Abstract: The invention involves in a control system for a model airplane, in particular, a kind of model airplane whose flight posture can be automatically controlled in real time according to the flight data determined through detection devices and air pressure sensors.

Abstract: The invention provides for systems, methods, and compositions for manipulation of sequences and/or activities of target sequences. Provided are vectors and vector systems, some of which encode one or more components of a CRISPR complex, as well as methods for the design and use of such vectors. Also provided are methods of directing CRISPR complex formation in eukaryotic cells and methods for selecting specific cells by introducing precise mutations utilizing the CRISPR/Cas system.

Abstract: The invention provides for systems, methods, and compositions for manipulation of sequences and/or activities of target sequences. Provided are vectors and vector systems, some of which encode one or more components of a CRISPR complex, as well as methods for the design and use of such vectors. Also provided are methods of directing CRISPR complex formation in eukaryotic cells and methods for selecting specific cells by introducing precise mutations utilizing the CRISPR/Cas system.

Abstract: The invention provides for systems, methods, and compositions for manipulation of sequences and/or activities of target sequences. Provided are vectors and vector systems, some of which encode one or more components of a CRISPR complex, as well as methods for the design and use of such vectors. Also provided are methods of directing CRISPR complex formation in eukaryotic cells and methods for selecting specific cells by introducing precise mutations utilizing the CRISPR/Cas system.

Abstract: The invention provides for systems, methods, and compositions for manipulation of sequences and/or activities of target sequences. Provided are vectors and vector systems, some of which encode one or more components of a CRISPR complex, as well as methods for the design and use of such vectors. Also provided are methods of directing CRISPR complex formation in eukaryotic cells and methods for selecting specific cells by introducing precise mutations utilizing the CRISPR/Cas system.

Abstract: The present invention discloses a fixed-wing and electric multi-rotor composite aircraft, including an electric multi-rotor dynamic system and a main controller, the fixed-wing dynamic system and electric multi-rotor dynamic system are mutually independent structurally, the main controller includes the fixed-wing control system and an electric multi-rotor control system which is used for controlling the operation of the electric multi-rotor dynamic system, the main controller is also used for controlling the fixed-wing control system and the electric multi-rotor control system to operate independently or synergistically, the rotor rotating plane of the electric multi-rotor dynamic system is parallel to the airframe central shaft. The aircraft is able to shift between two flying modes freely, and takes off, lands and flies like a helicopter as well as a fixed-wing aircraft. A fixed-wing aircraft-helicopter mixed mode can also be used in the take-off, landing and flying process.

Abstract: A brushless DC motor (100) and a radiating device thereof are provided. The brushless DC motor (100) includes a bracket (110), a stator (120) mounted on the bracket (110) and a rotor (130) rotating around the stator (120), the bracket (110) has an inner chamber (112), the rotor (130) has an opening (134) facing the inner chamber (112), wherein the radiating device includes a first radiator (142) which is provided in the inner chamber (112) of the bracket (110) and is thermal coupled with the stator (120) through the bracket (110) so as to send the heat out of the stator (120), and a turbine (144) which is provided within the opening (134) of the rotor (130) and is facing a first end (142a) of the first radiator (142) so as to discharge the heat sent from the first radiator (142) out of the motor (100) while the turbine (144) is rotating. The radiating device is simple in structure, and solves the problem of heat discharging of the large power brushless DC motor.

Abstract: A control servo includes a supporting frame, a motor, a driving shaft and a control slider. The supporting frame comprises a mount and a slider housing, wherein the motor is supported in the mount of the supporting frame. A driving gear is provided at an output end of the motor. The driving shaft is positioned longitudinally through the slider housing. A driven gear is provided at one end of the driving shaft to mesh with the driving gear. The driving shaft penetrates through the control slider while an upper portion of the control slider extends out of the slider housing. An electric brush is provided underneath the control slider. The control servo eliminates the use a potentiometer as installed in a traditional servo and the reduction gearbox so that the structure is simpler and lighter; thus it plays an important part in the miniaturisation of model aircraft.

Abstract: A brushless DC motor (100) and a radiating device thereof are provided. The brushless DC motor (100) includes a bracket (110), a stator (120) mounted on the bracket (110) and a rotor (130) rotating around the stator (120), the bracket (110) has an inner chamber (112), the rotor (130) has an opening (134) facing the inner chamber (112), wherein the radiating device includes a first radiator (142) which is provided in the inner chamber (112) of the bracket (110) and is thermal coupled with the stator (120) through the bracket (110) so as to send the heat out of the stator (120), and a turbine (144) which is provided within the opening (134) of the rotor (130) and is facing a first end (142a) of the first radiator (142) so as to discharge the heat sent from the first radiator (142) out of the motor (100) while the turbine (144) is rotating. The radiating device is simple in structure, and solves the problem of heat discharging of the large power brushless DC motor.

Abstract: A control servo includes a supporting frame, a motor, a driving shaft and a control slider. The supporting frame comprises a mount and a slider housing, wherein the motor is supported in the mount of the supporting frame. A driving gear is provided at an output end of the motor. The driving shaft is positioned longitudinally through the slider housing. A driven gear is provided at one end of the driving shaft to mesh with the driving gear. The driving shaft penetrates through the control slider while an upper portion of the control slider extends out of the slider housing. An electric brush is provided underneath the control slider. The control servo eliminates the use a potentiometer as installed in a traditional servo and the reduction gearbox so that the structure is simpler and lighter; thus it plays an important part in the miniaturisation of model aircraft.

Abstract: The invention relates to RF termination for reducing electrical signal reflections at the end of transmission line electrodes on an electro-optical (EO) optical modulator. The disclosed termination incorporates a RF tap which permits the monitoring of the RF power and reflection conditions at the EO modulator. The integrated termination/tap can also be integrated with detection circuitry, such as RF diodes and passive components, giving improved performance, lower cost manufacturability as well as a more compact and efficient package.

Abstract: A method is disclosed for checking model planes entering into a dive, as well as an anti-dive method and apparatus. The method of checking planes includes installation of a first optical sensor in the upper part of the plane, with installation angle upwardly intersecting with the front of the plane at ? degrees, that checks light intensity and outputs a first checked optical signal; installation of a second optical sensor in the bottom part of the plane, with its installation angle downwardly intersecting with the back of the plane at ? degrees, which checks light intensity and outputs a second checked optical signal. A comparison is made between the first and second checked optical signals, and when the difference in light intensity is smaller than a threshold, a warning signal is sent out indicating that the plane has entered into a dive.

Abstract: The invention relates to RF termination for reducing electrical signal reflections at the end of transmission line electrodes on an electro-optical (EO) optical modulator. The disclosed termination incorporates a RF tap which permits the monitoring of the RF power and reflection conditions at the EO modulator. The integrated termination/tap can also be integrated with detection circuitry, such as RF diodes and passive components, giving improved performance, lower cost manufacturability as well as a more compact and efficient package.

Abstract: The present invention relates to a method of checking model planes entering into a dive and an anti-dive method. Operating model planes necessitates a certain kind of skills. As regards a beginner, plane crashes often occur due to improper operations.

Abstract: An ultrasonic remote aeroplane for playing air-battle game includes a wing, a cockpit, a propeller, a tail pole, a fin, a rudder, a main remote circuit for receiving the propeller rotation controlling signal and rudder motion controlling signal carried high frequency carrier transmitted from a remote transmitter, and a driving system thereof. The remote aeroplane further includes an air-battle box including at least an ultrasonic transmitting tube, an ultrasonic receiving sensor, an attachment structure for fixing to the aeroplane, and a control circuit corresponding to them. The remote transmitter further transmits a high frequency carrier carrying a signal F3 for instructing the ultrasonic transmitting tube to transmit ultrasonic waves. The main remote circuit further includes a circuit for receiving the high frequency carrier carrying the signal F3 and separating out the signal F3.

Abstract: A speed regulated model airplane with double motor comprising a fuselage, a wing, a tail pale, a tail and a remote controller, wherein: a left cowling and a right cowling are hanged separately on the both ends of a connecting rod crossing said fuselage to contain each an individual motor for driving left propeller and right propeller respectively; an RF signal receiving and processing and motor driving circuit and a battery are arranged beneath a hatch cover of said fuselage; said RF signal receiving and processing and motor driving circuit is operative to activate a clockwise (or anticlockwise) rotation of left propeller and an anticlockwise (or clockwise) rotation of right propeller under the control by said remote controller; and said wing is substantially in a horizontal line shape and located on the top of said fuselage.

Abstract: An ultrasonic remote aeroplane for playing air-battle game comprising a wing, a cockpit, a propeller, a tail pole, a fin, a rudder, a main remote circuit for receiving the propeller rotation controlling signal and rudder motion controlling signal carried high frequency carrier transmitted form a remote transmitter, and a driving system thereof, wherein said remote aeroplane is characterized in that: further comprises an air-battle box including at least an ultrasonic transmitting tube, an ultrasonic receiving sensor, an attachment structure for fixing to the aeroplane, and a control circuit corresponding to them; said remote transmitter further transmits a high frequency carrier carrying a signal F3 for instructing said ultrasonic transmitting tube to transmit ultrasonic wave; and said main remote circuit further comprises a circuit for receiving the high frequency carrier carrying the signal F3 and separating out the signal F3.

Abstract: A remote electro-aeroplane is mainly characterized in that the turn rudder surface is jointed to the tail stabilizer by a plastic film on their upper faces with a separation of the elastic foaming material from the plastic film on their lower faces at their joint, wherein two flexible cables or nylon wires are connected to the left and the right racks arranged on the left and the right turn rudder surfaces with their one end respectively and to the servo means within the remote receiving device with their another end, and the restoration mechanisms are provided beneath the left and the right turn rudder surfaces respectively. Based on this structure, the aeroplane has the advantages of easy control with smooth fly in case of making a turn, and is particularly suitable for the primary player.