CN113753217A - Aircraft configuration with mission cabin - Google Patents
Aircraft configuration with mission cabin Download PDFInfo
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- CN113753217A CN113753217A CN202111102402.9A CN202111102402A CN113753217A CN 113753217 A CN113753217 A CN 113753217A CN 202111102402 A CN202111102402 A CN 202111102402A CN 113753217 A CN113753217 A CN 113753217A
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- fuselage
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- 238000010276 construction Methods 0.000 claims 1
- 230000007613 environmental effect Effects 0.000 claims 1
- 108010066057 cabin-1 Proteins 0.000 description 8
- 238000012423 maintenance Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Body Structure For Vehicles (AREA)
Abstract
The application belongs to the field of aircraft design, and particularly relates to an aircraft configuration with a mission cabin. The method comprises the following steps: the aircraft comprises a fuselage (6), a mission cabin (1), wings (5), landing gears, an empennage (3) and an engine (4). An opening is formed in the lower part of the machine body (6); the task cabin (1) is detachably arranged at an opening at the lower part of the machine body (6); the aircraft is characterized in that the wings (5) are arranged on the upper portion of the aircraft body (6) in a single-wing layout with a large aspect ratio, landing gear cabins (2) are arranged on the wings (5), and the distance from the landing gear cabins (2) to the aircraft body (6) is not less than the width of the task cabin (1); landing gears, three in number, wherein one landing gear is mounted on the lower portion of the fuselage (6), and two landing gears are mounted on the lower portion of the wing (5); the tail wing (3) is arranged at the tail part of the machine body (6); the engine (4) is arranged on the upper part of the machine body (6).
Description
Technical Field
The application belongs to the field of aircraft design, and particularly relates to an aircraft configuration with a mission cabin.
Background
The common task type aircraft carries out comprehensive design on task load and the aircraft, the aerodynamic layout, the structure and the airborne system of the aircraft are all designed around the task, a replaceable integrated task cabin is not provided, if other task capabilities of the aircraft are required to be expanded, the aircraft needs to be greatly changed, the cost is high, and quick replacement and installation cannot be realized.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide an aircraft configuration with a mission bay to address at least one of the problems with the prior art.
The technical scheme of the application is as follows:
an aircraft configuration having a mission bay, comprising:
the lower part of the machine body is provided with an opening;
the task cabin is detachably arranged at an opening at the lower part of the machine body;
the aircraft comprises a fuselage, wings, a landing gear cabin and a mission cabin, wherein the wings are arranged on the upper part of the fuselage in a high aspect ratio upper single wing layout, the landing gear cabin is arranged on the wings, and the distance from the landing gear cabin to the fuselage is not less than the width of the mission cabin;
landing gears, including three, wherein one of the landing gears is arranged on the lower part of the fuselage, and two of the landing gears are arranged on the lower part of the wing;
the tail wing is installed at the tail part of the machine body;
and the engine is mounted on the upper part of the machine body.
In at least one embodiment of the present application, the aircraft having a mission bay is configured as a manned or unmanned aircraft.
In at least one embodiment of the present application, the mission compartment includes a plurality of the mission compartments mounted on the front, middle and/or rear fuselages, respectively.
In at least one embodiment of the application, the task cabin comprises a plurality of types, and the different types of task cabins are provided with universal electric interfaces, hydraulic interfaces and environment control interfaces.
In at least one embodiment of the present application, an open flexible architecture avionics system is disposed in the mission bay.
In at least one embodiment of the present application, the tail is an H-type tail or a V-type tail.
In at least one embodiment of the application, the airplane configuration platform with the mission cabin is designed in a structure modularization mode and a system modularization mode.
The invention has at least the following beneficial technical effects:
according to the airplane configuration with the task cabin, the large-aspect-ratio upper single-wing and backpack engines are adopted, the main undercarriage cabin is arranged below the wings, and the task cabin convenient to replace is arranged at the lower part of the airplane body; through a fuselage open structure that can carry out effective control to fuselage overall deformation, can set up the task cabin of 1 or a plurality of convenient changes in fuselage lower part, control open structure deflection simultaneously, guarantee the convertibility in task cabin.
Drawings
FIG. 1 is a schematic illustration of an aircraft configuration having a mission bay according to one embodiment of the present application.
Wherein:
1-a task cabin; 2-a landing gear bay; 3-tail fin; 4-an engine; 5-an airfoil; 6-fuselage.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "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 used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1.
The present application provides an aircraft configuration having a mission bay, comprising: fuselage 6, mission bay 1, wings 5, landing gear, empennage 3, and engines 4.
Specifically, as shown in fig. 1, the lower part of the fuselage 6 is provided with an opening, the task cabin 1 is installed at the opening at the lower part of the fuselage 6 in a detachable manner, one or more convenient and replaceable task cabins 1 are arranged at the lower part of the fuselage 6 through a fuselage opening structure capable of effectively controlling the overall deformation of the fuselage 6, and in the embodiment, the front fuselage, the middle fuselage and the rear fuselage can be assembled with the replaceable task cabin 1.
The wings 5 are arranged on the upper part of the machine body 6 in a high aspect ratio upper single wing layout, the landing gear cabins 2 are arranged on the wings 5, and the distance from the landing gear cabins 2 to the machine body 6 is not less than the width of the task cabin 1, so that the task cabin 1 can be conveniently replaced; the landing gear comprises three landing gears, wherein one landing gear is arranged on the lower portion of the fuselage 6, and two landing gears are arranged on the lower portion of the wing 5.
Further, the tail wing 3 is installed at the tail part of the body 6, and the engine 4 is installed at the back of the body at the upper part of the body 6. In the preferred embodiment of the application, the flight 3 is an H-flight, but other arrangements, such as a V-flight, are also possible. In this embodiment, 2 or more engines 4 may be used, and the engines 4 may be disposed at positions such as a wing nacelle, in addition to the machine back, under the restriction of ensuring the replacement space of the mission nacelle 1.
The utility model provides an aircraft configuration with task cabin, layout form are applicable to the unmanned aerial vehicle, are applicable to unmanned aerial vehicle equally.
In a preferred embodiment of the present application, the mission chamber 1 may include a plurality of types, and the mission chamber 1 having different functions is replaced to realize a multi-mission capability such as carrying, delivering, refueling, reconnaissance, striking, and the like. Advantageously, in this embodiment, different types of task cabins 1 are provided with a universal electrical interface, a hydraulic interface, an environment control interface, and the like, and are further configured with an open flexible architecture avionics system, so that plug and play of the task cabin 1 is realized. Under the support of a standardized interface, the airplane capacity expansion can be quickly realized only by designing and lifting the task cabin 1.
In the preferred embodiment of the application, except for the task cabin 1, the aircraft platform also adopts the structure modularization and system modularization design, can realize the modularization of production, assembly, transportation, maintenance, through the quick dismouting of module, promote the aircraft rate of perfectness.
The airplane structure with the mission cabin is characterized in that an airplane platform and a mission system are separately designed. The aircraft adopts single-wing, backpack air intake, H type fin on the big aspect ratio, arranges the undercarriage cabin under the wing, through one kind can carry out the fuselage open structure of effective control to fuselage overall deformation, sets up the task cabin of 1 or a plurality of convenient changes in fuselage lower part. The task cabin 1 is provided with universal electrical, hydraulic, environment control and other interfaces, the plug and play of the task cabin is realized through an open flexible architecture avionics system, and the multitasking capabilities of carrying, delivering, refueling, reconnaissance, striking and the like are realized through reloading the task cabin with different functions. Under the support of a standardized interface, the airplane capacity expansion can be quickly realized only by the design and the promotion of a task cabin. Due to the universality of the aircraft platform, the configuration mode of the aircraft platform and the multi-type task cabin can be flexibly matched for use, and different task requirements can be met. Besides the task cabin, the aircraft platform also adopts the structure modularization and system modularization design, can realize the modularization of production, assembly, transportation, maintenance, through the quick dismouting of module, promotes the aircraft rate of perfectness.
The airplane structure with the task cabin adopts the modular design, the separation of an airplane platform and a task system is realized, the task cabin can be easily replaced through the pneumatic layout of the airplane, and therefore the multi-task reloading capacity of the airplane is realized. Besides the mission cabin, the aircraft platform also adopts the structure modularization and system modularization design, and the modularization of production, assembly, transportation and maintenance can be realized. Due to the universality of the aircraft platform, the configuration mode of the aircraft platform and the multi-type task cabin can be flexibly matched for use, and different task requirements can be met.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. An aircraft configuration having a mission bay, comprising:
the lower part of the machine body (6) is provided with an opening;
the task cabin (1) is detachably arranged at an opening at the lower part of the machine body (6);
the aircraft comprises wings (5), wherein the wings (5) are arranged on the upper portion of an aircraft body (6) in a high aspect ratio upper single wing mode, landing gear cabins (2) are arranged on the wings (5), and the distance from the landing gear cabins (2) to the aircraft body (6) is not less than the width of a task cabin (1);
landing gears, three in number, wherein one landing gear is mounted on the lower portion of the fuselage (6), and two landing gears are mounted on the lower portion of the wing (5);
the tail wing (3), the said tail wing (3) is installed in the afterbody of the said fuselage (6);
the engine (4), engine (4) is installed in fuselage (6) upper portion.
2. The aircraft configuration with a mission bay according to claim 1, wherein the aircraft configuration with a mission bay is a manned or unmanned aerial vehicle.
3. Aircraft configuration with a mission bay according to claim 1, characterized in that the mission bay (1) comprises a plurality of mission bays (1) mounted on the front, middle and/or rear fuselage, respectively.
4. The aircraft configuration with a mission bay according to claim 3, wherein the mission bay (1) comprises a plurality of types, different types of mission bays (1) having common electrical, hydraulic and environmental control interfaces provided therein.
5. Aircraft configuration with a mission bay according to claim 4, characterized in that an open flexible architecture avionics system is provided in the mission bay (1).
6. The aircraft configuration with a mission bay according to claim 1, characterized in that the empennage (3) is an H-or V-type empennage.
7. The aircraft configuration with a mission bay as claimed in claim 1, wherein the aircraft configuration platform with a mission bay is of modular design in construction and system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111102402.9A CN113753217A (en) | 2021-09-19 | 2021-09-19 | Aircraft configuration with mission cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111102402.9A CN113753217A (en) | 2021-09-19 | 2021-09-19 | Aircraft configuration with mission cabin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113753217A true CN113753217A (en) | 2021-12-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111102402.9A Pending CN113753217A (en) | 2021-09-19 | 2021-09-19 | Aircraft configuration with mission cabin |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050067526A1 (en) * | 2003-09-05 | 2005-03-31 | Supersonic Aerospace International, Llc | Wing gull integration nacelle clearance, compact landing gear stowage, and sonic boom reduction |
| CN107985597A (en) * | 2017-11-03 | 2018-05-04 | 西北工业大学 | A kind of shipping unmanned plane with modularization cargo hold |
| CN108045549A (en) * | 2017-12-31 | 2018-05-18 | 上海牧羽航空科技有限公司 | A kind of tiltrotor with separable function pod |
| CN109552625A (en) * | 2018-11-30 | 2019-04-02 | 陈达 | A kind of modularization fixed-wing unmanned plane |
| CN109878725A (en) * | 2019-03-31 | 2019-06-14 | 拓攻（南京）机器人有限公司 | A kind of fixed-wing logistics unmanned plane |
| CN213168574U (en) * | 2020-06-02 | 2021-05-11 | 王平 | Split type modularization helicopter |
-
2021
- 2021-09-19 CN CN202111102402.9A patent/CN113753217A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050067526A1 (en) * | 2003-09-05 | 2005-03-31 | Supersonic Aerospace International, Llc | Wing gull integration nacelle clearance, compact landing gear stowage, and sonic boom reduction |
| CN107985597A (en) * | 2017-11-03 | 2018-05-04 | 西北工业大学 | A kind of shipping unmanned plane with modularization cargo hold |
| CN108045549A (en) * | 2017-12-31 | 2018-05-18 | 上海牧羽航空科技有限公司 | A kind of tiltrotor with separable function pod |
| CN109552625A (en) * | 2018-11-30 | 2019-04-02 | 陈达 | A kind of modularization fixed-wing unmanned plane |
| CN109878725A (en) * | 2019-03-31 | 2019-06-14 | 拓攻（南京）机器人有限公司 | A kind of fixed-wing logistics unmanned plane |
| CN213168574U (en) * | 2020-06-02 | 2021-05-11 | 王平 | Split type modularization helicopter |
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Application publication date: 20211207 |