Auxiliary rudder surface control device for tilting ducted aircraft
A control device and aircraft technology, applied in aircraft control, aircraft parts, transportation and packaging, etc., can solve the problems of reduced aerodynamic efficiency of spoilers, increased spoiler hinge torque, and impact on aircraft loading capacity, etc., to reduce equipment Effects of weight, increased aerodynamic efficiency, and increased structural strength
Active Publication Date: 2021-12-28
JIANGXI HONGDU AVIATION IND GRP
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Problems solved by technology
[0002] Tilting ducted aircraft has the characteristics of fixed wings and rotors. During the vertical take-off and landing stage, flat spoilers are often arranged under the duct to control the attitude of the aircraft during the take-off phase. The aerodynamic efficiency of the flow sheet is reduced, which requires an increase in the area of the spoiler, which in turn leads to an increase in the hinge moment of the spoiler and an increase in weight, which ultimately affects the loading capacity of the aircraft
After the tilting duct aircraft is tilted to a horizontal state, the tail and rudder are used to control the aircraft, and the spoiler is in a useless state, but the flat auxiliary rudder control device is in the flow field at the tail of the duct, which will easily lead to an increase in the overall aircraft resistance , affecting the flight efficiency of the aircraft
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[0019] In order to make the technical means, creative features, goals and effects achieved by the present invention easy to understand, the present invention will be further described below in conjunction with specific illustrations.
[0020] see Figure 1 to Figure 8 The auxiliary rudder surface control device of the tilting ducted aircraft includes a honeycomb spoiler 1, a rotating mechanism 2, a propeller shaft 3, a duct 4, a propeller 5, a spoiler shrinkage shaft 6, and a spoiler deflection shaft 7; , the propeller 5 installed on the propeller shaft 3 is arranged under the duct 4, and the rudder surface composed of four honeycomb spoilers 1 is arranged under the propeller 5, and the honeycomb spoiler 1 is connected with the spoiler contraction shaft 6 , the spoiler shrinkage shaft 6 is connected with the spoiler deflection shaft 7, the spoiler deflection shaft 7 is connected with the rotation mechanism 2, the rotation mechanism 2 is installed on the propeller shaft 3, the ...
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The auxiliary rudder surface control device of the tilting ducted aircraft includes a honeycomb spoiler, a rotating mechanism, a propeller shaft, a duct and a propeller; wherein, a propeller installed on the propeller shaft is arranged under the duct, and a four-wheel drive is arranged below the propeller. The rudder surface composed of honeycomb spoilers, each honeycomb spoiler is connected with the corresponding spoiler contraction shaft, the spoiler contraction shaft is connected with the spoiler deflection shaft, and the spoiler deflection shaft is connected with the rotation mechanism Connected, the rotating mechanism is installed on the propeller shaft; and a shrinking mechanism for controlling the shrinkage of the honeycomb spoiler is arranged in the shrinking shaft of the spoiler; by using a honeycomb and retractable rudder surface, the hinge moment of the spoiler can be reduced, And reduce the motor power required by the propeller shaft, reduce the weight of the equipment; at the same time, the honeycomb spoiler is used to increase the structural strength, reduce the structural weight, have strong anti-separation ability, reduce the size of the spoiler, and effectively increase the economic efficiency of the aircraft.
Description
technical field [0001] The invention relates to the technical field of aircraft structure design, in particular to an auxiliary rudder surface control device for a tilting ducted aircraft. Background technique [0002] Tilting ducted aircraft has the characteristics of fixed wings and rotors. During the vertical take-off and landing stage, flat spoilers are often arranged under the duct to control the attitude of the aircraft during the take-off phase. The decrease of the aerodynamic efficiency of the spoiler requires an increase in the area of the spoiler, which in turn leads to an increase in the hinge moment of the spoiler and an increase in weight, which ultimately affects the loading capacity of the aircraft. After the tilting duct aircraft is tilted to a horizontal state, the tail and rudder are used to control the aircraft, and the spoiler is in a useless state, but the flat auxiliary rudder control device is in the flow field at the tail of the duct, which will eas...
Claims
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IPC IPC(8): B64C9/06B64C11/00
CPCB64C9/06B64C11/00
Inventor 杨波冷智辉李自启杨昌发吴萍胡志东黄琪
Owner JIANGXI HONGDU AVIATION IND GRP