CN108995803B - Foldable wave rider pneumatic layout structure and method of supersonic passenger plane - Google Patents
Foldable wave rider pneumatic layout structure and method of supersonic passenger plane Download PDFInfo
- Publication number
- CN108995803B CN108995803B CN201810587782.1A CN201810587782A CN108995803B CN 108995803 B CN108995803 B CN 108995803B CN 201810587782 A CN201810587782 A CN 201810587782A CN 108995803 B CN108995803 B CN 108995803B
- Authority
- CN
- China
- Prior art keywords
- wing
- configuration
- angle
- sweepback
- foldable
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C30/00—Supersonic type aircraft
-
- 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
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/40—Varying angle of sweep
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention mainly belongs to the technical field of pneumatic layout of waverider, and particularly relates to a foldable pneumatic layout of waverider of a supersonic passenger plane. The foldable type waverider pneumatic layout comprises a fuselage, a main wing, a strake wing, a vertical tail, a forward swept wing positioned on the main wing, a canard wing and a power device, wherein the backward swept angle of the canard wing and the forward swept angle of the forward swept wing can be adjusted; the wave rider pneumatic layout can be made to assume a deployed configuration or a folded configuration by adjusting the sweepback angle of the duck wing and the sweepfront angle of the sweepfront wing; the unfolding configuration has a large aspect ratio, and is suitable for low subsonic takeoff and landing and for transonic cruise; the folding configuration is a wave multiplier configuration and is suitable for supersonic cruise. The pneumatic layout of the foldable waverider gives consideration to the advantages of taking off and landing, transonic flight and supersonic cruise.
Description
Technical Field
The invention mainly belongs to the technical field of pneumatic layout of waverider, and particularly relates to a foldable waverider pneumatic layout structure and a foldable waverider pneumatic layout method for a supersonic passenger plane.
Background
The improvement of the cruising speed is always a pursuit target of the traveling flight of passenger planes, the global economy and culture fusion degree is high at present, intercontinental travel is not uncommon, but even the fastest jet passenger planes require more than ten hours to realize intercontinental travel at present, the comfort level and the timeliness are not satisfactory, and the supersonic passenger planes become hot spots of research of people again.
In recent years, researchers have proposed the idea of generating lift by using the pressure difference between the top and bottom of a shock wave, and this flow pattern is called a shock wave-expansion wave flow pattern. An aircraft applying the flow pattern is called a wave-rider aircraft, namely a wave-rider, and the flight Mach number of the aircraft can reach 20 at most. The profile of the aircraft is streamline, all the front edges of the aircraft are provided with the attached shock waves, and the aircraft can be applied to supersonic aircraft. The principle is that high-pressure fluid after the shock wave is limited on the lower surface of the aircraft, and the shock wave is attached to the lower surface of the aircraft and flies like riding on the shock wave. In the design, the shock wave is prevented from bypassing the front edge and leaking to the upper surface as much as possible, so that the lift-drag ratio which is much higher than that of the common appearance is obtained within the range of the designed attack angle. The airplane can meet the requirements of people on the supersonic aircraft and realize the ideal of quick travel.
For military applications, such as aerodrome aircraft, rocco corporation of america has developed, when studying XB-70 supersonic bombers, designers have placed an engine compartment and a large wedge-shaped air inlet on the belly of the XB-70 aircraft, and when the aircraft is flying at mach number 3, the shock waves emitted from the tip of the wedge-shaped air inlet are concentrated on the lower surface of the wing, causing a sudden increase in pressure on the lower surface of the wing, thus generating additional lift. The newly increased lift force becomes a compression lift force or a shock wave lift force, the value accounts for about 30% of the lift force of the whole aircraft, corresponding resistance is not increased at the moment, the supersonic lift-drag ratio of the aircraft is increased, and therefore the economy of the aircraft during supersonic cruise is improved.
Since the introduction of wave multipliers, research on wave multiplier configurations, particularly in the field of supersonic flight, has become relatively sophisticated. However, in the field of wide mach number flight, the application of the conventional waverider has inherent limitations, especially in low-speed flight, and the aircraft with the waverider configuration cannot exert the advantages thereof, and the main problems existing at present are as follows:
(1) because the layout of the waverider is mainly suitable for the supersonic speed flight stage, under the subsonic speed state and even the transonic speed state, the slope of the lifting line of the passenger plane of the waverider at the moment is very low due to the low aspect ratio, and the passenger plane has high induced resistance, so that the lift-drag ratio at the low speed is further reduced;
(2) the aircraft with the wave-rider layout has small span length, a high lift device with enough size is difficult to arrange at the rear edge, the pneumatic performance of the aircraft in a take-off and landing state is poor, and the requirement can be met only by a large take-off and landing field length;
(3) since the slope of the lift line is reduced due to the small aspect ratio, a large take-off attitude angle is required for take-off and landing of the wave rider layout, and in this case, a poor aerodynamic phenomenon such as air flow separation is likely to occur on the leeward side of the wave rider.
Based on the above analysis, further research is needed to design a novel aircraft with high and low speed aerodynamic design matching effects to obtain an aircraft with better aerodynamic performance in a wide speed range, and the novel aircraft with high and low speed aerodynamic design matching effects needs to meet the requirements of supersonic cruise and take off and landing performance and flight performance at subsonic speed.
Disclosure of Invention
In view of the above technical problems, the present invention provides a pneumatic layout structure and method for a foldable wave-rider of a supersonic passenger plane. The main design concept is summarized as follows: the low subsonic speed takeoff and landing and transonic speed cruising (if any) are in an unfolding configuration, and a small sweepback canard wing and a sweepback wing on a main wing are adopted at the moment so as to improve the lift-drag ratio and improve the take-off and landing performance; the folding type supersonic cruise aircraft is in a folding configuration when in supersonic cruise, at the moment, the sweepforward wings on the main wings rotate around the rotating shafts to change sweepforward angles and cling to two sides of the aircraft body, meanwhile, the small sweepback canard wings also start to change sweepback to rotate so that sweepback angles of the canard wings are increased, finally, the canard wings, the main wings and the aircraft body form a wave-rider configuration, and the folding type supersonic cruise aircraft is very suitable for supersonic cruise. The pneumatic layout can meet requirements of supersonic cruise and can also give consideration to take-off and landing performance and flight performance under subsonic speed.
The invention is realized by the following technical scheme:
a foldable wave rider pneumatic layout structure of a supersonic passenger plane comprises a plane body, a main wing, a strake wing, a vertical fin, a forward swept wing positioned on the main wing, a canard wing and a power device, wherein the backward swept angle of the canard wing and the forward swept angle of the forward swept wing can be adjusted; the pneumatic layout structure of the wave rider can be made to assume a folded configuration or a deployed configuration by adjusting the sweepback angle of the duck wing and the sweepback angle of the sweepback wing;
the aspect ratio of the unfolding structure can reach more than 6.0, and the folding structure is suitable for low subsonic takeoff and landing and for transonic cruise;
the folding configuration is a wave multiplier configuration and is suitable for supersonic cruise.
Further, the duck wing with the fuselage is connected, specifically is through setting up the pivot mechanism of duck wing root with the enhancement frame of fuselage is connected set up pivot hole and pivot on the pivot mechanism, can pass through the pivot is adjusted the sweptback angle of duck wing.
Further, in the process that the pneumatic layout structure of the waverider is changed from the unfolded configuration to the folded configuration, the sweepback angle of the duck wing is increased from the front edge sweepback angle of 15-22 degrees in the unfolded state to the front edge sweepback angle of 70-78 degrees in the folded state, and finally the fact that the rear edge of the duck wing is parallel to the front edge of the main wing is achieved, and the change of the sweepback angle of the duck wing in the folding process is completed;
further, the forward swept wing is connected with the main wing, specifically, the forward swept wing is connected with a forward wing beam of the main wing through a pivot mechanism arranged at a wing root of the forward swept wing, a rotating shaft hole and a rotating shaft are arranged on the pivot mechanism, and a forward swept angle of the forward swept wing can be adjusted through the rotating shaft.
Further, in the process that the wave-rider pneumatic layout structure is changed from the unfolded configuration to the folded configuration, the forward sweep angle of the forward sweep wing is increased from 37-47 degrees in the unfolded state to 85-90 degrees in the folded state, and finally the front edge of the forward sweep wing is attached to the airframe, so that the change of the forward sweep angle of the forward sweep wing in the folding process is completed.
The connection mode of the main wing and the fuselage is as follows: the main wing is hinged with the fuselage reinforcing frame through the front wing beam and the rear wing beam;
connection mode of strake wing and fuselage: the strake wing and the airframe are in a semi-fusion state and are hinged with the airframe frame through a wing rib at the wing root.
A configuration change method for a foldable wave rider pneumatic layout of a supersonic passenger plane adopts a foldable wave rider pneumatic layout structure, and the method can realize mutual transformation of an unfolded configuration and a folded configuration according to the requirement of a flight state so as to realize optimal flight performance under different flight states.
Further, the sweepback angle of the front edge of the canard wing is adjusted to be gradually increased until the rear edge of the canard wing is parallel to the front edge of the main wing, and the sweepback angle of the sweepback wing is adjusted to be gradually increased until the front edge of the sweepback wing is attached to the airplane body; at the moment, the canard wing, the main wing and the fuselage form a wave-rider configuration, namely, the conversion from the unfolding configuration to the folding configuration is completed.
Further, the method for realizing the transformation from the folding configuration to the unfolding configuration comprises the following steps: and adjusting the sweepback angle of the duck wing front edge to gradually decrease until the sweepback angle of the duck wing reaches the range of 15-22 degrees, and adjusting the sweepback angle of the forward swept wing to gradually decrease until the sweepback angle of the forward swept wing reaches the range of 37-47 degrees, thereby completing the conversion from the folding configuration to the unfolding configuration.
The invention has the beneficial technical effects that:
(1) the pneumatic layout of the waverider is at low subsonic velocity, the pneumatic layout of the foldable waverider is in an unfolded configuration, the folded waverider has a larger aspect ratio, and the aerodynamic advantages of the sweepforward wing and the canard wing are fully exerted at low speed, so that the maximum lift coefficient of the low-speed take-off and landing is obviously higher than that of the traditional waverider and can reach more than 1.2, and the folded waverider is suitable for take-off and landing;
(2) when the pneumatic layout of the waverider is transonic, compared with the traditional waverider layout, the unfolding configuration of the pneumatic layout of the foldable waverider has good low-speed pneumatic characteristic, and the stall attack angle can reach more than 16 degrees, so that the transonic cruise is suitable.
(3) The folding type wave rider pneumatic layout is contracted into the traditional wave rider pneumatic layout under the supersonic speed of the wave rider pneumatic layout.
(4) The foldable pneumatic layout of the passenger plane has the advantages of taking off and landing, transonic flight and supersonic cruise, is a civil passenger plane pneumatic layout capable of being used for high-low speed pneumatic characteristic matching design, and can provide reference for supersonic passenger plane design.
(5) The foldable wave-rider aerodynamic layout combines the advantages of the canard wing, the forward swept wing and the wave-rider with large aspect ratio, considers the compromise of high-speed and low-speed aerodynamic characteristics, has unique variable backward swept canard wing and open-close type forward swept wing, and is a novel aerodynamic layout form of a wide-range Mach number (the cruise Mach number is applicable to the range of 0.78-3.0) civil airplane.
Drawings
Fig. 1A is a deployed configuration (perspective view) of the pneumatic layout structure of the foldable waverider in the embodiment of the present invention;
fig. 1B is an expanded configuration (top view) of the pneumatic layout structure of the foldable waverider in the embodiment of the present invention;
fig. 1C is an expanded configuration (front view) of the pneumatic layout structure of the foldable waverider in the embodiment of the present invention;
fig. 1D is an expanded configuration (side view) of the pneumatic layout structure of the foldable waverider in an embodiment of the present invention;
fig. 2A is a folding configuration (perspective view) of the pneumatic layout structure of the foldable waverider in the embodiment of the present invention;
fig. 2B is a folded configuration (top view) of the pneumatic layout structure of the foldable waverider in the embodiment of the present invention;
fig. 2C is a folded configuration (front view) of the pneumatic layout structure of the foldable waverider in an embodiment of the present invention;
fig. 2D is a folded configuration (side view) of the pneumatic layout structure of the foldable waverider in an embodiment of the present invention.
Fig. 3 is a schematic diagram of the foldable waverider aerodynamic layout structure in the embodiment of the invention, which is transformed from the unfolded configuration to the folded configuration.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
On the contrary, the invention is intended to cover alternatives, modifications, equivalents and alternatives which may be included within the spirit and scope of the invention as defined by the appended claims. Furthermore, in the following detailed description of the present invention, certain specific details are set forth in order to provide a better understanding of the present invention. It will be apparent to one skilled in the art that the present invention may be practiced without these specific details.
Example 1
The embodiment provides a foldable type wave rider pneumatic layout structure of a supersonic passenger plane, which comprises a plane body, a main wing, a strake wing, a vertical tail, a forward swept wing positioned on the main wing, a canard wing and a power device, wherein the backward swept angle of the canard wing and the forward swept angle of the forward swept wing can be adjusted; the wave rider pneumatic layout structure can be made to assume a unfolding configuration or a folding configuration (as shown in figures 1A-D and 2A-D) by adjusting the back sweep angle of the duck wing and the front sweep angle of the front sweep wing;
the expansion structure has an aspect ratio of more than 6.0, and is suitable for low subsonic takeoff and landing and transonic cruise;
the folding configuration is a wave multiplier configuration and is suitable for supersonic cruise.
The duck wing with the fuselage is connected, specifically is through setting up the pivot mechanism of duck wing root with the enhancement frame of fuselage is connected set up pivot hole and pivot on the pivot mechanism, can pass through the pivot is adjusted the sweepback angle of duck wing.
In the process that the pneumatic layout structure of the waverider is changed from the unfolded configuration to the folded configuration, the sweepback angle of the duck wing is increased from the front edge sweepback angle of 15-22 degrees in the unfolded state to the front edge sweepback angle of 70-78 degrees in the folded state, and finally the rear edge of the duck wing is parallel to the front edge of the main wing, so that the change of the sweepback angle of the duck wing in the folding process is completed;
the forward swept wing is connected with the main wing, specifically, the forward swept wing is connected with a forward wing beam of the main wing through a pivot mechanism arranged at a wing root of the forward swept wing, a rotating shaft hole and a rotating shaft are arranged on the pivot mechanism, and a forward swept angle of the forward swept wing can be adjusted through the rotating shaft.
In the process of changing the pneumatic layout structure of the waverider from the unfolded configuration to the folded configuration, the forward sweep angle of the forward sweep wing is increased from 37-47 degrees in the unfolded state to 85-90 degrees in the folded state, and finally the front edge of the forward sweep wing is attached to the airframe, so that the change of the forward sweep angle of the forward sweep wing in the folded process is completed.
The connection mode of the main wing and the fuselage is as follows: the main wing is hinged with the fuselage reinforcing frame through the front wing beam and the rear wing beam;
connection mode of strake wing and fuselage: the strake wing and the airframe are in a semi-fusion state and are hinged with the airframe frame through a wing rib at the wing root.
A configuration change method for a foldable wave rider pneumatic layout of a supersonic passenger plane adopts a foldable wave rider pneumatic layout structure, and the method can realize mutual transformation of an unfolded configuration and a folded configuration according to the requirement of a flight state so as to realize optimal flight performance under different flight states.
The sweepback angle of the front edge of the canard wing is adjusted to be gradually increased until the rear edge of the canard wing is parallel to the front edge of the main wing, and the sweepback angle of the sweepback wing is adjusted to be gradually increased until the front edge of the sweepback wing is attached to the airplane body; at the moment, the canard wing, the main wing and the fuselage form a wave-rider configuration, namely, the conversion from the unfolding configuration to the folding configuration is completed.
The method for realizing the transformation from the folding configuration to the unfolding configuration comprises the following steps: and adjusting the sweepback angle of the duck wing leading edge to gradually decrease until the sweepback angle of the duck wing reaches the range of 15-22 degrees, and adjusting the sweepback angle of the forward swept wing to gradually decrease until the sweepback angle of the forward swept wing reaches the range of 37-47 degrees.
Through design, calculation and analysis, when the foldable wave rider aerodynamic layout structure provided by the embodiment is applied to a supersonic passenger plane:
(1) when taking off and landing at low subsonic velocity (H is 0km, and Ma is 0.2), if a foldable waverider unfolding configuration is adopted, the aerodynamic advantages of forward swept wings and duck wings at low speed are fully exerted, the slope and lift resistance of a lift line are greatly improved compared with those of the traditional waverider configuration, the taking off and landing performance can be obviously improved, and the foldable waverider is suitable for taking off and landing;
(2) when the vehicle is cruising at transonic speed (H is 10km, Ma is 0.8), if a foldable waverider body is adopted for unfolding, the aerodynamic characteristics of the foldable waverider body are superior to those of the traditional waverider body, such as the stall attack angle is increased, the lift-drag ratio is high, and the like;
(3) the good longitudinal aerodynamic characteristics fully reflect that the foldable wave rider in the research can obtain the optimal aerodynamic performance in different speed ranges by changing the shapes of the duck wing and the main wing, and has great development potential; the research can provide reference for the layout model selection work of the civil passenger plane flying at the wide-range speed.
The pneumatic layout structure of foldable waverider that this embodiment provided includes expansion configuration and folding configuration, and its main design philosophy concludes: the low subsonic speed takeoff and landing and transonic speed cruising (if any) are in an unfolding configuration, and a small sweepback canard wing and a sweepback wing on a main wing are adopted at the moment so as to improve the lift-drag ratio and improve the take-off and landing performance; the folding type supersonic cruise aircraft is in a folding configuration when in supersonic cruise, at the moment, the sweepforward wings on the main wings rotate around the rotating shafts to change sweepforward angles and cling to two sides of the aircraft body, meanwhile, the small sweepback canard wings also start to change sweepback to rotate so that sweepback angles of the canard wings are increased, finally, the canard wings, the main wings and the aircraft body form a wave-rider configuration, and the folding type supersonic cruise aircraft is very suitable for supersonic cruise. Two typical task configurations for this layout are: a small backward swept canard plus forward swept wing configuration at low subsonic and transonic speeds and a waverider configuration at supersonic speed.
A configuration change method for a foldable wave rider pneumatic layout of a supersonic passenger plane adopts a foldable wave rider pneumatic layout structure, and can realize mutual transformation of an unfolded configuration and a folded configuration (the transformation relation between the two configurations is shown in figure 3) according to the requirements of flight states so as to realize optimal flight performance under different flight states.
The method for realizing the transformation from the unfolded configuration to the folded configuration comprises the following steps: the sweepback angle of the front edge of the canard wing is adjusted to be gradually increased until the rear edge of the canard wing is parallel to the front edge of the main wing, and the sweepback angle of the sweepback wing is adjusted to be gradually increased until the front edge of the sweepback wing is attached to the airplane body; at the moment, the canard wing, the main wing and the fuselage form a wave-rider configuration, namely, the conversion from the unfolding configuration to the folding configuration is completed.
The method for realizing the transformation from the folding configuration to the unfolding configuration comprises the following steps: and adjusting the sweepback angle of the duck wing leading edge to gradually decrease until the sweepback angle of the duck wing reaches the range of 15-22 degrees, and adjusting the sweepback angle of the forward swept wing to gradually decrease until the sweepback angle of the forward swept wing reaches the range of 37-47 degrees.
Claims (6)
1. A foldable wave rider pneumatic layout structure of a supersonic passenger plane comprises a plane body, a main wing, a strake wing, a vertical fin, a forward swept wing positioned on the main wing, a canard wing and a power device, and is characterized in that the backward swept angle of the canard wing and the forward swept angle of the forward swept wing can be adjusted; the pneumatic layout structure of the wave rider can be made to assume a folded configuration or a deployed configuration by adjusting the sweepback angle of the duck wing and the sweepback angle of the sweepback wing;
the aspect ratio of the unfolding structure can reach more than 6.0, and the folding structure is suitable for low subsonic takeoff and landing and for transonic cruise;
the folding configuration is a wave multiplier configuration and is suitable for supersonic cruise;
the duck wing is connected with the fuselage, specifically is connected with the reinforcing frame of the fuselage through a pivot mechanism arranged at the wing root of the duck wing, a rotating shaft hole and a rotating shaft are arranged on the pivot mechanism, and the sweepback angle of the duck wing can be adjusted through the rotating shaft;
in the process that the pneumatic layout structure of the waverider is changed from the unfolded configuration to the folded configuration, the sweepback angle of the duck wing is increased from the front edge sweepback angle of 15-22 degrees in the unfolded state to the front edge sweepback angle of 70-78 degrees in the folded state, and finally the fact that the rear edge of the duck wing is parallel to the front edge of the main wing is achieved, and the change of the sweepback angle of the duck wing in the folding process is completed.
2. The aerodynamic layout structure of a foldable type passenger plane according to claim 1, wherein the forward swept wing is connected to the main wing, specifically, the forward swept wing is connected to a forward wing beam of the main wing through a pivot mechanism disposed at a wing root of the forward swept wing, a rotation shaft hole and a rotation shaft are disposed on the pivot mechanism, and a forward sweep angle of the forward swept wing can be adjusted through the rotation shaft.
3. The pneumatic layout structure of foldable passenger plane of claim 2, wherein during the change from the unfolded configuration to the folded configuration, the forward sweep angle of the forward swept wing increases from 37 ° to 47 ° in the unfolded configuration to 85 ° to 90 ° in the folded configuration, and finally the front edge of the forward swept wing is attached to the plane body, and the change of the forward sweep angle of the forward swept wing during the folding is completed.
4. A method for changing the configuration of a foldable wave rider pneumatic layout of a supersonic passenger plane, which adopts the foldable wave rider pneumatic layout structure as claimed in any one of claims 1-3, and is characterized in that the method can realize mutual transformation of an unfolded configuration and a folded configuration according to the requirement of a flight state so as to realize optimal flight performance under different flight states.
5. The method of claim 4, wherein the transition from the unfolded configuration to the folded configuration is performed by: the sweepback angle of the front edge of the canard wing is adjusted to be gradually increased until the rear edge of the canard wing is parallel to the front edge of the main wing, and the sweepback angle of the sweepback wing is adjusted to be gradually increased until the front edge of the sweepback wing is attached to the airplane body; at the moment, the canard wing, the main wing and the fuselage form a wave-rider configuration, namely, the conversion from the unfolding configuration to the folding configuration is completed.
6. The method of claim 4, wherein the transition from the folded configuration to the unfolded configuration is accomplished by: and adjusting the sweepback angle of the duck wing front edge to gradually decrease until the sweepback angle of the duck wing reaches 15-22 degrees, adjusting the sweepback angle of the forward swept wing to gradually decrease until the sweepback angle of the forward swept wing reaches 37-47 degrees, and finishing the conversion from the folding configuration to the unfolding configuration.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810587782.1A CN108995803B (en) | 2018-06-08 | 2018-06-08 | Foldable wave rider pneumatic layout structure and method of supersonic passenger plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810587782.1A CN108995803B (en) | 2018-06-08 | 2018-06-08 | Foldable wave rider pneumatic layout structure and method of supersonic passenger plane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108995803A CN108995803A (en) | 2018-12-14 |
| CN108995803B true CN108995803B (en) | 2021-03-23 |
Family
ID=64600432
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810587782.1A Active CN108995803B (en) | 2018-06-08 | 2018-06-08 | Foldable wave rider pneumatic layout structure and method of supersonic passenger plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108995803B (en) |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109436290B (en) * | 2018-12-20 | 2023-08-22 | 中国航空工业集团公司沈阳空气动力研究所 | Aircraft airfoil folding mechanism |
| CN110027704A (en) * | 2019-05-14 | 2019-07-19 | 厦门大学 | The fast domain Hypersonic waveriders aircraft of the width of variable-geometry and its design method |
| CN110510149A (en) * | 2019-08-23 | 2019-11-29 | 中国航天空气动力技术研究院 | A kind of Horizontal Take-off and Landing two-stage, which is entered the orbit, reuses sky and space plane layout |
| RU196130U1 (en) * | 2019-11-25 | 2020-02-18 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Supersonic Passenger Aircraft |
| RU196671U1 (en) * | 2019-11-25 | 2020-03-11 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Supersonic Passenger Aircraft |
| RU196128U1 (en) * | 2019-11-25 | 2020-02-18 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Supersonic Civil Aircraft |
| RU196109U1 (en) * | 2019-11-25 | 2020-02-17 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Supersonic Civil Aircraft |
| CN110979682A (en) * | 2019-12-30 | 2020-04-10 | 西北工业大学 | Variable-area duck-type forward-swept wing variant aircraft |
| CN111516871A (en) * | 2020-04-30 | 2020-08-11 | 浙江大学 | Supersonic stealth unmanned aerial vehicle with pneumatic stealth integrated design |
| CN112319813A (en) * | 2020-12-01 | 2021-02-05 | 李勇霖 | Sweepforward duck type flying wing pneumatic layout unmanned aerial vehicle |
| CN112606995A (en) * | 2020-12-24 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Wide-speed-range pneumatic stability control characteristic structure for flying wing layout |
| CN113184165A (en) * | 2021-05-28 | 2021-07-30 | 西北工业大学 | Hypersonic aircraft wing small wing folding mechanism and hypersonic aircraft |
| CN114313253B (en) * | 2022-03-03 | 2022-05-17 | 中国空气动力研究与发展中心计算空气动力研究所 | Aerodynamic layout and design method of high-lift-drag-ratio air-breathing hypersonic aircraft |
| CN114537636B (en) * | 2022-03-25 | 2023-03-24 | 西北工业大学 | Low-sonic-explosion low-resistance pneumatic layout configuration for large supersonic civil aircraft |
| CN117208194B (en) * | 2023-11-09 | 2024-01-09 | 清华大学 | Wing-hair reconfiguration type variant aircraft |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4569493A (en) * | 1983-03-14 | 1986-02-11 | Grumman Aerospace Corporation | Integrated multi-role variable sweep wing aircraft |
| CN85108795A (en) * | 1985-12-19 | 1987-06-24 | 弗克斯兄弟有限公司 | Aircraft grading design and manufacture method |
| DE3710914A1 (en) * | 1987-04-01 | 1988-10-20 | Florian Dipl Ing Windischbauer | Variable-geometry aircraft |
| US6575406B2 (en) * | 2001-01-19 | 2003-06-10 | The Boeing Company | Integrated and/or modular high-speed aircraft |
| US6857599B2 (en) * | 2002-12-30 | 2005-02-22 | Aerion Corporation | Highly swept canard with low sweep wing supersonic aircraft configuration |
| US7866599B2 (en) * | 2006-02-14 | 2011-01-11 | Lockheed-Martin Corporation | Integrated inward turning inlets and nozzles for hypersonic air vehicles |
| US7900865B2 (en) * | 2006-12-19 | 2011-03-08 | The Boeing Company | Airplane configuration |
| CN102267557B (en) * | 2011-04-27 | 2013-12-18 | 中国航天空气动力技术研究院 | Canard forward-sweep telescoping wing aerodynamic configuration with variable span wing area |
| CN103231795A (en) * | 2013-04-12 | 2013-08-07 | 成都飞机设计研究所 | Corporate aircraft engine upper placement and front swept wing duck type layout |
| CN203740126U (en) * | 2014-03-31 | 2014-07-30 | 冯加伟 | Morphing aircraft with wide flight envelope |
-
2018
- 2018-06-08 CN CN201810587782.1A patent/CN108995803B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN108995803A (en) | 2018-12-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108995803B (en) | Foldable wave rider pneumatic layout structure and method of supersonic passenger plane | |
| US6578798B1 (en) | Airlifting surface division | |
| US7475848B2 (en) | Wing employing leading edge flaps and winglets to achieve improved aerodynamic performance | |
| US6729577B2 (en) | Tail-braced wing aircraft and configurations for achieving long supersonic range and low sonic boom | |
| CN111315655B (en) | Assembly of three composite wings for an air, water, land or space vehicle | |
| CN108100212B (en) | Small aspect ratio self-adaptive variant flying wing layout fighter | |
| CN201023653Y (en) | Large aspect ratio sweep forward wings airplane pneumatic distribution | |
| US20070262205A1 (en) | Retractable multiple winglet | |
| CN210235305U (en) | Flying wing type airplane with variable outer wing sweepback angle and tiltable winglet | |
| CN110979682A (en) | Variable-area duck-type forward-swept wing variant aircraft | |
| CN111516871A (en) | Supersonic stealth unmanned aerial vehicle with pneumatic stealth integrated design | |
| US20050116116A1 (en) | Wing employing leading edge flaps and winglets to achieve improved aerodynamic performance | |
| US6935592B2 (en) | Aircraft lift device for low sonic boom | |
| CN112660381A (en) | Laminar flow control technology-based wing body fusion layout passenger plane layout method | |
| CN109436290B (en) | Aircraft airfoil folding mechanism | |
| CN110844071A (en) | Unmanned aerial vehicle capable of long-endurance wide-speed-range high-mobility cruise flight | |
| US3493197A (en) | Translating horizontal tail | |
| CN110775296A (en) | Design method for pressure center backward movement of reusable aerospace vehicle | |
| CN217598818U (en) | Pneumatic layout of unmanned aerial vehicle | |
| CN111017190A (en) | Large-scale civil passenger plane of integration overall arrangement | |
| CN115924104A (en) | Aircraft aerodynamic design method based on multi-section telescopic wing | |
| CN212423467U (en) | Unmanned aerial vehicle capable of long-endurance wide-speed-range high-mobility cruise flight | |
| EP0221204A1 (en) | Supersonic airplane | |
| CN209454975U (en) | A kind of aircraft aerofoil fold mechanism | |
| US20090173838A1 (en) | Narrow Wing System for Airplanes |
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 |