79 results about "Space craft" patented technology

The present invention provides a method, system and apparatus for robotic refueling of satellites. The system may include a dedicated refueling satellite launched directly from either earth, or alternatively it could be launched from another larger mother spacecraft or space station in which the refueling satellite is ferried into space in the case of the larger space craft or it may be stored on the space station until needed from which it can be launched. The system includes a robotic arm, suitable tools which can be affixed to the end effector of the robotic arm required for accessing, opening and closing the fuel fill valve on the satellite being serviced, storage and retrieval stations on a tool caddy on which the tools and various fuel fill valve caps are stored. The system is under teleoperation by a remotely located operator, for example located on earth, in the mother station or in the space station. Cameras are included focussed on the robotic arm and end effector and images are transmitted to the operator to allow the operator to direct and control the refueling procedure. The system may also be configured to be operated autonomously under computer control.

The present invention provides a method, system and apparatus for robotic refuelling of satellites. The system may include a dedicated refuelling satellite launched directly from either earth, or alternatively it could be launched from another larger mother spacecraft or space station in which the refuelling satellite is ferried into space in the case of the larger space craft or it may be stored on the space station until needed from which it can be launched. The system includes a robotic arm, suitable tools which can be affixed to the end effector of the robotic arm required for accessing, opening and closing the fuel fill valve on the satellite being serviced, storage and retrieval stations on a tool caddy on which the tools and various fuel fill valve caps are stored. The system is under teleoperation by a remotely located operator, for example located on earth, in the mother station or in the space station. Cameras are included focussed on the robotic arm and end effector and images are transmitted to the operator to allow the operator to direct and control the refuelling procedure. The system may also be configured to be operated autonomously under computer control.

The present invention is overall satellite vibration reducing isolator and aims at solving the problem that the overall satellite vibration reducing isolator has different longitudinal and transverse vibration isolating frequencies and the requirement of no reduction in transverse torsional rigidity of satellite support. The present invention resolves the vibration caused by the carrier rocket into one transverse vibration component and one longitudinal vibration component for subsequent separated vibration reduction and isolation. The overall satellite vibration reducing isolator includes satellite connect member, vibration reducing and isolating mechanism and carrier connecting member. The present invention makes it possible to use precise elements in space craft and lower satellite launching cost via reducing vibration of satellite.

The invention provides a rail-changing method which reduces the gravity loss of an aircraft, relating to aircraft rail-changing technical field. The invention comprises the steps of (1) before the rail of the aircraft is changed, rail power starting time, initial gesture and gesture angular speed are calculated on the ground; (2) the three parameters of the rail power starting time, the initial gesture and the gesture angular speed are optimized, thus leading the direction of the thrust to be always close to the speed direction of the aircraft in the rail-changing process of the aircraft; (3) the calculated parameters are input to the star; (4) the aircraft uniformly rotates according to the angular speed determined by the ground instruction parameters. The rail-changing method of the invention leads the rail-changing fuel consumption to be extremely close to the fuel consumption of the rail-changing in the speed direction and can effectively reduce the fuel consumption compared with the fixed thrust direction rail-changing method.

The invention relates to a silver electroplating technology for molybdenum foils used for panel substrate interconnecting flakes of solar cells of a space craft. The technology comprises the steps of molybdenum foils buffing and degreasing treatment, acid cleaning activation treatment, silver metal plasma injection, high temperature annealing treatment, silver leaching treatment, silver electroplating, EDS testing on the constituents of an electroplated layer, shape and morphology SEM observation, passivation for the electroplated molybdenum foils, and testing on the conductibility and the weldability of the electroplated molybdenum foils. The vacuum metal plasma injection technology provided by the invention comprises the following steps: injecting metallic elements as per certain energy and dosage into the molybdenum foil interconnecting flake material processed by buffing, degreasing treatment and acid cleaning activation treatment; carrying out silver leaching treatment after vacuum high temperature annealing; and carrying out non-cyanide silver electroplating so as to achieve a silver plating layer on the molybdenum foils, which is characterized by seamlessness, fine and round crystal grains and dense structure. The passivation treatment for the electroplated molybdenum foils gives the silver plating layer the ability to prevent the silver plating layer from being corroded by sulfide. Meanwhile, the conductibility and the weldability of electroplated aluminum foils are greatly improved without being affected by the passivation treatment.

The present invention provides one micro space generation module with photoelectric converter, thermoelectric converter and plasma-to-electricity converter integrated together, and the module has deposited photoelectronic film and hot ion emitting film, semiconductor photoelectronic element and other micro cell module units. The micro space generation module can realize excellent stepped energy utilization and may be used in various fields, especially as the high efficiency and long life cell for micro space craft and other effective load after being provided with isotope fuel. It may be usedin desert and other places with rich solar energy, and may be miniaturized for use in micro electromechanical system.

Vehicle propulsion systems and methods of propulsion are disclosed, as well as embodiments of fans and airfoils, technology that in some applications of the invention can provide both lift and thrust, and propulsion via cross flow fan, manifold and a plurality of airfoils. In some embodiments the invention is directed to the production of lift and thrust, and propulsion generally, based from air produced by a cross flow fan in accordance with the invention disclosed herein. In still further embodiments, lift and thrust may yet be generated from air produced from the cross flow fan even when unpowered, such as in a loss of power or in a stall condition. Applications of the invention apply broadly to propulsion systems, generally; however, some preferred embodiments have particular application for vehicles characterized or used in application such as traditional private and commercial aircraft, ground effects vehicles, military applications, amphibious applications, aerospace, aeronautical, and non-traditional vehicles such as experimental air planes, space craft, hover craft, and the like. The invention in some embodiments comprises technologies addressing preferred air flow, lift, and thrust and the reduction of drag and circulation losses. The invention may be further applicable for incorporation in aircraft and other vehicles wherein the ability to maximize initial vertical lift and takeoff is important, such as in instant take-off and landing, as well as the abilities to hover, to control the flight and landing of aircraft, and control in power-loss scenarios, addressing the prevention of stalls and allowing for controlled descents under continued propulsion. In some embodiments, the invention is further applicable for aircraft, shuttles and other vehicles as a ram jet engine system as a further alternative propulsion technology, having no requirement for forward movement for propulsion upon take-off.

This invention provides a coupling method for coupling a first and a second stiffening profile element for an outer skin of an aircraft or space craft. In a first step the stiffening profile elements are arranged on the outer skin in such a manner that the stiffening profile elements oppose each other with their respective front sides and enclose within themselves a cavity. Furthermore, a fixing hole is formed through a wall of at least one of the stiffening profile elements in the cavity inside a coupling zone of the stiffening profile element. An access opening is formed through the wall in the cavity along the coupling zone. A coupling strap, which couples the stiffening profile elements together, is fastened to the coupling zone by means of a fastening element guided through the fixing hole.

The present invention relates to a device for supporting systems, for example an electric cable or a fluid-carrying pipe, on a structure of an aircraft or space craft, and to an aircraft or space craft with such a device. The device has a basic bracket arrangement which can be fastened to at least one predetermined fastening section of the structure, and also has at least one system bracket for supporting the systems. The at least one system bracket can be fastened to the basic bracket arrangement locationally variable with respect to the fastening section. The advantage of the invention consists in the fact that a route of a system can be flexibly varied even during the equipment assembly, i.e. the structure is no longer modifiable or is only modifiable at considerable expense.