CN208198818U

CN208198818U - Rudder formula coaxal helicopter

Info

Publication number: CN208198818U
Application number: CN201820766042.XU
Authority: CN
Inventors: 杨伟
Original assignee: Individual
Current assignee: Individual
Priority date: 2018-05-22
Filing date: 2018-05-22
Publication date: 2018-12-07
Anticipated expiration: 2028-05-22

Abstract

The utility model discloses a kind of rudder formula coaxal helicopters, including coaxal helicopter ontology, vertically arranged the front direction rudder of front body two sides difference of coaxal helicopter ontology, two front direction rudder left-right rotations in vertical plane, a left and right directions rudder is respectively set in the body two sides, a rear direction rudder is arranged in the swing in vertical plane of left and right directions rudder, the body rear end, and rear direction rudder swings in the horizontal plane.The utility model is not only simple in structure, and can easily control the heading and flying height of helicopter, cheap.

Description

Rudder formula coaxal helicopter

Technical field

The utility model relates to a kind of rudder formula coaxal helicopters.

Background technique

The flight control mode of coaxal helicopter is the pitch by periodically adjusting upper layer and lower layer propeller, so that spiral shell Rotation paddle generates different lift in different orientation, causes paddle disk to tilt, goes straight up to what function was flown to different directions to reach The operation of purpose, this set system is extremely complex.

Summary of the invention

The purpose of this utility model is to provide a kind of rudder formula coaxal helicopters, are not only simple in structure, and can The heading and flying height of helicopter are easily controlled, it is cheap.

The purpose of this utility model is achieved in that a kind of rudder formula coaxal helicopter, including coaxal helicopter sheet Body, vertically arranged the front direction rudder of front body two sides difference of coaxal helicopter ontology, two front direction rudders are vertical A left and right directions rudder, left and right directions rudder front and back in vertical plane is respectively set in left-right rotation in face, the body two sides It swings, a rear direction rudder is arranged in the body rear end, and rear direction rudder swings in the horizontal plane.

The utility model use omnidirection rudder formula flight control system, i.e., helicopter be all around respectively mounted with it is a set of Rudder, for controlling the heading of helicopter, and the pitch of propeller adjusts the height for only being used to control flight.

Rudder at left and right sides of helicopter is used for the control in former and later two directions of helicopter, when the upper end of left and right rudder forward When inclination, the lower pressure gas stream that propeller generates flows through rudder face, can be generated due to the difference of the front and back air-flow velocity of rudder body forward Thrust, at this time helicopter flight forward；Otherwise when left and right rudder hypsokinesis, helicopter flies backward.

Rudder at two before and after helicopter flies for controlling a left side, the right side flies and rotation.When the upper end of front and back rudder is tilted to the left When, thrust to the left is generated, thus realize that a left side for helicopter flies, on the contrary when the rudder Right deviation of front and back, the helicopter right side flies.When front rudder "Left"-deviationist Afterwards when rudder Right deviation, helicopter is rotated to the left, and after front rudder Right deviation when rudder "Left"-deviationist, helicopter is rotated to the right.

Compared with traditional coaxial helicopter, the characteristics of system, is: 1, traditional coaxial helicopter to realize landing, it is preceding fly, Afterwards fly, Zuo Fei, the right side flies, hovers, turning to these movements, be to be realized by the pitch of periodic adjustment propeller, this is just So that various operations check and balance, control system is extremely complex, and winged hand will pass through very strict training, could grasp flight skill Ingeniously；And in rudder formula control system, the pitch of propeller adjusts the landing for being served only for control helicopter and hovering height, this is just So that the hovering of helicopter becomes to be very easy to control, by rudder complete independently, this makes direction again for the control of heading Control become very simple, therefore be easily achieved automatic Pilot.2, since rudder can bring resistance, area cannot Too big, this regulating power for allowing for the system is restricted, therefore rudder formula helicopter flies compared with pure helicopter Speed is slower, and wind loading rating decline can not make a stunt flying.

Detailed description of the invention

The utility model is described in further detail below in conjunction with attached drawing.

Fig. 1 is the schematic view of the front view of the utility model；

Fig. 2 is the overlooking structure diagram of the utility model.

Specific embodiment

A kind of rudder formula coaxal helicopter, as shown in Figure 1 and Figure 2, including being gone straight up to upper limb 1 and the coaxial of bottom wing 2 Machine ontology, the front body two sides of coaxal helicopter ontology pass through respectively steering engine and shaft 4 it is vertically arranged a front direction Rudder 3, two front direction rudders 3 swing in vertical plane, and a left and right directions rudder 5 is respectively set in the body two sides, A rear direction rudder is arranged in the swing in vertical plane around respective shaft of left and right directions rudder 5, the body rear end 6, rear direction rudder 6 swings around its shaft in the horizontal plane.

In addition to the rudder of front, rear, left and right, remaining is essentially identical with traditional coaxial helicopter structure.

In Fig. 2: two front rudders are synchronous interaction, by a servo driving, the upper edge of rudder can around respective shaft it is synchronous to Left or right side inclination；Port and starboard is synchronous interaction, and by a servo driving, the upper edge of rudder can be around respective shaft forward Side or back sweep；Rudder is by a servo driving afterwards, can alone to the left or right side inclination.

Claims

1. a kind of rudder formula coaxal helicopter, including coaxal helicopter ontology, it is characterized in that: the front of coaxal helicopter ontology Vertically arranged the front direction rudder of body two sides difference, two front direction rudder left-right rotations in vertical plane, the body A left and right directions rudder, the swing in vertical plane of left and right directions rudder, the body rear end setting is respectively set in two sides A rear direction rudder, rear direction rudder swing in the horizontal plane.