Author Affiliations
1Information and Navigation College, Air Force Engineering University, Xi’an 710077, China2College of Advanced Interdisciplinary Studies, National University of Defense Technology, Changsha 410073, China3College of Computer and Science, National University of Defense Technology, Changsha 410073, China4Teaching and Research Support Center, National University of Defense Technology, Changsha 410073, Chinashow less
Fig. 1. Schematic diagram of satellite and aircraft in the WGS-84 coordinate system.
Fig. 2. Schematic diagram of downlink satellite-to-aircraft QKD in the spherical coordinate system based on the aircraft. The satellite (Alice) flies in a certain orbit above the receiving aircraft (Bob).
Fig. 3. Schematic diagram of the distance between the BL and receiver telescope.
Fig. 4. Diagram of the satellite-to-aircraft QKD performance evaluation.
Fig. 5. Schematic diagram of photon aberrations evaluation. The photons propagate through the BL to the receiver telescope, and the wavefront aberration can be calculated by the ray-tracing method.
Fig. 6. Evaluated density field distribution of the DLR-F6 BL. The dimensions of the BL are .
Fig. 7. Total loss over the different incident angles. Here they are α = 0°, 90°, 180°, 270°.
Fig. 8. Schematic diagram of satellite-to-aircraft QKD from 12:00 on May 29, 2022, to 12:00 on June 5, 2022. The yellow arrow indicates the direction of flight of the aircraft.
Fig. 9. (a) Total loss in the satellite-to-aircraft QKD scenario; (b) estimated QBER over the communication time; (c) secure key rate over the communication time. The value of X0 is 66 mm and the aircraft flights toward the south. The intensity of signal states is 0.8, and the intensity of decoy states is 0.1.
Fig. 10. (a) Total loss in the satellite-to-aircraft QKD scenario; (b) estimated QBER over the communication time; (c) secure key rate over the communication time. The value of X0 is 66 mm and the aircraft flights toward the east. The intensity of signal states is 0.8, and the intensity of decoy states is 0.1.
Payload | Parm. | Description | Value |
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Aircraft | v | Flight speed | 0.7 Ma | hB | Altitude of aircraft | 10 km | ρh | Air density | 0.413 kg/m3 | τ | Extinction optical thickness[46] | 0.02 | Photon source | DT | Diameter of the transmitter telescope | 0.3 m | δT | Transmitter pointing precision[10] | 10 µrad | λ | Transmitter wavelength | 1550 nm | ω0 | Waist radius | 0.0949 m | r0 | Fried parameter in zenith[44] | 0.4 m | μ | Intensity of signal states | 0.8 | ν | Intensity of decoy states | 0.1 | N | System repetition rate | 100 MHz | Ps | Probability of signal states | 50% | Pd | Probability of decoy states | 30% | Pv | Probability of vacuum states | 25% | Receiving module | DR | Diameter of the receiver telescope | 0.5 m | ed | System detection error rate | 1% | pd | Dark count rate | 2 × 10−6 | ηd | Detector efficiency | 50% | ηs | Receiving optical module efficiency | 60% |
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Table 1. Parameters of Airborne QKD