337 results about "Airway" patented technology

The invention discloses an unmanned aerial vehicle route planning and dynamic management and control method for an urban low-altitude airspace, and relates to the technical field of unmanned aerial vehicle route planning and dynamic management and control, and the method comprises the steps: dividing the low-altitude airspace into a basic flight layer, a buffer anti-collision layer and an emergency guarantee layer in the vertical direction; setting different air route grades and limitation rules in different areas in the horizontal direction; generating a basic airway network skeleton and performing structure optimization; obtaining the operation state and environment updating data of the unmanned aerial vehicle; semantic annotation is carried out on each leg and node in the basic airway network skeleton, and airspace regulations, supervision rules, flight limiting areas, temporary control areas and recommended flight corridor information are embedded into a semantic layer of the airway network; and inputting the basic airway network skeleton, the semantic annotation information and the real-time monitoring data into an urban low-altitude airspace management and decision-making platform. According to the invention, cooperative scheduling and avoidance among multiple unmanned aerial vehicles are realized, and the operation efficiency of an air route network and the cooperative work capability of the unmanned aerial vehicles are improved.

The invention provides a multi-level low-altitude air route network construction method in a complex urban environment, and relates to the technical field of low-altitude air route construction, and the method comprises the steps: building a low-altitude flight rule base; performing three-dimensional discretization on the urban space, and dividing the airspace into three-dimensional grids; designing a risk assessment function R; dividing a plurality of height layers, and distributing the height layers for different types of aircrafts; constructing a multi-stage air route network; constructing an airspace three-dimensional airway model; based on the airspace three-dimensional air route model, adopting a hybrid iterative algorithm to optimize the air route planning of each height layer; performing path smoothing on the discrete path points generated by the hybrid iterative algorithm by adopting a B spline curve, and performing flight performance verification on the smoothed path to obtain a continuous flight path; and generating a low-altitude air route network according to the continuous flight path. According to the method, the defects in the aspects of complex urban environment processing, multi-source data integration, multi-level airspace division, path optimization and the like in the prior art can be overcome, so that safe, efficient and flexible low-altitude flight management is realized.

The invention provides an airway navigation system and method based on a bronchoscope view, and the system comprises a reconstruction module which obtains a bronchial tree 3D mask through CT image reconstruction; the model building module is used for obtaining a three-dimensional virtual map model comprising a 3D bronchial tree according to the 3D mask of the bronchial tree; the path extraction module is used for extracting all possible navigation paths from the bronchus entrance to the target part based on the 3D bronchus tree; the path selection module is used for selecting one navigation path as a target navigation path; the navigation module is used for guiding the bronchoscope to move along a target navigation path in the three-dimensional virtual map model based on a visual guide path; and the navigation auxiliary module maps the identified real-time part corresponding to the bronchoscope to the 3D bronchial tree for matching so as to realize dynamic synchronization of the real-time part corresponding to the bronchoscope and the target navigation path. According to the invention, reliable and convenient navigation in a complex airway network can be realized, misoperation is effectively avoided, time is saved, and operation difficulty is reduced.

The invention discloses a forming method of a stress pressurizing section of an S-shaped air inlet channel in the technical field of airplanes. The forming method comprises the following steps: 1) taking out carbon fiber / epoxy resin prepreg; 2) cleaning the surface of the mold for later use; (3) blanking; (4) inner skin paving is conducted according to the layer paving sequence; 5) conveying the workpiece into an autoclave for curing, and unbagging after curing and cooling; (6) punching and then demolding; (7) the surface of the inner skin is polished and cleaned up; (8) foam is positioned, and cap-shaped ribs are laid; (9) conveying the workpiece into an autoclave for curing, and unbagging after curing and cooling; the method comprises the following steps of (1) preparing a digital model, (2) extracting the bottom surface of a honeycomb core according to the digital model, cutting the honeycomb core with the same size by using a blanking machine, and then cutting and chamfering, (11) positioning and pre-forming the honeycomb core, (12) paving an outer skin according to a layer paving sequence, and (13) feeding a workpiece into an autoclave for curing, and demolding after curing and cooling, thereby ensuring the internal quality, the molded surface and the mechanical property of the air inlet channel.

The invention relates to an air route planning method based on an improved bidirectional fast random exploration tree algorithm, and is applied to the technical field of air route planning. The method comprises the following steps: acquiring a current node position, a target node position and terrain information of a target area of route planning; according to the terrain information, a search strategy combination of the target area is determined, the search strategy combination is used for constraining the extension direction of the air route nodes, and the air route nodes are determined based on an improved bidirectional fast random exploration tree algorithm. And determining a route node set according to the current node position, the target node position and the search strategy combination. The route nodes in the route node set are optimized, a target route is generated, and the target route is the route meeting the motion constraint of the fixed-wing aircraft. The expansion direction of the air route nodes is restrained through the search strategy combination, excessive redundant nodes caused during random sampling are avoided, and the convergence speed of air route planning can be increased. Therefore, the air route planning efficiency can be improved.

The invention provides a mine gas emission amount measuring and calculating method and system based on an ultrasonic wind speed sensor, and belongs to the field of coal mine gas monitoring. The transmitting end and the receiving end of the ultrasonic wind speed sensor are fixed to roadway sides on the two sides of a roadway respectively, and ultrasonic echo signals in the downstream direction and ultrasonic echo signals in the countercurrent direction are collected; determining ultrasonic downwind time and ultrasonic headwind time according to the ultrasonic echo signal in the downstream direction and the ultrasonic echo signal in the countercurrent direction, calculating wind speed based on an ultrasonic time difference method speed measurement principle, and transmitting the wind speed to a cloud server; introducing a wind speed correction coefficient, and calculating the air volume of each total return airway based on the wind speed, the roadway section area and the wind speed correction coefficient; the air outlet gas discharge amount is calculated based on the air volume of each total air return way and the gas amount of the corresponding total air return way, and the total gas emission amount of the mine is calculated and displayed in combination with the total gas extraction amount; the monitoring mode that a traditional wind speed sensor replaces a plane with a point is changed, and the accurate total gas emission amount is calculated.

The present invention specifically relates to a correction control method for calculating the fuel injection amount at different altitudes of a port injection engine, a pressure correction control method for optimizing the fuel injection amount under different environmental pressures, a correction curve of the intake manifold pressure and the oil rail pressure difference is creatively introduced in the model calculation, and the correction value at different altitudes and different intake manifold pressures is accurately calibrated to ensure that the air-fuel ratio can be controlled at a theoretical optimal level at different altitudes. The present invention is based on a large amount of road test data, including measurements at different ambient temperatures and different altitudes. Through big data statistical cluster analysis, it is found that the key factor affecting the accurate calculation of the fuel amount of the port injection engine is the pressure difference between the oil rail pressure and the intake manifold. Through this method, on the one hand, the fuel economy at high altitudes can be reduced, while ensuring high power output in plateau environments.

The invention belongs to the technical field of injection molding, and provides an injection molding part weld line eliminating method, electronic equipment and a storage medium, and the method comprises the steps that an injection mold simulation model of an injection molding part is constructed, and the injection mold simulation model is provided with a simulation air channel; modifying the airway data of the simulation airway to obtain a modified simulation model; performing injection molding based on the modified simulation model to obtain an injection molding part simulation result; modifying the air channel data of the injection mold based on the simulation result of the injection molding part to obtain a modified injection molding simulation mold; and based on the corrected injection molding simulation mold, obtaining an injection molding part without weld lines. According to the method, the updated simulation model can be obtained by modifying the airway data of the simulation airway of the simulation model, and the airway data of the injection mold is further modified according to the simulation result of the injection molding part, so that the generation of weld lines can be reduced or eliminated, errors and low efficiency caused by artificial experience data are reduced, the efficiency is improved, and the cost is reduced. And the product quality of the injection molded part is ensured.

The invention provides a bronchoscope real-time auxiliary navigation method and device and electronic equipment, and relates to the technical field of medical instruments.The bronchoscope real-time auxiliary navigation method comprises the steps that bronchoscope historical motion data and bronchoscope real-time operation data are obtained; analyzing the historical motion data of the bronchoscope to obtain an airway key structure, and constructing an airway three-dimensional model; and comparing the real-time operation data of the bronchoscope with the three-dimensional model to generate a real-time virtual induction pipeline. According to the invention, real-time trajectory tracking and pipeline induction technologies are combined, and auxiliary navigation support is provided for bronchoscope operation.

The invention discloses a free airway airspace strategic track conflict management method. The method comprises the following steps: S1, based on weather forecast provided by an ensemble forecast system, carrying out ensemble track prediction considering weather element time-varying characteristics; s2, measuring a conflict risk between the track points by using a conflict detection method based on a four-dimensional grid; s3, taking the revised waypoint selected by each flight and the height and Mach number at each waypoint as decision variables, and minimizing the total conflict risk of all flight paths, the total deviation of all flights and user preference flight paths, and the total unpredictability of all flights as objective functions; constructing a strategic conflict management model by taking a flight height layer constraint, a Mach number constraint and a restricted area constraint as constraint conditions; and S4, optimizing the constructed strategic conflict management model, and carrying out track adjustment according to the obtained optimized track. According to the method, a solution which has high robustness and meets the requirements of all parties can be provided for track conflict management in the strategic stage.

The utility model relates to the technical field of vehicle-mounted air conditioners, in particular to a vehicle-mounted air conditioner, which comprises an air conditioning box, a cooling unit, a heating unit, a temperature air door group and a sliding baffle group, an air inlet cavity, a mixing cavity and an air outlet cavity are arranged in the air conditioning box, and the air inlet cavity comprises a main flow channel, a cold air channel and a hot air channel. An air outlet of the total flow channel communicates with air inlets of the cold air channel and the hot air channel, air outlets of the cold air channel and the hot air channel communicate with an air inlet of the mixing cavity, an air outlet of the mixing cavity communicates with the air supply channels, airflow of the total flow channel enters the cold air channel and the hot air channel through the cooling unit, and airflow of the hot air channel enters the mixing cavity through the heating unit; the pipe wall of at least one air supply duct is opposite to the air outlet of the hot air duct and provided with a flow guide hole, the sliding baffle set adjusts the opening degree of the flow guide hole, and the temperature air door set adjusts the opening degree of the cold air duct and the hot air duct. The vehicle-mounted air conditioner can adjust the temperature difference between the air supply duct provided with the flow guide hole and the air supply duct not provided with the flow guide hole under the same temperature air door opening degree.

The invention discloses a data knowledge dual-driven unsupervised ship navigation mode identification method, and belongs to the technical field of ship traffic management. Comprising the following steps: acquiring AIS historical data sets of all ships; performing trajectory clustering based on a DBSCAN clustering algorithm of particle swarm optimization to obtain similar ship matching pairs; constructing a ship macroscopic navigation mode encoder based on a frequency domain multilayer sensor and a comparative learning method; constructing a ship microcosmic navigation mode decoder based on the hypergraph neural network; and acquiring real-time AIS data of a ship, and inputting the real-time AIS data into the trained ship macroscopic navigation mode encoder and the trained ship microcosmic navigation mode decoder to obtain intermediate features of a ship encountering scene. According to the method, the navigation mode of the ship in a habitual airway and the collision avoidance behavior mode in a multi-ship encounter scene are effectively extracted, and the limitation that the ship navigation mode recognition precision is insufficient in a single scale in the past is improved.

The utility model discloses a mine gas monitoring and early warning device, which belongs to the field of gas monitoring technology, including a mounting shell, a gas sensor is arranged in the mounting shell, a plurality of connecting tubes are arranged on the outer wall of the mounting shell, the connecting tubes are sealed and movably connected with a retractable sampling tube, a control plug for controlling the connection state between the connecting tube and the inside of the mounting shell is sealed and rotatably arranged in the mounting shell, a motor is fixedly installed at the bottom of the mounting shell, the output end of the motor is coaxially fixedly connected with the control plug, an L-shaped airway is opened in the control plug, and an exhaust fan is arranged at the output end of the airway. The mine gas monitoring and early warning device, by arranging a plurality of sampling tubes, intermittently driving the control plug to rotate by a motor, connecting different sampling tubes, and extracting the gas at the corresponding position of the sampling tube by the exhaust fan for detection, enables a single monitoring and early warning device to cover a wider detection range.

The invention discloses a low-altitude air route generation method, device and equipment and a storage medium, and belongs to the technical field of low-altitude flight. The method comprises the following steps: acquiring a three-dimensional space model and population density distribution of a target area; determining the path cost of each voxel based on the population density of each voxel at the ground projection in the three-dimensional space model, the obstacle state of each voxel and the distance between each voxel and the target facility; and taking a first position in the three-dimensional space model as a starting point, taking a second position in the three-dimensional space model as an end point, and taking the lowest sum of the path costs of voxels passing between the first position and the second position as a target to carry out path planning so as to obtain a target low-altitude airway. According to the scheme, the low-altitude aircraft can be far away from a densely populated area, avoids obstacles as much as possible and flies according to the instruction of the target facility in the target area, and meanwhile the flight efficiency and safety are guaranteed.

The invention provides a low-altitude airway flight height acquisition method and device, a storage medium and electronic equipment, and the method comprises the steps: determining the current air pressure height of an aircraft relative to a reference plane according to the current air pressure of the aircraft; according to the current geodetic height of the aircraft, the current satellite-based height of the aircraft relative to the datum plane is determined, and the current geodetic height is the height, measured through a satellite-based positioner at the current moment, between the aircraft and the geodetic ellipsoid; and performing fusion processing according to the current air pressure height and the current satellite-based height of the reference surface to determine the current fusion height of the aircraft relative to the reference surface. By uniformly setting the reference surface, acquiring the current air pressure height and the current satellite-based height of the aircraft relative to the reference surface, and performing fusion processing on the current air pressure height and the current satellite-based height, the height measurement error is effectively reduced, and the current fusion height with uniform measurement reference and higher accuracy is obtained.

The embodiment of the invention discloses a high-speed flight-oriented extraterrestrial planet atmosphere collection control device and method, and relates to the technical field of control or adjustment of non-electrical variables in aerospace equipment. A sampling port is connected with an air inlet channel, and the air inlet channel is connected with each air storage channel; the gas storage valve is mounted at the front end of the gas storage channel and used for controlling opening and closing of the gas storage channel; the air storage channels are connected with the corresponding air storage tanks, the six air storage channels and the six air storage tanks are arranged, and the adjusting devices are arranged in the air storage tanks and conduct control based on non-electric quantities such as temperature, pressure and air speed. The device is suitable for an extraterrestrial planet atmosphere collection task in a high-speed flight state, the planet spacecraft invades the planet atmosphere for multiple times, different target gases are collected in multiple times and stored and packaged respectively, extreme temperature and pressure caused by hypersonic flight can be dealt with, the state during gas collection can be kept, and the collection efficiency is improved. And the gas can be conveniently detected and utilized after being brought back to the ground.

The invention provides an upper airway segmentation and airflow simulation method based on a CBCT image. The method comprises the following steps: constructing an initial three-dimensional model; obtaining original image data and initial three-dimensional model data of the CBCT to be detected; processing the initial three-dimensional model data to obtain model parameter data; performing parameter setting on the initial three-dimensional model according to the model parameter data to obtain an airway three-dimensional model; and inputting the original image data of the CBCT to be detected into the airway three-dimensional model to obtain a speed cloud picture and a stress cloud picture. The problems that in the prior art, the imaging accuracy of the upper airway is low, and the overall change of the airway in the full-breathing process cannot be simulated are solved.

The utility model discloses a novel air passage detection device, which comprises a sensor outer cover, a sensor inner cover and a sensor outer cover, the air filtering cotton is arranged at the air inlet end of the front air channel and used for filtering air moisture and particle impurities; the sensor assembly is arranged at the gas outlet end of the front gas channel and used for detecting gas concentration and components; the sealing foam is arranged between the sensor outer cover and the sensor assembly in a filling manner and is used for enabling gas to enter the sensor assembly to prevent side leakage; the fan assembly comprises a rear air channel and is used for regulating and controlling the gas flow during preheating and working of the sensor assembly according to the gas concentration and sensitivity; the metal hose comprises a middle air passage and is used for adjusting a measurable range and a measurement angle; wherein the front air passage, the middle air passage and the rear air passage are sequentially communicated to form a detection air passage. According to the utility model, the measurable range and the measurement angle are adjusted, and the air moisture and particulate impurities are filtered by adopting the gas filtering cotton, so that the impact influence on the sensor during sampling is reduced.

According to the instruction consistency studying and judging device based on the data chain, consistency comparison between unit intentions and control instructions is achieved, potential conflicts are studied and judged, and flight safety is improved. The system comprises an air-ground data interaction cooperation system, an air-ground interconnection and instruction consistency research and judgment system, and a data link flight instruction verification and intention extraction system. The air-ground data interaction and cooperation system is used for acquiring and processing data required by system operation and providing data support for other modules; the air-ground interconnection and instruction consistency research and judgment system judges the timeliness according to the instruction type and continuously monitors the intention of the unit according to a certain strategy; the data link flight instruction verification and intention extraction system realizes real-time acquisition of activated airway and flight path profile data extracted from the airborne flight management system through a safety ground-air data link and extracts unit intention information and high-precision flight path profile information.

The invention discloses a non-control tower air route trajectory prediction method, system and device under environmental disturbance and a medium, belongs to air route trajectory prediction in the technical field of aviation, and solves the technical problem of low accuracy of air route trajectory prediction of an aircraft in a non-control tower terminal airspace in the prior art. The method comprises the following steps: designing a conditional variation auto-encoder to perform modeling on uncertainty of an external environment, and predicting an expected value of an environment factor of a future time node through Monte Carlo simulation; the method comprises the following steps: designing an air route prediction model based on a Transform architecture, taking wind direction and wind speed expectation, wind direction and wind speed time sequence data and air route time sequence position data after future P seconds as input, processing the input data through a self-attention mechanism, capturing spatio-temporal characteristics, and finally outputting position, speed and course information of an aircraft at a future time node. By combining the airway data, the environment data and the future environment prediction information, richer environment information is provided for the airway prediction model, so that the accuracy and robustness of airway prediction are improved.

The invention provides a flight section flight flow statistical method based on a system flight path and a flight plan, and the method comprises the steps: reading original business data through a business data interface, and carrying out the analysis to obtain flight path data and flight plan data; performing track association on the track data and the flight plan data to obtain space position information and flight plan data of the aircraft, storing the space position information and the flight plan data in a database, extracting corresponding business data from the space position information and the flight plan data, and recording the business data in the database; the extracted service data at least comprises spatio-temporal information of all flight paths passing through a flight path section and a fixed point; and determining a flow statistical result according to the extracted service data, and displaying the flow statistical result. The invention further provides a corresponding system. According to the method provided by the invention, accurate tracking of the real-time position of the air route is realized through fusion processing and judgment of the flight path and the flight plan data; and in combination with setting of the auxiliary points, the flights actually flying over the specific flight section can be more accurately screened out, the judgment accuracy is improved, and the accuracy of flow statistics of the flight section is ensured.

The invention relates to the technical field of artificial intelligence, in particular to an urban air traffic-oriented mixed reality airway dynamic generation method, which realizes fusion of an aircraft image and an actual environment image by constructing an augmented reality navigation system and utilizing a sensing device group, an ultra-wideband positioning base station network and a ground computing device, thereby realizing the dynamic generation of a mixed reality airway. A dynamic three-dimensional city scene is presented, meanwhile, the position and attitude information of the aircraft is obtained, environment perception of the aircraft is achieved, an augmented reality navigation system is optimized, the attitude detection precision is improved, the airspace congestion distribution condition in the future time period is predicted, a dynamic variable height layer is generated, the flight path is optimized, and the flight energy consumption is reduced. The problem of multi-target optimization of a three-dimensional air route is solved through a hybrid optimization algorithm, the optimal air route is dynamically generated in a city three-dimensional scene, augmented reality visual display is achieved, a pilot is assisted in recognizing the relative position relation between the aircraft and the environment, the power consumption of augmented reality display equipment is reduced, and the positioning precision is improved.

The invention relates to a dynamically adaptive airway stabiliser (1) comprising: - a flow channel (2) for guiding the expired air of a patient, wherein the flow channel (2) has three successive flow channel portions (3, 4, 5) and the first flow channel portion (3) is in the form of a mouthpiece; - a measuring unit (9) for determining a measured value of the volumetric breathing flow in the second flow channel portion (4); - an adjustment element (12) for changing the flow resistance of the third flow channel portion (5); - an evaluation and control unit (11) for evaluating the determined measured value and for controlling the adjustment element (12).

The invention relates to the technical field of image processing, in particular to an anesthesiology department airway intubation image recognition method based on artificial intelligence. The method comprises the following steps: acquiring an airway CT image of a patient at double view angles, constructing a multi-curvature airway model and generating a corresponding image; correcting the model image in combination with the inherent distortion parameter of the lens to obtain a distortion corrected image; secondly, the influence of different curvatures on distortion is quantified under a multi-curvature distortion correction image, and a curvature-direction-distortion correction factor mapping relation is generated; acquiring a current airway image in real-time intubation, extracting curvature features by performing pixel-level matching with the distortion correction image, associating the curvature features with the mapping relation, and determining a distortion correction index corresponding to the current airway image; and finally, performing double correction on the current airway image by combining the lens distortion parameter and the distortion correction index, and generating a high-credibility airway correction image for subsequent image recognition.

The present application discloses a variety of airway sampling devices and associated methods. According to an embodiment, an airway sampling device for taking a sample from a subject's airway is provided with a handle to be gripped by a user when taking the sample and a sampling head carried by the handle, the sampling head comprising a cavity with an opening for entry by the sample and a sample collection membrane located within the cavity for receiving the sample.

The invention provides a low-altitude traffic operation control method and system based on moving block. The method comprises the following steps: layering an airspace according to aircraft type performance and service types for the vertical take-off and landing aircraft, and distributing corresponding entering and leaving areas according to flight height layers of the aircraft; quasi-moving block is introduced into a low-altitude traffic system, an air route network and operation rules are designed, a free area-buffer area-block area three-level space structure of an aircraft is dynamically constructed according to the state of the aircraft, when the front aircraft occupies a certain block area, the first area in front of the block area is a buffer area, and the second area in front of the block area is a block area. The second zone in front of the blocking zone is a free zone, the aircraft flies in the free zone according to the current speed, and the aircraft is selected for braking in the buffer zone according to the braking distance obtained through calculation. According to the method, the braking curve is generated by dynamically dividing'free area-buffer area-block area 'and combining the braking performance, so that the safety redundancy is increased, and the safety and airspace utilization rate is improved.

The invention belongs to the technical field of wind tunnel simulation, and provides multi-environment simulation wind field test equipment which is of an axial symmetry structure and comprises a pressure stabilizing cabin, an inner cabin and an outer cabin, the pressure stabilizing cabin and the inner cabin are installed in the outer cabin in an up-down stacking mode, and an airflow circulation channel is formed between the pressure stabilizing cabin and the inner cabin and the outer cabin; two groups of expandable horizontal air passage roller shutters are arranged in the inner cabin, when the two groups of horizontal air passage roller shutters are in an expanded state, the two groups of horizontal air passage roller shutters and two oppositely arranged cabin walls in the inner cabin are enclosed to form a rectangular horizontal air flow channel, and the rectangular horizontal air flow channel can be matched with the air flow circulation channel to provide a horizontal linear flow wind field; and when the two groups of horizontal air passage roller shutters are in a storage state, the air flow circulating passage can be matched with the inner cabin and the pressure stabilizing cabin to provide a vertical air flow field or a rotating air flow field. The simulation requirements of various complex wind environments can be effectively met in a limited space range.

Disclosed are a method of determining branching levels of a plurality of airway branch segment regions of an airway region, the method comprising: determining branching levels of a plurality of first airway branch segment regions of an airway region included in a medical image from a root to a first order based on anatomical structure information; and determining branching levels of a plurality of second airway branch segment regions of the airway region from a bottom level to the first order.

The invention discloses an APU air inlet air door system. The length of an air inlet air door can be increased on the basis that an opening of an aircraft skin is not changed. The APU air inlet air door system comprises an air channel, an air inlet and an air outlet, the air inlet air door is used for opening or closing the air channel; the air inlet air door comprises an air door fixed section and an air door moving section capable of stretching out and drawing back relative to the air door fixed section, and when the air inlet air door is closed, the air door moving section can stretch out and draw back relative to the air door fixed section. When the air inlet air door is opened, the actuator enables the air door moving section to retract relative to the air door fixed section so as to shorten the overall length of the air inlet air door, and when the air inlet air door is opened, the actuator enables the air door moving section to extend relative to the air door fixed section so as to increase the overall length of the air inlet air door.

A back projection screen that allows the awake patient to move the head and neck freely and yet be able to look at the images that are displayed during surgery, but at the same time allows a surgery crew, in particular an anesthesiologist, to watch the airway passage and the consciousness state of the patient, and to monitor signs including color of the lips, eyes movement, verbal responses, skin sensitivity, and the like, as well as to maneuver for intubation or other procedures without removing the screen during surgery. The back projection screen allows also eye contact and / or face to face interaction, physically or virtually, with the surgeon or other members of the surgery team for effective communication and is suitable for easy cleaning or disinfection from bacteria or viruses as required by operating rooms.