Statistical reliability analysis of satellites by mass category: Does spacecraft size matter?

Dubos, Gregory F.; Castet, Jean‐François; Saleh, Joseph H.

doi:10.1016/j.actaastro.2010.04.017

Cited by 43 publications

(20 citation statements)

References 8 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In order to observe the effects of the failure rate on the optimized spare strategy solutions, a sensitivity analysis is performed for several values of failure rates. As can be derived from [34] and [35], failure rates can range from 0.001 to 0. The relative percentage of savings when using our unique multi-echelon approach using parking orbits compared to a single level of in-plane spares only is analyzed with respect to the TESSAC of each strategy.…”

Section: Sensitivity Analysismentioning

confidence: 99%

Optimal Satellite Constellation Spare Strategy Using Multi-Echelon Inventory Control

Jakob

Shimizu

Yoshikawa

et al. 2019

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

The recent growing trend to develop large-scale satellite constellations (i.e., mega-constellation) with low-cost small satellites has brought the need for an efficient and scalable maintenance strategy decision plan. Traditional spare strategies for satellite constellations cannot handle these mega-constellations due to their limited scalability in the number of satellites and/or frequency of failures. In this paper, we propose a novel spare strategy using an inventory management approach. We consider a set of parking orbits at a lower altitude than the constellation orbits for spare storage, and model the satellite constellation spare strategy problem using a multi-echelon (s,Q)-type inventory policy, viewing the Earth's ground as a supplier, the parking orbit spare stocks as warehouses, and the in-plane spare stocks as retailers. The accuracy of the proposed analytical model is assessed using simulations via Latin Hypercube Sampling. Furthermore, based on the proposed model, an optimization formulation is introduced to identify the optimal spare strategy, comprising the parking orbits' characteristics and all locations' policies, to minimize the maintenance cost of the system given performance requirements. The proposed model and optimization method are applied to a real-world satellite mega-constellation case to demonstrate their value. Nomenclature cap launch = Launch capacity (number of possible satellites per rocket), in units of satellites D plane = Demand for in-plane spares, in units of satellites D parking = Demand for parking spares, in units of batches Q plane E S plane = Expected number of backorders for in-plane spares over a replenishment cycle, in units of satellites

show abstract

Section: Sensitivity Analysismentioning

confidence: 99%

Optimal Satellite Constellation Spare Strategy Using Multi-Echelon Inventory Control

Jakob

Shimizu

Yoshikawa

et al. 2019

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

show abstract

“…The first study, produced as a follow-up paper to Castet and Saleh's survey, was performed by Dubos and investigates whether satellite reliability can be related to satellite size [25]. The same 1548 satellites from their previous paper were split into three groups according to mass: small (0-500 kg), medium (500-2500 kg) and large (>2500 kg).…”

Section: The Poor Reliability Of Low-cost Satellitesmentioning

confidence: 99%

“…The resultant reliability plots, derived through analytical means for the traditional microsatellite's avionics and simulation for the multicellular system, are shown in Figure 7. 25. In contrast to the CubeSat-scale system, the microsatellite-scale multicellular architecture shows a reliability advantage over the traditional, cross-strapped design, in all modes of operation.…”

Section: Reliability Comparisonmentioning

confidence: 99%

See 1 more Smart Citation

A multicellular architecture towards low-cost satellite reliability

Erlank

Bridges

2015

2015 NASA/ESA Conference on Adaptive Hardware and Systems (AHS)

View full text Add to dashboard Cite

A new class of low-cost satellites has the potential to reduce the cost of traditional space-based services. Unfortunately, to date, low-cost satellites have proven to suffer from poor reliability. While traditional techniques for increasing reliability are well known to satellite developers, these techniques are poorly suited for implementation on low-cost satellites due to intrinsic budgetary, mass and volume constraints. This research proposes that alternative techniques for increasing system reliability can be derived by studying biological organisms, which have proven their robustness by inhabiting even the harshest locations on earth. Both unicellular and multicellular organisms are examined. The result is a conceptual system architecture, based on initially identical, reconfigurable hardware blocks, or artificial cells, and a decentralized task management strategy. This multicellular architecture is described in detail. Finally, preliminary details of a planned implementation are given. This implementation aims to demonstrate that a significant portion of traditional satellite avionics can be replaced by the proposed artificial cells

show abstract

“…These studies are narrow in scope and lack a generalized methodology for the broader process of mission design and development. The third category is related to mission failures, whether review of missions or probabilistic analysis of system reliability [5,6,7]. According to [7], in a survey of 2500 spacecraft failures, 25% of the problems were attributed to design (functionality), 20% due to the environment and 24% were parts and quality related.…”

Section: Introductionmentioning

confidence: 99%

Rapid, automated, test, verification and validation for the CubeSats

2019

View full text Add to dashboard Cite

From the experiences learned in the ZA-CUBE-1 mission, bringing up of a small-scale mission assurance facility is reported. The first of a series of actions envisaged to accomplish the facility is achieving functional test and verification, and the same under modest temperature cycling. The former is initiated by setting up a test and measurement system comprising of the legacy equipment from the previous space project, while a thermal chamber is procured as a first-pass of environmental validation. The test system is driven autonomously using a highly pliant software controller, which is the executable tool for the conceived methodology of systems engineering life cycle and mission assurance. Besides automated electrical and temperature measurements, the software has been crafted to accommodate for Phase B/C deliverables by way of simulations, virtual prototypes, emulation of operation scenarios with hardware tools and the mission software-all unified in a single platform. The system is exploited in validating a S-band transmitter while economizing time, and in obtaining valuable insight in transmission performance over thermal loads, which may result in revising the mission requirements and impacting satellite system parameters. The goal of the work is to shorten the iterative mission engineering in top-down and bottom-up cycles, through automation and, ultimately ensure substantial consistency and traceability in the design flow.

show abstract

Statistical reliability analysis of satellites by mass category: Does spacecraft size matter?

Cited by 43 publications

References 8 publications

Optimal Satellite Constellation Spare Strategy Using Multi-Echelon Inventory Control

Optimal Satellite Constellation Spare Strategy Using Multi-Echelon Inventory Control

A multicellular architecture towards low-cost satellite reliability

Rapid, automated, test, verification and validation for the CubeSats

Contact Info

Product

Resources

About