CN2506536Y - Pilotless solar energy aerobat - Google Patents
Pilotless solar energy aerobat Download PDFInfo
- Publication number
- CN2506536Y CN2506536Y CN 01270983 CN01270983U CN2506536Y CN 2506536 Y CN2506536 Y CN 2506536Y CN 01270983 CN01270983 CN 01270983 CN 01270983 U CN01270983 U CN 01270983U CN 2506536 Y CN2506536 Y CN 2506536Y
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- CN
- China
- Prior art keywords
- wing
- solar power
- aerocraft
- driverless operation
- controlling
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Abstract
The utility model provides an unmanned solar energy space flight unit, which consists of an upper wing (1), a lower wing (2), a wing winglet (3), a solar battery panel (4), a left, middle and right measuring, controlling and airborne equipment cabins (5), (6) and (7), an energy system (8), a propeller (9) and a control system (10); wherein, wing ends of the upper wing (1) provided with a cathedral angle and the lower wing (2) provided with a dihedral angle are connected by the wing winglet (3). Meanwhile, a composite type flying wing aerobat whole is formed by the upper part and the lower part of the left, middle and right measuring, controlling and airborne equipment cabins (5), (6) and (7) respectively connected with the upper wing (1) and the lower wing (2). The upper wing surface of the upper and lower wings (1) and (2) are all provided with the solar battery panel (4), and the front edge of the lower wing (2) is provided with six propellers (9).
Description
Technical field
The utility model relates to a kind of high-altitude, during long the boat, and unpiloted aerocraft, especially adopting with the solar power is the driverless operation solar power aerocraft that drives power.
Background technology
The many countries of our times have been fully recognized that satellite aspect civil and military, synchronous satellite and high-altitude, the competition trend of driverless operation solar power aerocraft during long the boat, satellite is civilian, the use of military aspect, for example communication monitoring, relaying, celestial observation, the sampling of atmosphere sample, geoexploration, monitor rescue, monitoring and controlling traffic, the enemy is scouted, monitoring radio and radar or the like, the solar power aerocraft can both be finished, because the solar power aerocraft is in high-altitude flight, can obtain sufficient solar light irradiation, its drive energy is inexhaustible, compares with satellite, its manoevreability and road-holding property are all fine, can be arbitrarily long-time or short time running fix in required space, can accuracy control flying height and residing orientation, it is the remote control distributor workplatform that is better than satellite in this, from economy relatively, that just more is better than satellite, even do not compare with satellite, and in the high-altitude, compare among the push-button aircraft class during long the boat, if adopting solar power so when requiring high-altitude and long boat is drive energy, also is very favorable, therefore many countries development work that conducting a research energetically in this respect.
Period, U.S. Helios solar powered aircraft made a successful trial flight recently, some good tries have been disclosed, its aircraft general form is the big span, many oars, many fulcrums take-off and landing device, owing to adopted this aircraft general form, some adverse factors have also been brought, the problem of bringing structural weight to lay particular stress on as the big span, because elastic deformation is unfavorable for receiving the radiant energy of the sun more greatly, solve relatively difficulty of longitudinal stability and manipulation problem, the take-off and landing device of many fulcrums, bring increasing the weight of on flight resistance increasing and the structural weight, should learn a lesson when designing following solar power aerocraft in these unfavorable aspects in a word.
The applicant had once proposed " solar power driverless operation survey airplane " (patent No.: 94209702.5), obtained many useful experience and data through taking a flight test.
Comprehensive above-mentioned background technology is convenient to we require to propose driverless operation solar power aerocraft at new operation technique overall plan.
Summary of the invention
According to above-mentioned, the purpose of this utility model be to provide a kind of can: 1, make the radiation of the maximum as far as possible reception solar power of solar panel; 2, as much as possible reduce the induced drag of wing; 3, the performance of leaving a blank preferably; 4, make aircraft overall structure weight the lightest; 5, can more easily satisfy different military, the repacking of civilian requirement; 6, has the driverless operation solar power aerocraft of working service preferably.
To achieve these goals, the utility model is achieved through the following technical solutions: a kind of driverless operation solar power aerocraft, mainly by top wing (1), lower wing (2), wing tip winglet (3), solar panel (4), left, middle and right observing and controlling and airborne equipment cabin (5), (6), (7), energy resource system (8), propelling unit (9), control system (10) is formed, and wherein top wing (1) is for having sweepforward angle φ
1, inverted diherdral α
1Rectangular wing, lower wing (2) is for having sweepback angle φ
2, dihedral angle α
2Rectangular wing, lower wing (2) staggers with top wing (1) front and back, top wing (1) and lower wing (2) by wing tip winglet (3), pass through a left side at wing tip again, in, right observing and controlling and airborne equipment cabin (5), (6), the connection of (7) constitutes the aerocraft integral body of compound all-wing aircraft type, the top airfoil of top wing (1) and lower wing (2) all is covered with solar panel (4), and the leading edge position of lower wing (2) is provided with 6 propelling units (9).
Above-mentioned technical scheme has the following advantages and effect:
1, owing to adopted compound wing form, played the pneumatic effect of the big span, greatly reduce induced drag, and structural weight can be very light;
2, owing to adopted compound wing form, accomplished layout solar panel as much as possible;
3, because top wing 1 staggers with lower wing 2 front and back, the efficient that receives solar radiant energy is improved;
4, the integral layout of the utility model structure is reasonable, makes the structure-bearing route the shortest, has not only considered static strength, has taken into full account the requirement of aeroelasticity simultaneously;
5, the utility model energy resource system connection and reasonable arrangement has improved propulsion coefficient;
6, the utlity model has working service performance preferably.
Description of drawings
Figure 1A is a front elevation of the present utility model
Figure 1B is a birds-eye view of the present utility model
Fig. 1 C is a lateral plan of the present utility model
Fig. 2 is an energy resource system scheme drawing of the present utility model
Among the figure: 1-top wing, the upper left wing outer wing of 11-, the upper left wing wing centre section of 12-, the upper right wing wing centre section of 13-, the upper right wing outer wing of 14-, 2-lower wing, 21-lower-left wing outer wing, 22-lower-left wing wing centre section, 23-bottom right wing wing centre section, 24-bottom right wing outer wing, 3-wing tip winglet, 4-solar panel, 5-left side observing and controlling airborne equipment cabin, 51-left side take-off and landing device, observing and controlling airborne equipment cabin among the 6-, take-off and landing device among the 61-, the right observing and controlling airborne equipment of 7-cabin, the right take-off and landing device of 71-, the 8-energy resource system, the 81-switching device, 82-electrical storage device, 83-storage battery, the 84-electro-motor, the 9-propelling unit, 10-control system, 11-trammel beam
The specific embodiment
By Figure 1A, Figure 1B, shown in Fig. 1 C, the utility model is mainly by top wing 1, lower wing 2, wing tip winglet 3, solar panel 4, left, middle and right observing and controlling and airborne equipment cabin 5,6,7, energy resource system 8, propelling unit 9, control system 10 is formed, and wherein top wing 1 is for having sweepforward angle φ
1, inverted diherdral α
1Rectangular wing, lower wing 2 is for having sweepback angle φ
2, dihedral angle α
2Rectangular wing, lower wing 2 staggers with top wing 1 front and back, and top wing 1 and lower wing 2 are at wing tip, by wing tip winglet 3, again by a left side, in, right observing and controlling and airborne equipment cabin 5,6,7 connection, constitute the aerocraft integral body of compound all-wing aircraft type, the top airfoil of top wing 1 and lower wing 2 all is covered with solar panel 4, and the leading edge position of lower wing 2 is provided with 6 propelling units 9.
As seen from the figure, lower wing 2 staggers with top wing 1 front and back, does not cover mutually, can reach the effect that receives solar radiant energy preferably.
Because being oblong, wing brings convenience for layout solar panel 4.
The top wing 1 and the lower wing 2 actual spanes and not very big, but by being connected to form of wing tip winglet 3 the big pneumatic span, finally make induced drag very little, this point during to long boat aircraft be very favorable.
Top wing 1 and lower wing 2 are formed a convergent contour passage with wing tip winglet 3 simultaneously, and stream is comforted in elimination, and boundary-layer is piled up, and interference in air flow is the effect that favourable playing quickened air-flow and dredged whole air-flow, help improving the lift efficiency of aerocraft.
Know again, the sweepback of the sweepforward of top wing 1 and lower wing 2, what mainly consider is the needs that arrange at aerodynamic arrangement and position, because φ
1With φ
2The problem of less its boundary effect is also not serious.
As seen from the figure.Consider the assembly technology of wing, working service and transportation, the utility model top wing 1 are divided into upper left wing outer wing 11, upper left wing wing centre section 12, upper right wing wing centre section 13, upper right wing outer wing 14 is divided into four sections, and lower wing 2 is divided into lower-left wing outer wing 21, lower-left wing wing centre section 22, bottom right wing wing centre section 23, bottom right wing outer wing 24 is divided into four sections.Each section becomes stressed integral body by the attaching parts butt joint during use.
By figure also as can be known, the dihedral angle α of lower wing 2
2Absolute value greater than the inverted diherdral α of top wing 1
1Absolute value, the two comprehensive matching can more easily solve lateral stability, also satisfies propelling unit layout requirement when near the ground simultaneously.
By figure also as can be known, in left, middle and right observing and controlling and the airborne equipment bilge portion left, middle and right take-off and landing device 51,61,71 is installed, and is tricycle layout.
In the front portion in middle observing and controlling and airborne equipment cabin 6 trammel beam 11 that is used for weight balancing is installed, also can uses as Pitot tube.
Know that again control system 10 (among the figure for showing) is installed among left, middle and right observing and controlling and the airborne equipment cabin 5,6,7, it is handled assembly and realizes flicon of the present utility model by wherein guiding relevant controlsurface into.
By shown in Figure 2, be the schematic block diagram of energy resource system 8, this system is by solar panel 4, switching device 81, electrical storage device 82, storage battery 83, electro-motor 84, distributor 85, propelling unit 9 is formed.
Claims (6)
1, a kind of driverless operation solar power aerocraft, mainly by top wing (1), lower wing (2), wing tip winglet (3), solar panel (4), a left side, in, right observing and controlling and airborne equipment cabin (5), (6), (7), energy resource system (8), propelling unit (9), control system (10) is formed, and it is characterized in that: top wing (1) is for having sweepforward angle φ
1, inverted diherdral α
1Rectangular wing, lower wing (2) is for having sweepback angle φ
2, dihedral angle α
2Rectangular wing, lower wing (2) staggers with top wing (1) front and back, top wing (1) and lower wing (2) are at wing tip, pass through left, middle and right observing and controlling and airborne equipment cabin (5) again by wing tip winglet (3), (6), (7) the aerocraft integral body that connects and composes compound all-wing aircraft type, the top airfoil of top wing (1) and lower wing (2) all is covered with solar panel (4), and the leading edge position of lower wing (2) is provided with 6 propelling units (9).
2, driverless operation solar power aerocraft according to claim 1 is characterized in that: top wing (1), and by upper left wing outer wing (11), upper left wing wing centre section (12), upper right wing wing centre section (13), upper right wing outer wing (14) is formed.
3, driverless operation solar power aerocraft according to claim 1 is characterized in that: lower wing (2), and by lower-left wing outer wing (21), lower-left wing wing centre section (22), bottom right wing wing centre section (23), bottom right wing outer wing (24) is formed.
4, driverless operation solar power aerocraft according to claim 1 is characterized in that: the dihedral angle α of lower wing (2)
2Absolute value greater than the inverted diherdral α of top wing (1)
1Absolute value.
5, driverless operation solar power aerocraft according to claim 1 is characterized in that: energy resource system (8), by solar panel (4), switching device (81), electrical storage device (82), storage battery (83), electro-motor (84), distributor (85), propelling unit (9) is formed.
6, driverless operation solar power aerocraft according to claim 1 is characterized in that: trammel beam (11) is equipped with in the front portion in middle observing and controlling and airborne equipment cabin (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01270983 CN2506536Y (en) | 2001-11-16 | 2001-11-16 | Pilotless solar energy aerobat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01270983 CN2506536Y (en) | 2001-11-16 | 2001-11-16 | Pilotless solar energy aerobat |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2506536Y true CN2506536Y (en) | 2002-08-21 |
Family
ID=33676510
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 01270983 Expired - Fee Related CN2506536Y (en) | 2001-11-16 | 2001-11-16 | Pilotless solar energy aerobat |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2506536Y (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102730183A (en) * | 2012-07-03 | 2012-10-17 | 北京航空航天大学 | Novel solar airplane |
| CN112644686A (en) * | 2020-12-25 | 2021-04-13 | 中国航天空气动力技术研究院 | Tandem wing overall arrangement solar energy unmanned aerial vehicle |
-
2001
- 2001-11-16 CN CN 01270983 patent/CN2506536Y/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102730183A (en) * | 2012-07-03 | 2012-10-17 | 北京航空航天大学 | Novel solar airplane |
| CN102730183B (en) * | 2012-07-03 | 2015-01-07 | 北京航空航天大学 | Novel solar airplane |
| CN112644686A (en) * | 2020-12-25 | 2021-04-13 | 中国航天空气动力技术研究院 | Tandem wing overall arrangement solar energy unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |