1396 results about "Space environment" patented technology

The invention relates to a temperature measurement and calibration platform in space vacuum environment. The temperature measurement and calibration platform is favorable for realizing the simultaneous calibration of contact type temperature measurement and non-contact type temperature measurement, so the temperature measurement and calibration platform is served for heat vacuum and heat balance experiments of spacecrafts such as satellites, spaceship and the like. The temperature measurement and calibration platform comprises a constant temperature bath, wherein a double-sub-cavity vacuum cavity, the double-sub-cavity vacuum cavity comprises a first vacuum cavity body and a second vacuum cavity body, the first vacuum cavity body and the second vacuum cavity body are connected with a vacuum pumping device through a three-way valve, standard temperature indicator sensors are respectively arranged on the outer wall of the first vacuum cavity body and on the outer wall of the second vacuum cavity body, the standard temperature indicator sensors are connected with a temperature secondary meter, a laser light path reflecting device is arranged in the vacuum cavity of the first vacuum cavity body for calibrating a non-contact type temperature measuring system based on the tunable diode laser absorption spectrum technology, and the vacuum cavity of the second vacuum cavity body is used for accommodating a temperature sensor for calibrating a contact type temperature measuring system adopting the temperature sensor.

The invention relates to an image characteristic matching method. The image characteristic matching method includes the steps of pre-processing an obtained CCD (charge coupled device) image; extracting characteristic points of the pre-processed CCD image by a SURF operator and conducting matching image by the quasi epipolar line limit condition and minimum Euclidean distance condition to obtain the identical point information; establishing affine deformation relation between the CCD images according to the obtained identical point information; extracting the characteristic points of a reference image by Harris corner extracting operator, projecting the characteristics points to a searching image by the affine transformation to obtain points to be matched; in neighbourhood around the points to be matched, counting the correlation coefficient between the characteristic points and the points in the neighbourhood and taking extreme points as the identical points; and using the comprehensive results of twice matching as the final identical point information. According to the method of the invention, can match surface images of deep-space stars obtained in a deep-space environment is utilized for imaging matching to obtain high-precision identical point information of CCD images, so that the characteristic matching is realized.

The invention relates to the obstacle avoidance path planning technical field and provides an intelligent shopping cart, a planning method and device of the travelling path of the intelligent shopping cart. The planning method of the travelling paths of the intelligent shopping cart includes the following steps that: a starting point and a target point of the intelligent shopping cart are determined; the starting point and the target point are connected with each other through a straight line in a space environment, so that a virtual connection line in the space can be obtained; all vertices of each of obstacles through which the virtual connection line pass, the starting point and the target point are connected with each other through straight lines, and all visual lines are reserved, wherein the visual lines are line segments that do not pass through any obstacles; each reserved visual line is communicated with each other so as to form paths to be selected; and the length of each path to be selected is calculated, and a shortest path to be selected is determined as the travelling path of the intelligent shopping cart. With the planning method and device of the travelling path of the intelligent shopping cart of the invention adopted, the planning efficiency of the travelling path of the intelligent shopping cart can be improved.

The invention discloses a high-temperature high heat flow simulator for spacecraft vacuum heat tests in a space environment simulating chamber. The simulator mainly comprises infrared light arrays, a high-temperature insulation component unit, moving units, a temperature measuring unit and a temperature controlling unit. A plurality of infrared lights in the infrared light arrays are provided with reflective screens, the infrared lights are arrayed and combined to form the infrared light arrays according to requirements of heat flux density and uniformity, baffles surround the periphery of the infrared light arrays, high-temperature multi-layer insulation components are mounted among the infrared lights, a mounting baseplate and the baffles, and a high temperature region is limited in region formed through specimen irradiated face and the infrared light array high-temperature insulation components. According to the high-temperature high heat flow simulator, by means of unique design of the infrared light arrays and the high-temperature insulation components, technical difficulties of high-temperature high heat flow simulation when vacuum heat tests are performed on a spacecraft are solved, high-temperature high heat flow space environment can be simulated when vacuum heat tests are performed on spacecrafts in series of deep space exploration and space shuttles, and the spacecrafts can be tested.

The invention discloses a vacuum high/low temperature environmental simulation electromechanical transmission mechanism comprehensive performance experimental system, which comprises an experimental platform, a driving assembly, a vacuum high/low temperature experimental assembly, a normal temperature and normal pressure experimental assembly and a loading assembly. The driving assembly comprises a servo motor, an input end torque and speed sensor and an input end angle encoder; the vacuum high/low temperature experimental assembly comprises vacuum high/low temperature environmental simulation equipment, an optical platform, and input and output end magnetic fluid sealing shafts; and the loading assembly comprises an output end angle encoder, an output end torque and speed sensor and a torque motor. The vacuum high/low temperature environmental simulation equipment has low cost, the installation of the driving assembly and the loading assembly is performed outside a vacuum tank, and the installation and debugging are convenient. Due to the adoption of a modular design, the experimental system can test the comprehensive performance of a speed reducer and other rotating mechanisms under the conditions of space environment and normal temperature and normal pressure environment on the same experimental system, and has the advantages of strong adaptability of the equipment and high detection accuracy.

The invention provides a fountain code compiling method based on deep space communication environment. The method comprises the following steps of: A) dividing information bits to be transmitted to form a plurality of original information groups; B) performing fountain coding on the original information groups to form code groups; C, performing concatenated error correction coding on the code groups, and transmitting the code groups to a receiver by using a deep space channel; D, performing concatenated error correction decoding to recover the code groups; and E, after enough code groups are obtained, performing fountain decoding to recover all the original information groups. In the method, partial randomness in a conventional fountain coding process is limited for the characteristics of the deep space channel so as to effectively reduce coding redundancy overhead and directively solve the problems of limitations to the transmission power and memory space of fountain codes in a deep space environment on the premise of not changing original degree distribution.

The invention relates to a device and a method for on-orbit monitoring of charging of a satellite material surface, belonging to the technical field of space application. The device comprises an electron gun, a non-contact potentiometer probe, a three-dimensional transmission mechanism, a non-contact surface potentiometer, an electron beam current density measuring system, a monitoring electrode,a supporting structure, a first electromagnetic valve, a second electromagnetic valve, a diffusion pump, a third electromagnetic valve, a vacuum box, a mechanical pump, a vacuum penetrating wall, a measurement circuit interface and a measurement circuit. The test method comprises the steps as follows: sending an electron to a sample for monitoring the electrode surface under a vacuum condition, adjusting the position of the non-contact potentiometer probe through the three-dimensional transmission mechanism, recording charging potential Vsurface on the sample surface, measuring leakage current I through the measurement circuit, and finally obtaining a proportional relation coefficient K by known sample resistance rho according to the formula that Vsurface is proportional to KrhoI. According to the invention, the on-orbit surface charging condition of the satellite material is inverted by monitoring the leakage current of the sample in a space environment, and the device and the methodhas the advantage of simple physical structure and is easy to carry in space.

The invention discloses a full-automatic battery stack dismounting and conveying system for joining storage with production. The system comprises a tray conveying system, a battery stacking system, a battery stack dismounting system, an electric control system, a computer management system, a bar code information acquisition system and auxiliary equipment. At present, the domestic vehicle lead-acid battery manufacturing industry generally adopts a process mode of: manual stacking+manual cushion plate adding+forklift carrying+ground storage+forklift carrying+manual stack dismounting, and the mode mainly depends on manual operation and ground storage, so that the labor intensity of operators is high, the material unit area warehousing capacity is low, and the production efficiency is low; and as the operation space environment is weak, acid gas is harmful to human bodies, and forklifts and workers across work, potential safety hazards are generated. The system adopts a scheme of battery conveying line+robot automatic stacking+solid tray shuttle car carrying+robot automatic stack dismounting, reduces labors, reduces the labor intensity, effectively reduces the energy consumption, largely improves the working environment of workers, and improves the working efficiency.

A door assembly of a washing machine is disclosed, which opens and closes an inlet of the laundry. In a washing machine comprising a drum, a cabinet protecting the drum, an inlet formed on a front surface of the cabinet to throw the laundry in and out, and a door assembly provided on a front surface of the cabinet to open and close the inlet, the door assembly comprises an outer frame, a door deco connected with one surface of the outer frame, and a fitting portion selectively fixing and detaching the door deco to and from the outer frame. Since the door deco is easily fixed to the outer frame, it is possible to improve assembly performance of the door assembly. Also, the door deco can firmly be fixed to the outer frame without the space environment where the washing machine is arranged.

The invention provides an embedded satellite configuration. The embedded satellite configuration comprises a platform cabin, a loading cabin, a docking locking-unlocking mechanism, a non-contact magnetic suspension direct force control mechanism and a solar cell array. The platform cabin is in a hollow annular structure; the loading cabin is arranged in the platform cabin; the docking locking-unlocking mechanism and the non-contact magnetic suspension direct force control mechanism are arranged between the platform cabin and the loading cabin respectively; the solar cell array is arranged on the side of the platform cabin. Ultrahigh-precision ultrahigh-stability control requirements of satellites are met, quality characteristics and agile mobility performances of the satellites are improved, a loading space environment is improved, and influences of platform disturbance and thermal cycling on satellite loading are reduced. According to a design conception of non-contact split design and centralized control, the embedded satellite configuration has advantages of structural configuration compactness, high control precision, high environmental adaptability, low development risk, short cycle and simplicity and feasibility in integration and final assembly.

The invention discloses a test system for deformation measurement of a large spacecraft structure under a vacuum and low-temperature environment. The test system includes a vacuum and low-temperature container, a portal supporting mechanism, a low-temperature cantilever moving mechanism, photogrammetry CCD camera and protection cabin assemblies, a test piece supporting mechanism, a low-temperature reference meter, a temperature and air pressure control system, a motion control system, and a measurement data acquisition and processing system; two sets of photogrammetry CCD camera and protection cabin assemblies are symmetrically hung at two ends of the low-temperature cantilever moving mechanism, and 3m-rotation radius and +/-360-degree-reciprocating rotary movement photographing can be realized under the vacuum and low-temperature environment so as to realize the deformation measurement of the large spacecraft structure. With the test system of the invention adopted, the thermal deformation measurement of a certain 5m large umbrella antenna can be completed under a simulated space environment by using photogrammetric techniques, and the repeatability precision of the measurement of spatial point positions can achieve 20 microns.

The invention discloses a moon-exploration mechanical arm modularization joint based on absolute position measurement, relating to a moon-exploration mechanical arm modularization joint. The invention aims to solve the problems that a potentiometer is used as an absolute position sensor of the current mechanical arm modularization joint, thus global feedback of the joint position information can not be directly provided, signal fusion needs to be carried out, and the fusion algorithm is relatively troublesome. A DC brushless motor is installed in a casing, the small diameter end of a rotator magnet yoke of the DC brushless motor is connected with one end of an input interface; a harmonic reducer is fixedly connected with an internal seat of an angular contact bearing; an outer seat of the bearing, a flexible gear and an output ring flange are fixedly connected; an input shaft is fixedly installed in the outer seat of the bearing; the input shaft is fixedly installed in a supporting seat; the input shaft is fixedly installed in the input interface; a gland is fixedly connected with the supporting seat; a Hall sensor bracket is fixed on a second radial bearing supporting seat; and a back-to back twin angular contact bearing is installed between the inner seat of the angular contact bearing and the outer seat of the angular contact bearing. The invention is used for exploring ore and space environment on the surface of moon.

The invention provides a full-coverage path planning method of a mobile robot. The full-coverage path planning method is a novel coverage algorithm by solving the problems of optimizing of coverage division and path planning in the process; the pre-acknowledging of map space environment is not required; the areas are divided in the coverage process, and the process is an incremental type coverageprocess; the coverage is dynamically divided, and the obstacles which dynamically appear can be selected and planned in real time, so as to complete double tasks of coverage and obstacle avoidance. The full-coverage path planning method is not only suitable for map environments using topology environment rules, but also suitable for the environment spaces in the complicated areas; compared with the cow tillage division algorithm, more advantages are realized.

The invention provides a high-tolerance flexibility capture mechanism for space environment and relates to a capture mechanism; the capture mechanism solves the problems that the existing capture mechanism has low capture tolerance and can not meet high precision requirements of a capture mechanical arm; in the invention, the input end of a harmonic wave reducer is connected with the output end of a direct current brushless motor, the direct current brushless motor is fixedly arranged on an inner wall of a capture supporting barrel, a small gear is arranged on the output end of the harmonic wave reducer, the small gear is meshed with an inner gear, the inner gear is fixedly connected with a force moment sensor which is fixedly connected with a rotation ring, a fixing ring is fixedly connected with the inner side wall of the capture supporting barrel by a connecting ring, three steel wire nets are distributed in the inner cavity of the fixing cavity and the rotating ring, one end of each steel wire is fixedly connected with the inner wall of the fixing ring, the other end of each steel wire is connected with the rotating ring by a rotating shaft, and a capture cone on a capture interface device is connected with the three steel wires; the high-tolerance flexibility capture mechanism is used for capturing space load cabin under spatial high tolerance and microgravity environment.

The invention discloses a monitoring system and a monitoring method for SRAM type FPGA single particle functional interruption, and relates to the field of a single particle. The method comprises the steps of: A, setting a heavy ion beam flow with an initial LET value to irradiate a test board; B, judging whether a single particle functional interruption phenomenon happens to the test board, if so, recording that the single particle functional interruption phenomenon happens one time to the test board, and if not, considering that the single particle functional interruption phenomenon does not happen to the test board; C, judging whether the test board satisfies the following condition that the number of the single particle functional interruption phenomenon reaches a predetermined number or the total injection quantity of incident particles reaches a predetermined quantity, if so, performing a step D, and if not, performing the step B; D, judging whether a [sigma]-LET curve can be obtained by means of fitting, if so, obtaining the [sigma]-LET curve by means of fitting, and if not, adjusting the LET value of the heavy ion beam flow and performing the step B. The system and the method provided by the invention are capable of predicting the SEFI rate of an FPGA in various kinds of space environments.

The invention discloses a modularized split Sagnac interferometer, comprising a block prism formed by gluing two blocks of prisms, and two reflecting mirrors; the upper and lower non-transmission surfaces of the block prism are respectively bonded with a glass base plate, wherein the glass base plate at one surface is mounted with a metal mirror seat to form a cubic prism component; and the two reflecting mirrors are respectively installed into respect metal mirror frame to form two groups of reflecting mirror assemblies. The Sagnac interferometer also comprises a box body which is provided with installation holes for the cubic prism component and the two groups of reflecting mirror assemblies; and the cubic prism component and the two groups of reflecting mirror assemblies are respectively installed in corresponding installation holes on the box body to form the modularized split Sagnac interferometer. The modules are combined together to form the whole interferometer with high stability, which is in particular suitable for being applied in airborne or spaceborne Fourier transform imaging spectrometers. The modularized split Sagnac interferometer has compact structure, good processing and resetting manufacturability, high stability and repetition accuracy, and good adaptability to space environment.

The invention discloses an ultrahigh-temperature thermal current simulation system used for a spacecraft vacuum thermal test in a vacuum container. The ultrahigh-temperature thermal current simulation system mainly comprises a semi-cylindrical graphite heating array, high-reflectivity high-temperature thermal insulation assembly units, a graphite heating array installing support, an ultrahigh temperature measuring unit and a power-regulator power control unit. A plurality of graphite heating rods are arranged and combined into the semi-cylindrical graphite heating array according to the requirements for the density and uniformity of thermal currents. Each graphite heating rod is composed of a graphite heating body and a graphite electrode, alternating-current electricity supply is adopted, and wiring electrode leads penetrate through a high-current cabin-penetrating electricity supply flange arranged on a container wall of the vacuum low-temperature environment simulation container and are electrically connected with the temperature measuring unit and the power-regulator power control unit respectively. Through the unique design of the graphite heating array, the high-reflectivity high-temperature thermal insulation assembly units and the ultrahigh temperature measuring unit, measurement of and control over temperatures over 1800 DEG C in the space environment simulation container are achieved, and the ultrahigh-temperature thermal current simulation system is also suitable for high-temperature and high-thermal-current environment simulation requirements in vacuum thermal tests of all types of spacecraft.

The invention relates to a high/low temperature space environment simulating container with a high temperature change rate, comprising a main cabin body, a cabin door, a head sink arranged in the main cabin body, a door sealing structure for connecting the main cabin body and the cabin door, an insulating channel passing through the main cabin body, a sample carrier table, a high/low temperature camera assembly, a high/low temperature fluid stirrer, a temperature measuring system, a pressure measuring system and a vacuumizing structure. A non-high-vacuum environment is formed in the container and is filled with helium; besides radiative heat transfer same as the heat transfer manner of a heat vacuum tank, natural convection heat transfer, even forced convection heat transfer, is added in the cabin, so heat transfer speed is increased greatly, a high/low temperature environment (68K-373K) with a high temperature change rate and even temperature is provided to a sample to be measured. The high/low temperature space environment simulating container is stable, safe and reliable to work.

A method for cultivating vegetables in space environments includes simulating a space station environment according to special environmental conditions of cosmic space such as intense radiation (cosmic rays), micro-gravity, high vacuum, weak magnetic field (alternating magnetic field), vibration-free and sterility, growth habit and fertility characteristics of vegetables on the earth, and natural ecological conditions of the earth; creating water, fertilizer, air, heat and light conditions suitable for plants to grow through artificial control so as to achieve the purpose of production of the vegetables in the space environment. The method for cultivating the vegetables in the space environments is composed of a cultivation cabin greenhouse, suitable environment system control, a dense optical fiber system, temperature and humidity control, a carbon dioxide concentration regulation system, a nutrient solution circulation system and greenhouse external condition monitoring so as to achieve the control on humidity, temperature, carbon dioxide concentration, oxygen, nutrients and light intensity which are needed for plant growth. The method for cultivating the vegetables in the space environment is applicable to the cultivation of plants such as vegetables and flowers in the space environments such as large spacecrafts, international space stations, the moon and the mars as well at to space breeding.