CN116788534A - Pneumatic layout of large solar unmanned aerial vehicle - Google Patents
Pneumatic layout of large solar unmanned aerial vehicle Download PDFInfo
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- CN116788534A CN116788534A CN202310978286.XA CN202310978286A CN116788534A CN 116788534 A CN116788534 A CN 116788534A CN 202310978286 A CN202310978286 A CN 202310978286A CN 116788534 A CN116788534 A CN 116788534A
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- 230000009286 beneficial effect Effects 0.000 description 2
- 230000000875 corresponding effect Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 1
- 230000002596 correlated effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/50—Foldable or collapsible UAVs
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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
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
-
- 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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The application belongs to the field of large-scale solar unmanned aerial vehicles, and relates to a pneumatic layout of a large-scale solar unmanned aerial vehicle, which comprises a fuselage and a deformable wing, wherein the deformable wing comprises an outer side wing and an inner side wing; when the rotating shafts on all the aircraft bodies deflect to the maximum angle, the solar unmanned aerial vehicle is in a ground sliding state, so that the aircraft can slide and other operations are facilitated; when the rotating shafts on all the bodies deflect to proper angles, the wing direction size of the solar unmanned aerial vehicle can be adjusted, the runway can be fully utilized, the lift characteristic is considered, the lifting performance is improved, and the state is called as the lifting running state of the solar unmanned aerial vehicle; when the rotation shafts on all the aircraft bodies deflect to the minimum angle, the extension length of the whole aircraft is controlled to the maximum, and the aircraft is in an air flight mode of the solar unmanned aerial vehicle; when the solar unmanned aerial vehicle is in different stages of flight, the optimal state can be guaranteed to carry out the flight of the current stage, so that the efficient flight of the solar unmanned aerial vehicle is realized.
Description
Technical Field
The application belongs to the field of large-scale solar unmanned aerial vehicles, and particularly relates to a pneumatic layout of a large-scale solar unmanned aerial vehicle.
Background
The solar unmanned aerial vehicle is an unmanned aerial vehicle with the surface covered with a solar power generation device and utilizing solar energy and an onboard power storage device to push the aircraft to fly. Because the aircraft can utilize solar energy in the flight process, the maximum cruising ability of the aircraft is greatly improved, and the permanent cruising can be realized under the fault-free condition theoretically.
According to the performance characteristics of the solar unmanned aerial vehicle, the aircraft is suitable for completing tasks such as environment monitoring and relay guidance, and has the characteristics of convenience in application, high economy and the like.
The whole machine mainly generates power by solar energy, so the design of the solar unmanned aerial vehicle has the following characteristics:
1. the flying speed is low. The lower the flying speed is, the lower the power of air resistance acting is, and the lower the requirement on propulsion energy is;
2. the wing area is large. The larger the wing area, the more solar power generation devices can be deployed.
3. The pneumatic efficiency is high. The higher the aerodynamic efficiency, the less drag with the same lift, and the lower the energy requirements on the aircraft.
4. The aircraft is light in weight. The lighter the aircraft weight, the greater the payload for the same take-off weight, and the greater the aircraft's ability to complete the mission.
In summary, solar unmanned aerial vehicles are often designed in the form of large aspect ratios and large wing areas. The spanwise size of the solar unmanned aerial vehicle is positively correlated with the mission capability, and the existing solar unmanned aerial vehicle is short in range, poor in lifting performance and low in speed due to self energy limitation.
The existing large-scale solar unmanned aerial vehicle adopts layout forms such as a connecting wing, an all-wing aircraft, a multi-fuselage and the like, and combines the flexible wing technology and the elastic wing technology, so that the product design of the solar unmanned aerial vehicle is gradually perfected.
The larger the size of the solar unmanned aerial vehicle, the stronger the mission capability. The existing solar unmanned aerial vehicle size design is limited by the road surface conditions of ground sliding and take-off and landing running. On one hand, tires cannot exceed a taxiway area when the unmanned aerial vehicle slides on the ground, wings cannot interfere facilities beside the taxiway, and on the other hand, the main track and the width of the runway of the unmanned aerial vehicle meet the design specification requirements when the unmanned aerial vehicle slides on the runway. In summary, the width dimension of the taxiways and the width dimension of runways of the existing airports are key to the constraint of the dimension of the solar unmanned aerial vehicle, and are key to the constraint of the mission capability of the solar unmanned aerial vehicle.
In order to improve the task performance of the large-scale solar unmanned aerial vehicle, the design of an innovative wing is needed, so that the large-scale solar unmanned aerial vehicle can take account of the design requirements of ground sliding, take-off and landing running and air flight; therefore, how to design an innovative wing of a solar unmanned aerial vehicle is a problem to be solved.
Disclosure of Invention
The application aims to provide a pneumatic layout of a large solar unmanned aerial vehicle so as to solve the problems of low flying speed and short range caused by the limitation of an airport runway of the solar unmanned aerial vehicle in the prior art.
The technical scheme of the application is as follows: the aerodynamic layout of the large-scale solar unmanned aerial vehicle comprises a fuselage and deformable wings, wherein the fuselage is provided with at least three groups and multiple groups of fuselages are arranged side by side, the deformable wings are in a plurality of sections, the number of the sections of the deformable wings is twice that of the fuselages, the deformable wings comprise outer wings and inner wings, the outer wings are in two groups and are symmetrically arranged, the two groups of outer wings are respectively arranged on the two outermost groups of fuselages, the inner wings are provided with multiple groups and each group of inner wings are respectively arranged between two adjacent groups of fuselages, a fuselage rotating shaft is arranged at the position of the fuselage corresponding to the inner wings or the outer wings, the fuselage rotating shaft is connected with the inner wings or the outer wings, each group of inner wings is provided with two sections, wing rotating shafts are hinged between the two sections of the inner wings, a power part is arranged in the fuselage, and the output end of the power part is connected with the fuselage rotating shaft; the power piece can drive the machine body rotating shaft to rotate, the machine body rotating shaft can drive the inner side wings to deflect to different angles, and when the deflection of the inner side wings is maximum, a ground sliding state is formed; when the inner side wing deflects to the middle angle, a landing running state is formed; when the inboard wing deflects to a minimum angle, an airborne state is created.
Preferably, the outboard wing comprises a straight section and an inclined section connected with the straight section, the inclined Duan Sheyu is arranged on the outboard side of the straight section, the straight section is parallel to the direction of the spreading direction of the aircraft, the straight section is fixedly connected with the fuselage, and the inclined section is inclined to the direction of the spreading direction of the aircraft and inclined to the rear of the aircraft.
Preferably, the fuselage includes screw, power cabin, airborne equipment cabin, pivot structure cabin and fin section cabin that set gradually from front to back, the screw links to each other with the power cabin, the power cabin can drive screw work, the pivot structure inboard is located to the power spare, and the fin is located the end in fin section cabin.
The application relates to a pneumatic layout of a large solar unmanned aerial vehicle, which comprises a fuselage and a deformable wing, wherein the deformable wing comprises an outer wing and an inner wing; when the rotating shafts on all the aircraft bodies deflect to the largest angle, the inner side wings are tightly folded, and the spanwise dimension of the whole aircraft is controlled to be the smallest, so that the solar unmanned aerial vehicle is in a ground sliding state, and the aircraft can slide and other operations conveniently; when the rotating shafts on all the bodies deflect to proper angles, the inner wings are properly folded, and at the moment, the wing direction size of the solar unmanned aerial vehicle is adjustable, so that the runway can be fully utilized, the lift characteristic is taken into consideration, the lifting performance is improved, and the state is called as the lifting running state of the solar unmanned aerial vehicle; when the rotation shafts on all the aircraft bodies deflect to the minimum angle, the extension length of the whole aircraft is controlled to the maximum, and the aircraft is in an air flight mode of the solar unmanned aerial vehicle; when the solar unmanned aerial vehicle is in different stages of flight, the optimal state can be guaranteed to carry out the flight of the current stage, so that the efficient flight of the solar unmanned aerial vehicle is realized.
Drawings
In order to more clearly illustrate the technical solution provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are merely some embodiments of the application.
FIG. 1 is an isometric view of a ground taxi of a solar unmanned aerial vehicle;
FIG. 2 is an isometric view of a take-off and landing running state of a solar unmanned aerial vehicle;
FIG. 3 is an aerial flight attitude isometric view of the solar unmanned aerial vehicle of the present application;
FIG. 4 is a side view of a solar unmanned aerial vehicle of the present application;
FIG. 5 is a front view of the ground taxi of the solar unmanned aerial vehicle of the present application;
fig. 6 is a front view of the take-off and landing run state of the solar unmanned aerial vehicle;
fig. 7 is a front view of the solar unmanned aerial vehicle in an air flight state.
1. A body; 2. a deformable airfoil; 3. a propeller; 4. a power cabin; 5. an onboard equipment bay; 6. a rotating shaft structure cabin; 7. a tail section cabin; 8. a nose landing gear; 9. a rear landing gear; 10. an outboard wing; 11. an inboard wing; 12. a machine body rotating shaft; 13. wing pivot.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
The pneumatic layout of the large solar unmanned aerial vehicle, as shown in fig. 1-4, comprises a fuselage 1 and a deformable wing 2, wherein the fuselage 1 is provided with at least three groups and multiple groups of fuselages 1 are arranged side by side, and can be 3 groups, 5 groups, 7 groups or more, and each group of fuselages 1 is provided with a front landing gear 8 and a rear landing gear 9, and the following description is given by taking the three groups of fuselages 1 as an example.
The deformable wings 2 share multiple sections, the number of the sections of the deformable wings 2 is twice the number of the fuselage 1, the deformable wings comprise two groups of outer wings 10 and two groups of inner wings 11, the outer wings 10 share two groups of outer wings 10 and are symmetrically arranged, the two groups of outer wings 10 are respectively arranged on the two outermost groups of fuselage 1, the inner wings 11 are provided with multiple groups, each group of inner wings 11 are respectively arranged between the two adjacent groups of fuselage 1, fuselage rotating shafts 12 are arranged at positions of the fuselage 1 corresponding to the inner wings 11 or the outer wings 10, the fuselage rotating shafts 12 are connected with the inner wings 11 or the outer wings 10, each group of inner wings 11 is provided with two sections, wing rotating shafts 13 are hinged between the two sections of inner wings 11, power pieces are arranged in the fuselage 1, and output ends of the power pieces are connected with the fuselage rotating shafts 12;
the power piece can drive the machine body rotating shaft 12 to rotate, the machine body rotating shaft 12 can drive the inner side wing 11 to deflect to different angles, and when the deflection of the inner side wing 11 is maximum, a ground sliding state is formed; when the inner wing 11 deflects to an intermediate angle, a landing and take-off running form is formed; when the inboard wing 11 is deflected to a minimum angle, an airborne state of flight is established.
Under the condition of taking off and landing running, taking the main track parameter and the low-speed lift characteristic into consideration is one of key requirements; increasing aspect ratio is one of the key requirements to improve aerodynamic efficiency under air flight conditions.
When the rotation shafts on all the airframes 1 deflect to the largest angle, the inner side wings 11 are tightly folded, the spanwise dimension of the whole aircraft is controlled to the minimum, and the taxiing main track is controlled to the minimum, which is the ground taxiing state of the solar unmanned aerial vehicle, see fig. 1 and 5, and the ground taxiing state is compact in size, thereby being beneficial to controlling the spanwise dimension of the unmanned aerial vehicle and facilitating the taxiing and other operations of the aircraft.
When the rotation shafts on all the airframes 1 deflect to a proper angle, the angle is between 30 degrees and 60 degrees, the angle can be adjusted according to different models, the inner side wings 11 are properly folded, the take-off and landing main track and the extension length of the whole aircraft are controlled to the upper limit of the constraint range allowed by the runway, at the moment, the wing direction size of the solar unmanned aerial vehicle is adjustable, the runway can be fully utilized, the lift characteristics are considered, the take-off and landing performance is favorably improved, the main track parameter and the low-speed lift characteristics can be ensured, and the state is called the take-off and landing running state of the solar unmanned aerial vehicle, and is shown in fig. 2 and 6.
When the rotation shafts on all the airframes 1 deflect to the minimum angle, the inner side wings 11 are unfolded in a straight line, the unfolding length of the whole aircraft is controlled to be maximum, the air flight span is maximum, the aerodynamic efficiency is high, and the mission capability of the aircraft is enhanced, which is the air flight form of the solar unmanned aerial vehicle, and the solar unmanned aerial vehicle is shown in fig. 3 and 7.
Therefore, the ground sliding, take-off and landing running and air flight of the aircraft are realized by changing the angle of the aircraft wings, and when the solar unmanned aerial vehicle is in different stages of flight, the solar unmanned aerial vehicle can ensure the optimal state to carry out the flight of the current stage, so that the efficient flight of the solar unmanned aerial vehicle is realized; in addition, the three modes can be freely switched, and the solar unmanned aerial vehicle is beneficial to selecting the most suitable mode according to the flight state.
Preferably, the outboard wing 10 includes a straight section and an inclined section connected to the straight section, the inclined section is provided on the outboard side of the straight section, the straight section is provided parallel to the direction of the aircraft, the straight section is fixedly connected to the fuselage 1, and the inclined section is inclined to the direction of the aircraft and to the rear of the aircraft.
Preferably, fuselage 1 includes screw 3, power cabin 4, machine carries equipment compartment 5, pivot structure cabin 6 and fin section cabin 7 that set gradually from front to back, and screw 3 links to each other with power cabin 4, and power cabin 4 can drive screw 3 work, and the front end of power cabin 4 is the toper structure to reduce the windage, in the pivot structure cabin 6 was located to the power spare, the fin was located the end in fin section cabin 7, each partial compact structure on the aircraft under this design, occupation space is little, satisfies solar unmanned aerial vehicle's design demand.
The present application is not limited to the above embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present application are intended to be included in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (3)
1. The pneumatic layout of a large-scale solar unmanned aerial vehicle, its characterized in that: the variable-shape aircraft comprises an aircraft body (1) and variable-shape airfoils (2), wherein the aircraft body (1) is provided with at least three groups and a plurality of groups of aircraft bodies (1) are arranged side by side, the variable-shape airfoils (2) are provided with a plurality of sections, the number of the sections of the variable-shape airfoils (2) is twice that of the aircraft bodies (1), the variable-shape airfoils comprise outer-side airfoils (10) and inner-side airfoils (11), the outer-side airfoils (10) are provided with two groups and are symmetrically arranged, the two groups of outer-side airfoils (10) are respectively arranged on the two outermost groups of aircraft bodies (1), the inner-side airfoils (11) are provided with a plurality of groups and each group of inner-side airfoils (11) are arranged between the two adjacent groups of aircraft bodies (1), a fuselage rotating shaft (12) is arranged at the position of the aircraft body (1) corresponding to the inner-side airfoils (11) or the outer-side airfoils (10), each group of inner-side airfoils (11) is provided with two sections, the inner-side airfoils (11) are hinged between the two sections, the inner-side airfoils (11) are connected with power rotating shafts (13), and the power output parts (12) are connected with the fuselage rotating shafts (1);
the power piece can drive the machine body rotating shaft (12) to rotate, the machine body rotating shaft (12) can drive the inner side wing (11) to deflect to different angles, and when the deflection of the inner side wing (11) is maximum, a ground sliding state is formed; when the inner side wing (11) deflects to a middle angle, a landing run state is formed; when the inboard wing (11) deflects to a minimum angle, an airborne state is established.
2. The aerodynamic layout of a large solar unmanned aerial vehicle of claim 1, wherein: the outside wing (10) includes straight section and the slope section that links to each other with straight section, the outside of the straight section of slope Duan Sheyu, straight section is on a parallel with the spanwise direction setting of aircraft, straight section and fuselage (1) fixed connection, the slope section slope is in the spanwise direction of aircraft and to the rear slope of aircraft.
3. The aerodynamic layout of a large solar unmanned aerial vehicle of claim 1, wherein: fuselage (1) are including screw (3), power cabin (4), machine-mounted equipment compartment (5), pivot structure cabin (6) and fin section cabin (7) that set gradually from front to back, screw (3) link to each other with power cabin (4), power cabin (4) can drive screw (3) work, in pivot structure cabin (6) are located to the power spare, and the tail is located the end in fin section cabin (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310978286.XA CN116788534A (en) | 2023-08-04 | 2023-08-04 | Pneumatic layout of large solar unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310978286.XA CN116788534A (en) | 2023-08-04 | 2023-08-04 | Pneumatic layout of large solar unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116788534A true CN116788534A (en) | 2023-09-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310978286.XA Pending CN116788534A (en) | 2023-08-04 | 2023-08-04 | Pneumatic layout of large solar unmanned aerial vehicle |
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| Country | Link |
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| CN (1) | CN116788534A (en) |
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2023
- 2023-08-04 CN CN202310978286.XA patent/CN116788534A/en active Pending
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