A large ring deployable mechanism for space satellite antenna

Qi, Xiaozhi; Huang, Hailin; Li, Bing; Deng, Zongquan

doi:10.1016/j.ast.2016.09.014

Cited by 107 publications

(23 citation statements)

References 11 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Accordingly, the y-axis assembly clearance range runs from À2r jy to + 2r jy , while the z-axis assembly clearance range runs from À2r jz to + 2r jz . This can be expressed using equations (6) and (7) in the local coordinates…”

Section: Assembly Errors Between a Linkage And Spring Hingementioning

confidence: 99%

Design, fabrication, and evaluation of a passive deployment mechanism for deployable space telescope

Choi

Lee

Hwang

et al. 2019

Advances in Mechanical Engineering

View full text Add to dashboard Cite

This article presents a high precise deployment mechanism for a deployable space telescope to facilitate satellite miniaturization. It is designed with a passive deployment mechanism utilizing a spring hinge. In particular, the customized modules and an assembly jig are specifically designed to reduce alignment errors. To confirm the feasibility of the designed mechanism, three alignment errors that influence the optical performance of the structure-tilt, de-center, and despace-are theoretically analyzed for quarter, half, and full model, respectively. In the case of quarter model, significant results are obtained as a tilt of 21.12 mrad, a de-center of 2.20 mm, and a de-space of 1.71 mm. Based on the theoretical analysis, a deployment mechanism of the quarter model is fabricated, and the alignments of the deployment mechanism are experimentally investigated with a measurement platform consisting of five non-contact-based laser displacement sensors. In addition, the influence of gravity on the alignment error is analyzed and compensated by investigating the tendency of the alignment error according to the rotation degree of the measurement model for the direction of gravity. As a result of the gravity compensation, the proposed mechanism gives acceptable alignment errors as a tilt of 30.04 mrad, de-center of 8.92 mm, and de-space of 4.03 mm, which are controllable by employing the conventional focusing mechanism.

show abstract

Section: Assembly Errors Between a Linkage And Spring Hingementioning

confidence: 99%

Design, fabrication, and evaluation of a passive deployment mechanism for deployable space telescope

Choi

Lee

Hwang

et al. 2019

Advances in Mechanical Engineering

View full text Add to dashboard Cite

show abstract

“…The feature of the compact storage and the ability to be deployed into the service configuration of a large geometric volume make deployable mechanisms a perfect solution for the on-orbit activities. Researchers are devoted to investigating the deployable space mechanisms from reflector antennas to telescopes, radars and solar panels (Qi et al 2016(Qi et al , 2017. The motivation of this paper is to develop a deployable end-effector and detumbling mechanism to capture tumbling debris targets.…”

Section: R a F Tmentioning

confidence: 99%

Design of a novel deployable mechanism for capturing tumbling debris

Sun

2019

Transactions of the Canadian Society for Mechanical Engineering

View full text Add to dashboard Cite

Large quantities of man-made debris from decades of space exploration threaten the safety of future space activities. It is therefore urgent to perform active debris removal missions to maintain access to usable orbital space. This paper proposes a novel deployable end-effector and detumbling mechanism to capture tumbling debris. Three mechatronic subsystems for capture, transmission, and actuation are highly integrated in the end-effector, allowing compact storage during space transport. Grippers composed of constant-torque hinges endow the mechanism with a deployable function and ensure a steady envelope by means of caging, without the need for precise tracking and complex control. With only one actuator, simultaneous motion of the six grippers is implemented by arranging gears in a unique manner. The grippers are optimally designed to enlarge their envelope while reducing weight. A contact detumbling mechanism, composed of three dampers along three axes, is also provided based on revolute friction to slow tumbling debris with residual angular momentum. Two slip rings are ingeniously embedded in each damper to transmit electricity under conditions of signal interference and cable interwinding. Simulations of capturing and detumbling demonstrate the feasibility and effectiveness of the proposed mechanism.

show abstract

“…After deploying, the mechanism become stable because of its built-in adaptive supporting components. The representative deployable mechanisms are divided into two types; one is the cylindrical deployable mechanism [9,10], and the other is the cone deployable mechanism [11]. In the field of aerospace applications, deployable mechanisms are widely used to build large space mechanisms, such as deployable masts and antennas, etc., which play a significant role in space missions, such as earth observation, telecommunication, scientific research, and so on.…”

Section: Introductionmentioning

confidence: 99%

Design and Experiment of Banana De-Handing Device Based on Symmetrical Shape Deployable Mechanism

et al. 2020

View full text Add to dashboard Cite

Aiming at the problem that the banana de-handing device has poor radial deployment to the banana bunch stalk during the mechanized banana de-handing procedure, this paper presented a ring deployable mechanism based on a set of planar seven-bar linkages. It consists of multiple basic deployable units, which has great folding/deploying performance and is suitable for manufacturing a banana de-handing device, the diameter of which can be variably larger. The kinematics analysis of the mechanism was done, and the trajectory in space was obtained. When the mechanism is fully deployed, the diameter is 164 mm. The ratio of the folded height to the deployed diameter is 0.732, the ratio of the folded diameter to the deployed diameter is 0.262, and the ratio of the folded volume to the maximum of the deployed volume is 0.069. An experimental prototype of 500, 500, and 768 mm in length, width, and height was manufactured, and the deploying performance was analyzed to show the feasibility. Finally, experimental results show that 71.43% of the banana hands are de-handed successfully. The mechanism has a great deploying effect on banana bunch stalk, and the quality of the banana crown incision is good.

show abstract

A large ring deployable mechanism for space satellite antenna

Cited by 107 publications

References 11 publications

Design, fabrication, and evaluation of a passive deployment mechanism for deployable space telescope

Design, fabrication, and evaluation of a passive deployment mechanism for deployable space telescope

Design of a novel deployable mechanism for capturing tumbling debris

Design and Experiment of Banana De-Handing Device Based on Symmetrical Shape Deployable Mechanism

Contact Info

Product

Resources

About