1. RESEARCH POSTER PRESENTATION DESIGN © 2015
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Quantum Communication
Satellite
QCS
Quantum Communication
Satellite
QCS Mission
Delivering encrypted quantum communication keys between two different ground stations
through a constellation of satellites covering latitudes of ±70°, in a transition time of less
than 15 minutes, so that each ground station will be able to transfer information each 15
minutes.
Orbit Design
The orbit design team developed an optimal LEO constellation consisting of 80
satellites in 10 orbit planes: 80/8/3 Walker pattern with the orbit parameters:
𝒆 = 𝟎, 𝒂 = 𝟔𝟗𝟕𝟖. 𝟏𝟒 𝒌𝒎 , 𝒊 = 𝟔𝟓°
Additionally , deployment maneuvers for each orbit plane were planned using a
Hohmann transfer orbits. The entire deployment time is 𝚫𝑻 = 𝟐𝟖 𝒅𝒂𝒚𝒔 and requires
𝚫𝑽 = 𝟓. 𝟒𝟐
𝒎
𝒔
per satellite, and also stationkeepin
g maneuvers to avoid constellation breakup using a control box pulse each 0.5 [km] of
decay from the desired orbit. These maneuvers requires 𝚫𝑽 = 𝟐. 𝟐𝟕
𝒎
𝒔
per satellite.
Structure and Thermal Design
The structure and thermal design team designed a CubeSat
concept satellite of 20U size, with mass of 22 [kg ] carrying the
payload (quantum communication camera) along with bus systems and propulsion
block. Using SolidWorks simulation tool the structure has been tested to withstand
possible static and dynamic loads during the launch.
Thermal design is based on passive control. By using multilayer insulation materials and
proper radiation protection it was achieved that temperature inside the satellite
remains above 0 °𝐶 and less than 40 °𝐶 along the whole orbit period.
Structure and internal layout Thermal analysis
Attitude Determination & Control System
The ADCS team wrote a full 6DOF simulation of a satellite in orbit which included
various disturbance torques, magnetic and solar physical models, sensor and actuator
error models and also numerous ground stations and satellites. A comprehensive state
machine was designed and implemented in order to fulfill all maneuverability mission
requirements, along with the implementation of suitable controllers and estimators.
The appropriate sensors and actuators were selected and modelled and complete
mission scenario, which included the various communication and maintenance
command modes, was run and completed successfully.
Mission Scenario Command Modes Mission Scenario Pointing Accuracies
Constellation pattern Control box
Reliability
RBD and redundancy: The mode “QKD Pointing” is presented below in RBD form. It
exhibits redundancies in the reaction wheel, the star tracker, and in the battery:
𝑅 𝑄𝑃 = 0.9771
Satellite Reliability: This reliability will include communication modes, due to the superior
importance of the communication in our mission.
𝑅𝑡𝑟𝑎𝑛𝑠𝑓𝑒𝑟𝑟𝑖𝑛𝑔 𝑆𝑎𝑡. = 0.9293 𝑅 𝑟𝑒𝑐𝑒𝑖𝑣𝑖𝑛𝑔 𝑆𝑎𝑡. = 0.9419
The satellite's reliability numbers are sufficient for feasible performance.
Space Environment:
Understand the space environment phenomena at LEO orbits and monitor the
spacecraft through these phenomena to prevent degradation and decomposition.
Radiation in space mainly effects electrical components, and there's a need
to cover these components with a thin shielding layer of aluminum. 10Krad
is the radiation dose that most of the electrical components can withstand.
For safety measures, we used a safety factor and received 2mm optimal
aluminum layer thickness.
The following table summarize all materials used in the satellite that can be
damaged by atomic oxygen flux or by vacuum:
From the table we can infer that all materials shall withstand the atomic oxygen flux in
orbit. In addition, all the materials used in the satellite sub-systems are resilient to the
outgassing effects (all under the test values), and are eligible for use in space.
Power System
The power system produces and manages electrical power, and distributes it to the
satellite components
The system includes solar panels for power production, batteries for power storage, and
a power conditioning and distribution unit
A simulation enables an analysis of the system operation at different mission scenarios
Power production by solar panels for a typical mission scenario
0 1000 2000 3000 4000 5000 6000 7000 8000
0
20
40
60
80
Solar Panel Power Production vs. Time
Time [sec]
PowerProduction[W]
Propulsion
A cold gas propulsion system used
for deployment, orbit transfers
and disposal. The system is
composed of 2 propellant tanks, 4
thrusters and control valves, with
Krypton used as a propellant
Thrust: 0.1 [N]
Total velocity change: 14.7
[m/sec]
3D model of the propulsion system
Communication
The communication system is responsible on transferring important data such as:
Tracking & Telemetry, Command, and Inter satellite communication. The system
supports Satellite to Satellite and Ground to Satellite (and vice versa) communication.
Furthermore, The system has been designed to transfer encrypted data in an above
atmosphere path to minimize the possibility of eavesdropping. A Link budget simulation
have been designed in order to test and simulate different communication scenarios with
different communication components. 0 1000 2000 3000 4000 5000 6000 7000 8000
0
500
1000
1500
2000
2500
3000
X: 3452
Y: 1121
Ground Station distance
Distance[km]
Time [sec]
0 1000 2000 3000 4000 5000 6000 7000 8000
0
0.2
0.4
0.6
0.8
1
X: 3452
Y: 0
Time [sec]
Link
Satellite Cmmunication
0 = Not Established
1 = Established
0 1000 2000 3000 4000 5000 6000 7000 8000
0
500
1000
1500
2000
2500
3000
X: 3452
Y: 1121
Ground Station distance
Distance[km]
Time [sec]
0.6
0.8
1
ink
Satellite Cmmunication
0 = Not Established
1 = Established
Launcher
Launch
Vehicle
Number of
launches
(per year)
Multi-
Payload
Capacity
Cost (in
Million $)
Dnper-1 2 ----------- 0.16
Vega 2 2 0.62
LancherOne 3 6 3
Electron 11 4 7.7
Bloostar 4 3 3.6
Total Cost: 15.08M$
The final Launch Plan
Launch
Vehicle
Advantages
Vega &
Dnepr-1
Effective cost considerations,
Have high reliability,
Tested and fully informative.
Launcher
One,
Bloostar
&
Electron
Very good multi-payload
capacity,
High availability (Electron) and
terms of launch (Bloostar,
LauncherOne)