Special Issue "Vibration Control for Space Application"

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: closed (31 August 2021).

Special Issue Editor

Prof. Dr. Hyun-Ung Oh
E-Mail Website
Guest Editor
Department of Smart Vehicle System Engineering, CHOSUN University, 309 Pilmun-daero, Dong-gu, Gwangju 61452, Korea
Interests: satellite and payload thermo-mechanical system; cube satellite system and relevant technologies; vibration control for space applications; smart materials and structures for space applications; spaceborne mechanism; on-orbit thermal design and control; multi-functional structure; spaceborne electronics thermo-mechanical design; satellite AIT (Assembly Integration and Test)

Special Issue Information

Dear Colleagues,

“New Space” paradigm covers the mass production of small satellites for reaching orbit at low cost constellation mission. Vibration control strategy would be attractive to achieve a goal of “New Space” paradigm such as better, faster, cheaper and lighter satellite. To ensure the performance of high-resolution observation satellites, on-orbit vibration management is one of the important tasks to isolate the micro-jitter from the various disturbance sources such as reaction wheel assembly, gimbal-type antenna, cryogenic cooler and solar array driving mechanism. This shall be strictly managed especially for small satellites with a limited mass, volume area and budgets. Launch vibration load attenuation strategy also contributes on achieving a lower and shorter development cost and period and lighter-weight small satellite by reducing the design load and vibration test specifications for on-board components.

This special issue encompasses all aspects of vibration phenomena for on-orbit and launch vibration environments and their control methodologies based on passive, active and semi-active approaches for space applications. The scope covers technical topics such as: on-orbit vibration and control for large flexible structure and disturbance sources with mechanical moving parts; launch vibration and control for whole spacecrafts, payloads and launch vehicles; low shock holding and release mechanism and applications of using smart materials for vibration control of space structures. The special issue also includes dynamic behavior of deployment mechanism, structural design and vibration test of a novel small satellite system including CubeSat.

Prof. Dr. Hyun-Ung Oh
Guest Editor

Manuscript Submission Information

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Keywords

  • Vibration control
  • Damping
  • Small satellite
  • Launch vibration environmnet
  • Micro-jitter

Published Papers (6 papers)

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Research

Article
Modeling and Simulation of Heavy-Lift Tethered Multicopter Considering Mechanical Properties of Electric Power Cable
Aerospace 2021, 8(8), 208; https://doi.org/10.3390/aerospace8080208 - 01 Aug 2021
Viewed by 428
Abstract
In case of a fire at a high-rise building which is densely populated, an extension ladder is used to rescue people who have yet to evacuate to a safe place away from the fire, whereas those who are stranded at a height that [...] Read more.
In case of a fire at a high-rise building which is densely populated, an extension ladder is used to rescue people who have yet to evacuate to a safe place away from the fire, whereas those who are stranded at a height that is unreachable with the ladder should be promptly saved with different rescue methods. In this case, an application of the tethered flight system capable of receiving power over a power cable from the ground to a multicopter may guarantee effective execution of the rescue plan at the scene where fire is raging without any restrictions of the flight time. This article identified restrictions that should be considered in the design of a multicopter capable of tethered flight aimed to rescue stranded people at an inaccessible location with an extension ladder at a fire-ravaged high-rise building and assessed its feasibility. A power cable capable of providing dozens of kilowatts of electricity should be installed to enable the implementation of the rescue mission using the tethered multicopter. A flexible multi-body dynamics modeling and simulation with viscoelastic characteristics and heavy weight of power cable were carried out to evaluate the effects of such cable of the tethered flight system on the dynamic characteristics of the multicopter. The results indicate that as for a heavy-lift tethered multicopter designed to be utilized for rescue operations, the properties of the power cable, such as weight, rigidity and length, have a major impact on the position and attitude control performance. Full article
(This article belongs to the Special Issue Vibration Control for Space Application)
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Article
New Version of High-Damping PCB with Multi-Layered Viscous Lamina
Aerospace 2021, 8(8), 202; https://doi.org/10.3390/aerospace8080202 - 26 Jul 2021
Viewed by 416
Abstract
In a previous study, a high-damping printed circuit board (PCB) implemented by multilayered viscoelastic acrylic tapes was investigated to increase the fatigue life of solder joints of electronic packages by vibration attenuation in a random vibration environment. However, the main drawback of this [...] Read more.
In a previous study, a high-damping printed circuit board (PCB) implemented by multilayered viscoelastic acrylic tapes was investigated to increase the fatigue life of solder joints of electronic packages by vibration attenuation in a random vibration environment. However, the main drawback of this concept is its inability to mount electronic parts on the PCB surface area occupied by interlaminated layers. For the efficient spatial accommodation of electronics, this paper proposes a new version of a high-damping PCB with multilayered viscoelastic tapes interlaminated on a thin metal stiffener spaced from a PCB. Compared to the previous study, this concept ensures efficient utilization of the PCB area for mounting electronic parts as well as the vibration attenuation capability. Free vibration tests were performed at various temperatures to obtain the basic characteristics of the proposed PCB. The effectiveness of the proposed PCB was verified by random vibration fatigue tests of sample PCBs with various numbers of viscoelastic layers to compare the fatigue life of electronic packages. Full article
(This article belongs to the Special Issue Vibration Control for Space Application)
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Article
High Damping Passive Launch Vibration Isolation System Using Superelastic SMA with Multilayered Viscous Lamina
Aerospace 2021, 8(8), 201; https://doi.org/10.3390/aerospace8080201 - 26 Jul 2021
Viewed by 444
Abstract
Whole-spacecraft launch-vibration isolation systems are attractive for achieving the goal of better, faster, cheaper, and lighter small satellites by reducing the design-load and vibration-test specifications for on-board components. In this study, a three-axis passive launch-vibration isolation system, based on superelastic shape memory alloy [...] Read more.
Whole-spacecraft launch-vibration isolation systems are attractive for achieving the goal of better, faster, cheaper, and lighter small satellites by reducing the design-load and vibration-test specifications for on-board components. In this study, a three-axis passive launch-vibration isolation system, based on superelastic shape memory alloy (SMA) technology, was developed to significantly attenuate the dynamic launch loads transmitted to a small satellite. This provides a superior damping characteristic, achieved by superelastic SMA blades stiffened by multilayered thin plates with viscous lamina adhesive layers of acrylic tape. The basic characteristics of the proposed isolation system with various numbers of viscoelastic multilayers were obtained through a static load test. In addition, the effectiveness of the design was validated through a launch environment simulating sine and random vibration tests. Full article
(This article belongs to the Special Issue Vibration Control for Space Application)
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Article
Experimental CanSat Platform for Functional Verification of Burn Wire Triggering-Based Holding and Release Mechanisms
Aerospace 2021, 8(7), 192; https://doi.org/10.3390/aerospace8070192 - 16 Jul 2021
Viewed by 514
Abstract
In this study, we present the Diverse Holding and Release Mechanism Can Satellite (DHRM CanSat) platform developed by the Space Technology Synthesis Laboratory (STSL) at Chosun University, South Korea. This platform focuses on several types of holding and release mechanisms (HRMs) for application [...] Read more.
In this study, we present the Diverse Holding and Release Mechanism Can Satellite (DHRM CanSat) platform developed by the Space Technology Synthesis Laboratory (STSL) at Chosun University, South Korea. This platform focuses on several types of holding and release mechanisms (HRMs) for application in deployable appendages of nanosatellites. The objectives of the DHRM CanSat mission are to demonstrate the design effectiveness and functionality of the three newly proposed HRMs based on the burn wire triggering method, i.e., the pogo pin-type HRM, separation nut-type HRM, and Velcro tape-type HRM, which were implemented on deployable dummy solar panels of the CanSat. The proposed mechanisms have many advantages, including a high holding capability, simultaneous constraints in multi-plane directions, and simplicity of handling. Additionally, each mechanism has distinctive features, such as spring-loaded pins to initiate deployment, a plate with a thread as a nut for a high holding capability, and a hook and loop fastener for easy access to subsystems of the satellite without releasing the holding constraint. The design effectiveness and functional performance of the proposed mechanisms were demonstrated through an actual flight test of the DHRM CanSat launched by a model rocket. Full article
(This article belongs to the Special Issue Vibration Control for Space Application)
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Article
Numerical Evaluation of Structural Safety of Linear Actuator for Flap Control of Aircraft Based on Airworthiness Standard
Aerospace 2021, 8(4), 104; https://doi.org/10.3390/aerospace8040104 - 07 Apr 2021
Viewed by 727
Abstract
Airworthiness standards of Korea recommend verifying structural safety by experimental tests and analytical methods, owing to the development of analysis technology. In this study, we propose a methodology to verify the structural safety of aircraft components based on airworthiness requirements using an analytical [...] Read more.
Airworthiness standards of Korea recommend verifying structural safety by experimental tests and analytical methods, owing to the development of analysis technology. In this study, we propose a methodology to verify the structural safety of aircraft components based on airworthiness requirements using an analytical method. The structural safety and fatigue integrity of a linear actuator for flap control of aircraft was evaluated through numerical analysis. The static and fatigue analyses for the given loads obtained from the multibody dynamics analysis were performed using the finite element method. Subsequently, the margin of safety and vulnerable area were acquired and the feasibility of the structural safety evaluation using the analytical method was confirmed. The proposed numerical analysis method in this study can be adopted as an analytical verification methodology for the airworthiness standards of civilian aircraft in Korea. Full article
(This article belongs to the Special Issue Vibration Control for Space Application)
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Article
Development of a Novel Deployable Solar Panel and Mechanism for 6U CubeSat of STEP Cube Lab-II
Aerospace 2021, 8(3), 64; https://doi.org/10.3390/aerospace8030064 - 05 Mar 2021
Viewed by 902
Abstract
The structural safety of solar cells mounted on deployable solar panels in the launch vibration environment is a significant aspect of a successful CubeSat mission. This paper presents a novel highly damped deployable solar panel module that is effective in ensuring structural protection [...] Read more.
The structural safety of solar cells mounted on deployable solar panels in the launch vibration environment is a significant aspect of a successful CubeSat mission. This paper presents a novel highly damped deployable solar panel module that is effective in ensuring structural protection of solar cells under the launch environment by rapidly suppressing the vibrations transmitting through the solar panel by constrained layer damping achieved using printed circuit board (PCB)-based multilayered thin stiffeners with double-sided viscoelastic tapes. A high-damping solar panel demonstration model with a three-pogo pin-based burn wire release mechanism was fabricated and tested for application in the 6U CubeSat “STEP Cube Lab-II” developed by Chosun University, South Korea. The reliable release function and radiation hardness assurance of the mechanism in an in-orbit environment were confirmed by performing solar panel deployment tests and radiation tests, respectively. The design effectiveness and structural safety of the proposed solar panel module were validated by launch vibration and in-orbit environment tests at the qualification level. Full article
(This article belongs to the Special Issue Vibration Control for Space Application)
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