Institute of Space Technology: Hughes Ka Band System Assignment

This assignment provides a detailed overview of the Hughes Ka Band satellite communication system. It begins with an introduction to Hughes Network Systems and its global broadband satellite networks, highlighting the Spaceway 3 and Jupiter 1 satellites. The document explores the Spaceway system, detailing its regional configurations, frequency assignments, beam coverage, and satellite characteristics, including major spacecraft features and launch weight budgets. It also covers link performance objectives, power budgets, and communication links at various data rates. The analysis includes uplink and downlink power budgets, along with Matlab code for clear weather conditions. This assignment offers valuable insights into the technical aspects of Ka-band satellite communication, making it a comprehensive resource for students in electrical engineering and related fields.

HUGHES
(Ka Band System)
Assignment Of Satellite Communication
Submitted to Dr Qamar ul islam
Submitted by Nazish Iqbal
MS (NCS-01)
Registration no: 160412019
INSTITUTE OF SPACE TECHNOLOGY, ISLAMABAD
(FACULTY OF ELECTRICAL ENGINEERING)

HUGHES
(Ka Band system)
Hughes Network Systems, LLC (HUGHES) offers broadband satellite networks globally to large enterprises,
governments, small businesses, and consumers Hughes has manufactured and shipped more than 2.5 million
terminals to customers in over 100 countries.
Spaceway 3 Satellite.
In August 2007 Spaceway 3 Sattelite were launched. It is used by HughesNetTM to form the basis for its next
generation service. The Spaceway 3 satellite employs Ka-band, onboard digital processing, packet switching
and spot-beam technology for direct site-to-site connectivity at rates from 512 Kbps up to 16 Mbps. The
maximum throughput of the satellite is 10 Gbps.
Spaceway 3 spot beam coverage of North America

Jupiter 1 Satellite (also known as Echostar 17)
Hughes Network Systems, LLC (HUGHES) proclaimed in June 2009 that it will launch a next-generation,
high throughput satellite called Jupiter 1 in the first half 2012 to expand its HughesNetTM broadband Internet
service across North America. Designed to deliver over 100 Gbps throughput, the new Hughes satellite will
utilize an enhanced version of the IPoS standard.
The satellite will employ multi-spot beams (about 80), bent pipe Ka-band architecture and will provide
additional capacity for HughesNetTM service in North America. Its capabilities will augment the Spaceway 3
satellite system which Hughes put into commercial service in April, 2008. Space Systems/Loral will
manufacture Jupiter 1 which will be based on its SSL-1300 platform. The satellite will be designed for a
service life of 15 years or more
Satellite Information
Satellite Name: Echostar 17 (Jupiter 1, Spaceway 3)
Status: active
Position: 107° W (107.1° W)
NORAD: 38551
Cospar number: 2012-035A
Operator: EchoStar Corporation
Launch Information
Launch date: 5-Jul-2012
Launch site: Guiana Space Center
Launch vehicle: Ariane 5 ECA
Launch mass (kg): 6100
Dry mass (kg): 3497

Spacecraft information
Manufacturer: Space Systems Loral (SSL)
Model (bus): LS-1300
Orbit: GEO
Expected lifetime: 15 yrs.
SPACEWAY
The SPACEWAY™ system1 is a network of regional systems that will use satellites in the geostationary
satellite orbit (GSO) to provide cost-effective, two-way voice, medium- and high-speed data, image, video and
video telephony communications service to both business and individual users. Direct access to the satellites will
be available on demand throughout the world via inexpensive ultra-small aperture terminals (USATs).
SPACEWAY™ is a high capacity, high quality, yet very versatile system. A two satellite regional configuration
would therefore enable over 230,000 simultaneous telephone calls at 16 Kbps. The all-digital 16 Kbps circuits
utilized for telephony will ensure consistent high quality voice channels.
The high capacity of each SPACEWAY™ satellite is focused through the spot beams on the populated areas of
the world thereby creating a significant cost advantage in the delivery of its telecom services.
The SPACEWAY™ network is diverse from other proposed global networks in that its geostationary orbit
location makes it a truly market driven system: each satellite will make available extensive telecom services to
hundreds of millions of people within the continuous view of that satellite, providing immediate capacity
within a specific region of the world. SPACEWAY™ will be implemented in a phased, regional approach
beginning in 1998, expanding into a network of four interconnected regional systems:
(i) North America,
(ii) Asia Pacific
(iii) Central/South America, and
(iv) Europe/Africa.
The SPACEWAY™ network will provide in each of these regions the same low-cost, ubiquitous
communications services at data rates up to multiple megabits per second, while also providing worldwide
connectivity.

Fig:1 Spaceway global Network,phase 1 (initial operating capability by 2000), showing orbital locations.
Space Segment Characteristics
The deployment of the multibeam satellites at geostationary orbit will be accomplished on a phased regional
implementation. The proposed assignment of frequencies and polarizations to satellite beams, the geographic
coverage provided by these beams, and a description of the other satellite parameters are given below.
Frequency and Polarization Assignments
The SPACEWAY™ global network will utilize the 17.7 to 20.2 GHz portion of the Ka band for space-to-
Earth (downlink) transmissions, and the 27.5 through 30.0 GHz portion of the Ka band for Earth-to-space
(uplink) transmissions. This spectrum has been allocated on a worldwide basis for the Fixed-Satellite Service
("FSS").

Fig:2 Spaceway spectrum utilization in North America
Fig: 3 Spaceway spectrum utilization in Central and south America, Europe, Africa, and Asia Pacific

Beam Coverage Areas
The proposed system will provide spot beam coverage of all inhabited land areas of the world. An eight
satellite constellation provides service to 90% of the world's population. Figure 4 depicts the four regions of
coverage by the SPACEWAY™ system. The two satellites per region provide high EIRP and G/T coverage to
allow the use of small inexpensive earth terminals.
Fig:4 An eight-satelite system provides service to 90% of the world’s population
Satellite Characteristics
The major spacecraft characteristics are given in Table 1. The launch weight budget is presented in Table 2.
Table 1: Major Spacecraft Characteristics
General
Spacecraft bus HS-601
Stabilization
Transfer orbit
On-station
Spin stabilization
3 axis, momentum bias
Mission life 15 years
Eclipse capability 100 percent
Station keeping
North-South (orbital inclination)
East-West (longitudinal)
±0.05°
±0.05°
Antenna pointing
Normal (Precision two-axis RF beacon tracking) ±0.1°N-SandE-W
Backup (Earth sensor) ±0.2° N-S and E-W
Beam rotation (antenna axis attitude) ±0.25°

Communications
Number of communications beams
(Satellites 1 and 2 over each region)3
48
Communications beam bandwidth 125MHz
Transmitter redundancy 64 for 48
Communications channel receive flux
density per Hz (narrow beams, edge of coverage)
-182.6dBW/(m2Hz)
Communications channel receive flux
density per Hz (wide beams, edge of coverage)
-194.1 dBW/(m2Hz)
Emission Limitations
(Spurious level below unmodulated power)
Frequency offset by 50% -100% of BW <_-65 dBc
Frequency offset by 100% - 250% of BW <_-65 dBc
Frequency offset by > 250% of BW <_-65 dBc
Table 2 Launch Weight Budget
Category Weight, Lb.
Spacecraft dry 3785
10 year orbit sustenance propellent 883
Beginning of life (subtotal) 4668
Transfer orbit 3159
Total separated weight 7827
Table 3 Satellite Uplink G/T Budget
Narrow Spot Beam
Peak Edge of Cov.
Antenna gain (db) 46.50 41.50
System noise temperature (dB K) 27.60 27.60
G/T (dB/K) 18.90 13.90

Table 4 Satellite Downlink EIRP Budget
Fig:5 Spaceway system availability in selected cities in the Asia Pacific region
Link Performance Objectives and Power Budgets:
Communication Links
Communication services will be provided at rates from 16 Kbps to 1.544 Mbps (T1). User terminals will have
the capability to transmit and receive via 66 cm to 2 m aperture antennas with transmit powers that range from
0.1 W to 2.0 W transmit power,depending on data rate and the amount of uplink power control used to
compensate for rain attenuation. Up to 240 simultaneous 384 Kbps uplink signals may be supported in each
beam for a data throughput of 92 Mbps per polarization per beam per satellite. With twelve-fold frequency
reuse, the total data throughput is 4.4 Gbps per satellite.
The system performance objective is a bit error rate ("BER") of 10'10. Because of on-board demodulation and
remodulation of the signal, performance on the uplink and performance on the downlink are independent. Due
Narrow Spot Beam
Peak Edge of Cov.
Amplifier output power (db) 13.01 13.01
Repeater output losses (dB) 0.50 0.50
Antenna gain (dB) 46.50 41.50
EIRP (dBw) 59.01 54.01

to the error control coding used, the bit energy levels required of the two links are asymmetric. An Eft/No of
8.0 dB on the uplink and 5.0 dB on the downlink are required to meet the targeted BER. Table 5 is a summary
of the spot beam communication performance parameters for a data rate of 384kbps.
Table 5. Summary of Spot Beam Communication Performance Parameters
Performance requirement 1x10-10BER
Transponder bandwidth 125 MHz
Modulation QPSK
Uplink data rate 16 to 1,544 Kbps
Uplink channel bandwidth 500 to 2,000 KHz
Required uplink Eb/No 8.0 dB
Downlink data rate (per beam per polarization) 92 Mbps
Downlink channel bandwidth 125 MHz
Required downlink Eb/No 5.0 dB
Earth station diameter 66 cm to 2 m
Earth station amplifier power 1.0 - 2.0 W
Loss to antenna input 0.5 dB
Earth station receive system
noise temperature
24.4 dBK
Tables 6 and 7 provide sample link analysis calculations for uplink peak and edge-of-coverage paths and
downlink peak and edge-of-coverage paths, respectively, for the spot beams. Each table illustrates both clear
sky and rain conditions. These calculations assume 384 kbps service.
Table 6. Uplink Power Budgets
Peak of Coverage
Transmit power
Tramsmit losses
Ground transmit gain
Uplink path spreading
Uplink effective isotropic area
Atmosheric loss
Uplink rain loss
Satellite G/T (peak)
Bit rate
Boltzmann's constant
Clear
- 9.73 dBW
- 0.50 dB
44.45 dB
- 162.31 dB/MA2
- 50.85 dB/mA2
- 0.96 dB
0.00 dB
18.88 dB/K
55.87 dB Hz
- 228.60 dBW/K/Hz
Rain
- 3.01 dBW
- 0.50 dB
44.45 dB
- 162.31 dB/mA2
- 50.85 dB/mA2
- 0.96 dB
- 8.77 dB
18.88 dB/K
55.87 dB Hz
- 228.60 dBW/K/Hz
Thermal Eb/No
Cross-»pol Eb/No
Adjacent beam co-pol Eb/l
Adjacent system (east) Eb/l
Adjacent system (west) Eb/l
11.72dB
17.45 dB
17.95 dB
20.85 dB
20.85 dB
9.67 dB
17.45 dB
17.95 dB
20.85 dB
20.85 dB
Total Eb/l 9.29 dB 8.00 dB