Low-cost electrical system suitable for recyclable carrier rocket

An electrical system and launch vehicle technology, applied in general control systems, control/regulation systems, instruments, etc., can solve the problems of complex composition, unequipped equipment, and large amount of communication data on the rocket, and meet the requirements of bus technology and high Bandwidth, easy portability

An electrical system and launch vehicle technology, applied in general control systems, control/regulation systems, instruments, etc., can solve the problems of complex composition, unequipped equipment, and large amount of communication data on the rocket, and meet the requirements of bus technology and high Bandwidth, easy portability

CN110515296APending Publication Date: 2019-11-29江苏深蓝航天有限公司
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  • Low-cost electrical system suitable for recyclable carrier rocket
  • Low-cost electrical system suitable for recyclable carrier rocket

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Effect test

Embodiment 1

[0038] See attached figure 1 , the present disclosure provides a low-cost electrical system suitable for recoverable launch vehicles, including a multi-stage system, each stage system includes a first bus, a second bus, a number of nodes, and each node is simultaneously connected to the first The bus and the second bus are connected; the first buses of the adjacent two-level systems are connected to each other by a separate connector; the second buses of the adjacent two-level systems are connected to each other by a separate connector; the synchronization data between the nodes The exchange occurs periodically, that is, synchronous data exchange is performed between the nodes at fixed time intervals.

[0039]In this embodiment, the first network is formed between the first bus and each node, and the second network is formed between the second bus and each node. When the first network fails, each node will automatically select the second network to continue working; Similarly...

Embodiment 2

[0044] A low-cost electrical system suitable for recoverable launch vehicles, including the above-mentioned redundant system; each stage of the system is connected to a flight controller, an integrated navigation device, a servo mechanism, and a power distributor through each node; there is and only any one stage The flight controller is in the working state; when the flight controller in the non-working state detects that the communication of the flight controller of the previous priority sequence is cut off or fails, it will start the flight controller according to the sequence.

[0045] The priority sequence of the present disclosure means that there are multiple identical components in a redundant system, and the component startup has a sequence code, such as the first coded part, the second coded part, the third coded part...the third coded part only detects It will not start until both the first coding part and the second coding part are in communication cutoff or failure...

Embodiment 3

[0060] The aircraft described in this implementation includes the above-mentioned aircraft redundancy system. In addition, the aircraft should also include a load device, which connects the load device with the second separation connector of the secondary system, and connects the disconnector of the primary system. Connector. The dropout connector enables the connection of the primary system to the surface platform.

[0061] It is worth noting that both the first-level integrated navigation device and the second-level navigation device include a satellite navigation module, an inertial navigation module and a rate gyro module, and realize external perception through a satellite antenna. It is guaranteed that after each level is separated, the integrated navigation device of this level can be used for positioning and navigation, so as to realize recovery. And the integrated navigation device adopts satellite navigation positioning and inertial navigation composite method to pr...

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Abstract

The present disclosure provides a recyclable launch vehicle electrical system. The electrical system comprises multiple stages of systems, wherein each stage of systems comprises a first bus, a secondbus and multiple nodes, each node is connected with both the first bus and the second bus, the first buses of two adjacent stages of systems are connected with each other through a separation connector, the second buses of two adjacent stages of systems are connected with each other through a separation connector, synchronous data exchange is carried out among the nodes at fixed time intervals, each node can be connected with an independent main station, a standby main station can be started to take over control when detecting that the main station is lost, all parts can still independently complete work after separation is achieved, and thereby conditions are provided for recovery of separated rockets. The invention further provides a carrier rocket utilizing the electrical system. The system architecture not only has advantages of high bandwidth, high real-time performance, high reliability and easy expansion, but also the bus supports online switching of the main station, the system is convenient to transplant and simple and flexible in configuration, and is very suitable for a recyclable system rocket electrical system.

Description

technical field [0001] The present disclosure relates to the field of launch vehicles, and more particularly to a low-cost electrical system suitable for recoverable launch vehicles. Background technique [0002] The electrical system of the launch vehicle is the core system of the launch vehicle. It is responsible for signal acquisition, attitude control, timing command issuance, and control command execution of the launch vehicle. It needs to meet the requirements of high reliability and strong real-time performance. The electrical system architecture directly affects the comprehensive performance and reliability of the launch vehicle. [0003] At present, the electrical systems of launch vehicles in active service in China are all non-recyclable structures. Most of the electrical systems adopt a non-bus system or a dual-redundant 1553B bus system. Navigation devices and rocket computers are installed on the upper stage, and disposable silver-zinc batteries or thermal batt...

Claims

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Application Information

Patent Timeline
29 Nov 2019
Publication
CN110515296A
IPC
G05B9/03
CPC
G05B9/03
Inventors
不公告发明人