CN204802071U - Helios - Google Patents
Helios Download PDFInfo
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- CN204802071U CN204802071U CN201520475146.1U CN201520475146U CN204802071U CN 204802071 U CN204802071 U CN 204802071U CN 201520475146 U CN201520475146 U CN 201520475146U CN 204802071 U CN204802071 U CN 204802071U
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Abstract
The utility model provides a helios, which comprises a bod, set up in machine body surface's thin -film solar cell with set up in the inside controller of organism, two all -wing aircrafts that the organism set up including the symmetry, every all -wing aircraft is at least including the first end wing and the second end wing, and the first end wing rotates through first pivot with the second end wing to be connected, the controller is used for locating machine body surface's thin -film solar cell's illumination area and the solar radiation ability that unit area received according to the first pivot of the angel position control rotation of shining of sunlight with the increase. Thereby this helios's time of endurance and the reliable degree of flight have been improved.
Description
Technical field
The utility model relates to vehicle technology field.Specifically, a kind of Helios is related to.
Background technology
Helios, as the one of aircraft, refers to the aircraft using solar power as energy source.Since mid-term in 20th century, Helios research has become the emerging field that Global Aerospace industry is given priority to.
A kind of solar power flight instruments is had in prior art, comprise body, the short-range radar be arranged in body, equipment storehouse, long-range radar (LRR), solar power source, the front wing being arranged on body both sides, the empennage being arranged on After-Body and screw propeller, and the rear wing at wing rear portion and wing flap, solar power source comprises two power paths and is arranged on the plane skylight on wing and fuselage, and two power paths are respectively main power path and reserve power path; Main power path comprises solar panels circuit and gathers device, circuit control device and motor, and reserve power path comprises solar panels circuit and gathers device, storage battery, circuit control device and motor, and control circui district is made up of relay switch; Plane skylight accounts for 99% ~ 95% of wing and body area, the span 10 ~ 20m, take-off weight 300 ~ 600kg, and thrust-weight ratio is 0.1 ~ 0.3; Front wing and rear wing are connected to form rhombus framework, and front wing wing root is connected with forebody, and rear wing wing root is connected with vertical fin upper end, and rear wing wing tip is connected with the front wing span at front wing span 50%-70% place.
Angle due to sunshine is real-time change, when the sun on above-mentioned solar power flight instruments current flight ground is in initial rise or sunset state, plane skylight on fuselage is likely blocked, the part be not blocked is also because the too small solar radiant energy causing its unit area to obtain of angle of plane skylight and sunlight is very little, therefore its efficiency comparison obtaining solar power is low, affect by the factor such as weather, flight time very large, thus cause its fiduciary level to reduce.
Utility model content
For this reason, technical problem to be solved in the utility model is when the angle on the on-site sunshine of aircraft and ground is less, it is very low that it obtains efficiency of solar power, thus propose a kind ofly can control the Helios that the solar power improving acquisition was turned up or flattened to all-wing aircraft.
For solving the problems of the technologies described above, the utility model provides following technical scheme:
A kind of Helios, comprise body, be arranged at the thin-film solar cells of body surface and be arranged at the controller of internal body, body at least comprises symmetrically arranged two all-wing aircrafts, each all-wing aircraft at least comprises the first end wing and the second end wing, and the first end wing is connected by the first axis of rotation with the second end wing.
Preferably, two all-wing aircrafts are connected by the second axis of rotation.
Preferably, body also comprises fuselage and two the 3rd rotating shafts, and two all-wing aircrafts are arranged at the both sides of fuselage respectively and are rotationally connected respectively by the 3rd rotating shaft and fuselage.
Preferably, the upper surface of fuselage is provided with the v-depression extended along its length.
Preferably, also comprise the empennage being arranged at back body, empennage is two, and arranges in inverted V-shaped, and each empennage and fuselage are rotatably connected.
Preferably, the wing tip of fuselage head, all-wing aircraft and the wing tip of empennage are transparent material, and its inside is provided with the photovoltaic battery array towards fuselage front or top.
Preferably, the back edge of all-wing aircraft is provided with ducted fan; Thin-film solar cells adopts the mode of inlaying to be combined with body; Also comprise the Hi cell for energy supply, Hi cell is by being connected with body by detaching structure.
Preferably, the span of all-wing aircraft is 2-10 rice, and chord length is 12-50 centimetre.
Technique scheme of the present utility model has the following advantages compared to existing technology:
The Helios that the present embodiment provides, each all-wing aircraft of this aircraft comprises the first end wing and the second end wing, and the first rotating shaft connecting the first end wing and the second end wing can be controlled to rotate by controller, when the angle on sunshine and ground is less, controller just controls the first axis of rotation, and the angle making part be located at the sensitive surface of the thin-film solar cells of body surface and the direction of illumination of sunshine increases; When sunshine is with the angle on ground is comparatively large or close to time vertical, controller just controls the first axis of rotation, makes whole all-wing aircraft be horizontal stretching state.Namely can adjust in real time to increase the illuminating area of thin-film solar cells and the solar radiant energy of unit area reception according to the irradiating angle of sunshine, thus farthest solar power can be obtained, to improve the cruise duration of aircraft while the flight stability ensureing aircraft.
Accompanying drawing explanation
Fig. 1 is a kind of Helios structural representation of the utility model embodiment 1;
Fig. 2 is a kind of Helios structural representation of the utility model embodiment 2;
Fig. 3 is the structural representation that a kind of all-wing aircraft of the utility model embodiment 2 is in the Helios of the state of turning up.
In figure, Reference numeral is expressed as: 1-fuselage, 2-all-wing aircraft, the 21-first end wing, the 22-second end wing, 3-empennage, 41-first rotating shaft, 42-second rotating shaft, 43-the 3rd rotating shaft, 5-variable-distance screw propeller, 6-ducted fan, 7-Hi cell.
Detailed description of the invention
In order to make those skilled in the art person understand content of the present utility model better, below in conjunction with drawings and Examples, technical scheme provided by the utility model is described in further detail.
Embodiment 1
As shown in Figure 1, present embodiments provide a kind of Helios, comprise body, be arranged at the thin-film solar cells of body surface and be arranged at the controller of internal body, body comprises symmetrically arranged two all-wing aircrafts 2, each all-wing aircraft 2 at least comprises the first end wing 21 and the second end wing 22, and the first end wing 21 and the second end wing 22 are rotationally connected by the first rotating shaft 41, controller is used for controlling the first rotating shaft 41 according to the irradiating angle of sunshine and rotates to increase the illuminating area of the thin-film solar cells being located at body surface and the solar radiant energy of unit area reception.
In other alterable embodiments, all-wing aircraft 2 also can comprise the plural end wing, and as 3 or 4, adjacent two end wings are connected by axis of rotation, and therefore each all-wing aircraft 2 increases an end wing respectively needs corresponding increase rotating shaft.The end wing number of two all-wing aircrafts 2 also can be inconsistent, can consider and choose suitable end wing number to aspects such as the acquisition of solar power and the stability of aircraft self flight.
The Helios that the present embodiment provides, each all-wing aircraft 2 comprises the first end wing 21 and the second end wing 22, and the first rotating shaft 41 connecting the first end wing 21 and the second end wing 22 can be controlled to rotate by controller, when the angle on sunshine and ground is less, controller just controls the first rotating shaft 41 and rotates, and the angle making part be located at the sensitive surface of the thin-film solar cells on all-wing aircraft surface and the direction of illumination of sunshine increases; When sunshine is comparatively large with the angle on ground or close to time vertical, controller just controls the first rotating shaft 41 and rotates, make whole all-wing aircraft 2 in horizontal stretching state.Namely the relative angle of the first end wing 21 and the second end wing 22 on all-wing aircraft 2 can be adjusted in real time according to the irradiating angle of sunshine, with the solar radiant energy that the illuminating area and unit area that increase thin-film solar cells receive, thus farthest solar power can be obtained, to improve the cruise duration of aircraft while the flight stability ensureing aircraft.
Preferably, two all-wing aircrafts 2 of this aircraft are rotationally connected by the second rotating shaft 42, and as in Fig. 1, the first end wing 21 of the all-wing aircraft 2 of both sides is rotatably connected to together by the second rotating shaft 42.Controller also rotates to increase the illuminating area of the thin-film solar cells being located at body surface and the solar radiant energy of unit area reception for controlling the second rotating shaft 42 according to the irradiating angle of sunshine.Fuselage and the all-wing aircraft 2 of this aircraft combine together, can provide certain level and longitudinal permanence, the degree of stability of especially going off course after all-wing aircraft 2 turns up certain angle along the first rotating shaft 41 and the second rotating shaft 42.To a certain degree can also reduce the induced drag of all-wing aircraft 2, increase 1ift-drag ratio.Both sides all-wing aircraft 2 is asymmetric when turning up, i.e. can change the lift of both sides all-wing aircraft 2 when the angle angle of the first end wing 21 and the second end wing 22 is inconsistent on the all-wing aircraft 2 of both sides, thus be convenient to the control realizing body rolling.
Preferably, controller also can be used for adjusting according to the irradiating angle of sunshine and air objective the solar radiant energy that heading and flight attitude receive to increase the illuminating area of being located at the thin-film solar cells of body surface and unit area.Particularly, controller obtains the irradiating angle of sunshine according to current flight date, time and position.Position due to the sun is constant at a fixed time, therefore after obtaining current date and time, the position of the sun becomes can be known, in conjunction with the position of current flight device, just can know sunshine irradiating angle now, thus adjust the flight attitude of aircraft in conjunction with air objective, such as when the irradiating angle of sunshine lower (sunrise or sunset), can towards direction of illumination, if destination is not or not this direction, fuselage can be tilted to light source direction, make it can obtain maximum illuminating area and the solar radiation of unit area.
In addition, the back edge of all-wing aircraft 2 is provided with ducted fan 6, and it can form certain body negative pressure, increases lift.Thin-film solar cells adopts the mode of inlaying to be combined with body; and do not need to be made on covering or structure that assembly covers aircraft again; the thin-film solar cells that the mode of inlaying combines can improve the structural strength of aircraft; alleviate its weight thus reduce wing load, and equally with covering can protect aircraft.The electrode of thin-film solar cells is arranged on its reverse side, and is electrically connected at internal body.Also comprise the Hi cell 7 for energy supply, Hi cell 7 is by being connected with body by detaching structure.From the process taken off in ground, need more energy at aircraft, now can be provided by Hi cell 7, after completion of this process, in order to this Hi cell 7 can be cast aside by weight, the reduction energy consumption reducing aircraft.
In the present embodiment, the tow sides of body are equipped with thin-film solar cells, and thin-film solar cells can be efficient flexible GaAs thin-film solar cells or CIGS thin film solar cell or polycrystal silicon film solar cell.Internal body is also provided with lithium cell or other high-efficiency energy-storage batteries, can store the unnecessary electric energy changed by thin-film solar cells when sunny, is used for aircraft energy supply when sunlight is not enough.
In the present embodiment, the span of preferred all-wing aircraft 2 is 2-10 rice, and chord length is 12-50 centimetre.Although when other conditions such as material technology are constant, reduce wing load by reducing the size of aircraft, but due to the impact of air astringency and Reynolds number, the 1ift-drag ratio of aircraft can decline along with the reduction of aircraft size.The aircraft that the present embodiment provides has made it have very high 1ift-drag ratio by the design of all-wing aircraft 2 size and structure, specifically can reach more than 30.
In addition, this aircraft is also provided with GPS navigation system, radio altimeter gyroscope, radio-frequency transmissions receiving device etc., controls for autonomous navigation and flight.
Above-mentioned aircraft preferably flies at stratosphere middle part (3-4 myriametre height) to advection layer (1-2 myriametre height), because this region has good flight environment of vehicle and is subject to luminous environment.Aircraft can utilize electric energy rise to the highest can flight angle, then utilize potential energy to glide to advection layer, finally utilize electric energy to keep flat and fly, and interval circulation can carry out this flight course.This offline mode has good capacity usage ratio and less weight loading.The flying speed of aircraft can reach 50-200 kilometer/hour.
With all-wing aircraft 2 area 0.5 sq m, the span 3 meters, the aircraft that weight is 2 kilograms is example, the photovoltaic electric energy of the most about 200 watts can be obtained, aircraft 1ift-drag ratio 50, keep flat and fly required energy and be about 35 watts, flying speed can reach more than 100 kilometers of speed per hours, is enough to the impact resisting high-altitude turbulent flow and air-flow.
Embodiment 2
As shown in Figures 2 and 3, present embodiments provide another kind of Helios, comprise body, be arranged at the thin-film solar cells of body surface and be arranged at the controller of internal body, body comprises symmetrically arranged two all-wing aircrafts 2, each all-wing aircraft 2 at least comprises the first end wing 21 and the second end wing 22, and the first end wing 21 and the second end wing 22 are rotationally connected by the first rotating shaft 41, controller is used for controlling the first rotating shaft 41 according to the irradiating angle of sunshine and rotates to increase the illuminating area of the thin-film solar cells being located at body surface and the solar radiant energy of unit area reception.Body also comprises fuselage 1 and two the 3rd rotating shafts 43, two all-wing aircrafts 2 are arranged at the both sides of fuselage 1 respectively and are rotationally connected with fuselage 1 respectively by the 3rd rotating shaft 43, and controller also rotates to increase the illuminating area of the thin-film solar cells being located at body surface and the solar radiant energy of unit area reception for controlling the 3rd rotating shaft 43 according to the irradiating angle of sunshine.
The Helios that the present embodiment provides, the direction of illumination of controller Real-time Obtaining sunshine, when the angle on itself and ground is less, as shown in Figure 3, then controlling the first rotating shaft 41 and the 3rd rotating shaft 43 rotates until to be located at the solar radiant energy that the illuminating area of the thin-film solar cells of body surface and unit area receive maximum; When the angle on sunshine and ground is larger, as shown in Figure 2, then the first rotating shaft 41 is controlled and the state until all-wing aircraft 2 extends horizontally is rotated in the 3rd rotating shaft 43.Namely the rotation by controlling the first rotating shaft 41 and the 3rd rotating shaft 43 makes this aircraft farthest can obtain solar power.
Preferably, this aircraft also comprises the empennage 3 being arranged at fuselage 1 rear end, and empennage 3 is two, and arranges in inverted V-shaped.Each empennage 3 is rotatably connected with fuselage 1, and controller also can be used for controlling empennage 3 and rotates to increase the illuminating area of the thin-film solar cells being located at empennage 3 surface and the solar radiant energy of unit area reception.These two can relatively rotate with fuselage 1 and the empennage 3 arranged in inverted V-shaped can reduce the region area that sunshine is blocked, simultaneously compared to the empennage 3 that horizontal or vertical direction is arranged, it can reduce the resistance of aircraft, and the driftage that can also contribute to aircraft controls to control with rolling.
Preferably, the upper surface of fuselage 1 is provided with the v-depression extended along its length.Two upper edges of this v-depression are the place place of the 3rd rotating shaft 43, and it makes fuselage 1 be connected with the shape of all-wing aircraft 2 transition, can reduce the flight resistance of aircraft and obtain certain fuselage lift.
Preferably, the wing tip of fuselage 1 head, all-wing aircraft 2 and the wing tip of empennage 3 are transparent material, and its inside is provided with the photovoltaic battery array towards fuselage 1 front or top.Because thin-film solar cells is generally square or octagon, the whole outside face of body can not be covered completely, therefore in the place that thin-film solar cells does not cover, photovoltaic battery array is set by said method and this aircraft can be made to obtain more solar power.
In addition, in order to increase the solar radiant energy that the illuminating area of thin-film solar cells and unit area receive further, the face area of face area on all-wing aircraft 2 thickness direction and fuselage 1 side can be increased, and cover as far as possible comprehensively thin-film solar cells is set.
The fuselage 1 head front end of above-mentioned aircraft is also provided with small size variable-distance screw propeller 5, with when larger change occurs for flying height and speed, ensures the Effec-tive Function of aircraft.
Embodiment 3
Present embodiments provide a kind of control method of the controller for the Helios in above-described embodiment 1 and 2, comprise the steps:
First, the irradiating angle of sunshine is obtained;
Then, the illuminating area of the thin-film solar cells on computer body surface and the solar radiant energy of unit area reception;
Finally, when the solar radiant energy that illuminating area and unit area receive is less than predetermined threshold value, direction towards the solar radiant energy increasing illuminating area and unit area reception repeatedly adjusts the rotation of two the first rotating shafts 41, until the solar radiant energy that illuminating area and unit area receive is maximum.
The control method of the controller for Helios that the present embodiment provides, the rotation of the first rotating shaft 41 can be controlled in real time according to the irradiating angle of sunshine, to increase the angle angle of the light-receiving area of the thin-film solar cells of body surface and itself and sunshine, thus obtain solar power more efficiently, to increase the cruise duration of aircraft.
In addition, for the aircraft in embodiment 1, the rotation direction of the second rotating shaft 42 can also be adjusted, thus the angle between adjustment two first end wings 21, with by the rotation of adjustment first rotating shaft 41 thus the angle adjusted between the first end wing 21 and the second end wing 22 combine, the solar radiant energy that the maximum and unit area of the illuminating area of the thin-film solar cells being located at body surface is received is maximum.
For aircraft in embodiment 2, then can adjust the 3rd rotating shaft 43 and the first rotating shaft 41 of the every side of fuselage simultaneously, the angle of the first end wing 21 and the second end wing 22 is changed, ensure that the solar radiant energy that illuminating area and unit area receive is maximum.
In addition, also comprise and adjust heading, flight attitude according to the irradiating angle of sunshine and air objective, until the solar radiant energy that illuminating area and unit area receive is maximum.
For the aircraft in embodiment 2, also comprise control empennage 3 and rotate, increase the illuminating area of the thin-film solar cells on empennage 3 surface and the solar radiant energy of unit area reception.
Obviously, above-described embodiment is only for clearly example being described, and the restriction not to embodiment.For those of ordinary skill in the field, can also make other changes in different forms on the basis of the above description.Here exhaustive without the need to also giving all embodiments.And thus the apparent change of extending out or variation be still among the protection domain of the invention.
Claims (8)
1. a Helios, comprise body, be arranged at the thin-film solar cells of described body surface and be arranged at the controller of described internal body, described body at least comprises symmetrically arranged two all-wing aircrafts (2), it is characterized in that, each described all-wing aircraft (2) at least comprises the first end wing (21) and the second end wing (22), and the described first end wing (21) and the described second end wing (22) are rotationally connected by the first rotating shaft (41).
2. Helios as claimed in claim 1, it is characterized in that, two described all-wing aircrafts (2) are rotationally connected by the second rotating shaft (42).
3. Helios as claimed in claim 1, it is characterized in that, described body also comprises fuselage (1) and two the 3rd rotating shafts (43), and two described all-wing aircrafts (2) are arranged at the both sides of described fuselage (1) respectively and are rotationally connected respectively by described 3rd rotating shaft (43) and described fuselage (1).
4. Helios as claimed in claim 3, it is characterized in that, the upper surface of described fuselage (1) is provided with the v-depression extended along its length.
5. Helios as claimed in claim 3, it is characterized in that, also comprise the empennage (3) being arranged at described fuselage (1) rear end, described empennage (3) is two, and arrange in inverted V-shaped, each described empennage (3) and described fuselage (1) are rotatably connected.
6. Helios as claimed in claim 5, it is characterized in that, the wing tip of described fuselage (1) head, described all-wing aircraft (2) and the wing tip of described empennage (3) are transparent material, and its inside is provided with the photovoltaic battery array towards described fuselage (1) front or top.
7. the Helios according to any one of claim 1-6, is characterized in that, the back edge of described all-wing aircraft (2) is provided with ducted fan (6); Described thin-film solar cells adopts the mode of inlaying to be combined with body; Also comprise the Hi cell (7) for energy supply, described Hi cell (7) is by being connected with described body by detaching structure.
8. the Helios according to any one of claim 1-6, is characterized in that, the span of described all-wing aircraft (2) is 2-10 rice, and chord length is 12-50 centimetre.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520475146.1U CN204802071U (en) | 2015-07-03 | 2015-07-03 | Helios |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520475146.1U CN204802071U (en) | 2015-07-03 | 2015-07-03 | Helios |
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| CN204802071U true CN204802071U (en) | 2015-11-25 |
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| CN201520475146.1U Active CN204802071U (en) | 2015-07-03 | 2015-07-03 | Helios |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081062A (en) * | 2016-07-02 | 2016-11-09 | 朱幕松 | solar energy unmanned plane |
| CN106275386A (en) * | 2016-09-05 | 2017-01-04 | 锋源创新科技成都有限公司 | A kind of wing, the manufacture method of wing and unmanned plane |
| CN111377052A (en) * | 2018-12-28 | 2020-07-07 | 东汉太阳能无人机技术有限公司 | Photovoltaic power supply aircraft and photovoltaic cell module power adjusting method thereof |
| CN114180027A (en) * | 2021-12-24 | 2022-03-15 | 清华大学 | Control method and controller of morphing aircraft and application of controller |
-
2015
- 2015-07-03 CN CN201520475146.1U patent/CN204802071U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081062A (en) * | 2016-07-02 | 2016-11-09 | 朱幕松 | solar energy unmanned plane |
| CN106081062B (en) * | 2016-07-02 | 2018-01-19 | 朱幕松 | solar energy unmanned plane |
| CN106275386A (en) * | 2016-09-05 | 2017-01-04 | 锋源创新科技成都有限公司 | A kind of wing, the manufacture method of wing and unmanned plane |
| CN111377052A (en) * | 2018-12-28 | 2020-07-07 | 东汉太阳能无人机技术有限公司 | Photovoltaic power supply aircraft and photovoltaic cell module power adjusting method thereof |
| CN114180027A (en) * | 2021-12-24 | 2022-03-15 | 清华大学 | Control method and controller of morphing aircraft and application of controller |
| CN114180027B (en) * | 2021-12-24 | 2023-04-07 | 清华大学 | Control method and controller of morphing aircraft and application of controller |
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