Abstract: A flight support apparatus includes a flight support unit that displays a reference flight profile that is a flight profile as a reference, the flight profile indicating a flight specification at a plurality of spots included in a path from a departure place to a destination, corrects the reference flight profile according to a flight condition input by a user to prepare a corrected flight profile, and displays the prepared corrected flight profile together with the reference flight profile.

Abstract: To realize stable airspeed control considering remote turbulence, the present invention provides an aircraft speed information providing system includes: an airspeed measurement device that measures a present airspeed of an aircraft; an acceleration measurement device that measures present acceleration of the aircraft; a remote turbulence measurement device that measures remote turbulence in front of the aircraft; and a computation processing device that calculates a predicted airspeed of the aircraft on the basis of the measured present airspeed and present acceleration and the remote turbulence measured by the remote turbulence measurement device.

Abstract: To provide an electrified aircraft, and a method of controlling a regenerative electric power of the electrified aircraft where a path angle and a descending rate can be controlled with a good response independently from a speed while controlling the drag force of the propulsion drive system and where it is possible to maximize safely a generated electric power in each flight status at the time of descent or ascent. The electrified aircraft includes a propeller or a fan for propulsion; an electric drive motor for rotary-driving the propeller or the fan and for generating an electric power by the rotation of the propeller or the fan; and an estimation unit for estimating a drag force of the propeller or the fan or an electric power generation amount of the electric drive motor based on propulsion system parameters of the electric drive motor.

Abstract: To provide an electrified aircraft, and a method of controlling a regenerative electric power of the electrified aircraft where a path angle and a descending rate can be controlled with a good response independently from a speed while controlling the drag force of the propulsion drive system and where it is possible to maximize safely a generated electric power in each flight status at the time of descent or ascent. The electrified aircraft includes a propeller or a fan for propulsion; an electric drive motor for rotary-driving the propeller or the fan and for generating an electric power by the rotation of the propeller or the fan; and an estimation unit for estimating a drag force of the propeller or the fan or an electric power generation amount of the electric drive motor based on propulsion system parameters of the electric drive motor.

Abstract: A process for purifying an exhaust gas comprising carbon monoxide, hydrocarbons, nitrogen oxides, and sulfur oxides by periodically adjusting exhaust gas conditions from lean-burn to fuel-rich and by using a catalyst comprising an alumina support with lithium dissolved therein to form a solid solution, at least one first ingredient selected from the group consisting of platinum and palladium loaded on the alumina support, and at least one second ingredient selected from the group consisting of alkali elements, alkaline-earth elements, and rare-earth elements loaded on the support. Sulfates formed from sulfur oxides in the exhaust gas are decomposed by the lithium under the fuel-rich conditions to inhibit the alumina support from being acidified.

Abstract: A direct current voltage is applied between an anodic portion containing an oxidizing catalyst provided on one surface of a proton conductive solid electrolyte which separates the flow path of the gas to be treated into two parts, and a cathodic portion containing a reducing catalyst provided on the other surface of the solid electrolyte, the reducing catalyst comprising at least one selected from oxides of elements of Group 5A, Group 6A, and Group 7A of the periodic table, palladium, palladium alloys, transition elements carried on alumina, cerium oxide, and La.sub.1-x Sr.sub.x Co.sub.1-y Fe.sub.y O.sub.3 (where, 0.ltoreq.x.ltoreq.1, 0.ltoreq.y.ltoreq.1), while bringing a gas containing water vapor into contact with the anodic portion and bringing a gas containing nitrogen oxides into contact with the cathodic portion.