FIELD: space.
SUBSTANCE: group of inventions relates to control over artificial satellites in order to prevent their collision with space debris. Onboard system of the satellite by radar means determines the probability of such collisions from all directions inside a spheroid around the satellite. At sufficiently high probability the system calculates the deviation path basing on ephemeris data for the satellite and the debris generated by itself. Path is implemented by low-thrust engines when following the requirement of minimum change of the satellite orbit.
EFFECT: technical result of the group of inventions is improved reliability and simplified procedure of deviation from the satellite collision with space debris in autonomous or semi-autonomous mode.
32 cl, 4 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| METHOD OF MANOEUVRING DEVIATION OF SPACECRAFT ON ORBIT FROM COLLISION WITH OTHER BODIES | 2015 |
|
RU2586920C1 |
| WARNING OF DANGER IN NEAR-EARTH SPACE AND ON EARTH AND ACS TO THIS END | 2014 |
|
RU2570009C1 |
| SPACE DEBRIS SPACECRAFT | 2019 |
|
RU2703056C1 |
| SPACE DEBRIS CLEANUP DEVICE | 2021 |
|
RU2769579C1 |
| DEVICE FOR DELIVERY OR RETURN OF ARTIFICIAL SATELLITES | 2012 |
|
RU2600971C2 |
| METHOD OF REGISTERING APPROXIMATION OF AN ACTIVE OBJECT TO THE SPACECRAFT OF ORBITAL RESERVE IN THE REGION OF LOW EARTH ORBITS | 2017 |
|
RU2658203C1 |
| REMOVAL OF NON-FUNCTIONAL SPACECRAFT FROM GEOSTATIONARY ORBIT | 2014 |
|
RU2559392C1 |
| METHOD OF SIMULTANEOUS INJECTION OF SEVERAL SATELLITES INTO NON-COPLANAR ORBITS WITH USE OF HEAVILY ECCENTRIC ORBITS AND ATMOSPHERIC BRAKING | 1997 |
|
RU2220886C2 |
| SPACE DEBRIS NEAR THE GEOSTATIONARY ORBIT DETECTION AND MONITORING METHOD | 2018 |
|
RU2684253C1 |
| PROCEDURE OF AUTONOMOUS REDUCTION OF THRESHOLDS OF DETECTION AND FOLLOWING OF CARRIER SIGNALS RECEIVED IN ORBIT | 1997 |
|
RU2187127C2 |
