High precision relative position sensing system for co-navigating spacecraft, Year 1

This effort builds on internally developed technology for precise positioning, and develops a combined transverse (TAS) and longitudinal (PLR) precision position sensor suite. Previously, two separate sensors longitudinal and transverse wih different wavelengths, were developed to the point where the basic concept was demonstrated to be feasible at the desired separation distances. This FY19 effort is focused on combining the existing systems into one operational wavelength and one optical path. This requires development of a new sensor/transmitter concept. Two different approaches will be evaluated: one where the PLR transitions to the current TAS wavelength (635 nm), and the other where the TAS transitions to the current PLR wavelength (1550 nm). The best approach will be selected based on performance testing and trade studies identified in the FY19 effort. The entire optical system will also need to be redesigned to accommodate beam combining and separation from the two subsystems.

NASA has a number of applications requiring precise relative positioning between two or more spacecraft or other objects. These include servicing, rendezvous, formation flying, assembly operations. debris removal, and sample acquisition. Most on-going and previously funded formation flying efforts have been in support of a particular mission concept, which has driven the requirements for the system. For example, the LISA mission requires picometer resolution measurements at 2.5 million kilometer distances. Other applications, such as Beach Ball Coronagraph, pursued technologies for cm-level range accuracy. Although some of these technologies are impressive, they are often not widely applicable to other mission concepts. A more generic technology applicable to the mission classes addressed above is needed. Any mission concept that requires two or more objects to be held in precise alignment at separations greater than a few meters would benefit from this technology. For example, optical telescopes with long focal lengths could be constructed using two separate spacecraft, where a focusing optic is carried on one spacecraft while the camera capturing the focused image could be carried on a second spacecraft. The two spacecraft must maintain precise alignment to ensure an unsmeared image on the camera. Current technologies require large, rigid structures such as masts and booms mounted on a single, large spacecraft to ensure proper alignment between the imaging optic and the camera. Two small co-navigating spacecraft can be designed, built and launched faster and at much lower cost than a single large spacecraft.. This technology could also be used to assemble complex structures in space such as large microwave or radio antenna arrays.

This is early/mid-stage (TRL 3) — the most realistic path in is NASA SBIR/STTR, which funds small businesses and research institutions to develop technology aligned with NASA's needs (equity-free, phased funding). Check whether a current SBIR/STTR solicitation topic overlaps with this project's technology area, or contact the project directly (above) to ask.

None of these are guaranteed paths for this specific project — TechPort itself doesn't have an "apply" button. Reaching out to the contact(s) above with a specific question is usually the fastest way to find out what's actually open.