WO2010135604A2 - Système et procédé permettant de produire de l'énergie électrique à l'aide d'un système de production d'énergie embarqué captif - Google Patents

Système et procédé permettant de produire de l'énergie électrique à l'aide d'un système de production d'énergie embarqué captif Download PDF

Info

Publication number
WO2010135604A2
WO2010135604A2 PCT/US2010/035685 US2010035685W WO2010135604A2 WO 2010135604 A2 WO2010135604 A2 WO 2010135604A2 US 2010035685 W US2010035685 W US 2010035685W WO 2010135604 A2 WO2010135604 A2 WO 2010135604A2
Authority
WO
WIPO (PCT)
Prior art keywords
airfoil
controlling
flying
turbine driven
tether
Prior art date
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.)
Ceased
Application number
PCT/US2010/035685
Other languages
English (en)
Other versions
WO2010135604A3 (fr
Inventor
Joeben Bevirt
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
JOBY ENERGY Inc
Original Assignee
JOBY ENERGY Inc
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by JOBY ENERGY Inc filed Critical JOBY ENERGY Inc
Priority claimed from US12/784,294 external-priority patent/US20110127775A1/en
Priority claimed from US12/784,328 external-priority patent/US20100283253A1/en
Publication of WO2010135604A2 publication Critical patent/WO2010135604A2/fr
Publication of WO2010135604A3 publication Critical patent/WO2010135604A3/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D13/00—Assembly, mounting or commissioning of wind motors; Arrangements specially adapted for transporting wind motor components
    • F03D13/20—Arrangements for mounting or supporting wind motors; Masts or towers for wind motors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D9/00—Adaptations of wind motors for special use; Combinations of wind motors with apparatus driven thereby; Wind motors specially adapted for installation in particular locations
    • F03D9/20—Wind motors characterised by the driven apparatus
    • F03D9/25—Wind motors characterised by the driven apparatus the apparatus being an electrical generator
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—ELECTRIC POWER NETWORKS; CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J3/00—Circuit arrangements for AC mains or AC distribution networks
    • H02J3/38—Arrangements for feeding a single network from two or more generators or sources in parallel; Arrangements for feeding already energised networks from additional generators or sources in parallel
    • H02J3/381—Dispersed generators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/40—Use of a multiplicity of similar components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/90—Mounting on supporting structures or systems
    • F05B2240/92—Mounting on supporting structures or systems on an airbourne structure
    • F05B2240/921—Mounting on supporting structures or systems on an airbourne structure kept aloft due to aerodynamic effects
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—ELECTRIC POWER NETWORKS; CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J2101/00—Supply or distribution of decentralised, dispersed or local electric power generation
    • H02J2101/20—Dispersed power generation using renewable energy sources
    • H02J2101/28—Wind energy
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—ELECTRIC POWER NETWORKS; CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J3/00—Circuit arrangements for AC mains or AC distribution networks
    • H02J3/36—Arrangements for transfer of electric power between AC networks via high-voltage DC [HVDC] links; Arrangements for transfer of electric power between generators and networks via HVDC links
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/72—Wind turbines with rotation axis in wind direction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/728—Onshore wind turbines
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/76—Power conversion electric or electronic aspects

Definitions

  • This invention relates to power generation, and more specifically to airborne wind-based power generation.
  • Wind turbines for producing power are typically tower mounted and utilize two or three blades cantilevered out from a central shaft which drives a generator, usually requiring step up gearing due to the low rotational speed of the blades.
  • ground based electrical generation devices are somewhat hampered by the low power density and extreme variability of natural wind currents (in time and space) at low altitudes.
  • typical average power density at the ground is less than about 0.5 kilowatts per square meter (kW/m 2 ). Higher altitudes offer more promising energy densities.
  • a tethered airborne electrical power generation system which may utilize a strutted frame structure with airfoils built into the frame to keep wind turbine driven electrical generators which are within the structure airborne.
  • the primary rotors utilize the prevailing wind to generate rotational velocity.
  • electrical power generated is returned to ground using a tether that is also adapted to fasten the flying system to the ground.
  • the flying system is adapted to be able to use electrical energy to provide power to the generators which are used as motors to raise the system from the ground, or mounting support, into the air.
  • the system may then be raised into a prevailing wind and use airfoils in the system to provide lift while the system is tethered to the ground.
  • the motors may then resume operation as generators for electrical power generation.
  • the system may be somewhat planar in that many turbines may have their rotors substantially in one or more planes or planar regions.
  • the system may also be adapted to be assembled of modular components such that a variety of different numbers of turbines may be flown, yet the system may be substantially constructed from multiple similar members.
  • Figure 1 is a sketch of a strutted frame structure with a single plane of airfoils according to some embodiments of the present invention.
  • Figure 2 is a sketch of a strutted frame structure with two planes of airfoils according to some embodiments of the present invention.
  • Figure 2A is a sketch of a side view of a strutted frame structure with two planes of airfoils according to some embodiments of the present invention.
  • Figure 3 is a perspective view of a flying strutted frame structure with wind turbine driven generators according to some embodiments of the present invention.
  • Figure 4 is a side view of a flying strutted frame structure with wind turbine driven generators according to some embodiments of the present invention.
  • Figure 5 is a close up partial view of a flying strutted frame structure with wind turbine driven generators according to some embodiments of the present invention.
  • Figure 6 is a sketch of a strutted frame structure on the ground according to some embodiments of the present invention.
  • Figure 7 is a sketch of a flying structure according to some embodiments of the present invention.
  • Figure 8 is a cross-sectional view of a tether according to some embodiments of the present invention.
  • Figure 9 is a cross-sectional view of a tether according to some embodiments of the present invention.
  • Figure 10 is a sketch of a tether with a aerodynamic tether sheath according to some embodiments of the present invention.
  • Figure 11 is a perspective view of an airborne power generation system according to some embodiments of the present invention.
  • Figures 12A-B are a front and side view, respectively, of a stationary flight profile according to some embodiments of the present invention.
  • Figures 13A-B are a front and side view, respectively, of a cross-wind flying profile according to some embodiments of the present invention.
  • Figure 14 is a perspective view of an airborne power generation system with a front canard according to some embodiments of the present invention.
  • Figure 15 is a side view of a power generation system on the ground according to some embodiments of the present invention.
  • Figure 16 is a front view of a power generation system with a single airfoil according to some embodiments of the present invention.
  • an airborne power generation system is adapted to be built in varying sizes, and to provide differing levels of power, through the use of a modular design.
  • a strutted frame structure design with airfoil sections as part of the frame structure and with wind driven power generation turbines is adapted to be flown while tethered to a ground station.
  • the tether may be adapted to be the structural attachment to the ground and also the electrical power conduit between the frame structure and the ground.
  • the power generation system may be sized using modular aspects of both the structural and electrical design.
  • the strutted frame structure is planar, and in other aspects the strutted frame structure may have multiple planes of struts and airfoil sections.
  • the power generation system may be launched from the ground using vertical take-off with the assistance of ground power.
  • an airborne power generation system 10 utilizes a strutted frame structure 11 with wind turbine driven generators 14 arranged in planar frame.
  • the strutted frame structure 11 is attached to a ground station 13 using a tether 12 which may be attached to one or more central pylons 19 or other structural members.
  • the frame structure 11 has rows of airfoil sections 15 which are used in the horizontal positions within the frame.
  • the airfoils sections may all be of the same size and construction.
  • Wind turbine driven generators 14 may be placed at most of the junctions of the airfoil sections 15.
  • Support pylons 17 may also be placed at some junctions of the airfoil sections, and at the ends of the airfoil sections.
  • the support pylons are adapted to support guy wires 18 which may run from one or more inner pylons to the outer pylons, and which are adapted to add structural strength and stiffness to the frame structure under load.
  • the support pylons may extend both forward and rearward from the airfoil sections, allowing for the use support guy wires both in front of and rearward of the airfoil sections.
  • Cross supports 16 run from a junction between two airfoil sections of one row to the junction between two airfoil sections of the row above and/or below that row.
  • each of the airfoil sections may be identical. This allows for modularity in design in that systems of different sizes may be used without redesign of the airfoil sections, and without the associated costs of multiple manufacturing lines.
  • the airfoil sections may connect to different components at their ends, such as wind turbine driven generators or support pylons, different end fittings may be used as connections depending upon the location in the frame structure.
  • An airfoil section end fitting which connects along the perimeter of the frame structure will have a different number of connections than does an end fitting along the interior of the frame, for example.
  • cross supports may also be identical to each other.
  • the use of smaller, modular pieces in the strutted frame structure allows for cost reductions in shipping.
  • the major components, each of which may be repeatedly used in the assembly of a frame structure may be small enough such that they are easily fit into standard cargo containers.
  • Each of the wind turbine driven generators may be identical. With the use of many wind turbine driven generators, system reliability is enhanced in that the failure of a single generator may not interfere with the power generation capability of other generators. Thus, in the case of an airborne system, the loss of functionality of a single wind turbine driven generator would not necessitate the grounding of the system.
  • the frame structure may be designed against the power capability design needs such that varying amounts of redundancy are designed in, allowing for some wind turbine driven generators to fail and still have adequate system capability.
  • the airborne power generation system 10 is adapted to fly in a stationary position in winds aloft, or to engage in a cross-wind flying paradigm, or other flying method.
  • the airfoil sections are adapted to provide sufficient lift such that the frame structure 11 is able to maintain itself aloft while generating power.
  • the support pylons and guy wires are adapted to enhance the strength and stiffness of the frame structure.
  • the frame structure which consists of the cross supports and airfoil sections, is essentially a single plane of structure in some embodiments, wherein the leading edges of the airfoils are all in plane with each other.
  • an airborne power generation system 30 utilizes a strutted frame structure 31 with wind turbine driven generators 14 arranged in multi-planar frame.
  • the strutted frame structure 31 is attached to a ground station 13 using a tether 12 which may be attached to a central pylon 38.
  • the frame structure 31 has rows of airfoil sections 32 which are used in the horizontal positions within the frame.
  • the airfoils sections may all be of the same construction.
  • Wind turbine driven generators 14 may be placed at most of the junctions of the airfoil sections 32.
  • a first plane of airfoil sections has the leading edges of the airfoils in the same plane, as seen in Figure 2A.
  • a second plane of airfoil sections has the leading edges of the airfoil section at a plane behind and parallel to the first plane of airfoil sections.
  • Cross supports 33 run from a junction between two airfoil sections of one row to the junction between two airfoil sections of the row above and/or below that row. The cross supports 33 are also run from the junction between two airfoils in the first plane to the junction between two airfoils in the second plane.
  • the use of a second plane of airfoils behind the first plane of airfoils brings a variety of advantages.
  • One advantage is the stability of the flight of the two plane strutted frame structure.
  • Another advantage is that the strength and rigidity of the structure added by the second plane of airfoils and cross supports may eliminate the need for support guy wires, which also allows more junctions between airfoil sections in the front plane of airfoils to be available for power generation turbines.
  • Another advantage of the second plane of airfoils is the added lift generated by the additional airfoil sections.
  • the strutted frame structure 31 of the multi-planar airborne power generation system 30 may utilize the same modular airfoil segments 32 in both the front plane and the back plane of the structure.
  • the cross supports 33 which interlink the front plane airfoil segments may be identical to the cross supports which interlink the rear plane airfoil segments, and be identical to the cross supports which interlink the front plane and the rear plane segments.
  • FIGs 3, 4, and 5 illustrate an embodiment of the present invention wherein a power generation system utilizes a large single plane strutted frame structure 100 shown as may be seen when airborne and constrained by a tether 101.
  • the middle row 130 is wider than the rows of airfoils above and below 131, 132, 133, with each row successively shorter by the span of one airfoil segment.
  • Support pylons 124, 125 face forward and rearward for use with front support guy wires 141 and rear support guy wires 140. The support guy wires enhance strength and stiffness of the strutted frame structure.
  • the horizontal sections 121 of the frame structure are airfoil elements.
  • the cross struts 120, 122 are utilized to form equilateral triangle subsections of the frame structure in some embodiments.
  • Wind turbine driven generators 110 are placed at most of the junctions of the airfoils and cross struts, although support pylons 123, 124 are used at some locations.
  • the support guy wires 127 may link at a guy wire junction 126 and be routed to and attached to various locations depending upon the specific size and geometry of a particular modular design.
  • the leading edges of the different rows of airfoil segments may be staggered.
  • the rows of airfoil segments may be used to create a swept back wing shape.
  • the wind turbine driven generators may utilize blades which are pitch controllable.
  • the blade pitch may be controlled with mechanisms at the hub into which the blades are attached.
  • the blade pitch control may allow the blade pitch to be adjusted to allow for better efficiencies depending upon the apparent wind speed at the turbine, as well as limiting rotor speed in high speed winds.
  • the blade pitch control may also allow the drag of a turbine to be altered to allow for attitude control of the strutted frame structure using differential control of the drag of turbines throughout the structure.
  • Figures 6 and 7 illustrate the vertical take-off aspect of the power generation system.
  • the frame structure 200 is adapted to rest on the ground, or on a support structure, or float on water such that the front of the airfoil sections 201 is facing skyward and the power generation turbines 203 are also facing skywards.
  • the electrical portion of the system is adapted to receive power via the tether 204 from the ground station 205 and use that power the turbines as engines. The engines can thus raise the strutted frame structure from the ground into the air.
  • the control system may be adapted to first raise the frame structure in a horizontal position and then the frame may be moved to a vertical position, resulting in a tethered position and flying based upon lift of the airfoils.
  • the vertical take-off scenarios are used with single and multiplane systems.
  • the multiple rotors (four as seen if Figures 6 and 7) allow for a 2 dimensional spacing of the rotors, greatly enhancing the safety and controllability of the system during takeoff and landing. With the rotors spaced in two-dimensions relative to the plane of the ground, differentiation of thrust between the rotors allows for two-axis control of the structure during take-off and landing.
  • the wind turbine driven generators may operate as motor driven propellers during this aspect.
  • electrical power to power the motors during take-off and landing travels via the tether from the ground station. In some embodiments, the electrical power to power the motors during take-off and landing may come from a battery storage system on the structure itself.
  • attitude adjustments of the frame structure may be achieved using differential control of the wind turbine driven generators.
  • the drag on the upper portion of the structure may be increased, and the drag on the lower part of the structure may be decreased, resulting in a "tilt", or pitching up, of the frame structure.
  • the changes in drag may be due to changing the loading on the power generation turbines such that the turbine rotational speed is lessened or raised.
  • the attitude of the frame in general may be controlled using this differential control of the various turbines, which in turn allows for position control relative to wind direction, as well as altitude control.
  • attitude control and position control are used to implement path control of the flying structure.
  • pitch and yaw control of the structure may be implemented by varying the amount of drag of individual wind turbine driven generators.
  • positive thrust may be used at one or more generators (which then become thrusting motors).
  • attitude and altitude control may utilize control surfaces on the airfoils or otherwise mounted within the strutted frame structure.
  • a full sensor system, or portions thereof resides on the frame structure.
  • Sensors may include altitude sensors, attitude sensors, accelerometers, wind speed sensors, global positioning system monitoring, and other sensors.
  • the vehicle may include markers for infrared sensing of the structure from the ground or other observation points.
  • the structure may include on-board cameras to view the flight path, or the horizon, as desired by the control system and/or the user.
  • the power delivered from each generator will be joined in a system bus and then routed via electrical conductors in the tether to the ground.
  • the power from the airborne power generation system may be routed to the ground using high voltage DC.
  • the wind turbine driven generators may generate AC in the range of 400-5000 volts.
  • a motor controller is used to convert the AC output to a DC output in the same range as the AC input, wherein the AC motor voltage may be the same voltage as the DC output voltage of the motor controller, which may be referred to as the motor voltage.
  • the DC motor voltage is then converted to a high DC voltage, which is then the voltage at which power may be transferred to the ground via the tether.
  • the high voltage DC may be referred to as the tether voltage.
  • each motor controller for each wind turbine driven generators may have its own DC-DC converter.
  • the lower voltage DC output from each motor controller may go to one or more motor voltage busses, each of which then have one or more DC-DC converters which raise the voltage to the tether voltage.
  • the use of multiple motor voltage busses, each of which receives input from multiple generators, and each of which in turn has utilizes multiple DC-DC converters to convert to the tether voltage allows for redundancy of the converters per motor voltage bus such that the failure of a single DC-DC converter does not reduce the power transmission from that motor voltage bus in most if not all operating conditions.
  • the term motor controller is used for the unit which controls the motor when the unit is used as a motor, and also controls the unit when used as a generator.
  • the strutted frame structure is adapted for take-off from the ground using powered flight. The power may come from the ground station and be routed through the tether to the wind turbine driven generators, which then operate as motor driven propellers.
  • the electrical power delivery components used for airborne power generation may be adapted to transmit power in both directions.
  • the DC-DC converters may be Dual Active Bridge (DAB) DC-DC converters.
  • the DAB converter may use an SiC JFET cascade switch, which may give an advantage to the system in the form of size and mass savings.
  • the electrical system may use a single larger DC-DC converter to convert a single motor voltage bus to the higher tether voltage.
  • the electrical control system may also control the motor controllers for each individual wind turbine driven generator, allowing for control of overall power production, for attitude control of the flying frame, and for other reasons.
  • the tether used to attach the airborne system to the ground will be used to transmit power as well as being a structural attachment.
  • the tether may be wound around a drum on the ground that is used to reel in and out the tether as well as store the unused portion of the tether.
  • the main drum which is used to mechanically reel the tether in and out may have a limited number of revolutions of the tether on it, with the remainder of the tether trailing off of this main drum onto a storage drum. This may allow a rotation of the main drum to result in a more uniform amount of tether to be reeled regardless of the altitude of the flying system.
  • a tether 200 is adapted for both structural attachment and electrical conduction.
  • An outer layer 201 may be a polymer layer, such as Hytrel.
  • the outer layer 201 may be .75mm thick.
  • An inner layer 202 may be adapted to carry the tensile load.
  • the inner layer 202 may be of Kevlar and may be 2.3mm thick.
  • An inner core 203 may be of silicone with a mylar sheath and may be .lmm thick.
  • the conductors 204, 205 may use 1.4mm diameter copper surrounded by an insulator. In other embodiments, more conductors may be used.
  • a tether 210 may use a coaxial geometry.
  • the outer layer 211 may be of aluminum and be 2.7mm thick.
  • the use of aluminum as the outer conductor, on the outside of the tether, allows for convective cooling of one of the conducting portions of the tether.
  • the use of the outer portion of the tether as a conductor allows for the wound portions of the tether on the drum to create a common conductor, which can allow for current to be put in or taken out via the drum, thus not requiring current to flow in the captured, wound portions of the tether which may otherwise overheat.
  • the inner layer 212 may be adapted to carry the tensile load and may be Kevlar of 56.1mm thickness.
  • An insulator core 213 may used inside the inner layer 212.
  • a central conductor 214 may be of aluminum and be 19mm in diameter.
  • a tether assembly wherein a tether sheath has been placed over a tether may significantly reduce the drag of a tether.
  • the tether may have a certain drag while experiencing apparent winds.
  • a 0.4 inch cylindrical tether may have a drag force in a 35 mph wind of 0.15 pounds per linear foot of tether. At 65 mph, this drag may increase to 0.46 pounds per linear foot.
  • the sheathed tether drag may be 0.034 pounds per linear foot at 35 mph, and 0.062 pounds per linear foot at 65 mph.
  • the drag reduction may be in the range of 80- 90%.
  • the tether sheath may be manufactured in relatively short lengths, and then have the longer tether inserted through it.
  • a tether may be 1000 meters long.
  • the tether sheath could thus be manufactured in shorter lengths, in the range of 3-15 meters, and be inserted over the tether after the prior manufacture of both the tether and the sheath.
  • Tethers and tether sheaths according to embodiments of this invention may be advantageous not only for reduced drag but also for their dynamic effects.
  • a tether sheath may allow for rotation around the tether in a manner which enhances the dynamic stability performance of the system.
  • a 32OkW system may use 16 wind turbine driven generators.
  • the frame structure uses five rows of airfoil segments, with the middle row 8 segments wide, the next two (upper and lower) with 7 segments, and the top and bottom row having 6 airfoil segments each.
  • the system is designed around the nominal conditions of 12 meters/second of wind speed at 1000 meters. The system would use a cross- wind flying method resulting in a resultant wind speed of 49.2 meters/second.
  • a total of 44 airfoil segments would be used, each with a span of 2 meters and a chord length of 0.8 meters.
  • 84 cross struts would be used, with a length of 1.2 meters and a chord length of .4 meters.
  • the cross struts would use a symmetric airfoil shape to reduce drag.
  • Each of the wind turbine driven generators would be adapted to provide 2OkW while rotating at 3000 rpm using two 0.8 meter radius blades.
  • the power generation turbine would weigh 8kg.
  • the strutted frame structure with its turbines would weigh 964 kg, and the tether weight would be 1480 kg, for a total airborne mass of 2444 kg.
  • a IOOMW system may use 220 wind turbine driven generators.
  • the frame structure uses 13 rows of airfoil segments in its front plane of airfoils, with the middle row 20 segments wide, the next two (upper and lower) with 19 segments, with one less segment per row as distance from the middle row is increased, and with the top and bottom row having 14 airfoil segments each.
  • the frame structure uses 11 rows of airfoil segments in its rear plane of airfoils, with the middle row 19 segments wide, and one less airfoil segment per row in the upper and lower directions, with the top and bottom rows having 14 airfoil segments each.
  • the system is designed around the nominal conditions of 16 meters/second of wind speed at 6600 meters.
  • the system would use a cross-wind flying method resulting in a resultant wind speed of 66.2 meters/second.
  • a total of 390 airfoil segments would be used, each with a span of 12 meters and a chord length of 2.2 meters.
  • 1100 cross struts would be used, with a length of 12 meters and a chord length of 1.1 meters.
  • the cross struts would use a symmetric airfoil shape to reduce drag.
  • the cross struts With the cross struts the same length as the airfoil segments, the cross struts would run from each end of an airfoil segment on one row to the junction between two airfoil segments of the row above or below, forming an equilateral triangle.
  • the same cross struts would be used to connect the front plane of the frame structure to the rear plane of the frame structure, resulting in the rear plane rows being slightly above the front plane rows, traversing through the centroid to the equilateral triangle of the front row when viewed in a front perspective.
  • Each of the wind turbine driven generators would be adapted to provide 45OkW while rotating at 420 rpm using two 5.5 meter radius blades.
  • the power generation turbine would weigh 188kg.
  • Wind turbine driven generators would be mounted into the front row of airfoils only.
  • the strutted frame structure with its turbines would weigh 99,893 kg, and the total weight of the system including tether weight would be 375,408 kg.
  • the tether length would be 10,158 meters, with a tether diameter of 13.62 cm.
  • an airborne power generation system 900 may have two rows of airfoils 901, 902.
  • the system may be adapted to use a tether 903 with a nominal length of 1000m.
  • the system may utilize 12 turbine driven generators 904 which are mounted along the two rows of airfoils.
  • the turbines (propellers) may have a diameter of 2.4m.
  • the nominal total power rating of such a system may be IMW.
  • the system may be adapted for flying at 74 meters/second in an 8.5 meters/second ambient wind using a cross wind flight path such as a circular flight path.
  • the horizontal sections of the frame structure are airfoil elements.
  • Power generation turbines are placed at most of the junctions of the airfoils and cross struts.
  • the power generation turbines may utilize blades which are pitch controllable.
  • the blade pitch may be controlled with mechanisms at the hub into which the blades are attached.
  • the blade pitch control may allow the blade pitch to be adjusted to allow for better efficiencies depending upon the apparent wind speed at the turbine, as well as limiting rotor speed in high speed winds.
  • the blade pitch control may also allow the drag of a turbine to be altered to allow for attitude control of the strutted frame structure using differential control of the drag of turbines throughout the structure.
  • a flying frame structure 1300 adapted for airborne power generation may use a single airfoil 1301.
  • the system may use turbine driven generators 1302 above the airfoil 1301 and also generators 1303 which are below the airfoil.
  • the spacing both above and below the airfoil enhances the control of the structure by spacing the thrust/drag elements across two dimensions.
  • the airborne power generation structure flies in a substantially circular flight path 1011.
  • the airborne power generation structure may achieve a nominal average flight speed of 74 meter/second of composite apparent wind speed, which is substantially higher than the ambient wind speed.
  • the composite apparent wind speed is the resultant through the turbine from the cross-wind flying speed and the ambient wind speed.
  • an airborne power generation vehicle 1200 includes a front canard 1203 which may be mounted forward of the main part of the vehicle on a canard boom 1204.
  • a top airfoil 1201 and a bottom airfoil 1202 may each have four generators 1207 driven by turbines 1206.
  • the turbine driven generators may be operated as motor driven propellers.
  • the airborne power generation vehicle 1200 may be tethered to a ground stations with a tether 1205.
  • the tether 1205 may be a combination of a structural attachment and an electrical conduit.
  • the front canard 1203 on the canard boom 1204 may be adjusted in pitch using a canard controlling mechanism 1203.
  • Figure 15 illustrates a distinct advantage of an airborne power generation vehicle 1200 with a front canard 1203 with regard to vertical take-off and landing.
  • the airborne power generation vehicle 1200 may be adapted to engage in vertical take-off and landing.
  • the bottom of the vehicle 1200 (which is the rear in regular flight) while on the ground 1221 may reside upon struts 1220.
  • the front canard 1203 and the canard boom 1204 are extended upwards in the take-off position.
  • the front canard configuration blends well with the vertical take-off and landing aspects of the vehicle.
  • the entire front canard 1203 is adapted to pivot around an axis parallel to the leading edge of the front canard.
  • the canard controlling mechanism 1203 may pivot the front canard 1203 which in turn will cause a pitch change of the vehicle 1200.
  • Figures 9 A and 9B illustrate a front view and a top view, respectively, of the airborne power generation vehicle 1200 flown with a front canard 1203.
  • the vehicle 1200 may be controlled in pitch using the front canard, or using the front canard in conjunction with other methods described herein.

Landscapes

  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Wind Motors (AREA)

Abstract

La présente invention a trait à un système de production d'énergie électrique embarqué captif qui peut utiliser une structure de cadre renforcée pourvue de surfaces portantes construites dans le cadre afin de maintenir des générateurs entraînés par des éoliennes qui sont à l'intérieur de la structure embarquée. Les rotors primaires utilisent le vent dominant afin de produire une vitesse de rotation. L'énergie électrique produite est renvoyée au sol à l'aide d'une amarre qui est également conçue pour attacher le système volant au sol. Le système volant est conçu pour pouvoir utiliser l'énergie électrique en vue de fournir de l'énergie aux turbines primaires qui sont utilisées en tant que moteurs pour soulever le système à partir du sol, ou le support de montage, dans l'air. Le système peut alors être soulevé dans un vent dominant et utiliser les surfaces portantes dans le système afin de permettre le soulèvement tandis que le système est amarré au sol. Les moteurs peuvent ensuite recommencer l'opération en tant que turbines pour la production d'énergie électrique. Le système peut être globalement plan du fait que les rotors de nombreuses turbines peuvent sensiblement se situer sur un ou plusieurs plans ou une ou plusieurs régions planes. Le système peut également être conçu pour être constitué de composants modulaires de manière à ce qu'une variété de nombres différents de turbines puisse voler, bien que le système puisse être sensiblement constitué de multiples éléments similaires.
PCT/US2010/035685 2009-05-20 2010-05-20 Système et procédé permettant de produire de l'énergie électrique à l'aide d'un système de production d'énergie embarqué captif Ceased WO2010135604A2 (fr)

Applications Claiming Priority (16)

Application Number Priority Date Filing Date Title
US17984009P 2009-05-20 2009-05-20
US61/179,840 2009-05-20
US23652109P 2009-08-24 2009-08-24
US61/236,521 2009-08-24
US25817709P 2009-11-04 2009-11-04
US61/258,177 2009-11-09
US61/267,430 2009-12-01
US26743009P 2009-12-07 2009-12-07
US12/784,394 2010-02-20
US12/784,306 2010-05-20
US12/784,328 2010-05-20
US12/784,294 US20110127775A1 (en) 2009-05-20 2010-05-20 Airborne Power Generation System With Modular Structural Elements
US12/784,306 US20100295320A1 (en) 2009-05-20 2010-05-20 Airborne Power Generation System With Modular Electrical Elements
US12/784,328 US20100283253A1 (en) 2009-03-06 2010-05-20 Tethered Airborne Power Generation System With Vertical Take-Off and Landing Capability
US12/784,294 2010-05-20
US12/784,394 US20100295321A1 (en) 2009-05-20 2010-05-20 Method for Generating Electrical Power Using a Tethered Airborne Power Generation System

Publications (2)

Publication Number Publication Date
WO2010135604A2 true WO2010135604A2 (fr) 2010-11-25
WO2010135604A3 WO2010135604A3 (fr) 2011-01-13

Family

ID=43126992

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2010/035685 Ceased WO2010135604A2 (fr) 2009-05-20 2010-05-20 Système et procédé permettant de produire de l'énergie électrique à l'aide d'un système de production d'énergie embarqué captif

Country Status (1)

Country Link
WO (1) WO2010135604A2 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015039056A1 (fr) * 2013-09-16 2015-03-19 Google Inc. Procédés et systèmes de transition d'un véhicule aérien entre vol par vent de travers et vol stationnaire
WO2015094471A1 (fr) * 2013-12-19 2015-06-25 Google Inc. Commande de production de puissance fondée sur la trajectoire pour un véhicule aérien
WO2015103013A1 (fr) * 2013-12-30 2015-07-09 Google Inc. Procédés et systèmes de transition d'un véhicule aérien entre un vol par vent latéral et vol stationnaire
US9126682B2 (en) 2013-09-16 2015-09-08 Google Inc. Methods and systems for transitioning an aerial vehicle between hover flight and crosswind flight
US9151272B2 (en) 2013-12-31 2015-10-06 Google Inc. High frequency bi-directional AC power transmission
US10145356B1 (en) 2017-08-04 2018-12-04 X Development Llc Nodes for multiple aerial vehicles connected to a single ground station
EP3460232A1 (fr) * 2017-09-21 2019-03-27 Technische Universität München Système aéroporté et système et procédé de production d'énergie aéroportés

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2062599A (en) * 1933-12-11 1936-12-01 Boulton Aircraft Ltd Aeroplane
US4088285A (en) * 1976-09-15 1978-05-09 Japan Aircraft Manufacturing Co., Inc. Motor-glider
US4735552A (en) * 1985-10-04 1988-04-05 Watson William K Space frame wind turbine
DE19700182A1 (de) * 1997-01-04 1998-07-09 Industrieanlagen Betriebsges Luftfahrzeug mit einem im wesentlichen als aerostatischem Auftriebskörper ausgebildeten Rumpf
FR2760492B1 (fr) * 1997-03-10 2001-11-09 Jeumont Ind Systeme de production d'energie electrique associe a une eolienne
GB2331858A (en) * 1997-11-28 1999-06-02 Asea Brown Boveri A wind power plant
US7183663B2 (en) * 2001-11-07 2007-02-27 Bryan William Roberts Precisely controlled flying electric generators
AUPR871201A0 (en) * 2001-11-07 2001-11-29 Roberts, Bryan William Windmill kite
US7382113B2 (en) * 2006-03-17 2008-06-03 Yuan Ze University High-efficiency high-voltage difference ratio bi-directional converter

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2018103985A (ja) * 2013-09-16 2018-07-05 エックス デベロップメント エルエルシー 横風飛行とホバー飛行の間で航空車両を移行させる方法およびシステム
US9126675B2 (en) 2013-09-16 2015-09-08 Google Inc. Methods and systems for transitioning an aerial vehicle between crosswind flight and hover flight
US9126682B2 (en) 2013-09-16 2015-09-08 Google Inc. Methods and systems for transitioning an aerial vehicle between hover flight and crosswind flight
US9994314B2 (en) 2013-09-16 2018-06-12 X Development Llc Methods and systems for transitioning an aerial vehicle between hover flight and crosswind flight
US9637231B2 (en) 2013-09-16 2017-05-02 X Development Llc Methods and systems for transitioning an aerial vehicle between hover flight and crosswind flight
WO2015039056A1 (fr) * 2013-09-16 2015-03-19 Google Inc. Procédés et systèmes de transition d'un véhicule aérien entre vol par vent de travers et vol stationnaire
US9317043B2 (en) 2013-12-19 2016-04-19 Google Inc. Path based power generation control for an aerial vehicle
WO2015094471A1 (fr) * 2013-12-19 2015-06-25 Google Inc. Commande de production de puissance fondée sur la trajectoire pour un véhicule aérien
US9170582B2 (en) 2013-12-19 2015-10-27 Google Inc. Path based power generation control for an aerial vehicle
CN105873824A (zh) * 2013-12-30 2016-08-17 谷歌公司 在侧风飞行和悬停飞行之间转换飞行器的方法和系统
EP3483072A1 (fr) * 2013-12-30 2019-05-15 X Development LLC Procédés et systèmes de transition d'un véhicule aérien entre un vol par vent latéral et vol stationnaire
AU2018286597B2 (en) * 2013-12-30 2019-12-05 Makani Technologies Llc Methods and systems for transitioning an aerial vehicle between crosswind flight and hover flight
US9169013B2 (en) 2013-12-30 2015-10-27 Google Inc. Methods and systems for transitioning an aerial vehicle between crosswind flight and hover flight
EP3089911A4 (fr) * 2013-12-30 2017-08-16 X Development LLC Procédés et systèmes de transition d'un véhicule aérien entre un vol par vent latéral et vol stationnaire
US9174732B2 (en) 2013-12-30 2015-11-03 Google Inc. Methods and systems for transitioning an aerial vehicle between crosswind flight and hover flight
WO2015103013A1 (fr) * 2013-12-30 2015-07-09 Google Inc. Procédés et systèmes de transition d'un véhicule aérien entre un vol par vent latéral et vol stationnaire
US9151272B2 (en) 2013-12-31 2015-10-06 Google Inc. High frequency bi-directional AC power transmission
US9567979B2 (en) 2013-12-31 2017-02-14 X Development Llc High frequency bi-directional AC power transmisssion
US10145356B1 (en) 2017-08-04 2018-12-04 X Development Llc Nodes for multiple aerial vehicles connected to a single ground station
US10502179B2 (en) 2017-08-04 2019-12-10 Makani Technologies Llc Nodes for multiple aerial vehicles connected to a single ground station
EP3460232A1 (fr) * 2017-09-21 2019-03-27 Technische Universität München Système aéroporté et système et procédé de production d'énergie aéroportés
WO2019057634A1 (fr) * 2017-09-21 2019-03-28 Florian Bauer Système aéroporté et procédé et système de production d'énergie aéroporté
US11280317B2 (en) 2017-09-21 2022-03-22 kiteKRAFT UG (haftungsbeschrankt) Airborne system and airborne power generation system and method

Also Published As

Publication number Publication date
WO2010135604A3 (fr) 2011-01-13

Similar Documents

Publication Publication Date Title
US20100295320A1 (en) Airborne Power Generation System With Modular Electrical Elements
US20100283253A1 (en) Tethered Airborne Power Generation System With Vertical Take-Off and Landing Capability
US20110121570A1 (en) System and method for controlling a tethered flying craft using tether attachment point manipulation
US7582981B1 (en) Airborne wind turbine electricity generating system
US9388794B2 (en) Flying electric generators with clean air rotors
US20100032947A1 (en) Apparatus for generating power using jet stream wind power
US7188808B1 (en) Aerialwind power generation system and method
US7830033B2 (en) Wind turbine electricity generating system
US7786610B2 (en) Funneled wind turbine aircraft
US9109575B2 (en) Flying electric generators with clean air rotors
US20080048453A1 (en) Tethered Wind Turbine
EP2660151B1 (fr) Avion solaire autonome
US8109711B2 (en) Tethered autonomous air vehicle with wind turbines
US20100026007A1 (en) Apparatus and method for harvesting wind power using tethered airfoil
US20110266395A1 (en) Tether sheaths and aerodynamic tether assemblies
US20110101692A1 (en) Airborne wind powered generator
US20100221112A1 (en) System and method for airborne cyclically controlled power generation using autorotation
US9709026B2 (en) Airfoil for a flying wind turbine
KR20020093883A (ko) 액체 수소 성층권 항공기
US20140246862A1 (en) Airborne wind energy system
US9745962B2 (en) Radiator configuration for a flying wind turbine that passively controls airflow
US20100314886A1 (en) Funneled wind turbine aircraft featuring a diffuser
US20160002013A1 (en) Tether Winding
US20170121036A1 (en) Ground station for airborne wind turbine
CN201050449Y (zh) 系缆气球风力涡轮发电机

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 10778439

Country of ref document: EP

Kind code of ref document: A2

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 10778439

Country of ref document: EP

Kind code of ref document: A2