S band TT&amp;C antennas integrated with optical camera system for nanosatellites

Karibayev, B.A.; Meirambekuly, Nursultan; Namazbayev, Timur; Temirbayev, Amirkhan A.; Kadylbekkyzy, Elvira; Yessentaeva, Aidana

doi:10.1109/icecet55527.2022.9872558

Cited by 1 publication

(2 citation statements)

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“…2 [14]. In these studies, we did not demonstrate the advantage of this new approach in terms of energy budget optimization.…”

Section: Introductionmentioning

confidence: 75%

“…One of the approaches is using integrated antenna systems with solar panels or payloads. By integrating antennas into the surface area of the CubeSat, it becomes possible to simultaneously utilize the limited space for both communication and power generation purposes [10][11][12][13][14]. This integration eliminates the need for separate dedicated antenna structures, saving valuable space and reducing the overall size and weight of the CubeSat.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Reducing Energy Consumption in CubeSat Missions: The Integrated Antenna Approach

Ibrayev,

Meirambekuly,

Karibayev

et al. 2023

Preprint

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One of the future challenges of increasing the harnessed solar power is efficiency using of CubeSat sides. One of the approaches is using integrated antenna systems with solar panels or payloads. This study proposes a new approach to the use of integrated antenna systems in remote sensing missions. In this approach, due to the integration of antenna system with payload (in our case, with camera), it is possible to achieve a significant increase in the power generation. Calculations are carried out for cases when the antenna system are integrated with the optical system (α = 0°), which implies that they use one plane, in the second case they are spaced at an angle of α = 90° and in the third case when they are directed to opposite sides (α =180°). In the case of α = 0°, where the camera and antenna module are aligned co-axially, there is no energy expenditure for CubeSat orientation. However, in the other two cases, energy is required for rotation and maintenance of the specified orientation throughout the entire duration of the satellite's flight over the ground station, amounting to 111.99 mW when α = 90° and 44.33 mW when α = 180°.

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“…2 [14]. In these studies, we did not demonstrate the advantage of this new approach in terms of energy budget optimization.…”

Section: Introductionmentioning

confidence: 75%