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

Duct single screw aircraft based on Magnus effect

A technology of aircraft and propeller, which is applied in the field of aircraft, can solve problems such as poor safety, complex structure, and difficult control of flight movements, and achieve the effects of improving safety, high flight efficiency, and improving the influence of uncertain air turbulence

Active Publication Date: 2010-12-01
HARBIN INST OF TECH
View PDF3 Cites 13 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a ducted single-propeller aircraft based on the Magnus effect, so as to solve the problems of poor safety, complex structure, and difficult control of various flight actions in the existing coaxial double-propeller unmanned aircraft

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
  • Duct single screw aircraft based on Magnus effect
  • Duct single screw aircraft based on Magnus effect
  • Duct single screw aircraft based on Magnus effect

Examples

Experimental program
Comparison scheme
Effect test

specific Embodiment approach 1

[0018] Specific implementation one: as Figures 1 to 10 As shown, the ducted single-propeller aircraft based on the Magnus effect described in this embodiment includes a steering gear device 1, an airflow adjustment device 2, a power device 3 and an aircraft housing 4; the aircraft housing 4 includes an outer circle Cylinder 41, the steering gear device 1, the air flow adjustment device 2 and the power device 3 are arranged from bottom to top and are centrally installed on the outer cylinder 41 in the axial direction (ie the steering gear device 1, the airflow adjustment device 2 and the power device 3). The centerline of the device 3 coincides with the axis of the outer cylinder 41);

[0019] The steering gear device 1 is composed of four steering gear units, and each steering gear unit includes a hollow wheel 11 and a motor 12; The core wheels 11 are all placed in the inner cavity of the outer cylinder 41, and the four motors 12 are installed on the outer side wall of the o...

specific Embodiment approach 2

[0023] Specific implementation two: as Figures 1 to 4 As shown, the power device 3 in this embodiment is composed of a propeller 31 , a power source 32 and a frame 33 , the power source 32 is fixed on the upper end of the outer cylinder 41 through the frame 33 , and the propeller 31 is installed on the drive of the power source 32 . On the shaft, the drive shaft of the power source 32 drives the propeller 31 to rotate, and the axis of the drive shaft of the power source 32 coincides with the axis of the outer cylinder 41 . The end position of the drive shaft (rotation shaft) of the power source 32 is directly above the total mass center point 6 of the aircraft to ensure flight attitude stability. The propeller is fixed at the end of the rotating shaft. Other components and connection relationships are the same as in the first embodiment.

specific Embodiment approach 3

[0024] Specific implementation three: as Figures 1 to 4 As shown, the aircraft housing 4 in this embodiment further includes an inner cylinder 42, the inner cylinder 42 is coaxially arranged in the inner cavity of the outer cylinder 41, and the inner cylinder 42 is located below the power device 3, The lower end surface of the inner cylinder 42 is flush with the lower end surface of the outer cylinder 41 ; the plurality of grid plates 21 are arranged in the annular area between the inner cylinder 42 and the outer cylinder 41 . The provision of the inner cylinder 42 further ensures that the helical air flow is converted into a vertical jet air flow. Other compositions and connection relationships are the same as in the first or second embodiment.

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 relates to a duct single screw aircraft based on Magnus effect, relating to a duct single screw aircraft. The invention solves the problems of poor safety, complex structure and difficult realization of various flying behaviour control of the traditional coaxial double-screw unmanned aircraft. The invention has the technical scheme that a steering engine duct (I), an airflow regulation duct (II) and a power duct (III) are sequentially communicated; a power device (3) is used for generating spiral airflows in the power duct (III); an airflow regulation device (2) is used for converting the spiral airflows in the power duct (III) into vertical jet-type airflows; and the vertical jet-type airflows regulated in the steering engine duct (I) generate Magnus effect force on the lateral surfaces of a hollow core wheel (11). In the invention, the Magnus effect force generated during the rotation of the hollow core wheel is used as control input, and the aircraft further realizes various flying behaviours. The invention has the advantages of simple and compact structure, low energy consumption, safety, flexible behaviour, and the like.

Description

technical field [0001] The invention relates to a ducted single-propeller aircraft, in particular to a ducted single-propeller aircraft based on the Magnus effect, and belongs to the technical field of aircraft. Background technique [0002] At present, the coaxial twin-propeller UAV adopts two propellers, and under the same constraints, the propeller radius is only 70% of that of the single-rotor aircraft. Since the fuselage is included in the area of ​​the paddle, the overall longitudinal dimension is only about 60% of that of a single-propeller aircraft with a tail, thus reducing the moment of inertia in pitch and yaw. The above structural features show that the steering performance of the coaxial twin-prop aircraft is better than that of the single-prop aircraft with tail. But this is a design that uses two independent power units or a complex heading control system and a complex mechanical transmission system. At the same time, the high-speed rotating propeller is a fa...

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): B64C23/08B64C9/06
Inventor 赵杰金弘哲樊继壮王忠信
Owner HARBIN INST OF TECH
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