Seeing as solar panels have become more compact, reliable and sturdy; could we potentially build a collapsible solar-sail to "tow" things out of our solar system? I've seen a lot of questions tackling the feasibility of solar sails and their inability to easily "gimbal" effectively in space. In addition to this, a solar sail is hard to slow down. But I've never really seen an example of the solar sail "towing" a payload, are they too weak to accomplish this?

I guess my question is, for current solar-sail technology would it be viable to "tow" a probe outside of our solar system, then release it to get better control when we reach another system? If this is viable, what would be the maximum payload that a currently designed sail would be able to "tow" and are there any missions planned to launch a solar sail payload in progress now?

Edit:

A McKelvy has mentioned the solar sail mission "LightSail 2" as described in the following link: http://www.planetary.org/blogs/jason-davis/2016/20160229-meet-lightsail-2.html

Does anyone have any calculations done by that team for the maximum feasible payload on this mission for a 32 meter sail? That would be a good tid-bit for this question :).

• Solar sails and solar panels (for electrical power) have nothing in common. Jun 23, 2018 at 5:37

EDIT : I have added some more detail to my answer in response to the OP's comment.

Yes, it is theoretically possible to use a solar sail to place a spacecraft on an escape trajectory from the solar system. The key to achieving this is to have attitude control sufficient to place the sail at an oblique angle to the sun nadir direction. This would allow some pro-grade or retrograde force to be applied with a necessary force component in the radial-out direction. Doing this at around the same position over subsequent orbits would allow for a slow growth in the orbit size. It would require changing the attitude of the sail such that its surface was perpendicular to the radial direction during the "non-thrust" time spans such that the cosine factor goes to zero and solar pressure becomes minimal. The most optimal process for this will shift as the orbit becomes more eccentric, but it is entirely feasible as a source of useful delta-V on orbit.

$F_{net} = 2A_{sail}\frac{I_{f}}{c}cos^2(\alpha)$
Where $I_{f}$ is the incident irradiance, c is the speed of light in a vacuum, A is the area of the sail, and alpha is the angle the sail normal makes with the sun radial. An object orbiting around Earth is at approximately 1 AU from the sun, and therefore experiences a solar irradiance of 1.361 kW/m^2. For ease, I'm assuming the sail is square on to the sun, meaning maximum pressure and an alpha of 0 degrees; this takes the cosine factor to 1. Given these assumptions, the Force exerted by the sun on a 32 square meter sail is about 0.29 mN. This is an extremely small force, equivalent to 1/15000 of a pound. The benefit is it can be maintained for long periods of time, especially once the orbit is highly elliptical, and the craft doesn't need to carry large amounts of fuel. It is safe to say that the maximum useful payload would be on the order of just a few kilograms, but you can always put a heavier payload with reduced performance given enough patience. The force is directly proportional to the Area, so doubling the area would double the payload capacity.