An autonomous spacecraft propellant-gauging system, the system including a propellant tank, one or more heating devices, at least one temperature sensor and a processor. The heating devices are used to heat up the propellant tank, and the temperature sensors sense the temperature of the propellant content of the propellant tank. The processor controls operations of the heating devices and the temperature sensor. The processor further executes an algorithm to automate gauging of the propellant content of the propellant tank based on a reduced order model (ROM) and a number of parameters, and reports out an estimate of the mass of the remaining propellant of the propellant tank.

Fluid flow control valve comprising a tubular body extending in a longitudinal direction with a fluid inlet and a fluid outlet situated respectively at the two longitudinal ends of the body, the valve comprising a nozzle and a piston connected to the body, the piston being housed in the body, the nozzle being made up of a part provided with a fluid passage having a calibrated dimension, the passage emerging at one end of the nozzle and forming a seat, said seat being situated against a terminal end of the piston forming a shutter preventing the flow of fluid in the closed position of the valve, the piston comprising a body defining a passage for the fluid in the body for the flow of the fluid between the inlet and the outlet, the body of the valve consisting of a material having a different expansion coefficient from the piston or the nozzle, the valve comprising a heating member which, depending on the heating power delivered, makes it possible to separate the end of the nozzle and the piston by differential expansion, to allow the flow of fluid between the inlet and the outlet in an open position of the valve, characterized in that the terminal end of the piston comprises a ball that is crimped into the body of the piston.

To provide a sheet-like structure capable of highly accurately estimating a sheet-like shape. A sheet-like structure includes a sheet-like member and a plurality of detection sensors. The sheet-like member extends along an in-plane direction orthogonal to a thickness direction and receives light incident on the sheet-like member. The plurality of detection sensors are dispersedly arranged on the sheet-like member along the in-plane direction and are for detecting an incident angle of the light with respect to the sheet-like member at each arrangement position of the plurality of detection sensors.

A system and method for generating a force from a voltage difference applied across at least one electrically conductive surface. The applied voltage difference creates an electric field resulting in an electrostatic pressure force acting on at least one surface of an object. Asymmetries in the resulting electrostatic pressure force vectors result in a net resulting electrostatic pressure force acting on the object. The magnitude of the net resulting electrostatic pressure force is a function of the geometry of the electrically conductive surfaces, the applied voltage, and the dielectric constant of any material present in the gap between electrodes. The invention may be produced on a nanoscale using nanostructures such as carbon nanotubes. The invention may be utilized to provide a motivating force to an object. A non-limiting use case example is the use of electrostatic pressure force apparatus as a thruster to propel a spacecraft through a vacuum.

An electromagnetic propulsion system for the movement of spacecraft by means of ejection of the perturbed dark matter. In the present invention, to perturb and accelerate the dark matter, the electromagnetic energy generated by microwave generators is supplied to a number of position-adjustable electromagnetic vibrators that form a phased antenna array inside the waveguide. Since the dark matter permeates the Universe and its reserves are unlimited, it can be used as a working medium in the constant acceleration propulsion system for as long as the electric power supply lasts. Since the electromagnetic propulsion system has infinite reserves of the working medium, the specific impulse is also infinite. The speed of the dark matter jet approaches the speed of light.

A vacuum arc thruster device having a cathode rod disposed within a concentric insulator tube, and an anode electrode located at the distal edge of the insulator tube, separated from the cathode rod by the insulator tube. A controlled feeding mechanism moves the cathode towards the distal exit plane in a helical motion, the cathode rotating as it moves forward. The cathode rod is fixed in the center of a headless screw segment, which is rotated within a screw thread on the internal surface of a cylindrical wall of the device. As the erosion rate is concentrated at the exit plane, the screw action path enables uniform erosion around the cathode circumference, and cathode linear motion that can be matched to the radial erosion rate. The feeding rate and hence the thrust are proportional to the input power, which can be regulated by the pulse frequency.

A vacuum arc thruster device having a cathode rod disposed within a concentric insulator tube, and an anode electrode located at the distal edge of the insulator tube, separated from the cathode rod by the insulator tube. A controlled feeding mechanism moves the cathode towards the distal exit plane in a helical motion, the cathode rotating as it moves forward. The cathode rod is fixed in the center of a headless screw segment, which is rotated within a screw thread on the internal surface of a cylindrical wall of the device. As the erosion rate is concentrated at the exit plane, the screw action path enables uniform erosion around the cathode circumference, and cathode linear motion that can be matched to the radial erosion rate. The feeding rate and hence the thrust are proportional to the input power, which can be regulated by the pulse frequency.

A hybrid rocket engine with a vortex flow field injection system that produces a high-speed sustained vortex flow field is described. The hybrid rocket engine includes a generally cylindrical injection chamber with an inner circumference to comprise an outer edge of a solid propellant grain in the hybrid rocket engine. The engine also includes an injection system that has a throttle valve and an injector that injects injection fluid into the engine and produces a vortex flow-field for the injected fluid. The injector includes at least one primary feed line that distributes the injection fluid throughout a pre-swirl chamber and multiple orifices along an inner edge of the injection chamber. The pre-swirl chamber connects to the injection chamber and at least one of the primary feed lines and redirects a primary fluid flow of the injected fluid from a primary axial direction to a centrifugal direction.

The gyroscopic impulse motor rigidly attaches to a superstructure. The gyroscopic impulse motor transfers a plurality of independent torqueing forces to the superstructure. By independent is meant the amount of force applied by any first independent torqueing force is independent of the amount of torqueing force applied by any second independent torqueing force generated by the gyroscopic impulse motor. By independent is further meant that the selected direction any first independent torqueing force is independent of the selected direction of any second independent torqueing force generated by the gyroscopic impulse motor. By controlling the amount and direction of the plurality of independent torqueing forces applied by the gyroscopic impulse motor to the superstructure, the superstructure can be rotated. By properly aligning the amount and direction of the plurality of independent torqueing forces applied by the gyroscopic impulse motor, a net propulsive force can further be generated.

This device, the (‘Demon’ Quantum Mechanical, (H/C)/(Propulsion) system), replaces entirely, the (antiquated system of using Cryogens for cooling, in satellite applications). This device, is the ONLY application, which uses (Quantum Mechanics) for Propulsion/Thrusting. This device is the ONLY design to use (Quantum Mechanics) to (simultaneously Heat and Cool) in any application. This device is the ONLY design to use (Quantum Mechanics) to (simultaneously Heat and Cool) and for (Propulsion) in any application, —and due to the system (operating methods) and (weightless environment), —with EXPONENTIALLY greater (fuel) efficiency. This device (extends the (working service life) of Satellites requiring cooling) from MONTHS, to 50+ YEARS/more.