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

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 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.