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FCP1401-PH0A-TT&C-TEMP power point LBGR V2

The document outlines the specifications and missions of several cubesat satellites, including the GS-1, Orca2, Ascent, and ESRA satellites, which are designed for various tasks such as earth observation, scientific experiments, and space radiation analysis. It highlights advancements in satellite technologies, including autonomous navigation and propulsion systems, while also discussing integration with commercial-off-the-shelf components to reduce costs and enhance performance. Additionally, the document details mission objectives, orbital dynamics, and communication parameters for satellite operations.

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‫صفحه‬ 5 ‫از‬ 1 ‫بررسی‬ ‫زیرسیستم‬ TT&C ‫ماهواره‬ ‫های‬ CubeSat ‫ماموریت‬ ‫برای‬ GTO ‫پائيز‬ 1403 Geosynchronous transfer orbit (GTO)
‫صفحه‬ 5 ‫از‬ 2 ‫صفحه‬ GS-1 Satellite 16U
‫صفحه‬ 5 ‫از‬ 3 ‫صفحه‬ GS-1 Satellite 16U Multiple payloads including Earth observation, scientific experiments and bring-into-use (BIU) services at Ku, Ka and V/Q frequency bands. Demonstrating Infinite Orbits advanced autonomous vision-based navigation software, a major step toward our GEO life-extension mission. Utilizing the ENPULSION NANO AR³ thruster – which is the first ENPULSION thruster with vectoring capabilities to be used in GEO. 4 years in design and manufacturing 365 days in orbit 1146km electric orbit raising 2 slots station kept 125 degrees travelled across the GEO belt 1st in-orbit tests of our rendezvous solution 1st commercial CubeSat in GEO orbit.
‫صفحه‬ 5 ‫از‬ 4 ‫صفحه‬ GS-1 Satellite 16U
‫صفحه‬ 5 ‫از‬ 5 ‫صفحه‬ GS-1 Satellite 16U
‫صفحه‬ 5 ‫از‬ 6 ‫صفحه‬ OrCa2 Satellite 12U Originally, OrCa2 was slated to deploy into a Geosynchronous Transfer Orbit (GTO), so a 1 cm thick shielding box was developed to provide the non-radiation-hardened electronics some protection against the high radiation levels in that orbit. When the orbit was changed to be an SSO, the structure was not modified, as the electronics compartment provides a convenient method for integration.
‫صفحه‬ 5 ‫از‬ 7 ‫صفحه‬ ASCENT Satellite 12U
‫صفحه‬ 5 ‫از‬ 8 ‫صفحه‬ ASCENT Satellite 12U The Ascent mission is evaluating the performance of commercial-off-the-shelf technology and capabilities in the GEO space environment, only previously seen in LEO flight experiments. Ascent comprises several demonstrations that include flying two propulsion systems and the first GEO application of the Georgia Tech cold gas propulsion system to provide momentum management. BCT contacted the spacecraft on the first acquisition and continues to support on-orbit questions as needed.
‫صفحه‬ 5 ‫از‬ 9 ‫صفحه‬ ESRA Satellite 12U Experiment for Space Radiation Analysis (ESRA)
‫صفحه‬ 5 ‫از‬ 10 ‫صفحه‬ ESRA Satellite 12U The primary motivation for the ESRA payloads is to minimize size, weight, power, and cost while still providing necessary mission data. These new instruments will be demonstrated by ESRA through testing and on-orbit operations to increase their technology readiness level such that they can support the evolution of technology and mission objectives. This project will leverage a commercial off-the-shelf CubeSat avionics bus and commercial satellite ground networks to reduce the cost and timeline associated with traditional DemVal missions. The system will launch as a ride share with the DoD Space Test Program to be inserted in Geosynchronous Transfer Orbit (GTO) and allow observations of the Earth’s radiation belts. The ESRA CubeSat consists of two science payloads and several subsystems: the Wide-field-of-view Plasma Spectrometer, the Energetic Charged Particle telescope, high voltage power supply, payload processor, flight software architecture, and distributed processor module. The ESRA CubeSat will provide measurements of the plasma and energetic charged particle populations in the GTO environment for ions ranging from ~100 eV to ~1000 MeV and electrons with energy ranging from 100 keV to 20 MeV.
‫صفحه‬ 5 ‫از‬ 11 ‫صفحه‬ ESRA Satellite
‫صفحه‬ 5 ‫از‬ 12 ‫صفحه‬ SunRISE Satellites Deploy the 6 CubeSats in a Geosynchronous earth orbit (GEO). It will then be stationed about 10 Kilometers apart. Then it will be placed in a passive formation and will drift in the GEO. Once it is in operation it will be operated by JPL for a 12-month mission. The CubeSats will be used as one very large radio telescope and will use radio images of low-frequency emission from solar activity. They will then send down the information via the Deep Space Network. Together they will be able to create a 3D map to pinpoint the location a giant particle burst originated on the sun, then how it evolved as they expanded heading into space. The CubeSats will also be used, for the first time, to map the pattern of magnetic field lines reaching the from the Sun to interplanetary space.
‫صفحه‬ 5 ‫از‬ 13 ‫صفحه‬ SunRISE Satellites The mission will study also apart of the sun’s spectrum that can’t be seen on earth due to the ionosphere. It will also help provide information that Parker Solar Probe, Solar Orbiter, and the ground-based Solar Telescope can’t get. The CubeSats will use a DH-GNSS receiver, GNSS antennas, and deployable dipole antennas. Studying solar storms can allow scientists to predict how and when they form, data that can later be used to help better protect astronauts from dangerous solar radiation. It can help protect the spacecraft in orbit from damaging its internals from solar radiation.
‫صفحه‬ 5 ‫از‬ 14 ‫صفحه‬ SunRISE Satellites
‫صفحه‬ 5 ‫از‬ 15 ‫صفحه‬ SunRISE Satellites
‫صفحه‬ 5 ‫از‬ 16 ‫صفحه‬ NanoAvionics
‫صفحه‬ 5 ‫از‬ 17 ‫صفحه‬ NanoAvionics
‫صفحه‬ 5 ‫از‬ 18 ‫صفحه‬ M12P-nanoavionics -
‫صفحه‬ 5 ‫از‬ 19 ‫صفحه‬ NanoAvionics BUS 12U
‫صفحه‬ 5 ‫از‬ 20 ‫صفحه‬ NanoAvionics BUS 16U
‫صفحه‬ 5 ‫از‬ 21 ‫صفحه‬ An Improved S-Band CubeSat Communication 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Subsystem Design and Implementation
‫صفحه‬ 5 ‫از‬ 22 ‫صفحه‬ An Improved S-Band CubeSat Communication 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Subsystem Design and Implementation
‫صفحه‬ 5 ‫از‬ 23 ‫صفحه‬ An Improved S-Band CubeSat Communication 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Subsystem Design and Implementation
‫صفحه‬ 5 ‫از‬ 24 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 CUBESAT S band Transceiver
‫صفحه‬ 5 ‫از‬ 25 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 CUBESAT S band Transceiver
‫صفحه‬ 5 ‫از‬ 26 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Full-duplex Low-power S-band Transceiver
‫صفحه‬ 5 ‫از‬ 27 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Full-duplex Low-power S-band Transceiver
‫صفحه‬ 5 ‫از‬ 28 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 CubeSat TT&C UHF/VHF band Antenna
‫صفحه‬ 5 ‫از‬ 29 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 CUBESAT VHF/UHF Band Transceiver
‫صفحه‬ 5 ‫از‬ 30 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 CUBESAT VHF/UHF Band Transceiver DP-CRF-5549
‫صفحه‬ 5 ‫از‬ 31 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 BLOCK DIAGRAM OF DP-CRF-5549
‫صفحه‬ 5 ‫از‬ 32 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 10 Watt Power Amplifier
‫صفحه‬ 5 ‫از‬ 33 ‫صفحه‬ TT&C Block Diagram Amplifier 5 Watt CUBESAT VHF/UHF Band Transceiver DP-CRF-5549 Filter & Power Divder Filter & Combiner From VHF Band Antenna Tx (0.5 Watt) CUBESAT S Band Transceiver Endrosat Rx Tx (0.5 Watt) Amplifier 8 Watt Antenna Board 1 Antenna Board 2 Filter UHF Band Filter VHF Band Rx To UHF Band Antenna
‫صفحه‬ 5 ‫از‬ 34 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Example Block Diagram
‫صفحه‬ 5 ‫از‬ 35 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 External satellite layout
‫صفحه‬ 5 ‫از‬ 36 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Internal satellite layout
‫صفحه‬ 5 ‫از‬ 37 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Ground Station Antenna  ‫باند‬ ‫آنتن‬ UHF ‫باند‬ ‫و‬ S ‫به‬ ‫ردگیری‬ ‫قابلیت‬ ‫دارای‬ ‫مونوپالس‬ ‫روش‬  ‫دايروي‬ ‫نوع‬ ‫از‬ ‫آنتها‬ ‫تمامي‬ ‫پالريزاسيون‬ ‫باند‬ ‫آنتن‬ ‫بهره‬ UHF ‫برابر‬ 18dB ‫باند‬ ‫آنتن‬ ‫قطر‬ S ‫برابر‬ 7.3 ‫متر‬ ‫توان‬ ‫کننده‬ ‫تقویت‬ 10 ‫وات‬ ‫آنتن‬ ‫بهره‬ VHF ‫برابر‬ 12dB ‫توان‬ ‫کننده‬ ‫تقویت‬ 50 ‫وات‬
‫صفحه‬ 5 ‫از‬ 38 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Sky Noise Temperature ،‫کهکشان‬ ‫نویز‬ ‫اثرات‬ ‫منحنی‬ ‫این‬ ‫نویز‬ ‫و‬ ‫خورشید‬ ‫نویز‬ ،‫کیهانی‬ ‫پرتوهای‬ .‫بردارد‬ ‫در‬ ‫را‬ ‫اتمسفر‬
‫صفحه‬ 5 ‫از‬ 39 ‫صفحه‬ ‫لینک‬ ‫بودجه‬ ‫باند‬ ‫در‬ ‫فروسو‬ UHF 1 2 3 4 5 6 7 8 9 10 11 12 13 14 TT&C Downlink Parameters (UHF Band) Band width = 5 kHz Operational Mode Tx BFSK + Conv (1/2) Soft Decision Bit Rate 1.2 kbps Satellite Antenna Length 17 cm Gain Antenna 0 dB Tx Power 5 Watt Satellite EIRP 7 dBW Frequency 0.420 GHz Distance 42000 km Path Loss 177.37 dB Implementation Loss & Pointing Loss 2 + 3 dB Ground Station Antenna Gain 18 dB Ground Station G/T -6 dB/K C/N (Ground Station) 10.24 dB Es/N0 @ BER 10-6 7.3 dB (5.3 + 2) Link Margin 2.94 dB
‫صفحه‬ 5 ‫از‬ 40 ‫صفحه‬ ‫فراسو‬ ‫لینک‬ ‫بودجه‬ ‫باند‬ ‫در‬ VHF 1 2 3 4 5 6 7 8 9 10 11 12 13 14 TT&C Uplink Parameters (VHF Band) Band width = 20 kHz Operational Mode Tx BFSK + Conv (1/2) Hard Decision Bit Rate 4.8 kbps Ground Station Antenna Model Cross Yagi Gain Antenna 12 dB Tx Power 50 Watt (17 dBW) GS EIRP 29 dBW Frequency 0.145 GHz Distance 42000 km Path Loss 168.13 dB Implementation Loss & Pointing Loss 1 + 3 dB Satellite Antenna Length 55 cm Satellite Antenna G/T -30 dB/K C/N (Satellite) 12.46 dB Es/N0 @ BER 10-6 9.8 dB (8.8 + 1) Link Margin 2.69 dB
‫صفحه‬ 5 ‫از‬ 41 ‫صفحه‬ ‫فر‬ ‫لینک‬ ‫بودجه‬ ‫و‬ ‫سو‬ ‫سیگنال‬ Beacon 1 2 3 4 5 6 7 8 9 10 11 12 13 14 TT&C Downlink Parameters (UHF Band) Band width = 5 kHz Operational Mode Tx BFSK + Conv (1/2) Soft Decision Bit Rate 1.2 kbps Satellite Antenna Length 17 cm Gain Antenna 0 dB Tx Power 5 Watt Satellite EIRP 7 dBW Frequency 0.420 GHz Distance 42000 km Path Loss 177.37 dB Implementation Loss & Pointing Loss 2 + 3 dB Ground Station Antenna Gain 18 dB Ground Station G/T -6 dB/K C/N (Ground Station) 10.24 dB Threshold 7.3 dB (5.3 + 2) Link Margin 2.94 dB ‫با‬ ‫‌شود‬ ‫ی‬‫م‬ ‫مشاهده‬ ‫ه‬H‫ک‬ ‫همانطور‬ EIRP ‫حدود‬ 7 ‫فروسوی‬ ‫ک‬H ‫ن‬‫لی‬ ‫برای‬ ‫وات‬ ‫یبل‬H ‫س‬‫د‬ Beacon ‫حدود‬ ‫ه‬HH‫حاشی‬ ، 3 ‫برای‬ ‫دسیبل‬ ‫فاصله‬ 42000 .‫‌شود‬ ‫ی‬‫م‬ ‫محقق‬ ‫کیلومتری‬ ‫ن‬H ‫ت‬‫آن‬ ‫م‬H ‫ی‬‫ب‬ UHF ‫گین‬ ‫ا‬H ‫ب‬ ‫ی‬H ‫ن‬‫زمی‬ ‫تگاه‬H ‫س‬‫ای‬ 18 ‫حدود‬ ‫یبل‬H‫س‬‫د‬ 20 ‫برای‬ ‫که‬ ‫د‬H‫ش‬‫‌با‬ ‫ی‬‫م‬ ‫ه‬H‫ج‬‫در‬ .‫است‬ ‫مطلوب‬ ‫یابی‬ ‫موقعیت‬ ‫فر‬ ‫لینک‬ ‫بودجه‬ ‫و‬ ‫سو‬ ‫سیگنال‬ Beacon
‫صفحه‬ 5 ‫از‬ 42 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 BFSK& Conv(1/2) 0 2 4 6 8 10 12 14 16 18 Eb /N0 (dB) 10-8 10-7 10-6 10-5 10-4 10-3 10-2 10-1 100 BER BFSK-NonCoherent-Conv(1/2)-Hard Decision BFSK-NonCoherent-Conv(1/2)-Soft Decision Eb /N0 = 8.3 BER = 1.033e-06 Eb /N0 = 11.8 BER = 1.104e-06
‫صفحه‬ 5 ‫از‬ 43 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 MSK & GMSK
‫صفحه‬ 5 ‫از‬ 44 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 MSK & Conv(1/2) 0 2 4 6 8 10 12 14 16 18 Eb /N0 (dB) 10-8 10-7 10-6 10-5 10-4 10-3 10-2 10-1 100 BER MSK-NonCoherent-Conv(1/2) Hard Decision MSK-NonCoherent-Conv(1/2) Soft Decision Eb /N0 = 9.1 BER = 1.021e-06 Eb /N0 = 12 BER = 1.175e-06
‫صفحه‬ 5 ‫از‬ 45 ‫صفحه‬ ‫فر‬ ‫لینک‬ ‫بودجه‬ ‫و‬ ‫سو‬ ‫صورت‬ ‫به‬ FDD ‫باند‬ ‫در‬ S 1 2 3 4 5 6 7 8 9 10 11 12 13 14 TT&C Downlink Parameters (S Band) Band width = 30 kHz Operational Mode Tx GMSK (BT=0.35) + Conv (1/2) Soft Decision Bit Rate 19.2 kbps Satellite Antenna Diameter 7 cm Gain Antenna 0 dB (Main Beam: 5dB) Tx Power 4 Watt Satellite EIRP 6 dBW Frequency 2.2 GHz Distance 42000 km Path Loss 191.76 dB Implementation Loss & Pointing Loss 1 dB Ground Station Antenna Diameter 7.3 m Ground Station G/T 17 dB/K C/N (Ground Station) 14.07 dB Es/N0 @ BER 10-6 8.1 dB (6.1 + 2) Link Margin 5.97 dB
‫صفحه‬ 5 ‫از‬ 46 ‫صفحه‬ ‫فر‬ ‫لینک‬ ‫بودجه‬ ‫ا‬ ‫سو‬ ‫صورت‬ ‫به‬ FDD ‫باند‬ ‫در‬ S 1 2 3 4 5 6 7 8 9 10 11 12 13 14 TT&C Uplink Parameters (S Band) Band width = 30 kHz Operational Mode Tx GMSK (BT=0.35) + Conv (1/2) Hard Decision Bit Rate 19.2 kbps Ground Station Antenna Diameter 7.3 m Gain Antenna 42 dB Tx Power 10 Watt GS EIRP 52 dBW Frequency 2.1 GHz Distance 42000 km Path Loss 191.35 dB Implementation Loss & Pointing Loss 1 dB Satellite Antenna Diameter 7 cm Satellite Antenna G/T -25 dB/K C/N (Satellite) 18.48 dB Es/N0 @ BER 10-6 10 dB (9 + 1) Link Margin 8.48 dB
‫صفحه‬ 5 ‫از‬ 47 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 ACM
‫صفحه‬ 5 ‫از‬ 48 ‫صفحه‬ ‫فر‬ ‫لینک‬ ‫بودجه‬ ‫و‬ ‫سو‬ ‫صورت‬ ‫به‬ FDD ‫باند‬ ‫در‬ S 1 2 3 4 5 6 7 8 9 10 11 12 13 14 TT&C Downlink Parameters (S Band) Band width = 120 kHz Operational Mode Tx GMSK (BT=0.35) + Conv (1/2) Bit Rate 80 kbps Satellite Antenna Diameter 7 cm Gain Antenna 0 dB (Main Beam: 5dB) Tx Power 4 Watt Satellite EIRP 6 dBW Frequency 2.2 GHz Distance 20000 km Path Loss 185.33 dB Implementation Loss 1 dB Ground Station Antenna Diameter 7.3 m Ground Station G/T 17 dB/K C/N (Ground Station) 14.5 dB Es/N0 @ BER 10-6 9 dB Link Margin 5.5 dB
‫صفحه‬ 5 ‫از‬ 49 ‫صفحه‬ ‫فر‬ ‫لینک‬ ‫بودجه‬ ‫و‬ ‫سو‬ ‫صورت‬ ‫به‬ FDD ‫باند‬ ‫در‬ S 1 2 3 4 5 6 7 8 9 10 11 12 13 14 TT&C Downlink Parameters (S Band) Band width = 187.5 kHz Operational Mode Tx GMSK (BT=0.35) + Conv (1/2) Bit Rate 125 kbps Satellite Antenna Diameter 7 cm Gain Antenna 0 dB (Main Beam: 5dB) Tx Power 4 Watt Satellite EIRP 6 dBW Frequency 2.2 GHz Distance 24000 km Path Loss 186.89 dB Implementation Loss 1 dB Ground Station Antenna Diameter 7.3 m Ground Station G/T 17 dB/K C/N (Ground Station) 10.98 dB Es/N0 @ BER 10-6 9 dB Link Margin 1.98 dB ≈ 2 dB
‫صفحه‬ 5 ‫از‬ 50 ‫صفحه‬ ‫با‬ ‫مختلف‬ ‫های‬ ‫فاصله‬ ‫در‬ ‫بیت‬ ‫نرخ‬ ‫ماکزیمم‬ ‫لینک‬ ‫حاشیه‬ 3dB 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Mean (Rb) = 75 kbps 2.2 2.4 2.6 2.8 3 3.2 3.4 3.6 3.8 4 4.2 Distance [km] 104 30 40 50 60 70 80 90 100 110 120 130 R b [kbps] Rb for margin 3dB
‫صفحه‬ 5 ‫از‬ 51 ‫صفحه‬ ‫مشخصات‬ ‫درخت‬ Product Tree TT&C Antenna 4-patch Antenna Divider & Combiner 4-wire Antenna Transceiver S Band Modem VHF/UHF Band Modem Filter & Power supply Power Amplifire 8 Watt (S Band) 5 Watt (UHF Band)
‫صفحه‬ 5 ‫از‬ 52 ‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 ‫شما‬ ‫توجه‬ ‫از‬ ‫تشکر‬ ‫با‬

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FCP1401-PH0A-TT&C-TEMP power point LBGR V2

  • 1.
  • 2.
    ‫صفحه‬ 5 ‫از‬ 2‫صفحه‬ GS-1 Satellite 16U
  • 3.
    ‫صفحه‬ 5 ‫از‬ 3‫صفحه‬ GS-1 Satellite 16U Multiple payloads including Earth observation, scientific experiments and bring-into-use (BIU) services at Ku, Ka and V/Q frequency bands. Demonstrating Infinite Orbits advanced autonomous vision-based navigation software, a major step toward our GEO life-extension mission. Utilizing the ENPULSION NANO AR³ thruster – which is the first ENPULSION thruster with vectoring capabilities to be used in GEO. 4 years in design and manufacturing 365 days in orbit 1146km electric orbit raising 2 slots station kept 125 degrees travelled across the GEO belt 1st in-orbit tests of our rendezvous solution 1st commercial CubeSat in GEO orbit.
  • 4.
    ‫صفحه‬ 5 ‫از‬ 4‫صفحه‬ GS-1 Satellite 16U
  • 5.
    ‫صفحه‬ 5 ‫از‬ 5‫صفحه‬ GS-1 Satellite 16U
  • 6.
    ‫صفحه‬ 5 ‫از‬ 6‫صفحه‬ OrCa2 Satellite 12U Originally, OrCa2 was slated to deploy into a Geosynchronous Transfer Orbit (GTO), so a 1 cm thick shielding box was developed to provide the non-radiation-hardened electronics some protection against the high radiation levels in that orbit. When the orbit was changed to be an SSO, the structure was not modified, as the electronics compartment provides a convenient method for integration.
  • 7.
    ‫صفحه‬ 5 ‫از‬ 7‫صفحه‬ ASCENT Satellite 12U
  • 8.
    ‫صفحه‬ 5 ‫از‬ 8‫صفحه‬ ASCENT Satellite 12U The Ascent mission is evaluating the performance of commercial-off-the-shelf technology and capabilities in the GEO space environment, only previously seen in LEO flight experiments. Ascent comprises several demonstrations that include flying two propulsion systems and the first GEO application of the Georgia Tech cold gas propulsion system to provide momentum management. BCT contacted the spacecraft on the first acquisition and continues to support on-orbit questions as needed.
  • 9.
    ‫صفحه‬ 5 ‫از‬ 9‫صفحه‬ ESRA Satellite 12U Experiment for Space Radiation Analysis (ESRA)
  • 10.
    ‫صفحه‬ 5 ‫از‬ 10‫صفحه‬ ESRA Satellite 12U The primary motivation for the ESRA payloads is to minimize size, weight, power, and cost while still providing necessary mission data. These new instruments will be demonstrated by ESRA through testing and on-orbit operations to increase their technology readiness level such that they can support the evolution of technology and mission objectives. This project will leverage a commercial off-the-shelf CubeSat avionics bus and commercial satellite ground networks to reduce the cost and timeline associated with traditional DemVal missions. The system will launch as a ride share with the DoD Space Test Program to be inserted in Geosynchronous Transfer Orbit (GTO) and allow observations of the Earth’s radiation belts. The ESRA CubeSat consists of two science payloads and several subsystems: the Wide-field-of-view Plasma Spectrometer, the Energetic Charged Particle telescope, high voltage power supply, payload processor, flight software architecture, and distributed processor module. The ESRA CubeSat will provide measurements of the plasma and energetic charged particle populations in the GTO environment for ions ranging from ~100 eV to ~1000 MeV and electrons with energy ranging from 100 keV to 20 MeV.
  • 11.
    ‫صفحه‬ 5 ‫از‬ 11‫صفحه‬ ESRA Satellite
  • 12.
    ‫صفحه‬ 5 ‫از‬ 12‫صفحه‬ SunRISE Satellites Deploy the 6 CubeSats in a Geosynchronous earth orbit (GEO). It will then be stationed about 10 Kilometers apart. Then it will be placed in a passive formation and will drift in the GEO. Once it is in operation it will be operated by JPL for a 12-month mission. The CubeSats will be used as one very large radio telescope and will use radio images of low-frequency emission from solar activity. They will then send down the information via the Deep Space Network. Together they will be able to create a 3D map to pinpoint the location a giant particle burst originated on the sun, then how it evolved as they expanded heading into space. The CubeSats will also be used, for the first time, to map the pattern of magnetic field lines reaching the from the Sun to interplanetary space.
  • 13.
    ‫صفحه‬ 5 ‫از‬ 13‫صفحه‬ SunRISE Satellites The mission will study also apart of the sun’s spectrum that can’t be seen on earth due to the ionosphere. It will also help provide information that Parker Solar Probe, Solar Orbiter, and the ground-based Solar Telescope can’t get. The CubeSats will use a DH-GNSS receiver, GNSS antennas, and deployable dipole antennas. Studying solar storms can allow scientists to predict how and when they form, data that can later be used to help better protect astronauts from dangerous solar radiation. It can help protect the spacecraft in orbit from damaging its internals from solar radiation.
  • 14.
    ‫صفحه‬ 5 ‫از‬ 14‫صفحه‬ SunRISE Satellites
  • 15.
    ‫صفحه‬ 5 ‫از‬ 15‫صفحه‬ SunRISE Satellites
  • 16.
    ‫صفحه‬ 5 ‫از‬ 16‫صفحه‬ NanoAvionics
  • 17.
    ‫صفحه‬ 5 ‫از‬ 17‫صفحه‬ NanoAvionics
  • 18.
    ‫صفحه‬ 5 ‫از‬ 18‫صفحه‬ M12P-nanoavionics -
  • 19.
    ‫صفحه‬ 5 ‫از‬ 19‫صفحه‬ NanoAvionics BUS 12U
  • 20.
    ‫صفحه‬ 5 ‫از‬ 20‫صفحه‬ NanoAvionics BUS 16U
  • 21.
    ‫صفحه‬ 5 ‫از‬ 21‫صفحه‬ An Improved S-Band CubeSat Communication 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Subsystem Design and Implementation
  • 22.
    ‫صفحه‬ 5 ‫از‬ 22‫صفحه‬ An Improved S-Band CubeSat Communication 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Subsystem Design and Implementation
  • 23.
    ‫صفحه‬ 5 ‫از‬ 23‫صفحه‬ An Improved S-Band CubeSat Communication 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Subsystem Design and Implementation
  • 24.
    ‫صفحه‬ 5 ‫از‬ 24‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 CUBESAT S band Transceiver
  • 25.
    ‫صفحه‬ 5 ‫از‬ 25‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 CUBESAT S band Transceiver
  • 26.
    ‫صفحه‬ 5 ‫از‬ 26‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Full-duplex Low-power S-band Transceiver
  • 27.
    ‫صفحه‬ 5 ‫از‬ 27‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Full-duplex Low-power S-band Transceiver
  • 28.
    ‫صفحه‬ 5 ‫از‬ 28‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 CubeSat TT&C UHF/VHF band Antenna
  • 29.
    ‫صفحه‬ 5 ‫از‬ 29‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 CUBESAT VHF/UHF Band Transceiver
  • 30.
    ‫صفحه‬ 5 ‫از‬ 30‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 CUBESAT VHF/UHF Band Transceiver DP-CRF-5549
  • 31.
    ‫صفحه‬ 5 ‫از‬ 31‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 BLOCK DIAGRAM OF DP-CRF-5549
  • 32.
    ‫صفحه‬ 5 ‫از‬ 32‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 10 Watt Power Amplifier
  • 33.
    ‫صفحه‬ 5 ‫از‬ 33‫صفحه‬ TT&C Block Diagram Amplifier 5 Watt CUBESAT VHF/UHF Band Transceiver DP-CRF-5549 Filter & Power Divder Filter & Combiner From VHF Band Antenna Tx (0.5 Watt) CUBESAT S Band Transceiver Endrosat Rx Tx (0.5 Watt) Amplifier 8 Watt Antenna Board 1 Antenna Board 2 Filter UHF Band Filter VHF Band Rx To UHF Band Antenna
  • 34.
    ‫صفحه‬ 5 ‫از‬ 34‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Example Block Diagram
  • 35.
    ‫صفحه‬ 5 ‫از‬ 35‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 External satellite layout
  • 36.
    ‫صفحه‬ 5 ‫از‬ 36‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Internal satellite layout
  • 37.
    ‫صفحه‬ 5 ‫از‬ 37‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Ground Station Antenna  ‫باند‬ ‫آنتن‬ UHF ‫باند‬ ‫و‬ S ‫به‬ ‫ردگیری‬ ‫قابلیت‬ ‫دارای‬ ‫مونوپالس‬ ‫روش‬  ‫دايروي‬ ‫نوع‬ ‫از‬ ‫آنتها‬ ‫تمامي‬ ‫پالريزاسيون‬ ‫باند‬ ‫آنتن‬ ‫بهره‬ UHF ‫برابر‬ 18dB ‫باند‬ ‫آنتن‬ ‫قطر‬ S ‫برابر‬ 7.3 ‫متر‬ ‫توان‬ ‫کننده‬ ‫تقویت‬ 10 ‫وات‬ ‫آنتن‬ ‫بهره‬ VHF ‫برابر‬ 12dB ‫توان‬ ‫کننده‬ ‫تقویت‬ 50 ‫وات‬
  • 38.
    ‫صفحه‬ 5 ‫از‬ 38‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Sky Noise Temperature ،‫کهکشان‬ ‫نویز‬ ‫اثرات‬ ‫منحنی‬ ‫این‬ ‫نویز‬ ‫و‬ ‫خورشید‬ ‫نویز‬ ،‫کیهانی‬ ‫پرتوهای‬ .‫بردارد‬ ‫در‬ ‫را‬ ‫اتمسفر‬
  • 39.
    ‫صفحه‬ 5 ‫از‬ 39‫صفحه‬ ‫لینک‬ ‫بودجه‬ ‫باند‬ ‫در‬ ‫فروسو‬ UHF 1 2 3 4 5 6 7 8 9 10 11 12 13 14 TT&C Downlink Parameters (UHF Band) Band width = 5 kHz Operational Mode Tx BFSK + Conv (1/2) Soft Decision Bit Rate 1.2 kbps Satellite Antenna Length 17 cm Gain Antenna 0 dB Tx Power 5 Watt Satellite EIRP 7 dBW Frequency 0.420 GHz Distance 42000 km Path Loss 177.37 dB Implementation Loss & Pointing Loss 2 + 3 dB Ground Station Antenna Gain 18 dB Ground Station G/T -6 dB/K C/N (Ground Station) 10.24 dB Es/N0 @ BER 10-6 7.3 dB (5.3 + 2) Link Margin 2.94 dB
  • 40.
    ‫صفحه‬ 5 ‫از‬ 40‫صفحه‬ ‫فراسو‬ ‫لینک‬ ‫بودجه‬ ‫باند‬ ‫در‬ VHF 1 2 3 4 5 6 7 8 9 10 11 12 13 14 TT&C Uplink Parameters (VHF Band) Band width = 20 kHz Operational Mode Tx BFSK + Conv (1/2) Hard Decision Bit Rate 4.8 kbps Ground Station Antenna Model Cross Yagi Gain Antenna 12 dB Tx Power 50 Watt (17 dBW) GS EIRP 29 dBW Frequency 0.145 GHz Distance 42000 km Path Loss 168.13 dB Implementation Loss & Pointing Loss 1 + 3 dB Satellite Antenna Length 55 cm Satellite Antenna G/T -30 dB/K C/N (Satellite) 12.46 dB Es/N0 @ BER 10-6 9.8 dB (8.8 + 1) Link Margin 2.69 dB
  • 41.
    ‫صفحه‬ 5 ‫از‬ 41‫صفحه‬ ‫فر‬ ‫لینک‬ ‫بودجه‬ ‫و‬ ‫سو‬ ‫سیگنال‬ Beacon 1 2 3 4 5 6 7 8 9 10 11 12 13 14 TT&C Downlink Parameters (UHF Band) Band width = 5 kHz Operational Mode Tx BFSK + Conv (1/2) Soft Decision Bit Rate 1.2 kbps Satellite Antenna Length 17 cm Gain Antenna 0 dB Tx Power 5 Watt Satellite EIRP 7 dBW Frequency 0.420 GHz Distance 42000 km Path Loss 177.37 dB Implementation Loss & Pointing Loss 2 + 3 dB Ground Station Antenna Gain 18 dB Ground Station G/T -6 dB/K C/N (Ground Station) 10.24 dB Threshold 7.3 dB (5.3 + 2) Link Margin 2.94 dB ‫با‬ ‫‌شود‬ ‫ی‬‫م‬ ‫مشاهده‬ ‫ه‬H‫ک‬ ‫همانطور‬ EIRP ‫حدود‬ 7 ‫فروسوی‬ ‫ک‬H ‫ن‬‫لی‬ ‫برای‬ ‫وات‬ ‫یبل‬H ‫س‬‫د‬ Beacon ‫حدود‬ ‫ه‬HH‫حاشی‬ ، 3 ‫برای‬ ‫دسیبل‬ ‫فاصله‬ 42000 .‫‌شود‬ ‫ی‬‫م‬ ‫محقق‬ ‫کیلومتری‬ ‫ن‬H ‫ت‬‫آن‬ ‫م‬H ‫ی‬‫ب‬ UHF ‫گین‬ ‫ا‬H ‫ب‬ ‫ی‬H ‫ن‬‫زمی‬ ‫تگاه‬H ‫س‬‫ای‬ 18 ‫حدود‬ ‫یبل‬H‫س‬‫د‬ 20 ‫برای‬ ‫که‬ ‫د‬H‫ش‬‫‌با‬ ‫ی‬‫م‬ ‫ه‬H‫ج‬‫در‬ .‫است‬ ‫مطلوب‬ ‫یابی‬ ‫موقعیت‬ ‫فر‬ ‫لینک‬ ‫بودجه‬ ‫و‬ ‫سو‬ ‫سیگنال‬ Beacon
  • 42.
    ‫صفحه‬ 5 ‫از‬ 42‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 BFSK& Conv(1/2) 0 2 4 6 8 10 12 14 16 18 Eb /N0 (dB) 10-8 10-7 10-6 10-5 10-4 10-3 10-2 10-1 100 BER BFSK-NonCoherent-Conv(1/2)-Hard Decision BFSK-NonCoherent-Conv(1/2)-Soft Decision Eb /N0 = 8.3 BER = 1.033e-06 Eb /N0 = 11.8 BER = 1.104e-06
  • 43.
    ‫صفحه‬ 5 ‫از‬ 43‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 MSK & GMSK
  • 44.
    ‫صفحه‬ 5 ‫از‬ 44‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 MSK & Conv(1/2) 0 2 4 6 8 10 12 14 16 18 Eb /N0 (dB) 10-8 10-7 10-6 10-5 10-4 10-3 10-2 10-1 100 BER MSK-NonCoherent-Conv(1/2) Hard Decision MSK-NonCoherent-Conv(1/2) Soft Decision Eb /N0 = 9.1 BER = 1.021e-06 Eb /N0 = 12 BER = 1.175e-06
  • 45.
    ‫صفحه‬ 5 ‫از‬ 45‫صفحه‬ ‫فر‬ ‫لینک‬ ‫بودجه‬ ‫و‬ ‫سو‬ ‫صورت‬ ‫به‬ FDD ‫باند‬ ‫در‬ S 1 2 3 4 5 6 7 8 9 10 11 12 13 14 TT&C Downlink Parameters (S Band) Band width = 30 kHz Operational Mode Tx GMSK (BT=0.35) + Conv (1/2) Soft Decision Bit Rate 19.2 kbps Satellite Antenna Diameter 7 cm Gain Antenna 0 dB (Main Beam: 5dB) Tx Power 4 Watt Satellite EIRP 6 dBW Frequency 2.2 GHz Distance 42000 km Path Loss 191.76 dB Implementation Loss & Pointing Loss 1 dB Ground Station Antenna Diameter 7.3 m Ground Station G/T 17 dB/K C/N (Ground Station) 14.07 dB Es/N0 @ BER 10-6 8.1 dB (6.1 + 2) Link Margin 5.97 dB
  • 46.
    ‫صفحه‬ 5 ‫از‬ 46‫صفحه‬ ‫فر‬ ‫لینک‬ ‫بودجه‬ ‫ا‬ ‫سو‬ ‫صورت‬ ‫به‬ FDD ‫باند‬ ‫در‬ S 1 2 3 4 5 6 7 8 9 10 11 12 13 14 TT&C Uplink Parameters (S Band) Band width = 30 kHz Operational Mode Tx GMSK (BT=0.35) + Conv (1/2) Hard Decision Bit Rate 19.2 kbps Ground Station Antenna Diameter 7.3 m Gain Antenna 42 dB Tx Power 10 Watt GS EIRP 52 dBW Frequency 2.1 GHz Distance 42000 km Path Loss 191.35 dB Implementation Loss & Pointing Loss 1 dB Satellite Antenna Diameter 7 cm Satellite Antenna G/T -25 dB/K C/N (Satellite) 18.48 dB Es/N0 @ BER 10-6 10 dB (9 + 1) Link Margin 8.48 dB
  • 47.
    ‫صفحه‬ 5 ‫از‬ 47‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 ACM
  • 48.
    ‫صفحه‬ 5 ‫از‬ 48‫صفحه‬ ‫فر‬ ‫لینک‬ ‫بودجه‬ ‫و‬ ‫سو‬ ‫صورت‬ ‫به‬ FDD ‫باند‬ ‫در‬ S 1 2 3 4 5 6 7 8 9 10 11 12 13 14 TT&C Downlink Parameters (S Band) Band width = 120 kHz Operational Mode Tx GMSK (BT=0.35) + Conv (1/2) Bit Rate 80 kbps Satellite Antenna Diameter 7 cm Gain Antenna 0 dB (Main Beam: 5dB) Tx Power 4 Watt Satellite EIRP 6 dBW Frequency 2.2 GHz Distance 20000 km Path Loss 185.33 dB Implementation Loss 1 dB Ground Station Antenna Diameter 7.3 m Ground Station G/T 17 dB/K C/N (Ground Station) 14.5 dB Es/N0 @ BER 10-6 9 dB Link Margin 5.5 dB
  • 49.
    ‫صفحه‬ 5 ‫از‬ 49‫صفحه‬ ‫فر‬ ‫لینک‬ ‫بودجه‬ ‫و‬ ‫سو‬ ‫صورت‬ ‫به‬ FDD ‫باند‬ ‫در‬ S 1 2 3 4 5 6 7 8 9 10 11 12 13 14 TT&C Downlink Parameters (S Band) Band width = 187.5 kHz Operational Mode Tx GMSK (BT=0.35) + Conv (1/2) Bit Rate 125 kbps Satellite Antenna Diameter 7 cm Gain Antenna 0 dB (Main Beam: 5dB) Tx Power 4 Watt Satellite EIRP 6 dBW Frequency 2.2 GHz Distance 24000 km Path Loss 186.89 dB Implementation Loss 1 dB Ground Station Antenna Diameter 7.3 m Ground Station G/T 17 dB/K C/N (Ground Station) 10.98 dB Es/N0 @ BER 10-6 9 dB Link Margin 1.98 dB ≈ 2 dB
  • 50.
    ‫صفحه‬ 5 ‫از‬ 50‫صفحه‬ ‫با‬ ‫مختلف‬ ‫های‬ ‫فاصله‬ ‫در‬ ‫بیت‬ ‫نرخ‬ ‫ماکزیمم‬ ‫لینک‬ ‫حاشیه‬ 3dB 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Mean (Rb) = 75 kbps 2.2 2.4 2.6 2.8 3 3.2 3.4 3.6 3.8 4 4.2 Distance [km] 104 30 40 50 60 70 80 90 100 110 120 130 R b [kbps] Rb for margin 3dB
  • 51.
    ‫صفحه‬ 5 ‫از‬ 51‫صفحه‬ ‫مشخصات‬ ‫درخت‬ Product Tree TT&C Antenna 4-patch Antenna Divider & Combiner 4-wire Antenna Transceiver S Band Modem VHF/UHF Band Modem Filter & Power supply Power Amplifire 8 Watt (S Band) 5 Watt (UHF Band)
  • 52.
    ‫صفحه‬ 5 ‫از‬ 52‫صفحه‬ 1 2 3 4 5 6 7 8 9 10 11 12 13 14 ‫شما‬ ‫توجه‬ ‫از‬ ‫تشکر‬ ‫با‬