CN116985994A - Invisible aircraft - Google Patents
Invisible aircraft Download PDFInfo
- Publication number
- CN116985994A CN116985994A CN202311218901.3A CN202311218901A CN116985994A CN 116985994 A CN116985994 A CN 116985994A CN 202311218901 A CN202311218901 A CN 202311218901A CN 116985994 A CN116985994 A CN 116985994A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- stealth
- aileron
- flight
- stealth aircraft
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 claims description 17
- 230000008569 process Effects 0.000 claims description 15
- 210000001015 abdomen Anatomy 0.000 claims description 14
- 230000004927 fusion Effects 0.000 claims description 9
- 238000005096 rolling process Methods 0.000 claims description 5
- 230000009471 action Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The application discloses a stealth aircraft, which at least comprises: the aircraft nose, the main body, the outside aileron, the inside aileron, the vertical tail, the rudder, the elevator, the aircraft nose fairing and the engine, the outside aileron is symmetrically arranged at two sides of the main body respectively, and the inside aileron is symmetrically arranged at two sides of the main body respectively; a vertical tail, an elevator and a rudder are arranged at the tail part of the main machine body; the outer aileron and the inner aileron are used for controlling the roll flight of the invisible aircraft; the elevator is used for controlling the pitching flight of the stealth aircraft; the vertical tail and the rudder are used for controlling the invisible aircraft to fly backward, and the air layout of the aircraft disclosed by the application can provide the invisible aircraft with high-speed, high-maneuver and long-endurance backward flying capability, so that the battlefield survivability of the aircraft is greatly improved.
Description
Technical Field
The application belongs to the technical field of aircrafts, and particularly relates to a stealth aircraft.
Background
In complex battlefield environments, military aircraft are required to be high speed, high stealth performance as complex aeronautical machinery, while also preserving the mobility of the aircraft to increase the battlefield survivability of the aircraft. In the environment of a complex battlefield, not only forward flight is needed, but also reverse flight is needed in order to avoid actions, and under the reverse flight condition, the longitudinal stability, the transverse stability and the heading stability of the aircraft are difficult to maintain, so that the aircraft can only last for a period of tens of seconds to tens of seconds under the action of pneumatic inertia, cannot be maintained for a long time, and is difficult to meet tactical requirements in the environment of the complex battlefield.
The aircraft adopting the flying wing stealth layout is used as an aircraft with an advanced layout structure, the unusual layout characteristics determine that the operation stability characteristics of the aircraft are greatly different from those of the aircraft with the traditional layout, and for stealth performance, the tailless layout with the static and unstable characteristics further worsens the stability of the aircraft under the condition of back flight, and brings greater control difficulty and out-of-control risk. Due to the characteristic of stationarity, the stealth aircraft layout makes it more difficult to realize reverse maneuver during long voyage, thereby greatly reducing the survivability of the aircraft in complex environments.
Disclosure of Invention
The application aims to provide a stealth aircraft, a device, a terminal device and a storage medium, so as to solve the defects in the prior art, and the technical problems to be solved by the application are realized by the following technical scheme.
The embodiment of the application provides a stealth aircraft, which at least comprises: the aircraft nose, the host computer body, outside aileron, inboard aileron, stand the tail, rudder, elevator, aircraft nose fairing and engine, the said outside aileron is symmetrical to set up in the both sides of the said host computer body separately, the said inboard aileron is symmetrical to set up in the both sides of the said host computer body separately; the tail part of the main body is provided with the vertical tail, the elevator and the rudder;
the outer aileron and the inner aileron are used for controlling the roll flight of the stealth aircraft;
the elevator is used for controlling the pitching flight of the stealth aircraft;
the vertical tail and the rudder are used for controlling the invisible aircraft to fly backwards.
Optionally, the main body adopts a wing body fusion layout.
Optionally, in a case where the stealth aircraft is flying in the forward direction, the engine is located at the back of the stealth aircraft.
Optionally, the engine adopts a back air intake mode.
Optionally, under the condition that the stealth aircraft is in stealth forward flight, the aircraft nose fairing moves upwards to shield the air inlet channel.
Optionally, in the case of stealth forward flight of the stealth aircraft, the two side tails remain closed and merge with the outboard aileron and the inboard aileron; the outer aileron is used for controlling the flight direction and the flight roll under the stealth forward flight state; the elevator is used for controlling the pitching attitude of the stealth aircraft; the inner aileron is used as a spoiler to control the steering or rolling of the stealth aircraft in the stealth forward flight process; the rudder is used for flap use and for increasing the wing area of the stealth aircraft in a stealth forward flight state.
Optionally, under the condition that the stealth aircraft is in a reverse flight maneuver state, the engine is positioned at the abdomen of the stealth aircraft, and an abdomen air inlet mode is adopted.
Optionally, under the condition that the stealth aircraft is in a reverse flight maneuver state, the aircraft nose rotates so as to enable the aircraft nose fairing to keep in an upward state, and the engine air inlet channel positioned at the belly is prevented from being blocked.
Optionally, under the condition that the invisible aircraft flies in a reverse maneuvering state, the vertical tails on two sides of the main body are opened, so that the two vertical tails are in a vertical tail state with a preset angle.
Optionally, the rudders at the two side vertical tails are opened together with the vertical tails to form a dihedral angle with a preset angle, and the rudders are controlled to control the flight direction of the invisible aircraft; the outer ailerons symmetrically positioned on two sides are opened to serve as wing tip winglets or are fused with wings to increase the wing area; the inboard aileron is used for controlling the roll attitude of the stealth aircraft; the upgrade is used to control the pitch attitude of the stealth aircraft.
The embodiment of the application has the following advantages:
the embodiment of the application provides a stealth aircraft, which at least comprises: the aircraft nose, the main body, the outside aileron, the inside aileron, the vertical tail, the rudder, the elevator, the aircraft nose fairing and the engine, the outside aileron is symmetrically arranged at two sides of the main body respectively, and the inside aileron is symmetrically arranged at two sides of the main body respectively; a vertical tail, an elevator and a rudder are arranged at the tail part of the main machine body; the outer aileron and the inner aileron are used for controlling the roll flight of the invisible aircraft; the elevator is used for controlling the pitching flight of the stealth aircraft; the vertical tail and the rudder are used for controlling the invisible aircraft to fly backward, and the air layout of the aircraft disclosed by the application can provide the invisible aircraft with high-speed, high-maneuver and long-endurance backward flying capability, so that the battlefield survivability of the aircraft is greatly improved.
Drawings
In order to more clearly illustrate the embodiments of the application or the prior art solutions, the drawings which are used in the description of the embodiments or the prior art will be briefly described below, it being obvious that the drawings in the description below are only some of the embodiments described in the present application, and that other drawings can be obtained according to these drawings without inventive faculty for a person skilled in the art.
FIG. 1 is a schematic illustration of a stealth aircraft according to an embodiment of the present application;
FIG. 2 is a schematic representation of the planar shape of an aircraft in accordance with one embodiment of the present application;
FIG. 3 is a side view of a stealth flight in accordance with an embodiment of the present application;
FIG. 4 is a three-dimensional schematic of a stealth flight according to an embodiment of the present application;
FIG. 5 is a top plan view of a fly-over in accordance with an embodiment of the application;
FIG. 6 is a side view of a reverse fly in accordance with yet another embodiment of the application;
FIG. 7 is a three-dimensional schematic of the application in reverse flight;
reference numerals:
1-a machine head; 2-a main body; 3-engine; 4-outboard aileron; 5-inboard aileron; 6-rudder; 7-standing tail; 8-elevator.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the technical solutions of the present application will be clearly and completely described below with reference to specific embodiments and corresponding drawings. It will be apparent that the described embodiments are only some, but not all, embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
Referring to fig. 1, a schematic structural diagram of a stealth aircraft according to an embodiment of the present application includes at least: the aircraft nose 1, the main engine body 2, the outside aileron 4, the inside aileron 5, the vertical tail 7, the rudder 6, the elevator 8, the aircraft nose fairing and the engine 3, the outside aileron 4 is symmetrically arranged at two sides of the main engine body 2 respectively, and the inside aileron 5 is symmetrically arranged at two sides of the main engine body 2 respectively; a vertical tail 7, an elevator 8 and a rudder 6 are arranged at the tail part of the main body;
the outer aileron 4 and the inner aileron 5 are used for controlling the roll flight of the stealth aircraft; the inside aileron of the aileron is used in the back flying state, so that good direction control is provided for the aircraft; closing the outer aileron to enable the outer aileron to be fused with the wing under the back flying state, or opening the outer aileron to serve as a wing tip winglet, so that the aerodynamic lift of the aircraft is further improved;
the elevator 8 is used for controlling the pitching flight of the stealth aircraft; the elevators are symmetrically arranged at the tail part of the wing body fusion body and used for controlling flying pitching;
the vertical tail 7 and the rudder 6 are used for controlling the invisible aircraft to fly backwards. Under the stealth flight state, the vertical tail is fused with the wing to increase the area of the wing and improve the lift force. The vertical tail which is opened in the reverse flight state and the rudder which controls the flight direction provide better direction control capability for the aircraft;
the main machine body adopts a wing body fusion layout; the wing body fusion main body with symmetrical wing shape design is adopted, so that the stealth performance of the reverse flying maneuver is close to that of the forward flying maneuver, and the stealth capability of the aircraft is improved.
The machine head can rotate; and a nose fairing is arranged on the nose, and the nose fairing is used for shielding an engine air inlet channel, so that stealth performance is improved.
Under the condition that the invisible aircraft flies forward, the engine is positioned at the back of the invisible aircraft, the engine adopts a back air inlet mode, and the aircraft nose fairing runs upwards to shield an air inlet channel; the outer aileron is used for controlling the flight direction and the flight roll in the stealth forward flight state; for controlling the pitch attitude of the stealth aircraft; the inner aileron is used as a spoiler to control the steering or rolling of the stealth aircraft in the stealth forward flight process; rudders are used for flap usage to increase the wing area of stealth aircraft in stealth forward flight conditions.
Under the condition that the invisible aircraft is in a reverse flight maneuver state, the engine is positioned at the belly of the invisible aircraft, an belly air inlet mode is adopted, the aircraft nose rotates to enable the aircraft nose fairing to keep an upward state so as to avoid shielding an engine air inlet channel positioned at the belly, the aircraft nose rotates to keep the aircraft nose fairing upward, shielding of the air inlet channel is eliminated, the air input of the engine is ensured, thus the reverse flight maneuver in long voyage is kept, and the aircraft can maneuver at a large angle of attack under the reverse flight condition.
The rudders at the two side vertical tails are opened together with the vertical tails to form a dihedral angle with a preset angle, and the rudders are operated to control the flight direction of the invisible aircraft; the outer ailerons symmetrically positioned on two sides are opened to serve as wing tip winglets or are fused with wings to increase the wing area; the inner aileron is used for controlling the rolling gesture of the stealth aircraft; upgrades are used to control the pitch attitude of the stealth aircraft.
In a specific implementation process, the invisible aircraft comprises a fuselage, wings, ailerons, V-shaped vertical tails, rudders, elevators, engines, aircraft nose fairings and the like; wherein:
the fuselage wings adopt a wing body fusion layout to increase the stealth capacity of the aircraft;
ailerons are symmetrically arranged on two sides of the wing respectively and are used for controlling flying roll;
the elevators are symmetrically arranged at the tail part of the wing body fusion body and used for controlling flying pitching;
when the engine flies forward with high stealth performance, the engine is arranged at the back of the engine body, and a back air inlet mode is adopted; the V tail vertical tail and the wing form a fusion wing required by stealth flight; the rudder is used as a flap for adjusting the lifting performance of the aircraft; the elevators provide corresponding pitch control for the aircraft; the inner aileron is used as a spoiler; the aircraft nose fairing shields the air inlet channel upwards, so that the stealth capacity of the aircraft is improved;
when the reverse flying maneuver is performed: the aircraft nose rotates for the radome fairing makes progress, exposes engine intake duct entry in the belly, increases the air input, makes the aircraft can make the large angle of attack maneuver under the condition of falling. The two side vertical tails are opened to form a 45-degree dihedral angle to form a V-shaped vertical tail state; the rudder is opened along with the vertical tails at two sides to form a 45-degree dihedral angle so as to control the flight direction; the outer aileron is fixed, or opened upwards to serve as a wing tip winglet, so that the flying lift force is increased; the inner aileron controls the flying roll; the elevator controls the pitch performance of the aircraft.
As shown in fig. 1, the stealth aircraft layout suitable for long-endurance reverse flight maneuver provided by the application comprises a nose 1, a main body 2, an engine 3, an outer aileron 4, an inner aileron 5, a rudder 6, a vertical tail 7, an elevator 8 and the like. Symmetrical wing sections are adopted as the design basis of the main body of the aircraft body so as to ensure that the stealth performance of the aircraft body in reverse flight is close to that in normal flight. The aircraft plan shape of fig. 2 gives the overall dimensions of the aircraft, as well as the leading edge sweep and trailing edge forward sweep.
When in stealth flight, the aerodynamic layout of the flying wings shown in fig. 3 and 4 is adopted, namely, the flying direction of the aircraft is controlled without a vertical tail wing and a rudder in the flight process so as to increase the stealth performance in the flight process, and the specific implementation modes are as follows:
when in invisible forward flight, the engine is arranged at the back of the aircraft, and the aircraft flies in a back air inlet mode;
the aircraft nose fairing shields the air inlet channel upwards, so that stealth flight capacity of the aircraft is improved;
the two vertical tails at the two sides are kept in a closed state, so that the two vertical tails at the two sides are fused with the wing, the area of the wing is increased, the flight resistance is reduced, and the flight lift force is improved;
controlling the outer aileron to control the flight direction and the flight roll under the stealth flight state;
during the flight, the pitching attitude of the whole aircraft is controlled by an elevator; the inner aileron is used as a spoiler, so that the steering or rolling movement capability of the aircraft in the flight process and the lifting performance in the take-off and landing process are improved;
the rudder is used as a flap, so that the wing area in a stealth flight state is increased, the flight lift is improved, and the lifting performance in the take-off and landing process is also improved;
the flying maneuver adopts the aerodynamic layout of the flying wings as shown in fig. 5 to 7, so that the flying maneuver can be maintained for a long time while the flying maneuver is maintained, and the stealth performance of the flying maneuver is close to the stealth performance in the stealth flying state, namely, a vertical tail wing and a rudder for controlling the flying direction are added, the air inflow in the whole flying process is improved by adopting an belly air intake mode, and the flying maneuver and the large angle of attack maneuver for the long time are maintained, and the specific implementation process is as follows:
in the back flying maneuver state, the engine is arranged on the abdomen of the aircraft, and an abdomen air inlet mode is adopted; the aircraft nose rotates, keeps the aircraft nose radome upwards, avoids sheltering from the engine intake duct that is located the belly to increase the air input in the flight process, guarantee to realize long-endurance back-flying maneuver, and the air input under the big angle of attack maneuver state.
In the process of back flying, vertical tails on two sides are opened and are reversed by 45 degrees to form a V-shaped vertical tail state; in a back flying maneuver state, the rudders positioned at the vertical tails at two sides are opened together with the vertical tails to form a 45-degree dihedral angle, and the rudders are controlled to control the flying direction of the whole aircraft; the outer ailerons symmetrically positioned on two sides are opened to serve as wing tip winglets or are fused with wings to increase the wing area so as to improve the flying lift; the roll attitude of the whole aircraft is controlled by the inner ailerons positioned at two sides; the pitching attitude of the whole aircraft is controlled by an elevator positioned at the tail of the aircraft;
the embodiment of the application provides a variant stealth aircraft layout suitable for high maneuver, which comprises a wing fusion layout for stealth flight; flap, aileron, rudder and elevator layouts for improving lift and handling performance; vertical tail, horizontal tail and control surface layout for improving the maneuverability and stability of the aircraft under the condition of the reverse flight of the aircraft; aircraft engine layout. The aircraft pneumatic layout disclosed by the application can provide high-speed, high-mobility and long-endurance reverse flight capability for the stealth aircraft, and greatly improve the battlefield survivability of the aircraft.
The embodiment of the application provides a stealth aircraft, which at least comprises: the aircraft nose, the main body, the outside aileron, the inside aileron, the vertical tail, the rudder, the elevator, the aircraft nose fairing and the engine, the outside aileron is symmetrically arranged at two sides of the main body respectively, and the inside aileron is symmetrically arranged at two sides of the main body respectively; a vertical tail, an elevator and a rudder are arranged at the tail part of the main machine body; the outer aileron and the inner aileron are used for controlling the roll flight of the invisible aircraft; the elevator is used for controlling the pitching flight of the stealth aircraft; the vertical tail and the rudder are used for controlling the invisible aircraft to fly backward, and the air layout of the aircraft disclosed by the application can provide the invisible aircraft with high-speed, high-maneuver and long-endurance backward flying capability, so that the battlefield survivability of the aircraft is greatly improved.
It should be noted that the foregoing detailed description is exemplary and is intended to provide further explanation of the application. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the present application. As used herein, the singular is intended to include the plural unless the context clearly indicates otherwise. Furthermore, it will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, steps, operations, devices, components, and/or groups thereof.
It should be noted that the terms "first," "second," and the like in the description and the claims of the present application and the above figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the terms so used are interchangeable under appropriate circumstances such that the embodiments of the application described herein are capable of operation in sequences other than those illustrated or otherwise described herein.
Furthermore, the terms "comprise" and "have," as well as any variations thereof, are intended to cover a non-exclusive inclusion. For example, a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those elements but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways, such as rotated 90 degrees or at other orientations, and the spatially relative descriptors used herein interpreted accordingly.
In the above detailed description, reference is made to the accompanying drawings, which form a part hereof. In the drawings, like numerals typically identify like components unless context indicates otherwise. The illustrated embodiments described in the detailed description, drawings, and claims are not meant to be limiting. Other embodiments may be utilized, and other changes may be made, without departing from the spirit or scope of the subject matter presented herein.
The above description is only of the preferred embodiments of the present application and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims (10)
1. A stealth aircraft, the stealth aircraft comprising at least: the aircraft nose, the host computer body, outside aileron, inboard aileron, stand the tail, rudder, elevator, aircraft nose fairing and engine, the said outside aileron is symmetrical to set up in the both sides of the said host computer body separately, the said inboard aileron is symmetrical to set up in the both sides of the said host computer body separately; the tail part of the main body is provided with the vertical tail, the elevator and the rudder;
the outer aileron and the inner aileron are used for controlling the roll flight of the stealth aircraft;
the elevator is used for controlling the pitching flight of the stealth aircraft;
the vertical tail and the rudder are used for controlling the invisible aircraft to fly backwards.
2. The stealth aircraft of claim 1, wherein the main fuselage employs a wing-body fusion layout.
3. The stealth aircraft of claim 2, wherein the engine is located on the back of the stealth aircraft in the case of forward flight of the stealth aircraft.
4. A stealth aircraft according to claim 3, wherein the engine is back-air.
5. The stealth aircraft of claim 4, wherein the nose fairing is operable to block an inlet duct in the stealth forward flight of the stealth aircraft.
6. The stealth aircraft of claim 4, wherein in a stealth forward flight of the stealth aircraft, the two side tails remain closed and merge with the outboard aileron and the inboard aileron; the outer aileron is used for controlling the flight direction and the flight roll under the stealth forward flight state; the elevator is used for controlling the pitching attitude of the stealth aircraft; the inner aileron is used as a spoiler to control the steering or rolling of the stealth aircraft in the stealth forward flight process; the rudder is used for flap use and for increasing the wing area of the stealth aircraft in a stealth forward flight state.
7. The stealth aircraft of claim 2, wherein the engine is located on an abdomen of the stealth aircraft in a reverse maneuver of the stealth aircraft using an abdomen intake.
8. The stealth aircraft of claim 7, wherein in the event of a reverse maneuver of the stealth aircraft, the nose rotates to maintain the nose fairing in an upward position to avoid obscuring an engine intake located on a belly.
9. The stealth aircraft of claim 8, wherein in a reverse maneuver of the stealth aircraft, the tails on either side of the main body are opened to allow the two tails to assume a vertical condition at a predetermined angle.
10. The stealth aircraft of claim 9, wherein rudders at the two side tails open together with the tails, at a predetermined angle dihedral angle, steering rudders to control the direction of flight of the stealth aircraft; the outer ailerons symmetrically positioned on two sides are opened to serve as wing tip winglets or are fused with wings to increase the wing area; the inboard aileron is used to control the roll attitude of the stealth aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311218901.3A CN116985994B (en) | 2023-09-21 | 2023-09-21 | Invisible aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311218901.3A CN116985994B (en) | 2023-09-21 | 2023-09-21 | Invisible aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116985994A true CN116985994A (en) | 2023-11-03 |
| CN116985994B CN116985994B (en) | 2023-11-28 |
Family
ID=88525036
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311218901.3A Active CN116985994B (en) | 2023-09-21 | 2023-09-21 | Invisible aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116985994B (en) |
Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB592220A (en) * | 1942-02-23 | 1947-09-11 | Northrop Aircraft Inc | Improvements in airplanes |
| GB935656A (en) * | 1960-11-18 | 1963-09-04 | English Electric Co Ltd | Improvements in and relating to supersonic aircraft |
| JPH08230793A (en) * | 1995-02-23 | 1996-09-10 | Mitsubishi Heavy Ind Ltd | Aircraft |
| US20050040283A1 (en) * | 2003-08-18 | 2005-02-24 | Richard Tyler Frazer | Method of propulsion and attitude control in fluid environments and vehicles utilizing said method |
| US20050103929A1 (en) * | 2003-10-30 | 2005-05-19 | Supersonic Aerospace International, Llc | Supersonic aircraft with channel relief control |
| EP1695903A1 (en) * | 2005-02-25 | 2006-08-30 | Northrop Grumman Corporation | Aircraft with rotatable leading edge of fuselage and wings |
| CN103523223A (en) * | 2013-10-28 | 2014-01-22 | 中国航空工业集团公司哈尔滨空气动力研究所 | Transverse course control system and transverse course control method for flying wing configuration |
| FR2997924A1 (en) * | 2012-11-13 | 2014-05-16 | Nfelec | VERTICAL TAKE-OFF AIR VEHICLE AND HORIZONTAL FLIGHT |
| CN103879556A (en) * | 2014-03-31 | 2014-06-25 | 冯加伟 | Wide flight envelop morphing aircraft |
| CN104589938A (en) * | 2014-03-20 | 2015-05-06 | 中国特种飞行器研究所 | Cross-medium aircraft with changeable shape like flying fish |
| CN106184741A (en) * | 2016-09-30 | 2016-12-07 | 中国科学院工程热物理研究所 | A kind of flying wing type ducted fan VUAV |
| CN110203372A (en) * | 2019-06-28 | 2019-09-06 | 南京航空航天大学 | A kind of variant invisbile plane and its changing method and application |
| US20190389581A1 (en) * | 2018-06-22 | 2019-12-26 | Bombardier Inc. | Blended wing body aircraft |
| US10562623B1 (en) * | 2016-10-21 | 2020-02-18 | Birdseyeview Aerobotics, Llc | Remotely controlled VTOL aircraft |
| CN111766888A (en) * | 2019-06-27 | 2020-10-13 | 北京京东尚科信息技术有限公司 | Aircraft-based control method and aircraft |
| US11591066B1 (en) * | 2021-10-15 | 2023-02-28 | Blended Wing Aircraft, Inc. | Systems and methods for folding wings on an aircraft |
| US20230092771A1 (en) * | 2021-09-17 | 2023-03-23 | Blended Wing Aircraft, Inc. | Systems and methods for modular aircraft |
| CN115924059A (en) * | 2022-12-23 | 2023-04-07 | 中国航空工业集团公司西安飞机设计研究所 | Single sweepback flying wing horizontal tail fusion pneumatic layout aircraft |
| EP4163202A1 (en) * | 2021-10-11 | 2023-04-12 | The Boeing Company | Variable position airfoil |
| CN116119001A (en) * | 2022-12-16 | 2023-05-16 | 沈阳飞机设计研究所扬州协同创新研究院有限公司 | Straight-shaft type full-motion variable V-tail motion mechanism |
-
2023
- 2023-09-21 CN CN202311218901.3A patent/CN116985994B/en active Active
Patent Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB592220A (en) * | 1942-02-23 | 1947-09-11 | Northrop Aircraft Inc | Improvements in airplanes |
| GB935656A (en) * | 1960-11-18 | 1963-09-04 | English Electric Co Ltd | Improvements in and relating to supersonic aircraft |
| JPH08230793A (en) * | 1995-02-23 | 1996-09-10 | Mitsubishi Heavy Ind Ltd | Aircraft |
| US20050040283A1 (en) * | 2003-08-18 | 2005-02-24 | Richard Tyler Frazer | Method of propulsion and attitude control in fluid environments and vehicles utilizing said method |
| US20050103929A1 (en) * | 2003-10-30 | 2005-05-19 | Supersonic Aerospace International, Llc | Supersonic aircraft with channel relief control |
| EP1695903A1 (en) * | 2005-02-25 | 2006-08-30 | Northrop Grumman Corporation | Aircraft with rotatable leading edge of fuselage and wings |
| FR2997924A1 (en) * | 2012-11-13 | 2014-05-16 | Nfelec | VERTICAL TAKE-OFF AIR VEHICLE AND HORIZONTAL FLIGHT |
| CN103523223A (en) * | 2013-10-28 | 2014-01-22 | 中国航空工业集团公司哈尔滨空气动力研究所 | Transverse course control system and transverse course control method for flying wing configuration |
| CN104589938A (en) * | 2014-03-20 | 2015-05-06 | 中国特种飞行器研究所 | Cross-medium aircraft with changeable shape like flying fish |
| CN103879556A (en) * | 2014-03-31 | 2014-06-25 | 冯加伟 | Wide flight envelop morphing aircraft |
| CN106184741A (en) * | 2016-09-30 | 2016-12-07 | 中国科学院工程热物理研究所 | A kind of flying wing type ducted fan VUAV |
| US10562623B1 (en) * | 2016-10-21 | 2020-02-18 | Birdseyeview Aerobotics, Llc | Remotely controlled VTOL aircraft |
| US20190389581A1 (en) * | 2018-06-22 | 2019-12-26 | Bombardier Inc. | Blended wing body aircraft |
| CN111766888A (en) * | 2019-06-27 | 2020-10-13 | 北京京东尚科信息技术有限公司 | Aircraft-based control method and aircraft |
| CN110203372A (en) * | 2019-06-28 | 2019-09-06 | 南京航空航天大学 | A kind of variant invisbile plane and its changing method and application |
| US20230092771A1 (en) * | 2021-09-17 | 2023-03-23 | Blended Wing Aircraft, Inc. | Systems and methods for modular aircraft |
| EP4163202A1 (en) * | 2021-10-11 | 2023-04-12 | The Boeing Company | Variable position airfoil |
| US11591066B1 (en) * | 2021-10-15 | 2023-02-28 | Blended Wing Aircraft, Inc. | Systems and methods for folding wings on an aircraft |
| CN116119001A (en) * | 2022-12-16 | 2023-05-16 | 沈阳飞机设计研究所扬州协同创新研究院有限公司 | Straight-shaft type full-motion variable V-tail motion mechanism |
| CN115924059A (en) * | 2022-12-23 | 2023-04-07 | 中国航空工业集团公司西安飞机设计研究所 | Single sweepback flying wing horizontal tail fusion pneumatic layout aircraft |
Non-Patent Citations (4)
| Title |
|---|
| 杨小川;张思远;魏建烽;杜远红;刘瑞;毛仲君: "美国第五代航空靶机发展历程及应用趋势分析", 飞航导弹, no. 008 * |
| 洪苇江;李小婷;薛晖;杨乐;杨道宁: "前缘尖化对飞翼布局飞行器气动隐身性能影响", 南京航空航天大学学报, vol. 54, no. 002 * |
| 贾彩霞: "无人机轻质隐身技术的当前及未来", 2014(第五届)中国无人机大会 * |
| 陈奎;闫稳;王凌伟;王建生;: "一种新型高隐身低阻尼控制系统设计与仿真", 计算机仿真, no. 06 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116985994B (en) | 2023-11-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3868661A1 (en) | Fixed-wing short-takeoff-and-landing aircraft and related methods | |
| CN107310714B (en) | Flight control system of stealth unmanned aerial vehicle with flying wing layout and control method thereof | |
| CN105480416A (en) | Unmanned aerial vehicle with tilted rotors | |
| CN103209892A (en) | Aircraft with an integral aerodynamic configuration | |
| CN105366049A (en) | Vertical takeoff and landing unmanned aerial vehicle | |
| CN107264794B (en) | A control method for a detachable hybrid drive vertical take-off and landing unmanned aerial vehicle | |
| CN106114847B (en) | A kind of vertically taking off and landing flyer | |
| CN106240814A (en) | A kind of power-controlled tail sitting posture mixed layout vertically taking off and landing flyer | |
| CN108622369A (en) | Morphing aircraft wing structure | |
| CN108394556A (en) | A kind of efficient tilting rotor wing unmanned aerial vehicle | |
| CN111452969A (en) | A vertical take-off and landing tail-mounted flying-wing UAV | |
| CN107813928A (en) | One kind can vert more rotor twin fuselage canard configuration unmanned vehicles | |
| US8262017B2 (en) | Aircraft with forward lifting elevator and rudder, with the main lifting surface aft, containing ailerons and flaps, and airbrake | |
| CN108082471B (en) | Variant supersonic aircraft | |
| CN210235305U (en) | Flying wing type airplane with variable outer wing sweepback angle and tiltable winglet | |
| CN105905295A (en) | Vertical take-off and landing fixed wing aircraft | |
| CN211107954U (en) | A variant stealth aircraft | |
| CN103523223B (en) | Transverse course control system and transverse course control method for flying wing configuration | |
| CN110920881A (en) | A vertical take-off and landing unmanned transport aircraft and its control method | |
| CN207089635U (en) | The flight control system of the stealthy unmanned plane of Flying-wing | |
| CN116985994B (en) | Invisible aircraft | |
| CN114148516A (en) | Distributed tilting duct vertical take-off and landing aircraft and control method thereof | |
| CN112572788A (en) | Aircraft with cross-over supersonic pneumatic performance | |
| CN204264454U (en) | Novel high lift canard configuration connects rotor aircraft | |
| CN211253019U (en) | A vertical take-off and landing unmanned transport aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |