CN205836409U - One can self-service change type land and air double-used aircraft - Google Patents

Abstract

The utility model discloses one can self-service change type land and air double-used aircraft, belong to aircraft field.This utility model is mainly made up of aircraft body, conversion drive mechanism and lifting support mechanism etc., the wheeled rotor of aircraft body is fixed on the two ends of rotor crossbeam, conversion drive mechanism is rotated by gear conjugate control rotor crossbeam, makes wheeled rotor change in horizontally and vertically direction；Described lifting support mechanism includes that the 3rd motor, lifting screw and undercarriage, the 3rd motor are fixed on aircraft body, and undercarriage is rotationally connected with lifting screw, drives lifting screw relative flight device body to carry out elevating movement by the 3rd motor.This utility model is provided with the undercarriage with elevating function on aircraft body, so that aircraft can be changed between offline mode and land locomotion pattern voluntarily, intelligence degree is high, is suitable for investigating use in the wild.

Description

One can self-service change type land and air double-used aircraft

Technical field

This utility model relates to vehicle technology field, more particularly, it relates to one can self-service change type land and air double-used Aircraft.

Background technology

Quadrotor is a kind of relatively conventional and classical small aircraft, is widely used in military surveillance, resource is surveyed Survey, the civilian technical field such as take photo by plane.This Flight Vehicle Structure is compact, motion is flexible, suitably makes in small space or complex environment With.Need aircraft lands to scout under some particular cases, as inside building, the small space such as the thick grass woods are internal.In order to Realize the multifunction development of aircraft so that it is picture photographing can either be carried out on land, investigation can be observed again from the air, So proposing the concept of land and air double-used aircraft, and the most preferably developed.But empty land of the prior art is dual-purpose The structure of aircraft mostly is on quadrotor and directly adds four wheels, or is still that the rotation forces relying on rotor is empty Gas moves ahead, and these aircraft exist and control and the defect such as complicated in mechanical structure, ground running efficiency is low.

Through retrieval, prior art exists and directly utilizes the technical scheme that rotor uses as land locomotion wheel, as Chinese Patent Application No.: 201510251452.1, the applying date: on May 15th, 2015, invention and created name is: a kind of empty land two With quadrotor, this application case discloses the dual-purpose quadrotor in a kind of empty land, including four groups of actuators and driving Deformation mechanism, drives deformation mechanism to include driving motor, two driving shafts and two driven shafts, and driving shaft and driven shaft are arranged on Supporting on seat, drive motor to be provided with two motor output shafts, each motor output shaft is all connected by shaft coupling and a driving shaft Connecing, each driving shaft is all connected by gear pair and a driven shaft, and wherein the rotor support of two groups of actuators is respectively with two Individual driving shaft connects, and the rotor support of other two groups of actuators is connected with two driven shafts respectively.Four rotations in this application case During rotor aircraft flight aloft, rotor is positioned at horizontal direction, it is provided that flying power, when using on land, directly rotates rotor, Making it can be at road traveling as wheel, but this aircraft can only rely on operator manually to help changes, it is impossible to Field is changed voluntarily, and intelligence degree is low.

And for example Chinese Patent Application No.: 201610028258.1, the applying date: on January 13rd, 2016, this application case discloses A kind of novel airphibian wheel system, this wheel system can provide land locomotion and two kinds of duties of airflight.In land Under ground transport condition, car foreign steamer is in state perpendicular to the ground, and the running motor in transmission case module passes through transmission case gear train band The rotation of motor-car foreign steamer, thus realize land locomotion function；Aloft under state of flight, outer wheel can be adjusted by configuration modular converter Whole is surface state, the flight motor work of the most dual-purpose wheel module abreast, drives propeller rotational, thus realizes flying in the air Row function.

There is identical problem in this application case and above-mentioned first patent application, although can convert, but its turn Change and need dependence to be accomplished manually, it is impossible to realize intellectualized operation, it is therefore desirable to improve further.

Utility model content

1. utility model to solve the technical problem that

The purpose of this utility model is to overcome the rotor of land and air double-used aircraft in prior art can not self-service conversion Not enough, it is provided that one can self-service change type land and air double-used aircraft, this utility model is provided with on aircraft body to be had The undercarriage of elevating function, so that aircraft can be changed between offline mode and land locomotion pattern voluntarily, intelligent Degree is high, is suitable for investigating use in the wild.

2. technical scheme

For reaching above-mentioned purpose, the technical scheme that this utility model provides is:

One of the present utility model can self-service change type land and air double-used aircraft, including aircraft body, conversion driving machine Structure and lifting support mechanism, the wheeled rotor of described aircraft body is fixed on the two ends of rotor crossbeam, changes drive mechanism Rotated by gear conjugate control rotor crossbeam, make wheeled rotor change in horizontally and vertically direction；

Described lifting support mechanism includes that the 3rd motor, lifting screw and undercarriage, the 3rd motor are fixed on aircraft originally On body, undercarriage is rotationally connected with lifting screw, drives lifting screw relative flight device body to lift by the 3rd motor Motion.

Further improving as this utility model, two rotor crossbeams on described aircraft body are parallel to be set Putting, and connect two pieces of cross-beam connecting plates on rotor crossbeam, described rotor crossbeam is connected with cross-beam connecting plate by bearing；Horizontal Being provided with framework soleplate bottom beam connecting plate, described conversion drive mechanism and lifting support mechanism are installed on framework soleplate.

Further improving as this utility model, described 3rd motor is fixed on the frame ground bottom aircraft body On plate, equipped with the first lifter wheel on the output shaft of the 3rd motor, framework soleplate is rotationally connected the second lifter wheel, first liter Fall gear and the second lifter wheel engaged transmission；Screwed hole, lifting screw and the second lifting is had in the middle part of described second lifter wheel Gear is threaded engagement, and the top of lifting screw is rotationally connected with undercarriage.

Further improving as this utility model, described undercarriage is mainly supported by three frames arranged at equal intervals Bar forms, and described frame support bar is linked into an integrated entity by support bar crossbearer, connects lifting spiral shell in the junction of support bar crossbearer Bar.

Further improving as this utility model, the bottom of described frame support bar is provided with support bar chassis.

Further improve as this utility model, conversion drive mechanism include the first motor, the first conversion gear and Second conversion gear, described first motor is fixed on the framework soleplate of aircraft body, the rotary shaft of the first motor and second Conversion gear is fixing to be connected, and the first conversion gear is fixed on rotor crossbeam, by the first conversion gear and the second conversion gear Engaged transmission controls rotor crossbeam and rotates.

Further improving as this utility model, this aircraft also includes retaining mechanism, sets in described retaining mechanism It is equipped with lock plunger, rotor crossbeam is provided with locking mortise, lock plunger is inserted in locking mortise and makes rotor crossbeam circumferential Spacing.

Further improve as this utility model, retaining mechanism also includes the second motor, locking rotating disk, locking even Bar and slide bearings, described second motor and slide bearings are each attached on framework soleplate, lock rotating disk and are arranged on second On machine shaft, locking rotating disk being hinged with two symmetrically arranged locking connecting rods, the locking connecting rod other end is connected seat with locking Hinged, described lock plunger is fixed on locking and connects on seat；Offering slide opening in slide bearings, described lock plunger is from slide opening Pass and be inserted into locking in mortise.

Further improve as this utility model, rotor crossbeam offers two locking mortises, two locking tenons Eye is positioned on same cross section, and angle is 90 degree.

Further improving as this utility model, described wheeled rotor includes rotor motor, rotor blade and wheel rim, Described rotor motor is fixed on rotor crossbeam two ends, and rotor blade is connected with rotor machine shaft, the outer end of rotor blade and wheel Circle is connected, and is carved with anti-slip veins at wheel rim outer surface.

3. beneficial effect

The technical scheme using this utility model to provide, compared with prior art, has the advantages that

(1) one of the present utility model can self-service change type land and air double-used aircraft, aircraft body is arranged and rises and falls Frame supporting mechanism, undercarriage therein is rotationally connected with elevating screws bar, controls elevating screws bar by the 3rd motor and transports up and down Dynamic, then undercarriage can synchronization lifting；When being changed by offline mode landwards driving mode, by gear support aircraft originally Body, it is vertical direction that the most wheeled rotor is rotated by horizontal direction, then raises undercarriage, then can carry out land locomotion；Similarly, When being offline mode by land locomotion patten transformation, first land undercarriage, makes aircraft body be supported, then controls wheeled Rotor is converted to horizontal direction by vertical direction, then may utilize rotor flying；Owing to being not required to additional land locomotion module, greatly Alleviating the weight of self, flying power is greatly improved；

(2) one of the present utility model can self-service change type land and air double-used aircraft, rotor crossbeam pass through bearing and crossbeam Connecting plate is connected, and forms overall support, and rotor crossbeam can rotate relative to cross-beam connecting plate, arranges on rotor crossbeam Gear, then can control the rotation of rotor crossbeam, it is achieved offline mode and the conversion of land locomotion pattern, structure letter by gear It is single, it is easy to accomplish；

(3) one of the present utility model can self-service change type land and air double-used aircraft, utilize three frame support bars composition Undercarriage, supports more stable, and is easily achieved lifting, and the bottom of frame support bar is provided with support bar chassis, it is possible to increase Add the contact area with level point, also can be stable when ground out-of-flatness complete landing and conversion；

(4) one of the present utility model can self-service change type land and air double-used aircraft, be provided with retaining mechanism with coordinate turn Change drive mechanism, rotor crossbeam is offered two locking mortises at 90 degree of interval, lock plunger is inserted in locking mortise, then Rotor crossbeam cannot circumferentially rotate, and improves the steadiness of structure；Additionally, utilize a rotating disk to drive the locking connecting rod of both sides Motion, reasonable in design, principle is simple, it is simple to promote the use of.

Accompanying drawing explanation

Fig. 1 is land and air double-used aircraft of the present utility model structural representation under state of flight；

Fig. 2 is the structural representation using rotor blade to arrange at same plane in this utility model；

Fig. 3 is land and air double-used aircraft of the present utility model structural representation under land locomotion state；

Fig. 4 is rotor crossbeam and the attachment structure schematic diagram of cross-beam connecting plate in this utility model；

Fig. 5 is the structural representation changing drive mechanism in this utility model；

Fig. 6 is the structural representation of lifting support mechanism in this utility model；

Fig. 7 is the structural representation of retaining mechanism in this utility model.

Label declaration in schematic diagram: 101, rotor crossbeam；102, frame top board；103, cross-beam connecting plate；104, rotor Blade；105, wheel rim；106, framework soleplate；201, the first motor；202, the first conversion gear；203, locking mortise；204, Two conversion gears；301, the second motor；302, locking rotating disk；303, locking connecting rod；304, locking connects seat；305, sliding support Seat；306, lock plunger；401, frame support bar；402, support bar chassis；403, support bar crossbearer；404, the 3rd motor；405、 First lifter wheel；406, the second lifter wheel；407, lifting screw；408, screw rod chassis.

Detailed description of the invention

For further appreciating that content of the present utility model, in conjunction with the accompanying drawings and embodiments this utility model is described in detail.

Embodiment 1

In conjunction with Fig. 1, Fig. 2 and Fig. 3, the one of the present embodiment can self-service change type land and air double-used aircraft, including aircraft Body, conversion drive mechanism and lifting support mechanism, aircraft body is quadrotor, top be provided with supply module, Flight control modules, GPS locating module etc., also can be arranged as required to corresponding filming apparatus, signal investigation detection device, rescue Shaking apparatus etc., are not particularly limited service condition.

The rotor that the aircraft body of the present embodiment is installed is wheeled rotor, and wheeled rotor includes rotor motor, rotor Blade 104 and wheel rim 105, rotor motor is fixed on rotor crossbeam 101 two ends, and rotor blade 104 is connected with rotor machine shaft, The outer end of rotor blade 104 is connected with wheel rim 105, and is carved with anti-slip veins at wheel rim 105 outer surface.This wheeled rotor can be used as Flying rotor uses, again can be as wheel at land locomotion；Set anti-slip veins can increase friction, it is simple to land locomotion.

Owing to aircraft body is four rotor structures, so being arranged with two rotor crossbeams 101 in parallel, change drive mechanism Rotated by gear conjugate control rotor crossbeam 101, make wheeled rotor horizontally and vertically direction change, it is achieved offline mode and Conversion between land locomotion pattern.

Structure for aircraft body arranges and rotor blade 104 can be arranged in same level, such as institute in Fig. 2 Show, in order to avoid interfering between rotor blade 104 during flight, between two rotor crossbeams 101, need enough gaps；For Make more optimized structure, reduce the space that aircraft takies, it is also possible to rotor blade about 104 is shifted to install, i.e. at one On rotor crossbeam 101, rotor blade 104 is positioned at above rotor crossbeam 101, on another root rotor crossbeam 101, and rotor blade 104 are positioned at below rotor crossbeam 101, make the rotor blade 104 of both sides stagger, and have overlapping region at middle part, save space, Reduce the volume of aircraft body.

Owing to having intersection between rotor blade 104, although do not affect flight, but it is horizontal to need to control rotor when conversion The rotation direction of beam 101.As shown in fig. 1, rotor blade 104 position on right side is less than rotor blade 104 position in left side, only There is rotor blade 104 to rotate to the left simultaneously, just can complete the conversion of offline mode landwards driving mode.Similarly, by land Ground driving mode needs rotor blade 104 to rotate clockwise to the right, to complete patten transformation when being transformed into offline mode simultaneously.

In current land and air double-used aircraft, it is much to drive flight support frame at offline mode by multipair gear And change between driving mode, as small aircraft, its performance is had a major impact by flying power, in order to improve flying power, Need to make aircraft weight reduce as far as possible；And the conversion equipment that arranges is the most, weight is the biggest, can reduce aircraft undoubtedly Flying power.This big this problem of bright combination, has done bigger optimization design to the structure of aircraft.In the present embodiment, as 2, Fig. 4, connects two pieces of cross-beam connecting plates 103 on rotor crossbeam 101, and rotor crossbeam 101 is by bearing and cross-beam connecting plate 103 It is connected.On the one hand, two pieces of cross-beam connecting plates be arrangeding in parallel 103 play skeleton interconnection function, and rotor crossbeam 101 is connected to Together；On the other hand, it is connected by bearing between rotor crossbeam 101 with cross-beam connecting plate 103, makes the rotor crossbeam 101 can phase Cross-beam connecting plate 103 is rotated, as long as and cross-beam connecting plate 103 rotate 90 degree, just can realize the switching between different mode, tie Structure advantages of simple, it is simple to switching.

In order to fixing each mechanism module, being provided with framework soleplate 106 bottom cross-beam connecting plate 103, described conversion is driven Motivation structure and lifting support mechanism are installed on framework soleplate 106.Conversion drive mechanism includes 201, first turn of the first motor Gear changing 202 and the second conversion gear 204, namely directly utilize servomotor and rotate to control rotor crossbeam 101, decrease Unnecessary intermediate conversion gear.Cross-beam connecting plate 103 top is provided with frame top board 102, and this frame top board 102 1 aspect can To protect each mechanism module, on the other hand it is easily installed the parts such as flight control modules, GPS locating module.

Specifically, as it is shown in figure 5, the first motor 201 is fixed on the framework soleplate 106 of aircraft body, the first motor The rotary shaft of 201 is fixing with the second conversion gear 204 to be connected, and the first conversion gear 202 is fixed in the middle part of rotor crossbeam 101, the One conversion gear 202 and the second conversion gear 204 engaged transmission, Remote the second conversion gear 204 rotates, the second conversion tooth Take turns 204 motions and be delivered to the first conversion gear 202, and then drive rotor crossbeam 101 to rotate, patten transformation can be carried out.

What deserves to be explained is, although at present part quadrotor be capable of offline mode and land locomotion pattern it Between conversion, but its transformation process need to rely on manual operation more completes, and it not main reason is that in transformation process not Support arrangement has assisted conversion.Existing standard aircraft with undercarriage as support, if but undercarriage is applied to On double-used aircraft, rotary wing wheel face intangibly the most after conversion, it is impossible at land locomotion, therefore, carry out land and air double-used During Flight Vehicle Design, it is necessary to remove support means, accordingly, there exist the contradiction supported between conversion.

And lifting support mechanism set in the present embodiment solves this problem cleverly, specifically, as shown in Figure 6, Lifting support mechanism includes that the 3rd motor 404, lifting screw 407 and undercarriage, the 3rd motor 404 are fixed on aircraft body On, undercarriage is rotationally connected with lifting screw 407, and lifting screw 407 can rotate relative to undercarriage, but can drive undercarriage Synchronization lifting, drives lifting screw 407 relative flight device body to carry out elevating movement by the 3rd motor 404, and then can realize The purpose of ascending, descending frame.

Before take-off, rotor blade 104 is positioned at horizontal direction, and undercarriage can be as support；In flight course, if needed Land locomotion pattern to be converted to, then can control aircraft landing, after undercarriage lands, control the first motor 201 action, by First motor 201 drives rotor crossbeam 101 to rotate 90 degree, and rotor blade 104 turns to vertical direction, because there being undercarriage conduct Supporting, therefore, wheel rim 105 will not touch ground；After converting, control the 3rd motor 404 action, lifting screw 407 Rising and drive undercarriage to rise, wheel rim 105 comes into contact with ground, it is achieved the conversion between offline mode to land locomotion pattern. When needs are offline mode by land locomotion patten transformation, decline on the contrary, first control 404 undercarriages of the 3rd motor, by The whole aircraft body of gear support, is then converted to horizontal direction rotor blade 104 by vertical direction, it is achieved different moulds Conversion between formula.

Embodiment 2

The one of the present embodiment can self-service change type land and air double-used aircraft, its basic structure is same as in Example 1, and it is not It is with part: the present embodiment elevating movement by gear conjugate control lifting screw 407, it is possible to realize in other ways rising Fall, main as a example by gear conjugate control in the present embodiment.Specifically, the 3rd motor 404 is fixed on bottom aircraft body On framework soleplate 106, equipped with the first lifter wheel 405 on the output shaft of the 3rd motor 404, framework soleplate 106 passes through bearing Connect the second lifter wheel 406, make the second lifter wheel 406 can rotate relative to framework soleplate 106, but can not move axially.The One lifter wheel 405 is meshed with the second lifter wheel 406.

There is screwed hole in the middle part of second lifter wheel 406, i.e. on the middle part inwall of the second lifter wheel 406, be provided with interior spiral shell Stricture of vagina, lifting screw 407 engages with the female thread of the second lifter wheel 406；The top of lifting screw 407 rotates even with undercarriage Connect, i.e. lifting screw 407 can rotate relative to undercarriage and can not axially opposing move.

When the first lifter wheel 405 rotates, the second lifter wheel 406 and then rotates, and by screw thread, rotation is converted to The elevating movement of lifting screw 407, drives undercarriage to move up and down by lifting screw 407.Set undercarriage is permissible The structure such as shaft-like or circular, can play lifting supporting role in the case of not interfering flight.

Embodiment 3

In conjunction with Fig. 6, the one of the present embodiment can self-service change type land and air double-used aircraft, its basic structure and embodiment 2 Identical, its difference is: the undercarriage in the present embodiment is mainly by three frame support bars arranged at equal intervals 401 groups Becoming, frame support bar 401 is linked into an integrated entity by support bar crossbearer 403, three frame support bar 401 length phases of junction distance Deng, the circular hole of vertical direction of scrounging in the junction of support bar crossbearer 403, or adapter sleeve is installed, thus lifting screw 407 It is rotationally connected with undercarriage.If the length of frame support bar 401 is relatively big, can be right with framework soleplate 106 at frame top board 102 Through hole is offered in the position answered, and support bar crossbearer 403 is positioned at above frame top board 102, when undercarriage rises, does not interferes with Frame top board 102, reasonable in design.

When performing task in the wild, can be potentially encountered weak soil or out-of-flatness ground, local, in this case, flight Device body entirety may not be in level, if certain wheel rim first contacts to earth in transformation process, then aircraft may be made to topple over, nothing Method continues executing with task at road traveling.In order to ensure the stationarity of landing, the bottom of frame support bar 401 is provided with support bar Chassis 402, this support bar chassis 402 increases the contact area with ground, can cover out-of-flatness ground, local, it is to avoid topple over phenomenon Occur.Additionally, be provided with screw rod chassis 408 bottom lifting screw 407, at some extreme terrains, by screw rod chassis 408 energy Enough increase steadiness further.

Embodiment 4

The one of the present embodiment can self-service change type land and air double-used aircraft, its basic structure is same as in Example 3, and it is not It is with part: be provided with retaining mechanism on board the aircraft, as it is shown in fig. 7, retaining mechanism is provided with lock plunger 306, in rotation It is provided with locking mortise 203 on wing crossbeam 101, lock plunger 306 is inserted in locking mortise 203 and makes rotor crossbeam 101 circumferential Spacing.Offering two locking mortises 203 on rotor crossbeam 101, two locking mortises 203 are positioned on same cross section, and angle Be 90 degree, two locking mortises 203 respectively with rotor blade 104 position of rotor crossbeam 101 in the horizontal direction and during vertical direction Put corresponding.

Use gear to control to rotate, of long duration there will be unavoidably loosening, and by lock plunger 306 and locking mortise 203 Cooperation can increase the steadiness of connection.Specifically, retaining mechanism also includes the second motor 301, locking rotating disk 302, locking Connecting rod 303 and slide bearings 305, the second motor 301 and slide bearings 305 are each attached on framework soleplate 106, lock and turn Dish 302 is arranged in the second motor 301 rotating shaft, locking rotating disk 302 is hinged with two symmetrically arranged locking connecting rods 303, lock To be connected seat 304 hinged with locking to be close to bar 303 other end, and locking connecting rod 303 can relatively be locked connection seat 304 and be swung up and down, and locks Tight bolt 306 is fixed on locking and connects on seat 304；Offering slide opening in slide bearings 305, lock plunger 306 is worn from slide opening Go out to be inserted into lock in mortise 203.If being not provided with slide bearings 305, when lock plunger 306 is extracted out from locking mortise 203 After then cannot be inserted into, also cannot utilize locking rotating disk 302 drive the lock plunger 306 on both sides to work.

For the ease of lock plunger 306 is inserted locking mortise 203, one section of the head of lock plunger 306 is conical structure, head End is spherical crown shape, so as to play guide effect.

Time specifically used, rotor blade 104 is positioned at horizontal direction, and undercarriage can be as support；In flight course, if Needing to be converted to land locomotion pattern, then can control aircraft landing, after undercarriage lands, the second motor 301 makes locking turn Dish 302 rotates, and locking connecting rod 303 inwardly pulls lock plunger 306, and lock plunger 306 is extracted from locking mortise 203, and by sliding Support seat 305 to support；Control the first motor 201 action, the first motor 201 drive rotor crossbeam 101 to rotate 90 degree, rotor leaf Sheet 104 turns to vertical direction, because having undercarriage as support, therefore, wheel rim 105 will not touch ground；When converting Cheng Hou, the second motor 301 makes locking rotating disk 302 rotate backward, and locking connecting rod 303 pushes out lock plunger 306, lock plunger 306 Insert in locking mortise 203；Controlling the 3rd motor 404 action, lifting screw 407 rises and drives undercarriage to rise, wheel rim 105 by Gradually touch ground, it is achieved the conversion between offline mode to land locomotion pattern.When needs by land locomotion patten transformation for flying During row mode, decline, by the whole aircraft body of gear support, then on the contrary, first control 404 undercarriages of the 3rd motor Rotor blade 104 is converted to horizontal direction by vertical direction, it is achieved the conversion between different mode.

Feature between various embodiments of the present invention can be mutually combined, and is not limited to above-described embodiment.Owing to the present invention is in flight Be provided with the undercarriage with elevating function on device body so that aircraft can offline mode and land locomotion pattern it Between change voluntarily, intelligence degree is high, is suitable for investigating use in the wild.

Schematically being described this utility model and embodiment thereof above, this description does not has restricted, accompanying drawing Shown in be also one of embodiment of the present utility model, actual structure is not limited thereto.So, if this area Those of ordinary skill enlightened by it, creating in the case of objective without departing from this utility model, designing without creative The frame mode similar to this technical scheme and embodiment, all should belong to protection domain of the present utility model.

Claims (10)

1. can a self-service change type land and air double-used aircraft, including aircraft body and conversion drive mechanism, it is characterised in that: Also including that lifting support mechanism, the wheeled rotor of described aircraft body are fixed on the two ends of rotor crossbeam (101), conversion is driven Motivation structure is rotated by gear conjugate control rotor crossbeam (101), makes wheeled rotor change in horizontally and vertically direction；

Described lifting support mechanism includes the 3rd motor (404), lifting screw (407) and undercarriage, and the 3rd motor (404) is fixed On aircraft body, undercarriage is rotationally connected with lifting screw (407), drives lifting screw by the 3rd motor (404) (407) relative flight device body carries out elevating movement.

One the most according to claim 1 can self-service change type land and air double-used aircraft, it is characterised in that: described flight Two rotor crossbeams (101) on device body be arranged in parallel, and at rotor crossbeam (101) two pieces of cross-beam connecting plates of upper connection (103), described rotor crossbeam (101) is connected with cross-beam connecting plate (103) by bearing；Cross-beam connecting plate (103) bottom sets Being equipped with framework soleplate (106), described conversion drive mechanism and lifting support mechanism are installed on framework soleplate (106).

One the most according to claim 1 can self-service change type land and air double-used aircraft, it is characterised in that: described 3rd electricity Machine (404) is fixed on the framework soleplate (106) bottom aircraft body, equipped with first on the output shaft of the 3rd motor (404) Lifter wheel (405), framework soleplate (106) is rotationally connected the second lifter wheel (406), the first lifter wheel (405) and the Two lifter wheels (406) engaged transmission；There are screwed hole, lifting screw (407) and second in described second lifter wheel (406) middle part Lifter wheel (406) is threaded engagement, and the top of lifting screw (407) is rotationally connected with undercarriage.

One the most according to claim 3 can self-service change type land and air double-used aircraft, it is characterised in that: described undercarriage Mainly being made up of three frame support bars (401) arranged at equal intervals, described frame support bar (401) passes through support bar crossbearer (403) link into an integrated entity, connect lifting screw (407) in the junction of support bar crossbearer (403).

One the most according to claim 4 can self-service change type land and air double-used aircraft, it is characterised in that: described frame is propped up The bottom of strut (401) is provided with support bar chassis (402).

6. according to the one according to any one of Claims 1 to 5 can self-service change type land and air double-used aircraft, its feature exists In: conversion drive mechanism includes the first motor (201), the first conversion gear (202) and the second conversion gear (204), described the One motor (201) is fixed on the framework soleplate (106) of aircraft body, the rotary shaft of the first motor (201) and the second conversion Gear (204) is fixing to be connected, and the first conversion gear (202) is fixed on rotor crossbeam (101), by the first conversion gear (202) and the second conversion gear (204) engaged transmission controls rotor crossbeam (101) and rotates.

7. according to the one according to any one of Claims 1 to 5 can self-service change type land and air double-used aircraft, its feature exists In: this aircraft also includes retaining mechanism, is provided with lock plunger (306) in described retaining mechanism, sets on rotor crossbeam (101) It is equipped with locking mortise (203), lock plunger (306) is inserted and locking mortise (203) makes rotor crossbeam (101) spacing by circumference.

One the most according to claim 7 can self-service change type land and air double-used aircraft, it is characterised in that: in retaining mechanism Also include the second motor (301), locking rotating disk (302), locking connecting rod (303) and slide bearings (305), described second motor (301) being each attached on framework soleplate (106) with slide bearings (305), locking rotating disk (302) is arranged on the second motor (301) in rotating shaft, locking rotating disk (302) being hinged with two symmetrically arranged locking connecting rods (303), locking connecting rod (303) is another It is hinged that one end is connected seat (304) with locking, and described lock plunger (306) is fixed on locking and connects on seat (304)；In slide bearings (305) offering slide opening on, described lock plunger (306) passes from slide opening and is inserted into locking in mortise (203).

One the most according to claim 7 can self-service change type land and air double-used aircraft, it is characterised in that: rotor crossbeam (101) offering two lockings mortise (203) on, two lockings mortise (203) are positioned on same cross section, and angle is 90 degree.

10. according to the one according to any one of Claims 1 to 5 can self-service change type land and air double-used aircraft, its feature exists In: described wheeled rotor includes rotor motor, rotor blade (104) and wheel rim (105), and it is horizontal that described rotor motor is fixed on rotor Beam (101) two ends, rotor blade (104) is connected with rotor machine shaft, and the outer end of rotor blade (104) is solid with wheel rim (105) Even, and it is carved with anti-slip veins at wheel rim (105) outer surface.