CN211032992U - Helicopter tail rotor direct-drive and variable pitch mechanism - Google Patents
Helicopter tail rotor direct-drive and variable pitch mechanism Download PDFInfo
- Publication number
- CN211032992U CN211032992U CN201921572196.6U CN201921572196U CN211032992U CN 211032992 U CN211032992 U CN 211032992U CN 201921572196 U CN201921572196 U CN 201921572196U CN 211032992 U CN211032992 U CN 211032992U
- Authority
- CN
- China
- Prior art keywords
- helicopter
- connecting rod
- tail
- tail rotor
- displacement
- 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.)
- Active
Links
Images
Landscapes
- Toys (AREA)
Abstract
The utility model aims at providing a simple structure, dismouting and maintenance convenience, higher and the higher helicopter tail-rotor of displacement precision of security directly drive and displacement mechanism. The utility model discloses a helicopter afterbody and tail-rotor still include and directly drive structure and displacement structure, directly drive the structure and include driving motor, driving motor sets up the helicopter afterbody just driving motor's output shaft with the tail-rotor drive fit, the displacement structure is including all setting up displacement steering wheel and connecting rod structure on the helicopter afterbody, connecting rod structure with the displacement steering wheel cooperatees, connecting rod structure with the tail-rotor cooperatees. The utility model discloses be applied to unmanned helicopter's technical field.
Description
Technical Field
The utility model discloses be applied to unmanned helicopter's technical field, in particular to helicopter tail-rotor directly drives and displacement mechanism.
Background
The tail rotor of the helicopter is used for keeping the flight and adjusting the course of the helicopter, and when rotating, the tail rotor can be used as a vertical stabilizing surface to stabilize the flight of the helicopter. Generally, the tail rotor is mainly in a seesaw type, a universal joint type, a hinge type, a bearingless type and the like.
In the helicopter industry, the power of the tail rotor is generally from the main engine of the helicopter, the driving force of the tail rotor is closely related to the driving force of the main propeller, and the tail rotor and the main propeller share one driving source because the driving force is generally transmitted through a belt transmission mode. Meanwhile, the existing structure for changing the pitch of the tail rotor usually adopts belt transmission to adjust the pitch of the tail rotor so as to realize pitch change, and further, the direction of the airplane can be adjusted in the flying process.
At present, helicopters on the market generally adopt the mode of transmitting the power of main screw propeller driving source to the tail rotor by belt transmission mode in order to drive the tail rotor, and the phenomenon of skidding appears in this kind of transmission mode easily in the transmission process, and the security is lower to constitute an organic whole with the transmission of tail rotor and main screw propeller, the tail rotor displacement precision is lower, and the structure is complicated, and difficult dismouting is comparatively troublesome when maintaining or updating.
Therefore, a pitch-variable structure with simple structure, convenient assembly and disassembly and high pitch-variable precision and a driving structure capable of directly driving the tail rotor to act are needed.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that overcome prior art not enough, provide a simple structure, dismouting and maintenance convenience, the higher helicopter tail-rotor that reaches the displacement precision is higher directly drives and displacement mechanism.
The utility model adopts the technical proposal that: the utility model discloses it includes helicopter afterbody and tail-rotor, still includes and directly drives structure and displacement structure, it includes driving motor to directly drive the structure, driving motor sets up the helicopter afterbody just driving motor's output shaft with the tail-rotor drive cooperation, the displacement structure is including all setting up displacement steering wheel and connecting rod structure on the helicopter afterbody, connecting rod structure with the displacement steering wheel cooperatees, connecting rod structure with the tail-rotor cooperatees.
Further, the direct-drive structure further comprises a mounting seat arranged at the tail end of the tail of the helicopter, a heat dissipation supporting plate is arranged on one side of the mounting seat, a mounting supporting plate is arranged on the other side of the mounting seat, a through hole is formed in the mounting supporting plate, a driving motor is fixedly arranged on the heat dissipation supporting plate, a rotating shaft sleeve is fixedly arranged on an output shaft of the driving motor, one end of the rotating shaft sleeve penetrates through the through hole, a positioning hole is further formed in the rotating shaft sleeve, a transmission shaft is arranged on a tail rotor, one end of the transmission shaft is in transmission fit with the tail rotor, a positioning pin matched with the positioning hole is arranged at the other end of the transmission shaft, and the transmission shaft is matched.
Furthermore, a rolling bearing is sleeved on the rotating shaft sleeve, a limiting flange is arranged at one end, close to the driving motor, of the rolling bearing, the rolling bearing is matched with the through hole, and the limiting flange is matched with the installation supporting plate.
Further, the connecting rod structure includes long connecting rod, adaptor, installed part and connecting piece, long connecting rod is in the top of helicopter afterbody, the one end of long connecting rod with the displacement steering wheel is articulated mutually, be provided with on the other end of long connecting rod the adaptor, the installed part is fixed to be set up in the erection bracing board, the upper portion of the one end of connecting piece with the adaptor is fixed continuous just the lower part of the one end of connecting piece with the installed part is articulated mutually, the other end of connecting piece is provided with the arc wall, the upper and lower end of arc wall all sets up the locating part.
Further, be provided with slip axle sleeve and articulated frame on the transmission shaft, slip axle sleeve cover is established on the transmission shaft, articulated frame overlaps and establishes on the slip axle sleeve, the one end of slip axle sleeve is provided with left spacing boss, and the other end is provided with right spacing boss, articulated frame with right spacing boss cooperatees, articulated frame is in with the setting articulated subassembly on the tail-rotor is connected.
Further, the displacement structure is still including the displacement round wheel, the displacement round wheel cover is established the sliding shaft is sheathe in, the displacement round wheel sets up left side spacing boss with between the articulated frame, be provided with the annular on the displacement round wheel, the annular with the locating part cooperatees.
Furthermore, the pitch-variable structure further comprises two fixing rings arranged on the tail part of the helicopter, each fixing ring is arranged between the mounting seat and the pitch-variable steering engine, and the fixing rings are matched with the connecting rod structures.
Furthermore, a round hole is further formed in the mounting seat, and one end, provided with the adapter, of the long connecting rod penetrates through the round hole.
Further, the heat dissipation support plate and the installation support plate are provided with a protective cover therebetween, and the protective cover is provided with a recess.
Further, still be provided with the peephole on the safety shield, be provided with the protection closure on the peephole.
The utility model has the advantages that: because the utility model discloses an including helicopter afterbody and tail-rotor, still including directly driving structure and displacement structure, directly drive the structure and include driving motor, driving motor sets up the helicopter afterbody just driving motor's output shaft with the tail-rotor transmission cooperation, the displacement structure is including all setting up displacement steering wheel and connecting rod structure on the helicopter afterbody, connecting rod structure with the displacement steering wheel cooperatees, connecting rod structure with the tail-rotor cooperatees. Compared with the closest prior art, the utility model has the following advantages: the integral structure is simple and compact, the direct-drive tail rotor can independently adjust the rotating speed, and the environmental adaptability is good; the belt is driven relatively to the belt, so that the belt is convenient to disassemble; the driving structure is separated from the variable pitch structure, so that high-value components can be prevented from being bound; the steering engine directly drives the connecting rod structure to change the pitch, and the pitch changing precision is high.
Drawings
Fig. 1 is a schematic perspective view of the present invention;
fig. 2 is an exploded view of the direct drive structure of the present invention;
FIG. 3 is a schematic perspective view of the pitch-variable structure of the present invention;
FIG. 4 is a schematic perspective view of the protection cover of the present invention;
fig. 5 is a partial perspective view of the direct drive structure of the present invention;
FIG. 6 is an enlarged view of a portion of FIG. 1;
fig. 7 is an exploded view of a part of the structure of the present invention.
Detailed Description
As shown in fig. 1 to 7, the present invention specifically comprises: the utility model discloses it includes helicopter afterbody 1 and tail-rotor 2, still including directly driving structure and displacement structure, directly drive the structure and include driving motor 3, driving motor 3 sets up helicopter afterbody 1 just driving motor 3's output shaft with 2 transmission coordination of tail-rotor, the displacement structure is including all setting up displacement steering wheel 4 and connecting rod structure 5 on the helicopter afterbody 1, connecting rod structure 5 with displacement steering wheel 4 cooperatees, connecting rod structure 5 with 2 cooperatees of tail-rotor. The driving motor 3 is arranged on the tail part 2 of the helicopter and is directly matched with the tail rotor 2, so that the tail rotor is directly driven to rotate the tail rotor 2; variable pitch steering wheel 4 cooperatees with connecting rod structure 5, and connecting rod structure 5 cooperatees with tail-rotor 2 again, and this just makes variable pitch steering wheel 4, connecting rod structure 5 and tail-rotor 2 constitute a variable pitch structure wholly, and 4 actions of variable pitch steering wheel cooperate with tail-rotor 2 again through a series of actions of connecting rod structure 5 to accomplish the variable pitch action of tail-rotor 2.
In this embodiment, the direct-drive structure further comprises a mounting seat 6 arranged at the tail end of the tail portion 1 of the helicopter, a heat dissipation supporting plate 7 is arranged on one side of the mounting seat 6, a mounting supporting plate 8 is arranged on the other side of the mounting seat, a through hole 9 is formed in the mounting supporting plate 8, the driving motor 3 is fixedly arranged on the heat dissipation supporting plate 7, a rotating shaft sleeve 10 is fixedly arranged on an output shaft of the driving motor 3, one end of the rotating shaft sleeve 10 penetrates through the through hole 9, a positioning hole 11 is further formed in the rotating shaft sleeve 10, a transmission shaft 12 is arranged on the tail rotor 2, one end of the transmission shaft 12 is in transmission fit with the tail rotor 2, a positioning pin 13 matched with the positioning hole 11 is arranged at the other end of the transmission shaft 12, and the transmission shaft 12 is matched. The tail end of the tail part 1 of the helicopter is provided with a mounting seat 6, a heat dissipation support plate 7 and a mounting support plate 8 are arranged on the mounting seat, and the heat dissipation support plate 7 is used as a mounting plate of the driving motor 3 and is also a heat dissipation plate, so that the driving motor 3 can dissipate heat more quickly; the fixed rotatory axle sleeve 10 that sets up on driving motor 3's output shaft cooperates with transmission shaft 12, and locating pin 13 and locating hole 11 mutually support and make transmission shaft 12 and rotatory axle sleeve 10 can steadily, continuously operate.
In this embodiment, the rotating shaft sleeve 10 is sleeved with a rolling bearing 14, one end of the rolling bearing 14 close to the driving motor 3 is provided with a limiting flange 15, the rolling bearing 14 is matched with the through hole 9, and the limiting flange 15 is matched with the mounting support plate 8. The rolling bearing 14 is sleeved on the rotating shaft sleeve 10 and matched with the through hole 9 in the mounting support plate 8, therefore, the rolling bearing 14 is used as a supporting piece and a connecting piece, and as the limiting flange 15 is further arranged on the rolling bearing 14, and the diameter of the limiting flange 15 is larger than that of the through hole 9, the mounting support plate 8 can limit the position of the rolling bearing 14, so that the rolling bearing 14 can be located at a corresponding working position.
In this embodiment, the connecting rod structure 5 includes a long connecting rod 51, an adapter 52, a mounting part 53 and a connecting part 54, the long connecting rod 51 is located above the tail part 1 of the helicopter, one end of the long connecting rod 51 is hinged to the pitch-variable steering engine 4, the adapter 52 is arranged at the other end of the long connecting rod 51, the mounting part 53 is fixedly arranged on the mounting support plate 8, the upper part of one end of the connecting part 54 is fixedly connected to the adapter 52, the lower part of one end of the connecting part 54 is hinged to the mounting part 53, an arc-shaped groove 55 is arranged at the other end of the connecting part 54, and limiting parts 56 are arranged at the upper and lower ends of the arc-shaped groove 55. The connecting rod structure 5 mainly comprises a long connecting rod 51, an adapter 52, a mounting piece 53 and a connecting piece 54, the connecting rod structure 5 can be reasonably arranged on the tail part 2 of the helicopter through the hinging of the long connecting rod 51 and the variable-pitch steering engine 4, the hinging of the connecting piece 54 and the mounting piece 53 and the like, the other end of the connecting piece 54 is provided with an arc-shaped groove 55, the upper end and the lower end of the arc-shaped groove 55 are provided with limiting pieces 56, and the limiting pieces 56 are used for pulling the components on the transmission shaft 12 during variable pitch.
In this embodiment, be provided with slip axle sleeve 16 and articulated frame 17 on the transmission shaft 12, slip axle sleeve 16 cover is established on the transmission shaft 12, articulated frame 17 cover is established on slip axle sleeve 16, the one end of slip axle sleeve 16 is provided with left spacing boss 18, and the other end is provided with right spacing boss 19, articulated frame 17 with right spacing boss 19 cooperatees, articulated frame 17 with set up articulated subassembly 20 on the tail-rotor 2 is connected. The sliding shaft sleeve 16 can slide on the transmission shaft 12 and can rotate along with the transmission shaft 12, a left limiting boss 18 and a right limiting boss 19 are respectively arranged at two ends of the sliding shaft sleeve 16, the position of a hinge frame 17 sleeved on the sliding shaft sleeve 16 can be limited, and the angle, namely the variable pitch, of the wing on the tail rotor 2 can be adjusted by the hinge frame 18 through matching with a hinge assembly 20.
In this embodiment, the pitch structure further includes a pitch-variable circular wheel 21, the pitch-variable circular wheel 21 is sleeved on the sliding shaft sleeve 16, the pitch-variable circular wheel 21 is arranged between the left limiting boss 18 and the hinge frame 17, a ring groove 22 is arranged on the pitch-variable circular wheel 21, and the ring groove 22 is matched with the limiting part 56. The variable pitch round wheel 21 is sleeved on the sliding shaft sleeve 16 like the hinge frame 17, the left limiting boss 18 and the right limiting boss 19 are matched to stably limit the variable pitch round wheel 21 and the hinge frame 17 on the sliding shaft sleeve 16, the variable pitch round wheel 21 is provided with the annular groove 22, the annular groove 22 is arranged to enable the limiting part 56 to have a matching position, and the limiting part 26 cannot be blocked when the variable pitch round wheel 21 rotates, so that the rotation of the tail rotor 2 is influenced.
In this embodiment, the pitch-variable structure further includes two fixing rings 23 disposed on the tail portion 1 of the helicopter, each fixing ring 23 is disposed between the mounting seat 6 and the pitch-variable steering engine 4, and the fixing rings 23 are matched with the connecting rod structure 5. The fixing ring 23 is used for stably fixing the long connecting rod 51 on the tail 1 of the helicopter, so that the long connecting rod 51 can stably operate.
In this embodiment, a circular hole 24 is further formed in the mounting seat 6, and one end of the long connecting rod 51, which is provided with the adaptor 52, penetrates through the circular hole 24. The round hole 24 is arranged on the mounting seat 6, so that the long connecting rod 51 cannot be obstructed during mounting, the mounting is more convenient, and the structure is more reasonable.
In this embodiment, a protective cover 25 is disposed between the heat dissipation support plate 7 and the mounting support plate 8, and a recess 26 is disposed on the protective cover 25. The protective cover 25 is arranged, so that the driving motor 3 can be protected and prevented from being directly exposed outside, and the waterproof function can be realized in the rainy day, so that the whole application occasion is more variable; the recess 26 is provided so that the adaptor 52 above the recess 26 is not interfered during operation, thereby ensuring that the pitch-changing action is smoothly performed.
In this embodiment, the protective cover 25 is further provided with a peephole 27, and a protective plug 28 is arranged on the peephole. The peephole 27 is arranged to observe the condition of the driving motor 3 through the peephole 27, and the protective plug 28 is used for sealing the peephole 27 when the peephole 27 is not needed.
The utility model discloses a working process is: in the sailing process, the driving motor 3 drives the transmission shaft 12 to rotate, and the tail rotor 2 rotates; when the variable pitch is needed, the variable pitch steering engine 4 acts to pull the long connecting rod 51, then the adaptor 52 drives the connecting piece 54 to act, the limiting piece 56 pulls the variable pitch round wheel 21 to make the sliding shaft sleeve 16 act, and the hinge bracket 17 acts to pull the hinge assembly 20, so that the wing on the tail rotor 2 changes the inclination angle, and the variable pitch is completed.
While the embodiments of the present invention have been described in terms of practical embodiments, they are not intended to limit the scope of the invention, and modifications of the embodiments and combinations with other embodiments will be apparent to those skilled in the art in light of the present description.
Claims (10)
1. Helicopter tail rotor directly drives and displacement mechanism, including helicopter afterbody (1) and tail-rotor (2), its characterized in that: it is including directly driving structure and displacement structure, directly drive the structure and include driving motor (3), driving motor (3) set up helicopter afterbody (1) just the output shaft of driving motor (3) with tail rotor (2) transmission fit, the displacement structure is including all setting up displacement steering wheel (4) and connecting rod structure (5) on helicopter afterbody (1), connecting rod structure (5) with displacement steering wheel (4) cooperate, connecting rod structure (5) with tail rotor (2) cooperate.
2. The helicopter tail rotor direct drive and pitch change mechanism of claim 1, characterized in that: the helicopter tail end fixing device is characterized by further comprising a mounting seat (6) arranged at the tail end of the helicopter tail portion (1), a heat dissipation supporting plate (7) is arranged on one side of the mounting seat (6), an installation supporting plate (8) is arranged on the other side of the mounting seat (6), a through hole (9) is formed in the installation supporting plate (8), the driving motor (3) is fixedly arranged on the heat dissipation supporting plate (7), a rotating shaft sleeve (10) is fixedly arranged on an output shaft of the driving motor (3), one end of the rotating shaft sleeve (10) penetrates through the through hole (9), a positioning hole (11) is further formed in the rotating shaft sleeve (10), a transmission shaft (12) is arranged on the tail rotor (2), one end of the transmission shaft (12) is in transmission fit with the tail rotor (2), a positioning pin (13) matched with the positioning hole (11) is arranged at the other end, the transmission shaft (12) is matched with the rotary shaft sleeve (10).
3. The helicopter tail rotor direct drive and pitch change mechanism of claim 2, characterized in that: rotatory axle sleeve (10) are gone up the cover and are equipped with antifriction bearing (14), antifriction bearing (14) are close to the one end of driving motor (3) is provided with limit flange (15), antifriction bearing (14) with through-hole (9) looks adaptation, limit flange (15) with erection bracing board (8) cooperate.
4. The helicopter tail rotor direct drive and pitch change mechanism of claim 2, characterized in that: the connecting rod structure (5) comprises a long connecting rod (51), an adapter piece (52), a mounting piece (53) and a connecting piece (54), the long connecting rod (51) is located above the tail portion (1) of the helicopter, one end of the long connecting rod (51) is hinged to the variable-pitch steering engine (4), the adapter piece (52) is arranged at the other end of the long connecting rod (51), the mounting piece (53) is fixedly arranged on the mounting support plate (8), the upper portion of one end of the connecting piece (54) is fixedly connected with the adapter piece (52), the lower portion of one end of the connecting piece (54) is hinged to the mounting piece (53), an arc-shaped groove (55) is formed in the other end of the connecting piece (54), and limiting pieces (56) are arranged at the upper end and the lower end of the arc-shaped groove (55).
5. The helicopter tail rotor direct drive and pitch change mechanism of claim 4, characterized in that: be provided with slip axle sleeve (16) and articulated frame (17) on transmission shaft (12), slip axle sleeve (16) cover is established on transmission shaft (12), articulated frame (17) cover is established on slip axle sleeve (16), the one end of slip axle sleeve (16) is provided with left spacing boss (18), and the other end is provided with right spacing boss (19), articulated frame (17) with right spacing boss (19) cooperate, articulated frame (17) is in with the setting articulated subassembly (20) on tail-rotor (2) are connected.
6. The helicopter tail rotor direct drive and pitch change mechanism of claim 5, characterized in that: it is still including displacement circle wheel (21), displacement circle wheel (21) cover is established on slip axle sleeve (16), displacement circle wheel (21) set up left side spacing boss (18) with between articulated frame (17), be provided with annular (22) on displacement circle wheel (21), annular (22) with locating part (56) cooperate.
7. The helicopter tail rotor direct drive and pitch change mechanism of claim 2, characterized in that: the helicopter is characterized by further comprising two fixing rings (23) arranged on the tail portion (1) of the helicopter, wherein each fixing ring (23) is arranged between the mounting seat (6) and the variable-pitch steering engine (4), and the fixing rings (23) are matched with the connecting rod structures (5).
8. The helicopter tail rotor direct drive and pitch change mechanism of claim 4, characterized in that: the mounting seat (6) is further provided with a round hole (24), and one end, provided with an adapter (52), of the long connecting rod (51) penetrates through the round hole (24).
9. The helicopter tail rotor direct drive and pitch change mechanism of claim 2, characterized in that: the heat dissipation support plate (7) with be provided with protection casing (25) between installation backup pad (8), be provided with on protection casing (25) sunken (26).
10. The helicopter tail rotor direct drive and pitch change mechanism of claim 9, characterized in that: the protective cover (25) is further provided with a peephole (27), and a protective blocking piece (28) is arranged on the peephole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921572196.6U CN211032992U (en) | 2019-09-20 | 2019-09-20 | Helicopter tail rotor direct-drive and variable pitch mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921572196.6U CN211032992U (en) | 2019-09-20 | 2019-09-20 | Helicopter tail rotor direct-drive and variable pitch mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211032992U true CN211032992U (en) | 2020-07-17 |
Family
ID=71542455
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921572196.6U Active CN211032992U (en) | 2019-09-20 | 2019-09-20 | Helicopter tail rotor direct-drive and variable pitch mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211032992U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117782508A (en) * | 2024-02-23 | 2024-03-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Helicopter tail rotor mechanism for wind tunnel test and tail rotor variable pitch control method |
-
2019
- 2019-09-20 CN CN201921572196.6U patent/CN211032992U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117782508A (en) * | 2024-02-23 | 2024-03-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Helicopter tail rotor mechanism for wind tunnel test and tail rotor variable pitch control method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2589683C (en) | Compact tiltrotor pylon-conversion actuation system | |
| EP2631173B1 (en) | Coaxial counter-rotating rotor system | |
| US10676182B2 (en) | Tilting coaxial rotor for a rotary wing aircraft | |
| US6062508A (en) | Compound aircraft | |
| US10752343B2 (en) | Electric propulsion system for a rotary wing aircraft | |
| CN211032992U (en) | Helicopter tail rotor direct-drive and variable pitch mechanism | |
| CN113460298A (en) | Motor tilting mechanism and tilting rotor aerocar | |
| CN106741904B (en) | Composite unmanned aerial vehicle | |
| WO2005019029A3 (en) | Reduced visibility rotorcraft and method of controlling flight of reduced visibility rotorcraft | |
| CN205524941U (en) | Magnetic suspension variable -pitch propeller oar and aircraft | |
| US3176774A (en) | Helicopter drive control | |
| CN106741903B (en) | Hybrid unmanned aerial vehicle | |
| CN219192543U (en) | Ducted unmanned aerial vehicle screw pitch-changing mechanism | |
| EP3286080B1 (en) | Connector assembly for rotor head swashplate | |
| CN107031835B (en) | Rotor unmanned aerial vehicle becomes oar radius variable pitch device | |
| CN211076330U (en) | Tilt-rotor mechanism and tilt-rotor unmanned aerial vehicle | |
| CN210191817U (en) | Gyroplane without runway | |
| CN114649679A (en) | Transmitting antenna for interfering navigation signals of unmanned aerial vehicle | |
| CN111776210A (en) | Unmanned aerial vehicle is with protection casing that has scalable regulation | |
| US2420764A (en) | Directional propeller control | |
| CN210027883U (en) | Propeller hub with adjustable propeller pitch | |
| CN211001888U (en) | Four rotor unmanned aerial vehicle camera linkage | |
| CN220884817U (en) | Unmanned aerial vehicle | |
| CN219821753U (en) | Coaxial three-rotor aircraft lifting system | |
| CN216232961U (en) | Rotor wing device with strong anti-interference performance and aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |