Stackable satellite dispensing configuration

Patent metadata

Field	Value
Publication number	US-11577861-B1
Application number	US-202117410433-A
Country	US
Kind code	B1
Filing date	Aug 24, 2021
Priority date	Aug 24, 2021
Publication date	Feb 14, 2023
Grant date	Feb 14, 2023

Abstract

Technology is disclosed for a spacecraft launch restraint and dispensing structure. Stacks of spacecrafts may be arranged around a central post. The dispensing structure has primary tie-down mechanisms that axially clamp the stacks of spacecrafts when in a stowed position. Each primary tie-down mechanism may have a rod located between two adjacent stacks, such that the rod tensions two stacks. In a deployment position, the primary tie-down rods extend away from the stack such that an ejection path is cleared. The dispensing structure also includes secondary tie-down mechanisms that radially connect the spacecrafts to the central post. After the primary tie-down rods are moved to the deployment position, the secondary tie-down mechanisms still hold the spacecrafts. The spacecrafts may be deployed by issuing control signals to the secondary tie-down mechanisms when the primary tie-down rods are in the deployment position.

First claim

What is claimed is:

1. An apparatus comprising:
a central structure around which a plurality of stacks of spacecrafts are grouped, the central structure aligned with a central axis;
a plurality of primary tie-down mechanisms configured to axially tie-down the plurality of stacks of spacecrafts, each primary tie-down mechanism having a primary tie-down rod and a clamp, the primary tie-down rod that when in a first position extends from a top to a bottom of two adjacent stacks of the spacecrafts with the clamp extending over top surfaces of two adjacent spacecrafts at the top of the two adjacent stacks, wherein a pair of the primary tie-down mechanisms clamp a stack of the spacecrafts together axially, each primary tie-down rod when in a second position extends away from the two adjacent stacks to allow spacecrafts in the two adjacent stacks to be released radially from the central axis; and
a plurality of secondary tie-down mechanisms connected to the central structure, the plurality of secondary tie-down mechanisms comprising a plurality of secondary tie-down rods configured to hold the spacecrafts radially to the central structure both when the primary tie-down rods are in the first position and the second position.

2. The apparatus of claim 1 , wherein the secondary tie-down mechanisms are configured to release the secondary tie-down rods responsive to a control signal in order to radially release the spacecrafts when the primary tie-down rods are in the second position.

3. The apparatus of claim 1 , wherein each primary tie-down mechanism comprises a release mechanism configured to release a corresponding primary tie-down rod from the first position to the second position responsive to a control signal.

4. The apparatus of claim 1 , wherein the central structure comprises a structural post aligned with the central axis, wherein the plurality of secondary tie-down mechanisms are attached to the structural post.

5. The apparatus of claim 4 , wherein:
the structural post comprises a plurality of cups, each cup is configured to receive a cone of one of the spacecrafts to hold the respective spacecraft in place.

6. The apparatus of claim 1 , wherein the central structure comprises a non-structural post aligned with the central axis, wherein the plurality of secondary tie-down mechanisms are attached to the non-structural post.

7. The apparatus of claim 1 , further comprising a launch adaptor, wherein the plurality of primary tie-down mechanisms are configured to tie the spacecrafts to the launch adaptor, wherein the central structure is connected to the launch adaptor.

8. The apparatus of claim 1 , further comprising the plurality of stacks of spacecrafts, wherein each spacecraft comprises a first structural member and a second structural member, a first of the primary tie-down mechanisms when in the first position is configured to pre-tension the first and the second structural members of two stacks of the spacecrafts.

9. The apparatus of claim 1 , further comprising the plurality of stacks of spacecrafts, wherein:
the plurality of stacks of spacecrafts comprise a plurality of levels of spacecrafts;
each spacecraft comprises a rigid cone; and
one or more of the secondary tie-down rods connect rigid cones of the spacecrafts at each respective level of the stacks such that the spacecrafts at the respective level form a rigid structure, the rigid cones formed from a load bearing material.

10. The apparatus of claim 1 , wherein:
the plurality of stacks of spacecrafts comprise a plurality of levels of spacecrafts; and
a first of the plurality of secondary tie-down mechanisms further comprises one or more ejection springs connected to the central structure, the one or more ejection springs configured to radially eject two spacecrafts in different stacks, the two spacecrafts at the same level of the plurality of stacks of spacecrafts.

11. The apparatus of claim 10 , further comprising a controller configured to issue control signals to the plurality of secondary tie-down mechanisms to simultaneously eject the two spacecrafts at the same level of the plurality of stacks.

12. A method of dispensing spacecrafts, the method comprising:
releasing a plurality of primary tie-down rods from a first position to a second position after launch of a launch vehicle to clear an ejection path for spacecrafts of a plurality of stacks of spacecrafts to be ejected, wherein in the first position each primary tie-down rod extends from a top to a bottom of two adjacent stacks of the spacecrafts with a clamp extending over top surfaces of two adjacent spacecrafts at the top of the two adjacent stacks, wherein in the first position two of the primary tie-down rods clamp a stack together axially, wherein in the second position each primary tie-down rod extends away from the two adjacent stacks to allow spacecrafts in the two adjacent stacks to be released radially from a central axis; and
releasing each of a plurality of secondary tie-down rods in a release sequence when the primary tie-down rods are in the second position to dispense each of the spacecrafts radially from the central axis in accordance with the release sequence.

13. The method of claim 12 , wherein releasing each of the plurality of secondary tie-down rods in a release sequence when the primary tie-down rods are in the second position to dispense each of the spacecrafts radially from the central axis in accordance with the release sequence comprises:
actuating a secondary tie-down release mechanism to simultaneously eject two of the spacecraft from different stacks.

14. The method of claim 12 , further comprising:
issuing, by a controller, control signals to actuators connected to the plurality of secondary tie-down rods to instruct the respective actuators to simultaneously eject two of the spacecrafts from different stacks.

15. A satellite launch and dispensing system, the system comprising:
a launch vehicle adaptor configured to connect to a launch vehicle;
a central structure connected to the launch vehicle adaptor;
a plurality of stacks of satellites grouped around the central structure, the satellites arranged in a plurality of layers of multiple satellites;
a plurality of primary tie-down mechanisms each comprising a primary tie-down rod and a clamp, wherein each primary tie-down rod has a first position in which the primary tie-down rod extends from a top to a bottom of two adjacent stacks of the satellites with the clamp extending over top surfaces of two adjacent satellites at the top of the two adjacent stacks, in the first position the primary tie-down mechanism axially clamps the two stacks together and holds the two adjacent stacks to the launch vehicle adaptor, each primary tie-down rod having a second position in which the primary tie-down rod extends away from the two adjacent stacks to allow satellites in the two adjacent stacks to be released radially from the central structure; and
a plurality of secondary tie-down mechanisms connected to the central structure, wherein each secondary tie-down mechanism is configured to radially hold a respective satellite to the central structure when the primary tie-down rods associated with the respective satellite are in both the first position and in the second position.

16. The satellite launch and dispensing system of claim 15 , wherein:
each satellite comprises a first structural member and a second structural member, the first structural member configured to provide structural support to the satellite when a first of the primary tie-down rod is in the first position, the second structura

Assignees

• Maxar Space Llc

Inventors

• Baghdasarian Varouj

Classifications

• B64G1/10 Primary

  Artificial satellites; Systems of such satellites; Interplanetary vehicles (space shuttles B64G1/14) · CPC title

• B64G1/6457

  Springs; Shape memory actuators · CPC title

• B64G1/642

  Clamps, e.g. Marman clamps · CPC title

• B64G1/643 Primary

  for arranging multiple satellites in a single launcher · CPC title

• B64G1/645

  Separators · CPC title