RU-2024132930-A - Method 1 for launching a spacecraft (SC) into a heliostationary orbit of an artificial quasi-satellite (AS) of Earth, Venus and Mercury

Inventors

• Кузьменков Евгений Васильевич

Assignees

• Кузьменков Евгений Васильевич

Dates

Publication Date

20260504

Application Date

20241101

Claims (5)

1. 1. Method 1 for launching into a heliostationary orbit an artificial quasi-satellite of the Earth, Venus and Mercury, containing a rocket engine and a course and orientation stabilization system, wherein at the first stage a preliminary flight is carried out in the mode of an artificial Earth satellite, then at the second stage a maneuver is performed tangentially to its orbit in the direction of its movement, acquiring an orbital velocity of about 30 km/s and the quality of a helio-satellite.
2. 2. Method 1 according to paragraph 1, characterized in that, in order to increase safety, reduce costs and flight time, the quasi-satellite (SA) 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. 3. Method 1 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 the spacecraft’s flight at an angle of 16° to the Sun, while maintaining its general planetary direction of motion.
4. 4. Method 1 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 for its geometric addition with the relative speed in the heliocentric orbit of 30 km/s, increasing the total speed to the orbital speed of Venus, equal to 35 km/s.
5. 5. Method 1 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 spacecraft is transferred into a “1-1” resonance with the planet Venus with a sufficiently elongated elliptical orbit, obtaining its final quality of a quasi-satellite and an orbital velocity of 35 km/s, and as a result it regularly crosses the orbits of three planets: Mercury, Venus and Earth.