Systems and methods for launching a plurality of spacecraft
Systems and methods for launching a plurality of spacecraft, provided in a stack of spacecraft, from a launch vehicle traveling along an in-track path include releasing, in a first separation event occurring at a first time, a first spacecraft from the stack of spacecraft using a first separation force having a first separation force in-track component along the in-track path. Subsequently, in a second separation event occurring at a second time, a second spacecraft is released from the stack of spacecraft using a second separation force having a second separation force in-track component along the in-track path, wherein the second time occurs a first time delay after the first time. The first and second separation in-track components may be different, such as by varying a magnitude of the separation force or an angle at which the spacecraft is launched.
1. A method of launching a plurality of spacecraft provided in a stack of spacecraft from a launch vehicle, the launch vehicle traveling along an in-track path, the method comprising:
actuating at least one first biasing element to generate a first separation force having a first separation force in-track component along the in-track path, the plurality of the spacecraft including a first spacecraft and a second spacecraft, the at least one first biasing element disposed between the first spacecraft and the second spacecraft;
releasing, in a first separation event occurring at a first time, the first spacecraft from the stack of spacecraft using the first separation force;
actuating at least one second biasing element to generate a second separation force having a second separation force in-track component along the in-track path, the at least one second biasing element associated with the second spacecraft, the second separation force different from the first separation force, the second separation force in-track component different from the first separation force in-track component; and
releasing, in a second separation event at a second time after the first time, the second spacecraft from the stack of spacecraft using the second separation force.
2. The method of claim 1 , wherein the first separation force in-track component is less than the second separation force in-track component.
3. The method of claim 1 , wherein the first separation force in-track component is greater than the second separation force in-track component.
4. The method of claim 3 , wherein a first magnitude of the first separation force is greater than a second magnitude of the second separation force.
5. The method of claim 3 , wherein:
the launch vehicle is oriented in a forward direction along the in-track path during the first separation event; and
the launch vehicle is oriented in a first rotated direction angularly offset from the forward direction along the in-track path by a first rotation angle during the second separation event.
6. The method of claim 5 , wherein the first rotation angle is 180 degrees.
7. The method of claim 5 , wherein the first rotation angle is 60 degrees.
8. The method of claim 1 , wherein the plurality of the spacecraft include a third spacecraft, and further including:
releasing, in a third separation event at a third time after the second time, the third spacecraft from the stack of spacecraft using a third separation force having a third separation force in-track component along the in-track path.
9. The method of claim 8 , wherein the first separation force in-track component is greater than the second separation force in-track component, and the second separation force in-track component is greater than the third separation force in-track component.
10. The method of claim 9 , wherein:
the launch vehicle is oriented in a forward direction along the in-track path during the first separation event;
the launch vehicle is maintained in the forward direction along the in-track path during the second separation event; and
the launch vehicle is oriented in a first rotated direction angularly offset from the forward direction by a first rotation angle during the third separation event.
11. The method of claim 9 , wherein:
during the first separation event, the launch vehicle is oriented in a forward direction along the in-track path;
during the second separation event, the launch vehicle is oriented in a first rotated direction angularly offset from the forward direction by a first rotation angle; and
during the third separation event, the launch vehicle is oriented in a second rotated direction angularly offset from the forward direction by a second rotation angle, wherein the second rotation angle is different from the first rotation angle.
12. A system to launch a plurality of spacecraft from a launch vehicle traveling along an in-track path, the system comprising:
a stack of spacecraft releasably coupled to the launch vehicle, the stack of spacecraft including at least a first spacecraft releasably coupled to a second spacecraft;
a first separation assembly releasably coupling the first spacecraft and the second spacecraft;
at least one first biasing element disposed between the first spacecraft and the second spacecraft;
a second separation assembly associated with the second spacecraft;
at least one second biasing element associated with the second spacecraft; and
a stack separation controller to:
actuate the at least one first biasing element to generate a first separation force having a first separation force in-track component along the in-track path;
actuate the first separation assembly to release the first spacecraft from the stack of spacecraft during a first separation event at a first time;
actuate the at least one second biasing element to generate a second separation force having a second separation force in-track component along the in-track path, the second separation force different from the first separation force, the second separation force in-track component different from the first separation force in-track component and
actuate the second separation assembly to release the second spacecraft from the stack of spacecraft during a second separation event at a second time after the first time.
13. The system of claim 12 , wherein the first separation force in-track component generated by the at least one first biasing element is greater than the second separation force in-track component generated by the at least one second biasing element.
14. The system of claim 13 , wherein a first magnitude of the first separation force generated by the at least one first biasing element is greater than a second magnitude of the second separation force generated by the at least one second biasing element.
15. The system of claim 13 , further including a launch vehicle controller to:
control the launch vehicle to be oriented in a forward direction along the in-track path during the first separation event; and
control the launch vehicle to be oriented in a first rotated direction angularly offset from the forward direction by a first rotation angle during the second separation event.
16. The system of claim 12 , wherein:
the stack of spacecraft further includes a third spacecraft releasably coupled to the second spacecraft;
the second biasing element is disposed between the second spacecraft and the third spacecraft;
a third separation assembly is associated with the third spacecraft;
at least one third biasing element is associated with the third spacecraft; and
the stack separation controller is to:
actuate the at least one third biasing element to generate a third separation force having a third separation force in-track component along the in-track path; and
actuate the third separation assembly to release the third spacecraft from the stack of spacecraft during a third separation event at a third time after the second time.
17. The system of claim 16 , wherein the first separation force in-track component generated by the at least one first biasing element is greater than the second separation force in-track component generated by the at least one second biasing element, and the second separation force in-track component generated by the at least one second biasing element is greater than the third separation force in-track component generated by the at least one third biasing element.
18. The system of claim 17 , further including a launch vehicle controller to:
control the launch vehicle to be oriented in a forward direction along the in-track path during the first separation event;
control the launch vehicle to be maintained in the forward direction along the in-track path during the second separation event; and
control the launch vehicle to be oriented in a first rotated direction angularly offset from the forward direction of the in-track path by a first rotation angle during the third separation event.
19. The system of claim 17 , further including a launch vehicle controller to:
control the launch vehicle to be oriented in a forward direction along the in-track path during the first separation event;
control the launch vehicle to be oriented in a first rotated direction angularly offset from the forward direction by a first rotation angle during the second separation event; and
control the launch vehicle to be oriented in a second rotated direction angularly offset from the forward direction by a second rotation angle during the third separation event, wherein the second rotation angle is different from the first rotation angle.
20. A method of launching a plurality of spacecraft provided in a stack of spacecraft from a launch vehicle, the launch vehicle traveling along an in-track path, the method comprising:
in response to actuating at least one first biasing element to generate a first separation force having a first separation force in-track component along the in-track path, releasing, in a first separation event occurring at a first time, a first spacecraft from the stack of spacecraft based on the first separation force, the plurality of the spacecraft including the first spacecraft, a second spacecraft, a third spacecraft, and a fourth spacecraft, the at least one first biasing element disposed between the first spacecraft and the second spacecraft;
in response to actuating at least one second biasing element to generate a second separation force having a second separation force in-track component along the in-track path, releasing, in a second separation event occurring at a second time after the first time, the second spacecraft from the stack of spacecraft based on the second separation force, the at least one second biasing element disposed between the second spacecraft and the third spacecraft;
in response to actuating at least one third biasing element to generate a third separation force having a third separation force in-track component along the in-track path, releasing, in a third separation event occurring at a third time after the second time, the third spacecraft from the stack of spacecraft based on the third separation force; and
in response to actuating at least one fourth biasing element to generate a fourth separation force having a fourth separation force in-track component along the in-track path, releasing, in a fourth separation event occurring at a fourth time after the third time, the fourth spacecraft from the stack of spacecraft based on the fourth separation force; and
wherein each of the first, second, third and fourth separation force in-track components is different from other of the first, second, third, and fourth separation force in-track components.