Current missions on Small Solar System Bodies (SSSB) imply long surveying and characterization phases before surface landing is attempted, which decrease time for potential
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enable a safe autonomous landing to increase mission lifetime and scien-tific return of upcoming SSSB missions. INTRODUCTION . The in situ exploration of Small Solar System Bodies
In this study, we develop a dynamical model with dynamics, contact, and control modules to simulate a legged probe with solar panels landing on a small body with weak
High-fidelity dynamical landing model has several advantages: 1) The landing model considered the flexible deformation of the solar panels instead of simply modeling it as a rigid body; 2) This model can simulate a probe of arbitrary shape; 3) The parameters of the contact algorithm have clear physical meanings that can well characterize the soil physical
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Article "Technical progress in landing mechanisms for exploring small solar system bodies" Detailed information of the J-GLOBAL is an information service managed by the Japan Science and Technology Agency (hereinafter referred to as "JST"). It provides free access to secondary information on researchers, articles, patents, etc., in science and technology, medicine and
and development of solar cells in battery-powered UAVs. Formorethanadecade,smallsolar-andbattery-powered electric UAVs were the subject of research and development [1, 5–19]. Seven small solar UAVs (i.e., So Long, Sky-Sailor, Sun-Sailor, Sun Surfer, AtlantikSolar AS-2, University of Minnesota''s SUAV, and Cranfield University''s Solar UAV)
Their unique combination of efficient capabilities, resource-friendly design and inherent robustness makes them attractive as a mission element at the frontiers of exploration of the
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A landing shoulder is provided on a series of collets extending from a frangible ring. The collets are biased into a groove which is itself in a recess in the wellhead housing. Deployment of the landing shoulder in its retracted position allows an additional string of casing to be run which is nominally close to the inside seal bore diameter of the wellhead housing.
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Robust Landing Site Detection for Flight over Small Solar System Bodies. January 2022; DOI:10.2514/6.2022 A. M., “Imaging flash LIDAR for saf e landing on solar system bodies and spacecraft
A new small unmanned aircraft system (UAS) boasts something no other has been able to do thus far: continuous flight for 9 hours and all on the clean energy of solar power. AeroVironment''s 13
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For landing on a small Solar System body, in principle, the following concepts can be considered: • Penetrators (as proposed, e.g., for Vesta). • Classical Landers with
Landing on the surfaces of small solar system bodies (3SBs) is a prerequisite for maximizing the value of probes and provides technical reserves for the resource development of 3SBs and
Semantic Scholar extracted view of "Technical progress in landing mechanisms for exploring small solar system bodies" by Canhui Yin et al.
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Existing mathematical design models for small solar-powered electric unmanned aerial vehicles (UAVs) only focus on mass, performance, and aerodynamic analyses. Presently, UAV designs
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In the controlled landing mode, the time required for the probe to make a stable landing on the small body similarly decreases as Young''s modulus of the solar panels decreases (Fig. 9 C), which of course, leads to a different final landing position (Fig. 9 D). In brief, compared to rigid-body dynamical model, the flexible solar panels can absorb part of the impact energy,
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Landing on the surface of small solar system bodies helps to maximize probes value. Few probes have landed on the surface of small solar system bodies. Microgravity and uncertain surface make challenges to the landing of probes. Suppression of rebounding and tipping over of probes is crucial issues.
Discussion on new schemes for landing on small solar system bodies More landing cushioning schemes for exploration missions to 3SBs is essential to be considered. The mechanical cushioning structure can respond to external excitation in real time.
Few probes have landed on the surface of small solar system bodies. Microgravity and uncertain surface make challenges to the landing of probes. Suppression of rebounding and tipping over of probes is crucial issues. Both passive and controlled active landing-cushioning are worth solutions.
Small solar system bodies (3SBs) have the characteristics of large number, wide distribution and different compositions. Current mainstream theories suggest that 3SBs originated from condensed planetesimals in primitive solar nebulae and formed synchronously with the formation of the solar system 4.5 billion years ago [ 1 ].
The principle of this method is that the lander uses a charging gun to push the balls of the space device into the 3SB in advance; then, the balls are charged and opposite charges are generated on the lander. As a result, the lander will be adsorbed on the surface via the formed electric field force.
Soft landings of probes on 3SBs will be realized by the dedicated mechanism and its cushioning mode. In the current missions, the Philae lander, which was the subprobe of the Rosetta orbiter, was equipped with a dedicated landing mechanism.
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