Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64B—LIGHTER-THAN AIR AIRCRAFT
  • B64B1/00—Lighter-than-air aircraft
  • B64B1/58—Arrangements or construction of gas-bags; Filling arrangements
  • B64B1/60—Gas-bags surrounded by separate containers of inert gas

Definitions

• Unmanned aerial vehicle for telecommunication or other scientific purposes
• the invention relates to an unmanned aerial vehicle for telecommunication or other scientific purposes, for stationing at a predetermined altitude in the stratosphere, according to the preamble of claim 1.
• gas-filled balloons high altitude balloons
• telecommunications and / or surveillance platforms in the stratosphere is known, for example, from the US 5,104,059 known.
• a particular problem of such balloons arises from the temperature differences to which they are exposed during the day on the one hand and at night on the other hand. During the day, the surface of the balloon is exposed to direct sunlight, and the gas inside the balloon is heated by solar radiation, increasing gas pressure. At night, on the other hand, the ambient and gas temperature and thereby also the gas pressure in the balloon sink. This places even more demands on the material and construction of the pressurized balloon. It also makes it difficult to maintain the altitude and platform position relative to the earth.
• the present invention has for its object to provide an unmanned aerial vehicle of the type mentioned, in which the platform-carrying, filled with gas balloon can be optimally maintained in the desired height and position, and he also has a long life ,
• the balloon carrying the platform is arranged inside an outer balloon which can be inflated into an aerodynamic outer shape in the stratosphere, and at least one low-pressure or high-pressure isolation chamber filled with a medium flows between this outer balloon and the inner balloon the inner balloon is formed, as a medium for the isolation chamber a Gas with a low thermal conductivity is used, the negative effects of temperature differences on the gas pressure in the inner balloon are largely avoided, so that it can be made of a lighter and cheaper material, and its lifetime is increased sustainably.
• the platform position relative to the earth can be maintained as unchanged as possible.
• FIG. 1 shows a first embodiment of an inventive aircraft in side view.
• FIG. 2 shows a part of the aircraft according to FIG. 1 in cross section
• Fig. 3 shows a second embodiment of an inventive aircraft in side view
• Fig. 4 shows a further variant of an inventive aircraft in a schematic longitudinal section or partially in view.
• FIG. 1 schematically shows an unmanned aerial vehicle 1 with a platform 10, a so-called “high altitude platform”, provided in particular for wireless communication and / or other scientific purposes in the stratosphere it occupies a stationary position to the ground, or it may also be arranged to be movable relative to the earth, if it for example, should be positioned stationary to a satellite in space flying.
• This aircraft is not only suitable as a telecommunication transmission station but also for scientific measurement purposes, a broadcasting station for TV or radio stations, for photographic purposes, as a weather station and much more. It is equipped with a GPS and other control devices, so that an automatic board control of the aircraft is made possible, with a remote control from a control center on Earth an electronic connection.
• the aircraft 1 is already at the desired height of 20 to 30 km, which is advantageous with respect to the wind conditions.
• the platform 10 which is equipped with corresponding devices (payload plane), is supported by a balloon 1 1 filled with gas, preferably helium 12.
• this platform 10 would be supported by supporting elements 17 extending around the balloon 11, such as Example tapes or the like, worn.
• the balloon 1 1 expediently having a pumpkin shape or another shape is located inside an outer balloon 12 having an aerodynamic outer shape, which passes through the platform 10 by means of the balloon 11 to the desired height, preferably 20.7 km, without problem the troposphere was filled with a medium and inflated into the aerodynamic outer shape.
• the outer balloon 12 is equipped at a rear end with a vertical and vertical stabilizer 13, 14.
• the propeller 15 are controlled with individual speeds to keep the aircraft always in the same direction to the earth's surface.
• the propellers 15 may also be pivotally mounted on the platform 10 and thus serve both of the above-mentioned purposes.
• the aircraft 1 according to the invention is also equipped with a controller and with an electronic autopilot system.
• a gas having a low thermal conductivity preferably xenon or krypton
• the thermal conductivity of krypton is 0.00949 W / m K, that of xenon 0.00569 W / m K.
• the inner balloon 1 1 is filled with this gas low or high pressure isolation chamber 20 is formed, through which the balloon 11 of which, for example, during the night and on the day resulting large temperature differences so to speak shielded and its temperature or its gas pressure is kept as constant as possible.
• the characteristic of poor thermal conductor gas preferably xenon or krypton is supplied as shown in FIG. 2 by means of a pump 21 from a memory 24 via a supply line 23 into the isolation chamber 20, the pump 21 and a supply of the gas in a separate, a Balancing chamber-forming balloon 28 allows, which provides for constant pressure and constant volume in the low or high pressure isolation chamber 20 and thus also for maintaining the aerodynamic outer shape of the outer balloon 12.
• the gas is thereby freed from any moisture before it enters the isolation chamber 20 arrives.
• a pressure and temperature measurement 26 and 27, which are connected to a control unit not shown in detail.
• the inner balloon 11 is preferably filled with helium (but it could also be another gas, such as hydrogen).
• a helium store 43 is connected via a line 49 to the interior of the balloon 11.
• a pump 47 allows a supply of helium either in this balloon 1 1 or in an additional balloon 58 which serves as a compensation chamber for pressure control of the entire aircraft. It is provided to the control unit available pressure measurement 48 in the line 49.
• the helium is supplied under pressure in the platform 10 supporting inner balloon 11, including a non-illustrated compressor is present.
• the pressure conditions in the inner balloon 1 1 are now controlled so that the temperature remains as constant as possible in its interior and thereby preferably corresponds to the night temperature of the outside air.
• the insulation chamber 20 filled with the gas having a low thermal conductivity ensures that the temperature differences of the outside air during the day and at night have as little effect on the internal balloon 11 as possible.
• a pressure increase in the balloon 1 1 is detected, so lets To escape via a pressure reduction valve, a portion of the helium in the additional balloon 58.
• the pressure measurement 48 indicates a pressure below the set point, the helium is pumped back into the inner balloon 1 1.
• the outer balloon 12 whose base material is polyethylene or the like, is provided with a solar collector film 40 over part of its surface, as shown in FIG.
• the electrical energy produced by solar radiation during the day is stored by means of batteries.
• the outer balloon 12 is also provided with an infrared collector film 41, with which the infrared radiation from the earth during the night is utilized.
• the infrared collector film 41 on the inside of the solar collector film 40 is preferably as a dark, about 12 micron thick aluminum film, a paint layer o.a. educated.
• Both the outer balloon 12, and the inner balloon 11 are advantageously made of a transparent plastic material, in which case the Infrarotkollektorfilm 41 is mounted on the earth facing the inside of the outer balloon 12.
• the infrared radiation can then penetrate from below through the two balloons and helps to compensate for the otherwise occurring during the night cooling temperature.
• the infrared collector film 41 covers a larger area of the outer balloon 12 than the solar collector film 40.
• the solar collector film 40 and the infrared collector film 41 are covered by a plastic foam layer, for example polystyrene, or by a different insulating material. covers. so that there is no excessive heating of the balloon surface.
• both the outer balloon 12 and the inner balloon 1 1 made of an aluminized plastic, which is a multi-layer material in which applied to a plastic, preferably polyethylene base an aluminum layer, in turn, by a plastic layer is covered.
• the aluminum layer on the one hand, causes reflection of rays and, on the other hand, improves the gas impermeability properties, i. less gas can escape through the balloon. Thanks to the reflection of rays, their thermal effect, which is to be "shielded" by the insulation chamber, can be reduced, and a solar collector film can again be applied to the surface of the outer balloon or over a region thereof.
• a chamber 20 ' which is arranged between the inner periphery of the outer balloon 12 and the outer circumference of the balloon 11 and extends helically around the balloon, is defined, which is bounded by transverse webs 50.
• a chamber 20 "arranged on the inner circumference of the outer balloon 12 and in turn helically spaced around the balloon 11 can be formed, which is formed by an approximately rectangular cross-section envelope or sheaths 50 '.
• these chambers 20 ', 20 are filled with the low thermal conductivity gas, for example xenon or krypton, and thus the low or high pressure isolation chamber is at least partially formed around the balloon 11.
• the low thermal conductivity gas for example xenon or krypton
• the outer balloon 12 can in turn be provided with the solar collector film and the infrared collector film, with which the solar radiation during the day and the infrared radiation from the earth at night are energetically utilized.
• the transverse webs 50 or these casings 50 'then expediently in turn - the same as the two balloons 1 1, 12 - preferably made of a transparent plastic material.
• both the outer balloon and the inner balloon 11 could be made of an aluminized plastic.
• the aircraft can remain in use much longer and together Platform 10 better maintain its position relative to the earth (or to a particular area on Earth) than is the case with conventional balloons.
• the aircraft 1 is of course equipped with a complete control, so that it is automatically in the desired position to the earth's surface. In addition, it is connected to a control center on the ground, so that data exchange and control options from Earth are feasible.
• Fig. 4 shows an unmanned aerial vehicle, which is designed to be the same as that of FIG. 1.
• the same reference numerals are therefore used for the unchanged parts.
• the outer balloon 12 and disposed within this, the platform 10 supporting, filled with gas balloon 1 1 available.
• the inner balloon 11 at least one additional balloon 31 is arranged with an inlet and outlet valve for a discharge or admission of gas, preferably air.
• a constant pressure is generated in the balloon surrounding this 1 1.
• a corresponding pressure regulation is provided in the balloon 31, which is not shown in detail, in which a pressure measurement in the inner balloon 1 1 takes place.
• the air can be removed from the additional balloon 31 or let in via a pump, so that in this way the pressure in the inner balloon 11 can be kept constant or adjusted as desired.
• the inner balloon 11 and the outer balloon 12 are held as another feature of the invention on its underside by a connecting means 34 to each other. This results in optimum stability of the aircraft. Also, the additional balloon 31 in the inner balloon 1 1 is also held on the underside of the latter.
• an anodized aluminum layer is present on the underside of the outer balloon as outer jacket. seen with which the infrared radiation is to be absorbed at night to generate heat in the isolation chamber.
• the platform 10 is connected in the context of the invention by a connecting element 30 with the underside of the outer balloon 12.
• the platform 10 is in this case held by an articulated joint 33 articulated to the outer balloon 12 and detachable by a not-shown coupling of this outer balloon.
• an electromagnetic is used as a coupling, by means of which a release without complicated mechanical devices is made possible.
• the isolation chamber 20 for the gas circulation on the underside of the outer balloon 12 is provided with one or more inlets 36 and on the top with one or more outlets 36 '. This allows for optimal cooling of the aircraft at daytime.

Applications Claiming Priority (2)

Publications (1)

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ID=37054240

Family Applications (1)

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• 2006
  • 2006-07-01 EP EP06762333A patent/EP1971519A1/de not_active Withdrawn
  • 2006-07-01 US US12/160,119 patent/US8286910B2/en not_active Expired - Fee Related
  • 2006-07-01 CA CA002636630A patent/CA2636630A1/en not_active Abandoned
  • 2006-07-01 AU AU2006334867A patent/AU2006334867A1/en not_active Abandoned
  • 2006-07-01 KR KR1020087017416A patent/KR20080092377A/ko not_active Application Discontinuation
  • 2006-07-01 WO PCT/EP2006/006409 patent/WO2007079788A1/de active Application Filing
  • 2006-07-01 JP JP2008549769A patent/JP2009522170A/ja active Pending
  • 2006-07-01 CN CN200680050719XA patent/CN101443231B/zh not_active Expired - Fee Related
• 2008
  • 2008-07-09 ZA ZA200805991A patent/ZA200805991B/xx unknown

Non-Patent Citations (1)

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