Patents Assigned to Planetary Systems Corporation
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Patent number: 11572202Abstract: A system and method for installing, deploying, and recovering a plurality of spacecraft that provides an ease of use and structural stability, and facilitates a standardization of spacecraft design. In embodiments of this invention, threaded rods are arranged orthogonal to a surface of a baseplate, and each spacecraft includes a coupling mechanism that selectively engages or disengages each threaded rod. Each spacecraft is added to the stack by engaging its coupling mechanism and rotating the threaded rods while the preceding spacecraft on the stack disengage their coupling mechanisms, thereby enabling the spacecraft to travel along the threaded rods toward the baseplate. When all of the spacecraft are added to the stack, the stack is preloaded by rotating the treaded rods into a terminator component at the top of the stack while the coupling mechanisms in all of the spacecraft are disengaged. Spacecraft are deployed by reversing the process.Type: GrantFiled: December 21, 2021Date of Patent: February 7, 2023Assignee: Planetary Systems CorporationInventors: Walter Holemans, Ryan Williams
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Patent number: 11565833Abstract: After deploying its payload, the final stage of a launch vehicle is maneuvered to couple the nosecone of the launch vehicle to the ‘rear’, or ‘engine-end’ of the final stage. The nosecone covers the engine of the final stage, to protect the engine and related components from the heat of re-entry and the impact of landing. Placing the nosecone over the engine and orienting the combination such that the nosecone ‘leads’ the final stage during re-entry, places the center of gravity of the combination ahead of the center of pressure in the direction of travel. Accordingly, the combination is inherently stable as it re-enters the atmosphere and falls to earth. Parachutes and directional devices are used to provide a controlled soft landing.Type: GrantFiled: September 9, 2020Date of Patent: January 31, 2023Assignee: Planetary Systems CorporationInventors: Walter Holemans, Ryan Williams
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Publication number: 20220119135Abstract: A system and method for installing, deploying, and recovering a plurality of spacecraft that provides an ease of use and structural stability, and facilitates a standardization of spacecraft design. In embodiments of this invention, threaded rods are arranged orthogonal to a surface of a baseplate, and each spacecraft includes a coupling mechanism that selectively engages or disengages each threaded rod. Each spacecraft is added to the stack by engaging its coupling mechanism and rotating the threaded rods while the preceding spacecraft on the stack disengage their coupling mechanisms, thereby enabling the spacecraft to travel along the threaded rods toward the baseplate. When all the spacecraft are added to the stack, the stack is preloaded by rotating the treaded rods into a terminator component at the top of the stack while the coupling mechanisms in all of the spacecraft are disengaged. Spacecraft are deployed by reversing the process.Type: ApplicationFiled: December 21, 2021Publication date: April 21, 2022Applicant: Planetary Systems CorporationInventors: Walter HOLEMANS, Ryan Williams
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Publication number: 20220111980Abstract: A system and method for installing, deploying, and recovering a plurality of spacecraft that provides an ease of use and structural stability, and facilitates a standardization of spacecraft design. In embodiments of this invention, threaded rods are arranged orthogonal to a surface of a baseplate, and each spacecraft includes a coupling mechanism that selectively engages or disengages each threaded rod. Each spacecraft is added to the stack by engaging its coupling mechanism and rotating the threaded rods while the preceding spacecraft on the stack disengage their coupling mechanisms, thereby enabling the spacecraft to travel along the threaded rods toward the baseplate. When all of the spacecraft are added to the stack, the stack is preloaded by rotating the treaded rods into a terminator component at the top of the stack while the coupling mechanisms in all of the spacecraft are disengaged. Spacecraft are deployed by reversing the process.Type: ApplicationFiled: December 21, 2021Publication date: April 14, 2022Applicant: Planetary Systems CorporationInventors: Walter Holemans, Ryan Williams
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Patent number: 11267591Abstract: A system and method for installing, deploying, and recovering a plurality of spacecraft that provides an ease of use and structural stability, and facilitates a standardization of spacecraft design. In embodiments of this invention, threaded rods are arranged orthogonal to a surface of a baseplate, and each spacecraft includes a coupling mechanism that selectively engages or disengages each threaded rod. Each spacecraft is added to the stack by engaging its coupling mechanism and rotating the threaded rods while the preceding spacecraft on the stack disengage their coupling mechanisms, thereby enabling the spacecraft to travel along the threaded rods toward the baseplate. When all of the spacecraft are added to the stack, the stack is preloaded by rotating the treaded rods into a terminator component at the top of the stack while the coupling mechanisms in all of the spacecraft are disengaged. Spacecraft are deployed by reversing the process.Type: GrantFiled: July 15, 2019Date of Patent: March 8, 2022Assignee: Planetary Systems CorporationInventors: Walter Holemans, Ryan Williams
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Publication number: 20210070480Abstract: After deploying its payload, the final stage of a launch vehicle is maneuvered to couple the nosecone of the launch vehicle to the ‘rear’, or ‘engine-end’ of the final stage. The nosecone covers the engine of the final stage, to protect the engine and related components from the heat of re-entry and the impact of landing. Placing the nosecone over the engine and orienting the combination such that the nosecone ‘leads’ the final stage during re-entry, places the center of gravity of the combination ahead of the center of pressure in the direction of travel. Accordingly, the combination is inherently stable as it re-enters the atmosphere and falls to earth. Parachutes and directional devices are used to provide a controlled soft landing.Type: ApplicationFiled: September 9, 2020Publication date: March 11, 2021Applicant: Planetary Systems CorporationInventors: Walter HOLEMANS, Ryan Williams
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Patent number: 10703512Abstract: A spacecraft coupling system includes a locking component that can be deformed and placed into a stable state that locks one component into a mating component, and can easily be released from the deformed state, decoupling the two components. The locking component may include a central ring, a plurality of leaf elements arranged at the perimeter of the locking component, and a plurality of fins that extend outward from the ring to the plurality of leaf elements. A rotation of the ring element while the component is held stationary causes the fins to urge the leaf elements toward the receiving surface areas and to subsequently tension the leaf elements against surfaces on the mating component. To reduce cost and complexity, the locking component comprises a metal, such as titanium, that can be formed using an additive manufacturing process, commonly termed a 3-D printing process.Type: GrantFiled: June 16, 2017Date of Patent: July 7, 2020Assignee: Planetary Systems CorporationInventor: Walter Holemans
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Publication number: 20200017243Abstract: A system and method for installing, deploying, and recovering a plurality of spacecraft that provides an ease of use and structural stability, and facilitates a standardization of spacecraft design. In embodiments of this invention, threaded rods are arranged orthogonal to a surface of a baseplate, and each spacecraft includes a coupling mechanism that selectively engages or disengages each threaded rod. Each spacecraft is added to the stack by engaging its coupling mechanism and rotating the threaded rods while the preceding spacecraft on the stack disengage their coupling mechanisms, thereby enabling the spacecraft to travel along the threaded rods toward the baseplate. When all of the spacecraft are added to the stack, the stack is preloaded by rotating the treaded rods into a terminator component at the top of the stack while the coupling mechanisms in all of the spacecraft are disengaged. Spacecraft are deployed by reversing the process.Type: ApplicationFiled: July 15, 2019Publication date: January 16, 2020Applicant: Planetary Systems CorporationInventors: Walter HOLEMANS, Ryan Williams
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Publication number: 20170283097Abstract: A spacecraft coupling system includes a locking component that can be deformed and placed into a stable state that locks one component into a mating component, and can easily be released from the deformed state, decoupling the two components. The locking component may include a central ring, a plurality of leaf elements arranged at the perimeter of the locking component, and a plurality of fins that extend outward from the ring to the plurality of leaf elements. A rotation of the ring element while the component is held stationary causes the fins to urge the leaf elements toward the receiving surface areas and to subsequently tension the leaf elements against surfaces on the mating component. To reduce cost and complexity, the locking component comprises a metal, such as titanium, that can be formed using an additive manufacturing process, commonly termed a 3-D printing process.Type: ApplicationFiled: June 16, 2017Publication date: October 5, 2017Applicant: Planetary Systems CorporationInventor: Walter HOLEMANS
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Patent number: 9707748Abstract: A spacecraft coupling system includes an integral component that can be deformed and placed into a stable state that locks one component into a mating component, and can easily be released from the deformed state, decoupling the two components. The integral component may include a central ring, a plurality of leaf elements arranged at the perimeter of the component, and a plurality of fins that extend outward from the ring to the plurality of leaf elements. A rotation of the ring element while the component is held stationary causes the fins to urge the leaf elements toward the receiving surface areas and to subsequently force the leaf elements against surfaces on the mating component. To reduce cost and complexity, the integral component is a metal, such as titanium, that can be formed using an additive manufacturing process, commonly termed a 3-D printing process.Type: GrantFiled: October 3, 2014Date of Patent: July 18, 2017Assignee: Planetary Systems CorporationInventor: Walter Holemans
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Patent number: 9415883Abstract: A canisterized satellite dispenser includes one or more of: a pair of guide rails that eliminate the requirement of a rectangular profile for the satellite; a preload system that secures the canisterized satellite during transport and launch, and releases to deploy the canisterized satellite; a constant-force spring to provide a uniform and predictable dispensing force; an external rectangular profile in each dimension; and internal support surfaces that simplify the design of canisterized satellites, particularly those with deployable components. Each canisterized satellite includes a pair of opposing flanges on a lower portion of the satellite that ride in a channel formed by the dispenser's guide rails and restraining flanges; no other support constraints are imposed. During travel and launch, the satellite flanges are held against the restraining flanges, rigidly fixing the satellite to the dispenser until the satellite is deployed.Type: GrantFiled: November 21, 2013Date of Patent: August 16, 2016Assignee: Planetary Systems CorporationInventors: Walter Holemans, Ryan Hevner
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Publication number: 20150097085Abstract: A spacecraft coupling system includes an integral component that can be deformed and placed into a stable state that locks one component into a mating component, and can easily be released from the deformed state, decoupling the two components. The integral component may include a central ring, a plurality of leaf elements arranged at the perimeter of the component, and a plurality of fins that extend outward from the ring to the plurality of leaf elements. A rotation of the ring element while the component is held stationary causes the fins to urge the leaf elements toward the receiving surface areas and to subsequently tension the leaf elements against surfaces on the mating component. To reduce cost and complexity, the integral component is a metal, such as titanium, that can be formed using an additive manufacturing process, commonly termed a 3-D printing process.Type: ApplicationFiled: October 3, 2014Publication date: April 9, 2015Applicant: Planetary Systems CorporationInventor: Walter HOLEMANS
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Publication number: 20140319283Abstract: A canisterized satellite dispenser includes one or more of: a pair of guide rails that eliminate the requirement of a rectangular profile for the satellite; a preload system that secures the canisterized satellite during transport and launch, and releases to deploy the canisterized satellite; a constant-force spring to provide a uniform and predictable dispensing force; an external rectangular profile in each dimension; and internal support surfaces that simplify the design of canisterized satellites, particularly those with deployable components. Each canisterized satellite includes a pair of opposing flanges on a lower portion of the satellite that ride in a channel formed by the dispenser's guide rails and restraining flanges; no other support constraints are imposed. During travel and launch, the satellite flanges are held against the restraining flanges, rigidly fixing the satellite to the dispenser until the satellite is deployed.Type: ApplicationFiled: November 21, 2013Publication date: October 30, 2014Applicant: Planetary Systems CorporationInventors: Walter Holemans, Ryan Hevner
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Patent number: 7861976Abstract: Latching elements on a first structure are configured to securely engage corresponding bearings on a second structure, via a lateral member that drives all of the latching elements simultaneously. When engaged, or when disengaged, the system is in a stable state, requiring no active force by the controlling system to maintain the system in each state. Preferably, each latching element is coupled to the lateral member via a pinion that provides a mechanical advantage that substantially reduces the force required on the lateral member to effect the coupling or decoupling. Also preferably, the elements are formed from extruded aluminum forms, thereby providing for a relatively inexpensive and lightweight configuration that is particularly well suited for spacecraft applications.Type: GrantFiled: May 26, 2009Date of Patent: January 4, 2011Assignee: Planetary Systems CorporationInventor: Walter Holemans
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Patent number: 6390416Abstract: An easy to use, and reuse, separation connector is disclosed that comprises a first component having a plurality of leaf elements with protrusions, and a second component having a recess for receiving the leaf element protrusions. The protrusions of the leaf elements are secured within the recess by a tensioned band, or in an alternative embodiment, by an expansion band; the protrusions and recess are formed so as to provide an efficient and effective load and torque bearing surface that requires minimal tension on the tensioned band, or minimal compression on the expansion band. A shearing structure is also presented that minimizes translation of the leaf elements with respect to the receiving surface. When the band is released, springs or other means urge the leaves away from the mating surface, thereby allowing for the separation of the connected items. Preferably, the leaves are hinged, allowing for ease of coupling and decoupling to the mating surface.Type: GrantFiled: September 28, 2001Date of Patent: May 21, 2002Assignee: Planetary Systems CorporationInventor: Walter Holemans
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Publication number: 20020014558Abstract: An easy to use, and reuse, separation connector is disclosed that comprises a first component having a plurality of leaf elements with protrusions, and a second component having a recess for receiving the leaf element protrusions. The protrusions of the leaf elements are secured within the recess by a tensioned band, or in an alternative embodiment, by an expansion band; the protrusions and recess are formed so as to provide an efficient and effective load and torque bearing surface that requires minimal tension on the tensioned band, or minimal compression on the expansion band. A shearing structure is also presented that minimizes translation of the leaf elements with respect to the receiving surface. When the band is released, springs or other means urge the leaves away from the mating surface, thereby allowing for the separation of the connected items. Preferably, the leaves are hinged, allowing for ease of coupling and decoupling to the mating surface.Type: ApplicationFiled: September 28, 2001Publication date: February 7, 2002Applicant: Planetary Systems CorporationInventor: Walter Holemans
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Publication number: 20010017337Abstract: An easy to use, and reuse, separation connector is disclosed that comprises a first component having a plurality of leaf elements with protrusions, and a second component having a recess for receiving the leaf element protrusions. The protrusions of the leaf elements are secured within the recess by a tensioned band, or in an alternative embodiment, by an expansion band; the protrusions and recess are formed so as to provide an efficient and effective load and torque bearing surface that requires minimal tension on the tensioned band, or minimal compression on the expansion band. A shearing structure is also presented that minimizes translation of the leaf elements with respect to the receiving surface. When the band is released, springs or other means urge the leaves away from the mating surface, thereby allowing for the separation of the connected items. Preferably, the leaves are hinged, allowing for ease of coupling and decoupling to the mating surface.Type: ApplicationFiled: May 4, 2001Publication date: August 30, 2001Applicant: Planetary Systems CorporationInventor: Walter Holemans
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Patent number: 6227493Abstract: An easy to use, and reuse, separation connector is disclosed that comprises a first component having a plurality of leaf elements with protrusions, and a second component having a recess for receiving the leaf element protrusions. The protrusions of the leaf elements are secured within the recess by a tensioned band; the protrusions and recess are formed so as to provide an efficient and effective load and torque bearing surface that requires minimal tension on the tensioned band. In a preferred embodiment, the tensioned band is detensioned by a thermal device that melts the band. When the band is melted, springs or other devices urge the leaves away from the mating surface, thereby allowing for the separation of the connected items.Type: GrantFiled: April 6, 1999Date of Patent: May 8, 2001Assignee: Planetary Systems CorporationInventor: Walter Holemans