The X-band transmitter is a major subsystem of a satellite, which carries out the function of downloading the satellite mission data, without which, the satellite mission fails. This fact enriches the need for in-house X-band transmitter design which may be used for many other missions and simplifies any changes required according to mission changes. The main goal of this short project is to develop highly qualified high data rate X-band transmitter engineering model for Egyptian Experimental satellites series and similar satellites with fully Egyptian hand. The proposed subsystem should satisfy all the satellite requirements including throughput, resistance to environmental conditions, mechanical interface, electrical interface, etc. This project aims at building the on-board equipment of the X-band transmitter to be used in the engineering model of MisrSat-2 satellite and, if qualified, to be used in MisrSat-2 satellite. This transmitter will provide using different data rate in downloading the images, which will increase the productivity of the satellite while keeping the signal quality the same. In addition, project aims at building the capacity of the engineers those are members of the space program in NARSS, through the development of the X-band transmitter in a compact, low power consuming and lightweight manner to be used on board a LEO remote sensing satellite, in downloading the image data collected by the satellite imagery devices. This is one of the important components onboard the satellite which has to be developed according to the latest technologies and be tested for the space environment. The work in the project will be achieved in 4 phases occupying 24 months to have an engineering model of the transmitter. If the developed transmitter is selected to be launched after passing the qualification tests, there will be another sub-project (with separate budget) to qualify this transmitter to be used in the flying satellite and then the whole project will span then for 30 months

July 01, 2019

Major objectives are expected from this project, as can be seen from participation of the Egyptian industry in manufacturing of space-qualified products; manufacturing capabilities are investigated under the framework of this project as follow:


Outcome: X-band transmitter can be summarized in the following points:

  1. Reception of the payload data serially through the payload interface with the X-band transmitter.
  2. Performing the required digital signal processing (encoding, scrambling) on the received payload data.
  3. Forming of the transmitted waveform through modulating the RF carrier with the processed data from payload, filtering and amplifying of the modulated RF signal to the required signal level.
  4. Performing the self-test of the X-band transmitter with test data pattern.
  5. Passing telemetry information about X-band transmitter health through telemetry interface.
  6. Support of interfaces with adjacent subsystems:
    1. Support of interfaces with Imager subsystem
    2. Support of interfaces with satellite power supply
    3. Support of interfaces with Satellite on-board computer
  7. The X-band equipment should provide transmission of data flow transferred from the payload subsystem with a rate of up to 150 Mbps with rate selection capability. Note. The structure of the data flow should be agreed with the developer of MisrSat-2 satellite at the system requirements development phase.
  8. The X-band transmitter should provide modulation types (OQPSK).
  9. Mass of the X-band transmitter should not exceed 3 kg.
  10. Power consumed by the X-band transmitter should not be more than 80 W.
  11. Probability of the X-band transmitter non-failure operation should not be less than 0.97 for the 6-months Experimental satellite lifetime. For laboratory implementation using commercial and industrial grade components, the reliability should be dramatically decreased.
  12. Environmental conditions
    • At temperature variation inside the non-sealed satellite body from minus 10°С up to +45°С.
    • Under zero gravity.
    • Humidity from 50% to 80% at a temperature from -15°C up to 35°С and normal atmospheric pressure (86…106 kPa).


Division : Space Sciences and Strategic Studies