阅读说明：本技术 火箭电气系统及其控制方法 (Rocket electrical system and control method thereof ) 是由 彭小波 漆光平 王硕 朴胜志 于 2020-06-15 设计创作，主要内容包括：本发明涉及航空航天技术领域,具体涉及一种火箭电气系统及其控制方法。一种火箭电气系统,包括：对应每一级设置的子电气系统；实现不同级间的所述子电气系统通信连接的总线；其中,所述子电气系统包括：接收级间信号的主计算机；与所述主计算机通信连接的电源以及终端设备；连接在所述主计算机与所述终端设备间的电器控制总成；以及实现所述子电气系统内部通信连接的级内总线。本发明中将火箭总的电气系统分设成若干子电气系统,并将若干子电气系统以集中－分布式设置的方式分布在火箭的每一舱段中,不同的子电气系统以通信总线互联,初步解决电气总系统过于集中导致的电气网络复杂以及稳定性差的问题。(The invention relates to the technical field of aerospace, in particular to a rocket electrical system and a control method thereof. A rocket electrical system comprising: a sub-electrical system provided corresponding to each stage; a bus enabling the sub-electrical system communication connections between different levels; wherein the sub-electrical system comprises: a host computer receiving the inter-stage signal; a power supply and a terminal device communicatively connected to the host computer; an electric appliance control assembly connected between the main computer and the terminal equipment; and an intra-level bus that enables communication connections within the sub-electrical system. According to the invention, the general electric system of the rocket is divided into a plurality of sub-electric systems, the sub-electric systems are distributed in each cabin section of the rocket in a centralized-distributed arrangement mode, and different sub-electric systems are interconnected through a communication bus, so that the problems of complex electric network and poor stability caused by over-centralized electric system are primarily solved.)

1. A rocket electrical system comprising:

a sub-electrical system provided corresponding to each stage;

a bus enabling the sub-electrical system communication connections between different levels;

wherein the sub-electrical system comprises:

a host computer receiving the inter-stage signal;

a power supply and a terminal device communicatively connected to the host computer;

an electric appliance control assembly connected between the main computer and the terminal equipment;

and an intra-level bus that enables communication connections within the sub-electrical system.

2. A rocket electrical system as recited in claim 1, wherein said electrical control assembly comprises a power distribution module, a power supply module, and a main control module, said power distribution module, power supply module, and main control module being interconnected by said intra-level bus.

3. A rocket electrical system as recited in claim 2, wherein said electrical control assembly further comprises any one or more of a timing module, a telemetry module, a signal acquisition module, and a satellite navigation module.

4. A rocket electrical system as recited in any one of claims 1-3, wherein redundant operating mechanisms are employed within said appliance control assembly.

5. A rocket electrical system as recited in claim 4, wherein a two-mode redundant operating mechanism is employed within said appliance control assembly.

6. A rocket electrical system as recited in claim 5, wherein said two-mode redundant operating mechanism is a primary backup mechanism, and wherein the backup is a hot backup.

7. A rocket electrical system as recited in claim 4, wherein three-mode and above redundancy mechanisms are employed within said appliance control assembly, said three-mode and above redundancy mechanisms employing minority majority-compliant voting mechanisms.

8. A rocket electrical system as recited in any one of claims 5-7, wherein said intra-stage buses are provided in at least two sets.

9. A rocket electrical system as claimed in any one of claims 5-7, wherein said bus and said intra-stage bus are both switched communication buses.

10. A rocket electrical system as recited in claim 9, wherein the communication links are established stage-by-stage upon random power-up between the stages.

11. A rocket electrical system according to claim 10 wherein each stage is further provided with a rocket ground interface.

12. A control method, comprising:

acquiring a power supply instruction;

the ground power equipment is connected with the rocket-ground interface to establish rocket-ground communication;

acquiring a ground instruction, wherein the ground instruction comprises a power distribution instruction and a power failure instruction;

judging whether the ground command is a power distribution command or not;

if yes, sending a power distribution instruction step by step in a relay mode through the bus and the intra-stage bus, supplying power to electrical components on each branch by the power supply module, and establishing communication connection between the terminal equipment and the main computer;

judging whether the ground command is a power-off command or not;

if so, the power module stops supplying power to the electrical element.

Technical Field

The invention relates to the technical field of aerospace, in particular to a rocket electrical system and a control method thereof.

Background

The existing carrier rocket electrical system is mainly centralized in structure and has a unified center for calculation, control and information interaction, once a central controller fails, the rocket has a full rocket fault and is not beneficial to flight, and the reliability needs to be improved. Due to excessive concentration, the cable net of the whole arrow is very complex, and the cable winding path is not good and heavy.

In order to solve the above problem, patent CN110988564A discloses a segmented rocket electrical system, comprising: the multistage electrical systems are correspondingly arranged in all cabin sections of the rocket; each level of electric system comprises a battery, a control device and an execution device; the control devices of the electrical systems at all levels are connected through bus communication. The whole electrical system is arranged in different cabin sections in a distributed mode, and the problems of poor stability and complex network caused by centralized arrangement of the electrical system are solved.

However, the existing electrical equipment has a single function, and the number of electrical equipment required in distributed arrangement is large, which results in complex system topology and heavy weight, and causes a certain negative effect on carrying capacity.

Disclosure of Invention

Therefore, the technical problem to be solved by the invention is to overcome the defect of complex structure of the rocket electrical system in the prior art, thereby providing a rocket electrical system and a control method thereof.

In order to solve the above problems, the present invention provides a rocket electrical system comprising: a sub-electrical system provided corresponding to each stage; a bus enabling the sub-electrical system communication connections between different levels; wherein the sub-electrical system comprises: a host computer receiving the inter-stage signal; a power supply and a terminal device communicatively connected to the host computer; an electric appliance control assembly connected between the main computer and the terminal equipment; and an intra-level bus that enables communication connections within the sub-electrical system.

Furthermore, the electrical appliance control assembly comprises a power distribution module, a power supply module and a main control module, wherein the power distribution module, the power supply module and the main control module are interconnected through the intra-level bus.

Furthermore, the electrical control assembly further comprises any one or more of a timing module, a telemetry module, a signal acquisition module and a satellite navigation module.

Furthermore, a redundancy working mechanism is adopted in the electric appliance control assembly.

Furthermore, a two-mode redundancy working mechanism is adopted in the electric appliance control assembly.

Further, the two-module redundancy working mechanism is a main backup mechanism, wherein the backup is a hot backup.

Furthermore, a triple-modular redundancy mechanism and a triple-modular redundancy mechanism are adopted in the electric appliance control assembly, and a minority majority-compliant voting mechanism is adopted in the triple-modular redundancy mechanism and the triple-modular redundancy mechanism.

Further, the intra-stage buses are provided in at least two sets.

Further, the bus and the intra-level bus are both switched communication buses.

Further, after being randomly electrified, the communication connection is established step by step in the order of a competition mode.

Furthermore, each stage is also provided with an arrow-ground interface.

The invention also provides a control method, which comprises the following steps: acquiring a power supply instruction;

the ground power equipment is connected with the rocket-ground interface to establish rocket-ground communication;

acquiring a ground instruction, wherein the ground instruction comprises a power distribution instruction and a power failure instruction;

judging whether the ground command is a power distribution command or not;

if yes, sending a power distribution instruction step by step in a relay mode through the bus and the intra-stage bus, supplying power to electrical components on each branch by the power supply module, and establishing communication connection between the terminal equipment and the main computer;

judging whether the ground command is a power-off command or not;

if so, the power module stops supplying power to the electrical element.

The technical scheme of the invention has the following advantages:

1. the rocket electrical system in the invention comprises: a sub-electrical system provided corresponding to each stage; a bus for realizing the communication connection of the sub-electrical systems between different levels; wherein, sub-electric system includes: a host computer receiving the inter-stage signal; a power supply and a terminal device communicatively connected to the host computer; an electric appliance control assembly connected between the main computer and the terminal equipment; and an intra-level bus that implements the intra-subsystem communication connections.

According to the invention, the electric system of the rocket assembly is divided into a plurality of sub-electric systems, the sub-electric systems are distributed in each cabin level of the rocket in a centralized-distributed arrangement mode, and different sub-electric systems are interconnected through a communication bus, so that the problems of complex electric appliance network and poor stability caused by over-centralized electric system are primarily solved.

Furthermore, an electrical control assembly is arranged in each sub-electrical system, and the electrical control assembly integrates the basic functions of various electrical components, so that the problem that the carrying capacity is influenced due to the fact that the number of electrical equipment in a cabin section is too large because a plurality of electrical equipment are arranged for realizing different control functions is solved.

2. The electric appliance control assembly in the rocket electric system adopts a redundancy working mechanism, and when one system of the redundancy working mechanism fails, a backup system is arranged to ensure the working stability of the electric appliance control assembly, so that the working stability of the whole rocket electric system is improved.

3. The two-mode redundancy working mechanism in the rocket electric system is a main backup mechanism, wherein the backup is hot backup, and the hot backup system is also in a standby starting state while the main system works, so that when the main system fails, the main system can be replaced by the main system in the shortest time, and the influence caused by the failure is reduced to the maximum extent.

4. The invention has the advantages that the intermediate-level buses of the rocket electrical system are arranged into at least two sets, so that at least one set is ensured to be in a standby state, and the problem of communication interruption caused by the failure of the single-set intermediate-level bus is solved.

5. According to the rocket electrical system, communication connection is established step by step in a competition mode sequence after all the levels are randomly electrified, and the transmission mode ensures that non-adjacent equipment is not communicated directly, so that the length of an intra-level communication bus and the flexibility of connection expansion among all the equipment are reduced.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.

FIG. 1 is a diagram of a distributed architecture of a rocket electrical system according to example 1 of the present invention;

FIG. 2 is a diagram of distributed power supply of a rocket electrical system in embodiment 1 provided by the present invention;

FIG. 3 is a schematic structural diagram of an electrical appliance control assembly according to embodiment 1 of the present invention;

fig. 4 is a schematic structural diagram of a dual-redundancy main/standby mode in embodiment 1 according to the present invention;

FIG. 5 is a schematic structural diagram of a triple redundancy voting scheme in embodiment 1 of the present invention;

fig. 6 is a flowchart of a control method of a rocket electrical system according to embodiment 2 of the present invention.

Detailed Description

The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.