# US 8,146,867 B2 · Modular spacecraft design architecture

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- Number: US 8,146,867 B2
- Document ID: US8146867B2
- Status: Granted
- Kind: B2
- Application number: 11/151,906
- Filed: 2005-06-14
- Published: 2006-01-26
- Granted: 2012-04-03
- Earliest claimed: 2004-06-14
- Assignees: AeroAstro, Inc.
- Inventors: Luis G. Jordan; Thomas W. Vaneck; Scott A. McDermott; Jonathon Miller; Simon Morris Shand Weiss; Robert A. Summers
- Web page: https://patentgrep.com/patent/US8146867B2

## CPC

- B64G 1/10: Artificial satellites; Systems of such satellites; Interplanetary vehicles (space shuttles B64G1/14)
- B64G 1/428: {Power distribution and management}
- B64G 1/223: {Modular spacecraft systems}
- B64G: COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR

## Abstract

A spacecraft architecture and accompanying standard allows for the creation of a spacecraft using an assortment of modules that comply with the standard. The standard preferably includes both mechanical and electrical compatibility criteria. To assure physical/mechanical compatibility, the structure of each module is constrained to be compatible with any other compatible module. To minimize the interference among modules, the extent of each module in select dimensions is also constrained. To assure functional compatibility, a common communication format is used to interface with each module, and each public-function module is configured to respond to requests for function capabilities that it can provide to other functions. Each module is preferably designed to provide structural support to the assemblage of modules, and an anchor module is provided or defined for supporting the entire assemblage and coupling the assemblage to other structures, such as a launch vehicle.

## Claims

### Claim 1

A spacecraft system comprising a stack of modules, the stack of modules including:
an anchor module,
an upper module, and
a plurality of intermediate modules arranged between the anchor module and the upper module,
wherein:
each intermediate module of the plurality of intermediate modules provide a common mechanical interface and a common electrical interface, such that a coupling of each intermediate module to its adjacent modules provides a structural integrity and an electronic integrity that extends across an entirety of the stack of modules, and
each intermediate module is configured to be substantially thermally isolated from other modules on the stack.

### Claim 2 (depends on 1)

The spacecraft system of claim 1, wherein the structural integrity and electronic integrity is substantially unaffected by an order of arrangement of the intermediate modules between the anchor module and the upper module.

### Claim 3 (depends on 1)

The spacecraft system of claim 1, wherein the electronic interface is further structured such that power distribution among the plurality of intermediate modules is unaffected by an order of arrangement of the intermediate modules between the anchor module and the upper module.

### Claim 4 (depends on 1)

The spacecraft system of claim 1, wherein the intermediate modules provide a plurality of functional capabilities, and
the plurality of functional capabilities are substantially unaffected by an order of arrangement of the intermediate modules.

### Claim 5 (depends on 1)

The spacecraft system of claim 1, wherein the intermediate modules include a power supply module that is configured to provide power to each of the other intermediate modules via the coupling of the electrical interface between adjacent intermediate modules.

### Claim 6 (depends on 5)

The spacecraft system of claim 5, wherein the anchor module includes one or more solar panels, operably coupled to the power supply module to provide power to the power supply module.

### Claim 7 (depends on 1)

The spacecraft system of claim 1, wherein:
each intermediate module is generally structured as a polygon, and
each intermediate module includes corner posts at each vertex that are configured to be coupled to an adjacent module on the stack of modules, to provide a primary load path between the upper module and the anchor module.

### Claim 8 (depends on 1)

The spacecraft system of claim 1, wherein:
each intermediate module is generally structured as a polygon, and
one or more walls of the polygon includes ribs that provide structural support.

### Claim 9 (depends on 8)

The spacecraft system of claim 8, wherein the ribs also facilitate thermal transfer.

### Claim 10 (depends on 1)

The spacecraft system of claim 1, wherein:
each intermediate module is generally structured as a polygon,
one or more walls of the polygon are structured to facilitate thermal transfer, and
a height of at least one of the intermediate modules is determined based on the thermal transfer provided by the one or more walls of the polygon.

### Claim 11 (depends on 1)

The spacecraft system of claim 1, wherein each intermediate module is generally structured as a hexagon.

### Claim 12 (depends on 1)

The spacecraft system of claim 1, wherein protrusions from each module, in a launch position, are constrained to within a height of the module.

### Claim 13 (depends on 1)

The spacecraft system of claim 1, wherein the electrical interface of the intermediate modules includes a plug and a socket for coupling to a corresponding socket and plug on adjacent modules on the stack.

### Claim 14 (depends on 13)

The spacecraft system of claim 13, wherein at least one of the plug and socket are mounted on each intermediate module using pliant couplings to facilitate the coupling to the corresponding socket and plug.

### Claim 15 (depends on 1)

The spacecraft system of claim 1, wherein the anchor module includes a coupling device that facilitates coupling the spacecraft system to a launch vehicle.

### Claim 16 (depends on 15)

The spacecraft system of claim 15, wherein the upper module provides a support base for one or more payload components.

### Claim 17 (depends on 1)

The spacecraft system of claim 1, wherein the stack of modules includes:
a communications module,
an attitude determination module,
an attitude control module,
a power supply module, and
a solar panel module.

### Claim 18 (depends on 1)

The spacecraft system of claim 1, further including an exoskeleton that is configured to absorb launch loads and configured to be separable from the stack of modules after launch.

### Claim 19 (depends on 18)

The spacecraft system of claim 18, wherein the exoskeleton is configured to couple to the stack of modules via columns that provide radially-inward forces to at least two modules of the stack of modules.

### Claim 20 (depends on 18)

The spacecraft system of claim 18, wherein the exoskeleton is configured to couple to the stack of modules via wedge clamps.

### Claim 21 (depends on 20)

The spacecraft system of claim 20, wherein each module of the stack of modules is configured to include recesses that are configured to receive the wedge clamps.

### Claim 22 (depends on 1)

The spacecraft system of claim 1, wherein the electrical interface includes an 12C data bus with an inverse channel.

### Claim 23 (depends on 1)

The spacecraft system of claim 1, wherein each intermediate module includes a current sensor that is configured to decouple the module from the electrical interface if current above a threshold value is detected.

### Claim 24 (depends on 1)

The spacecraft system of claim 1, wherein each intermediate module is configured to respond to a request for services from any other module.

### Claim 25 (depends on 1)

The spacecraft system of claim 1, wherein the anchor module includes one or more line-termination components operably coupled to the common electrical interface.

### Claim 26 (depends on 1)

The spacecraft system of claim 1, wherein the anchor module includes one or more solar panels.

### Claim 27 (depends on 26)

The spacecraft system of claim 26, wherein the one or more solar panels are configured to be contained substantially within the anchor module.

### Claim 28 (depends on 27)

The spacecraft system of claim 27, wherein the anchor module includes one or more lateral deployment mechanisms that are configured to deploy the one or more solar panels after launch.

### Claim 29 (depends on 28)

The spacecraft system of claim 28, wherein the one or more deployment mechanisms are further configured to control an orientation of the one or more solar panels after the one or more solar panels are deployed.

### Claim 30 (depends on 26)

The spacecraft system of claim 26, wherein the anchor module includes one or more batteries operably coupled to the solar panels and to the common electrical interface.

### Claim 31 (depends on 26)

The spacecraft system of claim 26, wherein the anchor module includes a voltage regulator that receives power from the one or more solar panels and provides at least one regulated supply voltage to the common electrical interface.

### Claim 32 (depends on 1)

The spacecraft system of claim 1, wherein the anchor module includes one or more antennas.

### Claim 33 (depends on 1)

The spacecraft system of claim 1, wherein each intermediate module is configured to provide a thermal integrity that is independent of an order of arrangement of the modules on the stack.

### Claim 34 (depends on 1)

The spacecraft system of claim 1, wherein each intermediate module is configured to provide an electrically conductive path between surfaces of adjacent modules, so as to maintain a substantially uniform potential across and among all surfaces of the stack of modules.

### Claim 35

A spacecraft system comprising a stack of modules, the stack of modules including:
an anchor module,
an upper module, and
a plurality of intermediate modules arranged between the anchor module and the upper module,
wherein:
each intermediate module of the plurality of intermediate modules provide a common mechanical interface and a common electrical interface, such that a coupling of each intermediate module to its adjacent modules provides a structural integrity and an electronic integrity that extends across an entirety of the stack of modules,
each intermediate module is generally structured as a polygon, with a plurality of tabs and a plurality of recesses on a periphery of the polygon, and
the plurality of tabs are configured to couple to corresponding plurality of recesses in an adjacent module on the stack of modules.

### Claim 36

A spacecraft system comprising a stack of modules, the stack of modules including:
an anchor module,
an upper module, and
a plurality of intermediate modules arranged between the anchor module and the upper module,
wherein:
each intermediate module of the plurality of intermediate modules provide a common mechanical interface and a common electrical interface, such that a coupling of each intermediate module to its adjacent modules provides a structural integrity and an electronic integrity that extends across an entirety of the stack of modules, and
each intermediate module includes one or more elements that facilitate a determination of the intermediate module's relative location on the stack of modules.

### Claim 37

1 A spacecraft system comprising a stack of modules, the stack of modules including:
an anchor module,
an upper module, and
a plurality of intermediate modules arranged between the anchor module and the upper module,
wherein:
each intermediate module of the plurality of intermediate modules provide a common mechanical interface and a common electrical interface, such that a coupling of each intermediate module to its adjacent modules provides a structural integrity and an electronic integrity that extends across an entirety of the stack of modules, and
each intermediate module includes one or more elements that facilitate a determination of the intermediate module's relative orientation within the stack of modules.

### Claim 38

A spacecraft system comprising a stack of modules, the stack of modules including:
an anchor module,
an upper module, and
a plurality of intermediate modules arranged between the anchor module and the upper module,
wherein
each module of the plurality of intermediate modules:
has a common cross-section profile that is substantially hexagonal in form, and
provides a common mechanical interface, such that a coupling of each intermediate module to its adjacent modules provides a structural integrity that extends across an entirety of the stack of modules.

### Claim 39 (depends on 38)

The spacecraft system of claim 38, wherein the structural integrity is substantially unaffected by an order of arrangement of the intermediate modules between the anchor module and the upper module.

### Claim 40 (depends on 38)

The spacecraft system of claim 38, including an electronic interface that provides power distribution among the plurality of intermediate modules and is unaffected by an order of arrangement of the intermediate modules between the anchor module and the upper module.

### Claim 41 (depends on 40)

The spacecraft system of claim 40, wherein the anchor module includes one or more solar panels that provide power to the plurality of intermediate modules.

### Claim 42 (depends on 41)

The spacecraft system of claim 41, wherein each intermediate module includes a plurality of tabs and a plurality of recesses on a periphery of the module, and the plurality of tabs are configured to couple to corresponding plurality of recesses in an adjacent module on the stack of modules.

### Claim 43 (depends on 38)

The spacecraft system of claim 38, wherein each intermediate module includes corner posts at each vertex of the module that are configured to be coupled to an adjacent module on the stack of modules, to provide a primary load path between the upper module and the anchor module.

### Claim 44 (depends on 38)

The spacecraft system of claim 38, wherein:
one or more walls of each intermediate module are structured to facilitate thermal transfer, and
a height of at least one of the intermediate modules is determined based on the thermal transfer provided by the one or more walls.

### Claim 45 (depends on 44)

The spacecraft system of claim 44, wherein the one or more walls are structured to provide low-impedance electrical conductivity to walls of adjacent modules in the stack.

### Claim 46 (depends on 45)

The spacecraft system of claim 45, wherein the one or more walls are structured to provide thermal isolation from adjacent modules in the stack.

### Claim 47 (depends on 38)

The spacecraft system of claim 38, wherein each intermediate module includes a plug and a socket for coupling to a corresponding socket and plug on adjacent modules on the stack of modules.

### Claim 48 (depends on 38)

The spacecraft system of claim 38, wherein the anchor module includes a coupling device that facilitates coupling the spacecraft system to a launch vehicle.

### Claim 49 (depends on 38)

The spacecraft system of claim 38, wherein the upper module provides a support base for one or more payload components.

### Claim 50 (depends on 38)

The spacecraft system of claim 38, further including an exoskeleton that is configured to absorb launch loads and configured to be separable from the stack of modules after launch.

### Claim 51 (depends on 50)

The spacecraft system of claim 50, wherein the exoskeleton is configured to couple to the stack of modules via columns that provide radially-inward forces to at least two modules of the stack of modules.

### Claim 52 (depends on 50)

The spacecraft system of claim 50, wherein the exoskeleton is configured to couple to the stack of modules via wedge clamps.

### Claim 53 (depends on 52)

The spacecraft system of claim 52, wherein each module of the stack of modules is configured to include recesses that are configured to receive the wedge clamps.

### Claim 54 (depends on 38)

The spacecraft system of claim 38, wherein each intermediate module includes a locator component that facilitates a determination of the intermediate module's relative location on the stack of modules.

### Claim 55 (depends on 38)

The spacecraft system of claim 38, wherein the anchor module includes one or more line-termination components operably coupled to a common electrical interface.

### Claim 56 (depends on 38)

The spacecraft system of claim 38, wherein the anchor module includes one or more antennas.

### Claim 57

A spacecraft module that includes:
a function component,
an electrical interface to the function component, and
a mechanical interface,
wherein:
the mechanical interface is configured to couple the spacecraft module in series between a pair of adjacent modules, independent of a function of each of the adjacent module, and to provide a structural integrity to the pair of adjacent modules and the spacecraft module,
the electrical interface is configured to couple each of the pair of adjacent modules to the function component and to each other, and
the module is configured to be substantially thermally isolated from the adjacent modules.

### Claim 58 (depends on 57)

The spacecraft module of claim 57, wherein the spacecraft module has a profile that is substantially similar to a profile of each of the adjacent modules.

### Claim 59 (depends on 58)

The spacecraft module of claim 58, wherein the profile is substantially hexagonal.

### Claim 60 (depends on 57)

The spacecraft module of claim 57, wherein the mechanical interface includes posts at each vertex of the spacecraft module that serves to couple the spacecraft module in series between the pair of adjacent modules.

### Claim 61 (depends on 60)

The spacecraft module of claim 60, wherein the spacecraft module includes a recess at each vertex that is configured to facilitate coupling of the module to an exoskeleton.

### Claim 62 (depends on 57)

The spacecraft module of claim 57, further including one or more elements that facilitate a determination of a location of the module relative to the adjacent modules.

### Claim 63 (depends on 57)

The spacecraft module of claim 57, further including one or more elements that facilitate a determination of an orientation of the module relative to the adjacent modules.

### Claim 64 (depends on 57)

The spacecraft module of claim 57, wherein the mechanical interface includes a plurality of sidewalls.

### Claim 65 (depends on 64)

The spacecraft module of claim 64, further including a plurality of sidewalls that facilitate thermal transfer, and wherein a height of the module is dependent upon an amount of thermal transfer provided by the plurality of sidewalls.

### Claim 66 (depends on 57)

The spacecraft module of claim 57, wherein the module is configured to provide thermal control of the function component.

### Claim 67 (depends on 57)

The spacecraft module of claim 57, further including a plurality of sidewalls, each sidewall of the plurality of sidewalls being configured to include at least one element that facilitates electrical contact with at least one of the adjacent modules.

### Claim 68 (depends on 67)

The spacecraft module of claim 67, wherein the electrical contact is provided via thin strands of conductive material.

### Claim 69 (depends on 67)

The spacecraft module of claim 67, wherein the electrical contact is provided via a coil of conductive material arranged between the at least one element of the sidewall and a baseplate of one of the adjacent modules.

### Claim 70 (depends on 67)

The spacecraft module of claim 67, wherein the at least one element that facilitates electrical contact is coated with electrically conductive material that is resistant to abrasion.

### Claim 71 (depends on 70)

The spacecraft module of claim 70, wherein the at least one element includes nickel plating.

### Claim 72 (depends on 67)

The spacecraft module of claim 67, further including a baseplate that is configured to include at least one element that facilitates electrical contact with at least one of the adjacent modules.

### Claim 73 (depends on 72)

The spacecraft module of claim 72, wherein the electrical contact is provided via thin strands of conductive material arranged between the baseplate and one or more walls of one of the adjacent modules.

### Claim 74

A spacecraft module comprising:
a plurality of solar panels that are arranged:
to be stored substantially within an interior of the spacecraft module during a launch of the spacecraft module, and
to be deployed substantially exterior to the spacecraft module after the launch of the spacecraft module, and
a plurality of deployment mechanisms that are configured to extend the panels in the radial direction during deployment,
wherein:
the plurality of solar panels include substantially rigid panels that are configured to be extended in a radial direction from the interior of the spacecraft during deployment, and
the plurality of deployment mechanisms are also configured to provide control of an orientation of the plurality of panels after deployment.