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Short takeoff and landing (STOL) small aircraft based on tilting power system

A power system and aircraft technology, applied in the direction of aircraft, automatic control, aircraft power transmission, etc., can solve the problems of low flight speed, complex structure, short range and flight time, etc.

Inactive Publication Date: 2011-08-24
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Small fixed-wing aircraft have high flight speed and long range, but have high requirements for take-off and landing conditions (runway length, runway flatness); although small unmanned helicopters have low requirements for take-off and landing conditions, they have complex structures and low flight speeds. Less range and flight time

Method used

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  • Short takeoff and landing (STOL) small aircraft based on tilting power system
  • Short takeoff and landing (STOL) small aircraft based on tilting power system
  • Short takeoff and landing (STOL) small aircraft based on tilting power system

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example

[0035] Example: short takeoff-level flight-short landing

[0036] When used in an environment with harsh take-off and landing conditions, first tilt the nose at a certain angle to generate an upward and forward pulling force, and activate the attitude adjustment system for short-distance takeoff. After reaching a certain altitude, the power system slowly turns to a horizontal state. After the horizontal flight speed accumulates to a certain value, the attitude adjustment system is turned off and converted to a normal level flight. After completing the mission and returning home, tilt the power system up and use the attitude control system when landing, reduce the flight speed, and perform a short-distance landing at a low speed.

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PUM

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Abstract

The invention provides a small aircraft, comprising an aircraft body (3), an airfoil (11), a horizontal tail (4), a vertical tail (9), a power system part (1) located at the front part of the aircraft body (3), and a propeller (14) located at the front part of the power system (1); the small aircraft is characterized by further comprising a tilting mechanism (2) located at the upper middle part of the aircraft body, wherein the power system (1) is connected with the aircraft in a tiltable manner by the tilting mechanism (2), so that the propeller (14) of the power system (1) can axially tilt correspondingly. The small aircraft further comprises a pitching posture adjusting system arranged at the tail part of the aircraft body and used for controlling the pitching of the aircraft when the aircraft takes off.

Description

technical field [0001] The invention relates to the design of a small aircraft with a short-distance take-off and landing function, and belongs to the field of aviation aircraft design. Background technique [0002] Small unmanned aerial vehicles have the advantages of low cost, good cost-effectiveness, no risk of casualties, strong survivability, good maneuverability, and convenient use. With the rapid development of material science, microelectronics technology, and computer technology, small unmanned aerial vehicles are widely used in military tasks such as battlefield reconnaissance and surveillance, positioning and calibration, damage assessment, electronic warfare, and border patrols, nuclear radiation detection, aerial photography, etc. , Aviation prospecting, disaster monitoring, traffic patrol, public security monitoring and other civilian fields. [0003] Aircraft that can complete complex tasks often use conventional rolls to take off and land, and the roll dista...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/02B64C13/18B64C13/24
Inventor 万志强雷萤王耀坤周磊王川
Owner BEIHANG UNIV
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