A power storage device includes: a power storage stack which includes a plurality of power storage cells; a heating member that heats the power storage stack; a cooling member that cools the power storage stack; a first pressing member that presses the heating member against the power storage stack; a second pressing member that presses the cooling member against the power storage stack; and a sheet member covering the bottom of the power storage stack so that an enclosed space is formed between the sheet member and the power storage stack in a cross section of the power storage stack, wherein the sheet member has a first surface and a second surface, the cooling member is disposed on the first surface, within the enclosed space, and the heating member is disposed on the second surface, on an outer side of the enclosed space.

Disclosed is a solid electrolytic capacitor 1 including capacitor elements 2A to 2C, an anode terminal 4, and a resin package body enclosing at least the capacitor elements, the capacitor elements 2A to 2C each including an anode body 6 having a porous portion as a surface layer, a dielectric layer 7, and a cathode part 8 covering at least part of the dielectric layer 7. The anode body 9 has a cathode forming portion and an anode thin-thickness portion adjacent to the cathode forming portion. The dielectric layer 7 covers at least part of a surface of the porous portion in the cathode forming portion. The porous portion is removed in the anode thin-thickness portion or is thinner in the anode thin-thickness portion than in the cathode forming portion. The anode body is connected to the anode terminal 4 at the anode thin-thickness portion.

A propulsion system for use with an aircraft includes a gas turbine engine, an electric power system, and at least one propulsor. The gas turbine engine includes a compressor, a combustor, and a turbine. The electric power system includes a generator coupled to the gas turbine engine to generate electrical energy, power electronics connected to the generator to receive the electrical energy from the generator, and a motor configured to produce rotational energy in response to receiving electric energy from the power electronics. The propulsor is configured to use rotational energy received from the motor of the electric power system to generate thrust for propelling the aircraft.

An electronic control device includes: a circuit board to which electronic components are mounted; an electrolytic capacitor that is mounted to the circuit board, and includes a bottom facing the circuit board, and includes a pressure reduction mechanism disposed in the bottom and structured to release internal pressure of the electrolytic capacitor; and a housing containing the circuit board. The housing includes a pocket that opens at a position to face the electrolytic capacitor mounted to the circuit board and contains the electrolytic capacitor. The pocket includes in its inner periphery a bottom wall surface and a side wall surface that surround the electrolytic capacitor. The electrolytic capacitor is covered by heat dissipation material filling a space between the pocket and a part of the electrolytic capacitor wherein the part faces the bottom wall surface and the side wall surface of the pocket.

A capacitor that comprises a capacitor element is provided. The capacitor element comprises a deoxidized and sintered anode body that is formed from a powder having a specific charge of about 35,000 μF*V/g or more. Further, a dielectric overlies the anode body and a solid electrolyte overlies the dielectric. The capacitor also exhibits a normalized aged leakage current of about 0.1% or less.

A propulsion system for use with an aircraft includes a gas turbine engine, an electric power system, and at least one propulsor. The gas turbine engine includes a compressor, a combustor, and a turbine. The electric power system includes a generator coupled to the gas turbine engine to generate electrical energy, power electronics connected to the generator to receive the electrical energy from the generator, and a motor configured to produce rotational energy in response to receiving electric energy from the power electronics. The propulsor is configured to use rotational energy received from the motor of the electric power system to generate thrust for propelling the aircraft.

An electronic control device includes: a circuit board including a substrate and an electrolytic capacitor connected to the substrate; a heat sink including a recess that houses the electrolytic capacitor; and heat dissipation material provided in the recess. The electrolytic capacitor has an end surface facing a bottom surface of the recess, and the heat dissipation material is in contact with the end surface and the bottom surface.

A method for heating an energy storage device having a core with an electrolyte, the method including: providing the energy storage device having inputs and characteristics of a capacitance across the electrolyte and the core and internal surface capacitance between the inputs which can store electric field energy between internal electrodes of the energy storage device that are coupled to the inputs; switching between a positive input voltage and a negative input voltage provided to one of the inputs at a frequency sufficient to effectively short the internal surface capacitance of the energy storage device to generate heat and raise a temperature of the electrolyte; and discontinuing the switching when the temperature of the electrolyte is above a predetermined temperature that is considered sufficient to increase a charging efficiency of the energy storage device.

A thin-film energy storage device comprising a substrate; a first electrode comprising a fuse portion; a second electrode; an electrolyte between the first electrode and the second electrode; and an electrical connector, different from the first electrode, connected to the first electrode by the fuse portion.

A solid electrolytic capacitor includes a capacitor element. The capacitor element includes an anode foil, a dielectric layer, a solid electrolyte layer, and a cathode lead-out layer. The anode foil includes a first part and a second part other than the first part. The first part has an etched surface, and a second part has an unetched surface. The dielectric layer is formed on the etched surface of the first part in the anode foil. The solid electrolyte layer is formed on at least a part of a surface of the dielectric layer. The cathode lead-out layer is formed on at least a part of a surface of the solid electrolyte layer. An insulating protective layer covers a boundary part between the first part and the second part as well as an end of the cathode lead-out layer and an end of the solid electrolyte layer.