Balloon-space power supply system

FIELD: transport.

SUBSTANCE: invention relates to systems intended for power supply of ground objects from space. Power supply system comprises, at least, one space solar power station 1, ground control station 2 with accumulation system 3, and intermediate power reception station composed of controlled tethered balloon. Solar photo converters 5 and lasers 6 are arranged on the surface of balloon 4 for guidance to space power station 1 while on side facing the Earth IR converters 7 are arranged. Balloon 4 is preferably shaped to disc retained above clouds by cable 8 connecting it with ground system 3. Motors 9 connected with service module 10 are mounted on side surface of balloon 4. Cable 8 is connected with the system of balloon gas bags 11. Space solar power station 1 represents the Earth satellite composed of self-contained photo converting modules, focusing mirror system, super condensers, and remote power transmission system. Besides, it comprises instrumentation-propulsion module with control systems and data exchange system.

EFFECT: higher power production efficiency.

4 cl, 3 dwg

 

The invention relates to power supply systems, namely terrestrial consumers from space.

Known space solar power to provide electricity terrestrial consumers, including solar power plant and a system for remote transmission of energy on Earth in the form of microwave or laser radiation (application for a patent RU №94032672/11 from 08.09.1994, B64G 9/00; patent RU No. 2094334 from 18.04.1994, B64G 1/44, Chetland, "Space technology", M., ed. World, 1986, str-237). The disadvantages of these plants are:

1. Large design, which cannot be transported to orbit all at once, requiring a large number of start-up of the launch complex and expensive Assembly in space;

2. Multi-step conversion of solar energy equipment with large size parameters and the complex and heavy cable network, increasing the risk of failure of individual nodes and, in extreme cases, the equipment as a whole;

3. When using a laser beam as a method of energy transfer, the absence of reception of energies above the cloud zone will result in the loss of part of the radiation in the troposphere and, therefore, decrease the efficiency of the process.

4. When using the microwave beam as a method of energy transfer, with the considerable divergence, its area on the Earth will reach a large size, which requires the creation of the same size of the receiving rectenna that leads to higher power and lower efficiency of the receiving elements rectenna, which leads to lowering the efficiency of the power plant, increasing the area occupied by the ground point of the energy, as well as to the deterioration of ecological safety of the radiation field at the location of rectina;

Also known solar power, placed on a tethered aircraft lighter than air, on surfaces of which are covered with flexible solar cells, and the devices are located above the cloud layer (patents for inventions: EN No. 2377440 dated 18.06.2008, F03G 6/00; RU №2389900 from 16.03.2009, F03G 6/00). The disadvantages of these plants are:

1. The spherical shape of the balloon, leading to inefficient use of solar cells and, consequently, reduce the efficiency of the process to generate electricity;

2. Using film solar cells, having by their physical nature of low efficiency;

3. Daily operations of winding on the drum and unwinding with his rope-cable, which significantly increases the risk of accidents and wear and tear of the unit.

4. Use to generate electricity only solar radiation.

The closest is taken for about Otep, the power supply system of terrestrial consumers from space, which includes at least one space solar power and the ground station receiving energy transmitted from space solar power (inventor's certificate SU # 946372 from 31.10.1980, H01J 17/00, B64G 1/10). The disadvantages of this system are:

1. The presence of the cosmic power and a separate space relay or flotilla separate cosmic power plants with passive repeaters that redirects energy, greatly complicates and increases the costs of implementation of this power;

2. When the transmission power using a microwave beam, which has a significant divergence directly to Earth, its surface area on the Earth will reach a large size, which, as mentioned above, requires the same size of the receiving rectenna that, in turn, leads to higher power and lower efficiency of the receiving elements rectenna, and, accordingly, leads to a decrease in efficiency of the power plant, increasing the area occupied by the ground point of the energy, as well as to the deterioration of ecological safety of the radiation field at the location of rectina;

The technical solution of the present invention is directed to the achievement of the technical result consists in HC is the chances of improving the amount of energy in a smaller surface receiving the item, as well as to improve environmental performance in the area of the specified item.

Below, in the disclosure of the invention and the description of its implementation and use, including in cases of execution, shall be called and other types achieved technical result.

This technical result is achieved by the fact that, as known, is used as a prototype, the power supply system that includes at least one space solar power and the ground station receiving energy transmitted from a space solar power station, the proposed balloon-space energy system is supplied with the intermediate point of the energy representing the aircraft lighter than air as managed tethered balloon, with mounted on it service management module balloon. On the surface the specified device, facing away from the surface of the Earth are solar panels, for example three-stage nano-heterostructure the solar cells, and laser focused on space power. On the surface of the balloon facing the surface of the Earth, are infrared panels and above service module, with the specified balloon attached above the zone of clouds by means of a rope, cable, Saedinenie ground point of the energy. Tethered balloon made disc-shaped and forms the perimeter of the lateral surface evenly mounted motors (best of four), United with the service module. On the cable-the cable that goes from the service module, sequentially fixed obespechivaushyi balloon shell. Space solar power station is a satellite placed in orbit, consisting of Autonomous (independent) photoperiodic modules focusing the beam on the Ground, mirror systems, supercapacitors, remote power transmission, instrumentation and propulsion compartment with control systems, and systems for receiving control commands and outputting information about the state of operation of the satellite to the ground station.

The specified implementation of energy systems using intermediate receiving ground point as the aircraft lighter than air (tethered balloon), fixed at a height above cloud level, allows not only to take energy from space stations, but due to the location on its disc-shaped surface of the triple junction heterostructure and infrared panels in greater numbers than on the spherical surface, to increase production of electricity from solar radiation, and to use the e is ergiu thermal radiation of the Earth. Location above Ground level can reduce the area occupied ground adoptive point, in addition, clouds below the aircraft, do not close the panels located on its surface, and the development of their energy coming from the Sun, goes all day time, additionally, the cloud does not scatter the laser radiation from space solar power. The use of rope-cable allows you to avoid significant losses in energy transfer and destabilizing stability of the aircraft - and balloon-on the same, and obespechivanie cable-cable, directed and posting on additional balloon membranes. In addition, a uniform location on the perimeter of the balloon membrane having the form of a disk, electric motors allows you to maintain a static state intermediate receiving item (for example, when the wind) and to ensure its slope, seeking to normal against laser radiation with space solar power. The proposed system implementation can significantly reduce the area of its ground segment, significantly increasing the number of the received power (laser radiation from the space station, solar radiation and infrared radiation from the Earth).

The entity from whom retene illustrated by drawings, showing:

- figure 1 - balloon-space energy system;

- figure 2 - the balloon panels;

- figure 3 - ground segment system.

The proposed balloon-space energy system includes at least one space solar power system 1, the ground station receive power, including ground control station 2 power system and storage system 3, and an intermediate point of the intake of energy, representing an aircraft lighter than air as managed tethered balloon 4. On the surface of the balloon 4, facing away from the surface of the Earth are solar panels 5 and the laser 6 for guidance on space power plant 1, and on the side facing to the surface of the Earth, bred infrared solar cells 7. For the convenience of placing the panels 5 and 7 aircraft 4 is made in the form of a disc. When the device 4 is fixed above the zone of clouds through the cable-cable 8 connected to the cumulative ground system 3. On the side surface of the balloon 4 evenly along the circumference mounted electric motors 9, United with mounted in the bottom center of the balloon 4 service module 10, which houses all the control apparatus and apparatus for automotive and balloon, cables and antenna for accepting control signals from a ground point and issuance of state information systems of the balloon (not shown), the cable-the cable 8 extending from the service module 10, sequentially fixed obespechivaushyi balloon sheath 11. Space solar power plant 1 is a satellite placed in orbit, consisting of Autonomous (independent) photoperiodic modules focusing the beam on the Ground of the mirror system, supercapacitors, remote power transmission, instrumentation and propulsion compartment with control systems, and systems for receiving control commands and outputting information about the state of operation of the satellite to the ground station (not shown).

Balloon-space energy system works as follows.

After all diagnostics, pre-launch and guidance of the balloon 4 to receive laser radiation from the space stations 1, with a ground control station 2 is fed the signal to the main portion of space the plants 1 to start work in normal mode.

Next, the principle of operation is more convenient to split into two segments:

The space segment.

When space solar power plant 1 is located at the illuminated part of the orbit, the electric current generated by photoprobes what aalami, located in fotoizluchayuschih module charges the supercapacitor and, in parallel, is the power of the laser diode bars that are used to pump a fiber laser. Further along the optical fiber from each fotoizluchayuschih module radiation comes in a mirrored system, located on the head part of the solar cosmic power plant 1, which is summed up in a single laser beam, and thereafter, is transmitted to the panels 5, located on the upper surface of the balloon 4.

When space solar power plant 1 is located on the unlit side of the orbit, the electric current required to power the laser diode bars, produced from the supercapacitors.

Ground segment.

To maintain a stable connection with the satellite 1 uses a laser 6 for guidance on space power plant 1 and the electric motor 9 that supports the balloon 4 in a static position and ensuring the slope of the balloon 4 in the direction of the satellite 1.

In the lit time of day located in the upper part of the balloon 4, the panels 5 are processed solar energy and laser radiation coming from space stations 1. Infrared panels 7, located on the lower part of the balloon 4, process heat coming from the Earth's surface. Next, the entire electric current flows through the ROS-cable 8 to the drive system 3, located on the Ground.

In a dark time of day located in the upper part of the balloon 4, the panels 5 are processed laser radiation coming from the comic of the power plant 1. The panels 7, located on the lower part of the balloon 7, process heat coming from the Earth's surface. Equipment located in the service module 10 provides diagnostics, transmission of signals from the balloon to the ground control station and provides the electric motors 9.

This ensures-hybrid solar space power.

Thus, the proposed design of the balloon and space energy systems by introducing an intermediate point of the energy acceptance of the above-mentioned construction, will significantly reduce the area of the surface segment of the energy system, significantly increasing the number of the received power (laser radiation from the space station, solar radiation and infrared radiation from the Earth). In addition, this energy system can be used not only on Earth, but also by development of other planets.

1. Balloon-space energy system that includes at least one space solar power and the ground station receive power and, transmitted with a space solar power station, characterized in that the system is equipped with an intermediate point of the energy representing the aircraft lighter than air as managed tethered balloon with mounted on it service module, while on the surface the specified device, facing away from the surface of the Earth are solar panels and laser focused on space solar power, and on the surface facing the surface of the Earth, are infrared panels and above the utility management module of the balloon, with the specified balloon attached above the zone of clouds through the cable-cable connected to the ground point of the energy.

2. Balloon-space energy system according to claim 1, characterized in that the aircraft is lighter than air performed-shaped, and on the perimeter of the lateral surface evenly mounted motors, United with the service module.

3. Balloon-space energy system according to claim 1, characterized in that between the service module and the ground point of the energy on the cable-the cable that goes from the service module, sequentially fixed obespechivaushyi balloon shell.

4. The balloon cosmic energy the system according to claim 1, characterized in that the space solar power stations are placed in orbit, the satellite comprising independent of each other photoperiodic modules focusing the ray mirror systems, supercapacitors, remote power transmission, instrumentation and propulsion compartment with control systems, and systems for receiving control commands and outputting information about the state of operation of the satellite to the ground station.



 

Same patents:

FIELD: transport.

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EFFECT: higher reliability of manufacture.

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EFFECT: higher efficiency of overcoming sand runs.

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Kytoon // 2372248

FIELD: aircraft engineering.

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EFFECT: increased time of continuous operation at larger altitudes.

FIELD: transportation.

SUBSTANCE: balloon has an envelope filled with a gas lighter than air and/or with a hot air, a rigid carcass carrying the said envelope, a nacelle, slings to suspend the nacelle and anchor cables. The nacelle is tightly coupled with the envelope and features a funnel-like widening at its top and a central channel along its lengthwise axis to limit air intake into the envelope. The balloon envelope can be made from conducting material to make an electrode in a storage battery intended for utilisation of atmospheric electricity, or can be used as an antenna, or can house a particular antenna for communication purposes.

EFFECT: expanded potentialities.

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FIELD: navigation.

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EFFECT: enhanced reliability.

3 cl, 2 dwg

FIELD: means for support of navigation of air platforms used for forming wireless information transmission systems within line-of-sight range in preset geographic region.

SUBSTANCE: proposed method includes creation of lifting force of flying vehicle for keeping the platform at preset altitude and holding the flying vehicle and air platform in preset point of surface with the aid of flexible rod which is used as channel for feeding the supply energy for forming the thrust vector of flying vehicle lifting force. According to invention, gaseous medium is used as energy carrier for forming the supply energy. Working medium is charged under pressure to energy supply channel of flexible rod and at outlet of this channel energy of gaseous working medium is converted into energy creating the lifting force of flying vehicle. For creating the lifting force, energy of gaseous working medium in form of combustible or natural gas may be converted into electric power or reactive thrust at output of energy supply channel. According to first version, instrument bay of air platform is provided with at least one fuel element for conversion of combustible or natural gas energy into electrical energy and flexible rod is provided with hollow channel whose lower end is brought into communication with combustible or natural gas source; upper end of flexible rod is provided with at least one fuel element whose electrical output is connected with input of electric motor of tractor propeller. According to second version, flexible rod is provided with hollow channel whose lower end is brought into communication with combustible or natural gas source or compressed air source and upper end is connected with rotating engine of tractor propeller made in form of jet engine or in form of ramjet engine provided with ignition element for ignition of combustible or natural gas or in form of converter for conversion of compressed air pressure into rotary motion of tractor propeller.

EFFECT: enhanced reliability of navigation of air platforms due to enhanced lightning protection and climatic stability of power supply to tractor propeller engine and air platform instruments.

7 cl, 2 dwg

FIELD: aerostatics.

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EFFECT: increased service life of aerostat; enhanced stability of aerostat.

2 cl, 1 dwg

FIELD: aerostation.

SUBSTANCE: proposed captive balloon has envelope made from gas-tight material and captive cables. Captive balloon is additionally provided with aerodynamic stabilization unit made in form of feathering unit secured on rod passing through upper pole of balloon envelope by means of lines; feathering unit is provided with keel; feathering unit is made in form of three-dimensional streamlined body inflated by air flow; when it is filled with air, it has shape of aerodynamic wing in plane of longitudinal section. Three-dimensional body is formed by upper and lower gores stretched on framework; edges of these gores are fastened over their perimeter forming air intake slotted opening and inner cavity filled with air flow. In zone of intake hole, upper gore has sizes exceeding sizes of lower gore, so that when three-dimensional body is filled with air, upper gore overhangs above lower gore.

EFFECT: simplified construction of balloon stable to wind load.

3 cl, 4 dwg

FIELD: transportation power systems.

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EFFECT: enhanced efficiency and reliability of system in upper layers of troposphere.

2 cl, 2 dwg

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