Truss structure

Patent metadata

Field	Value
Publication number	US-2016251093-A1
Application number	US-201615053998-A
Country	US
Kind code	A1
Filing date	Feb 25, 2016
Priority date	Feb 27, 2015
Publication date	Sep 1, 2016
Grant date	—

Abstract

A spacecraft includes a 3-D closed truss structure including at least four coupling nodes and at least six strut elements, attached together by a plurality of joints, each coupling node including at least two legs, each strut element disposed between and attached with a respective pair of the plurality of coupling nodes. Each coupling node is attached, at respective ones of the plurality of joints, with at least two strut elements. Each strut element is attached at a first end with a first leg of a first coupling node and is attached at a second end with a second leg of a second coupling node, the first leg being substantially longer than the second leg.

First claim

What is claimed is:

1 . A spacecraft comprising:
a 3-D closed truss structure including at least four coupling nodes and at least six strut elements, attached together by a plurality of joints, each coupling node including at least two legs, each strut element disposed between and attached with a respective pair of the plurality of coupling nodes; wherein
each coupling node is attached, at respective ones of the plurality of joints, with at least two strut elements; and
each strut element is attached at a first end with a first leg of a first coupling node and is attached at a second end with a second leg of a second coupling node, the first leg being substantially longer than the second leg.

2 . The spacecraft of claim 1 , wherein the truss structure is configured to be fabricated by:
forming a dry fit assembly of the plurality of coupling nodes and the plurality of strut elements, the dry fit assembly being self-supporting; aligning the dry fit assembly; and rigidizing each joint.

3 . The spacecraft of claim 2 , wherein the dry fit assembly includes one or more dry fitted joints configured to resist gravitational forces and incidental contact, and to yield to a persistently applied force in the range of about 5 - 30 pounds.

4 . The spacecraft of claim 2 , wherein rigidizing each joint includes affixing each joint with an adhesive.

5 . The spacecraft of claim 2 , wherein rigidizing each joint includes injecting an adhesive between mating surfaces of a respective coupling node and strut element and allowing the adhesive to cure.

6 . The structure of claim 2 , wherein, between the step of aligning the dry fit assembly and the step of rigidizing each joint, disassembly of any joint is avoided.

7 . The spacecraft of claim 1 , wherein at least one of the plurality of strut elements is a thin-walled structural member fabricated from a carbon composite material.

8 . The spacecraft of claim 1 , wherein at least one of the plurality of coupling nodes is produced using an additive manufacturing method.

9 . The spacecraft of claim 1 , wherein each joint includes one or both of an O-ring and an elastomeric insert.

10 . The spacecraft of claim 1 , wherein each joint includes a coupling node, a strut element and at least one O-ring, and the strut element has a sliding fit with respect to the respective coupling node and the least one O-ring.

11 . The spacecraft of claim 1 , wherein each joint includes a coupling node, a strut element and at least one elastomeric insert, the elastic insert including a compliant seal having an outer edge surface configured to engage with an internal mating surface of a strut element.

12 . The spacecraft of claim 11 , wherein each joint includes an external seal disposed proximate to an end facing surface of the strut element.

13 . The spacecraft of claim 1 , wherein an outer diameter of a leg of at least one coupling node is less than an inner diameter of a mating strut element.

14 . The spacecraft of claim 1 , wherein the truss structure:
includes at least ten coupling nodes; is at least 100 ft. 3 in volume; has a stiffness corresponding to a first resonance frequency of 20 Hz or higher; and has an alignment accuracy of better than 0.01 inches or 0.05 degrees.

15 . A structure comprising:
a plurality of coupling nodes; and a plurality of strut elements, each strut element disposed between and attached with a respective pair of the plurality of coupling nodes; wherein
the structure is a 3-D closed truss structure including at least four coupling nodes and at least six strut elements connected at a plurality of joints, wherein each coupling node is attached with at least two strut elements, the structure being configured to be fabricated by:
forming a dry fit assembly of the plurality of coupling nodes and the plurality of strut elements, the dry fit assembly being self-supporting;
aligning the dry fit assembly; and
rigidizing each joint.

16 . The structure of claim 15 , wherein rigidizing each joint includes affixing each joint with an adhesive.

17 . The structure of claim 15 , wherein, between the step of aligning the dry fit assembly and the step of rigidizing each joint, disassembly of any joint is avoided.

18 . The structure of claim 15 , wherein each strut element is attached at a first end with a first leg of a first coupling node and is attached at a second end with a second leg of a second coupling node, each coupling node including a plurality of legs, and the first leg being substantially longer than the second leg.

19 . A method for fabricating a structure, the method comprising:
forming a dry fit assembly of a 3-D closed truss structure including at least four coupling nodes and at least six strut elements connected at a plurality of joints, each coupling node being attached with at least two strut elements, each strut element disposed between and attached with a respective pair of the plurality of coupling nodes, the dry fit assembly being self-supporting; aligning the dry fit assembly; and rigidizing each joint.

20 . The method of claim 19 , wherein each strut element is attached at a first end with a first leg of a first coupling node and is attached at a second end with a second leg of a second coupling node, the first leg being substantially longer than the second leg.

Assignees

• Space Systems/Loral LLC

Inventors

• Hijmans Carey Graham
• Freestone Michael Paul

Classifications

• G06F30/23

  using finite element methods [FEM] or finite difference methods [FDM] · CPC title

• F16B11/008

  of tubular elements or rods in coaxial engagement · CPC title

• F16B7/185

  with a node element · CPC title

• F16B7/00

  Connections of rods or tubes, e.g. of non-circular section, mutually, including resilient connections ({F16B11/008, F16B17/00 take precedence;} umbrella frames A45B25/02; welding or soldering of connections B23K; vehicle connections in general B60D; railway couplings B61G; bicycle frames B62K; couplings for transmitting rotation F16D; couplings for tubes conveying fluids F16L) · CPC title

• B64G1/10 Primary

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