CN106628201A - Unmanned plane capable of adapting different taking-off and landing modes and different mission loads by replacing multiple power combinations - Google Patents
Unmanned plane capable of adapting different taking-off and landing modes and different mission loads by replacing multiple power combinations Download PDFInfo
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- CN106628201A CN106628201A CN201611126983.9A CN201611126983A CN106628201A CN 106628201 A CN106628201 A CN 106628201A CN 201611126983 A CN201611126983 A CN 201611126983A CN 106628201 A CN106628201 A CN 106628201A
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- 230000005611 electricity Effects 0.000 claims description 91
- 210000000744 eyelid Anatomy 0.000 claims description 45
- 238000000465 moulding Methods 0.000 claims description 21
- 230000008878 coupling Effects 0.000 claims description 18
- 238000010168 coupling process Methods 0.000 claims description 18
- 238000005859 coupling reaction Methods 0.000 claims description 18
- 230000006978 adaptation Effects 0.000 claims description 8
- 239000007787 solid Substances 0.000 claims description 4
- 238000012423 maintenance Methods 0.000 abstract description 3
- 230000009286 beneficial effect Effects 0.000 abstract 1
- 238000004321 preservation Methods 0.000 abstract 1
- 238000007493 shaping process Methods 0.000 abstract 1
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 9
- 239000000741 silica gel Substances 0.000 description 7
- 229910002027 silica gel Inorganic materials 0.000 description 7
- 239000002360 explosive Substances 0.000 description 5
- 238000005096 rolling process Methods 0.000 description 4
- 238000005183 dynamical system Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 208000031481 Pathologic Constriction Diseases 0.000 description 2
- 150000001875 compounds Chemical class 0.000 description 2
- 210000001215 vagina Anatomy 0.000 description 2
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000499 gel Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000000377 silicon dioxide Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Forklifts And Lifting Vehicles (AREA)
- Toys (AREA)
Abstract
The invention discloses an unmanned plane capable of adapting different taking-off and landing modes and different mission loads by replacing multiple power combinations. The unmanned plane comprises a fuselage, a left wing, a right wing, an empennage, a main power module A, a main power module B, an auxiliary power module A, an auxiliary power module B and an empennage shaping module C. The unmanned plane has the beneficial effects that (1) the unmanned plane has various power combination modes, the unmanned plane can adapt to various occasions on the same unmanned fuselage platform, and the universality and platform performance of the unmanned plane are greatly improved; and (2) all the modules are designed in a modular mode, the transferring operation performance is improved, transportation, preservation, maintenance and debugging of the unmanned plane are greatly facilitated, and the unmanned plane is quite convenient to use and economical.
Description
Technical field
The present invention relates to a kind of SUAV, and in particular to a kind of many power combinations are changed and adapt to different landing modes not
With the unmanned plane of mission payload, belong 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 in unmanned aerial vehicle design manufacture
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 connect 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 and platform of unmanned plane
Property is relatively low.
If completing specific task using specific type, there is that cost of possession is high, take up room big, transport difficult
The problems such as.
The content of the invention
To solve the deficiencies in the prior art, it is an object of the invention to provide a kind of many power combinations are changed adapts to different rising
The unmanned plane of drop mode different task load.
In order to realize above-mentioned target, the present invention 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) is 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：
Aforementioned 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,
Aforementioned 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,
The symmetrical left and right sides for being arranged on fuselage (10) of aforementioned active force module A (50) or 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 aforementioned 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 aforementioned 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 moulding module C (90) of aforementioned tail is adjusted with an electricity, not with 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).
A kind of aforesaid many power combinations change the unmanned plane for adapting to different landing mode different task load, and its feature exists
In aforementioned active force module A (50) also has：Support component and wing coupling assembly, wherein：
Aforementioned support component includes：Upper trouserss (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 trouserss (516), aforementioned limited block (508) is fixedly connected by screw with left floor (515) and right floor (506), front
State bearing (507) to be respectively pressed in the groove of left floor (515) and right floor (506), aforementioned connecting rod (514) is installed in rocking arm
(513) on, on the output shaft of steering wheel (511), aforementioned steering wheel (511) is screwed installation to aforementioned rocking arm (513)
On steering wheel frame (512), aforementioned first wire casing (509) is connected on the second wire casing (510), aforementioned second wire casing (510) connection
On steering wheel frame (512), aforementioned steering wheel frame (512) is screwed and is connected with left floor (515) and right floor (506), front
State trouserss (505) and lower trouserss (516) are screwed and are connected on left floor (515) and right floor (506)；
Aforementioned wing coupling assembly includes：Upper trouserss (517), wing connection frame (518), rear trouserss (519) and under
Trouserss (520), upper trouserss (517), lower trouserss (520) and rear trouserss (519) are screwed are arranged on respectively
Wing connects 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).
A kind of aforesaid many power combinations change the unmanned plane for adapting to different landing mode different task load, and its feature exists
In aforementioned active force module B (60) also has：Front support component, rear support component and wing coupling assembly, wherein：
Aforementioned front support component includes：Left floor (605), right floor (604), upper trouserss (606) and lower trouserss
(607), aforementioned 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) peace by electricity
It is mounted between left floor (605) and right floor (604), electricity is adjusted and electricity tune installing plate (612), upper trouserss are stamped on seat (11)
(606) above left floor (605) and right floor (604), lower trouserss (607) are 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 aforementioned rear support component is identical with the structure of front support component；
Aforementioned wing coupling assembly includes：Wing connection frame (608) and middle trouserss (609), middle trouserss (609)
It is above wing connection frame (608) and following；
Aforementioned front support component and rear support component be screwed respectively installed in the front end of wing coupling assembly and
Rear end.
A kind of aforesaid 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：Front 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 eyelid covering of tail (704) and the left eyelid covering of tail (718), front 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) adjust in mounting seat (717) installed in electricity, the input line of brushless electric machine (710) is welded on electricity and adjusts on the outfan of (705),
Steering wheel (702) and the supporting setting of steering wheel (714), and respectively arrange a set of on front main frame (701) and rear main frame 712, brushless electricity
Machine (710), motor install rotating shaft (707) and connecting rod (709) is screwed respectively on motor mount (708),
Motor mount (708) is screwed on front main frame (701) and rear main frame 712, connecting rod (709) and steering wheel
(714) connect, the right eyelid covering of tail (704) and the right setting of the left the first from left of eyelid covering (718) of tail, and respectively spiral shell connected by pretension
Nail (703) is connected on front main frame (701) and rear main frame 712.
A kind of aforesaid 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：Front main frame (810), rear main frame (805), right support frame (803), left support frame
(807), electricity adjusts mounting seat (808), the right eyelid covering of tail (801) and the left eyelid covering of tail (809), front 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 adjust in mounting seat (808) installed in electricity, and brushless electric machine (806) is screwed installed in rear master
On frame (805), and input line is welded on electricity and adjusts on the outfan of (802), the right eyelid covering of tail (801) and the left eyelid covering of tail
The right setting of (809) one the first from left, and be connected on front main frame (810) and rear main frame (805) by pretension attachment screw respectively.
A kind of aforesaid many power combinations change the unmanned plane for adapting to different landing mode different task load, and its feature exists
In the moulding module C (90) of aforementioned tail also has：Front main frame (903), rear main frame (905), right support frame (904), left support frame
(906), electricity adjusts mounting seat (907), the right eyelid covering of tail (902) and the left eyelid covering of tail (908), front 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 eyelid covering of tail (902) and the left the first from left of eyelid covering (908) of tail are right
Arrange, and be connected on front main frame (903) and rear main frame (905) by pretension attachment screw (901) respectively.
The invention has benefit that：
(1) unmanned plane of the invention, with various power combination patterns, can be real on same unmanned plane body platform
Existing various adaptation scenes, greatly improved the versatility and platform of unmanned plane；
(2) unmanned plane of the invention, each module adopts modular design, not only increases transition transaction capabilities, and
And greatly facilitate the transport of unmanned plane, maintenance, maintenance and debug, it is extremely convenient and economical to use.
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 front 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 trouserss 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-, trouserss under 516-, the upper trouserss of 517-, 518- wings connection frame, trouserss after 519- are 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 trouserss of 606-, 607-
Lower trouserss, 608- wings connection frame, trouserss 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 eyelid 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
Eyelid 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 eyelid covering of 809- tails, main frame before 810-；
The moulding module C of 90- tails,
901- pretension attachment screws, the right eyelid 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 eyelid covering of 908- tails.
Specific embodiment
Make specific introduction to the present invention below in conjunction with the drawings and specific embodiments.
With reference to Fig. 6, Fig. 7, Fig. 8 and Fig. 9, many power combinations of the present invention are changed the different landing mode different tasks of adaptation and are carried
The unmanned plane of lotus, including：Fuselage 10, port wing 20, starboard wing 30 and empennage 40, wherein, empennage 40 is threadedly coupled with fuselage 10.
Additionally, also including：Active force module A 50, active force module B60, secondary power module A 70, pair power module B80 and tail are moulding
Module C90, selects using 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 so that the unmanned plane of the present invention be adapted to it is various
Scene.
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, according to the needs of practical situation, 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
With reference to Fig. 1 (a), Fig. 1 (b) and Fig. 1 (c), there is 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
With reference to Fig. 1 (a), Fig. 1 (b) and Fig. 1 (c), support component includes：Upper trouserss 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 trouserss 516.
Limited block 508 is fixedly connected by screw with left floor 515 and right floor 506；
Bearing 507 is respectively pressed in 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 trouserss 505 and lower trouserss 516 are screwed and are connected on left floor 515 and right floor 506.
2nd, wing coupling assembly
With reference to Fig. 1 (a), Fig. 1 (b) and Fig. 1 (c), wing coupling assembly includes：Upper trouserss 517, wing connection frame 518,
Trouserss 519 and lower trouserss 520 afterwards.
Upper trouserss 517, lower trouserss 520 and rear trouserss 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 and adjusts lid 525 and electricity tune
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：
With reference to Fig. 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
Stricture of vagina connects, 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
Stricture of vagina connects.
2nd, active force module B
With reference to Fig. 2 (a) and Fig. 2 (b), there are active force module B60 two electricity to adjust 601 and two motors 602, wherein, should
Two motors 602 are located at respectively foremost and rearmost end, 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
With reference to Fig. 2 (a) and Fig. 2 (b), front support component includes：Left floor 605, right floor 604, upper trouserss 606 and under
Trouserss 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 trouserss 606 are screwed installed in left rib
Above plate 605 and right floor 604, lower trouserss 607 are 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
With reference to Fig. 2 (a) and Fig. 2 (b), the structure of rear support component is identical with the structure of front support component, no longer goes to live in the household of one's in-laws on getting married
State.
3rd, wing coupling assembly
With reference to Fig. 2 (a) and Fig. 2 (b), wing coupling assembly includes：Wing connects frame 608 and middle trouserss 609.
Middle trouserss 609 are screwed above wing connection frame 608 and following.
With reference to Fig. 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：
With reference to Fig. 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
With reference to Fig. 3 (a), Fig. 3 (b) and Fig. 3 (c), there is 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：Front main frame 701, rear main frame 712, right support frame 715, a left side
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 eyelid covering 704 of tail and the left eyelid covering 718 of tail.
Front 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 outfan that electricity adjusts 705
On；
Steering wheel 702 and the supporting setting of steering wheel 714, and respectively arrange a set of on front main frame 701 and rear main frame 712；
Brushless electric machine 710, motor installs rotating shaft 707 and connecting rod 709 is screwed respectively installed in motor mount
On 708, motor mount 708 is screwed on front 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 eyelid covering 704 of tail and the right setting of the left the first from left of eyelid covering 718 1 of tail, and pass through pretension attachment screw 703 respectively
It is connected on front main frame 701 and rear main frame 712.
The right eyelid covering 704 of tail and the left eyelid 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 eyelid covering 704 of tail and the left eyelid covering 718 of tail are fastened by connection insert 711.
The mounting means of secondary power module A 70：
With reference to Fig. 9, secondary power module A 70 is fixedly mounted on the end of fuselage 10 by pretension attachment screw.
4th, secondary power module B
With reference to Fig. 4 (a) and Fig. 4 (b), there is 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：Front main frame 810, rear main frame 805, right support frame 803, left support
Frame 807, electricity adjust the right eyelid covering 801 of mounting seat 808, tail and the left eyelid covering 809 of tail.
Front 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 installed in rear main frame 805
On, and input line be welded on electricity adjust 802 outfan on；
The right eyelid covering 801 of tail and the right setting of the left the first from left of eyelid covering 809 1 of tail, and connected by pretension attachment screw respectively
On front main frame 810 and rear main frame 805.
The mounting means of secondary power module B80：
With reference to Fig. 6 and Fig. 7, secondary power module B80 is fixedly mounted on the end of fuselage 10 by pretension attachment screw.
5th, the moulding module C of tail
With reference to Fig. 5 (a) and Fig. 5 (b), the moulding module C90 of tail has：Front 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 eyelid covering 902 of tail and the left eyelid covering 908 of tail, do not have
There is brushless electric machine.
Front 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 eyelid covering 902 of tail and the right setting of the left the first from left of eyelid covering 908 1 of tail, and pass through pretension attachment screw 901 respectively
It is connected on front main frame 903 and rear main frame 905.
The mounting means of the moulding module C90 of tail：
With reference to Fig. 8, the moulding module C90 of tail is fixedly mounted on the end of fuselage 10 by pretension attachment screw.
Select using 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, is not provided with active force 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, is respectively mounted active force module between port wing 20 and fuselage 10, between starboard wing 30 and fuselage 10
B60, as shown in Figure 7；
(3), double dynamical front pull-type rolling start unmanned plane pattern：It is solid by pretension attachment screw in the end of fuselage 10
The moulding module C90 of Dingan County's installation tail, is respectively mounted active force mould between port wing 20 and fuselage 10, 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, is respectively mounted active force module A 50 between port wing 20 and fuselage 10, between starboard wing 30 and fuselage 10,
As shown in Figure 8.
As can be seen here, by selecting using different active force module As, active force module B, secondary power module A, secondary power
The module B and moulding module C of tail, the unmanned plane of the present invention can form various power combination patterns, so that it can be fitted
Several scenes, versatility and platform are answered to be greatly improved.
It should be noted that above-described embodiment the invention is not limited in any way, all employing equivalents or equivalent change
The technical scheme that the mode changed is obtained, all falls within protection scope of the present invention.
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) is 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 symmetrical left and right sides for being arranged on fuselage (10) of the active force module A (50) or 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 the tail is adjusted with an electricity, not with 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 trouserss (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
Trouserss (516), the limited block (508) is fixedly connected by screw with left floor (515) and right floor (506), the axle
Hold (507) to be respectively pressed in 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 trouserss (516) are screwed and are connected on left floor (515) and right floor (506)；
The wing coupling assembly includes：Upper trouserss (517), wing connection frame (518), rear trouserss (519) and lower rectification
Cover (520), upper trouserss (517), lower trouserss (520) and rear trouserss (519) are screwed respectively installed in wing
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 left floor (515) and right floor installed in support component
(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 trouserss (606) and lower trouserss (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 trouserss (606) are installed
Above left floor (605) and right floor (604), lower trouserss (607) are 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 connection frame (608) and middle trouserss (609), middle trouserss (609) are installed
It is above wing connection frame (608) and following；
The front support component and rear support component are screwed respectively installed in the front-end and back-end of wing coupling assembly.
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：Front 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 eyelid covering of tail (704) and the left eyelid covering of tail (718), front 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 adjust in mounting seat (717) installed in electricity, and the input line of brushless electric machine (710) is welded on electric tune
(705) on outfan, steering wheel (702) and the supporting setting of steering wheel (714), and on front main frame (701) and rear main frame (712)
Respectively arrange a set of, brushless electric machine (710), motor install rotating shaft (707) and connecting rod (709) is screwed respectively installed in electricity
In machine mounting seat (708), motor mount (708) is screwed on front main frame (701) and rear main frame (712),
Connecting rod (709) is connected with steering wheel (714), the right eyelid covering of tail (704) and the right setting of the left the first from left of eyelid covering (718) of tail, and point
Not Tong Guo pretension attachment screw (703) be connected on front 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：Front main frame (810), rear main frame (805), right support frame
(803), left support frame (807), electricity adjust mounting seat (808), the right eyelid covering of tail (801) and the left eyelid covering of tail (809), front 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 adjust 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) outfan on, the right eyelid covering of tail (801) and
The right setting of the left the first from left of eyelid covering (809) of tail, and respectively front main frame (810) and rear main frame be connected to by pretension attachment screw
(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 the tail also has：Front main frame (903), rear main frame (905), right support frame
(904), left support frame (906), electricity adjust mounting seat (907), the right eyelid covering of tail (902) and the left eyelid covering of tail (908), front 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 eyelid covering of tail (902) and the left eyelid covering of tail
The right setting of (908) one the first from left, and respectively front main frame (903) and rear main frame (905) be connected to by pretension attachment screw (901)
On.
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| CN201611126983.9A CN106628201B (en) | 2016-12-09 | 2016-12-09 | Unmanned aerial vehicle with multiple power combinations, capable of being replaced and adapted to different take-off and landing modes and different task loads |
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|---|---|---|---|
| CN201611126983.9A CN106628201B (en) | 2016-12-09 | 2016-12-09 | Unmanned aerial vehicle with multiple power combinations, capable of being replaced and adapted to different take-off and landing modes and different task loads |
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| CN108382590A (en) * | 2018-02-24 | 2018-08-10 | 浙江天遁航空科技有限公司 | Composite wing unmanned plane |
| CN108545180A (en) * | 2018-04-18 | 2018-09-18 | 黑龙江省农业机械维修研究所 | Gu it is a kind of it is more-- from rotor combined type unmanned vehicle |
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| CN111731475A (en) * | 2020-06-30 | 2020-10-02 | 湖南航天宏图无人机系统有限公司 | Vertical take-off and landing tilting composite wing aircraft |
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| US10894600B2 (en) | 2017-07-06 | 2021-01-19 | Autel Robotics Co., Ltd. | Aircraft, tilt driving mechanism and control method thereof |
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