7287results about "Cosmonautic vehicles" patented technology

A wireless power transfer system includes: a plurality of power transmitters, each of which transmits a microwave; and a rectenna base station which receives the microwave to generate power. The rectenna base station includes: a rectenna; and control section which specifies an identification code for identifying each power transmitter and generates a command signal to change a phase of the power transmitter specified by identification code so as to increase a power value received at the rectenna. Each of the power transmitters comprises: a plurality of transmission antenna elements, each of which transmits the microwave to the rectenna base station; and a phase controller which makes phase change of the microwave based on the command signal from the phase monitor and control section of the rectenna base station if the identification code matches a stored identification code.

Compression exerted by a clamp collar integral to a molded plastic flexible shaft coupling accommodating angular shaft misalignment upon the circumferential outward surface of a radially compressible molded sleeve insert located in a shaft bore of the flexible coupling facilitates engagement of a reduced diameter shaft located within the sleeve insert. Use of a sleeve insert having a different internal diameter similarly accommodates flexible coupling to another diameter shaft. Utilization of sleeve inserts selected from a plurality of different reduced internal diameters and exterior diameters sized to fit either shaft bore enables flexible coupling of both multiple matched shaft diameters and an exponential number of differing opposed shaft diameter combinations within a range limited by the flexible coupling shaft bores. Radial compressibility of the sleeve insert is facilitated by the utilization of resilient material, interruption of the circumferential extension by a longitudinal slot, or both. Utilization of congruent longitudinally uniform, radially non-uniform, flexible coupling shaft bore and insert sleeve outward surfaces provides additional torque transmission capacity.

Embodiments are disclosed for a vehicle control system and related sub-components that together provide an operator with a plurality of specific modes of operation, wherein various modes of operation incorporate different levels of autonomous control. Through a control user interface, an operator can move between certain modes of control even after vehicle deployment. Specialized autopilot system components and methods are employed to ensure smooth transitions between control modes. Empowered by the multi-modal control system, an operator can even manage multiple vehicles simultaneously.

Methods and apparatuses provide surveillance of a convoy. At least one unmanned aerial vehicle (UAV) obtains images around the convoy's position to provide information about potential hostile activity while the UAV follows a generally curvilinear path around the convoy as instructed by one of the convoy vehicles. Path planner algorithm software is executed by the controlling convoy vehicle in which position and velocity information regarding the unmanned aerial vehicle and the convoy are processed to determine values of control variables. The determined values are sent to the unmanned aerial vehicle over a wireless communications channel. The path of the surveillance vehicle may be changed in order to provide evasive measures to avoid an attack on the surveillance vehicle by an adversary.

The present invention relates to a propulsion system of a vertical takeoff and landing aircraft or vehicle moving in any fluid or vacuum and more particularly to a vector control system of the vehicle propulsion thrust allowing an independent displacement with six degrees of freedom, three degrees of translation in relation to its centre of mass and three degrees of rotation in relation to its centre of mass. The aircraft displacement ability using the propulsion system of the present invention depends on two main thrusters or propellers and which can be tilted around pitch is (I) by means of tilting mechanisms and, used to perform a forward or backward movement, can be tilted around roll axis (X) by means of tilting mechanisms and, used to perform lateral movements to the right or to the left and to perform upward or downward movements (Z), the main thrusters being further used to perform rotations around the vehicle yaw axis (Z) and around the roll is (X). The locomotion function also uses one or two auxiliary thrusters or propellers and mainly used to control the rotation around the pitch axis, these thrusters or propellers and being fixed at or near the longitudinal is of the vehicle, with there thrust perpendicular or nearly perpendicular to the roll and pitch axis of the vehicle.

A system for alerting the occupant of a vehicle that the vehicle is in or approaching a zone of awareness. For instance, the system may be used to alert the pilot or flight crew of an aircraft that the aircraft is on or approaching a runway, and may identify the specific runway. Thus, the invention also provides a method of reducing unintentional incursions of taxiing aircraft onto runways. The system generally includes a storage device or memory, a positioning system such as a GPS that typically repeatedly determines the location of the vehicle, an alerting device such as an alarm or display, and a processor, all of which are typically located on the vehicle. The processor typically compares the location of the vehicle with stored location information for various zones of awareness and initiates an alert when appropriate. The processor may take into consideration the velocity and direction of travel of the vehicle. Zones of awareness may be defined by coordinates, such as the end points of line segments. Audible alarms may include a voice warning, and may be able to be silenced until the vehicle leaves the zone of awareness. On aircraft, the system may reference the centerline of the runway, for example, alerting when the aircraft is within 150 feet of the centerline. The system may be disabled when the aircraft is in flight.

A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a first fan assembly disposed upstream from the core gas turbine engine, a first gearbox coupled to the first fan assembly, and a second gearbox coupled to a booster compressor such that the booster compressor rotates in a rotational direction that is opposite to the rotational direction of the first fan assembly. A method of assembling the above turbofan engine assembly is also described herein.

A method of converting air internal energy into useful kinetic energy is based on air flowing through substantially convergent nozzle, which accelerates the air as the cross section of the nozzle decreases thus increasing the air kinetic energy. The increment of the kinetic energy equals to the decrement of air internal energy, i.e., air temperature. Within said nozzle a turbine is placed to convert airflow kinetic energy into mechanical energy that transformed into electrical energy or transferred into a gearbox to provide driving moment. Devices uses this method could use natural wind as airflow source or artificial airflow means. Devices, which incorporate means to create airflow artificially, can be used as engines for land, sea and flying vehicle. Since air temperature drops within the nozzle, moisture condensation exists and liquid water can be accumulated for further use.

The present invention provides a solar cell comprising a substrate, a first buffer layer disposed above the base layer, a second buffer layer disposed above the first buffer layer, a first boron compound layer disposed above the second buffer layer, a second boron compound layer disposed above the first compound layer, and a window layer disposed above the second compound layer, wherein the first compound layer comprises a first type of doping, wherein the second compound layer comprises a second type of doping, wherein the second buffer layer comprises a higher energy bandgap than the first compound layer, and wherein the first buffer layer and the second buffer layer permit a boron content in the first compound layer and the second compound layer to be greater than 3 %.

The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, (b) extends into the cylindrical vessel, and (c) can be moved along the longitudinal axis, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle creates a plasma that discharges through the hollow electrode nozzle.

A foldable member in the shape of a tube with at least one predetermined hinge area along the length of the tube and opposing sets of elongated slots in the tube at the hinge area thereof forming separated longitudinal strips of tube material between the slots which fold when subjected to localized buckling forces, each slot of each set of elongated slots separated longitudinally along the length of the tube from each adjacent slot by a bridge element of tube material. A collapsible structure constructed of such foldable members.

A gas turbine engine system includes a fan (14), a housing (28) arranged about the fan, a gas turbine engine core having a compressor (16) at least partially within the housing, and a fan bypass passage (30) downstream of the fan for conveying a bypass airflow (D) between the housing and the gas turbine engine core. A nozzle (40) associated with the fan bypass passage includes a first nozzle section (54a) that is operative to move in a generally axial direction to influence the bypass airflow, and a second nozzle section that is operative to also move in a generally axial direction between a stowed position and a thrust reverse position that diverts the bypass airflow in a thrust reversing direction. An actuator (42) selectively moves the first nozzle section and the second nozzle section to influence the bypass airflow and provide thrust reversal.

A method for obtaining warranty registration of products, facilitating return of lost products, and expediting warranty service on defective products comprising providing a unique identifier on or within each product; providing a lost and found system comprising the steps of marking each product with return instructions and a reward offer to any person who finds said product after it has been lost; and offering to return each product to a registered owner in the event said product is lost and returned by said person who finds it if said owner provides data comprising owner identification and date said product was purchased at retail; providing said data to a manufacturer or other warrantor in order to register said warranty.

A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a counter-rotating fan assembly including a forward fan assembly and an axially aft fan assembly to the low-pressure turbine such that the forward fan assembly rotates in a first direction and the aft fan assembly rotates in an opposite second direction, and coupling a booster compressor directly to the low-pressure turbine such that the booster compressor rotates in the first direction.

A device for protecting against arcing events solar array panels and control equipment supplying a main power bus is provided. The control equipment comprises a regulator for controlling a solar array voltage (VS) and includes a power dump stage for shunting the solar array voltage as a function of a control signal. The device comprises a voltage drop detection circuit for generating a voltage drop detection signal (VD) when a voltage drop is detected in the solar array voltage (VS), and an arc-quenching circuit comprising a system for generating an output signal (VO) which is applied as the control signal to the power dump stage so as to shunt the solar array voltage (VS) when a voltage drop is detected by the voltage drop detection circuit.

Methods and apparatuses provide surveillance of a convoy. At least one unmanned aerial vehicle (UAV) obtains images around the convoy's position to provide information about potential hostile activity while the UAV follows a generally curvilinear path around the convoy as instructed by one of the convoy vehicles. Path planner algorithm software is executed by the controlling convoy vehicle in which position and velocity information regarding the unmanned aerial vehicle and the convoy are processed to determine values of control variables. The determined values are sent to the unmanned aerial vehicle over a wireless communications channel. The path of the surveillance vehicle may be changed in order to provide evasive measures to avoid an attack on the surveillance vehicle by an adversary.

A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a counter-rotating fan assembly including a forward fan assembly and an axially aft fan assembly to the low-pressure turbine such that the forward fan assembly rotates in a first direction and the aft fan assembly rotates in an opposite second direction, and coupling a booster compressor directly to the low-pressure turbine such that the booster compressor rotates in the first direction.