Search

4 results found
Thermal Infrared Imager Assessment Study for the Asteroid Impact Mission

ESA’s Asteroid Impact Mission (AIM) is both a Technology Mission of Opportunity, and a mission to greatly improve our understanding of asteroid physical properties and their response to a hypervelocity impact event on their surface. The AIM mission is combined with the Double Asteroid Redirection Test (DART). Both missions complement one another in a joint asteroid impact test and observation campaign called Asteroid Impact & Deflection Assessment (AIDA). The Thermal InfraRed Imager (TIRI) is Thermal IR imager of the AIM mission.

The Netherlands

15/M64-a

Cosine Research
Assessment of an Anchoring Device for CubeSat Landers

The current study has evaluated the feasibility of a CubeSat anchoring device in the context of AIM mission. By enabling this capability on a Cubesat type nanosatellite, the overall AIM mission will be further augmented with in-situ scientific measurements such as close surface visual observations, on site plume ejecta monitoring, impact induced accelerations and seismic wave propagated through asteroid body, etc. Moreover, the anchoring device has a strong reuse potential in the context of SSA by the utilisation of Cubesats or small platforms for debris removal techniques.

Romania

16/701

Institute of Space...
Assessment of a Low Velocity PicoSat Orbital Deployer for AIM and Interplanetary Missions

The output of the activity should show the necessary engineering changes to an existing CubeSat deployer to meet AIM mission and system requirements and prepare an appropriate interface definition for accommodation on the AIM spacecraft including among others:
- Identification of the requirements for a LV-POD in an interplanetary environment, first addressing the needs of AIM and extending to generic interplanetary missions.
- Review of technology to extend existing CubeSat deployment systems and identification of their limitations.

The Netherlands

15/M63

Innovative Solutions in...
System analysis of deployable components for micro landers in low gravity environment

The project entitled "System analysis of deployable components for micro landers in low gravity environment" is conducted within the framework of the ESA contract no. 4000117150/16/NL/HK/hh. Its goal is to perform an analysis and trade-off between the various design options for antennas and solar array deployment mechanisms (including a comparison between the fixed and deployable configurations) of the MASCOT-2 lander in the micro-gravity environment of Didymoon.

Poland

15/725

Space Research Centre of...

Filter by programme:

Filter by start year:

Filter by end year:

Filter by keywords:

Filter by contractor:

Filter by country:

Filter by application domain: