CN217146389U - Rotor of gyroplane and gyroplane - Google Patents
Rotor of gyroplane and gyroplane Download PDFInfo
- Publication number
- CN217146389U CN217146389U CN202220471025.XU CN202220471025U CN217146389U CN 217146389 U CN217146389 U CN 217146389U CN 202220471025 U CN202220471025 U CN 202220471025U CN 217146389 U CN217146389 U CN 217146389U
- Authority
- CN
- China
- Prior art keywords
- rotor
- gyroplane
- rotorcraft
- brake
- fuselage
- 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
- Flexible Shafts (AREA)
Abstract
The utility model provides a rotor and gyroplane of gyroplane. The rotor comprises a rotor body, a brake device, a driving device and at least one connecting cable. The rotor body is connected with the body of the rotorcraft. The brake device is respectively connected with the rotor wing main body and the body of the rotorcraft. The driving device is arranged on the body of the gyroplane. The first end of the connecting cable is connected with the driving device, the second end of the connecting cable is connected with the brake device, and the connecting cable is used for pulling the rotor wing main body under the condition that the driving device works so as to change an included angle between the rotor wing main body and the body of the rotorcraft.
Description
Technical Field
The utility model relates to a gyroplane technical field, more specifically relates to a rotor and gyroplane of gyroplane.
Background
The gyroplane is called rotation gyroplane entirely, is a gyroplane that utilizes the air incoming flow to drive the rotation of rotor in order to produce lift, and the power when gyroplane flies comes from the screw of aircraft afterbody, and it directly links to each other with the power take off of gyroplane, and rotatory air that blows backward that gets up drives the aircraft and moves ahead, and the top rotor receives the air drive rotation of incoming flow and produces lift to realize the flight of aircraft.
In the course of implementing the inventive concept, the inventors found that there are at least the following problems in the related art: after the rotor of gyroplane breaks down, the risk of the gyroplane crash out of control is higher.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model provides a rotor and gyroplane of gyroplane.
An aspect of the utility model provides a rotor of gyroplane, include:
a rotor body connected to the body of the rotorcraft;
a brake device which is respectively connected with the rotor wing main body and the body of the gyroplane;
a drive device provided on the body of the rotorcraft; and
at least one connecting cable, a first end of said connecting cable being connected to said drive means and a second end of said connecting cable being connected to said brake means, said connecting cable being adapted to pull said rotor body in the event of operation of said drive means so as to change the angle between said rotor body and the fuselage of said rotorcraft.
According to the utility model discloses an embodiment, above-mentioned brake equipment includes:
the brake main body is rotatably connected with the rotor wing main body;
and the angle adjusting device is respectively connected with the brake main body and the body of the gyroplane in a rotating way, and is connected with the second end of the connecting cable.
According to the utility model discloses an embodiment, above-mentioned angle adjusting device includes:
a first end of the first connecting rod is rotatably connected with the body of the rotorcraft through a first pivot;
a second link, a first end of the second link being rotatably connected to a second end of the first link through a second pivot, a second end of the second link being rotatably connected to the brake body through a third pivot;
wherein the connecting cable is connected to a second end of the first connecting rod, the second pivot, or a first end of the second connecting rod.
According to the utility model discloses an embodiment, above-mentioned drive arrangement includes the lead screw slip table, and above-mentioned lead screw slip table includes:
a sliding table support;
the first motor is arranged on one side of the sliding table support;
the first end of the screw rod is in transmission connection with the first motor, and the second end of the screw rod is in rotary connection with the side wall of the other side, opposite to the first motor, of the sliding table support; and
and a nut rotatably engaged with the lead screw, the nut being connected to the first end of the connecting cable.
According to the utility model discloses an embodiment, above-mentioned screw is provided with at least one connecting hole, and every above-mentioned connecting hole is connected with the first end of one above-mentioned connecting cable.
Another aspect of the present invention provides a rotorcraft, including:
a body; and
the rotor of the above embodiment, wherein the rotor is connected to the fuselage.
According to the utility model discloses an embodiment, above-mentioned gyroplane still includes:
and the side wall of the connecting neck is rotatably connected with the brake device, and the rotor wing main body of the rotor wing is connected with the fuselage through the connecting neck.
According to the utility model discloses an embodiment, the rotor main part of above-mentioned rotor includes:
a rotor member;
and the support seat is respectively and rotatably connected with the connecting neck and the brake device, and the rotor wing part is supported on the support seat.
According to the utility model discloses an embodiment, above-mentioned rotor main part still includes:
the connecting piece is rotatably arranged on the supporting seat, and the rotor wing part is arranged on the connecting piece.
According to the utility model discloses an embodiment, above-mentioned gyroplane still includes:
the driving mechanism is in transmission connection with the connecting piece;
wherein, above-mentioned actuating mechanism includes:
the transmission gear is coaxially connected with the connecting piece;
and the power output device is arranged on the supporting seat and is in meshing transmission with the transmission gear.
According to the utility model discloses a rotor and gyroplane of gyroplane, under the condition that the gyroplane breaks down, can make rotor main part and gyroplane's fuselage change through drive arrangement pulling rotor main part to can avoid the gyroplane to take place the dive crash, consequently overcome at least partially behind the rotor of gyroplane breaks down, the higher technical problem of risk of gyroplane crash out of control, and then reached the risk that reduces the gyroplane crash out of control.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent from the following description of the embodiments of the present invention with reference to the accompanying drawings, in which:
figure 1 schematically shows a structural schematic view of a rotor of a rotorcraft according to an embodiment of the present invention;
figure 2 schematically shows a structural schematic view of a rotor of a rotorcraft according to another embodiment of the present invention;
fig. 3 schematically shows a perspective structure diagram of a screw sliding table according to an embodiment of the present invention;
fig. 4 schematically shows a schematic bottom view of a screw slide according to an embodiment of the invention; and
fig. 5 schematically shows a schematic structural view of a rotorcraft according to an embodiment of the present invention.
In the above figures, the reference numerals have the following meanings:
100-a rotor body;
200-a brake device;
210-a brake body;
220-angle adjustment means;
221-first connecting rod;
222-a second connecting rod;
300-a drive device;
310-a slipway support;
320-a first motor;
330-a lead screw;
340-a nut;
400-connecting cables;
500-fuselage;
600-connecting neck;
700-a support seat;
800-a connector;
900-a drive mechanism;
901-drive gear;
902-power take-off.
Detailed Description
Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings. It should be understood that the description is intended to be illustrative only and is not intended to limit the scope of the present invention. In the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the invention. It may be evident, however, that one or more embodiments may be practiced without these specific details. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The terms "comprises," "comprising," and the like, as used herein, specify the presence of stated features, steps, operations, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, or components.
All terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art unless otherwise defined. It is noted that the terms used herein should be interpreted as having a meaning that is consistent with the context of this specification and should not be interpreted in an idealized or overly formal sense.
Where a convention analogous to "at least one of A, B and C, etc." is used, in general such a construction is intended in the sense one having skill in the art would understand the convention (e.g., "a system having at least one of A, B and C" would include but not be limited to systems that have a alone, B alone, C alone, a and B together, a and C together, B and C together, and/or A, B, C together, etc.).
Gyroplanes may be classified into manned gyroplanes and unmanned gyroplanes. Wherein, unmanned rotation gyroplane is usually through controlling aircraft control surface pivoted an executive component control main rotor, nevertheless takes place emergency failure at unmanned rotation gyroplane and makes under the out of control condition of rotor, can make gyroplane dive downwards to cause the gyroplane to take place the crash.
In view of the above, according to the present general inventive concept, there is provided a rotor of a rotorcraft and a rotorcraft. The rotor comprises a rotor body, a brake device, a driving device and at least one connecting cable. The rotor body is connected with the body of the rotorcraft. The brake device is respectively connected with the rotor wing main body and the body of the rotorcraft. The driving device is arranged on the body of the gyroplane. The first end of the connecting cable is connected with the driving device, the second end of the connecting cable is connected with the brake device, and the connecting cable is used for pulling the rotor wing main body under the condition that the driving device works so as to change an included angle between the rotor wing main body and the body of the rotorcraft.
Fig. 1 schematically shows a structural schematic view of a rotor of a rotorcraft according to an embodiment of the present invention.
As shown in fig. 1, the rotor of the rotorcraft may include a rotor body 100, a brake device 200, a drive device 300, and at least one connecting cable 400. Rotor body 100 is coupled to the fuselage of the rotorcraft. Brake 200 is connected to rotor body 100 and the body of the rotorcraft, respectively. The drive device 300 is provided on the fuselage of the rotorcraft. A first end of the link cable 400 is connected to the driving device 300, a second end of the link cable 400 is connected to the braking device 200, and the link cable 400 is used to pull the rotor body 100 under the operation of the driving device 300 so as to change the angle between the rotor body 100 and the body of the rotorcraft.
According to the utility model discloses an embodiment, brake equipment 200 is applicable to when the gyroplane shuts down, brakes the rotor.
According to the utility model discloses an embodiment, drive arrangement 300 is applicable to under the condition that emergency trouble took place at the gyroplane, can drive connecting cable 400 and remove certain distance.
According to the utility model discloses an embodiment, under the condition that the emergency trouble took place for the gyroplane, drive arrangement 300 pulling connecting cable 400 to make connecting cable 400 pull the brake equipment 200 of being connected with rotor main part 100, with the angle that changes rotor main part 100 for the fuselage of gyroplane, thereby can change its posture of diving under the downward circumstances of diving of gyroplane emergency trouble, avoid the gyroplane to take place the dive crash.
According to the utility model discloses an embodiment, under the condition that the gyroplane breaks down, can make rotor main part 100 change with the fuselage of gyroplane through drive arrangement 300 pulling rotor main part 100 to can avoid the gyroplane to take place the dive crash, consequently overcome at least partially behind the rotor of gyroplane breaks down, the higher technical problem of risk of gyroplane crash out of control, and then reached the technological effect who reduces the risk of gyroplane crash out of control.
Fig. 2 schematically shows a structural schematic view of a rotor of a rotorcraft according to another embodiment of the present invention.
As shown in fig. 2, the brake apparatus 200 may include a brake main body 210 and an angle adjusting means 220. The brake body 210 is rotatably coupled to the rotor body 100. The angle adjusting device 220 is respectively connected with the brake main body 210 and the body of the rotorcraft in a rotating way, and the angle adjusting device 220 is connected with the second end of the connecting cable 400.
According to an embodiment of the present invention, the rotor body 100 performs a circular rotation motion with respect to the brake body 210 to generate an upward lift force.
According to the utility model discloses an embodiment, angle adjusting device 220 can refer to the device that can suitably change the fuselage contained angle of rotor main part 100 and gyroplane. During the flight of the rotorcraft, the flight state of the rotorcraft, such as forward flight, backward flight, etc., can be controlled by the angle adjustment device 220.
According to the utility model discloses an embodiment, under the condition that the gyroplane breaks down emergently, drive arrangement 300 makes rotor main part 100 be close to one side downward sloping of gyroplane afterbody through connecting cable 400 pulling angle adjusting device 220 to make the gyroplane obtain ascending lift under the condition of dive, avoided the possibility that the gyroplane took place the dive crash.
As shown in fig. 2, the angle adjusting means 220 may include a first connecting rod 221 and a second connecting rod 222. A first end of the first link rod 221 is pivotally connected to the body of the rotorcraft via a first pivot. A first end of the second link lever 222 is rotatably connected to a second end of the first link lever 221 via a second pivot, and a second end of the second link lever 222 is rotatably connected to the brake main body 210 via a third pivot. The connecting cable 400 is connected to the second end of the first connecting rod 221, the first end of the second pivot or second connecting rod 222.
According to the embodiment of the present invention, the linkage of the first connecting rod 221 and the second connecting rod 222 can control the brake main body 210 to brake the rotor main body 100.
According to the embodiment of the present invention, under the condition that the rotorcraft has an emergency failure, the connecting cable 400 pulls the second end of the first connecting rod 221, the first end of the second pivot or the second connecting rod 222, so that the first connecting rod 221 pulls the brake main body 210 downward, thereby changing the size of the included angle between the rotor main body 100 and the fuselage of the rotorcraft.
Fig. 3 schematically shows according to the utility model discloses a spatial structure sketch of lead screw slip table. Fig. 4 schematically shows a schematic bottom view of a screw slide table according to an embodiment of the present invention.
As shown in fig. 3 and 4, the driving device 300 may include a screw sliding table, and the screw sliding table may include: the sliding table comprises a sliding table support 310, a first motor 320, a lead screw 330 and a nut 340. The first motor 320 is disposed at one side of the slide mount 310. The first end of the lead screw 330 is in transmission connection with the first motor 320, and the second end of the lead screw 330 is in rotational connection with the side wall of the other side of the sliding table support 310 opposite to the first motor 320. The nut 340 is rotatably engaged with the lead screw 330, and the nut 340 is coupled with the first end of the connecting cable 400.
According to the utility model discloses an embodiment, lead screw slip table can also include the speed reducer of being connected with first motor 320 and lead screw 330 respectively.
According to the utility model discloses an embodiment, under the condition that the gyroplane breaks down emergently, first motor 320 drives lead screw 330 and takes place to rotate, under this condition, the screw 340 of being connected with lead screw 330 takes place to remove on lead screw slip table to make connecting cable 400 can stimulate brake equipment 200, so that change the size of contained angle between the fuselage of rotor main part 100 and gyroplane.
According to an embodiment of the present invention, the driving device 300 may further include a second motor and a winch. The second motor is arranged on the body of the gyroplane, the winch is connected with the output shaft of the second motor, and the connecting cable 400 is wound on the winch.
According to the utility model discloses an embodiment, under the condition that the gyroplane breaks down promptly, the second motor rotates so that connecting cable 400 twines on the capstan winch for connecting cable 400 can stimulate brake equipment 200, so that change the size of contained angle between the fuselage of rotor main part 100 and gyroplane.
As shown in fig. 3, the nut 340 is provided with at least one coupling hole, each of which is coupled to a first end of one of the coupling cables 400.
According to the utility model discloses an embodiment, can't carry out emergency control to the gyroplane when avoiding single connecting cable 400 condition such as fracture, can set up respectively with the screw 340 on a plurality of connecting cables 400 that a plurality of connecting holes are connected to can also continue to carry out emergency control to the rotor under certain connecting cable 400 cracked condition.
Fig. 5 schematically shows a schematic structural view of a rotorcraft according to an embodiment of the present invention.
As shown in fig. 5, a rotorcraft may include a fuselage 500 and a rotor as described above, the rotor being coupled to the fuselage 500.
According to the utility model discloses an embodiment can set up the recess on the fuselage 500 to set up the drive arrangement 300 of rotor in the recess, so that fuselage 500 surface keeps leveling, and then the windage when reducing the gyroplane flight.
According to the utility model discloses an embodiment, under the condition that the gyroplane breaks down, can make rotor main part 100 change with gyroplane's fuselage 500 through drive arrangement 300 pulling rotor main part 100 to can avoid the gyroplane to take place the dive crash, consequently overcome at least partially behind the rotor of gyroplane breaks down, the higher technical problem of risk of gyroplane crash out of control, and then reached the technological effect who reduces the risk of gyroplane crash out of control.
As shown in fig. 5, the rotorcraft may further include a connecting neck 600.
The side wall of the neck 600 is rotatably connected to the brake 200, and the rotor body 100 of the rotor is connected to the body 500 through the neck 600.
According to the utility model discloses an embodiment is connected fuselage 500 and rotor through connecting neck 600, is connected with brake equipment 200 simultaneously. Under the condition that drive arrangement 300 worked, connecting cable 400 pulling angle adjusting device 220 to make the contained angle between the second connecting rod 222 of first connecting rod 221 change, thereby make the one side downward sloping that is close to the tail of rotor body 100 who is connected with brake equipment 200, thereby avoid the emergence of the dive crash that the gyroplane out of control caused.
As shown in fig. 5, the rotor body 100 of the rotor may include a rotor component (not shown in fig. 5) and a bearing 700. The bearing 700 is rotatably coupled to the coupling neck 600 and the brake 200, respectively, and the rotor part is supported on the bearing 700.
As shown in fig. 5, the rotor body 100 may further include a connector 800. The link 800 is rotatably mounted on the support base 700 and the rotor part is mounted on the link 800.
According to the utility model discloses an embodiment, through connecting piece 800 with rotor part pivoted install on supporting seat 700, at the in-process that the gyroplane flies, rotor part carries out circular motion with connecting piece 800 for supporting seat 700. And under the condition that the gyroplane breaks down emergently, the gyroplane dives downwards, and drive arrangement 300 has changed the contained angle size between supporting seat 700 and the fuselage 500 through connecting cable 400 this moment to make the gyroplane obtain ascending lift, reduced the possibility that takes place the dive and crash.
As shown in fig. 5, the rotorcraft may further include a drive mechanism 900. The driving mechanism 900 is in transmission connection with the connecting member 800.
According to an embodiment of the present invention, the driving mechanism 900 may include a transmission gear 901 and a power take-off 902. The transmission gear 901 is coaxially connected to the connection member 800. The power output device 902 is installed on the supporting seat 700, and the power output device 902 is meshed with the transmission gear 901 for transmission.
According to the utility model discloses an embodiment, power take-off 902 can include the motor and set up the output gear on the motor output shaft, and output gear meshes with drive gear 901.
According to the utility model discloses an embodiment, under the condition of gyroplane flight, the motor drives the rotor part through meshed output gear and drive gear 901 and rotates to make the gyroplane obtain ascending lift.
It will be appreciated by a person skilled in the art that various combinations and/or combinations of the features recited in the various embodiments and/or claims of the invention are possible, even if such combinations or combinations are not explicitly recited in the invention. In particular, various combinations and/or combinations of the features recited in the various embodiments and/or claims of the present invention may be made without departing from the spirit and teachings of the invention. All such combinations and/or associations fall within the scope of the present invention.
The embodiments of the present invention have been described above. However, these examples are for illustrative purposes only and are not intended to limit the scope of the present invention. Although the embodiments are described separately above, this does not mean that the measures in the embodiments cannot be used in advantageous combination. The scope of the invention is defined by the appended claims and equivalents thereof. Various alternatives and modifications can be devised by those skilled in the art without departing from the scope of the present invention, and these alternatives and modifications are intended to fall within the scope of the present invention.
Claims (10)
1. A rotor for a rotorcraft, comprising:
a rotor body connected to a fuselage of the rotorcraft;
the brake device is respectively connected with the rotor wing main body and the body of the gyroplane;
a drive device provided on a fuselage of the rotorcraft; and
at least one connecting cable, the first end of connecting cable with drive arrangement connects, the second end of connecting cable with brake equipment connects, the connecting cable is used for being in the pulling under the condition of drive arrangement work the rotor main part, in order to change the rotor main part with the contained angle between the fuselage of gyroplane.
2. A rotor as claimed in claim 1, wherein said braking means comprises:
the brake main body is rotatably connected with the rotor wing main body;
the angle adjusting device, the angle adjusting device respectively with the brake main part the fuselage of gyroplane rotates and is connected, the angle adjusting device with the second end connection of connecting cable.
3. A rotor as claimed in claim 2, wherein said angular adjustment means comprises:
the first end of the first connecting rod is rotatably connected with the body of the rotorcraft through a first pivot;
a first end of the second connecting rod is rotatably connected with a second end of the first connecting rod through a second pivot, and a second end of the second connecting rod is rotatably connected with the brake main body through a third pivot;
wherein the connecting cable is connected to the second end of the first connecting rod, the second pivot, or the first end of the second connecting rod.
4. A rotor as claimed in claim 1, wherein the drive arrangement includes a lead screw ramp, the lead screw ramp including:
a sliding table support;
the first motor is arranged on one side of the sliding table support;
a first end of the screw is in transmission connection with the first motor, and a second end of the screw is in rotation connection with a side wall of the other side of the sliding table support, which is opposite to the first motor; and
the screw nut is rotatably matched with the screw rod and connected with the first end of the connecting cable.
5. A rotor as claimed in claim 4, wherein the nut is provided with at least one attachment aperture, each attachment aperture being attached to a first end of one of the attachment cables.
6. A rotorcraft, comprising:
a body; and
a rotor as claimed in any one of claims 1 to 5, wherein the rotor is connected to the fuselage.
7. The rotorcraft according to claim 6, further comprising:
the connecting neck, the lateral wall of connecting neck with brake equipment rotates and is connected, the rotor main part of rotor passes through the connecting neck with the fuselage is connected.
8. A rotorcraft according to claim 7, wherein the rotor body of the rotor includes:
a rotor member;
the supporting seat is respectively connected with the connecting neck and the brake device in a rotating mode, and the rotor wing part is supported on the supporting seat.
9. The rotorcraft according to claim 8, wherein the rotor body further comprises:
a connector rotatably mounted on the support base, the rotor component being mounted on the connector.
10. The rotorcraft according to claim 9, further comprising:
the driving mechanism is in transmission connection with the connecting piece;
wherein the drive mechanism comprises:
the transmission gear is coaxially connected with the connecting piece;
and the power output device is arranged on the supporting seat and is in meshing transmission with the transmission gear.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220471025.XU CN217146389U (en) | 2022-03-04 | 2022-03-04 | Rotor of gyroplane and gyroplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220471025.XU CN217146389U (en) | 2022-03-04 | 2022-03-04 | Rotor of gyroplane and gyroplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217146389U true CN217146389U (en) | 2022-08-09 |
Family
ID=82693041
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220471025.XU Active CN217146389U (en) | 2022-03-04 | 2022-03-04 | Rotor of gyroplane and gyroplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217146389U (en) |
-
2022
- 2022-03-04 CN CN202220471025.XU patent/CN217146389U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3564122B1 (en) | Hybrid tiltrotor drive system | |
| US10112705B2 (en) | Off-board gyrocopter take-off systems and associated methods | |
| US20190084669A1 (en) | Tiltrotor with inboard engines | |
| JP7053772B2 (en) | Precision operator for aircraft autothrottle or autopilot | |
| JP4712092B2 (en) | Aircraft automatic speed control device | |
| KR101895366B1 (en) | the improved hybrid drone | |
| EP2902314B1 (en) | High lift system for an aircraft and aircraft having such a high lift system | |
| EP2698312B1 (en) | Energy extraction using a kite | |
| CN212386689U (en) | Three-rotor tilt rotor aircraft capable of tilting | |
| JP2021506655A (en) | Aircraft wing and rotor vectorization system | |
| IL35864A (en) | Multiple helicopter lift system and a method for increasing its load transporting capacity | |
| US11661194B2 (en) | Power transmission system | |
| EP2851289B1 (en) | Leading and trailing edge device deflections during descent of an aircraft | |
| CN217146389U (en) | Rotor of gyroplane and gyroplane | |
| US3439888A (en) | Aircraft propulsion mounting arrangement | |
| WO2019157588A1 (en) | Transmission system for aircraft structure | |
| US10745118B2 (en) | Variable ratio gearbox for a rotary wing aircraft tail rotor | |
| US11372427B2 (en) | System and method for enhanced altitude control of an autogyro | |
| JP4629504B2 (en) | Apparatus and method for autorotation control of small unmanned helicopter aircraft | |
| US20210276710A1 (en) | Aircraft and method for operating an aircraft | |
| CN111645081A (en) | Lightweight mechanical arm system loaded on unmanned aerial vehicle and control method thereof | |
| KR102445237B1 (en) | Vertical takeoff and landing aircraft | |
| KR102600288B1 (en) | Unmanned vehicle having propellant apparatus for aerial and underwater operation | |
| CN220221114U (en) | Unmanned aerial vehicle screw torque converter | |
| CN210653634U (en) | Fixed wing aircraft capable of vertically taking off and landing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |