32 results about "Space-based solar power" patented technology

The present invention is primarily directed to cost-effective systems for using large reflective elements that track the sun on two axes to concentrate solar energy onto a receiver that can convert the sun's optical energy to a form usable for extensive displacement of combustion of fossil fuels. The structures of the tracker frame, tracking mechanism and tracker supports are co-optimized with the optical elements and the receiver for high efficiency, low cost, and ease of assembly, making moderate and large-scale implementations cost-competitive with fossil fuels for peak power, and, with suitable storage, for base-load power and dispatchable peaking power in sunny locations. Improvement to small-tracker two-axis systems and one-axis tracking systems that focus in two dimensions are also included, as are improvements in systems for space-based solar power.

A space-based solar power station, a power generating satellite module and/or a method for collecting solar radiation and transmitting power generated using electrical current produced therefrom is provided. Each solar power station includes a plurality of satellite modules. The plurality of satellite modules each include a plurality of modular power generation tiles including a photovoltaic solar radiation collector, a power transmitter and associated control electronics. Numerous embodiments relate to efficient power generation tiles. In one embodiment, an efficient power generation tile includes: at least one photovoltaic material; and at least one concentrator that redirects incident solar radiation towards a photovoltaic material such that the photovoltaic material experiences a greater solar flux relative to the case where the photovoltaic material experiences unaltered solar radiation.

A solar cell assembly or sub-array for space applications that comprises a string of series connected space qualified solar cells, one of the solar cells being a final solar cell of the string of solar cells. The final solar cell has at least one oblique cut corner. The solar cell assembly further comprises a contact member connected to the final solar cell through a blocking diode, positioned in correspondence with the space provided by the space provided by the oblique cut corner.

A space solar concentrator based on deployable reflectors attached to a panel base is described. Each of the reflectors includes sides coated with reflective coating on surfaces facing away from the base. In one embodiment, the sides of the reflector have thicker portion to provide stiffness for deployment absent compressive force, and thinner portion to reduce weight and storage energy. In another embodiment, both reflective sides are unfolded when the reflectors are in stowed position. During deployment, a stop side will limit the deployment of both reflective sides and ensure the proper reflecting position. In addition, these embodiments reduce the storage energy.

A flexible hybrid coverglass for spacecraft solar panels comprised of small beads of either fused silica or ceria-doped borosilicate glass embedded in a matrix of conventional coverglass adhesives. These beads may also be used in a matrix of Kapton as the solar panel's substrate which may be combined with flexible solar cells to form flexible solar panels.

Systems and methods in accordance with various embodiments of the invention implement mirrors that are more transparent to specific regions of the electromagnetic spectrum (e.g. the microwave region of the electromagnetic spectrum) relative to conventional metallic mirrors (e.g. mirrors made form aluminum or silver). In one embodiment, a space-based solar power system includes: a photovoltaic material; and a mirror that is—relative to a 10 μm thick sheet of aluminum—more transparent to at least one of a substantial portion of the microwave region of the electromagnetic spectrum and a substantial portion of the radio wave region of the electromagnetic spectrum; where the mirror is configured to focus incident visible light onto the photovoltaic material.

A modular, lightweight, high-survivable, photovoltaic flexible blanket assembly for a space solar array is disclosed. The modular blanket is an accordion foldable or rollable flexible photovoltaic solar panel blanket assembly comprising a plurality of common photovoltaic modules spaced in an orthogonal pattern. Each module is mechanically attached with multiple low profile fasteners on their backside to an open weave mesh tensioned backplane structure. The backplane forms a tensioned dimensionally stable planar surface in the deployed configuration onto which the modules are suspended. Each module is common and comprised of a rectangular substrate that includes solar cell assemblies, circuitry, exposed electrical contacts for integration of blanket-level harnessing, and frontside and rearside shielding and coatings as required for the mission application. The blanket assembly may be dispersed with an open pattern of compliant and formable material on the backside to provide insulation against the vigorous vibration of the launch environment.

The invention discloses a space solar energy utilization method, which can effectively utilize space solar energy on a large scale. A solar collection and utilization device in a satellite or an airship or a high-altitude aircraft is supported or fixed or adjusted through a network bracket which accords with the needed specified shape and consists of pipelines filled with gas or liquid. Planar objects for receiving solar energy in the solar collection and utilization device are attached to or fused on the network of the pipelines filled with gas or liquid; the planar objects can be reflective gathering films for sunlight; the sunlight subjected to reflective gathering is converted into parallel light and is projected onto other satellites or airships or various aircrafts or ground receiving stations in a form of the parallel light; the projected objects generate power or continuously transmit the parallel light; if more than one solar collection and utilization device is arranged, the plurality of solar collection and utilization devices at different positions can project the light onto the same projected object.

This invention discloses a condenser for a space solar energy power station which comprises an annular inflatable air bag made of flexible materials. A light-reflecting thin film made of flexible materials is fixed on the annular surface of the annular inflatable air bag; a support rod made of rigid materials passes through the center of the light-reflecting thin film and is fixed with the light-reflecting thin film; the focus where the support rod is positioned on the light-reflecting thin film surface is provided with a photovoltaic member; the annular inflatable air bag is connected to the support rod through pulling ropes; the lengths of the pulling ropes can be adjusted to enable the light-reflecting thin film to form a cone-shaped reflection surface and the apex angle of the cone-shaped reflection surface can be adjusted; the cone-shaped reflection surface is plated with a light-reflecting layer; and when the annular air bag is in an inflating state, the light-reflecting thin film which is in a foldable state is expanded. The condenser for the space solar energy power station is characterized in that the ratio of the expanding area to the folding volume is high, which is beneficial for rocket emission, and an oversized condensation solar reflector is obtained. The condenser for the space solar energy power station is applicable to the space solar energy power station and the earth solar energy power station.

Disclosed is a circulation type space-based solar power system, the system including: one or more solar modules; a conveyor belt on which the solar modules are attached, whereby the solar modules move between a solar power generating position and a recovery position, the solar modules receiving sunlight to generate solar power in the solar power generating position, and not receiving sunlight in the recovery position; a driver moving the conveyor belt; and a protective plate blocking cosmic rays incident to the solar modules located in the recovery position. The system can generate solar power for a long time by moving the solar modules between the solar power generating position and the recovery position. While some of the solar modules generate solar power, the remaining solar modules having damage are recovered.

The invention discloses a space solar energy base station. The space solar energy base station is characterized in that the space solar energy base station can be arranged on an earth preliminary orbit, a geo-synchronous orbit, a sun synchronous orbit or a sunlight planetary satellite orbit requiring providing focusing; the base station utilizes flexible-umbrella type folding and telescoping light concentration units to reflect the space solar energy after being focused to a device used by terminal equipment; the space solar energy base station is formed by a plurality of light concentration units which utilize the umbrella type telescoping structure; the angle of the sunlight focused through each light concentration unit can be changed through an independent reflective mirror, and the focusing degree of the sunlight can be improved too; and finally, the sunlight is reflected to the terminal equipment through the independent reflective mirror.

The present invention generally is a system and method for ground, atmospheric and space based solar powered electrical energy generation and transmission of beamed microwave power. Specifically it is a system and method for generating electrical energy from a plurality of photovoltaic cells dispersed on a flexible surface each in close proximity to and functionally connected to microwave generating and transmitting means for controllably forming one or more stronger microwave beams by combining a plurality of much weaker individual microwave beams. The invention can be a microwave beam weapon for detecting and transferring microwave energy to non-cooperative targets or it clear orbital debris by momentum transfer to space object through microwave radiation pressure. Most practically it can provide electric power and microwave beam weapon defense to remote military and civilian facilities, including forward operating bases.

The invention provides an electric rail train segmented power supplying system using solar energy and a control method thereof. The system comprises a control terminal and a receiving terminal. The control terminal comprises a plurality of spatial solar power stations, a plurality of electric power transmitters and a plurality of positioning controllers, wherein the spatial solar power stations are geostationary satellites provided with solar power stations; the plurality of electric power transmitters and the plurality of positioning controllers are installed on the plurality of spatial solar power stations. The receiving terminal comprises a plurality of electric power receivers, multiple groups of high-capacity storage batteries and a plurality of positioning information transmitters, wherein the electric power receivers, the high-capacity storage batteries and the positioning information transmitters are respectively installed on the top and inside an electric rail train; and the high-capacity storage batteries, the electric power receivers and the positioning information transmitters are interconnected for supplying power to the electric rail train. Being characterized of energy-saving, and environment-friendly, and being precise in positioning, the provided electric rail train segmented power supplying system using the solar energy and the control method thereof can achieve the wireless segmented power supply to the electric rail train.

The invention discloses a pyramid building construction technology which is mainly used for space base construction and mainly solves the problems that in the prior art, a large quantity of manpower, financial resources, energy sources and resources need to be put into space base construction. The construction method that sand and stones which are collected nearby a space base are melted by adopting high temperature generated when sunlight in focused and then applied to a building is adopted, in the construction method, a space solar energy base station (the application number is 2015108331435) matched with the space base needs to be put in the early stage, a base construction robot or spaceman is needed, and main materials of the building are locally obtained. Compared with an existing space base construction scheme, the resource investment is greatly reduced, after the base is constructed, the space solar energy base station serves as the energy sources of the base and the important factors for long-term stationing of animals, plants and humans, and light energy supplied by the space solar energy base station can locally change the environmental factors nearby the base. A pyramid structure is adopted in the building structure for resisting cosmic rays, solar wind, meteor strike, crustal movement and some certain natural factors.

The present invention discloses a multi-mode driven carrying system applicable to the space flight and is used for solving the problem that the residence time of space carriers is short due to the limited fuel. The solution is derived from the multiple modes of the power source of the carrying system: one mode refers to the liquid hydrogen and liquid oxygen fuel carried by a carrier per se, to be used for providing conventional jet power; one mode refers to the microwave drive mode of which the energy comes from the power generated by solar power panels carried by the carrier per se; one mode refers to the electronic linear accelerator drive mode; and one mode refers to the power given by a ''closed drive'', the energy comes from the electric energy generated by a space solar power station, and the energy is inputted into the carrier through microwaves. The ''closed drive'' consists of two separate systems, which can independently provide power. The multi-mode driven carrying system applicable to the space flight allows for the coordinated use of a variety of energy sources, for the space flight of spacecrafts having different purposes, such as carrying unmatched satellites from the low orbit to the designed orbit; the multi-mode driven carrying system applicable to the space flight can serve as a carrying system for deep space travel; and the multi-mode driven carrying system applicable to the space flight can serve as a carrier used for removing space debris and capable of working for a long time, and the like.