Side-by-side multiple launch configuration
View Patent ↗A launch vehicle payload that includes at least two spacecraft is disclosed. The launch vehicle includes a single payload adapter. Each spacecraft has a launch vehicle adapter structure providing a respectively coplanar structural interface directly with the single launch vehicle payload adapter. The spacecraft share a launch vehicle payload fairing volume substantially side-by-side and are detachably coupled together such that a positive clearance is provided between adjacent, non-abutting structural body surfaces of each spacecraft.
1. A payload for a launch vehicle, the payload including at least two spacecraft, wherein:
the launch vehicle includes a payload adapter;
each spacecraft has a launch vehicle adapter structure providing a respectively coplanar structural interface directly with the payload adapter; and
the spacecraft share a launch vehicle payload fairing volume substantially side-by-side and are detachably coupled together, in a launch configuration, by at least one holddown device extending from between facing non-abutting body surfaces of the at least two spacecraft such that a positive clearance is provided between facing non-abutting body surfaces of each spacecraft.
2. The payload of claim 1 , wherein the coplanar structural interface is substantially orthogonal to a longitudinal axis of the launch vehicle.
3. The payload of claim 1 , wherein at least one of the at least two spacecraft is a dummy structure that simulates a real spacecraft, structurally supports another of the at least two spacecraft, and completes an interface with the launch vehicle for launch.
4. The payload of claim 1 , wherein the at least two spacecraft are detachably secured relative to each other by the at least one holddown device, the at least one holddown device being configured to be released after launch.
5. The payload of claim 4 , wherein the at least one holddown device is detached only after performing at least one orbit raising maneuver with an onboard propulsion system of at least one of the at least two spacecraft.
6. The payload of claim 4 , wherein the at least one holddown device is detached only after performing at least one orbit raising maneuver with an onboard propulsion system of only one of the at least two spacecraft.
7. The payload of claim 1 , wherein:
at least one of the two spacecraft is configured to be deployed in an on-orbit configuration having an orbital plane, the spacecraft having a yaw axis within the orbital plane and directed from a spacecraft coordinate system origin toward nadir, a pitch axis orthogonal to the orbit plane and passing through the spacecraft coordinate system origin, and a roll axis orthogonal to the pitch axis and the yaw axis and passing through the spacecraft coordinate system origin;
the spacecraft includes a first panel and a third panel substantially disposed, in the on-orbit configuration, respectively, orthogonal to the pitch axis and facing toward opposite directions, each panel having a first width in a first direction parallel to the roll axis; and a second and a fourth panel substantially disposed, in the on-orbit configuration, respectively, orthogonal to the roll axis and having a second width in a second direction parallel to the pitch axis, wherein:
an aspect ratio of the first width to the second width is substantially greater than one.
8. The payload of claim 7 , wherein the aspect ratio is at least two.
9. The payload of claim 7 , wherein the facing non-abutting body surfaces of each spacecraft are generally orthogonal to the pitch axis.
10. The payload of claim 1 , wherein:
at least a portion of each spacecraft has a substantially ‘U’ shaped configuration, including a central recess, and two outboard segments;
at least one outboard segment of a first spacecraft is disposed, in the launch configuration, within the central recess of a second spacecraft.
11. An apparatus for launch by a launch vehicle, the apparatus comprising a first spacecraft and a second spacecraft, wherein:
the launch vehicle includes a payload adapter;
each of the first spacecraft and the second spacecraft has a launch vehicle adapter structure providing a respectively coplanar structural interface directly with the payload adapter; and
the first spacecraft is configured to share, substantially side-by-side with the second spacecraft, a launch vehicle payload fairing volume, and is detachably coupled with the second spacecraft by at least one holddown device extending from between facing non-abutting body surfaces of the first spacecraft and the second spacecraft such that a positive clearance is provided between the facing non-abutting body surfaces.
12. The apparatus of claim 11 , wherein the positive clearance defines a first volume within the launch vehicle payload fairing volume, and deployable appendages of one or both of the first spacecraft and the second spacecraft are disposed within the first volume during launch.
13. The apparatus of claim 11 , wherein at least one spacecraft adaptor has a plurality of reinforced points that to correspond to reinforced points in the launch vehicle interface adapter structure.
14. The apparatus of claim 11 , wherein:
at least one spacecraft of the first spacecraft and the second spacecraft is deployed in an on-orbit configuration having an orbital plane, the at least one spacecraft having a yaw axis within the orbital plane and directed from a spacecraft coordinate system origin toward nadir, a pitch axis orthogonal to the orbit plane and passing through the spacecraft coordinate system origin, and a roll axis orthogonal to the pitch axis and the yaw axis and passing through the spacecraft coordinate system origin;
the at least one spacecraft includes a first panel and a third panel substantially disposed, in the on-orbit configuration, respectively, orthogonal to the pitch axis and facing toward opposite directions, each panel having a first width in a first direction parallel to the roll axis; and a second and a fourth panel substantially disposed, in the on-orbit configuration, respectively, orthogonal to the roll axis and having a second width in a second direction parallel to the pitch axis, wherein:
an aspect ratio of the first width to the second width is substantially greater than one.
15. The apparatus of claim 14 , wherein the aspect ratio is at least two.
16. The apparatus of claim 14 , wherein the facing non-abutting body surfaces of each of the first spacecraft and the second spacecraft are generally orthogonal to the pitch axis.
17. The apparatus of claim 11 , wherein the at least one holddown device is configured to be released after launch.
18. The apparatus of claim 17 , wherein the at least one holddown device is detached only after performing one or more orbit raising maneuver with an onboard propulsion system of at least one of the two spacecraft.
19. The apparatus of claim 17 , wherein the at least one holddown device is detached only after performing an orbit raising maneuver with an onboard propulsion system of only one of the first spacecraft and the second spacecraft.
20. The apparatus of claim 11 , wherein:
at least a portion of each spacecraft has a substantially ‘U’ shaped configuration, including a central recess, and two outboard segments;
at least one outboard segment of a first spacecraft is disposed within the central recess of a second spacecraft.