A multidiscipline solution to support space systems engineering

Transcription

1 Overview 06 February 2014

2 A multidiscipline solution to support space systems engineering Offering a wide scope of applications and ensuring the sharing of data and models along the design

3 Overview System analysis software development started with ESA and CNES more than 20 years ago Systema development company funding for more than 15 years Experience on observation and scientific spacecraft (BepiColombo, Mars-Express, Gaia ) and telecommunication spacecraft (Direct TV, ASTRA, Intelsat, Inmarsat...) Development of new version (Systema V4) initiated in 2006 Regular improvements and new applications developments Software distribution (Thermica, Dosrad ) for more than 15 years A worldwide community of users of the different applications (Europe, US, Japan, China, Korea, Russia ) including the main prime contractors and agencies

4 Key features Open Space engineering An open and evolutionary framework A set of engineering applications to support design Interactive Multi disciplinary A set of toolboxes to define the analysis scenario A multidisciplinary model description to support concurrent engineering

5 Systema distribution Airbus DS Development Distribution worldwide MSC Software MSC Thermica Distribution worldwide Hirain Technologies Systema Distribution in China Sojitz Aerospace Systema Distribution in Japan AbleMax Systema Distribution in Korea

6 Release policy / services Two versions in parallel: Long term support (LTS): 4.5.x Based on the functional scope of Systema Offers stability Release of patches if needed Short term support (STS): 4.6.X, 4.7.X Integrates major improvements Next release: Systema planed in June 2014 Services Dedicated training can be organised in Astrium Toulouse or in customer premise Short course are regularly organized Thermica workshop organized every 2 to 3 years

7 A multidisciplinary solution Radiations Space environment Fluid dynamics Electromagnetism Properties Environment Geometry 2D Applications Thermics SYSTEMA 3D Mission Video User interface Trajectory Propulsion Schematics Kinematics Network Power RF

8 Systema framework It provides a set of functionalities required to make an analysis CAD import / model generation / meshing / properties / results display Trajectory definition (Keplerian or general) Kinematics description (pointing laws or general) Mission scenario description / results display / animation Processing: defining the computation case and the run parameter Applications are plug-in package described by XML files Systema framework is also a powerful stand-alone application to perform mission and kinematics analysis

9 Systema geometry Import CAD or mechanical models (Nastran) Create models Manage shells and volumes Set application properties Define and control surfaces meshing Manage material files Define non geometrical parameters Display results Model scripting

10 Systema trajectory Manage solar system planets Define Keplerian orbits Import general trajectory Define planet base or rover mission Visualize eclipse phases Display trajectory characteristics Animate whole spacecraft trajectory

11 Systema kinematics Generic kinematics definition Define kinematics tree Specify joints between objects Set orientation of the main body Define moving bodies Set pointing laws Import general kinematics

12 Systema mission Assemble model, trajectory and kinematics Define and sequences kinematics phases Animate the spacecraft in the solar system Define computation points Display mission parameters (misalignment ) Manage timeline Display and animate results Export images and videos

13 Systema processing Define the computation case Chain several computation modules Set run parameters Launch computation Batch execution

14 Systema V4 applications V4 applications: Thermica: integrated thermal chain: radiation, conduction, temperature Dosrad: radiation dose computation GTD: Antenna patterns / coupling / field mapping: General Theory of Diffraction Plume: plume impingement analysis Debris: debris and micrometeoroids impacts Some of the applications listed above may be subject to export restriction

15 Systema V3 applications V3 environment: Available on Windows (commercial package Exceed is mandatory), Linux and Unix Limited capabilities for model generation and mission definition V3 applications: Mass: mass, balancing and inertia computation Outgassing: contamination by material outgassing (migration from V3 to V4 on-going) Atomox: erosion by atomic oxygen Perturbations: air drag, solar pressure, gravity gradient, magnetic moment Some of the applications listed above may be subject to export restriction

16 V4 Thermica Thermica is an integrated thermal chain used for the design of the thermal control In feasibility studies For technological choices (e.g.: passive or active controls) During correlation with test predictions Thermica computes Thermal radiation exchanges with space and between surfaces External fluxes: Sun, Earth Albedo, Earth infra-red emission Thermal conduction in structures Temperatures calculation : Thermisol Advanced features Solar system management: flux, albedo and planets model Dependent properties: wavelengths, incidence

17 V4 Thermica Solar Fluxes on Telecommunication satellite Temperatures Curves & Tables On E3000 Rocsat2 mirror temperature

18 V4 Dosrad Dosrad computes the radiation dose received by electronic components or material when exposed to the environment Dose integration performed by an efficient solid angle sectoring analysis: Rays are traced from the dose point outwards through the spacecraft For each ray, the amount of shielding encountered is determined taking into account the material density From the dose depth curve, the weighted dose contribution is calculated The average doses per mesh and then per face are obtained Surfaces with thickness or volumes Computation: equipment dose/shielding, component dose, dose mapping Advanced features; honeycomb management, rays display

19 V4 Dosrad Rays display Shielding of equipments Dose cartography on a satellite wall

20 V4 Plume The thruster flow may impinge spacecraft surfaces It is necessary to evaluate the effects of the thruster plume: During the spacecraft design During the spacecraft life for propellant budget evaluation Systema-Plume computes the impact of thruster flow field on a geometry: Dynamic perturbations (perturbing forces and torques) Heat flux (convective or radiative) Surfaces contamination and degradation It is done in a two steps approach: Computation of the undisturbed flow field from the thruster chamber to the far field Evaluation of impacts on a 3D geometry: Gas Liquid droplets

21 V4 Plume Pressure distribution on the solar array of an observation satellite Thermal fluxes on a complete model of a telecom satellite Thruster flow field

22 V4 GTD The structure may disturb the RF properties of antennas TTC antenna patterns, Side lobes level Cross polarization level Antenna to antenna coupling Radiated EMC compatibility Systema-GTD modeling approach Based on General / Unified Theory of Diffraction (GTD / UTD) Using an efficient ray-tracing methodology to handle complex geometries Valid if the objects are larger than the wavelength Computation of Far field antenna characteristics Coupling between antennae Mapping of electric field

23 V4 Far Field Results GTD Electric field Computation Ray Display

24 V4 Debris Debris and micrometeoroids may impact spacecraft elements leading: Penetration of the external walls Penetration of internal equipments Cratering of surfaces (mirror, solar array) Systema-Debris modeling approach Environment described by standard STENVI file Impacted surfaces computed by ray-tracing taking into account shadowing Several ballistic limit equations available: single wall, multiple walls, SRL Crater size equations to compute crater depth and diameter Computation of Number of impacts/penetrations on a meshed surface Probability of No-Penetration of selected elements

25 V4 Debris Space debris environment (STENVI file) Probability of penetration in internal equipments

26 V3 Outgassing In vacuum, the coatings and materials may outgas contaminants species The objective of the Outgassing software is to evaluate the deposit of contaminants on the spacecraft surfaces, such as mirror, thermal coatings as function of time The calculation proceeds in two main steps Computation of the mass transfer factors between surfaces using Monte-Carlo method Time integration of the deposit

27 V3 Outgassing

28 V3 Atomox At altitudes between 200 km and 700 km, the residual atmosphere consists primarily of atomic oxygen (AO) The orbiting motion through this atmospheric AO can generate a flux The incident AO can lead to oxidation and erosion of outer materials and to degradation of surface properties The Systema Atomox computes the fluence of atomic oxygen and the induced erosion taking into account: Standard environment models Thermal motion Multiple reflections Real kinematics of the satellite

29 V3 Atomox Atomic oxygen : influence of solar activity Erosion level on a telescope

30 V3 Perturbations Requirement of an accurate knowledge of the perturbations for on-orbit control (maintain the orbit parameters) attitude control (maintain the orientation of cameras, antennas ) sizing of thrusters, momentum wheel, tanks, attitude control laws Perturbations computes air drag (residual atmosphere for low orbiting spacecraft) solar pressure (photon flux) Earth albedo and infra-red radiation pressure (photon flux) thermal imbalances (induced by spacecraft photons emission) gravity gradient (Earth gravitation generating a torque) magnetic moment (Earth magnetic field generating a torque)

31 V3 Perturbations Air drag forces on SPOT5 Inmarsat 4 model

32 V3 Mass Mass and balancing (component rearrangement or balance masses) are critical for the design The Mass software is a set a mass-related modules interfaced with the Systema framework Mass allows the engineer to Generate mass property of primitive shapes Generate a listing of data showing current mass, center of mass and principal moments of inertia Generate mass budget for a given configuration Generate mass history report, mass property report Analyze static and dynamic balancing Analyze mass sensitivity Generate inputs required for analysis

33 V3 Mass Mass data Mass properties

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