System-Level Multicriteria Modelling of Payload Operational Times for Communication Satellite Missions in LEO

Ekpo, Sunday; Adebisi, Bamidele; George, Danielle; Kharel, Rupak; Uko, Mfon C.

doi:10.2174/2210687104666140620221119

Cited by 9 publications

(25 citation statements)

References 32 publications

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“…Based on the database of past spacecraft missions, the communication and planetary spacecraft would require at least 56 and 122 W, respectively, for an appreciable mission accomplishment [1]. From (11), the total in-orbit PERs of capability-based microsatellites for communication missions in LEO are similar to the case studies 1 and 2 in (12) and (13). Table IV shows the HASS power budget analysis for a communication mission.…”

Section: B Communication Missionmentioning

confidence: 86%

“…Single-use, computer-aided models for conceptual design represent a system engineering design process tool for the entire spacecraft modules and their respective integrated subsubsystems and subsystems [2], [3], [11]- [13]. This approach allows for a more detailed analysis of the spacecraft subsystems and their interdependencies than the back-of-the-envelope technique.…”

Section: Satellite System Engineeringmentioning

confidence: 99%

“…where k is the power per unit mass or specific power (W/kg) for each satellite category, f (P pl ) is the payload power (W), and C is a mission-based power constant (W) [1], [3]. Equation (11) represents the complete in-orbit total spacecraft power budget function for the conceptual design of a capability-based small satellite system. Table I states the core bus subsystem power allocation for capability-based small satellite systems (such as an HASS) [1].…”

Section: Satellite System Engineeringmentioning

confidence: 99%

“…From (11), the total in-orbit PERs of capability-based small satellites for meteorology missions in LEO are presented as follows: 1) Microsatellites Case study 1…”

Section: A Meteorology Missionmentioning

confidence: 99%

“…Ekpo and George [5] considers the design methodology of adaptive small satellites that enables an optimal architecture for a mission. Ekpo and George [5] and and Ekpo et al [11] explore the fact that an adaptive small satellite design problem is a multicriteria optimization design problem that must be judiciously assessed for a cost-effective first-pass success. The parametric models presented in this paper cover other satellite missions as well with an allowance for adapting the models to suit next-and future-generation satellite system engineering design processes.…”

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: B Communication Missionmentioning

confidence: 86%

Section: Satellite System Engineeringmentioning

confidence: 99%

Section: Satellite System Engineeringmentioning

confidence: 99%

“…From (11), the total in-orbit PERs of capability-based small satellites for meteorology missions in LEO are presented as follows: 1) Microsatellites Case study 1…”

Section: A Meteorology Missionmentioning

confidence: 99%