scholarly journals Iluminasi Panel Surya pada Satelit Orbit Rendah Ekuatorial

2019 ◽  
Vol 7 (3) ◽  
pp. 480
Author(s):  
DESTI IKA SURYANTI ◽  
SRI RAMAYANTI ◽  
MOHAMMAD MUKHAYADI
Keyword(s):  
Design Process ◽  
Triple Junction ◽  
Low Cost ◽  
Solar Panel ◽  
Satellite Orbits ◽  
Small Satellite ◽  
Solar Panels ◽  
Efficient Design ◽  
Small Satellites ◽  
Satellite Design

ABSTRAKDesain satelit telah berkembang ke arah miniaturisasi untuk mengurangi biaya peluncuran. Satelit kecil menyediakan platform berbiaya rendah untuk misi luar angkasa. Salah satu permasalahan utama satelit kecil adalah terbatasnya ketersediaan daya. Karena ketersediaan daya diperlukan agar subsistem satelit dapat bekerja, maka pada proses desain satelit perlu dilakukan analisis dan estimasi ketersediaan daya selama satelit mengorbit dengan tetap mempertahankan kekompakan dan volume yang diberlakukan oleh standar. Penelitian ini bertujuan untuk mengetahui kondisi iluminasi matahari pada panel surya dari berbagai alternatif desain penempatan sehingga diperoleh sebuah desain yang efisien. Iluminasi maksimum sebuah panel surya triple junction yang terpasang secara body mounted pada satelit kurang lebih sebesar 60%. Berdasarkan hasil penelitian ini, kombinasi pemasangan 3 body mounted panel surya dan 2 simple deploy panel surya menghasilkan persentase iluminasi dua kali lipat dibandingkan 5 body mounted panel surya.Kata kunci: panel surya triple junction, iluminasi, body mounted, simple deploy, daya ABSTRACTSatellite design has envolved towards miniaturization to reduce launch costs. Small satellites provide a low-cost platform for space missions. One of the main problems with small satellites is the limited availability of power. Because the availability of power is needed so that the satellite subsystem can work, the satellite design process needs to analyze and estimated power availability as long as the satellite orbits while maintaining the compactness and volume imposed by the standard. This study aims to determine the conditions of solar illumination on solar panels from various alternative design placements in order to obtain an efficient design. Maximum illumination of triple junction solar panel mounted on a small satellite is approximately 60%. Based on the results of this study, the combination of installing 3 body mounted solar panels and 2 simple deploy solar panels produced twice the illumination percentage compared to 5 body mounted solar panels.Keywords: solar panel triple junction, illumination, body mounted, simple deploy, power

scholarly journals Low-profile tunable radiator for small satellite application

2017 ◽  
Vol 9 (7) ◽  
pp. 1397-1407
Author(s):  
Nevena Šaponjić ◽  
Tomislav Debogović ◽  
Frédéric Bongard ◽  
Pedro Robustillo-Bayon ◽  
Maria Carolina Vigano ◽  
...  
Keyword(s):  
High Frequency ◽  
Low Cost ◽  
Basic Element ◽  
Small Satellite ◽  
High Frequency Band ◽  
Small Satellites ◽  
Low Profile ◽  
Low Mass ◽  
Left And Right ◽  
Vibration Tests

A tunable radiator for space application has been developed to meet stringent requirements in terms of electrical and environmental specifications but also low mass, simple manufacturing and low cost. The element is based on the folded planar inverted F-antenna, with size of one quarter of wavelength. It is mechanically tunable to adjust input impedance for any various positions on the satellite body and possible obstacles and protrusions. Results in terms of radiation pattern, S parameters, shock and vibration tests are presented. The antenna operates in ultra-high frequency band (400 MHz) in linear polarization. It has been designed to act as the basic element for miniaturized multi-function antenna systems on board of small satellites that can operate in three different radiating modes and in both left and right hand circular polarizations.

Performance Evaluation of Fractal Array Antenna for Small Satellite Applications

2016 ◽  
Vol 3 (2) ◽  
pp. 356 ◽  
Author(s):  
Yemane Ghebremedhin Teklehaimanot ◽  
Sinshaw Bekelle ◽  
Mohammed Ismail
Keyword(s):  
Antenna Array ◽  
Solar Panel ◽  
Patch Antennas ◽  
Small Satellite ◽  
Radiation Characteristics ◽  
Small Satellites ◽  
Microstrip Patch Antennas ◽  
Compact Size ◽  
High Efficient ◽  
Satellite Applications

<p class="Default">The possible antenna which can be integrated with relatively large flat structure of solar panel of small satellites is patch antenna. The main problem of common Microstrip patch antennas is that they only operate at one or two frequencies, restricting the number of bands that equipment is capable of supporting. Another issue is that, due to the very strict space that a solar panel has, setting up more antenna array is very difficult. To reduce these problems, the use of fractal shaped antennas integrated on solar cells will be analyzed. The small satellite applications demand a high efficient multi-band antenna with a very compact size. A 2x2 Sierpinski Fractal antenna array is modeled and simulated using HFSS. The proposed work has resulted in multiband operation 10.2 GHz and 18.3GHz with increased bandwidth and radiation characteristics betterment, with added advantage of light weight and smaller dimension which is important where cost to payload is a constraint in satellites.</p>

scholarly journals Design, Implementation, and Operation of a Small Satellite Mission to Explore the Space Weather Effects in LEO

Aerospace ◽  
2019 ◽  
Vol 6 (10) ◽  
pp. 108 ◽  
Author(s):  
Isai Fajardo ◽  
Aleksander Lidtke ◽  
Sidi Bendoukha ◽  
Jesus Gonzalez-Llorente ◽  
Rafael Rodríguez ◽  
...  
Keyword(s):  
Space Weather ◽  
Low Cost ◽  
Low Earth Orbit ◽  
Space Environment ◽  
Small Satellite ◽  
Satellite Mission ◽  
Particle Detectors ◽  
Small Satellites ◽  
Environment Effects ◽  
Institute Of Technology

Ten-Koh is a 23.5 kg, low-cost satellite developed to conduct space environment effects research in low-Earth orbit (LEO). Ten-Koh was developed primarily by students of the Kyushu Institute of Technology (Kyutech) and launched on 29 October 2018 on-board HII-A rocket F40, as a piggyback payload of JAXA’s Greenhouse gas Observing Satellite (GOSAT-2). The satellite carries a double Langmuir probe, CMOS-based particle detectors and a Liulin spectrometer as main payloads. This paper reviews the design of the mission, specifies the exact hardware used, and outlines the implementation and operation phases of the project. This work is intended as a reference that other aspiring satellite developers may use to increase their chances of success. Such a reference is expected to be particularly useful to other university teams, which will likely face the same challenges as the Ten-Koh team at Kyutech. Various on-orbit failures of the satellite are also discussed here in order to help avoid them in future small spacecraft. Applicability of small satellites to conduct space-weather research is also illustrated on the Ten-Koh example, which carried out simultaneous measurements with JAXA’s ARASE satellite.

scholarly journals Development of Pogo Pin-Based Holding and Release Mechanism for Deployable Solar Panel of CubeSat

2019 ◽  
Vol 2019 ◽  
pp. 1-13 ◽  
Author(s):  
Shankar Bhattarai ◽  
Hongrae Kim ◽  
Sung-Hoon Jung ◽  
Hyun-Ung Oh
Keyword(s):  
Low Cost ◽  
Reaction Force ◽  
Structural Safety ◽  
Release Mechanism ◽  
Solar Panels ◽  
Constraint Force ◽  
Small Satellites ◽  
Out Of Plane ◽  
Safety And Reliability ◽  
Low Constraint

CubeSats are revolutionary to the space industry and are transforming space exploration which enables the next generation of scientists and engineers to complete all phases of space missions. Deployable solar panels have been widely used for the generation of enough power in CubeSats due to their limited volume area for solar cell integration. In general, the cable cutting release mechanism have been used in 1U-3U small satellites because of its simplicity and low cost. However, this mechanism has a low constraint force and is unable to apply constraints along the in-plane and out-of-plane directions. In this study, for the improvement of the conventional cable cutting mechanism, a spring-loaded pogo pin-based nichrome burn wire holding and release mechanism (HRM) was proposed and fabricated. The pogo pin constitutes an immensely attractive function for the holding and release mechanism of solar panels because it works as an electrical interface to provide power, a separation spring to initiate the reaction force to deploy the panels, and a status switch to determine deployments. In addition, the proposed mechanism guarantees the loading capability along the in-plane and out-of-plane directions of solar panels, the synchronous release of multiple panels, and a handling simplicity that differentiates it from the conventional mechanism. The design feasibility, structural safety, and reliability of the mechanism were verified through functionality tests and launch and on-orbit environmental tests. The proposed pogo pin-based holding and release mechanism would be equally applicable for other CubeSat deployable appendages.

Orbital Launcher NERVA as the First Proof of the Discontinuous Variational Solution for the Atmospheric Ascent

2014 ◽  
Vol 555 ◽  
pp. 91-101
Author(s):  
Radu D. Rugescu ◽  
Dragos Ronald Rugescu ◽  
Efim Micu
Keyword(s):  
Sierra Nevada ◽  
Space Flight ◽  
Low Cost ◽  
Rocket Engines ◽  
Space Technology ◽  
Small Satellite ◽  
Small Satellites ◽  
Upper Stage ◽  
Orbital Injection ◽  
Space Launcher

Since the earliest days of astronautics, more than a century ago, low cost space launchers persevered to be a long desire for the space flight thinkers. Once space flight became a daily business along the late `50-s, first by consuming large financial resources, the interest for cheap space launchers became even more laud. Today’s growing interest in small satellites have bolstered a large series of space technology companies including Virgin Galactic Corp., Garvey Spacecraft Corp., Quantum Research International, Ventions LLC, Sierra Nevada Corp., Generation Orbit Launch Services and even the giant Boeing to work on the development of various types of such vehicles, some of them of actually small size. They have announced recent progresses in their efforts to develop and test small-satellite launchers and rocket engines. Romanian space launcher effort includes the NERVA project, with the ORVEAL compound engine for the upper stage, securing the orbital injection, project developed by the team of professors and researchers from ADDA Ltd, Bucharest. This project is based on a series of innovative concepts, including the optimal ascent program first proposed by the ADDA team by means of the new discontinuous variational optimization, which is here described in detail.

scholarly journals Simulator Panel Surya Ekonomis untuk Pengujian MPPT pada Kondisi Berbayang Sebagian (Low Cost PV Photovoltaic Simulator for MPPT Testing under Partial Shading)

2020 ◽  
Vol 9 (1) ◽  
pp. 110-115 ◽  
Author(s):  
Novie Ayub Windarko ◽  
Muhammad Nizar Habibi ◽  
Mochamad Ari Bagus Nugroho ◽  
Eka Prasetyono
Keyword(s):  
Power Supply ◽  
Low Cost ◽  
Solar Panel ◽  
Maximum Power ◽  
Solar Panels ◽  
Maximum Power Point ◽  
Partial Shading ◽  
Dc Power ◽  
Dc Power Supply ◽  
Power Point

This paper describes a low-cost solar panel simulator for Maximum Power Point Tracking (MPPT) method testing, especially under partially shading conditions. The simulator consists of a DC power supply and a solar panel. The simulator works to emulate the characteristics of solar panels without depending on artificial illumination or sunlight. The simulator can represent the needed irradiation through the settings on the DC power supply. The experimental setup is developed to emulate the characteristics of solar panels at Standard Test Conditions (STC) irradiation conditions as well as varying irradiation conditions. Testing is done to emulate irradiation varies from 200-1,000 W/m2. To emulate the characteristics of solar panels in partial shading conditions, two DC power supply units and two solar panels are used. Each solar panel is simulated to receive different solar irradiations. The test results show that the simulator can emulate the characteristics of solar panels under partial shading conditions which has several maximum power points. Furthermore, partial shading conditions are simulated under varying irradiation conditions which resulted varying maximum power point values.

scholarly journals The Verification of Nanosatellites Solar Panels Automatic Deployment in Microgravity Conditions

2021 ◽  
Author(s):  
Akram Abdellatif ◽  
Ali H. Ali ◽  
Mohamed E. El-sayed ◽  
Nermine M. Elhusseiny ◽  
Youmna Mabrouk ◽  
...  
Keyword(s):  
Research Council ◽  
Parabolic Flight ◽  
National Research Council ◽  
Solar Panel ◽  
Microgravity Environment ◽  
Solar Panels ◽  
Efficient Design ◽  
Microgravity Conditions ◽  
Automatic Deployment ◽  
Main Factor

AbstractThe solar panels installed on a CubeSat are considered the main energy source of a nanosatellites. The deployment mechanism of a solar panel must be analyzed and tested extensively. Any suggested solar panel design should present a low vibrating free spinning deployment mechanism. This paper examines various types of solar panels to reach a conclusion of the efficient design when deployed on a 1U or 2U unit. However, calculations, analysis, simulations do not always give an extensive picture of how the satellite shall behave during deployment. Thus, testing in a microgravity environment gives a more accurate answer of how the satellite shall behave. In our work, various solar panels mechanisms are developed and eventually tested in microgravity. The first accordion structure for a 1U structure is tested in a microgravity environment through a parabolic flight with the National Research Council Falcon 20 aircraft. The results are recorded and analyzed to optimize the next design. The second design is based on a drag-sail mechanism for a 2U structure. The design is improved upon the first experiment results for the next parabolic flight. The simulated amount of power generated in orbit is also a main factor in our evaluation.

The Design of a Small Satellite for Earth Observation

1996 ◽  
Vol 210 (4) ◽  
pp. 323-332 ◽  
Author(s):  
S J Gardner ◽  
G G Swinerd ◽  
A K Ward
Keyword(s):  
Low Cost ◽  
Earth Observation ◽  
Low Earth Orbit ◽  
Small Satellite ◽  
Satellite Design ◽  
The Earth ◽  
Wide Range ◽  
Low Mass ◽  
Available Technology ◽  
Selection Of

The concept of the Teaching Company Scheme Satellite (TuCSAT), has been developed to meet the requirements of the Earth observation user community for inexpensive and flexible opportunities to launch remote sensing instruments into low earth orbit (LEO). This paper describes the satellite design process, together with the philosophy behind the selection of a baseline mission. The satellite is shown to demonstrate the ability to meet a wide range of requirements within a strict low mass and low cost philosophy, while making use of currently available technology in order to achieve the design aims.

Contradiction Analysis and Solution in the R&D of High-Power Solar LED Street Lamp Controller

2019 ◽  
Vol 12 (1) ◽  
pp. 12-19
Author(s):  
Zhengwang Xu ◽  
Wei Mei ◽  
Jiaqi Yu ◽  
Jiarui Zhang ◽  
Yuchun Yi ◽  
...  
Keyword(s):  
Power Supply ◽  
High Efficiency ◽  
Low Cost ◽  
Solar Panel ◽  
Battery Voltage ◽  
Supply Circuit ◽  
Led Light ◽  
Power Supply Circuit ◽  
Side Mode ◽  
Dual Power

As being restricted by factors such as cost, efficiency and size, the development of high-power solar LED street light controller is faced with plenty of difficulties. In case that a structure of two independent DC/DC is applied as the main circuit, it has to face problems such as large size and high cost; in case of applying the bidirectional BUCK/BOOST circuit, it requires change-over switches to control the solar panel and LED light. As being restricted by withstanding voltage, on-resistance and cost, a PMOS device cannot be used as the change-over switch of solar panel and LED light. However, when being used as a change-over switch, an NMOS device must apply the low-side mode under which the negative ends of the mentioned three parts are cut off. In the condition of applying the low-side mode, a differential circuit must be used to detect the voltage of the solar panel. Furthermore, in order to make sure batteries can still be regularly charged after wearing out in daylight, the controller must be supplied with power through a dual power supply circuit that can obtain power from both the solar panel and the battery. The demander has a requirement on extremely low standby power consumption of the product, and thus it is necessary to minimize the circuit that is live while working in standby mode. Methods: The bidirectional BUCK/BOOST circuit structure is applied to the main circuit to realize a higher change-over efficiency while giving considerations to both cost and size. The NMOS device, model IRFB4410ZPBF, with a price of about three yuan, is used as the switching device, and the low-side mode is applied, that is the switches inserted in between negative end of the solar panel or LED light and that of the DC/DC circuit. The low-cost rail-to-rail operational amplifier LM358 is used to form a differential amplification circuit for detecting the voltage of the solar panel. A XL1509-12E1 chip that only costs 0.88 yuan/pc is selected as the main change-over chip for the power supply, which has realized the highly-efficient and low-cost change-over of the power supply. A dual power supply circuit and a step-down protective circuit are designed for the XL1509-12E1 change-over chip. By comparing solar panel voltage with battery voltage, the solar panel booting circuit is realized. Only when solar panel voltage is higher than battery voltage, does the system program start to power it up for running, so that the outage of most of the circuits of the system under standby mode does not consume energy. Furthermore, the solar panel voltage detecting circuit, the solar panel booting circuit and several return difference functions are corrected during system debugging. Results: The circuit board of the entire controller features small size, low cost and high efficiency. It measures about 100*62*18mm in size, costs about 60 yuan, and the charge/discharge change-over efficiency reaches up to over 95%. The controller has many functions: it is capable of operating within a large scope, in which, solar panel voltage is subject to 15~50V, LED light voltage is subject to 15~60V, battery voltage is subject to 10~35V and battery-end charge/discharge current is 10A; it is capable of adapting to monocrystalline silicon/multicrystalline silicon/thin-film and many other kinds of solar panels, as well as lithium/lead-acid and many other kinds of batteries; it is capable of detecting the conversion of day and night, automatically controlling charging and discharging and automatically making adaptive adjustment according to seasonal variations; the current to be consumed during standby will be maintained below 3mA, and thus the power consumption is extremely low. Conclusion: By selecting the bidirectional BUCK/BOOST circuit structure, applying low-side mode for switching of solar panel and LED light, using a differential circuit to detect solar panel voltage, using a low-cost DC/DC chip to realize power supply change-over, designing a dual power supply circuit, introducing solar panel booting circuit and other hardware design, as well as MPPT algorithm, state recognition and control, return difference control and other software design, a solar LED street light control product featuring small size, low cost, high efficiency and multiple functions is successfully developed.

scholarly journals Design of a high-stability heterogeneous clock system for small satellites in LEO

GPS Solutions ◽  
2021 ◽  
Vol 25 (3) ◽  
Author(s):  
Damon Van Buren ◽  
Penina Axelrad ◽  
Scott Palo
Keyword(s):  
Low Power ◽  
High Stability ◽  
Time Frame ◽  
System Stability ◽  
Small Satellite ◽  
Crystal Oscillator ◽  
Small Satellites ◽  
Clock System ◽  
Wide Range

AbstractWe describe our investigation into the performance of low-power heterogeneous timing systems for small satellites, using real GPS observables from the GRACE Follow-On mission. Small satellites have become capable platforms for a wide range of commercial, scientific and defense missions, but they are still unable to meet the needs of missions that require precise timing, on the order of a few nanoseconds. Improved low-power onboard clocks would make small satellites a viable option for even more missions, enabling radio aperture interferometry, improved radio occultation measurements, high altitude GPS navigation, and GPS augmentation missions, among others. One approach for providing improved small satellite timekeeping is to combine a heterogeneous group of oscillators, each of which provides the best stability over a different time frame. A hardware architecture that uses a single-crystal oscillator, one or more Chip Scale Atomic Clocks (CSACs) and the reference time from a GPS receiver is presented. The clocks each contribute stability over a subset of timeframes, resulting in excellent overall system stability for timeframes ranging from less than a second to several days. A Kalman filter is used to estimate the long-term errors of the CSACs based on the CSAC-GPS time difference, and the improved CSAC time is used to discipline the crystal oscillator, which provides the high-stability reference clock for the small satellite. Simulations using GRACE-FO observations show time error standard deviations for the system range from 2.3 ns down to 1.3 ns for the clock system, depending on how many CSACs are used. The results provide insight into the timing performance which could be achieved on small LEO spacecraft by a low power timing system.

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