Space conveyer Results of Advanced Research Schematic of

Space conveyer Results of Advanced Research

Schematic of rope system with rope location along the Earth radius Center of mass l НST VST l l L l l End-block Нb l Vb l Fig. 1 Rope length L=270 km. Нb = 180 km station orbital velocity VST = 7644 m/s НST = 450 km end-block velocity Vb = 7320 m/s circular velocity at the altitude Нb Vb = 7800 m/s overload at the end-block р = 0. 12

Oscillator dynamic characters VST НST l max l l l B C Нb VA D VC l l Velocity at point А VA = 6810 m/s Velocity at point С VC = 7830 m/s Overload at point А p = 0. 31 Overload at point С p = 0. 08 max ~ 55 0 period of oscillation T = 4500 s. А Fig. . 2

Schematic of station angular orientation control by means of rope system Center of mass 1 А 1 2 1 А 2 (a) А 1 (b) С 1 2 А 2 Control of rope (C 1) location relative to the station’s center of mass is realized by means of automatic change of rope segments (A 1 or A 2) lengths. (а) - before the control; (b) - during the control process. End-block fig. 3

“Turned over” version of Space oscillator (C) (A) End-block Altitude of the station orbit Rope length НST = 450 km. L = 270 km. Position (C): end-block velocity V = 8490 м/с overload р = 0. 3 VST Fig. 4

Scheme of loads exchange in “turned over” version of Space oscillator. Phase 1 Initial oscillator position Vrot. Phase 4 Cargo C 2 separation Vorb. C 1 C 2 Vrot. Phase 3 Exchange cargo C 1 with C 2 C 1 C 2 Fig. 5 Phase 2 Docking cargo C 1 at the end-block

Sling schematic with cargoes docked at the end-blocks Utilization of sling-based transport system for launching the payload to interplanetary trajectory Cargo 1 S 2 End-block C 1 C 2 Center of masses Vorb S 1 End-block Cargo 2 fig. 6 Fig 7

Velocity pulses distributions along the trace “Earth - Moon” 11. 2 km/s Elliptic orbit 2 Sling near Moon 9. 4 km/s Elliptic orbit 1 8. 9 km/s Sling 1 5. 8 km/s Delivery by means of rocket Velocity pulse values Earth surface Fig. 8