CN206344990U - Individual lift device - Google Patents
Individual lift device Download PDFInfo
- Publication number
- CN206344990U CN206344990U CN201621238876.0U CN201621238876U CN206344990U CN 206344990 U CN206344990 U CN 206344990U CN 201621238876 U CN201621238876 U CN 201621238876U CN 206344990 U CN206344990 U CN 206344990U
- Authority
- CN
- China
- Prior art keywords
- wing
- lift device
- driving cabin
- individual lift
- piggyback pod
- 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.)
- Expired - Fee Related
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Abstract
The utility model discloses a kind of individual lift device, this individual lift device includes driving cabin and piggyback pod, wing is connected between driving cabin and piggyback pod, the wingtip of wing two is provided with propeller, wing is buzzard-type wing, and the leading edge of the wing root of wing is close to head-shield, and trailing edge is located at the bottom of driving cabin；The leading edge of the wingtip of wing is close to the top of piggyback pod, trailing edge is close to the bottom of piggyback pod, due to the buzzard-type wing that wing is large area, the maximum gauge of wing is larger, there is space to place the luggage of driver, and propeller can carry out turn-back to the wing tip vortex of wing, and propeller can also maintain individual lift device horizontal flight without rotation at a high speed, so voyage is remote, endurance is long.
Description
Technical field
The utility model is related to a kind of aircraft, more particularly to a kind of individual lift device.
Background technology
Chinese invention patent 2008100702333 discloses a kind of light aerobat capable of landing or taking-off vertically, and this is a kind of tailstock formula
Individual lift device, during VTOL, driver stands in driving cabin, and shrouded propeller blowout slip-stream carries out VTOL, this
When propellerslip can blow on the wing and empennage of driving cabin bottom both sides, and by corresponding rudder face deflection produce it is pneumatic
Power, the posture to the aircraft of plumbness is controlled, by the deflection forward of the rudder face on wing, and individual lift device can be by
Gradually lean forward to the horizontal attitude for having low incidence, now driver is in crouch down posture driving, and individual lift device enters horizontal flight shape
State, but the shrouded propeller of this light aerobat capable of landing or taking-off vertically the surfaces of revolution be located at driver chest, once propeller therefore
Barrier is projected, and driver may be damaged, and the driving cabin space of this aircraft is limited, and driver is difficult to place oneself
Luggage；Chinese invention patent 2009101689487 discloses a kind of individual lift device, and this individual lift device is to forenamed vertical
Lightweight aircraft of rising and falling is improved, but still has propeller to be damaged to driver, and is difficult to place luggage
Defect.
NASA in 2010 discloses a kind of puffin individual lift device, and this puffin individual lift device also uses tailstock
Formula is laid out, and wing uses M type flat shapes, and the motor of driving propeller is arranged on the highest point of M type wings, the rotation of propeller
Turn plane higher than driving cabin head-shield, even if propeller failure is projected, driver will not also be damaged, but this sole flight
The driving cabin of device still space is limited, and driver is still difficult to the luggage for having space to place oneself；And wing area is smaller, the wing
Carry big, it is necessary to which propeller rotation ability maintenance level flight at a high speed, the voyage and endurance influence on individual lift device is larger.
1940s American charles Annemarie Zimmermanns have invented a kind of F5U aircrafts, and nickname " flight pancake " is adopted
With the wing of the large area of low aspect ratio, and engine and propeller, and propeller are provided with two wingtips of wing
Direction of rotation and wing wing tip vortex direction of rotation on the contrary, the slip-stream of the torsion of two propellers can be to wingtip during flight
Vortex carries out turn-back, makes the aircraft of low aspect ratio and also has larger lift coefficient and lift-drag ratio, aircraft is had certain warp
Ji property, but this F5U aircrafts can only STOL, it is impossible to VTOL.
The content of the invention
Purpose of the present utility model is just to provide a kind of individual lift device herein, this individual lift device inner space compared with
Greatly, the luggage for enabling driver there is space to place oneself, and voyage is remote, and endurance is long.
The utility model individual lift device includes driving cabin, and the transparent head-shield in driving cabin head, piggyback pod is located at driving cabin
Both sides, the Plane of rotation for the propeller that piggyback pod head is set exceedes head-shield height, and the length of piggyback pod is close with driving cabin simultaneously
It is streamlined, wing is connected between driving cabin and piggyback pod, the piggyback pod bottom side outside with respect to driving cabin is provided with by X
The X-type empennage of stabilization and X rudder faces composition, X-shaped empennage wingtip is provided with the buffer being made up of loop bar and pillar, the driving cabin back of the body
Portion is provided with hatch door, and wing is buzzard-type wing, and the leading edge of the wing root of wing is close to head-shield, and trailing edge is located at the bottom of driving cabin；Wing
Wingtip leading edge close to the top of piggyback pod, trailing edge is close to the bottom of piggyback pod.
Because wing is buzzard-type wing, and the wing root of wing leading edge close to head-shield, trailing edge is located at the bottom of driving cabin；Machine
The leading edge of the wingtip of the wing is close to the top of piggyback pod, and trailing edge is close to the bottom of piggyback pod, and the chord length of such wing is larger, thickness
It is corresponding larger, there can be space to place the luggage of driver, luggage can be placed on the maximum gauge position of wing；Due to wing
Aspect ratio it is smaller, wing tip vortex can be very big during horizontal flight, but propeller is arranged on the wingtip of wing two, the rotation side of propeller
To the direction of rotation with wing tip vortex on the contrary, the slip-stream that propeller is reversed can carry out turn-back to the wing tip vortex of wing,
Reduce the wing tip vortex of wing, wing is had larger lift coefficient and lift-drag ratio, due to the advantageous effect of propeller, propeller
Individual lift device horizontal flight can also be maintained with less high rotating speed, so individual lift device voyage is remote, endurance is long.
The beneficial effects of the utility model：The wing of the utility model individual lift device is the buzzard-type wing of large area, wing
Maximum gauge it is larger, there is space to place the luggage of driver, and propeller the wing tip vortex of wing can be carried out it is reverse
Reverse, propeller can also maintain individual lift device horizontal flight without rotation at a high speed, so voyage is remote, endurance is long.
Brief description of the drawings
Fig. 1 is the front perspective view that the utility model individual lift device stands on ground；
Fig. 2 is the front perspective view of the utility model individual lift device VTOL state；
Fig. 3 is the front perspective view of the utility model individual lift device level flight condition.
1. driving cabin in figure；2. head-shield；3. wing；4. piggyback pod；5. propeller；6.X stabilizations；7.X rudder faces；8a. is disturbed
Flow plate；8b spoilers；9. main wheel；10. loop bar；11. pillar；12. hatch door.
Embodiment
The utility model is described in further detail with reference to the accompanying drawings and examples.Such as Fig. 1, shown in 2,3, this reality
Include driving cabin 1 with Novel one-player aircraft, the transparent head-shield 2 in driving cabin head, piggyback pod 4 is located at the both sides of driving cabin 1, power
The Plane of rotation for the propeller 5 that the head of cabin 4 is set exceedes the height of head-shield 2, and the length of piggyback pod 4 is close with driving cabin and in streamline
Type, is connected with wing 3 between driving cabin 1 and piggyback pod 4, the bottom of piggyback pod 4 side outside with respect to driving cabin 1 is provided with by X
The X-type empennage that stabilization 6 and X rudder faces 7 are constituted, X-shaped empennage wingtip is provided with the buffer being made up of loop bar 10 and pillar 11, driven
Sail the back of cabin 1 and be provided with hatch door 12, wing 3 is buzzard-type wing, and the leading edge of the wing root of wing 3 is close to head-shield 2, and trailing edge is located at driving cabin
1 bottom；The leading edge of the wingtip of wing 3 is close to the top of piggyback pod 4, and trailing edge is close to the bottom of piggyback pod 4.
Because wing 3 is buzzard-type wing, and the wing root of wing 3 leading edge close to head-shield 2, trailing edge is located under driving cabin 1
Portion；The leading edge of the wingtip of wing 3 close to the top of piggyback pod 4, trailing edge close to the bottom of piggyback pod 4, the chord length of such wing 3 compared with
Greatly, thickness is also corresponding larger, can have space to place the luggage of driver, and luggage can be placed on the maximum gauge position of wing 3
Put；Because the aspect ratio of wing 3 is smaller, wing tip vortex can be very big during horizontal flight, but propeller 5 is arranged on 3 liang of wingtips of wing,
The direction of rotation of propeller 5 and the direction of rotation of wing tip vortex are on the contrary, the slip-stream that propeller 5 is reversed can be to the wingtip of wing 3
Vortex carries out turn-back, reduces the wing tip vortex of wing 3, wing 3 is produced enough lift and maintains individual lift device
Horizontal flight, due to the advantageous effect of propeller 5, propeller can also maintain individual lift device level to fly with less high rotating speed
OK, so individual lift device voyage is remote, endurance is long.
Such as Fig. 1, shown in 2,3, the maximum gauge position of the lower aerofoil of the wing 3 is provided with spoiler 8a, top airfoil
Maximum gauge position is provided with spoiler 8b.
Because wing is asymmetric aerofoil profile, so in VTOL and floating state, propellerslip can be produced to wing
The raw aerodynamic force moved horizontally backward, so being provided with spoiler 8a, top airfoil in the maximum gauge position of the lower aerofoil of wing 3
Maximum gauge position be provided with spoiler 8b, in individual lift device VTOL and floating state, spoiler 8a and flow-disturbing
Plate 8b is opened, and this can destroy the aerofoil profile of wing 3, the slip-stream of propeller 5 is not produced move horizontally backward pneumatic to wing 3
Power, the VTOL and hovering for individual lift device is stablized.
Such as Fig. 1, shown in 2,3, the leading edge of the wing 3 is parallel with trailing edge.
The leading edge of wing 3 is parallel with trailing edge, and this can make wing profile succinct, attractive in appearance.
Such as Fig. 1, shown in 2,3, the bottom of driving cabin 1 has a main wheel 9.
The bottom of driving cabin 1 has a main wheel 9, and the weight of such driver can be directly passed to main wheel 9, and load path is straight
Connect, and main wheel 9 is installed in the afterbody that driving cabin 1 shrinks, make driving cabin resistance small, on ground, can be moved by main wheel 9
Individual lift device.
Piggyback pod bottom is provided with the X-type empennage being made up of X stabilizations 6 and X rudder faces 7, and such individual lift device is vertical
Landing and level flight condition can be manipulated；X-shaped empennage wingtip is provided with the buffering being made up of loop bar 10 and pillar 11
Device, such individual lift device, which stands in ground, enough stable areas, and resistance is small；The back of driving cabin 1 is provided with hatch door 12,
Driver enters from the back of driving cabin 1, and driver crouches down and driven during individual lift device horizontal flight, and hatch door 12, which is located in, to be driven
The person of sailing back, driver haves a sense of security；The connection driving cabin 1 of wing 3 and piggyback pod 4 of individual lift device, individual lift device is in whole
Body block structure, similar all-wing aircraft, structure efficiency is high, and intensity is high, and weight can be lighter；Individual lift device can be using pure electronic dynamic
Force system, but be oil electric mixed dynamic system in suitable dynamical system at this stage；This individual lift device is needed using actively steady
Determine system and carry out artificial increase surely.
When individual lift device stands in ground and needs to take off vertically, the spoiler 8a and top airfoil of the lower aerofoil of wing 3 are opened
Spoiler 8b, while propeller 5, which is started working, produces slip-stream, the thrust of slip-stream and the pulling force of propeller 5 exceed individual lift device
Weight, individual lift device is taken off vertically, the slip-stream for the rear screw shaft 5 that takes off can blow over to be made up of X stabilizations 6 and X rudder faces 7
X empennages, deflect X rudder faces 7 by computer and servo control mechanism and produce controling power, individual lift device is kept perpendicular attitude, one flies
Row device rises to the appropriate reduction rotating speed of propeller 5 after certain altitude, and individual lift device enters floating state；Individual lift device is outstanding
When stopping state and needing horizontal flight, pack up the spoiler 8a of the lower aerofoil of wing 3 and the spoiler 8b of top airfoil, at the same X rudder faces 7 to
Preceding deflection, X empennages can produce controling power backward, the controling power meeting produced due to X empennages in individual lift device bottom, X empennages
Individual lift device is set to bow, at this moment propeller 5 can produce component forward, this component moves forward individual lift device, after
Continuous to strengthen this trend, individual lift device turns to the horizontal attitude of low incidence gradually, and at this moment wing 3 produces lift and loads one
The weight of aircraft, propeller 5 pulls individual lift device flight forward, and the X empennages that X stabilizations 6 and X rudder faces 7 are constituted are to one
The longitudinal direction of aircraft, is laterally manipulated with course motion, at this moment, because the slip-stream that propeller 5 is reversed counteracts the wing of wing 3
The tip is vortexed, and wing 3 has larger lift coefficient and lift-drag ratio, and the rotating speed of propeller 5 less can also maintain individual lift device water greatly
Flat flight, thus individual lift device voyage is remote, endurance is long；Individual lift device needs to be changed into floating state from level flight condition
When, X rudder faces 7 are upward deflected, and X empennages produce downward controling power, and this power makes individual lift device come back gradually, slow down forward
Flight, continue to strengthen this trend, individual lift device, which comes back, arrives perpendicular attitude, and propeller 5 produces lift load sole flight
The weight of device, deflects X rudder faces 7 by computer and servo control mechanism and produces controling power, individual lift device is kept perpendicular attitude, open
The spoiler 8a of the lower aerofoil of the wing 3 and spoiler 8b of top airfoil, makes individual lift device not produce moving horizontally backward, one
Aircraft enters floating state；Individual lift device reduces the rotating speed of propeller 5, due to spiral when floating state wants vertical landing
The lift that oar 5 is produced is slightly less than the weight of individual lift device, and individual lift device slowly declines, until main wheel 9 and pillar 11 are contacted
Ground, stops propeller 5 and rotates, pack up spoiler 8a and spoiler 8b, individual lift device vertical landing process terminates.
Finally illustrate, above example is only unrestricted to illustrate the technical solution of the utility model, although ginseng
The utility model is described in detail according to preferred embodiment, it will be understood by those within the art that, can be to this
The technical scheme of utility model is modified or equivalent substitution, without departing from the objective and model of technical solutions of the utility model
Enclose, it all should cover among right of the present utility model.
Claims (4)
1. a kind of individual lift device, including driving cabin（1）, the transparent head-shield in driving cabin head（2）, piggyback pod（4）Positioned at driving
Cabin（1）Both sides, piggyback pod（4）The propeller that head is set（5）Plane of rotation exceed head-shield（2）Highly, piggyback pod（4）Length
Spend, driving cabin close and streamlined with driving cabin（1）And piggyback pod（4）Between be connected with wing（3）, piggyback pod（4）Bottom
With respect to driving cabin（1）Outside side is provided with by X stabilizations（6）With X rudder faces（7）The X-type empennage of composition, X-shaped empennage wingtip
It is provided with by loop bar（10）And pillar（11）The buffer of composition, driving cabin（1）Back is provided with hatch door（12）, its feature exists
In：Wing（3）For buzzard-type wing, wing（3）Wing root leading edge close to head-shield（2）, trailing edge is positioned at driving cabin（1）Bottom；Machine
The wing（3）Wingtip leading edge close to piggyback pod（4）Top, trailing edge is close to piggyback pod（4）Bottom.
2. individual lift device according to claim 1, it is characterised in that the wing（3）Lower aerofoil maximum gauge
Position is provided with spoiler（8a）, the maximum gauge position of top airfoil is provided with spoiler（8b）.
3. individual lift device according to claim 1, it is characterised in that wing（3）Leading edge it is parallel with trailing edge.
4. individual lift device according to claim 1, it is characterised in that driving cabin（1）Bottom has a main wheel（9）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621238876.0U CN206344990U (en) | 2016-11-19 | 2016-11-19 | Individual lift device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621238876.0U CN206344990U (en) | 2016-11-19 | 2016-11-19 | Individual lift device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206344990U true CN206344990U (en) | 2017-07-21 |
Family
ID=59318191
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621238876.0U Expired - Fee Related CN206344990U (en) | 2016-11-19 | 2016-11-19 | Individual lift device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206344990U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU185829U1 (en) * | 2018-04-18 | 2018-12-19 | Александр Александрович Горбунов | Aircraft vertical take-off and landing with an ellipse (disk) wing |
| CN112339988A (en) * | 2020-10-29 | 2021-02-09 | 中电科芜湖通用航空产业技术研究院有限公司 | Equal-load three-piece wing tip sail sheet structure and design method thereof |
-
2016
- 2016-11-19 CN CN201621238876.0U patent/CN206344990U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU185829U1 (en) * | 2018-04-18 | 2018-12-19 | Александр Александрович Горбунов | Aircraft vertical take-off and landing with an ellipse (disk) wing |
| CN112339988A (en) * | 2020-10-29 | 2021-02-09 | 中电科芜湖通用航空产业技术研究院有限公司 | Equal-load three-piece wing tip sail sheet structure and design method thereof |
| CN112339988B (en) * | 2020-10-29 | 2022-10-25 | 中电科芜湖通用航空产业技术研究院有限公司 | Equal-load three-piece wing tip sail sheet structure and design method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170721 Termination date: 20171119 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |