CN108100213A - A kind of rotation cabin suitable for airplane mode conversion - Google Patents
A kind of rotation cabin suitable for airplane mode conversion Download PDFInfo
- Publication number
- CN108100213A CN108100213A CN201810000544.6A CN201810000544A CN108100213A CN 108100213 A CN108100213 A CN 108100213A CN 201810000544 A CN201810000544 A CN 201810000544A CN 108100213 A CN108100213 A CN 108100213A
- Authority
- CN
- China
- Prior art keywords
- cabin
- rotation
- stent
- fuselage
- mode conversion
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
- B64C1/069—Joining arrangements therefor
Abstract
The invention discloses it is a kind of suitable for airplane mode conversion rotation cabin, including：Head, fuselage, tail, propeller, undercarriage, wing, engine, rotation cabin and stent locking device, rotation cabin, hatch door, swing-around trajectory and stent, cabin rotation control tooth, rotatable cabin stent and aircraft are fixed end, servo step motor, level control private to take step motor control gear, the centre position of the fuselage is equipped with swing-around trajectory and stent, the inner cavity of the swing-around trajectory and stent is equipped with rotation cabin, and the rotation cabin is mounted on stent locking device on swing-around trajectory and stent by rotating cabin；The present invention effectively reduces structural complexity, reduces the difficulty of manufacture cost and technique, reduces security and adaptability that manipulation difficulty improves flight.
Description
Technical field
The present invention relates to aircraft technical fields, are specifically a kind of rotation cabin suitable for airplane mode conversion.
Background technology
The mankind have the ideal flown in the air as birds very early.For a long time, the mankind are most for the fantasy that can fly up into the sky
Various methods.With the continuous development of science and technology, the dream that the mankind fly in the air becomes reality.It is current manned
Device change of flight pattern by more rotor flying patterns to the mutual inverse conversion of fixed-wing offline mode all using propeller change angle come
It completes, it is complicated, manufacture is of high cost, technology difficulty is big, operation difficulty is big, danger coefficient is high.
The content of the invention
It is an object of the invention to provide a kind of rotation cabin suitable for airplane mode conversion, to solve above-mentioned background
The problem of being proposed in technology.
To achieve the above object, the present invention provides following technical solution：
A kind of rotation cabin suitable for airplane mode conversion, including：Head, fuselage, tail, propeller, undercarriage, machine
The wing, engine, rotation cabin and stent locking device, rotation cabin, hatch door, swing-around trajectory and stent, cabin rotation control tooth,
Rotatable cabin stent and aircraft are fixed end, servo step motor, horizontal control private take step motor control gear.The machine
Head and tail are located at the rear and front end of fuselage respectively, are mounted on wing at left and right sides of the fuselage, the wing is equipped with altogether
Two groups and every group include two pairs of wings, and one of which wing is mounted on the front end of fuselage and close to the position of head, another
Group wing is mounted on the rear end of fuselage and is mounted on propeller on the position of tail, the wing, the fuselage
Centre position is equipped with swing-around trajectory and stent, and the inner cavity of the swing-around trajectory and stent is equipped with rotation cabin, the whirler
Cabin is mounted on stent locking device on swing-around trajectory and stent by rotating cabin, the cabin rotation control tooth fitting installation
The a quarter of the isometrical circle of cabin is rotated in the periphery of rotation cabin and about, the side of the rotation cabin is equipped with servo
Stepper motor, the servo step motor are equipped with horizontal control private by transmission shaft and take step motor control gear, the machine
Rotation control tooth in cabin takes step motor control gear with level control private and is meshed.
As further embodiment of the present invention：The swing-around trajectory and stent are installed on body and with rotating cabin cabin
It is fitted closely by slideway.
As further embodiment of the present invention：Rotatable cabin stent is equipped between the swing-around trajectory and stent and fuselage with flying
Row device is fixed end and is connected to a fixed.
As further embodiment of the present invention：The rotation cabin passes through magnetic force motor switch control with stent locking device
System.
As further embodiment of the present invention：The rotation cabin shape can make cylinder, circle, ellipse as needed
Shape and other shapes.
As further embodiment of the present invention：Stent cradle form can be taken between the rotation cabin and stent.
As further embodiment of the present invention：Cabin rotation control tooth can be placed in fuselage and isometrical for cabin
Round a quarter.
As further embodiment of the present invention：The rotation cabin, can also be to rotating cabin under same principle, structure
Body transverse horizontal is adjusted, i.e., keeps rotation cabin laterally vertical with horizontal conservation degree with fuselage within the specific limits.
As further embodiment of the present invention：Hatch door in the rotation cabin is installed, has direction-indicating arrow on door.
As further scheme of the invention：Suitable for conversion offline mode in need aircraft, i.e., vertical
Mutual inverse conversion of more rotor flying patterns to fixed-wing offline mode drops.
Compared with prior art, the beneficial effects of the invention are as follows：It is that can be taken as needed using pilot of the present invention
Corresponding ground conversion or aerial conversion are fixed due to taking propeller of the present invention, engine, need not shift one's position just
The conversion of offline mode can be completed, and does not reduce the comfort level of seating and does not increase the difficulty of handling goods.Reduction finishes
Structure complexity reduces the difficulty of manufacture cost and technique, reduces security and adaptability that manipulation difficulty improves flight.
Description of the drawings
Fig. 1 is rotation cabin top view.
Fig. 2 rotates cabin front view for the state that takes off vertically.
Fig. 3 rotates cabin side view for the state that takes off vertically.
Fig. 4 rotates cabin rearview for the state that takes off vertically.
Fig. 5 rotates cabin floor for the state that takes off vertically and changes side view of the state.
Fig. 6 rotates cabin side view for fixed-wing state of flight.
In figure：1- heads, 2- fuselages, 3- tails, 4- propellers, 5- undercarriages, 6- wings, 7- engines, 8- whirlers
Cabin and stent locking device, 9- rotation cabins, 10- hatch doors, 11- swing-around trajectories and stent, 12- cabins rotation control tooth, 13- rotations
Turn cabin stent and be fixed end, 14- servo step motors with aircraft, the horizontal control privates of 15- take step motor control gear.
Specific embodiment
Below in conjunction with the attached drawing in the embodiment of the present invention, the technical solution in the embodiment of the present invention is carried out clearly complete
Ground describes, it is clear that described embodiment is only part of the embodiment of the present invention, instead of all the embodiments.Based on this
Embodiment in invention, the every other reality that those of ordinary skill in the art are obtained without making creative work
Example is applied, belongs to the scope of protection of the invention.
Please refer to Fig.1~6, in the embodiment of the present invention, a kind of rotation cabin suitable for airplane mode conversion, including：
Head 1, fuselage 2, tail 3, propeller 4, undercarriage 5, wing 6, engine 7, rotation cabin and stent locking device 8, rotation
Cabin 9, hatch door 10, swing-around trajectory and stent 11, cabin rotation control tooth 12, rotatable cabin stent and aircraft are fixed end
13rd, servo step motor 14, horizontal control private take step motor control gear 15.
So-called rotation cabin refer to be placed on slideway can the rotation of 90 degree of head horizontal direction reciprocal circular motion manned capsule
Room.
So-called hatch door refers to upper and lower personnel and loads the exit and entrance of cargo, has direction-indicating arrow on door.
So-called swing-around trajectory and stent, be placed on body with aircraft body one closely pasted by slideway with cabin
It closes, for rotation cabin 90 degree of axial reciprocatings of head horizontal direction rotate on it track and stent.
So-called cabin rotation control tooth, refers to be placed in that cabin periphery is isometrical with cabin, synchronous with cabin quadrant
Gear tooth.
Rotatable cabin stent is fixed end with aircraft and refers to aircraft swing-around trajectory stent and airframe connection.
So-called servo step motor, which refers to be controlled by during aircraft conversion offline mode, flies control horizontal rotation gyro,
By the cabin rotation with being fixed on cabin periphery gear is controlled to be twisted the rotation of Synchronization Control cabin and remain cabin and ground
Level is kept for 90 degree.
So-called horizontal control private takes step motor control gear and refers to be fixed on body to be connected simultaneously with servo step motor
Synchronous gear, it is synchronous that it with cabin rotation control tooth is twisted completion the two.
So-called rotation cabin and stent locking device refer to be placed in hole on body, are placed in the pin of cabin in aircraft
It is controlled by magnetic force motor switch during conversion offline mode, opens or lock as needed and complete the one of rotation cabin and stent
Body or separation move so as to complete rotatable cabin with the integrated or splitization of aircraft.
The head 1 and tail 3 are located at the rear and front end of fuselage 2 respectively, and the left and right sides of the fuselage 2 is respectively mounted organic
The wing 6, the wing 6 is equipped with two groups and every group altogether includes two pairs of wings 6, and one of which wing 6 is mounted on the front end of fuselage 2 simultaneously
And close to the position of head 1, another group of wing 6 is mounted on the rear end of fuselage 2 and on the position of tail 3, the wing 6
Propeller 4 is mounted on, the centre position of the fuselage 2 is equipped with swing-around trajectory and stent 11, the swing-around trajectory and stent
11 inner cavity is equipped with rotation cabin 9, and the rotation cabin 9 is mounted on swing-around trajectory by rotating cabin with stent locking device 8
And on stent 11, the cabin rotation control tooth 12 is jointly mounted to the periphery of rotation cabin 9 and about rotation cabin 9 is isometrical
Round a quarter, the side of the rotation cabin 9 are equipped with servo step motor 14, and the servo step motor 14 passes through biography
Moving axis is equipped with horizontal control private and takes step motor control gear 15, and the cabin rotation control tooth 12 is walked with the private clothes of horizontal control
Stepper motor control gear 15 is meshed.It is described rotation 9 shape of cabin can make as needed cylinder, circle, ellipse and its
Its shape；Stent cradle form can be taken between the rotation cabin 9 and stent.Cabin rotation control tooth 12, can be with
Be placed in fuselage and for the isometrical circle of cabin a quarter；The rotation cabin 9, can also be to rotation under same principle, structure
Favourable turn cabin body transverse horizontal is adjusted, i.e., rotation cabin is kept laterally to be kept for 90 degree with horizontal with fuselage within the specific limits
Vertically；Hatch door 10 is installed in the rotation cabin 9.
The present invention operation principle be：
Specific embodiment one：Cabin is completed to rotate in the air.Under halted state, rotation cabin timbering machine body joins to aircraft
Fixing end 13 is vertical to 90 degree of holding with before ground flying device, and rotation cabin 9 keeps vertical with 90 degree of ground level, rotates cabin
9 is parallel with body 2, and rotatable cabin is locked with stent locking device 8, upper and lower personnel, handling goods, and aircraft enters the shape that takes off
State.It takes off vertically into after reaching height needed for vertical more rotor flying pattern conversions, aircraft enters abnormal flight, by vertical more
Rotor flying pattern is converted to fixed-wing flying method, at this point, rotatable cabin and stent locking device 8 are in electric magnetic switch drive
Lower opening, head horizontal direction rotates fuselage forward, and rotation cabin 9 is controlled in the servo step motor 14 for flying control horizontal gyro control
Remain that rotation cabin 9 is vertical with 90 degree of heading ground level under system.When airframe 2 and ground reach direction of circling in the air
When horizontal, i.e. zero angle, while airframe 2 and rotation cabin 9 reach 90 degree it is vertical when rotatable cabin and stent locking device 8 exist
It is locked again under electric magnetic switch drive, rotation cabin 9 forms an entirety again with body, and at this moment aircraft enters fixation
Wing offline mode, rotation cabin complete aerial conversion.Aircraft is completed to turn from more rotor flying modes to fixed-wing flying method
It changes.
Specific embodiment two：Cabin is completed to rotate on ground.In aircraft under the halted state of ground, cabin bracket is rotated
With aircraft be fixed end 13 with before ground flying device to keep 90 degree it is vertical, rotate cabin holding it is vertical with 90 degree of ground,
It is parallel with body 2 to rotate cabin 9, rotatable cabin is locked with stent locking device 8, and upper and lower personnel, handling goods fasten safety
Band, the good cargo hatch door of bondage are closed.Aircraft is in takeoff condition at this time, and rotation cabin is with stent locking device 8 in magnetic switch
Driving under open, servo step motor 14 vertical rotary fly control gyroscope control under driving rotation the horizontal tail of cabin aircraft
Parallel to the ground, 2 vertical 90 degree of cabin 9 and fuselage is rotated by 90 ° backward.Rotatable cabin drives with stent locking device in magnetic switch
It is locked again under dynamic.At this point, aircraft takeoff, and complete in the air horizontal to fixed-wing from more rotors flying method that takes off vertically
Flying method is converted.
The reverse transformation of both the above cabin conversion regime only needs to can be realized the execution of above procedure inverted order.
The present invention in swing-around trajectory, during offline mode convert, rotates cabin head to preceding to the beginning using cabin
It keeps perpendicular to the ground eventually, to meet the needs of airplane mode conversion, meets the needs of different flying methods, reduce structure
Complexity reduces the difficulty of manufacture cost and technique, improves the security and adaptability of flight.The present invention is suitable for all
Need to convert the aircraft of offline mode, i.e. the more rotor flying patterns of VTOL are to the mutual inverse conversion of fixed-wing offline mode.
It is obvious to a person skilled in the art that the invention is not restricted to the details of above-mentioned exemplary embodiment, Er Qie
In the case of without departing substantially from spirit or essential attributes of the invention, the present invention can be realized in other specific forms.Therefore, no matter
From the point of view of which point, the present embodiments are to be considered as illustrative and not restrictive, and the scope of the present invention is by appended power
Profit requirement rather than above description limit, it is intended that all by what is fallen within the meaning and scope of the equivalent requirements of the claims
Variation is included within the present invention.Any reference numeral in claim should not be considered as to the involved claim of limitation.
Moreover, it will be appreciated that although this specification is described in terms of embodiments, but not each embodiment is only wrapped
Containing an independent technical solution, this description of the specification is merely for the sake of clarity, and those skilled in the art should
Using specification as an entirety, the technical solutions in each embodiment can also be properly combined, forms those skilled in the art
It is appreciated that other embodiment.
Claims (10)
1. a kind of rotation cabin suitable for airplane mode conversion, including：Head（1）, fuselage（2）, tail（3）, propeller
（4）, undercarriage（5）, wing（6）, engine（7）, rotation cabin and stent locking device（8）, rotation cabin（9）, hatch door
（10）, swing-around trajectory and stent（11）, cabin rotation control tooth（12）, rotatable cabin stent and aircraft be fixed end（13）、
Servo step motor（14）, horizontal control private take step motor control gear（15）, which is characterized in that the head（1）And machine
Tail（3）It is located at fuselage respectively（2）Rear and front end, the fuselage（2）The left and right sides be mounted on wing（6）, the wing
（6）Being equipped with two groups and every group altogether includes two pairs of wings（6）, one of which wing（6）Mounted on fuselage（2）Front end and lean on
Nearly head（1）Position, another group of wing（6）Mounted on fuselage（2）Rear end and close to tail（3）Position, the machine
The wing（6）On be mounted on propeller（4）, the fuselage（2）Centre position swing-around trajectory and stent are installed（11）, the rotation
Transition road and stent（11）Inner cavity be equipped with rotation cabin（9）, the rotation cabin（9）By rotating cabin dress is locked with stent
It puts（8）Mounted on swing-around trajectory and stent（11）On, the cabin rotation control tooth（12）It is jointly mounted to rotation cabin（9）'s
Periphery and about rotation cabin（9）The a quarter of isometrical circle, the rotation cabin（9）Side be equipped with servo stepping electricity
Machine（14）, the servo step motor（14）Horizontal control private is equipped with by transmission shaft and takes step motor control gear（15）,
The cabin rotation control tooth（12）Step motor control gear is taken with level control private（15）It is meshed.
2. the rotation cabin according to claim 1 suitable for airplane mode conversion, which is characterized in that the rotation rail
Road and stent（11）It is installed on body（2）Above and with rotating cabin（9）Cabin is fitted closely by slideway.
3. the rotation cabin according to claim 1 suitable for airplane mode conversion, which is characterized in that the rotation rail
Road and stent（11）With fuselage（2）Between be equipped with rotatable cabin stent and aircraft and be fixed end（13）It is connected to a fixed.
4. the rotation cabin according to claim 1 suitable for airplane mode conversion, which is characterized in that the whirler
Cabin and stent locking device（8）It is controlled by magnetic force motor switch.
5. the rotation cabin according to claim 1 suitable for airplane mode conversion, which is characterized in that the whirler
Cabin（9）Shape can make cylinder, circle, ellipse and other shapes as needed.
6. the rotation cabin according to claim 1 suitable for airplane mode conversion, which is characterized in that the whirler
Cabin（9）Stent cradle form can be taken between stent.
7. the rotation cabin according to claim 1 suitable for airplane mode conversion, which is characterized in that the cabin rotation
Turn control tooth（12）Can be placed in fuselage and for the isometrical circle of cabin a quarter.
8. the rotation cabin according to claim 1 suitable for airplane mode conversion, which is characterized in that the whirler
Cabin（9）Under same principle, structure, rotation cabin body transverse horizontal can also be adjusted, i.e., protected within the specific limits
Rotation cabin is held laterally to keep with horizontal with fuselage（90）Degree is vertical.
9. the rotation cabin according to claim 1 suitable for airplane mode conversion, which is characterized in that the whirler
Cabin（9）On hatch door is installed（10）, have direction-indicating arrow on door.
10. the rotation cabin according to claim 1 suitable for airplane mode conversion, which is characterized in that suitable for institute
The aircraft of conversion offline mode in need, i.e. mutual reverse of the more rotor flying patterns of VTOL to fixed-wing offline mode
It changes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810000544.6A CN108100213A (en) | 2018-01-02 | 2018-01-02 | A kind of rotation cabin suitable for airplane mode conversion |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810000544.6A CN108100213A (en) | 2018-01-02 | 2018-01-02 | A kind of rotation cabin suitable for airplane mode conversion |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108100213A true CN108100213A (en) | 2018-06-01 |
Family
ID=62218349
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810000544.6A Pending CN108100213A (en) | 2018-01-02 | 2018-01-02 | A kind of rotation cabin suitable for airplane mode conversion |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108100213A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111361738A (en) * | 2020-03-18 | 2020-07-03 | 李秀英 | Floor unmanned aerial vehicle express delivery system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2747160Y (en) * | 2004-11-19 | 2005-12-21 | 刘光炜 | Cabin able to keep pilot in horizontal posture |
| CN101766524A (en) * | 2008-12-31 | 2010-07-07 | 上海连能机电科技有限公司 | Multi-position health-care machine |
| CN102730192A (en) * | 2011-04-14 | 2012-10-17 | 戴瑾 | Vertical take-off and landing aircraft |
| CN106043686A (en) * | 2016-07-18 | 2016-10-26 | 四川傲势乐翼科技有限公司 | Vertical take-off and landing fixed wing aircraft |
| CN106379524A (en) * | 2016-09-23 | 2017-02-08 | 齐继国 | Aircraft with multiple vertical take-off and landing aircraft module units |
-
2018
- 2018-01-02 CN CN201810000544.6A patent/CN108100213A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2747160Y (en) * | 2004-11-19 | 2005-12-21 | 刘光炜 | Cabin able to keep pilot in horizontal posture |
| CN101766524A (en) * | 2008-12-31 | 2010-07-07 | 上海连能机电科技有限公司 | Multi-position health-care machine |
| CN102730192A (en) * | 2011-04-14 | 2012-10-17 | 戴瑾 | Vertical take-off and landing aircraft |
| CN106043686A (en) * | 2016-07-18 | 2016-10-26 | 四川傲势乐翼科技有限公司 | Vertical take-off and landing fixed wing aircraft |
| CN106379524A (en) * | 2016-09-23 | 2017-02-08 | 齐继国 | Aircraft with multiple vertical take-off and landing aircraft module units |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111361738A (en) * | 2020-03-18 | 2020-07-03 | 李秀英 | Floor unmanned aerial vehicle express delivery system |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180601 |