Abstract: Provided herein, in some embodiments, are methods and compositions for treatment of subjects with ?-thalassemia and subjects with severe sickle cell disease using autologous CRISPR-Cas9 modified CD34+ human hematopoietic stem and progenitor cells.

Abstract: Disclosed is a cooling circuit for cooling a heat load in an aircraft system, having: a compressor; a turbine connected to the compressor by a shaft, the turbine configured to drive the compressor via the shaft when RAM air pressure into a turbine inlet is above a first threshold; and a motor connected to the shaft configured to drive the compressor when RAM air pressure at the turbine inlet is below the first threshold to cause the compressor to draw air into the turbine inlet, through the turbine, a heat exchanger in fluid communication with the heat load, the compressor, and out of a compressor outlet.

Abstract: A thermal management system for one or more aircraft components includes a bleed airflow source at a gas turbine engine of the aircraft, one or more turbines configured to expand the bleed airflow, thus lowering a temperature of the bleed airflow, the bleed airflow driving rotation of the one or more turbines. One or more heat exchangers are in fluid communication with the one or more turbines. The one or more heat exchangers are configured to exchange thermal energy between the bleed airflow and a thermal load. One or more electrical generators are operably connected to the one or more turbines. The one or more electrical generators are configured to convert rotational energy of the one or more turbines to electrical energy.

Abstract: An environmental control system of an aircraft includes at least one heat exchanger and a compression device arranged in fluid communication with the at least one heat exchanger. The compression device includes a plurality of components including a first component and a second component coupled by a shaft. A first bleed port is arranged in fluid communication with the first component and a second bleed port, distinct from the first bleed port, is arranged in fluid communication with the second component.

Abstract: An environmental control system of an aircraft including a compression device including a compressor having a compressor inlet and a compressor outlet, a primary inlet for supplying a first medium to the compressor inlet, and a secondary inlet for supplying a second medium to the compressor inlet.

Abstract: A system includes a plurality of sensors, a controller and a component. The plurality of sensors are configured to obtain sensed data indicative of characteristics of an environment. The controller is configured with a reduced order model to output a predicted parameter based on the sensed data. The reduced order model is generated on an external computer system using a high-fidelity physics-based model. The controller is configured to control the component based on the predicted parameter.

Abstract: An environmental control system (ECS) for an aircraft includes at least one cooling turbine, and a turbine bypass valve disposed fluidly upstream of the at least one cooling turbine. The turbine bypass valve is configured to direct a first portion of an ECS output airflow to a first air load at a first pressure via a first outlet passage, and direct a second portion of the ECS output airflow across a cooling turbine of the at least one cooling turbine and to a second air load at a second pressure lower than the first pressure for cooling thereof.

Abstract: An environmental control system of an aircraft includes at least one heat exchanger and a compression device arranged in fluid communication with the at least one heat exchanger. The compression device includes a plurality of components including a first component and a second component coupled by a shaft. A first bleed port is arranged in fluid communication with the first component and a second bleed port, distinct from the first bleed port, is arranged in fluid communication with the second component.

Abstract: Provided are methods of treating bladder cancer (e.g., urothelial carcinoma, UC) in a subject having bladder cancer, e.g., UC, with an effective dose regimen of an anti-PD-L1 antibody, e.g., durvalumab, or an antigen binding fragment thereof. Also provided are methods in which an anti-PD-L1 antibody is used in combination with another immunotherapeutic agent, e.g., tremelimumab to treat a bladder cancer, e.g., UC, in a subject having bladder cancer. In some cases, the subject undergoing treatment is identified as having a bladder cancer or tumor that is PD-L1-low/neg, or PD-L1-high. Methods are also provided in which anti-PD-L1 antibody treatment of bladder cancer is used following a standard of care or first-line therapy in subjects who have progressed following such therapies or who have relapsed after a prior treatment regimen.

Abstract: A bleed air control system and method include first and second flow paths, first and second flow control valves, and a controller. The first flow path is configured to carry a first bleed air flow and includes a heat transfer device configured to transfer heat to or from the first bleed air flow. The second flow path is configured to carry a second bleed air flow. The first and second flow paths merge downstream to provide a combined bleed air flow. The first flow control valve is positioned to control the first bleed air flow, and the second flow control valve is positioned to control the second bleed air flow. The controller is configured to control the first and second flow control valves to control a temperature and flow of the combined bleed air flow.

Abstract: A method and system for predicting heat exchanger blockage in an aircraft is provided. The method includes generating a reduced order model (ROM) that predicts a ram air fan (RAF) surge margin that correlates to a heat exchanger blockage parameter, calculating, using the ROM, a predicted RAF surge margin value using a sensor signal received from a sensor connected to a ram air fan (RAF), calculating the heat exchanger blockage parameter using at least the predicted RAF surge margin value, and reporting, to a user, the heat exchanger blockage parameter that indicates when a heat exchanger blockage condition is present.

Abstract: A defrost cycle time of an aircraft vapor cycle refrigeration system is adaptively controlled. A pressure of refrigerant at an inlet of a compressor of the vapor cycle refrigeration system is sensed. A defrost cycle of the vapor cycle refrigeration system is initiated in response to the sensed pressure being less than a threshold pressure. The defrost cycle is terminated upon expiration of the defrost cycle time. The defrost cycle time is based upon a time duration of the cooling cycle.

Abstract: Aircraft fuel tank inerting systems and methods are provided. The aircraft fuel tank inerting systems include a fuel tank having fuel therein, an evaporator container fluidly connected to the fuel tank and arranged to receive inerting fuel from the fuel tank, the evaporator container evaporating the inerting fuel to generate a first reactant, a second reactant source arranged to supply a second reactant, and a catalyst fluidly connected to the evaporator container and arranged to receive the first reactant and the second reactant, wherein the catalyst includes a catalyst material to induce a chemical reaction between the first reactant and the second reactant to generate an inert gas, wherein the inert gas is supplied into an ullage of the fuel tank.

Abstract: Operational parameters of an aircraft vapor cycle refrigeration system are measured via a plurality of sensors while the vapor cycle refrigeration system is operating. The measured operational parameters are transmitted to a computer system. The computer system generates, using a first reduced order model corresponding to an unclogged state of a filter of the vapor cycle refrigeration system, a first predicted discharge pressure of a compressor based on the measured operational parameters. The computer system generates, using a second reduced order model that corresponds to a clogged state of the filter, a second predicted discharge pressure of the compressor based on the measured operational parameters. The computer system determines a remaining useful life of the filter based on the first predicted discharge pressure, the second predicted discharge pressure, and a measured discharge pressure of the compressor. The computer system outputs an indication of the remaining useful life of the filter.

Abstract: A system includes a plurality of sensors, a controller and a component. The plurality of sensors are configured to obtain sensed data indicative of characteristics of an environment. The controller is configured with a reduced order model to output a predicted parameter based on the sensed data. The reduced order model is generated on an external computer system using a high-fidelity physics-based model. The controller is configured to control the component based on the predicted parameter.

Abstract: A computer implemented method to determine aircraft sensor failure and correct aircraft sensor measurement in an aircraft system is provide. The computer implemented method includes determining, using a physics-based high-fidelity model, a high-fidelity system response over operating conditions during which sensor drift of a sensor of interest can be detected, creating, using an aircraft system controller, a reduced order model (ROM) using the high-fidelity system response, wherein the ROM correlates with the sensor of interest when operating normally, calculating, using the ROM, at least one reduced order sensor value, determining an error value between the reduced order sensor value and a sensor measurement reading from the sensor of interest, and comparing the error value to an error threshold, wherein the sensor of interest has failed when the error value is greater than the error threshold.

Abstract: A method and system for predicting heat exchanger blockage in an aircraft is provided. The method includes generating a reduced order model (ROM) that predicts a ram air fan (RAF) surge margin that correlates to a heat exchanger blockage parameter, calculating, using the ROM, a predicted RAF surge margin value using a sensor signal received from a sensor connected to a ram air fan (RAF), calculating the heat exchanger blockage parameter using at least the predicted RAF surge margin value, and reporting, to a user, the heat exchanger blockage parameter that indicates when a heat exchanger blockage condition is present.

Abstract: A method for treating polycystic ovarian syndrome and related conditions with a compound (I): or a pharmaceutically acceptable salt thereof.

Abstract: A method for treating polycystic ovarian syndrome and related conditions with a compound (I): or a pharmaceutically acceptable salt thereof.

Abstract: A method for treating polycystic ovarian syndrome and related conditions with a compound (I): or a pharmaceutically acceptable salt thereof.