RU2013144363A - METHOD FOR RESERVING A SPACE VEHICLE IN A GEOSTATIONARY ORBIT - Google Patents

Abstract

A method of reserving a spacecraft in a geostationary orbit, including determining the reservation period, launching the spacecraft into a geostationary orbit at the calculated point according to the launch scheme with the initial inclination and longitude of the ascending node of the spacecraft’s orbit, which allow evolution to obtain an inclination towards the end of the reservation term that is close to zero, which differs the fact that they determine the required deviation of the starting position of the reservation (SPR) from the longitude of the working position by the ratio: where Δλ is the required deviation; t is the planned reservation period, day; - longitudinal acceleration; - longitude drift speed at the beginning of the reservation period; - longitude drift speed at the end of the reservation period; a - semi-axis of the quasi-stationary orbit, km; ΔU (λ) - disturbing geopotential at the longitude of the working position; ΔU (λ) is the disturbing geopotential at the longitude of the DSS, determine the required initial sidereal period of the spacecraft to the DSS by the ratio: where is the average motion, s; T is stellar day, 86164 s; λ is the longitude of the nearest point of stable equilibrium, east , bring the spacecraft to the SPR by period and longitude e; the spacecraft is switched to the hardware spin mode, when approaching the working position, the spacecraft is taken out of the spin and, if necessary, refinements are made to the inclination and eccentricity vectors according to the collocation conditions.

Claims (1)

A method of reserving a spacecraft in a geostationary orbit, including determining the reservation period, launching the spacecraft into a geostationary orbit at a calculated point according to the launching scheme with the initial inclination and longitude of the ascending node of the spacecraft’s orbit, which allows evolution to obtain an inclination towards the end of the reservation term that is close to zero, which differs the fact that they determine the required deviation of the starting position of the reservation (SPR) from the longitude of the working position by the ratio: $$\Delta \lambda =-\ddot{\lambda }\cdot \frac{t^2}{2},$$

where Δλ is the required deviation; t is the planned reservation period, day; $$\ddot{\lambda }=\frac{\dot{\lambda }-{\dot{\lambda }}_0}{t}$$

- longitudinal acceleration; $$\dot{\lambda }=\pm {\left({\dot{\lambda }}_0^2+R\right)}^{\frac{\mathrm{one}}{2}}$$

- longitude drift speed at the beginning of the reservation period; $${\dot{\lambda }}_0$$

- longitude drift speed at the end of the reservation period; $$R=\frac{6}{a_{cm}^2}\cdot \left[\Delta U\left(\lambda {}_0\right)-\Delta U\left({\lambda }_{\mathrm{FROM}PR}\right)\right],$$

a _cm - semimajor axis of the quasistationary orbit, km; ΔU (λ ₀ ) - disturbing geopotential at the longitude of the working position; ΔU (λ _SPR ) - perturbing geopotential at longitude SPR, determine the required initial sidereal period of spacecraft circulation to SPR by the ratio: $$T=\frac{2\pi }{n-\dot{\lambda }\cdot sign\left({\lambda }_0\cdot {\lambda }^{*}\right)},$$

Where $$n=\frac{2\pi }{T_{s\mathrm{at}}}$$

- average movement, s ^-1 ; T _stars - stellar day, 86164 s; λ ^* - longitude of the nearest point of stable equilibrium, east longitude, bring spacecraft to the DSS by period and longitude; the spacecraft is switched to the hardware spin mode, when approaching the working position, the spacecraft is taken out of the spin and, if necessary, refinements are made to the inclination and eccentricity vectors according to the collocation conditions.