Abstract: The present disclosure generally relates to combinations of resistive change elements and resistive change element arrays thereof. The present disclosure also generally relates to combinational resistive change elements and combinational resistive change element arrays thereof. The present disclosure additionally generally relates to devices and methods for programming and accessing combinations of resistive change elements. The present disclosure further generally relates to devices and methods for programming and accessing combinational resistive change elements.

Abstract: Aircraft and methods and systems for determining airspeed of an aircraft. The methods and systems allow for calculation of airspeed in near-ground and on-ground aircraft operation. A GPS altitude and a vertical acceleration of the aircraft are obtained for a current time frame. A geometric altitude for the previous time frame is determined, and the difference between the GPS altitude and geometric altitude are combined with the vertical acceleration to calculate a geometric altitude rate of change. The geometric altitude rate of change is used to calculate a pressure altitude rate of change, which is used to calculate a pressure altitude for the aircraft. A static pressure is calculated from the pressure altitude, and the airspeed is calculated using the static pressure.

Abstract: Resistive change element cells sharing a selection device and resistive change element arrays including a plurality of resistive change element cells and a plurality of selection devices arranged in a group of at least two resistive change element cells sharing one selection device configuration are disclosed. According to some aspects of the present disclosure a group of resistive change element cells can be arranged on one level above a selection device. According to some aspects of the present disclosure a group of resistive change element cells can be arranged on multiple levels above a selection device.

Abstract: A clip-on fan includes a specialized clamping clip 56 that is attached to rectangular or cylindrical tent poles that are commonly used for grow tents. Fans are essential components for growing in tents and the current designs clip-on fans do not meet the needs of indoor growers. The clip-on fan comprising a fan assemblage and clip clasp assemblage arranged at the base of the complete product, wherein the clip 5 is able to grasp to the vertical tubular structure of a grow tent; The grasping clasp 5 assembly consists of: a left clip plate 51, a right clip plate 52, a clip plate rotation shaft 53, a clip spring 54, a fan connection hole 55 and, a clip clamp opening 56. The left and right clip plates are connected in a bilateral symmetry through the clip plate rotation shaft at the central connection position.

Abstract: A foldable lamp holder comprises two side supports, and each of the side supports comprises a first support and a second support, which are symmetrically arranged with each other; ends of the first support and the second support on the same side are hinged; the first support and the second support are respectively provided with a plurality of lamp bar interfaces. The lamp can extended along with the side supports, an LED lamp tube moves outwards simultaneously along with the side supports, thereby extending the irradiation range of the lamp. The ballast can be hung in various ways. The ballast can be connected to the foldable lamp holder as an integrated lamp through the extension on a ballast shell. In addition, the lamp can be hung in various ways.

Abstract: A system and method for estimating a plurality of airspeed parameters of an aircraft is disclosed. The system comprises one or more processors and a memory coupled to the processor. The memory storing data comprises a database and program code that, when executed by the one or more processors, causes the system to receive a plurality of operating parameters that each represent an operating condition of the aircraft. The system is further caused to determine a stability-axis drag coefficient based on the plurality of operating parameters. The stability-axis drag coefficient quantifies a stability-axis drag of the aircraft created during high speed conditions. The system is caused to determine a body-axis lift coefficient based on the plurality of operating parameters, which corresponds to a lift of the aircraft created along a vertical body-axis. The system is also caused to determine a dynamic pressure, which is used to estimate the airspeed parameters.

Abstract: The present technology relates to methods, devices and systems for volume visualization and interaction in a virtual reality environment.

Abstract: A system and method for estimating a plurality of airspeed parameters of an aircraft is disclosed. The system comprises one or more processors and a memory coupled to the processor. The memory storing data comprising a database and program code that, when executed by the one or more processors, causes the system to receive a plurality of operating parameters that each represent an operating condition of the aircraft. The system is further caused to determine a model based dynamic pressure based on the operating parameters. The model based dynamic pressure is estimated based on steady flight conditions of the aircraft. The system is further caused to determine a bridge based dynamic pressure based on at least a temperature deviation and an inertial speed vector. The bridge based dynamic pressure is estimated for extreme flight conditions of the aircraft.

Abstract: Devices and methods for programming resistive change elements using an electrical stimulus are disclosed. According to some aspects of the present disclosure the devices and methods program at least one resistive change element within at least one resistive change element cell in a resistive change element array using an electrical stimulus having a voltage level greater than a steady state voltage level that can be supplied by a power supply.

Abstract: Devices and methods for programming resistive change elements using an electrical stimulus are disclosed. According to some aspects of the present disclosure the devices and methods program at least one resistive change element within at least one resistive change element cell in a resistive change element array using an electrical stimulus having a voltage level greater than a steady state voltage level that can be supplied by a power supply.

Abstract: Devices and methods for accessing resistive change elements in a resistive change element array to determine resistive states of the resistive change elements are disclosed. According to some aspects of the present disclosure the devices and methods access resistive change elements in a resistive change element array through a variety of operations. According to some aspects of the present disclosure the devices and methods supply an amount of current tailored for a particular operation. According to some aspects of the present disclosure the devices and methods compensate for circuit conditions of a resistive change element array by adjusting an amount of current tailored for a particular operation to compensate for circuit conditions of the resistive change element array.

Abstract: Resistive change element cells sharing a selection device and resistive change element arrays including a plurality of resistive change element cells and a plurality of selection devices arranged in a group of at least two resistive change element cells sharing one selection device configuration are disclosed. According to some aspects of the present disclosure a group of resistive change element cells can be arranged on one level above a selection device. According to some aspects of the present disclosure a group of resistive change element cells can be arranged on multiple levels above a selection device.

Abstract: Aircraft and methods and systems for determining airspeed of an aircraft. The methods and systems allow for calculation of airspeed in near-ground and on-ground aircraft operation. A GPS altitude and a vertical acceleration of the aircraft are obtained for a current time frame. A geometric altitude for the previous time frame is determined, and the difference between the GPS altitude and geometric altitude are combined with the vertical acceleration to calculate a geometric altitude rate of change. The geometric altitude rate of change is used to calculate a pressure altitude rate of change, which is used to calculate a pressure altitude for the aircraft. A static pressure is calculated from the pressure altitude, and the airspeed is calculated using the static pressure.

Abstract: Devices and methods for programming resistive change elements using an electrical stimulus are disclosed. According to some aspects of the present disclosure the devices and methods program at least one resistive change element within at least one resistive change element cell in a resistive change element array using an electrical stimulus having a voltage level greater than a steady state voltage level that can be supplied by a power supply.

Abstract: Devices and methods for accessing resistive change elements in a resistive change element array to determine resistive states of the resistive change elements are disclosed. According to some aspects of the present disclosure the devices and methods access resistive change elements in a resistive change element array through a variety of operations. According to some aspects of the present disclosure the devices and methods supply an amount of current tailored for a particular operation. According to some aspects of the present disclosure the devices and methods compensate for circuit conditions of a resistive change element array by adjusting an amount of current tailored for a particular operation to compensate for circuit conditions of the resistive change element array.

Abstract: Devices and methods for accessing resistive change elements in a resistive change element array to determine resistive states of the resistive change elements are disclosed. According to some aspects of the present disclosure the devices and methods access resistive change elements in a resistive change element array through a variety of operations. According to some aspects of the present disclosure the devices and methods supply an amount of current tailored for a particular operation. According to some aspects of the present disclosure the devices and methods compensate for circuit conditions of a resistive change element array by adjusting an amount of current tailored for a particular operation to compensate for circuit conditions of the resistive change element array.

Abstract: A system and method for estimating a plurality of airspeed parameters of an aircraft is disclosed. The system comprises one or more processors and a memory coupled to the processor. The memory storing data comprising a database and program code that, when executed by the one or more processors, causes the system to receive a plurality of operating parameters that each represent an operating condition of the aircraft. The system is further caused to determine a model based dynamic pressure based on the operating parameters. The model based dynamic pressure is estimated based on steady flight conditions of the aircraft. The system is further caused to determine a bridge based dynamic pressure based on at least a temperature deviation and an inertial speed vector. The bridge based dynamic pressure is estimated for extreme flight conditions of the aircraft.

Abstract: A system and method for estimating a plurality of airspeed parameters of an aircraft is disclosed. The system comprises one or more processors and a memory coupled to the processor. The memory storing data comprises a database and program code that, when executed by the one or more processors, causes the system to receive a plurality of operating parameters that each represent an operating condition of the aircraft. The system is further caused to determine a stability-axis drag coefficient based on the plurality of operating parameters. The stability-axis drag coefficient quantifies a stability-axis drag of the aircraft created during high speed conditions. The system is caused to determine a body-axis lift coefficient based on the plurality of operating parameters, which corresponds to a lift of the aircraft created along a vertical body-axis. The system is also caused to determine a dynamic pressure, which is used to estimate the airspeed parameters.

Abstract: Disclosed is a device for adjusting the height of a suspended lamp, which includes at least a guide roller combination, an operating cord, a limiting member, a controlling member and an adjusting shell, the adjusting shell being connected to the lamp, and the guide roller combination and the limiting member being arranged in the adjusting shell, a circumferential end surface of the guide roller combination includes an inwardly recessive roller groove in a radial direction thereof, the operating cord is arranged within the roller groove, one end of the operating cord exits through the adjusting shell and is fixed at an upper end in a lamp moving area range, the other end of the operating cord exits through the adjusting shell to become a free end.