CN112977786B - Flexible tubular fuselage wing-group aircraft - Google Patents
Flexible tubular fuselage wing-group aircraft Download PDFInfo
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- CN112977786B CN112977786B CN202110264930.8A CN202110264930A CN112977786B CN 112977786 B CN112977786 B CN 112977786B CN 202110264930 A CN202110264930 A CN 202110264930A CN 112977786 B CN112977786 B CN 112977786B
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 38
- 239000011159 matrix material Substances 0.000 claims description 28
- 238000006243 chemical reaction Methods 0.000 claims description 13
- 239000010409 thin film Substances 0.000 claims description 11
- 238000004891 communication Methods 0.000 claims description 3
- 239000010408 film Substances 0.000 claims description 3
- 230000000007 visual effect Effects 0.000 claims 1
- 238000010521 absorption reaction Methods 0.000 abstract description 2
- 230000000694 effects Effects 0.000 abstract description 2
- 238000012423 maintenance Methods 0.000 description 7
- 230000003287 optical effect Effects 0.000 description 6
- 239000000463 material Substances 0.000 description 5
- 230000002427 irreversible effect Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 230000003139 buffering effect Effects 0.000 description 3
- 230000010355 oscillation Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
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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
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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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
- B64D47/00—Equipment not otherwise provided for
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- 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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
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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)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Manipulator (AREA)
- Battery Mounting, Suspending (AREA)
Abstract
The invention discloses a flexible tubular fuselage group wing aircraft, which comprises a flexible tubular fuselage, wherein the flexible tubular fuselage comprises more than two fuselage units which are sequentially connected end to end, the fuselage units are tubular, the pipe wall of each fuselage unit is provided with a flexible structural layer, each fuselage unit is provided with an electric rotor wing device, a flight control system and a power supply, the power supply is respectively connected with the electric rotor wing devices and the flight control system, and the flight control system is connected with the electric rotor wing devices. The aircraft with the flexible tubular fuselage and the group wings has the advantages that the fuselage of the aircraft with the flexible tubular fuselage and the group wings has an energy absorption effect when collision occurs, the damage to the fuselage is avoided, and the structural form of the fuselage can be reconstructed.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to a multi-rotor unmanned aerial vehicle.
Background
At present, most of unmanned aerial vehicles with multiple rotors have rigid fuselages, and common types include four rotors, six rotors, eight rotors and the like. These multi-rotor drones are ubiquitous with the following problems:
(1) Rigid fuselages are susceptible to damage. Unmanned aerial vehicle often can be because accidents such as collision, crash take place for misoperation, spare part inefficacy and external environment influence etc. in the flight process, therefore its rigidity fuselage takes place irreversible deformation, damage etc. very easily after the collision to lead to inevitable cost of maintenance. Secondly, a battery, an electronic speed regulator, a motor, various sensors and the like are arranged in the unmanned aerial vehicle body, and a rigid body structure cannot absorb energy when collision occurs, so that parts in the unmanned aerial vehicle body are easy to lose efficacy after being impacted, and the maintenance cost of the unmanned aerial vehicle is greatly improved;
(2) The fuselage structure is fixed and has no reconfigurability. Common many rotor unmanned aerial vehicle has just confirmed the structural style of fuselage at the beginning of the design, just can't change after the design. And this characteristic also has caused the unmanned aerial vehicle fuselage once damaged just can't continue to accomplish the flight task, must carry out maintenance and just can fly again.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a flexible tubular fuselage group wing aircraft, wherein the fuselage of the aircraft has an energy absorption function when in collision, the damage of the fuselage is avoided, and the structural form of the fuselage can be reconstructed.
The invention relates to a flexible tubular fuselage group wing aircraft, which comprises a flexible tubular fuselage, wherein the flexible tubular fuselage comprises more than two fuselage units which are sequentially connected end to end, the fuselage units are tubular, a flexible structure layer is arranged on the tube wall of each fuselage unit, an electric rotor wing device, a flight control system and a power supply are arranged on each fuselage unit, the power supply is respectively connected with the electric rotor wing device and the flight control system, and the flight control system is connected with the electric rotor wing device.
The invention relates to a flexible tubular fuselage group wing aircraft, wherein the tube wall of a fuselage unit comprises an inner matrix structure layer and an outer matrix structure layer which are both tubular, the inner matrix structure layer is positioned in the tube cavity of the outer matrix structure layer, a power supply is arranged between the inner matrix structure layer and the outer matrix structure layer, the power supply is a flexible thin film battery layer, the flexible thin film battery layer is connected with a battery manager, the flexible structure layer comprises an inner flexible structure layer and an outer flexible structure layer, the inner flexible structure layer is arranged on the inner tube wall of the inner matrix structure layer, and the outer flexible structure layer is arranged on the outer tube wall of the outer matrix structure layer.
The invention relates to a flexible tubular fuselage winged aircraft, wherein a flexible thin film battery layer comprises at least one flexible battery cell, and the flexible battery cell is connected with a battery manager.
The invention relates to a flexible tubular fuselage cluster wing aircraft, wherein two ends of each fuselage cell are provided with a power connector, each power connector comprises a positive terminal, a negative terminal and a common ground terminal, the positive terminal is connected with the positive pole of a flexible battery cell, the negative terminal is connected with the negative pole of the flexible battery cell, the common ground terminal is connected with the negative pole of the flexible battery cell, and power supplies on two adjacent mutually connected fuselage cells are connected in parallel through the power connectors.
The invention relates to a flexible tubular fuselage group wing aircraft, wherein one end of each fuselage unit is provided with a permanent magnet connector, the other end of each fuselage unit is provided with an electromagnet connector, and two adjacent fuselage units are connected through the permanent magnet connectors and the electromagnet connectors.
The invention relates to a flexible tubular fuselage group wing aircraft, wherein a flight control system comprises a flight controller and a sensor which are connected with each other, the flight controller is connected with an electric rotor wing device, and the flight controller is also connected with a battery manager.
The invention relates to a flexible tubular fuselage group wing aircraft, wherein sensors comprise an accelerometer, a gyroscope, a magnetic compass, a barometer, an ultrasonic sensor, a vision sensor and a satellite positioning sensor.
The invention relates to a flexible tubular fuselage group wing aircraft, wherein two ends of a fuselage unit are respectively provided with a photoelectric signal connector, the photoelectric signal connectors are connected with a power supply, each photoelectric signal connector comprises a photoelectric emitting module, a photoelectric receiving module and a photoelectric conversion module, the photoelectric receiving module is connected with the photoelectric conversion module, and the photoelectric conversion module is connected with a flight controller.
The invention relates to a flexible tubular fuselage winged aircraft, wherein the flight controller is connected with a master controller through a communication bus.
The invention relates to a flexible tubular fuselage group wing aircraft, wherein more than three electric rotor wing devices and flight control systems are arranged on a fuselage unit, the electric rotor wing devices and the flight control systems are arranged in a one-to-one correspondence manner, the flight control systems are connected with the corresponding electric rotor wing devices, the more than three electric rotor wing devices are arranged along the length direction of the fuselage unit, the more than three flight control systems are also arranged along the length direction of the fuselage unit, a permanent magnet connector and an electromagnet connector are connected in an inserting manner, a plug is arranged on the electromagnet connector, and a socket matched with the plug is arranged on the permanent magnet connector.
The flexible tubular fuselage wing-grouped aircraft is different from the prior art in that the flexible tubular fuselage comprises more than two fuselage units which are sequentially connected end to end, and the tube walls of the fuselage units are provided with flexible structural layers which can effectively reduce fuselage damage and irreversible deformation caused by aircraft collision, and meanwhile, the flexible structural layers have strong buffering and energy-absorbing functions, can effectively reduce impact and oscillation on parts in the collision process, and reduce time and manpower and material cost required by maintenance. Because each fuselage cell has electronic rotor device, flight control system and power, therefore, each fuselage cell is an independent flight cell, when a single or multiple fuselage cells break down, other fuselage cells can still fly normally; when the flexible tubular fuselage breaks, namely the fuselage is divided into two parts, each part after the breakage can be independently used as a complete aircraft, and the aircraft breaks again, namely the fuselage is divided into four parts, and so on, until the broken part does not have flight capability any more. It follows that the fuselage structural form of the invention can be reconfigured.
The invention will be further described with reference to the accompanying drawings.
Drawings
FIG. 1 is a front view of a flexible tubular fuselage cluster wing aircraft of the present invention;
FIG. 2 is a top view of the flexible tubular fuselage winged aircraft of the present invention;
FIG. 3 is a schematic view of the structure of the fuselage cell of the present invention;
FIG. 4 isbase:Sub>A cross-sectional view taken along line A-A of FIG. 3;
FIG. 5 is an enlarged view of a portion of FIG. 3 at B;
fig. 6 is a view showing a state of connection between two adjacent body units according to the present invention;
FIG. 7 is a schematic diagram of the parallel connection of the flexible battery cells of the various fuselage cells of the present invention;
fig. 8 is a diagram of a flight control network for a flexible tubular fuselage cluster wing aircraft of the present invention.
Detailed Description
As shown in fig. 1 and fig. 2-8, the flexible tubular fuselage group wing aircraft comprises a flexible tubular fuselage, the flexible tubular fuselage comprises more than two fuselage units 1 connected end to end in sequence, the fuselage units 1 are tubular, and the tube wall of the fuselage units 1 is provided with a flexible structural layer made of flexible materials. The aircraft body unit 1 is provided with an electric rotor wing device 2, a flight control system and a power supply. The power supply is connected with the electric rotor wing device 2 and the flight control system respectively (here, the connection is an electrical connection), that is, the power supply supplies power to the electric rotor wing device 2 and the flight control system. The flight control system is connected to (here, electrically connected to) the electric rotor apparatus 2, that is, the flight control system controls the operation of the electric rotor apparatus 2.
As shown in fig. 1 and 2, the flexible tubular fuselage, as an aircraft body structure, can be bent and deformed in various directions. Each electronic rotor device 2 is linear dispersion and installs on flexible tubulose fuselage, arranges along the length direction of flexible tubulose fuselage promptly, and electronic rotor device 2 is prior art, and its specific structure is not repeated herein. The flight control system is also installed on the flexible tubular fuselage in a linear dispersed manner, namely arranged along the length direction of the flexible tubular fuselage.
As shown in fig. 3 and in combination with fig. 4 and 5, the flexible tubular fuselage cluster wing aircraft of the present invention includes a tubular inner matrix structure layer 104 and a tubular outer matrix structure layer 103 on the wall of the fuselage cell 1, where the inner matrix structure layer 104 and the outer matrix structure layer 103 are both made of a material with a certain rigidity. The inner matrix structure layer 104 is located in a tube cavity of the outer matrix structure layer 103, a power supply is arranged between the inner matrix structure layer 104 and the outer matrix structure layer 103, the power supply is a flexible thin film battery layer 105, and the flexible thin film battery layer 105 is connected with the battery manager 6 (here, the connection is an electrical connection). The flexible thin film battery layer 105 is a conventional one, and the detailed structure and operation principle thereof are not described in detail. The flexible thin film battery layer 105 is arranged between the inner matrix structure layer 104 and the outer matrix structure layer 103 in an adhesion mode. Both the inside and the outside of the lumen of the fuselage cell 1 can serve as load-bearing areas.
The flexible structure layer comprises an inner flexible structure layer 102 and an outer flexible structure layer 101, wherein the inner flexible structure layer 102 is arranged on the inner pipe wall of the inner base structure layer 104 in a bonding mode, and the outer flexible structure layer 101 is also arranged on the outer pipe wall of the outer base structure layer 103 in a bonding mode. The outer flexible structure layer 101, the outer matrix structure layer 103, the flexible thin film battery layer 105, the inner matrix structure layer 104 and the inner flexible structure layer 102 form a sandwich structure together.
As shown in fig. 3, the flexible tubular fuselage winged aircraft of the present invention, wherein the flexible thin film battery layer 105 comprises at least one flexible battery cell, which is connected to the battery manager 6. When the number of the flexible battery cells is more than two, the number of the battery managers 6 is more than two, the number of the flexible battery cells is the same as that of the battery managers 6, the flexible battery cells and the battery managers 6 are arranged in a one-to-one correspondence mode, and each flexible battery cell is connected with the corresponding battery manager 6. The battery manager 6 controls the charging and external power supply of the flexible battery unit, and detects the electric quantity and the working state of the flexible battery unit. The flexible battery and the battery manager 6 are prior art, and detailed descriptions of the structure and operation principle thereof are omitted.
As shown in fig. 6, the flexible tubular fuselage cluster wing aircraft of the present invention is provided with power connectors at both ends of the fuselage cells 1, wherein the power connectors include a positive terminal 11, a negative terminal 13 and a common ground terminal 12, the positive terminal 11 is connected with (connected as electrically connected to) the positive pole of the flexible battery cell, the negative terminal 13 is connected with (connected as electrically connected to) the negative pole of the flexible battery cell, the common ground terminal 12 is connected with (connected as electrically connected to) the negative pole of the flexible battery cell, and the power sources on two adjacent interconnected fuselage cells 1 are connected in parallel through the power connectors.
In the case of one body unit 1 provided with two or more flexible battery cells, the positive electrodes of the two or more flexible battery cells are all connected to the positive terminal 11 (here, connected electrically), the negative electrodes are all connected to the negative terminal 13 (here, connected electrically), and the negative electrodes are also all connected to the common ground terminal 12 (here, connected electrically), whereby it can be seen that the two or more flexible battery cells are arranged in parallel by being connected to the positive terminal 11, the negative terminal 13, and the common ground terminal 12.
After the two body units 1 are connected, the two body units 1 are referred to as a first body unit and a second body unit, a positive terminal 11 of a first body unit connection terminal (the terminal connected to the second body unit) is connected to a positive terminal 11 of a second body unit connection terminal (the terminal connected to the first body unit), a negative terminal 13 of the first body unit connection terminal is connected to a negative terminal 13 of the second body unit connection terminal, and a common ground terminal 12 of the first body unit connection terminal is connected to a common ground terminal 12 of the second body unit connection terminal. This connects the power supplies of the first body unit and the second body unit in parallel.
As shown in fig. 7, after the three body units 1 are connected, the three body units 1 are referred to as a first body unit, a second body unit, and a third body unit, positive terminals 11 at both ends of the second body unit are connected to positive terminals 11 of connection ends of the first body unit and the third body unit (the ends are connected to the second body unit), respectively, negative terminals 13 at both ends of the second body unit are connected to negative terminals 13 of the connection ends of the first body unit and the third body unit, respectively, and common ground terminals 12 at both ends of the second body unit are connected to common ground terminals 12 of the connection ends of the first body unit and the second body unit, respectively. Two flexible battery units are provided in each of the first body unit, the second body unit, and the third body unit. Positive terminals 11 (two positive terminals 11 are provided and are respectively located at two ends of the first body unit) on the first body unit are respectively connected to the positive electrodes of the first flexible battery unit and the second flexible battery unit, negative terminals 13 (two negative terminals 13 are provided and are respectively located at two ends of the first body unit) on the first body unit are respectively connected to the negative electrodes of the first flexible battery unit and the second flexible battery unit, and common ground terminals 12 (two common ground terminals 12 are provided and are respectively located at two ends of the first body unit) on the first body unit are respectively connected to the negative electrodes of the first flexible battery unit and the second flexible battery unit. Positive terminals 11 (two positive terminals 11 are provided, and are respectively located at two ends of the second body unit) on the second body unit are respectively connected to the positive electrodes of the third flexible battery unit and the fourth flexible battery unit, negative terminals 13 (two negative terminals 13 are provided, and are respectively located at two ends of the second body unit) on the second body unit are respectively connected to the negative electrodes of the third flexible battery unit and the fourth flexible battery unit, and common ground terminals 12 (two common ground terminals 12 are provided, and are respectively located at two ends of the second body unit) on the second body unit are respectively connected to the negative electrodes of the third flexible battery unit and the fourth flexible battery unit. Positive terminals 11 (two positive terminals 11 are provided, and are respectively located at two ends of the third body unit) on the third body unit are respectively connected to the positive electrodes of the fifth flexible battery unit and the sixth flexible battery unit, negative terminals 13 (two negative terminals 13 are provided, and are respectively located at two ends of the third body unit) on the third body unit are respectively connected to the negative electrodes of the fifth flexible battery unit and the sixth flexible battery unit, and common ground terminals 12 (two common ground terminals 12 are provided, and are respectively located at two ends of the third body unit) on the third body unit are respectively connected to the negative electrodes of the fifth flexible battery unit and the sixth flexible battery unit. It follows that the two flexible battery cells in the first body unit are arranged in parallel, as are the two flexible battery cells in the second and third body units. In this way, the first, second and third fuselage cells are connected in parallel via the power supply connectors with their respective power supplies, that is to say, the first, second, third, fourth, fifth and sixth flexible battery cells are arranged in parallel, so as to build up a dc bus supply network for the entire group-wing aircraft. Therefore, the power supplies of the fuselage units 1 are arranged in parallel, namely the flexible battery units of the power supplies are arranged in parallel, so that the problem that the whole power supply network is not influenced to supply power to the aircraft in order to prevent one flexible battery unit from being broken down is solved, and the normal flight of the aircraft is ensured.
As for the change of the number of the body units 1 and the number of the flexible battery units included in the flexible thin film battery layer 105, the principle is the same as that of the three body units 1 connected to each other, and the description thereof is omitted.
As shown in fig. 3 and fig. 6, the flexible tubular fuselage group-wing aircraft of the invention is characterized in that one end of each fuselage cell 1 is provided with a permanent magnet connector 7, the other end of each fuselage cell 1 is provided with an electromagnet connector 5, and two adjacent fuselage cells 1 are connected through the permanent magnet connectors 7 and the electromagnet connectors 5. The individual fuselage units 1 can be connected structurally as a flexible tubular fuselage by means of the permanent magnet connectors 7 and the electromagnet connectors 5. By switching the pole direction of the electromagnet connector 5, the connection and separation of two adjacent body units 1 can be realized. In this embodiment, the permanent magnet connector 7 and the electromagnet connector 5 are connected in a plugging manner, that is, a plug is arranged on the electromagnet connector 5, and a socket matched with the plug is arranged on the permanent magnet connector 7.
As shown in fig. 1 and 2, the flexible tubular fuselage cluster wing aircraft of the invention, wherein the flight control system comprises a flight controller 4 and a sensor 3 which are connected with each other, the flight controller 4 is connected with an electric rotor device 2, and the flight controller 4 is also connected with a battery manager 6. The connections are all electrical connections.
The invention relates to a flexible tubular fuselage winged aircraft, wherein the sensors 3 comprise an accelerometer, a gyroscope, a magnetic compass, a barometer, an ultrasonic sensor, a vision sensor and a satellite positioning sensor.
As shown in fig. 6, the flexible tubular fuselage winged aircraft of the present invention has a photoelectric signal connector at each of two ends of the fuselage cell 1, and the photoelectric signal connector is connected to a power supply (where the connection is an electrical connection), that is, the power supply supplies power to the photoelectric signal connector. The photoelectric signal connector comprises a photoelectric transmitting module 8, a photoelectric receiving module 9 and a photoelectric conversion module 10, wherein the photoelectric receiving module 9 is connected with the photoelectric conversion module 10 (here, the connection is electric connection), and the photoelectric conversion module 10 is connected with the flight controller 4 (here, the connection is electric connection). When the two fuselage cells 1 are joined together, one of the fuselage cells 1 is referred to as the fourth fuselage cell and the other fuselage cell 1 is referred to as the fifth fuselage cell. The photoemission module 8 of the fourth body unit connection end (the end connected to the fifth body unit) is arranged opposite to the photoemission module 9 of the fifth body unit connection end (the end connected to the fourth body unit), and the photoemission module 9 of the fourth body unit connection end is arranged opposite to the photoemission module 8 of the fifth body unit connection end. At this time, the photoelectric emission module 8 of the fourth body unit connection end emits the first optical signal to the photoelectric reception module 9 of the fifth body unit connection end, the photoelectric reception module 9 of the fifth body unit connection end receives the first optical signal and transfers it to the photoelectric conversion module 10 of the fifth body unit connection end, and the photoelectric conversion module 10 of the fifth body unit connection end converts the first optical signal into the first electrical signal and transfers it to the flight controller 4 of the fifth body unit; meanwhile, the photoelectric emission module 8 of the fifth body unit connection end emits the second optical signal to the photoelectric reception module 9 of the fourth body unit connection end, the photoelectric reception module 9 of the fourth body unit connection end receives the second optical signal and transfers it to the photoelectric conversion module 10 of the fourth body unit connection end, and the photoelectric conversion module 10 of the fourth body unit connection end converts the second optical signal into the second electrical signal and transfers it to the flight controller 4 of the fourth body unit. That is, when the flight controllers 4 of the fourth and fifth body units simultaneously receive the electrical signal (i.e., the flight controller 4 of the fourth body unit receives the second electrical signal, and the flight controller 4 of the fifth body unit receives the first electrical signal), it can be determined that the fourth and fifth body units are in the connected state. In contrast, when the flight controllers 4 of the fourth and fifth body units cannot receive the electric signal, it can be judged that the fourth and fifth body units are in the separated state. It can be seen that the signal and command transmission of the aircraft is realized by the photoelectric signal connector connected to the control network between the fuselage cells 1.
As shown in fig. 8, the flexible tubular fuselage cluster wing aircraft of the invention, wherein the flight controller 4 is connected with a general controller (not shown in the figure) through a communication bus 14, forms a flight control network. In fig. 8, the battery manager 6 is connected to the electric rotor apparatus 2, and it means that the battery manager 6 controls the power supply (i.e., the flexible film battery layer 105) of the electric rotor apparatus 2.
As shown in fig. 1 and 2, the flexible tubular fuselage cluster-wing aircraft of the present invention is provided with three or more electric rotor devices 2 and three or more flight control systems on the fuselage unit 1, wherein the electric rotor devices 2 and the flight control systems are arranged in a one-to-one correspondence, the flight control systems are connected to the corresponding electric rotor devices 2, the three or more electric rotor devices 2 are arranged along the length direction of the fuselage unit 1, and the three or more flight control systems are also arranged along the length direction of the fuselage unit 1. In this embodiment, the flexible tubular fuselage cluster wing aircraft comprises three fuselage units 1 connected end to end in sequence, wherein three electric rotor devices 2 are arranged on each fuselage unit 1, and the three electric rotor devices 2 are connected with the fuselage units 1 in a linear arrangement, i.e. arranged along the length direction of the fuselage units 1.
For one fuselage cell 1, the various sensors 3 in each flight control system are connected to the flight controller 4 in that flight control system, the respective electric rotor apparatuses 2 are connected to the respective flight controllers 4 in the flight control system, and the battery manager 6 is also connected to the flight controller 4, so that the sensors 3, the electric rotor apparatuses 2, and the battery manager 6 are all connected to the flight control network.
The flexible tubular fuselage wing-grouped aircraft is different from the prior art in that the flexible tubular fuselage comprises more than two fuselage units 1 which are sequentially connected end to end, and the tube wall of the fuselage units 1 is provided with a flexible structural layer, so that the flexible structural layer can effectively reduce fuselage damage and irreversible deformation caused by aircraft collision, has stronger buffering and energy-absorbing functions, can effectively reduce impact and oscillation on parts in the collision process, and reduces time and manpower and material cost required by maintenance. Because each fuselage cell 1 is provided with an electric rotor device 2, a flight control system and a power supply, each fuselage cell 1 is an independent flight cell, and when one or more fuselage cells 1 are in failure, other fuselage cells 1 can still fly normally; when the flexible tubular fuselage breaks, namely the fuselage is divided into two parts, each part after the breakage can be independently used as a complete aircraft, and the aircraft breaks again, namely the fuselage is divided into four parts, and so on, until the broken part does not have flight capability any more. It follows that the fuselage structural form of the invention can be reconfigured.
The invention has the following beneficial effects:
(1) The group wing configuration enables the aircraft to have extremely high reliability, and when a single or a plurality of electric rotor wing devices 2 break down, the aircraft can continue to complete a preset flight task or return flight maintenance;
(2) The flexible fuselage structure can effectively reduce fuselage damage and irreversible deformation caused by aircraft collision, has strong buffering and energy-absorbing effects, can effectively reduce impact and oscillation on parts in the collision process, and reduces time, manpower and material cost required by maintenance;
(3) The flexible fuselage unit 1 enables the aircraft to have extremely strong reconfigurability, and normal flight of the aircraft cannot be influenced when a single flexible fuselage unit 1 breaks down or even when the flexible tubular fuselage breaks. When a single or multiple flexible fuselage cells 1 fail, the aircraft still has the ability to complete the flight mission; when the flexible tubular fuselage breaks, namely the fuselage is divided into two parts, each part after the breakage can be independently used as a complete aircraft, and the aircraft breaks again, namely the fuselage is divided into four parts, and so on, until the broken part does not have flight capability any more.
The above-described embodiments are merely illustrative of the preferred embodiments of the present invention, and do not limit the scope of the present invention, and various modifications and improvements made to the technical solution of the present invention by those skilled in the art without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.
Claims (9)
1. A flexible tubular fuselage cluster wing aircraft, characterized in that: comprises a flexible tubular body, the flexible tubular body comprises more than two body units which are sequentially connected end to end, the body units are tubular, the pipe wall of the body unit is provided with a flexible structure layer, the body unit is provided with an electric rotor wing device, a flight control system and a power supply, the power supply is respectively connected with the electric rotor wing device and the flight control system, the flight control system is connected with the electric rotor wing device,
the pipe wall of fuselage cell is including all being pipy interior matrix structure layer and outer matrix structure layer, interior matrix structure layer is located the lumen of outer matrix structure layer, be equipped with the power between interior matrix structure layer and the outer matrix structure layer, the power is flexible film battery layer, flexible film battery layer is connected with the battery manager, flexible structure layer includes interior flexible structure layer and outer flexible structure layer, interior flexible structure layer is located on the interior pipe wall of interior matrix structure layer, outer flexible structure layer is located on the outer pipe wall of outer matrix structure layer.
2. The flexible tubular fuselage cluster wing aircraft of claim 1, wherein: the flexible thin film battery layer includes at least one flexible battery cell connected with the battery manager.
3. The flexible tubular fuselage cluster wing aircraft of claim 2, wherein: the two ends of the machine body unit are respectively provided with a power connector, each power connector comprises a positive terminal, a negative terminal and a common ground terminal, the positive terminal is connected with the positive pole of the flexible battery unit, the negative terminal is connected with the negative pole of the flexible battery unit, the common ground terminal is connected with the negative pole of the flexible battery unit, and power supplies on two adjacent mutually connected machine body units are connected in parallel through the power connectors.
4. The flexible tubular fuselage cluster wing aircraft of claim 3, wherein: one end of each machine body unit is provided with a permanent magnet connector, the other end of each machine body unit is provided with an electromagnet connector, and every two adjacent machine body units are connected through the permanent magnet connectors and the electromagnet connectors.
5. The flexible tubular fuselage cluster wing aircraft of claim 4, wherein: the flight control system comprises a flight controller and a sensor which are connected with each other, the flight controller is connected with the electric rotor wing device, and the flight controller is also connected with the battery manager.
6. The flexible tubular fuselage cluster wing aircraft of claim 5, wherein: the sensors include accelerometers, gyroscopes, magnetic compasses, barometers, ultrasonic sensors, visual sensors and satellite positioning sensors.
7. The flexible tubular fuselage cluster wing aircraft of claim 6, wherein: the aircraft is characterized in that photoelectric signal connectors are arranged at two ends of the aircraft body unit and connected with a power supply, each photoelectric signal connector comprises a photoelectric emitting module, a photoelectric receiving module and a photoelectric conversion module, each photoelectric receiving module is connected with the corresponding photoelectric conversion module, and each photoelectric conversion module is connected with the corresponding aircraft controller.
8. The flexible tubular fuselage cluster wing aircraft of claim 7, wherein: the flight controller is connected with the master controller through a communication bus.
9. The flexible tubular fuselage cluster wing aircraft of claim 8, wherein: electric rotor device and flight control system in the fuselage unit all establish to more than three, electric rotor device and flight control system one-to-one arrange, flight control system is connected with corresponding electric rotor device, three more electric rotor device arranges along the length direction of fuselage unit, three more flight control system also arranges along the length direction of fuselage unit, permanent magnet connector and electromagnet connector are connected through the mode of pegging graft, be equipped with the plug on the electromagnet connector, be equipped with on the permanent magnet connector with plug assorted socket.
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| US6308912B1 (en) * | 1997-10-21 | 2001-10-30 | Natural Colour Kari Kirjavainen Oy | Rotorcraft |
| CN102602540A (en) * | 2011-12-26 | 2012-07-25 | 华南师范大学 | Solar electric helicopter |
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