Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Engine mechanical accelerator operating system for helicopter

An engine throttle, operating system technology, applied in aircraft power plant, aircraft parts, transportation and packaging, etc., can solve problems such as accurate relationship

Pending Publication Date: 2021-01-05
CHINA HELICOPTER RES & DEV INST
View PDF11 Cites 2 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the implementation of the active control method, only the relationship between the collective distance and the fuel supply is established, and the other quantities that cause load changes cannot establish an accurate relationship with the fuel supply, and can only rely on the feedback adjustment of the speed change

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Engine mechanical accelerator operating system for helicopter
  • Engine mechanical accelerator operating system for helicopter
  • Engine mechanical accelerator operating system for helicopter

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0037] The principle of the engine mechanical throttle operating system for a helicopter of the present invention is to combine active control quantity and passive control quantity signals through mechanical connection, so as to realize precise control of engine power.

[0038] 1. Active control signal:

[0039] The active control signal is mainly realized through the collective pitch-throttle linkage mechanism.

[0040] The primary task of collective pitch-throttle linkage design is to design collective pitch-throttle linkage characteristics, to determine the parameter relationship of collective pitch-throttle linkage, so as to achieve the balance between the required power and the available power of the engine in the change of rotor load.

[0041] The determination of collective distance-throttle linkage parameters mainly takes the following three steps;

[0042] Calculate the given helicopter collective distance-required power characteristic curve;

[0043] Engine given t...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The invention belongs to the technical field of helicopter power system design, and discloses an engine mechanical accelerator operating system for a helicopter, which comprises an accelerator ring, atotal distance rod, a first elastic pull rod, a rotor rotating speed adjusting executing mechanism, a total distance accelerator connecting rocker arm, an output elastic pull rod, a second elastic pull rod and a total distance linkage mechanism, the total distance rod and the total distance linkage mechanism form a total distance pre-input adjusting structure; the rotor rotating speed adjusting executing mechanism and the second elastic pull rod form a rotor rotating speed feedback input adjusting structure; the accelerator ring and the first elastic pull rod form an accelerator ring manual input adjusting structure; the rotor rotating speed feedback input adjusting structure and the manual input adjusting structure are connected in series and connected with the total distance pre-input adjusting structure in parallel through the total distance accelerator connecting rocker arm. The total-pitch accelerator connecting rocker arm is connected to an engine accelerator rocker arm throughan output elastic pull rod, so that the power of an engine output shaft is balanced with the supply and demand of required power of a helicopter, and the rotor rotating speed is kept constant.

Description

technical field [0001] The invention belongs to the technical field of helicopter power system design, and relates to an engine mechanical throttle operating system for a helicopter. Background technique [0002] The flight conditions and states of the helicopter are constantly changing, such as take-off, hovering, climbing, cruising, sliding, landing, etc. The power required by the helicopter is different in different flight states, so the engine throttle control system needs to adjust the output shaft power of the engine in real time to balance it with the supply and demand of the power required by the helicopter, so as to keep the rotor speed constant. [0003] Generally, the larger the collective distance, the greater the power required. Therefore, in the design process of the engine throttle control system, the collective pitch-throttle linkage device is usually used to actively control the engine throttle, and the position information of the collective pitch lever is ...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
IPC IPC(8): B64D31/02
CPCB64D31/02
Inventor 段勇亮王青松林森什刘芳
Owner CHINA HELICOPTER RES & DEV INST
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com