CN106347704A - Flight control testing device - Google Patents
Flight control testing device Download PDFInfo
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- CN106347704A CN106347704A CN201610807093.8A CN201610807093A CN106347704A CN 106347704 A CN106347704 A CN 106347704A CN 201610807093 A CN201610807093 A CN 201610807093A CN 106347704 A CN106347704 A CN 106347704A
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- locating part
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Abstract
The invention discloses a flight control testing device. The flight control testing device comprises a base, an outer shaft sleeve, an inner shaft sleeve and a rotating mechanism for achieving static flight tests of an unmanned aerial vehicle, wherein the rotating mechanism comprises a turntable and a connecting shaft which are connected mutually, the connecting shaft penetrates through the inner shaft sleeve, the outer shaft sleeve is in sleeved connection with the outer side of the inner shaft sleeve, and the outer shaft sleeve is connected with the base. The inner shaft sleeve comprises a sleeve casting and a boss, the boss is arranged in the middle of the peripheral wall of the sleeve casing, the peripheral wall of the sleeve casing is further in sleeved connection with at least two first bearings, and at least two first bearings are in abutting connection with two ends of the boss respectively. The technical scheme aims at ensuring that the flight control testing device can be suitable for frequent static flight tests of the unmanned aerial vehicle.
Description
Technical field
The present invention relates to unmanned air vehicle technique field is and in particular to a kind of fly control test device.
Background technology
With scientific and technological development, unmanned plane is more and more universal in our real-life uses, and unmanned plane extensively should
For in all trades and professions.When studying the flight attitude of unmanned plane with controlling it design, research worker is passed through quiet mostly
State aviation simulator is acquired to data such as the course angular dimensions under unmanned plane during flying state, pitching angular dimensions and studies, but
Existing static state aviation simulator structure is relatively simple, connects and not fasten between each part, is not suitable for bearing frequently unmanned
Machine static state flight test.
Content of the invention
The main object of the present invention is to provide a kind of winged control test device connecting more fastening it is intended to guarantee to fly control test
Device can suitably frequently unmanned plane static state flight test.
For achieving the above object, winged control test device proposed by the present invention includes base, outer shaft, internal axle sleeve and in order to reality
The rotating mechanism of existing unmanned plane static state flight test；Described rotating mechanism includes interconnective turntable and connecting shaft, described company
Spindle runs through described internal axle sleeve, and described outer shaft is socketed on outside described internal axle sleeve, and described outer shaft connects described base；Institute
State internal axle sleeve and include sleeve pipe and boss, described boss is located in the middle part of described sleeve pipe periphery wall, and described sleeve pipe periphery wall is also socketed
There are at least two clutch shaft bearings, clutch shaft bearing described at least two is abutted with the two ends of described boss respectively.
Preferably, described turntable includes rotation platform, fixed plate, two fixed seats, rotating shaft and in order to fixing unmanned plane
Installed part, two described fixed seats are respectively arranged on described rotation platform two ends, and described rotating shaft two ends are connected respectively two institutes
State fixed seat, described rotation platform is connected with described connecting shaft by described fixed plate, described installed part is located at described rotating shaft.
Preferably, described winged control test device also includes connector, locating part and fixture, described connecting shaft, connector
It is socketed successively from the inside to the outside with locating part, and described connector is threadeded with described fixed plate, deviating from of described locating part connects
The side of spindle connects described fixture, and one end that described fixture deviates from locating part is abutted with described outer shaft.
Preferably, described locating part includes the first locating part and the second locating part, described first locating part and second spacing
Part is threaded, is threadeded with described fixture in one end away from the second locating part of described first locating part, and described second
Threadeded with described fixture in one end away from the first locating part of locating part.
Preferably, described connecting shaft is vertical with the plane that described rotation platform is located；Described rotating shaft and described rotation platform
The plane being located is parallel.
Preferably, described turntable also includes second bearing, and described second bearing is sheathed between described rotating shaft and fixed seat,
The side that two described fixed seats mutually deviate from is equipped with baffle plate.
Preferably, described installed part is two, and two described installed parts are between two described fixed seats.
Preferably, described clutch shaft bearing is four, and one of described clutch shaft bearing is sheathed on described internal axle sleeve and fixation
Between part, clutch shaft bearing described in the other three is sheathed between described internal axle sleeve and outer shaft.
Preferably, described base includes base plate and column, and described column two ends connect described base plate and outer shaft respectively.
Preferably, between described clutch shaft bearing and described outer shaft, all logical between described clutch shaft bearing and described fixture
Cross screw to fix.
In technical solution of the present invention, described winged control test device is connected in order to place the turntable of unmanned plane by connecting shaft,
Described unmanned function is made to be fixed on described turntable, and then by the synergism of described connecting shaft and described turntable so that no
Man-machine enable various flight attitudes, the convenient flight attitude parameter to unmanned plane is acquired and studies；And described connecting shaft
Outside is arranged with internal axle sleeve and outer shaft, can further ensure that the steadiness that described connecting shaft connects, and prevents because of multiple flight examination
Test and lead to connect axle fracture the occurrence of it is ensured that described winged control test device adapt to frequently flight test.
Brief description
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
Have technology description in required use accompanying drawing be briefly described it should be apparent that, drawings in the following description be only this
Some embodiments of invention, for those of ordinary skill in the art, on the premise of not paying creative work, acceptable
Structure according to these accompanying drawings obtains other accompanying drawings.
Fig. 1 is the fractionation structural representation of the part-structure flying control test device in one embodiment of the invention；
Fig. 2 is the fractionation structural representation of the turntable flying control test device in another embodiment of the present invention；
Fig. 3 is the structural representation that in Fig. 2, outer shaft, fixture, locating part, connector are connected with fixed plate；
Fig. 4 is the top view of Fig. 3；
Fig. 5 is the sectional view of b-b in Fig. 4；
Fig. 6 is the decomposition texture schematic diagram of outer shaft in Fig. 3.
Drawing reference numeral illustrates:
| Label | Title | Label | Title |
| 10 | Turntable | 20 | Base |
| 30 | Outer shaft | 40 | Internal axle sleeve |
| 50 | Connecting shaft | 60 | Clutch shaft bearing |
| 70 | Connector | 80 | Locating part |
| 90 | Fixture | 11 | Rotation platform |
| 12 | Fixed plate | 13 | Fixed seat |
| 14 | Rotating shaft | 15 | Installed part |
| 16 | Second bearing | 17 | Baffle plate |
| 21 | Base plate | 22 | Column |
| 31 | Inner sleeve | 32 | Overcoat |
| 41 | Sleeve pipe | 42 | Boss |
| 81 | First locating part | 82 | Second locating part |
| 83 | Circulus | 84 | Lug |
| 85 | Plug connector |
The realization of the object of the invention, functional characteristics and advantage will be described further in conjunction with the embodiments referring to the drawings.
Specific embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation description is it is clear that described embodiment is only a part of embodiment of the present invention, rather than whole embodiments.Base
Embodiment in the present invention, those of ordinary skill in the art obtained under the premise of not making creative work all its
His embodiment, broadly falls into the scope of protection of the invention.
It is to be appreciated that the directional instruction (such as up, down, left, right, before and after ...) of institute is only used in the embodiment of the present invention
In explaining the relative position relation between each part, motion conditions etc. under a certain particular pose (as shown in drawings), if should
When particular pose changes, then directionality instruction also correspondingly changes therewith.
In addition, in the present invention such as relating to the description of " first ", " second " etc. is only used for describing purpose, and it is not intended that
Indicate or imply its relative importance or the implicit quantity indicating indicated technical characteristic.Thus, define " first ",
The feature of " second " can be expressed or implicitly include at least one this feature.In describing the invention, the containing of " multiple "
Justice is at least two, such as two, three etc., unless otherwise expressly limited specifically.
In the present invention, unless otherwise clearly defined and limited, term " connection ", " fixation " etc. should be interpreted broadly,
For example, " fixing " can be to be fixedly connected or be detachably connected, or integral；Can be mechanically connected or
Electrical connection；Can be to be joined directly together it is also possible to be indirectly connected to by intermediary, can be the connection or two of two element internals
The interaction relationship of individual element, limits unless otherwise clear and definite.For the ordinary skill in the art, can basis
Concrete condition understands above-mentioned term concrete meaning in the present invention.
In addition, the technical scheme between each embodiment of the present invention can be combined with each other, but must be general with this area
Based on logical technical staff is capable of, will be understood that this when the combination appearance of technical scheme is conflicting or cannot realize
The combination of technical scheme does not exist, also not within the protection domain of application claims.
The present invention proposes a kind of winged control test device.
Refer to Fig. 1 to Fig. 5, in an embodiment of the present invention, this fly control test device, including base 20, outer shaft 30,
Internal axle sleeve 40 and the rotating mechanism (sign) in order to realize unmanned plane static state flight test；Described rotating mechanism includes mutually interconnecting
The turntable 10 connecing and connecting shaft 50, described connecting shaft 50 runs through described internal axle sleeve 40, and described outer shaft 30 is socketed on described interior axle
Outside set 40, and described outer shaft 30 connects described base 20；Described internal axle sleeve 40 includes sleeve pipe 41 and boss 42, described boss
42 are located in the middle part of described sleeve pipe 41 periphery wall, and described sleeve pipe 41 periphery wall is also socketed with least two clutch shaft bearings 60, two
Described clutch shaft bearing 60 is abutted with the two ends of described boss 42 respectively.
Turntable 10 that described winged control test device connects to place unmanned plane by connecting shaft 50 is so that described unmanned plane
Described turntable 10 can be fixed on, and then by the synergism of described connecting shaft 50 and described turntable 10 so that unmanned function is real
Existing various flight attitudes, the convenient flight attitude parameter to unmanned plane is acquired and studies.Described connecting shaft 50 outside is sheathed
There are internal axle sleeve 40 and outer shaft 30, the steadiness that described connecting shaft 50 connects can be further ensured that, prevent because of multiple flight test
And lead to connecting shaft 50 fracture the occurrence of it is ensured that described winged control test device adapt to frequently flight test.Described
The two ends of boss 42 are respectively sleeved on clutch shaft bearing 60, can bear the axial stress that heavier body produces it is ensured that described connection
The fixation at Zhou50Zhou center, and rubbing of internal axle sleeve 40 generation described in described winged control test device motor process can be effectively reduced
Wipe coefficient.
Referring in particular to Fig. 2, described turntable 10 includes rotation platform 11,12, two fixed seats 13 of fixed plate, rotating shaft 14 and
In order to the installed part 15 of fixing unmanned plane, two described fixed seats 13 are respectively arranged on described rotation platform 11 two ends, described rotating shaft
14 two ends are connected respectively two described fixed seats 13, and described installed part 15 is located at described rotating shaft 14, described rotation platform 11
It is fixedly connected with described connecting shaft 50 by described fixed plate 12.Specifically, unmanned plane is installed on described installed part 15, described turn
Axle 14 rotatable movement, and then can guarantee that the smooth of flight attitude of unmanned plane is carried out.
Continue referring to Fig. 1 and Fig. 3, described winged control test device also includes connector 70, locating part 80 and fixture 90；
Described connecting shaft 50, connector 70 and locating part 80 are socketed from the inside to the outside successively, and described connector 70 and described fixed plate 12
Threaded, the side deviating from connecting shaft 50 of described locating part 80 connects described fixture 90, and described fixture 90 deviates from limit
One end of position part 80 is abutted with described outer shaft 30.
Specifically, described connecting shaft 50 sequentially passes through described connector 70, locating part 80 and fixture 90 from top to bottom, and
Described locating part 80 is sheathed on outside described connector 70, and in order to fasten described connector 70, the two ends of described fixture 90 are divided
Do not connect and be arranged between described locating part and internal axle sleeve 40, and described internal axle sleeve 40 and described fixture 90 at least described in one
One bearing 60.Described connector 70 is connected with described turntable 10, when unmanned plane is installed on turntable 10 and drives described turntable 10
During motion, and then described connector 70, the rotation of connecting shaft 50 can be driven, described interior axle is driven by described connecting shaft 50 simultaneously
The rotating so that described clutch shaft bearing 60 can bear the axial stress of unmanned plane generation it is ensured that described of set 40 and clutch shaft bearing 60
Fly control test device and adapt to complete the static flight simulation action of unmanned plane.
Further, described locating part includes the first locating part 81 and the second locating part 82.A preferred reality in the present invention
Apply in scheme, described locating part also includes two circuluses 83, the opening of two described circuluses 83 is oppositely arranged with shape
Become a circular ring structure；Described first locating part 81 is connected to its opening side that deviates from of circulus 83 described in, and described second
Locating part 82 is connected to the side deviating from its opening of another described circulus 83.The opposite end of described circulus is all provided with
It is equipped with lug 84, described lug 84 is provided with screwed hole (sign), screw passes through described screwed hole, can with nut screw connection
To realize controlling the tightness of two described circuluses 83, so that locating part fastening or pine are from described connecting shaft 50.
In the present embodiment, each described lug 84 respectively arranges two screwed holes, and two screws pass through screwed hole to tie two described ring-types
Structure 84 connects into a circular ring structure.Described first locating part 81 and the second locating part 82 generally triangular structure, described first
Locating part 81 and described second locating part 82 are provided with a through hole (sign) away from one end of described circulus 83, and one inserts
Fitting 85 passes through described through hole that described locating part is fixing with described fixture 90, so that when locating part is fastenedly connected axle 50
When, connecting shaft 50 is unable to opposed fixed member 90 and rotates.It is appreciated that the corresponding described plug connector 85 of described fixture 90 and described logical
Hole is provided with spliced eye (sign), and described plug connector 85 passes through described through hole and is fixed on described grafting in the hole, described grafting
Part 85 can be screw, and described spliced eye corresponds to screwed hole, and certainly, described plug connector 85 can not also have screw thread, only need
Insertion grafting in the hole realizes locating part and the fixation of fixture 90.
Described winged control test device can realize the winged control test of unmanned plane rotation attitude and rollover attitude.Described rotation appearance
The attitude test switching of state and described rollover attitude is carried out by regulating and controlling described locating part 80, when test rollover attitude, needs
Guarantee that unmanned plane will not rotate, that is, connecting shaft 50 no longer rotates relative to internal axle sleeve 40, outer shaft 30, now only need to gently screw convex
Nut at ear 84, described circulus 83 fastens described connecting shaft 50, then uses plug connector 85 to pass through through hole again, makes spacing
Part 80 is fixing with fixture 90, thus connecting shaft 50 will not rotate relative to flying control test device lower half.During test rotation attitude,
Plug connector 85 is extracted in through hole, more slightly unclamps the screw between described first locating part 81 and the second locating part 82, then
Described connector 70 rotation of turntable 10 can be driven according to unmanned plane and rotate it is ensured that the rotation attitude of unmanned plane smooth enter
OK.
It should be noted that described connecting shaft 50 is vertical with the plane that described rotation platform 11 is located；Described rotating shaft 14 with
The plane that described rotation platform 11 is located is parallel, and then can ensure that described winged control test device enables unmanned plane difference angle
Flight attitude.
Refer to Fig. 2, described turntable 10 also includes second bearing 16, described second bearing 16 be sheathed on described rotating shaft 14 with
Between fixed seat 13, the side mutually deviating from of two described fixed seats 13 is equipped with baffle plate 17.Described second bearing 16 is passed through
Screw is connected with described fixed seat 13, and can reduce the spin friction coefficient of described rotating shaft 14, and described fixed seat 13 is born described
The radial stress of second bearing 15, and fixation is played to described second bearing 15；Described baffle plate 16 can withstand described second
The axial stress that bearing 15 produces.
Preferably, described installed part 15 is two, and two described installed parts 15, between two described fixed seats 13, are used
To facilitate the installation of unmanned plane.
In one preferred embodiment of the present invention, described clutch shaft bearing 60 is four, 60 sets of clutch shaft bearing wherein described in
Located between described internal axle sleeve 40 and fixture 90, clutch shaft bearing 60 described in the other three is sheathed on described interior axle from top to bottom successively
Between set 40 and outer shaft 30.Wherein, described fixture 90 lower edge is abutted with described outer shaft 30, and then by described first axle
Hold 60 completely obscured it is ensured that described winged control test device profile aesthetic property.It should be noted that in four described bearings 60,
What two middle described bearings 60 bore is the axial stress of connecting shaft 50, and what another two bearing bore is the footpath of connecting shaft 50
To stress.
Referring in particular to Fig. 6, in a preferred embodiment of the present invention, described outer shaft 30 includes inner sleeve 31 and overcoat
32, described overcoat 32 one end inwall is provided with female thread, and described inner sleeve 31 one end periphery wall is provided with external screw thread corresponding with female thread,
And then make described inner sleeve 31 and overcoat 32 threaded, further facilitate the installing/dismounting of described outer shaft 30.
Preferably, described base 20 includes base plate 21 and column 22, and described column 22 two ends connect described base plate 21 respectively
With outer shaft 30.
It should be noted that between described clutch shaft bearing 25 and described outer shaft 30, described clutch shaft bearing 25 solid with described
Determine all to be screwed between part 90.
The foregoing is only the preferred embodiments of the present invention, not thereby limit the present invention the scope of the claims, every this
Under the design of invention, the equivalent structure transformation made using description of the invention and accompanying drawing content, or directly/indirectly it is used in it
He is included in the scope of patent protection of the present invention technical field of correlation.
Claims (10)
1. a kind of fly control test device it is characterised in that including base, outer shaft, internal axle sleeve and static in order to realize unmanned plane
The rotating mechanism of flight test；Described rotating mechanism includes interconnective turntable and connecting shaft, and described connecting shaft runs through described
Internal axle sleeve, described outer shaft is socketed on outside described internal axle sleeve, and described outer shaft connects described base；Described internal axle sleeve includes
Sleeve pipe and boss, described boss is located in the middle part of described sleeve pipe periphery wall, and described sleeve pipe periphery wall is also socketed with least two
One bearing, clutch shaft bearing described at least two is abutted with the two ends of described boss respectively.
2. as claimed in claim 1 fly control test device it is characterised in that described turntable include rotation platform, fixed plate, two
Individual fixed seat, rotating shaft and the installed part in order to fixing unmanned plane, two described fixed seats are respectively arranged on described rotation platform two ends,
Described rotating shaft two ends are connected respectively two described fixed seats, and described rotation platform is by described fixed plate and described connecting shaft
Connect, described installed part is located at described rotating shaft.
3. as claimed in claim 2 fly control test device it is characterised in that described winged control test device also include connector,
Locating part and fixture, described connecting shaft, connector and locating part are socketed from the inside to the outside successively, and described connector is solid with described
Fixed board is threaded, and the side deviating from connecting shaft of described locating part connects described fixture, and described fixture deviates from locating part
One end abut with described outer shaft.
4. fly control test device as claimed in claim 3 it is characterised in that described locating part includes the first locating part and second
Locating part, described first locating part and the second locating part are threaded, described first locating part away from the one of the second locating part
Threadeded with described fixture in end, one end away from the first locating part of described second locating part is with described fixture screw thread even
Connect.
5. fly control test device as claimed in claim 2 it is characterised in that what described connecting shaft and described rotation platform were located
Plane is vertical；The plane that described rotating shaft is located with described rotation platform is parallel.
6. fly control test device as claimed in claim 2 it is characterised in that described turntable also includes second bearing, described the
Located between described rotating shaft and fixed seat, the side that two described fixed seats mutually deviate from is equipped with baffle plate to two bearing holder (housing, cover)s.
7. fly control test device as claimed in claim 2 it is characterised in that described installed part is two, two described installations
Part is between two described fixed seats.
8. as in claim 1-7 arbitrary described winged control test device it is characterised in that described clutch shaft bearing be four, its
In a described clutch shaft bearing be sheathed between described internal axle sleeve and fixture, clutch shaft bearing described in the other three is sheathed on described interior
Between axle sleeve and outer shaft.
9. fly control test device as claimed in claim 8 it is characterised in that described base includes base plate and column, described vertical
Post two ends connect described base plate and outer shaft respectively.
10. as claimed in claim 8 fly control test device it is characterised in that between described clutch shaft bearing and described outer shaft,
All fixed by screw between described clutch shaft bearing and described fixture.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610807093.8A CN106347704B (en) | 2016-09-06 | 2016-09-06 | Fly control test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610807093.8A CN106347704B (en) | 2016-09-06 | 2016-09-06 | Fly control test device |
Publications (2)
| Publication Number | Publication Date |
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| CN106347704A true CN106347704A (en) | 2017-01-25 |
| CN106347704B CN106347704B (en) | 2019-04-26 |
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ID=57859340
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610807093.8A Active CN106347704B (en) | 2016-09-06 | 2016-09-06 | Fly control test device |
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| Country | Link |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107336845A (en) * | 2017-06-12 | 2017-11-10 | 工业和信息化部计算机与微电子发展研究中心（中国软件评测中心） | A kind of electronic Navigation of Pilotless Aircraft flight control system testing stand |
| CN107839897A (en) * | 2017-11-15 | 2018-03-27 | 深圳市科比特航空科技有限公司 | The disconnected oar test device of unmanned plane |
| CN109466795A (en) * | 2018-12-04 | 2019-03-15 | 湖南山河科技股份有限公司 | A kind of unmanned helicopter automatically testing platform |
| WO2019104625A1 (en) * | 2017-11-30 | 2019-06-06 | 深圳市大疆创新科技有限公司 | Connection structure, power system and unmanned aerial vehicle |
| CN112399066A (en) * | 2019-08-15 | 2021-02-23 | 中国科学院长春光学精密机械与物理研究所 | Aviation scout load slant distance focusing device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102180270A (en) * | 2011-03-10 | 2011-09-14 | 北京航空航天大学 | Microminiature rotorcraft experiment platform and application thereof |
| WO2012009198A2 (en) * | 2010-07-14 | 2012-01-19 | University Of Florida Research Foundation, Inc. | System and method for assessing the performance of an attitude control system for small satellites |
| CN102991725A (en) * | 2012-12-07 | 2013-03-27 | 中国飞机强度研究所 | Pole restraint device |
| CN204056315U (en) * | 2014-07-04 | 2014-12-31 | 沈阳航空航天大学 | Multi-rotor aerocraft four-degree-of-freedom experimental bench |
| CN204250381U (en) * | 2014-12-03 | 2015-04-08 | 中国人民解放军海军航空工程学院 | A kind of depopulated helicopter stability augmentation equipment pid parameter ground tune-up tester |
| CN206012989U (en) * | 2016-09-06 | 2017-03-15 | 深圳一电航空技术有限公司 | Fly control test device |
-
2016
- 2016-09-06 CN CN201610807093.8A patent/CN106347704B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012009198A2 (en) * | 2010-07-14 | 2012-01-19 | University Of Florida Research Foundation, Inc. | System and method for assessing the performance of an attitude control system for small satellites |
| CN102180270A (en) * | 2011-03-10 | 2011-09-14 | 北京航空航天大学 | Microminiature rotorcraft experiment platform and application thereof |
| CN102991725A (en) * | 2012-12-07 | 2013-03-27 | 中国飞机强度研究所 | Pole restraint device |
| CN204056315U (en) * | 2014-07-04 | 2014-12-31 | 沈阳航空航天大学 | Multi-rotor aerocraft four-degree-of-freedom experimental bench |
| CN204250381U (en) * | 2014-12-03 | 2015-04-08 | 中国人民解放军海军航空工程学院 | A kind of depopulated helicopter stability augmentation equipment pid parameter ground tune-up tester |
| CN206012989U (en) * | 2016-09-06 | 2017-03-15 | 深圳一电航空技术有限公司 | Fly control test device |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107336845A (en) * | 2017-06-12 | 2017-11-10 | 工业和信息化部计算机与微电子发展研究中心（中国软件评测中心） | A kind of electronic Navigation of Pilotless Aircraft flight control system testing stand |
| CN107839897A (en) * | 2017-11-15 | 2018-03-27 | 深圳市科比特航空科技有限公司 | The disconnected oar test device of unmanned plane |
| WO2019104625A1 (en) * | 2017-11-30 | 2019-06-06 | 深圳市大疆创新科技有限公司 | Connection structure, power system and unmanned aerial vehicle |
| CN109466795A (en) * | 2018-12-04 | 2019-03-15 | 湖南山河科技股份有限公司 | A kind of unmanned helicopter automatically testing platform |
| CN109466795B (en) * | 2018-12-04 | 2022-03-29 | 湖南山河科技股份有限公司 | Automatic test platform of unmanned helicopter |
| CN112399066A (en) * | 2019-08-15 | 2021-02-23 | 中国科学院长春光学精密机械与物理研究所 | Aviation scout load slant distance focusing device |
| CN112399066B (en) * | 2019-08-15 | 2023-11-14 | 中国科学院长春光学精密机械与物理研究所 | Aviation reconnaissance load inclined distance focusing device |
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|---|---|
| CN106347704B (en) | 2019-04-26 |
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Effective date of registration: 20191204 Address after: Room 812, enterprise service center, No. 17, section 3, west section of Changjiang North Road, Lingang Economic Development Zone, Yibin City, Sichuan Province Patentee after: Sichuan Yidian Aviation Technology Co., Ltd Address before: Baoan District Shiyan street Shenzhen city Guangdong province 518108 Songbai road Tangtou junctions electric science and Technology Park Co-patentee before: Shenzhen AEE Technology Co., Ltd. Patentee before: Shenzhen Yidian Aviation Technology Co., Ltd. |
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