Abstract: An antenna array has a plurality of square or rectangular antenna assemblies. Each assembly includes a first antenna assembly surface with a solar cell and a second antenna assembly with one or more antenna elements. The antenna assemblies are interconnected without gaps therebetween to form a first contiguous array surface comprised of the first antenna assembly surfaces and a second contiguous array surface comprised of the second antenna assembly surfaces. The antenna assemblies are connected together by mechanically stored-energy connectors, such as spring tape, that self-deploy the array in space without the use of electric energy.

Abstract: Methods and systems for implementing a Jupiter aerospace mission can enable delivery of a science payload to a Jupiter orbit on a direct Earth-to-Jupiter trajectory. Solar power and use of avionics also allow a fast assembly, integration, and test process compared to past outer Solar System missions. The spacecraft can include an aerodynamic forebody, a shell, and a thermal protection system. The spacecraft can manage the radiation environment, generate solar power, and return data to Earth with a robust radio-frequency (RF) amplification and antenna gain.

Abstract: A solar array structure for a spacecraft is based on a modular approach, allowing for arrays to be designed, and designed to be modified, and manufactured in reduced time and with reduced cost. The embodiments for the solar array are formed of multiple copies of a “bay” of a multiple strings of solar array cells mounted on semi-rigid face-sheet structural elements. The bays are then placed into frame structures made of tubes connected by nodes to provide an easily scalable, configurable, and producible solar array wing structure. This allows for rapid turnaround of program specific designs and proposal iterations that is quickly adaptable to new/future PhotoVoltaic (PV) technologies and that can create uniquely shaped (i.e., not rectangular) arrays, allowing for mass production with simple mass producible building blocks.

Abstract: A method of controlling a spacecraft is provided. The method includes one or more of calculating, by a control device, spacecraft position, attitude, and velocity, the spacecraft including a plurality of blade actuators controlling pitch for a plurality of blades, the plurality of blades extending radially away from a spacecraft core and including material configured to be deflected by solar pressure, receiving mission plan updates for the spacecraft, calculating an updated trajectory based on the position, attitude, velocity, mission plan updates, and past spacecraft behavior, generating maneuver parameters for the spacecraft from the updated trajectory, creating new blade pitch profiles for a plurality of blade actuators, from the maneuver parameters, sending controls corresponding to the new blade pitch profiles to the plurality of blade actuators, and transitioning from current blade pitch profiles to the new blade pitch profiles.

Abstract: In accordance with various embodiments of the disclosed subject matter, a system and method is configured for scheduling and invoking power sharing among satellites within a constellation of satellites such that energy storage systems at a target satellite may by charged prior to the use of electric propulsion thrust activation or other high electricity demand operations (or such operations contemporaneously augmented) by power beams transmitted from other (source) satellites within the constellation.

Abstract: A system for positioning at least one satellite in working orbit, characterized in that the system for positioning satellites in working orbit comprises: a first attachment device configured to attach a first satellite to the system for positioning satellites in working orbit; a main propulsion device with solid propulsion comprising a plurality of parallel solid-propellant cartridges; a secondary propulsion device which is re-ignitable; at least one position sensor configured to measure the position of said system; a monitoring unit connected to said at least one position sensor and which is configured to control a firing of the cartridges of the main propulsion device to move said system from a transfer orbit to a working orbit of the first satellite, said monitoring unit being further configured to control an opening of the first attachment device to separate said system from the first satellite.

Abstract: The present invention provides a stackable drone and a drone swarm comprising at least two stackable drones. Each drone comprising: a fuselage comprising a first end and a second end; a mating structure arranged in the fuselage and configured to have an opening at the first end of the fuselage, the mating structure forming a mating recess on a first side of the fuselage, the mating recess having an opening at the first side of the fuselage for receiving a mating projection from a further stacking unmanned aerial vehicle. The stackable drones do not require a large area of ground for take-off and landing, require only a small space for storage and transportation. When landing, based on the conical or pyramidal structure, the drone may slide down by gravitational force into the mating recess of another drone thereunder without needs of high precision positioning or alignment system.

Abstract: Multi-functional coilable thin-walled structures that can be implemented within space-based satellite modules, and methods for their manufacture are provided. Multi-functional coilable thin-walled structures are comprised of at least one longeron that is capable of rolling and collapsing upon itself. In some embodiments, the coilable thin-walled longeron is a flange longeron. The flange longeron contains at least two major regions: a web and a plurality of flanges. The web region comprises portions of flanges that are bonded to one another. The plurality of flanges separate from one another on the same end of the web region. The plurality of flanges are similar in thickness and shape.

Abstract: A vehicle lift system configured for wireless charging is disclosed. The vehicle lift system includes a vehicle lift and a light transmitter. The vehicle lift includes a base, a carriage, a lift actuator, a battery, and a photovoltaic receiver. The carriage is configured for receiving a wheel of a vehicle. The lift actuator is configured to vertically raise and lower the carriage relative to the base. The battery is configured to provide electrical energy to the vehicle lift. The photovoltaic receiver is electrically coupled with the battery. The light transmitter is configured for transmitting electrical energy to said photovoltaic receiver. Thus, the battery of the vehicle lift can be recharged wirelessly, such that the vehicle lift need not have a wired power connection.

Abstract: A deployable device includes a supporting structure, a mandrel able to move in rotation with respect to the supporting structure about a first axis Z, a membrane able to pass from a rolled-up configuration rolled up around the mandrel about the first axis Z to a deployed configuration deployed along a second axis X substantially perpendicular to the first axis Z. The device comprises two fittings secured to the mandrel at their centre, arranged one on either side of the membrane and comprising first stubs on their periphery, a casing extending between the two fittings, the casing comprising second stubs of a shape complementing the shape of the first stubs, the casing being able to pass from a rolled-up configuration at least partially enveloping the membrane in the rolled-up configuration to a deployed configuration at least partially superposed on the membrane in the deployed configuration.

Abstract: Satellites having autonomously deployable solar arrays are disclosed. A disclosed example satellite includes a solar array, a sensor to detect that the satellite has exited a launch vehicle, a processor to enable ignition of squibs of a squib array based on the satellite exiting the launch vehicle, and a squib controller to control the ignition of the squibs based on a firing sequence of the squibs, where the squib controller is to vary the firing sequence to autonomously deploy the solar array.

Abstract: At least first and second solar panels are provided, wherein: each of the first and second solar panels is comprised of a substrate having one or more solar cells bonded thereto, and a frame for supporting the substrate and the solar cells; the frame has a cutout or opening in a center of the frame under the solar cells and, when deployed, the cutout or opening enables cooling of the solar cells through the substrate by exposing a back side of the substrate for transferring or radiating heat directly through the cutout or opening of the frame; and the frame of the first solar panel is configured to be nested inside the cutout or opening of the frame of the second solar panel when the first and second solar panels are stowed in a stacked configuration.

Abstract: An apparatus includes a satellite in the form of a plate having a thickness being smaller than a width of the satellite. The apparatus also includes a plurality of contact points distributed on a face of the satellite, allowing for one or more additional satellites to be stacked upon the satellite.

Abstract: A display device is disclosed. The display device comprises: a display unit for displaying an image; a support for supporting the display unit; and a rotating unit for rotatably connecting the display unit to one surface part of the support; wherein the rotating unit rotates the display unit after tilting the same in a first tilting direction with respect to the one surface part of the support.

Abstract: A reflector antenna system comprising: a hoop assembly configured to expand between a collapsed configuration and an expanded configuration; a mesh reflector secured to the hoop assembly such that when the hoop assembly is in the collapsed configuration the mesh reflector is collapsed within the hoop assembly and when the hoop assembly is in the expanded configuration the mesh reflector is expanded to a shape that is intended to concentrate RF energy in a desired pattern; a mast assembly including an extendible boom to which the hoop assembly is secured by cords; and an antenna feed that is located on a vehicle so as to face a concave surface of the mesh reflector that is intended to concentrate RF energy in the desired pattern.

Abstract: A plurality of shape memory alloy tubes (SMTs) of one or more shape memory alloy (SMA) types is configured as an element in a rotary actuator system in a nested manner. In various configurations, the nested SMTs provide one or more modes of multiplication (torque output or angular displacement), rotation reversibility and bias loading. The innovation provides for leveraging the modes for reductions in the rotary actuator system size, weight, or complexity or combinations thereof, or providing improved and more stable actuation capabilities in a given envelope.

Abstract: The disclosed technology includes systems, methods, and mechanism configurations related to satellite solar panels, including stowing arrangements, deployment sequences, special purpose hinges, hold down and release mechanisms, and associated components for controlled deployment of the satellite solar panels.

Abstract: The disclosed technology includes systems, methods, and mechanism configurations related to satellite solar panels, including stowing arrangements, deployment sequences, special purpose hinges, hold down and release mechanisms, and associated components for controlled deployment of the satellite solar panels.

Abstract: A device comprises a platform constructed and arranged to be mounted to one or more solar array modules and one or more solar irradiance sensors on the platform configured to receive incident solar energy, the one or more solar irradiance sensors oriented on the platform so that the received incident solar energy is comparable to that received by the solar array modules, the one or more solar irradiance sensors providing solar irradiance signals in response to the incident solar energy. A processor is on the platform, the processor configured to receive the solar irradiance signals and, in response, generating a performance reference metric based on the solar irradiance signals, the performance reference metric related to the expected performance of the one or more solar array modules to which the platform is mounted. A transmitter is on the platform, the transmitter configured to periodically transmit the performance reference metric to a receiver.

Abstract: Systems and methods are described herein for a dual-voltage power system. In some aspects, a dual-voltage power system can include a first battery module and a second battery module. In some aspects, the first battery module operates at a first voltage and the second battery module operates at a second voltage. In some aspects, the first battery module delivers power to a plurality of primary systems. In some aspects, the second battery module delivers power to a plurality of parasitic systems.

Abstract: The present disclosure provides, among other things, a deployable solar array comprising: an array of electromagnetic transducer devices such as photovoltaic devices; and a flexible, elongated, rectangular sheet for supporting the array of electromagnetic transducer devices composed of a composite laminate having a predetermined pattern of graphite fiber plies which impart a predefined tension in the planar surface of the sheet so that it curls into a planar sheet with a uniform radius of curvature along its major axis.

Abstract: Deployable solar panels are disclosed. In some embodiments, the deployable solar panel includes an extendable member comprising a composite material and having a length and a width; a plurality of hinges, each of the plurality of hinges extending across the width of the extendable member, the plurality of hinges comprising composite material and a shape memory polymer; and a plurality of solar panels coupled with the extendable member. In some embodiments, the deployable solar panel includes a lenticular shape extending along the length of the extendable member.

Abstract: A method is described to reduce Global Warming by reflecting solar irradiance. Thin reflective sheets are flown under control in the upper atmosphere above Earth, in contrast to reflecting from Space orbits or the ground. The high altitude enables nearly total reflection. Two general embodiments use translational and/or rotational motion of the sheets to hold sheets stretched while providing aerodynamic lift, while a third uses buoyant aerostatic lift. During the daytime solar power is used. During the night the low wing loading of the sheets facilitates gliding flight without descending into controlled airspace. Sheets can be arrayed to increase aspect ratio and decrease induced drag. By following the summer sun, effectiveness is increased. A swarm of reflectors around the south Polar Circle can reduce summer melting of ice enough to reverse the rise in sea level.

Abstract: A floating power generation station comprises a floating hull with a shelter structure containing photovoltaic solar panels are arranged on a chain of floats, each hinged one to the next. The system can be deployed onto a large flat area, e.g., surface of inlet or bay, where the solar panel chain(s) can be extended out. The power generation station may include air displacement tubes that have a lower end immersed in water, and which feed into a plenum where check valves direct air unidirectionally to an air turbine that powers an electric generator. Air turbines or wind turbines on the barge can be raised or tipped up for collection of wind energy. The captured energy is stored on a bank of on-board storage batteries. Energy can be collected and stored, and the barge can be brought to shore when and where needed. This arrangement can be configured for ground-based deployment. The power generation station can be configured for use on dry land.

Abstract: One embodiment provides a solar roof tile module. The module includes a plurality of solar roof tiles positioned side by side and one or more tile spacers. The tiles are electrically and mechanically coupled to each other. A tile spacer is positioned between two adjacent solar roof tiles, thereby preventing water leakage. A solar roof tile can include a front cover, a back cover, and a plurality of photovoltaic strips positioned between the front and back covers. Each photovoltaic strip includes a first edge busbar located on an edge of a first surface and a second edge busbar located on an opposite edge of a second surface, and the photovoltaic strips are arranged in such a way that the first edge busbar of a photovoltaic strip overlaps with a second edge busbar of an adjacent photovoltaic strip, thereby forming a serial connection among the photovoltaic strips.

Abstract: The Structural Origami ARray (SOAR) concept is an extremely high performance, deployable solar array system that delivers high power output and exceeds state-of-the-art packaging efficiencies. Unlike existing Z-folding panels or rolled architectures, this approach utilizes an origami-inspired two-dimensional packaging scheme of a flexible blanket/substrate that is coupled with a simple and compact deployable supporting structure that stabilizes the array by external tension or internal support. This enables large deployed areas populated with high efficiency photovoltaic (PV) cells or antenna elements, which compactly stows in a square form factor with thin stack height that minimizes impingement on spacecraft bus internal volume.

Abstract: Solar cell array assemblies or modules mounted on a space vehicle having discrete predefined pressure sensitive adhesive (PSA) regions thereon. In certain embodiments, the solar cell array modules may be conveniently mounted on the surface of a panel of a space vehicle or satellite with the discrete predefined PSA regions sized and shaped to match portions of the panel.

Abstract: A torque generation system includes: a plurality of solar array panels and/or solar array panel divisions; and a torque controller configured to control an electricity generation ratio of each of the plurality of solar array panels and/or solar array panel divisions to generate torque.

Abstract: Foldable photovoltaic assemblies and methods of manufacturing such assemblies, including a transparent top sheet having a fold line and a conductive interconnection pattern spanning the fold line. The conductive interconnection pattern includes inter-cell connections configured to interconnect individual photovoltaic cells to form photovoltaic submodules, and also inter-submodule connections configured to interconnect photovoltaic submodules to form an assembly of submodules, which in some cases may be a fully assembled photovoltaic module. The inter-submodule connections span the fold line and are oriented at non-perpendicular angles relative to the fold line.

Abstract: An imaging system includes a metering structure and a plurality of foldable members disposed around a periphery of the metering structure. Each foldable member in the plurality of foldable members includes an arm comprising a strain deployable composite and a reflector disposed on the arm. The arm in a respective foldable member in the plurality of foldable members is configured to hold the respective foldable member toward the metering structure in a first state and to hold the respective foldable member away from the metering structure in a second state such that the reflector of the respective foldable member forms part of a sparse aperture in the second state.

Abstract: A deployable assembly comprises a supporting structure, a set of panels, each being linked to the adjacent panel by a hinge defining an intermediate axis of rotation, capable of switching from a stowed configuration in which the panels are folded one on top of the other to a deployed configuration, by rotation of the panels about the respective intermediate axes of rotation, wherein the panels are arranged substantially in the same plane, an articulation device defining a main axis of rotation of the set of panels relative to the supporting structure. The set of panels is rotationally mobile about the intermediate axes of rotation and the main axis of rotation to switch from the stowed configuration to the deployed configuration and the set of panels is only rotationally mobile about the main axis of rotation in deployed configuration to orient the set of panels relative to the supporting structure.

Abstract: An apparatus for satellite selection within a multi-satellite communication system, comprising an antenna, receiver, and transmitter, and a processing module configured to calculate a normalized distance metric for the plurality of user spot beams of a first and second satellite, select the user spot beam with the lowest normalized distance metric, and determine which of the at least first or second satellite is transmitting the selected user spot beam. Further, a method for increasing the aggregate capacity of a satellite communications network, comprising identifying high traffic regions within a coverage area of a first satellite, determining which user spot beams of the first satellite are available to each of the identified regions, determining a normalized distance metric for each user spot beam identified, and plotting a second beam pattern of a second satellite to produce at least one user spot beam with a lower normalized distance metric.

Abstract: Described herein is a thrust system for a vehicle that includes at least three electrical power controllers, at least four electrical switches each configured to receive electrical power from at least one of the at least three electrical power controllers, and at least three thrusters each configured to receive electrical power from at least one of the at least three electrical switches. The at least four electrical switches are operable to switch a supply of electrical power from any of the at least three electrical power controllers to any one of the at least three thrusters.

Abstract: An apparatus for satellite selection within a multi-satellite communication system, comprising an antenna, receiver, and transmitter, and a processing module configured to calculate a normalized distance metric for the plurality of user spot beams of a first and second satellite, select the user spot beam with the lowest normalized distance metric, and determine which of the at least first or second satellite is transmitting the selected user spot beam. Further, a method for increasing the aggregate capacity of a satellite communications network, comprising identifying high traffic regions within a coverage area of a first satellite, determining which user spot beams of the first satellite are available to each of the identified regions, determining a normalized distance metric for each user spot beam identified, and plotting a second beam pattern of a second satellite to produce at least one user spot beam with a lower normalized distance metric.

Abstract: The present invention provides a method for disturbance compensation based on a sliding mode disturbance observer for a spacecraft with a large flexible appendage, comprising steps of: a) building a spacecraft attitude control system; b) constructing an external system, the external system being incorporated with an uncertain portion of a damping matrix of a flexible appendage of the spacecraft; the external system being incorporated with an uncertain portion of a rigidity matrix of the flexible appendage of the spacecraft and describing a sum of flexible vibration and environmental disturbance; c) configuring a sliding mode disturbance observer for estimating the value of the sum of flexible vibration and environmental disturbance; d) compounding a nominal controller with the sliding mode disturbance observer in step c) to obtain a compound controller; the compound controller compensating for the sum of flexible vibration and environmental disturbance.

Abstract: Photovoltaic cells, facilities, systems and methods, as well as related compositions, are disclosed. Embodiments involve providing a sensor in association with a photovoltaic facility to form a sensor-pv facility; and providing the sensor-pv facility in a kit adapted for purchase by a consumer to be deployed in a home environment.

Abstract: A sun synchronous orbiting shield to block sun light to the earth. Shade is provided to the earth and travels across the earth as the earth rotates mitigating the effects of sunlight on global warming.

Abstract: There may be situations in which a ship at sea is lost and GPS is not available due to jamming, and neither a position fix nor GPS is available. A system and method allow estimation of ship position (SPOS) using only single radar range measurements and satellite ephemeris data. The same radar can determine ship velocity using radar range rate information.

Abstract: In a concentrated solar photoelectric system, at least one controllable radiation attenuation element (e.g., an array of controllable pixels or segments) is arranged to selectively attenuate transmission of radiation to a photoelectric element (e.g., a solar panel). Liquid crystals may provide attenuation utility without necessity for mechanical actuation. Attenuation may be controlled responsive to at least one sensor to maintain each portion of the photoelectric element at or below a maximum power conversion point. Non-planar attenuators and/or lenses may be provided. One or more thermal exchange fluid channels may be in thermal communication with the thermoelectric element.

Abstract: An apparatus and method for portable solar panel assemblies configured to enable the unit to be transported by multiple means in order to provide both grid tied and off grid power as needed. Solar panel assemblies are configured to have a range of rotation of approximately 0 to 25 degrees in two directions to allow efficient sunlight capture. The solar panel assembly in the closed position will allow for more compact and aerodynamic profile when being transported.

Abstract: A retractable and re-deployable boom assembly is provided for collecting electromagnetic energy, for instance in outer space. The assembly may include a boom having a deployable length and a first layer comprising a flexible substrate formed in a lenticular shape that elastically deforms, and a second layer thereon comprising an array of electromagnetic transducers, which may be positioned on adjacent flexible parabolic reflectors. The assembly may be placed into at least two different configurations: a stowed configuration where the majority of the length is elastically deformed; and a deployed configuration where the majority of the length is not deformed, and where the lenticular shape of the boom provides it with rigidity. The assembly may also have a rotational drive mechanism.

Abstract: A dozen or more orbiting solar generators stay in constant touch. They can be congregated rapidly in space at any desired secret location. Once congregated they all focus their energy to a death star. This death star is a newly launched ICBM with a microwave or laser collector. A laser generator uses this huge energy to project a non-nuclear death ray to a target. The target could be a city, a ship or a satellite. In the event of an asteroid approaching earth, this system could destroy an asteroid. In peacetime the orbiting solar generators supply electric power to an earth based power grid.

Abstract: A spacecraft comprises a hybrid assembly equipped with at least one solar panel characterized in that said assembly comprises at least one solar cell provided with luminous energy concentration means and said assembly also comprises at least one solar cell with no luminous energy concentration means.

Abstract: Extensible solar arrays configured to support one or more rollable solar panel units and that feature yoke segments and array segments that are configured to be stowed with their long axes substantially parallel to a spacecraft's roll axis. The yoke segments and array segments may be transitioned to a deployed configuration where the yoke segments are substantially perpendicular to the position the yoke segments were in in the stowed configuration, and the array segments are substantially perpendicular to the yoke segments. Some implementations of the extensible solar arrays may also include a rigid solar panel supported by one of the yoke segments.

Abstract: A directionally-controlled roll-out elastically deployable solar array structure is disclosed. The structure includes one or more longitudinal elastic roll out booms that may be closed section or open section to allow for efficient rolled packaging onto a lateral mandrel. A flexible photovoltaic blanket is attached to a tip structure and to a lateral base support structure, but remains uncoupled from the longitudinal booms. The solar array system may be stowed simultaneously into a rolled package comprised of the roll out booms and the flexible planar blanket together, or onto independent rolls. Alternatively, the system may be stowed by rolling the booms, and accordion Z-folding the hinged flexible photovoltaic blanket into a flat stack. Structural deployment is motivated by the elastic strain energy of the roll out booms, and several methods of deployment direction control are provided to ensure a known, controlled, and unidirectional deployment path of the elastically unrolling booms.

Abstract: A spacecraft may include a module structure having a plurality of module sides. The spacecraft may include a central cylinder extending through a center of the spacecraft. The central cylinder may be the only closed cross-section extending along a longitudinal axis of the spacecraft.

Abstract: A Deployable Morphing Modular Solar Array (DMMSA) for deploying Deployable Morphing Modular Solar Power Assemblies (DMMSPAs) from a spacecraft is provided. The DMMSA comprises a Root Staging and Deployment Mechanism (RSDM) mounted to a spacecraft. A plurality of petal assemblies are rotatably secured to the RSDM with each petal assembly having at least DMMSPA secured thereon and each DMMSPA having a slight V-configuration. A launch restraint assembly stacks and sandwiches the petal assemblies prior to deployment with the launch restraint assembly pre-loading each petal assembly's one or more DMMSPA into a substantially flat configuration. Upon release of the launch restraint assembly, the stacked and sandwiched petal assemblies rotate relative to the spacecraft and each petal assemblies DMMSPA elastically morphs from the substantially flat configuration into the slight V-configuration.

Abstract: This disclosure is directed to apparatuses, systems, and methods associated with the stowing, deploying, and deployment of a solar cell array. With reference to some exemplary embodiments this disclosure teaches apparatuses, systems, and methods directed to a solar cell array system that is a relatively lightweight, compact, and self-contained structure that securely stores, protects, and deploys the solar array. With reference to some exemplary embodiments this disclosure teaches apparatuses, systems, and methods for deploying a solar cell array that is held in the deployed configuration by self-contained compressive force and tensile force members such that no loads are carried through the solar cell panels.

Abstract: An attitude estimator that uses sun sensor outputs as the only attitude determination measurements to provide three-axis attitude information. This is accomplished by incorporating the Euler equation into the estimator. An unscented Kalman filter is employed to accommodate various nonlinear characteristics and uncertainties of the spacecraft dynamics and thus improve the robustness and accuracy of the attitude estimate.

Abstract: A dozen or more orbiting solar generators stay in constant touch. They can be congregated rapidly in space at any desired secret location. Once congregated they all focus their energy to a death star. This death star is a newly launched ICBM with a microwave or laser collector. A laser generator uses this huge energy to project a non-nuclear death ray to a target. The target could be a city, a ship or a satellite. In the event of an asteroid approaching earth, this system could destroy an asteroid. In peacetime the orbiting solar generators supply electric power to an earth based power grid.