9 results about "Infrared radiometer" patented technology

The invention belongs to the technical field of flight trajectory optimization, and particularly relates to a multi-algorithm trajectory optimization method for a hypersonic gliding aircraft. The method comprises the following steps: S1, setting each optimization algorithm to adopt a unified initialization parameter and a unified to-be-optimized parameter; s2, calculating an attack angle at the current flight speed according to an attack angle piecewise function; s3, calculating the height, the speed, the voyage, the heat flow, the dynamic pressure and the overload at each moment according to the motion equation of the aircraft; s4, infrared radiation energy at the terminal moment is determined according to the infrared radiation calculation model, penalty quantities caused by the height error, the voyage error and the speed error at the terminal moment are superposed, and final energy is obtained; step S5, calculating optimal parameters to be optimized by using each optimization algorithm by taking the minimum final energy as an optimization target and taking the condition that heat flow, dynamic pressure and overload are not higher than set values as constraint conditions; and S6, selecting an optimal solution from the optimization algorithms. According to the invention, the calculation efficiency and robustness are improved.

The application discloses an infrared radiometer rotational flow purging device and a design method, and relates to the technical field of aero-engine monitoring. The device comprises a purging airflow sleeve, an air inlet, a rotational flow generating pipe, a first pipe opening, a second pipe opening, an optical sensing element, and rotational flow generating holes. The open end of the purging airflow sleeve is opposite to a monitoring heat source. The rotational flow generating pipe is coaxially arranged in the purging airflow sleeve. The rotational flow generating pipe has the first pipe opening facing the monitoring heat source and the second pipe opening extending out of the purging airflow sleeve. The middle section of the rotational flow generating pipe is used for arranging the optical sensing element for receiving infrared radiation. The pipe body of the rotational flow generating pipe is provided with a plurality of rotational flow generating holes between the position of the optical sensing element and the first pipe opening. The airflow is separated from the large-size pollution particles at the rotational flow generating holes and enters the rotational flow generating pipe to form rotational flow. The application separates and blocks the pollutants before the optical sensing element through the multiple airflows containing rotational flow, fundamentally reduces the lens fouling rate, and improves the measurement stability and reliability.

The invention discloses an infrared radiometer rotational flow purging device and a design method, and relates to the technical field of aero-engine monitoring, the infrared radiometer rotational flow purging device comprises a purging airflow sleeve, a rotational flow generating pipe, a gas inlet, a gas outlet, a gas outlet, a gas outlet and a gas outlet, the rotational flow generating pipe is provided with a first pipe orifice facing a monitoring heat source and a second pipe orifice extending out of the blowing airflow sleeve, the middle section of the rotational flow generating pipe is used for arranging an optical sensing element for receiving infrared radiation, and a plurality of rotational flow generating holes are formed in the pipe body of the rotational flow generating pipe between the optical sensing element and the first pipe orifice; airflow is divided at the rotational flow generation hole and separated from large-size contaminant particles and enters the rotational flow generation pipe to form rotational flow, pollutants are effectively separated and blocked in front of an optical sensing element through multiple airflows containing rotational flow, the lens scaling rate is fundamentally reduced, and the measurement stability and reliability are improved.

This invention discloses a method for solving the spectral emissivity of a wall surface based on a GRU network with an attention mechanism, comprising the following steps: dual-temperature calibration of an infrared radiometer using a reference blackbody; measuring the wall surface target using the calibrated infrared radiometer and calculating the target reference spectral radiance using the measurement results; constructing a GRU network model with an attention mechanism and training the model using the target reference spectral radiance data after removing atmospheric interference-related bands; using the trained network to predict and correct the mid-wave infrared and long-wave infrared regions, and solving the wall surface emissivity using the corrected spectral radiance. This method for solving the spectral emissivity of a wall surface, by constructing a recurrent neural network model, can correct the target reference spectral radiance, effectively eliminating the influence of atmospheric absorption on the emissivity solution and improving the accuracy of the wall surface spectral emissivity solution.

The present application relates to the technical field of rocket engine, and particularly relates to a ground engine exhaust flame infrared radiation end-to-end prediction method based on a neural network, which comprises the following steps: step one: calculating a rocket engine exhaust flame infrared radiation dataset; step two: constructing an asymmetric convolutional encoder and a parallel deconvolutional decoding module; step three: taking a type spectrum parameter dataset as an input dataset; after processing exhaust flame infrared radiation intensity distribution cloud data, taking the exhaust flame infrared radiation intensity distribution cloud data together with exhaust flame infrared radiation integral intensity data as an output dataset; step four: dividing the input dataset and the output dataset into a training set and a test set; training and testing the neural network; step five: inputting the type spectrum parameters into the neural network to calculate exhaust flame infrared radiation data of a rocket engine to be tested. The present application solves the problems of a large number of calculation links, long calculation time and difficulty in meeting massive calculation requirements of the existing rocket engine exhaust flame infrared radiation calculation method, and is suitable for rocket engines.

The utility model discloses a device for on-orbit calibration of an infrared radiation measuring instrument, which belongs to the technical field of thermal metrology and comprises an artificial black body used for generating thermal radiation with set intensity; the cooling pipe type light path system is used for transmitting radiation emitted by the artificial black body; comprising at least one low-temperature refrigeration device used for maintaining a low-temperature environment of the light path system; the off-axis ellipsoidal reflector is used for converging and reflecting radiation to the infrared radiation measuring instrument; the light path switching mechanism is used for changing the pose of the off-axis ellipsoidal reflector and realizing light path switching among different infrared radiation measuring instruments; and the control system can control the radiation intensity of the artificial black body and the action of the light path switching mechanism. By integrating the artificial black body, the cooling pipe type light path system, the off-axis ellipsoid reflector, the light path switching mechanism and the control system, the infrared radiation measuring instrument is accurately calibrated, and the problem that the measurement precision is reduced due to the fact that the on-orbit time is too long is solved.

This invention relates to the field of infrared interference smoke screen technology, and particularly to a composite detection device and method for the infrared transmittance of interference smoke screens in a vacuum. The device includes: a vacuum tank, a vacuum pump, an electronic vacuum gauge, a temperature sensor, a humidity sensor, a target temperature simulation module, a simulation module controller, an interference smoke screen sample module, an ignition head, an igniter, a Fourier transform spectrometer, an infrared radiometer, an infrared thermal imager, a three-way solenoid valve, pipes, a filter, a flow meter, a computer module, a programmable logic controller (PLC), and a power supply. The Fourier transform spectrometer, infrared radiometer, and infrared thermal imager are used as composite transmittance testing methods to achieve the effectiveness of interference smoke under composite testing technology. A testing device with the same target temperature simulation module and the same testing environment is constructed to ensure consistency in the parameter acquisition environment. By combining actual transmittance detection data and measurement data from the multi-layer filter membrane kit, the material, particle size, and shape adjustment direction of the interference smoke screen are determined. The computer module and PLC control the device's operating procedure, improving the device's automation.

This invention discloses an on-orbit radiometric calibration method for the thermal infrared channel of a meteorological satellite, comprising the following steps: selecting a suitable working time for the field calibration test based on satellite transit information and weather conditions at the calibration site; using an unmanned surface vessel (USV) carrying an infrared radiometer CE312, releasing the USV via a dock approximately two hours before satellite transit, and navigating on a pre-set route on the lake surface. This invention significantly saves manpower, material resources, and financial investment by utilizing the USV to automatically observe and acquire water surface radiation brightness temperature; by combining this with the acquisition of encrypted atmospheric profile data from radiosondes, the calibration frequency can be greatly increased, and calibration accuracy can be further improved; by comparing the entrance pupil brightness temperature information obtained from the thermal infrared channels of various satellites, the spatial distribution of brightness temperature during the synchronous test period at the calibration site and the degree of influence of cloud and weather conditions on the lake surface can be analyzed, providing significant reference for the selection of the synchronous testing area.

The invention relates to the technical field of infrared remote sensing, in particular to an infrared spectrum collaboration device based on an electric control baffle, which comprises a Fourier infrared imaging spectrometer, the Fourier infrared imaging spectrometer comprises an interferometer, an area array detector, a laser and a laser detector, and the infrared spectrum collaboration device further comprises the electric control baffle, and the electric control baffle is movably arranged in front of a movable mirror of the interferometer and is configured to switch the mode of the infrared spectrum collaboration device through a moving-in or moving-out state. By adding the electric control baffle in the Fourier infrared imaging spectrometer, the Fourier infrared imaging spectrometer, the infrared radiometer and the infrared camera can be rapidly switched, efficient infrared spectrum collaboration is achieved, infrared image information of a target and spectral information with high spectral resolution can be more effectively obtained at the same time, and the method is suitable for large-scale popularization and application. Rapid and flexible switching of a single instrument among multiple working modes is realized, and high efficiency, high precision and system integration are considered.