52 results about "Atmosphere of Earth" patented technology

The invention relates to a multi-objective optimization anti-interference filtering method for a SINS / GPS / polarized light combined navigation system, and relates to the multi-objective optimization anti-interference filtering method for the SINS / GPS / polarized light combined navigation system of carriers in earth atmosphere, wherein the carriers comprise unmanned plane, ship, vehicles and the like. The method is characterized by: classifying SINS, GPS, polarization sensors, and interferences in the environment, interference modeling for different type interference, designing an interference observer to cancel the interferences that can be modeled, inhibiting Gaussian random variables by H2 optimization technology, and inhibiting norm-bounded unknown variables by H-infinity optimization method. According to the multi-objective optimization anti-interference filtering method, the characteristics of the interferences in the SINS / GPS / polarized light combined navigation system is fully utilized, interference cancellation and interference inhibition are carried out by using the method of designing the interference observer and robust technology, and the method is usable for improving navigation precision of the carriers in the earth atmosphere.

The invention discloses a method and device for cleaning space debris. According to the method, electromagnetic force is applied to the space debris running on an original orbit; the speed and / or direction of the space debris are / is changed under the action of the electromagnetic force; the space debris of which the speed is changed is changed to run on a new orbit under the action of gravity; at least the height of the perigee of the space debris on the new orbit is smaller than the height of the perigee of the space debris on the original orbit; the space debris running on the new orbit finally falls into the atmosphere of the earth under the action of atmosphere resistance. The device comprises a satellite bearing platform which is provided with an electric field device cleaning the space debris or a magnetic field device cleaning the space debris or a combination of the electric field device and the magnetic field device. The method and device for cleaning the space debris do not have high requirements for the accuracy of position detection of the space debris, micro space debris can be effectively cleaned, solar energy can be fully utilized for power generation, and self-carried energy is saved. The device for cleaning the space debris has the advantages of being simple in structure, low in manufacturing cost, and better in pulse action effect.

In some embodiments of the invention, methods and devices are provided that perturb a trajectory of a space-orbital object. For example, a spacecraft may be sent to a location near a space-orbital object orbiting the Earth. A net may be released from the spacecraft in a manner (e.g., with a given alignment, direction and velocity) that results in the net contacting and / or entangling with the object. This contact or entanglement may alter a velocity of the space-orbital object and thereby may alter its orbital path. In some instances, the net's velocity is sufficient to experience increase drag by the Earth's atmosphere, relative to the drag it would have otherwise experienced if the net did not contact the object.

A means for harvesting local energy and using it to generate local electric power is disclosed which uses as its energy source P-Static charge generated on the external surfaces of aircraft flying through the earths atmosphere or generated on the external surfaces of electrically ungrounded objects immersed in the wind and subjected to the impact of charge generating ingredients contained in the atmosphere or wind. The P-Static charge is collected and stored in a high voltage rechargeable capacitor storage unit at several thousand volts with energy removed from the storage unit as needed and converted to low voltage DC or AC power which, in turn, is used to power local, low power consumption electronic chips and devices. Data measured by the chips or devices is relayed wirelessly back to a receiver located within the aircraft or object with the wireless transmitter also powered by the P-Static Electrical Power System.

An increasing level of carbon dioxide gas in the earth's atmosphere has been determined and is generally accepted by the scientific community. The human contribution to increases in the percentage of carbon dioxide in the atmosphere has been identified as a driving force of global climate change.The impact of global climate change might be mitigated by means to reduce or stabilize the percentage of carbon dioxide in the atmosphere.The invention provides a means for cleaning the atmosphere of carbon dioxide molecules by dissociation and refining the by-products into valuable fuels and other substances. It is taught that solar energy can be used to energize a photonic crystal producing the power and specific frequency required for localized excitation of CO2 molecules in a specific vibration mode and to the majority exclusion molecular structures comprising atmospheric gases sufficient to break covalent bonds of CO2, thereby producing reactant by-product that can be collected and refined into valuable substances and fuel.

Systems and methods for concentrating solar energy in the high earth atmosphere and transmitting the concentrated solar energy to the earth's surface. A system includes a light weight solar concentrator, supported by a light weight, rigid, buoyant, structure (36). The buoyant structure is suspended high in the earth's atmosphere above clouds and weather. Steerable mirrors, and / or a steerable structure, enable the concentrator to track the sun. In one embodiment, a buoyant light pipe (20) enables the transmission of concentrated solar energy from the high altitude concentrator to the earth's surface for further use. The system provides concentrated solar energy for use at any location on the earth, such use including generation of electricity via thermal or photovoltaic means and, direct and indirect process heat. A high solar concentration ratio enables high temperature, and hence high efficiency heat engine operation. With the provision of a thermal storage unit a system can provide utility scale continuous electricity generation at any location on the planet.

A method for developing and utilizing a Space Cruiser vehicle efficiently combines resources from relevant end users in industry and the military. The preferred vehicle has an elongated conical shell with an elliptical transverse cross section. The cabin of the vehicle preferably has a circular transverse cross section, leaving space between the cabin and the shell to store vehicle fuel. The cabin is insulated and capable of supporting occupants in a shirt-sleeve, air-breathing environment whether in the Earth's atmosphere or in outerspace. The vehicle is capable of being launched from conventional aircraft, and also being stored in and launched from a space shuttle or orbiting space station.

A space based orbital kinetic energy weapon system and method of using same is provided. The space based orbital kinetic energy weapon system includes a satellite having a control system configured to maintain an orbit in outer space around the earth and to deorbit the satellite on a desired trajectory corresponding to an earth based target upon a command, and a projectile object operably connected to the satellite. The projectile object includes a dense mass and a heat shield operably surrounding the mass such that at least a portion of the mass survives reentry into the earth's atmosphere and strikes the earth based target delivering its kinetic energy.

A method and system for deploying a spacecraft into a target orbit includes the use of controllable aerodynamic surfaces that can be deployed to facilitate a change in the inclination angle of the trajectory of the spacecraft. In a typical embodiment, the spacecraft includes an orbit transfer vehicle containing the aerodynamic structure, and a satellite that is to be placed into the target orbit. The spacecraft is launched to a higher-energy orbit than the target orbit, and the energy released by traveling to the target orbit is used to change the inclination angle. After entering a transfer orbit that includes a passage through the upper limits of the earth's atmosphere, the orbit transfer vehicle deploys the aerodynamic structure, and controls the aerodynamic surfaces of the structure to induce lift forces that alter its inclination angle each time the vehicle enters the atmosphere.

Systems and methods for concentrating solar energy in the high earth atmosphere and transmitting the concentrated solar energy to the earth's surface. A system includes a light weight solar concentrator, supported by a light weight, rigid, buoyant, structure (36). The buoyant structure is suspended high in the earth's atmosphere above clouds and weather. Steerable mirrors, and / or a steerable structure, enable the concentrator to track the sun. In one embodiment, a buoyant light pipe (20) enables the transmission of concentrated solar energy from the high altitude concentrator to the earth's surface for further use. The system provides concentrated solar energy for use at any location on the earth, such use including generation of electricity via thermal or photovoltaic means and, direct and indirect process heat. The uses of process heat include desalination and hydrogen or methanol or other fuel production. A high solar concentration ratio enables high temperature, and hence high efficiency heat engine operation. With the provision of a thermal storage unit a system can provide utility scale continuous electricity generation and process heat at any location on the planet.

The present invention is realized by apparatus and methods for harvesting, storing, and generating energy by permanently placing a large rigid buoyant platform high in the earth's atmosphere, above clouds, moisture, dust, and wind. Long, strong and light tethers can connect the buoyant structure to the ground which can hold it in position against wind forces. Weights suspended from the buoyant platform with cables are raised and lowered by electric winches to store and release gravitational potential energy. High voltage transmission lines electrically connect the platform to the earth's surface. Electrical energy from the high voltage transmission lines or from photovoltaic arrays on the platform can be stored as gravitational potential energy and subsequently released as electricity from generators driven from the stored gravitational potential energy and used on the platform or transmitted via the high voltage transmission lines.

An aircraft fire prevention system provides oxygen depleted (hypoxic) air for the fuel tank and / or cargo compartment protection; the system does not employ compressed air for the production of hypoxic air, which allows to save energy and fuel and to reduce negative impact on the earth atmosphere.

The invention discloses an aerospace flying saucer aircraft, and belongs to the cutting-edge technology in the field of aerospace. The aerospace flying saucer aircraft is provided with a direct dual-shaft counter-rotating turbo-shaft engine and a rocket engine; when the aerospace flying saucer aircraft flies in the atmosphere of the earth, the direct dual-shaft counter-rotating turbo-shaft engine is utilized to provide power; when the aerospace flying saucer aircraft flies in outer space, the rocket engine is utilized to provide power; and when the aerospace flying saucer aircraft flies in the atmosphere of the earth, the two engines can be started simultaneously, and the aerospace flying saucer aircraft does not need a runway, can vertically take off and land, and can freely fly at a high speed or a low speed through control. The aerospace flying saucer aircraft radically solves the technical problems of a disc-shaped aircraft and a circular aircraft; unique innovative concepts and scientific and reasonable designs are shown in the aspects of the integral structure, the power device, the control of flying balance, the control of flying direction and the like; and at present, the aerospace flying saucer aircraft developed and manufactured has important significance for development of the airspace strategy of China, airspace security and airspace battles.

The present invention is realized by apparatus and methods for placing a large rigid buoyant platform in the low stratosphere of earth's atmosphere at an altitude of about 20 km, above clouds, moisture, dust, and wind. The platform can serve several uses, either individually or in any combination. These uses include uninterrupted radio and light communications, radar and optical observation including very powerful radars and solar power electricity generation. Long, strong and light tethers connect the buoyant structure to the ground which hold it in position against wind forces. The electricity output from a photovoltaic array is used to power platform uses and can also be coupled to high voltage transmission lines which transmit power from the platform to the earth's surface during daylight hours. Power can also be transmitted up to the platform during darkness to power facilities mounted on the platform ensuring continuous operation.

An experiment system with six different re-entry experiment locations for testing high temperature re-entry materials, creating new thermal protection systems, proving innovative new concepts for spacecraft exterior surfaces and the incremental development of next generation aerospace materials. A commercial transportation system to and from orbit provides a 24-hour return cycle for the experiments on a surface actually re-entering the earth's atmosphere. Now using existing doors, hatches and other points on the reusable launch vehicle's exterior, the actual re-entry environment is experienced by test specimens with quick turn around for a wide variety of different re-entry temperatures ranges for broad testing and development purposes. The reusable launch vehicle launches, remains in orbit for 24 hours and returns to provide an actual test environment for the exterior experiment system.

A fastening device for use in a spacecraft comprises a shaft and a head, which is connected by a first solder to the shaft. The first solder comprises a material of which the melting point is lower than the temperature acting on the fastening device on re-entry of a spacecraft equipped with fastening device into the earth's atmosphere.

An Airborne Elevator Apparatus capable of deploying at the same time multiple service loads at different altitudes in the Earth's atmosphere by physically separating tether weight carrier function from the service load weight carrier function of a common aerostat. The tether weight carrier function is performed by at least one airborne canopy assembly (20) filled with lighter than air gas, which has enough lifting power to support its own weight and the weight of the attached airborne cables (30). The service load carrier function is performed by several airborne booster assemblies (51). Designed to glide on the apparatus's airborne cables (30), an airborne booster assembly (51) filled with lighter than air gas has enough lifting power to carry its own weight and the weight of a service load at altitudes below the uppermost canopy. For stability purposes, the apparatus is designed to rotate around its vertical axis.

An aircraft fire prevention system provides oxygen depleted (hypoxic) air for the fuel tank and / or cargo compartment protection; the system does not employ compressed air for the production of hypoxic air, which allows to save energy and fuel and to reduce negative impact on the earth atmosphere.

The sun imparts 174 petawatt per second on the earth, and a large portion of this energy is absorbed by the earth's atmosphere in the form of translational energy for the gaseous molecules, i.e. continuous random motion in the average speed range of 500 meters per second on earth's surface. This invention utilizes a partition with large number of through-holes which all have the characteristic of providing greater cross section for gas molecules to transit from one side to the other than the reverse, thus creating a higher statistical probability for the molecules to move from one side of the partition to the other side. By stacking a number of such partitions to emphasize the direction of movement probability of the gas molecules within a container having two open ends, the number of gas molecules at the end of the stack will be more numerous than at the head, thus a pressure differential is established, and this pressure difference is used to push against the stacks of the partition to provide thrust on the container or to drive a turbine to generate electricity or to perform works.

A method for protecting communications between an aircraft and a spacecraft in outer space including flying the aircraft in the earth's atmosphere at an altitude above 40,000 feet from the earth, and preferably above 50,000 feet, and transmitting a signal from the aircraft to the spacecraft having a frequency within a range of 50-70 GHz. The method includes selecting the frequency of the signal based on the altitude of the aircraft and the elevation angle between the spacecraft the aircraft.

A method for neutralizing or reducing the carbon footprint from carbon dioxide emissions due to human activities related to the combustion or use of carbon containing fuels. This method includes an initial step of capturing carbon dioxide and then chemically recycling it to form and provide a permanent inexhaustible supply of carbon containing fuels or products, which subsequently can be combusted or used without increasing the carbon dioxide content of the atmosphere. Thus, the current lifestyles that rely extensively on conventional carbon containing fuels and products can continue indefinitely without harming the environment to preserve and even improve the earth's atmosphere for the benefit of future generations.

The invention discloses a long-acting vacuum satellite, and particularly relates to a flight device which uses a vacuum chamber as a floating device and can float in atmosphere for a long time. A vacuum airship manufacturing theory is not a novel theory, but a vacuum airship does not exist in the world so far, because the vacuum chamber which can bear atmospheric pressure cannot be manufactured on the ground through current materials and current technologies. According to the vacuum satellite disclosed by the invention, the characteristic that the higher the altitude of the earth atmosphere is, the lower the air pressure is is adopted, so that the vacuum chamber can be lifted to a high altitude and then is vacuumized. The characteristic that the atmospheric pressure in the high altitude is low so that the air pressure difference is insufficient to damage the vacuum chamber is adopted, therefore, the aircraft can float in the atmosphere for a long term, and some work of a man-made satellite is replaced.

Super strong, super long tensile structures, connected to the anchor(s) on the Moon, ‘suspend’ in the Earth's atmosphere assemblies of wind energy catching devices (like turbines) positioned about 10-20 kilometers above the Earth's surface. The wind is actually an airflow generated by the Earth's rotation. The caught energy is converted to electricity and transmitted to Earth. A flat keel, attached to each assembly of turbines, stabilizes the assembly in the direction of the wind. The entire apparatus is stationary relative to the Moon and rotates around the Earth together with the Moon.

An active vortex control system (AVOCS) includes a set of primary injectors that inject gas into a cavity to generate a vortex in front of and possibly around components inside the cavity. The vortex interferes with an external flow field in an opening to the cavity to protect the components from the external environment. Sets of secondary injectors may inject gas at a reduced mass flow into the cavity to compensate for energy losses to maintain the coherence of the vortex. The AVOCS is well suited for use in windowless endo- and exo-atmospheric interceptors to protect the electro-optical imagers and optical components from Earth atmosphere.

An Airborne Elevator Apparatus capable of deploying at the same time multiple service loads at different altitudes in the Earth's atmosphere by physically separating tether weight carrier function from the service load weight carrier function of a common aerostat. The tether weight carrier function is performed by at least one airborne canopy assembly (20) filled with lighter than air gas, which has enough lifting power to support its own weight and the weight of the attached airborne cables (30). The service load carrier function is performed by several airborne booster assemblies (51). Designed to glide on the apparatus's airborne cables (30), an airborne booster assembly (51) filled with lighter than air gas has enough lifting power to carry its own weight and the weight of a service load at altitudes below the uppermost canopy. For stability purposes, the apparatus is designed to rotate around its vertical axis.

The invention discloses a method and a device for removing space debris. The method is to apply electromagnetic force to the space debris running in the original orbit; the size and / or direction of the speed of the space debris change under the action of the electromagnetic force; ; The perigee height of the space debris at least in the new orbit is lower than the perigee height of the space debris in the original orbit; the space debris in the new orbit will eventually fall into the earth's atmosphere under the action of atmospheric drag. The device includes a satellite carrying platform; the satellite carrying platform is provided with an electric field device or a magnetic field device or a combination of the electric field device and the magnetic field device for removing space debris. The present invention does not require high precision for space debris position detection, can effectively remove tiny space debris, can fully utilize solar energy to generate electricity, saves energy, and has the beneficial effects of simple structure, low manufacturing cost and better pulse effect.

A spacecraft 10 includes wings 11 or an airframe 12 which generates lift in an atmosphere 2, a thruster 14 which accelerates or decelerates rotating speed in an orbit, an attitude controller 16 which controls an attitude of the airframe 12, and an orbital plane controller 18 which controls the orbital plane change. The orbital plane controller causes the spacecraft 10 to enter the earth's atmosphere 2 within a pre-change orbital plane Fb (A→B→C), changes the orbital plane by using the lift of the wings 11 or airframe 12 in the earth's atmosphere 2 (C→D→E), and then lifts the spacecraft 10 up to the post-change orbital altitude (E→F).