CN105398566A - Unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle Download PDFInfo
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- CN105398566A CN105398566A CN201410458158.3A CN201410458158A CN105398566A CN 105398566 A CN105398566 A CN 105398566A CN 201410458158 A CN201410458158 A CN 201410458158A CN 105398566 A CN105398566 A CN 105398566A
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Abstract
The present invention discloses an unmanned aerial vehicle, which comprises a battery, a control circuit assembly, multiple groups of paddle assemblies, and a body, wherein the paddle assemblies are circumferentially arranged around the body and comprise paddle arms, paddle blades and a motor electrically connected to the control circuit assembly, one ends of each paddle arm are hinged to the body, the unmanned aerial vehicle further comprises a paddle locking assembly and gas rods corresponding to each paddle arm in a one-to-one manner, the arm body between both ends of the paddle arm is connected to the body through the gas rod, the paddle assembly has a folding state and an expanding state, the paddle locking assembly maintains the folding state paddle assembly at the folding state, and the gas rods expand the folding state paddle assembly to achieve the expanding state and maintains the expanding state paddle assembly at the expanding state, such that the packaging structure for transportation is reduced, and the space volume occupied during the storage is reduced. In addition, the paddle assembly is expanded through the driving by the gas rods, and the manual installation is not required.
Description
Technical field
The present invention relates to vehicle technology field, especially relate to a kind of unmanned plane.
Background technology
In this year, unmanned plane is subject to increasing attention with its simple structure, the easily feature such as manipulation and higher safety performance.Unmanned plane of the prior art, its paddle arm and fuselage are mostly one-body molded, part is also had to be paddle arm is divided into first paragraph paddle arm and second segment paddle arm two parts, first paragraph paddle arm and fuselage one-body molded, second segment paddle arm is connected with first paragraph paddle arm detouchable, solve the problem of transport, storage space to a certain extent, but still need artificial installation when in use, comparatively loaded down with trivial details.
Summary of the invention
Main purpose of the present invention is to provide a kind of unmanned plane, is intended to, while saving transport and storage space further, reach in use also without the need to manually installing the object of paddle arm.
For achieving the above object, the invention provides a kind of unmanned plane, comprise battery, control circuit assembly, many group oar assemblies and fuselage, described oar assembly is arranged around the circumference of described fuselage, described oar assembly comprises paddle arm, blade and the motor be connected with described control circuit electrical component, one end and the described fuselage of each described paddle arm are hinged, described unmanned plane also comprise lock oar assembly and with each described paddle arm gas bar one to one, arm body between described paddle arm two ends is connected with described fuselage by gas bar described in, described oar assembly has folded state and deployed condition, the described oar assembly being in folded state is remained on folded state by described lock oar assembly, the described oar assembly being in folded state is expanded to deployed condition and remains on deployed condition by described gas bar.
Preferably, described fuselage comprises upper casing, lower casing, and the supporting seat assembly between described upper casing and lower casing, described supporting seat assembly comprises with each described paddle arm one_to_one corresponding and the supporting seat arranged around a circumference, described supporting seat is provided with adaptive and for the accommodating clearance position being in the paddle arm of folded state with described paddle arm, one end of described paddle arm offers the first paddle arm mounting hole, the relative both sides of described clearance position offer supporting seat mounting hole respectively, each described paddle arm is hinged on corresponding supporting seat respectively by the fastener that runs through described supporting seat mounting hole and the first paddle arm mounting hole, described supporting seat also offers the first gas bar via hole that is corresponding with the position of described gas bar and that can swing for described gas bar, described gas bar is through described first gas bar via hole, and its one end is hinged on it the arm of described paddle arm, and the other end is hinged on described fuselage.
Preferably, described fuselage also comprises the upper fixed cap and lower fixed cap that are fixed together, described lower fixed cap is fixedly connected with described lower casing with between described lower casing at described supporting seat assembly, described unmanned plane also comprises and the rotating shaft one to one of each described gas bar, be provided with between the end face that fixed lid matches with described lower fixed cap and cooperatively interact and the positioning groove of accommodating each described rotating shaft, fixed covering offers the second gas bar via hole corresponding with the position of each described rotating shaft, described gas bar is through described second gas bar via hole, its one end is set in described rotating shaft hinged with described fuselage rotationally.
Preferably, described lock oar assembly comprises around described fuselage and for the banding part of tightening the described oar assembly being in folded state and be located on described fuselage for locking and the latching device unclamping described banding part.
Preferably, described banding part comprises bandage body and is located at described bandage body two ends and buckles with the left and right of through hole, described latching device comprises and has a telescopic shaft and the electromagnet be connected with described control circuit electrical component, described electromagnet is fixed on described lower casing, when described oar assembly is in folded state, telescopic shaft described in described solenoid actuated is protruding and be inserted in the through hole of described left and right button, to be fixed together by described left and right button.
Preferably, described banding part comprises bandage body and is located at described bandage body two ends and with the left side of through hole, right button, described latching device comprises gear, tooth bar, expansion link and the lock oar motor be connected with described control circuit electrical component, described tooth bar is installed on described lower casing slidably, the output shaft that described gear is fixed on described lock oar motor is connected with a joggle with described tooth bar, described expansion link is connected to one end of described tooth bar, when described oar assembly is in folded state, described lock oar motor drives described expansion link protruding and is inserted into a described left side, in the through hole of right button, with by a described left side, right button is fixed together.
Preferably, described lock oar assembly comprises lock blade, blasting cartridge, explosion lead-in wire and Blasting Control unit, what described blasting cartridge was provided with accommodating explosive agent seals chamber up for safekeeping, one end of described explosion lead-in wire is connected with the explosive agent in described blasting cartridge, the other end is connected with described Blasting Control unit, described Blasting Control unit is connected with described control circuit electrical component, and when described oar assembly is in folded state, described blasting cartridge and described lock blade are fixed together.
Preferably, described motor comprises the motor body of the outer end being fixed on described paddle arm, with the rotating disk be fixed on the output shaft of described motor body, described rotating disk is convexly equipped with two fixed legs, the center of line and the jante et perpendiculaire of described rotating disk between described two fixed legs, described blade comprises first paragraph blade and second segment blade, the coupling end of described first paragraph blade and second segment blade all offers the blade mounting hole with described fixed leg adaptation, described first paragraph blade and second segment blade are socketed on described two fixed legs respectively by the blade mounting hole on it rotationally, when described oar assembly is in folded state, first paragraph blade and second segment blade draw in and jointly enclose in the space of formation in each described paddle arm.
Preferably, the cross-sectional plane of described paddle arm is in " recessed " font.
A kind of unmanned plane provided by the present invention, by adopting the oar assembly of collapsible design, because of this reduce packaging structure for transporting and reduce deposit time shared spatial volume, oar assembly is driven by gas bar and launches, without the need to artificial installation simultaneously.
Accompanying drawing explanation
Fig. 1 is the structural representation of unmanned plane of the present invention in deployed condition;
Fig. 2 is the structural representation of unmanned plane of the present invention at folded state;
Fig. 3 is the oar assembly of unmanned plane of the present invention and the mounting structure schematic diagram of fuselage;
Fig. 4 is the three-dimensional assembly diagram of the fuselage of unmanned plane of the present invention;
Fig. 5 is the exploded view of the fuselage shown in Fig. 2;
Fig. 6 is the structural representation of the supporting seat shown in Fig. 3;
Fig. 7 is the structural representation of the upper fixed cap shown in Fig. 3;
Fig. 8 is the structural representation of the lower fixed cap shown in Fig. 5;
Fig. 9 is the structural representation of the first detailed description of the invention of lock oar assembly of unmanned plane of the present invention;
Figure 10 is the structural representation of lock oar assembly the second detailed description of the invention of unmanned plane of the present invention;
Figure 11 is the structural representation of the oar assembly of unmanned plane of the present invention;
Figure 12 is the structural representation of the motor shown in Figure 11;
Figure 13 is the structural representation of the blade shown in Figure 11.
The realization of the object of the invention, functional characteristics and advantage will in conjunction with the embodiments, are described further with reference to accompanying drawing.
Detailed description of the invention
Should be appreciated that specific embodiment described herein only in order to explain the present invention, be not intended to limit the present invention.
The invention provides a kind of unmanned plane, it is folding Rotor Helicopter, see Fig. 1 to Fig. 3, in the preferred embodiment of unmanned plane of the present invention, this unmanned plane comprises battery (not shown), control circuit assembly (not shown), many groups oar assembly 200 and fuselage 100, the chamber for set battery and control circuit assembly is provided with in fuselage 100, battery is storage battery, such as lithium cell, electric energy is provided for the associated components to unmanned plane, control circuit assembly comprises multiple control module, such as controlling unmanned plane during flying attitude flight control modules, for the Big Dipper module (such as GPS module) of the unmanned plane that navigates, and the data processing module etc. of the environmental information to obtain for the treatment of relevant airborne equipment.In better embodiment, fuselage 100 in cylindric, and is described fuselage 100 to be provided with six groups of oar assemblies 200, and as shown in Figure 1, these six groups of oar assemblies 200 are evenly arranged around the circumference of fuselage 100.Should be appreciated that the number of the oar assembly 200 shown in figure is only citing, when practical application, this number can be selected flexibly, such as in other embodiments, fuselage 100 is provided with the oar assembly 200 of four groups of oar assemblies 200 or other any suitable numbers.
Particularly, the motor 220 that oar assembly 200 comprises paddle arm 210, blade 230 and is connected with control circuit electrical component, blade 230 is arranged on the output shaft of motor 220, one end and the fuselage 100 of each paddle arm 210 are hinged, and motor 220 is arranged on the other end of paddle arm 210, in addition, this unmanned plane also comprise lock oar assembly 400 and with each paddle arm 210 gas bar 300 one to one, the arm body between each paddle arm 210 two ends is connected with fuselage 100 respectively by a gas bar 300.Therefore, by this telescopic gas bar 300, corresponding paddle arm 210 is driven to turn an angle (such as 90 degree) around the hinge axes of itself and fuselage 100, also be, oar assembly 200 has folded state and deployed condition, preferably, when oar assembly 200 is in folded state, paddle arm 210 turns to and fuselage 100 position side by side; When oar assembly 200 is in deployed condition, paddle arm 210 turns to the vertical position of fuselage 100.Wherein, the oar assembly 200 being in folded state is remained on folded state by lock oar assembly 400, and when removing its lock function when locking oar assembly 400 and starting, the oar assembly 200 being in folded state is expanded to deployed condition and remains on deployed condition by gas bar 300.
It is worth mentioning that, the cross-sectional plane of paddle arm 210 is in " recessed " font, and when unmanned plane launches flight, the paddle arm 210 of this version has better aerodynamic performance, plays the effect of stable unmanned plane and reduction flight resistance.
As can be seen here, unmanned plane of the present invention is by adopting the oar assembly 200 of collapsible design, and because of spatial volume shared when the packaging structure that this reduces for transporting and reducing is deposited, oar assembly drives expansion, without the need to artificial installation by gas bar simultaneously.
Particularly, see Fig. 4 to Fig. 6, fuselage 100 comprises upper casing 110, lower casing 120 and the supporting seat assembly between upper casing 110 and lower casing 120, and the two ends up and down of supporting seat assembly are fixedly connected with lower casing 120 with upper casing 110 respectively by screw.Wherein, this supporting seat assembly comprises with each paddle arm 210 one_to_one corresponding and the supporting seat 130 arranged around a circumference, and preferably, supporting seat 130 is arranged around an even circumferential, thus reduces the difficulty of balance unmanned plane, and improves the stability of unmanned plane.Supporting seat 130 is provided with adaptive and for the accommodating clearance position being in the paddle arm 210 of folded state with paddle arm 210, upper casing 110 cylindrically, there is the chamber of set battery and control circuit assembly, the annular side portions 122 that lower casing 120 comprises rounded body 121 and upwards extends to form from the periphery of body 121, and this annular side portions 122 caves inward and is formed with the depressed part 123 corresponding with the position of the clearance position of each supporting seat 130, therefore when the length of paddle arm 210 is greater than the height of supporting seat 130, the lower casing 120 be positioned at below supporting seat 130 also can not cause interference to the paddle arm 210 being in folded state.When oar assembly 200 is in folded state, what paddle arm 210 was overlapping with fuselage 100 is partially submerged into the clearance position and depressed part 123 of supporting seat 130, therefore can reduce volume when unmanned plane is in folded state, be convenient to packed and transported, transmitting and air-drop.See Figure 11, one end of paddle arm 210 offers the first paddle arm mounting hole 211, the both sides that the clearance position of supporting seat 130 is relative offer supporting seat mounting hole 1321 respectively, and the first paddle arm mounting hole 211 is suitable with supporting seat mounting hole 1321, each paddle arm 210 is hinged on corresponding supporting seat 130 respectively by the fastener (such as, this fastener is bearing pin or screw rod) always wearing supporting seat mounting hole 1321 and the first paddle arm mounting hole 211.See Fig. 6, in one embodiment, supporting seat 130 comprises body 131 in straight plate, is positioned at the side plate 132 of these body 131 both sides and is positioned at the top board 133 of this body 131 upper end, its latus inframedium 132 and top board 133 are all vertical with body 131, two side plates 132 and top board 133 limit the clearance position of accommodating paddle arm 210 jointly, and supporting seat mounting hole 1321 is opened on biside plate 132.
Be understandable that, by the supporting seat assembly all-in-one-piece between upper casing 110 and lower casing 120, thus the assembly process of unmanned plane can also be simplified and improve the bulk strength of unmanned plane in other embodiment.
Particularly, see Fig. 3, supporting seat 130 also offers the first gas bar via hole 1311 (corresponding to Fig. 6) that is corresponding with the position of gas bar 300 and that can swing for this gas bar 300, this the first gas bar via hole 1311 is opened on body 131, preferably, the first gas bar via hole 1311 is the waist-shaped hole of strip shape.Gas bar 300 is through the first gas bar via hole 1311 of supporting seat 130, and its one end is hinged on it the arm of paddle arm 210, and the other end is hinged on fuselage 100.It should be noted that, the long straight portion that the arm body of paddle arm 210 refers between paddle arm 210 two ends divides, and position when articulated position can be launched according to the length of gas bar 300 and paddle arm 210 between gas bar 300 and paddle arm 210 is determined, is not restricted this.When locking oar assembly 400 and removing the restriction to oar assembly 200, oar assembly 200 can turn to deployed condition under the driving of the piston rod of gas bar 300, the expansion process of oar assembly 200 does not need other engine installations to provide power, and gas bar 300 can provide stable support to the oar assembly 200 being in deployed condition.It can thus be appreciated that exhibition oar assembly 200 structure of the present embodiment is simple, with low cost.It is worth mentioning that, other any suitable piston rod piece also can be adopted to substitute the gas bar 300 of the present embodiment, but this piston rod piece should possess the feature such as little, lightweight that takes up room, concrete structure about piston rod piece can design according to the version of gas bar 300 and principle of work, and therefore not to repeat here.
Further, see Fig. 7 and Fig. 8, fuselage 100 also comprises the upper fixed cap 140 and lower fixed cap 150 that are fixed together, and upper fixed cap 140 and lower fixed cap 150 are the loop configuration being provided with a central through hole, thus alleviate the weight of unmanned plane.Be fixedly connected with by screw between upper fixed cap 140 with lower fixed cap 150, such as, upper fixed cap 140 offers some mounting holes 143 around its central through hole, lower fixed cap 150 offers the tapped bore 156 corresponding with the position of the mounting hole 143 of upper fixed cap 140.Wherein, lower fixed cap 150 is between supporting seat assembly with lower casing 120 and be fixedly connected with lower casing 120, lower fixed cap 150 comprises the body 151 of tabular, the end face that body 151 docks with upper fixed cap 140 is convexly equipped with the annular relief 152 of the central through hole around lower fixed cap 150, and the sidewall of body 151 caves inward and is formed with the breach 157 corresponding with the position of the clearance position of supporting seat 130, thus satisfied requirement paddle arm 210 is contained in the clearance position of supporting seat 130.Supporting seat 130 is also fixedly connected with by screw with lower fixed cap 150, such as, body 151 offers the through hole 155 corresponding with the position of the side plate 132 of supporting seat 130, as shown in Figure 8, through hole 155 is positioned near the dual-side of breach 157, and the bottom surface of the side plate 132 of supporting seat 130 offers the tapped bore (not shown) corresponding with the position of through hole 155, screw passes through hole 155 and screws in the tapped bore of the side plate 132 of supporting seat 130 and be fastened on supporting seat 130 by lower fixed cap 150.In addition, unmanned plane also comprises and each gas bar 300 rotating shaft one to one 310, be provided with between the end face that upper fixed cap 140 matches with lower fixed cap 150 and cooperatively interact and the positioning groove of each rotating shaft 310 accommodating, this positioning groove is made up of two parts groove be separately positioned on upper fixed cap 140 and lower fixed cap 150, such as, the medial surface of upper fixed cap 140 is arranged with to be evenly arranged around its center and with the upper deep-slotted chip breaker 141 of rotating shaft 310 adaptation, the upper surface of lower fixed cap 150 is arranged with corresponding with the position of deep-slotted chip breaker on each 141 and with the arc lower groove 153 of rotating shaft 310 adaptation, in order to improve the constant intensity of rotating shaft 310, arc lower groove 153 is positioned on annular protrusion 152, upper fixed cap 140 also offers the second gas bar via hole 142 corresponding with the position of each rotating shaft 310, and the upper surface of lower fixed cap 150 is also provided with the groove 154 corresponding with the position of each the second gas bar via hole 142 or through hole, thus meet the matching requirements of gas bar 300.Gas bar 300 is through the second gas bar via hole 142 of upper fixed cap 140, and its one end is socketed in rotating shaft 310 hinged with fuselage 100 rotationally, therefore improves the Joint strenght of gas bar 300 articulated structure.
It is worth mentioning that, the articulated structure between gas bar 300 and fuselage 100 also has numerous embodiments, and such as, in the present embodiment, above-mentioned rotating shaft 310 is wholely set with lower fixed cap 150, thus simplifies the structure design of fuselage 100, alleviates the weight of unmanned plane.
In an embodiment of the present invention, lock oar assembly 400 has numerous embodiments, lock oar assembly 400 comprises around fuselage 100 and for the banding part of tightening the oar assembly 200 being in folded state and be located at for locking and the latching device unclamping this banding part on fuselage 100, and wherein the formation of banding part and latching device and principle of work will hereafter elaborate.
Fig. 9 shows lock oar assembly first embodiment of unmanned plane of the present invention.In the present embodiment, banding part comprises bandage body 410 and is located at bandage body 410 two ends and buckles 411 and rightly buckle 412 with through hole left, bandage body 410 can be plastic cement flat rubber belting, also can be fiber or nylon flat rubber belting, because bandage body 410 is flexible-belt, therefore be suitable for the oar assembly 200 being in folded state to tighten, and oar assembly 200 can not be damaged.Latching device comprises and has a telescopic shaft 421 and the electromagnet 420 be connected with control circuit electrical component, this electromagnet 420 is fixed on lower casing 120, such as can be fixed by screws in together between the two, electromagnet 420 can be positioned on the upper surface of lower casing 120, also can be positioned on the lower surface of lower casing 120.When electromagnet 420 is positioned at the upper surface of lower casing 120, the through hole 124 (corresponding to Fig. 5) passing this annular side portions 122 for telescopic shaft 421 also need be offered in the annular side portions 122 of lower casing 120.When oar assembly 200 is in folded state, electromagnet 420 drives telescopic shaft 421 protruding and is inserted under the control of control circuit assembly leftly buckles 411 and rightly buckle in the through hole of 412, so that left button 411 and right button 412 are fixed together, thus by all oar assemblies 200 being locked on fuselage 100 around the fuselage bandage body 410 of 100 1 weeks; And when oar assembly 200 will launch, electromagnet 420 under the control of control circuit assembly, drive telescopic shaft 421 inwardly to retract and from left buckle 411 and right button the through hole of 412 exit, to make left button 411 and right button 412 depart from mutually, thus bandage body 410 and fuselage 100 are departed from.Thus, by this lock oar assembly 400 can realize easily to the locking of oar assembly 200 with unclamp.
Figure 10 shows lock oar assembly second embodiment of unmanned plane of the present invention.In the present embodiment, the latching device lock oar motor 430 that comprises gear 431, tooth bar 432, expansion link 433 and be connected with control circuit electrical component.Wherein, tooth bar 432 is installed on lower casing 120 slidably, same as above, on the upper surface that latching device can be positioned at lower casing 120 or lower surface, tooth bar 432 is fixed on lower casing 120 by the fastener 434 that has chute, tooth bar 432 has the structure matched with the chute of fastener 434, therefore tooth bar 432 be limited in fastener 434 chute in moving linearly, the output shaft that gear 431 is fixed on lock oar motor 430 is connected with a joggle with tooth bar 432, and expansion link 433 is connected to one end of tooth bar 432.When oar assembly 200 is in folded state, lock oar motor 430 under the control of control circuit assembly just then drive expansion link 433 protruding and be inserted into and leftly buckle 411 and rightly buckle in the through hole of 412, so that left button 411 and right button 412 are fixed together, thus by all oar assemblies 200 being locked on fuselage 100 around the fuselage bandage body 410 of 100 1 weeks; And when oar assembly 200 will launch, lock oar motor 430 under the control of control circuit assembly reversion and drive expansion link 433 inwardly to retract and from left buckle 411 and right button the through hole of 412 exit, to make left button 411 and right button 412 depart from mutually, thus bandage body 410 and fuselage 100 are departed from.Thus, by this lock oar assembly 400 also can realize easily to the locking of oar assembly 200 with unclamp.
In addition, lock oar assembly of the present invention also has other embodiments, such as, lock oar assembly comprises lock blade, blasting cartridge, explosion lead-in wire and Blasting Control unit (all not shown in figure), what wherein blasting cartridge was provided with accommodating explosive agent seals chamber up for safekeeping, the impulsive force produced to reduce explosion impacts unmanned plane, blasting cartridge is preferably nonmetallic pipe and makes, explosive agent can be pressed powder explosive, also can be liquid explosive, when practical application, corresponding fried pharmacy type can be adopted as required; One end of explosion lead-in wire is connected with the explosive agent in blasting cartridge, and the other end is connected with Blasting Control unit, and Blasting Control unit is connected with control circuit electrical component.In better embodiment, adopt the agent of pulsed arc fired charge, therefore one end generation high-voltage arc of Blasting Control unit for making explosion lead-in wire be positioned at blasting cartridge, and the control of controlled circuit unit.When oar assembly 200 is in folded state, blasting cartridge is fixed together with lock blade, thus enclose the loop configuration being formed and tighten the oar assembly 200 being in folded state, when oar assembly 200 will launch, under the control of control circuit assembly, Blasting Control unit makes explosion go between and produces high-voltage arc, to ignite blasting cartridge, thus make to be enclosed the loop configuration formed disconnected by blasting cartridge and lock blade, and then lock oar assembly is separated with unmanned plane.In the present embodiment, lock blade can be the Plastic Parts of strip shape, also can be the banding part shown in Fig. 9 and Figure 10, such as, lock blade is above-mentioned banding part, then blasting cartridge is inserted in the through hole of left button 411 and right button 412, left button 411 and right button 412 to be fixed together, thus by being locked on fuselage 100 around the fuselage bandage body 410 of 100 1 weeks by all oar assemblies 200; And when oar assembly 200 will launch, under the control of control circuit assembly, Blasting Control unit makes explosion lead-in wire produce high-voltage arc, to ignite blasting cartridge, thus left button 411 and right button 412 are departed from mutually, and then bandage body 410 and fuselage 100 are departed from.
See Figure 11 to Figure 13, in the present embodiment, motor 220 comprises the motor body 221 of the outer end being fixed on paddle arm 210, with the rotating disk 222 be fixed on the output shaft of motor body 221, rotating disk 222 can be circular, ellipse and other any suitable shapes, as shown in the figure, in order to make rotating disk 222 more steady in rotation process, the shape of preferred rotating disk 222 is circular, rotating disk 222 is convexly equipped with two fixed legs (being the first fixed leg 223 and the second fixed leg 224 respectively), first fixed leg 223 and the second fixed leg 224 are positioned in the same radial alignment of rotating disk 222, and the center of line and the jante et perpendiculaire of rotating disk 222 between the first fixed leg 223 and the second fixed leg 224, blade 230 comprises first paragraph blade 231 and second segment blade 232, the coupling end 2311 of first paragraph blade 231 offers the blade mounting hole 2312 with the first fixed leg 223 adaptation, in like manner, the coupling end of second segment blade 232 offers the blade mounting hole (not shown) with the second fixed leg 224 adaptation, first paragraph blade 231 is socketed on the first fixed leg 223 by the blade mounting hole 2312 on it rotationally, and prevent first paragraph blade 231 from deviating from by arranging position limiting structure in the end of the first fixed leg 223, such as, the end of the first fixed leg 223 is provided with outside thread, can carry out spacing to first paragraph blade 231 by the nut being arranged on the end of the first fixed leg 223, the connection structure of second segment blade 232 and assembly method are identical with first paragraph blade 231, therefore not to repeat here.Be understandable that, in order to satisfied flight requirement, first paragraph blade 231 and second segment blade 232 Central Symmetry.It can thus be appreciated that, when oar assembly 200 is in folded state, by by first paragraph blade 231 and second segment blade 232 folded side by side, can space be saved; And when oar assembly 200 is in deployed condition, first paragraph blade 231 and second segment blade 232 from folded side by side State Transferring to the state of being arranged in a straight line, can achieve the autonomous expansion of blade 230 under the driving of motor 220.It is worth mentioning that, when oar assembly 200 is in deployed condition, motor 220 and blade 230 are positioned at the lower position of paddle arm 210, and the motor 220 of this arrangement form and blade 230 can save space when oar assembly 200 is in folded state.
Should be understood that; these are only the preferred embodiments of the present invention; can not therefore limit the scope of the claims of the present invention; every utilize specification sheets of the present invention and accompanying drawing content to do equivalent structure or equivalent flow process conversion; or be directly or indirectly used in other relevant technical fields, be all in like manner included in scope of patent protection of the present invention.
Claims (9)
1. a unmanned plane, is characterized in that, comprise battery, control circuit assembly, many group oar assemblies and fuselage, described oar assembly is arranged around the circumference of described fuselage, described oar assembly comprises paddle arm, blade and the motor be connected with described control circuit electrical component, one end and the described fuselage of each described paddle arm are hinged, described unmanned plane also comprise lock oar assembly and with each described paddle arm gas bar one to one, arm body between described paddle arm two ends is connected with described fuselage by gas bar described in, described oar assembly has folded state and deployed condition, the described oar assembly being in folded state is remained on folded state by described lock oar assembly, the described oar assembly being in folded state is expanded to deployed condition and remains on deployed condition by described gas bar.
2. unmanned plane as claimed in claim 1, it is characterized in that, described fuselage comprises upper casing, lower casing, and the supporting seat assembly between described upper casing and lower casing, described supporting seat assembly comprises with each described paddle arm one_to_one corresponding and the supporting seat arranged around a circumference, described supporting seat is provided with adaptive and for the accommodating clearance position being in the paddle arm of folded state with described paddle arm, one end of described paddle arm offers the first paddle arm mounting hole, the relative both sides of described clearance position offer supporting seat mounting hole respectively, each described paddle arm is hinged on corresponding supporting seat respectively by the fastener that runs through described supporting seat mounting hole and the first paddle arm mounting hole, described supporting seat also offers the first gas bar via hole that is corresponding with the position of described gas bar and that can swing for described gas bar, described gas bar is through described first gas bar via hole, and its one end is hinged on it the arm of described paddle arm, and the other end is hinged on described fuselage.
3. unmanned plane as claimed in claim 2, it is characterized in that, described fuselage also comprises the upper fixed cap and lower fixed cap that are fixed together, described lower fixed cap is fixedly connected with described lower casing with between described lower casing at described supporting seat assembly, described unmanned plane also comprises and the rotating shaft one to one of each described gas bar, be provided with between the end face that fixed lid matches with described lower fixed cap and cooperatively interact and the positioning groove of accommodating each described rotating shaft, fixed covering offers the second gas bar via hole corresponding with the position of each described rotating shaft, described gas bar is through described second gas bar via hole, its one end is set in described rotating shaft hinged with described fuselage rotationally.
4. the unmanned plane as described in claim 1,2 or 3, it is characterized in that, described lock oar assembly comprises around described fuselage and for the banding part of tightening the described oar assembly being in folded state and be located on described fuselage for locking and the latching device unclamping described banding part.
5. unmanned plane as claimed in claim 4, it is characterized in that, described banding part comprises bandage body and is located at described bandage body two ends and buckles with the left and right of through hole, described latching device comprises and has a telescopic shaft and the electromagnet be connected with described control circuit electrical component, described electromagnet is fixed on described lower casing, when described oar assembly is in folded state, telescopic shaft described in described solenoid actuated is protruding and be inserted in the through hole of described left and right button, to be fixed together by described left and right button.
6. unmanned plane as claimed in claim 4, it is characterized in that, described banding part comprises bandage body and is located at described bandage body two ends and with the left side of through hole, right button, described latching device comprises gear, tooth bar, expansion link and the lock oar motor be connected with described control circuit electrical component, described tooth bar is installed on described lower casing slidably, the output shaft that described gear is fixed on described lock oar motor is connected with a joggle with described tooth bar, described expansion link is connected to one end of described tooth bar, when described oar assembly is in folded state, described lock oar motor drives described expansion link protruding and is inserted into a described left side, in the through hole of right button, with by a described left side, right button is fixed together.
7. the unmanned plane as described in claim 1,2 or 3, it is characterized in that, described lock oar assembly comprises lock blade, blasting cartridge, explosion lead-in wire and Blasting Control unit, what described blasting cartridge was provided with accommodating explosive agent seals chamber up for safekeeping, one end of described explosion lead-in wire is connected with the explosive agent in described blasting cartridge, the other end is connected with described Blasting Control unit, described Blasting Control unit is connected with described control circuit electrical component, when described oar assembly is in folded state, described blasting cartridge and described lock blade are fixed together.
8. unmanned plane as claimed in claim 1, it is characterized in that, described motor comprises the motor body of the outer end being fixed on described paddle arm, with the rotating disk be fixed on the output shaft of described motor body, described rotating disk is convexly equipped with two fixed legs, the center of line and the jante et perpendiculaire of described rotating disk between described two fixed legs, described blade comprises first paragraph blade and second segment blade, the coupling end of described first paragraph blade and second segment blade all offers the blade mounting hole with described fixed leg adaptation, described first paragraph blade and second segment blade are socketed on described two fixed legs respectively by the blade mounting hole on it rotationally, when described oar assembly is in folded state, first paragraph blade and second segment blade draw in and jointly enclose in the space of formation in each described paddle arm.
9. unmanned plane as claimed in claim 1, is characterized in that, the cross-sectional plane of described paddle arm is in " recessed " font.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410458158.3A CN105398566B (en) | 2014-09-10 | 2014-09-10 | Unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410458158.3A CN105398566B (en) | 2014-09-10 | 2014-09-10 | Unmanned plane |
Publications (2)
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106094857A (en) * | 2016-08-22 | 2016-11-09 | 京东方科技集团股份有限公司 | The flight control method of unmanned plane, wearable device and unmanned plane, device |
| CN106184794A (en) * | 2016-08-30 | 2016-12-07 | 成都汇丁科技有限公司 | A kind of unmanned plane for taking photo by plane |
| CN106240807A (en) * | 2016-07-28 | 2016-12-21 | 上海航天控制技术研究所 | A kind of unmanned plane collecting photoelectric detection integrative |
| CN106394885A (en) * | 2016-09-21 | 2017-02-15 | 深圳飞马机器人科技有限公司 | Portable folding method for quad-rotor unmanned aerial vehicle and quad-rotor unmanned aerial vehicle |
| CN107738746A (en) * | 2017-08-30 | 2018-02-27 | 中北大学 | Folding automatic running on transmisson line unmanned plane |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4712978A (en) * | 1986-12-01 | 1987-12-15 | Tiemann James P | Helicopter blade and the like stand-off and folding device |
| US6161994A (en) * | 1998-02-03 | 2000-12-19 | Lang; Gunter | Device for cleaning the working area of chip removal machines |
| CN102442423A (en) * | 2010-10-12 | 2012-05-09 | 徐延宇 | Adjustable-height foldable propeller |
| CN102905972A (en) * | 2010-06-15 | 2013-01-30 | 贝尔直升机泰克斯特龙公司 | Method and apparatus for in-flight blade folding |
| CN103332291A (en) * | 2013-06-14 | 2013-10-02 | 南京航空航天大学 | Folding and unfolding mechanism for air-drop hex-rotor wing unmanned aerial vehicle |
| CN103979107A (en) * | 2014-05-21 | 2014-08-13 | 北京理工大学 | Folding rotor-type unmanned aerial vehicle |
| CN204210727U (en) * | 2014-09-10 | 2015-03-18 | 深圳一电科技有限公司 | Unmanned plane |
-
2014
- 2014-09-10 CN CN201410458158.3A patent/CN105398566B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4712978A (en) * | 1986-12-01 | 1987-12-15 | Tiemann James P | Helicopter blade and the like stand-off and folding device |
| US6161994A (en) * | 1998-02-03 | 2000-12-19 | Lang; Gunter | Device for cleaning the working area of chip removal machines |
| CN102905972A (en) * | 2010-06-15 | 2013-01-30 | 贝尔直升机泰克斯特龙公司 | Method and apparatus for in-flight blade folding |
| CN102442423A (en) * | 2010-10-12 | 2012-05-09 | 徐延宇 | Adjustable-height foldable propeller |
| CN103332291A (en) * | 2013-06-14 | 2013-10-02 | 南京航空航天大学 | Folding and unfolding mechanism for air-drop hex-rotor wing unmanned aerial vehicle |
| CN103979107A (en) * | 2014-05-21 | 2014-08-13 | 北京理工大学 | Folding rotor-type unmanned aerial vehicle |
| CN204210727U (en) * | 2014-09-10 | 2015-03-18 | 深圳一电科技有限公司 | Unmanned plane |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106240807A (en) * | 2016-07-28 | 2016-12-21 | 上海航天控制技术研究所 | A kind of unmanned plane collecting photoelectric detection integrative |
| CN106094857A (en) * | 2016-08-22 | 2016-11-09 | 京东方科技集团股份有限公司 | The flight control method of unmanned plane, wearable device and unmanned plane, device |
| CN106184794A (en) * | 2016-08-30 | 2016-12-07 | 成都汇丁科技有限公司 | A kind of unmanned plane for taking photo by plane |
| CN106394885A (en) * | 2016-09-21 | 2017-02-15 | 深圳飞马机器人科技有限公司 | Portable folding method for quad-rotor unmanned aerial vehicle and quad-rotor unmanned aerial vehicle |
| CN106394885B (en) * | 2016-09-21 | 2018-07-10 | 深圳飞马机器人科技有限公司 | The portable folding method of quadrotor unmanned plane |
| CN107738746A (en) * | 2017-08-30 | 2018-02-27 | 中北大学 | Folding automatic running on transmisson line unmanned plane |
| CN107738746B (en) * | 2017-08-30 | 2019-10-01 | 中北大学 | Folding automatic running on transmisson line unmanned plane |
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