CN111811319A - Small-size transmission control box - Google Patents

Abstract

A small-sized launch control box is characterized in that a power panel is arranged between a bottom plate and a middle plate, a core panel is arranged in the middle plate, an electric connector used for realizing up-to-up signal cross-linking with an airplane and down-to-down signal cross-linking with a missile is arranged on one side of the middle plate, and a double-coaxial contact piece is split into three core wires in the electric connector; the function board is arranged between the middle board and the cover board and is positioned above the core board, and meanwhile, the function board has the function of mutually converting 1553B and RS422 data; the core board comprises a DSP circuit and an FPGA circuit which are connected with each other; the missile launcher has a small volume, can be installed in the missile launcher, can convert 1553B and RS422 data into each other, has the functions of analyzing and recombining the data, further realizes data forwarding among different buses, has a launch control function, and can realize launching of missiles.

Description

Small-size transmission control box

Technical Field

The invention relates to the technical field of launch control, in particular to a small launch control box.

Background

The missile 1553B communication interface conforms to the GJB1188A specification, a GJB599 III series electric connector is selected, the 1553B communication interface needs two double-coaxial contact pieces, and in order to complete communication with a missile, a launching control box needs two double-coaxial contact pieces in the lower interface, but the electric connector is usually large in size, so that the size of the launching control box cannot be miniaturized.

The traditional RS422-1553B launching control box generally comprises an upper interface and a lower interface, wherein the upper interface is generally connected with a launching vehicle or an airplane, the lower interface is connected with a missile, and the launching control box connected with the launching vehicle is generally arranged in a launching box and has small volume constraint. The launch control box connected with the airplane is generally installed in the hair-guiding frame, and the available space in the hair-guiding frame is small, so that the launch control box with the two interfaces cannot be installed in the hair-guiding frame.

Disclosure of Invention

The technical problem to be solved by the present invention is to provide a small-sized launch control box to solve the above-mentioned problems in the background art.

The technical problem solved by the invention is realized by adopting the following technical scheme:

a small-sized launch control box comprises a bottom plate, a middle plate, a cover plate, a power panel, a core panel, a function panel and an electric connector, wherein the power panel is arranged between the bottom plate and the middle plate; the function board is arranged between the middle board and the cover board and is positioned above the core board, and meanwhile, the function board has the function of mutually converting the data of 1553B and RS 422; the core board comprises a DSP circuit and an FPGA circuit which are connected with each other.

In the invention, the power panel comprises a secondary power conversion module, a surge peak suppression module and a filtering module.

In the present invention, the core board further includes a power supply output control circuit.

In the invention, the DSP circuit is connected with the FPGA circuit through an EMIF interface.

In the invention, the function board comprises a three-time power supply conversion circuit, a 1553B circuit, an RS422 circuit, a 232 circuit and a discrete magnitude processing circuit.

In the invention, the three core wires split from the double coaxial contact pieces are a plus wire, a minus wire and a shielding wire.

In the invention, an FPGA data storage unit is arranged in the FPGA circuit.

In the invention, a memory is arranged in the DSP circuit.

In the invention, the operation flow of the emission control box is as follows:

1) data reception

The FPGA circuit receives data of the slave aircraft/missile and stores the data in the FPGA data storage unit, the DSP circuit reads the data in the FPGA data storage unit into a memory in the DSP circuit through an EMIF interface, and an application layer calls an API function to obtain the data according to the requirement;

2) data transmission

The application layer calls an API function to send, stores a data result obtained through calculation into a memory inside the DSP circuit and sends the data result to the FPGA circuit through an EMIF interface, the FPGA circuit temporarily stores received data in an FPGA data storage unit, and a controller of the FPGA circuit sends the temporarily stored data to an airplane or a guided missile;

the aircraft supplies power to the launching control box through the electric connector, the launching control box receives a control command issued by the aircraft after self-checking is normal, and the launching control box supplies power to the missile after receiving the power supply command; the launching control box receives the state information of the missile by using the 1553B communication port, analyzes and recombines the data into RS422 communication data, updates the state information of the missile, and forwards the state information of the missile to the airplane; the launching control box receives an instruction issued by the airplane by using the RS422 communication port, analyzes and recombines the data into 1553B communication data after receiving the data transmitted by the RS422 communication port, so that the 1553B communication protocol between the launching control box and the guided missile is met, and the guided missile forwards the control instruction according to the control logic after the launching control box is packaged; when the missile fails, the launching control box forwards the missile fault to the airplane, and the airplane manually cuts off the power supply of the launching control box according to the control logic after receiving the missile fault information.

Has the advantages that:

1) the hair guide rack is small in size and can be arranged in the hair guide rack;

2) the 1553B and RS422 data can be mutually converted, and the data can be analyzed and recombined, so that data forwarding among different buses is realized;

3) the missile launching system has the launching control function and can realize the launching of missiles.

Drawings

Fig. 1 is a schematic structural diagram of a preferred embodiment of the present invention.

Fig. 2 is a schematic diagram of a preferred embodiment of the present invention.

FIG. 3 is a schematic diagram of the connection according to the preferred embodiment of the present invention.

Detailed Description

In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further explained below by combining the specific drawings.

Referring to fig. 1 to 3, a small-sized launch control box includes a bottom plate 1, a middle plate 2, a cover plate 3, a power supply plate 4, a core plate 5, a function plate 6 and an electrical connector 7, wherein the power supply plate 4 is installed between the bottom plate 1 and the middle plate 2, the core plate 5 is installed in the middle plate 2, the electrical connector 7 is arranged on one side of the middle plate 2, and the function plate 6 is installed between the middle plate 2 and the cover plate 3 and is located above the core plate 5;

the power panel 4 comprises a secondary power conversion module, a surge peak suppression module and a filtering module;

the core board 5 comprises a DSP circuit, an FPGA circuit and a power supply output control circuit;

the function board 6 comprises a tertiary power supply conversion circuit, a 1553B circuit, an RS422 circuit, a 232 circuit and a discrete magnitude processing circuit;

the electric connector 7 is used for realizing signal cross-linking of an upper part and an airplane 8 and signal cross-linking of a lower part and a missile 11, the airplane 8 is connected with a launching control box 10 and the missile 11 which are installed on a missile guide frame 9 through a cable 12, and when the electric connector 7 is designed, the double-coaxial contact element is split into three core wires, namely a plus wire, a minus wire and a shielding wire, for example, MuxA is split into MuxA +, MuxA and MuxA-GND, so that a GJB599 III series electric connector with the double-coaxial contact element is not required to be selected, and the signal of the electric connector 7 selected in the embodiment is J29A-51 ZKW.

In this embodiment, the workflow is as follows:

1) data reception

The FPGA circuit receives data of the slave aircraft/missile and stores the data in the FPGA data storage unit, the DSP circuit reads the data in the FPGA data storage unit into a memory in the DSP circuit through an EMIF interface, and an application layer calls an API function to obtain the data according to the requirement;

2) data transmission

The application layer calls an API function to send, stores a data result obtained through calculation into a memory inside the DSP circuit and sends the data result to the FPGA circuit through an EMIF interface, the FPGA circuit temporarily stores received data in an FPGA data storage unit, and a controller of the FPGA circuit sends the temporarily stored data to an airplane or a guided missile;

the aircraft supplies power to the launching control box through the electric connector 7, the launching control box receives a control instruction issued by the aircraft after self-checking is normal, and the launching control box supplies power to the missile after receiving the power supply instruction; the launching control box receives the state information of the missile by using the 1553B communication port, analyzes and recombines the data into RS422 communication data, updates the state information of the missile, and forwards the state information of the missile to the airplane; the launching control box receives an instruction issued by the airplane by using the RS422 communication port, analyzes and recombines the data into 1553B communication data after receiving the data transmitted by the RS422 communication port, so that the 1553B communication protocol between the launching control box and the guided missile is met, and the guided missile forwards the control instruction according to the control logic after the launching control box is packaged; when the missile fails, the launching control box forwards the missile fault to the airplane, and the airplane manually cuts off the power supply of the launching control box according to the control logic after receiving the missile fault information.

In the embodiment, the DSP circuit has a main frequency of 200 MHz; a memory: FLASH ROM: 1M 16 bit; SDRAM: 8M 32 bit;

power supply: DC 28V;

communication of the electrical connector 7: the 1 path is RS422, the baud rate is adjustable, and the 1553B bus BC node has one path, the baud rate and 1 Mbps; AD: 2-path, resolution 12 bits; DO:3, providing an output of no less than 28V/10A per lane; and 3 paths of DI.

Claims (9)

1. A small-sized launch control box comprises a bottom plate, a middle plate, a cover plate, a power supply plate, a core plate, a function plate and an electric connector, and is characterized in that the power supply plate is arranged between the bottom plate and the middle plate, the core plate is arranged in the middle plate, the electric connector used for realizing up-to-up signal crosslinking with an airplane and down-to-down signal crosslinking with a missile is arranged on one side of the middle plate, and a double-coaxial contact piece is split into three core wires in the electric connector; the function board is arranged between the middle board and the cover board and is positioned above the core board, and meanwhile, the function board has the function of mutually converting the data of 1553B and RS 422; the core board comprises a DSP circuit and an FPGA circuit which are connected with each other.

2. The compact launch control box of claim 1 wherein said power strip comprises a secondary power conversion module, a surge spike suppression module and a filtering module.

3. The compact launch control pod of claim 1 wherein the core board further comprises a power supply output control circuit.

4. The compact transmit control box of claim 1, wherein the DSP circuitry and the FPGA circuitry are connected via an EMIF interface.

5. The compact emission control box of claim 1, wherein the function board comprises a cubic power conversion circuit, a 1553B circuit, an RS422 circuit, a 232 circuit and a discrete quantity processing circuit.

6. The compact emission control box of claim 1, wherein said three cores split from said dual coaxial contacts are + wire, -wire and shield wire.

7. The compact emission control box of claim 1, wherein the FPGA circuit is provided with an FPGA data storage unit.

8. The compact emission control pod of claim 1, wherein the DSP circuitry has a memory disposed therein.

9. The compact launch control box according to any one of claims 1 to 8, wherein the launch control box operates as follows:

1) data reception

The FPGA circuit receives data of the slave aircraft/missile and stores the data in the FPGA data storage unit, the DSP circuit reads the data in the FPGA data storage unit into a memory in the DSP circuit through an EMIF interface, and an application layer calls an API function to obtain the data according to the requirement;

2) data transmission

The application layer calls an API function to send, stores a data result obtained through calculation into a memory inside the DSP circuit and sends the data result to the FPGA circuit through an EMIF interface, the FPGA circuit temporarily stores received data in an FPGA data storage unit, and a controller of the FPGA circuit sends the temporarily stored data to an airplane or a guided missile;

the aircraft supplies power to the launching control box through the electric connector, the launching control box receives a control command issued by the aircraft after self-checking is normal, and the launching control box supplies power to the missile after receiving the power supply command; the launching control box receives the state information of the missile by using the 1553B communication port, analyzes and recombines the data into RS422 communication data, updates the state information of the missile, and forwards the state information of the missile to the airplane; the launching control box receives an instruction issued by the airplane by using the RS422 communication port, analyzes and recombines the data into 1553B communication data after receiving the data transmitted by the RS422 communication port, so that the 1553B communication protocol between the launching control box and the guided missile is met, and the guided missile forwards the control instruction according to the control logic after the launching control box is packaged; when the missile fails, the launching control box forwards the missile fault to the airplane, and the airplane manually cuts off the power supply of the launching control box according to the control logic after receiving the missile fault information.

Images