CN106628201B - Unmanned aerial vehicle with multiple power combinations, capable of being replaced and adapted to different take-off and landing modes and different task loads - Google Patents
Unmanned aerial vehicle with multiple power combinations, capable of being replaced and adapted to different take-off and landing modes and different task loads Download PDFInfo
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- CN106628201B CN106628201B CN201611126983.9A CN201611126983A CN106628201B CN 106628201 B CN106628201 B CN 106628201B CN 201611126983 A CN201611126983 A CN 201611126983A CN 106628201 B CN106628201 B CN 106628201B
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- 238000007493 shaping process Methods 0.000 claims abstract description 10
- 230000006978 adaptation Effects 0.000 claims abstract description 5
- 230000001105 regulatory effect Effects 0.000 claims description 18
- 238000000465 moulding Methods 0.000 claims description 12
- 230000008878 coupling Effects 0.000 claims description 3
- 238000010168 coupling process Methods 0.000 claims description 3
- 238000005859 coupling reaction Methods 0.000 claims description 3
- 238000003466 welding Methods 0.000 claims description 2
- 238000012423 maintenance Methods 0.000 abstract 1
- 238000009434 installation Methods 0.000 description 11
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 8
- 239000000741 silica gel Substances 0.000 description 8
- 229910002027 silica gel Inorganic materials 0.000 description 8
- 238000010586 diagram Methods 0.000 description 5
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Classifications
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- B64D27/40—
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- 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
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- 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
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- 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
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- 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
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- 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)
- Toys (AREA)
- Forklifts And Lifting Vehicles (AREA)
Abstract
The invention discloses an unmanned aerial vehicle with multiple power combinations for changing different task loads adapting to different take-off and landing modes, which comprises the following components: fuselage, left wing, right wing, fin, main power module A, main power module B, vice power module A, vice power module B and tail shaping module C. The invention has the advantages that: (1) The unmanned aerial vehicle has multiple power combination modes, can realize multiple adaptation scenes on the same unmanned aerial vehicle body platform, and greatly improves the universality and the platform performance of the unmanned aerial vehicle; (2) Each module adopts the modularized design, so that not only is the transfer operation performance improved, but also the transportation, maintenance and debugging of the unmanned aerial vehicle are greatly facilitated, and the unmanned aerial vehicle is extremely convenient and economical to use.
Description
Technical Field
The invention relates to a small unmanned aerial vehicle, in particular to an unmanned aerial vehicle with multiple power combinations for changing different task loads adapting to different take-off and landing modes, and belongs to the technical field of unmanned aerial vehicles.
Background
The power system of the unmanned aerial vehicle is used for providing thrust for the flight of the unmanned aerial vehicle, and is an important part in the design and manufacture of the unmanned aerial vehicle. Because of the different landing sites, endurance, cruising radius, loading on tasks, etc., the unmanned aerial vehicle may need to change different power systems.
However, the power system of a general small unmanned aerial vehicle is fixedly connected with the machine body, so that the application of various adaptation scenes and various power combination modes on the same unmanned aerial vehicle machine body platform is difficult to realize, and the universality and the platfonn of the unmanned aerial vehicle are low.
If a specific machine type is used for completing a specific task, the problems of high occupation cost, large occupation space, difficult transportation and the like exist.
Disclosure of Invention
In order to solve the defects of the prior art, the invention aims to provide the unmanned aerial vehicle which is suitable for the replacement of multiple power combinations and different task loads in different take-off and landing modes.
In order to achieve the above object, the present invention adopts the following technical scheme:
an unmanned aerial vehicle of different task loads of adaptation different take-off and land modes is changed in many power combinations includes: fuselage (10), left wing (20), right wing (30) and fin (40), fin (40) and fuselage (10) threaded connection, its characterized in that still includes: a main power module A (50), a main power module B (60), a secondary power module A (70), a secondary power module B (80) and a tail shaping module C (90), wherein:
the main power module A (50) is provided with an electric regulator (523) and a motor (501), wherein the motor (501) is positioned at the forefront end, an output shaft points to the front of the unmanned aerial vehicle, a propeller (526) is arranged on the output shaft of the motor (501),
the main power module B (60) is provided with two electric regulators (601) and two motors (602), wherein the two motors (602) are respectively positioned at the forefront end and the rearmost end, an output shaft points to the upper part of the unmanned aerial vehicle, a propeller (603) is arranged on the output shaft of the motor (602),
the main power module A (50) or the main power module B (60) is symmetrically arranged on the left side and the right side of the machine body (10) and is in threaded connection with the machine body (10), the left wing (20) and the right wing (30) are respectively arranged on the outer side of the main power module A (50) or the main power module B (60) and are in threaded connection with the main power module A (50) or the main power module B (60), or the main power module A (50) or the main power module B (60) is not arranged between the left wing (20) and the machine body (10) and between the right wing (30) and the machine body (10), and the left wing (20) and the right wing (30) are directly in threaded connection with the machine body (10);
the auxiliary power module A (70) is provided with an electric regulator (705) and a brushless motor (710), wherein the brushless motor (710) is positioned in the middle, an output shaft points to the upper part of the unmanned aerial vehicle, a propeller (713) is arranged on the output shaft of the brushless motor (710),
the auxiliary power module B (80) is provided with an electric regulator (802) and a brushless motor (806), wherein the brushless motor (806) is positioned at the rearmost end, the output shaft points to the rear of the unmanned aerial vehicle, the propeller (804) is arranged on the output shaft of the brushless motor (806),
the tail molding module C (90) has an electric regulator, does not have a brushless motor,
the auxiliary power module A (70), the auxiliary power module B (80) or the tail shaping module C (90) are fixedly arranged at the tail end of the machine body (10) through pre-tightening connecting screws.
The unmanned aerial vehicle with the multi-power combination replacement adapted to different take-off and landing modes and different task loads is characterized in that the main power module A (50) further comprises: support assembly and wing coupling assembly, wherein:
the foregoing support assembly includes: the steering engine comprises an upper fairing (505), a right rib plate (506), a bearing (507), a limiting block (508), a first wire groove (509), a second wire groove (510), a steering engine (511), a steering engine frame (512), a rocker arm (513), a connecting rod (514), a left rib plate (515) and a lower fairing (516), wherein the limiting block (508) is fixedly connected with the left rib plate (515) and the right rib plate (506) through screws, the bearing (507) is respectively pressed into grooves of the left rib plate (515) and the right rib plate (506), the connecting rod (514) is arranged on the rocker arm (513), the rocker arm (513) is arranged on an output shaft of the steering engine (511), the steering engine (511) is fixedly arranged on a steering engine frame (512) through screws, the first wire groove (509) is connected with the second wire groove (510), the second wire groove (510) is connected with the steering engine frame (512), the steering engine frame (512) is fixedly connected with the left rib plate (515) and the right rib plate (506) through screws, and the upper fairing (505) and the lower fairing (516) are fixedly connected with the left rib plate (506) through screws;
the aforementioned wing connection assembly comprises: the upper fairing (517), the wing connecting frame (518), the rear fairing (519) and the lower fairing (520) are respectively fixedly arranged on the upper surface, the lower surface and the rear end of the wing connecting frame (518) through screws;
the motor (501) is arranged at the front end of the supporting component through a motor base (502), the wing connecting component is fixedly arranged at the rear end of the supporting component through screws, and the electric regulator (523) is fixedly arranged on a left rib plate (515) and a right rib plate (506) of the supporting component through screws.
The unmanned aerial vehicle with the multi-power combination and replacement adapted to different take-off and landing modes and different task loads is characterized in that the main power module B (60) further comprises: front support assembly, back support assembly and wing coupling assembly, wherein:
the front support assembly includes: the motor comprises a left rib plate (605), a right rib plate (604), an upper fairing (606) and a lower fairing (607), wherein the left rib plate (605) and the right rib plate (604) are symmetrically arranged left and right, an electric regulator (601) is arranged between the left rib plate (605) and the right rib plate (604) through an electric regulator seat (11), an electric regulator mounting plate (612) is covered on the electric regulator seat (11), the upper fairing (606) is arranged above the left rib plate (605) and the right rib plate (604), the lower fairing (607) is arranged below the left rib plate (605) and the right rib plate (604), and a motor (602) is arranged between the left rib plate (605) and the right rib plate (604) through a motor fixing seat (610);
the structure of the rear supporting component is identical to that of the front supporting component;
the aforementioned wing connection assembly comprises: a wing connection frame (608) and an intermediate fairing (609), the intermediate fairing (609) being mounted above and below the wing connection frame (608);
the front support component and the rear support component are respectively and fixedly arranged at the front end and the rear end of the wing connecting component through screws.
The aforementioned unmanned aerial vehicle with multiple power combination replacement adapted to different take-off and landing modes and different task loads is characterized in that the aforementioned auxiliary power module a (70) further comprises: the steering engine comprises a front main frame (701), a rear main frame 712, a right support frame (715), a left support frame (716), an electric adjustment mounting seat (717), a steering engine (702), a steering wheel (714), a motor mounting rotating shaft (707), a connecting rod (709), a motor mounting seat (708), a tail right skin (704) and a tail left skin (718), wherein the front main frame (701), the rear main frame 712, the right support frame (715), the left support frame (716) and the electric adjustment mounting seat (717) are connected together through screws and assembled into a frame, the electric adjustment (705) is mounted on the electric adjustment mounting seat (717), an input line of the brushless motor (710) is welded on an output end of the electric adjustment (705), the steering engine (702) and the steering wheel (714) are arranged in a matched mode, the front main frame (701) and the rear main frame 712 are respectively provided with a set, the brushless motor (710), the motor mounting rotating shaft (707) and the connecting rod (709) are respectively fixedly mounted on the motor mounting seat (708) through screws, the motor mounting seat (708) is fixedly mounted on the front main frame (701) and the tail main frame (712) through screws, the steering engine mounting seat (712) is fixedly mounted on the tail left skin (712) and the left skin is connected with the front main frame (703) through screws and the left steering wheel (712) in a matched mode, and the steering engine (712) is connected with the steering engine through the left skin (712).
The aforementioned unmanned aerial vehicle with multiple power combination replacement adapted to different take-off and landing modes and different task loads is characterized in that the aforementioned auxiliary power module B (80) further comprises: front main frame (810), back main frame (805), right braced frame (803), left braced frame (807), electric regulating mount pad (808), tail right skin (801) and tail left skin (809), front main frame (810), back main frame (805), right braced frame (803), left braced frame (807) and electric regulating mount pad (808) are in the same place through screw connection to assemble into a frame, electric regulating (802) are installed on electric regulating mount pad (808), brushless motor (806) are installed on back main frame (805) through screw fixation, and the input wire welding is on the output of electric regulating (802), tail right skin (801) and tail left skin (809) are one side by one right side setting, and are connected on front main frame (810) and back main frame (805) through pretension connecting screw respectively.
The unmanned aerial vehicle with the multi-power combination and replacement suitable for different take-off and landing modes and different task loads is characterized in that the tail molding module C (90) further comprises: front main frame (903), back main frame (905), right braced frame (904), left braced frame (906), electric regulating mount pad (907), tail right skin (902) and tail left skin (908), front main frame (903), back main frame (905), right braced frame (904), left braced frame (906) and electric regulating mount pad (907) are connected together through the screw to assemble into a frame, electric regulating is installed on electric regulating mount pad (907), tail right skin (902) and tail left skin (908) are set up about one, and connect on front main frame (903) and back main frame (905) through pretension connecting screw (901) respectively.
The invention has the advantages that:
(1) The unmanned aerial vehicle has various power combination modes, can realize various adaptation scenes on the same unmanned aerial vehicle body platform, and greatly improves the universality and the platform property of the unmanned aerial vehicle;
(2) According to the unmanned aerial vehicle, each module adopts a modularized design, so that not only is the transfer operation performance improved, but also the unmanned aerial vehicle is greatly convenient to transport, maintain and debug, and the unmanned aerial vehicle is extremely convenient and economical to use.
Drawings
FIG. 1 (a) is an exploded view of a main power module A;
FIG. 1 (b) is a schematic diagram of the structure of the main power module A after assembly;
FIG. 1 (c) is a schematic diagram of the assembled main power module A;
FIG. 2 (a) is an exploded view of the main power module B;
FIG. 2 (B) is a schematic diagram of the assembled main power module B;
FIG. 3 (a) is an exploded view of the secondary power module A;
FIG. 3 (b) is a schematic view of the secondary power module A after assembly;
FIG. 3 (c) is a schematic diagram of the assembled secondary power module A;
FIG. 4 (a) is an exploded view of the secondary power module B;
FIG. 4 (B) is a schematic diagram of the assembled secondary power module B;
FIG. 5 (a) is an exploded view of the tail shaping module C;
FIG. 5 (b) is a schematic view of the assembled tail molding module C;
FIG. 6 is a schematic structural view of a single-power tail-propelled jogging takeoff unmanned aerial vehicle;
FIG. 7 is a schematic structural view of a multi-powered composite vertical take-off and landing drone;
FIG. 8 is a schematic structural view of a dual-power front-pull ski-takeoff drone;
fig. 9 is a schematic structural view of a vertical lift tiltrotor unmanned aerial vehicle.
Meaning of reference numerals in the drawings:
10-fuselage, 20-left wing, 30-right wing, 40-tail wing;
50-a main power module a,
501-a motor, 502-a motor seat, 503-a clamp spring, 504-a rotating shaft, 505-an upper fairing, 506-a right rib plate, 507-a bearing, 508-a limiting block, 509-a first wire slot, 510-a second wire slot, 511-a steering engine, 512-a rudder frame, 513-a rocker arm, 514-a connecting rod, 515-a left rib plate, 516-a lower fairing, 517-an upper fairing, 518-a wing connecting frame, 519-a rear fairing, 520-a lower fairing, 521-an electric adjustment mounting plate, 522-an upper heat conducting silica gel, 523-an electric adjustment, 524-a lower heat conducting silica gel, 525-an electric adjustment cover and 526-a propeller;
60-a main power module B,
601-electric tuning, 602-a motor, 603-a propeller, 604-a right rib plate, 605-a left rib plate, 606-an upper fairing, 607-a lower fairing, 608-a wing connecting frame, 609-a middle fairing, 610-a motor fixing seat, 611-an electric tuning seat, 612-an electric tuning mounting plate, 613-an upper heat conducting silica gel and 614-a lower heat conducting silica gel;
70-a secondary power module A,
701-a front main frame, 702-a steering engine, 703-a pre-tightening connecting screw, 704-a tail right skin, 705-an electric tuning, 706-a bearing, 707-a motor installation rotating shaft, 708-a motor installation seat, 709-a connecting rod, 710-a brushless motor, 711-a connecting insert, 712-a rear main frame, 713-a propeller, 714-a steering wheel, 715-a right supporting frame, 716-a left supporting frame, 717-an electric tuning installation seat, 718-a tail left skin;
80-a secondary power module B, wherein,
801-a front main frame, 802-an electric tuning, 803-a right support frame, 804-a propeller, 805-a rear main frame, 806-a brushless motor, 807-a left support frame, 808-an electric tuning mounting seat, 809-a tail left skin and 810-a front main frame;
90-a tail molding module C,
901-pretightening connecting screws, 902-a tail right skin, 903-a front main frame, 904-a right support frame, 905-a rear main frame, 906-a left support frame, 907-an electric tuning mounting seat, 908-a tail left skin.
Detailed Description
The invention is described in detail below with reference to the drawings and the specific embodiments.
Referring to fig. 6, 7, 8 and 9, the multi-power combined replacement unmanned aerial vehicle adapting to different take-off and landing modes and different task loads of the invention comprises: fuselage 10, left wing 20, right wing 30, and tail 40, wherein tail 40 is threadably coupled to fuselage 10. Furthermore, the method further comprises: the main power module A50, the main power module B60, the auxiliary power module A70, the auxiliary power module B80 and the tail molding module C90 are selected to use different main power modules A50, main power modules B60, auxiliary power modules A70, auxiliary power modules B80 and tail molding modules C90, so that various power combination modes can be formed, and the unmanned aerial vehicle can adapt to various scenes.
The main power module a50 and the main power module B60 are installed between the left wing 20 and the fuselage 10 and between the right wing 30 and the fuselage 10. Of course, the main power module a50 or the main power module B60 may not be provided between the left wing 20 and the fuselage 10, and between the right wing 30 and the fuselage 10, and the left wing 20 and the right wing 30 may be directly screwed with the fuselage 10, as shown in fig. 6, according to the actual situation.
The structure of the main power module a50, the main power module B60, the sub power module a70, the sub power module B80, and the tail shaping module C90 will be described in detail.
1. Main power module A
Referring to fig. 1 (a), 1 (b) and 1 (c), the main power module a50 has one electric motor 523 and one motor 501, the motor 501 is located at the forefront end, and the output shaft is directed to the front of the unmanned aerial vehicle, and the propeller 526 is mounted on the output shaft of the motor 501. In addition, the main power module a50 further has: a support assembly and a wing attachment assembly.
1. Support assembly
Referring to fig. 1 (a), 1 (b) and 1 (c), the support assembly includes: an upper fairing 505, a right rib 506, bearings 507, a stop block 508, a first wire slot 509, a second wire slot 510, a steering engine 511, a steering engine rack 512, a rocker arm 513, a connecting rod 514, a left rib 515, and a lower fairing 516.
The limiting block 508 is fixedly connected with the left rib plate 515 and the right rib plate 506 through screws;
the bearings 507 are respectively pressed into the grooves of the left rib 515 and the right rib 506;
the connecting rod 514 is arranged on the rocker arm 513, the rocker arm 513 is arranged on an output shaft of the steering engine 511, and the steering engine 511 is fixedly arranged on the rudder frame 512 through screws;
the first wire slot 509 is connected to the second wire slot 510, the second wire slot 510 is connected to the steering engine bracket 512, and the steering engine bracket 512 is fixedly connected with the left rib plate 515 and the right rib plate 506 through screws;
the upper cowling 505 and the lower cowling 516 are fixedly connected to the left rib 515 and the right rib 506 by screws.
2. Wing connection assembly
Referring to fig. 1 (a), 1 (b) and 1 (c), the wing connection assembly includes: an upper fairing 517, a wing attachment frame 518, a rear fairing 519, and a lower fairing 520.
The upper fairing 517, the lower fairing 520, and the aft fairing 519 are fixedly mounted to the upper, lower, and aft ends of the wing attachment frame 518, respectively, by screws.
The motor 501 is fixedly arranged in the motor base 502 through screws, a clamp spring 503 and a rotating shaft 504 are arranged on the outer wall of the motor base 502, wherein the clamp spring 503 can be clamped on the rotating shaft 504, and the rotating shaft 504 can be inserted into a bearing 507 at the front end of the supporting component; the wing connecting component is fixedly arranged at the rear end of the supporting component through a screw; the electric tuning 523 is placed in an electric tuning installation space formed by the electric tuning cover 525 and the electric tuning installation plate 521, the upper side and the lower side of the electric tuning 523 are respectively provided with an upper layer of heat conducting silica gel 522 and a lower layer of heat conducting silica gel 524, and the electric tuning cover 525 is fixedly installed on the left rib plate 515 and the right rib plate 506 of the supporting component through screws.
The main power module A50 is installed in the following way:
referring to fig. 8 and 9, the main power module a50 is symmetrically disposed at both left and right sides of the fuselage 10 and is screw-coupled with the fuselage 10, and the left wing 20 and the right wing 30 are respectively disposed at the outer sides of the main power module a50 and are screw-coupled with the main power module a 50.
2. Main power module B
Referring to fig. 2 (a) and 2 (B), the main power module B60 has two electric motors 601 and two motors 602, wherein the two motors 602 are respectively located at the foremost and rearmost ends, and an output shaft is directed above the unmanned aerial vehicle, and a propeller 603 is mounted on the output shaft of the motor 602. In addition, the main power module B60 further has: a front support assembly, a rear support assembly and a wing attachment assembly.
1. Front support assembly
Referring to fig. 2 (a) and 2 (b), the front support assembly includes: a left rib 605, a right rib 604, an upper fairing 606, and a lower fairing 607.
The left rib plate 605 and the right rib plate 604 are symmetrically arranged left and right, the electric regulator 601 is fixedly arranged between the left rib plate 605 and the right rib plate 604 through an electric regulator seat 611 by means of screws, upper heat conducting silica gel 613 is arranged on the electric regulator 601, lower heat conducting silica gel 614 is arranged below the electric regulator seat 601, an electric regulator mounting plate 612 is covered on the electric regulator seat 611, an upper fairing 606 is fixedly arranged on the left rib plate 605 and the right rib plate 604 by means of screws, and a lower fairing 607 is fixedly arranged below the left rib plate 605 and the right rib plate 604 by means of screws.
The motor 602 is fixedly mounted between the left rib 605 and the right rib 604 by a motor fixing base 610 and by means of fixing bolts.
2. Rear support assembly
Referring to fig. 2 (a) and 2 (b), the structure of the rear supporting assembly is identical to that of the front supporting assembly, and will not be described again.
3. Wing connection assembly
Referring to fig. 2 (a) and 2 (b), the wing connection assembly includes: a wing connection frame 608 and an intermediate fairing 609.
The middle fairing 609 is fixedly mounted above and below the wing attachment frame 608 by screws.
Referring to fig. 2 (a) and 2 (b), the front and rear support assemblies are fixedly installed at the front and rear ends of the wing connection assembly by screws, respectively.
The main power module B60 is installed in the following way:
referring to fig. 7, the main power module B60 is symmetrically disposed at both left and right sides of the fuselage 10 and is screw-coupled with the fuselage 10, and the left wing 20 and the right wing 30 are respectively disposed at the outer sides of the main power module B60 and screw-coupled with the main power module B60.
3. Auxiliary power module A
Referring to fig. 3 (a), 3 (b) and 3 (c), the subsidiary power module a70 has one electric motor 705 and one brushless motor 710, wherein the brushless motor 710 is located at the middle and the output shaft is directed to the upper side of the unmanned aerial vehicle, and the propeller 713 is mounted on the output shaft of the brushless motor 710. In addition, the sub-power module a70 further has: front main frame 701, rear main frame 712, right support frame 715, left support frame 716, electric tuning mount 717, steering engine 702, steering wheel 714, motor mounting shaft 707, link 709, motor mount 708, aft right skin 704, and aft left skin 718.
The front main frame 701, the rear main frame 712, the right support frame 715, the left support frame 716 and the electric adjustment mounting seat 717 are connected together by screws and assembled into a frame;
the electric tone 705 is mounted on the electric tone mounting seat 717, and an input wire of the brushless motor 710 is welded on an output end of the electric tone 705;
the steering engine 702 and the steering wheel 714 are arranged in a matched mode, and a set of steering wheels are arranged on the front main frame 701 and the rear main frame 712 respectively;
the brushless motor 710, the motor installation rotating shaft 707 and the connecting rod 709 are respectively and fixedly installed on the motor installation seat 708 through screws, the motor installation seat 708 is fixedly installed on the front main frame 701 and the rear main frame 712 through screws, the connecting rod 709 is connected with the rudder plate 714, and the bearing 706 is preloaded on the motor installation rotating shaft 707;
the tail right skin 704 and the tail left skin 718 are disposed side-by-side and are connected to the front main frame 701 and the rear main frame 712 by pre-tightening connection screws 703, respectively.
Limiting grooves are formed in the right tail skin 704 and the left tail skin 718, the shapes of the limiting grooves are matched with the connecting inserts 711, and the right tail skin 704 and the left tail skin 718 are fastened through the connecting inserts 711.
The installation mode of the auxiliary power module A70 is as follows:
referring to fig. 9, the sub power module a70 is fixedly installed at the end of the body 10 by a pre-tightening connection screw.
4. Auxiliary power module B
Referring to fig. 4 (a) and 4 (B), the secondary power module B80 has an electric motor 802 and a brushless motor 806, wherein the brushless motor 806 is located at the rearmost end, and the output shaft is directed to the rear of the unmanned aerial vehicle, and the propeller 804 is mounted on the output shaft of the brushless motor 806. In addition, the sub-power module B80 further has: a front main frame 810, a rear main frame 805, a right support frame 803, a left support frame 807, an electrical tuning mount 808, a tail right skin 801, and a tail left skin 809.
The front main frame 810, the rear main frame 805, the right support frame 803, the left support frame 807 and the electric tuning mount 808 are connected together by screws and assembled into one frame;
the electric tone 802 is mounted on the electric tone mounting base 808, the brushless motor 806 is fixedly mounted on the rear main frame 805 by screws, and an input wire is welded on an output end of the electric tone 802;
the tail right skin 801 and the tail left skin 809 are disposed side by side and are connected to the front main frame 810 and the rear main frame 805 by pre-tightening connection screws, respectively.
The installation mode of the auxiliary power module B80 is as follows:
referring to fig. 6 and 7, the subsidiary power module B80 is fixedly installed at the end of the body 10 by a pre-tightening connection screw.
5. Tail moulding module C
Referring to fig. 5 (a) and 5 (b), the tail shaping module C90 has: front main frame 903, rear main frame 905, right support frame 904, left support frame 906, electrical tone mount 907, electrical tone (not shown), tail right skin 902, and tail left skin 908, do not have a brushless motor.
The front main frame 903, the rear main frame 905, the right support frame 904, the left support frame 906, and the electric tuning mount 907 are connected together by screws, and assembled into one frame;
the electric tone is arranged on the electric tone mounting seat 907;
tail right skin 902 and tail left skin 908 are disposed side-to-side and are connected to front main frame 903 and rear main frame 905, respectively, by pre-tightening connection screws 901.
The mounting mode of the tail molding module C90 is as follows:
referring to fig. 8, the tail molding module C90 is fixedly installed at the end of the body 10 by a pre-tightening connection screw.
Various power combining modes can be formed by selecting and using different main power module a50, main power module B60, auxiliary power module a70, auxiliary power module B80 and tail shaping module C90, for example:
(one), single-power tail pushing type running takeoff unmanned aerial vehicle mode: the auxiliary power module B80 is fixedly installed only at the tail end of the fuselage 10 through a pre-tightening connecting screw, and no main power module is arranged between the left wing 20 and the fuselage 10 and between the right wing 30 and the fuselage 10, as shown in FIG. 6;
(II), a multi-power combined type vertical take-off and landing unmanned aerial vehicle mode: the tail end of the fuselage 10 is fixedly provided with a secondary power module B80 through a pre-tightening connecting screw, and a main power module B60 is arranged between the left wing 20 and the fuselage 10 and between the right wing 30 and the fuselage 10, as shown in FIG. 7;
(III), double-power front-pull type running takeoff unmanned aerial vehicle mode: the tail molding module C90 is fixedly arranged at the tail end of the machine body 10 through a pre-tightening connecting screw, and a main power module A50 is arranged between the left wing 20 and the machine body 10 and between the right wing 30 and the machine body 10, as shown in FIG. 8;
(IV), a vertical take-off and landing tilt rotor unmanned aerial vehicle mode: the auxiliary power module A70 is fixedly arranged at the tail end of the fuselage 10 through a pre-tightening connecting screw, and the main power module A50 is arranged between the left wing 20 and the fuselage 10 and between the right wing 30 and the fuselage 10, as shown in fig. 8.
Therefore, by selecting and using different main power module A, main power module B, auxiliary power module A, auxiliary power module B and tail molding module C, the unmanned aerial vehicle can form various power combination modes, so that the unmanned aerial vehicle can adapt to various scenes, and the universality and the platformability are greatly improved.
It should be noted that, the above embodiments are not intended to limit the present invention in any way, and all the technical solutions obtained by adopting equivalent substitution or equivalent transformation fall within the protection scope of the present invention.
Claims (5)
1. An unmanned aerial vehicle of different task loads of adaptation different take-off and land modes is changed in many power combinations includes: fuselage (10), left wing (20), right wing (30) and fin (40), fin (40) and fuselage (10) threaded connection, its characterized in that still includes: a main power module A (50), a main power module B (60), a secondary power module A (70), a secondary power module B (80) and a tail shaping module C (90), wherein:
the main power module A (50) is provided with an electric regulator (523) and a motor (501), wherein the motor (501) is positioned at the forefront end, an output shaft points to the front of the unmanned aerial vehicle, and a propeller (526) is arranged on the output shaft of the motor (501);
the main power module B (60) is provided with two electric regulators (601) and two motors (602), wherein the two motors (602) are respectively positioned at the foremost end and the rearmost end, an output shaft points to the upper part of the unmanned aerial vehicle, and a propeller (603) is arranged on the output shaft of the motor (602);
the main power module A (50) or the main power module B (60) is symmetrically arranged on the left side and the right side of the machine body (10) and is in threaded connection with the machine body (10), the left wing (20) and the right wing (30) are respectively arranged on the outer side of the main power module A (50) or the main power module B (60) and are in threaded connection with the main power module A (50) or the main power module B (60), or the main power module A (50) or the main power module B (60) is not arranged between the left wing (20) and the machine body (10) and between the right wing (30) and the machine body (10), and the left wing (20) and the right wing (30) are directly in threaded connection with the machine body (10);
the auxiliary power module A (70) is provided with an electric regulator (705) and a brushless motor (710), wherein the brushless motor (710) is positioned in the middle, an output shaft points to the upper part of the unmanned aerial vehicle, and a propeller (713) is arranged on the output shaft of the brushless motor (710);
the auxiliary power module B (80) is provided with an electric regulator (802) and a brushless motor (806), wherein the brushless motor (806) is positioned at the rearmost end, the output shaft points to the rear of the unmanned aerial vehicle, the propeller (804) is arranged on the output shaft of the brushless motor (806),
the tail molding module C (90) is provided with an electric regulator and is not provided with a brushless motor;
the auxiliary power module A (70), the auxiliary power module B (80) or the tail shaping module C (90) are fixedly arranged at the tail end of the machine body (10) through a pre-tightening connecting screw, wherein:
the main power module A (50) further has: support assembly and wing coupling assembly, wherein:
the support assembly includes: the steering engine comprises an upper fairing (505), a right rib plate (506), a bearing (507), a limiting block (508), a first wire groove (509), a second wire groove (510), a steering engine (511), a steering engine frame (512), a rocker arm (513), a connecting rod (514), a left rib plate (515) and a lower fairing (516), wherein the limiting block (508) is fixedly connected with the left rib plate (515) and the right rib plate (506) through screws, the bearing (507) is respectively pressed into grooves of the left rib plate (515) and the right rib plate (506), the connecting rod (514) is arranged on the rocker arm (513), the rocker arm (513) is arranged on an output shaft of the steering engine (511), the steering engine (511) is fixedly arranged on a steering engine frame (512) through screws, the first wire groove (509) is connected with the second wire groove (510), the second wire groove (510) is connected with the steering engine frame (512), and the steering engine frame (512) is fixedly connected with the left rib plate (515) and the right rib plate (506) through screws;
the wing connection assembly includes: the upper fairing (517), the wing connecting frame (518), the rear fairing (519) and the lower fairing (520) are respectively fixedly arranged on the upper surface, the lower surface and the rear end of the wing connecting frame (518) through screws;
the motor (501) is arranged at the front end of the supporting component through a motor seat (502), the wing connecting component is fixedly arranged at the rear end of the supporting component through a screw, and the electric regulator (523) is fixedly arranged on a left rib plate (515) and a right rib plate (506) of the supporting component through the screw;
the main power module B (60) also has a front support assembly, a rear support assembly, and a wing connection assembly.
2. The unmanned aerial vehicle of claim 1, wherein the unmanned aerial vehicle is adapted to different take-off and landing modes and different task loads, and is characterized in that:
the front support assembly includes: the motor comprises a left rib plate (605), a right rib plate (604), an upper fairing (606) and a lower fairing (607), wherein the left rib plate (605) and the right rib plate (604) are symmetrically arranged left and right, an electric regulator (601) is arranged between the left rib plate (605) and the right rib plate (604) through an electric regulator seat (11), an electric regulator mounting plate (612) is covered on the electric regulator seat (11), the upper fairing (606) is arranged above the left rib plate (605) and the right rib plate (604), the lower fairing (607) is arranged below the left rib plate (605) and the right rib plate (604), and a motor (602) is arranged between the left rib plate (605) and the right rib plate (604) through a motor fixing seat (610);
the structure of the rear supporting component is identical to that of the front supporting component;
the wing connection assembly includes: a wing connection frame (608) and an intermediate fairing (609), the intermediate fairing (609) being mounted above and below the wing connection frame (608);
the front support component and the rear support component are respectively and fixedly arranged at the front end and the rear end of the wing connecting component through screws.
3. The unmanned aerial vehicle for replacing a multi-power combination adapted to different take-off and landing modes and different task loads according to claim 1, wherein the auxiliary power module a (70) further comprises: the front main frame (701), the rear main frame (712), the right support frame (715), the left support frame (716), the electric adjustment mounting seat (717), the steering engine (702), the steering wheel (714), the motor mounting rotating shaft (707), the connecting rod (709), the motor mounting seat (708), the tail right skin (704) and the tail left skin (718), the front main frame (701), the rear main frame (712), the right support frame (715), the left support frame (716) and the electric adjustment mounting seat (717) are connected together through screws and assembled into a frame, the electric adjustment (705) is mounted on the electric adjustment mounting seat (717), the input line of the brushless motor (710) is welded on the output end of the electric adjustment (705), the steering engine (702) and the steering wheel (714) are arranged in a matched mode, a set of the steering engine (702) and the steering wheel (714) is arranged on the front main frame (701) and the rear main frame (712), the brushless motor (710), the motor mounting rotating shaft (707) and the connecting rod (709) are fixedly mounted on the motor mounting seat (708) through screws respectively, the motor mounting seat (708) is fixedly mounted on the front main frame (701) and the tail left skin (714) through screws, the steering wheel (714) is fixedly mounted on the front main frame and the tail left skin (712) and the tail left skin (718) respectively, and are connected to the front main frame (701) and the rear main frame (712) by pre-tightening connecting screws (703), respectively.
4. The unmanned aerial vehicle for multi-power combined replacement adapting to different take-off and landing modes and different task loads according to claim 1, wherein the auxiliary power module B (80) further comprises: front main frame (810), back main frame (805), right braced frame (803), left braced frame (807), electric regulating mount pad (808), tail right skin (801) and tail left skin (809), front main frame (810), back main frame (805), right braced frame (803), left braced frame (807) and electric regulating mount pad (808) are in the same place through screw connection to assemble into a frame, electric regulating (802) are installed on electric regulating mount pad (808), brushless motor (806) are installed on back main frame (805) through screw fixation, and the input wire welding is on the output of electric regulating (802), tail right skin (801) and tail left skin (809) are one side by one right side setting, and are connected on front main frame (810) and back main frame (805) through pretension connecting screw respectively.
5. The unmanned aerial vehicle for multi-power combined replacement adapting to different take-off and landing modes and different task loads according to claim 1, wherein the tail shaping module C (90) further comprises: front main frame (903), back main frame (905), right braced frame (904), left braced frame (906), electric regulating mount pad (907), tail right skin (902) and tail left skin (908), front main frame (903), back main frame (905), right braced frame (904), left braced frame (906) and electric regulating mount pad (907) are connected together through the screw to assemble into a frame, electric regulating is installed on electric regulating mount pad (907), tail right skin (902) and tail left skin (908) are set up about one, and connect on front main frame (903) and back main frame (905) through pretension connecting screw (901) respectively.
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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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| US10894600B2 (en) | 2017-07-06 | 2021-01-19 | Autel Robotics Co., Ltd. | Aircraft, tilt driving mechanism and control method thereof |
| GB2564473B (en) | 2017-07-13 | 2020-09-16 | Blue Bear Systems Res Ltd | Unmanned air vehicles |
| CN107672779A (en) * | 2017-10-16 | 2018-02-09 | 珠海天晴航空航天科技有限公司 | A kind of combined type multi-rotor unmanned aerial vehicle |
| CN108382590A (en) * | 2018-02-24 | 2018-08-10 | 浙江天遁航空科技有限公司 | Composite wing unmanned plane |
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| IT201900007857A1 (en) * | 2019-06-03 | 2020-12-03 | Massimo Lucchesini | Remotely piloted aircraft. |
| CN110406684A (en) * | 2019-08-05 | 2019-11-05 | 江苏心源航空科技有限公司 | A kind of tailstock formula vertical take-off and landing drone power device |
| CN111731475B (en) * | 2020-06-30 | 2022-12-02 | 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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