CN210804037U

CN210804037U - Intermediate device integrated electronic single machine for carrier rocket remote measuring system

Info

Publication number: CN210804037U
Application number: CN201921792501.2U
Authority: CN
Inventors: 刘倩; 张永杰; 李雷; 李亮; 胡斌; 谢立; 颜晓明; 龚敏
Original assignee: Shanghai Aerospace System Engineering Institute
Current assignee: Shanghai Aerospace System Engineering Institute
Priority date: 2019-10-23
Filing date: 2019-10-23
Publication date: 2020-06-19
Anticipated expiration: 2029-10-23

Abstract

The utility model discloses an intermediate unit synthesizes electron unit for carrier rocket remote measurement system comprises instruction transform module, analog transform module, adopts and compiles module and power module. The instruction conversion module is used for isolating and converting the electrified switching value signals and the non-electrified switching value signals on the arrow into standard TTL signals, and the modularized and expanded design is realized through bus multiplexing. The analog conversion module is used for isolating and converting analog direct current signals with different levels into analog signals of 0-5V. The collecting and compiling module takes the FPGA as a core and comprises a multi-path analog switch, an A/D conversion module and a digital interface module. The sampling and coding module converts the collected instruction signal, analog signal and digital signal into serial data according to the requirements of a frame format wave channel table and sends the serial data out. The utility model discloses integrate original many telemetering measurement intermediate devices into a product, improved software and hardware resource sharing degree, very big reduction development cost and test cost.

Description

Intermediate device integrated electronic single machine for carrier rocket remote measuring system

Technical Field

The utility model relates to a telemetering measurement intermediate device field, in particular to an intermediate device synthesizes electron unit for carrier rocket remote measurement system.

Background

The telemetering intermediate device is an interface device of external systems such as a carrier rocket telemetering system, a control system, a propellant utilization system and the like, is a remote measurement conversion circuit device between two systems (devices), and has the task of converting measured signals of various types and ranges of digital quantity, switching value and analog quantity of the external systems into standardized electric signals which are suitable for being acquired and transmitted remotely by programmable rocket telemetering transmission equipment of the telemetering system, and simultaneously needs to be electrically isolated from the external systems so as to reduce interference among the systems and avoid the influence of internal faults of the telemetering system on the normal work of the external systems.

At present, the telemetric intermediate device includes various types such as a command converter for on-off signal measurement, a direct current converter for analog signal measurement, a digital converter for digital signal measurement, a rotational speed measuring unit for engine turbopump rotational speed measurement, and the like. Each intermediate device is independently designed, and the sharing of software and hardware resources cannot be realized; part of products are still subjected to analog measurement and are easily interfered; each product needs to be matched with corresponding test equipment for verification, the product development period is long, and the design and test cost is high.

The utility model discloses a scheme is to the improvement that above-mentioned problem goes on current telemetering measurement intermediate device.

SUMMERY OF THE UTILITY MODEL

For solving the problem such as the conversion equipment kind is many, software and hardware resource sharing is poor, development cost height in the middle of the current remote measuring system to promote remote measuring intermediate unit measuring accuracy and digital degree, the utility model discloses a carry out remote measuring intermediate unit integrated design, provide an intermediate unit comprehensive electron unit for carrier rocket remote measuring system.

In order to achieve the purpose of the utility model, the technical scheme adopted for solving the technical problem is as follows:

an intermediate device integrated electronic single machine for a carrier rocket remote measuring system comprises an instruction conversion module, an analog conversion module, a collecting and editing module and a power supply module, wherein:

the instruction conversion module is used for isolating and converting the electrified switching value signals and the non-electrified switching value signals on the arrow into standard TTL signals, and realizing modularization and extension design through bus multiplexing;

the analog conversion module is used for isolating and converting analog direct current signals of different levels into analog signals of 0-5V;

the collecting and editing module is used for controlling the functions and the time sequence of the whole machine, converting the collected instruction signals, analog signals and digital quantity signals into serial data according to the requirements of a frame format channel table and sending the serial data out;

the power module is used for supplying power to the whole machine and has the functions of filtering and isolating.

Further, the editing module comprises an FPGA, a multi-channel analog switch, an a/D conversion module and a digital interface module, wherein:

the multi-channel analog switch and the A/D conversion module are used for collecting analog signals, receiving direct current signals on the internal bus and switch switching signals output by the FPGA and converting the analog signals into binary data;

the FPGA sends out bus multiplexing gating signals to the instruction conversion module through the internal bus and receives instruction data from the internal bus in a time-sharing manner;

the digital interface circuit is used for receiving digital data and sending all types of received data to the next-stage central program unit through the interface according to the requirements of the frame format channel table.

Furthermore, the electronic single machine also comprises an internal bus, all modules of the electronic single machine are connected through the internal bus, and the number of the measured instruction signals and the number of the analog signals can be increased by adding the functional modules on the internal bus.

Furthermore, the electronic single machine also comprises a digital quantity bus, the digital quantity bus is adopted for external data transmission of the electronic single machine, and the number of digital quantity signal measuring circuits can be increased by adding the functional module on the digital quantity bus.

Furthermore, the digital quantity interface circuit comprises an optical coupling isolation mode and an RS422 mode according to different connection objects.

The utility model discloses owing to adopt above technical scheme, make it compare with prior art, have following advantage and positive effect:

1. the utility model discloses an intermediate device integrated electronic unit for a carrier rocket telemetering system integrates original multiple telemetering intermediate devices into one product, improves the software and hardware resource sharing degree, and greatly reduces the development cost and the test cost;

2. the utility model discloses an intermediate device integrated electronic single machine for a carrier rocket remote measuring system effectively improves the digitization degree of the remote measuring intermediate device, thereby reducing the interference degree of the measured signal, simplifying the design of an interface circuit and improving the measuring precision;

3. a intermediate device synthesizes electron unit for carrier rocket remote measurement system divides the module according to the function to interconnect through the inner bus, improved modularization, the level of unitization of product, and possess nimble extending capability.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort. In the drawings:

fig. 1 is a functional block diagram of an intermediate device integrated electronic unit for a remote measuring system of a launch vehicle according to the present invention.

Detailed Description

The technical solution in the embodiments of the present invention will be clearly and completely described and discussed below with reference to the accompanying drawings of the present invention, and it is obvious that only some examples, not all examples, of the present invention are described herein, and all other embodiments obtained by a person of ordinary skill in the art without creative work belong to the protection scope of the present invention based on the embodiments of the present invention.

As shown in fig. 1, the utility model discloses an intermediate device synthesizes electron unit for carrier rocket remote measuring system, including instruction transform module, analog transform module, adopt and compile module and power module, wherein:

the instruction conversion module is used for isolating and converting the electrified switching value signals and the non-electrified switching value signals on the arrow into standard TTL signals, and the modularized and expanded design is realized through bus multiplexing. The isolation of the command signal is realized by a photoelectric coupler, and the existence of the switching value signal is converted into the 0 and 1 states of the digital signal, and then the digital signal is connected to the bus multiplexing chip 54HC 244. Gating of the HC244 is controlled 54 by the codec module to time-share command signals to the internal bus.

The analog conversion module is used for isolating and converting analog direct current signals with different levels into analog signals of 0-5V. The analog signal isolation is realized by adopting an optical coupling isolation operational amplifier, and has the functions of input matching and output amplitude limiting. The isolated and transformed DC signal is connected to the internal bus.

the power module is used for supplying power to the whole machine and has the functions of filtering and isolating. In this embodiment, the power module may filter an input primary power and convert the input primary power into a secondary power, so as to supply power to each functional module inside the product and ensure sufficient current driving.

the digital interface circuit is used for receiving digital data and sending all types of received data to the next-stage central program unit through the interface according to the requirements of the frame format channel table. In this embodiment, the digital interface circuit includes an optical coupling isolation mode and an RS422 mode according to different connection objects.

In this embodiment, the modules in the electronic unit are connected by an internal bus, and the internal bus data includes: power signals, control signals, command data, analog data. The number of the measuring paths of the instruction signals and the analog signals can be increased by adding the functional module on the internal bus.

In this embodiment, the electronic single machine externally transmits data by using a digital quantity bus, and the number of digital quantity signal measurement paths can be increased by adding a functional module to the digital quantity bus.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention should be covered by the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. An intermediate device integrated electronic single machine for a carrier rocket remote measuring system is characterized by comprising an instruction conversion module, an analog conversion module, a collecting and editing module and a power supply module, wherein:

2. The integrated electronic stand-alone unit of intermediate device for a remote measuring system of a launch vehicle according to claim 1, wherein the editing module comprises an FPGA, a multi-way analog switch, an a/D conversion module and a digital interface module, wherein:

3. The integrated electronic stand-alone unit of intermediate device for remote measuring system of carrier rocket as claimed in claim 1, further comprising an internal bus, wherein the modules of said electronic stand-alone unit are connected by the internal bus, and the number of the measured command signals and analog signals is increased by adding functional modules to the internal bus.

4. The integrated electronic single machine for the intermediate device of the remote measuring system of the launch vehicle of claim 1, characterized in that it further comprises a digital bus, and the digital bus is used for the external data transmission of the electronic single machine, and the number of the digital signal measuring paths is increased by adding the functional module on the digital bus.

5. The integrated electronic stand-alone unit of an intermediate device for a remote sensing system of a launch vehicle as claimed in claim 1, wherein the digital interface circuit type includes an optical coupling isolation mode and an RS422 mode according to different connection objects.