CN206243488U - Many power combinations change the unmanned plane for adapting to different landing mode different task load - Google Patents
Many power combinations change the unmanned plane for adapting to different landing mode different task load Download PDFInfo
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- CN206243488U CN206243488U CN201621346360.8U CN201621346360U CN206243488U CN 206243488 U CN206243488 U CN 206243488U CN 201621346360 U CN201621346360 U CN 201621346360U CN 206243488 U CN206243488 U CN 206243488U
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Abstract
The unmanned plane for adapting to different landing mode different task load is changed the utility model discloses a kind of many power combinations, including：Fuselage, port wing, starboard wing, empennage, active force module A, active force module B, secondary power module A, the pair power module B and moulding module C of tail.It is of the present utility model to be beneficial in that：(1) with various power combination patterns, various adaptation scenes can be realized on same unmanned plane body platform, the versatility and platform of unmanned plane greatly improved；(2) each module uses modular design, not only increases transition transaction capabilities, and greatly facilitates the transport of unmanned plane, maintenances, maintenance and debug, and uses extremely convenient and economy.
Description
Technical field
The utility model is related to a kind of SUAV, and in particular to a kind of many power combinations are changed and adapt to different landing sides
The unmanned plane of formula different task load, belongs to unmanned air vehicle technique field.
Background technology
The dynamical system of unmanned plane is used for providing thrust for the flight of unmanned plane, is particularly significant during unmanned aerial vehicle design is manufactured
A part.Because the differences such as landing place, cruising time, cruising radius, the mission payload of carrying, unmanned plane may need more
Change different dynamical systems.
However, the dynamical system of general SUAV be connected firmly with body together with, it is difficult to it is same nobody
Various adaptation scenes, the application of various power combination patterns are realized on machine body platform, causes the versatility of unmanned plane and platform
Property is relatively low.
If completing specific task using specific type, have that cost of possession is high, take up room big, transport difficult
The problems such as.
Utility model content
To solve the deficiencies in the prior art, the purpose of this utility model is to provide a kind of many power combinations to change adaptation not
With the unmanned plane of landing mode different task load.
In order to realize above-mentioned target, the utility model is adopted the following technical scheme that：
A kind of many power combinations change the unmanned plane for adapting to different landing mode different task load, including：Fuselage (10),
Port wing (20), starboard wing (30) and empennage (40), empennage (40) are threadedly coupled with fuselage (10), it is characterised in that also include：
Active force module A (50), active force module B (60), secondary power module A (70), secondary power module B (80) and the moulding module of tail
C (90), wherein：
Foregoing active force module A (50) adjusts (523) and a motor (501) with an electricity, wherein, aforementioned motor
(501) positioned at foremost, and output shaft points to the front of unmanned plane, output shaft of the propeller (526) installed in motor (501)
On,
Foregoing active force module B (60) adjusts (601) and two motors (602) with two electricity, wherein, both of the aforesaid motor
(602) it is located at foremost and rearmost end respectively, and output shaft points to the top of unmanned plane, and propeller (603) is installed in motor
(602) on output shaft,
Foregoing active force module A (50) or the symmetrical left and right sides for being arranged on fuselage (10) of active force module B (60), and
And be threadedly coupled with fuselage (10), port wing (20) and starboard wing (30) are separately positioned on active force module A (50) or active force
The outside of module B (60), and be threadedly coupled with active force module A (50) or active force module B (60), or, port wing
(20) and fuselage (10) between, active force module A (50) or active force mould are not provided between starboard wing (30) and fuselage (10)
Group B (60), port wing (20) and starboard wing (30) are directly threadedly coupled with fuselage (10)；
Aforementioned auxiliary power module A (70) adjusts (705) and a brushless electric machine (710) with an electricity, wherein, it is foregoing brushless
Motor (710) is positioned at middle part, and output shaft points to the top of unmanned plane, and propeller (713) is installed in brushless electric machine (710)
On output shaft,
Aforementioned auxiliary power module B (80) adjusts (802) and a brushless electric machine (806) with an electricity, wherein, it is foregoing brushless
Motor (806) is positioned at rearmost end, and output shaft points to the rear of unmanned plane, and propeller (804) is installed in brushless electric machine (806)
Output shaft on,
The foregoing moulding module C (90) of tail is adjusted with an electricity, without brushless electric machine,
Aforementioned auxiliary power module A (70), secondary power module B (80) or the moulding module C (90) of tail connect spiral shell by pretension
Nail is fixedly mounted on the end of fuselage (10).
Foregoing a kind of many power combinations change the unmanned plane for adapting to different landing mode different task load, and its feature exists
In foregoing active force module A (50) also has：Support component and wing coupling assembly, wherein：
Foregoing support component includes：Upper radome fairing (505), right floor (506), bearing (507), limited block (508), first
Wire casing (509), the second wire casing (510), steering wheel (511), steering wheel frame (512), rocking arm (513), connecting rod (514), left floor (515)
With lower radome fairing (516), foregoing limited block (508) is fixedly connected by screw with left floor (515) and right floor (506), preceding
State bearing (507) to be respectively pressed into the groove of left floor (515) and right floor (506), foregoing connecting rod (514) is installed in rocking arm
(513) on, on the output shaft of steering wheel (511), foregoing steering wheel (511) is screwed installation to foregoing rocking arm (513)
On steering wheel frame (512), foregoing first wire casing (509) is connected on the second wire casing (510), foregoing second wire casing (510) connection
On steering wheel frame (512), foregoing steering wheel frame (512) is screwed and is connected with left floor (515) and right floor (506), preceding
State radome fairing (505) and lower radome fairing (516) is screwed and is connected on left floor (515) and right floor (506)；
Foregoing wing coupling assembly includes：Upper radome fairing (517), wing connect frame (518), rear radome fairing (519) and under
Radome fairing (520), upper radome fairing (517), lower radome fairing (520) and rear radome fairing (519) are screwed are arranged on respectively
Wing is connected above frame (518), following and rear end；
By motor cabinet (502) installed in the front end of support component, wing coupling assembly passes through screw to aforementioned motor (501)
The rear end of support component is fixedly mounted on, electricity adjusts (523) to be screwed left floor (515) and the right side installed in support component
On floor (506).
Foregoing a kind of many power combinations change the unmanned plane for adapting to different landing mode different task load, and its feature exists
In foregoing active force module B (60) also has：Front support component, rear support component and wing coupling assembly, wherein：
Foregoing front support component includes：Left floor (605), right floor (604), upper radome fairing (606) and lower radome fairing
(607), foregoing left floor (605) and the first from left right side of right floor (604) are symmetrical arranged, and electricity adjusts (601) to adjust seat (11) to pacify by electricity
Between left floor (605) and right floor (604), electricity is adjusted and electricity tune installing plate (612), upper radome fairing is stamped on seat (11)
(606) above left floor (605) and right floor (604), lower radome fairing (607) is installed in left floor (605) and the right side
Below floor (604), motor (602) by motor fixing seat (610) installed in left floor (605) and right floor (604) it
Between；
The structure of foregoing rear support component is identical with the structure of front support component；
Foregoing wing coupling assembly includes：Wing connects frame (608) and middle radome fairing (609), middle radome fairing (609)
Connect above frame (608) and following installed in wing；
Foregoing front support component and rear support component be screwed respectively installed in the front end of wing coupling assembly and
Rear end.
Foregoing a kind of many power combinations change the unmanned plane for adapting to different landing mode different task load, and its feature exists
In aforementioned auxiliary power module A (70) also has：Preceding main frame (701), rear main frame 712, right support frame (715), left support frame
(716), electricity adjusts mounting seat (717), steering wheel (702), steering wheel (714), motor to install rotating shaft (707), connecting rod (709), motor peace
Dress seat (708), the right covering of tail (704) and the left covering of tail (718), preceding main frame (701), rear main frame 712, right support frame
(715), left support frame (716) and electricity adjust mounting seat (717) by screw connection together, and be assembled into a framework, electricity is adjusted
(705) adjusted in mounting seat (717) installed in electricity, the input line of brushless electric machine (710) is welded on electricity and adjusts in the output end of (705),
Steering wheel (702) and steering wheel (714) supporting setting, and respectively set a set of on preceding main frame (701) and rear main frame 712, brushless electricity
Machine (710), motor install rotating shaft (707) and connecting rod (709) is screwed on motor mount (708) respectively,
Motor mount (708) is screwed on preceding main frame (701) and rear main frame 712, connecting rod (709) and steering wheel
(714) connect, the right covering of tail (704) and tail left covering (718) the right setting of the first from left, and spiral shell connected by pretension respectively
Nail (703) is connected on preceding main frame (701) and rear main frame 712.
Foregoing a kind of many power combinations change the unmanned plane for adapting to different landing mode different task load, and its feature exists
In aforementioned auxiliary power module B (80) also has：Preceding main frame (810), rear main frame (805), right support frame (803), left support frame
(807), electricity adjusts mounting seat (808), the right covering of tail (801) and the left covering of tail (809), preceding main frame (810), rear main frame
(805), right support frame (803), left support frame (807) and electricity adjust mounting seat (808) by screw connection together, and be assembled into
One framework, electricity adjusts (802) to be adjusted in mounting seat (808) installed in electricity, and brushless electric machine (806) is screwed after being arranged on main
On frame (805), and input line is welded on electricity and adjusts in the output end of (802), the right covering of tail (801) and the left covering of tail
(809) the one right settings of the first from left, and be connected on preceding main frame (810) and rear main frame (805) by pretension attachment screw respectively.
Foregoing a kind of many power combinations change the unmanned plane for adapting to different landing mode different task load, and its feature exists
In the foregoing moulding module C (90) of tail also has：Preceding main frame (903), rear main frame (905), right support frame (904), left support frame
(906), electricity adjusts mounting seat (907), the right covering of tail (902) and the left covering of tail (908), preceding main frame (903), rear main frame
(905), right support frame (904), left support frame (906) and electricity adjust mounting seat (907) by screw connection together, and be assembled into
One framework, electricity is adjusted and is arranged on electricity tune mounting seat (907), and the right covering of tail (902) and the left the first from left of covering (908) of tail are right
Set, and be connected on preceding main frame (903) and rear main frame (905) by pretension attachment screw (901) respectively.
It is of the present utility model to be beneficial in that：
(1) unmanned plane of the present utility model, with various power combination patterns, can be in same unmanned plane body platform
On realize various adaptation scenes, the versatility and platform of unmanned plane greatly improved；
(2) unmanned plane of the present utility model, each module uses modular design, not only increases transition workability
Energy, and transport, maintenance, maintenance and the debugging of unmanned plane are greatly facilitated, it is extremely convenient and economical to use.
Brief description of the drawings
Fig. 1 (a) is the explosive view of active force module A；
Fig. 1 (b) is that active force module A will assemble the structural representation for finishing；
Fig. 1 (c) is the structural representation that the assembling of active force module A is finished；
Fig. 2 (a) is the explosive view of active force module B；
Fig. 2 (b) is the structural representation that active force module B assemblings are finished；
Fig. 3 (a) is the explosive view of secondary power module A；
Fig. 3 (b) is that secondary power module A will assemble the structural representation for finishing；
Fig. 3 (c) is the structural representation that secondary power module A assembling is finished；
Fig. 4 (a) is the explosive view of secondary power module B；
Fig. 4 (b) is the structural representation that secondary power module B assemblings are finished；
Fig. 5 (a) is the explosive view of the moulding module C of tail；
Fig. 5 (b) is the structural representation that the moulding module C assemblings of tail are finished；
Fig. 6 is the structural representation of single-power tail pushing-type rolling start unmanned plane；
Fig. 7 is the structural representation of many Power compound formula VUAVs；
Fig. 8 is the structural representation of double dynamical preceding pull-type rolling start unmanned plane；
Fig. 9 is the structural representation of VTOL tilting rotor wing unmanned aerial vehicle.
The implication of reference in figure：
10- fuselages, 20- port wings, 30- starboard wings, 40- empennages；
50- active force module As,
501- motors, 502- motor cabinets, 503- jump rings, 504- rotating shafts, the upper radome fairings of 505-, the right floors of 506-, 507- axles
Hold, 508- limited blocks, the wire casings of 509- first, the wire casings of 510- second, 511- steering wheels, 512- steering wheel framves, 513- rocking arms, 514- connects
Bar, the left floors of 515-, radome fairing under 516-, the upper radome fairings of 517-, 518- wings connection frame, radome fairing after 519- is whole under 520-
Stream cover, 521- electricity adjusts installing plate, 522- upper stratas heat conductive silica gel, 523- electricity to adjust, and 524- lower floors heat conductive silica gel, 525- electricity adjusts lid,
526- propellers；
60- active force module B,
601- electricity is adjusted, 602- motors, 603- propellers, the right floors of 604-, the left floors of 605-, the upper radome fairings of 606-, 607-
Lower radome fairing, 608- wings connection frame, radome fairing in the middle of 609-, 610- motor fixing seats, 611- electricity adjusts seat, 612- electricity to adjust and install
Plate, the upper heat conductive silica gels of 613-, heat conductive silica gel under 614-；
70- pair power module As,
Main frame before 701-, 702- steering wheels, 703- pretension attachment screws, the right covering of 704- tails, 705- electricity is adjusted, 706- axles
Hold, 707- motors install rotating shaft, 708- motor mounts, 709- connecting rods, 710- brushless electric machines, 711- connection inserts, after 712-
Main frame, 713- propellers, 714- steering wheels, 715- right support frames, 716- left support frames, 717- electricity adjusts mounting seat, and 718- tails are left
Covering；
80- pair power module B,
Main frame before 801-, 802- electricity is adjusted, 803- right support frames, 804- propellers, main frame after 805-, 806- brushless electric machines,
807- left support frames, 808- electricity adjusts mounting seat, the left covering of 809- tails, main frame before 810-；
The moulding module C of 90- tails,
901- pretension attachment screws, the right covering of 902- tails, main frame before 903-, 904- right support frames, main frame after 905-,
906- left support frames, 907- electricity adjusts mounting seat, the left covering of 908- tails.
Specific embodiment
Make specific introduction to the utility model below in conjunction with the drawings and specific embodiments.
Reference picture 6, Fig. 7, Fig. 8 and Fig. 9, many power combinations of the present utility model are changed and adapt to different of different landing modes
The unmanned plane of load of being engaged in, including：Fuselage 10, port wing 20, starboard wing 30 and empennage 40, wherein, empennage 40 and the screw thread of fuselage 10
Connection.Additionally, also including：Active force module A 50, active force module B60, secondary power module A 70, pair power module B80 and machine
The moulding module C90 of tail, selection uses different active force module As 50, active force module B60, secondary power module A 70, secondary power
The module B80 and moulding module C90 of tail, can form various power combination patterns, so that unmanned plane of the present utility model
It is adapted to several scenes.
Active force module A 50, active force module B60 are installed between port wing 20 and fuselage 10 and starboard wing 30 and machine
Between body 10.Certainly, the need for according to actual conditions, between port wing 20 and fuselage 10, can between starboard wing 30 and fuselage 10
To be not provided with active force module A 50 or active force module B60, but make port wing 20 and starboard wing 30 directly with the screw thread of fuselage 10
Connection, as shown in Figure 6.
Be described in detail below active force module A 50, active force module B60, secondary power module A 70, pair power module B80 and
The structure of the moulding module C90 of tail.
First, active force module A
There is reference picture 1 (a), Fig. 1 (b) and Fig. 1 (c), active force module A 50 electricity to adjust 523 and a motor 501,
Motor 501 is located at foremost, and output shaft points to the front of unmanned plane, and propeller 526 is arranged on the output shaft of motor 501
On.Additionally, active force module A 50 also has：Support component and wing coupling assembly.
1st, support component
Reference picture 1 (a), Fig. 1 (b) and Fig. 1 (c), support component include：Upper radome fairing 505, right floor 506, bearing 507,
Limited block 508, the first wire casing 509, the second wire casing 510, steering wheel 511, steering wheel frame 512, Rocker arm 5 13, connecting rod 514, left floor 515
With lower radome fairing 516.
Limited block 508 is fixedly connected by screw with left floor 515 and right floor 506；
Bearing 507 is respectively pressed into the groove of left floor 515 and right floor 506；
Connecting rod 514 is arranged on Rocker arm 5 13, and Rocker arm 5 13 is arranged on the output shaft of steering wheel 511, and steering wheel 511 passes through screw
It is fixedly mounted on steering wheel frame 512；
First wire casing 509 is connected on the second wire casing 510, and the second wire casing 510 is connected on steering wheel frame 512, steering wheel frame 512
It is screwed and is connected with left floor 515 and right floor 506；
Upper radome fairing 505 and lower radome fairing 516 are screwed and are connected on left floor 515 and right floor 506.
2nd, wing coupling assembly
Reference picture 1 (a), Fig. 1 (b) and Fig. 1 (c), wing coupling assembly include：Upper radome fairing 517, wing connection frame 518,
Radome fairing 519 and lower radome fairing 520 afterwards.
Upper radome fairing 517, lower radome fairing 520 and rear radome fairing 519 are screwed connect frame installed in wing respectively
Above 518, below and rear end.
Motor 501 is screwed and is installed in motor cabinet 502, and the He of jump ring 503 is provided with the outer wall of motor cabinet 502
Rotating shaft 504, wherein, jump ring 503 can be stuck in rotating shaft 504, and rotating shaft 504 is inserted into the bearing 507 of the front end of support component
In；Wing coupling assembly is screwed installed in the rear end of support component；Electricity adjusts 523 to be placed on electricity tune lid 525 and electricity is adjusted
The electricity that installing plate 521 is collectively formed is adjusted in installing space, and electricity adjusts 523 both sides to be up and down respectively arranged with upper strata heat conductive silica gel 522
With lower floor heat conductive silica gel 524, electricity adjusts lid 525 to be screwed left floor 515 and right floor 506 installed in support component
On.
The mounting means of active force module A 50：
Reference picture 8 and Fig. 9, the symmetrical left and right sides for being arranged on fuselage 10 of active force module A 50, and with the spiral shell of fuselage 10
Line is connected, and port wing 20 and starboard wing 30 are separately positioned on the outside of active force module A 50, and with the spiral shell of active force module A 50
Line is connected.
2nd, active force module B
There are reference picture 2 (a) and Fig. 2 (b), active force module B60 two electricity to adjust 601 and two motors 602, wherein, should
Two motors 602 are located at foremost and rearmost end respectively, and output shaft points to the top of unmanned plane, and propeller 603 is arranged on
On the output shaft of motor 602.Additionally, active force module B60 also has：Front support component, rear support component and wing connection group
Part.
1st, front support component
Reference picture 2 (a) and Fig. 2 (b), front support component include：Left floor 605, right floor 604, upper radome fairing 606 and under
Radome fairing 607.
Left floor 605 and the first from left right side of right floor 604 1 are symmetrical arranged, and electricity tune 601 is by electricity tune seat 611 and solid by screw
Dingan County is mounted between left floor 605 and right floor 604, and electricity to be adjusted and be placed with heat conductive silica gel 613 above 601, is placed below
Lower heat conductive silica gel 614, electricity is adjusted and electricity tune installing plate 612 is stamped on seat 611, and upper radome fairing 606 is screwed installed in left rib
Above plate 605 and right floor 604, lower radome fairing 607 is screwed under left floor 605 and right floor 604
Face.
Motor 602 is fixedly mounted on left floor 605 and right floor 604 by motor fixing seat 610 and by fixing bolt
Between.
2nd, rear support component
Reference picture 2 (a) and Fig. 2 (b), the structure of rear support component are identical with the structure of front support component, no longer go to live in the household of one's in-laws on getting married
State.
3rd, wing coupling assembly
Reference picture 2 (a) and Fig. 2 (b), wing coupling assembly include：Wing connects frame 608 and middle radome fairing 609.
Middle radome fairing 609 is screwed above wing connection frame 608 and following.
Reference picture 2 (a) and Fig. 2 (b), front support component and rear support component are screwed connect installed in wing respectively
The front-end and back-end of connected components.
The mounting means of active force module B60：
Reference picture 7, the active force module B60 symmetrical left and right sides for being arranged on fuselage 10, and connect with the screw thread of fuselage 10
Connect, port wing 20 and starboard wing 30 are separately positioned on the outside of active force module B60, and connect with active force module B60 screw threads
Connect.
3rd, secondary power module A
There is reference picture 3 (a), Fig. 3 (b) and Fig. 3 (c), secondary power module A 70 electricity to adjust 705 and a brushless electric machine
710, wherein, brushless electric machine 710 is located at middle part, and output shaft points to the top of unmanned plane, and propeller 713 is arranged on brushless electricity
On the output shaft of machine 710.Additionally, secondary power module A 70 also has：Preceding main frame 701, rear main frame 712, right support frame 715, left branch
Support frame 716, electricity adjust mounting seat 717, steering wheel 702, steering wheel 714, motor install rotating shaft 707, connecting rod 709, motor mount 708,
The right covering 704 of tail and the left covering 718 of tail.
Preceding main frame 701, rear main frame 712, right support frame 715, left support frame 716 and electricity adjust mounting seat 717 to connect by screw
It is connected together, and is assembled into a framework；
Electricity is adjusted 705 to be arranged on electricity and is adjusted in mounting seat 717, and the input line of brushless electric machine 710 is welded on the output end that electricity adjusts 705
On；
Steering wheel 702 and the supporting setting of steering wheel 714, and respectively set a set of on preceding main frame 701 and rear main frame 712；
Brushless electric machine 710, motor installs rotating shaft 707 and connecting rod 709 is screwed installed in motor mount respectively
On 708, motor mount 708 is screwed on preceding main frame 701 and rear main frame 712, connecting rod 709 and steering wheel 714
Connection, motor to be installed and be pressed with bearing 706 in advance in rotating shaft 707；
The right covering 704 of tail and the left right setting of the first from left of covering 718 1 of tail, and pass through pretension attachment screw 703 respectively
It is connected on preceding main frame 701 and rear main frame 712.
The right covering 704 of tail and the left covering 718 of tail are respectively formed on limited location groove, the shape of stopper slot be connected insert
711 are adapted, and the right covering 704 of tail and the left covering 718 of tail are fastened by connecting insert 711.
The mounting means of secondary power module A 70：
Reference picture 9, secondary power module A 70 is fixedly mounted on the end of fuselage 10 by pretension attachment screw.
4th, secondary power module B
There is reference picture 4 (a) and Fig. 4 (b), secondary power module B80 an electricity to adjust 802 and a brushless electric machine 806, its
In, brushless electric machine 806 is located at rearmost end, and output shaft points to the rear of unmanned plane, and propeller 804 is arranged on brushless electric machine
On 806 output shaft.Additionally, pair power module B80 also has：Preceding main frame 810, rear main frame 805, right support frame 803, left support
Frame 807, electricity adjust the right covering 801 of mounting seat 808, tail and the left covering 809 of tail.
Preceding main frame 810, rear main frame 805, right support frame 803, left support frame 807 and electricity adjust mounting seat 808 to connect by screw
It is connected together, and is assembled into a framework；
Electricity is adjusted 802 to be arranged on electricity and is adjusted in mounting seat 808, and brushless electric machine 806 is screwed main frame 805 after being arranged on
On, and input line be welded on electricity adjust 802 output end on；
The right covering 801 of tail and the left right setting of the first from left of covering 809 1 of tail, and connected by pretension attachment screw respectively
On preceding main frame 810 and rear main frame 805.
The mounting means of secondary power module B80：
Reference picture 6 and Fig. 7, secondary power module B80 are fixedly mounted on the end of fuselage 10 by pretension attachment screw.
5th, the moulding module C of tail
Reference picture 5 (a) and Fig. 5 (b), the moulding module C90 of tail have：Preceding main frame 903, rear main frame 905, right support frame
904th, left support frame 906, electricity adjust mounting seat 907, electricity to adjust (not shown), the right covering 902 of tail and the left covering 908 of tail, do not have
There is brushless electric machine.
Preceding main frame 903, rear main frame 905, right support frame 904, left support frame 906 and electricity adjust mounting seat 907 to connect by screw
It is connected together, and is assembled into a framework；
Electricity is adjusted and is arranged in electricity tune mounting seat 907；
The right covering 902 of tail and the left right setting of the first from left of covering 908 1 of tail, and pass through pretension attachment screw 901 respectively
It is connected on preceding main frame 903 and rear main frame 905.
The mounting means of the moulding module C90 of tail：
Reference picture 8, the moulding module C90 of tail is fixedly mounted on the end of fuselage 10 by pretension attachment screw.
Selection uses different active force module As 50, active force module B60, secondary power module A 70, secondary power module B80
Module C90 moulding with tail, can form various power combination patterns, for example：
(1), single-power tail pushing-type rolling start unmanned plane pattern：Only pass through pretension attachment screw in the end of fuselage 10
The secondary power module B80 of fixed installation, active force is not provided between port wing 20 and fuselage 10, between starboard wing 30 and fuselage 10
Module, as shown in Figure 6；
(2), many Power compound formula VUAV patterns：It is solid by pretension attachment screw in the end of fuselage 10
The secondary power module B80 of Dingan County's dress, between port wing 20 and fuselage 10, is respectively mounted active force module between starboard wing 30 and fuselage 10
B60, as shown in Figure 7；
(3), double dynamical preceding pull-type rolling start unmanned plane pattern：It is solid by pretension attachment screw in the end of fuselage 10
Install the moulding module C90 of tail for Dingan County, between port wing 20 and fuselage 10, active force mould is respectively mounted between starboard wing 30 and fuselage 10
Group A50, as shown in Figure 8；
(4), VTOL tilting rotor wing unmanned aerial vehicle pattern：Peace is fixed by pretension attachment screw in the end of fuselage 10
The secondary power module A 70 of dress, between port wing 20 and fuselage 10, is respectively mounted active force module A 50 between starboard wing 30 and fuselage 10,
As shown in Figure 8.
As can be seen here, by selecting to use different active force module As, active force module B, secondary power module A, secondary power
The module B and moulding module C of tail, unmanned plane of the present utility model can form various power combination patterns, so that it can
To adapt to several scenes, versatility and platform are greatly improved.
It should be noted that above-described embodiment does not limit the utility model in any form, all use equivalents or wait
The technical scheme that the mode of conversion is obtained is imitated, is all fallen within protection domain of the present utility model.
Claims (6)
1. a kind of many power combinations change the unmanned plane for adapting to different landing mode different task load, including：Fuselage (10), a left side
Wing (20), starboard wing (30) and empennage (40), empennage (40) are threadedly coupled with fuselage (10), it is characterised in that also include：It is main
Power module A (50), active force module B (60), secondary power module A (70), secondary power module B (80) and the moulding module C of tail
(90), wherein：
The active force module A (50) adjusts (523) and a motor (501) with an electricity, wherein, motor (501) position
In foremost, and output shaft points to the front of unmanned plane, propeller (526) on the output shaft of motor (501),
The active force module B (60) adjusts (601) and two motors (602) with two electricity, wherein, described two motors
(602) it is located at foremost and rearmost end respectively, and output shaft points to the top of unmanned plane, and propeller (603) is installed in motor
(602) on output shaft,
The active force module A (50) or the symmetrical left and right sides for being arranged on fuselage (10) of active force module B (60), and with
Fuselage (10) is threadedly coupled, and port wing (20) and starboard wing (30) are separately positioned on active force module A (50) or active force module B
(60) outside, and being threadedly coupled with active force module A (50) or active force module B (60), or, port wing (20) and machine
Active force module A (50) or active force module B (60) are not provided between body (10), between starboard wing (30) and fuselage (10),
Port wing (20) and starboard wing (30) are directly threadedly coupled with fuselage (10)；
The secondary power module A (70) adjusts (705) and a brushless electric machine (710) with an electricity, wherein, the brushless electric machine
(710) positioned at middle part, and output shaft points to the top of unmanned plane, output of the propeller (713) installed in brushless electric machine (710)
On axle,
The secondary power module B (80) adjusts (802) and a brushless electric machine (806) with an electricity, wherein, the brushless electric machine
(806) positioned at rearmost end, and output shaft points to the rear of unmanned plane, and propeller (804) is defeated installed in brushless electric machine (806)
On shaft,
The moulding module C (90) of tail is adjusted with an electricity, without brushless electric machine,
The secondary power module A (70), secondary power module B (80) or the moulding module C (90) of tail are solid by pretension attachment screw
Dingan County is mounted in the end of fuselage (10).
2. a kind of many power combinations according to claim 1 change nobody of the different landing mode different task load of adaptation
Machine, it is characterised in that the active force module A (50) also has：Support component and wing coupling assembly, wherein：
The support component includes：Upper radome fairing (505), right floor (506), bearing (507), limited block (508), the first wire casing
(509), the second wire casing (510), steering wheel (511), steering wheel frame (512), rocking arm (513), connecting rod (514), left floor (515) and under
Radome fairing (516), the limited block (508) is fixedly connected by screw with left floor (515) and right floor (506), the axle
(507) are held to be respectively pressed into the groove of left floor (515) and right floor (506), the connecting rod (514) on rocking arm (513),
On the output shaft of steering wheel (511), the steering wheel (511) is screwed installed in steering wheel frame the rocking arm (513)
(512) on, first wire casing (509) is connected on the second wire casing (510), and second wire casing (510) is connected to steering wheel frame
(512) on, the steering wheel frame (512) is screwed and is connected with left floor (515) and right floor (506), the upper rectification
Cover (505) and lower radome fairing (516) are screwed and are connected on left floor (515) and right floor (506)；
The wing coupling assembly includes：Upper radome fairing (517), wing connect frame (518), rear radome fairing (519) and lower rectification
Cover (520), upper radome fairing (517), lower radome fairing (520) and rear radome fairing (519) are screwed installed in wing respectively
Above connection frame (518), below and rear end；
By motor cabinet (502) installed in the front end of support component, wing coupling assembly is screwed the motor (501)
Installed in the rear end of support component, electricity adjusts (523) to be screwed installed in the left floor (515) of support component and right floor
(506) on.
3. a kind of many power combinations according to claim 1 change nobody of the different landing mode different task load of adaptation
Machine, it is characterised in that the active force module B (60) also has：Front support component, rear support component and wing coupling assembly,
Wherein：
The front support component includes：Left floor (605), right floor (604), upper radome fairing (606) and lower radome fairing (607),
The left floor (605) and the first from left right side of right floor (604) are symmetrical arranged, and electricity adjusts (601) to adjust seat (11) installed in a left side by electricity
Between floor (605) and right floor (604), electricity is adjusted and electricity tune installing plate (612) is stamped on seat (11), and upper radome fairing (606) is installed
Above left floor (605) and right floor (604), lower radome fairing (607) is installed in left floor (605) and right floor (604)
Below, motor (602) is by motor fixing seat (610) between left floor (605) and right floor (604)；
The structure of the rear support component is identical with the structure of front support component；
The wing coupling assembly includes：Wing connects frame (608) and middle radome fairing (609), and middle radome fairing (609) is installed
Connect above frame (608) and following in wing；
The front support component and rear support component are screwed installed in the front-end and back-end of wing coupling assembly respectively.
4. a kind of many power combinations according to claim 1 change nobody of the different landing mode different task load of adaptation
Machine, it is characterised in that the secondary power module A (70) also has：Preceding main frame (701), rear main frame (712), right support frame
(715), left support frame (716), electricity adjust mounting seat (717), steering wheel (702), steering wheel (714), motor to install rotating shaft (707), connect
Bar (709), motor mount (708), the right covering of tail (704) and the left covering of tail (718), preceding main frame (701), rear main frame
(712), right support frame (715), left support frame (716) and electricity adjust mounting seat (717) by screw connection together, and be assembled into
One framework, electricity adjusts (705) to be adjusted in mounting seat (717) installed in electricity, and the input line of brushless electric machine (710) is welded on electric tune
(705) in output end, steering wheel (702) and steering wheel (714) supporting setting, and on preceding main frame (701) and rear main frame (712)
Respectively set a set of, brushless electric machine (710), motor install rotating shaft (707) and connecting rod (709) is screwed installed in electricity respectively
In machine mounting seat (708), motor mount (708) is screwed on preceding main frame (701) and rear main frame (712),
Connecting rod (709) is connected with steering wheel (714), the right covering of tail (704) and tail left covering (718) the right setting of the first from left, and point
Not Tong Guo pretension attachment screw (703) be connected on preceding main frame (701) and rear main frame (712).
5. a kind of many power combinations according to claim 1 change nobody of the different landing mode different task load of adaptation
Machine, it is characterised in that the secondary power module B (80) also has：Preceding main frame (810), rear main frame (805), right support frame
(803), left support frame (807), electricity adjust mounting seat (808), the right covering of tail (801) and the left covering of tail (809), preceding main frame
(810), rear main frame (805), right support frame (803), left support frame (807) and electricity adjust mounting seat (808) to exist by screw connection
Together, and it is assembled into a framework, electricity adjusts (802) to be adjusted in mounting seat (808) installed in electricity, and brushless electric machine (806) is by screw
After being fixedly mounted on main frame (805), and input line be welded on electricity adjust (802) output end on, the right covering of tail (801) and
Tail left covering (809) the right setting of the first from left, and preceding main frame (810) and rear main frame be connected to by pretension attachment screw respectively
(805) on.
6. a kind of many power combinations according to claim 1 change nobody of the different landing mode different task load of adaptation
Machine, it is characterised in that the moulding module C (90) of tail also has：Preceding main frame (903), rear main frame (905), right support frame
(904), left support frame (906), electricity adjust mounting seat (907), the right covering of tail (902) and the left covering of tail (908), preceding main frame
(903), rear main frame (905), right support frame (904), left support frame (906) and electricity adjust mounting seat (907) to exist by screw connection
Together, and it is assembled into a framework, electricity is adjusted and is arranged on electricity and adjusts in mounting seat (907), the right covering of tail (902) and the left covering of tail
(908) the one right settings of the first from left, and preceding main frame (903) and rear main frame (905) be connected to by pretension attachment screw (901) respectively
On.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621346360.8U CN206243488U (en) | 2016-12-09 | 2016-12-09 | Many power combinations change the unmanned plane for adapting to different landing mode different task load |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621346360.8U CN206243488U (en) | 2016-12-09 | 2016-12-09 | Many power combinations change the unmanned plane for adapting to different landing mode different task load |
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| Publication Number | Publication Date |
|---|---|
| CN206243488U true CN206243488U (en) | 2017-06-13 |
Family
ID=59005938
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106628201A (en) * | 2016-12-09 | 2017-05-10 | 北京奇正数元科技股份有限公司 | Unmanned plane capable of adapting different taking-off and landing modes and different mission loads by replacing multiple power combinations |
| CN108313264A (en) * | 2018-01-26 | 2018-07-24 | 易瓦特科技股份公司 | Adjustable rotor engine body system for fixed-wing unmanned plane |
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| CN108313263A (en) * | 2018-01-26 | 2018-07-24 | 易瓦特科技股份公司 | Fuselage dynamical system for fixed-wing unmanned plane |
| CN108408021A (en) * | 2018-01-26 | 2018-08-17 | 易瓦特科技股份公司 | Airframe structure for fixed-wing unmanned plane |
| CN108408020A (en) * | 2018-01-26 | 2018-08-17 | 易瓦特科技股份公司 | Adjustable rotor engine body device for fixed-wing unmanned plane |
| CN108482664A (en) * | 2018-01-26 | 2018-09-04 | 易瓦特科技股份公司 | Adjustable rotor engine body structure for fixed-wing unmanned plane |
| CN108482662A (en) * | 2018-01-26 | 2018-09-04 | 易瓦特科技股份公司 | Fuselage power plant for fixed-wing unmanned plane |
| CN108528714A (en) * | 2018-01-26 | 2018-09-14 | 易瓦特科技股份公司 | Adjustable rotor engine head device for fixed-wing unmanned plane |
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| CN106628201A (en) * | 2016-12-09 | 2017-05-10 | 北京奇正数元科技股份有限公司 | Unmanned plane capable of adapting different taking-off and landing modes and different mission loads by replacing multiple power combinations |
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| CN108313264A (en) * | 2018-01-26 | 2018-07-24 | 易瓦特科技股份公司 | Adjustable rotor engine body system for fixed-wing unmanned plane |
| CN108313265A (en) * | 2018-01-26 | 2018-07-24 | 易瓦特科技股份公司 | Fuselage construction for fixed-wing unmanned plane |
| CN108313263A (en) * | 2018-01-26 | 2018-07-24 | 易瓦特科技股份公司 | Fuselage dynamical system for fixed-wing unmanned plane |
| CN108408021A (en) * | 2018-01-26 | 2018-08-17 | 易瓦特科技股份公司 | Airframe structure for fixed-wing unmanned plane |
| CN108408020A (en) * | 2018-01-26 | 2018-08-17 | 易瓦特科技股份公司 | Adjustable rotor engine body device for fixed-wing unmanned plane |
| CN108482664A (en) * | 2018-01-26 | 2018-09-04 | 易瓦特科技股份公司 | Adjustable rotor engine body structure for fixed-wing unmanned plane |
| CN108482662A (en) * | 2018-01-26 | 2018-09-04 | 易瓦特科技股份公司 | Fuselage power plant for fixed-wing unmanned plane |
| CN108528714A (en) * | 2018-01-26 | 2018-09-14 | 易瓦特科技股份公司 | Adjustable rotor engine head device for fixed-wing unmanned plane |
| CN108528704A (en) * | 2018-01-26 | 2018-09-14 | 易瓦特科技股份公司 | Fixed-wing unmanned plane |
| CN108528705A (en) * | 2018-01-26 | 2018-09-14 | 易瓦特科技股份公司 | Power tail apparatus for fixed-wing unmanned plane |
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