Laser intersatellite links (LISLs) are envisioned between satellites in upcoming satellite constellations, such as the one in phase I of SpaceX's Starlink. Within a constellation, satellites can establish LISLs with other satellites in the same orbital plane (OP) or in different OPs. We present a classification of LISLs based on the location of satellites within a constellation and of LISLs' duration. Then, using the satellite constellation for phase I of Starlink, we study the effect that varying a satellite's LISL range has on the number of different types of LISLs it can establish with other satellites. In addition to permanent LISLs, we observe a significant number of temporary LISLs between satellites in crossing OPs. Such LISLs can play a vital role in achieving low-latency paths within next-generation optical wireless satellite networks.

Laser Intersatellite Links in a Starlink Constellation: A Classification and Analysis

Due to the high directionality and short wavelength of laser transmission in space, satellite laser communication can achieve high speed, wide bandwidth, high precision, and high security with no electromagnetic spectrum constraints. It has become a promising direction to construct the laser space network. Recently, relative products, on-orbit demonstrations, and researches have been conducted on laser space networks. Considering this network as a graph, this paper presents a comprehensive survey from nodes, edges, to architectures of this graph, corresponding to laser communication terminals, laser space links, and laser space network architectures. For each content, current achievements are introduced and future trends are analyzed accordingly. Through this survey paper, we aim to present the prospect to develop laser space networks in the next space generation and provide potential research directions to interested researchers or engineers. 

/pdf/a-survey-on-laser-space-network-terminals-links-and-1fij7lmz.pdf

A Survey on Laser Space Network: Terminals, Links, and Architectures

The pointing jitter originated from the random mechanical vibration of the optical platform and the noise associated with the optomechanical sensor system unquestionably deteriorate the performance of the inter-satellite optical link. The impact of the jitter changes significantly with the receiver architecture. In this paper, we present a mathematical model to investigate the link performance in the presence of angular pointing jitters for different receiver architectures. Alongside the statistical pointing error model, the derived model incorporates key receiver design parameters such as detector radius, receiver aperture size, f-number of the lens system, and beam compression ratio to study the impact of receiver architecture on the pointing jitter. As an example, a CubeSat optical receiver is analyzed. We show that by careful selection of beam compression ratio and f-number, more than 5 orders of magnitude bit error rate improvement is achievable even at large pointing error.

Impact of receiver architecture on small satellite optical link in the presence of pointing jitter

Beaconless angle-of-arrival tracking with improved receiver sensitivity and tracking precision for free-space optical communications

Advanced space missions, e.g., interplanetary exploration and Earth observation embrace constellation or swarm-like CubeSat configuration to achieve unprecedented spatial and temporal resolutions at a significantly lower investment. The realization of high-speed inter-CubeSat data communication link is mandatory to ensure the success of such missions. In this article, we present a scalable high-speed CubeSat crosslink implementation based on the wavelength-selective optical transceiver (WSOT) design. System performance based on the state-of-the-art components that satisfy the stringent size, weight, power, and cost requirements has been investigated. We estimate that with a 15 mm transceiver aperture size and 1 W peak bit power, the system attains communication distance up to 125 and 80 km for 400 Mb/s and 800 Mb/s data rates, respectively. Additionally, we present the optical and mechanical design of five transceiver units that can fit inside a 3U CubeSat to achieve a full field of regard (360°) to enable omnidirectional high-speed optical communication. Further performance improvements are possible through incorporating advanced amplifiers, error correction coding, and large aperture optics.

Realization of Omnidirectional CubeSat Crosslink by Wavelength-Selective Optical Transceiver

The CubeSat Laser Infrared CrosslinK mission is a joint Massachusetts Institute of Technology (MIT), University of Florida (UF), and NASA Ames Research Center effort to develop laser communications (lasercom) transceivers. The terminals demonstrate full-duplex intersatellite communications and ranging capability using commercial components to enable future large constellations or swarms of nanosatellites as coordinated distributed sensor systems. CLICK will demonstrate a crosslink between two CubeSats that each host a The lasercom terminals are direct-detect and rate scalable, designed to achieve a 20 Mbps crosslink at ranges from 25 km to 580 km and operate full-duplex at 1537 nm and 1563 nm with 200 mW of transmit power and a 14.6 arcscecond (0.07 milliradian) full width half max (FWHM) beamwidth. The terminals also use a 976 nm, 500 mW, 0.75 degree FWHM beacon and a quadcell for initial acquisition, and a low-rate radio crosslink for exchanging orbit information. The payload transmitter is a master oscillator power amplifier (MOPA) with fiber Bragg grating for pulse shaping and MEMS fast steering mirror (FSM) for fine pointing, modeled after the MIT Nanosatellite Optical Downlink Experiment. The transceiver leverages UF’s Miniature Optical Communications Transmitter (MOCT) including a chip-scale atomic clock (CSAC). The receiver implements both a time to digital converter (TDC) as well as pulse recovery and matched filtering for precision ranging.

https://www.spiedigitallibrary.org/conference-proceedings-of-spie/11180/111800Y/The-CubeSat-Laser-Infrared-CrosslinK-Mission-CLICK/10.1117/12.2535953.pdf

The CubeSat Laser Infrared CrosslinK Mission (CLICK)

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The CubeSat Laser Infrared CrosslinK Mission (CLICK)