CN106564612A

CN106564612A - Taking off structure for carrier-borne aircraft

Info

Publication number: CN106564612A
Application number: CN201610555422.4A
Authority: CN
Inventors: 张斌
Original assignee: Individual
Current assignee: Individual
Priority date: 2015-10-08
Filing date: 2016-07-15
Publication date: 2017-04-19
Also published as: CN206394907U

Abstract

The invention relates to a taking off structure for a carrier-borne aircraft, in particular to a taking off structure for the carrier-borne aircraft of a vertical take-off and landing fixed-wing aircraft in patent 2015203521439. The taking off structure is characterized by consisting of a driving motor, a motor deceleration driving device, an aircraft taking off rotary moment driving output shaft and a gear clutch, wherein an aircraft wing structure is in a beam wing structure; the driving motor and the motor deceleration driving device are mounted and fixed under a flight deck; the aircraft taking off rotary moment driving output shaft is driven and controlled by the driving motor and the motor deceleration driving device, and runs through the flight deck; an aircraft taking off rotary moment shaft driving output shaft is divided into two parts by the gear clutch, and an active driving shaft is under the gear clutch; and the aircraft taking off rotary moment driving output shaft is jointed to a complete coaxial shaft through the gear clutch, and a complete rotary axial-moving whole can be combined in a shaft end and hole end structure manner.

Description

Carrier-borne aircraft takes off structure

（One）Technical field

The structure the present invention relates to a kind of carrier-borne aircraft takes off, especially with the main wing of the definition of patent 2015203521439, patent A kind of carrier-borne aircraft of the VTOL fixed wing airplane of aircraft tails of 2015207683907 definition takes off structure.

（Two）Background technology

At present, patent 2015203521439, in the aircraft of VTOL fixed wing airplane, can consume when autonomous dynamic takes off Substantial amounts of energy, for load, voyage, mobility have large effect.

（Three）The content of the invention

In view of in the past the shortcoming of VTOL aircraft with it is not enough, it is an object of the invention to provide one kind on surface ship by warship The carrier-borne aircraft that the electric energy of ship conveniently takes off takes off structure.

The technical solution adopted for the present invention to solve the technical problems is：A kind of carrier-borne aircraft takes off structure, it is characterized in that：By Patent 2015203521439, patent 2015207683907, the fixed wing airplane of VTOL fixed wing airplane technical scheme are made Take off object for carrier-borne aircraft, by motor, motor reduction driving device, take off turning moment and drive output shaft, gear Clutch is constituted, and aircraft wing structure is beam type wing structure.

Motor, motor reduction driving device are fixed on below naval vessels flight-deck, take off turning moment Drive output shaft motor driven, motor reduction driving device to drive, control and fly through deck, take off turning moment The dynamic output shaft of axle is divided into two by engagement sleeve, is active drive shaft below engagement sleeve, more than engagement sleeve be from Moving axis, takes off turning moment and drives output shaft to be connected into complete concentric shafts by engagement sleeve, and with shaft end, hole The frame mode at end be combined into a complete, shaft end with nose end as bearing rotary, the entirety of axially-movable.

Take off aircraft when turning moment drives active drive axial direction one direction of output shaft to accelerate to rotate synchronously even Speed accelerates rotation, and when active drive axle reversely accelerates rotation, aircraft moment departs from, i.e., driven rotating rate of shaft is less than or equal to During active drive rotating rate of shaft, aircraft is at the uniform velocity or acceleration rotates, and driven rotating rate of shaft is more than active drive axle rotation speed During rate, driven shaft upward vertical movement, aircraft moment depart from, and take off the driven shaft and aircraft of the dynamic output shaft of axis of torque Wing spar is integrated, and parallel with aircraft Z vertical shafts through the center of gravity of airplane, i.e., parallel with aircraft yaw axle, takes off rotation Torque drives output shaft, aircraft wing spar to make using metal material, by welding or casting, fastened by screw technique system It is made for an overall structure.

In addition a kind of carrier-borne aircraft takes off a refined carrier-borne aircraft takeoff method of structure, includes following step in the process of taking off vertically Suddenly：

Step 1, patent 2015203521439, the aircraft of VTOL fixed wing airplane pass through engagement sleeve and take off Turning moment drives the active drive axle of output shaft to be closely connected, and the left and right entirely dynamic aileron of aircraft manipulates backspin in servomechanism and goes to Takeoff condition angle, i.e., positive and negative to rotate to the aerodynamic effect less than 45 degree the acute angle for balancing, patent 2015207683907 is rotated VTOL fixed wing airplane moves vertical tail entirely, makes aircraft move full vertical tail complete into an angle of 90 degrees, i.e. aircraft with the aircraft X longitudinal axis The circle that dynamic vertical tail is rotated with aircraft is tangent, makes to move full vertical tail resistance minimum in aircraft rotary motion.

Step 2, motor start, motor torque square through motor reduction driving device deceleration, amplify again by flying Machine turning moment of taking off drives output shaft output, drives the rotation of VTOL fixed wing airplane, while VTOL fixed-wing flies Two electromotors of machine are counter each other to be pushed away, and takes advantage of a situation to form and take off turning moment driving output shaft turning moment in the same direction, and Driven rotating rate of shaft is less than or equal to active drive rotating rate of shaft, and driving output shaft is same with turning moment is taken off to make aircraft Step rotation.

Step 3, when rotating speed be close to VTOL fixed wing airplane take off require when, motor brake deceleration, aircraft rise Torque of flying in circles drives the active drive axle synchronous brake of output shaft to slow down, and two electromotors of VTOL fixed wing airplane continue It is counter each other to push away, and continuation acceleration of taking advantage of a situation, the driven rotating rate of shaft for taking off turning moment driving output shaft is made more than master It is dynamic to drive rotating rate of shaft, the left and right entirely dynamic aileron of VTOL fixed wing airplane further to adjust balance under the control of the computer Aerodynamic condition, engagement sleeve are separated under airplane ascensional force effect into upper and lower two parts, and aircraft is taken advantage of a situation and taken off vertically, and depart from female Warship.

Step 4, VTOL fixed wing airplane are rotated with itself, and the mode of vertical ascent rises to safe altitude, Servomechanism is controlled by airborne computer, the pitch of the complete dynamic aileron in left and right is manipulated respectively, or is manipulated the inclined of complete dynamic vertical tail Gyration, realizes that VTOL fixed wing airplane is realized from rotary motion flying to tapered auger line moving the transformation of flight, The resultant motion of the linear motion that the circular flight motion that i.e. three dimensions inside radius becomes larger is gradually increasing with height.

Step 5, VTOL fixed wing airplane control servomechanism by airborne computer, manipulate respectively in safe altitude The pitch of the complete dynamic aileron in left and right, and the deflection angle of complete dynamic vertical tail is manipulated, continued with the motion flight of tapered auger line Climb, and the radius of tapered auger line motion flight increasing finally breaks away from tapered auger line with rectilinear flight campaign Motion flight, finally realizes the motion of rectilinear flight mode, in the process real time management or so engine power and thrust side To.

It is the reverse movement of step 4, step 5 in VTOL fixed wing airplane descent.

The invention has the beneficial effects as follows, the present invention provides patent 2015203521439, and VTOL fixed wing airplane is in warship The technical scheme taken off on ship, takes off relative to the helicopter of traditional autonomous dynamic, and AV8B's takes off vertically with significantly excellent More property, for fleet air defense, ocean escort, aircraft carrier miniaturization is respectively provided with important meaning and far-reaching influence.

（Four）Description of the drawings

Fig. 1 is that carrier-borne aircraft of the present invention takes off the schematic perspective view of structure.

Fig. 2 is that carrier-borne aircraft of the present invention takes off the engagement sleeve generalized section of structure.

Fig. 3 is that the take off turning moment of taking off of structure of carrier-borne aircraft of the present invention drives that output shaft aircraft portions are three-dimensional to be illustrated Figure.

1. motor in figure, 2. engagement sleeve, 3. engagement sleeve shaft end, 4. engagement sleeve nose end, 5. spar.

（Five）Specific embodiment

The main wing of the definition of patent 2015203521439, a kind of VTOL of aircraft tail of the definition of patent 2015207683907 Fixed wing airplane, by taking Fig. 1, Fig. 2, Fig. 3 as an example, takes off the driven shaft and aircraft wing spar of the dynamic output shaft of axis of torque It is integrated, and it is parallel with aircraft Z vertical shafts through the center of gravity of airplane, i.e., it is parallel with aircraft yaw axle, take off axis of torque The active drive axle of dynamic output shaft and motor reduction driving device one, motor reduction driving device can be reduction gear box, Belt deceleration group etc., and Motor drive driven, when aircraft weight is less big, motor can from three asynchronous machines With competent, can just control rotating speed using the converter of industrial general, rotation take off boost phase airborne computer with it is carrier-borne Motor computer data is exchanged, linkage, so as to the rotating speed for accurately controlling motor, coordinates VTOL fixed wing airplane Complete dynamic aileron pitch, aircraft engine acc power controls to adjust airplane ascensional force, takes off from warship in real time.

Claims

1. a kind of carrier-borne aircraft takes off structure, it is characterized in that：By patent 2015203521439, patent 2015207683907, vertically The fixed wing airplane of fixed wing airplane technical scheme of rising and falling takes off object as carrier-borne aircraft, and by motor, decelerating through motor drives Device, takes off turning moment and drives output shaft, engagement sleeve to constitute, and aircraft wing structure is beam type wing structure, is driven Galvanic electricity machine, motor reduction driving device are fixed on below naval vessels flight-deck, are taken off turning moment and are driven output Axle motor driven, motor reduction driving device drive, control and fly through deck, take off the dynamic output of axis of torque Axle is divided into two by engagement sleeve, is active drive shaft below engagement sleeve, more than engagement sleeve is driven shaft, aircraft Turning moment of taking off drives output shaft to be connected into complete concentric shafts by engagement sleeve, and with shaft end, the structure of nose end Mode be combined into a complete, shaft end with nose end as bearing rotary, the entirety of axially-movable.

2. a kind of carrier-borne aircraft according to claim 1 takes off structure, it is characterized in that：Take off turning moment and drive output Aircraft synchronous uniform velocity or acceleration when active drive axial direction one direction of axle accelerates rotation rotates, and active drive axle reversely accelerates During rotation aircraft moment depart from, i.e., driven rotating rate of shaft be less than or equal to active drive rotating rate of shaft when, aircraft at the uniform velocity or Accelerate rotation, when driven rotating rate of shaft is more than active drive rotating rate of shaft, driven shaft upward vertical movement, aircraft moment take off From, the driven shaft for taking off the dynamic output shaft of axis of torque is integrated with aircraft wing spar, and pass through the center of gravity of airplane and Aircraft Z vertical shafts are parallel, i.e., parallel with aircraft yaw axle, take off turning moment and drive output shaft, aircraft wing spar to use Metal material makes, and becomes an overall structure by welding or casting, the making of fastened by screw technique.

3. a kind of carrier-borne aircraft according to claim 1 takes off structure, it is characterized in that carrier-borne aircraft takes off the refined carrier-borne of structure Machine takeoff method comprises the steps in the process of taking off vertically：

4. step 2, motor start, motor torque square through motor reduction driving device deceleration, amplify again by aircraft Turning moment of taking off drives output shaft output, drives the rotation of VTOL fixed wing airplane, while VTOL fixed wing airplane Two electromotors are counter each other to be pushed away, and taking advantage of a situation to form and take off turning moment and drive output shaft turning moment in the same direction, and from The moving axis speed of rotation be less than or equal to active drive rotating rate of shaft, make aircraft with take off turning moment drive output shaft synchronous Rotation.

5. step 3, when rotating speed be close to VTOL fixed wing airplane take off require when, motor brake deceleration is taken off Turning moment drives the active drive axle synchronous brake of output shaft to slow down, and two electromotors of VTOL fixed wing airplane continue mutual Push away for counter, and continuation of taking advantage of a situation accelerates, the driven rotating rate of shaft for taking off turning moment driving output shaft is made more than actively Rotating rate of shaft, the left and right entirely dynamic aileron of VTOL fixed wing airplane is driven further to adjust Balance Air under the control of the computer Dynamic state, engagement sleeve are separated under airplane ascensional force effect into upper and lower two parts, and aircraft is taken advantage of a situation and taken off vertically, and depart from mother ship carrier.

6. step 4, VTOL fixed wing airplane are rotated with itself, and the mode of vertical ascent rises to safe altitude, are led to Airborne computer control servomechanism is crossed, the pitch of the complete dynamic aileron in left and right, or the deflection for manipulating complete dynamic vertical tail is manipulated respectively Angle, realizes that VTOL fixed wing airplane is realized from rotary motion flying to tapered auger line moving the transformation of flight, i.e., The resultant motion of the linear motion that the circular flight motion that three dimensions inside radius becomes larger is gradually increasing with height.

7. step 5, VTOL fixed wing airplane control servomechanism by airborne computer in safe altitude, manipulate respectively left The pitch of right complete dynamic aileron, and the deflection angle of complete dynamic vertical tail is manipulated, continue to climb with tapered auger line motion flight Rise, and the radius of tapered auger line motion flight increasing last broken away from tapered auger line with rectilinear flight campaign and transported Dynamic flight, finally realizes the motion of rectilinear flight mode, in the process real time management or so engine power and thrust direction.