A method and system for communication switching between an electric rudder system on a missile and a power distributor

Abstract

This invention discloses a communication switching method and system between an onboard electric rudder system and a power distributor, belonging to the field of onboard communication technology. The flight control unit and the electric rudder system communicate via an onboard cable network using a 1553B bus. The power distributor, as a subsystem of the electric rudder system, communicates with the electric rudder system using RS422. Different sub-addresses distinguish whether the command data sent from the flight control unit to the rudder system is rudder system command data or power distributor command data, and whether the feedback data from the rudder system to the flight control unit is rudder system feedback data or power distributor feedback data, thus achieving communication between the flight control unit, the electric rudder system, and the power distributor. This reduces the number of onboard cables, leaving space and weight margins for other subsystems or combat components, thereby improving the overall performance of the rocket.

Description

Technical Field

[0001] This invention relates to the field of missile-borne communication technology, and in particular to a communication switching method and system for a missile-borne electric rudder system and a power distributor. Background Technology

[0002] The electric control system is a classic actuator in the aerospace field and a crucial component of the flight control system for integrated systems such as rockets and drones. The power distributor is a vital energy distribution component in the aerospace field and an important part of the energy network for integrated systems like rockets and drones. In rocket design, separate onboard cables are typically laid for the control system and power distributor to physically connect to the flight control assembly. This allows the rocket to receive command data sent from the flight control assembly to the control system, as well as command data sent from the flight control assembly to the power distributor. Simultaneously, feedback data from both the control system and the power distributor is fed back to the flight control assembly. However, allocating separate onboard cables for the control system and power distributor limits the weight and space margin of other individual components or combat parts, which is detrimental to improving the overall performance of the rocket. Summary of the Invention

[0003] The purpose of this invention is to improve the overall performance of rockets and to provide a communication switching method and system for the onboard electric control system and the power distributor.

[0004] The objective of this invention is achieved through the following technical solution:

[0005] Firstly, a communication switching method between a missile-mounted electric rudder system and a power distributor is provided, including the following:

[0006] The flight control system and the electric rudder system communicate via the missile's onboard cable network using the 1553B bus;

[0007] As a subsystem of the electric steering system, the power distributor uses different sub-addresses of the electric steering system to receive control command data from the steering system and send feedback data to the power distributor.

[0008] In a communication switching method between an onboard electric rudder system and a power distributor provided in some possible embodiments, the power distributor and the electric rudder system communicate using RS422.

[0009] In a communication switching method between an onboard electric rudder system and a power distributor provided in some possible embodiments, the sub-address includes sub-address 1, sub-address 2, sub-address 3, and sub-address 4. Sub-address 1 is used to receive control command data issued by the flight control assembly to the electric rudder system, sub-address 2 is used to send feedback data from the rudder system, sub-address 3 is used to receive control command data issued by the flight control assembly to the power distributor, and sub-address 4 is used to send feedback data from the power distributor.

[0010] In a communication switching method between an onboard electric rudder system and a power distributor provided in some possible embodiments, the use of different sub-addresses of the electric rudder system to receive control command data between the rudder system and the power distributor includes:

[0011] After receiving the instruction data, sub-address 1 of the electric steering system parses it according to the agreed frame format and uses it to control the operation of the electric steering system.

[0012] After receiving the instruction data, sub-address 3 of the electric steering system assembles the data according to the agreed frame format and sends it to the power distributor via the RS422 serial port to control the operation of the power distributor.

[0013] In a communication switching method between an onboard electric rudder system and a power distributor provided in some possible embodiments, the use of different sub-addresses of the electric rudder system to transmit feedback data between the rudder system and the power distributor includes:

[0014] Feedback data from the electric rudder system is written into the register at sub-address 2 according to the agreed frame format. After the flight control assembly sends the rudder system sub-address 2 data transmission command, the data is sent to the 1553B bus.

[0015] After receiving the feedback data from the power distributor sent by the power distributor via the RS422 serial port, the electric rudder system frames the data according to the agreed frame format and writes the framed data into the register corresponding to sub-address 4. After waiting for the flight control unit to send the data transmission command to sub-address 4, the system sends the data to the 1553B bus.

[0016] In a communication switching method between an onboard electric rudder system and a power distributor provided in some possible embodiments, the instruction data received by the sub-address 1 includes controlling the movement of the rudder motor, reading and writing rudder system control parameters, and updating the rudder system control program online.

[0017] In a communication switching method between an onboard electric rudder system and a power distributor provided in some possible embodiments, the instruction data received by the sub-address 3 includes controlling the power distributor to perform power distribution operations to other individual units and updating the power distributor control program.

[0018] Secondly, a communication switching system is provided, including an electric rudder system, a flight control assembly, and a power distributor. The flight control assembly and the electric rudder system are connected via an onboard cable network using a 1553B bus. The power distributor, as a subsystem of the electric rudder system, uses different sub-addresses of the electric rudder system to receive control command data from the rudder system and send feedback data to the power distributor.

[0019] In a communication switching system provided in some possible embodiments, the electric steering system and the power distributor are connected via an RS422 bus.

[0020] In a communication switching system provided in some possible embodiments, the electric steering system and the power distributor are physically connected via plug-in connectors.

[0021] It should be further noted that the technical features corresponding to the above-mentioned options and embodiments can be combined or substituted with each other to form new technical solutions without conflict.

[0022] Compared with the prior art, the beneficial effects of the present invention are:

[0023] (1) This invention enables communication between the flight control unit and the electric rudder system via an onboard cable network using a 1553B bus. The power distributor, as a subsystem of the electric rudder system, communicates with the electric rudder system using RS422. The different sub-addresses distinguish whether the command data sent by the flight control unit to the rudder system is rudder system command data or power distributor command data, and whether the feedback data returned by the rudder system to the flight control unit is rudder system feedback data or power distributor feedback data. This achieves communication between the flight control unit, the electric rudder system, and the power distributor. This reduces the number of onboard cables, leaving space and weight margins for other subsystems or combat components, and improving the overall performance of the rocket.

[0024] (2) The present invention can reduce the cost of the entire missile by reducing the number of cables on the missile and improve the cost-effectiveness of the rocket.

[0025] (3) It is scalable and can extend communication switching to communication switching between other types of single units on the missile, as well as communication conversion between 1553B communication and other communication methods, thereby improving the overall performance and cost-effectiveness of the rocket. Attached Figure Description

[0026] Figure 1 This is a flowchart illustrating a communication switching method between an onboard electric rudder system and a power distributor, as shown in an embodiment of the present invention. Detailed Implementation

[0027] The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0028] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0029] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other. Parts of the present invention not described in detail are common knowledge to those skilled in the art.

[0030] In one exemplary embodiment, a communication switching method between a missile-mounted electric rudder system and a power distributor is provided, including the following:

[0031] The flight control system and the electric rudder system communicate via the missile's onboard cable network using the 1553B bus;

[0032] As a subsystem of the electric steering system, the power distributor uses different sub-addresses of the electric steering system to receive control command data from the steering system and send feedback data to the power distributor.

[0033] Specifically, this invention primarily uses 1553B bus communication as the main communication method on the missile. The flight control unit and the electric rudder system communicate via the 1553B bus through the missile's cable network. The power distributor, as a subsystem of the electric rudder system (a subsystem refers to a device or unit that receives data transmission services via the 1553B bus), communicates with the electric rudder system using RS422 and is connected via plug-in connectors. The power distributor, as a subsystem of the electric rudder system, distinguishes between rudder system command data and power distributor command data sent by the flight control unit based on different sub-addresses, and between rudder system feedback data and power distributor feedback data returned by the electric rudder system to the flight control unit, thus enabling communication between the flight control unit, the electric rudder system, and the power distributor. This reduces the number of cables on the missile, leaving space and weight margins for other subsystems or combat components, thereby improving the overall performance of the rocket.

[0034] Furthermore, the electric rudder system not only needs to communicate with the flight control unit, but also, as an intermediary, needs to receive command data (frame format as shown in Table 1) sent by the flight control unit to the distributor via the 1553B bus. It then parses the data and sends it to the distributor using RS422 communication according to the agreed-upon command frame format (frame format as shown in Table 2). The distributor sends its feedback data (frame format as shown in Table 3) back to the rudder system via RS422 communication. The electric rudder system parses the data, frames it according to the agreed-upon command frame format (frame format as shown in Table 4), and writes it into the register of the corresponding sub-address. After waiting for the flight control unit to send the "transmit data command word" for that sub-address, it sends the distributor's feedback data to the 1553B bus. The method of writing the command sub-frame into the sub-address register is implemented through program code according to the interface timing of the 1553B bus communication chip.

[0035] Specifically, the sub-address includes sub-address 1, sub-address 2, sub-address 3 and sub-address 4. Sub-address 1 is used to receive control command data issued by the flight control assembly to the electric rudder system. Sub-address 2 is used to send feedback data from the electric rudder system. Sub-address 3 is used to receive control command data issued by the flight control assembly to the power distribution unit. Sub-address 4 is used to send feedback data from the power distribution unit.

[0036] Table 1. Command data frame format sent by the flight control unit to the power distribution unit.

[0037]

[0038] Table 2. Format of command data frames sent from the steering system to the power distributor.

[0039]

[0040]

[0041] Table 3. Feedback data frame format sent from the power distributor to the steering system

[0042]

[0043] Table 4. Format of the power distribution feedback data frame sent from the rudder system to the flight control assembly.

[0044]

[0045]

[0046] As shown in Table 1, the rudder system receives the self-test command data sent by the flight control unit to the power distributor as: "0300007E 8011 2023 1031 1620 0000 0000 0000 1A69". After removing the frame header "0300 007E" and the checksum "1A69", the remaining data "8011 2023 1031 16200000 0000 0000" is framed according to the frame format in Table 2. The framed self-test command data is: "7E7E507E 8011 2023 1031 1620 0000 0000 0000 0351", which is then sent to the power distributor via the RS422 serial port.

[0047] After receiving the self-test command, the power distributor performs a self-test. Upon completion, it sends self-test feedback data (feedback frame format as shown in Table 3) to the control system. The self-test feedback data is: “7E7E 507E0811 2023 1031 16200000 0000 0000 029D”. After receiving the self-test feedback data from the power distributor to the flight control system, the control system removes the frame header “7E7E 507E” and the checksum “029D”, and frames the remaining data “0811 2023 1031 1620 0000 00000000” according to Table 4. The framed self-test feedback data is: “0400 007E 0811 2023 103116200000 0000 0000”. 1A67” writes it into the register at sub-address 4, and waits for the flight control unit to send the “transmit data command word” at sub-address 4 before sending the feedback data of the distributor to the 1553B bus.

[0048] For specific data processing procedures, please refer to... Figure 1 The flight control unit acts as a bus controller, controlling the data flow on the 1553B bus, while the electric rudder system acts as a remote terminal. Different sub-addresses of the electric rudder system are used to receive control commands and send feedback data to the rudder system and power distributor.

[0049] Furthermore, the specific functions of different sub-addresses are as follows:

[0050] Sub-address 1: After receiving the instruction data, the sub-address 1 of the electric servo system parses it according to the agreed frame format, and uses it to control the servo motor movement, read and write servo system control parameters, and update the servo system control program online.

[0051] Sub-address 2: Feedback data from the electric rudder system is written to the register of sub-address 2 according to the agreed frame format. After waiting for the bus controller (flight control assembly) to send the rudder system sub-address 2 data transmission command, the data is sent to the 1553B bus.

[0052] Sub-address 3: After receiving the instruction data, the sub-address 3 of the electric steering system frames the data according to the agreed frame format and sends it to the power distributor via the RS422 serial port. This is used to control the power distributor to perform power distribution operations on other individual units, update the power distributor control program, etc.

[0053] Sub-address 4: After receiving the feedback data from the distributor sent by the distributor through the RS422 serial port, the electric rudder system frames it according to the agreed frame format and writes the framed data into the register corresponding to sub-address 4. After waiting for the bus controller (flight control combination) to send the rudder system sub-address 4 data transmission command, the system sends the data to the 1553B bus.

[0054] In another exemplary embodiment, a communication switching system is provided, including an electric rudder system, a flight control assembly, and a power distributor. The flight control assembly and the electric rudder system are connected via an onboard cable network using a 1553B bus. The power distributor, as a subsystem of the electric rudder system, uses different sub-addresses of the electric rudder system to receive control command data and send feedback data between the rudder system and the power distributor. The electric rudder system and the power distributor communicate via an RS422 bus. The flight control assembly and the electric rudder system are physically connected using the onboard cable network, and the electric rudder system and the power distributor are physically connected in a stacked manner using plug-in connectors. Compared to connecting the electric rudder system and the flight control assembly separately via cables, this reduces the onboard space occupied by the electric rudder system and the power distributor.

[0055] The above detailed embodiments are a description of the present invention. It should not be considered that the specific embodiments of the present invention are limited to these descriptions. For those skilled in the art, several simple deductions and substitutions can be made without departing from the concept of the present invention, and all of these should be considered to fall within the protection scope of the present invention.

Claims

1. A communication switching method between an onboard electric control system and a power distributor, characterized in that, Includes the following: The flight control system and the electric rudder system communicate via the missile's onboard cable network using the 1553B bus; As a subsystem of the electric rudder system, the power distributor uses different sub-addresses of the electric rudder system to receive control command data from the rudder system and send feedback data. The sub-addresses include sub-address 1, sub-address 2, sub-address 3 and sub-address 4. Sub-address 1 is used to receive control command data issued by the flight control assembly to the electric rudder system. Sub-address 2 is used to send feedback data from the rudder system. Sub-address 3 is used to receive control command data issued by the flight control assembly to the power distributor. Sub-address 4 is used to send feedback data from the power distributor. The method of using different sub-addresses of the electric steering system to receive control command data and send feedback data to the steering system and power distributor includes: After receiving the instruction data, sub-address 1 of the electric steering system parses it according to the agreed frame format and uses it to control the operation of the electric steering system. After receiving the instruction data, sub-address 3 of the electric steering system assembles the data according to the agreed frame format and sends it to the power distributor via the RS422 serial port to control the operation of the power distributor. Feedback data from the electric rudder system is written into the register at sub-address 2 according to the agreed frame format. After the flight control assembly sends the rudder system sub-address 2 data transmission command, the data is sent to the 1553B bus. After receiving the feedback data from the power distributor sent by the power distributor via the RS422 serial port, the electric rudder system frames the data according to the agreed frame format and writes the framed data into the register corresponding to sub-address 4. After waiting for the flight control unit to send the data transmission command to sub-address 4, the system sends the data to the 1553B bus.

2. The communication switching method between the missile-mounted electric control system and the power distributor according to claim 1, characterized in that, The power distributor and the electric steering system communicate using RS422.

3. The communication switching method between the missile-mounted electric control system and the power distributor according to claim 1, characterized in that, The instruction data received by sub-address 1 includes controlling the movement of the servo motor, reading and writing servo system control parameters, and updating the servo system control program online.

4. The communication switching method between the missile-mounted electric control system and the power distributor according to claim 1, characterized in that, The instruction data received by sub-address 3 includes controlling the power distributor to perform power distribution operations to other individual machines and updating the power distributor control program.

5. A communication switching system, comprising an electric rudder system, a flight control assembly, and a power distribution unit, characterized in that, The flight control assembly and the electric rudder system are connected via a 1553B bus through the missile's onboard cable network. The power distributor, as a subsystem of the electric rudder system, uses different sub-addresses of the electric rudder system to receive control command data from the rudder system and send feedback data to the power distributor. The sub-address includes sub-address 1, sub-address 2, sub-address 3 and sub-address 4. Sub-address 1 is used to receive control command data issued by the flight control assembly to the electric rudder system. Sub-address 2 is used to send feedback data from the rudder system. Sub-address 3 is used to receive control command data issued by the flight control assembly to the power distribution unit. Sub-address 4 is used to send feedback data from the power distribution unit. The method of using different sub-addresses of the electric steering system to receive control command data and send feedback data to the steering system and power distributor includes: After receiving the instruction data, sub-address 1 of the electric steering system parses it according to the agreed frame format and uses it to control the operation of the electric steering system. After receiving the instruction data, sub-address 3 of the electric steering system assembles the data according to the agreed frame format and sends it to the power distributor via the RS422 serial port to control the operation of the power distributor. Feedback data from the electric rudder system is written into the register at sub-address 2 according to the agreed frame format. After the flight control assembly sends the rudder system sub-address 2 data transmission command, the data is sent to the 1553B bus. After receiving the feedback data from the power distributor sent by the power distributor via the RS422 serial port, the electric rudder system frames the data according to the agreed frame format and writes the framed data into the register corresponding to sub-address 4. After waiting for the flight control unit to send the data transmission command to sub-address 4, the system sends the data to the 1553B bus.

6. A communication switching system according to claim 5, characterized in that, The electric steering system is connected to the power distributor via an RS422 bus.

7. A communication switching system according to claim 6, characterized in that, The electric steering system and the power distributor are physically connected via plug-in connectors.

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