CN110920862B - Aircraft and body flap thereof - Google Patents
Aircraft and body flap thereof Download PDFInfo
- Publication number
- CN110920862B CN110920862B CN201911169568.5A CN201911169568A CN110920862B CN 110920862 B CN110920862 B CN 110920862B CN 201911169568 A CN201911169568 A CN 201911169568A CN 110920862 B CN110920862 B CN 110920862B
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- opening
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- plate
- body flap
- flap
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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Abstract
The embodiment of the application relates to the technical field of aerospace, in particular to an aircraft and a body flap thereof. A body flap for an aircraft comprises a plate-shaped body, one side of which is provided with an opening. The body flap can reduce the jet flow interference through the opening arranged on the plate-shaped body, so that the pitching trim characteristic of the aircraft during the operation of the engine is improved.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to an aircraft and a body flap thereof.
Background
The existing plane-symmetric aircraft with a main engine is different from the existing traditional axisymmetric aircraft such as rockets, missiles and the like in appearance, the aerodynamic layout of the existing plane-symmetric aircraft can generate larger lift force, and the aerodynamic control surface-body flap is usually arranged on the tail end face with the longest force arm due to the requirement of pitching trim control.
Because the jet pipe of the plane-symmetric aircraft is short, most of the body flap is positioned right below the outlet of the jet pipe, so that the body flap is close to the jet pipe of the main engine, and jet flow obviously interferes with the body flap. Although the disturbance force generated by the jet flow of the engine is far smaller than the thrust of the engine, the action direction of the disturbance force is vertical to the body flap, and the force arm is obviously longer, so that the pitching moment generated by the jet flow disturbance is not small relative to the pitching moment generated by the thrust of the engine, and a large adverse effect is caused on the control of an aircraft.
The pneumatic specialty starts from a jet flow interference flow field mechanism, and jet flow interference borne by the body flap is obviously reduced by changing the appearance of the body flap and dredging jet flow. The concept and scheme about the design of the body flap are not seen at home and abroad.
Disclosure of Invention
The embodiment of the application provides an aircraft and a body flap thereof, wherein the body flap can reduce jet flow interference by changing the shape, and can improve the pitching trim characteristic of the aircraft during the operation of an engine.
According to a first aspect of embodiments of the present application, there is provided a body flap for an aircraft, comprising a plate-like body, one side of which is provided with an opening.
Preferably, the opening is trapezoidal or trumpet-shaped, and the width of the opening gradually increases from the center of the plate-shaped body to the side provided with the opening.
Preferably, the waists forming the opening are each constituted by a straight or curved edge.
Preferably, the plate-shaped body has a plane-symmetrical structure.
Preferably, the plate-shaped body has a rectangular plate-shaped structure.
In addition, according to a second aspect of the embodiment of the application, an aircraft is further provided, wherein the aircraft comprises an engine and further comprises any body flap provided by the technical scheme; the opening of the body flap corresponds to the position of the corresponding spray pipe outlet of the engine, and the opening is used for dredging the jet flow of the engine.
Preferably, the aircraft is a plane-symmetric aircraft.
The aircraft and the body flap thereof provided in the embodiment of the application have the following beneficial effects:
the body flap is arranged on the plate-shaped body of the body flap, so when the body flap is arranged on the aircraft, the body flap can be arranged on the rear side of a spray pipe of an engine of the aircraft, the opening of the body flap is opposite to the outlet position of the spray pipe, fluid sprayed out of the spray pipe can directly pass through the opening, jet flow interference of jet flow on the body flap is eliminated or reduced, acting force of the jet flow on the body flap is reduced, and therefore the body flap can reduce the received jet flow interference through the opening arranged on the plate-shaped body, and the pitching trim characteristic of the aircraft during the operation of the engine is improved.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the application and together with the description serve to explain the application and not to limit the application. In the drawings:
fig. 1 is a schematic perspective view of a body flap for an aircraft according to an embodiment of the present disclosure.
Reference numerals:
1-body flaps; 11-a plate-like body; 12-an opening; 111-a first side; 112-a second side edge; 113-a third side; 114-a fourth side; 115-top edge; 116-waist.
Detailed Description
In order to make the technical solutions and advantages of the embodiments of the present application more apparent, the following further detailed description of the exemplary embodiments of the present application with reference to the accompanying drawings makes it clear that the described embodiments are only a part of the embodiments of the present application, and are not exhaustive of all embodiments. It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict.
The embodiment of the application provides an aircraft and a body flap for the aircraft, and the aircraft can be a plane-symmetric aircraft and also can be an axisymmetric aircraft. The aircraft can be any aircraft with engines, such as rockets, missiles, airplanes, space shuttles and the like.
Example one
As shown in the structure of fig. 1, the embodiment of the present application provides a body flap 1 for an aircraft, and the body flap 1 includes a plate-shaped body 11, and an opening 12 is provided at one side of the plate-shaped body 11. As shown in the structure of fig. 1, the plate-shaped body 11 is a rectangular plate-shaped structure provided with an opening 12, and the plate-shaped body 11 has a first side 111 and a second side 112 which are oppositely arranged, and a third side 113 and a fourth side 114 which are oppositely arranged; the opening 12 is disposed on the second side 112. When the body flap 1 is manufactured, the body flap 1 can be directly processed into the shape of the body flap 1 in fig. 1, or a rectangular plate can be prepared first, and then a piece of the rectangular plate is cut to form the opening 12.
Since the opening 12 is provided on the plate-shaped body 11 of the body flap 1, when the body flap 1 is mounted on an aircraft, the body flap 1 can be mounted on the rear side of a nozzle of an engine of the aircraft, and the opening 12 of the body flap 1 is opposite to the outlet position of the nozzle, so that fluid ejected from the nozzle can directly pass through the opening 12, thereby eliminating or reducing jet flow interference of jet flow on the body flap 1, and reducing the acting force of the jet flow on the body flap 1, therefore, the body flap 1 can reduce the jet flow interference received through the opening 12 provided on the plate-shaped body 11, and thus improving the pitch trim characteristic of the aircraft during the operation of the engine.
In a specific embodiment, as shown in the structure of fig. 1, the opening 12 may be trapezoidal or trumpet-shaped, and the width H of the opening 12 gradually increases from the center of the plate-shaped body 11 to the side where the opening 12 is disposed. As shown in the structure of fig. 1, the opening 12 is substantially trapezoidal, and the top side 115 of the trapezoid is located at the center of the plate-shaped body 11, the bottom side of the trapezoid coincides with the second side 112, and the width H of the opening 12 gradually increases from the center of the plate-shaped body 11 to the side where the opening 12 is located, that is, the width H of the opening 12 gradually increases from the first side 111 of the plate-shaped body 11 to the second side 112; the waist 116 of the trapezoid can be a straight side or an arc side formed by arcs, and as shown in the structure of fig. 1, the waist 116 of the trapezoid forming the opening 12 is formed by the arc side.
Since the airflow gradually diverges during the injection process, the width H of the opening 12 in the body flap 1 gradually increases from the center of the plate-like body 11 toward the second side 112 on which the opening 12 is provided, so that the contact and interference between the injected airflow and the plate-like body 11 can be reduced, and the force and jet flow interference of the airflow ejected from the engine nozzle on the body flap 1 can be further reduced.
In another specific embodiment, the opening 12 may be arc-shaped, and the width H of the opening 12 gradually increases from the center of the plate-shaped body 11 to the side where the opening 12 is disposed. The shape of the opening 12 can be arc-shaped structures such as a semicircle, an ellipse, a spherical crown and the like, and the opening 12 adopts the arc-shaped structure, so that the phenomenon of stress concentration of the plate-shaped body 11 can be avoided, and the service life of the body flap 1 and the flight safety of the aircraft can be improved.
As shown in the structure of fig. 1, the plate-like body 11 may be a plane-symmetric structure, such as: a rectangular plate-like structure; the shape of the opening 12 is also formed in an axisymmetric pattern, and the shape of the opening 12 may be a trapezoidal, semicircular, or other surface symmetric shape.
Example two
The embodiment of the application also provides an aircraft, which can be a plane-symmetric aircraft and comprises an engine and any one of the body flaps 1 provided by the embodiments; the opening 12 of the body flap 1 corresponds to the position of the corresponding nozzle outlet of the engine, and the opening 12 is used for channeling the jet flow of the engine.
Because the aircraft is provided with the body flap 1, and the opening 12 of the body flap 1 corresponds to the position of the outlet of the nozzle of the engine, the jet flow of the engine can directly pass through the opening 12, so that the airflow jetted by the engine is prevented from directly acting on the body flap 1, the jet flow interference of the engine on the body flap 1 can be reduced, and the pitch trim characteristic of the aircraft during the operation of the engine is improved.
While the preferred embodiments of the present application have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all alterations and modifications as fall within the scope of the application.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (3)
1. A body flap for an aircraft, characterized by comprising a plate-like body, one side of which is provided with an opening;
wherein, when the body flap is installed on the aircraft, the body flap is installed at the rear side of a spray pipe of an engine of the aircraft, and the opening of the body flap is opposite to the outlet position of the spray pipe;
the plate-shaped body is of a plane-symmetric structure, the shape of the opening is an axisymmetric figure, and the width of the opening is gradually increased from the center of the plate-shaped body to the side edge provided with the opening;
the plate-shaped body is of a rectangular plate-shaped structure provided with an opening, and the plate-shaped body is provided with a first side edge and a second side edge which are oppositely arranged, and a third side edge and a fourth side edge which are oppositely arranged; the opening is arranged on the second side edge;
the opening is trapezoidal, the top edge of the trapezoid is positioned at the center of the plate-shaped body, the bottom edge of the trapezoid is superposed with the second side edge, and the width H of the opening is gradually increased from the center of the plate-shaped body to the side edge provided with the opening;
the waist of the trapezoid is an arc-shaped edge formed by an arc line.
2. An aircraft comprising an engine, further comprising the body flap of claim 1; the opening of the body flap corresponds to the position of the corresponding spray pipe outlet of the engine, and the opening is used for dredging the jet flow of the engine.
3. The aircraft of claim 2, wherein the aircraft is a plane-symmetric aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911169568.5A CN110920862B (en) | 2019-11-26 | 2019-11-26 | Aircraft and body flap thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911169568.5A CN110920862B (en) | 2019-11-26 | 2019-11-26 | Aircraft and body flap thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110920862A CN110920862A (en) | 2020-03-27 |
| CN110920862B true CN110920862B (en) | 2022-04-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911169568.5A Active CN110920862B (en) | 2019-11-26 | 2019-11-26 | Aircraft and body flap thereof |
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| Country | Link |
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| CN (1) | CN110920862B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR695584A (en) * | 1929-05-17 | 1930-12-18 | Improvements to surfaces subject to air resistance | |
| CN103158856A (en) * | 2013-04-12 | 2013-06-19 | 北京航空航天大学 | Light airscrew flying wing aircraft capable of taking off and landing in short distance |
| CN105035306A (en) * | 2015-08-14 | 2015-11-11 | 龙川 | Jet-propelled flap lift augmentation joined wing system and aircraft thereof |
| CN205168899U (en) * | 2015-11-05 | 2016-04-20 | 北京淳一航空科技有限公司 | Two vertical fin unmanned aerial vehicle of stationary vane |
| CA2830352C (en) * | 2011-03-30 | 2016-09-27 | The Society Of Japanese Aerospace Companies | High-lift device of flight vehicle |
| CN109677608A (en) * | 2018-11-27 | 2019-04-26 | 西华大学 | Tailless flying wing coupling power aircraft |
-
2019
- 2019-11-26 CN CN201911169568.5A patent/CN110920862B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR695584A (en) * | 1929-05-17 | 1930-12-18 | Improvements to surfaces subject to air resistance | |
| CA2830352C (en) * | 2011-03-30 | 2016-09-27 | The Society Of Japanese Aerospace Companies | High-lift device of flight vehicle |
| CN103158856A (en) * | 2013-04-12 | 2013-06-19 | 北京航空航天大学 | Light airscrew flying wing aircraft capable of taking off and landing in short distance |
| CN105035306A (en) * | 2015-08-14 | 2015-11-11 | 龙川 | Jet-propelled flap lift augmentation joined wing system and aircraft thereof |
| CN205168899U (en) * | 2015-11-05 | 2016-04-20 | 北京淳一航空科技有限公司 | Two vertical fin unmanned aerial vehicle of stationary vane |
| CN109677608A (en) * | 2018-11-27 | 2019-04-26 | 西华大学 | Tailless flying wing coupling power aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110920862A (en) | 2020-03-27 |
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