CN117342019A - Variable chord length full-wing type tilting rotor solar unmanned aerial vehicle - Google Patents
Variable chord length full-wing type tilting rotor solar unmanned aerial vehicle Download PDFInfo
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- CN117342019A CN117342019A CN202311503504.0A CN202311503504A CN117342019A CN 117342019 A CN117342019 A CN 117342019A CN 202311503504 A CN202311503504 A CN 202311503504A CN 117342019 A CN117342019 A CN 117342019A
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- 230000007613 environmental effect Effects 0.000 claims 1
- 238000005516 engineering process Methods 0.000 abstract description 8
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 6
- 230000008901 benefit Effects 0.000 description 5
- 238000005265 energy consumption Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 238000011161 development Methods 0.000 description 4
- 230000002457 bidirectional effect Effects 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 230000010363 phase shift Effects 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
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Classifications
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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
- B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/20—Vertical take-off and landing [VTOL] aircraft
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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
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
- B64U30/295—Rotors arranged in the 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
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
- B64U30/296—Rotors with variable spatial positions relative to the UAV body
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/30—Supply or distribution of electrical power
- B64U50/31—Supply or distribution of electrical power generated by photovoltaics
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Abstract
The invention discloses a variable-chord-length all-wing type tilting rotor solar unmanned aerial vehicle, which comprises three sections of wings, a fuselage, rotors, solar panels, an energy storage system and a tilting mechanism, wherein the three sections of wings are formed by splicing wings with two chord lengths, the solar panels are paved on the upper surfaces of the wings, and the energy storage system in the wings is charged; the four rotors are respectively arranged at the position, close to the front edge and the position, close to the rear edge, of the main wing through the tilting mechanism, and the front rotor tilts upwards and then the front rotor tilts downwards when the front flying switch is vertical. The invention combines the existing tilting rotor unmanned aerial vehicle technology and solar power technology, has the characteristics of a solar unmanned aerial vehicle and a tilting rotor unmanned aerial vehicle, and has the characteristics of quick cruising flight, long endurance, no pollution, vertical take-off and landing, hovering and the like.
Description
Technical Field
The invention relates to a solar unmanned aerial vehicle, and belongs to the technical field of aerospace.
Background
Tiltrotor aircraft is an aircraft of variable flight mode that combines the advantages of both fixed-wing aircraft and gyroplanes. Compared with a fixed wing aircraft, the aircraft can take off and land vertically, has low requirements on runways and has better field adaptability; compared with the conventional helicopter, the helicopter has the advantages of higher cruising speed and farther voyage, smaller vibration, lower fuel consumption and larger carrying capacity. Furthermore, tiltrotor aircraft have a wider flight envelope than helicopters and fixed wing aircraft. With the continuous development and wide application of unmanned aerial vehicle technology, the tilt rotor technology is also widely applied to the unmanned aerial vehicle field. The tilting rotor unmanned aerial vehicle takes off and land swiftly, flight speed is fast, the payload is big, can hover and carry out the task, can wide application in many task scenes such as unmanned aerial vehicle commodity circulation, agricultural plant protection, electric power inspection, reconnaissance, and application prospect is wide. Tiltrotors can be divided into two categories by the number of rotors: dual-rotor tiltrotors (typically represented by V-22 in the united states) and quad-rotor tiltrotors (typically represented by blue whales and V380 in china). In the military field, the tilting rotor unmanned aerial vehicle utilizes the performance advantages thereof, and is mostly applied to combat occasions such as special army combat and offshore combat. Because of strong maneuverability and long voyage, the method provides great convenience for task execution under severe combat environment. In addition, the device is applied to the ocean combat action, so that the coverage of the air combat can be greatly improved, and the combat force of the army is improved to a certain extent. In the civil field, the efficient performance advantage of the tilt rotor unmanned aerial vehicle saves a large amount of cost, and has considerable application value in unmanned aerial vehicle transportation. Thus, tiltrotor aircraft may be a typical model of a logistical unmanned aircraft. And the two logistics tap enterprises of Shunfeng and Beijing east for trial flight are completed in the present year, and the tilting rotor unmanned aerial vehicle is adopted as one of main models for the research and development of the logistics unmanned aerial vehicle.
The development of high-altitude ultra-long-endurance unmanned aerial vehicle is paid unprecedented attention worldwide, and in order to meet urgent requirements of persistent monitoring, various types of unmanned aerial vehicles are proposed in multiple countries, wherein energy and power are extremely critical, and the unmanned aerial vehicle is a bottleneck of development of the endurance capability of the unmanned aerial vehicle. Solar energy is an effective energy solution in the future of unmanned aerial vehicles, and solar energy unmanned aerial vehicles with ultra-long endurance convert light energy into electric energy by utilizing solar cells, wherein one part of the solar energy is used for daytime cruising, the other part of the solar energy is stored in an energy storage system and used for night cruising, and the bottleneck of 'permanent' flight which cannot be realized by conventional unmanned aerial vehicles is broken theoretically, so that the solar unmanned aerial vehicle becomes a hot spot for unmanned aerial vehicle field research in recent years. The unmanned aerial vehicle has the characteristics of no pollution and long navigation time, and can be widely applied to the military and civil fields of earth observation, air early warning, reconnaissance monitoring, communication relay and the like. Compared with a satellite, the satellite has the advantages of small signal transmission loss and high precision, can realize permanent residence of a target area, has no problem of a reentry cycle, and has low production and operation cost; compared with the traditional aircraft, the aircraft has wide coverage area and long air-time; compared with aerostat, the aerostat has good operability and strong maneuverability. In future war, the solar unmanned aerial vehicle with ultra-long endurance plays an important role in space attack and defense and information countermeasure, becomes an important supplement for air strength, and further promotes the integrated development of air and sky.
However, the solar unmanned aerial vehicle under research at present is a fixed wing type, and cannot realize vertical take-off, landing and hovering; at present, a four-axis tilting rotor aircraft generally adopts a fuel engine, and long-endurance flight cannot be realized.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, provides a variable chord length all-wing type tilting rotor solar unmanned aerial vehicle, combines the existing tilting rotor unmanned aerial vehicle technology and solar power technology, has the characteristics of the solar unmanned aerial vehicle and the tilting rotor unmanned aerial vehicle, and has the characteristics of fast cruising flight, long voyage, no pollution, vertical take-off and landing, hovering and the like.
The technical scheme adopted for solving the technical problems is as follows:
a variable chord length full-wing type tilting rotor solar unmanned aerial vehicle comprises three sections of wings, a fuselage, a rotor, a solar panel, an energy storage system and a tilting mechanism.
The three-section wing is formed by splicing two kinds of wings with chord length, and a solar panel is paved on the upper surface of the wing to charge an energy storage system in the wing; the four rotors are respectively arranged at the position, close to the front edge and the position, close to the rear edge, of the main wing through the tilting mechanism, and when the front flying is switched to be vertical, the front rotor tilts upwards and then the rear rotor tilts downwards.
The section shape of the three-section wing, which is vertical to the front edge, meets the aerofoil structure requirement of the glider, and can generate upward lifting force.
The fuselage with the idler wheels is arranged under the three-section wing, so that the lifting requirement can be met.
The three-section wing adopts a frame structure, and the frame is made of carbon fibers.
The rotor wing is driven by a brushless direct current motor.
The beneficial effects of the invention are as follows:
(1) Vertical take-off and landing and hovering. At present, the solar unmanned aerial vehicle under research is all fixed wing type, can't realize vertical take-off and land and hover in midair, and operational environment restriction is more, adopts the rotor that verts can realize vertical take-off and land and hover in midair function easily, promotes place adaptability, satisfies complicated place and takes-off and land the demand.
(2) And (5) long endurance. Solar energy is used as energy, so that the energy can be supplemented in the flight process; the rotor wing is driven by adopting the direct current motor, and the energy conversion efficiency is far higher than that of a fuel engine. Theoretically, if the conversion efficiency of the solar cell panel is high enough, the energy storage system can realize uninterrupted flight under the condition of large enough capacity per unit weight and reasonable structural weight.
(3) By adopting the variable chord length three-section wing layout, not only the induced resistance can be reduced, but also the purposes of reducing weight and fully utilizing structural strength can be achieved to a great extent by reasonably arranging the strength of each part of the wing on the premise of meeting the requirement of the pavement.
(4) Adopt full wing formula overall arrangement, not only its surface lighting area of effectual increase and battery accommodation can also improve unmanned aerial vehicle flight aerodynamic characteristics, combines rotor system that verts simultaneously, can guarantee that wing fuselage is in better flight condition all the time, improves unmanned aerial vehicle flight in-process's aerodynamic lift, reduces unmanned aerial vehicle's energy consumption, increases its duration.
Drawings
FIG. 1 is a schematic diagram of the present invention;
FIG. 2 is a schematic diagram of the operation of a solar energy system;
in the figure, the three-section wing comprises a 1-section wing body, a 2-rotor wing, a 3-solar panel, a 4-energy storage system, a 5-energy management system, a 6-automatic flight control system, a 7-airframe with rollers, an 8-tilting mechanism and a 9-wing tip winglet.
Detailed Description
The invention will now be described in further detail with reference to the accompanying drawings and specific examples, which include but are not limited to the following examples.
The invention provides a variable chord length full-wing type tilting rotor solar unmanned aerial vehicle, which combines a tilting rotor unmanned aerial vehicle technology and a solar power technology, and mainly comprises three sections of wings, a rotor wing, a solar cell panel, an energy storage system, an energy management system, an automatic flight control system, a fuselage with rollers, a tilting mechanism, a wing tip winglet and the like, wherein the structure is shown in figure 1, the working principle of the solar system is shown in figure 2, an implementation circuit of the energy management system is a BBB integrated three-port converter circuit for voltage rising and falling and energy transmission, and a PWM (pulse width modulation) and double phase shift control strategy is adopted to control the bidirectional energy transmission of the circuit (the PWM and double phase shift control bidirectional Buck-Boost integrated three-port DC-DC converter is referred to in detail as Sun Xiaofeng, shen Yanfeng and Huo Qingying, solar school report and 2016 (05): 1180-1189). The three-section wing comprises a main wing arranged in the middle and two ailerons symmetrically arranged on two sides of the main wing. The wing tip winglet is arranged at two ends of the three-section wing.
The three-section wing adopts a frame structure, and the frame is made of carbon fibers, so that the structural strength is ensured, and the weight is reduced. Different from the straight wings of the traditional solar unmanned aerial vehicle, the three-section wing is formed by splicing wings with two chord length sizes, the structure is more compact, and the structural strength can be more fully utilized. The surface skin, the three-section wing profile (section shape) is an asymmetric concave wing, the lift coefficient is large, the three-section wing can generate larger lift in the unmanned aerial vehicle flight process, and the energy consumption is reduced. The rotor is distributed at the four corners of main wing, is connected with tilting mechanism, and the rotor is driven by brushless DC motor, through brushless DC motor's rotation drive rotor rotation, provides flight power. The solar cell panel is paved on the surface of the three sections of wings, and absorbs the energy of solar radiation and converts the energy into electric energy. The energy management system can adjust the flight state and the energy supply form according to the factors such as ambient light conditions, flight height, wind direction and the like so as to achieve the purpose of increasing the duration, when the electric energy converted by the solar cell panel is larger than the electric energy consumed for maintaining the unmanned aerial vehicle in the flight state, for example, the output power of a motor can be increased when sunlight is strong, the flight attitude is adjusted, the unmanned aerial vehicle can fly to a higher height and a higher speed, the energy storage system is charged, and the energy waste is reduced; when the electric energy converted by the solar cell panel is insufficient to maintain the unmanned aerial vehicle in a flight state, for example, the night illumination is insufficient, the output power of the motor is properly reduced, the flight attitude is adjusted, the flight height of the unmanned aerial vehicle is reduced, the potential energy of the unmanned aerial vehicle is converted into the flight kinetic energy, the energy consumption of an energy storage system is reduced, the energy storage system outputs the electric energy, and the stable flight of the unmanned aerial vehicle is realized. The energy management system is realized by selecting a PWM plus double phase shift control bidirectional Buck-Boost integrated three-port DC-DC converter. The energy storage system is installed in the three-section wing and is used for storing and outputting electric energy. The energy storage system can be charged on the ground, and can be fully charged before flying, so that the endurance time can be effectively prolonged. The automatic flight control system is a core part of the unmanned aerial vehicle, realizes self-stabilization and task functions by controlling the rotation speed of a motor and the tilting angle of a tilting mechanism, and is installed inside the three-section wing together with the energy management system. The machine body with the rollers adopts a form similar to an undercarriage of an airplane and is used for ground parking support or running takeoff of an unmanned plane. The tilting mechanism is used for adjusting the angle of the rotor wing in a certain range, so that the unmanned aerial vehicle is switched between a vertical mode and a horizontal flight mode and the flight attitude of the unmanned aerial vehicle is adjusted.
The working modes of the automatic flight control system and the energy management system are as follows:
firstly, fully charging a battery on the ground, outputting high power by an energy management system during take-off, improving the rotating speed of a rotor wing to promote thrust, adjusting the tilting angle of the rotor wing and the attack angle of the unmanned aerial vehicle by an automatic flight control system through a tilting mechanism, and ensuring the rapid take-off of the unmanned aerial vehicle under the combined action of aerodynamic force and thrust generated by the rotor wing; when the unmanned aerial vehicle quickly climbs to a certain height, the energy output and the attack angle of the unmanned aerial vehicle are adjusted to enable the unmanned aerial vehicle to slowly climb, meanwhile, solar cells on the surface of the wing absorb solar energy and convert the solar energy into electric energy to charge an energy storage system, an automatic flight control system and an energy management system work in a coordinated mode, and the energy input is larger than the energy output under the condition that illumination is sufficient, and the energy storage system is in a charged state; at night, the energy consumption is reduced by descending by gliding. Through the above-mentioned circulation work, realize unmanned aerial vehicle's long-time duration.
The chord-length-variable full-wing type tilting rotor solar unmanned aerial vehicle provided by the embodiment of the invention has the wing area of 1.96m 2 Total weight 5kg, wherein energy storage system weight 0.5kg, equipped with 4 single power 330w brushless dc motors. The solar cell panel is fully paved on the upper surface of the three sections of wings, the maximum electric energy generation power is 320w, and the maximum capacity of the energy storage system is 5300mAh. Before taking off, the battery is fully charged on the ground, the taking off time is preferably at the morning, 4 motors work together, so that the unmanned aerial vehicle takes off vertically at the speed of 3m/s, when the flying height reaches more than 3000m, the flying posture is adjusted, the flying is mainly carried out, the battery slowly rises, the motor outputs about 30% of power until the unmanned aerial vehicle flies to the positionAfter the height of 5000m, the motor keeps flying flatly, and the output power of the motor is reduced to 20 percent. In the process, the solar panels on the surfaces of the three sections of wings absorb solar energy to charge the energy storage system, and in the flat flight section, the energy consumed by the motor is smaller than the energy converted by the solar panels, and the energy storage system is in a slow charging state until the energy storage system is full and is always in a full-electricity state. When the solar energy is at night, the output power of the motor is reduced to about 15%, the unmanned aerial vehicle keeps descending slowly, so that the energy consumption is reduced, the solar energy can continue to rise until the solar energy reaches a certain intensity, and the solar energy can realize long-time cruising through circulation.
Claims (6)
1. The utility model provides a full wing formula of variable chord rotor solar unmanned aerial vehicle that verts, includes three sections wings, fuselage, rotor, solar cell panel, energy storage system and tilting mechanism, its characterized in that: the three-section wing is formed by splicing two wings with chord length, and specifically comprises a main wing in the middle and two ailerons symmetrically arranged on two sides of the main wing; the solar cell panel is paved on the upper surface of the wing and is used for charging an energy storage system arranged in the wing; the four rotors are respectively arranged on the main wing close to the front edge and the rear edge through the tilting mechanism, and when the unmanned aerial vehicle is switched from forward flight to vertical, the rotor arranged at the front edge tilts upwards and the rotor arranged at the rear edge tilts downwards; the machine body is provided with rollers and is arranged at the lower part of the three-section wing.
2. The variable chord full wing tilt rotor solar unmanned aerial vehicle of claim 1, wherein: the section shape of the three-section wing, which is vertical to the front edge, meets the aerofoil structure requirement of the glider, and can generate upward lifting force.
3. The variable chord full wing tilt rotor solar unmanned aerial vehicle of claim 1, wherein: wing tip winglets are arranged at two ends of the three-section wing.
4. The variable chord full wing tilt rotor solar unmanned aerial vehicle of claim 1, wherein: the three-section wing adopts a frame structure, and the frame is made of carbon fibers.
5. The variable chord full wing tilt rotor solar unmanned aerial vehicle of claim 1, wherein: the rotor wing is driven by a brushless direct current motor.
6. The variable chord full wing tilt rotor solar unmanned aerial vehicle of claim 1, wherein: the unmanned aerial vehicle energy management system is used for adjusting the flight state and the energy supply form of the unmanned aerial vehicle according to environmental factors, so that the purpose of increasing the duration of the unmanned aerial vehicle is achieved.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311503504.0A CN117342019A (en) | 2023-11-13 | 2023-11-13 | Variable chord length full-wing type tilting rotor solar unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311503504.0A CN117342019A (en) | 2023-11-13 | 2023-11-13 | Variable chord length full-wing type tilting rotor solar unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN117342019A true CN117342019A (en) | 2024-01-05 |
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| CN202311503504.0A Pending CN117342019A (en) | 2023-11-13 | 2023-11-13 | Variable chord length full-wing type tilting rotor solar unmanned aerial vehicle |
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| CN (1) | CN117342019A (en) |
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- 2023-11-13 CN CN202311503504.0A patent/CN117342019A/en active Pending
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