CN105882989A - Installation platform for bilateral hanging detection system of helicopter with three-dimensional static stability - Google Patents
Installation platform for bilateral hanging detection system of helicopter with three-dimensional static stability Download PDFInfo
- Publication number
- CN105882989A CN105882989A CN201610302232.1A CN201610302232A CN105882989A CN 105882989 A CN105882989 A CN 105882989A CN 201610302232 A CN201610302232 A CN 201610302232A CN 105882989 A CN105882989 A CN 105882989A
- Authority
- CN
- China
- Prior art keywords
- housing
- helicopter
- rotating disk
- tail
- vertical tail
- 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.)
- Granted
Links
- 230000003068 static effect Effects 0.000 title claims abstract description 23
- 238000001514 detection method Methods 0.000 title claims abstract description 16
- 230000002146 bilateral effect Effects 0.000 title claims abstract description 12
- 238000009434 installation Methods 0.000 title claims abstract description 10
- 230000004323 axial length Effects 0.000 claims description 10
- 238000000034 method Methods 0.000 abstract 3
- 230000005484 gravity Effects 0.000 description 6
- 238000005096 rolling process Methods 0.000 description 5
- 230000001629 suppression Effects 0.000 description 3
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 208000013623 stereotypic movement disease Diseases 0.000 description 1
- 230000032258 transport Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Devices Affording Protection Of Roads Or Walls For Sound Insulation (AREA)
Abstract
The invention relates to an installation platform for a bilateral hanging detection system of a helicopter with three-dimensional static stability. The installation platform comprises a shell, vertical wings, horizontal wings, a front turntable and a rear turntable, wherein the two vertical wings are symmetrically mounted on vertical symmetrical walls of the circumferential surface of the shell and can be rotated for 5-10 degrees; the two horizontal wings are symmetrically mounted on the horizontal symmetrical walls of the circumferential surface of the shell; the front turntable and the rear turntable are respectively located on the head part and the tail part; an upper wing surface of the vertical wing of the installation platform on the left side of the helicopter faces to the left side of the shell; the upper wing surface of the vertical wing of the installation platform on the right side of the helicopter faces to the right side of the shell; the shell, the front turning shaft and the rear turning shaft are coaxial with each other. In the installation platform provided by the invention, two dragging bodies stretch toward the two sides in a flying process; the detection scope of the detector is expanded; the mutual collision in the flying process and the mutual interference of the signal of the detector are avoided; the shaking and swinging of the dragging bodies in the flying process are reduced; the detection precision and operation efficiency are increased.
Description
Technical field
The present invention relates to aviation towing field, be a kind of in bilateral hanging towing mode, and towed body can be kept quiet surely
Hanging detection system mounting platform qualitatively.
Background technology
Aviation towing is application technology widely, and as pulled target drone, helicopter hanger transports, helicopter is gloomy
Woods fire extinguishing, airborne geophysical prospecting, helicopter are searched and latent etc. will be applied this technology.During towing, towed body is subject to
The disturbance flowed can move, and the stability of this aircraft and towed body itself to performing towing task is all unfavorable
, when towed body more than one, in addition it is also necessary to prevent from colliding between each towed body, it is therefore necessary to towed body
Stability and skyborne position are controlled by.Patent at home and abroad there are some stable to multiple spot hanging and towed body
The design of property.A kind of helicopter hanger is disclosed in the utility model patent that notification number is CN202029999U.Institute
The helicopter multiple spot hangar system stated is one quadra of hanging under helicopter, hangs four groups of goods in the corner of square frame
Thing, but the stability of goods is not controlled by by it, the phase para-position of the most uncontrollable four groups of goods in flight course
Put.The constancy system of a kind of helicopter hanger is proposed in the innovation and creation of Publication No. CN102874413A,
This system has installed the device of similar vertical fin additional at the rear of Under-Slung Loads, it is possible to make hanging object produce the static stability in course,
But horizontal static stability cannot be ensured.One is proposed in the innovation and creation of Publication No. US2012043414A1
Plant the device that suppression hanging object swings, realize the swing of suppression hanging object by installing feedback control system additional, and can only
The swing of suppression rope, it is impossible to the attitude of hanging object itself is controlled by.
Summary of the invention
For overcoming the static stability of hanging object present in prior art poor, it is impossible to control the deficiency of hanging object attitude,
The present invention proposes a kind of helicopter bilateral hanging detection system mounting platform with three-dimensional static stability.
The present invention includes housing, vertical tail, horizontal tail, front rotating disk and rear rotating disk, wherein: described vertical tail, has two
Individual, it is symmetrically installed in the vertical symmetry plane of described housing circumferential surface；Described horizontal tail has two, symmetrical
It is arranged on the horizontal symmetry face of described housing circumferential surface；Described front rotary shaft is positioned at housing head, and this forward
The front end face of axle is affixed with housing, and the rear end of this front rotary shaft loads in the centre bore of front rotating disk；Described rear rotating shaft is positioned at shell
Internal afterbody, and the rear end face of this rear rotating shaft is affixed with housing；Rear rotating disk is set with in rotating shaft in the rear.This is vertical
The wing is complete dynamic aerofoil, is connected with housing by rotating shaft；Described rotating shaft is positioned at 1/4 chord length of this vertical tail, wing root；Should
Vertical aerofoil does-5 °～10 ° rotations around this rotating shaft.When installing described vertical tail, it is positioned at the installation on the left of aircraft and puts down
The top airfoil of the vertical tail, of platform, towards the left side of housing, is positioned at the top airfoil court of the vertical tail, of mounting platform on the right side of aircraft
To the right side of housing.Described housing, front rotary shaft are coaxial with rear rotating shaft three.
Described housing uses the body of revolution of combining form, is made up of with back segment leading portion.The head of this housing is semielliptical
Body.
Described horizontal tail uses the rectangle aerofoil without sweepback, and the upper counterangle is 5 °, and established angle is 0 °；Aerofoil profile uses
NACA012 aerofoil profile；The aspect ratio of horizontal tail is 0.25；This horizontal tail leading edge be positioned at described housing axial length 35～
At 40%.
Described vertical tail, uses the rectangle aerofoil without sweepback, and aerofoil profile uses NACA2410 aerofoil profile；The aspect ratio of vertical tail,
It is 0.25；The position of this vertical tail, leading edge is identical with the axial location of described horizontal tail.
The front end face of described front rotating disk is positioned at the 25.6% of described housing axial length；The front end face position of described rear rotating disk
At described housing axial length 89.7%.The external diameter of described front rotating disk and the external diameter of rear rotating disk are all slightly less than housing inner diameter
Ensure that it can be freely rotatable in enclosure interior.Fix at the circumferential surface of described front rotating disk and the circumferential surface of rear rotating disk
There is the rope hook for connecting rope.
Described mounting platform has two, is hung the both sides at helicopter respectively by rope.
In magnetic air detects, it is desirable to use multiple detector to increase investigative range simultaneously, ensure each towed body simultaneously
Between do not collide, be not wound around between tow strap, this is necessary for being controlled position of detector of hanging,
Bigger investigative range can be covered.Meanwhile, only ensureing that the stability in course is inadequate, towed body to be made is not
Invert, it is necessary to provide the stability of vertical and horizontal for it.
In the present invention, two detectors of peace hanging below helicopter, detector is contained in employing semielliptical and cylinder knot
Closing in the towed body of profile, towed body has a pair horizontal tail and a pair vertical tail,.Horizontal tail uses the RECTANGULAR WINGS without sweepback
, there is certain upper counterangle in face, provides Lateral static stability for towed body.In order to enable towed body when cruise to directly
The both sides of the machine of liter are pulled open, and vertical tail, must provide for aerodynamic force laterally.Therefore, vertical tail, uses the low speed having lift
Aerofoil profile, uses complete dynamic aerofoil, and aerofoil flat shape is rectangle.Horizontal tail and vertical tail, all use the wing of relatively low aspect ratio
Face so that the position of aerofoil Center of Pressure, close proximity to housing axis, reduces rolling moment.The aerofoil profile of horizontal tail and axle
After the axial location of the aerodynamic center selecting guarantee aerofoil of installation site is positioned at the center of gravity axial location of towed body,
Ensure the Longitudinal static stability of towed body.Towed body is connected with helicopter with 2 ropes, the axial position of rope hook hanging point
Put and be symmetrically arranged at both sides before and after towed body center of gravity axial location.The position of rope hook hanging point is adjustable in the circumferential
, to ensure that the position of rope pull can be through the axis of towed body.Hook point adjusting means is one and is arranged on
Rotating disk on fixing bearing, rotating disk can rotate around bearing.Front and back hook point adjusting means is separate,
Can work independently from each other.
The present invention obtains and provides the benefit that:
First, two towed bodys can open to both sides in flight course, it is possible to avoids two towed bodys flying
Journey occurs mutually collision, the most awing ensures that two towed bodys have enough distances between detector, it is to avoid
The signal of detector interferes
Second, two towed bodys keep opening in flight course, it is possible to make its investigative range covered become big, two
Horizontal range between towed body can be adjusted according to the drift angle of flight speed and vertical tail.If speed during flight
Degree is V∞, the density flowed is ρ∞, the lifting line fixed rate of interest of vertical tail, is CLα, vertical tail, drift angle is α, single vertically
The area of the wing is S, and towed body and the gross mass loading detector therein are m, a length of l of the rope that hanging uses,
Then according to stress balance principle, tow and the angle of horizontal direction during flightFor:
Then horizontal range d between two towed bodys is,
3rd, the horizontal tail of towed body has the upper counterangle of 5 °, it is ensured that towed body is laterally to have rolling quiet surely
Qualitative.Its principle is: have the aerofoil at the upper counterangle, and when towed body occurs rolling to the left, it is pneumatic that left wing face produces
The horizontal component of power reduces, and vertical component increases, and the horizontal component of the aerodynamic force that right flank face produces increases, vertical component
Reducing, now the lift on left wing face is more than the lift in right flank face, makes towed body produce rolling moment to the right, forces
Towed body rolling to the right, returns to initial attitude.
4th, the axially mounted position of towed body horizontal tail ensure that integral pitch aerodynamic center, after center of gravity, makes to drag
Drag body and there is Longitudinal static stability.Its principle is: calculate through CFD, when flight speed is at 100km/h to 200km/h
Between time, the pitching aerodynamic center of towed body between 2962.5mm to 3002.0mm foremost, static-stability
Nargin, between 25.3% to 26.0%, has enough static margins, and the change in location of aerodynamic center is little.When dragging
When draging body new line, the angle of attack of horizontal tail increases, and the lift of generation increases, and according to aerodynamic theory, rises
The incremental contribution of power is in aerodynamic center, and after aerodynamic center is positioned at center of gravity, now the increment of lift produces power of bowing
Square, forces towed body to be bowed, and returns to initial attitude.
5th, the axially mounted position of towed body vertical tail, ensure that overall driftage aerodynamic center, after center of gravity, makes to drag
Drag body and there is directional static stability.Its principle is: calculate through CFD, when flight speed is at 100km/h to 200km/h
Between time, the driftage aerodynamic center of towed body between 2962.5mm to 3029.6mm foremost, static-stability
Nargin, between 25.3% to 26.7%, has enough static margins, and the change in location of aerodynamic center is little, and
With pitching aerodynamic center very close to.When towed body occurs driftage to the left, vertical tail, produces cross force to the left and increases
Amount, this incremental contribution is at driftage aerodynamic center, and after being positioned at center of gravity due to driftage aerodynamic center, cross force increment produces
Raw yawing to the right, forces towed body to be gone off course to the right, returns to initial attitude.
6th, according to above five effects produced, it is possible to reduce towed body rocking and swinging in flight course,
Be conducive to reducing the detection noise of detector, improve the precision of detection, improve sphere of action and the signal of detector simultaneously
Intensity, improves working performance.
Accompanying drawing explanation
Fig. 1 is that the mounting platform of the present invention is at the installation site schematic diagram performed on towing helicopter.
Fig. 2 is the structural representation of housing；Wherein: Fig. 2 a is front view, Fig. 2 b is left view.
Fig. 3 is the structural representation of housing；Wherein: Fig. 3 a is front view, Fig. 3 b is the A-A direction view of Fig. 3 a.
In figure: 1. helicopter, 2. rope, 3. housing, 4. vertical tail, 5. horizontal tail, 6. before rotating disk, 7. after rotating disk, 8.
Front rotary shaft, 9. after rotating shaft, 10. rope hook hanging point.
Detailed description of the invention
The present embodiment is the mounting platform of a kind of helicopter bilateral hanging detection system with three-dimensional static stability, this peace
Assembling platform has two.As it is shown in figure 1, the housing of two mounting platforms hangs the both sides at helicopter respectively by rope.
Described mounting platform includes housing 3, vertical tail, 4, horizontal tail 5, front rotating disk 6 and rear rotating disk 7, wherein: institute
The vertical tail, 4 stated has two, is symmetrically installed on longitudinally asymmetric of described housing 3 circumferential surface；Described water
The flat wing 5 has two, is symmetrically installed on the horizontal symmetry face of described housing 3 circumferential surface；In described housing
Head has front rotary shaft 8, rotating disk 6 before being set with on this front rotary shaft 8；Afterbody in described housing have after rotating shaft 9
Rotating disk 7 after being set with in this rear rotating shaft 9.
As in figure 2 it is shown, the housing in the present embodiment uses the body of revolution of combining form, it is made up of with back segment leading portion, with
Convenient placement detecting devices in this housing.Fixed by screw after described leading portion is overlapped with back segment.Shell after combination
The head of body is semiellipsoid, a length of 1000mm of spheroid semi-major axis, a length of 500mm of semi-minor axis；Should
The middle part of housing is isometrical cylinder section, and the external diameter of this isometrical cylinder section is 1000mm, a length of 2500mm；This housing
Afterbody is semiellipsoid, a length of 400mm of semi-major axis, a length of 500mm of semi-minor axis.
Described horizontal tail uses the rectangle aerofoil without sweepback, the symmetrical both sides being fixedly mounted on housing.Described horizontal tail
The upper counterangle be 5 °, established angle is 0 °, aerofoil profile use NACA012 aerofoil profile, the aspect ratio of horizontal tail is 0.25；
This horizontal tail leading edge is positioned at described housing axial length 35～40%.In the present embodiment, chord length is 2000mm, single
The length of the wing is 500mm.This horizontal tail leading edge distance housing axial distance foremost is 1500mm, is positioned at described
At housing axial length 38.5%.
Described vertical tail, uses the rectangle aerofoil without sweepback, and aerofoil profile uses NACA2410 aerofoil profile, is symmetrically mounted on described
Housing upper surface and lower surface.The aspect ratio of described vertical tail, is 0.25；The position of this vertical tail, leading edge and described level
The axial location of the wing is identical.In the present embodiment, the chord length of described vertical tail, is 2000mm, and the length of single-blade is 500mm,
The leading edge distance housing axial distance foremost of this vertical tail, is 1500mm.
This vertical tail, is complete dynamic aerofoil, is connected with housing by rotating shaft.Described rotating shaft is positioned at this vertical tail, wing root section 1/4
At chord length.This vertical tail, rotates between-5 °～10 ° around this rotating shaft.When installing described vertical tail, it is positioned at aircraft
The top airfoil of the vertical tail, of the mounting platform in left side, towards the left side of housing, is positioned at the vertical of mounting platform on the right side of aircraft
The top airfoil of the wing is towards the right side of housing.
As shown in Figure 3.The front end face of described front rotating disk is positioned at the 25.6% of described housing axial length；Turn after described
The front end face of dish is positioned at described housing axial length 89.7%.The external diameter of described front rotating disk and the external diameter of rear rotating disk all omit
Ensure that it can be freely rotatable in enclosure interior less than housing inner diameter.At the circumferential surface of described front rotating disk and rear rotating disk
Circumferential surface is fixed with the rope hook for connecting rope.
In the present embodiment, front rotating disk 6 is positioned at distance housing head 1000mm foremost, rotating disk thickness 50mm, peace
It is contained on front rotary shaft 8.The front end face of described front rotary shaft 8 is affixed with housing 3.Rear rotating disk 7 is positioned at distance head front end
At 3500mm, rotating disk thickness 50mm, it is arranged in rear rotating shaft 9.Described rear rotating shaft 9 is affixed with housing 3.Described
Housing, front rotary shaft and the dead in line of rear rotating shaft three.
The external diameter of described front rotating disk 6 and the external diameter of rear rotating disk 7 are all slightly less than housing 3 internal diameter, it is ensured that it can be at housing
3 is internal freely rotatable.The diameter of front rotary shaft 8 and rear rotating shaft 9 ensures that its intensity must be enough to support each rotating disk.Rope hook
10 circumferential surface being fixed on described front rotating disk and the circumferential surfaces of rear rotating disk, are used for connecting rope 2.
The result calculated according to CFD, uses the present embodiment, when between flight speed is at 100km/h to 200km/h,
Longitudinal static margin of detector between 25.3% to 26.0%, course static margin 25.3% to 26.7% it
Between, the result of calculating shows that detector has the strongest static stability.
Claims (6)
1. a helicopter bilateral hanging detection system mounting platform with three-dimensional static stability, it is characterised in that include shell
Body, vertical tail, horizontal tail, front rotating disk and rear rotating disk, wherein: described vertical tail, has two, symmetrical installation
In the vertical symmetry plane of described housing circumferential surface；Described horizontal tail has two, is symmetrically installed on described shell
On the horizontal symmetry face of body circumferential surface；Described front rotary shaft is positioned at housing head, and the front end face of this front rotary shaft
Affixed with housing, the rear end of this front rotary shaft loads in the centre bore of front rotating disk；Described rear rotating shaft is positioned at housing afterbody,
And the rear end face of this rear rotating shaft is affixed with housing；Rear rotating disk is set with in rotating shaft in the rear；This vertical tail, is complete dynamic
Aerofoil, is connected with housing by rotating shaft；Described rotating shaft is positioned at 1/4 chord length of this vertical tail, wing root；This vertical tail,
-5 °～10 ° rotations are done around this rotating shaft in face；When installing described vertical tail, it is positioned at mounting platform on the left of aircraft
The top airfoil of vertical tail, towards the left side of housing, be positioned at mounting platform on the right side of aircraft vertical tail, top airfoil towards
The right side of housing；Described housing, front rotary shaft are coaxial with rear rotating shaft three.
There is the helicopter bilateral hanging detection system mounting platform of three-dimensional static stability, its feature the most as claimed in claim 1
Being, described housing uses the body of revolution of combining form, is made up of with back segment leading portion；The head of this housing is half
Spheroid.
There is the helicopter bilateral hanging detection system mounting platform of three-dimensional static stability, its feature the most as claimed in claim 1
Being, described horizontal tail uses the rectangle aerofoil without sweepback, and the upper counterangle is 5 °, and established angle is 0 °；Aerofoil profile is adopted
Use NACA012 aerofoil profile；The aspect ratio of horizontal tail is 0.25；This horizontal tail leading edge is positioned at described housing axial length
At 35～40%.
There is the helicopter bilateral hanging detection system mounting platform of three-dimensional static stability, its feature the most as claimed in claim 1
Being, described vertical tail, uses the rectangle aerofoil without sweepback, and aerofoil profile uses NACA2410 aerofoil profile；Vertical tail,
Aspect ratio is 0.25；The position of this vertical tail, leading edge is identical with the axial location of described horizontal tail.
There is the helicopter bilateral hanging detection system mounting platform of three-dimensional static stability, its feature the most as claimed in claim 1
Being, the front end face of described front rotating disk is positioned at the 25.6% of described housing axial length；The front end of described rear rotating disk
Face is positioned at described housing axial length 89.7%；The external diameter of described front rotating disk and the external diameter of rear rotating disk are all slightly less than shell
Internal footpath ensures that it can be freely rotatable in enclosure interior；Circumferential surface and the circumference of rear rotating disk at described front rotating disk
Surface is fixed with the rope hook for connecting rope.
There is the helicopter bilateral hanging detection system mounting platform of three-dimensional static stability, its feature the most as claimed in claim 1
Being, described mounting platform has two, is hung the both sides at helicopter respectively by rope.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2016100401608 | 2016-01-21 | ||
| CN201610040160 | 2016-01-21 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105882989A true CN105882989A (en) | 2016-08-24 |
| CN105882989B CN105882989B (en) | 2018-07-06 |
Family
ID=56703406
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610302232.1A Expired - Fee Related CN105882989B (en) | 2016-01-21 | 2016-05-09 | Helicopter bilateral hanging detection system mounting platform with three-dimensional static stability |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105882989B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112389665A (en) * | 2020-10-30 | 2021-02-23 | 中国直升机设计研究所 | Novel hanging object combined pneumatic surface stability augmentation system and design method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5836062A (en) * | 1997-04-16 | 1998-11-17 | Sikorsky Aircraft Corporation | Apparatus for assembling a helicopter main rotor blade subassembly |
| US20090166498A1 (en) * | 2007-12-28 | 2009-07-02 | Alion Science And Technology Corporation | Trailing edge blade clamp |
| WO2009131600A3 (en) * | 2008-04-26 | 2010-01-07 | Sikorsky Aircraft Corporation | Main rotor blade with integral cuff |
| CN203806143U (en) * | 2014-04-16 | 2014-09-03 | 徐鹏 | Installation platform assembly of aerophotography platform |
| CN104192325A (en) * | 2014-09-03 | 2014-12-10 | 北京卫星环境工程研究所 | Supporting device guaranteeing special posture of star sensor test piece |
| CN204056309U (en) * | 2014-07-08 | 2014-12-31 | 哈尔滨飞机工业集团有限责任公司 | A kind of photoelectric nacelle erecting stage |
-
2016
- 2016-05-09 CN CN201610302232.1A patent/CN105882989B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5836062A (en) * | 1997-04-16 | 1998-11-17 | Sikorsky Aircraft Corporation | Apparatus for assembling a helicopter main rotor blade subassembly |
| US20090166498A1 (en) * | 2007-12-28 | 2009-07-02 | Alion Science And Technology Corporation | Trailing edge blade clamp |
| WO2009131600A3 (en) * | 2008-04-26 | 2010-01-07 | Sikorsky Aircraft Corporation | Main rotor blade with integral cuff |
| CN203806143U (en) * | 2014-04-16 | 2014-09-03 | 徐鹏 | Installation platform assembly of aerophotography platform |
| CN204056309U (en) * | 2014-07-08 | 2014-12-31 | 哈尔滨飞机工业集团有限责任公司 | A kind of photoelectric nacelle erecting stage |
| CN104192325A (en) * | 2014-09-03 | 2014-12-10 | 北京卫星环境工程研究所 | Supporting device guaranteeing special posture of star sensor test piece |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112389665A (en) * | 2020-10-30 | 2021-02-23 | 中国直升机设计研究所 | Novel hanging object combined pneumatic surface stability augmentation system and design method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105882989B (en) | 2018-07-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP6480003B2 (en) | Adjustable landing gear assembly for unmanned aerial vehicles | |
| US20170283048A1 (en) | Convertable lifting propeller for unmanned aerial vehicle | |
| CN106043668B (en) | A kind of aerodynamic arrangement of three-control aircraft | |
| US20210009264A1 (en) | Flying object and flying object position control system | |
| CN103395498B (en) | A kind of dihedral angle optimization method improving Flying-wing's aircraft lateral directional flying qualities | |
| CN109141429B (en) | Method for designing flight path of near space ball-borne solar unmanned aerial vehicle in throwing process | |
| CN105564664B (en) | Short distance takes off method | |
| CN110418755A (en) | A kind of unmanned vehicle | |
| CN108177777A (en) | Aircraft based on wingtip vortex lift-increasing | |
| CN104417750A (en) | Tandem tilt rotor aircraft | |
| CN205239885U (en) | Airship | |
| CN108082471A (en) | A kind of variant supersonic plane | |
| CN103350750A (en) | Lift compensation type high speed aircraft | |
| CN101774429A (en) | Small UAV aerodynamic layout for vertical rope-type recovery | |
| CN105882989A (en) | Installation platform for bilateral hanging detection system of helicopter with three-dimensional static stability | |
| CN105109669B (en) | Aircraft recovery spin improving device | |
| CN204568062U (en) | One can be hovered flapping wing aircraft | |
| CN104670495B (en) | One can hover flapping wing aircraft and flight mode | |
| CN104554739B (en) | A kind of inlet lip that can strengthen and adjust tailless configuration's vector stability | |
| CN107215462B (en) | Landing method and landing device for vertical take-off and landing fixed wing unmanned aerial vehicle | |
| Cummings | Introduction: SACCON Unihabited Combat Aerial Vehicle Experimental and Numerical Simulations | |
| CN205738056U (en) | A kind of aerodynamic arrangement of the big aircraft of strategy | |
| CN206278270U (en) | A kind of VUAV vector puller system | |
| AU2012101594A4 (en) | A Supporting System for Pressure Measuring Test of the Entire Aircraft | |
| CN204701766U (en) | Arrow formula vertical take-off and landing aircraft (VTOL aircraft) |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180706 Termination date: 20190509 |