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Aircraft and control method thereof

A control method and technology for an aircraft, applied in the field of aircraft, can solve the problems of no long-term endurance, no vertical take-off and landing, and the need for a runway.

Active Publication Date: 2016-06-01
CHENGDU FANGZHOU INTELLIGENT CONTROL TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Fixed-wing aircraft use wings to generate lift, need a runway, and do not have the ability to take off and land vertically; rotor-type aircraft have the ability to take off and land vertically, but do not have long-term endurance and the ability to float with the help of wings

Method used

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  • Aircraft and control method thereof

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Embodiment

[0042] Such as figure 1 As shown, an aircraft includes a fuselage 1, a nose 11, a left wing 2, a right wing 3, a control system, a left rudder surface 4, a right rudder surface 5, a left motor 6, a right motor 7, a left vertical tail 8 and a right vertical tail. Tail 9. The two sides of the fuselage are respectively provided with a left wing and a right wing which can glide by means of airflow during level flight, and the bottom of the left wing and the right wing is provided with a left rudder surface and a right rudder surface which can adjust the activity angle, and the bottom of the left wing and the right wing are also respectively A left vertical empennage and a right vertical empennage as a landing gear are provided; a left motor and a right motor equipped with propellers are also respectively arranged on the left wing and the right wing. The output end of the control system is connected with the left motor, the right motor, the left rudder surface and the right rudder...

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Abstract

The invention discloses an aircraft and a control method thereof.The defects of fixed wing type aircrafts and rotary wing type aircrafts in the prior art are overcome.The aircraft comprises an aircraft body, an aircraft head, a left wing, a right wing, a control system, a left control plane, a right control plane, a left motor, a right motor, a left vertical tail and a right vertical tail.The left wing and the right wing are arranged on the two sides of the aircraft body respectively and can glide with the assistance of airflow in the flat flying process, the left control plane and the right control plane are arranged at the bottom of the left wing and the bottom of the right wing and can be adjusted in moving angle, and the left vertical tail and the right vertical tail are arranged at the bottom of the left wing and the bottom of the right wing respectively and serve as an undercarriage.The left motor and the right motor are installed on the left wing and the right wing respectively and are provided with propellers.The output end of the control system is connected with the left motor, the right motor, the left control plane and the right control plane, and the control system comprises a processor, a gyroscope and an accelerometer, wherein the gyroscope and the accelerometer are connected with the processor.By means of the technical scheme, problems in the prior art can be well solved.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to an aircraft and a control method thereof. Background technique [0002] With the development of science and technology, the technology of unmanned aerial vehicles is becoming more and more advanced. There are mainly two types of unmanned aerial vehicles on the market, namely fixed-wing aircraft and rotary-wing aircraft. Due to structural limitations, fixed-wing aircraft and rotary-wing aircraft each have their advantages and disadvantages. Fixed-wing aircraft use wings to generate lift, need a runway, and do not have the ability to take off and land vertically; rotor-type aircraft have the ability to take off and land vertically, but do not have long-term endurance and the ability to float with the help of wings. Contents of the invention [0003] The purpose of the present invention is to overcome the defects of the prior art, to provide an aircraft and its control method, w...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/22B64C9/00B64C19/00B64D27/24B64D31/00G05D1/08
CPCG05D1/0808G05D1/0858B64C9/00B64C19/00B64C27/22B64D27/24B64D31/00B64U10/00B64U2201/10B64U50/19
Inventor 孙宇舟
Owner CHENGDU FANGZHOU INTELLIGENT CONTROL TECH CO LTD
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