The invention relates to a rudder control assembly (2) for a missile (1), the rudder control assembly (2) comprising: a first actuator (20) connectable to a rudder (16), which first actuator (20) is configured to steer the rudder (16) when connected to the rudder (16); a coupling element (22) for connecting the first actuator (20) to the rudder (16); and a second actuator (24) for locking the rudder (16) in a fixed position, wherein the second actuator (24) comprises a locking element (26), which is configured to lock and unlock the rudder (16) and which locking element (26) also is configured to connect the first actuator (20) with the rudder (16) by means of the coupling element (22) when unlocking the rudder (16). The invention also relates to a missile (1), comprising a rudder control assembly (2). The invention also relates to a method, performed by a control device (100), for testing a first actuator (20) of a rudder control assembly (2) for a missile (1). The invention also relates to a computer program (P) and to a computer-readable medium.

A computer implemented method is provided for in-flight trajectory steering a vehicle by an optimal path to either a preplanned or in-flight commanded destination. The method includes incorporating realistic environmental physical constants; setting initial angle of attack (AoA) and initial AoA rate; incrementing flight AoA; measuring operation parameters; establishing a flight trajectory; calculating an optimal trajectory; comparing flight trajectories; and commanding flight control. The plurality of physical constants include for gravity and atmospheric conditions, the latter typically provided in tabular form, the flight AoA increments from the initial AoA and any prior increments. The plurality of operation parameters of the vehicle includes pressure, velocity and flight path angle. The flight trajectory denotes the path of the vehicle to its destination based on the operation parameters using the physical constants. The optimal trajectory is based on with altitude (based on physical constants) and velocity (based on measured operation parameters) of the vehicle. The flight trajectory is compared to the optimal trajectory as a steering correction by altering the flight AoA. The vehicle's flight control involves executing the steering correction at the flight AoA.

Provided is a tailstock type vertical take-off and landing unmanned aerial vehicle and a control method thereof. The unmanned aerial vehicle is mainly composed of a fuselage, wings, ailerons, empennages, an elevator, a rudder, an engine, an attitude adjustment nozzle, a landing gear, and the like. The wings are symmetrically arranged on both sides of the middle of the fuselage; the ailerons are hinged to the trailing edges of the wings on the both sides; the empennages are located at the tail of the fuselage, and a form of vertical empennages+horizontal empennages or V-shaped empennages can be used; the elevator and rudder are hinged to the trailing edges of the empennages; the engine is arranged at the tail of the fuselage for producing main thrust.

A course correction system for a projectile can include a pre-steering trajectory determination module. The pre-steering trajectory determination module can be configured to receive a series of possible trajectories from an estimation module including a physical model defining trajectory as a function of gravitational pull and one or more launch variables, and receive a sensor data from one or more on-board sensors of the projectile. The pre-steering trajectory determination module can also be configured to reduce the possible trajectories from the estimation module to one or more refined trajectories using the sensor data, and output the one or more refined trajectories.

A system and method to aid in guidance, navigation and control of a guided projectile including a precision guidance munition assembly is provided. The system and method obtain raw position data during flight of the guided projectile, the raw position data including a plurality of position data points from the guiding sensor for determining positions of the guided projectile, establish a window including a portion of the plurality of position data points, smooth the portion of the plurality of position data points in the window, and determine a reduced noise position estimate of the guided projectile, based, at least in part, on the smoothed portion of the plurality of position data points in the window. The system and method may determine a velocity estimate of the guided projectile and predict an impact point of the guided projectile relative to a target.

A system including a system controller configured to transmit a first amount of commands in order to produce a desired effect by a group of actuators acting in combination. A system controller configured to control a group of at least two actuators in order to produce at least one combined effect, wherein the number of actuators is greater than or equal to the number of effects. A system controller configures to independent and variable bandwidths or responses of the desired effects produced by the actuators acting in combination.

In a guiding device, a communication device receives a signal containing detection data of a target, and a processing unit. In the processing unit, a course setting section sets a flight course for a lofted flight based on the detection data, and a guiding section determines a progressing direction based on the flight course and outputs a guidance signal containing the progressing direction. The course setting section sets a first flight course when the flying object is launched. Also, the course setting section changes the first flight course to a second flight course based on the detection data after launching of the flying object.

A method and system for nonlinear trajectory shaping guidance law capable of providing a robust guidance solution suitable for multi-mission, multi-mode operations. The nonlinear trajectory shaping guidance law offers (1) a dual layered GL gains calculation: (i) NTS time varying adjustment accounting for engine on/off and L/D variation and (ii) general explicit guidance algorithm based sub-optimal fixed-gain selection while still maintaining its trajectory shaping capability for short range to go missions; (2) flight path angle (FPA) command tracking and following to ensure a high probability of target destruction while minimizing collateral damages; (3) high precision impact point calculation factoring in target location errors or motion and maneuvering uncertainties; and (4) heading error angle minimization.

The invention presents a system optimizing control coefficients of flight object under complex environmental effects using hybrid Fuzzy Logic and PID variant controller. The proposed system includes: target module, seeker module, guidance module, control module, dynamics module. The fuzzy logic controller is applied to determine the parameters coefficients of a proportional integral derivative (PID) based on the effect of these coefficients on the system response. The control module is less affected by the accuracy of the mathematical model and can perform well in environments with impact noise.

A rescue system includes a wearable article, such as a wristband, which includes a radio frequency identification (RFID) tag, a radio frequency (RF) beacon, and a power supply. One or more RFID readers (collectively, an RF network) are located on a vessel, the RFID readers being configured to communicate with the RFID tag. Should the RF network detect a passenger overboard event, a modular rocket system is deployed. The modular rocket system comprises a guidance module, the guidance module including a guidance system for guiding the modular rocket system toward a target. A flight control module is removably attached to the guidance module, said flight control module including a plurality of airfoils. A flotation module is removably attached to the flight control module, said flotation module including a flotation device. A rocket motor module removably attached to the flotation module, said rocket motor module including a rocket motor configured to propel the modular rocket system.