Abstract: Disclosed are means, methods and compositions of matter useful for stimulation enhancement of T cell homing into tumors and overcoming tumor microenvironment. In one embodiment the invention provides an engineered T cell in which engagement of T cell receptor on said T cell results in upregulation of T cell attracting chemokines so as to induce an increased proportion of T cells to tumor cells. In another embodiment, T cell chemokine secreting cells are administrated intratumorally in order to augment T cell infiltration into said tumors. In other embodiments administration of lymphopoietic cytokines is performed intratumorally to enhance viability of T cells approaching and residing in the microenvironment. Combinations of agents which counteract tumor microenvironment induced immune suppression are also disclosed.

Abstract: A battery system having a battery pack with a positive pole, a negative pole, at least one battery cell, and a pack voltage divider, and at least one high-voltage coupling network electrically connectable to the battery pack, having a positive terminal, a negative terminal, and a link voltage divider. The pack voltage divider comprises a first measuring resistance (RM1) and a first measuring switch (SM1) connected to one another between the negative pole and a first reference point, and a second measuring resistance (RM2) and a second measuring switch (SM2) connected to one another between the positive pole and the first reference point. The link voltage divider comprises a third measuring resistance (RM3) connected between the negative terminal and a second reference point, and a fourth measuring resistance (RM4) connected between the positive terminal and the second reference point.

Abstract: Disclosed are aptamers designed to bind immunological checkpoint molecules while concurrently suppressing tumor associated gene expression through delivery of DNA molecules encoding short hairpin DNA. In one embodiment the invention provides an aptamer capable of binding PD-1 and/or PD-1 ligand while concurrently possessing ability to induce RNA interference to one more multiple other immune inhibitory and/or oncogenesis related genes. In one embodiment such a dual-targeting aptamer is utilized to induce systemic tumor abscopal effect.

Abstract: The present invention features solid pharmaceutical compositions comprising Compound 1 and Compound 2. In one embodiment, the solid pharmaceutical composition includes (1) a first layer which comprises 100 mg Compound 1, as well as a pharmaceutically acceptable hydrophilic polymer and a pharmaceutically acceptable surfactant, all of which are formulated in amorphous solid dispersion; and (2) a second layer which comprises 40 mg Compound 2, as well as a pharmaceutically acceptable hydrophilic polymer and a pharmaceutically acceptable surfactant, all of which are formulated in amorphous solid dispersion.

Abstract: Disclosed are combination therapies for cancer utilizing the leverage of the adaptive immune system through chimeric antigen receptor (CAR) T cells, combined with leveraging the innate immune system by using CAR-macrophages (CAR-M) and CAR-natural killer (NK) cells. In some embodiments, the invention teaches the initial modification of the tumor microenvironment by administration of CAR-M and CAR-NK. The alteration of the tumor microenvironment results in reduction of barriers for CAR-T cells to enter the tumor, which allows for efficacy of CAR-T in treatment of solid tumors. In some embodiments adjuvant immunotherapies are utilized to expand immunological attack such as addition of complement, immunotherapeutic antibodies, chemotherapy and radiotherapy approaches.

Abstract: The aircraft threat envelope protection system employs a threat envelope data structure in a computer-readable medium that stores at least one trigger condition for each of a plurality of different types of threats associated with the aircraft, and modeled using a common schema. A processor computes plural different projected trajectories representing different possible aircraft paths through spacetime. The processor associates at least some of the plurality of the threats to specific trigger points in spacetime along each of the projected trajectories. The processor will deprecate ones of the projected trajectories when they are deemed not viable to recover from a threat. The processor initiates an aircraft protective response when all projected trajectories but one have been deprecated and the aircraft is within a predetermined proximity to the closest trigger point in spacetime along the non-deprecated trajectory.

Abstract: A method of checking accuracy of an air data probe system onboard a vehicle is disclosed. An embodiment of the method involves: calculating airspeed measurements from air data provided by the probe system; calculating vehicle speed measurements based on sensor data collected from at least one sensor system onboard the vehicle, wherein the vehicle speed measurements are distinct and independent of the airspeed measurements, and the vehicle speed measurements are calculated without using the air data; comparing a calculated airspeed measurement against a calculated vehicle speed measurement to obtain a speed difference, wherein the calculated airspeed measurement and the calculated vehicle speed measurement correspond to a measurement time during which the vehicle is moving forward; and initiating at least one corrective action onboard the vehicle when magnitude of the speed difference exceeds a threshold value.

Abstract: The aircraft threat envelope protection system employs a threat envelope data structure in a computer-readable medium that stores at least one trigger condition for each of a plurality of different types of threats associated with the aircraft, and modeled using a common schema. A processor computes plural different projected trajectories representing different possible aircraft paths through spacetime. The processor associates at least some of the plurality of the threats to specific trigger points in spacetime along each of the projected trajectories. The processor will deprecate ones of the projected trajectories when they are deemed not viable to recover from a threat. The processor initiates an aircraft protective response when all projected trajectories but one have been deprecated and the aircraft is within a predetermined proximity to the closest trigger point in spacetime along the non-deprecated trajectory.

Abstract: The aircraft threat envelope protection system employs a threat envelope data structure in a computer-readable medium that stores at least one trigger condition for each of a plurality of different types of threats associated with the aircraft, and modeled using a common schema. A processor computes plural different projected trajectories representing different possible aircraft paths through spacetime. The processor associates at least some of the plurality of the threats to specific trigger points in spacetime along each of the projected trajectories. The processor will deprecate ones of the projected trajectories when they are deemed not viable to recover from a threat. The processor initiates an aircraft protective response when all projected trajectories but one have been deprecated and the aircraft is within a predetermined proximity to the closest trigger point in spacetime along the non-deprecated trajectory.

Abstract: The processor supplies flight commands to the flight control system by selectively blending pilot input with control signals from the autopilot. The processor generates a projected recovery trajectory through successive iterations, each beginning at the current aircraft location and using a recovery constraint selectable by the processor to influences a degree of flight aggressiveness. A detection system that identifies and invokes a state of threat existence if a threat exists along the projected recovery trajectory. The processor during threat existence in a first iteration commands an initial soft recovery, with permitted blended pilot input. If the threat exists on subsequent iteration, the processor commands a more aggressive recovery while attenuating blended pilot input.

Abstract: An aircraft includes a processor, an airframe, a pitch attitude flight control surface coupled with the airframe, a nose wheel coupled with the airframe, main wheels coupled with the airframe, and a brake system coupled with the main wheels. The processor is programmed to determine that the aircraft has entered a braking segment of a landing phase of a flight of the aircraft while the aircraft is on a ground surface and to command the pitch attitude flight control surface with a nose up command during the braking segment in response to determining that the aircraft has entered the braking segment. The nose up command causes the pitch attitude flight control surface to generate a downforce that increases traction between the main wheels and the ground surface due to a weight shift from the nose wheel to the main wheels and directly due to the downforce on the main wheels.

Abstract: The present invention relates to an active (immunostimulatory) composition comprising at least one RNA, preferably a mRNA, encoding at least two (preferably different) antigens capable of eliciting an (adaptive) immune response in a mammal. The invention furthermore relates to a vaccine comprising said active (immunostimulatory) composition, and to the use of said active (immunostimulatory) composition (for the preparation of a vaccine) and/or of the vaccine for eliciting an (adaptive) immune response for the treatment of lung cancer, particularly of non-small cell lung cancers (NSCLC), preferably selected from the three main sub-types squamous cell lung carcinoma, adenocarcinoma and large cell lung carcinoma, or of disorders related thereto. Finally, the invention relates to kits, particularly to kits of parts, containing the active (immunostimulatory) composition and/or the vaccine.

Abstract: Aircraft, auto speed brake control systems, and methods for controlling drag of an aircraft are provided. In one example, an aircraft includes an aircraft structure. A drag device is operatively coupled to the aircraft structure between a stowed and a deployed position and/or an intermediate deployed position. A speed brake controller is in communication with the drag device to control movement. An autothrottle-autospeedbrake controller is in communication with the speed brake controller and is configured to receive data signals. The autothrottle-autospeedbrake controller is operative to direct the speed brake controller to control movement of the drag device between the stowed position and the deployed position and/or the intermediate deployed position in response to at least one of the data signals.

Abstract: A flight control system for controlling an aircraft during a variable engine thrust takeoff operation operative to perform a method including calculating a calculated acceleration in response to a takeoff distance and a selection of a variable engine thrust takeoff mode, generating an initial thrust control signal in response to the calculated acceleration, controlling a thrust of an aircraft engine in response to the initial thrust control signal, measuring a measured acceleration of the aircraft, generating an updated thrust control signal in response to a difference between the calculated acceleration and the measured acceleration, and controlling the thrust of the aircraft engine in response to the updated thrust control signal.

Abstract: The processor supplies flight commands to the flight control system by selectively blending pilot input with control signals from the autopilot. The processor generates a projected recovery trajectory through successive iterations, each beginning at the current aircraft location and using a recovery constraint selectable by the processor to influences a degree of flight aggressiveness. A detection system that identifies and invokes a state of threat existence if a threat exists along the projected recovery trajectory. The processor during threat existence in a first iteration commands an initial soft recovery, with permitted blended pilot input. If the threat exists on subsequent iteration, the processor commands a more aggressive recovery while attenuating blended pilot input.

Abstract: Flight control systems, flight control methods, and aircraft are provided.

Abstract: Avionics systems, aircraft, and methods are provided. An avionics system for a subject aircraft includes an intruder aircraft detection device and a processor. The processor is programmed to: identify an intruder aircraft using the intruder aircraft detection device; predict a future path of the intruder aircraft; estimate strength, size, and location characteristics of a wake vortex created by the intruder aircraft at future points in time along the future path; calculate a potential trajectory with potential positions of the subject aircraft at each of the future points in time; compare the potential positions with the strength, size, and location characteristics of the wake vortex at each of the future points in time to identify a wake conflict; and maneuver the subject aircraft based on the wake conflict.

Abstract: An aircraft includes a processor, an airframe, a pitch attitude flight control surface coupled with the airframe, a nose wheel coupled with the airframe, main wheels coupled with the airframe, and a brake system coupled with the main wheels. The processor is programmed to determine that the aircraft has entered a braking segment of a landing phase of a flight of the aircraft while the aircraft is on a ground surface and to command the pitch attitude flight control surface with a nose up command during the braking segment in response to determining that the aircraft has entered the braking segment. The nose up command causes the pitch attitude flight control surface to generate a downforce that increases traction between the main wheels and the ground surface due to a weight shift from the nose wheel to the main wheels and directly due to the downforce on the main wheels.

Abstract: Aircraft, auto speed brake control systems, and methods for controlling drag of an aircraft are provided. In one example, an aircraft includes an aircraft structure. A drag device is operatively coupled to the aircraft structure between a stowed and a deployed position and/or an intermediate deployed position. A speed brake controller is in communication with the drag device to control movement. An autothrottle-autospeedbrake controller is in communication with the speed brake controller and is configured to receive data signals. The autothrottle-autospeedbrake controller is operative to direct the speed brake controller to control movement of the drag device between the stowed position and the deployed position and/or the intermediate deployed position in response to at least one of the data signals.

Abstract: The processor supplies flight commands to the flight control system by selectively blending pilot input with control signals from the autopilot. The processor generates a projected recovery trajectory through successive iterations, each beginning at the current aircraft location and using a recovery constraint selectable by the processor to influences a degree of flight aggressiveness. A detection system that identifies and invokes a state of threat existence if a threat exists along the projected recovery trajectory. The processor during threat existence in a first iteration commands an initial soft recovery, with permitted blended pilot input. If the threat exists on subsequent iteration, the processor commands a more aggressive recovery while attenuating blended pilot input.