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Portfolio

Company Astro- und Feinwerktechnik Adlershof GmbH
Contact Maik Hartmann
Position Vice Director (ppa.)
E-Mail m.hartmann@astrofein.com
Address Albert-Einstein-Str. 12
12489 Berlin
Country
Phone +49 (30) 6392 10 00
Fax +49 (30) 6392 10 02
Internet www.astrofein.com

Astro- und Feinwerktechnik Adlershof GmbH

Our competencies in one sentence

With over 20 years’ experience in developing, manufacturing and testing highly reliable precision and mechanical engineering components, sub-assemblies and devices, we, Astro- und Feinwerktechnik Adlershof GmbH, are a reliable partner for science and industry, specialized in the field of components and systems used in the aerospace industry.

Products and Services and R&D

Products like Reaction Wheels, Gyro Systems, Solar Panels, CubeSat Deployer – PicoSatellite Launcher, Deployable Boom, MGSE, EGSE, GSE, Optical Technologies like filter Wheels and Camera Development, Test Beds and Apparatus Engineering like Attitude Control System, Test Facilities and Test Bed for Rotation Sensor, Services like Environmental simulation (Pyroshock, Shock, Vibration, Thermal, Thermal-Vacuum, Static Load, MOI, CoG) Research and Development, Manufacturing, FEM, Structural and Thermal Analysis, Electronical Design, Software Engineering, Quality Assurance.

Special Infrastructure and Equipment

Our own manufacturing facilities with modern machinery, own test laboratory with shaker, pyroshock test facility, thermal-vacuum chamber, Center of Gravity test facility, Thermal chamber, clean room ISO8, Attitude Control System test facility for small satellite,   measuring laboratory for quality assurance

Certification

DIN EN 9100:2100

Customers

Airbus, Thales, OHB, Rolls Royce, Cern, ESA,TESAT Spacecom, RUAG,DIEHL Aerospace, TU Berlin, Helmholtz Zentrum Berlin, Max Plank Institut, Jena Optronik, Cosine; Ferdinand Braun Instititut, DESY, RWTH Aachen, First Sensor, Jenoptik, Berliner Glas, Picoquant, Vialight, Axelspace

Missions

Astro- und Feinwerktechnik Adlershof GmbH

2020

STEP

Reaction Wheel 90 – RW to control satellite attitude
2019

H2Sat Heinrich-Hertz

GermanTelecommunications satellite mission

Fraunhofer On-Board Processor (FOBP) – reconfigurable on-board processor (OBP) for communication applications
KERAMIS GEO (Ceramic Microwave Circuits for Satellite Communication)
2019

Sentinel 4 on MTG

Earth observation

Mechanical Ground Support Equipment (MGSE)–> Handling of optical instrument Sentinel-4 UVN
2018

Esail

identification and tracking of seafaring vessels on Earth

PanelMechanism – Gyros, ADCS I/F units, Magnetometers, Reaction Wheels und GPS
2017

BepiColombo

Europe´s mission to Mercury

MERTIS (Mercury Radiometer and Thermal Infrared Spectrometer) – MERTIS, imaging spectrometer for surface investigation of Merkur
2017

DEOS

key technologies to find, approach, catch and dispose the satellite

Subsystem structure
2017

Solar Orbiter

Satellite to explore the sun from nearest possible distance

Spectrometer/Telescope for Imaging X-rays (STIX) for observation of X-rays
2016

Baumanets 2

Experimental satellite for On Orbit Verification of new technologies

Reaction Wheel 90 – RW to control satellite attitude
2016

BeeSat-4

Space Verification of technologies for picosatellites

Reaction Wheel 1 – RW to control satellite attitude
2016

BIROS

ACS, Technology demonstration

Reaction Wheel 90
Reaction Wheel 90; AGS-1 – RW90 and high integrated rate sensor AGS-1 to control satellite attitude
2016

ESEO

measure radiation levels and test technologies for future missions

Reaction Wheel 90 – RW to control satellite attitude
2016

Nano-JASMINE

Infrared exploration, tasks of astrometry

Reaction Wheel 1: RW1 – RW to control satellite attitude
2016

SEAM

3U CubeSat nanosatellite for measurements of magnetic and electric fields in the Earth ionosphere.

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle
2016

WNISAT-1R

nanosatellite for north arctic routes and atmosphere monitoring

Reaction Wheel 90: RW to control satellite attitude
2015

GOMX-3

evaluate components in space

Reaction Wheel 1 and TPL
Reaction Wheel 1 and TPL – RW to control satellite attitude and TripleSatelliteLauncher to ensure the safety of the CubeSat and protect the launch vehicle
2015

Tianwang-1

CubeSats constellations for space networking and communication experiments

Reaction Wheel 1 – RW to control satellite attitude
2015

TUPEX-5

parabolic flight campaign of TU- and process measurement datas

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle
2015

TW-1 Mission

Chinesische Tianwang-1 Satelitenkonstellation zur Orbitkommunikation

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle
2013

BeeSat-2

Space Verification of technologies for picosatellites

Reaction Wheel 1 – RW to control satellite attitude
PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle
2013

BeeSat-3

Space Verification of technologies for picosatellites

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle
2013

OPTOS

Demonstration new technologies in spacecraft development

Reaction Wheel 1: RW to control satellite attitude
2013

SOMP

Technology Verification and amateur radio satellite of the Techniche Universität Dresden, which is built to the 1U-CubeSat form factor; measurement of atomic oxygen of the upper atmosphere

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle
2013

UWE-3

experimental satellite; system expansion to attitude control system, test of soft- and hardwaredesigns

Reaction Wheel 1 – RW to control satellite attitude
2013

WNISAT-1

nanosatellite for north arctic routes and atmosphere monitoring

Reactionwheel 1 – RW to control satellite attitude
2010

TET-1

On-Orbit-Verification (OOV)

Reaction Wheel 90 – RW to control satellite attitude
2009

BeeSat-1

Space Verification of technologies for picosatellites

Reaction Wheel 1: RW to control satellite attitude
PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle
2009

ITÜp-Sat1

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle
2009

Swiss-Cube

Launch of a new swiss communication system with satellite and ground station

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle
2009

UWE-2

experimental satellite; system expansion to attitude control system, test of soft- and hardwaredesigns

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle
2007

LAPAN-TubSat (2005)

Earth observation Satellit of TU berlin and Indonesian space agency LAPAN

Ground Support Equipment / tailored transport container for a safe transport of satellite
2005

Venus Express

Mapping of the Venus

PFS Planetary Fourier IR Spectrometer – instrument for infrared spectroscopy; informations about the nature of atmosphere
2004

MFP Satellite

Multifunctional Plattform Satellite EADS

Developing of a solar array
2004

Rosetta

Comet chaser with Lander

MUPUS Thermal Mapper und ROLIS – measuring the mechanical and thermal properties of external comet layers
2003

Double Star

satellite based space mission by CNSA and ESA --> investigation of earth's magnetic field and the interaction with solar wind

Deployable Booms for satellites
2003

Mars Express

Complete mapping of Mars

PFS Planetary Fourier IR Spectrometer – instrument for infrared spectroscopy; informations about the nature of atmosphere
2003

Mars NetLander Mission

Exploration of Mars

studies with camera systems
2001

BIRD

infrared earth observation for fire fighting

Reaction Wheel 90 – RW to control satellite attitude
2001

MAROCSAT

satellite for research and earth observation

GSE (Ground Support Equipment) for small satellites / tailored transport container for a safe transport of satellite
1997

CASSINI Mission

Exploration of Saturn and it´s moons

Cosmic Dust Analyzer (CDA) – analysis of ice and dust grains in and near the Saturn system
1996

MARS ’96 Mission / Mars 8

Exploration of Mars

WAOSS Stereo Camera
PFS Planetary Fourier IR Spectrometer
1995

IRS-C Satellit

earth observation to support the national economy of India (agricultur, water resources, forestry...)

Festkörperspektroskopie (studies of material properties of solid states)
n.a.

ARTES 21

development support of communications satellites and satellites for earth observation and navigation

Panel Mechanism, Gyros, ADCS I/F units, Magnetometers, Reaction Wheels and GPS in TRITON Platforms
n.a.

ARTES 3-4

development support of communications satellites and satellites for earth observation and navigation

GPS Receiver – Global Positioning System
n.a.

CubeSat Deployer for small satellites

The PicoSatellite Launcher (PSL) family is designed to ensure the safety of the CubeSat and to protect the launch vehicle (LV)
n.a.

Deployable Booms for satellites

Deployable Booms for satellites
n.a.

EGSE

EGSE (Electrical Ground Support Equipment)
n.a.

Family of reaction wheels

product line of reaction wheels (RW1, RW35, RW90, RW150, RW250)for small satellites
n.a.

Gyro-System

The ASG-1 is a high integrated rate sensor for space applications
n.a.

MGSE

MGSE (Mechanical Ground Support Equipment)
n.a.

OGSE

OGSE (Optical Ground Support Equipment)
n.a.

Sensor systems for seismic reconnaissance

Sensor systems for seismic reconnaissance
n.a.

Solar panels

fold-out solar panel structures
n.a.

Test bed for rotation sensors /Test Beds and Apparatus Engineering

Test bed for rotation sensors /Test Beds and Apparatus Engineering
n.a.

Test Beds and Apparatus Engineering / ACSTest bed (Attitude Control System)

ACS Test Facility for the verification of micro and mini satellite busses
© Konzept Informationssysteme GmbH
Programmable Digital Current Regulator (DCR)

The Programmable Digital Current Regulator (DCR) allows to control the output current for different applications with high flexibility. Execution and control parameters can be defined unsing an intuitve operator interface and menu structure. The DCR will deliver the appropriate current curve for the indiviual current curve based on the defined parameters.

© Konzept Informationssysteme GmbH
PERIGEE

The desktop application PERIGEE has been developt for the high and complex requirements of space missions and helps project teams to cope with the high degree of complexity through the usage of modern UI concepts. Within short time the communication both among satellite components and between satellite and ground can be defined by using ECSS-E-ST-70-41C (PUS-C).

Verification & Test

- Software Verification
- Board Level Testing for On-Board Mass Memory Unit (MMU)

Unit Testing, Software Development

- Unit Testing of a performance analysis tool of the navigation system
- Development of a data extractor for NetCDF files

Validation, Check-Out & FV

- Validation of On-Board Computer
- Functional Verification of the Data Handling Systems (DHS)

Check-Out & FV, Software Development (OBSW), Unit Testing

- Check-Out & FV
- Development of Central Software Modules
- Unit Testing
- EFM/PFM RTE Bench Commisionin

Advanced Closed Loop System (ACLS)

Requirements Engineering and Risk & Failure Analyses (FMEA)

Software Development (UI)

Development of UI components and tools for the Mission Operation Center (MOC)

Software Development (RTS), Check-Out & FV

- Development of the On-Board Computer Simulators
- Development of RTS modules
- Check-Out & FV

Test Management, Validation, Check-Out & FV

- Test Management for Validation of Onboard Software und Real-Time Simulator
- Support of OBSW IST

Software Development

Software Development for System Database

Check-Out & FV, Software Development (RTS)

- Functional Verification of the Drag Free Attitude Control Systems (DFACS)
- Entwicklung von Softwaremodulen für die Real-Time Simulator (RTS) Umgebung

Software Development (SCOE, EGSE)

- Development of SCOE Software for Instrument Simulator
- Development of a Source Packet Analyser

Software Development (UI)

Front-End (UI) Development of the video data management system for the Electromagnetic Levitator (EML) in the Microgravity  User  Support  Centre (MUSC)

Software Development (KARS)

Development of the On-Board Software Prototype "Controller for autonomous Space Systems (KARS)"

Check-Out & FV

Functional Verification on Satelliten System Level

Software Development (RTS)

Development of Software Modules for the  Real-Time Simulator (RTS) Environment

Check-Out & FV, Software QA

Functional Verification on Satelliten System Level

Software Development, Check-Out & FV

Software Development of the Payload Module (PLM) Simulator

Software Development (RTS)

Development of Software Modules and Drivers for the  Real-Time Simulator (RTS) Environment

WISDOM antenna

The actual antenna geometry (copper) is introduced after the laminate manufacturing by etching.

Check-Out & FV, Software Development (OBSW, EGSE), Software QA, Unit Testing

- Support of SVT, OST and SFT of the Data Handling System (DHS)
- Development of Payload Controllers in Central Software (CSW)
- QA and Unit Testing for CSW and MMUF software
- Development of Tools for AIT and Check-Out

Support for Structures Analysis for primary structure

A Power Distribution Unit distributes electrical energy into a complete instrument or satellite

Battery Management System – A Battery Management System organises charging and discharging of a battery with the feature to enable longest possible lifetime of the battery in orbit.

-Translate- Over Temperature External Electronics Box for ISS (Übertemperaturschutzschalter)

-Translate- Hochspannungsversorgung für Elektronenstrahlmikroskope

ASP-Equipment entwickelt und fertigt eine flüssigkeitsgekühlte Power Supply Unit für ein ultragenaues Elektronenstrahlmikroskop mit Anbindung an einen CAN Bus. Die Leistung beträgt 1500W. Zahlreiche Ausgangsspannungen bis 20.000V.

-Translate- High Power Amplifier für das Bodensegment

ASP-Equipment entwickelt und produziert High Power Amplifier für das Bodensegment im Ku Band, DBS Band und Tri-Band (C, X, Ku) .

-Translate- Batteriemanagementsysteme

Entwicklung eines ITAR freien autarken Batteriemangementsystem (BMS). Das BMS wird heute in Stückzahlen von etwa 50 Einheiten pro Jahr exklusiv an einen namhaften europäischen Hersteller für Raumfahrtbatterien geliefert.

– Translate- High Power Amplifier für das Bodensegment

ASP-Equipment entwickelt und produziert High Power Amplifier für das Bodensegment im Ku Band, DBS Band und Tri-Band (C, X, Ku).

– TRANSLATR – DC/DC Converter für Sternsensoren

ASP-Equipment entwickelt und produziert DC/DC Converter für Sternsensoren als Produkt in Stückzahlen von etwa 40 Stück pro Jahr für einen führenden deutschen Ausrüstungshersteller.

– TRANSLATION – DC/DC Konverter für die Energieversorgung in Luftfahrzeugen

ASP-Equipment entwickelt und fertigt einen Hochleistungskonverter für die Energieversorgung in Luftfahrzeugen für Brennstoffzellen bis 150.000W.

A Latching Current Limiter operates as a electronic fuse in order to protect a particular assembly

Test module

Test environment for in orbit verification of Point-of-Load voltage converter based on the SPPL12420RH chip

On-board Computer – Satellite’s Central Computer

On-board Computer – Lander’s Central Computer

On-board Computer

Satellite's Central Computer

Mass Memory Unit – Instrument Control Unit

- Receiving, formatting and storing of science data
- Instrument Control

Crypto System

On-board and Ground Crypto System

Crypto System (On-board and Ground Crypto System)

Crypto System – On-board and Ground Crypto System

Data Handling Unit – Receiving and formatting of science data

Ground Equipment – Special Check-Out Equimpent for the crypto system

Payload Data Handling Unit – Design & Development of the Mass Memory Unit

Ground Crpyto (De-/Encryption Unit of the ground segment)

Command & Data Processing Unit – Control the ICI Instrument, receiving data from the instrument as well as supplying internal and external power sources

Mass Memory – Receiving, formatting and storing of science data from multiple instruments

v5_toolcenter als Ergänzung cb-cert

Zeit und Kosteneinsparung, Qualitätsverbesserung in der Konstruktion

Context based certification.
Software zur ganzheitlichen Darstellung von komplexen Prozessen inklusive Resourcen, Standards, Rollen, Properties.
Basis für Riskmangement und Zertifizierungen.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magnetometer

The Magnetometer is an instrument for measuring three-dimensional magnetic fields. It is based on the fluxgate principle, using three independent ring-core sensor heads for each orthogonal axis.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

Magentic Torquer

These devices interact with the Earth’s magnetic field and create control torque, which can be adjusted to the required value. Combined with one or more reaction wheels, they provide all the control you need to maintain your spacecraft’s attitude, from low-Earth orbit up to geo-stationary orbit. And, unlike thrusters, torquers do not need valuable consumables, are low power components and high reliable.

COSIMA

Mass spectrometer for analysis of dust particles in the immediate surroundings of the comet

Modelling and development of the communication channels, Data structure, data fusion and data evaluation in the central ground segment Visualization based on 3D geographical maps

Joint research project with:
Eureka: Sensor Technology, Telematics
DLR: Remote Sensing
University Würzburg: Pico-Satellites
Zentrum für Telematik e.V.: Satellite Network

RAMS Analysis

Execution of RAMS (Reliability, Availability, Maintainability, Safety) Analysis with focus on hazard analysis and FMEA.

Consulting SW development processes

Plans for software develoment, verification and verification, CM, design

Product Assurance Maintenance & Support Engineering


  • Definition of test concepts: test / integration / work instructions, circuit plans

  • First article inspections, acceptance tests

  • Equipment safety files

  • Operational Tests

  • Generation of verification documents, verification at hardware

  • RAMS calculations and analyses

  • Integrated Logistic Support / Logistic Support Analysis (ILS/LSA) plans

  • LORA, LCC

  • Technical Documentation

Verification for Security Aspects SW Engineering Management

Definition of Security Test Cases covering all security aspects on system level
Analysis of impact of security requirements, accreditatin, certificatin
Definition and execution of security test procedures

External and internal MLI for the S-4 instrument

Instrument Radiator Assembley

MagBoom MLI

MLI for magnetometer

Contactless health monitoring via piezo-actuators

sensors and RFID Technology for automotive and aircraft industry

Lightweight, deployable, portable ground antenna

for high data rates, usable for various applications like first aid, journalsm, expeditions, military

3D-Printing, Additive Layer Manufacturing, Design Guidelines, Analysis Guidelines

Antennas for Satellite & Ground Applications

Deployable Structure Subsystems
Lightweight CFRP Structures
Thermal Hardware
MLI
New Materials

Ka-Band antennna

Secondary structures for STCS

MGSE for PLM Batch 1 MGSE

MGSE for the sunshield

MLI for the sunshield

MLI and sunshield for the antenna

Ka-Band North Beam Antenna

Radiators for the Sentinel 4 Instrument

MLI for the Sentinel 4 Instrument

MLI for the MTO mirrors

MLI for the thermal dummies

MLI for an external instrument

MLI for the telescope

Optical Baffle

Instrument Structure Engineering Support

MLI for FAD Mechanism

MLI for the complete Telescope

Multilayer Insulation

MLI for Cassis Instrument

Multilayer Insulations; HPS equipped the whole EDM Module inside and outside with MLI and will land with 10kg MLI on Martian surface

MLI for EDM Entry Module

Multilayer Insulations; HPS equipped the whole EDM Module inside and outside with MLI and will land with 10kg MLI on Martian surface

MLI for an external instrument

Thermal protection of camera housing

Protection of an external camera against heat from aeroflux during launch

Ceramic structures and mirrors

ECM has succesfully manufactured structures and mirrors in small series up to 250 parts up to
size of 2m.

Camera Structures for Astronomy Telescopes

Our products increases the perfomance also for ground based optics and telescopes. Example: Large Survey Synoptics Telecope (LSST)

Mirrors for large space mirror from room temperature RT down to Cryo

Star Sensor Bracket

Star Sensor Bracket

Pointing Mirror (MERTIS)

Focal plane

Camera Structure

All Cesic Telecope

All Cesic Telecope

3U sized cubesat

Berlin Space Tech has developed an integrated attitude control system for the satellite.

power and interface unit

redundant gyro system (IMU)

redundant star tracker

Satellite System

80 kg micro satellite carrying 3 payloads. Two hyper spectral cameras (VNIR & SWIR) and one high resolution real time video camera.

ITAR freier COTS DC/DC Converter

Development, Qualification and Manufacturing of the converter

The converter is based on a unique ASP-design with the effect of a high efficiency without use of ITAR-restricted parts.

SMT assembly of PCB´s according to ESA standards

The assembly line for SMD manufacturing is verified according to ECSS-Q-ST-70-38C through ESA. ASP-Equipment is enabled to manufacture PCB´s for Flight Models

DC/DC Converter – A DC/DC-Converter converts electrical voltage from a particular level to a different level

Auxiliary Power Supply – An auxiliary Power Supply converts electrical voltage from a particular level to a different level

High Voltage Power Supply – A high voltage power supply provides high precision high voltage in the range of several thousan volt to a scientific instrument

DC/DC Converter – A DC/DC-Converter converts electrical voltage from a particular level to a different level

COTS Converter (Commercial off the shelf ITAR free converter)

PDU – A Power Distribution Unit distributes electrical energy in a complete instrument or satellite

DC/DC Converter – A DC/DC-Converter converts electrical voltage from a particular level to a different level

Hocheffizienter Hochstromkonverter – A high-efficient high-current converter is optimized to provide a comination of low voltage and high currents to digital equipment featuring a high efficiency factor

Battery Management System – A Battery Management System organises charging and discharging of a battery with the feature to enable longest possible lifetime of the battery in orbit

DC/DC Converter – A DC/DC-Converter converts electrical voltage from a particular level to a different level

Instrument Power Unit Power Distribution Unit – Ultra accurate power supply and distribution system for a complete optival high-precision instrument A Power Distribution Unit distributes electrical energy to a number of equipments.

Battery and Battery Management System – A Battery Management System organises charging and discharging of a battery with the feature to enable longest possible lifetime of the battery in orbit.

DC/DC Converter – A DC/DC-Converter converts electrical voltage from a particular level to a different level

Power Supply Unit – A Power Supply Unit provides conditioned electrical power to an equipment

DC/DC Converter – A DC/DC-Converter converts electrical voltage from a particular level to a different level

High Voltage Multiplier – A high voltage multiplexer generates from a typical bus-voltage an output voltage of several thousands volts.

DC/DC Converter – A DC/DC-Converter converts electrical voltage from a particular level to a different level

Capillary Channel Flow Electrical Subsystem for ISS (Power Supply for an experiment)

Electronic Power Conditioner (EPC) for Space Communikation – An EPC provides the electrical power for a Communication Tube (eg. TWT, Klystron). The output voltage varies between 20 Volt and 20.000Volt

Battery Management System – A Battery Management System organises charging and discharging of a battery with the feature to enable longest possible lifetime of the battery in orbit.

DC/DC Converter – A DC/DC-Converter converts electrical voltage from a particular level to a different level.

DC/DC Converter Electronic Power Conditioner – converts electrical voltage from a particular level to a different level.

Power Conditioning Unit – A Power Conditioning Unit provides stable electrical energy to a number of equipments.

DC/DC Converter – DC/DC-Converter converts electrical voltage from a particular level to a different level

Software development – Database backend and asteroid trajectory propagator

Software development – Development of tools for system concept analysis, clean space, pointing error engineering, FDIR, launcher GNC

Launcher selection and orbit injection

Support GNC system – De-orbitation and risk analysis, visualization GNC console, real-time camera/LIDAR simulation

Mission analysis, trajectory optimisation, life time prediction

AOCS SCOE (special check-out equipment for AOCS)

S-Band TMTC unit

RF-Communications Equipment for remote Control (256 kbps Uplink) and Video-/ Data Downlink (4 Mbps)

© SpaceTech
ISS Demonstrator, ICARUS Animal Tag

The ISS Demonstrator consists of Antennas für transmission and reception and the required electronics. The animal tag consist of an extremely light tag, including GPS, Solar array, battery and micrelectronis.

© DLR
Frequency reference unit (FRU)

The FRU provides the frequency references for the oscillator and the optical parametrical oscillator of the pulsed laser source. It contains several diode lasers, a methane cell, a wavemeter and the associated electronics.

© ESA
Structure and mechanism of the calibration subsystem – Mechanical structure with motordriven filter wheel mechanism and baffles

Sunhield with solar generator (SSH)

The Sunshield protects the telescope from the thermal, visible and infrared radiation of the sun and provides the required operational power.

© ESA
Solar generators with deployment mechanisms

3 Solar generators with deployment mechanisms, including HDRM

OGSE (Optical Ground Support Equipment)

Im Bereich des Optical Ground Support Equipments bietet die Astro- und Feinwerktechnik Adlershof GmbH attraktive Lösungsbausteine aus erfolgreichen Projekten zu der Gestaltung von Messplätzen.

© NASA EOS
Laser Ranging Interferometer (LRI)

Retroreflector, Optical Bench, Instrument AIT BUS: Primary Structure, Tertiary structure, Antenna Boom, MGSE

LRI: High precission optics and highly stable optomechanics (CFRP, Zerodur, titanium) for beam shaping, routing and detection
BUS: highly stable CFRP Structures and a deployment mechanism.

Developing of a solar array

Deployable Booms for satellites

As the outer segments and the complete boom fold out separately, there are only two degrees of freedom during each fold-out procedure; only three degrees of freedom in the case of spin-stabilized satellites. The design principle of the Double Star boom can be adapted to a variety of spinstabilized satellites. A concept for an active, springdriven deployment, using redundant deployment springs at the hinges is available for non-spinning satellites. Both versions can be realized either with one or two boom segments. The length of the deployed boom can be extended to more than four meters, depending on the dimensions of the spacecraft and on the mass to be deployed.

© SpaceTech
System engineering and part procurement support

Solar generators, Coldgas propulsion system, Satellite primary structure

Ground Support Equipment / tailored transport container for a safe transport of satellite

© Artist's concept of the Gokturk 2 satellite. Credit: Turkish Aerospace Inc.
Solar generators with deployment mechanisms and pyrodrive modules

High resolution remote sensing satellite, resolution 2.5 m(PAN),5 m(MS)

Solar generators with deployment mechanisms and pyrodrive modules

Spectrometer/Telescope for Imaging X-rays (STIX) for observation of X-rays

Subsystem structure


  • Mechanism

  • Thermal control

  • Energy supply

  • Attitude control

  • AIV of client satellite

  • GSE

© Korea Aerospace Industries Ltd.
Deployment mechanism of the solar generators

High resolution earth observation for GIS, 0.7 m GSD

The patented deployment mechanisms of the solar generators are optimized for high torque, low friction and low shock loads

PanelMechanism – Gyros, ADCS I/F units, Magnetometers, Reaction Wheels und GPS

Mechanical Ground Support Equipment (MGSE)–> Handling of optical instrument Sentinel-4 UVN

VDI2230:2014

Systematic analysis of highly loaded bolt connections



ECSS-E-HB-32-23A

Threaded Fasteners Handbook

Product development

Design and analysis, full qualification campaign

Development of Reliability Approaches, Case Study

Requirments Definition, Trade-Off Studies, Structures and Thermal Analyses

Test Prediction, -plan,  -campaign and -correlation

Structures and Thermal Analysis payload equipment

Structures and Thermal Analysis payload equipment

Structures and Thermal Analysis payload equipment

Structures and Acoustic Analysis for primary structure

Support for Structures Analysis for primary structure

Structures and Acoustic Analysis for primary structure

- Mechanical test planning and
on-site test lead engineering (including whole S/C)

Software Engineering Consultancy

Coding, test and debugging on various software modules

System Test of Precise Time Facility (PTF) at GCC Oberpfaffenhofen

The PTF generates the Galileo system time. We developed the Systrem Test Specification and conducted a software based system test of the PTF Oberpaffenhofen.

IRS Instrument Control Unit System Software Engineering Consultancy

On-board Software for control of the IRS payload, an infrared telscope and interferometer, plus auxiliary devices

Gravity CIAO

Gravity CIAO is a second generation instrument for the Very Large Telescope Interferometer (VLTI), designed to enhance the near-infrared astrometric and spectro-imaging capabilities of VLTI. KTO has analysed the optical performance of the instrument.

Erosion Deposition Monitor

The EDM diagnostic monitors the chamber walls of the ITER fusion reactor for surface erosion and/or material deposition after plasma operations. For this non-contact in-situ surface analysis the system is relying on a dual beam speckle interferometry. KTO is responsible for the system design as well as for optical and opto-mechanical design.

H-Alpha and Visible Spectroscopy (H-alpha)

As an optical diagnostics, the H-alpha instrument measures emissions from hydrogen isotopes and impurities in the ITER fusion process. KTO is responsible for the system design as well as for optical and opto-mechanical design.

Software for calibration and alignment

Definition of line shape stability and optical alignment requirements

Straylight analysis of the SSH baffle

Antennenfrontends / LC-Phasenschieber / Verteilernetzwerke / Synthesizer


  • Entwicklung von agilen antennenfrontends und Komponenten für mobilen Satellitenkommunikation

  • HF-Verteilernetzwerke und HF-Komponenten für Satellitenpayloads

IOV des “flexiblen DOCON” (Down-Converter von 30 auf 20GHz)

Synthesizer-Experiment mit Synthesizer-, Mischer-, Verstärker-und SPDT-Schalter-Modulen in LTCC.

Materials and processes

The manufacturing technologies developed for aerospace projects provide the INVENT GmbH with the means for customer-specific manufacturing of lightweight components and high performance materials that enable extreme conditions like temperature, stiffness of thermal expansion in correlation with weight minimization. Therefor weigth- and performance-optimized materials from aerospace application are employed. The corresponding processes have been developed in the scope of aerospace programmes and, thus, are available for terrestrial applications.

Optical Bench for LINC-NIRVANA of the LBT (Large Binocular Telescope)

For the interferometric camera the optical bench was manufactured as large scale high precision mounting table from Aluminum/CFRP-sandwich platform and CFRP-wound struts with a maximum allowable deformation of 0.01 mm

Support structure for particle accelerator

etc. are employed for the construction of particle accelerators, as the required lightweight design can be combined with low thermal expansion.

Antenna reflectors

Combining latest premium materials from R&D in an optimised sandwich design enables a significant performance increase compared to traditional aluminum construction methods. CFRP/CFRP reflectors are therefore able to transmit higher data speeds at a lower antenna weight even under extreme space conditions with temperatures of +/-150°C.

STANT (2009-2011)

FLANT (2012-2015)

HISST (2009-2011)

HISST2 (2011-2012)

H2KAR (2012-2018)

Heat transfer plate and Magnetic torquer frame

INVENT designed and manufactured magnetic torquer (air coil) frames for the SWARM satellites. Further on, thermally high conductive CFRP plates made of K13 pitch fibre were made.

BELA (BepiColombo Laser Altimeter) support structures

The BELA SPU, a straylight protection unit for the BepiColombo laseraltimeter, was designed, analysed and manufactured by INVENT. The key challenges for this unit were the very small dimensions, severe mass requirements and the Gold plating on CFRP sandwich parts.

ARA reflector – INVENT will manufacture the Euclid HGA reflector assembly

Support structures

INVENT is in charge of the development and manufacturing of Meteosat Third Generation (MTG) support structures which includes the helium tank, mid thruster, reaction wheel and panel supports.

Thermal Plate

INVENT manufactured thermal plates from highly conductive CFRP (featuring K13 pitch fibre) for the GRACE-FO satellite.

Aluminum sandwich panels

INVENT manufactured Aluminum/Aluminum sandwich panels incl. all inserts for the FormoSat 5 satellite.

Aluminum sandwich panels

INVENT manufactured approx. 70 Aluminum/Aluminum sandwich raw panels for the first 14 Galileo satellites.

CFRP waveguides and thermally high conductive parts

Following a 3 year development INVENT manufactures raw CFRP waveguides and thermally high conductive CFRP parts for the SAR antennas of TerraSAR-X, Tandem-X and Sentinel 1A + B since 2004. Within these projects INVENT made more than 5000 CFRP parts for several QMs and FMs.

CFRP waveguides and thermally high conductive parts

Following a 3 year development INVENT manufactures raw CFRP waveguides and thermally high conductive CFRP parts for the SAR antennas of TerraSAR-X, Tandem-X and Sentinel 1A + B since 2004. Within these projects INVENT made more than 5000 CFRP parts for several QMs and FMs.

CFRP waveguides and thermally high conductive parts

Following a 3 year development INVENT manufactures raw CFRP waveguides and thermally high conductive CFRP parts for the SAR antennas of TerraSAR-X, Tandem-X and Sentinel 1A + B since 2004. Within these projects INVENT made more than 5000 CFRP parts for several QMs and FMs.

Isostatic mount

In the frame of the Herschel project INVENT developed and built mechanically high-stressed, but thermally isolating, isostatic mounts, made of CFRP & aluminum. Further on, a thermal strap out of copper and CFRP could be developed. All components work under cryogenic temperatures between 2 and 4 K.

Aladin baffle trusswork

The ALADIN sun baffle consists of a CFRP strut framework. Each strut features CFRP inserts (to cover CTE mismatch) for the strut connection.

STSA and IOU suspensions

The IOU (Instrument Optical Unit) and the STSA (Star Tracker Sensor Assembly) supports were designed as CFRP/AlBeMet and Titanium/Invar bipods. The major design driver was the required mechanical performance going simultaneously with a small thermal conductivity and expansion.

DMA boom

The deployable mast assembly (DMA) consists of a CFRP boom with titanium fittings, which support the Rover's stereo camera system.

OIMS primary structure, TSA hexapod

The Sentinel 4 UVN OIMS consists of CFRP sandwich panels, monolithic CFRP, GFRP and metallic parts. The Nadir Baffle (service temp. 140 °C) incl. CFRP vanes is fully bonded by adhesive. The TSA hexapod structure is made of CFRP struts incl. Titanium fittings.

Primary structure

The eROSITA structure is mainly built out of adhesive bonded CFRP/Aluminum sandwich panels for the optical bench and Aluminum/Aluminum sandwich panels for   radiators. Further on, CFRP struts (hexapod for opt. bench), GFRP struts for the radiator truss work and monolithic CFRP parts have been developed and assembled by INVENT.

Primary and tertiary structures

The ExoMars load-bearing structure of the orbiter mainly consists of CFRP & aluminum sandwich with
>5300 metallic inserts, heterogeneous aluminum cores, structural and thermal doublers, grounding and painting   (next to the central tube - not by INVENT). Additionally various CFRP, aluminum and titanium brackets for reaction wheels, LGA, He-tanks and star trackers were developed and manufactured

Development and porting of Earth observation data processing software to various languages and platforms

Responsibility for operations engineering for various onboard systems and for the development of ground software.

Preparation and execution of ground, flight and mission operations. Constellation management.

Specification, design, development, integration, test, operation and sustaining engineering of the control center and communications infrastructure

Verteilernetzwerk 1 auf 32 für das Antennensystem

Class-US (ZIM cooperation project)

Development of a non distructive inspection device for measuring and classifying multi-layer bonding connecitons using ultra-sonic.

Optimized fibre reinforced plastic fuselage shell (SAB Project)

Development and test of innovative load and cost optimized structural concepts for stiffener elements and fuselage shells considering the specific local load situation and efficient manufacutring

3D-Preform Test

Imaging eddy current inspection and numerical simuation of 3D deformation behavior for CFRP layups

HTS tasks: design and manufacturing of a test setup for inspecting dry layups and simulation and prediction of results of NDI

PICASSO (EU FP7 Projekt)

PICASSO - imProved reliabIlity inspeCtion of Aeronautic structure
through Simulation Supported POD
HTS tasks: Determination of POD-curves (Probability of Detection) by simulation approaches for aeronautic applications

Coosi – Cool Sensor Integration – Robust component lintegrated US-Sensor systems

Integration of health monitoring sensors for monitoring of CFRP structures in aircraft

HTS tasks: concept definition of ultra sonic sensor integration; simulation; tests and NDI

Feasibility Study for Magneto-resistive angular sensors for space applications

Feasibility study and market assessment for the potential use of magneto-resistive angular sensores for spacecraft mechansims

Deployable Membrane and Support to Deorbiting Subsystem

Development of a large, thin, yet robust membrane for deacceleration and deorbiting of post-operational spacecraft from LEO orbits

Secondary Payload Unit “Apollon”

Compact, flexible to use, lightweight secondary payload unit enabling global atomic oxygen measurements in low Earth orbits

Ultra Light Deployment Mechanisms

Passive, lightweight, yet very stiff and temperature stable CFRP deployment mechanisms for segmented telecom antenna

Multi-axial deployment and pointing mechanism (MEP)

Multi-axial deployment and pointing mechanism for telecom and telemetry antenna on GEO spacecraft

Engineering Support for structual design and analysis for the NIR SO

Mechanical and thermo-mechanical analyses for the structural design of the NIR SO

Development and Engineering support for Focal Plane Assembly and Telescope Optics

System Engineering Support, Finite Elemente Simulation and AIT-Management for Telescope Optics and Focal Plane Assembly

Development and Support during Production of Core Sample Handling System

Handling mechanisms for the delivery of a core sample from the drill unit to the ExoMars rover internal analytical laboratory drawer

3 Instrument mechanisms für optical payload

Shutter and Calibration Mechanism
SWIR Switch Mirror
Full Aperture Diffursor

High performance mechanisms for sun and dark calibration an for switching to the redundant detector

Bonding jig for magnetometer boom

High precision manufactured bonding jig for the production of the CFRP magnetometer boom with a total length of about 3 m

High Gain Antenna Deployment and Pointing Mechanism and design of Tri-Pod

Deployment and pointing mechanisms for main antenna, enables pointing along to axes to ensure communication and telemetry contact with Earth

Complete electrical, mechanical harness development, manufacturing and installation

- Electrical & harness engineering (EM/FM)

- Drawer design support

- EM/FM harness manufactruring

- GSE

 

Harnesses, Adaptor, GSE

- Test harness

- TB/TV Test harness

- Umbilical adaptor harness for FM

- External harness

- DBAS Adaptor for FM

- GSE complete

Harnesses, Mockup

- Instruments FM Harness

- Complete instruments test harness

- Mockup

Harnesses

- EFM Harness

- EGSE Harness

Harnesses

- MPO-ETB Initial harness

- MTM-ETB Harness

- RTE Extension harness (EM/PFM)

- ATB Harness

MGSE (Mechanical Ground Support Equipment)

MGSE Transport Container for Small Satellites / Instruments

The container system of Astro- und Feinwerktechnik Adlershof GmbH is individually suited to the size of your satellites or instruments. Our assurance of safe transportation goes without saying.
With these premises, we offer you optimal solutions for your transportation needs


  • hermetically sealed inner areas

  • defined gas atmospheres

  • vibration-reduced transportation

  • data connections for data recording during transport

  • adapters for transport systems (Euro / ISO pallets, lifts)

Deployable Booms for satellites

As the outer segments and the complete boom fold out separately, there are only two degrees of freedom during each fold-out procedure; only three degrees of freedom in the case of spin-stabilized satellites.
The design principle of the Double Star boom can be adapted to a variety of spinstabilized satellites. A concept for an active, springdriven deployment, using redundant deployment springs at the hinges is available for non-spinning satellites.
Both versions can be realized either with one or two boom segments. The length of the deployed boom can be extended to more than four meters, depending on the dimensions of the spacecraft and on the mass to be deployed.

Complete electrical, mechanical harness development, manufacturing and installation

- Electrical & harness engineering (EM/FM)

- Harness MAIT for test & flight harness

- Gesamtsyst.-Verkabelung und -installation (EM/FM)

- Subsystem harness & system integration (EM/FM)

- EMC harness, test adapter & break out boxes

 

fold-out solar panel structures

a panel structure consisting of 3 panels, development of a fold-out system with four exact constructional replicas and completely independent solar panels for small satellites

ACS Test Facility for the verification of micro and mini satellite busses

The ACS Test Facility includes:


  • air bearing table with a platform allowing free 360° rotation around the vertical axis and between 20° and 30° around the horizontal axes

  • high precision in-orbit earth magnetic field simulation

  • electronic center of gravity (CoG) calibration

  • adjustable and movable sun simulation

  • WLAN command line

  • safety mechanisms for save operation and satellite mounting

  • power supply and distributio

The PicoSatellite Launcher (PSL) family is designed to ensure the safety of the CubeSat and to protect the launch vehicle (LV)

the primary payload and other satellites to be launched. After the safe transportation of the device into the orbit, a deployment with a high reliability and a low spin rate is achieved by patented design principles. After a successful deployment, a telemetry signal is available for the launch provider.


The family of CubSat Deployer consists of the Single Picosatellite Launcher (SPL), the Double Picosatellite Launcher (DPL) and the Triple Picosatellite Launcher (TPL). The SPL is used to deploy one 1U CubeSat. The DPL is used to deploy one 2U CubeSat or two 1U CubeSats etc. The product line relies on a modular and redundant design

The ASG-1 is a high integrated rate sensor for space applications

It is designed especially for small satellite applications. Outstanding features are low mass and size as well as the low energy consumption. The ASG-1 measures angular increments in three orthogonal axes. Using these angular increments, the rotation speed of the satellite and the relative position of the satellite in relation to a starting point are calculated.

Transfer of space know how and technologies in terrestrical applications

product line of reaction wheels (RW1, RW35, RW90, RW150, RW250)for small satellites

reaching from the world's smallest commercial reaction wheel RW 1 (10-4 Nms) to the RW 250 (4 Nms). The reaction wheels RW 90 and RW 1 are already flight proven. Four reaction wheels RW 90 come into operation at the small satellite TET-1 (launch in 2012).  State of the art feedback systems in combination with model based controller algorithms making smart reaction wheels the ideal solution for zero-momentum attitude control strategies because these reaction wheels will operate with high accuracy as well in the "low wheel speed region". Astro- und Feinwerktechnik Adlershof GmbH

Sensor systems for seismic reconnaissance

Test bed for rotation sensors /Test Beds and Apparatus Engineering

Test bed for rotational speed sensors. The test bed allows new combinations of measuring tasks. Therefore the sensors can be checked under different application scenarios.

Main functions:
• wide speed range
• high temperature loads
• Rotational vibrations of the code wheel
• maximum air gap
• air gap jumps
• free positioning of the sensors in four axes in relation to the code wheel

KERAMIS GEO (Ceramic Microwave Circuits for Satellite Communication)

Concept study for a future logistic van, driving semi-autonomous with electric drive

and an electric double-sliding door Concept, Planning, Execution and Presentation of the System Failure Analysis – due to the operational concept and scenario Risk and Hazard Analysis and System Failure Modes and Effects Analysis

Fraunhofer On-Board Processor (FOBP) – reconfigurable on-board processor (OBP) for communication applications

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle

ESABASE2 Space Environment Analsyis Tool

Development of an application to analyse the mission risk against space debris particles and meteoroids.
etamax has developed the tools and also provides analysis support to industry to demonstrate compliance with space debris standards and requirements.

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle

Implemetation of GUI testa utomation tools. Automation of manual tests.

GUI Test automation system for SCOS 2000 Mission Control System.
The System provides the capability to simulate manual inputs into the GUI.
This allows the exact repetition of tests needing human interaction

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle

PSL (PicoSatelliteLauncher) – family of PicoSatellite Launcher (PSL) ensure the safety of the CubeSat and protect the launch vehicle

communications relay for data transmission among satellites and UAVs and ground stations

European constellation of state of the art GEO satellites that will relay information and data between satellites, spacecraft, UAVs, and ground stations.

Reaction Wheel 90 – RW to control satellite attitude

Weather data

Wettersatelliten betrieben von EUMETSAT mit dem Hauptinstrument Hauptmessinstrument SEVIRI (Spinning Enhanced Visible and InfraRed Imager)

Reactionwheel 1 – RW to control satellite attitude

Reaction Wheel 90 – RW to control satellite attitude

Reaction Wheel 90 – RW to control satellite attitude

Reaction Wheel 90; AGS-1 – RW90 and high integrated rate sensor AGS-1 to control satellite attitude

Reaction Wheel 90 – RW to control satellite attitude

complete manufacturing of MTG cable harness – harness assembly of all components/ units (sensors, actuators) with power und data management units

Reaction Wheel 90 – RW to control satellite attitude

Reaction Wheel 1 and TPL – RW to control satellite attitude and TripleSatelliteLauncher to ensure the safety of the CubeSat and protect the launch vehicle

complete manufacturing of Galileo cable harness – harness assembly of all components/ units (sensors, actuators) with power und data management units

Reaction Wheel 1 – RW to control satellite attitude

Reaction Wheel 1 – RW to control satellite attitude

Reaction Wheel 1 – RW to control satellite attitude

Reaction Wheel 1 – RW to control satellite attitude

Reaction Wheel 90: RW to control satellite attitude

CAD Harness Design for EDRS-C – complete CATIA V5 design of system harness loom segregation loom design DMU bundle routing mass assessment, COG assessment, as build adaptation between DMU and physical Mock-up for applications in high security terrestric environments

Reaction Wheel 1: RW to control satellite attitude

Reaction Wheel 1: RW1 – RW to control satellite attitude

Reaction Wheel 1: RW to control satellite attitude

GSE (Ground Support Equipment) for small satellites / tailored transport container for a safe transport of satellite

MERTIS (Mercury Radiometer and Thermal Infrared Spectrometer) – MERTIS, imaging spectrometer for surface investigation of Merkur

Design of EDRS cable harness (MCAD) complete manufactuiring of cable harness – harness assembly of all components/ units (sensors, actuators) with power und data management units

PFS Planetary Fourier IR Spectrometer – instrument for infrared spectroscopy; informations about the nature of atmosphere

Panel Mechanism, Gyros, ADCS I/F units, Magnetometers, Reaction Wheels and GPS in TRITON Platforms

GPS Receiver – Global Positioning System

Propulsion System MICROJET

Microjet, developed by AIG (Aerospace Innovation GmbH) of Berlin, is a modularly designed propulsion system for Nanosatellites and Microsatellites based on the gas-resistojet-concept. It consists of a PST (Pressure Tank Unit) with nitrogen which is filled or drained, respectively, through a FDU (Fill and Drain), a FCU (Flow Control Unit) responsible for the control of correct propellant mass flow, as well as one or more THUs (Thruster Units). Each of these THUs contains a pulse valve and a nozzle for the actual thrust generation. Additionally, according to the definition of the Resistojet-concept, an electrical resistance-heating element might be applied for higher performance demands. The entire propulsion system is controlled by the PCU (Propulsion Control Unit), which can also be resigned of, if the satellite itself is capable to control the Microjet propulsion subsystems.

PFS Planetary Fourier IR Spectrometer – instrument for infrared spectroscopy; informations about the nature of atmosphere

Propulsion System AQUAJET

Aquajet is a small satellite propulsion system designed and developed at AI (Aerospace Innovation GmbH), Berlin. The objective is on-orbit qualification/verification of the Aquajet system performance on the TET-1 mission. The Aquajet micropropulsion device is an enabling system, small enough to provide its services to future pico- and nanosatellite missions. In particular, the micropropulsion device is an enabler for the positional control of nanosatellite constellations.

Festkörperspektroskopie (studies of material properties of solid states)

MUPUS Thermal Mapper und ROLIS – measuring the mechanical and thermal properties of external comet layers

Cosmic Dust Analyzer (CDA) – analysis of ice and dust grains in and near the Saturn system

studies with camera systems

research stations on the Mars should collect scientific information

PFS Planetary Fourier IR Spectrometer

instrument for infrared spectroscopy; informations about the nature of atmosphere

WAOSS Stereo Camera

WAOSS stereo camera (Wide-Angle Optoelectronic Stereo Scanner) global topographical mapping with good ground resolution.

EGSE (Electrical Ground Support Equipment)

Das EGSE dient der Integration und Inbetriebnahme sowie dem Test eines Satelliten bzw. der Satellitenkomponenten.

Die Aufgaben eines EGSE umfassen:

◾Energieversorgung des Satelliten

◾Erfassung, Darstellung und Archivierung von Messwerten

◾Senden von Telekommandos

◾Empfang von Telemetrie

◾Telemetrie-Verarbeitung, Interpretation, Darstellung und Archivierung

◾Entwicklung, Validierung und Ausführung von (Flug-)Prozeduren

Reaction Wheel 90

Reaction Wheel 1 and TPL

Radiators with different coatings

GFRP struts for PLM

MLI for NOMAD Instrument

Multilayer Insulations; HPS equipped the whole EDM Module inside and outside with MLI and will land with 10kg MLI on Martian surface