangular handle is the same as that of the cross section of the caster telescopic tube 1-6.
In the rear support assembly, 2 long vertical supports 3-2, 2 short vertical supports 3-3 and 2 rear support cross supports 3-4 are welded into a stable frame; the long vertical support 3-2 is respectively provided with a rear support first hole 3-A and a rear support second hole 3-B, the two rear support first holes 3-A and the two rear support second holes 3-B are respectively coaxial, and the rear support first holes 3-A are embedded with the quick-release pin bushings; then, the axis of the second supporting hole 3-B is used as an axis to round the right angle at one side of the long vertical support 3-2, and the radius of the right angle is equal to the distance between the axis of the rotating shaft hole of the rotating shaft support 1-1 and the bottom surface of the through groove; two end surface areas of the rear support second hole 3-B are in clearance fit with the through groove of the rotating shaft support 1-1 by adopting a base hole system, the thickness tolerance of the two end surface areas of the rear support second hole 3-B is f7, and the opening width tolerance of the through groove of the rotating shaft support 1-1 is H8, so that the rear support component 3 is ensured to be smoothly inserted into the rotating shaft support 1-1 and can rotate flexibly; 2 rear supporting blocks 3-1 are arranged on the upper parts of the long vertical supports 3-2 and the short vertical supports 3-3, the supporting blocks are manufactured according to the characteristic structure of a supported machine body, the machine body can be stably supported by adopting engineering plastic materials, and the bracket vehicle can be used among different types of airplanes by replacing different supporting blocks; 4 rear support rectangular handles 3-6 are arranged on 2 rear support cross braces 3-4, are collinear in pairs, are positioned at the same side of the 3-2 fillet directions of the long vertical supports, and have the same model as the rectangular handles 2-5.
The inclined strut 4 is a rectangular long rod structure, through holes are formed at two ends, and in order to enable the front strut assembly 2 and the rear strut assembly 3 to be perpendicular to the main frame assembly 1, the axial distance between the holes at two ends of the inclined strut 4 serving as a fixing piece must be equal to the axial distance between the first hole 2-A and the third hole 1-C of the front strut and the axial distance between the first hole 3-A and the second hole 1-C of the rear strut.
In the caster wheel mounting assembly, a common mounting structure of a large-load caster wheel is a flat plate four-corner bolt connection, the caster wheel is mounted on a caster wheel adapter 5-2 to realize the quick mounting and quick dismounting of the caster wheel, and the proper caster wheel can be quickly replaced according to different pavement pavements; when the caster 5-1 and the caster adapter 5-2 are connected, a bolt reversely passes through the mounting holes of the caster 5-1 and the caster adapter 5-2 from bottom to top, an avoidance blind hole is manufactured at the corresponding position of the bottom of the caster mounting plate 5-4, and a nut and a bolt which are exposed are hidden in the avoidance blind hole; the caster adapter 5-2 is inserted into a caster first hole 5-A in the caster mounting plate 5-4 and connected by a fourth quick-release pin 5-5; a group of caster second holes 5-B are formed in the caster mounting plate 5-4, and the extending width of the caster can be quickly adjusted according to the pavement condition, namely the wheel track of the left caster and the wheel track of the right caster are adjusted, so that the bottom contact width of the bracket vehicle is changed, and the running stability is improved.
The draw bar 6 is a long rod structure, one end of the draw bar is provided with a through hole, the other end of the draw bar is provided with a handle, the draw bar can be quickly disassembled and assembled through the third quick-release pin 11, the draw bar can rotate around the third quick-release pin 11, operators with different heights can draw the bracket vehicle, and the draw bar can be quickly fixed at the bottom of the main frame through a binding belt when being folded.
A use process that is used for collapsible debugging bracket car of fixed wing unmanned aerial vehicle is:
after the bracket vehicle is unfolded, the aircraft body is placed on the front support and the rear support, and the front support component clamps the characteristic structure of the aircraft body to limit the freedom degree of the heading and the unfolding direction of the aircraft body; the rear support assembly supports the airframe, so that the whole aircraft airframe can be safely and stably supported.
1 deployment of commissioning cradle carts
Placing a main frame 1, selecting a proper caster 5-1 according to the pavement condition to be connected with a caster mounting plate 5-4, inserting the caster telescopic sleeve 1-6 on the bottom surface of the main frame 1, and adjusting the extending width to be connected with a first quick-release pin 7; rotating the front support assembly 2 and the rear support assembly 3 to be vertical to the main frame 1, and connecting and fixing the front support assembly and the rear support assembly with the inclined support 4 by using a second quick release pin 10; and connecting the traction rod connecting seats 1-8 of the main frame 1 and the traction rod 6 by using a third quick-release pin 11, so that the unfolding process is completed.
2 folding of debugging bracket car
Fig. 6 is a schematic view of a folding process of a foldable unmanned aerial vehicle debugging bracket vehicle, wherein 4 caster wheel assemblies 5 are pulled out, and caster wheels 5-1 are inserted into rectangular handles 2-5 and 3-6 on the inner sides of a front support assembly 2 and a rear support assembly 3 towards the outer side of the bracket vehicle; pulling out the second quick release pin 10 of the inclined strut, rotating the inclined strut 4 to be parallel to the vertical strut 1-3 of the main frame, inserting the second quick release pin 10 into the quick release pin sleeve 1-5 of the main frame, and fixing the inclined strut 4 on the side edge of the main frame 1; the front supporting component 2, the rear supporting component 3 and the caster wheel component 5 respectively rotate backwards and forwards to be contacted with the main frame 1 and are clamped by the limiting pieces 1-7; the unloading drawbar 6 is fixed at the bottom of the main frame 1 by binding belts 1-9. Fig. 7 is a front schematic view of a folding state of a foldable unmanned aerial vehicle debugging bracket vehicle, and fig. 8 is a back schematic view of the folding state of the foldable unmanned aerial vehicle debugging bracket vehicle, so far, the folding process is completed.
Claims (10)
1. A foldable debugging bracket vehicle for a fixed-wing unmanned aerial vehicle is characterized by comprising a main frame assembly (1), a front support assembly (2), a rear support assembly (3), an inclined support (4), a caster wheel mounting assembly (5) and a traction rod (6); the bottom of the main frame component (1) is provided with a caster wheel mounting component (5), the front end is provided with a front support component (2), the rear end is provided with a rear support component (3), and the main frame component (1), the front support component (2) and the rear support component (3) are provided with inclined supports (4); the front end of the main frame component (1) is provided with a traction rod (6); the inclined support (4) is connected with the main frame assembly (1) through a rotatable shaft, and is connected with the front support assembly (2) and the rear support assembly (3) through a detachable pin shaft, so that the inclined support (4) can be folded onto the main frame assembly (1); the front supporting component (2) and the rear supporting component (3) are connected with the main frame component (1) through rotatable shaft connection.
2. The foldable commissioning cradle cart for fixed-wing drones of claim 1, wherein: the main frame subassembly is welded into "day" style of calligraphy frame by three stull and two erects to prop, puts the thing board and is located the main frame inboard, and the frame four corners is equipped with the pivot support, and fore-and-after stull is equipped with truckle telescope tube, is equipped with four through-holes that are used for the round pin axle on the erectting of both sides.
3. The foldable commissioning cradle cart for fixed-wing drones of claim 1, wherein: the front supporting assembly and the rear supporting assembly form a frame by two vertical supports and two transverse supports, and through holes are formed in the side faces of the vertical supports.
4. A foldable commissioning cradle cart for fixed wing drones according to claim 1 or 2, characterized in that: the inclined support (4) is connected with a through hole on the side surface of a vertical support of the main frame assembly (1) in a rotatable shaft manner, and is connected with through holes of vertical supports on two sides of the main frame assembly (1), the front support assembly (2) and the rear support assembly (3) in a detachable pin shaft manner, so that the inclined support (4) can be folded onto the main frame assembly (1); the vertical supports of the front supporting component (2) and the rear supporting component (3) are connected with the rotating shaft supports at four corners of the main frame component (1) through rotatable shaft connection.
5. The foldable commissioning cradle cart for fixed-wing drones of claim 1, wherein: the upper end of the caster wheel mounting assembly (5) is provided with a caster wheel mounting plate (5-4) which is inserted into a caster wheel telescopic sleeve (1) of the main frame assembly (1) and fixedly positioned by a first quick-release pin (7) through holes in the main frame assembly (1) and the caster wheel mounting plate (5-4).
6. The foldable commissioning cradle cart for fixed-wing drones of claim 1, wherein: and the hole positions connected by the pin shafts are provided with quick-release pin sleeves.
7. The foldable commissioning cradle cart for fixed-wing drones of claim 1, wherein: the upper end of the front support component (2) is provided with a front support block (2-1) which is matched with the characteristic structure of the placed airplane body.
8. The foldable commissioning cradle cart for fixed-wing drones of claim 1, wherein: the upper end of the rear supporting component (3) is provided with a rear supporting block (3-1) which is matched with the characteristic structure of the plane body.
9. The foldable commissioning cradle cart for fixed-wing drones of claim 1, wherein: spacing pieces (1-7) are arranged on two vertical supports of the main frame component (1), the installation position of the main frame component does not interfere with the inclined supports (4), and the front support component (2) and the rear support component (3) are clamped when the front support component (2) and the rear support component (3) are folded.
10. The foldable commissioning cradle cart for fixed-wing drones of claim 1, wherein: the main structure adopts an aluminum profile.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110072570.1A CN112678199A (en) | 2021-01-20 | 2021-01-20 | A collapsible debugging bracket car for fixed wing unmanned aerial vehicle |
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| CN202110072570.1A CN112678199A (en) | 2021-01-20 | 2021-01-20 | A collapsible debugging bracket car for fixed wing unmanned aerial vehicle |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060066065A1 (en) * | 2004-09-29 | 2006-03-30 | Delaware Capital Formation, Inc. | Removable caster system |
| DE202008014185U1 (en) * | 2008-10-24 | 2009-04-23 | Hagemeier, Franz | Hub shunting trolley for ultralight aircraft |
| CN203662155U (en) * | 2012-11-09 | 2014-06-25 | 新秀丽Ip控股有限责任公司 | Luggage case provided with casing with changeable depth |
| CN206781811U (en) * | 2017-03-01 | 2017-12-22 | 天弘(苏州)科技有限公司 | Anti-rollover loads stroller |
| CN108502206A (en) * | 2018-03-16 | 2018-09-07 | 中国航天空气动力技术研究院 | A kind of multipurpose double-layer unmanned aerial vehicle body pallet for transporting |
| CN209904794U (en) * | 2018-12-28 | 2020-01-07 | 成都四威高科技产业园有限公司 | Foldable bracket vehicle |
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2021
- 2021-01-20 CN CN202110072570.1A patent/CN112678199A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060066065A1 (en) * | 2004-09-29 | 2006-03-30 | Delaware Capital Formation, Inc. | Removable caster system |
| DE202008014185U1 (en) * | 2008-10-24 | 2009-04-23 | Hagemeier, Franz | Hub shunting trolley for ultralight aircraft |
| CN203662155U (en) * | 2012-11-09 | 2014-06-25 | 新秀丽Ip控股有限责任公司 | Luggage case provided with casing with changeable depth |
| CN206781811U (en) * | 2017-03-01 | 2017-12-22 | 天弘(苏州)科技有限公司 | Anti-rollover loads stroller |
| CN108502206A (en) * | 2018-03-16 | 2018-09-07 | 中国航天空气动力技术研究院 | A kind of multipurpose double-layer unmanned aerial vehicle body pallet for transporting |
| CN209904794U (en) * | 2018-12-28 | 2020-01-07 | 成都四威高科技产业园有限公司 | Foldable bracket vehicle |
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Application publication date: 20210420 |