Abstract: Methods and systems disclosed herein relate generally to evaluating resource loads to determine when to transform queues and to specific techniques for transforming at least part of queues so as to correspond to alternative resources.

Abstract: A programmable logic device includes logic blocks such as a logic array blocks (LAB) that can be configured as a random access memory (RAM) or as a lookup table (LUT). A mode flag is provided to indicate the mode of operation of configuration logic such as a configuration RAM (CRAM) used during partial reconfiguration of a logic block. An enable read flag is provided to indicate if values stored in the configuration logic are to be read out or a known state is to be read out during a data verification process. Thus, exclusion and inclusion of portions of a region of configuration logic from data verification and correction processes allow a region of configuration logic to store both a design state and a user defined state. Moreover, the region of configuration logic may be dynamically reconfigured from one state to another without causing verification errors.

Abstract: Launch vehicle systems and methods for landing and recovering a booster stage and/or other portions thereof on a platform at sea or on another body of water are disclosed. In one embodiment, a reusable space launch vehicle is launched from a coastal launch site in a trajectory over water. After booster engine cutoff and upper stage separation, the booster stage reenters the earth's atmosphere in a tail-first orientation. The booster engines are then restarted and the booster stage performs a vertical powered landing on the deck of a pre-positioned sea-going platform. In one embodiment, bidirectional aerodynamic control surfaces control the trajectory of the booster stage as it glides through the earth's atmosphere toward the sea-going platform. The sea-going platform can broadcast its real-time position to the booster stage so that the booster stage can compensate for errors in the position of the sea-going platform due to current drift and/or other factors.

Abstract: A programmable logic device includes logic blocks such as a logic array blocks (LAB) that can be configured as a random access memory (RAM) or as a lookup table (LUT). A mode flag is provided to indicate the mode of operation of configuration logic such as a configuration RAM (CRAM) used during partial reconfiguration of a logic block. An enable read flag is provided to indicate if values stored in the configuration logic are to be read out or a known state is to be read out during a data verification process. Thus, exclusion and inclusion of portions of a region of configuration logic from data verification and correction processes allow a region of configuration logic to store both a design state and a user defined state. Moreover, the region of configuration logic may be dynamically reconfigured from one state to another without causing verification errors.

Abstract: A programmable logic device includes logic blocks such as a logic array blocks (LAB) that can be configured as a random access memory (RAM) or as a lookup table (LUT). A mode flag is provided to indicate the mode of operation of configuration logic such as a configuration RAM (CRAM) used during partial reconfiguration of a logic block. An enable read flag is provided to indicate if values stored in the configuration logic are to be read out or a known state is to be read out during a data verification process. Thus, exclusion and inclusion of portions of a region of configuration logic from data verification and correction processes allow a region of configuration logic to store both a design state and a user defined state. Moreover, the region of configuration logic may be dynamically reconfigured from one state to another without causing verification errors.

Abstract: A programmable logic device includes logic blocks such as a logic array blocks (LAB) that can be configured as a random access memory (RAM) or as a lookup table (LUT). A mode flag is provided to indicate the mode of operation of configuration logic such as a configuration RAM (CRAM) used during partial reconfiguration of a logic block. If the mode flag indicates a design state, the configuration logic associated with the logic block is included in data verification and correction processes. If the mode flag indicates a user defined state, the configuration logic associated with the logic block is excluded from data verification and correction processes. Thus, exclusion and inclusion of portions of a region of configuration logic from data verification and correction processes allow a region of configuration logic to store both a design state and a user defined state without causing deleterious effects.

Abstract: A programmable logic device includes logic blocks such as a logic array blocks (LAB) that can be configured as a random access memory (RAM) or as a lookup table (LUT). A mode flag is provided to indicate the mode of operation of configuration logic such as a configuration RAM (CRAM) used during partial reconfiguration of a logic block. An enable read flag is provided to indicate if values stored in the configuration logic are to be read out or a known state is to be read out during a data verification process. Thus, exclusion and inclusion of portions of a region of configuration logic from data verification and correction processes allow a region of configuration logic to store both a design state and a user defined state. Moreover, the region of configuration logic may be dynamically reconfigured from one state to another without causing verification errors.

Abstract: Clock switch-over circuits and methods provide clock signals to clock routing networks. According to one embodiment, a multiplexer selects between a first clock signal and a second clock signal in response to a switch select signal received from a control circuit. A storage circuit stores an enable signal in response to an output clock signal of the multiplexer. A logic circuit transmits the output clock signal of the multiplexer to a clock routing network in response to the enable signal from the storage circuit. At least one signal is transmitted from the clock switch-over circuit to the control circuit.

Abstract: Clock switch-over circuits and methods provide clock signals to clock routing networks. According to one embodiment, a multiplexer selects between a first clock signal and a second clock signal in response to a switch select signal received from a control circuit. A storage circuit stores an enable signal in response to an output clock signal of the multiplexer. A logic circuit transmits the output clock signal of the multiplexer to a clock routing network in response to the enable signal from the storage circuit. At least one signal is transmitted from the clock switch-over circuit to the control circuit.

Abstract: Launch vehicle systems and methods for landing and recovering a booster stage and/or other portions thereof on a platform at sea or on another body of water are disclosed. In one embodiment, a reusable space launch vehicle is launched from a coastal launch site in a trajectory over water. After booster engine cutoff and upper stage separation, the booster stage reenters the earth's atmosphere in a tail-first orientation. The booster engines are then restarted and the booster stage performs a vertical powered landing on the deck of a pre-positioned sea-going platform. In one embodiment, bidirectional aerodynamic control surfaces control the trajectory of the booster stage as it glides through the earth's atmosphere toward the sea-going platform. The sea-going platform can broadcast its real-time position to the booster stage so that the booster stage can compensate for errors in the position of the sea-going platform due to current drift and/or other factors.

Abstract: Multiple-use rocket engines and associated systems and methods are disclosed. A method in accordance with a particular embodiment includes launching a two-stage vehicle have a first stage and a second stage carried by the first stage. The first stage can be powered with a first rocket engine having first rocket engine components, including a first combustion chamber, arranged in a first component configuration. The method can further include separating the second stage from the first stage, and powering the second stage with a second rocket engine having second engine components arranged in a second component configuration. The second rocket engine components can include a second combustion chamber that is interchangeable with the first combustion chamber. In further particular embodiments, recovered engine components from the first stage may be used to power the second stage of the same or a different two-stage vehicle.

Abstract: A programmable logic device (PLD) includes a signal distribution network, separate from the high-quality, low-skew clock distribution networks of the PLD, for distributing, from peripheral input/output regions of the PLD, clock-type signals. The signal distribution network includes a central periphery clock bus, located near a group of peripheral input/output regions, for conducting clock-type signals from those regions onto a clock spine of the PLD. The clock spine may be dedicated to the signal distribution network, or may be part of a high-quality, low-skew clock distribution network covering all or part of the PLD. The signal distribution network allows greater skew than such high-quality, low-skew clock distribution networks, but nevertheless is of higher quality, and allows less skew, than the general programmable interconnect and routing resources.

Abstract: An experiment system with six different re-entry experiment locations for testing high temperature re-entry materials, creating new thermal protection systems, proving innovative new concepts for spacecraft exterior surfaces and the incremental development of next generation aerospace materials. A commercial transportation system to and from orbit provides a 24-hour return cycle for the experiments on a surface actually re-entering the earth's atmosphere. Now using existing doors, hatches and other points on the reusable launch vehicle's exterior, the actual re-entry environment is experienced by test specimens with quick turn around for a wide variety of different re-entry temperatures ranges for broad testing and development purposes. The reusable launch vehicle launches, remains in orbit for 24 hours and returns to provide an actual test environment for the exterior experiment system.

Abstract: An experiment system with six different re-entry experiment locations for testing high temperature re-entry materials, creating new thermal protection systems, proving innovative new concepts for spacecraft exterior surfaces and the incremental development of next generation aerospace materials. A commercial transportation system to and from orbit provides a 24-hour return cycle for the experiments on a surface actually re-entering the earth's atmosphere. Previously expensive arc jet wind tunnels attempted to simulate the re-entry temperatures and ever changing re-entry flow environment for researchers. Now using existing doors, hatches and other points on the reusable launch vehicle's exterior, the actual re-entry environment is experienced by test specimens with quick turn around for a wide variety of different re-entry temperatures ranges for broad testing and development purposes.

Abstract: An experiment system with six different re-entry experiment locations for testing high temperature re-entry materials, creating new thermal protection systems, proving innovative new concepts for spacecraft exterior surfaces and the incremental development of next generation aerospace materials. A commercial transportation system to and from orbit provides a 24-hour return cycle for the experiments on a surface actually re-entering the earth's atmosphere. Now using existing doors, hatches and other points on the reusable launch vehicle's exterior, the actual re-entry environment is experienced by test specimens with quick turn around for a wide variety of different re-entry temperatures ranges for broad testing and development purposes. The reusable launch vehicle launches, remains in orbit for 24 hours and returns to provide an actual test environment for the exterior experiment system.

Abstract: Circuitry for providing an input data signal to other circuitry on an integrated circuit includes a course delay chain and a fine delay chain. These two delay chains are cascadable, if desired, to provide a very wide range of possible amounts of delay which can be finely graded by use of the fine delay chain.

Abstract: Circuitry for providing an input data signal to other circuitry on an integrated circuit includes a course delay chain and a fine delay chain. These two delay chains are cascadable, if desired, to provide a very wide range of possible amounts of delay which can be finely graded by use of the fine delay chain.

Abstract: An orbital experiment system with different internal experiment locations within a reusable launch vehicle making daylong delivery trips to space. The experiments get access to the attributes of low earth orbit, the reusable launch vehicle's power and other subsystems. The experimenter utilizes uniform experiment trays having a uniform connector for connection to an experiment management unit mounted on the orbital vehicle. The experiment management unit provides power and data from the orbital vehicle related to the operation of the orbital vehicle and permits an experiment check simulation prior to integration into the launch vehicle. The uniform size and connectivity requirements provide low cost options for the delivery of an experiment into space and the return of the experiment from space.

Abstract: An experiment system with six different re-entry experiment locations for testing high temperature re-entry materials, creating new thermal protection systems, proving innovative new concepts for spacecraft exterior surfaces and the incremental development of next generation aerospace materials. A commercial transportation system to and from orbit provides a 24-hour return cycle for the experiments on a surface actually re-entering the earth's atmosphere. Now using existing doors, hatches and other points on the reusable launch vehicle's exterior, the actual re-entry environment is experienced by test specimens with quick turn around for a wide variety of different re-entry temperatures ranges for broad testing and development purposes. The reusable launch vehicle launches, remains in orbit for 24 hours and returns to provide an actual test environment for the exterior experiment system.

Abstract: An orbital experiment system with different internal experiment locations within a reusable launch vehicle making daylong delivery trips to space. The experiments get access to the attributes of low earth orbit, the reusable launch vehicle's power and other subsystems. The experimenter utilizes uniform experiment trays having a uniform connector for connection to an experiment management unit mounted on the orbital vehicle. The experiment management unit provides power and data from the orbital vehicle related to the operation of the orbital vehicle and permits an experiment check simulation prior to integration into the launch vehicle. The uniform size and connectivity requirements provide low cost options for the delivery of an experiment into space and the return of the experiment from space.