Abstract: An improved stable approach monitor (SAM) system provides an audible advisory to a pilot when an aircraft is on a final landing approach. More specifically, the SAM system compares a measured airspeed of the aircraft to a predetermined flap placard speed. If the measured airspeed exceeds the predetermined flap placard speed then the improved SAM system provides an audible advisory indicating the airspeed of the aircraft is too fast. Advantageously, this audible advisory should prevent the pilot from attempting to deploy the flaps at an excessive airspeed and in turn focuses the pilot's attention on the problem at hand, which would be to reduce the airspeed of the aircraft. Once the airspeed is equal to or below the predetermined flap placard speed, the improved SAM system may provide another audible advisory informing the pilot to commence deployment of the flaps.

Abstract: A method for aiding the management of an aircraft flight according to an active flight plan receiving a control clearance transmitted at a current time includes a step of computing a reception flight plan based on the said control clearance, a step of storing the said reception flight plan in a memory space dedicated to the said reception flight plan. The method also includes, prior to the step of computing a reception flight plan: a step of determining the time, called the recognition time, assumed to have to elapse between the current time and a time at which the said control clearance is assumed to be recognized; a step of attribution, to the said control clearance, of a destination flight plan as a function of the recognition time, the said destination flight plan being the temporary flight plan when the recognition time is included in a first time slot and the destination flight plan being a secondary flight plan when the recognition time is included in a second time slot longer than the first time slot.

Abstract: A control circuit for operating the lights of a vehicle. In one embodiment, the rear lights of the vehicle are controlled by the control circuit. The control circuit illuminates two or more of the vehicle lights in a common pattern to indicate a specific vehicle operation. When the vehicle simultaneously performs two operations, the controller may transition the lights to illuminate in different patterns to clearly indicate the separate vehicle operations. The controller may further provide for adjusting the light intensity of one or more of the lights. The lights may be adjusted to have a similar intensity to prevent confusion when the different lights are used in combination to indicate a vehicle operation.

Abstract: Technologies are described herein for providing a list of alternate diversion airports that is based on up-to-date and accurate information received electronically at the aircraft. The list of alternate diversion airports may be prioritized according to a normal mode when the aircraft is operating under normal flight conditions, or a non-normal mode when the aircraft is operating in an emergency situation. In one aspect of the present disclosure, a system includes an alternate airport diversion planner program that generates the list of alternate diversion airports based on diversion planning information received at an aircraft. The alternate airport diversion planner program subsequently receives periodic updates of the diversion planning information, which is used to update the list of alternate diversion airports that is provided to a pilot of the aircraft.

Abstract: An on-engine data storage device for a gas turbine engine includes a housing, an interface device, and a memory device. The interface device can communicate with a peripheral device. The memory device is mounted within the housing and is operable to store engine data related to the gas turbine engine.

Abstract: The Surface Hold Advisor Using Critical Sections is a system and method for providing hold advisories to surface controllers to prevent gridlock and resolve crossing and merging conflicts among vehicles traversing a vertex-edge graph representing a surface traffic network on an airport surface. The Advisor performs pair-wise comparisons of current position and projected path of each vehicle with other surface vehicles to detect conflicts, determine critical sections, and provide hold advisories to traffic controllers recommending vehicles stop at entry points to protected zones around identified critical sections. A critical section defines a segment of the vertex-edge graph where vehicles are in crossing or merging or opposite direction gridlock contention.

Abstract: Disclosed are systems and methods for driver performance assessment and improvement. The systems and methods may be: active for warning purposes only; passive for monitoring purposes only; and active and passive. Any of the foregoing system and methods may be cooperative as well.

Abstract: A brake monitoring system is described for use on aircraft having carbon brakes. The system displays the number of times the brakes have been applied in a preselected counting interval such as during each takeoff and landing cycle. By raising the pilot's awareness of the number of times the brakes have been applied, a more efficient brake use is encouraged in view of the knowledge that carbon brake wear is substantially a function of the number of applications rather than the total energy that is converted thereby. Additionally, the monitoring system provides an indication of the temperature of the brakes which encourages the pilot to maintain a minimum temperature therein beyond which wear is reduced.

Abstract: Methods and apparatus are provided for transmitting incursion alerts to a plurality of in-flight aircraft in accordance with preconfigured pilot preferences. The apparatus comprises a data store module containing data sets against which the pilot preferences are evaluated during flight, including weather, airspace and flight restrictions, ground delay programs, and air traffic information. The apparatus further includes a flight path module containing route and position information for each aircraft. An incursion alert processing module evaluates the flight path, data store, and pilot preferences and generates incursion alerts which are transmitted to each aircraft during flight, either directly or via ground based dispatchers or flight operations personnel.

Abstract: An aircraft hover system for enabling an aircraft to hover at a target spatial location represented by GPS location coordinates. The hover system includes a display screen rendering a display including live video feed of the terrain below the airborne aircraft, a first mark overlaying the video feed, the first mark representing the current position of the aircraft relative to the terrain, and a perimeter surrounding the first mark, the portion of the terrain within the perimeter being substantially magnified compared to that of the terrain outside of the perimeter. The hover system is configured such that, as the aircraft approaches the target spatial location, the distance between the first mark and a second mark on the display gradually decreases until and finally the first and second marks coincide; the second mark representing the target spatial location.

Abstract: A system and method for a terrain awareness warning system. The system includes a radar system configured to transmit a first radio frequency wave and receive a second radio frequency wave and a display for receiving a display signal representative of a terrain and a terrain awareness warning system. The terrain awareness warning system includes a forward-looking terrain logic configured to be in communication with the radar system and to process a terrain signal from the radar system.

Abstract: Collision with ground/water/terrain and midair obstacles is one of the common causes of severe aircraft accidents. The various data from the coremicro AHRS/INS/GPS Integration Unit, terrain data base, and object detection sensors are processed to produce collision warning audio/visual messages and collision detection and avoidance of terrain and obstacles through generation of guidance commands in a closed-loop system. The vision sensors provide more information for the Integrated System, such as, terrain recognition and ranging of terrain and obstacles, which plays an important role to the improvement of the Integrated Collision Avoidance System.

Abstract: An emergency descent system for turbocharged piston engine powered aircraft. The flight management system is configured to challenge the pilot after a period of inactivity. Acknowledgment from the pilot resets the timer for subsequent challenge. Lack of timely pilot response sets off an alarm sequence. Lack of response to the alarm sequence sets off emergency descent by way of control by the flight management system of rate of descent, heading, ground track, and engine power by adjustment to the wastegate to the turbocharger. The control by the flight management system may incorporate direct control of the aircraft airspeed in the descent, and that may be enhanced by engine power adjustments. Upon reaching a selected target altitude, the aircraft engine power may be restored via the adjustment of the wastegate controller. At any time, when the pilot regains useful consciousness, the entire emergency descent sequence may be interrupted and normal control restored by the pilot.

Abstract: A device for the coherent management of data deriving from different surveillance systems of an aircraft includes: a flight management system, the function of which is to assist the crew in following a flight plan of the aircraft and an associated trajectory; a surveillance system, the function of which is to detect any obstacles in proximity to the aircraft; a warning management system, the function of which is to detect abnormal situations and to display for the crew, where appropriate, warnings, such as potentially critical alarms or non-critical alerts, and the associated procedures to be followed when such exist; in which said flight management system, said surveillance system and said warning management system are interconnected and cooperate so that at least the warning management system has access to the flight plan of the aircraft, and is configured to display for the crew a summary of the situation when the surveillance system detects an obstacle that the aircraft should avoid according to the fligh

Abstract: A monitor on-board an aircraft which uses radio altitude measurements as the basic observable altitude during runway approach. The basic concept utilizes the aircraft's navigation system, which includes means to store and retrieve radio altitude thresholds as a function of the distance along the desired path from the runway thresholds. These threshold functions are determined in advance based on a radio altitude reference which is defined as the expected radio altimeter measurement that would be made if the airplane were exactly on the desired reference path. Vertical containment monitoring is achieved by comparing the radio altitude measurement to computed thresholds for both too high and too low. During the approach, an annunciation message can be generated if the radio altitude measurement is above or below the threshold limits.

Abstract: A system having a first motion sensor configured to sense movement of an object on a first side of a portal, the object including an RFID tag, a first RFID reader being activated by the first motion sensor when the first motion sensor senses movement of the object, the first RFID reader reading the RFID tag, a second motion sensor configured to sense movement of the object on a second side of the portal and a second RFID reader being activated by the second motion sensor when the second motion sensor senses movement of the object, the second RFID reader reading the RFID tag, wherein, when one of the first and second motion sensors sense movement of the object, the other one of the first and second motion sensors is deactivated for a predetermined period of time.

Abstract: Systems and methods for selectively altering a ground proximity warning message. In an embodiment, a ground proximity warning system for a flight vehicle includes a processor that is configured to generate a look-ahead envelope that defines a region extending outwardly from the flight vehicle and to generate a terrain proximity message when the defined region intersects a terrain feature. An interface device is coupled to the processor that is operable to configure the system in a first operating mode wherein the generated terrain proximity message is selectively suppressed, and a second operating mode wherein the terrain proximity message is not suppressed.

Abstract: A method and a device for activating an automatic piloting mode of an aircraft are disclosed. The device can include means for engaging an automatic pilot mode, when (i) the current distance of the aircraft with respect to a reference position on the ground belongs to a determined distance range, and (ii) the current height of the aircraft is at most equal to a reference height associated to the automatic pilot mode.

Abstract: The present invention is a communication system for implementation on-board an aircraft. The communication system includes an Audio Control Panel (ACP) including a first input device associated with an installed component and a second input device associated with an uninstalled component. The communication system further includes a Radio Interface Unit (RIU) which is communicatively coupled to the ACP. The communication system further includes an Engine Indicating and Crew Alerting System (EICAS) which includes a Display Management Computer (DMC), the EICAS being communicatively coupled to the RIU and an Aircraft Personality Module (APM) of the communication system. The DMC may be configured for evaluating an input device status (generated based upon an input received via the second input device) against an APM configuration file, and based upon said evaluation, providing an aural and/or visual alert to a user that an input device associated with an uninstalled component has been activated.

Abstract: System for detecting wake turbulence (SDWT) of a first aircraft, which can be embedded onboard a second aircraft, comprising: first means (DET1) for determining the roll (Roll2) of the second aircraft; second determination means (DET2) of an envelope (CRollRef) of reference roll curves which is representative of a wake turbulence created by the first aircraft; means (COMP) for comparing, over a sliding window, the roll (Roll2) of the second aircraft and the envelope (CRollRef) of reference roll curves; and alarm means (AL) for forewarning the pilot of the second aircraft of the detection of wake turbulence of the first aircraft when the said comparison is below a resemblance threshold (SS).

Abstract: The invention relates to a helicopter, comprising a tail jib (12), at least one distance sensor (16.1) attached to the tail jib (12) for capturing a distance (A) from an object (18) that may be present in a surrounding area of the tail jib (12), and an electric evaluation unit (20), which is connected to the distance sensors (16) and equipped to calculate a position of the object (18) relative to the helicopter (10). According to the invention, a collision avoidance apparatus is provided, which is designed to avoid a collision of a person with the tail jib (12).

Abstract: A automation equipment control system comprises a general purpose computer with a general purpose operating system in electronic communication with a real-time computer subsystem. The general purpose computer includes a program execution module to selectively start and stop processing of a program of equipment instructions and to generate a plurality of move commands. The real-time computer subsystem includes a move command data buffer for storing the plurality of move commands, a move module linked to the data buffer for sequentially processing the moves and calculating a required position for a mechanical joint. The real-time computer subsystem also includes a dynamic control algorithm in software communication with the move module to repeatedly calculate a required actuator activation signal from a joint position feedback signal.

Abstract: Methods for flying multiple aircraft in a predetermined formation in which a relative navigation grid is emitted from at least one of the aircraft, a spatial relationship is calculated based on the emitted relative navigation grid, and a relative position of at least one aircraft is altered to position the aircraft in the predetermined formation when the spatial relationship does not conform with the predetermined formation.

Abstract: A flap advisory system provides an advisory to a pilot informing that a speed of the aircraft should be attended to because of a current or desired flap setting. More specifically, the flap advisory system compares a measured airspeed of the aircraft either directly to a flap placard speed or to a marginal speed range set below the flap placard speed for a given flap setting. If the measured airspeed is determined to be excessive then the system provides an advisory indicating the airspeed is too fast. Further, the system may provide an advisory when a movement of a flap handle is detected such that continued movement of the flap handle would place the flaps in a setting that is inappropriate for the measured airspeed.

Abstract: A method is provided for assisting in rejoining a vertical descent trajectory that an aircraft is assumed to have to follow, using a flight management system FMS embedded onboard the aircraft, and includes the following steps: calculation of a vertical deviation VDEV, in the vertical plane, between the aircraft and the vertical descent trajectory, and comparison between the vertical deviation VDEV and a predetermined deviation threshold SVDEV; when the vertical deviation VDEV reaches the deviation threshold SVDEV, a step during which the activation of an optimized mode for catching up on the vertical descent trajectory is authorized; if the optimized mode for catching up on the vertical descent trajectory is activated, piloting of the aircraft by the flight management system FMS in optimized catch-up mode, that is to say at minimum thrust with a target rejoining speed in level VCRP and a target rejoining speed in downward trajectory, the target rejoining speed in level VCRP being equal to the maximum L/D rati

Abstract: A process for generating computer flight plans on the Internet with the elements of: a raw XY&Z database of chart data, a data base containing aircraft data, a software system to create VFR, IFR and Road charts, an Internet web site accessible by a Client computer, a software system which computes flight plans requested by the Client computer, a software system which allows for navigation data and aircraft editing by means of the Internet web site Client computer, and a software system which allows for outputting flight plans by means of the Internet web site Client computer. A alternate embodiment includes wherein said elements include a local area network consisting of a service and number of local Client computers or an Intranet network which is connected by means other than wires such as infrared or radio signals.

Abstract: The device (1) includes means (2, 3, 4) for observing the overall conditions of the aircraft and for determining whether the lateral behavior thereof is normal.

Abstract: Systems, computer program products, and methods for displaying navigation performance based flight path deviation information during the final approach segment to a runway and during landing of non-precision flight modes are provided. Improved graphical depictions of navigation performance based flight path deviation information provide pilots and flight crew members with clear, concise displays of the dynamic relationship between ANP and RNP, mode and aspect of flight and related procedures, intersecting flight paths, and current actual flight path deviation from a predefined flight path during the final approach segment to a runway and during landing. For example, an enhanced IAN display may include NPS-type deviation scales to show RNP/ANP relationships and predetermined RNP markers to alert the pilots and flight crew members that the FMC has transitioned from an NPS display for RNAV (LNAV/VNAV) flight procedures to an enhanced IAN display for a non-precision (non-xLS) approach and/or landing.

Abstract: An information presentation device includes: a directional information obtaining element for obtaining directional information based on a signal from an enhancement device for safety or comfort of a passenger of a vehicle; an information presentation controller for generating a driving signal based on the directional information; and a stimulation element including multiple vibrators for generating a traveling wave of vibration in an in-vehicle element. A directionality of the traveling wave corresponds to the directional information. The stimulation element transmits the traveling wave to the passenger so that the passenger perceives the directionality of the traveling wave.

Abstract: An assisted piloting method for an aircraft having at least two engines (2, 3) includes monitoring a set of parameters (Ng, T4, Tq) of the engines. A first limit indicator (10) displays information relating to a value of a limiting parameter of the engines. The limiting parameter is the parameter (Ng, T4, Tq) of the engines that is the closest to its limit. An assisted piloting mode is activated during which each parameter (Ng, T4, Tq) is maintained below a predetermined threshold whenever the first limit indicator is not in a position to display the information.

Abstract: A voice-activated command and control system for remotely-controlled vehicles includes a voice-activated control module, a microphone, and a verbal or visual feedback indicator such as a speaker. The operator speaks instructions into the microphone to activate control functions on the vehicle. Confirmation of receipt and/or status of the verbally commanded instructions are sent back to the operator such as spoken through the speaker. The microphone and speaker can be implemented, for example, either in a headset (with a microphone and earphones) worn by the operator, or in the hand-held controller for the vehicle. The system can be alternately implemented without the speaker or other feedback element.

Abstract: A system configured for viewing meteorological data and generating said alerts in an aircraft. The system includes a navigation screen configured to display meteorological data in a monitoring plane at a determined altitude (Zs), and an altitude determination unit configured to determine the current altitude (Zp) of the aircraft. A processor is configured to determine the difference in altitude (Dz) between the aircraft's current altitude (Zp) and the altitude of the monitoring plane (Zs). The determined altitude difference (Dz) is compared with a first predetermined deviation threshold (S1), and a first alert (A1) is emitted under conditions in which the altitude difference (Dz) attains or exceeds the first predetermined deviation threshold (S1) and the altitude difference (Dz) diverges.

Abstract: The present invention relates to a method of flying safely and at low altitude in an aircraft, in which method unsafe relief (R0) of terrain is determined as is the position of at least one high point (4, 5) representing an obstacle (4?, 5?) overlying said unsafe relief (R0). A main volume (V0) is added to said unsafe relief (R0), the main volume being defined between a main volume base (2) placed on the unsafe relief (R0) and an envelope (1), thereby obtaining safe relief (R1) for overflying that contains at least said unsafe relief (R0) and said main volume (V0), said main volume base (2) having an area (2?) defined by a closed peripheral curve (3) resting on said unsafe relief (R0), said envelope (1) being generated using a moving segment (S) of predetermined length (L) extending from said high point (4, 5) to a second point (3?) moving along said peripheral curve (3).

Abstract: Systems and methods for tracing aircraft vortices. One method includes directing a tracer from a first aircraft into a vortical flow generated by the first aircraft. The method can further include detecting a characteristic corresponding to the presence of the tracer directed into the vortical flow. Based at least in part on the detected characteristic, the method can include directing the flight of the first aircraft, or a second aircraft following the first aircraft, or both.

Abstract: The device for checking speed intended for an aircraft ready to land on deck on a moving vehicle, the aircraft having a current vertical speed, called the first speed, and a threshold value of vertical downward speed relating to the vertical speed of the moving vehicle, called the “low threshold”, the ship having an absolute vertical speed, called the second speed, comprises a display and means for receiving data originating from the aircraft, notably its vertical absolute speed. The device includes a calculator making it possible to generate on the display a graduated speed gauge including a fixed cursor indicating the first vertical speed and a second moving cursor indicating the speed of the ship, a third moving cursor indicating the low threshold, the graduation being centered around the value of the first vertical speed.

Abstract: Disclosed are a method and device for attenuating vertical turbulence encountered by an aircraft during flight. Incorporated into the method and device is a wind determination device, which is used to determine a vertical wind component existing outside the aircraft. A severity level determination unit is used to determine a severity level of the vertical wind component determined by the wind determination device. A control unit calculates at least one control order based on the vertical wind component determined by the wind determination device. In addition, the control unit determines the actual existence of activation conditions determined according to the severity level determined by the severity level determination unit. Upon verifying the activation conditions, the control unit transmits the control order to at least one actuator of the at least one controllable movable member.

Abstract: The present invention provides methods and apparatuses that reduce pilot workload and increase the performance and efficiency of the pilot's control of the aircraft. The present invention comprises methods and apparatuses for determining the presence and type of an emergency condition, for example by detecting corresponding sensor outputs or by accepting input from a pilot or a combination thereof; and then responding to that emergency by initiating a pre-determined set of actions specific to the determined emergency. Embodiments of the invention can include the ability to monitor engine conditions as well as control electrical functions such as the fuel boost pump, alternator field, battery contactor and other important electrical devices. Some examples described below assume a single-engine piston aircraft for ease of illustration. The invention can also be applied to multi engine and turbine powered aircraft as well.

Abstract: A method of alerting an occupant of a seat assembly of the occurrence of a triggering event comprising the steps of monitoring for the occurrence of the triggering event, vibrating the seat assembly and/or probing the seat assembly.

Abstract: A method and apparatus for searching and generating trajectory content in a navigation device are provided. The method includes establishing a predetermined search region from a current position; extracting information about first parcels included in the established search region and information about second parcels including information about links of specific trajectory content; and determining whether the specific trajectory content is included in the established search region by comparing the information about the first parcels with the information about the second parcels.

Abstract: A system according to aspects of the present invention includes a processor, a user interface (including a display) in communication with the processor, and a memory in communication with the processor. The processor executes instructions stored in the memory to present a first symbol on the display of the user interface that indicates the bearing to an off-scale vehicle, and to present a second symbol on the display that indicates the path of travel of the off-scale vehicle. The present invention provides a more accurate representation of the bearing and track of off-scale traffic compared to conventional traffic display systems.

Abstract: The invention relates to a method for automatic detection of turbulence by a second aircraft, by information exchange between the second aircraft and at least a first aircraft. The first aircraft has means for transmitting information and the second aircraft has means for receiving the information transmitted by the first aircraft. The method includes the identification of information about turbulence liable to be encountered by the second aircraft, by analyzing the information received from the first aircraft. An alarm is activated on the basis of the turbulence information.

Abstract: The present invention relates to a device and methods for filtering anti-collision alerts for aircraft having a locating system charting the position of the aircraft and estimating the precision of its position. A navigation system of the aircraft calculates at least the actual speed of the aircraft, the speed instruction and a first deviation between the instruction and the actual speed, and the deviation being compared with a first reference overshoot threshold. An anti-collision system generates alerts. An alarms manager of the aircraft centralizes the alerts transmitted by the terrain anti-collision equipment of the aircraft to the crew. The alerts each posses a coding of the danger level, and the danger levels form part of a first predetermined set. The alert filter according to the invention filters sets of alerts according to the coding of their danger level.

Abstract: The present invention relates to a method of protecting an aircraft in approach by signalling against the risks of collision with the terrain in steep-sided environments, in order to avoid unwanted warnings emanating from the clearance sensors of the onboard TAWS system while protecting the aircraft when it fails to observe the published procedure, and this equally in a landing procedure and in a take-off procedure. The method includes conferring an additional function on the conventional TAWS functions, specific to the detection of the potential risks of collision of the aircraft with the terrain when following procedures of reduced protection corridor type, and this without modifying either the logics or the characteristics of the clearance sensor or sensors as currently defined in the TAWSs of the state of the art.

Abstract: There is provided a personal navigation system, including a head-mounted orientation sensor, a coordinate position sensor, a head-mounted display, and a processor receiving an input from the head-mounted orientation sensor and an input from the coordinate position sensor and providing a visually sensible output for displaying on the head-mounted display.

Abstract: The invention describes a method and device for preventing useless alarms generated by an anticollision system on board an airplane and according to which the duration (dcap) of a phase of capture of a setpoint altitude (Zc) by the airplane is between a predetermined minimum execution deadline (dmin) and a predetermined maximum execution deadline (dmax).

Abstract: Aircraft attitude systems are provided. A representative aircraft attitude system includes: a detection system operative to determine an attitude of an aircraft in which the detection system is mounted; a warning system operative to alert a pilot when the attitude of the aircraft corresponds to at least one predefined attitude parameter from a set of predefined attitude parameters, the predefined attitude parameters including pitch, bank and yaw; and a recovery system operative to provide progressive flight control positioning directives to the pilot for returning the aircraft to a flight attitude within the predefined attitude parameters.

Abstract: A system indicating to a pilot that an aircraft has passed the limit-point of success of a standard vertical avoidance maneuver is disclosed. To determine the limit-point, the system monitors a penetration of a model of the terrain being flown over into a first protection volume linked to the aircraft and configured so as to model a standard vertical avoidance maneuver path executed without delay. To determine disengagement azimuth sectors, the system monitors the penetrations of the model of the terrain being flown over into a second protection volume with large azimuth aperture, linked to the aircraft and configured so as to contain the limit-point protection volume and, for the various azimuths covered, paths of a composite maneuver beginning with change-of-heading maneuvers with which to reach the azimuth concerned and continuing with the standard terrain vertical avoidance maneuver.

Abstract: Disclosed is a method and device, which provide an enhanced ability to monitor the navigation of an aircraft during a phase of flight in which the aircraft is close to the ground in which the aircraft uses positional information supplied by a satellite positioning system for the navigation. A display screen is used to display a first characteristic sign representing a selected setpoint value for a height parameter of the aircraft. The display screen also displays a second characteristic sign representing a current auxiliary value expressed in the form of an achievable height parameter. An alert is emitted when the second characteristic sign is determined to be within a predetermined height value of the first characteristic sign, and the alert is shown in visual format on the display screen. An alarm is also emitted following a predetermined time after the alert is emitted, if the setpoint value is not replaced by a new setpoint value.

Abstract: A method and device for determining critical buffeting loads on a structure of an aircraft is disclosed. The device (1) comprises means (2, UC) implementing a semi-empirical method for determining the critical loads generated by some buffeting on the structure of the airplane.

Abstract: The invention relates to a device for monitoring obstructions for an aircraft including data storage, an anticollision device and viewing devices, wherein the monitoring device comprises a detector to detect in real-time obstructions, of terrain type and of human constructions type, in a close environment of the aircraft in a flight situation, a sensor to identify the obstructions at risk calculating identification parameters, a circuit to calculate criticality of the obstructions, a display to display both the obstructions with the identification and criticality parameters of the obstructions, and a generator of alerts to describe the situation according to a combination of the identification and criticality parameters. One or more embodiments of the invention is a monitoring system adapted for zones close to the aircraft and in the flight zones not visible to the crew. One or more embodiments of the invention applies particularly to helicopters executing low-altitude flights.