Спутник технологический. ALMASat 1. [Редактировать]

ALMASat 1 – итальянский искусственный спутник Земли, созданный для исследования некоторых технологий. Разработан Болонским университетом. Представляет собой куб с ребром 30 см и диагональю 52 см, весом 12,5 кг. Внутри – разбит на шесть модульных секций, изготовленных из высококачественного аэрокосмического алюминия, усиленного 8 пластинами из нержавеющей стали. В основе корпуса лежат 4 солнечных батареи, закрепленные на алюминиевом основании. Такая конструкция была выбрана для того, чтобы обеспечить разделенные по модулям компоненты спутника энергией, потребляющие разные объемы энергии и занимающие разный объем с помощью укороченной многофункциональной шины. На этапе проектирования спутника верхняя крышка была перепроектирована на другой материал углеводородное волокно. Это позволило снизить массу спутника. Спутник был выведен с космодрома Куру ракетой-носителем «Вега» 13 февраля 2012 года на полярную орбиту, с которой будет снижаться, работая в течение 25 лет.

Дополнительные наименования

#НаименованияПоиск в новостяхПоиск в документах
1ALma MAter SATellite 1НайтиНайти
238078НайтиНайти

Дополнительная классификация

#Наименования
1Страна оператор(владелец) - Италия
2Страна производитель - Италия

Технические характеристики

#ХарактеристикаЗначение
1Масса, кг12.5

Характеристики орбиты

#ХарактеристикаЗначение
1Наклонение, град69.5
2Апогей, км1174.6
3Перигей, км313.8
4Период, минут99.5
5Длинный диаметр эллипса, км7115

Пусковые характеристики

#ХарактеристикаЗначение
1Код NSSDC2012-006B

Информация об удачном запуске

#ХарактеристикаЗначение
1Космодром Космодром Куру
2Дата пуска2012-02-13 at 10:00:00 UTC
3Полезная нагрузка 1xLARES
4Полезная нагрузка 1xALMASat 1
5Полезная нагрузка 1xe-st@r
6Полезная нагрузка 1xGoliat
7Полезная нагрузка 1xMasat 1
8Полезная нагрузка 1xXaTcobeo
9Полезная нагрузка 1xObject G
10Полезная нагрузка 1xObject H
11Полезная нагрузка 1xPW-Sat 1
12Полезная нагрузка 1xRobusta
13Полезная нагрузка 1xUniCubeSat-GG
14Ракета-носитель 1xВега

Найдено 59 документов по запросу «ALMASat 1». [Перейти к поиску]


Дата загрузки: 2017-03-18
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0.27/5
... all the members of the ALMASat Microsatellite Laboratory for the invaluable..., 2006, “Analisi termica del microsatellite ALMASat,” Thesis, BSc, University of Bologna... from 2004 is involved in ALMASat project, the first microsatellite developed... from 2004 is involved in ALMASat project, the first microsatellite developed.... 2-6, 2006. E. Troiani, D. Bruzzi, S. Gianotti, P. Tortora, “ALMASat Microsatellite Structural Analysis: Finite Elements... from 2004 is involved in ALMASat project, the first microsatellite developed.... Publications: P. Tortora, F. Giulietti, A. Corbelli, V. Fabbri, “ALMASat Attitude Control Hardware-in-the... from 2004 is involved in ALMASat project, the first microsatellite developed.... Publications: P. Tortora, F. Giulietti, A. Corbelli, V. Fabbri, “ALMASat Attitude Control Hardware-in-the...



Дата загрузки: 2016-12-24
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0.18/5
... development of a second microsatellite, named ALMASat-EO, a three-axis stabilized microsatellite... Orbit microsatellite ALMASat-EO ............................................................ 10 1.3.2 Radioscience mission orbiting Jupiter ......................................................................... 12 ALMASat-EO... ............................................................................................ 33 2.7.3 Bit Error Rate ............................................................................................................... 34 ALMASat-EO high-speed transmitter subsystem... Figures Figure 1: ALMASat-EO bus structure ............................................................................................... 11 Figure 2: ALMASat-EO attitude during Earth images acquisition.................................................... 12 Figure 3: ALMASat-EO... embedded software....................................... 26 Figure 11: ALMASat-EO TT&C antenna system ............................................................................. 29... 20: block diagram of the ALMASat-EO optical payload electronic ...................................... 37... Allan DEViation Automatic Frequency Control ALMASat MultiSpectral Camera Advanced Orbiting Systems... the completion of the microsatellite ALMASat-1, the first microsatellite entirely designed... at the University of Bologna. ALMASat-1 was successfully launched on-board... expertise in space technology: the ALMASat-1 project is an example of... interest in microsatellite development. The ALMASat-EO mission [11], described in... tested is referred to the ALMASat-EO microsatellite communication systems, as... space. 1.3.1 Low Earth Orbit microsatellite ALMASat-EO The Microsatellites and Space... missions. While the precursor microsatellite, ALMASat-1, was successfully launched on-board... assembling the next generation of ALMASat satellite, ALMASat-EO whose project started... s.r.l.. The main purpose of the ALMASat-EO project is related to... will carry on-board the ALMASat MultiSpectral Camera (AMSC) payload in... a mass smaller than 35 kg. ALMASat-EO bus structure is shown... the images geo-referencing requirements. ALMASat-EO attitude during images acquisition... to the top of the ALMASat-EO structure, and an S-band... with the EO payload. Figure 1: ALMASat-EO bus structure 11 Innovative... systems for space communication Figure 2: ALMASat-EO attitude during Earth images... radio systems for space communication 2 ALMASat-EO TT&C communication subsystem As... subsystem of the microsatellite platform ALMASat-EO, the TT&C architecture has.... Moreover, as a critical subsystem in ALMASat-EO architecture, a dedicated emergency power... shown in this figure. Figure 3: ALMASat-EO tray dedicated to the... necessity to use powerful µC for ALMASat-EO electronic boards. Figure 4 shows...&C board and the rest of ALMASat-EO electronic subsystem are shown... and downlink paths on–board ALMASat-EO, giving the possibility to.... The hybrid coupler used in ALMASat-EO is a passive six-ports... minimum power dissipation. Figure 11: ALMASat-EO TT&C antenna system 29... space communication 3 ALMASat-EO high-speed transmitter subsystem The ALMASat-EO mission... an integrated part of the ALMASat-EO optical payload, as shown... 20: block diagram of the ALMASat-EO optical payload electronic 3.1 Requirements... the multispectral camera. During an ALMASat-EO orbit the optical payload... the FPGA device chosen for ALMASat-EO optical payload. Therefore, a single.... (5) 𝑏𝑎𝑛𝑑𝑙𝑜𝑠𝑠𝑙𝑒𝑠𝑠 = 88080384/4 = 22020096 𝑏𝑖𝑡 The goal of ALMASat-EO mission is to acquire... minutes of reliable link between ALMASat-EO and the GS at... after the definitive assignation of ALMASat-EO orbit and the calculation... at 5 V and 3.3 V are derived from ALMASat-EO power bus consisting of...&C antenna system placed of the ALMASat-EO top plate. In addition... the completion of the microsatellite ALMASat-1 that has been successfully launched... development of a second microsatellite, called ALMASat-EO, a three-axis stabilized microsatellite... multispectral camera on-board the ALMASat-EO spacecraft. A second study on..., Germany [10] P. Tortora et al, “ALMASat-1 launch onboard the Vega maiden... Earth observation using the enhanced ALMASat microsatellite bus”, IAA Conference on...



Дата загрузки: 2017-01-04
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0.27/5
United Nations Secretariat ST/SG/SER.E/652 Distr.: General 18 September 2012 Original: English Committee on the Peaceful Uses of Outer Space Information furnished in conformity with the Convention on Registration of Objects Launched into Outer Space Note verbale dated 28 August 2012 from the Permanent Mission of Italy to the United Nations (Vienna) addressed to the Secretary-General The Permanent Mission of Italy to the United Nations (Vienna) presents its compliments to the Secretary-General of the United Nations and, in accordance with article IV of the Convention on Registration of Objects Launched into Outer Space (General Assembly resolution 3235 (XXIX), annex), has the honour to transmit information on Italian space objects LARES and ALMaSat-1 (see annex). V.12-55976 (E) 200912 *1255976* 210912 ST/SG/SER.E/652 Annex Registration data on space objects launched by Italy* Laser Relativity Satellite (LARES) International designator: 2012-006A Name of space object: Laser Relativity Satellite (LARES) Name of launching State: Italy Satellite owner: Italian Space Agency Date and location of launch: 13 February 2012 at 1000 hrs UTC Guiana Space Centre, Kourou, French Guiana Launch vehicle: Vega Basic orbital parameters: Nodal period: 114.75 minutes Inclination: 69.49 degrees Apogee: 1,450.00 kilometres Perigee: 1,450.00 kilometres Nominal geographical longitude (if applicable): Not applicable General function: The Laser Relativity Satellite (LARES) is a national mission of the Italian Space Agency. The mission’s main scientific goal is to test Albert Einstein’s theory of general relativity by the highly accurate measurement of the relativistic Lense-Thirring effect using the International Laser Ranging Service (ILRS) network (see www.lares-mission.com) LARES is a passive satellite in the shape of a sphere measuring 0.38 m in diameter and with a weight of 360 kg, made of solid tungsten. The satellite accommodates 96 mirrors, known as Corner Cube Reflectors, which are capable of reflecting ILRS laser beams The LARES support system, which includes the LARES satellite separation subsystem, will remain attached to the Vega’s Attitude Vernier Upper Module __________________ * 2 The registration data are reproduced in the form in which they were received. V.12-55976 ST/SG/SER.E/652 ALMaSat-1 International designator: 2012-006B Name of space object: ALMaSat-1 Name of launching State: Italy Satellite owner: Italian Space Agency and University of Bologna, Italy Date and location of launch: 13 February 2012 at 1000 hrs UTC Guiana Space Centre, Kourou, French Guiana Launch vehicle: Vega Basic orbital parameters: Nodal period: 102.5 minutes Inclination: 69.49 degrees Apogee: 1,450 kilometres Perigee: 310 kilometres Nominal geographical longitude (if applicable): Not applicable General function: ALMaSat-1 is an educational microsatellite built by the University of Bologna The dimensions of the satellite are 0.30 × 0.30 × 0.30 m and the weight is 12.5 kg The goal of the mission is technological demonstration of a modular design capability to be used for various technological tests and Earth observation missions. The main objective of the first mission is to test the key performances of this low-cost multi-purpose bus and, in particular, of an innovative cold-gas propulsion module. The performance of the propulsion module will be demonstrated by lowering the altitude of ALMaSat-1 in order to control its re-entry For further information, see www.almasat.unibo.it V.12-55976 3



Дата загрузки: 2017-01-30
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0.16/5
... is based on both ALMASat-EO and ALMASat-1 heritage. As detailed in... as in the case of ALMASat-1. Thus the main bus is... payloads, has been inherited from ALMASat-EO and the payloads arrangement... unregulated type. Based on the ALMASat heritage the solar array will... 17: ESEO structure S/S based on ALMASat platform Concerning the payload complement... is the adaptation of the ALMASat platform to the specific mission... a tray-based architecture inherited from ALMASat-1, ALMASat-EO and several microsatellite platforms...



Дата загрузки: 2016-12-25
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0.17/5
... the University of Bologna [3], named ALMASat-EO, the design, development and... mission simulation and receiver requirements ALMASat-EO is the first Earth... is the successor of the ALMASat-1 microsatellite, successfully launched onboard the... order to achieve its task, ALMASat-EO will mount an on... m at 650 km altitude. Figure 1: ALMASat-EO CAD exploded view The... requirements summary According to the ALMASat-EO mission specifications and the... radio occultation experiment on board ALMASat-EO mission” NAVITEC 2010, ESTEC... the preliminary design of the ALMASat-EO GNSS subsystem: hardware design...



Дата загрузки: 2017-01-30
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0.25/5
XX Congresso Nazionale AIDAA – Milano, 2009 ALMASAT-1 COMMUNICATION SYSTEM ARCHITECTURE AND TEST CAMPAIGN F. Antonini1, D. Cinarelli1 and P. Tortora1 1. II Facoltà di Ingegneria - DIEM, Università di Bologna, via Fontanelle, 40, 47100 Forlì (FC) fabio.antonini@unibo.it, davide.cinarelli@unibo.it, paolo.tortora@unibo.it Abstract (Topic: Space Engineering and Technology) The university microsatellite project ALMASat-1, started in 2003, is now reaching its launch date, at present scheduled at the end of 2009 on-board the VEGA Maiden Flight. The communication system consists of a full-duplex low data-rate link at VHF-UHF band and a high data-rate S-band downlink. Both systems have been fully assembled and before their integration on the spacecraft a very intensive test campaign is necessary in order to evaluate the performance of the whole communication system and estimate the reliability of the link budgets. This paper gives a description of the ALMASat-1 communication system architecture, emphasizing the functional and performance tests carried out before their final integration on the spacecraft Flight Model. The on-board ALMASat-1 UHF transmitting system includes a main and a backup transmitter (in cold redundancy) realizing analog FM modulation, a hybrid coupler that produces four 90-degrees phase shifted signals and a vase turnstile configuration antenna system. The VHF receiving system includes a monopole antenna and a main and a backup receiver (in hot redundancy). Both systems communicate with a Terminal Node Controller, a modem managing data and implementing the amateur-radio AX.25 protocol. Figure 1 shows the communication system tray with all components assembled and the three-dimensional radiation pattern of the VHF-UHF antenna system. In order to test the system reliability, typical and critical operational conditions must be simulated. First of all, Packet Error Rate free-space reception-transmission tests both for VHF uplink and UHF downlink were performed. A satellite link is hardly reproducible in free- space condition tests without using an anechoic chamber, because a reflected path is always generated by the Earth. However, using directive antennas and a line-of-sight link between the transmitter and the receiver, this phenomenon is largely eliminated. Using a spectrum analyzer, a variable attenuator and the ALMASat Ground Station, statistics about lost packets percentage varying the received power were determined. This simulation test-bed allows testing the TT&C system reliability in order to evaluate the successful reception of information also considering the worst propagation conditions case. Matching test using an Anritsu MS462 Vector Network Analyzer were also performed in order to verify the real input and output impedance of all components of the communication system. In this way, a direct evaluation of the power loss caused by reflected waves due to impedance mismatching was carried out and the estimated value accounted for in link budget. Lastly, in order to test the phase shift introduced by the hybrid coupler, an analysis using a Tektronix TDS6000 9GHz Oscilloscope were realized, comparing the four signals generated by the coupler simultaneously. This paper will focus also on the design and assembly of an experimental high data-rate S-band downlink system carried on-board ALMASat-1. This includes a modulator receiving data from the TNC and driving a frequency synthesizer that realizes a direct digital FSK modulation. A Quadrifilar Helix antenna is used in order to perform a right handed circular polarization. In order to receive and decoding this signal on the ground, a first down-conversion at UHF band is carried out. The FSK demodulation is performed at an intermediate frequency of 10 MHz by an IFD board. Then, digital data are processed by a modem and a TNC using G3RUH amateur-radio standard. Packet Error Rate tests, using the same test-bed of TT&C link, were performed also for S-band downlink and will be thoroughly described in this paper. XX Congresso Nazionale AIDAA – Milano, 2009 Fig. 1: ALMASat-1 communication system tray (left) and VHF-UHF antennas 3-D radiation pattern (right)



Дата загрузки: 2017-06-15
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0.35/5
... October 2007 ESA/ESTEC Summary • ALMASat-1 Microsatellite Project; • Cold Gas Micropropulsion... Art; • Conclusion and Future Work. ALMASat Microsatellite: Project Context University Microsatellite... system to be flown on ALMASat-1 microsatellite •Three-axis stabilization and... the thrust level required for ALMASat-1 mission, the pointing error and... has been chosen for the ALMASat-1 microsatellite mission requirements. Micropropulsion System...@unibo.it Web: http://www.almasat.org



Дата загрузки: 2016-12-24
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0.38/5
... payloads that were released were Almasat, designed by the University of... (deg) Mean anomaly (deg) AVUM Almasat 120724 43716.1 120724 43716.1 7247144... mutual distances between three CubeSats, Almasat and AVUM. The data plotted... to be between AVUM and Almasat, with a value of about 1.3 km... the semi-major axis of Almasat at around 22 km/year... in the mean motion brings Almasat in a position closer to the...: • larger orbiting objects (LARES, AVUM, Almasat) have orbits that lie far...



Дата загрузки: 2016-12-25
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0.11/5
... CubeSats and an Italian satellite ALMASat-1 were placed on orbits of... Witkowski Altitude at perigee 320 ALMASat-1 Altitude 315 e-st@r 310 Goliat... Argument of perigee 400 350 ALMASat-1 300 e-st@r 250 Goliat 200...ł Jaworski, Tomasz Witkowski Eccentricity 0,09 ALMASat-1 Eccentricity 0,08 e-st@r 0,07 Goliat... of mean motion 5,00E-03 ALMASat-1 4,00E-03 derivative e-st@r 3,00E... change of the parameters for ALMASat-1, which is a cube (30 cm..., is two times smaller for ALMASat-1. PW-Sat’s orbit degrades. Mathematical...



Дата загрузки: 2016-11-02
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0.04/5
...én llevaba a los satélites (LARES, ALMASAT 1, Xatcobeo, E-ST@R, PW-SAT, UniCubeSat...én llevaba a los satélites (LARES, ALMASAT 1, Xatcobeo, ROBUSTA, E-ST@R, PW-SAT...én llevaba a los satélites (LARES, ALMASAT 1, Xatcobeo, ROBUSTA, PW-SAT, UniCubeSat...ón. Vida útil proyectada de 4 años. ALMASAT 1 13.02.2012 Italia EXP... también llevaba a los satélites (ALMASAT 1, Xatcobeo, ROBUSTA, EST@R, PW-SAT...én llevaba a los satélites (LARES, ALMASAT 1, ROBUSTA, E-ST@R, PW-SAT, UniCubeSat...én llevaba a los satélites (LARES, ALMASAT 1, Xatcobeo, ROBUSTA, E-ST@R, UniCubeSat GG...én llevaba a los satélites (LARES, ALMASAT 1, Xatcobeo, ROBUSTA, E-ST@R, UniCubeSat GG...én llevaba a los satélites (LARES, ALMASAT 1, Xatcobeo, ROBUSTA, E-ST@R, UniCubeSat GG...