Landing on small bodies: From the Rosetta Lander to MASCOT and beyond

Ulamec, Stephan; Biele, Jens; Bousquet, Pierre; Gaudon, Philippe; Geurts, Koen; Ho, Tra‐Mi; Krause, Christian; Lange, Caroline; Willnecker, R.; Witte, Lars

doi:10.1016/j.actaastro.2013.02.007

Cited by 37 publications

(20 citation statements)

References 22 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…MASCOT-2 is a small (≈ 10 kg) lander, based on the design of MASCOT (1) which is part of the Hayabusa 2 mission (Jaumann et al, 2013;Ulamec et al, 2014). It will be deployed from the mother spacecraft and land on the secondary.…”

Section: Aim Baseline Payloadmentioning

confidence: 99%

Science case for the Asteroid Impact Mission (AIM): A component of the Asteroid Impact & Deflection Assessment (AIDA) mission

Michel

Cheng

Küppers

et al. 2016

Advances in Space Research

103

View full text Add to dashboard Cite

The Asteroid Impact & Deflection Assessment (AIDA) mission is a joint cooperation between European and US space agencies that consists of two separate and independent spacecraft that will be launched to a binary asteroid system, the near-Earth asteroid Didymos, to test the kinetic impactor technique to deflect an asteroid. The European Asteroid Impact Mission (AIM) is set to rendezvous with the asteroid system to fully characterise the smaller of the two binary components a few months prior to the impact by the US Double Asteroid Redirection Test (DART) spacecraft. AIM is a unique mission as it will be the first time that a spacecraft will investigate the surface, subsurface, and internal properties of a small binary near-Earth asteroid. In addition it will perform various important technology demonstrations that can serve other space missions.The knowledge obtained by this mission will have great implications for our understanding of the history of the Solar System. Having direct information on the surface and internal properties of small asteroids will allow us to understand how the vaious processes they undergo work and transform these small bodies as well as, for this particular case, how a binary system forms. Making these measurements from up close and comparing them with ground-based data from telescopes will also allow us to calibrate remote observations and improve our data interpretation of other systems. With DART, thanks to the characterization of the target by AIM, the mission will be the first fully documented impact experiment at asteroid scale, which will include the characterization of the target's properties and the outcome of the impact. AIDA will thus offer a great opportunity to test and refine our understanding and models at the actual scale of an asteroid, and to check whether the current extrapolations of material strength from laboratory-scale targets to the scale of AIDA's target are valid. Moreover, it will offer a first check of the validity of the kinetic impactor concept to deflect a small body and lead to improved efficiency for future kinetic impactor designs. This paper focuses on the science return of AIM, the current knowledge of its target from ground-based observations, and the instrumentation planned to get the necessary data.

show abstract

Section: Aim Baseline Payloadmentioning

confidence: 99%

Science case for the Asteroid Impact Mission (AIM): A component of the Asteroid Impact & Deflection Assessment (AIDA) mission

Michel

Cheng

Küppers

et al. 2016

Advances in Space Research

103

View full text Add to dashboard Cite

show abstract

“…They provide 'ground truth', analyse samples in their natural environment, and allow sub-surface investigation [4]. A few of the challenges are strict requirements, harsh landing site, and short development phase, in addition to wanting to create an innovative design [5]. The asteroid is a very small body, and consequently with very low gravity, this means that it will be very difficult to land on the surface.…”

Section: The Mascot Projectmentioning

confidence: 99%

“…The MASCOT team has had to overcome many challenges over the development phase. Due to Hayabusa-II orbital location, communication with the lander will not be possible during night time, and communication to Earth will only be possible using the main spacecraft [4,5,6]. In addition, there is a lot of uncertainty regarding the properties of the surface of the asteroid.…”

Section: The Mascot Projectmentioning

confidence: 99%

Applying OntoREM to a Space Mission: Developing Requirements for the MASCOT Lander

Antonini

Lange

Kossmann

et al. 2014

INCOSE International Symp

Self Cite

View full text Add to dashboard Cite

OntoREM is an Ontology‐driven Requirements Engineering Methodology supported by software tooling, developed jointly by UWE and Airbus. OntoREM has been tested using a number of pilot cases in various domains at Airbus. In this research, OntoREM is applied to a space mission called MASCOT (Mobile Space Asteroid Scout) developed by DLR (Deutsches Zentrum für Luft‐ und Raumfahrt), Germany, together with CNES (Centre National d'Etudes Spatiales), France, and the Japanese Space Agency (JAXA). The research provided the opportunity to carry out a comparative critical evaluation of the outcomes of the application of OntoREM to MASCOT versus the outcomes of a more traditional Systems Engineering approach as applied by DLR‐Bremen. The key objective was to generate an alternative set of MASCOT requirements using OntoREM based on the existing set of MASCOT system requirements, and to compare the quality of the resulting requirements with the quality of the existing requirements in terms of correctness, completeness and consistency. The application of OntoREM to MASCOT has been successful, it appears that OntoREM is suitable for the development of requirements for space mission programmes and creates quality improvements when generating requirement specifications. About 100% additional project and system requirements were identified, while a re‐usable MASCOT project domain ontology was built during the process that may be generalised for future lander missions.

show abstract

“…1.010 -6 0.510 Experimental investigations of such type of heat pipes were linked to the development of the Mascot lander TCS [14,17] and therefore include different geometries: 1D (the straight-line), 2D (bending in one plane in similar manner as the Flight HP) and the 3D Qualification and Flight configuration (Figure 7). 1D geometry tests confirmed the principle of the temperature regulation; the 2D tests have demonstrated their transport ability in the condition of the minimal effect of Earth gravity; the 3D test showed the HP performance under the gravity condition in the reflux mode, in the orientation, similar to the thermal vacuum test with the whole TCS (gravity assisted).…”

Section: Variable Conductance Heat Pipes With Changing Inner Heat Tramentioning

confidence: 99%

“…Literature sources contain not sufficient and in some cases contradictory information on the operation of such types of heat pipes in the wide range of exploitation temperatures and powers. Therefore, in the Institute of space systems of German Aerospace Center (DLR, Bremen, Germany) in the frame of the project Mascot [14] (design of "miniature lander for asteroid studies") the comparative study of longitudinal heat transfer in three types of heat pipes that are perspective for the project implementation has been undertaken.…”

Section: Introductionmentioning

confidence: 99%

Study of longitudinal heat transfer in low temperature heat pipes with axial grooves and discrete metal fibres for space thermal control systems

Baturkin¹,

Ho²

2016

Heat Transfer XIV: Simulation and Experiments in Heat Transfer and Its Applications

View full text Add to dashboard Cite

Heat pipe technology became an integral part of the thermal control systems of space missions to transfer heat and control the temperature. The selection, design and the integration of heat pipes in space hardware requires the knowledge about their thermal performance. One of the major characteristics is the longitudinal resistance. This paper presents the experimental results of the longitudinal heat transfer in constant and variable thermal resistance heat pipes (HP) with diameters between 0.006 to 0.012 m: "a") aluminium -ammonia HP with axial grooved capillary structure; "b") stainless steel -methanol HP with stainless steel discrete metal fibre capillary structure; "c") copper -methanol HP with copper discrete metal fibre capillary structure. The tests have been performed within a wide range of operation parameters: heat sink temperature from -75 up to +60 o C, the transferred heat power from 0.5 up to 100 W, the axial heat flux density up to 250 W/cm 2 . As characteristic parameter the longitudinal thermal resistance R HP =(T ev -T con )/Q HP is used, where Q HP is the transferred heat power and T ev and T con are the average temperatures of the heat input and output zones, respectively. For the HPs "a" the parameter R HP varies from 0.06 to 0.045 K/W. The change of T con has no essential impact on the HP thermal resistance. For the HP "b", R HP changes from 80 to 4 K/W. The physical basis of such behaviour is related to the formation of vapor and non-condensable gas boundary in the coldest part of the heat pipe and, as consequence, a heat transfer intensity variation. The HPs "c" have shown essential impact of T con on resistance, which varies from 70 to 0.4 K/W. The physical basis of such behaviour is connected a change of the vapor flow regime in the inner vapor space and with change of the inner heat transfer intensity. The comparison of the longitudinal heat transfer characteristics of different types of heat pipes allows us to define their functional abilities in thermal control systems (TCS) for different space applications and to use these data in TCS mathematic models.

show abstract

Landing on small bodies: From the Rosetta Lander to MASCOT and beyond

Cited by 37 publications

References 22 publications

Science case for the Asteroid Impact Mission (AIM): A component of the Asteroid Impact & Deflection Assessment (AIDA) mission

Science case for the Asteroid Impact Mission (AIM): A component of the Asteroid Impact & Deflection Assessment (AIDA) mission

Applying OntoREM to a Space Mission: Developing Requirements for the MASCOT Lander

Study of longitudinal heat transfer in low temperature heat pipes with axial grooves and discrete metal fibres for space thermal control systems

Contact Info

Product

Resources

About