CN211766236U - Modularized unmanned helicopter facing configuration and task system - Google Patents
Modularized unmanned helicopter facing configuration and task system Download PDFInfo
- Publication number
- CN211766236U CN211766236U CN201922308085.0U CN201922308085U CN211766236U CN 211766236 U CN211766236 U CN 211766236U CN 201922308085 U CN201922308085 U CN 201922308085U CN 211766236 U CN211766236 U CN 211766236U
- Authority
- CN
- China
- Prior art keywords
- assembly
- fuselage
- helicopter
- tail
- section
- 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
- 239000002828 fuel tank Substances 0.000 claims description 11
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 230000000712 assembly Effects 0.000 abstract 1
- 238000000429 assembly Methods 0.000 abstract 1
- 239000003921 oil Substances 0.000 description 15
- 238000000034 method Methods 0.000 description 5
- 230000008859 change Effects 0.000 description 4
- 238000013461 design Methods 0.000 description 4
- 230000017525 heat dissipation Effects 0.000 description 4
- 230000005484 gravity Effects 0.000 description 3
- 239000000446 fuel Substances 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Landscapes
- Toys (AREA)
Abstract
The utility model discloses an unmanned helicopter of modularization towards configuration and task system, include: a fuselage midsection assembly; the device comprises a front-section fuselage assembly, a middle-section fuselage assembly and a plurality of front-section fuselage assemblies, wherein the front-section fuselage assembly comprises a plurality of front sections of the fuselage; the fuselage middle section assembly is selectively detachably connected with one of the fuselage rear sections; and the mounting assembly comprises a plurality of task loads and a propulsion propeller, and the middle fuselage section assembly is selectively detachably connected with one of the plurality of task loads and the propulsion propeller. The utility model discloses an unmanned helicopter realizes the modularization assembly at manufacturing and technology assembly stage, can realize the unmanned helicopter configuration of quick replacement when satisfying the customer demand, uses and the mission planning stage in the later stage, can realize load system's quick replacement, avoids dismantling the complete machine structure.
Description
Technical Field
The utility model belongs to the technical field of unmanned helicopter technique and specifically relates to a towards configuration and task system's unmanned helicopter of modularization.
Background
In recent years, with the continuous development of the world aviation level, the design level of helicopters is also promoted, and various helicopters with novel configurations and different functions are generated successively. In order to reduce repeated design work, optimize platform performance, simplify a task system replacement method and shorten working hours, CN105882988A proposes a method for rapidly mounting and dismounting a load of an unmanned aerial vehicle, CN103274046A proposes a method for designing a task load-oriented modular unmanned helicopter, which divides the helicopter into a flight module and a task load module, and CN204021256U proposes a method for modularly designing a task load system, and optimizes a replacement mode of the task load system. However, the design ideas are directed at single-rotor tail rotor configurations or single configurations such as coaxial configurations and multi-rotor configurations, and the rapid replacement of the unmanned helicopter cannot be realized.
SUMMERY OF THE UTILITY MODEL
The utility model discloses aim at solving one of the technical problem that exists among the prior art at least. Therefore, an object of the utility model is to provide an unmanned helicopter of modularization towards configuration and task system, the unmanned helicopter of modularization towards configuration and task system realizes the modularization assembly in manufacturing and technology assembly stage, can realize the unmanned helicopter configuration of quick replacement when satisfying customer's demand, uses and the task planning stage in the later stage, can realize load system's quick replacement, avoids dismantling the complete machine structure.
According to the utility model discloses unmanned helicopter of modularization towards configuration and task system, include: the aircraft body middle section assembly comprises an enclosure, an engine arranged in the enclosure and a rotor arranged at the top of the enclosure; the engine comprises a plurality of engine bodies, a front-section engine body assembly, a rear-section engine body assembly and a front-section engine body assembly, wherein the engine bodies are used for dissipating heat of the engine bodies; the helicopter comprises a helicopter body middle section assembly, a helicopter body rear section assembly and a helicopter body control system, wherein the helicopter body rear section assembly comprises a plurality of helicopter body rear sections used for controlling the course of the helicopter, the course control modes of the plurality of helicopter body rear sections are different from each other, the helicopter body middle section assembly is selectively detachably connected with one of the plurality of helicopter body rear sections, and the helicopter body rear section is positioned at the rear end of the helicopter body middle section assembly; the mounting assembly comprises a plurality of task loads and propelling propellers, the middle section of the machine body assembly is selectively detachably connected with one of the task loads and the propelling propellers, and the mounting assembly is located on the left side and the right side of the middle section of the machine body assembly.
According to the utility model discloses towards configuration and task system's unmanned helicopter of modularization realizes the modularization assembly at manufacturing and technology assembly stage, can realize the unmanned helicopter configuration of quick replacement when satisfying customer's demand, uses and the mission planning stage in the later stage, can realize load system's quick replacement, avoids dismantling overall structure.
In addition, according to the utility model discloses unmanned helicopter of modularization towards configuration and task system can also have following additional technical characteristics:
according to the utility model discloses an embodiment, fuselage back end includes tail-rotor subassembly, single vertical fin subassembly or two vertical fin subassemblies, wherein: the tail rotor assembly comprises a tail beam and a tail rotor, the front end of the tail beam is suitable for being detachably connected with the middle section assembly of the machine body, and the rear end of the tail beam is connected with the tail rotor; the single vertical tail assembly comprises a tail beam and a single vertical tail, the front end of the tail beam is suitable for being detachably connected with the middle section assembly of the machine body, and the rear end of the tail beam is connected with the single vertical tail; the double vertical tail assembly comprises a tail beam and double vertical tails, the front end of the tail beam is suitable for being detachably connected with the machine body middle section assembly, and the rear end of the tail beam is connected with the double vertical tails.
According to an embodiment of the invention, the mission load comprises a missile, a loudspeaker or a fire extinguishing bomb.
According to an embodiment of the utility model, towards configuration and task system's unmanned helicopter of modularization still includes the oil tank subassembly, the oil tank subassembly includes a plurality of oil tanks, and is a plurality of the volume of oil tank is mutually different, the engine is optionally with a plurality of one in the oil tank links to each other.
According to an embodiment of the present invention, the oil tank is detachably connected to the top of the housing.
According to the utility model discloses an embodiment, the oil tank includes two subtanks, two the subtank is located respectively the both sides of the rotor shaft of rotor.
According to the utility model discloses an embodiment, the casing includes the upper casing and locates the lower casing of upper casing below, the upper casing with the lower casing can be dismantled and link to each other, the engine is located in the lower casing, the rotor is located the top of upper casing.
According to the utility model discloses an embodiment, the fuselage anterior segment with the lower casing can be dismantled and link to each other.
According to the utility model discloses an embodiment, the fuselage anterior segment with the upper shell can be dismantled continuously.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
fig. 1 is a schematic view of a fuselage forward section assembly of an unmanned helicopter in accordance with an embodiment of the present invention;
fig. 2 is a schematic view of a rear fuselage section assembly of an unmanned helicopter in accordance with an embodiment of the present invention;
fig. 3 is a schematic view of a mounting assembly of an unmanned helicopter in accordance with an embodiment of the present invention;
fig. 4 is a schematic view of a tank assembly of the unmanned helicopter in accordance with an embodiment of the present invention;
fig. 5 is a schematic view of an unmanned helicopter in which a midship assembly is coupled to a tail rotor assembly in accordance with an embodiment of the present invention;
fig. 6 is a schematic view of an unmanned helicopter in which a midship assembly is coupled to a double vertical tail assembly in accordance with an embodiment of the present invention;
fig. 7 is a schematic view of an unmanned helicopter in which a mid-fuselage assembly is connected to a tail rotor assembly and a propulsion propeller in accordance with an embodiment of the present invention.
Reference numerals:
an unmanned helicopter 100;
a fuselage mid-section assembly 1; a housing 11; an upper case 111; a lower case 112; a rotor 12;
a fuselage forepart assembly 2; a fuselage forward section 21;
a rear fuselage section assembly 3; a rear fuselage section 31; a tail rotor assembly 311; a double vertical tail assembly 312; a tail boom 301; a tail rotor 302; a double vertical tail 303;
mounting the component 4; a mission load 41; a propulsion propeller 42;
a tank assembly 5; an oil tank 51; the sub-tanks 511.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present invention, and should not be construed as limiting the present invention.
A configuration and mission system oriented modular unmanned helicopter 100 according to an embodiment of the present invention is described below with reference to fig. 1-7.
Referring to fig. 1-7, a configuration and mission system oriented modular unmanned helicopter 100 according to an embodiment of the present invention includes: the aircraft comprises an aircraft body middle section component 1, an aircraft body front section component 2, an aircraft body rear section component 3 and a mounting component 4.
Fuselage middle section subassembly 1 includes casing 11, locate the engine in casing 11 and locate the rotor 12 at casing 11 top, fuselage anterior segment subassembly 2 includes a plurality of fuselage anterior segments 21 that are used for carrying out the heat dissipation to the engine, and the heat dissipation power of a plurality of fuselage anterior segments 21 is different each other, and fuselage middle section subassembly 1 can be dismantled with one of a plurality of fuselage anterior segments 21 selectively and link to each other, and fuselage anterior segment 21 is located the front end of fuselage middle section subassembly 1. Here, "plurality" means two or more, for example, as shown in fig. 1, the forward-fuselage section assembly 2 includes two forward-fuselage sections 21.
It can be understood that when the operation conditions of the unmanned helicopter 100 are different, the power of the engine will not be used, and thus the heating degree of the engine during operation will be different, by making the front-end fuselage assembly 2 include a plurality of front-end fuselage sections 21 for radiating the engine, and the heat-radiating powers of the plurality of front-end fuselage sections 21 are different from each other, the front-end fuselage section 21 matched with the front-end fuselage section can be selected according to the operation conditions of the unmanned helicopter 100, for example, when the power of the engine is higher, the middle-end fuselage assembly 1 can be connected with the front-end fuselage section 21 with higher heat-radiating power, and the front-end fuselage section 21 with higher heat-radiating power is used; when the power of the engine is small, the fuselage middle section assembly 1 can be connected with the fuselage front section 21 with small heat dissipation power, and the fuselage front section 21 with small heat dissipation power is used for dissipating heat of the engine. Optionally, a universal interface adapted to each of the plurality of fuselage front sections 21 may be disposed on the fuselage middle section assembly 1, and any one of the plurality of fuselage front sections 21 may be connected to the front end of the fuselage middle section assembly 1 through the universal interface.
The rear fuselage section assembly 3 comprises a plurality of rear fuselage sections 31 used for controlling the course of the helicopter, the course control modes of the plurality of rear fuselage sections 31 are different from each other, the middle fuselage section assembly 1 can be selectively detachably connected with one of the plurality of rear fuselage sections 31, and the rear fuselage section 31 is positioned at the rear end of the middle fuselage section assembly 1. The unmanned helicopter 100 configuration can be quickly replaced by selectively removably attaching the mid-fuselage assembly 1 to one of the plurality of aft fuselage sections 31. Optionally, a universal interface adapted to the plurality of rear fuselage sections 31 may be disposed on the middle fuselage section assembly 1, and any one of the plurality of rear fuselage sections 31 may be connected to the rear end of the middle fuselage section assembly 1 through the universal interface. Here, "a plurality" means two or more, for example, as shown in fig. 2, the rear-fuselage assembly 3 includes two rear-fuselage sections 31.
The mounting assembly 4 comprises a plurality of task loads 41 and propulsion propellers 42, the mid-fuselage assembly 1 is selectively detachably connected with one of the plurality of task loads 41 and the propulsion propellers 42, and the mounting assembly 4 is positioned at the left side and the right side of the mid-fuselage assembly 1. By selectively removably attaching the mid-fuselage assembly 1 to one of the plurality of mission loads 41 and propulsion propellers 42, not only is a quick change drone 100 configuration (as shown in fig. 7) possible, but a quick change of the load system is also possible. Optionally, a universal interface adapted to both the plurality of mission loads 41 and the plurality of propulsion propellers 42 may be disposed on the mid-fuselage assembly 1, and any one of the plurality of mission loads 41 and the plurality of propulsion propellers 42 may be connected to the left and right sides of the mid-fuselage assembly 1 through the universal interface. Here, "plurality" means two or more, for example, as shown in fig. 3, mount assembly 4 includes four task loads 41.
According to the utility model discloses towards configuration and task system's unmanned helicopter of modularization 100, realize the modularization assembly in manufacturing and technology assembly phase, can realize the unmanned helicopter of quick replacement 100 configuration simultaneously satisfying customer's demand, use and the mission planning phase in the later stage, can realize load system's quick replacement, avoid dismantling the overall structure.
In an embodiment of the present invention, the rear fuselage section 31 includes a tail rotor assembly 311, a single vertical tail assembly or a double vertical tail assembly 312, wherein: the tail rotor assembly 311 comprises a tail beam 301 and a tail rotor 302, the front end of the tail beam 301 is suitable for being detachably connected with the middle section assembly 1 of the fuselage, and the rear end of the tail beam 301 is connected with the tail rotor 302; the single vertical tail assembly comprises a tail beam 301 and a single vertical tail, the front end of the tail beam 301 is suitable for being detachably connected with the middle section assembly 1 of the machine body, and the rear end of the tail beam 301 is connected with the single vertical tail; the double vertical tail assembly 312 comprises a tail beam 301 and a double vertical tail 303, wherein the front end of the tail beam 301 is suitable for being detachably connected with the middle section assembly 1 of the fuselage, and the rear end of the tail beam 301 is connected with the double vertical tail 303.
Wherein, the rear fuselage section assembly 3 may only include any two of the tail rotor assembly 311, the single vertical tail assembly, or the double vertical tail assembly 312, for example, the rear fuselage section assembly 3 only includes the tail rotor assembly 311 and the single vertical tail assembly, or the rear fuselage section assembly 3 only includes the single vertical tail assembly and the double vertical tail assembly 312, or the rear fuselage section assembly 3 only includes the tail rotor assembly 311 and the double vertical tail assembly 312 (as shown in fig. 2); of course, the rear fuselage section assembly 3 may also include a tail rotor assembly 311, a single vertical tail assembly, or a double vertical tail assembly 312. The unmanned helicopter 100 configuration can be quickly replaced by selectively removably attaching the mid-fuselage assembly 1 to one of the plurality of aft fuselage sections 31 (as shown in fig. 5 and 6).
In one embodiment of the present invention, mission load 41 comprises a missile, loudspeaker, or fire bomb.
In an embodiment of the present invention, the unmanned helicopter 100 further comprises a fuel tank assembly 5, the fuel tank assembly 5 comprises a plurality of fuel tanks 51, the volumes of the plurality of fuel tanks 51 are different from each other, and the engine is selectively connected to one of the plurality of fuel tanks 51. Here, "a plurality" means two or more, for example, as shown in fig. 4, the tank assembly 5 includes two tanks 51. It can be understood that when the flight range and the time of the unmanned helicopter 100 are different, the fuel consumption required by the unmanned helicopter 100 will also be different, and by making the fuel tank assembly 5 include a plurality of fuel tanks 51, the volumes of the plurality of fuel tanks 51 are different from each other, and the appropriate fuel tank 51 can be selected to be connected with the engine according to the operation condition of the unmanned helicopter 100, which is beneficial to the fuel economy of the whole helicopter.
In one embodiment of the present invention, as shown in fig. 5-7, the oil tank 51 is detachably attached to the top of the cabinet 11. Compared with other design schemes that the oil tank 51 is positioned at the front fuselage section 21 and the rear fuselage section 31, along with the consumption of fuel oil, the gravity center change of the oil tank 51 has smaller influence on the airframe, and the spanwise gravity center of the airframe is nearly unchanged, which is more favorable for flight control. Further, as shown in fig. 4 to 7, the oil tank 51 includes two sub-oil tanks 511, and the two sub-oil tanks 511 are respectively provided on both sides of the rotor shaft of the rotor 12, so that the influence of the change in the center of gravity of the oil tank 51 on the body can be further reduced.
In one embodiment of the present invention, as shown in fig. 5-7, the housing 11 includes an upper housing 111 and a lower housing 112 disposed below the upper housing 111, the upper housing 111 is detachably connected to the lower housing 112, the engine is disposed in the lower housing 112, and the rotor 12 is disposed on the top of the upper housing 111. By making the housing 11 include the upper housing 111 and the lower housing 112 detachably connected, when the power system is maintained, the lower housing 112 can be detached from the whole machine separately, which is convenient for maintenance.
Optionally, the front fuselage section 21 is detachably connected with the lower casing 112, and the front fuselage section 21 is connected with the lower casing 112 into a whole, so that the front fuselage section 21 and the lower casing 112 can be integrally detached from the whole machine when the power system is maintained, and the connection between the front fuselage section 21 and the engine is not required to be detached, so that the maintenance is more convenient.
Further, the front body section 21 is detachably connected to the upper housing 111. That is, the front body section 21 is detachably connected to the lower housing 112 and also detachably connected to the upper housing 111, so that the connection strength between the front body section 21 and the middle body section 1 can be improved.
In the present application, the specific connection mode of the "detachable connection" is not limited, and may be, for example, a snap connection, a screw connection, or the like.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplification of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
In the description of the present invention, unless otherwise expressly specified or limited, the first feature "on" or "under" the second feature may include both the first and second features being in direct contact, and may also include the first and second features being in contact, not being in direct contact, but rather being in contact with each other through additional features therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an illustrative embodiment," "an example," "a specific example," or "some examples" or the like mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
Claims (9)
1. A modular unmanned helicopter oriented to a configuration and mission system, comprising:
the aircraft body middle section assembly comprises an enclosure, an engine arranged in the enclosure and a rotor arranged at the top of the enclosure;
the engine comprises a plurality of engine bodies, a front-section engine body assembly, a rear-section engine body assembly and a front-section engine body assembly, wherein the engine bodies are used for dissipating heat of the engine bodies;
the helicopter comprises a helicopter body middle section assembly, a helicopter body rear section assembly and a helicopter body control system, wherein the helicopter body rear section assembly comprises a plurality of helicopter body rear sections used for controlling the course of the helicopter, the course control modes of the plurality of helicopter body rear sections are different from each other, the helicopter body middle section assembly is selectively detachably connected with one of the plurality of helicopter body rear sections, and the helicopter body rear section is positioned at the rear end of the helicopter body middle section assembly;
the mounting assembly comprises a plurality of task loads and propelling propellers, the middle section of the machine body assembly is selectively detachably connected with one of the task loads and the propelling propellers, and the mounting assembly is located on the left side and the right side of the middle section of the machine body assembly.
2. The configuration and mission system oriented modular unmanned helicopter of claim 1, wherein the rear fuselage section comprises a tail rotor assembly, a single vertical tail assembly, or a double vertical tail assembly, wherein:
the tail rotor assembly comprises a tail beam and a tail rotor, the front end of the tail beam is suitable for being detachably connected with the middle section assembly of the machine body, and the rear end of the tail beam is connected with the tail rotor;
the single vertical tail assembly comprises a tail beam and a single vertical tail, the front end of the tail beam is suitable for being detachably connected with the middle section assembly of the machine body, and the rear end of the tail beam is connected with the single vertical tail;
the double vertical tail assembly comprises a tail beam and double vertical tails, the front end of the tail beam is suitable for being detachably connected with the machine body middle section assembly, and the rear end of the tail beam is connected with the double vertical tails.
3. The configuration and mission system oriented modular unmanned helicopter of claim 1, wherein the mission load comprises a missile, a loudspeaker, or a fire extinguishing bomb.
4. The configuration and mission system-oriented modular unmanned helicopter of claim 1, further comprising a tank assembly, said tank assembly comprising a plurality of tanks, said plurality of tanks differing from each other in volume, said engine being selectively connectable to one of said plurality of tanks.
5. The configuration and mission system oriented modular unmanned helicopter of claim 4, wherein the fuel tank is removably attached to the top of the housing.
6. The configuration and mission system oriented modular unmanned helicopter of claim 5, wherein the fuel tank comprises two sub-tanks, one on each side of the rotor shaft of the rotor.
7. The configuration and mission system oriented modular unmanned helicopter of claim 1, wherein said housing comprises an upper housing and a lower housing disposed below said upper housing, said upper housing being removably attached to said lower housing, said engine being disposed within said lower housing, said rotor being disposed on top of said upper housing.
8. The configuration and mission system oriented modular unmanned helicopter of claim 7, wherein the forward section of the fuselage is removably attached to the lower housing.
9. The configuration and mission system oriented modular unmanned helicopter of claim 8, wherein the forward section of the fuselage is removably attached to the upper hull.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922308085.0U CN211766236U (en) | 2019-12-19 | 2019-12-19 | Modularized unmanned helicopter facing configuration and task system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922308085.0U CN211766236U (en) | 2019-12-19 | 2019-12-19 | Modularized unmanned helicopter facing configuration and task system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211766236U true CN211766236U (en) | 2020-10-27 |
Family
ID=72976119
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922308085.0U Active CN211766236U (en) | 2019-12-19 | 2019-12-19 | Modularized unmanned helicopter facing configuration and task system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211766236U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110963018A (en) * | 2019-12-19 | 2020-04-07 | 清华大学 | Modularized unmanned helicopter facing configuration and task system |
-
2019
- 2019-12-19 CN CN201922308085.0U patent/CN211766236U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110963018A (en) * | 2019-12-19 | 2020-04-07 | 清华大学 | Modularized unmanned helicopter facing configuration and task system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11420761B2 (en) | Autonomous propeller propulsion system for an aircraft, said autonomous propeller propulsion system comprising a fuel cell | |
| US20210269152A1 (en) | Distributed electric energy pods network and associated electrically powered vehicle | |
| CN106143898B (en) | A kind of VTOL tilting rotor fixed wing aircraft | |
| US8511613B2 (en) | Modular externally accessible batteries for an aircraft | |
| KR102581305B1 (en) | Aircraft wing beams with integrated power cells and related systems and methods | |
| US20200277061A1 (en) | Aircraft having hybrid-electric propulsion system with electric storage located in fuselage | |
| CN102923296A (en) | Modularized unmanned aerial vehicle | |
| EP3594113B1 (en) | An apparatus for adjusting the center of gravity of a vertical take-off and landing aircraft | |
| WO2000020273A2 (en) | Aircraft with removable structural payload module | |
| CN107697280B (en) | A load-carrying structure for electric unmanned aerial vehicle | |
| CN108750101A (en) | A kind of super maneuver high speed compound unmanned rotary wing aircraft, assembly, assembly and disassembly methods | |
| CN110626495A (en) | Small coaxial double-rotor type unmanned aerial vehicle | |
| CN110963018A (en) | Modularized unmanned helicopter facing configuration and task system | |
| CN101792022B (en) | Small multipurpose unmanned aerial vehicle with oil tank embedded into blended wing body | |
| CN211766236U (en) | Modularized unmanned helicopter facing configuration and task system | |
| CN105329448B (en) | A kind of vertical take-off and landing drone oil electric mixed dynamic system | |
| CN112722289A (en) | Self-rotary wing aircraft combined with multi-shaft rotor wing | |
| US6666404B1 (en) | Tripodal modular unmanned rotorcraft | |
| CN209241305U (en) | A kind of Bi-Tail-Boom Layout unmanned plane | |
| WO2022121444A1 (en) | Hybrid light manned aircraft having fixed wings and rotor wings, and aircraft | |
| CN101804865A (en) | Small multi-purpose unmanned aerial vehicle | |
| CN214138980U (en) | Self-rotary wing aircraft combined with multi-shaft rotor wing | |
| CN205203397U (en) | VTOL unmanned aerial vehicle oil -electricity hybrid vehicle system | |
| CN112407269A (en) | Mixed aircraft of stationary vane rotor | |
| CN103213683A (en) | Small multipurpose unmanned plane with oil tank embedded into blended wing body |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |