WO2018058004A1 - Systèmes de batterie d'aéronef et aéronef le comprenant - Google Patents

Systèmes de batterie d'aéronef et aéronef le comprenant Download PDF

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Publication number
WO2018058004A1
WO2018058004A1 PCT/US2017/053118 US2017053118W WO2018058004A1 WO 2018058004 A1 WO2018058004 A1 WO 2018058004A1 US 2017053118 W US2017053118 W US 2017053118W WO 2018058004 A1 WO2018058004 A1 WO 2018058004A1
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WO
WIPO (PCT)
Prior art keywords
planar substrates
electrochemical cells
planar
cells
battery module
Prior art date
Application number
PCT/US2017/053118
Other languages
English (en)
Inventor
Albert Spencer GORE
Original Assignee
Impossible Aerospace Corporation
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
Priority claimed from US15/713,545 external-priority patent/US20180086472A1/en
Application filed by Impossible Aerospace Corporation filed Critical Impossible Aerospace Corporation
Priority to CA3036708A priority Critical patent/CA3036708A1/fr
Priority to EP17854052.2A priority patent/EP3516717A4/fr
Priority to CN201780058674.9A priority patent/CN109845007A/zh
Priority to MX2019003275A priority patent/MX2019003275A/es
Publication of WO2018058004A1 publication Critical patent/WO2018058004A1/fr
Priority to IL265446A priority patent/IL265446A/en

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Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M50/00—Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
    • H01M50/20—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders
    • H01M50/204—Racks, modules or packs for multiple batteries or multiple cells
    • H01M50/207—Racks, modules or packs for multiple batteries or multiple cells characterised by their shape
    • H01M50/213—Racks, modules or packs for multiple batteries or multiple cells characterised by their shape adapted for cells having curved cross-section, e.g. round or elliptic
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M50/00—Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
    • H01M50/20—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders
    • H01M50/249—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders specially adapted for aircraft or vehicles, e.g. cars or trains
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M6/00—Primary cells; Manufacture thereof
    • H01M6/42—Grouping of primary cells into batteries
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M2200/00—Safety devices for primary or secondary batteries
    • H01M2200/10—Temperature sensitive devices
    • H01M2200/103—Fuse
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M2220/00—Batteries for particular applications
    • H01M2220/20—Batteries in motive systems, e.g. vehicle, ship, plane
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M50/00—Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
    • H01M50/50—Current conducting connections for cells or batteries
    • H01M50/502—Interconnectors for connecting terminals of adjacent batteries; Interconnectors for connecting cells outside a battery casing
    • H01M50/505—Interconnectors for connecting terminals of adjacent batteries; Interconnectors for connecting cells outside a battery casing comprising a single busbar

Definitions

  • the invention is in the field of electric aircraft and directed more particularly to load-bearing composite structures including battery modules that make these aircraft both lighter and able to store greater amounts of energy for greater endurance.
  • Electric-powered aircraft exist for both human transportation as well as the more familiar unmanned aircraft systems (UASs), sometimes also called unmanned aerial vehicles (UAVs) or just “drones,” that will be referred to herein collectively as electric aircraft.
  • UASs unmanned aircraft systems
  • UAVs unmanned aerial vehicles
  • Electric aircraft like aircraft that combust fuel for power, are limited by how much energy they can carry and by their own weight. Electric aircraft designs thus seek to minimize aircraft weight and maximize the stored energy content of the power supply, typically a collection of batteries. Improving the stored energy content to mass ratio for an aircraft measured in Wh/kg (sometimes referred to as a specific energy) will allow the aircraft to either carry a greater payload, remain in the air longer, traverse a greater distance, or some combination of these.
  • UAV UAV
  • multirotor aircraft One class of UAV is the multirotor aircraft.
  • Present commercial multirotor aircraft quadcoptors having four rotors being a common example
  • hover endurances on the order of 20-30 minutes. These endurances are limited due to a combination of the high-power requirements of these vehicles and a relatively low cell mass / total vehicle mass ratio in part due to the low energy density of required high-power battery cells. All applications of electric aircraft are improved by increasing the aircraft specific energy which enables lower discharge rates for the cells, which generally improves cell longevity.
  • Today's multirotor aircraft generally share a common design: three or more rotors, each powered by its own electric motor, placed some distance away from the vehicle's center of mass, all powered by a central energy storage system (usually a lithium-ion polymer type battery), at or near the center of mass. Some alternate designs, however, locate separate batteries in nacelles beneath the motor/rotor pairs. Housings or beams, generally made of plastic or composites, carry structural loads between each rotor and the central hub, which can include a payload and/or the energy storage system. Wires or printed circuit boards (PCBs) are typically used to carry current from the central energy storage system to the several motors.
  • PCBs printed circuit boards
  • Battery packs for electric vehicles have become commonplace among major automakers, and a number of patents have been filed that use batteries packs or cells to provide rigidity to existing structures or to provide crash absorption.
  • the structure of the battery has been used to augment an existing load- bearing structure, but in no instance does the battery structure serve as the sole load-bearing structure.
  • An exemplary battery module of the present invention for use in an electric aircraft, comprises a first planar substrate, a second planar substrate disposed essentially parallel to the first planar substrate, and a plurality of electrochemical cells secured to and between the first and second planar substrates.
  • the first and second planar substrates each define a plane and the cells are arranged with their longitudinal axes parallel to the planes of the planar substrates.
  • the first planar substrate includes an array of rectangular slots and the cells engage with the slots. That is, the cells fit lengthwise into the slots, and in some instances protrude through the slots.
  • the first and second planar substrates each define a plane and the cells are arranged with their longitudinal axes perpendicular to the planes of the planar substrates.
  • the first planar substrate includes apertures and some of the cells are disposed through those apertures, where the apertures are sized to the cross-section of the cells such that a cylindrical cell would engage with a circular aperture.
  • the planar substrates comprise PCBs, but other lightweight substrates can be used.
  • Simple battery modules can be assembled from flat and rectangular planar substrates, but battery modules can also be constructed from non- rectangular planar substrates. Battery modules designed to fit within complex volumes can be created from planar substrates with varied shapes, such as an airfoil rib.
  • Planar substrates can be formed to curved surfaces such as that of a fuselage. Planar substrates can also be shaped to have a footprint, or planform, of a multirotor aircraft.
  • the first planar substrate comprises a metal layer having isolated sections defined therein by gaps in the metal layer, wherein the first planar substrate includes a number of terminals, each terminal configured for making an electrical connection to one of the plurality of electrochemical cells.
  • the planar substrates can be PCBs with patterned copper layers.
  • the terminals can include, for example, bonding pads defined within a metal layer and next to holes through the PCB. In some of these embodiments, the bonding pad is electrically connected to the metal layer by a fuse.
  • a cell of the plurality of cells is in electrical contact with the metal layer of the substrate through the hole, such as by a metal ribbon disposed through the hole and electrically connected both to the cell and to the metal layer.
  • the planar substrates can have metal layers on both sides, or on only one side, and/or on embedded layers. The metal layers both conduct current from the cells to motors and other components, but also can communicate monitoring and control signals.
  • a suitable cell for the exemplary battery module comprises the 18650 format, but other cylindrical and non-cylindrical cells can be employed.
  • the cells are secured to one or both planar substrates with an adhesive that adheres each cell to the respective substrate.
  • the bottoms of the cans of the cells are adhered flat against a planar substrate, while in other embodiments a longitudinal line along the length of the can is adhered to the planar substrate, or the cell can be inserted through an aperture in the planar substrate and adhered around the circumference defined by the intersection of the two.
  • the planar substrate can include rectangular slots into which the cells fit, and the cells can be adhered to the planar substrate along at least the long sides of the rectangles.
  • topcaps of the cells optionally can also be adhered, soldered, or welded to planar substrates.
  • a join to the topcap can serve as the connection between the metal layer and the cell's positive polarity; a join to the shoulder, side, or bottom of the can may provide the connection between another metal layer and the cell's negative polarity.
  • the electrical connections can also be made in other ways, such as wires or the ribbons already noted.
  • the cells are instead secured between the planar substrates by tensioners attached to both planar substrates, where the tensioners span between the two planar substrates to provide a compressive load to the cells.
  • Tensioners can also be used in combination with bonding through adhesives, soldering or welding.
  • Various embodiments can include one or more discrete components disposed on either or both planar substrates, or on an auxiliary substrate.
  • Discrete components can comprise, for example, sensors, connectors, and integrated circuits (ICs).
  • ICs can include a charge controller or microcontroller, as just two examples.
  • exemplary battery modules of the present invention for use in electric aircraft, consist of, or consist essentially of a first planar substrate, a second planar substrate disposed essentially parallel to the first planar substrate, and a plurality of electrochemical cells secured to and between the first and second planar substrates.
  • Still other exemplary battery modules of the present invention comprise, consist of, or consist essentially of a number of essentially parallel planar substrates, and a layer of electrochemical cells secured to and between every two adjacent planar substrates of the number of planar substrates, where the planar substrates include metal layers that provide electrical connections to and between the cells.
  • the longitudinal axes of the cells in adjacent layers are parallel but not coaxial.
  • the longitudinal axes of the cells within each layer are parallel to the planes defined by the planar substrates secured on either side thereof; additionally, the cells of each layer comprise a plurality of rows, and the cells in adjacent rows are staggered relative to one another. In some of the latter embodiments, the cells in adjacent layers are staggered relative to one another.
  • the cells of adjacent layers are electrically connected in series across the planar substrate, of the plurality of planar substrates, disposed therebetween.
  • the planar substrates include rectangular slots and the cells engage with the slots.
  • the planar substrates include apertures sized to receive the cells, and the cells extend through those apertures.
  • the cells are cylindrical and the negative polarity of each cell is connected to a metal layer of a planar substrate of the plurality of planar substrates by an electrical connection made to the metal layer and to the cylindrical side of each cell.
  • An exemplary electric aircraft of the present invention comprises, consists of, or consists essentially of a load-bearing structure including a number of essentially parallel planar substrates and a layer of electrochemical cells secured to and between every two adjacent planar substrates of the number of planar substrates, where at least one planar substrate of the plurality of substrates includes one or more metal layers that provide electrical connections between the electrochemical cells.
  • the aircraft can be a multirotor aircraft having at least three arms, the number of essentially parallel planar substrates is two planar substrates, and the planar substrates have a footprint of the multirotor aircraft.
  • electrical aircraft also includes hybrid electric aircraft.
  • Load-bearing structures can also comprise components of fixed-wing aircraft, such as the fuselage, wings, and tail.
  • one, or both, of the two planar substrates includes rectangular slots and the electrochemical cells engage with the slots.
  • the electrochemical cells of the layer of cells secured between the two planar substrates are oriented with their longitudinal axes disposed perpendicular to the planes defined by the planar substrates.
  • points of equal electric potential on the arms are electrically connected, and in some of these embodiments the aircraft further comprises discrete circuitry for battery management disposed on one of the two planar substrates, where the integrated circuit is configured to provide a battery management system.
  • An exemplary method of making a battery module comprises providing at least two planar substrates, securing a plurality of cells to and between the at least two planar substrates, and electrically connecting the positive and negative polarities of each cell of the plurality of cells to one or more metal layers on the at least two planar substrates.
  • the step of providing the at least two planar substrates includes patterning metal layers on the at least two planar substrates.
  • the step of providing the at least two planar substrates can also include defining holes in one of the at least two planar substrates.
  • the step of securing the plurality of cells to and between the at least two planar substrates includes inserting some of the cells partially through the holes and fastening the inserted cells to the one of the at least two planar substrates.
  • the holes are rectangular and the step of securing the plurality of electrochemical cells to and between the at least two planar substrates includes engaging some of the electrochemical cells with the rectangular holes and fastening the engaged electrochemical cells to the one of the at least two planar substrates.
  • the step of electrically connecting the positive and negative polarities of each cell to metal layers on the at least two planar substrates includes, for at least some of the cells, electrically connecting one end of a metal ribbon to the topcap of the cell, passing the other end of the metal ribbon through a hole, and electrically connecting the other end to a metal layer on the one of the at least two planar substrates.
  • Holes can be defined in planar substrates by techniques such as laser machining and waterjet machining, for example.
  • FIG. 1 is a perspective view of a battery module according to an exemplary embodiment of the present invention.
  • FIG. 2 is a top view of a portion of a planar substrate of the battery module of FIG. 1.
  • FIG. 3 is a schematic illustration of an arrangement of electrochemical cells within a battery module, according to an exemplary embodiment of the present invention.
  • FIG. 4 is a perspective view of a battery module according to another exemplary embodiment of the present invention.
  • FIG. 5 is a schematic representation of three successive planar substrates having cells secured therebetween, according to various embodiments of the present invention.
  • FIG. 6 is a schematic representation of four successive planar substrates having cells secured therebetween in a staggered arrangement, according to various embodiments of the present invention.
  • FIGs. 7 and 8 are perspective views of battery modules constructed according to the arrangements of FIGs. 5 and 6, respectively.
  • FIG. 9 a perspective view of a battery module according to still another exemplary embodiment of the present invention.
  • FIG. 10 shows a top view of a battery module according to yet another exemplary embodiment of the present invention. This drawing also serves as a top view of a row of cells of the embodiment of FIG. 9.
  • FIGs. 11 and 12 are perspective views of two further battery modules according to still additional exemplary embodiments of the present invention.
  • FIG. 13 is a perspective view of a battery module according to another exemplary embodiment of the present invention.
  • FIGs. 14 and 15 are side and front views, respectively, of the battery module of FIG. 13.
  • FIG. 16 is a perspective view of a multirotor aircraft according to exemplary embodiments of the present invention.
  • FIG. 17 is a side view of the multirotor aircraft of FIG. 16.
  • FIGs. 18 and 19 are top and bottom views, respectively, of the multirotor aircraft of FIG. 16.
  • FIGs. 20-22 are circuit schematic representations of cell arrangements for multirotor aircraft according to embodiments of the present invention.
  • FIG. 23 is a circuit schematic representation of battery protection and fusing between arms of a multirotor aircraft according to embodiments of the present invention.
  • FIGs. 24-26 are perspective views of cell arrangements for multirotor aircraft having six, four, and three arms, respectively, according to embodiments of the present invention.
  • FIGs. 27-28 are perspective views of two different battery module arrangements for quadcoptors according to embodiments of the present invention.
  • the present invention is directed to load-bearing battery modules for electric aircraft.
  • Such modules comprise a composite structure composed of electrochemical cells sandwiched between planar substrates such as PCBs.
  • the present invention is also directed to electric aircraft comprising such load-bearing structures, including both fixed wing and multirotor aircraft, manned and unmanned, for aerial photography and surveillance, surveying, transportation of people and goods, and other purposes.
  • the present invention is also directed to methods of making such load-bearing structures and electric vehicles.
  • these airframe architectures replace load-bearing structural mass, that detracts from the cell mass / total vehicle mass ratio for the aircraft, with a structure that is still load-bearing but which also includes energy-storing mass as a substantial fraction of the load-bearing member. Raising the cell mass / total vehicle mass ratio for the aircraft in this way improves endurance and performance.
  • these composite structures include arrangements in which the cells set with their longitudinal axes perpendicular to the planes of the planar substrates. Other examples have the longitudinal axes of the cells running parallel to the planes of the planar substrates. In some of these embodiments, rectangular slots cut into the planar substrates are sized to allow the cells to sit down into the substrates, in some instances partially protruding through those substrates. In both arrangements, the cells are secured to the planar substrates by adhesives, soldering, welds, and/or other mechanical means, while metal layers on the planar substrates connect to the cells to deliver power to electrical components such as the motors.
  • an electric aircraft includes physically separated but electrically interconnected cells which share charge through balancing traces or wires, such as between arms under unbalanced loads.
  • a benefit of this architecture are shorter primary current paths from the cells to the motors that they power, in addition to the improved cell mass / total vehicle mass ratio.
  • passive fuses or active battery protection circuitry are provided to isolate malfunctioning cells from the motors they power, enhancing reliability of systems with full powertrain redundancy.
  • FIG. 1 illustrates an exemplary battery module 100 of the present invention.
  • the battery module 100 comprises a plurality of electrochemical cells 110 secured to, and secured between, two planar substrates 120, 130, such that the assembly forms a load-bearing structure.
  • the structure is load-bearing in that it resists bending, torsional, compressive, and tensile loadings.
  • the battery module 100 may be sheathed for safety, cooling performance, or as part of the vehicle outer mold line, the cover does not meaningfully contribute to structural strength in some embodiments.
  • the battery module 100 consists of, or consists essentially of, a plurality of electrochemical cells 110 secured to and between the two planar substrates 120, 130.
  • Suitable electrochemical cells 110 include cells of the 18650 cylindrical cell format, as well as AAA, AA, C, D, the 26650 format, and the 21700 cylindrical format. Essentially, any prism-shaped cell with, for example, a rectangular, triangular, hexagonal, or oval cross-section can be used, but cylindrical cells provide advantages to the airflow therebetween, in certain embodiments, as discussed further below. Suitable cells 110 can also employ a lithium-ion NCA cathode with a blended silicon/graphite anode to achieve high specific energy. Cells with chemistry reasonably similar to this are commercially available today in the Panasonic NCR18650GA and LG Chemical INR18650MJ1.
  • NMC, LCO, LMO, NMCA, sulfur, or other cathode chemistries may be employed to achieve differing electrical properties.
  • pure graphite, pure silicon, metallic lithium, titanate, or other anode chemistries may also be employed.
  • any battery cell chemistry packaged into the above cell formats may be a valid embodiment.
  • Planar substrates 120, 130 include metal traces or wires or other conductive means to distribute electricity from the cells 110 to electric systems such as electric motors when the cells 110 are discharging, and to recharge the cells 110 as needed, as well as to carry control and monitoring signals.
  • Electric systems such as electric motors when the cells 110 are discharging, and to recharge the cells 110 as needed, as well as to carry control and monitoring signals.
  • Commercially available integrated circuits providing battery management, avionics, and the like can be placed on either or both planar substrates 120, 130 or separate planar substrates, as discussed further below.
  • each planar substrate 120, 130 can include a voltage sensor, shunt resistor, transistor and controller (or receiver) to passively bleed charge and balance cells 110 during charging. Additional such components can include thermistors, fans, heaters, and thermostats for cell thermal control. Battery protection circuits, provided with alternate current paths, may be included on the planar substrates 120, 130 to bypass certain cell groups (reducing voltage) to provide for cell failure tolerance.
  • each planar substrate 120, 130 can also host a variety of flight sensors - whether inertial, pressure, or otherwise, enabling a "smart structure" able to provide feedback to a flight controller or pilot.
  • Suitable planar substrates 120, 130 can include PCBs, flex materials such as PET and PI films, engineering plastics and glass-reinforced plastics, Kevlar and carbon fiber composite pieces, and foams.
  • PCBs can be formed not only from traditional fiberglass resin composites but also from other engineering substrates such as insulated aluminum, ceramics, and impregnated paper (FR-2).
  • a suitable example of a PCB includes a .030" FR4 substrate with 1 oz copper layers on either side. It should be noted that the planar substrates 120, 130 also provide an insulating layer between any metal layers thereon and the cells 110, such as the FR4 substrate in the above example.
  • planar substrate is meant herein to encompass not only flat substrates but also substrates that conform to shapes dictated by the shape of a vehicle.
  • both planar substrates 120, 130 are flat and are disposed essentially parallel to one another.
  • the planar substrates 120, 130 are essentially parallel in that they are locally parallel such that the cells 110 disposed therebetween are aligned with their longitudinal axes perpendicular to the planes defined by both planar substrates 120, 130 at the points of connection.
  • Suitable materials for planar substrates 120, 130 have a surface energy or 30 mJ/m 2 or more in order for adhesives to adhere well thereto. Another property, in various embodiments, is an elongation to break of 1% or more.
  • the planar substrates 120, 130 comprise PCBs having metal plating on both surfaces, inner surfaces 140 that face the cells 110, and opposing outer surfaces 150 that face away from the cells 110.
  • the planar substrates 120, 130 have the conductive means on only one surface, which can be either the inner surface 140 or outer surface 150.
  • the metal on the outer surfaces 150 comprises a sheet of a uniform thickness of a metal such as copper, having gaps 160 defined therein to provide electrical insulation between electrically isolated sections 170 of the metal layer and other such traces formed from the metal layer.
  • large sections 170 that span several cells 110 electrically join those cells 110 in parallel; these sections 170 are sometimes called power planes or equipotentials.
  • the pattern of gaps 160 in the metal layers generally mirror one another on the opposing PCBs, and all cells 110 connected to a given section 170 are aligned so their currents are additive.
  • the number of cells 110 per section 170 is the same for all or many sections 170 in a battery module 100.
  • Cells 110 in adjacent sections 170 can be aligned opposite one another, in various embodiments.
  • Neighboring sections 170 can be connected in series or in parallel to provide current at the proper voltage. Such electrical connections can be provided through connections in the metal layer, or by wires that bridge over gaps 160, or the like, and can optionally include fuses.
  • the planar substrates 120, 130 comprise terminals 180 for making electrical connections between the cells 110 and the sections 170.
  • FIG. 2 illustrates an enlarged view of a portion 200 of the surface 150 of planar substrate 120 of FIG. 1.
  • the current carrying metal sections 170 are on the outer surfaces 150 and the planar substrates 120, 130 additionally include holes 210 therethrough, one for each of the terminals 180. These holes 210 allow for a connection through the thickness of the planar substrates 120, 130 to the cells 110.
  • the holes 210 advantageously further reduce the mass of the planar substrates 120, 130.
  • the connection is made by an electrically conductive ribbon 220, such as nickel-plated copper, disposed through the hole 210.
  • ribbon 220 examples include nickel, steel, aluminum, and copper optionally plated with tin, silver, nickel, or gold.
  • a ribbon 220, as used herein, encompasses strips of material ranging in thickness from foils to thin sheets. Instead of ribbons disposed through holes in planar substrates, electrical connections through the planar substrates can be made by metal-filled vias, for example.
  • Terminals 180 optionally include a bonding pad 230 defined in the current carrying metal sections 170 by additional gaps 160 that surround the bonding pads 230, electrically isolating them from the remainder of the metal layer of the section 170.
  • the electrical connection to a cell 110 is made through the ribbon 220 to the bonding pad 230, such as by soldering, welding, or adhering the ribbon 220 with an electrically conductive adhesive, for example.
  • the connection of the ribbon 220 to the cell 110 can be made, for instance, using resistance, ultrasonic, or laser welding, or electrically conductive adhesives.
  • Other embodiments do not include defined bonding pads 230, as such, and the electrical connections are made directly to the section 170.
  • FIG. 2 also shows a fuse 240 for each terminal 180 that electrically connects the bonding pad 230 to the remainder of the metal layer of the section 170.
  • the connections between sections 170 of the metal layer can optionally be connected with fuses.
  • the fuses 240 can comprise narrow traces defined in the metal layer that connect the bonding pads 230 to the larger sections 170, or can comprise welded thin ribbons or wire interconnects, designed to fuse at the appropriate current.
  • the fuse 240 comprises a surface-mounted fuse such as the Bel Fuse C1H series. A separate fuse 240 for every cell 110 better protects against external shorts, enhancing electrical safety.
  • fuses 240 may be present for only the positive connections, or only the negative connections, or neither.
  • the planar substrates 120, 130 also include metal traces 190 on the inner surfaces 140 facing the cells 110.
  • these traces 190 permit monitoring of the cells 110 for voltage sensing and cell balancing purposes, and can also carry control signals.
  • FIG. 1 shows an exemplary arrangement in which one side of each planar substrate 120, 130 is used primarily for the conduction of electricity from, and back to, the cells 110, while the other side is used primarily for control and monitoring, but all of the functions can be performed on just one side, and the present invention also embraces multi-layer planar substrates 120, 130 in which electrical conduction is provided along buried conduction layers, patterned in the same manner as already disclosed. As needed, soldermask, conformal coating, and/or a gap-enforced adhesive can be used to insulate the cells 110 from these metal layers.
  • the cells 110 are secured to both planar substrates 120, 130.
  • the term "secured” is used herein according to its ordinary meaning of fixed or attached firmly so that it cannot be moved.
  • securing the cells 110 to both planar substrates 120, 130 provides a rigid structure capable of carrying loads.
  • Various techniques, alone or in combination, can be used to secure the cells 110 between the planar substrates 120, 130 including bonding through the use of adhesives such as epoxies, soldering, welding, as well as the use of tensioners (not shown) attached to both planar substrates 120, 130 and spanning therebetween to provide a compressive load to the cells 110.
  • Suitable tensioners include, for instance, high-strength wires, fasteners, threads, and cable ties. Threads and wires can be weaved through holes or grommets in the planar substrates 120, 130, analogous to the design of a biplane wing, to add further torsional and bending stiffness. To add further resistance to peel, small flanges or brackets (not shown) mounted to one or both of the planar substrates 120, 130 can be used to bracket the cells 110 from one or more directions and enhance the strength of the cell-substrate bond.
  • compliant spacers are selective placed, such as around the positive terminals of the cells 110, with thru -holes for the terminals, that sit in between the cells 110 and the planar substrates 120, 130.
  • These spacers in some instances about 1mm thick, can be made of foam, springs, or of cut rubber such as EPDM/neoprene can be used to compensate for normal variances in cell heights.
  • other spacers such as a laser or blade-cut polyethylene foam honeycomb, can be placed between cells 110 to maintain minimum cell spacing to ensure electrical creepage and clearance requirements are met.
  • Physical loads such as electric motors, control surfaces, avionics, etc.
  • Control systems can include a battery management and protection system that includes resistive or charge shuttling cell balancing, temperature sensing, overcharge protection, over-discharge protection, cell voltage sensing, current sensing, state of charge/energy estimation, state of health estimation, and telemetry.
  • Such functionality can be provided in one or more discrete components 195 mounted on one or both of the planar substrates 120, 130.
  • Discrete components 195 can include battery balancing ICs such as the Linear Technology LTC6811 which can also be added, along with the accompanying transforming hardware (such as one LT8584 and accompanying discrete components per series count), to enable onboard charge shuttling between battery modules 100.
  • Discrete components 195 can also include sensors and connectors, for example, in addition to ICs.
  • Discrete components 195 can include a microcontroller (such as an ATMega series) capable of driving a set of power transistors, either through logic-level direct drive or through a FET driver IC (See FETs 2310 in FIG. 23), to connect or disconnect the battery module 100 from a load.
  • the microcontroller also can control battery cooling fans or heating means, as discussed further below.
  • some or none of the above battery management functionality may be included.
  • some or all of the discrete components 195 can be disposed on a separate circuit board (not shown) in electrical communication with the planar substrates 120, 130.
  • voltage sense traces may be extended to a central position with a connector used for off-board battery balancing by a multi-pin charger (not shown).
  • FIG. 3 provides a schematic illustration of just one suitable cell grid 300 with a to- scale cell spacing according to an exemplary embodiment that employs cells 110 of the 18650 cylindrical cell format.
  • Cells 110 pitched 23mm center-to-center provide adequate airflow around and between the cells 110, in this example when driven by a cooling fan.
  • three rows of cells 110 comprise a repeating unit 310 that are stacked together.
  • Choice of cell grid arrangement is an engineering decision based, at least in part, upon the required cooling and available blowing pressure head/volume rate. Hexagonally close-packed configurations of cells 110 provide low pressure drops with forced-air cooling systems, described in greater detail below.
  • cells 110 may be packed with different spacings to increase packing efficiency or thermal performance, and also may be packed in non-hexagonally symmetric configurations.
  • FIG. 4 provides an illustration of a battery module 400 according to another exemplary embodiment.
  • the planar substrates 410 have a footprint, or planform, in the shape of an airfoil rib.
  • the battery modules such as battery module 100 can be extended with multiple additional planar substrates to form extended load-bearing structures such as electric aircraft wings as in battery module 400.
  • the longitudinal rows of cells 110 form parallel spars while the planar substrates 410 serve as ribs. In other embodiments, these orientations are reversed such that the cells 110 are used as ribs and the planar substrates 410 comprise spars.
  • Structures comprising multiple stacked planar substrates allow for further arrangements of cells 110 in which the cells 110 are staggered relative to one another as illustrated in FIG. 4, as compared to the prior embodiment of FIG. 1 in which the cells 110 are simply arranged in a single layer.
  • at least some planar substrates 410 include apertures 420 therethrough where the apertures 420 are sized to accept a cell 110 disposed longitudinally therethrough.
  • the diameter of the apertures 420 is sized to be greater than a diameter of the cell 110, but no larger than necessary for the cell 110 to fit snuggly therein.
  • Planar substrates 410 at the ends of the module 400 need not have such apertures 420 but may still include them as the apertures 420 also lessen the overall mass of the planar substrates 410. Additional apertures can be included even where space is too limited for cells 110, as shown, just to further reduce mass.
  • the cells 110 are staggered such that half of the cells 110 make electrical contact only to successive even numbered planar substrates 410, e.g. the 4 th and 6 th planar substrates 410, or successive odd numbered planar substrates 410.
  • the cell 110 can be secured to this intermediate planar substrate 410 using a non- electrically conductive adhesive.
  • a positive terminal of the cell 110 is electrically connected to a planar substrate 410 in the manner discussed above, while the negative connection to the cell 110 is made through the sidewall, also referred to as the can, of the cell 110 at the aperture 420 of an adjacent planar substrate 410.
  • Electrical connections between the cans of the cells 110 and the planar substrates 410 at the apertures 420 can be achieved with electrically conductive adhesives, for example, which also serve to secure the cells 110 to the planar substrates 410. Staggering cells 110 in this manner is discussed further with respect to FIG. 6. It is noted that a 400V assembly (about 96 cells 110 in series) of 18650 lithium-ion cells 110 would result in a semi-wingspan of 6.5 meters - similar to that of a Cessna 172.
  • FIG. 5 is a schematic representation of three successive planar substrates 500 having cells 110 secured therebetween.
  • the cells 110 are secured to the planar substrates 500 on either side in the manner discussed above.
  • the cells 110 in successive layers are aligned coaxially, that is, cells 110 form rows across the layers where each cell 110 of the row shares a common longitudinal axis, L.
  • the cells 110 of successive layers are not coaxial, though they may be in every second layer or every third layer, for example. Staggering cells 110 in this manner provides clearance around the interconnects (e.g., terminals 180), and also provides venting space above and below the cells 110 to help prevent lithium-ion runaways.
  • Planar substrates 500 are configured, in these embodiments, such that interconnects on opposite sides of the planar substrate 500 are electrically connected. In this way, the cells 110 in successive layers can be arranged, as shown, to be connected electrically in series.
  • a line 510 represents the connection between sides of the planar substrate which could be a metal plug within a via through the planar substrate 500, for example.
  • FIG. 6 is a schematic representation of an arrangement in which cells 110 are staggered in the manner described with respect to the embodiment of FIG. 4.
  • the cells 110 are secured to planar substrates 600 in the manner discussed above.
  • the positive topcap of each cell 110 is connected to a terminal 180 (FIG. 2) while the side 610 of the cell 110 is used for the negative connection and is electrically connected to the planar substrate 600 through which it passes, such as with conductive epoxy.
  • This connection to the side 610 of the cell 110 is represented by line 620, and can also be made by welding, soldering, or any other metal joining technique discussed herein.
  • the cells 110 are staggered by a fraction of the cell length, such as by a half (as shown) or by thirds.
  • the cells 110 in these embodiments, can also be staggered in the manner described with respect to FIG. 5 to not be coaxial from one layer to the next.
  • Planar substrates 600 are configured, in these embodiments, such that interconnects on opposite sides of the planar substrate 600 are electrically connected. In this way, the cells 110 in successive layers can be arranged, as shown, to be connected electrically in series. It is noted that, in addition to the bonded electrical connections such as welding and soldering, electrical connections can be made to one or both of the positive and negative polarities of the cells 110 by a spring-loaded connector, or other non-bonded electrical connection.
  • FIGs. 7 and 8 show, respectively, a battery module 700 constructed according to the arrangement of FIG. 5 and a battery module 800 constructed according to the arrangement of FIG. 6.
  • the substrate-cell-substrate unit can be repeated along the longitudinal axis of the cells 110 to add both voltage and length to the battery module 700, 800.
  • one end of the battery module 700, 800 carries the highest voltage (Pack +) while the other end carries Ground.
  • a bus bar or cable (not shown) can be used to connect an electrical load, in these embodiments.
  • other embodiments can have equal numbers of cells 110 oriented in opposite directions.
  • the planar substrate 500, 600 at one end of the battery module700, 800 can include an electrical U turn in order to place both the Pack + and Ground terminals (not shown) at the other side of the battery module 700, 800.
  • each planar substrate 500, 600 represents an equipotential and thus connects the same sides of similar- voltage cells 110.
  • planar substrates 120, 130 have metal layers patterned with gaps 160 to create sections 170 of equipotential
  • Planar substrates 500, 600 can, of course, have sections 170 to provide two or more voltages to match the desired cell counts with real world geometry. For instance, a short wing which needs to produce a high voltage or a tapered wing where the large base holds +1 series and +2series cells 110 while the small end only holds one series count. Inversely, multiple PCB's may contain cells of the same voltage through appropriate interconnecting and busing. Long wings of low voltage require cells 110 on different planar substrates 500, 600 to be put in parallel. To fit the form of real aircraft structures, the number of cells 110, their locations, as well as the footprints of the planar substrates 500, 600 may change with each successive layer. By doing so, the forms of a wide variety of aerospace structures can be created, including fuselages, landing gear, pods, tails, hubs, ducts, and more.
  • FIG. 9 shows a perspective view of still another battery module 900 of the present invention
  • FIG. 10 shows a top view of a battery module 1000 comprising a single column of cells 110, and as such, is also representative of a top view of a column from battery module 900.
  • the embodiment of FIG. 10 can be used as an arm of a multirotor aircraft, for example.
  • Planar substrates 910 include a number of rectangular slots 920 that are at least as long as the cells 110, but narrower than a diameter thereof.
  • One cell 110 is disposed in each slot 920 and engages with the slot 920, and in some embodiments partially protrudes through the slot 920.
  • planar substrates are displaced by a cell diameter by being affixed along a line on the surface of the can of the cells 110.
  • FIGs. 11 and 12 show perspective views of still further battery modules 1100, 1200 of the present invention.
  • the battery module 1100 is constructed in the manner described for battery modules 900, 1000 but in this example the cells 110 in alternating columns are staggered, in this example by half of a cell height.
  • the battery module 1200 extends the structure to further parallel layers, as shown.
  • the cells 110 in successive layers can also be staggered, in this case offset in the transverse direction.
  • FIGs. 7-9, 11, and 12 can be further formed to meet the many non-rectangular designs in aerospace structures such as fuselages, wings, pods, and tails, and for UAV structures like arms, frames, motor mounts, and landing gear. This is achieved by varying the footprints of the planar substrates and varying the number of cells in the lattice to work within the available space.
  • One way to design battery modules for an aerospace structure is to first establish footprints, or outlines, for the battery module, or modules if multiple modules are to form a larger assembly, to assume the approximate cross section of the structure. Appropriate mounting points for coupling to secondary structures and loads can be added.
  • a wing FIG.
  • this footprint may be long and tapered, with an aspect ratio of 5-20: 1.
  • the metal layers can optionally be segmented into sections 170 as needed to optimize part cost and shipping logistics.
  • Cell positions are then established to, for example, minimize current path length, maintain regulatory creepage and clearance distances, provide appropriate clearances on all sides of the cells 110 to prevent thermal runaway propagation, and limiting structural discontinuities.
  • Staggering cells 110 longitudinally is one way to limit structural discontinuities.
  • space can also be provided for thermal control features such as fans and heaters, discussed further below.
  • Cells 110 and cell slots 920 are then spaced such that cells 110 of similar potentials (series-counts) are proximal. Successive series counts are then placed adjacently - most efficiently, head-to-tail longitudinally. Sections of a metal layer are designed onto the PCBs to bus current from one cell group to the next.
  • planar substrates can optionally be thermally formed or strained with board-mounted components already included before assembly.
  • FIGs. 13-15 show perspective, side and front views, respectively, of an exemplary battery module 1300 including a housing 1310 having fans 1320.
  • the embodiment shown in these drawings can be the battery module 100 (FIG. 1) with the addition of housing 1310.
  • the housing 1310 in this embodiment, encloses the four open sides defined between the two planar substrates 120, 130.
  • sides of the housing 1310 can be formed from thin gauge plastic (-.005" polycarbonate as one example), such as by vacuum forming, with openings defined therein as needed for features such as vents and fans 1320.
  • the plastic in some embodiments is formed as flat sheets, but in other embodiments the plastic is formed to improve or manifold forced airflow.
  • housing 1310 can be optionally disposed over and below the planar substrates 120, 130 to further insulate these components.
  • the battery module 500 may be enclosed with shrink wrap, and the housing 510 formed of composites, or with additional connecting PCBs or flexible circuits.
  • ambient air is circulated through the matrix of cells 110 using one or more fans 1320 controlled, for example, by the battery management system. More or less airflow is required depending on the power profile required compared to the internal resistance of the cells, and air may be circulated either for heating or cooling. Cooling can enhance longevity and discharge rate capability, for example, while heating can improve a cell's capacity by lowering its resistance.
  • the air may be heated or chilled by an external HVAC system (not shown). Heating can also be achieved by resistive heaters placed within the battery module 1300.
  • liquid or phase change cooling systems may fill the spaces between cells 110.
  • battery module 1300 can be sealed with a dielectric liquid inside the housing 1310 and in a saturated atmosphere, where the liquid has a boiling point in the proper range; the liquid boils off of the cells 110 and then condenses on a radiator elsewhere in the assembly to remove heat.
  • planar substrates 120, 130 can be used to join points of equal potential between adjacent planar substrates 120, 130.
  • PCBs for example, may be electrically connected using harnesses, flex circuits, or board connectors. In embodiments in which a battery management system manages both planar substrates 120, 130 but is disposed on only one of them, such a connection is necessary so that the battery management system has access to the cell voltages collected on the other planar substrate.
  • Main power bus connections to the battery modules 100, 400, and 700-1300 can be achieved by terminal connectors (not shown) that are soldered or welded, for example, onto open areas on the metal layer of the planar substrate 120, 130 or through holes thereof.
  • terminal connectors not shown
  • power connector wires may be directly soldered to these places without resort to terminal connectors.
  • a battery module can include a separate series stack of high- power cells 110 that is electrically segregated from the other cells 110, and selectively connected to the remainder of the battery module by turning on power transistors or using some other power relay mechanism.
  • Additional components can be limited to digital cameras, transceivers, and optional GPS modules, such as a GPS micro-chip. Still further embodiments are directed to hybrid electric multirotor aircraft.
  • FIG. 16 illustrates an exemplary embodiment of a multirotor aircraft 1600 comprising four rotors 1610 each driven by an electric motor 1620.
  • FIG. 17 shows the same aircraft 1600 from a side view.
  • the motor/rotor combination is set at the end of an arm 1630 extending from a central hub 1640. Locating the rotors 1610 away from the center axis of the aircraft 1600 provides roll and pitch control, with yaw control provided by transferring momentum to and from the rotors 1610.
  • each arm 1630 comprises a sandwich of cells 110 arranged between planar substrates 1650 as shown in FIGs. 1 and 10.
  • a lightweight vacuum formed or foam shroud is attached to the vehicle's arms 1630 to improve its aerodynamic properties and reduce drag on the thrust stream.
  • the shroud furthermore can be used to improve impact tolerance.
  • FIG. 16 also illustrates the primary current path in an arm 1630 (arrows), following through the periodically inverted battery cells 110 to a motor controller and motor 1620.
  • FIG. 16 also illustrates select secondary current paths 1660 between equipoentials on different arms 1630 for cell balancing.
  • the planar substrates 1650 have a footprint of the planform of the quadcopter such that the central hub 1640 and the four arms 1630 are integral.
  • the cells 110 are secured to the planar substrates 1650 with an adhesive.
  • the cells 110 are not adhered but instead are mechanically secured with tensile wire, fasteners, thread, or clamps, for example. Some of these embodiments include a compressive material between the cells 110 and the planar substrates 1650 to accommodate variations in the cells 110.
  • the planar substrates 1650 each comprise a circuit board made of a .030" thick FR-4 substrate having two layers of 1 oz thickness copper plated with lead-free solder backing.
  • thicker copper is used to enable higher current densities.
  • the thickness of the FR-4 may be varied as well to alter mechanical properties.
  • metallic substrates such as used in PCBs made from insulated aluminum substrates, can be used to offer higher heat spreading properties for configurations in which onboard power electronics, battery management, charging, DC-to-DC voltage converters, and motor controllers can see performance or longevity improvements from sinking heat to the rest of the airframe.
  • Substrate thickness may also vary to satisfy structural requirements.
  • Electrical interconnects in some of these embodiments, are made by resistance welding nickel ribbons to the positive and negative terminals of cells 110, the ribbons are passed through holes 210 in the PCBs and are reflow soldered to unmasked lead-free bonding pads 230 on the outer surfaces 150.
  • SMT fuses such as the Bel Fuse C1H
  • Connections to the positive and negative potentials of cells 110 can also be made by laser or ultrasonically welding a foil to the cell 110, ultrasonically welding a wire, or other techniques, and in the other embodiments, can be joined to the bonding pads 230 with an otherwise soldered, welded, or adhered joint.
  • the cells 110 comprise the 18650 format and employ a lithium-based chemistry.
  • Other embodiments employ other cylindrical cell form factors, such as AAA, AA, C, D, 21700, and 26650, for example.
  • Non-cylindrical cells 110 also may be used, as well as non-lithium based rechargeable cells 110. Different cell geometries may be employed to change the aerodynamic, structural, or electrical properties of the resulting electromechanical assembly. It is noted that 72 of the 18650 format lithium-ion cells 110 are used in the embodiment of aircraft 1600 where the cells 110 are arranged in groups (strings) of twelve cells 110 in parallel, and six strings are placed in series (6S, 12P) for a total of approximately 3.6 kg of cell mass and 900 Wh of energy. In some embodiments, as much as 70%, 75%, and 77% cell mass / vehicle mass ratio is achievable in these embodiments after adding motors 1620 and avionics.
  • the aircraft specific energy is about 175 Wh/kg. In some embodiments, over 80% cell mass / vehicle mass ratio is attainable.
  • the planar substrates 1650 can bus current both span wise out to the motors 1620 and towards the center axis of the vehicle 1600 for regulation and avionics power.
  • some configurations include cells 110 that are electrically interconnected only to one planar substrate 1650.
  • both the positive topcap and the can of the cell 110 are electrically connected to conductors on the same planar substrate 1650.
  • the positive topcap can be bonded in the manner described above with a metal ribbon extending through a hole in the planar substrate 1650, while a weld to the shoulder of a cell 110 forms the negative connection.
  • the electrical interconnects between the cells 110 and planar substrate 1650 comprise a wire or nickel ribbons 220 resistance welded to the positive topcaps and the negative cans of the cells 110. Laser or ultrasonically welding can be used in place of resistance welding, in some embodiments.
  • the ribbons 220 are passed through holes 210 and reflow soldered to unmasked lead-free bonding pads 230 on the outer surfaces 150. Welding or conductive adhesive can also be used in place of soldering. SMT fuses, such as the Bel Fuse C1H series, connect the bonding pads 230 to metal layers on the planar substrates 1650.
  • a flight controller In some embodiments of aircraft 1600, a flight controller, GPS module, radios, motor controllers, sensors, and a battery management system are all included onboard the planar substrates 1650. Extra conducting layers can be connected to enable the greater schematic complexity of modern flight controllers.
  • the outer surfaces 150 include metal layers that are predominantly employed for current collection, power busing, cell interconnections, and fusing, while metal layers on the inner surfaces 140 are used for data traces, voltage sensing, current return loops, and battery balancing and management.
  • metal layers on the inner surfaces 140 are used for data traces, voltage sensing, current return loops, and battery balancing and management.
  • additional layers are included to route traces for battery management systems, flight control electronics, power systems, or other avionics.
  • each arm 1630 of the multirotor aircraft 1600 contains cells 110 in a series and parallel configuration to reach the full potential required by the motor inverter/speed controller for that arm 1630.
  • Inverter power transistors (not shown) can be integrated into each of the distal ends of at least one of the two planar substrates 1650 or disposed on an additional substrate (not shown), in either case, directly adjacent to a motor 1620.
  • In steady flight and with a perfectly balanced cells 110 within each arm 1630, all the current required for each motor 1620 is sourced from cells 110 within the supporting arm 1630.
  • power can be bused between different arms 1630 through board traces connecting each series-count of cells in parallel.
  • cells 110 can be used as primary structure for the vehicle's core.
  • some or all cells 110 can form structure directly beneath each rotor 1610 which is an advantageous configuration for minimizing cantilevered weight, with lightweight structural/electrical connections between the rotors 1610 yielding a rigid vehicle.
  • cells 110 are used structurally as landing gear, or can simply be located beneath the motor 1620 to minimize bending loads.
  • a flexible circuit interconnect (not shown) provides electrical connections between the two planar substrates 1650 for battery management.
  • connectors soldered harnesses, or other conductors can be used.
  • substrate-to-substrate connectors or other means of electrical interconnection can add torsional rigidity to the arm 1630 in addition to providing connections between planar substrates 1650.
  • Exemplary flexible printed circuits suitable for use in the present invention are disclosed in US Patent Application pre-Grant Publication 2014/0212695 Al by Lane et al. and published on July 31, 2014 which is incorporated herein by reference.
  • a battery management system resides in the hub 1640 of one or both of the planar substrates 1650 and provides functionality including overcharge protection, over-discharge protection, voltage balancing, over-temperature protection, power projection and state of charge estimation, along with various vehicle-level telemetry.
  • the battery management system may be highly integrated with a flight controller of the multirotor aircraft 1600, which in some embodiments may be integrated with the one of the planar substrates 1650. Other embodiments fully exclude or limit the functionality of the battery management system.
  • FIGs. 18 and 19 are top and bottom views of the aircraft 1600, showing the distribution of power planes and locations of various cell equipotentials.
  • each arm 1630 includes four cells 110 directly below the motor 1620 and 12 more cells 110 along the length of the arm 1630 for a total of 18 cells 110. These are grouped into three sets of six cells 110 each, where the cells 110 in each set share a common orientation. In FIGs. 18 and 19 each set of six cells 110 attaches to a section 170 so all six cells 110 are connected in parallel. These sets are, in turn, connected in series and to the motor 1620. It is also noted that these illustrations show that the planar substrates 1650 comprise the footprint of the quadcoptor and as such, all four arms 1630 are integral with the hub 1640. Alternatively, four battery modules 1000 can be connected to a hub 1640.
  • FIG. 20 provides a circuit schematic representation of an exemplary layout of cells 110 in a multirotor aircraft similar to aircraft 1600. While the circuit 2000 has four-fold symmetry, the same arrangement can be extended to other symmetries. Cells 110 are shown increasing in series count radially outwards. A common ground exists at the center (not shown). In FIG. 20, M represents a motor and inverter/speed controller assembly, the electrical load. The positive most terminal of each battery module is positioned radially outward, with the ground towards the aircraft's center.
  • cells 110 are connected in series, and preferably oriented with their longitudinal axes arranged coaxially and aligned with the axis of the structural member in question, such as an arm. Wires or traces connecting points of equal potential in different arms may be used to share charge between them for either slow balancing or transient current sharing. For clarity, only one balance net 2010 is shown for illustration.
  • FIG. 21 provides a circuit schematic representation of another exemplary layout of cells 110 in a multirotor aircraft.
  • the cells 110 are electrically connected so as to form a "U" current path. Balancing nets and the common ground are not shown.
  • the radial "U" path eliminates the waste mass of a return current bus as the most positive and negative potentials are co-located at the site of the electrical load.
  • FIG. 22 provides a circuit schematic representation of yet another exemplary layout of cells 110 for a multirotor aircraft, in this instance, an H-figure multirotor (two arms which branch to become four).
  • Cells 110 are first located together in the first set of arms, then split to half the parallel count in the branched arms, while, remaining electrically connected.
  • cells 110 of some potentials may be co-located while those of other potentials may be physically spread apart, but connected with balance conductors.
  • Five balance nets 2200 are shown, as well as a common ground 2210.
  • FIG. 23 provides a circuit schematic representation of exemplary battery protection and fusing between arms of a multirotor aircraft, but could represent any two parallel circuits within or between battery modules.
  • low current fuses 2300 are used to connect points of equal but intermediate potential while battery protection field-effect transistors (FETs) 2310 can be used at the top potential.
  • FETs field-effect transistors
  • FIG. 24 shows an exemplary arrangement of cells 110 for a hexacopter comprising six arms. Cells 110 are shown alternating in orientation every parallel group of four cells 110 to enable series interconnects.
  • FIG. 25 shows a four-armed embodiment of the example shown in FIG. 24. This arrangement is also similar to that provided in aircraft 1600, however, that arrangement had four cells 110 beneath each motor 1620 and 18 cells 110 per arm 1630 with sets of six parallel cells 110 alternating in orientation, whereas in FIG. 25 16 cells 110 are arranged in four sets of four parallel cells 110 alternating in orientation, with only two intended to be beneath each motor. It will be appreciated that for both illustrated cell arrangements, the longitudinal axes of the cells 110 can be either perpendicular or parallel to the planes of the planar substrates to which they are secured.
  • FIG. 26 shows an exemplary arrangement of cells 110 for a tricoptor or Y6-style hexacoptor, defined as having two rotors at the end of each arm, one above and one below.
  • each motor receives power from the cells of the respective arm, mostly eliminating current sharing, resulting in shorter current path lengths, lower resistive losses, and less metal mass devoted to current conduction.
  • These embodiments also benefit aerodynamically by eliminating the protrusion caused by a large, centrally located battery system. Distributing the cells 110 rather than concentrating them together in a central battery system also improves fire tolerance.
  • FIG. 27 shows a battery module 2700 in the form of a quadcoptor. It will be appreciated that the mass of this structure is almost entirely that of the cells 110.
  • FIG. 28 shows a battery module 2800 also in the form of a quadcoptor. Again, the mass of this structure is almost entirely that of the cells 110.
  • a standard 22V assembly (six cells 110 in series) corresponds to an arm length of 390 millimeters, which is similar to the frame arm length of a DJI S1000 (389mm).
  • PCB can be replaced with a flexible circuit board made via cutting or etching processes on a plastic stiffener. See US Patent Application pre-Grant Publication 2014/0212695 Al by Lane et al.

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  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Electrochemistry (AREA)
  • General Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Connection Of Batteries Or Terminals (AREA)

Abstract

Des modules de batterie pour aéronef électrique sans pilote et humain comprennent deux substrats plans avec des cellules électrochimiques fixées entre des éléments structurels porteurs de charge à partir desquels des aéronefs ayant une plus grande endurance peuvent être construits. Les cellules peuvent être orientées perpendiculairement ou parallèlement aux substrats, et dans ce dernier cas, les substrats peuvent comprendre des fentes auxquelles les cellules s'adaptent. Les cellules peuvent être fixées sur les substrats par des adhésifs, par soudage, par brasage et similaire, ainsi que par des tendeurs mécaniques. Des modules de batterie peuvent être formés sur les formes de parties d'aéronef telles que des ailes. L'invention concerne également un aéronef à rotors multiples dans lequel les bras et d'autres parties de l'aéronef sont construits à partir de tels modules de batterie.
PCT/US2017/053118 2016-09-25 2017-09-23 Systèmes de batterie d'aéronef et aéronef le comprenant WO2018058004A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
CA3036708A CA3036708A1 (fr) 2016-09-25 2017-09-23 Systemes de batterie d'aeronef et aeronef le comprenant
EP17854052.2A EP3516717A4 (fr) 2016-09-25 2017-09-23 Systèmes de batterie d'aéronef et aéronef le comprenant
CN201780058674.9A CN109845007A (zh) 2016-09-25 2017-09-23 飞行器电池系统和包括飞行器电池系统的飞行器
MX2019003275A MX2019003275A (es) 2016-09-25 2017-09-23 Sistemas de bateria de aeronave y aeronave que incluye los mismos.
IL265446A IL265446A (en) 2016-09-25 2019-03-18 Battery systems for aircraft and aircraft that include them

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US201662399431P 2016-09-25 2016-09-25
US201662399470P 2016-09-25 2016-09-25
US62/399,431 2016-09-25
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US201762469262P 2017-03-09 2017-03-09
US201762469324P 2017-03-09 2017-03-09
US201762469201P 2017-03-09 2017-03-09
US62/469,262 2017-03-09
US62/469,324 2017-03-09
US62/469,201 2017-03-09
US15/713,539 2017-09-22
US15/713,545 2017-09-22
US15/713,545 US20180086472A1 (en) 2016-09-25 2017-09-22 Aircraft Battery Systems and Aircraft Including Same
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NO20191467A1 (en) * 2019-12-11 2021-06-14 Griff Aviation As An aerial vehicle
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