347 results about "Thrust control" patented technology

An automatic takeoff thrust management system can be used in an aircraft with at least two engines. The management system comprises an aircraft status sensor or set of sensors capable of detecting establishment of takeoff climb conditions, and engine failure detectors respectively coupled to the at least two engines and capable of detecting engine failure. The management system further comprises thrust control modules respectively coupled to the at least two engines and capable of controlling the thrust of the engines, and a controller coupled to the aircraft status sensors, the engine failure detectors, and the thrust control modules. The controller reduces thrust by a selected amount upon detecting establishment of takeoff climb conditions and, if engine failure is detected, restoring thrust to an initial or a higher schedule.

The system is used for taxiing an aircraft and comprises at least one multi-spool gas turbine engine, the engine having an electrical motor in a torque-driving engagement with a low pressure spool of the engine. The low pressure spool has a propulsor connected thereon to generate thrust when rotated. A controller is connected to the electrical motor and an electrical power source to control an amount of electrical power provided from the power source to the electrical motor so as to drive the propulsor and cause at least a major portion of the thrust to be generated by the propulsor for moving the aircraft during taxiing.

The invention discloses a power positioning system and method for an unmanned ship. The system comprises a sensor measurement system, a control system and a power and propulsion system. The method comprises steps as follows: a hydrodynamic model of the unmanned ship under the action of multiple factors is established, and standard description of control of the unmanned ship is realized; the ship movement position and course are measured by various sensors installed on the unmanned ship, complicated real-time computing is performed by a computer, a multi-vector thrust control technology is used for decoupling control of the power positioning system, the purpose of cooperative control of thrust, rotating speeds and pitch angle is achieved, a thrust device of the unmanned ship is further controlled to produce propulsion force and torque to resist disturbing force caused by the outside environment, and the target ship position and ship heading of the unmanned ship are kept.

An unmanned aircraft includes a forward propulsion system comprising one or more forward thrust engines and one or more corresponding rotors coupled to the forward thrust engines; a vertical propulsion system comprising one or more vertical thrust engines and one or more corresponding rotors coupled to the vertical thrust engines; and a pitch angle and throttle control system, comprising a processor configured to receive a first pitch angle command; and generate a second pitch angle command and a forward thrust engine throttle command based on a bounded pitch angle for the aircraft.

A magnetically driven pump includes a casing, a containment shell fixed to the casing, a shaft fixed at a closed end of the containment shell, an impeller rotatable about the shaft within the casing and containment shell, and a magnetic coupling removably secured to the impeller and rotatable about the shaft. The pump also includes a rear bearing positioned between the propeller and the shaft that is rotatable about the shaft, and a thrust control valve that includes a thrust ring positioned between the containment shell and the rear bearing. An opening of the thrust control valve is defined by a variable spacing between the thrust ring and the rear bearing.

The present invention relates to haptic feedback for operating at least one manual flight control device (21) for controlling the cyclic pitch of the blades (5) of a rotary wing (4) of a hybrid helicopter (1) via power assistance (27). Said operations of said control device (21) are defined according to a predetermined damping force relationship (A) that is a function of an instantaneous load factor of the hybrid helicopter (1) in such a manner that the instantaneous load factor is maintained between its minimum and maximum limit values in proportion to a position of a thrust control member (20) between its minimum and maximum thrust values (23, 22).

An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T / V”) module and a second T / V module, and an electronics module. The electronics module provides commands to the two T / V modules. The two T / V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T / V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

A watercraft includes a number of subassemblies, including an inflatable hull, a drive system, a battery, a seat assembly and a steering and thrust control. Each of the subassemblies of may be of one or more particular designs which are detailed herein. A watercraft in accordance with the teaching herein may use one or more of these designs and each such watercraft is within the scope of this disclosure.

An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T / V”) module and a second T / V module, and an electronics module. The electronics module provides commands to the two T / V modules. The two T / V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T / V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

The invention relates to the aerospace field, and provides a rendezvous docking method and device of a space non-cooperative target. The method comprises the steps of guiding the space non-cooperative target to a system capture range through ground guideness; determining measurement angle of sight, relative distance and azimuthal angle respectively according to the simplest combination of measurement components capable of determining relative parameters of the space non-cooperative target; carrying out relative navigation by using an extended Kalman filter algorithm, according to the capture measurement results; tracking track the target by executing CW reference trajectory guidance and linear reference trajectory guidance respectively to according to navigation results and giving out a relative position and relative speed equation of an ideal trajectory; and carrying out thrust control by adopting a PID control law and a pseudo rate pulse modulator during an approaching process. Through capturing, tracking and approaching of the space non-cooperative target, autonomous capturing, continuous tracking and stable approaching of the space non-cooperative target can be finished after a spacecraft enters a work range of capturing the non-cooperative target, thereby realizing rendezvous docking of the space non-cooperative target.

The present invention relates to a solid rocket motor control system that uses state of the art electrically ignited, extinguishable and throttleable propellants. In embodiments, the control system is implemented by a software algorithm embedded in missile flight controllers and contains all control system elements and control compensation that performs thrust control for many defense and space rocket motor applications, for example.

The invention discloses a technology for constructing a mined tunnel by adopting a composite tooth supporttunneling construction technology of composite tooth support through mining method, which comprises a composite tooth support processing technology, a segment staggering and concave-convex phenomenon control technology, a segment waterproofing technology, a shield thrust control measurement and a tracing and monitoring technology. The technology for constructing the mined tunnel by adopting the composite tooth supportcomposite tooth support through mining method is characterized in that, in the composite tooth support processing technology, composite tooth supports are installed in original grouting holes and used for supporting, and the tension of the composite tooth supports and vertical bolts controls segments; in the segment staggering and concave-convex phenomenon control technology, combines the pea gravel spraying and is combined with the shield tail synchronous grouting; in the segment waterproofing technology, water swelling stopper is installed on single edge of each segment; the shield thrust control measurement comprises guide platform quality control, shield axis control and shield stage thrust control; and the tracing and monitoring technology comprises tunnel segment attitude instant tracing and monitoring and deformation detection. The composite tooth support through mining methodinvention can shorten construction period and achieve maximum staggering between two segments and maximum staggering between two rings and has the advantages of low cost.

A vectored thrust control module for an aircraft that includes a servo system that couples to the aircraft structure at an output shaft connection point. A thrust motor assembly is fully supported by the servo system and rotates a bladed component to provide thrust to the aircraft. Further, the thrust motor assembly is rigidly connected with the servo system to rotate together about a longitudinal axis thrust line with respect to the aircraft structure. The bladed component and the thrust motor assembly generate a line of thrust that extends through the connection point of the servo system to the aircraft structure.

A method and system for actively controlling thrust pressure in a steam turbine is disclosed. The method may comprise monitoring a thrust pressure affecting a thrust fitting in a steam turbine, and adjusting the thrust pressure to maintain a desired thrust pressure on the thrust fitting in the steam turbine.

The invention relates to the field of linear motor control, in particular to a method for restraining the pulsation of a thrust system of a linear motor; the method adopts a sliding mode thrust controller and a magnetic flux controller, the thrust deviation and the magnetic flux deviation are selected as controlled variables, an integral sliding mode surface which is composed of the thrust deviation and the magnetic flux deviation design the sliding mode motion trajectory, thereby a system can move according to the sliding mode trajectory and the output thrust and the magnetic flux can better track specified value, wherein, a fuzzy controller utilizes the fuzzy control method which uses language information and data information to approach any specified continuous function to solve the jitter problem of a sliding mode control system. The method has the advantages that: a direct drive control system of the linear motor has strong coupling property, nonlinear property, multiple variables and unique end effect, the use of the direct thrust control method of the fuzzy sliding mode linear motor with high robust performance can solve the impacts of various factors on the control performance, thereby achieving the purposes of restraining the thrust pulsation of the linear motor and obtaining great dynamic response performance.

The invention discloses an aircraft fluidic thrust vector control system. With the control system, 306-degree flying attitudes of the aircraft can be controlled; response time of the control system is shortened; control precision of the control system is increased; a structure of the control system is simplified; and the weight of the aircraft is reduced. The aircraft fluidic thrust vector control system comprises a fuel gas turbine engine, a main airflow channel, a secondary flow nozzle, a secondary flow channel assembly and a Coanda effect surface. A small part of the gas is introduced out from an engine compression chamber to be used as a secondary flow gas source of the vector thrust control system in the same direction, and is injected into the secondary flow channel by using a Coanda effect. A wall attachment effect is produced after the secondary flow in the same direction with the main airflow flows through the Coanda effect surface, and Coanda effect is further generated by guiding the main airflow along the wall attachment direction, so that a deflection torque is obtained. Precision control for pitching, being off-course and rolling of the aircraft can be realized by controlling the outflow direction and the flow rate of the secondary flow.

The invention discloses a one-phase open-circuit fault-tolerant direct thrust control method for a five-phase permanent magnet linear motor. Firstly, a Clark transform matrix and an inverse matrix thereof are derived based on fault-tolerant phase current. On the above basis, a stator flux linkage on alpha-beta is derived, a stator virtual flux linkage is defined according to the requirements of acircular stator flux linkage trajectory, and thus the voltage compensation on alpha-beta is derived. The stator actual voltage on the alpha-beta is derived by a modulation function of a voltage sourceinverter, and voltage is combined with voltage compensation and stator current, and a stator virtual flux linkage and thrust are observed by a stator flux observer and a thrust observer. Then statorvirtual target votlage is calculated according to given thrust, a given stator flux linkage amplitude and the observed stator virtual flux linkage and thrust. Finally, the stator actual voltage is calculated by the voltage and the voltage compensation, and the motor is controlled by the voltage by the voltage source inverter. According to the method, a thrust fluctuation caused by a motor failureis suppressed, and more importantly, the dynamic performance and steady state performance are consistent with that in a normal condition.

A thrust vectorable fan variable area nozzle (FVAN) includes a synchronizing ring, a static ring, and a flap assembly mounted within a fan nacelle. An actuator assembly selectively rotates synchronizing ring segments relative the static ring to adjust segments of the flap assembly to vary the annular fan exit area and vector the thrust through asymmetrical movement of the thrust vectorable FVAN segments. In operation, adjustment of the entire periphery of the thrust vectorable FVAN in which all segments are moved simultaneously to maximize engine thrust and fuel economy during each flight regime. By separately adjusting the segments of the thrust vectorable FVAN, engine trust is selectively vectored to provide, for example only, trim balance or thrust controlled maneuvering.

A magnetically driven pump includes a casing, a containment shell fixed to the casing, a shaft fixed at a closed end of the containment shell, an impeller rotatable about the shaft within the casing and containment shell, and a magnetic coupling removably secured to the impeller and rotatable about the shaft. The pump also includes a rear bearing positioned between the propeller and the shaft that is rotatable about the shaft, and a thrust control valve that includes a thrust ring positioned between the containment shell and the rear bearing. An opening of the thrust control valve is defined by a variable spacing between the thrust ring and the rear bearing.

A method of controlling the yaw attitude of a hybrid helicopter including a fuselage and an additional lift surface provided with first and second half-wings extending from either side of the fuselage, each half-wing being provided with a respective first or second propeller. The hybrid helicopter has a thrust control suitable for modifying the first pitch of the first blades of the first propeller and the second pitch of the second blades of the second propeller by the same amount. The hybrid helicopter includes yaw control elements for generating an original order for modifying the yaw attitude of the hybrid helicopter by increasing the pitch of the blades of one propeller and decreasing the pitch of the blades of the other propeller, the original order is optimized as a function of the position of the thrust control to obtain an optimized yaw control order that is applied to the first and second blades.

An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust vectoring module and a second thrust vectoring module, and an electronics module. The electronics module provides commands to the two thrust vectoring modules. The two thrust vectoring modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as thrust vectoring modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

The invention discloses an optimal orbital transfer method of a low-earth-orbit satellite under a limited thrust by taking J2 perturbation into consideration, relates to the optimal orbital transfer method of the low-earth-orbit satellite, and belongs to the field of aerospace. The optimal orbital transfer method comprises the following steps of: establishing a dynamic equation of a spacecraft by taking the J2 perturbation into consideration; solving a Hamiltonian function H corresponding to an optimal fuel consumption performance index according to the states of the spacecraft at the beginning and the end; solving an optimal control rate and a corresponding covariance equation according to a pontryagin maximum principle; constructing a two-point boundary value problem shooting equation set meeting the optimal fuel consumption according to an optimal control condition of a variational method; solving the two-point boundary value problem shooting equation set according to the states of the spacecraft at the beginning and the end as well as the flight time to obtain the optimal control rate formed by an optimal thrust control direction and an engine switching function; and controlling the orbital transfer of the satellite by using the control rate, so that the real-time performance and the orbital transfer precision in the transfer process of the low-earth-orbit satellite can be increased, and the fuel consumption required for the orbital transfer is reduced. The optimal orbital transfer method disclosed by the invention is suitable for the orbital transfer process of the low-earth-orbit satellite when a limited thrust model is adopted by an engine.

An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust vectoring module and a second thrust vectoring module, and an electronics module. The electronics module provides commands to the two thrust vectoring modules. The two thrust vectoring modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as thrust vectoring modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

A solid propellant thrust control system, method, and apparatus for controlling combustion of solid propellants in an opposing grains solid propellant rocket engine (OGRE) is provided. In particular, an opposing grains rocket engine and propulsion system is provided, in which actuator means connected are connected to solid propellant grains disposed in the pressure vessel of the engine. The actuator means are operable to selectively move the solid propellant grains together or apart relative to one another, such that the burning ends of the solid propellant grains decrease or increase relative to one another. This action controls the rate of combustion of the solid propellant grains by varying spacing distance between the burning ends of the solid propellant grains, and enables extinguishment and reignition of the OGRE. Further, a method is providing for controlling the burn rate of solid propellant grains undergoing combustion in an opposing grains rocket engine.

A method for estimating engine thrust, wherein the method includes obtaining information about an initial dynamic state of the engine and updating the information about the initial dynamic state of the engine to reflect a second dynamic state of the engine. The method also includes generating engine thrust estimates, wherein the thrust estimates facilitate implementing direct thrust control.

A method and system for actively controlling thrust pressure in a steam turbine is disclosed. The method may comprise monitoring a thrust pressure affecting a thrust fitting in a steam turbine, and adjusting the thrust pressure to maintain a desired thrust pressure on the thrust fitting in the steam turbine.

The invention discloses an automatic and random grouping push control system of a shield tunneling machine. The automatic and random grouping push control system comprises a push oil cylinder reverse control device set and a plurality of push oil cylinder thrust control device sets, the signal control ends of the push oil cylinder thrust control device sets and the signal control end of the push oil cylinder reverse control device set are connected with an upper computer of the shield tunneling machine, and the upper computer sends signals to the push oil cylinder thrust control device sets and the push oil cylinder reverse control device set to adjust the push posture of the shield tunneling machine in real time by adjusting the maximum thrust of an oil cylinder. The shield tunneling machine can advance precisely along designed tracks, construction quality can be improved, and construction efficiency can be improved.

A thrust vectorable fan variable area nozzle (FVAN) includes a synchronizing ring, a static ring, and a flap assembly mounted within a fan nacelle. An actuator assembly selectively rotates synchronizing ring segments relative the static ring to adjust segments of the flap assembly to vary the annular fan exit area and vector the thrust through asymmetrical movement of the thrust vectorable FVAN segments. In operation, adjustment of the entire periphery of the thrust vectorable FVAN in which all segments are moved simultaneously to maximize engine thrust and fuel economy during each flight regime. By separately adjusting the segments of the thrust vectorable FVAN, engine trust is selectively vectored to provide, for example only, trim balance or thrust controlled maneuvering.

A nozzle assembly for thrust or thrust vector control of a rocket or ramjet, comprising an elongated nozzle housing and a pair of vane members mounted for pivotal movement within a central portion of the nozzle housing. The vane members extend vertically or transversely between the upper and lower portions of the nozzle housing near the forward portion thereof, and extend longitudinally in the nozzle housing from the forward end portion thereof to a point near the rear end portion thereof. The vane members are pivotable about axes disposed between the forward and rear ends thereof, and are movable between an open position wherein they are in substantially parallel relation and a closed position wherein their forward ends are in engagement with each other and their rear ends are in engagement with the adjacent inner surface of the nozzle housing. An operating mechanism is operatively connected to the vane members to move them simultaneously or individually between the open and closed positions for thrust control or thrust vector control.