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FEDERAL SPACE AGENCY Lavochkin Association. CREATION OF HIGH-EFFECTIVE SOLAR POWER SYSTEMS ON THE BASE OF RIGIDIZABLE STRUCTURES – STEP FORWARD IN THE SPACE SOLAR ENERGY DEVELOPMENT. 10-12 March, 200 8 Ljubljana, Slovenia. Constantly growing energy needs of the mankind. - PowerPoint PPT Presentation
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1Copyright © Lavochkin Association, March 2008
10-12 March, 2008Ljubljana, Slovenia
FEDERAL SPACE AGENCYFEDERAL SPACE AGENCY
Lavochkin AssociationLavochkin Association
CREATION OF HIGH-EFFECTIVE SOLAR POWER SYSTEMS ON
THE BASE OF RIGIDIZABLE STRUCTURES – STEP FORWARD IN
THE SPACE SOLAR ENERGY DEVELOPMENT
2Copyright © Lavochkin Association, March 2008
Depletion in the nearest future of tradition power sources such as oil, gas and coal
Constantly growing energy needs of the mankind Problem of new
effective and available ways of power generation
3Copyright © Lavochkin Association, March 2008
SOLAR POWER SYSTEMS (SPS)
SPACE SPS GROUND SPS
SPACE SOLAR POWER STATIONS
SOLAR POWER STATIONS
POWER SYSTEMS OF SPACECRAFT
INDUSTRIAL SPACE POWER SYSTEMS
SOLAR POWER CONCENTRATOR
COMBINED SPS
4Copyright © Lavochkin Association, March 2008
BACKGROUNDBACKGROUND
Scheme of deployable space structure developed in Japan“Ultra-lightweight structures
technology for space solar power” Keith Belvin NASA Langley
Sept. 10-12, 2002
Scheme of deployable structure with elliptical solar power concentrators (on the top) and space-based solar power generators for geo stationary
orbits [NASA Suntower]
SPACE POWER STATIONS
5Copyright © Lavochkin Association, March 2008
BACKGROUNDBACKGROUND
SPACECRAFT POWER SYSTEMS
Conceptual drawing of Champollion spacecraft intended for Deep space mission using electric propulsion (SEP mission) with deployable and rigidizable solar array
6Copyright © Lavochkin Association, March 2008
Relatively small sizes of the modern spacecraft complicate delivery into space of large-sized constructions, first of all solar batteries, antennas, telescopes and transport systems such as “solar sail” with sizes of tens and hundreds of square meters.
PROBLEM:
On-ground manufacturing of thin-walled deployable or inflatable work pieces, that can be compactly folded, delivered into the orbit and transformed into a fixed construction
POSSIBLE SOLUTION:
7Copyright © Lavochkin Association, March 2008
Main effectiveness criteria of solar power systems
low cost of power supply to the consumer
simplicity and reliability of operation
safety of power delivery to the consumer
8Copyright © Lavochkin Association, March 2008
New light and high-effective solar arrays require application of flexible panels and new solar cell technologies, such as thin film cells.
The main advantages of thin film cells:
high power/mass ratio
high tolerance to small damages such as micro-meteorite impacts
high tolerance to the enhanced radiation
substantially lower cost
9Copyright © Lavochkin Association, March 2008
Comparative technical and economical parameters of the present and prospective solar arrays providing generation of 1 kW of electrical power
Type of photovoltaic cell Single-crystal
silicon Single-crystal
gallium arsenideAmorphous silicon
on the thin-film base
Array area, m2 6.06 2.74 10.00
Array mass, kg 13.58 7.59 5.1
Array specific mass, kg/m2 2.24 2.77 0.51
Specific power of photovoltaic cells, kW/m2
0.165 0.365 0.09
Specific power of 1 kg of solar array, kW/kg
0.074 0.132 0.28
Cost of 1 kW of electrical power in the near-Earth orbit, k$
200 525 56.5
10Copyright © Lavochkin Association, March 2008
TECHNICAL REQUIREMENTS TO THE SPACECRAFT SOLAR POWER SYSTEMS
The inflatable and rigidizable structure (IRIS) designed as a load-carrying structure of the solar power system should be compatible with thermal and mechanical environment specified for space technique.
Inflatable and rigidizable structures should be designed taking into account typical satellite in-orbit environment: radiation, ultraviolet radiation, atomic oxygen debris and meteorites environment
Orbit LEO GEO
Altitude, km 800 35794
Orientation polar equatorial
Revolution period
100 min 24 h
Eclipse duration
34 min 1.2 h
Temperature limitations (C)
+100/ -130 +80/ -170
11Copyright © Lavochkin Association, March 2008
MAIN TASKS OF THE ISTC PROJECTS
12Copyright © Lavochkin Association, March 2008
ISTC PARTNER PROJECT # ISTC PARTNER PROJECT # 28352835
MAIN TASKS OF THE PROJECT #2835
Selection of materials and technologies complying the requirements to the developed structure of the experimental solar array.
Determination and experimental confirmation of the required parameters and characteristics.
Development and industrial utilization of the rigidizable structure manufacturing technology.
Qualification tests of the developed experimental solar array.
Determination of the program of the experimental panel in-orbit qualification
13Copyright © Lavochkin Association, March 2008
ISTC PARTNER PROJECT # ISTC PARTNER PROJECT # 28352835
RESULTS OF STUDIES CARRIED OUT WITHIN THE PROJECT #2835
SELECTION OF TECHNOLOGY AND MATERIALS
Methods of polymeric materials rigidization in space
Chemical methods rigidization as a result of chemical reactions under influence of heating (solar IR-
radiation); rigidization as a result of chemical reactions under influence of solar UV-radiation; rigidization under influence of vapours of chemical substances evaporating in
space vacuum and diffusing through the wall impregnated with a polymeric binding;
irreversible change of the wall's rigidity as a result of polymeric compositions foaming in vacuum, which is accompanied with chemical reactions
Physical methods reversible change of the wall's rigidity as a result of physical transformations of
polymer under consecutive heating/cooling; irreversible change of the wall's rigidity as a result of physical transformations
during removal of low-molecular components from material composition in space vacuum.
14Copyright © Lavochkin Association, March 2008
ISTC PARTNER PROJECT # ISTC PARTNER PROJECT # 28352835
SELECTION OF TECHNOLOGY AND MATERIALS
RESULTS OF STUDIES CARRIED OUT WITHIN THE PROJECT #2835
1. In the result of studies compositions of polymer composite materials were developed which can be harden due to physical transformations in polymeric matrix caused by removal of temporary plasticizer in vacuum.
2. Directive technological procedures for manufacturing of fragments of the IRIS panel load-bearing framework according to the basic and reserve variants of rigidization were developed .
3. Systematic studies of materials properties before and after hardening were carried out.
4. Carried out studies showed high reliability of developed methods of structure rigidization and confirmed the possibility of reliable deployment of hardenable structural elements without significant distortion of their shape.
5. Method of industrial producing of the composite material prepreg made of the aramid fabric and polymeric binder on the basis of the polyvinyl alcohol was developed.
6. Technology of manufacturing of the thin-wall tube from the prepreg by high-frequency and thermal pulse welding was developed, and a methodology of assembly and testing of the tubular frame was developed as well.
15Copyright © Lavochkin Association, March 2008
ISTC PARTNER PROJECT # ISTC PARTNER PROJECT # 28352835
At the final phase of the project #2835 models of the solar array experimental panels were developed, manufactured and tested
SELECTION OF TECHNOLOGY AND MATERIALS
RESULTS OF STUDIES CARRIED OUT WITHIN THE PROJECT #2835
16Copyright © Lavochkin Association, March 2008
ISTC PROJECT # ISTC PROJECT # 28328366
MAIN TASKS OF THE FLIGHT QUALIFICATION OF THE EXPERIMENTAL RIGIDIZABLE SOLAR ARRAY
to work out the technique of deployment of the rigidizable structures;
to work out of the technique of structures rigidization in conditions of the orbital flight;
to acquire the IRIS images and their transmission to the Earth;
to acquire characteristics of the rigidized structures and their transmission to the Earth
17Copyright © Lavochkin Association, March 2008
ISTC PROJECT # ISTC PROJECT # 28328366
Upper Stage “FREGAT”
IRIS 2
Adapter
IRIS 1
Upper Stage “FREGAT”
IRIS 2
Adapter
IRIS 1
MAIN TASKS OF THE FLIGHT QUALIFICATION OF THE EXPERIMENTAL RIGIDIZABLE SOLAR ARRAY
The IRIS Demonstrator is intended for in-orbit qualification experiment with the inflatable rigidizable structures.
The IRIS Demonstrator is arranged on the Fregat upper stage adapter and it is compatible with Fregat on-board housekeeping equipment
18Copyright © Lavochkin Association, March 2008
ISTC PROJECT # ISTC PROJECT # 28328366
IRIS DEMONSTRATOR MISSION PROFILE
Flight duration of the Demonstrator with inflatable rigidizable structures should be long enough for deployment of two IRIS panels, fulfillment of all necessary measurements and data transmission to the Earth.
Measurements transmitted to the Earth, necessary for the mission fulfillment, should be received by two ground stations.
19Copyright © Lavochkin Association, March 2008
ISTC PROJECT # ISTC PROJECT # 28328366
SYSTEM OF DYNAMIC PARAMETERS MEASUREMENT
The flight Demonstrator and its measurements system have to correspond to the following success criteria:
reception on the Earth of the flight data demonstrating safe
deployment of the two IRIS panels;
reception on the Earth of the flight data demonstrating the
successful rigidization of the inflated rigidizable elements.
MAIN TASKS OF THE FLIGHT QUALIFICATION OF THE EXPERIMENTAL RIGIDIZABLE SOLAR ARRAY
20Copyright © Lavochkin Association, March 2008
ISTC PROJECT # ISTC PROJECT # 28328366
MAIN TASKS OF THE FLIGHT QUALIFICATION OF THE EXPERIMENTAL RIGIDIZABLE SOLAR ARRAY
21Copyright © Lavochkin Association, March 2008
ISTC PROJECT # ISTC PROJECT # 28328366
CONCLUSION
Development of solar power system is stipulated by application of new prospective technologies and materials.
The qualitative level of the modern and future solar power systems is defined by the level of technical and economical perfection of the developed space technique.
Application of new prospective technologies of thin-film photoelectrical converters and rigidizable structures allows to achieve significant increasing of effectiveness of modern solar power systems.
22Copyright © Lavochkin Association, March 2008
Thank you for your kind attention
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