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) | Viewed by 47373

Special Issue Editor

School of Aerospace and Mechanical Engineering, Korea Aerospace University, 76, Hanggongdaehak-ro, Deogyang-gu, Goyang-si 10540, Gyeonggi-do, Republic of 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; thermo-mechanical design of spaceborne electronics; satellite AIT (Assembly Integration and Test)
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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

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Keywords

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

Published Papers (14 papers)

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Research

16 pages, 11035 KiB  
Article
Prediction and Validation of Landing Stability of a Lunar Lander by a Classification Map Based on Touchdown Landing Dynamics’ Simulation Considering Soft Ground
by Yeong-Bae Kim, Hyun-Jae Jeong, Shin-Mu Park, Jae Hyuk Lim and Hoon-Hee Lee
Aerospace 2021, 8(12), 380; https://doi.org/10.3390/aerospace8120380 - 06 Dec 2021
Cited by 5 | Viewed by 3161
Abstract
In this paper, a method for predicting the landing stability of a lunar lander by a classification map of the landing stability is proposed, considering the soft soil characteristics and the slope angle of the lunar surface. First, the landing stability condition in [...] Read more.
In this paper, a method for predicting the landing stability of a lunar lander by a classification map of the landing stability is proposed, considering the soft soil characteristics and the slope angle of the lunar surface. First, the landing stability condition in terms of the safe (=stable), sliding (=unstable), and tip-over (=statically unstable) possibilities was checked by dropping a lunar lander onto flat lunar surfaces through finite-element (FE) simulation according to the slope angle, friction coefficient, and soft/rigid ground, while the vertical touchdown velocity was maintained at 3 m/s. All of the simulation results were classified by a classification map with the aid of logistic regression, a machine-learning classification algorithm. Finally, the landing stability status was efficiently predicted by Monte Carlo (MC) simulation by just referring to the classification map for 10,000 input datasets, consisting of the friction coefficient, slope angles, and rigid/soft ground. To demonstrate the performance, two virtual lunar surfaces were employed based on a 3D terrain map of the LRO mission. Then, the landing stability was validated through landing simulation of an FE model of a lunar lander requiring high computation cost. The prediction results showed excellent agreement with those of landing simulations with a negligible computational cost of around a few seconds. Full article
(This article belongs to the Special Issue Vibration Control for Space Application)
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12 pages, 3073 KiB  
Article
Research on Control of Stewart Platform Integrating Small Attitude Maneuver and Vibration Isolation for High-Precision Payloads on Spacecraft
by Weichao Chi, He Ma, Caihua Wang and Tianyu Zhao
Aerospace 2021, 8(11), 333; https://doi.org/10.3390/aerospace8110333 - 07 Nov 2021
Cited by 9 | Viewed by 2163
Abstract
The Stewart platform, a classical mechanism proposed as the parallel operation apparatus of robots, is widely used for vibration isolation in various fields. In this paper, a design integrating both small attitude control and vibration isolation for high-precision payloads on board satellites is [...] Read more.
The Stewart platform, a classical mechanism proposed as the parallel operation apparatus of robots, is widely used for vibration isolation in various fields. In this paper, a design integrating both small attitude control and vibration isolation for high-precision payloads on board satellites is proposed. Our design is based on a Stewart platform equipped with voice-coil motors (VCM) to provide control force over the mechanism. The coupling terms in the dynamic equations of the legs are removed as the total disturbance by the linear active disturbance rejection control (LADRC). Attitude maneuver and vibration isolation performance is verified by numerical simulations. Full article
(This article belongs to the Special Issue Vibration Control for Space Application)
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19 pages, 4323 KiB  
Article
Thermo-Mechanical Design and Validation of Spaceborne High-Speed Digital Receiver Unit for Synthetic Aperture Radar Application
by Soo-Jin Kang, Sung-Woo Park, Hye-Yoon Choi, Gu-Hyun Ryu, Jong-Pil Kim, Sung-Hoon Jung, Se-Young Kim, Hyon-Ik Lee and Hyun-Ung Oh
Aerospace 2021, 8(10), 305; https://doi.org/10.3390/aerospace8100305 - 16 Oct 2021
Cited by 2 | Viewed by 2150
Abstract
This paper presents the effectiveness of the thermo-mechanical design of a high-speed digital receiver unit (HSDRU) developed for spaceborne synthetic aperture radar applications. The main features of HSDRU’s thermo-mechanical design include the thermal management of high-heat dissipation units by adopting heat sinks with [...] Read more.
This paper presents the effectiveness of the thermo-mechanical design of a high-speed digital receiver unit (HSDRU) developed for spaceborne synthetic aperture radar applications. The main features of HSDRU’s thermo-mechanical design include the thermal management of high-heat dissipation units by adopting heat sinks with the additional function of structural stiffeners and securing the heat rejection path to the upper side of electronics that interfaces the foil radiator for the on-orbit passive thermal control of electronics exposed to deep space environments. The thermal design, which adopts a thermal gap pad, is closely related to the solder joint fatigue life in a launch vibration environment, owing to its initial compressive static load between the heat sink and heat dissipation units that enhances the heat transfer capability. The effectiveness of the design was validated via the qualification level of launch environment tests. Full article
(This article belongs to the Special Issue Vibration Control for Space Application)
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14 pages, 8243 KiB  
Article
Design of Robust Control System of Magnetic Suspension and Balance System through Harmonic Excitation Simulation
by Dong-Kyu Lee
Aerospace 2021, 8(10), 304; https://doi.org/10.3390/aerospace8100304 - 15 Oct 2021
Viewed by 1339
Abstract
The magnetic suspension and balance system (MSBS) uses magnetic force and moment to precisely control the movement of the test object located at the center of the test section without mechanical contact, and at the same time measure the external force acting on [...] Read more.
The magnetic suspension and balance system (MSBS) uses magnetic force and moment to precisely control the movement of the test object located at the center of the test section without mechanical contact, and at the same time measure the external force acting on the test object. If such an MSBS is installed around the test section of the wind tunnel so that the position and attitude angle of the test object follow the harmonic function, various vibration tests can be performed on structures subjected to aerodynamic loads without the influence of the mechanical support. Because the control force and moment in the MSBS is generated by a number of electromagnets located around the test section, it is necessary to apply the adaptive control algorithm to the position and attitude control system so that the experiment can be carried out stably despite the sudden performance change of each electromagnet and electric power supply. In this study, a fault-tolerant position and attitude angle control system was designed through an adaptive control algorithm, and the effectiveness was verified through simulation under the condition that the electric power supply of MSBS failed. Full article
(This article belongs to the Special Issue Vibration Control for Space Application)
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18 pages, 8975 KiB  
Article
An Evaluation Method for Dry Friction Damping of Ring Damper in Gas Turbine Engines under Axial Vibration
by Shimin Gao and Yanrong Wang
Aerospace 2021, 8(10), 302; https://doi.org/10.3390/aerospace8100302 - 15 Oct 2021
Cited by 4 | Viewed by 2014
Abstract
The blisks and labyrinth seals in gas turbine engines are typical rotating periodic structures. Vibration problems will inevitably occur during the operation, which can easily lead to High Cycle Fatigue failure of the structure. Adding ring damper is an effective means of structural [...] Read more.
The blisks and labyrinth seals in gas turbine engines are typical rotating periodic structures. Vibration problems will inevitably occur during the operation, which can easily lead to High Cycle Fatigue failure of the structure. Adding ring damper is an effective means of structural vibration reduction. The damper uses the dry friction of the contact surface to dissipate the vibration energy, improve the damping of the system, and then reduce the vibration response of the structure. The structures have a nodal diameter and modal shape, and the forced vibration often presents the characteristics of traveling wave. In this paper, an evaluation method for dry friction damping of ring damper under the axial component of traveling wave vibration is established. For the given vibration stress at the critical location, the equivalent damping ratio provided by the ring damper is calculated based on the friction energy dissipation and the damping characteristic curve that is the equivalent damping ratio varying with the vibration stress is obtained. This method can avoid calculating the nonlinear dry friction forced response and is suitable for the design stage. The damping of split ring dampers with rectangular section for one blisk and labyrinth seal is analyzed in this paper. It is shown that rotating speed, friction coefficient, section area and material density significantly influence the damping characteristics. There are many factors affecting the damping characteristics of the damping, so it is necessary to comprehensively consider various factors and multiple modes for vibration reduction design. Full article
(This article belongs to the Special Issue Vibration Control for Space Application)
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18 pages, 5018 KiB  
Article
Development of On-Board Tilt Mirror Calibration Mechanism without Holding and Release Mechanism
by Yeon-Hyeok Park, Mun-Shin Jo, Hun-Young Kim, Dai-Ho Ko and Hyun-Ung Oh
Aerospace 2021, 8(10), 284; https://doi.org/10.3390/aerospace8100284 - 01 Oct 2021
Viewed by 2330
Abstract
The on-board tilting mirror calibration mechanism has a mechanical driving part that helps to achieve the main functional modes of deployment and stow when calibrating a spaceborne imaging sensor. In general, it is necessary to consider a holding and release device in the [...] Read more.
The on-board tilting mirror calibration mechanism has a mechanical driving part that helps to achieve the main functional modes of deployment and stow when calibrating a spaceborne imaging sensor. In general, it is necessary to consider a holding and release device in the mechanism design, to secure the structural safety of the mechanical driving part in severe launch environments. However, in the present study, we proposed a novel design strategy based on mass balancing, to guarantee mechanical safety on the driving part of the tilt mirror mechanism, although the implementation of the holding and release mechanism was not considered in the design. The effectiveness of the proposed design was experimentally verified via launch vibration and life cycle tests. The test results demonstrated that the mechanism fulfills all the required functions, and the design approach proposed in this study is effective for ensuring mechanical safety on the driving part of the tilting mirror mechanism in severe launch vibration environments. Full article
(This article belongs to the Special Issue Vibration Control for Space Application)
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15 pages, 3350 KiB  
Article
Experimental Validation for the Performance of MR Damper Aircraft Landing Gear
by Bang-Hyun Jo, Dae-Sung Jang, Jai-Hyuk Hwang and Yong-Hoon Choi
Aerospace 2021, 8(9), 272; https://doi.org/10.3390/aerospace8090272 - 19 Sep 2021
Cited by 7 | Viewed by 2958
Abstract
The landing gear of an aircraft serves to mitigate the vibration and impact forces transmitted from the ground to the fuselage. This paper addresses magneto-rheological (MR) damper landing gear, which provides high shock absorption efficiency and excellent stability in various landing conditions by [...] Read more.
The landing gear of an aircraft serves to mitigate the vibration and impact forces transmitted from the ground to the fuselage. This paper addresses magneto-rheological (MR) damper landing gear, which provides high shock absorption efficiency and excellent stability in various landing conditions by adjusting the damping force using external magnetic field intensity. The performance and stability of an MR damper was verified through numerical simulations and drop tests that satisfied aviation regulations for aircraft landing gear. In this study, a prototype MR damper landing gear, a drop test jig, and a two-degree-of-freedom model were developed to verify the performance of the MR damper, with real-time control, for light aircraft landing gear. Two semi-active control algorithms, skyhook control and hybrid control, were applied to the MR damper landing gear. The drop tests were carried out under multiple conditions, and the results were compared with numerical simulations based on the mathematical model. It was experimentally verified that as the shock absorption efficiency increased, the landing gear’s cushioning performance significantly improved by 17.9% over the efficiency achieved with existing passive damping. Full article
(This article belongs to the Special Issue Vibration Control for Space Application)
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15 pages, 2988 KiB  
Article
Active Flutter Suppression of Smart-Skin Antenna Structures with Piezoelectric Sensors and Actuators
by Chang-Yull Lee and Ji-Hwan Kim
Aerospace 2021, 8(9), 257; https://doi.org/10.3390/aerospace8090257 - 11 Sep 2021
Cited by 3 | Viewed by 1868
Abstract
A smart-skin antenna structure is investigated for active flutter control with piezoelectric sensors and actuators. The skin antenna is designed as a multilayer sandwich structure with a dielectric polymer to perform the role of antenna or radar structures. The governing equations are developed [...] Read more.
A smart-skin antenna structure is investigated for active flutter control with piezoelectric sensors and actuators. The skin antenna is designed as a multilayer sandwich structure with a dielectric polymer to perform the role of antenna or radar structures. The governing equations are developed according to the first-order shear deformation theory, and von Karman strain–displacement relationships are used for the moderate geometrical nonlinearity. To consider the supersonic airflow, first-order piston theory is performed for the aerodynamic pressures. The linear quadratic regulator (LQR) method is applied as a control algorithm, and Newmark’s method is studied to obtain the numerical results. In the present study, the effects of placements and shape of piezoelectric patches are discussed on the flutter control of the model in detail. In addition, the numerical results show that the skin antenna model can effectively suppress the panel flutter behaviors of the model, optimal conditions of piezoelectric patches are obtained for skin antenna structures. Full article
(This article belongs to the Special Issue Vibration Control for Space Application)
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18 pages, 6712 KiB  
Article
Modeling and Simulation of Heavy-Lift Tethered Multicopter Considering Mechanical Properties of Electric Power Cable
by Hyeok-Min Kwon and Dong-Kyu Lee
Aerospace 2021, 8(8), 208; https://doi.org/10.3390/aerospace8080208 - 01 Aug 2021
Cited by 1 | Viewed by 2441
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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14 pages, 5416 KiB  
Article
New Version of High-Damping PCB with Multi-Layered Viscous Lamina
by Tae-Yong Park, Seok-Jin Shin and Hyun-Ung Oh
Aerospace 2021, 8(8), 202; https://doi.org/10.3390/aerospace8080202 - 26 Jul 2021
Cited by 2 | Viewed by 2827
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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14 pages, 2317 KiB  
Article
High Damping Passive Launch Vibration Isolation System Using Superelastic SMA with Multilayered Viscous Lamina
by Yeon-Hyeok Park, Seong-Cheol Kwon, Kyung-Rae Koo and Hyun-Ung Oh
Aerospace 2021, 8(8), 201; https://doi.org/10.3390/aerospace8080201 - 26 Jul 2021
Cited by 14 | Viewed by 4360
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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21 pages, 6337 KiB  
Article
Experimental CanSat Platform for Functional Verification of Burn Wire Triggering-Based Holding and Release Mechanisms
by Shankar Bhattarai, Ji-Seong Go and Hyun-Ung Oh
Aerospace 2021, 8(7), 192; https://doi.org/10.3390/aerospace8070192 - 16 Jul 2021
Cited by 4 | Viewed by 6636
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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14 pages, 6159 KiB  
Article
Numerical Evaluation of Structural Safety of Linear Actuator for Flap Control of Aircraft Based on Airworthiness Standard
by Dong-Hyeop Kim, Young-Cheol Kim and Sang-Woo Kim
Aerospace 2021, 8(4), 104; https://doi.org/10.3390/aerospace8040104 - 07 Apr 2021
Cited by 3 | Viewed by 3182
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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24 pages, 6631 KiB  
Article
Development of a Novel Deployable Solar Panel and Mechanism for 6U CubeSat of STEP Cube Lab-II
by Shankar Bhattarai, Ji-Seong Go, Hongrae Kim and Hyun-Ung Oh
Aerospace 2021, 8(3), 64; https://doi.org/10.3390/aerospace8030064 - 05 Mar 2021
Cited by 9 | Viewed by 5628
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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