ANISOTROPIC HEAT-SHIELDING MATERIALS: PROSPECTS FOR APLICATION IN THE RE-ENTRY MODULE HEAT SHIELD
DIAGNOSTICS OF DEFECTS OF THERMAL PROTECTIONS INFLATABLE RE-ENTRY VEHICLES
STRUCTURAL DESIGN AND ANALYSIS OF AN AEROSHELL FOR A HUMAN CREW ENTRY VEHICLE IN MARTIAN ATMOSPHERE
ENGINEERING CHALLENGES IN CONFIGURING A MODULAR CRYOGENIC UPPER STAGE
MOTION ESTIMATION OF MEMBRANE SPACE STRUCTURE USING ORBIT MEASUREMENT DATA
STATIC AND DYNAMIC CHARACTERIZATION OF A METALLIC COMPONENT OF VEGA-C INTERSTAGE 2/3
THE RADIATION ENVIRONMENT AND EFFECTS ANALYSIS OF THE LUMIO MISSION
DYNAMIC RESPONSE AND BEHAVIOR SIMULATION OF A THERMAL BOOT EMPLOYED IN A HEAVY LIFT LAUNCH VEHICLE
LTO-MWCNTS BASED NANOCOMPOSITE FLEXIBLE ELECTRODES FOR LI ION BATTERIES
Werkstoffe im Automobilbau : ATZ, MTZ extra
HIGH STRENGTH FIBER REINFORCED SYNTACTIC FOAM COMPOSITES AS INTERPLANETARY THERMAL PROBE MATERIAL
SIMULATION OF RAREFIED HYPERSONIC FLOWS BY USING THE DIRECT SIMULATION MONTE CARLO METHOD
IN-SITU CONSTRUCTION ON MARS : 3D PRINTING AND CONVENTIONAL SINTERING OF MARS SOHL SIMULANT (JMSS-1)
AN ADDITIVE MANUFACTURING REDESIGN OF A BOX EQUIPMENT WITHIN A LOGISTIC 4.0 FRAMEWORK
TOPOLOGY OPTIMIZATION FOR 3D PRINTING WITH SELECTIVE PLACEMENT OF CNT YARN REINFORCEMENT
SENSOR COATINGS FOR HIGH-TEMPERATURE MEASUREMENTS IN SPACE APPLICATION
SUITABILITY OF MANUFACTURING PROCESSES FOR IN-SPACE MANUFACTURING OF SPACECRAFT COMPONENTS
THE PERMIAM™ ADDITIVE MANUFACTURING PROCESS FOR OPEN POROSITY IN
AN OVERVIEW OF THE APPLICATION OF 3D PRINTED SPACECRAFT STRUCTURES WITHIN THE REDSHIFT PROJECT
SLS PRODUCTION FRICTION STIR PLUGS BY SOLID STATE ADDITIVE DEPOSITION
EXPERIMENTAL VERIFICATION OF TWO-DIMENSIONAL SELF-DEPLOYABLE SPACE STRUCTURES WITH CONVEX-PANEL
A NEW DEVICE AND METHOD FOR SIMULATING HYPERSONIC AEROTHERMAL ENVIRONMENT
A PREDICTIVE THERMO-ORBITAL MODEL FOR ANALYSIS OF SUN SYNCHRONOUS ORBITS OF NANOSATELLITES
DEVELOPMENT OF A THERMAL DESIGN MODEL FOR A SMALL SPACECRAFT WITH INTEGRATED HEAT PIPES
AEROTHERMAL ANALYSIS AND THERMAL PROTECTION OF GRID FINS FOR REENTRY ROCKETS
WHEN GSE BECOMES EQUALLY DEMANDING AS THE LIGHT WEIGHT STRUCTURE: A SOFT COVER FOR THE EUCLID BAFFLE