Regulated-Element Frost Beamformer for Vehicular Multimedia Sound Enhancement and Noise Reduction Applications

2018

IREASE

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.

Section: Resultsmentioning

confidence: 99%

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

2018

IREASE

“…Taking the derivative of equation ( 4) as a function of the receiver bandwidth with receiver 10 ln shows that a reconfigurable front receiver (LNA) subsystem [8], [22] would be an ideal device architecture for fiber communications application to achieve and sustain band noise figure regime for multi…”

Section: (mentioning

confidence: 99%

“…For the designed ematical is the operating frequency in GHz. The model represented by (6) has a coefficient of determination of = 8 GHz ce receiver sensitivity Taking the derivative of equation ( 4) as a function of constraints shows that a reconfigurable front [8], [22] would be an ideal integrated satellite communications application to achieve and sustain frequency…”

Section: Mfonobong Uko Sunday Ekpomentioning

confidence: 99%

“…Where the noise figure of the receiver front-end s changes over the operating bandwidth and with time, the relevant estimating relationship is utilized for circuit specific model validation. For the designed based math , is given by: shows that a reconfigurable front [8], [22] would be an ideal integrated satellite communications application to achieve and sustain band noise figure regime for multi…”

mentioning

confidence: 99%

See 1 more Smart Citation

8-12 GHz pHEMT MMIC Low-Noise Amplifier for 5G and Fiber-Integrated Satellite Applications

Uko

2020

IREASE

The fifth-generation (5G) radio access technology promises to revolutionise integrated earth-space communications applications for ubiquitous, seamless and broadband services. The assigned sub-6 GHz and millimetre-wave 5G frequencies require the sensitivity of the receiver front-end subsystem(s) to detect and amplify the desired signal at a noise floor of less than -90 dBm for a cost-effective infrastructure deployment. This paper presents a broadband Monolithic Microwave Integrated Circuit (MMIC) Low-Noise Amplifier (LNA) design based on a 0.15 µm gate length Indium Gallium Arsenide (InGaAs) pseudomorphic high electron mobility transistor (pHEMT) technology for 5G and fiber-integrated satellite communications applications. The designed three-stage 8-12 GHz LNA implements a common-source topology. The MMIC LNA subsystem performance demonstrates an industry-leading in-band gain response of 40 dB; a noise figure of 1.0 dB; and a power dissipation of 43 mW. For a constant bandwidth receiver, the sensitivity changes by approximately 1.5 dB over the operating satellite signal frequency. Similarly, for a variable bandwidth receiver, the sensitivity changes by approximately 1.5 dB over the channel bandwidth. Moreover, the sensitivity margin of the designed LNA is 40 dB and this holds a great promise for real-time radio access component-level reconfiguration applications.

“…This holds a great promise for reconfigurable low-noise amplifier architectures that can offer inorbit device-level reconfiguration for mission optimization [13]. This is applicable in distributed satellite networks (including satellite constellation, formation flying spacecraft, fractionated spacecraft, and swarms/clusters) [17], [18] with adaptive broadband beamforming [19], [20] capabilities. Most of the published works on distributed satellite systems emphasize formal representation and analysis [17] without the physical layer design constraints and enhancements.…”

Section: B Link Budget Analysismentioning

confidence: 99%

Parametric System Engineering Analysis of Capability-Based Small Satellite Missions

2019

IEEE Systems Journal

Self Cite

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.