In-orbit service
In-orbit service
In-orbit service
IN-ORBIT SERVICE
Service spacecraft
As market of the in-orbit servicing develops, it opens massive opportunities for satellite operators, launch services provider and other space activities participants to efficiently approach the issues related to the in-orbit servicing of the satellites. Service spacecraft may become irreplaceable assistants in deorbiting of space debris, accumulation of which has become global issue as the mankind keeps exploring the outer space.
Area of application of the Yuzhnoye-developed service spacecraft is in-orbit servicing of the client satellites in low near-Earth orbit.
These spacecraft are unique in their versatility, fit for docking with various types of SC and space debris objects, capable of providing wide range of services. Multiple use will be provided.
In-orbit service SC consists of the following:
• rendezvous system;
• grabbing system;
• control system;
• communications system;
• propulsion system;
• power supply system;
• thermal control system;
• intersystem cabling.
Service spacecraft renders the following in-orbit services to the client spacecraft in the low near-Earth orbits:
• placing client satellites into the required orbital position;
• placing client satellites to the target orbit in case they were misplaced into the off-nominal orbit;
• keeping the client satellites in the specified orbital positions;
• placing waste client satellites to the orbit with perigee altitude of 400 km or to the graveyard orbit.
Interorbital transport vehicle performs such operations as maneuvering to transfer to the orbit of the client satellites and rendezvous with them; shockless grabbing/docking with satellites, as well as interorbital transfer of satellites.
Main specifications of the in-orbit service SC
In-orbit service spacecraft | |
Range of service orbits: | |
– altitude, km | (500….1500)±100 |
– inclination, deg | (0….180)±1 |
– orbital position, deg | ±180 |
Accuracy of orbital position maintenance, deg | 0,1 |
Mass after separation from the rocket (LV), kg | ~ 2400 |
Active life, years | 5 |
Client satellite | |
Mass, kg | 250 – 3000 |
Solar arrays span, m | 5 – 20 |
Overall dimensions, m | 2×1×1 – 8×4×4 |
IN-ORBIT SERVICE
IN-ORBIT SERVICE
As market of the in-orbit servicing develops, it opens massive opportunities for satellite operators, launch services provider and other space activities participants to efficiently approach the issues related to the in-orbit servicing of the satellites. Service spacecraft may become irreplaceable assistants in deorbiting of space debris, accumulation of which has become global issue as the mankind keeps exploring the outer space.
Area of application of the Yuzhnoye-developed service spacecraft is in-orbit servicing of the client satellites in low near-Earth orbit.
These spacecraft are unique in their versatility, fit for docking with various types of SC and space debris objects, capable of providing wide range of services. Multiple use will be provided.
In-orbit service SC consists of the following:
• rendezvous system;
• grabbing system;
• control system;
• communications system;
• propulsion system;
• power supply system;
• thermal control system;
• intersystem cabling.
Service spacecraft renders the following in-orbit services to the client spacecraft in the low near-Earth orbits:
• placing client satellites into the required orbital position;
• placing client satellites to the target orbit in case they were misplaced into the off-nominal orbit;
• keeping the client satellites in the specified orbital positions;
• placing waste client satellites to the orbit with perigee altitude of 400 km or to the graveyard orbit.
The interorbital transport vehicle performs such operations as maneuvering to transfer to a client satellite orbit and approach the satellite; shock-free capture of/docking with the satellites, and interorbital towing of the satellites.
Main specifications of the in-orbit
service SC
In-orbit service spacecraft | |
Range of service orbits: | |
– altitude, km | (500….1500)±100 |
– inclination, deg | (0….180)±1 |
– orbital position, deg | ±180 |
Accuracy of orbital position maintenance, deg | 0,1 |
Mass after separation from the rocket (LV), kg | ~ 2400 |
Active life, years | 5 |
Client satellite | |
Mass, kg | 250 – 3000 |
Solar arrays span, m | 5 – 20 |
Overall dimensions, m | 2×1×1 – 8×4×4 |