Planetary Systems Corporation

Other

Marine Robotics, LLC

Cta Space Systems, Inc.

Experimental Propulsion Lab, LLC

Autonomous Marine Systems, Inc.

Walter Holemans

Ryan Adam Williams

Vincent Vandyck

Matthew Dushku

Ryan Hevner

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.

System and method for efficient deployment and retrieval of space vehicles

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.

System and method to attach and remove space vehicles

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 &#x2018;leads&#x2019; 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.

Recovery of a final stage of a spacecraft launch vehicle

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.

Printed spacecraft separation system

A substantially hollow wingsail is configured to enable electrical components to be situated within the wingsail. In particular, the wingsail may be configured to contain the solar panels used to power the other electrical components of the vessel, as well as other items that are conventionally situated on the exterior of the vessel, such as antennas, navigation lights, and so on. The interior of the wingsail may also include a deployment device for deploying components stored in the wingsail into the sea or the atmosphere. The surface of the wingsail may include transparent or translucent areas to provide light to the solar panels, as well as optical and electromagnetic reflective areas within the wingsail to enhance the performance of the solar panels and antennas. The wingsail may also include an internal light that illuminates the translucent areas of the wingsail for enhanced visibility to other vessels.

Housing electrical components in a wingsail

A substantially hollow wingsail is configured to enable electrical components to be situated within the wingsail. In particular, the wingsail may be configured to contain the solar panels used to power the other electrical components of the vessel, as well as other items that are conventionally situated on the exterior of the vessel, such as antennas, navigation lights, and so on. The surface of the wingsail may include transparent or translucent areas to provide light to the solar panels, as well as optical and electromagnetic reflective areas within the wingsail to enhance the performance of the solar panels and antennas. The wingsail may also include an internal light that illuminates the translucent areas of the wingsail for enhanced visibility to other vessels.

Housing electrical components in a translucent wingsail

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.

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.

Canisterized satellite dispenser

Propulsion systems and method for making a propulsion system include additively manufacturing a casing body into a single-piece structure having no bonded or bolted joints. The casing body defines a combustion chamber therein and is at least partially composed of a material useful as a solid rocket fuel and capable of being consumed during combustion. Other embodiments are also described.

Additive manufactured propulsion system

A fleet of autonomous sailing vessels that are equipped with monitoring and communication equipment for reporting environmental and other conditions. For optimal stability, the autonomous sailing vessels are multi-hulled vessels (catamarans) with self-righting capabilities. Each sailing vessel sends and receives information via one or more satellite links, using solar power to power the communications equipment as well as the monitoring equipment. Each sailing vessel includes an auto-sailtrim system to maintain a desired attack angle with the wind, and electric propulsion for use as required to maintain a desired heading. A modular design is used to support mission-specific payloads.

Autonomous sailboat for oceanographic monitoring

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.

Latching separation system

A spring-based deployment system deploys a mass at a limited velocity. Using techniques common to the art of timepieces, the motion of a gear, like the rotation of a clock's second hand, is controlled to occur at a substantially constant rate. In a preferred embodiment, an escapement is used to limit the amount of motion per unit time, thereby limiting the velocity. During the period of motion, a high-force can be applied to overcome friction and other adverse affects. Because the amount of motion is limited by the escapement, the amount of kinetic energy produced by this high-force is limited, and thus the shock effects introduced when the deployed mass is stopped at its deployed state are limited. An optimized design can by achieved via an appropriate tradeoff between total deployment time and controlled deployment rate.

Constant rate deployment device

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. Multiple sections of leaf elements can be employed to form a perimeter structure corresponding to the structure of the mating surface.

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Washington, DC, United States of America

Walter Holemans