Samsung Electro-mechanics Co., Ltd.

Korea Aerospace Research Institute

Seong Wook Choi

Gun Woo Moon

Dong Seong Oh

Byoung Woo Ryu

Myeong Kyu Lee

Sung Ho Chang

Jong Pil Kim

Bong Chul Kim

Don Sik Kim

Tae Won Heo

Jong Sun Kim

Young Woon Choi

Dong Joong Kim

Dong Wook Lee

Sang Cheol Bong

Jun Ho Cho

Am Cho

Kyu Min Cho

Sam Ok Koo

Yu Shin Kim

Young Shin Kang

Jai Moo Kim

Byeong Woo Ryu

Deog-Kwan Kim

Byoung Hee Lee

A tilt prop aircraft is provided, including a first longitudinal support member and a second longitudinal support member capable of tilting relatively to each other, a tilt actuator disposed on the second longitudinal support member, a first power transmission member rotated by the tilt actuator, a second power transmission member fixed to the first longitudinal support member and coupled to the first power transmission member to transmit a rotational movement of the first power transmission member by turning 90 degrees in different planes, a crank fixed to the second longitudinal support member and extending through a slot in the first longitudinal support member and protruding inwardly from the first longitudinal support member, and a connecting rod connected to the crank so as to be relatively rotatable to the crank, and connected to the pitch control rod.

Tilt prop aircraft

The flying object according to one embodiment comprises: a main body; a main wing formed on a side surface of the main body; a duct-shaped first propulsion part which is provided outside the main wing and can be tilted; a second propulsion part arranged behind the main body; horizontal tail wings formed on both side surfaces of the second propulsion part; and a control part for controlling the movement of the first propulsion part, second propulsion part, and horizontal tail wings, wherein the control part controls the second propulsion part and the horizontal tail wings according to the tilt angle of the first propulsion part.

Flying object and flying object position control system

A tilt-prop aircraft is configured to operate in a vertical take-off and landing (VTOL) mode or a forward flight mode by adjusting a tilt angle of a rotor connected to a wing. The tilt-prop aircraft includes: a blade included in the rotor and configured to rotate to produce lift and thrust; and a tilt center shaft configured to connect the rotor and the wing to each other and adjust the tilt angle of the rotor with respect to a flight plane of the tilt-prop aircraft, wherein when the tilt angle of the rotor is adjusted, a pitch angle of the blade is varied by a power transmission unit mechanically interlocked with the tilt center shaft.

Tilt-prop aircraft

There is provided a switching mode power supply including: a direct current (DC)/DC converting unit converting a DC power level; an auxiliary power supply unit discharged in a no load mode in which a load is not connected to an output terminal of the DC/DC converting unit; and a controlling unit sensing a change in impedance according to whether or not the load is connected to the output terminal to thereby determine whether or not the switching mode power supply is in the no load mode, and driving a pulse width modulation integrated chip (PWM IC) when a voltage level of the auxiliary power supply unit is at a preset level or less in the no load mode.

Switching mode power supply

Provided is a high performance tilt rotor aircraft in which a nacelle tilt angle and a flaperon angle mechanically interlock with each other. In the tilt rotor aircraft having nacelles in which rotors are mounted in left and right main wings and configured so that the nacelles rotate according to whether the tilt rotor aircraft conducts forward flight or vertical take-off and landing flight, each of the main wings is provided with a flaperon, and the nacelle and the flaperon are connected to each other by a power transfer unit, such that the flaperon also rotates together with the nacelle at the time of rotation of the nacelle, thereby allowing a change in a nacelle tilt angle to lead to a change in a flaperon angle.

High performance tilt rotor aircraft in which nacelle tilt angle and flaperon angle mechanically interwork with each other

The present invention relates to an adapter power supply, which includes a switching unit for switching a DC voltage; a transformer which has a primary winding connected to the switching unit, a secondary winding electromagnetically coupled to the primary winding, and an auxiliary winding electromagnetically coupled to the primary winding; a rectifier for rectifying a voltage outputted from the transformer; and a controller for controlling the switching unit to operate according to the PWM scheme in a normal operation mode, and to operate according to a quasi-resonant scheme in a standby mode, by detecting information of a load connected to the rectifier.

Adapter power supply having variable switching mode

A switching mode power supply includes an EMI filter unit, a PFC unit, a DC/DC unit, a PFC controller including a feedback stage to which a link voltage at an output side of the PFC unit is fed back and an overvoltage protection stage, a DC/DC controller generating a burst mode operation signal in a light-load or no-load condition, an error signal generation unit for sensing an output voltage of the power supply to generate an error signal, and a control unit for enabling the PFC unit to operate in a burst mode by connecting the overvoltage protection stage and the feedback stage. When the error signal is smaller than a predetermined value, the DC/DC controller generates the burst mode operation signal. When the link voltage fed back to the feedback stage exceeds a threshold voltage of the overvoltage protection stage, the PFC controller deactivates the PFC unit.

Switching mode power supply for reducing standby power

There is provided a bridgeless power factor correction circuit that corrects a power factor by complementarily switching two switches according to phase of input power without using rectifier bridge diodes. A bridgeless power factor correction circuit according to an aspect of the invention may include: a switching unit having a plurality of switches and alternately switching input AC power; a stabilizing unit rectifying and smoothing the power switched by the switching unit; and a control unit controlling an alternate switching operation between the plurality of switches according to phases of the input power.

Bridgeless power factor correction circuit

An advantage of the present invention is to provide an adapter power supply which varies a link voltage of DC power serving an input power of a DC/DC converter according to variation of a load current estimated by measuring a secondary current using a lossless current measurement technique at a primary terminal of a transformer of the DC/DC converter and thus presuming a load current of an output power. An adapter power supply according to present invention may include an AC/DC converter converting a commercial AC power into a DC power; a DC/DC converter including a transformer composed of a primary terminal and a secondary terminal in order to output an output power by converting a link voltage of the DC power; and a controller presuming a load current of the output power through a primary current of the transformer and varying the link voltage of the DC power according to variation of the estimated load current.

Adapter power supply

Growing community of inventors

Daejeon, South Korea

Seong Wook Choi