34results about How to "Guarantee the development progress" patented technology

The invention discloses a method for optimizing an SAR antenna directional diagram test. The method includes the steps of establishing an active phased array antenna directional diagram calculating mathematics model according to the electromagnetic field theory, obtaining and calculating basic data of an active phased array antenna, calculating and storing all wave position antenna amplitude phase weight coefficients of the SAR antenna according to the design requirement and engineering realizability, and using a near-field test method to obtain antenna sub-array directional diagrams at different positions of an antenna array plane under a planar near-field test system environment. The test time of an SAR antenna directional diagram test is greatly shortened, the satellite development progress is ensured and accelerated and a reference is provided for test SAR antenna directional diagram of subsequent radar satellite models.

The invention discloses a leak rate detection apparatus and method for the connection position of a pressure control system and a spacecraft sealed compartment, for vacuum thermal testing. The apparatus comprises a leak rate detection tool, a high-precision vacuum measuring device, the spacecraft sealed compartment, a pressure simulation control system pipeline and a helium mass spectrum leak detection system, wherein the helium mass spectrum leak detection system comprises an auxiliary suction pump, a helium mass spectrum leak detector, a vacuum standard leakage hole, a pipeline, a valve and the like; the high-precision vacuum measuring device comprises a vacuometer, an electric connector, a communication cable, a vacuum gauge and an auxiliary container; the leak rate detection tool is respectively connected with the spacecraft sealed compartment, the pressure simulation control system pipeline and the helium mass spectrum leak detection system through a flange; and the auxiliary container in the high-precision vacuum measuring device is installed in the spacecraft sealed compartment.

The invention discloses a rocket weapon or emitter launching system. The rocket weapon or emitter launching system is characterized by comprising a base platform which is fixedly arranged on the ground during use, a rising vertical platform which one end of the rising vertical platform is rotatably fixed at a fixed position of the base platform, an inclined supporting platform which one end of theinclined supporting platform is connected with the rising vertical platform in a rotatable mode and the other end of the inclined supporting platform is a free end, wherein a locking structure is arranged at the position, away from the fixed position, of the base platform, when the rising vertical platform is vertically rotated to a preset angle, the free end of the inclined supporting platform is fixedly locked on the base platform through the locking structure arranged on the base platform. According to the system and the method, a pure mechanical structure scheme is adopted to complete thedesign of a box type rocket launching device, the problems of emission tasks under the conditions of low cost, fast rhythm and high reliability are solved, and the system and the method have the characteristics of easiness in operation, low in cost, high in strength, and the emission mode types of the box type rocket is widened.

The invention discloses a method for optimizing an SAR antenna directional diagram test. The method includes the steps of establishing an active phased array antenna directional diagram calculating mathematics model according to the electromagnetic field theory, obtaining and calculating basic data of an active phased array antenna, calculating and storing all wave position antenna amplitude phase weight coefficients of the SAR antenna according to the design requirement and engineering realizability, and using a near-field test method to obtain antenna sub-array directional diagrams at different positions of an antenna array plane under a planar near-field test system environment. The test time of an SAR antenna directional diagram test is greatly shortened, the satellite development progress is ensured and accelerated and a reference is provided for test SAR antenna directional diagram of subsequent radar satellite models.

The invention discloses a method for automatically switching a 3D mode, a storage medium and an intelligent television, and the method comprises the steps: when receiving an instruction of entering the 3D mode, converting a 2D signal into left and right eye images, and converting the left and right eye images into a 3D image with a 3D effect; and when an instruction of exiting the 3D mode is received, judging whether the current picture is a 3D picture, and if yes, exiting the current 3D picture. According to the invention, a unified 3D mode switching standard process is formulated from the perspective of application; in this way, automatic switching can be achieved in the switching process of all the applications, switching of all the applications is not needed, the logic problem of 3D switching in a project is reduced, the project development progress is guaranteed, automatic 3D switching is achieved to a certain degree, and great convenience is brought to a user.

The invention discloses a method for simultaneously realizing laser code scanning PDA (Personal Digital Assistant) and mobile phone code scanning suitable for an intelligent logistics system, and belongs to the technical field of Android application development. Aiming at the problem that two sets of codes are generally required to be developed because the same APP in the technical field normally realizes the code scanning mechanism in both Android PDA and Android mobile phone, the invention provides a code scanning mechanism realization method simultaneously suitable for laser code scanning PDA and mobile phone, a comprehensive technical solution is provided by combining computer program design and biological principles, the method can be simultaneously applied to industrial Android PDA equipment with a laser scanning head or common Android mobile phone / tablet equipment with a camera function under the condition of not changing a row of codes. According to the method provided by the invention, under the condition that the test PDA is lacked, a developer can realize code scanning function development by using a common Android mobile phone, and the PDA equipment does not need to be adapted for the code scanning function subsequently, so that the production efficiency is improved, the development progress is guaranteed, and the cost for application maintenance and upgrading is reduced.

The invention discloses a DF file verification method based on the ARINC661. The DF file verification method based on the ARINC661 is characterized by comprising the following steps that firstly, a DF file is led in, information of the DF file is read and stored in a unified global variable, after the DF file is led in successively, data are analyzed and displayed according to a logical hierarchical structure, and attribute values and types of all parts are displayed in rows; secondly, a CDS server is started; thirdly, dynamic verification is performed on the DF file; fourthly, a test scrip of the Python format is automatically generated according to attributes of the corresponding parts of a DF and based on the ARINC661 protocol specifications, an execution environment and management are provided, original manual operation is converted into a script file to be stored, and therefore the verification process can be repeated. According to the DF file verification method based on the ARINC661, time in analyzing question reasons can be reduced, more emphasis of project testing can be put on logical functions, and therefore the development progress and the development efficiency of a whole project are ensured.

The rocket weapon or launcher launch system is characterized in that it includes: a base platform, which is fixed on the ground when in use; an erecting platform, one end of which is rotatably fixed on a fixed position of the base platform; The erecting platform is rotatably connected, and the other end is a free end, wherein a locking structure is provided at a position away from the fixed position of the base platform, and when the erecting platform is erected and rotated to a predetermined angle, the free end of the inclined support platform It is fixed and locked on the base platform by a locking structure arranged on the base platform. The invention adopts a purely mechanical structure scheme to complete the design of the box-type rocket launching device, solves the problem of launching tasks under the conditions of low-cost, fast-paced and high-reliability development, has the characteristics of easy operation, low cost, and high strength, and broadens the range of box-type rocket launchers. Type of rocket launch mode.

The invention discloses a leak rate detection apparatus and method for the connection position of a pressure control system and a spacecraft sealed compartment, for vacuum thermal testing. The apparatus comprises a leak rate detection tool, a high-precision vacuum measuring device, the spacecraft sealed compartment, a pressure simulation control system pipeline and a helium mass spectrum leak detection system, wherein the helium mass spectrum leak detection system comprises an auxiliary suction pump, a helium mass spectrum leak detector, a vacuum standard leakage hole, a pipeline, a valve and the like; the high-precision vacuum measuring device comprises a vacuometer, an electric connector, a communication cable, a vacuum gauge and an auxiliary container; the leak rate detection tool is respectively connected with the spacecraft sealed compartment, the pressure simulation control system pipeline and the helium mass spectrum leak detection system through a flange; and the auxiliary container in the high-precision vacuum measuring device is installed in the spacecraft sealed compartment.

The invention discloses a power consumption anomaly detection method and a power consumption anomaly detection device for a mobile terminal. The power consumption anomaly detection method for the mobile terminal comprises the following steps: controlling the mobile terminal to circularly run in more than two working modes; detecting the power consumption rate of the mobile terminal; if the power consumption rate exceeds a preset power consumption rate threshold value and the mobile terminal is in a screen-out state at present, recording and storing a journal file corresponding to the mobile terminal in the current state; if the power consumption rate exceeds the preset power consumption rate threshold value and the mobile terminal is in a bright screen state at present, judging whether the work current value of the mobile terminal exceeds a preset work current threshold value or not in the current working mode; if yes, recording and storing the journal file corresponding to the mobile terminal in the current state; if not, returning to perform the step of detecting the power consumption rate of the mobile terminal and the subsequent steps. According to the technical scheme, the method and the device can effectively improve the power consumption anomaly debugging efficiency of the mobile terminal.

The invention discloses a video player system, a development method thereof and an installation operation method thereof. The installation operation method comprises the following steps: automatically determining a type of a present processor; according to a requirement, installing a decoder module which is subjected to compilation optimization at local or on a server. According to the system and the methods in the invention, a user has a user experience of smoothly playing a video file, quantity of installation packages when publishing a player is reduced, on-line independent upgrade of a decoder is supported, development and maintenance cost are reduced, and cooperation development is facilitated.

The invention provides an optical fibre cooling head suitable for a high-power semiconductor laser optical fibre coupling module. In the scheme, the optical fibre cooling head comprises an outer cylinder and a cavity sleeving in the outer cylinder; the cavity comprises a support part and an axial centre; the support part is arranged outside the axial centre and connected with the inner wall of the outer cylinder; the axial centre is a hollow channel; a coupled optical fibre is arranged in one end of the axial centre; an optical fibre joint is arranged at the other end of the axial centre; the area between the axial centre and the outer cylinder is a heat dissipation channel; the direction of the heat dissipation channel is the same to that of the coupled optical fibre; and a water inlet and a water outlet communicated with the heat dissipation channel are arranged on the outer cylinder. The optical fiber cooling head in the scheme provided by the invention has the advantages of being compact in structure, high in flexibility and integration level and easy to maintain and replace.

The invention discloses a loading device for loading a rocket into a storage and transportation launch box, which includes a guide rail, a trolley, a supporting frame car and a hoist, and the trolley is placed on the guide rail and can be moved along the longitudinal direction of the guide rail. Move; the winch is connected with the trolley through a pull rope, so as to drive the trolley to move on the guide rail; the support frame car is placed on the guide rail and can move longitudinally along the guide rail , the support frame car is provided with a three-axis motion platform for receiving the rocket and adjusting the position of the rocket; the cart includes a car body and two fork plates arranged on the car body, and the two fork plates Plates are set up and down, so as to be used to co-operate with the tapered head of the rocket to drive the rocket to move, so that the rocket enters the storage and transportation launch box. The present invention is easy to assemble during use, and all operations can be completed by cooperating with a crane and operators according to the requirements of on-site command.

The invention discloses a universal load manager ground detection test board card, which is deployed between an upper computer and a load manager of a device to be tested, is used for testing common function interfaces of load managers of different task models, and is characterized in that the test board card comprises a load configuration management module and a common function interface module; wherein the load configuration management module is used for storing a load format configuration table sent by an upper computer in an external load configuration table Flash; the reading module is used for reading configuration information pre-stored in an external load configuration table Flash and performing corresponding processing according to a command sent by an upper computer; the communication module is used for sending the generated scientific data, the control signal and the acquisition signal to an external common function interface module, and is also used for sending an execution result of the ground detection test board card to an upper computer; and the common function interface module is used for realizing a connection circuit with a common function interface of the load manager.

The invention discloses a radiometer ground detection system and method. The system is used for testing an on-satellite receiver unit and an on-satellite digital control unit on the ground. The systemincludes a temperature measurement data input module (5), an analog temperature measurement data output module (6), an output module (7) of each channel voltage of an analog receiver and a data processing module (8). The temperature measurement data input module (5) is used for reading temperature measurement data output by the on-satellite receiver unit; the analog temperature measurement data output module (6) is used for simulating a temperature measurement circuit to output periodic data to the on-satellite digital control unit; and the output module (7) of each channel voltage of the analog receiver is used for simulating functions of the analog receiver to output cold air, over-the-ground and observation level signals of each channel for the on-satellite digital control unit to perform collection and testing. The data processing module (8) is used for receiving a data packet sent by the on-satellite digital control unit, and sending the data packet to an upper computer. The system has the advantages of being small in size, multiple in functions and high in universality.

A satellite ground power supply and distribution test equipment generalization design method relates to the satellite ground power supply and distribution test equipment design field. A largest envelope which makes that equipment resource configuration reaches demands of all the researched-satellite-to-ground power supply and distribution test equipment is included. Enough redundant backups and extensible resources are reserved and a construction rule of various kinds of resources in the equipment is made. Aiming at different requirements of different satellites to a cell on-off interface circuit and the like, a driving power supply in the power supply and distribution test equipment and a passive contact point of an electromagnetic relay are simultaneously led out to an equipment output interface, and each satellite can complete control mode conversion through a special design of a cable plug according to a detailed design of a satellite power supply controller. The test equipment can be applied to a subsequent satellite without any reconstruction. Material resource cost is greatly reduced and rapid interchange of the test equipment among the different satellites is realized. Simultaneously, a processing unit can realize production line type development and a development period of the equipment is greatly shortened.

The invention belongs to flight control technology and relates to improvement on the redundancy control switch of a flight control system. The system comprises a manual quad four-pole double-throw switch [1] consisting of a first single-pole double-throw switch, a second single-pole double-throw switch, a third single-pole double-throw switch and a fourth single-pole double-throw switch, and is characterized in that: a light-operated switch [2] is provided; the public end of the fourth single-pole double-throw switch of the manual quad four-pole double-throw switch [1] is connected with a 27Vpower supply; the normally-open contact of the fourth single-pole double-throw switch of the manual quad four-pole double-throw switch [1] is connected with the power supply input end of the light-operated switch [2] and a redundancy control switch position indicating lamp; the signal input end of the light-operated switch [2] is connected with a fourth redundancy control signal output end; and the signal output end of the light-operated switch [2] is connected with the fourth redundancy control signal output end of the flight control system. In the invention, the requirements of the novel flight control system can be met without replacing the conventional four-pole double-throw switch, and the research progress of the novel flight control system is ensured.