A Multicriteria Optimisation Design of SPSE for Adaptive LEO Satellites Missions Using the PSI Method

Ekpo, Sunday

doi:10.2514/6.2013-5470

Cited by 4 publications

(13 citation statements)

References 8 publications

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“…The abovementioned analysis was applied in the derivation of the mass allocation of HASS systems for communication, planetary, and meteorology missions based on past spacecraft historical database/missions and the American Institute of Aeronautics and Astronautics guidelines [1]- [3], [8].…”

Section: Satellite System Engineeringmentioning

confidence: 99%

“…The power estimations for the various subsystems are utilized to develop the link budget and the operational times [8] of the payload subsystem. The payload-based PER P t used to derive the total METSAT power requirements P T is given by [3]…”

Section: Table III Hass Mass Budget Analysis For a Meteorology Missionmentioning

confidence: 99%

“…The Clementine spacecraft, launched to image and map the moon surface, utilized two star trackers (each 4.5 W and 0.29 kg), an integrated laser ranger and high-resolution imager (9.5 W, 1.12 kg), long-wave infrared imager (13 W, 2.1 kg), near-infrared imager (11 W, 1.92 kg), and ultraviolet-visible imager (4.5 W, 0.41 kg). The system engineering design parameters [3], [8] The payload-based PER P t , which is used to derive the total planetary satellite system power requirements P T , is given by [3] P t = 1.13P pl + 122.…”

Section: Planetary Missionmentioning

confidence: 99%

“…Thus, all the HASS subsystems can directly access the resources of the other subsystems. In this paper, mass and power margins are the critical resources under investigation for achieving an optimal, economical, reliable, and sustainable capability-based small satellite mission [1], [8], [9].…”

Section: Introductionmentioning

confidence: 99%

“…Other documented small satellite missions have been mission-based and application-specific [6] with no particular published guiding system engineering design principles. Moreover, the integrated cost, size, weight, and power (C-SWaP) limitations of small satellites are not the core systemlevel design considerations [8] since commercial-off-the-shelf components are often favored for this type of mission. Ekpo and George [5] and Waseem and Sadiq [10] provide small satellite architecture technologies, and model-based systems engineering in conceptual design of small satellites that satisfy delineated "all-analog" and "all-digital" system designs only.…”

Section: Introductionmentioning

confidence: 99%

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Parametric System Engineering Analysis of Capability-Based Small Satellite Missions

Ekpo

2019

IEEE Systems Journal

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To achieve appropriate link budget and system engineering analyses of capability-based small satellites missions, an objective assessment and computation of the component-, subsystem-, and system-levels parameters requirements must be carried out. This paper presents the measurement-derived parametric models for the system engineering analysis of communication, meteorology, planetary, and other small satellite programs with recourse to the initial mission, conceptual design, and postmission objectives. Mass and power margins are the critical resources under investigation besides the link contingencies and operational times. The case study spacecraft systems engineering analyses indicate a transmit power for data transmission uplink and downlink of at least 33 dBm for the generic communication, meteorology, and planetary missions applications. The presented parametric models also reveal a signal-to-noise ratio of at least 16 dB per radio communication link for worst case noise floor and path loss. For a 30-W power utilization, a two-power communicationoverpower mode mission operates for an extra 8.3 min compared with a three-power payload-overpower mode mission. This holds a great promise for the development of adaptive subsystems for reconfigurable multiband, and multistandard transponders for multipurpose missions and postmission applications.

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Section: Satellite System Engineeringmentioning

confidence: 99%

Section: Table III Hass Mass Budget Analysis For a Meteorology Missionmentioning

confidence: 99%

Section: Planetary Missionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Parametric System Engineering Analysis of Capability-Based Small Satellite Missions

Ekpo

2019

IEEE Systems Journal

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Metasurface-Backed Polarization-Diversified Microstrip Patch Antenna for Biomedical Multi-communication Applications

Ghosh,

Saha,

Chakraborty

et al. 2024

Signals and Communication Technology

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Thermal Subsystem Operational Times Analysis for Ubiquitous Small Satellites Relay in LEO

Ekpo

2018

IREASE

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The success of the satellite subsystems engineering depends on the optimal design, modeling, simulation, and validation of the deliverables of the conceptual and mission design objectives. This paper presents the operational times analysis of the thermal control subsystem onboard a 97-kg microsatellite in low-Earth orbit during an eclipse period. Power-storing, communication downlink and uplink, payload processing, and thermal control overpower modes were implemented for a communication mission under worst-case orbital patterns. An embedded digital temperature and lighting controller circuitry was designed and practically validated to effect a desired logic. For an average eclipse period of 34.4 mins, the operational times of the thermal subsystem at altitudes of 400 km, 500 km, and 600 km are 38.6 mins, 38.1 mins, and 37.7 mins respectively. Moreover, the thermal control subsystem simulation reveals that reducing the operational times of non-thermal control subsystems during the eclipse period by 50 % can result in an operational factor of safety of over 1.5. At least 10 dB data link transmission margin can be achieved. The reported findings show that the operational times of spacecraft subsystems overpower modes can be reconfigured in orbit to reliably sustain the operating conditions of the capability-based satellite components for ubiquitous communication.

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A Multicriteria Optimisation Design of SPSE for Adaptive LEO Satellites Missions Using the PSI Method

Cited by 4 publications

References 8 publications

Parametric System Engineering Analysis of Capability-Based Small Satellite Missions

Parametric System Engineering Analysis of Capability-Based Small Satellite Missions

Metasurface-Backed Polarization-Diversified Microstrip Patch Antenna for Biomedical Multi-communication Applications

Thermal Subsystem Operational Times Analysis for Ubiquitous Small Satellites Relay in LEO

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