EP0196793A1
Expired / Lapsed
EP
⏱️ 0.0 years remaining
Modular spacecraft system
Assignee: SPACE INDUSTRIES, INC.
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Filing: 1986-03-05
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Granted: —
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Expires: 2006-03-05
Abstract
Abstract A modular spacecraft system adapted for orbital flight is capable of expansion by the connection of at least two substantially identical spacecraft modules (20), each of which is capable of independent operation. Each spacecraft module comprises a spacecraft body (21), at least one solar array (44, 46;) extendible outwardly from the spacecraft body, and at least one structural interface means (36) for connecting one spacecraft module to another spacecraft module. Methods for deployment of a spacecraft system utilizing a reusable space vehicle are also disclosed.
Inventors
- 👤 Maxime A. Faget
- 👤 Caldwell C. Johnson
- 👤 David J. Bergeron Iii
Bibliographic Details
Application Number
—
Jurisdiction
EP
Data Source
google_patents
Last Synchronized
2026-11-02 02:53
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/22; B64G1/64; B64G1/641; B64G1/10; B64G1/12; B64G1/223; B64G1/002; B64G1/006; B64G1/14; B64G1/222; B64G1/2221; B64G1/2222; B64G1/2223; B64G1/42; B64G1/44; Y; Y10; Y10S; Y10S136/00; Y10S136/291; Y10S136/292
Claims Analysis
Total Claims: 19
Claim 1
Independent Claim
75 words
1 . A modular spacecraft system adapted for orbital flight, and capable of expansion by the connection of substantially identical spacecraft modules, which are capable of independent operation, wherein said modular spacecraft system comprises at least two spacecraft modules, each of said spacecraft modules comprising: a spacecraft body; at least one solar array extendible outwardly from the spacecraft body; and at least one structural interface means for connecting one spacecraft module to another spacecraft module.
Claim 2
Dependent Claim
75 words
1 . A modular spacecraft system adapted for orbital flight, and capable of expansion by the connection of substantially identical spacecraft modules, which are capable of independent operation, wherein said modular spacecraft system comprises at least two spacecraft modules, each of said spacecraft modules comprising: a spacecraft body; at least one solar array extendible outwardly from the spacecraft body; and at least one structural interface means for connecting one spacecraft module to another spacecraft module.
Claim 3
Dependent Claim
24 words
The modular spacecraft system of claim 1 wherein each spacecraft module comprises two solar arrays extendible outwardly from opposite sides of the spacecraft body.
Claim 4
Dependent Claim
42 words
The modular spacecraft system of claim 1 wherein each solar array includes articulation means to permit the solar array to rotate to a position in which it does not mechanically interfere with or occlude the solar array on an adjacent spacecraft module.
Claim 5
Dependent Claim
30 words
The modular spacecraft system of claim 1 wherein at least one spacecraft module further comprises a gravity gradient stabilization means which is extendible and retractable relative to the spacecraft body.
Claim 6
Dependent Claim
30 words
The modular spacecraft system of claim 4 wherein the gravity gradient stabilization means further comprises an articulation means for adjusting the angle at which it extends from the spacecraft body.
Claim 7
Dependent Claim
91 words
The modular spacecraft system of claim 4 wherein each spacecraft body has three orthogonal axes, the solar array is extendible outwardly from a point on the spacecraft body which is generally along an axis parallel to one of the orthogonal axes, the gravity gradient stabilization means is extendible and retractable relative to the spacecraft body generally along an axis parallel to a second of the orthogonal axes, and the structural interface means is located on a side of the spacecraft in a position normal to the third of the orthogonal axes.
Claim 8
Dependent Claim
36 words
7 . The modular spacecraft system of claim 6 wherein the solar array comprises articulation means to permit the solar array to rotate about an axis parallel to the second orthogonal axis of the spacecraft body.
Claim 9
Dependent Claim
34 words
The modular spacecraft system of claim 7 wherein the spacecraft body has a generally cylindrical shape and the articulation means permits rotation about an axis parallel to the longitudinal axis of the spacecraft body.
Claim 10
Dependent Claim
95 words
9 . A spacecraft module adapted for orbital flight and connectable to a substantially identical spacecraft module, said spacecraft module comprising: a spacecraft body having a generally cylindrical shape; at least one solar array extendible outwardly from the spacecraft body, wherein said solar array comprises an articulation means to permit the solar array to rotate about an axis parallel to the longitudinal axis of the spacecraft body; and at least one structural interface means for connecting one spacecraft module to another spacecraft module so that the longitudinal axes of their respective spacecraft bodies are parallel.
Claim 11
Dependent Claim
95 words
9 . A spacecraft module adapted for orbital flight and connectable to a substantially identical spacecraft module, said spacecraft module comprising: a spacecraft body having a generally cylindrical shape; at least one solar array extendible outwardly from the spacecraft body, wherein said solar array comprises an articulation means to permit the solar array to rotate about an axis parallel to the longitudinal axis of the spacecraft body; and at least one structural interface means for connecting one spacecraft module to another spacecraft module so that the longitudinal axes of their respective spacecraft bodies are parallel.
Claim 12
Dependent Claim
26 words
The spacecraft module of claim 9, further comprising a gravity gradient stabilization means which is extendible and retractable relative to one end of the spacecraft body.
Claim 13
Dependent Claim
52 words
The spacecraft module of claim 10 wherein the spacecraft body further comprises an inner chamber having a generally cylindrical shape which is located within the spacecraft body in a position such that the longitudinal axis of the inner chamber is parallel to and displaced from the longitudinal axis of the spacecraft body.
Claim 14
Independent Claim
212 words
A method for deployment of a spacecraft module from a reusable space vehicle comprising a cargo bay, a berthing adapter facing outwardly from within the cargo bay and haying a structural interface means attached to its outer end, and a remote manipulator arm, said method comprising: (a) placing at least two connectable elements of a spacecraft module in the cargo bay, a first of said elements comprising a structural interface means for connection to the structural interface means of the berthing adapter; (b) transporting the spacecraft module elements to a desired orbital position; (c) using the remote manipulator arm to remove the first module element from the cargo bay and place the first module element on the berthing adapter so that the structural interface means of the first module element connects to the structural interface means of the berthing adapter; (d) using the remote manipulator arm to remove a second module element from the cargo bay and attach the second module element to the first module element; (e) repeating step (d) until all of the module elements are removed from the cargo bay and assembled to form the spacecraft module; (f) disconnecting the spacecraft module from the berthing adapter and releasing the spacecraft module into orbital flight using the remote manipulator arm.
Claim 15
Independent Claim
212 words
A method for deployment of a spacecraft module from a reusable space vehicle comprising a cargo bay, a berthing adapter facing outwardly from within the cargo bay and haying a structural interface means attached to its outer end, and a remote manipulator arm, said method comprising: (a) placing at least two connectable elements of a spacecraft module in the cargo bay, a first of said elements comprising a structural interface means for connection to the structural interface means of the berthing adapter; (b) transporting the spacecraft module elements to a desired orbital position; (c) using the remote manipulator arm to remove the first module element from the cargo bay and place the first module element on the berthing adapter so that the structural interface means of the first module element connects to the structural interface means of the berthing adapter; (d) using the remote manipulator arm to remove a second module element from the cargo bay and attach the second module element to the first module element; (e) repeating step (d) until all of the module elements are removed from the cargo bay and assembled to form the spacecraft module; (f) disconnecting the spacecraft module from the berthing adapter and releasing the spacecraft module into orbital flight using the remote manipulator arm.
Claim 16
Independent Claim
253 words
A method for assembly of a modular spacecraft system utilizing a reusable space vehicle comprising a cargo bay, a berthing adapter facing outwardly from within the cargo bay and having a structural interface means attached to its outer end, and a remote manipulator arm, said method comprising: (a) placing a first spacecraft module in the cargo bay, said first spacecraft module comprising a structural interface means for connecting the first spacecraft module to a second spacecraft module; (b) transporting the first spacecraft module to a desired orbital position with respect to a second spacecraft module already in orbital flight, said second spacecraft module comprising at least two structural interface means, one for connection to the structural interface means of the berthing adapter and another for connection to the structural interface means of the first spacecraft module; (c) using the remote manipulator arm to capture the second spacecraft module and place the second spacecraft module on the berthing adapter so that the structural interface means of the second spacecraft module connects to the structural interface means of the berthing adapter; (d) using the remote manipulator arm to remove the first spacecraft module from the cargo bay and attach the first spacecraft module to the. second spacecraft module by connecting the structural interface means of the first spacecraft module to the structural interface means of the second spacecraft module to form a modular spacecraft system; (e) disconnecting the modular spacecraft system from the berthing adapter; and (f) releasing the modular spacecraft system into orbital flight.
Claim 17
Independent Claim
253 words
A method for assembly of a modular spacecraft system utilizing a reusable space vehicle comprising a cargo bay, a berthing adapter facing outwardly from within the cargo bay and having a structural interface means attached to its outer end, and a remote manipulator arm, said method comprising: (a) placing a first spacecraft module in the cargo bay, said first spacecraft module comprising a structural interface means for connecting the first spacecraft module to a second spacecraft module; (b) transporting the first spacecraft module to a desired orbital position with respect to a second spacecraft module already in orbital flight, said second spacecraft module comprising at least two structural interface means, one for connection to the structural interface means of the berthing adapter and another for connection to the structural interface means of the first spacecraft module; (c) using the remote manipulator arm to capture the second spacecraft module and place the second spacecraft module on the berthing adapter so that the structural interface means of the second spacecraft module connects to the structural interface means of the berthing adapter; (d) using the remote manipulator arm to remove the first spacecraft module from the cargo bay and attach the first spacecraft module to the. second spacecraft module by connecting the structural interface means of the first spacecraft module to the structural interface means of the second spacecraft module to form a modular spacecraft system; (e) disconnecting the modular spacecraft system from the berthing adapter; and (f) releasing the modular spacecraft system into orbital flight.
Claim 18
Independent Claim
319 words
A method for assembly of a modular spacecraft system utilizing a reusable space vehicle comprising a cargo bay, a berthing adapter facing outwardly from within the cargo bay and having a structural interface means attached to its outer end, and a remote manipulator arm, said method comprising: (a) placing at least two connectable elements of a first spacecraft module in the cargo bay, a first of said elements comprising a structural interface means for connecting the first spacecraft module to a second spacecraft module; (b) transporting the first spacecraft module elements to a desired orbital position with respect to a second spacecraft module in orbital flight; said second spacecraft module comprising at least two structural interface means, one for connection to the structural interface means of the berthing adapter and another for connection to the structural interface means of the first spacecraft module; (c) using the remote manipulator arm to capture the second spacecraft module and place the second spacecraft module on the berthing adapter so that the structural interface means of the second spacecraft module connects to the structural interface means of the berthing adapter; (d) using the remote manipulator arm to remove the first module element from the cargo bay and attach the first module element to the second spacecraft module by connecting the structural interface means of the first module element to the structural interface means of the second spacecraft module; (e) using the remote manipulator arm to remove a second module element from the cargo bay and attach the second module element to the first module element; (f) repeating step (e) until all of the module elements are removed from the cargo bay and assembled to form the first spacecraft module which is connected to the second spacecraft module to form the modular spacecraft system; (g) disconnecting the modular spacecraft system from the berthing adapter; and (h) releasing the modular spacecraft system into orbital flight.
Claim 19
Independent Claim
319 words
A method for assembly of a modular spacecraft system utilizing a reusable space vehicle comprising a cargo bay, a berthing adapter facing outwardly from within the cargo bay and having a structural interface means attached to its outer end, and a remote manipulator arm, said method comprising: (a) placing at least two connectable elements of a first spacecraft module in the cargo bay, a first of said elements comprising a structural interface means for connecting the first spacecraft module to a second spacecraft module; (b) transporting the first spacecraft module elements to a desired orbital position with respect to a second spacecraft module in orbital flight; said second spacecraft module comprising at least two structural interface means, one for connection to the structural interface means of the berthing adapter and another for connection to the structural interface means of the first spacecraft module; (c) using the remote manipulator arm to capture the second spacecraft module and place the second spacecraft module on the berthing adapter so that the structural interface means of the second spacecraft module connects to the structural interface means of the berthing adapter; (d) using the remote manipulator arm to remove the first module element from the cargo bay and attach the first module element to the second spacecraft module by connecting the structural interface means of the first module element to the structural interface means of the second spacecraft module; (e) using the remote manipulator arm to remove a second module element from the cargo bay and attach the second module element to the first module element; (f) repeating step (e) until all of the module elements are removed from the cargo bay and assembled to form the first spacecraft module which is connected to the second spacecraft module to form the modular spacecraft system; (g) disconnecting the modular spacecraft system from the berthing adapter; and (h) releasing the modular spacecraft system into orbital flight.
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