Spacecraft rendezvous and docking techniques
Techniques for performing spacecraft rendezvous and/or docking include operating a first orbiting spacecraft, the first spacecraft including a sensor arrangement, a first processor and a first inter-satellite link (ISL) arrangement and performing one or both of a rendezvous operation and a docking operation with the first spacecraft and a second orbiting spacecraft, the second spacecraft including one or more actuators. The performing one or both of the rendezvous operation and the docking operation includes determining a pose and pose rate of the second spacecraft relative to the first spacecraft using observations made by the sensor arrangement and determining a desired approach trajectory for the second spacecraft.
1. A method comprising:
operating a first orbiting spacecraft, the first spacecraft including a sensor arrangement, a first processor and a first inter-satellite link (ISL) arrangement; and
performing one or both of a rendezvous operation and a docking operation with the first spacecraft and a second orbiting spacecraft, the second spacecraft including one or more actuators; wherein:
the one or more actuators include one or more thrusters, reaction wheels, magnetic torquers, or solar sails; and the performing one or both of the rendezvous operation and the docking operation includes:
using observations made by the sensor arrangement to determine (a) a pose and pose rate of the second spacecraft relative to the first spacecraft, and (b) a desired approach trajectory for the second spacecraft; and
transmitting to the second spacecraft, by way of the first ISL arrangement, instructions to follow the desired approach trajectory, the instructions including a sequence of maneuvers and/or commands to the one or more actuators.
2. The method of claim 1 , wherein determining the desired approach trajectory for the second spacecraft is performed by the first processor.
3. The method of claim 1 , wherein performing one or both of the rendezvous operation and the docking operation includes transmitting to the second spacecraft, by way of the first ISL arrangement, a signal indicating a twelve degree of freedom (12 DOF) error in pose and pose rate with respect to the desired approach trajectory.
4. The method of claim 1 , wherein performing one or both of the rendezvous operation and the docking operation includes:
operating the second orbiting spacecraft, the second spacecraft including a second processor and a second ISL arrangement;
receiving, at the second spacecraft, by way of the second ISL arrangement, the instructions;
processing the instructions with the second processor; and
executing, with the second processor one or both of the sequence of maneuvers and the set of actuator commands in accordance with the processed instructions.
5. The method of claim 1 , wherein the sensor arrangement includes one or more of an optical imaging subsystem, a lidar subsystem and a radar subsystem.
6. The method of claim 1 , wherein the actuators include one or more of thrusters, reaction wheels, magnetic torquers, and solar sails.
7. A first spacecraft comprising a sensor arrangement, a first processor and a first inter-satellite link (ISL) arrangement, wherein
the sensor arrangement is configured to make observations of a second spacecraft;
the first processor is configured to determine (a) a pose and pose rate of the second spacecraft relative to the first spacecraft using the observations, and (b) a desired approach trajectory for the second spacecraft in order to execute one or both of a rendezvous operation and a docking operation; and
the first spacecraft is configured to control one or both of the rendezvous operation and the docking operation by:
transmitting to the second spacecraft, by way of the first ISL arrangement, instructions to follow the desired approach trajectory, the instructions including a sequence of maneuvers to be executed by the second spacecraft and/or commands to one or more of thrusters, reaction wheels, magnetic torquers, or solar sails on board the second spacecraft.
8. The first spacecraft of claim 7 , wherein the first spacecraft is configured to control one or both of the rendezvous operation and the docking operation by transmitting to the second spacecraft, by way of the first ISL arrangement, a signal indicating a twelve degree of freedom error in pose and pose rate with respect to the desired approach trajectory.
9. The first spacecraft of claim 7 , wherein one or both of the rendezvous operation and the docking operation include:
operating the second spacecraft, the second spacecraft including a second processor and a second ISL arrangement;
receiving, at the second spacecraft, by way of the second ISL arrangement, the instructions;
processing the instructions with the second processor; and
executing, with the second processor one or both of the sequence of maneuvers and the set of actuator commands in accordance with the processed instructions.
10. The first spacecraft of claim 7 , wherein the sensor arrangement includes one or more of an optical imaging subsystem, a lidar subsystem and a radar subsystem.
11. A system comprising:
a first orbiting spacecraft including a sensor arrangement, a first processor and a first inter-satellite link (ISL) arrangement; and
a second orbiting spacecraft including a second processor and one or more actuators; wherein:
the one or more actuators include one or more thrusters, reaction wheels, magnetic torquers, or solar sails
the sensor arrangement is configured make observations of the second spacecraft;
the system is configured to perform one or both of a rendezvous operation and a docking operation of the first spacecraft and the second spacecraft by one or both of the rendezvous operation and the docking operation includes:
using observations made by the sensor arrangement to determine (a) a pose and pose rate of the second spacecraft relative to the first spacecraft, and (b) a desired approach trajectory for the second spacecraft; and
transmitting to the second spacecraft, by way of the first ISL arrangement, instructions to follow the desired approach trajectory, the instructions including a sequence of maneuvers and/or commands to the one or more actuators.
12. The system of claim 11 , wherein determining the desired approach trajectory for the second spacecraft is performed by the first processor.
13. The system of claim 11 , wherein the first spacecraft is configured to control one or both of the rendezvous operation and the docking operation by transmitting to the second spacecraft, by way of the first ISL arrangement, a signal indicating a twelve degree of freedom error in pose and pose rate with respect to the desired approach trajectory.
14. The system of claim 11 , wherein one or both of the rendezvous operation and the docking operation includes:
operating the second orbiting spacecraft, the second spacecraft including a second processor and a second ISL arrangement;
receiving, at the second spacecraft, by way of the second ISL arrangement, the instructions;
processing the instructions with the second processor; and
executing, with the second processor one or both of the sequence of maneuvers and the set of actuator commands in accordance with the processed instructions.
15. The system of claim 11 , wherein the sensor arrangement includes one or more of an optical imaging subsystem, a lidar subsystem and a radar subsystem.
16. The system of claim 11 , wherein the actuators include one or more of thrusters, reaction wheels, magnetic torquers, and solar sails.