2.1

The OSIRIS program

The OSIRIS development of highly compact and efficient payload focusses on high data rates for small Low Earth Orbit (LEO) satellites. Satellites of this class have a mass of 1 – 500 kg and often support missions for Earth observation. OSIRIS follows a roadmap for the development which is presented in Figure 1.

Figure 1:

OSIRIS development roadmap

The OSIRIS development started with two scientific missions on the satellites Flying Laptop (OSIRISv1) and BiROS (OSIRISv2) which have been launched in 2017 and 2016, respectively. The missions shall demonstrate data rates of 200 Mbit/s and 1 Gbit/s as typical payloads on Earth observation satellites.

Based on these two scientific missions, the development has been split in two main directions:

The following sections will give a more detailed insight in the missions shown in the development roadmap.

2.2

OSIRIS on Flying Laptop (OSIRISv1)

The Flying Laptop satellite is the first mission of University of Stuttgart’s small satellite program to demonstrate new technologies in space (see Figure 2). The satellite has a total mass of roughly 120 kg and carries remote sensing cameras as primary payload. For the high data rate transmission of the mission data to ground, FLP is furthermore equipped with the first generation of OSIRIS terminals (see Figure 3). The payload consists of a power supply unit as well as a laser unit with two independent laser sources. In this configuration, the payload consumes 26 W and adds 1.3 kg to the satellite mass while transmitting data with up to 1 W of optical output power, at a data rate of up to 200 Mbit/s. The transmission laser divergence is therefore adapted to the pointing accuracy of the satellite, using the body pointing with the star cameras as reference.

Figure 2:

Flying Laptop (FLP) Satellite of University of Stuttgart

Figure 3:

OSIRIS payload for the FLP

The Flying Laptop satellite finished the commissioning phase and is currently used for an extensive measurement and experiment campaign with the optical ground stations of DLR Oberpfaffenhofen. The goal is to demonstrate the optical downlink capabilities of OSIRIS and to transmit mission data. Besides that, the results will be an important input towards the current CCSDS standardization of optical LEO downlinks.

2.3

OSIRIS on BIROS (OSIRISv2)

The second generation of OSIRIS is installed on the BiROS satellite (see Figure 4). The primary payload of the satellite is an Earth observation payload for fire detection with high demand regarding downlink data rate. Therefore, the satellite is equipped with the OSIRIS payload, providing data rates up to 1 Gbit/s. To achieve the increased data rates, the transmit divergence has been decreased to keep the optical output power constant. The pointing towards the ground station is handled by the attitude control system of the satellite. To achieve the required accuracy, OSIRIS has been equipped with an additional tracking sensor which allows measuring the angular offset from the beacon emitted by the optical ground station and providing this information as an input for the attitude control. Figure 5 shows the OSIRIS payload onboard the satellite, which consists of an optical bench (right), laser modules (middle) and tracking electronics (left). With the additional tracking sensor, the OSIRIS payload adds 1.65 kg to the satellite mass and consumes up to 37 W with maximum optical output power.

Figure 4:

BiROS Satellite

Figure 5:

OSIRIS payload onboard the BiROS satellite

2.4

OSIRIS4Cubesat

OSIRISv1 as well as OSIRISv2 have been used as technology demonstration missions for the OSIRIS technology concept. The concept is on the one hand based on COTS components, but includes on the other hand an optimized development process, considering the special boundary conditions of COTS components and the requirements of “New Space” missions.

Based on the qualified parts in the previously presented missions, a miniaturized version is currently under development. It has a form factor of less than 10 × 10 × 3 cm³ (Figure 7 illustrated the installation in a 1 Unit Cubesat). Together with the low power consumption of only 8 W (during operation), the payload provides the flexibility to be flown on almost any CubeSat mission. With an additional weight of 300 grams, the CubeSat can utilize links with up to 100 Mbit/s, allowing for a data troughput of up to 4 Gbyte/day considering only one OGS in the central European region (including statistical cloud coverage). The downlink data rate is adapted to the mission needs of current CubeSat missions. With increasing need for higher data rates, also the downlink data rate of OSIRIS4CubeSat will be increased. To achieve those high data rates in the very compact form factor, OSIRIS4CubeSat follows a hybrid approach regarding the pointing: while the CubeSat bus has to provide a pointing accuracy within +/-1°, OSIRIS is equipped with a highly precise internal pointing unit, compensating remaining offsets of the satellite’s attitude control system (ACS). This approach allows receiving 100 Mbit/s on ground with only 100 mW of transmission power on the satellite, necessary for the payload’s low power consumption. Błąd! Nie można odnaleźć źródła odwołania. shows the payload for CubeSat missions. It consists of a baseplate which carries all electrical components and the optomechanics.

Figure 6:

Illustration of CubeSat with OSIRIS terminal installed

Figure 7:

OSIRIS payload for CubeSats (Picture: Tesat)

OSIRIS4CubeSat is the first step towards industrialization and is conducted in close collaboration with Tesat Spacecom. While DLR is developing and integrating the prototype and leading the demonstration mission in 2018, Tesat is preparing the technology for a commercial roll-out after the demonstration phase.

2.5

OSIRIS on Bartolomeo (OSIRISv3)

OSIRISv3 is the third OSIRIS generation. Building upon the background and experiences of the other OSIRIS developments, OSIRISv3 will operate at a higher data rate of 10 Gbps, and incorporate a number of additional subsystems, for instance:

Figure 8 shows a mockup of the third OSIRIS generation. DLR cooperates with Airbus DS to demonstrate OSIRIS on the ISS’ Bartolomeo platform. Bartolomeo is an external payload platform mounted on the Columbus module. Figure 9 illustrates Bartolomeo on the ISS together with OSIRIS. OSIRISv3 is planned for launch in 2019.

Figure 8:

Mock Up of third generation OSIRIS terminal

Figure 9:

Artist’s illustration of OSIRIS installed on the Airbus DS Bartolomeo platform (Picture © Airbus)

2.6

Further OSIRIS developments

Besides the previously mentioned projects and demonstrations, DLR is currently working on further payloads with the goal of extending the functionalities of OSIRIS with quantum communication capabilities. This is includes the QUBE project, which is funded by the German Ministry of Education and Research and lead by LMU München. Further partners are the Max Plank Institute for the Science of Light, OHB System AG, and the Zentrum für Telematik Würzburg. QUBE has the goal to extend OSIRIS4Cubesat with functionalities enabling quantum communication experiments.

In addition, DLR participates in the SES-lead QUARTZ project [7]. Within QUARTZ, DLR will extend the functionalities of OSIRISv3 to enable the exchange of quantum keys between a satellite platform and Earth. The goal of QUARTZ is to demonstrate an operational quantum key distribution system by 2022.

3.1

General status of OSIRISv1 and OSIRISv2 commissioning

DLR is currently still in the process of performing experiments with both OSIRISv1 and OSIRISv2. As both satellites are scientific technology demonstration missions with a number of experimental payloads, OSIRIS experiments couldn’t be performed right after satellite launch and have to be planned according to the availability of the satellites. This has resulted in the fact that experiments with OSIRIS are spread over a larger time span than originally anticipated.

For both systems, a calibration between the pointing direction of the OSIRIS transmit collimators to the satellite bus needs to be performed. Despite the fact that such a calibration was performed on ground, vibrations during launch likely led to a slight misalignment of OSIRIS compared to the satellite’s bus reference. This misalignment must be measured and compensated. For this purpose, DLR is currently conducting downlink experiments with both satellites. As of August 2018, these experiments are still ongoing.

Parallel to this, the laser sources onboard the satellites were commissioned in orbit. Both the sources on Flying Laptop and BIROS perform as expected. The next section will show telemetry data for both laser systems.

3.2

EDFA operation in orbit

Figure 10 and Figure 11 show In-Orbit results of the Erbium Doped Fiber Amplifier (EDFA) within OSIRISv2 on BIROS. The measured output power of 30 dBm is as specified, and the temperature of the EDFA increases moderately during operation, as expected.

Figure 10:

EDFA operation onboard BIROS (Input & output power)

Figure 11:

EDFA operation onboard BIROS (Temperatures)

The same is apparent for the EDFA within OSIRISv1 onboard Flying Laptop. Figure 12 shows an output power profile validating different power levels, and temperature results, measured in-orbit.

Figure 12:

EDFA operation onboard Flying Laptop

Therefore, the laser sources of OSIRISv1 and OSIRISv2 (which build on the same heritage) could be successfully commissioned and function well after more than one year of operation in Space.