Method 2 for launching an artificial quasi-satellite of Earth, Mars and the asteroid belt into heliostationary orbit

Inventors

Кузьменков Евгений Васильевич

Assignees

Кузьменков Евгений Васильевич

Dates

Publication Date: 20260504
Application Date: 20241101

Claims (5)

1. Method 2 for launching into a heliostationary orbit an artificial quasi-satellite of the Earth, Mars and the asteroid belt, containing a rocket engine and a course and orientation stabilization system, wherein at the first stage a preliminary flight is carried out in the artificial geosatellite mode, then at the second stage a maneuver is performed tangentially to its orbit in the direction of the Earth's motion, acquiring an orbital velocity of about 30 km/s and the quality of a heliosatellite:
2. Method 2 according to paragraph 1, characterized in that, in order to increase safety, reduce costs and flight time, the heliosatellite is in free flight mode for 60 days and twenty hours in a heliocentric orbit, reaching the Lagrange point (libration), in which it, with a significantly smaller mass, is gravitationally neutral, since it avoids the influence of two more massive bodies - the Sun and the Earth.
3. Method 2 according to paragraph 1, characterized in that, in order to increase safety, reduce costs and flight time, the course stabilization and orientation system at the Lagrange point at the third stage changes the direction of flight of the heliosatellite at an angle of 19 degrees from the Sun, against the general planetary direction of motion.
4. Method 2 according to paragraph 1, characterized in that, in order to increase safety, reduce costs and flight time, the direction of flight is changed at a speed of 18 km/s to geometrically subtract it from the relative speed in the heliocentric orbit of 30 km/s, reducing the speed to the orbital speed of Mars, equal to 24 km/s.
5. Method 2 according to paragraph 1, characterized in that, in order to increase safety, reduce costs and flight time, the course stabilization and orientation system of the heliosatellite is transferred into a “1-1” resonance with the planet Mars with a sufficiently elongated elliptical orbit, obtaining its final quality of a quasi-satellite and an orbital velocity of 24 km/s, and as a result it regularly crosses the orbits of the Earth, Mars and the asteroid belt.