Whole-spacecraft passive launch isolation

Wilke, Paul S.; Johnson, Conor D.; Fosness, Eugene R.

doi:10.2514/6.1997-1199

Cited by 5 publications

(4 citation statements)

References 1 publication

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“…This necessitates that system-level analysis be used in the design of any whole-spacecraft isolation system, specifically, full coupled loads analysis (CLA) using detailed models of launch vehicles, all payloads and adapters, and flight load events. 4 The introduction of the isolation system itself changes the dynamics of a launch system. Along with the typical design constraints of weight, volume and strength, restrictions on the allowable system effects help dictate the design of the isolators.…”

Section: Figure 6 Softride Design Methodology For Whole-spacecraft Lmentioning

confidence: 99%

ESPA: EELV Secondary Payload Adapter With Whole-Spacecraft Isolation for Primary and Secondary Payloads

Maly¹,

Wilke²,

Fowler³

et al. 2000

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Public reporting burden for the collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to a penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. ESPA will be implemented on the new generation of expendable launch vehicles, the Evolved Expendable Launch Vehicle-Medium (EELV-M) boosters. ESPA will provide a cost-effective means for launching up to six small satellites, plus a large primary payload, on a single booster, while minimizing added impacts on the primary payload. In fact, ESPA can improve the dynamic environment seen by the primary payload through the use of whole-spacecraft, passive isolation systems. Vibration or shock isolation systems will be available for primary payloads; shock isolation will be offered for all secondary spacecraft. With whole-spacecraft isolation for all payloads, the addition of secondary payloads to the launch stack is expected to be transparent to the primary payload dynamic environment. ESPA is expected to reduce the launch dynamic environment for all payloads while shrinking the cost of launching a small satellite to less than 5% of the cost of a dedicated launch vehicle.

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Section: Figure 6 Softride Design Methodology For Whole-spacecraft Lmentioning

confidence: 99%

ESPA: EELV Secondary Payload Adapter With Whole-Spacecraft Isolation for Primary and Secondary Payloads

Maly¹,

Wilke²,

Fowler³

et al. 2000

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“…Details of the SoftRide isolation system can be found in Refs. [16][17][18][19]. A model of the isolation resulting from a system such as SoftRide is created in the mirror model.…”

Section: Isolationmentioning

confidence: 99%

Vibroacoustic launch analysis and alleviation of lightweight, active mirrors

Cohan

Miller

2011

Opt. Eng

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Lightweight, active, silicon carbide mirrors can increase the capability of space-based optical systems. However, launch survival is a serious concern for such systems, with the vibrations and acoustics from launch threatening to damage the optics. Therefore, a dynamic, statespace launch model has been developed with which one can quickly analyze the survival probability of many designs and also directly analyze launch load alleviation techniques. This paper discusses the launch model from which launch stress and survival probability are obtained, as well as launch load alleviation techniques that may increase the probability of launch survival. Three launch load alleviation techniques are presented and analyzed: whole spacecraft isolation, passive shunt circuits using the existing embedded actuators, and active damping using the existing actuators. All of the techniques reduce the launch stress, but at the expense of mass and complexity. The launch model allows for early identification of lightweight, active mirror designs which will survive launch, and the alleviation techniques expand the feasible design space by decreasing the launch stress and increasing the probability of launch survival. C 2011 Society of Photo-Optical Instrumentation Engineers (SPIE).

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“…The whole-spacecraft vibration isolation usually requires a redesign of the adaptor with vibration isolation performance, but without changing the original structure of the satellite, or introduction of vibration isolation devices between the carrier rocket and the satellite [4]. A vibration isolator installed between the adapter and the payload to isolate the vibration load has been widely studied [5].…”

Section: Introductionmentioning

confidence: 99%

Dynamics Analysis of Active Variable Stiffness Vibration Isolator for Whole-Spacecraft Systems Based on Nonlinear Output Frequency Response Functions

Zhang

Zhu

et al. 2020

Acta Mech. Solida Sin.

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In order to improve the harsh dynamic environment experienced by heavy rockets during different external excitations, this study presents a novel active variable stiffness vibration isolator (AVS-VI) used as the vibration isolation device to reduce excessive vibration of the whole-spacecraft isolation system. The AVS-VI is composed of horizontal stiffness spring, positive stiffness spring, parallelogram linkage mechanism, piezoelectric actuator, acceleration sensor, viscoelastic damping, and PID active controller. Based on the AVS-VI, the generalized vibration transmissibility determined by the nonlinear output frequency response functions and the energy absorption rate is applied to analyze the isolation performance of the whole-spacecraft system with AVS-VI. The AVS-VI can conduct adaptive vibration suppression with variable stiffness to the whole-spacecraft system, and the analysis results indicate that the AVS-VI is effective in reducing the extravagant vibration of the whole-spacecraft system, where the vibration isolation is decreased up to above 65% under different acceleration excitations. Finally, different parameters of AVS-VI are considered to optimize the whole-spacecraft system based on the generalized vibration transmissibility and the energy absorption rate.

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Whole-spacecraft passive launch isolation

Cited by 5 publications

References 1 publication

ESPA: EELV Secondary Payload Adapter With Whole-Spacecraft Isolation for Primary and Secondary Payloads

ESPA: EELV Secondary Payload Adapter With Whole-Spacecraft Isolation for Primary and Secondary Payloads

Vibroacoustic launch analysis and alleviation of lightweight, active mirrors

Dynamics Analysis of Active Variable Stiffness Vibration Isolator for Whole-Spacecraft Systems Based on Nonlinear Output Frequency Response Functions

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