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Spin control system and aircraft

A control system and aircraft technology, applied in the field of aircraft, can solve problems such as slow flight speed, loss of airflow power, serious accidents, etc., and achieve the effect of inhibiting self-rotation

Active Publication Date: 2017-02-08
古丰科技(深圳)有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although the helicopter can take off and land vertically, the airflow induced by the helicopter rotor will diverge to the surroundings, resulting in a large loss of airflow power, and the flight speed is relatively slow.
Moreover, the helicopter rotor is huge and exposed, and it is very easy to cause serious accidents due to contact with objects

Method used

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  • Spin control system and aircraft
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  • Spin control system and aircraft

Examples

Experimental program
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Embodiment

[0057] Such as figure 1 As shown, the aircraft 100 includes an aircraft body 10 , the aircraft body 10 is in the shape of a domed saucer, which is similar to the shape of a flying saucer in film and television works, or similar to the shape of a bowler hat. The structural material of the aircraft body 10 can be the same material as that of the aircraft. When the aircraft 100 is flying at high altitude, the aircraft body 10 is under internal pressure, so duralumin with high tensile strength and fatigue resistance needs to be used as the skin material. The frame of the aircraft body 10 is made of super duralumin, and the reinforced frame that bears a relatively large load is made of high-strength structural steel or titanium alloy.

[0058] The aircraft body 10 is hollow, and the hollow interior is an accommodating space. The interior of the aircraft body 10 can be divided into several parts, such as the cockpit, crew compartment, storage compartment, toilet and so on. The dome...

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PUM

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Abstract

The invention provides a spin control system applied to an aircraft. The aircraft comprises a power unit in circling motion; the spin control system comprises an air inlet ring and an air outlet ring; the airflow in the air inlet ring and the airflow in the air outlet ring are communicated when the power unit rotates; a plurality of air outlet ring flow-disturbing fins are arranged on the air outlet ring, and the air outlet ring flow-disturbing fins translate the tangential airflow of the power unit into the radial airflow. The invention further provides an aircraft with the spin control system. The spin control system and the aircraft disclosed by the invention adopt the air outlet ring flow-distributing fins to translate the highly rotated airflow inhaled and coerced by the power unit into the radially ejected airflow, namely, the spin momentum balance of the spin airflow is realized, and the carried function of the spin flow is sufficiently utilized. The spin control system defuses the independent rotation of the aircraft caused by the power unit on the aircraft, and guarantees the normal flight.

Description

technical field [0001] The invention relates to the field of aircraft, in particular to a spin control system and an aircraft. Background technique [0002] The more common aircraft are fixed-wing aircraft and helicopters. Fixed-wing aircraft refers to an aircraft that is heavier than air and flies in the atmosphere with forward thrust or pull generated by the power plant and lift generated by the fixed wings of the fuselage. But fixed-wing aircraft all will go through long acceleration or deceleration when taking off or landing, and turning is difficult, and instant steering cannot be realized. [0003] A helicopter is a heavier-than-air aircraft that takes off and lands vertically by means of one or more rotors. Although the helicopter can take off and land vertically, the airflow induced by the helicopter rotor will diverge around, causing a large loss of airflow power and flying at a slower speed. And the helicopter rotor is huge and exposed, which is very easy to cau...

Claims

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Application Information

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IPC IPC(8): B64C39/00B64C39/06B64D27/16
CPCB64C39/001B64C39/064B64D27/16
Inventor 不公告发明人
Owner 古丰科技(深圳)有限公司
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