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.

Delamination detection in composites using wave modulation spectroscopy with a novel active nonlinear acousto-ultrasonic piezoelectric sensor

2011 ◽  
Vol 22 (18) ◽  
pp. 2193-2206 ◽  
Author(s):  
Nikolaos A. Chrysochoidis ◽  
Antigoni K. Barouni ◽  
Dimitris A. Saravanos
Keyword(s):  
High Frequency ◽  
Low Cost ◽  
Piezoelectric Sensor ◽  
Crack Size ◽  
Basic Element ◽  
High Frequency Signal ◽  
Modulation Spectroscopy ◽  
Wave Modulation ◽  
Active Sensor ◽  
Delamination Cracks

A novel structural health monitoring (SHM) methodology, based on nonlinear wave modulation spectroscopy, is presented for the detection of delamination cracks in composites. The basic element is a novel active nonlinear acousto-ultrasonic piezoelectric sensor enabling low-cost and wide-frequency operational bandwidth. The active sensor configuration involves two piezoceramic wafer actuators, each one excited with a low- and high-frequency signal respectively, and a piezoceramic sensor, all permanently bonded on the tested structure. Experiments are conducted on two sets of composite strips containing delamination cracks of different sizes. Measured results illustrate first the efficiency of the nonlinear ultrasonics methodology to detect delamination cracks, as well as, the potential and benefits of the new active sensor. The sensitivity of the active sensor response to the crack size and the applied high-frequency carrier signals at the actuators, vary at various frequency and voltage levels indicating the appropriate testing setup. Additionally repeatability of proposed SHM methodology is studied.

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 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.

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 A Telemetry, Tracking, and Command Antennas System for Small-Satellite Applications

Electronics ◽  
2019 ◽  
Vol 8 (6) ◽  
pp. 689 ◽  
Author(s):  
Paolo Squadrito ◽  
Patrizia Livreri ◽  
Loreto Di Donato ◽  
Concetto Squadrito ◽  
Gino Sorbello
Keyword(s):  
Low Cost ◽  
Axial Ratio ◽  
Field Pattern ◽  
Impedance Bandwidth ◽  
Wide Angle ◽  
Small Satellite ◽  
Space Applications ◽  
Left Hand ◽  
Low Profile ◽  
Satellite Applications

Circularly polarized (CP) antennas are used in space applications for telemetry tracking and command (TT&C). In this paper, we present an antenna for a TT&C system that can employ only four antennas to achieve a wide quasi-isotropic coverage. The proposed single-feed circular polarized annular patch antenna is low profile and compact. It exhibits a wide impedance bandwidth of 19.7%, wide-angle circular polarization with an on-axis maximum gain higher than 6 dBi and an axial ratio below 4 dB in the frequency band 2.0–2.3 GHz. The developed low-cost antenna can be used for small-satellite data downlink where only two right hand circular polarized (RHCP) antennas and two left hand circular polarized (LHCP) antennas would be required since each antenna has an adequate CP gain on a wide angle. A prototype antenna has been fabricated and measured. The experimental validation shows a good agreement of the measured impedance bandwidth, axial ratio, and far-field pattern with the ones predicted by numerical full-wave study.

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.

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