Abstract: An apparatus, system, and method for deployment of an electronic warfare (EW) asset are provided. The system includes a projectile launching device capable of launching a projectile round. An EW asset is detachably carried by the projectile round. A deployable parachute is attached to the EW asset, wherein the EW asset is configured to be suspended from the parachute when the EW asset is detached from the projectile round. The related method is used for suppression or obscuration of enemy counterfire radar (CFR) system by initiating an EW effect by the EW asset as the EW asset floats towards a ground surface.

Abstract: 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.

Abstract: Systems and methods for deploying smart munitions may provide targeting metadata generated by surveillance networks to munitions deployment and guidance systems for smart munitions. Targeting metadata may be received by a conduit system and automatically processed to generate guidance and deployment data actionable by a munitions deployment platform.

Abstract: The present invention relates to projectiles and munitions, and more specifically to such in flight. More particularly the present invention relates to projectiles and munitions in flight equipped with one or more image sensors adapted for acquiring image data of the environment surrounding the projection or munition in flight. The present invention further relates to systems and methods for correcting or stabilizing motion effects and artifacts present in the image data related to the movement or motion of the projectile or munition in flight, including spin or rotation of the projectile or munition.

Abstract: A method for launching a round from an airborne platform, receiving a plurality of RF signals at the round, determining an amount of time between a first and second received RF signal, where the second signal is a multi-path signal and the first signal is a direct path signal. An altitude of the round is determined based on the delay between the first and second received signal and aligning the round's flight path with an initial velocity vector of the aircraft platform to reduce dispersion. The round can include a plurality of sensors for detecting the RF signals. The second received RF signal may be a multi-path signal having been reflected off of the earth's surface or another object on the earth's surface. The altitude of the round can be determined using the known altitude of the airborne platform, the delay of time between the first and second received signals, and the speed of light.

Abstract: A firearm having an aim-compensation system. The firearm includes a barrel and is configured to fire a projectile. The firearm further includes a sensor disposed on the firearm that determines an orientation of the firearm. The firearm further includes a control unit that determines an intended point-of-aim of the firearm and an actual expected point-of-aim of the firearm based on the orientation of the firearm, and the control unit determines a differential of the intended point-of-aim and the actual expected point-of-aim. The firearm further includes a muzzle device arranged on the barrel which is in communication with the control unit, wherein, when the projectile is fired, the muzzle device directs a gas toward the projectile in an amount and direction based on the differential determined by the control unit so as to exert an aerodynamic force on the projectile to alter the trajectory of the projectile towards the intended point-of-aim.

Abstract: A method for measuring a distance to a target in a multi-user environment by means of at least one sensor, comprising: irradiating the environment by means of a series of radiation pulses, wherein series of radiation pulses are emitted at a determined repetition rate and with a determined random delay; collecting pulses that are reflected or scattered from the environment to at least a detector connected to at least one chronometer; assigning a timestamp at every detected pulse on the detector; subtracting the added delay from every registered timestamp coming from the chronometer, the result corresponding to the time of arrival; determining the statistical distribution of said time of arrival; determining the distance to the target from said statistical distribution.

Abstract: The various implementations described herein include methods, devices, and systems for determining locations of an electronic device. In one aspect, a method is performed at a computing system having one or more processors and memory. The method includes obtaining device identification information for the electronic device; broadcasting a request based on the device identification information that the electronic device be enabled to transmit or reflect location information using a radar technique; receiving a signal from the electronic device, the signal indicating a location of the electronic device using a radar technique; and determining the location of the electronic device based on the received signal.

Abstract: A method of using an unmanned aerial vehicle (UAV) to guide a target includes receiving a location signal from one or more sensors of the UAV, receiving an input signal from a user device for guiding the target that defines at least one of a travel route, a permissible region, or an impermissible region, comparing the location signal to the input signal to determine whether the target is deviating from the travel route, exiting the permissible region, or entering the impermissible region, and initiating, via the UAV or an attachment mechanism coupled between the UAV and the target, a deterrent mechanism in response to determining that the target is deviating from the travel route, exiting the permissible region, or entering the impermissible region.

Abstract: A soft-kill countermeasure system utilizing a tracking radar to enhance existing countermeasures and enable new countermeasures to be utilized to combat the ever evolving and increasing sophistication of threats. The use of the tracking radar may further allow for immediate threat defeat confirmation which may allow for rapid or immediate redirection of the countermeasure system to address additional simultaneous threats.

Abstract: A relay communication station is remotely controlled without increasing communication traffic of a feeder link of communication to be relayed between a communication relay apparatus such as a HAPS located in an upper airspace and a communication network on the ground side or on the sea side.

Abstract: 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.

Abstract: Systems and methods for deploying smart munitions may provide targeting metadata generated by surveillance networks to munitions deployment and guidance systems for smart munitions. Targeting metadata may be received by a conduit system and automatically processed to generate guidance and deployment data actionable by a munitions deployment platform.

Abstract: The system and method of attitude determination by pulse beacon and extremely low cost inertial measuring unit. A pulse beacon is used to generate a plurality of pulses detected by a detector or receiver located on the rear of a projectile such that direction of arrival can be determined. A synchronized clock proved for velocity and range information. Altitude can also be determined and may use an altimeter or the like. The use of a low cost IMU is possible with internal calibration by the system. Real-time attitude information provides for correction for crosswind and other drift enabling the system to have less down range dispersion.

Abstract: Techniques are provided for geolocation of a radar emitting source. A methodology implementing the techniques according to an embodiment includes calculating time difference of arrival (TDOAs) of ground emitter radar pulses, within a dwell period, between two long baseline interferometer (LBI) antennas. The TDOA calculations are based on a precision estimate of the time of arrival of the radar pulses. The method further includes calculating an LBI phase wrap disambiguation factor based on (1) the TDOAs, (2) an average of frequencies of the radar pulses within the dwell period, and (3) an average of phase shifts of the radar pulses between the LBI antennas within the dwell period. The method further includes mapping a curve of points onto the surface of the earth based on an LBI cone angle calculation employing the LBI phase wrap disambiguation factor. The curve of points is associated with a geolocation of the ground emitter.

Abstract: A method of using an unmanned aerial vehicle (UAV) to guide a target includes receiving, via the UAV, a signal indicative of a target area for guiding the target, determining an indicator based on a location of the UAV and/or a location of the target area while the target is in motion, and performing, via the UAV, an operation in response to the indicator.

Abstract: A targeting system for guidance correction of a projectile along a flight path toward a target. The targeting system includes seeker/guidance system mounted on the projectile which controls guidance of the projectile along the flight path toward the target. A remote fire control system receives and displays a survey image of a battlefield and enables an operator to mark location coordinates of the target in the survey image. Based on the location coordinates, the fire control system defines a reference image and transmits the reference image and location coordinates to the seeker/guidance system for use in guiding the projectile toward the target. If the target moves as the projectile travels toward the target, the remote fire control system enables the operator to update the location coordinates and transmit only an offset of the coordinates to the seeker/guidance system which then adjusts or corrects the flight path of the projectile.

Abstract: Systems and methods for deploying smart munitions may provide targeting metadata generated by surveillance networks to munitions deployment and guidance systems for smart munitions. Targeting metadata may be received by a conduit system and automatically processed to generate guidance and deployment data actionable by a munitions deployment platform.

Abstract: A missile system wherein a missile carrier delivers a plurality of submissiles over a target area. A passive or active scanner on the missile carrier repeatedly scans the target area as the missile carrier descends by drag brake over the target area. Submissile assignment to identified targets is performed at a selected altitude. A data processor controls the launching of the submissiles and actively guides the submissiles for substantial portions of their flights via optical fiber or wire links separately connecting each submissile to the missile carrier. Each submissile includes either passive or active identification devices enabling the data processor to track the submissiles individually. A missile assignment table stores a correspondence between identified targets and submissiles assigned thereto. Submissile assignment is effected on the basis of the strength of target signature.

Abstract: Upon loss of a valid track of a remotely-sensed command guided vehicle, a delta actuator command including an orthogonal component orthogonal to the straight-line path is generated as a next sample of a time-based alternating signal. The time-based delta actuator command is added to the nominal actuator command, which is “held” upon loss of valid track, to maneuver the vehicle in first and second orthogonal directions back and forth across the straight-line path to increase an area of vehicle motion relative to the tracker's FOV. This increases the likelihood of recapture of the vehicle given vehicle motion after track is broken. The penalty is a reduction in energy efficiency. In certain embodiments, this is accomplished without modification to guidance system hardware or the existing tracking valid or invalid guidance algorithms.

Abstract: Systems, methods, and apparatus for a virtual transponder utilizing inband commanding are disclosed. A disclosed method comprises transmitting, by a hosted payload (HoP) operation center (HOC), encrypted hosted commands to a hosted receiving antenna. The method further comprises transmitting, by the hosted receiving antenna, the encrypted hosted commands to a payload antenna on a vehicle. Also, the method comprises transmitting, by a host spacecraft operations center (SOC), encrypted host commands to the vehicle. Additionally, the method comprises reconfiguring a payload on the vehicle according to unencrypted host commands and/or unencrypted hosted commands. In addition, the method comprises transmitting, by the payload antenna, payload data to a host receiving antenna and/or hosted receiving antenna. Also, the method comprises transmitting encrypted host telemetry to the host SOC, and transmitting encrypted hosted telemetry to the host SOC.

Abstract: A vehicle-mounted millimeter-wave communication device for performing communication while temporally changing a communication direction by using an antenna unit capable of changing directivity includes: a detection unit configured to detect a direction of a communication partner present around a host vehicle; and a communication control unit configured to perform control such that communication is performed, in which a longer communication time is set for the direction of the communication partner than another direction. The communication control unit preferably performs control that sets a long communication time for the direction of the communication partner in the case where the type of the content of communication with the communication partner is related to control of a vehicle, and in the case where the volume of the communication with the communication partner is not less than a threshold value.

Abstract: The invention relates to a method for detecting and tracking targets in a series of successive images, said method comprising limiting the number of spots which are the subject of simultaneous tracking or false leads. The operation of the tracking module is thereby improved without having to increase a detection threshold of said spots. The detection threshold can even be reduced, such that the detection haul is increased and the tracking of each target is more continuous, without the probability of false alarms itself being increased.

Abstract: An aircraft flight data monitoring and reporting system is provided. The system comprises: an onboard flight data recording and reporting unit; a zero-configuration service discoverer; a remote base station; a remote flight data monitoring storage and analysis unit; a wireless communication link; and a network, the wireless communication link and network for communications between the aircraft flight data monitoring and reporting system and each of the base station and the flight data monitoring storage and analysis unit, wherein the zero-configuration service discoverer facilitates auto-discovering between the flight data recording and reporting unit and the base station.

Abstract: Provided is a remote control system which controls a work machine from a remote place in order to improve safety and workability and to reduce fatigue of an operator. In the remote control system which controls the work machine from a remote place, a seat where the operator sits is driven to be inclined in conjunction with the machine, so that inclination information of the machine at the time of traveling is provided to the operator to be sensible and the safety and the workability are improved. On the other hand, a large inclined vibration caused by the work of the machine is not transferred to the operator since an inclination amount of the seat is kept when the machine is not traveling, so that the fatigue of the operator is reduced.

Abstract: The application relates to a wireless rotating instrumentation package for collecting data from a spinning rotor head of a rotary wing aircraft. The application also relates to a method of wirelessly collecting data from a spinning rotor head of a rotary wing aircraft.

Abstract: Systems and methods are disclosed herein for determining relative orientation between a self-propelled device and a mobile computing device by utilizing the asymmetric radiation pattern of communication link emissions by the self-propelled device. Upon establishing the communication link, the self-propelled device may perform a spin, thereby enabling the self-propelled device and/or the mobile computing device to detect radiated pulses due to the asymmetry in the link. A direction may be determined based on such pulses, which may be utilized for calibration purposes.

Abstract: A method is presented by which a missile body roll angle relative to earth coordinates can be deciphered onboard the missile from ground-data relayed to the missile during flight The present method comprises of a horizontal pair and a vertical pair of antennas on the ground and an up-down pair and a right-left pair of antennas onboard the missile. The ground to pairs signals are sinusoidally amplitude modulated in 90° phase difference between the two pairs, causing the transmitted wave polarity to rotate in the modulation frequency. A reference pulse is transmitted from the ground whenever the wave polarity vector crosses a prescribed ground antenna direction, thereby enabling the missile to measure its body up, down, right and left directions relative to earth up, down, right and left directions and to further respectively align them together.

Abstract: Embodiments of the disclosure provide a display apparatus, a display apparatus fault analysis system and a display apparatus fault analysis method. The display apparatus fault analysis system comprises a display apparatus and a server. The display apparatus comprises: a display chip configured to generate a target video or a target image according to a display instruction; an image capturer configured to capture the target image; a detection unit configured to, upon receipt of a fault detection instruction, send the display instruction to the display chip, compare the target image frame or the target image with a predetermined reference image to obtain a difference between the target image frame or the target image and the predetermined reference image, and generate a fault code based on the difference; and a communication module configured to transmit the fault code to a server.

Abstract: The invention relates to a rotationally stabilized projectile (1) for launching from a barrel, which projectile (1) comprises a front projectile part (22), a rear projectile part (20) comprising a rotating band (4), and an intermediate projectile part (21) comprising a freely rotatable middle section (2) arranged with guide wings (3) for improving the gliding capability and guidance capability during the gliding phase and end phase of the projectile. The guide wings (3) are arranged extensibly on the freely rotatable middle section (2), and the intermediate projectile part (21) also comprises a regulator device (14) for regulating the rotation of the middle section (2). The invention also relates to a method for guiding a rotationally stabilized projectile.

Abstract: A location and guidance system including a flying craft and a reception device. The flying craft includes a plurality of antennas distributed around its fuselage and emitting rearwards with rectilinear polarization, the emitted signals being specific to each antenna, the positions and the dimensions of the antennas being configured such that the body of the flying craft avoids by masking for at least one antenna the reflections of the signal emitted by this antenna off the ground or off lateral obstacles whatever the position of the flying craft. The reception device is placed substantially on a trajectory axis of the flying craft and configured to be oriented to sight the rear thereof and includes at least two single-pulse antennas operating in orthogonal planes determines a position of the flying craft by analyzing the emitted signals received by the antennas of the reception device.

Abstract: A counter-flying object system that includes a sensor array including an active sensor for detecting and tracking the flying object. An interceptor missile launcher for launching an interceptor to intercept the flying object, wherein upon launching of the interceptor, the sensor array determines the location of the interceptor and sends the object's and interceptor's locations to a control system. The control system provides mission data to the interceptor based on the object's and interceptor's locations for guiding the interceptor toward the flying object and activating a fragmentation warhead on or in the vicinity of the flying object when a lethality criteria is met.

Abstract: After a vehicle has entered a curve, a deviation (Sch) between a target turning state quantity Td and an actual turning state quantity Ta is computed. In a stage in which Sch does not reach a predetermined value after the vehicle has entered the curve, the possibility of the vehicle traveling in the curve is judged to be low, and the reliability of the curve information Rc, Pc is judged to be low. In this case, a determination for prohibiting execution of control (So=0) is made. In a stage after Sch has reached the predetermined value, the possibility of the vehicle traveling in the curve is judged to be high, and the reliability of the curve information Rc, Pc is judged to be high. In this case, a determination for permitting execution of the control (So=1) is made. Deceleration control is started and executed only when a control start condition is satisfied, and the determination for permission is made.

Abstract: A system and method of guiding a remote aerial vehicle toward a designated target includes an imaging sensor which generates sequential video images of the target area from the remote aerial vehicle and transmits the images to a control center via the video portion of a communications data link. The control center receives and displays the plurality of video images on a video display. An image selection signal is generated at the control center and transmitted to the remote aerial vehicle for commanding the imaging sensor to continuously transmit one of the sequential video images. A target designation signal, corresponding to the azimuth and elevation of the desired target on the continuously displayed video image, is generated and transmitted via a command portion of the data link to the remote aerial vehicle. The target designation signal is processed and an updated target position is computed to compensate for time delays.

Abstract: A weapon and weapon system, and methods of manufacturing and operating the same. In one embodiment, the weapon includes a warhead having destructive elements. The weapon also includes a folding lug switch assembly that provides a mechanism to attach the weapon to a delivery vehicle and is configured to close after launching from the delivery vehicle, thereby satisfying a criterion to arm the warhead. The weapon still further includes a guidance section including an antenna configured to receive mission data before launching from the delivery vehicle and further configured to receive instructions after launching from the delivery vehicle to guide the weapon to a target.

Abstract: An unmanned aerial vehicle with a camera and conventional sensors, where the processor navigates the vehicle based at least in part on the image data and the sensor data. A method for navigating an unmanned aerial vehicle where a processor navigates the vehicle based at least in part on image data corrected by traditional sensor data.

Abstract: A projectile and associated method are provided for seeking a target that has been laser designated even though the projectile does not include a laser receiver. A projectile includes an aerodynamic body and a GPS receiver configured to receive GPS signals indicative of a location of the aerodynamic body. The projectile also includes a radio receiver configured to receive radio signals from an offboard laser receiver that provide information relating to a location of the target based upon laser designation of the target. Further, the projectile includes a processor configured to direct flight of the aerodynamic body toward the target based upon the location of the aerodynamic body as determined from the GPS signals and the location of the target based upon the information provided by the offboard laser receiver.

Abstract: A method for guiding a gun-fired or mortared round towards an intended target. The method including: capturing image data from an image pick-up device during a descent of the round; transmitting the image data to a control platform remotely located from the round; transmitting guidance information to the round from the remote platform based on the captured image data; varying a flight path of the round based on the guidance information to guide the round towards its intended target.

Abstract: A system for guiding a gun-fired or mortared round towards an intended target, the system including a round having: a forward facing image pick-up device for capturing image data; a first transceiver; guidance device for varying a flight path of the round; and a first processor. The system further including a control platform remotely located from the round, the control platform having: a second transceiver; a second processor; an input device; and a display. Where the first processor transmits image data from the image pick-up device through the first transceiver to the second processor through the second transceiver, the second processor transmits guidance information from the second transceiver to the first processor through the first transceiver and the first processor controls the guidance device based on the guidance information to guide the round towards the intended target.

Abstract: A method for determining a position of a device in a reference coordinate system. The method including: receiving, at the device, less than all of GPS signals necessary to determine the position of the device in the reference coordinate system; transmitting a signal from a? illuminating source defined in the reference coordinate system; receiving the signal at a cavity waveguide disposed on the device; and determining the position of the device in the reference coordinate system based on the GPS signals and the signal received in the cavity waveguide. The signal received in the cavity waveguide can also be used to confirm a position determined by the GPS signals.

Abstract: An inductive or capacitative programming of a projectile is disclosed. A waveguide is used for the programming, the electromagnetic field being concentrated in the waveguide. The used programming unit includes at least one waveguide which is preferable located and/or integrated in the region of the muzzle, for example in front of the muzzle brake. A transmission coupler for the transmission is fed by a signal generator. The information relating to the projectile is modulated to the carrier frequency in the modulator. A reception coupler integrated on/in the projectile is electrically interconnected to a store or processor in the projectile. The reception coupler receives the modulated signal and transmits it to the processor which is where the eventual programming takes place.

Abstract: A sensor system uses ground emitters to illuminate a projectile in flight with a polarized RF beam. By monitoring the polarization modulation of RF signals received from antenna elements mounted on the projectile, both angular orientation and angular rate signals can be derived and used in the inertial solution in place of the gyroscope. Depending on the spacing and positional accuracies of the RF ground emitters, position information of the projectile may also be derived, which eliminates the need for accelerometers. When RF signals of ground emitter/s are blocked from the guided projectile, the sensor deploys another plurality of RF antennas mounted on the projectile nose to determine position and velocity vectors and orientation of incoming targets.

Abstract: A method for onboard determination of a roll angle of a projectile. The method including: transmitting a polarized RF signal from a reference source, with a predetermined polarization plane; receiving the signal at a pair of polarized RF sensor cavities positioned symmetrical on the projectile with respect to a reference roll position on the projectile; measuring a difference between an output of the pair of polarized RF sensor cavities resulting from the received signal to determine zero output roll positions of the projectile; and comparing an output of the pair of polarized RF sensor cavities at each of the zero output positions to determine when the projectile is parallel to the predetermined polarization plane. The method can also include analyzing an output of at least one third sensor positioned on the projectile to determine whether the roll angle position of the projectile is up as compared to the horizon.

Abstract: Some embodiments relate to a method of controlling a flight of a flight vehicle according to a first mode of operation and changing the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation. Other embodiments relate to a flight-control system for a flight vehicle configured to control a flight of a flight vehicle according to a first mode of operation and to control the flight of the flight vehicle according to a second mode of operation to use less energy than the first mode of operation. Other embodiments relate to a control actuation system configured to control positions of aerodynamic elements in a flight vehicle in response to commands from a guidance system according to a first mode of operation and to change the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation.

Abstract: A hostile missile is identified as being of a type which maneuvers aerodynamically within the atmosphere when it performs an exoatmospheric maneuver which significantly changes its specific energy. When the determination is made that the hostile missile is an atmospheric maneuvering missile, the hostile missile is engaged with an interceptor which is guided toward a predicted intercept point (PIP) assuming horizontal hostile missile flight at an altitude above a specified minimum altitude.

Abstract: A system is provided for the remote control of a spinning projectile, the system comprising: a polarized radiation source emitting polarized radiation wherein commands are encoded; a projectile round; a polarized radiation receiver disposed on the projectile round and configured to receive the polarized radiation; and a projectile steering mechanism, the mechanism directing movement of the projectile according to the commands communicated by means of rotation of polarization of the polarized radiation source.

Abstract: A lightweight, man-portable weapon delivery system includes a fuselage, and first and second wings mounted to opposing sides of the fuselage. The system includes an electric motor for driving a propeller for providing thrust to propel the system. The electric motor is mounted to the fuselage, and configured to be remotely started by a user. The system includes an imaging device mounted to the system and configured to capture images of a theater of operations of the system. The system includes a communication circuit in communication with the imaging device and configured to transmit the images from the imaging device to the user for viewing the theater of operations of the system for remotely steering the system. The communication circuit is configured to receive commands from the user for steering the system into the target. The system includes a payload configured to store the ordnance.

Abstract: A method for engaging a target missile includes sensing the position of the target and of an interceptor missile, and determining time-to-go to intercept and direction of thrust of the interceptor. A one-step intercept solution is determined based on position estimates of the target and the interceptor and is used to iteratively estimate at least two components of a three-dimensional unit thrust vector, and apply updated guidance commands to the interceptor. A system for thrust vector control of an interceptor against a target missile includes a processor for receiving sensed target signals, determining a one-step initial solution to produce time-to-go and current direction of thrust of the interceptor, iteratively estimating at least two components of a three-dimensional unit thrust vector, and producing a guidance vector for application to the interceptor.

Abstract: A method for commanding an attitude change of a boosting missile to tend to maintain good communication link quality includes the step of precalculating attenuation of a link between the boosting missile and a ground station in the presence and absence of multiple missile plumes. If the actual link attenuation is less than the precalculated attenuation in the absence of multiple missile plumes, no attitude change is commanded. If the actual link attenuation exceeds the precalculated value, the actual link attenuation is compared with the calculated attenuation in the presence of multiple missile plumes. If the calculated multiple plume RF attenuation is less than the actual link attenuation, the attenuation is deemed to be caused by some factor other than multiple plume attenuation, and produces a flag for commanding a change in attitude.

Abstract: A method for correcting a trajectory of terminally guided ammunition is provided. In order to achieve a high probability of hits, in particular when firing in bursts (continuous fire, rapid single shot fire), it is provided that every individual ammunition is addressed separately. The “imprinting” is performed based on the beam rider guidance principle of terminally guided ammunition. Every individual ammunition reads only the guidance beam identified for this ammunition and can, using additional information, determine its absolute roll attitude in space in order to achieve the proper triggering of the correcting propulsion unit.