SIASAIL-I solar sail: From system design to on-orbit demonstration mission

Liu, Jinguo; Zhao, Pengyuan; Wu, Chenchen; Ren, Weijia; Liu, Lei; Tang, Yingying; Ji, Chenyang; Sang, Xiaoru

doi:10.1016/j.actaastro.2021.11.034

Cited by 26 publications

(7 citation statements)

References 28 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Inspired by SIASAIL-I (Liu et al, 2022), we propose an APS, which can provide a stable external force to LVP until F f is sufficient enough. The whole process of APS is shown in Figure 6.…”

Section: Auxiliary Penetration Schemementioning

confidence: 99%

Two novel approaches for solving the contradiction between efficient penetration and low recoil for the low‐velocity penetrator

Xu,

Feng,

Liu

et al. 2024

Journal of Field Robotics

Self Cite

View full text Add to dashboard Cite

The low‐velocity penetrator (LVP) is a planetary penetration device that can drive itself to a target depth through its internal periodic impacts. When LVP generates impact energy, it inevitably produces a recoil that can only be counteracted by friction with the soil, if there is no other auxiliary device. Unfortunately, LVP is extraordinarily sensitive to the recoil during the initial stage since the small contact area with the soil results in minor friction between them. Significantly, once the recoil exceeds the friction, LVP cannot work properly and may even retreat, inducing mission failure. In this paper, we develop an optimized LVP with an auxiliary device for lower recoil and higher performance. Specifically, we establish a dynamic model to analyze the single‐cycle motion of LVP and provide essential support for its optimization and design. Meanwhile, an integration method is proposed to calculate the friction between LVP and the soil reasonably and accurately. On the basis of these, we obtain the optimal mass and stiffness parameters of LVP that meet both high penetration efficiency and low recoil. Furthermore, only relying on the parameter optimization is insufficient to eliminate the recoil, and an auxiliary penetration scheme is proposed to provide an external force counteracting the recoil until LVP arrives at a certain depth. Through multiple comparative penetration experiments, we validate the effectiveness of our approaches in promoting penetration ability, stability, and restraining the recoil of LVP. This work provides two novel approaches for solving the contradiction of efficient penetration while reducing the recoil for LVP.

show abstract

“…Inspired by SIASAIL-I (Liu et al, 2022), we propose an APS, which can provide a stable external force to LVP until F f is sufficient enough. The whole process of APS is shown in Figure 6.…”

Section: Auxiliary Penetration Schemementioning

confidence: 99%

Two novel approaches for solving the contradiction between efficient penetration and low recoil for the low‐velocity penetrator

Xu,

Feng,

Liu

et al. 2024

Journal of Field Robotics

Self Cite

View full text Add to dashboard Cite

show abstract

“…In actual working conditions, the thermal resistance wire is usually used to fuse nylon ropes. The feasibility of this method has 9 Space: Science & Technology also been verified in many space deployment mechanisms [35]. We use a scissor to replace the function of thermal resistance wires, in order to simplify the fusing process and carry out multiple sets of deployment tests.…”

Section: Ground Experiments Verificationmentioning

confidence: 99%

1U-Sized Deployable Space Manipulator for Future On-Orbit Servicing, Assembly, and Manufacturing

et al. 2022

Self Cite

View full text Add to dashboard Cite

Miniaturized, multifunctional, and economical on-orbit service satellites have been increasingly used with the continuous increase of space exploration missions. In this paper, an innovative deployable manipulator is designed, named Cubot, which can be stowed in 1 U-sized (10 cm×10 cm×10 cm) space. With CubeSat as the carrier, the deployable Cubot aims to achieve a variety of on-orbit operation tasks including space debris removal and space station on-orbit maintenance, for future on-orbit servicing, assembly, and manufacturing (OSAM). A kinematics modeling method of a space manipulator with passive joints is proposed, and the motion equation of the manipulator is derived. Considered the elastic potential energy stored in the passive joint during deployment, the momentum change of Cubot is simulated and analyzed. As the main forced element, the end effector is analyzed using FEA. Dynamic stress response with respect to the force distribution and the clamping angle is analyzed to evaluate mechanical performances of the end-effector component. Deployment tests are conducted to verify the feasibility of Cubot based on a principled prototype, which aims to provide engineering and practical experience for the development of this field.

show abstract

“…29 On the other hand, origami-inspired patterns of space deployable structures in various on-orbit flight attempts range from most common ''Z-Fold'' (e.g. LightSail, SIASAIL-1), 30 to ''Fan-like'' (e.g. MegaFlex), 31 to ''Spinning-Fold'' (e.g.…”

Section: Introductionmentioning

confidence: 99%

Configuration design and crease topology of origami-inspired spinning space deployable structures

Tang,

Liu,

et al. 2024

Proceedings of the Institution of Mechanical Engineers, Part C:

Self Cite

View full text Add to dashboard Cite

Origami-inspired space deployable structures can be transformed from the folded states into the deployed states in orbit, which satisfied the demands of complex space missions and had been widely used in the space field. It remains to be investigated how the space deployable structures realized a large deployable ratio in the crease design process of origami patterns for the storage space limitation of spacecraft structures. Origami-inspired Regular Polygons Deployable Structures (RPDS) were proposed by designing the origami configurations and analyzing the deployable mechanism from existing space deployable structures, and a novel crease topology with three different approaches was presented in repeating origami modules to enhance the deployable ratio. The topology results indicated that the deployable ratio of RPDS can be increased effectively by shortening the storage height or performing multi-stage deployment, and the flexibility of RPDS can be verified by changing the shape of the central body. The configuration rationality and deployable reliability of RPDS are confirmed by kinematic modeling and numerical simulation. This study provides new insights into extraordinary geometrical and folding properties of origami-inspired deployable structures via configuration design and crease topology, which can be extended to other origami patterns in various origami-inspired applications.

show abstract

SIASAIL-I solar sail: From system design to on-orbit demonstration mission

Cited by 26 publications

References 28 publications

Two novel approaches for solving the contradiction between efficient penetration and low recoil for the low‐velocity penetrator

Two novel approaches for solving the contradiction between efficient penetration and low recoil for the low‐velocity penetrator

1U-Sized Deployable Space Manipulator for Future On-Orbit Servicing, Assembly, and Manufacturing

Configuration design and crease topology of origami-inspired spinning space deployable structures

Contact Info

Product

Resources

About