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Integrated controller and aircraft applied to aircraft

An integrated controller and aircraft technology, applied in the field of aircraft control, can solve the problems of inconvenient maintenance, large size, and poor scalability, and achieve the effect of fast and simple plugging process, good scalability, and improved efficiency

Active Publication Date: 2022-08-09
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the electrical control system in traditional rockets is composed of multiple discrete stand-alone machines, which are large in size, heavy in weight, poor in scalability and inconvenient in maintenance, and are no longer suitable for the needs of small rockets.

Method used

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  • Integrated controller and aircraft applied to aircraft
  • Integrated controller and aircraft applied to aircraft
  • Integrated controller and aircraft applied to aircraft

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Embodiment Construction

[0028] In order to make the technical solutions and advantages of the embodiments of the present application more clear, the exemplary embodiments of the present application will be described in further detail below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present application, and Not all embodiments are exhaustive. It should be noted that the embodiments in the present application and the features of the embodiments may be combined with each other in the case of no conflict.

[0029] This embodiment provides an integrated controller, which can be applied to an aircraft. The aircraft can be an aircraft that can fly in the atmosphere, such as an airship, an airplane, etc., or a spacecraft that can fly outside the atmosphere, such as an artificial satellite, a manned spacecraft, a space probe, a space shuttle, etc., or it can also be for rockets or missiles.

[0030] figure 1 This is an explode...

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Abstract

Embodiments of the present application provide an integrated controller applied to an aircraft and the aircraft, wherein the integrated controller includes: a chassis, and functional modules, a backplane, and an interface board disposed in the chassis; the inner wall of the chassis is provided with a plurality of modules slot, at least two functional modules are inserted into the module slot from the front end of the chassis along the direction of the center line of the chassis; the backplane is perpendicular to the center line of the chassis, and is connected to the rear end of the chassis; the interface board is connected to the chassis The center line of the interface board is vertical, is connected to the rear end of the chassis, and is located on the outside of the backplane; the interface in the interface board exposes the rear end surface of the chassis. The integrated controller applied to the aircraft and the aircraft provided by the embodiments of the present application have the advantages of integration and miniaturization.

Description

technical field [0001] The present application relates to aircraft control technology, and in particular, to an integrated controller applied to an aircraft and an aircraft. Background technique [0002] A rocket is an aircraft that relies on the reaction force generated by the ejection of the working medium by the engine to propel forward. It is a vehicle for space flight, and is usually used to launch satellites, manned spacecraft and lunar probes. In recent years, with the continuous advancement of the commercialization market, commercial rockets have emerged in the market. Most commercial rockets are small solid launch vehicles with relatively low cost, short launch cycles, and flexible launch sites, which do not depend on fixed launch sites. For example, vehicle-mounted mobile launch methods can be used. [0003] In order to meet the development and launch requirements of small rockets, the internal power system and electrical control system are also developing towards...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F1/18G06F1/20G06F13/38
CPCG06F1/183G06F1/20G06F13/382Y02T50/40
Inventor 杨春雷丛恩博姜开陈俊杰史若冲常新月苏忠威万桂斌魏敏孙润宇李学思张涛樊姣荣王若凡任新宇王冀宁年永尚
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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