TINA Small Force-Controlled Robotic Arm for Exploration and Small Satellites

DLR.de/en TINA Small force-controlled robotic arm for exploration and small satellites

Brief description The robotic arm TINA is a four-axis space demonstrator to investigate autonomous operations during exploration missions on Earth.

Aims The aim of the research project is to demonstrate the technology needed for a small, force-controlled robotic arm for use in space. By selecting specific components, it is possible to use TINA in Parties involved microgravity conditions as well as on Earth. DLR Institute of Robotics and Mechatronics

Applications Facts and figures

- Exploration, rover - Degrees of freedom: up to 7 - Controller: hard real time - Small satellites - Size: up to 2 m long - Radiation hardness: - Weight: 1.6 kg per joint various levels possible - Data transmission: - Tools: different end effectors can be Spacewire selected - Data rate: 3kHz - Supply voltage: +20V to +70V

@DLR_en DLR.de/en TINA Small force-controlled robotic arm for exploration and small satellites

The design of TINA follows the ‘qualifiable’ philosophy of DEXHAND [1], which uses industrial-grade components with a similar performance to their space equivalents and follows the ECSS guidelines closely, or uses the industrial-grade versions of radiation-hardened electronic components. This philosophy ensures that the transition to a fully qualified design can be achieved with a minimum number of changes. It also provides an almost perfect version for thermal and EMI modelling. Another big advantage is the low price compared to the fully qualified, radiation-hardened version, which allows the construction of multiple test arms for grasp- ing, object handling and many other applications.

Each joint is made up of a brushless DC motor in combination with a resolver for commutation and position sensing, a harmonic drive gearbox, a brake for safety reasons and a torque sensor to give TINA the ability to ‘feel’. Due to the torque sensor, the robot not only has high positioning accuracy, it can also detect if it is touching an object and then immediately stop its movement. The resolver on the link side enables high positional accuracy for the end effector.

Controlled by a SOC, each joint has a microcontroller and a FPGA. The field-oriented control of the motor is realised in the FPGA. The microcontroller functions are limited to simple management and logging. This ar- chitecture guarantees hard real-time behaviour and offers exceptional flexibility with respect to the auxiliary functions.

The communication between the joints and the OBC uses SpaceWire with a three kHz cycle time. The joints accept a single +20V to +70V supply or two separate supplies, one for the logic and one for the motor; this gives greater efficiency.

[1] https://www.dlr.de/rm/en/desktopdefault.aspx/tabid-9656/16605_read-40532/

Deutsches Zentrum für Luft- und Raumfahrt (DLR) German Aerospace Center @DLRen Maximilian Maier · Email [email protected] · DLR.de/en DLR.de/en INTEGRATION OF COMMERCIAL SPACEFLIGHT INTO THE AIR TRANSPORT SYSTEM Interoperable data exchange for safe and efficient launch and re-entry operations

Brief description The FAA Office of Commercial Space Transportation and DLR are seek- ing to identify the data that may need to be exchanged between United States and European Air Navigation Service Providers (ANSPs) prior to, during and after a space launch or re-entry operation that is initiated in one country and traverses the airspace of another country. This data exchange should facilitate improved situational awareness, allowing US and European ANSPs to respond as necessary in the event of a vehicle failure.

Aims Develop and conduct collaborative demonstrations of the exchange of key data between ANSPs. This will facilitate the safe and efficient Parties involved management of global airspace during launch and re-entry operations. The demonstration of simulated real-world scenarios will result DLR Institute of Flight Guidance in the identification of key parameters for exchange in reaction to FAA Office of Commercial Space Trans- time-critical non-nominal events. portation

Applications Outlook Facts and figures

- Improved situational aware- - Improve situational awareness - The number and type of commercial ness for ANSPs during launch and safety space launches and re-entry operations and re-entry operations - Enable efficient operation of is continuously increasing at a global - Improved ability to respond an increasing number of com- level to non-nominal scenarios in mercial launch and re-entry - Initial attempt by the FAA and DLR to a manner that addresses the operations share their unique capabilities using the potential hazards to public - Develop interoperability of Commercial Space Integration Lab and safety global air and space traffic Air Traffic Validation Center, located in management systems the USA and Germany respectively - Develop the digitalisation/auto- - Leverage existing international data mation of spaceflight planning standards and infrastructure by using and monitoring processes a data exchange approach based on System Wide Information Management (SWIM) @DLR_en DLR.de/en COMMERCIAL SPACE INTEGRATION INTO THE AIR TRAFFIC SYSTEM Interoperable data exchange for safe and efficient launch and reentry operations

The FAA and DLR are cooperating on a demonstration that will exchange launch and re-entry data to determine the usability of the exchange process within the global airspace environment. This joint activi- ty is aimed at facilitating improved situational awareness, allowing ANSPs to respond as necessary in the event of a launch or re-entry failure. Through a series of operational scenarios, the exchange of launch and re-entry vehicle data will be demonstrated and the effectiveness of the exchanged data will be assessed for non-nominal events during a launch to orbit or re-entry from orbital operations. The demonstration’s technical solution will utilise System Wide Information Management (SWIM) core services. The key data parameters will enable information sharing among the various users and stakeholders in the air transport system, allowing for improved accuracy and availability of flight information updates, consistency of flight planning in different Air Traffic Management (ATM) system domains, and safer transition of flights between the affected domains.

Deutsches Zentrum für Luft- und Raumfahrt (DLR) German Aerospace Center Sven Kaltenhaeuser · E-Mail [email protected] · DLR.de/en @DLRen Dirk-Roger Schmitt · E-Mail [email protected] · DLR.de/en DLR.de/en Compact Modular Motor Controller Three phase brushless DC motor driver for space environment

Brief description The small, highly integrated 300W Compact Motor Controller is ideal for small mechanisms, small robotic arms, pan-tilt units and similar applications. It has a position sensing interface and three phase current sensing stage for high level current control.

Objectives The aim of the research project is the development of a modular motor controller for future use in robotic space missions, such as MASCOT on board Hayabusa2. Parties involved DLR Institute of Robotcs and Mechatronics

Applications Facts and figures

- Small mechanisms, - Size: 67mm x 111mm - Radiation: up to 40kRad - Small robotic arms - Digital Voltage: +12V DC SEL LET threshold of 80 - Pan-tilt units - Power Voltage: +12V to +70V DC MEV*cm2/mg - Rover - Motor Current: Up to 10A - Control Feedback: field oriented - Similar applications - Communication: CAN; UART; control; six-step commutation; EtherCat; Spacewire; Ethernet sliding mode controller - Position Feedback: Resolver; - Unique Features: external motor Potentiometer; Digital Encoder redundancy switching - Auxiliary Sensor Interface: Force Torque Sensor

@DLR_en

Factsheet_Motor Controller_GB_7663639.indd 1 19.03.19 09:34 DLR.de/en Compact Modular Motor Controller Three phase brushless DC motor driver for space environment

The small, highly integrated 300-watt compact motor controller is a newly developed, three-phase brushless DC motor drive for use in space. With the experience gained during drivetrain development for MASCOT, which is DLR’s microlander contribution to JAXA’s Hayabusa2 mission, the need for radiation-hardened and compact motion-controller electronics was recognised. Taking into consideration the growing interest in microlander systems as well as small and lightweight mechatronic components for space robotics and exploration, the decision was made to continue development in order to evolve a modular controller that meets the needs of future missions. It is ideal for small mechanisms, small robotic arms, pan-tilt units and similar applications. It offers a rich set of analogue and digital interfaces that can be used for absolute position-sensing circuits, such as resolvers or magnetoresistive sensors. A commutation interface for Hall sensors is also available, as well as an integrated bridge driver with active current limiting. In addition to the sophisticated position-sensing interface, a three-phase current-sensing stage has been developed. This allows the implementation of high-level current control, i.e. field-oriented control methods. These control methods optimise the dynamic performance of the actuator while reducing the power consumption and the system noise of the motor-supply stage. The board features a fault-tolerant soft-core processor, as well as redundant motor and resolver interfaces. The redundant motor interface allows the connection of two controller boards to one motor without electrical crosstalk. With powerful communications bus interface options – such as SpaceWire, EtherCAT and RS422 – the board may be considered to be a flexible component that can be integrated into space systems in a very straightforward manner. The small form factor improves and simplifies the thermal management and the integration into small systems.

The motor controller benefits from the knowledge gained from the MASCOT mission, which successfully completed its mission in October 2018.

Deutsches Zentrum für Luft- und Raumfahrt (DLR) German Aerospace Center, Institute of Robotics and Mechatronics @DLRen Maximilian Maier · Email [email protected] · DLR.de/en

Factsheet_Motor Controller_GB_7663639.indd 2 19.03.19 09:34 DLR.de/en InSight/HP3 Interior Exploration using Seismic Investigations, Geodesy and Heat Transport

Brief description In May 2018, the NASA InSight space probe will embark on its journey to Mars, with the goal of investigating its geophysical properties. On board the lander are the French space agency’s (CNES) SEIS seismom- eter, the HP3 sensor package developed by DLR and JPL’s RISE experiment.

Aims The InSight mission is intended to comprehensively examine the interior Parties involved structure of our planetary neighbour. After the landing, SEIS will measure the waves from ‘Marsquakes’ that travel through the planet’s interior. HP3 DLR, Lockheed Martin, JPL (NASA), will determine the heat flow and some of the physical properties of the Institut de Physique du Globe de Paris Martian soil; RISE will measure the precession and nutation of the spin axis.

Applications Outlook Facts and figures

- Exploration - Geophysical exploration of the - Launch: May 2018 - Basic research Moon, Mars and Mercury - Arrival: 26 November 2018 - Planetary physics - In-situ exploration of the - Mission duration: 2 Earth years - Comparative planetology subsurface Second heat flow measurement on a - Sampling celestial body since Apollo 17 (1972)

@DLR_en

26159_Factsheet_InSight_GB_RZ_190319.indd 1 19.03.19 09:36 DLR.de/en InSight/HP3 Interior Exploration using Seismic Investigations, Geodesy and Heat Transport

Just six months after its launch in May 2018, the InSight lander will touch down on the surface of Mars. The mission is part of NASA’s successful Discovery programme and for the first time will intensively examine the interior of our planetary neighbour – its crust, mantle and core. While Earth has experienced many changes as a result of plate tectonics, Mars has undergone less of a radical change since its formation four and a half billion years ago. Scientists are hoping that InSight will provide answers to questions regarding the earliest developments of Mars and enable them to draw conclusions about the evolutionary history of the Red Planet and Earth. The landing site in Elysium Planum is located in the northern lowlands, approximately 1500 kilometres south of the Elysium Mons volcano. After landing, the Seismic Experiment for Interior Structures (SEIS) will start to record the seismic waves from ‘Marsquakes’ and providing data to understand the planet’s history. The Rotation and Interior Structure Experiment (RISE) will register minimal changes in the planet’s axis alignment and also allow conclusions to be drawn about its interior structure. DLR is sending a heat flow probe to the Red Planet, namely the Heat Flow and Physical Properties Pack- age (HP3). A so-called ‘mole’ will penetrate to a depth of five metres using an internal hammering mech- anism that will drive heat sensors into the ground. These will supply readings fully automatically and from various depths during an entire Martian year – the equivalent of two Earth years. An infrared radiometer will also measure the temperature profile on the surface. The combination of both data sets makes it possible to deduce the heat flow in the planet’s interior. The instrument was primarily developed at the DLR Insti- tute of Planetary Research and tested at the DLR Institute of Space Systems. After InSight has landed, DLR’s Microgravity User Support Center in Cologne will take over HP3 operations.

Deutsches Zentrum für Luft- und Raumfahrt (DLR) German Aerospace Center @DLRen Ulrich Köhler · E-Mail [email protected] · DLR.de/en

26159_Factsheet_InSight_GB_RZ_190319.indd 2 19.03.19 09:36 DLR.de/en GESTRA Experimental space monitoring radar

Brief description GESTRA (German Experimental Space Surveillance and Tracking Radar) is an experimental space monitoring radar. The sensor is being developed and built by the Fraunhofer Institute for High Frequency Physics and Radar Techniques FHR and financed by DLR with funds from the German Feder- al Ministry for Economic Affairs and Energy (BMWi). The space monitoring system is scheduled to start delivering data in 2019.

Aims For the first time, GESTRA is making it possible for Germany to inde- Parties involved pendently track, identify and catalogue objects in space. The equipment is intended to record orbital data from satellites and debris in low Earth DLR Space Administration, FHR Wacht- orbit at an altitude of between 300 and 3000 kilometres. berg, DLR and German Air Force Space Situational Awareness Centre

Applications Outlook Facts and figures

- Establishment, maintenance - Sustainable and safe satellite op- Start: planned for 2019 and operation of an orbital eration for space-based services Size: housing container: 18 m x 4 m x 4 data catalogue by the DLR and products, from navigation m, mass: approx. 90 t, and German Air Force Space systems to Earth observation and radiation dome: 5 m, Situational Awareness Centre communications diameter: 5 m in Uedem. - Strategies for addressing the Properties: transmitting frequency, - Development of system com- growing amount of space resi- 1280 – 1380 MHZ, beam angle max. petence and expertise in space due/debris 20 degrees zenith distance, no ionising situational awareness, as a radiation basis for operational space surveillance

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26159_Factsheet_Gestra_GB_RZ_150319.indd 1 15.03.19 09:28 DLR.de/en GESTRA Experimental space monitoring radar

GESTRA (German Experimental Space Surveillance and Tracking Radar) is an experimental space monitoring radar designed to record the orbital data of satellites and debris in Low Earth Orbit at an altitude of between 300 and 3000 kilometres. It is expected to conduct its first measurements from 2019. The radar is operated by the joint DLR and German Air Force Space Situational Awareness Centre in Uedem. GESTRA is also intended to work in conjunction with other large-scale facilities, such as the space observation radar, TIRA, or the radio telescope, Effelsberg, in order to expand expertise in so-called bi- and multi-static radar operation. This is based on the radar-supported observation of objects in space, involving several, spatially separated transmitters and receivers. Smaller objects, in particular, can therefore be more easily detected and more accurately determined. There are around 16,000 recorded and catalogued space debris objects, usually with a diameter of at least 10 centimetres. The largest accumulation of space debris is located at an altitude of around 900 kilometres, the site of frequently used orbits. We esti- mate that there are a total of 29,000 objects larger than 10 cm, 750,000 objects larger than 1 cm and 150 million objects larger than 1 mm.

The GESTRA data will be made available to research institutions in Germany, and form the basis of future developments in operational space surveillance. GESTRA is also a major step towards implementing the German government’s space strategy, which places a great deal of importance on establishing its own capacity to continuously record the space situation, including in an international context. The ability to continuously monitor space objects in order to prevent the collision of satellites and other objects is therefore being systematically developed and expanded in Germany.

Deutsches Zentrum für Luft- und Raumfahrt (DLR) German Aerospace Center @DLRen Gerald Braun · E-Mail [email protected] · DLR.de/en

26159_Factsheet_Gestra_GB_RZ_150319.indd 2 15.03.19 09:28 CIMON® The flying astronaut assistant – technology demonstration

Brief description

CIMON® (Crew Interactive MObile companioN) could be described as a ‘flying brain’ – an autonomous astronaut assistant. Powered by Artificial Intelligence, this globally unique technology demonstration will support the work of astronauts on the ISS and will bring advances to the fields of Industry 4.0, medicine and care, as well as education.

Objectives CIMON® uses the ISS as a test environment for trialling new Parties involved technologies. CIMON® aims to demonstrate that human-machine interaction can support the work of astronauts and increase their DLR Space Administration, Airbus, IBM efficiency. In future, the flying companion could be used, for example, Watson, Reichert Design, LMU Munich, to present and explain a wide range of information and instructions Helden & Mayglöckchen, Darmstadt Uni- for scientific experiments and repairs. versity of Applied Sciences (h_da), ESA

Applications Outlook Facts and figures

- Supporting the work of - Assistance systems for Launch: SpaceX CRS-15, 29 June 2018 astronauts human-machine interaction Commissioning: 14./15. Nov. 2018 - Preparation for long-term (Industry 4.0, the Internet of Scientific support: exploration missions Things …) Judith Buchheim and Alexander Choukèr - Human-machine psychosocial - Medicine and care Diameter: 32 cm interaction - Use in education Properties: Autonomous navigation using air jet propulsion, voice and object recognition, information display, video data, etc.

@DLR_en DLR.de/en

Factsheet_Cimon_GB_7662426.indd 1 19.03.19 09:29 CIMON® The flying astronaut assistant – technology demonstration

Technology demonstration – astronaut assistance system

CIMON® is an innovative and globally unique astronaut assistance system developed and built in Germany. This autonomous flying system is equipped with Artificial Intelligence (AI) from IBM and was used for the first time by ESA astronaut Alexander Gerst during the ‘horizons’ mission. The DLR Space Adminis- tration awarded Airbus the contract to undertake the CIMON® project using funds from the German Federal Ministry for Economic Affairs and Energy (BMWi), and it was specially developed for use in the European Columbus module of the ISS. CIMON® aims to demonstrate that human-machine interaction can support the work of astronauts and increase their efficiency. The flying companion can present and explain a wide range of information and instructions for scientific experiments and repairs. One big advantage of CIMON® is that the astronaut can work freely with both hands while having voice-controlled access to documents and media. A further application of CIMON® is its use as a mobile camera for operational and scientific purposes. The flying companion can carry out routine tasks, such as docu- menting experiments, searching for objects and taking inventory. CIMON® can also see, hear, speak and understand. Cameras and facial recognition software for orientation and video documentation serve as its ‘eyes’. Ultrasound sensors measure distances to avoid collisions. Its ‘ears’ are comprised of several microphones for spatial detection and a directional microphone for good voice recognition. CIMON®’s ‘mouth’ is a loudspeaker, through which it can speak and play music. The heart of the AI for understanding speech is the Watson AI technology from the IBM Cloud. The AI for autonomous navigation comes from Airbus and is used for movement planning and object recognition. CIMON® is largely produced using a 3D printing process and, with a diameter of 32 centimetres, is slightly larger than a football. CIMON® can freely move and rotate in any direction using air jets. Using these jets, it can turn to an astronaut if it is addressed, nod and shake its head, and independently follow the user on command. Terrestrial applications for the CIMON® technologies are expected in Industry 4.0 (in robotic industrial production, for example), medicine and care, as well as education.

Deutsches Zentrum für Luft- und Raumfahrt (DLR) German Aerospace Center @DLRen Dr. Christian Karrasch · E-Mail [email protected] · DLR.de/en DLR.de/en

Factsheet_Cimon_GB_7662426.indd 2 19.03.19 09:29 DESIS DLR Earth Sensing Imaging Spectrometer

Brief description

DESIS is a hyperspectral camera developed and built by DLR in collabo- ration with Teledyne Brown Engineering (TBE). DESIS is used for Earth observation and operated on board the ISS by the MUSES (Multi-User System for Earth Sensing) platform developed by Teledyne Brown Engineering.

Aims

DESIS is intended to supply hyperspectral data to support scientific, humanitarian and commercial goals. It provides information to assess the situation following environmental disasters, to help farmers Parties involved manage their land in a targeted manner, and to provide scientists with a basis for innovative atmospheric correction algorithms. DLR, Teledyne Brown Engineering

Applications Outlook Facts and figures

- Earth observation - Global ecosystem monitoring Launch: 29 June 2018 - Humanitarian aid - Further development of Size: 900 x 600 x 500 mm - Commercial data products hyperspectral technologies Number of spectral channels: 235 from space - Improved response to Spectral Range: 400 -1000 nm - Targeted agriculture humanitarian crises Spectral Pitch: 2,5 nm - New research using Pixel resolution (ground sample hyperspectral data distance): 30 m

@DLR_en DLR.de/en

26159_Factsheet_DESIS_GB_RZ_191319.indd 1 19.03.19 10:23 DESIS DLR Earth Sensing Imaging Spectrometer

With increasing global industrialisation, the impact of humans on Earth’s food supply is constantly growing. Using hyperspectral data, scientists can monitor and develop the dynamic relationships between geophysical parameters on an intercontinental scale. The DESIS imaging spectrometer can depict the land surface, oceans and atmosphere with great accuracy. Unlike conventional satellite-based spectrometers, DESIS has a high number of channels in range of 400 to 1000 nanometer. The instrument records hyperspectral data using 235 channels with a spectral pitch of 2.5 nanometres, covering the visible and near infrared spectrum. It has been developed to obtain a pixel resolution (ground sample distance) of 30 metres from the 400-kilometre orbit of the ISS.

The spectrometer has been developed to operate on the MUSES instrument platform. DESIS was launched to the International Space Station (ISS) on board a SpaceX rocket on 29 June 2018. From there, DESIS will observe Earth’s surface around the clock, providing experts with information about the current state of, and any changes to, the land and ocean surface. This will enable them to better understand environmental processes or make statements about the current state of forest and agricultural land in order to improve global food production, for example. In addition, data from the ISS instrument will quickly be available in the event of a disaster, enabling it to assist emergency services with their deployments. The developers aim to combine the data from all MUSES instruments and thereby develop advanced methods for remote sensing. The remote sensing instruments can also be returned to Earth after their operational life of between three and five years, in order to more closely examine the impact of the space environment on them.

Two DLR institutes are involved in the project: The DLR Institute of Optical Sensor Systems built the instrument as part of the space segment subproject, while DLR’s Earth Observation Center (EOC) in Oberpfaffen- hofen is managing the ground segment subproject, which is responsible for the reception, processing and transfer of the data into applications.

Deutsches Zentrum für Luft- und Raumfahrt (DLR) German Aerospace Center @DLRen Uwe Knodt · E-Mail [email protected] · DLR.de/en DLR.de/en

26159_Factsheet_DESIS_GB_RZ_191319.indd 2 19.03.19 10:23 Black Engine technology Transpiration-cooled ceramic high-performance rocket engines

Brief description

The highly innovative and future competitive transpiration-cooled ceramic thrust chamber for high-performance rocket engines consists of three major components: the CMC cone injector, the CMC combustion chamber and the CMC supersonic expansion nozzle (CMC – Ceramic Matrix Composites – microporous fibre-reinforced ceramic materials). The technology is an excellent example of the sophisticated application of modern hybrid structural design with the exploitation of specific inherent material properties.

Aims Parties involved

The development targets highly reliable and reusable future rocket DLR and Black Engine Aerospace UG. engines for the New Space market, which is experiencing significant Potentially also ESA, established space growth. Extended lifetime, high operational safety, high efficiency transportation and satellite industries. with low weight and noticeably reduced operation and maintenance costs are the drivers for this research and development programme.

Applications Outlook Facts and figures

- High thrust main stage rocket - Creation of cost-effective - Two-year ongoing innovation engines future downstream service project (TRL 5) for the transfer of the - Highly efficient upper stage from space to Earth technology from research to industry rocket engines - Preparedness for future - Universal LOX/LNG ceramic rocket - Attractive for both ELV – high-velocity human thrust chamber demonstrator for 60 Expendable Launch Vehicles space- or cross-country flight kN thrust and RLV – Reusable Launch - Preparation of licensing procedures Vehicles - Planning of production capacities

@DLR_en DLR.de/en

26159_Factsheet_Black Engine_GB_RZ_290319.indd 1 29.03.19 09:11 Black Engine technology Transpiration-cooled ceramic high-performance rocket engines

The name Black Engine comes from the use of predominantly black carbon fibres used in the composite components that make up the hybrid structure system. Currently, the ceramic LOX/LCH4 or LOX/LH2 rocket thrust chamber technology – represented by the first full-scale and near-market demonstrator – which will soon be available, promises high operational reliability, high durability and high reusability. The ceramic cone injector offers high ignition reliability and combustion efficiency; the multilayered CMC expansion nozzle enhances the efficiency of the entire rocket engine system by reducing cooling system requirements and overall design complexity. In addition, an innovative CMC journal bearing technology will increase the durability and reusability of future turbo-pumps, which play an important role in reliable propellant feed systems. System simplifications allowed by production-redundant non-integrated design lead to cost reductions for manufacturing, operation and maintenance. Load-decoupled and low-fatigue structural design promises long engine lifetimes, targeting standards achieved by today’s aircraft engines. High thermal resistance at high operating efficiency is permitted by the use of CMC materials. An approximately 25 per- cent lower structural weight with extremely high load capacity seems to be feasible. Significant cost savings even in comparison to the new 3D-printed metal launch vehicle engines are also possible. The combination of long-life thrust chambers and turbo-pumps addresses increased future competitiveness, which will be seen as a long-term advantage for imminent New Space applications, looking specifically at today’s reusable and return-capable first stages. Furthermore, this new engine technology is, on the one hand, scalable from lower in-space exploration thrust levels up to high thrust lift-off propulsion levels. On the other hand, such new ceramic rocket propulsion systems seem to be attractive price-wise for both reusable launch vehicles (RLV) and for expendable launch vehicles (ELV). Finally, hypersonic and sub-orbital space flight can be well supported by this new technology. Today’s growing space transportation market can be an essen- tial platform or accelerator to advance innovative technologies more than in recent years. Let us seize this opportunity!

Deutsches Zentrum für Luft- und Raumfahrt (DLR) German Aerospace Center @DLRen Markus Ortelt · Email [email protected] · DLR.de/bt/en DLR.de/en

26159_Factsheet_Black Engine_GB_RZ_290319.indd 2 29.03.19 09:11