Abstract: An operation management apparatus includes a surrounding environment estimating unit, an energy calculator, and a time changer. The surrounding environment estimating unit is configured to estimate a surrounding environment at a returning start time of a movable body. The energy calculator is configured to search, based on the surrounding environment, a returning route along which the movable body performs the returning, to a first position from a second position, that is started at the returning start time, and calculate an energy amount necessary for the returning. The time changer is configured to advance the returning start time by a predetermined time period until the energy amount reaches or falls below a predetermined value. The surrounding environment estimating unit and the energy calculator are configured to respectively perform the estimation of the surrounding environment and the calculation of the energy amount, each time the time changer changes the returning start time.

Abstract: A motor includes poles P having a remanence Mr of 0.9 T or more, a coercivity HcJ of 0.80 MA/m or more, and a maximum energy product (BH)max of 150 kJ/m3 or more, which sets a center point Pc of the magnetic poles in a circumferential direction on a rotor outer circumferential surface to a maximum thickness tmax, wherein when a line connecting the Pc and a rotational axis center Rc is Pc-Rc, a straight line connecting an arbitrary point Px in the circumferential direction on the rotor outer circumferential surface and the Rc is Px-Rc, an apex angle of the lines Pc-Rc and Px-Rc is ?, a number of pole pairs is Pn, a circumferential direction magnetic pole end is Pe, and a magnetic pole end biasing distance ?LPe of the circumferential direction magnetic pole ends Pe is ?×tmax (? is a coefficient).

Abstract: A stereo distance measuring apparatus includes a first optical camera and a second optical camera, a position-posture calculator, an image corrector, and a stereo distance measuring unit. The first and second optical cameras are provided in an elastic structure part of an aircraft and separated from each other. The first and second optical cameras constitute a stereo camera. The position-posture calculator calculates, on the basis of a displacement amount of the elastic structure part, first and second position-posture information regarding positions and postures of the first and second optical cameras, respectively. The image corrector generates first and second corrected images by correcting, on the basis of the first and second position-posture information, positions and orientations of images taken by the first and second optical cameras, respectively. The stereo distance measuring unit calculates a distance to a photographing target, on the basis of the first and second corrected images.

Abstract: A rare earth bonded magnet comprises a rare earth-iron-based magnetic powder and a thermosetting resin composition. The thermosetting resin composition is obtained by blending a dicyclopentadiene type epoxy resin as a base resin and dicyandiamide as a curing agent. The dicyclopentadiene type epoxy resin includes a predetermined structure wherein an average value of a repeating unit n is 1 to 3.

Abstract: A travel path setting apparatus includes an information acquiring unit, a memory, a predictable scenario creating unit, and a path searching unit. The information acquiring unit acquires surrounding information on a surrounding situation of a movable body. The memory stores a probability model related to the surrounding situation of the movable body. The predictable scenario creating unit creates, on a basis of the surrounding information and the probability model, a plurality of predictable scenarios for each of a plurality of predetermined times in future. The predictable scenarios are each the surrounding situation of the movable body that is predicted for corresponding one of the predetermined times. The path searching unit searches for and sets the travel path on a basis of the predictable scenarios created by the predictable scenario creating unit.

Abstract: A path searching apparatus includes: a path searching unit that searches for an optimal path of a movable body that performs traveling from a start node to a goal node by performing a path searching process based on A-Star algorithm, and a predicting unit that predicts a surrounding situation of the movable body at each of times in future. The path searching unit determines whether a first surrounding situation involves a change from a second surrounding situation, on a basis of the predicted surrounding situation, and upon determining that the first surrounding situation involves the change, updates an estimated smallest cost value h* of a node on which the searching has been already performed, on a basis of the first surrounding situation.

Abstract: A motor includes poles P having a remanence Mr of 0.9 T or more, a coercivity HcJ of 0.80 MA/m or more, and a maximum energy product (BH)max of 150 kJ/m3 or more, which sets a center point Pc of the magnetic poles in a circumferential direction on a rotor outer circumferential surface to a maximum thickness tmax, wherein when a line connecting the Pc and a rotational axis center Rc is Pc-Rc, a straight line connecting an arbitrary point Px in the circumferential direction on the rotor outer circumferential surface and the Rc is Px-Rc, an apex angle of the lines Pc-Rc and Px-Rc is ?, a number of pole pairs is Pn, a circumferential direction magnetic pole end is Pe, and a magnetic pole end biasing distance ?LPe of the circumferential direction magnetic pole ends Pe is ?×tmax (? is a coefficient).

Abstract: An automatic takeoff and landing apparatus for an aircraft for realizing a takeoff run and performing an ascending flight of the aircraft up to a target altitude at takeoff; and for realizing an approaching flight and performing a landing run of the aircraft at landing.

Abstract: An automatic landing apparatus for an aircraft includes: an altitude sensor; an airspeed sensor; an attitude angle sensor; a direction sensor; a position sensor; a landing command inputting section; and a control device, including: an approaching flight control section for realizing an approaching flight along a predetermined path by controlling a propulsion device and a control surface, in response to a landing command; a flare control section for controlling the propulsion device to provide a minimum output and controlling the control surface to perform a flare when the altitude of the aircraft becomes less than a predetermined landing altitude; and a landing run control section for realizing a landing run by controlling the propulsion device to maintain the minimum output and controlling the control surface to maintain the attitude angle and the traveling direction of the aircraft when the airspeed of the aircraft becomes less than a predetermined landing speed.

Abstract: An automatic takeoff apparatus for an aircraft includes: an altitude sensor; an airspeed sensor; an attitude angle sensor; a direction sensor; a takeoff command inputting section; and a control device for controlling a propulsion device and an control surface of the aircraft, wherein the control device includes: a takeoff run control section for realizing a takeoff run by controlling the propulsion device to provide a maximum output and by controlling the control surface to maintain the attitude angle and the traveling direction constant, in response to the takeoff command; a rotation control section for controlling the control surface to rotate when the airspeed exceeds a predetermined speed; and an ascending flight control section for controlling the propulsion device and the control surface to perform an ascending flight up to a target altitude with a predetermined speed maintained, when the altitude exceeds a predetermined altitude.

Abstract: An automatic takeoff apparatus for an aircraft includes: an altitude sensor; an airspeed sensor; an attitude angle sensor; a direction sensor; a takeoff command inputting section; and a control device for controlling a propulsion device and an control surface of the aircraft, wherein the control device includes: a takeoff run control section for realizing a takeoff run by controlling the propulsion device to provide a maximum output and by controlling the control surface to maintain the attitude angle and the traveling direction constant, in response to the takeoff command; a rotation control section for controlling the control surface to rotate when the airspeed exceeds a predetermined speed; and an ascending flight control section for controlling the propulsion device and the control surface to perform an ascending flight up to a target altitude with a predetermined speed maintained, when the altitude exceeds a predetermined altitude.

Abstract: A navigation apparatus with image recognition, includes: an imaging section for obtaining a stereo image of a target spot; an inertial information detecting section for measuring an attitude angle of a body and an acceleration of the body; an image process calculating section for calculating a relative position of the body with respect to the target spot based on the stereo image and the attitude angle; and a navigation calculating section for calculating navigation information based on the attitude angle, the acceleration and the relative position.

Abstract: An unmanned helicopter includes an altitude control device for giving a command of a collective pitch blade angle based on an altitude change rate command, etc., and performing altitude control of an airframe and takeoff device, upon reception of a takeoff start command from the ground, for causing the airframe to take off and climbing the airframe to a first altitude while increasing the collective pitch blade angle without performing the altitude control of the altitude control device and then causing the altitude control device to start the altitude control. The unmanned helicopter further includes descending device for causing the airframe to descend to a second altitude while changing descent rate command of the altitude control device and giving a descent rate command smaller than the descent rate command to the second altitude to the altitude control device for causing the airframe to descend from the second altitude to the ground.

Abstract: An automatic takeoff apparatus for an aircraft includes: an altitude sensor; an airspeed sensor; an attitude angle sensor; a direction sensor; a takeoff command inputting section; and a control device for controlling a propulsion device and an control surface of the aircraft, wherein the control device includes: a takeoff run control section for realizing a takeoff run by controlling the propulsion device to provide a maximum output and by controlling the control surface to maintain the attitude angle and the traveling direction constant, in response to the takeoff command; a rotation control section for controlling the control surface to rotate when the airspeed exceeds a predetermined speed; and an ascending flight control section for controlling the propulsion device and the control surface to perform an ascending flight up to a target altitude with a predetermined speed maintained, when the altitude exceeds a predetermined altitude.

Abstract: A navigation apparatus with image recognition, includes: an imaging section for obtaining a stereo image of a target spot; an inertial information detecting section for measuring an attitude angle of a body and an acceleration of the body; an image process calculating section for calculating a relative position of the body with respect to the target spot based on the stereo image and the attitude angle; and a navigation calculating section for calculating navigation information based on the attitude angle, the acceleration and the relative position.

Abstract: An unmanned helicopter 20 includes altitude control device for giving a command of a collective pitch rudder angle based on an altitude change rate command, etc., and performing altitude control of an airframe and takeoff device, upon reception of a takeoff start command from the ground, for causing the airframe to take off and climbing the airframe to a first altitude while increasing the collective pitch rudder angle without performing the altitude control of the altitude control device and then causing the altitude control device to start the altitude control. The unmanned helicopter further includes descending device for causing the airframe to descend to a second altitude while changing descent rate command of the altitude control device and giving a descent rate command smaller than the descent rate command to the second altitude to the altitude control device for causing the airframe to descend from the second altitude to the ground.