The solar cells produce electrical power (current) from incident sunlight. However, individual solar cells generate very little power. So, in order to generate more power, a group of cells that are present in an array form can be used. Solar arrays are primarily used in satellites in order to provide power to other subsystems.
There are two types of solar arrays that are used in satellites. Those are cylindrical solar arrays and rectangular solar arrays or solar sail. Cylindrical solar arrays are used in spinning satellites. Only part of the cylindrical array will be covered under the sunshine at any given time. Due to this, electric power gets generated from the partial solar array. This is the drawback of this type. The drawback of cylindrical solar arrays is overcome with Solar sail. This one produces more power because all solar cells of solar sail are exposed to sunlight.
In space at Low Earth Orbit, the sunlight is not filtered by the atmosphere. The efficiency of a solar panel depends of the wavelength of the photons that it can absorb. Therefore, in a space context with a larger wavelength of photons available than at Earth, the technology used for the solar cells has to be able to absorb the maximum amount of photons. More, since the area available of the solar panel is strongly limited on the CubeSat (each side size 100 cm², and has to integrate solar cells but also sensors and wires). The triple junction technology solar cells have a layer well adapt to a large wavelength area with an absorption wavelength from 300 nm to 1700 nm. This option but also other types of technology have been study in the State of the Art document.
Solar panels on spacecraft supply power for two main uses:
- Power to run the sensors, active heating, cooling and telemetry.
- Power for electrically powered spacecraft propulsion, sometimes called electric propulsion or solar-electric propulsion.
For both uses, a key figure of merit of the solar panels is the specific power (watts generated divided by solar array mass), which indicates on a relative basis how much power one array will generate for a given launch mass relative to another. Another key metric is stowed packing efficiency (deployed watts produced divided by stowed volume), which indicates how easily the array will fit into a launch vehicle. Yet another key metric is cost (dollars per watt)
Roll-Out Solar Array (ROSA)
The Roll-Out Solar Array (ROSA) and its larger version ISS Roll-Out Solar Array (iROSA) are lightweight, flexible power sources designed by NASA to be deployed and used in space. This new type of solar array provides much more energy than traditional solar arrays at much less mass. Traditional solar panels used to power satellites are bulky, with heavy panels folded together using mechanical hinges. Given a space-bound payload is limited in its mass and volume by necessity, ROSA is 20 percent lighter (with a mass of 325 kg (717 lb)) and one-fourth the volume of rigid panel arrays with the same performance.
ROSA is a flexible and rollable solar array that operates the same way a measuring tape unwinds on its spool. The new solar array design rolls up to form a compact cylinder for launch with significantly less mass and volume, potentially offering substantial cost savings as well as an increase in power for satellites. ROSA has a center wing made of a flexible material that supports the strings of photovoltaic cells that produce electricity.
Both the sides of the wing have a narrow arm that extends through the length of the wing to provide support to the array, called a high strain composite boom. The booms look like split tubes made of a stiff composite material, flattened and rolled up lengthwise. The array does not need any motor to unfurl. This is achieved using the potential energy stored in the booms that is released as each boom transitions from a coil shape to a straight support arm. The solar wings are then deployed due to strain energy in rolled booms that are present at the two ends of the structure.
Deployable Space Systems ROSA Solar Array (Roll-Out Solar Array)
DSS’s patented and award-winning ROSA Solar Array (Roll-Out Solar Array) is a simple highly modular elastically deployable tensioned blanket technology that elastically and immediately deploys in a known linear direction with high margin under its own strain energy. No complicated or expensive motors or controllers are required for deployment. Innovative stiff and strong tubular boom structures provide ‘integrated mechanism/deployment kinematic’ features with no complex mechanisms.
The innovative deployable structure maintains stiffness during the entire deployment sequence. An Integrated Modular Blanket Assembly (IMBA) with common mass-produced photovoltaic modules / SPM’s provides a highly manufacturable assembly that accommodates all types and sizes of photovoltaics and concentrator technologies.
The ROSA technology eliminates many known problems associated with competing flexible blanket solar arrays. ROSA provides lighter weight, more compact stowage, more modularity, higher reliability, better scalability, low parts count, higher performance, and significantly lower cost than currently available solar arrays.
The ROSA technology is being implemented on the following flight programs:
- Maxar / NASA PPE Gateway (two 33kW BOL size wings)
- Boeing / NASA International Space Station (six 25kW BOL size wings)
- APL/NASA DART (6kW BOL size array)
- Maxar Ovzon 3 (8kW size array)
- Maxar LS1300 GEO Qual (30kW BOL size array)
- Maxar Legion-class GEO product line (6-to-12kW BOL size arrays)
- Boeing Proprietary (1kW BOL size array)
- Thales Space Inspire (20kW BOL size array)
- U.S. Air Force AFRL Flight Demonstration (2kW size array)
- New-space constellation programs (4-to-6kW BOL size arrays)
- Dynetics / Maxar / NASA Human Landing System (HLS) (6kW BOL deployable/retractable arrays)