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 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 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.