2.1

Lunar Laser Communications Demonstration (LLCD)

NASA’s first demonstration of optical communication came in 2013, with the Lunar Laser Communications Demonstration (LLCD) mission, aboard the Lunar Atmosphere Dust and Environment Explorer (LADEE)³. LLCD was a collaborative effort between NASA Goddard Space Flight Center (GSFC), NASA Jet Propulsion Laboratory (JPL), and Massachusetts Institute of Technology-Lincoln Laboratories (MIT-LL). LLCD demonstrated several key attributes of optical communication systems such as error-free data downlink rates of up to 622 Mb/s from the moon (400,000 km). The closest performance by an RF Ka-band radio system was achieved by the system onboard the Lunar Reconnaissance Orbiter (2009) that used a 0.75 meter antenna to deliver data at 100 Mb/s. Even though the space-based laser terminal provided significantly better performance as compared to the RF system it required only half the mass (30.7 kg as compared to 61 kg) and 25 percent less power (90 W as compared to120 W).⁴ Another important capability demonstrated by LLCD was a 20-Mb/s uplink, which can be crucial for human space exploration systems since it can be used for real time high-definition video conferencing with astronauts from the moon. Finally the LLCD mission demonstrated precision ranging to the spacecraft, achieving centimeter level range resolution.

2.2

Laser Communications Relay Demonstration (LCRD)

Currently NASA is developing the Laser Communications Relay Demonstration (LCRD) mission. LCRD will be a long term demonstration of a relay based optical communications system. It is designed to demonstrate high-bandwidth, bidirectional optical communications relay services between geosynchronous orbit (GEO) and Earth or LEO users. The mission objectives are:

The project is a collaborative effort between NASA GSFC, NASA JPL, and MIT-LL, and will fly on an Orbital ATK (OATK) satellite.

The LCRD payload consists of two independent laser communication terminals, which are connected via a new electronic switch to provide high-speed frame switching and routing between the two optical space terminals (OSTs) while also serving as the interface to the host spacecraft. With two optical space terminals, LCRD can relay information between two ground stations or an orbiting spacecraft at LEO and a ground station. LCRD has an additional High Bandwidth bi-directional communications path via the Host Radio Frequency (RF) link for added flexibility and enabling demonstrations of diverse optical communications architectures and scenarios.

3.1

Integrated Laser Communications Relay Demonstration (LCRD) Low-Earth Orbit (LEO) User Modem and Amplifier Terminal (ILLUMA-T)

ILLUMA-T is a NASA mission sponsored by the Space Communications and Navigation (SCaN) Program Office. It is destined for the International Space Station (ISS) as an external payload attached to the Japanese Experiment Module - Exposed Facility (JEM-EF). ILLUMA-T’s overarching objective is to demonstrate an optical communications user terminal capable of high bandwidth data transfer between Low Earth Orbit (LEO) and a ground station via a geosynchronous (GEO) relay satellite. The ILLUMA-T payload will communicate primarily with the LCRD (Laser Communication Relay Demonstration) payload (which will be located at GEO). The LCRD payload will then relay the information to one of two dedicated ground stations on the surface of the Earth. The ILLUMA-T payload will also be capable of pointing to a ground station; however, this a contingency mode for use if LCRD is unavailable. ILLUMA-T will be the first demonstration of a LEO user of the LCRD system. It will demonstrate pointing and tracking from a moving spacecraft at LEO to the GEO relay satellite, and vice versa, and end-to-end operational utility of optical communications with return link rates from ISS to ground of up to 1.244 Gbps and forward link rates from ground to ISS of up to 51 Mbps.

The potential operational optical links of the ILLUMA-T payload are illustrated in figure 1. The primary link, shown as a solid arrows, connect the ISS to the LCRD payload at GEO. The contingency link, shown as dashed arrows connect ILLUMA-T payload to ground stations.

Figure 1:

ILLUMA-T operational characteristics. Primary mission requirement is to communicate through LCRD

The ILLUMA-T payload will be installed on the Japanese Experiment Module-Exposed Facility (JEM-EF). Figure 2 shows a schematic of the ISS and the location where ILLUMA-T payload will be installed. The ILLUMA-T will be facing forward as the ISS orbits the earth.

Figure 2:

Schematic of the ISS and location where ILLUMA-T payload

The details of the ILLUMA-T payload are shown in Figure 3. On display in figure 3(a) is the ILLUMA-T enclosure. It shows the relative positioning of the optical module with respect to the Payload Interface Unit (PIU) which is the interface between the payload and the JEM-EF/ISS, and the H-fixture and grapple fixture which are used for robotic transfer of the payload. Figure 3(b) displays the various parts and subsystems of the ILLUMA-T payload and their relative positioning. There are four key subsystem in ILLUMA-T:

3.2

Orion EM-2 Optical Communications Terminal (O2O)

O2O is a NASA project sponsored by NASA’s Human Exploration and Operations (HEO) Mission Directorate. O2O’s main objective is to provide bi-directional optical communications capability to the Orion Multi-Purpose Crew Vehicle (MPCV) series of spacecraft, starting with the demonstration of operational utility on Exploration Mission-2 (EM-2). It will be the first time a human exploration mission will rely on optical communications for its high-bandwidth link. The O2O project is a collaborative effort between GSFC, MIT-LL, JPL, and NASA’s Johnson Space Center/Lockheed Martin.

EM2 is a ~7-14 day mission that will transport humans to lunar vicinity for the first time since the Apollo missions. The primary communications link for the Orion vehicle is an S-band RF link that operates at rates of up to a few Mbps. The optical communications capability being developed for EM-2 will demonstrate direct-to-Earth return rates of up to 80-250 Mbps and forward rates up to 20 Mbps. The link architecture is very similar to the LLCD design.

Figure 3:

(a) ILLUMA-T enclosure (b) Details of ILLUMA-T Payload

The graphic in Figure 4 depicts the O2O project high level architecture. Bidirectional communication will be established between the Orion spacecraft at the moon and the Orion operations center at Johnson Space Center through the O2O terminal located in the Crew Module Adapter, an optical ground terminal, and the SN ground network.

Figure 4:

O2O high level system architecture

The key subsystem of O2O is the optical module which is responsible for accurately pointing the laser light towards earth and the optical ground station. This optical module will be coupled to a 1-W 1550-nm pulseposition modulation (PPM) modem to provide the downlink to Earth. A small ground terminal coupled to photon-counting detectors will be sufficient to receive the downlink signal at the planned data rates. The O2O project is classified as a Development Test Objective (DTO) project the optical link will not be used all the time, rather it will be primarily used for high-rate file transfers to and from the Orion vehicle, video streaming and other applications over the course of the EM-2 mission.

The O2O hardware is mounted onto the Orion spacecraft in three distinct zones. The Optical Module and the Controller Electronics Module are mounted on the exterior of the spacecraft on the Crew Module Adapter (CMA) via its own vibration isolation system to isolate against the Orion launch loads. For better thermal coupling and dissipation, the Modem Module and the Power Converter unit are co-located on a vibration-isolated pallet mounted to the interior of the CMA. The arrangement of the three modules with respect to the CMA is illustrated in Figure 5.

Figure 5.

Depiction of where O2O optical communications modules on the Orion Spacecraft, and each of the three Modules: 1 – Optical Module, 2 – Controller Electronics Module, and 3 – Modem Module and Power Converter Unit.

3.3

Modular, Agile, Scalable Optical Terminal (MAScOT)

In an effort to support the varying needs of future missions, NASA together with MIT-LL have evolved the optical terminal technology that was developed for previous missions, like LLCD and LCRD. Recent development efforts have focused on evolving optical module design to make it more capable and reduce recurring costs associated with meeting various mission requirements. Both O2O and ILLUMA-T are using a common optical terminal based on a new design developed at MIT-LL for use in a wide variety of laser link scenarios, the Modular, Agile, Scalable Optical Terminal (MAScOT), see the schematics in figure 6.⁵ MAScOT was first developed to provide a terminal for spacecraft in LEO where wide field of regard and fast slew rates are required. Key features of the MAScOT architecture is its modularity and scalability. The ILLUMA-T and O2O programs will demonstrate the viability of the MAScOT design for space missions, maturing it for operational use on future space missions. While current efforts are developing ~10-cm user terminals, larger apertures based on the same terminal design are also envisioned for future applications.

Figure 6:

MAScOT Optical Terminal (a) as-built CAD, (b) Gimbal Field Of Regard (FOR), 90° to -30° by 360°, and (c) Photograph of engineering unit, 10-cm MAScOT developed for use on Orion and the ISS

MAScOT has greater than hemispherical field-of-regard with pointing and tracking capabilities that can support fast-moving platforms in low-Earth orbit as is the case of the ISS. The 10-cm aperture is coupled to the back-end optics assembly via a Coudé path. The MAScOT terminal is coupled to a modem via optical fibers which connect to the back-end optics assembly. The MAScOT architecture is modular in that its subassemblies (the telescope, latch and gimbal, and back-end optics) may be developed independently by different groups so long as they adhere to specifications at the subassembly interfaces. The architecture is scalable in that various sizes of telescope may be accommodated without significant changes to the other subassemblies. For these reasons, it is believed that this terminal design will find many applications in cis-Lunar space and beyond.

An important aspect of the O2O and ILLUMA-T optical terminals development is industry participation. A significant part of the optical module subassemblies will be provided by industry as a result of competitive proposal processes. The schematic in figure 7 shows the various optical module subassemblies and the various companies responsible for putting it together. This was done for several reasons including taking advantage of industrial knowhow and expertise in optical communication, and to make sure that industry will be able to satisfy the needs of future missions. It is also expected that adaptation of industrial processes will reduce the cost of optical communication equipment and making them more affordable.

Figure 7:

Optical module subassembly breakdown and industry partnerships