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Space probes headed for the far reaches of our Solar System rely on radioisotope thermoelectric generators for power (Cassini–Huygens, Voyager 1, Voyager 2).

Presumably this is because solar power isn't feasible at large distances from the Sun. With the current technology available, what is considered the "safe zone" that solar arrays can be used as a reliable source to power a space craft?

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Presumably this is because solar power isn't feasible at large distances from the Sun.

There is a possibility to use solar energy as long as the arrays receive a quantity of energy greater than the working level of a photo voltaic cell. This includes the full solar system. The solar cell usability under low intensity is constantly improving.

But, right... being able to collect only very little energy is not sufficient to power any space probe for the time being.


With the current technology available, what is considered the "safe zone" that solar arrays can be used as a reliable source to power a space craft?

The energy required for a given mission can be obtained by adjusting the size of the solar arrays, but this adjustment has an upper limit. The other way it to use more efficient cells:

From Wikipedia:

enter image description here
Larger image.

"Cell efficiencies are measured under standard test conditions (STC) unless stated otherwise. STC specifies a temperature of 25 °C and an irradiance of 1000 W/m² with an air mass 1.5 (AM1.5) spectrum. [...] This represents solar noon near the spring and autumn equinoxes in the continental United States with surface of the cell aimed directly at the sun."

Cells work outside of STC very well, as soon as working conditions are taken into account in the design:

"Inner planetary missions and missions to study the sun within a few solar radii require solar arrays capable of withstanding temperatures above 450 °C and functioning at high solar intensities (HIHT). Outer planetary missions require solar arrays that can function at low solar intensities and low temperatures (LILT). In addition to the near-sun missions, missions to Jupiter and its moons also require solar arrays that can withstand high-radiation levels." (Source: Space Solar Cells and Arrays - Bailey, Raffaelle)

There are also different possibilities to concentrate light on cells to prevent low intensity efficiency degradation, and to obtain more energy from the same cell area:

Practical usuability of solar arrays in space

Overall, this Nasa's study (2007) assume solar arrays are practically usable as far as the Jupiter orbit (5.2 AU, Ultraflex products), and that Saturn (10 AU) mission will be achievable in near-term.

enter image description here
(Juno mission for Jupiter)

"Near term Ultraflex arrays and state-of-art multi junction cells can provide capability to perform low power (200-300 W) missions out to 10 AU."

However several factors are to be taken into consideration.


Size of the solar arrays

The quantity of energy received at some distance from the Sun is driven by an inverse square law. See this question on Physics.SE for more details:

"PV works great near the Earth, at 1 AU from the Sun, where we receive about 1400 Watts per square meter [...] At Saturn, nearly 10AU from the Sun, there's 1/100th power. Fine, if a spacecraft carries solar arrays 100 times bigger than would be used near Earth." -- For Juno mission: "Its 45 m² planar array produces 9.6 kW BOL at 1 AU and 414 W at 5.5 AU"

BOL / begin of life: Cells efficiency decreases with time, as they are exposed to radiations (protons, UV, IR, etc).

The first problem arises in term of arrays size to deliver the electrical energy you need, and whether the spacecraft can accommodate such size or not.

Eclipse

The spacecraft in orbit around a celestial body will not receive Sun light when behind this body. Some energy storage mean is required.

enter image description here
(Source: Britannica)

Planetary albedo

A celestial body may reflect Sun light to the probe arrays, increasing energy production.

Robustness of the arrays

Arrays may be destroyed during launch, or in orbit by debris. As they become larger their robustness is difficult to maintain without adding mass to the system.

Cost of the launch

The larger the energy required, or the further the spacecraft from the Sun, the more expensive the arrays due to their size. The cost of the launch is also impacted due to the corresponding variation in mass.

At some point other sources of energy will become cheaper to build and to launch.

Maximum current output

If the mission has a need for more current than the arrays are able to produce, and it's not suitable to increase the arrays size then energy must be stored at the rate the array can deliver it, then consumed at the higher rate required until the battery is empty, and then wait for the battery to be charged again.

Working discontinuously may be acceptable or not. In addition battery effectiveness decreases over time, and dust or propellant may dim the solar radiations. Long missions may not be able to accommodate these issues.

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There are at least two problems with solar photovoltaic cells (not considering concentrators) in the outer solar system: the low power of the sun, and the low temperature of the cells.

For the Cassini mission to Saturn (9–10 AU from the Sun), NASA investigated solar as an alternative. They calculated the surface area that would be required, and concluded that the mass of the solar arrays required would result in a spacecraft with a mass exceeding anything that could be launched with existing technology, and would severely inhibit manoeuvrability. They concluded that it would have been possible, but that the scientific cost would be too high:

From the Cassini Environmental Impact Statement, chapter 2, page 2-53 onward. For one alternative configuration,

The addition of this size array, in conjunction with the other modifications required to implement solar power, increased the spacecraft dry mass by 1,337 kg (2,948 lb). With the mass of the propellants, the Huygens Probe, and the launch adapter, the total spacecraft mass would increase to 7,228 kg (15,935 lb), far exceeding the launch capacity of the Titan IV (SRMU)/Centaur of 6,234 kg (13,743 lb) for a trajectory to Saturn (JPL 1994a).

or, for another one,

To further reduce the size of the arrays, the power available to the science instruments was reduced by 50 percent. Because of the large moment of inertia created 2 by the large solar panels (397 m²[4,269 ft²] and 585 kg [ 1,290 lb]) (JPL 1994a), the time required to turn and maneuver the spacecraft during its exploration of the Saturnian system would increase by a factor of between 4 and 18 compared with the compact RTG-powered spacecraft. The resulting impacts on the mission's science objectives would be serious and include increased times for image mosaics, inadequate turn rates for fields and particles instruments, reduced image resolution due to inadequate target motion compensation, loss of instrument observation time during turns for communicating with Earth, and insufficient turn rates to support radar observation of Titan's cloud-enshrouded surface.

More recently, two missions to Jupiter (4.9–5.5 AU from the Sun) use solar arrays: NASA's Juno is currently (2013) cruising to Jupiter, due to arrive August 2016. ESA's Juice is to launch in 2022. Both use solar photovoltaics, and are the furthest-away spacecraft to do so to date.

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  • $\begingroup$ There is one more unfortunate aspect to this story. Politics and funding. In mission design, you will chose RTGs in a lot of cases towards Jupiter and beyond. The advantages are overwhelming. However, funding does not always permit it. Juno is using solar arrays to save money. Forget about engineering. Besides, ESA missions do not allow RTGs. It is some insane political mess in Europe, so deep space stuff by ESA will always use something else. There is again no technical reasoning behind this decision in case of Juice. $\endgroup$ – s-m-e Jul 22 '13 at 23:38
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    $\begingroup$ @ernestopheles How is cost not an intricate aspect of mission design? And there are good reasons why ESA does not allow RTGs; Plutonium is not funny. Mars '86 is still rotting somewhere in the Andes along with its highly toxic Plutonium, and if the kind of accident that recently happened with the Proton rocket carrying Glonass happens when there's 5 kg Plutonium on-board, cleanup costs are immense and who knows how many people get cancer. The NASA EIS statements linked in the question I linked contain more details. $\endgroup$ – gerrit Jul 22 '13 at 23:43
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    $\begingroup$ Of course, one may discuss the pros and cons, and RTGs certainly have engineering advantages. But I do not agree that there is no technical reasoning. Safety is a technical issue. The choice in the balance between cost, safety, scientific advantages etc., that's ultimately political, but engineering aspects such as presented in NASAs EISes are relevant. $\endgroup$ – gerrit Jul 22 '13 at 23:49
  • $\begingroup$ From an ethical point I agree. From a technical point, I am one of those 'lobbying' to allow RTGs in ESA missions whenever I can. It is a bit weird, I know. Safety is an issue, too, but it is more an issue of the launcher and people doing their job right. It is by far the best available technology, so why not use it, take a risk and handle it professionally? (I think we should take this discussion off this place ...) $\endgroup$ – s-m-e Jul 22 '13 at 23:54
  • $\begingroup$ I'd love to see a well-documented answer to this relevant question! $\endgroup$ – gerrit Jul 23 '13 at 9:06

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