68results about How to "Save research and development costs" patented technology

The invention provides a satellite temperature control method allowing rapid responding and multi-orbit adaption, wherein by adopting a heat pipe network, reinforcing contact thermal conduction, and spraying a high-emissivity thermal control coating inside a satellite to reinforce in-cabin thermal conduction and radiation heat exchange, a temperature field is distributed uniformly in a cabin; a whole satellite temperature level is adjusted by a compensative electric heater; a nightside of a side plate of the satellite is taken as a major heat dissipation face, the outer surface of the nightside is sprayed with a white paint, and all the other outer surfaces of the satellite body, except for the major heat dissipation face, are covered by multiple layers of thermal insulation assemblies; and components outside the satellite are sprayed with a white paint thermal control coating. A propelling cabin has independent design, wherein the entire outside of the cabin is covered by the multiple layers of the thermal insulation assemblies, a baseplate inside the cabin is covered by the multiple layers of the thermal insulation assemblies, and the propelling cabin is finally integrated with a platform cabin. By integral design of machinery, heat and electricity, the satellite temperature control method allowing the rapid responding and the multi-orbit adaption provided by the invention realizes thermal control requirements of the whole satellite under conditions of a sun-synchronous orbit and an inclined track by the temperature control method.

The invention relates to a method for obtaining control value of temperature behind a turbine of an aviation engine at high altitude and high speed. The method comprises the following steps of (1) screening several parameters which are mostly related with the engine efficiency from an engine logbook; (2) on the basis of using the known control values of the temperature behind the turbines of morethan hundreds of engines at high altitude and high speed as a training set, establishing a nervous network, using the selected parameters as input nodes, and using the control value of the temperaturebehind the turbine as the target value to train; after training, obtaining a nervous network model for calculating the control value of the temperature behind the turbine of the aviation engine at high altitude and high speed.

The invention relates to the technical field o radar systems, discloses an external radiation source radar real-time signal processing method based on multi-CPU processing, and a multi-CPU computer or server is utilized to realize external radiation source radar real-time signal processing with a general programming language, thereby increasing the flexibility of realization of signal processing of an external radiation source radar. The whole signal processing process of the external radiation source radar is split into a plurality of processing steps of clutter suppression, correlation processing and target detection, each step runs on a different CPU resource, the processing time of each step is smaller than accumulation time of a set of data, i.e., if a signal loss phenomenon does not occur, continuity and real-time performance of signal processing are realized, and through the method provided by the invention, clutter cancellation processing can be completed, the flexibility of signal processing of the external radiation source radar is improved, and real-time performance of signal processing of the external radiation source radar is realized. In addition, the development period of signal processing of the external radiation source radar can also be shortened, and requirements for development technicians by signal processing of the external radiation source radar are lowered.

The invention discloses an optical registration method and system for an LFOV (large field of view) and small-F-number line-surface combined remote sensing camera. The method comprises steps as follows: connecting a to-be-registered camera body and a table board of a two-dimensional turntable; step S200: determining the best focal plane position of a linear array channel and a surface array channel of a camera; establishing a light path for registration; making sure that reflecting light can fill a full aperture of a camera lens; drawing an orthogonal reticle cross on a screen of a display, and enabling a reticle cross target to be focused to and imaged in the center of the display; making a pixel of a linear array CCD parallel to the horizontal line of the reticle cross of the display; making a first row of pixels of a surface array CCD parallel to the horizontal line of the reticle cross of the display; aligning the Xth row of pixels of the surface array CCD parallel to the reticle cross of the display; verifying whether the Xth row of pixels of the surface array CCD are aligned to the horizontal line of the reticle cross of the display. The problems about high-accuracy system integration and linear array-surface array optical registration of an LFOV, small-F-number, light and small remote sensing camera are solved once.

The invention relates to a remote radar calibration satellite system, which comprises a measurement and control operation control center, a ground application system, a reflective radar calibration satellite and a responsive measurement and control device calibration satellite, wherein the measurement and control operation control center is used for completing satellite launching and early orbitalsection measurement and control tasks, long-term operation section measurement and control management and load data receiving tasks; the ground application system is used for calibration satellite service planning, precision orbit data processing and publishing of a precision satellite orbit for each user; the reflective radar calibration satellite provides an RCS reference and a precise positionreference for calibration of a ground reflection-type radar device; and the responsive measurement and control device calibration satellite provides a precise position reference for calibration of aground response-type measurement and control device. The existing technical resources can be thoroughly used, the calibration requirements of the user can be met to the maximum degree, and the application range of the calibration satellite is expanded actively.

The invention discloses a synchronous control method of the motion of a combined supporting mechanism of a wind tunnel. First, a tail supporting mechanism is identified as an active control object, and a stripe hanging supporting mechanism is identified as a follow-up control object; second, the characteristics including dynamic response time difference, motion speed and the like of the two independent supporting mechanisms in the combined supporting mechanism are tested and data of the characteristics are recorded; finally, the effect that the auxiliary supporting mechanism follows the main supporting mechanism in real time is achieved through sequential control of instructions, and corresponding safety strategies are adopted to cope with risks likely to exist in the process of a test, so that the test suffers no risk at all. The synchronous control method has the advantages that through the synchronous control over the two independent supporting mechanisms, combination supporting of an aircraft model is achieved, and a new test technology is provided for an aerodynamic test of the aircraft model in the wind tunnel; the method is good in operability, strong in engineering adaptability and high in safety and can meet special requirements in the technical field of wind tunnel supporting interference tests, greatly save equipment development expenditure and shorten the development period.

The invention relates to a whole aircraft drop simulation predication and testing method. The method comprises whole aircraft drop simulation predication analysis and whole aircraft drop test; a drop height and a pitch angle of a whole aircraft are obtained and are used as state parameters of the whole aircraft drop test; the whole aircraft drop test is carried out according to theoretical simulation predication so as to obtain an acceleration impact environment capable of being borne by equipment on the aircraft in a landing impact process, and provide important test evidences to check the accuracy of test technological conditions of a landing impact mechanical environment; meanwhile, whether indications including designed routes and the like of an undercarriage buffering system under the landing impact environment meet the requirements or not is realized; when a whole aircraft is at an electrified closed loop working state of a GNC (Global Navigation Chart) system, the GNC system has adaptability to a landing large-impact load environment, and important guarantees are provided for the success of an aircraft flying verification test.

Provided is a flexible support micro-vibration testing device for simulating a whole satellite. The flexible support micro-vibration testing device comprises a brace supporting structure, a six-component force sensor, an acceleration sensor, a data acquiring and processing system, a rigid platform, and an adaptive support. A whole satellite simulated member is a test object. The top of the brace supporting structure is fixed to the six-component force sensor through an interface. The six-component force sensor is fixed to the whole satellite simulated member through the adaptive support. The acceleration sensor is pasted onto the brace supporting structure. The data acquiring and processing system is connected with the six-component force sensor and the acceleration sensor. The rigid platform is equipped with a plurality of ground racks. The brace supporting structure is fixed to the ground racks on the rigid platform through screws. The flexible support micro-vibration testing device may control and change the rigidity of a whole test system, simulates a transverse fundamental frequency satellite from 5 to 15Hz, has level support structures each of which forms the function of a measuring subsystem in order to simulate the flexible support of a single machine and components to a brace, a single cabin, and a whole satellite.

The invention discloses a VPX computer processing board based on VITA series standards. The VPX computer processing board comprises a COM Express module, a VPX function carrier plate, a panel and a VPX connector, wherein the COM Express module, the panel and the VPX connector are all mounted on the VPX function carrier plate; a VGA signal output from the COM Express module is led to the panel through a VGA interface; the COM Express module is connected with the panel; the COM Express module is connected with the VPX connector through a PCIE bridge; a RaidIO bridge chip is further connected between the COM Express module and the VPX connector; PCIE can be converted into a RapidIO bus through the RapidIO bridge chip; 1 path of PCIE x4 can convert 1 path of RapidIO x4 and is compatible with 1 path of PCIE x1 and converts 1 path of RapidIO x1; conversion of 4 paths of PCIE to 4 paths of RapidIO buss can be achieved at most; 1 path of PCIE3.0 x16 can be converted into 5 paths of PCIE x16 through the PCIE bridge at most; the PCIE bridge is further compatible with PCIE1.0 and PCIE2.0. On the basis of the principle, diverse demands of users can be met, the development period is shortened, and the research expenditure can be lowered.

The invention discloses a method for converting different normal matrix test data. The method comprises the following steps of: randomizing a function related to test data, obtaining massive simulation test data under each normal matrix by utilizing a Monte-Carlo simulation technology, and then estimating normal environmental factors used for conversion on different normal matrix test data by utilizing the simulation test data to complete conversion between small sample test data among different normal matrixes. The method has the beneficial effect that the normal environmental factor used for conversion on different normal matrix test data is obtained by utilizing the Monte-Carlo simulation technology, on one hand, enough test data can be obtained to achieve the performance parametric reliability evaluation requirement, on the other hand, the number of system tests on a product is increased to obtain enough reliability evaluation data, thus development expenditure and development time are greatly saved.

The invention relates to the technical field of centroid deviation measurement methods, in particular to a centroid deviation measurement method for conical cylindrical parts. The centroid deviation measurement method includes the following steps: measuring the axial centroid of a conical cylindrical part: placing the conical cylindrical part horizontally, arranging a first support and a second support at the front and back ends of the conical cylindrical part respectively, and determining the axial centroid of the conical cylindrical part according to the distances between and the weights ofthe conical cylindrical part, the first support and the second support; measuring the radial centroid deviation of the conical cylindrical part; and lifting the conical cylindrical part, measuring theobtained centroid position according to the axial centroid, and calculating the radial centroid deviation of the conical cylindrical part according to the triangular function relationship of the conical cylindrical part after lifting. The centroid deviation measurement method provided by the invention is designed for conical cylindrical parts, has certain universality for mass deviation measurement, does not need to develop special measurement equipment, has the characteristics of short investment time and low development cost, and can be used to complete the centroid deviation measurement ofconical cylindrical parts in an economical and convenient way.

A navigation information filtering method increasing moving alignment precision is disclosed. The method includes receiving, by an information interface assembly, navigation data sent by a comprehensive navigation device, subjecting the navigation data to point elimination, limiting and filtering treatment, and outputting an angle, an angular velocity and a ship velocity. The method overcomes a problem of how to obtain smooth and continuous transfer alignment information used for aircrafts through processing high-frequency navigation data in a situation that a shipboard platform is accompanied with vertical and horizontal swing.

The invention relates to a parallel processing platform robot. The parallel processing platform robot comprises a controller, a first moving mechanism, a second moving mechanism, a third moving mechanism and a processing platform. The first moving mechanism is connected with the processing platform through a first connecting rod. The second moving mechanism is connected with the processing platform through a second connecting rod. The third moving mechanism is connected with the processing platform through a third connecting rod. The controller is used for controlling the first moving mechanism, the second moving mechanism and the third moving mechanism to drive the three connecting rods to move to drive the processing platform to remain horizontal and rise and drop in the vertical direction. The first moving mechanism, the second moving mechanism and the third moving mechanism of the parallel processing platform robot are arranged in parallel, and the space can be saved; the parallelprocessing platform robot is simple in overall structure, easy to produce and machine and capable of increasing production benefits, reducing the labor risk and realizing factory automation and can beapplied to various types of processing and manufacturing fields, save the development cost and improve the operational capability of the processing platform.