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Euclid scientific space probe

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Euclid scientific space probe

The Euclid probe is an ESA cosmological mission to study the nature of the dark universe – both its dark energy and its dark matter. To this end, the probe includes a telescope 1.2 m in diameter allowing it to make observations in the visible and near-infrared ranges, with ample bandwidth and spectroscopy. The objective is to investigate the distance-redshift relationship and the evolution of the cosmic structures by measuring shapes and redshifts of distant galaxies– observation looks back on 10 billion years of cosmic history.

Euclid will be launched in 2020 from Kourou, French Guiana in a Soyuz rocket and will maintain a Lissajous orbit around the solar system’s second Lagrangian libration point (L2), 1.5 million km from the Earth.

The mission will also involve a highly extensive exploration of extra-galactic space, employing various techniques, the most salient of which are WGL (Weak Gravitational Lensing) which consists of detecting dark matter through the bending of light by gravity, and BAO (Baryonic Acoustic Oscillations), a technique which allows regular fluctuations in the visible baryonic matter in the universe to be observed.

Euclid High Gain Antenna Gimbal

At Sener we are responsible for the design, production, integration, verification and validation of the deployment and gimbal mechanism for the High-Gain Antenna (HGA), the vehicle’s main antenna, which will allow Euclid to communicate with the tracking stations on Earth for the purpose of sending scientific data.

The project consists of developing a precision mechanism with three axes, one for deploying the antenna and the other two for pointing. Two radio signals are transmitted through the mechanism from the satellite to the antennas. The signals are K band for the high-gain antenna and X band for the low-gain antenna. The K band rotary joint and the actuator have been developed by Sener.

Secondary Mirror Refocusing Mechanism (M2M)

We develop the Secondary Mirror Refocusing Mechanism (M2M). The M2MM is a positioning mechanism with 5 degrees of freedom which allows the movement and adjustment of the secondary mirror (M2M) of the EUCLID telescope to guarantee the optical quality required in orbit, necessary to recover telescope misalignment caused by the difference in conditions between the earth and space.

AOCS/GNC system

In this first-level mission, at Sener we are the prime contractor for the satellite’s Attitude and Orbit Control System (AOCS/GNC). With the exception of the scientific payload, this is the spacecraft”s most complex system, and it needs to attain an unprecedented level of stability, approaching 75 milliseconds of arc in periods of over 11 minutes. To do so, it needs to perform start-up and shut-down operations on the reaction wheels each time there is an observation, which gives rise to a hitherto unimplemented wheel operation cycle. These levels of precision also require the use of a high-precision micro-propulsion system and a guidance sensor built into the telescope’s focal plane.

Mechanical Ground Support Equipment (MGSE)

We are also responsible for the design, manufacture and testing of thirteen support units for the assembly of the large satellite comprising the Euclid probe. The company is developing this project under contract from Thales Alenia Space, the prime contractor of the space mission.

The essential sub-systems which form part of the Mechanical Ground Support Equipment (MGSE) are units which position the satellite on different surfaces. They incorporate additional mechanisms for keeping the structure in the desired position, even if there is a shift in the centre of gravity, as occurs when new elements are installed.

At Sener we are also to build a simulator of the Euclid satellite, simulating its dimensions, its mass and the position of its centre of gravity. In the heaviest configuration, the one used in the resistance tests, at 4.7 tonnes, the equipment’s mass is double that of the Euclid probe.

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Euclid Mechanical Ground Support Equipment (MGSE)

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High gain Antenna Deployment and Pointing Mechanism of the Euclid probe

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Secondary Mirror Refocusing Mechanism (M2M) of the Euclid telescope

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Attitude and orbit control system (AOCS) for Euclid

Sener/InternationalPage 13

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Sener Space / Science & Earth observation / Space

Attitude and orbit control system (AOCS) for Euclid

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Client: THALES Alenia Space

Country: Space

Sener is responsible for the AOCS subsystem, under the direct coordination of Thales Alenia Space Italy (TASI), principal contractor for the mission.

Sener is in charge of the entire subsystem, which includes the equipment, functions and SW that control its attitude (pointing) and orbital position. The AOCS’s sensors include:

Fine Guidance Sensor (FGS)
Inertial Measurement Unit (IMU)
Star Trackers (STR)
Coarse Rate Sensors (CRS) and Sun Sensors (SS)
Reaction Wheels (RWL)
Micro Propulsion Subsystem (MPS) and Reaction Control Subsystem (RCS)

Eight Sener subcontractors from different countries are participating in the subsystem (including subcontractors from the Netherlands,

Sener is responsible for the AOCS subsystem, under the direct coordination of Thales Alenia Space Italy (TASI), principal contractor for the mission.

Sener is in charge of the entire subsystem, which includes the equipment, functions and SW that control its attitude (pointing) and orbital position. The AOCS’s sensors include:

Fine Guidance Sensor (FGS)
Inertial Measurement Unit (IMU)
Star Trackers (STR)
Coarse Rate Sensors (CRS) and Sun Sensors (SS)
Reaction Wheels (RWL)
Micro Propulsion Subsystem (MPS) and Reaction Control Subsystem (RCS)

Eight Sener subcontractors from different countries are participating in the subsystem (including subcontractors from the Netherlands, France, Germany, Italy, Portugal, and the US), while the client itself is providing the FGS, MPS and RCS.

The operating logic includes multiple modes and functions which are implemented in the SW of the AOCS, while also integrated in the SW of the central computer. The functions of the AOCS include determining and controlling the satellite’s attitude in all the modes; orbital maneuvers; equipment management and control; fault management (FDIR); interactions with the central software; and management of the AOCS’s data, telemetry and telecommands.

The project includes the preliminary and detailed design, production, verification, classification, delivery, and in-orbit commissioning. The AOCS provides hitherto unseen levels of performance in terms of pointing and stability (75 milli-arcsec., 99.7% C.L.), which will also give the FGS, IMU, MPS, etc. the highest levels of performance. Furthermore, the RWL must compensate for any disturbances (including those caused by the actuation of the mechanisms), while also preventing the transmission of the characteristic (micro-)vibrations, meaning they require very special characteristics and operation.

The AOCS’s SW corresponding to its different modes will be generated using Model Based Design Tools, with subsequent automatic generation of code from these models for the first time on an ESA scientific mission.

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Secondary Mirror Refocusing Mechanism (M2M) of the Euclid telescope

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Sener Space / Science & Earth observation / International

Secondary Mirror Refocusing Mechanism (M2M) of the Euclid telescope

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Client: ADS F / TAS-I / ESA

Country: International

At Sener, we develop the Secondary Mirror Refocusing Mechanism (M2M). The M2MM is a positioning mechanism with 5 degrees of freedom which allows the movement and adjustment of the secondary mirror (M2M) of the Euclid telescope to guarantee the optical quality required in orbit, necessary to recover telescope misalignment caused by the difference in conditions between the earth and space.

Characteristics:

Radiation environment: The unit is designed to tolerate a uniformly distributed total dose of 22 krad inside the box.

Characteristics:

Radiation environment: The unit is designed to tolerate a uniformly distributed total dose of 22 krad inside the box.
Mass: MDE 2.1 kg. Harness 1.6Kg. Mechanism 4.45 kg
Thermal:
– MDE operating range: 250K – 313K; non operating range: 230K – 313K.
– M2MM operating range: 110K – 313K.
– Harness operating range from 110K to 313K and support a gradient of 203K.
– Special cabling to connect the mechanisms to the electronics with low thermal conductivity.
– Max. dissipation by conduction for MDE < 8W .
– Max. dissipation by radiation for MDE < 2W.
– Harness transfer in cryogenic zone < 0.0005 W in non-operational mode
Functional: Mechanical Resolution is half micron resolution over a travel of +/- 225 µm with stable positions and high load capability to withstand launch loads without losing a given position in a compact volume.
– Positioning method based on a stepper motor.
– Adjustment in 3 degrees of freedom of translation.
– Adjustment in 2 degrees of freedom of rotation.
– Linear resolution <0.050 μm.
– Angular resolution <5μrad.
– Range of linear operation 300 μm.
– Range of angular operation 2mrad.
– Precision of 2 μm for linear adjustments.
– Precision of 30 μrad for angular adjustments.
Redundancy: Two fully redundant sections in a single box.
Power: Each section powered by a 10W isolation converter.
Control: Each section provided with an “intelligent” device capable of decoding all telecommands received via serial channels, (MIL-STD-1553, preferred) providing the switching sequences required by the motors, and encoding the status information to provide serial telemetry.
Compact electronics for the operation and control of the twin mechanisms (up to 10 degrees of freedom).
Motors drive: Ten independently biphased motors (with main and redundant wiring) can be managed by MDE main and redundant section in cold redundancy.

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GAIA. Sunshield Drive Electronics (SDE)

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Sener Space / Science & Earth observation / Space

GAIA. Sunshield Drive Electronics (SDE)

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Client: ADS GmbH / ESA

Country: Space

The Sunshield Drive Electronics (SDE) is an electrical unit designed to control a stepper motors per section (Main or Redundant) which shall actuate over the of the GAIA Deployable Sunshield Assembly (DSA) Structure.

During the qualification campaign of the GAIA Deployable Sunshield Assembly (DSA) it was identified the need of implementation of an active motorisation device apart and in addition to the implemented deployment springs on each of the 12 section that forms the Sunshield. The deployment of the DSA is actuated by those springs mounted on each DSA section at the deployment. The implementation of two actuators linked to two opposite frames through a four bar linkage provides braking capability during a nominal deployment as well as additional motorisation in case resistances to the deployment increase. This improves the reliability ae level of the hinges and provides motorisation to overcome the resistance forces acting against thnd motorisation of the deployment.

The DSA Drive Subsystem includes the following hardware :

Two Sunshield Bar-linkaje Mechanisms (SBM) with stepper motor actuator
Two Sunshield Drive Electronics (SDE) one for each actuator
The two harnesses connecting the Sunshield Bar-linkaje Mechanisms and the Sunshield Drive Electronics

The SDE are formed by two electronic boxes that contains two electronic sections each one. These units are recurrent units from M2MM MDE of GAIA.

The SDE is an electrical unit designed to control a stepper motors per section (Main or Redundant) which shall actuate over the DSA Structure. The stepper motor mechanisms shall allow the DSA deployment.

Each SDE unit is housed in a single aluminum box, and it is internally divided in two fully similar sections, denoted as main and redundant, which are working in cold redundancy. The spacecraft is in charge of selection the nominal or redundant section. Every section is comprised of a hybridised DC/DC converter with integrated EMI filter, and one semi-rigid board. Each section shall command the motor using a current control loop. This scheme allows reducing the power deliver to the motor in the low temperatures where the motor resistance is lower.

A MIL-STD-1553 bus is used to manage the communication between the SDE units and the spacecraft. This link shall be used to send and receive all the telecommands and telemetries involving the motor commanding.

The Sunshield Drive Electronics (SDE) interfaces with the Power Control and Distribution Unit of GAIA satellite for the power and with the CDMU of GAIA satellite for the command control and housekeeping data. The SDE interfaces with nominal and redundant channels of mechanism actuators.

The main functions of the SDE are:

DC/DC power conversion to provide secondary supplies to internal electronic part and to actuator drivers
Acquisition of command to be applied to the actuators from 1553B bus of GAIA SVM
House-keeping Monitoring and status transmission to 1553B bus of GAIA SVM
Provision of power to drive the actuator
Provision of excitation voltage to actuator potentiometers

The redundancy philosophy is a cold redundancy, i.e. Two electronic parts (main and redundant) drive one actuator on its nominal and redundant interfaces, however the activation of main and redundant parts will have a short overlap period. Both redundant and nominal electronics are kept within one SDE electronics box.

cHARACTERISTICS:
Mass: 2.2 kg.
Size: 175 high, 130 long and 95 wide.
Thermal: SDE unit is designer to have an operating range from 250K to 313K and non operating range of 230K to 313K. The MDE shall manage the M2MM that will have an operating range from 110K to 313K.
Power:
– Power input bus: +28V
– Power Consumption: 15W (Duty cycle 100%); 12W (Duty cycle 75%); 9W (Duty cycle 50%)
– The max. dissipation by conduction for SDE < 8W
– The max. dissipation by radiation for SDE < 2W.
Radiation environment: The unit is designed to tolerate a uniformly distributed total dose of 22 krad inside the box.
Redundancy: Two fully redundant sections in a single box.
Power conditioning: Every section has to be provided with an isolation converter with an integrated EMI filter
Control: Every section is to be provided with an “intelligent” device capable of decoding all telecommands received via serial channels, providing the switching sequences required by the motors, and encoding the status information to provide serial telemetry.
Motors drive: Up to ten independently biphased motors (with main and redundant wiring) can be managed by MDE main and redundant section in cold redundancy.

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High gain Antenna Deployment and Pointing Mechanism of the Euclid probe

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Sener Space / Communications in Space / Space

High gain Antenna Deployment and Pointing Mechanism of the Euclid probe

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Client: TAS-E / TAS-I / ESA

Country: Space

Sener is developing the high gain antenna deployment and pointing mechanism (HGA ADPM) for the Euclid scientific space probe. It is a precision assembly comprised of three axes, one for antenna deployment and the other two for pointing. The assembly transmits two radio-frequency signals from the satellite to the antennae. The signals are on the K band (between 25.5 and 27 GHz) for the high gain antenna, and on the X band (between 7.1 and 8.5 GHz) for the low gain antenna.

Main mechanism components:

Actuators: The number of actuators and rotation axes are the same.

Main mechanism components:

Actuators: The number of actuators and rotation axes are the same. In this case there are three: for deployment, azimuth, and elevation. Each one of them comprises among others:

Stepper motor
Integrated bearing system
Gear (harmonic)
Positioning sensors (fine and coarse potentiometers for each Az. & El.))
Machined parts
Internal ball bearing
K band rotary joint: a rigid joint used to transmit the radiofrequency single despite the assembly”s rotation. There is one on each actuator.
X band cable: used to transmit the X band signal.
Flexible cable: used to send the electric signals and power to the actuator, sensors, thermistors and thermal resistances.
L-structure: the structural element that joins the actuators.
Support: the structural element that joins the deployment actuator to the interface with the satellite.
The K band rotary joint and the actuator are specific Sener developments.

Characteristics:

Mass: 10.5 kg.
Power: 6.5 W per moving axis (steer).
Pointing precision: ±0.005º in open loop.
Speeds: 0.3º/s per axis.
Radio frecuency (RF):
· Insertion Loss (K band/X band): < 1.2 dB / 1.5 dB
· Return Loss (K band/X band): > 18 dB / > 16.5 dB
· Radio-frequency power handling (K band/X band): min. 100 W/ min. 20 W

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Solar Orbiter High Gain Antenna Subsystem (HGA S/S)

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Sener Space / Communications in Space / Space

Solar Orbiter High Gain Antenna Subsystem (HGA S/S)

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Client: Airbus DS UK / ESA

Country: Space

The main objective of the project was to design, manufacture, integrate, test and deliver the satellite’s complete antenna subsystem. This subsystem comprises four independent devices:

High Gain Antenna Major Assembly (HGAMA)

In turn, the HGAMA consists of:

An “axially displaced ellipse” reflector antenna made of titanium whose main reflector has a diameter of 1100 mm.
A boom that permits antenna operation separately from the satellite.
A two-axis antenna pointing mechanism (APM).
Thermal shields and blankets to protect the entire assembly.

The main objective of the project was to design, manufacture, integrate, test and deliver the satellite’s complete antenna subsystem. This subsystem comprises four independent devices:

High Gain Antenna Major Assembly (HGAMA)

In turn, the HGAMA consists of:

An “axially displaced ellipse” reflector antenna made of titanium whose main reflector has a diameter of 1100 mm.
A boom that permits antenna operation separately from the satellite.
A two-axis antenna pointing mechanism (APM).
Thermal shields and blankets to protect the entire assembly.
Four Hold-down and Release Mechanisms
Antenna Pointing Mechanism Electronics (APME) located inside the satellite to control antenna pointing.

Medium Gain Antenna Major Assembly (MGAMA)

In turn, the MGAMA consists of:

A horn antenna
A 700-mm boom to articulate the antenna.
Heat shield for the boom and thermal protection blankets of the APM.
A Hold-down and Release Mechanism
A single-axis Antenna Pointing Mechanism (APM) at the end of the boom.
Antenna Pointing Mechanism Electronics (APME) located inside the satellite.

The MGAMA has certain similarities with the assembly of the same name being developed at Sener for the BepiColombo Mission.

Low Gain Antennas (LGAs)

Two Low Gain Antennas (LGAs) with semi-omnidirectional coverage, the combination of which allows the satellite to establish a communications link with the Earth in emergences or loss of attitude.

Characteristics:
The high gain antenna operates on the X band with gains of more than 36.5 dBi in downlink and more than 35.0 dBi in uplink.
The antenna operates at a power of 48.45 dBm in the required setting at less than 0.28 AU (astronomical units). The temperatures it must withstand during the science phase are 585ºC in areas exposed to the sun, and it has a special coating developed specially to guarantee that it will operate even in such a harsh environment.
The unit operates on two axes at speeds of 0.5º/seconds with pointing stabilities compatible with the radio-frequency requirements.
The medium gain antenna also operates on the X band with a gain of 22.3 dBi in downlink and 20.5 dBi in uplink with a power of 48.48 dBm. The antenna also operates during the science phase at the minimum distance from the sun, withstanding temperatures of 550ºC.
The low gain antenna operates during the phase closest to Earth on the X band, transmitting the satellite’s telemetry data.

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SOLAR ORBITER. Instrument boom

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Sener Space / Science & Earth observation / International

SOLAR ORBITER. Instrument boom

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Client: ADS UK / ESA

Country: International

The Solar Orbiter deployable boom function is to support and deploy four instruments which, due to their sensitivity to magnetic fields, need to be placed far from the electromagnetic disturbances generated by the satellite.

It consists of three rigid sections joined by two deployment mechanisms. Each section consists of titanium pieces affixed to CFRP pipes. During launch, the boom remains undeployed and secured to the satellite’s panels by means of a tripod and two hold-down mechanisms, while a third hold-down mechanism keeps the two deployable sections joined together. Once in orbit, deployment takes place in two sequences. Initially the two hold-down mechanisms are released and both sections are rotated 195° by the internal deployment mechanism until a stop point is reached, which defines the deployed position. The intermediate moving mechanism is then released and the external section rotates 180° with regard to the internal section by means of the external deployment mechanism, reaching the deployed position.

The deployment mechanisms consist of one hinge with spherical bearings and are clock spring-actuated. A viscous damper is included for smooth deployment. The mechanisms have a mechanical end-of-deployment stop point together with a hook-up system. They also include a potentiometer as a position sensor plus switches to monitor the final positions.

In order to adapt the subsystem to the thermal atmosphere, thermal control is included, which comprises both passive elements (thermal blankets and paint with suitable thermal-optical properties), and active elements (electric heaters and thermistors).

The subsystem includes the instrument cable bundles, the wiring required to transmit the signals from the position sensors and the thermistors, and the wiring to supply power to the electric heaters.

One important characteristic is the routing and fixing of the wiring along the pipes and around the deployment mechanisms.

Due to the strict magnetic cleanliness requirements, as far as possible, all the materials used are amagnetic (titanium, aluminium, CFRP, Vespel, beryllium copper, etc.), and in unavoidable cases of materials with a certain residual magnetism, exhaustive demagnetisation is performed.

Characteristics:
Undeployed length: 2250 mm
Deployed length: 4400 mm
Subsystem mass: 35 kg
Instrument and wiring mass: 9.7 kg
Stiffness – undeployed: 80 Hz
Stiffness – deployed: 1.1 Hz
Deployment angle – internal articulation: 195º
Deployment angle – external articulation : 180º
Deployment times – first section: < 90 s
Deployment times – second section: < 90 s
Vibration sine: 10 g
Vibration random: 13 grms

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AUTOPLAK Efficiency for the microbiology laboratory

Sener/InternationalPage 13

07.08.2013

Format: pdf

AUTOPLAK is an automatic sample inoculation and streaking system for Petri dishes in microbiology laboratories.

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Fllight Models Delivered

Sener/InternationalPage 13

08.17.2012

Format: pdf

AUTOPLAK is an automatic sample inoculation and streaking system for Petri dishes in microbiology laboratories.

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High efficiency thermal cycles technology for municipal solid waste

Sener/InternationalPage 13

03.22.2011

Format: pdf

AUTOPLAK is an automatic sample inoculation and streaking system for Petri dishes in microbiology laboratories.

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Space

Science & Earth observation

Euclid scientific space probe

Euclid scientific space probe

Euclid High Gain Antenna Gimbal

Secondary Mirror Refocusing Mechanism (M2M)

AOCS/GNC system

Mechanical Ground Support Equipment (MGSE)

Content related to this project

Euclid Mechanical Ground Support Equipment (MGSE)

High gain Antenna Deployment and Pointing Mechanism of the Euclid probe

Secondary Mirror Refocusing Mechanism (M2M) of the Euclid telescope

Contact us

Attitude and orbit control system (AOCS) for Euclid

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Euclid Mechanical Ground Support Equipment (MGSE)

High gain Antenna Deployment and Pointing Mechanism of the Euclid probe

Secondary Mirror Refocusing Mechanism (M2M) of the Euclid telescope

Contact us

Secondary Mirror Refocusing Mechanism (M2M) of the Euclid telescope

Characteristics:

Characteristics:

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Secondary Mirror Refocusing Mechanism (M2M) of the Euclid telescope

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GAIA. Sunshield Drive Electronics (SDE)

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High gain Antenna Deployment and Pointing Mechanism of the Euclid probe

Main mechanism components:

Main mechanism components:

Characteristics:

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SOLAR ORBITER. Instrument boom

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