Iodine frequency references for space

11th International LISA Symposium

Schuldt, Thilo^1 ; Döringshoff, Klaus^2 ; Oswald, Markus^3,4 ; Johann, Ulrich^4 ; Peters, Achim^2 ; Braxmaier, Claus^1,3

German Aerospace Center (DLR), Linzer Straße 1, Bremen

28359, Germany^1

Humboldt-University Berlin, Newtonstr. 15, Berlin

12489, Germany^2

University Bremen, Center of Applied Space Technology and Microgravity (ZARM), Am Fallturm 1, Bremen

28359, Germany^3

Airbus DS GmbH, Claude-Dornier-Straße, Immenstaad

88090, Germany^4

关键词: Engineering modeling;    Frequency stabilization;    Fundamental physics;    Gravitational-wave detection;    Hyperfine transition;    Inter satellite distances;    Optical frequency references;    Stability requirements;   

Others  :  https://iopscience.iop.org/article/10.1088/1742-6596/840/1/012050/pdf
DOI  :  10.1088/1742-6596/840/1/012050

来源: IOP

【 摘 要 】

Optical frequency references are a key element for the realization of future space missions. They are needed for missions related to tests of fundamental physics, gravitational wave detection, Earth observation and navigation and ranging. In missions such as GRACE follow-on or LISA the optical frequency reference is used as light source for high-sensitivity inter-satellite distance metrology. While cavity-based systems are current baseline e.g. for LISA, frequency stabilization on a hyperfine transition in molecular iodine near 532 nm is a promising alternative. Due to its absolute frequency, iodine standards crucially simplify the initial spacecraft acquisition procedures. Current setups fulfill the GRACE-FO and LISA frequency stability requirements and are realized near Engineering Model level. We present the current status of our developments on Elegant Breadboard (EBB) and Engineering Model (EM) level taking into account specific design criteria for space compatibility such as compactness (size iodine spectroscopy EM: 38 × 18 × 10 cm3) and robustness. Both setups achieved similar frequency stabilities of ∼ 1 • 10-14at an integration time of 1 s and below 5 • 10-15at integration times between 10 s and 1000 s. Furthermore, we present an even more compact design currently developed for a sounding rocket mission with launch in 2017.