CN210235306U - A flying wing aircraft with variable airfoil - Google Patents
A flying wing aircraft with variable airfoil Download PDFInfo
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- CN210235306U CN210235306U CN201920744686.3U CN201920744686U CN210235306U CN 210235306 U CN210235306 U CN 210235306U CN 201920744686 U CN201920744686 U CN 201920744686U CN 210235306 U CN210235306 U CN 210235306U
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- 230000009286 beneficial effect Effects 0.000 abstract description 3
- 230000003044 adaptive effect Effects 0.000 description 1
- 230000003416 augmentation Effects 0.000 description 1
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- 230000000694 effects Effects 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
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- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The utility model discloses a changeable all-wing aircraft of wing section, all-wing aircraft includes the inner wing, the outer wing of setting in the inner wing both sides, the aileron at inner wing rear is set up, the outer wing is by preceding rib, well rib and back rib three-section are constituteed, well rib is connected with the inner wing through first connecting axle and second connecting axle, preceding rib can be for the first connecting axle of the rotatory connection of well rib, back rib can be for the rotatory second connecting axle of connecting of well rib, rib is rotatory around first connecting axle before the first drive arrangement control, rib is rotatory around the second connecting axle after the second drive arrangement control. The utility model discloses following beneficial effect has: the change of the aerodynamic shape of the flying wing type aircraft under different conditions is realized, the flying cost is reduced, the flying performance is improved, and a new idea is provided for the development of the future flying wing type aircraft.
Description
Technical Field
The utility model belongs to aircraft design field, concretely relates to changeable all-wing aircraft formula aircraft of wing section.
Background
The development of electronic technology and computer control technology, the wire control stability augmentation technology and the static stability relaxation technology are gradually mature, and conditions are provided for the development of the flying wing type pneumatic layout airplane. The flying wing type pneumatic layout has excellent lift resistance characteristics, the technical development enables the flying wing type pneumatic layout to overcome the defects in the aspect of control, the flying wing type layout becomes one of the pneumatic layouts which are mainly researched by various countries, and even the tailless flying wing layout is proposed to be the optimal pneumatic layout form of the unmanned fighter.
At home and abroad, not only the Nosrop Getroman B-2 flying wing type invisible strategy bomber has been practically applied, but also the research on the aerodynamic characteristics of flying wing type layout aircrafts is continuously carried out. With the development of economy, the comprehensive requirements of people on flight tasks are continuously improved, and the aircraft can stably execute various tasks under the condition of severe change and always keep good flight performance, which is a new requirement of people on the aircraft and is a great trend of the development of flying wing type aircrafts.
SUMMERY OF THE UTILITY MODEL
In view of the above-mentioned technical problem, the utility model provides a changeable all-wing aircraft of wing section aims at developing the changeable all-wing aircraft of wing section, through the realization way of studying variant aircraft design, combines all-wing aircraft formula overall arrangement, provides a variant all-wing aircraft that changes the wing section at the flight in-process.
In order to solve the technical problem, the technical scheme of the utility model as follows:
the utility model provides a changeable all-wing aircraft of wing section, all-wing aircraft includes the inner wing, sets up the outer wing in inner wing both sides, sets up the aileron at inner wing rear, the outer wing comprises preceding rib, middle wing rib and back rib three-section, the middle wing rib is connected with the inner wing through first connecting axle and second connecting axle, preceding rib can be for the rotatory first connecting axle of connection of middle wing rib, back rib can be for the rotatory second connecting axle of connection of middle wing rib, and first drive arrangement control preceding rib is rotatory around first connecting axle, and second drive arrangement control back rib is rotatory around the second connecting axle.
Further, first drive arrangement includes preceding pull rod, preceding branch and front drive hydraulic cylinder, preceding pull rod one end is articulated with preceding rib, the one end and the well rib of preceding branch are articulated, preceding drive hydraulic cylinder jar cylinder end is articulated with well rib, and the front strut is located between preceding pull rod and the preceding drive hydraulic cylinder, and the other end of preceding pull rod, the other end of preceding branch and the three tip of the tailpiece of the piston rod of the preceding drive hydraulic cylinder are articulated at the same point.
Further, the second drive arrangement includes back pull rod, back branch and back drive hydraulic cylinder, back pull rod one end is articulated with back wing rib, the one end and the middle wing rib of back branch are articulated, back drive hydraulic cylinder tube end is articulated with middle wing rib, and the back branch is located between back pull rod and the back drive hydraulic cylinder, and the other end of back pull rod, the other end of back branch and the three tip in the tailpiece of the piston rod of back drive hydraulic cylinder are articulated at the same point.
Further, the first driving device and the second driving device are provided in plurality.
Further, the first driving device and the second driving device are provided with 3.
Further, the first driving device and the second driving device are connected with a hydraulic control system.
Compared with the prior art, the utility model discloses following beneficial effect has:
the utility model has the advantages that: based on the morphing aircraft and the self-adaptive technology, the excellent aerodynamic characteristics of the flying wing aircraft are considered. The change of the aerodynamic shape of the flying wing type aircraft under different conditions is realized, the flying cost is reduced, the flying performance is improved, and a new idea is provided for the development of the future flying wing type aircraft.
Drawings
FIG. 1 is a top view of a flying wing aircraft of the present invention;
FIG. 2 is a side view of the outer wing of the present invention;
FIG. 3 is a top view of the outer wing of the present invention;
fig. 4 is a schematic view of an outer wing structure according to an embodiment of the present invention;
FIG. 5 is a schematic diagram of an embodiment of the present invention;
FIG. 6 is a schematic view of a third outer wing structure of the embodiment of the present invention;
FIG. 7 is a schematic view of a structure of four outer wings according to an embodiment of the present invention;
in the figure, an inner wing 1, an outer wing 2, an aileron 3, a front wing rib 2.1, a middle wing rib 2.2, a rear wing rib 2.3, a first connecting shaft 2.4, a second connecting shaft 2.5, a front pull rod 2.6, a front pull rod 2.7, a front driving hydraulic cylinder 2.8, a rear pull rod 2.9, a rear pull rod 2.10 and a rear driving hydraulic cylinder 2.11.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "axial", "circumferential", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
In the present invention, unless otherwise expressly stated or limited, the terms "disposed," "mounted," "connected," and "fixed" are to be construed broadly, e.g., as meaning either a fixed connection or a removable connection; may be a mechanical connection; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature.
As shown in fig. 1, the flying wing aircraft of the present invention includes an inner wing 1, outer wings 2 disposed on both sides of the inner wing 1, and ailerons 3 disposed behind the inner wing 1.
As shown in fig. 2, based on the development of the adaptive technology of the morphing aircraft, the novel flying wing aircraft with variable wing profiles mainly has a structure of a segmented wing rib and a rotatable connecting mechanism, and the wing profiles are changed by the segmented rotation of the wing rib, so that the requirements of adopting different wing profiles under different environment and flight mission requirements are met.
Specifically, the outer wing 2 is composed of three sections, namely a front wing rib 2.1, a middle wing rib 2.2 and a rear wing rib 2.3, the middle wing rib 2.2 is connected with the inner wing 1 through a first connecting shaft 2.4 and a second connecting shaft 2.5, the front wing rib 2.1 can be connected with the first connecting shaft 2.4 in a rotating mode relative to the middle wing rib 2.2, the rear wing rib 2.3 can be connected with the second connecting shaft 2.5 in a rotating mode relative to the middle wing rib 2.3, the first driving device controls the front wing rib 2.1 to rotate around the first connecting shaft 2.4, and the second driving device controls the rear wing rib 2.3 to rotate around the second connecting shaft 2.5.
Meanwhile, as further shown in fig. 2, the first driving device includes a front pull rod 2.6, a front support rod 2.7 and a front driving hydraulic cylinder 2.8, one end of the front pull rod 2.6 is hinged to the front wing rib 2.1, one end of the front support rod 2.7 is hinged to the middle wing rib 2.2, a cylinder end of the front driving hydraulic cylinder 2.8 is hinged to the middle wing rib 2.2, the front support rod 2.7 is located between the front pull rod 2.6 and the front driving hydraulic cylinder 2.8, and the other end of the front pull rod 2.6, the other end of the front support rod 2.7 and a piston rod end of the front driving hydraulic cylinder 2.8 are hinged at the same point; the second driving device comprises a rear pull rod 2.9, a rear support rod 2.10 and a rear driving hydraulic cylinder 2.11, one end of the rear pull rod 2.9 is hinged to the rear wing rib 2.3, one end of the rear support rod 2.7 is hinged to the middle wing rib 2.2, the cylinder barrel end of the rear driving hydraulic cylinder 2.11 is hinged to the middle wing rib 2.2, the rear support rod 2.10 is located between the rear pull rod 2.9 and the rear driving hydraulic cylinder 2.11, and the other end of the rear pull rod 2.9, the other end of the rear support rod 2.10 and three end portions of the piston rod end of the rear driving hydraulic cylinder 2.11 are hinged at the same point.
As shown in fig. 3, the first driving device and the second driving device are provided in plural numbers, preferably 3 numbers. The first driving device and the second driving device are connected with a hydraulic control system.
Figure 2 shows a schematic view of the front rib 2.1, the middle rib 2.2 and the rear rib 2.3 in an unrotated position, i.e. in situ,
fig. 4 shows that the front rib 2.1 is bent downward (rotated downward), the middle rib 2.2 is at the original position, and the rear rib 2.3 is at the original position, and has better performance at a lower speed, so that the requirements of taking off and landing can be met.
Fig. 5 shows the front rib 2.1 in the original position, the middle rib 2.2 in the original position, and the rear rib 2.3 bent upward (rotated upward), which can increase the stall angle of attack and be used for air combat and maneuver in the airplane.
Fig. 6 shows that the front rib 2.1 is bent upward (rotated upward), the middle rib 2.2 is at the original position, and the rear rib 2.3 is at the original position, and the drag coefficient is greatly reduced when the reynolds number is large, and the wing profile is suitable for high-speed flight.
Fig. 7 shows that the front rib 2.1 is in the original position, the middle rib 2.2 is in the original position, and the rear rib 2.3 is bent downward (rotated downward), so that the effect of increasing the lift of the flap can be achieved, and the wing is suitable for cruising.
And according to fig. 4, 5, 6, 7, a free rotation combination of the leading rib 2.1, the middle rib 2.2 and the trailing rib 2.3 can be made in combination with the actual needs.
Compared with the prior art, the utility model discloses following beneficial effect has:
the utility model has the advantages that: based on the morphing aircraft and the self-adaptive technology, the excellent aerodynamic characteristics of the flying wing aircraft are considered. The change of the aerodynamic shape of the flying wing type aircraft under different conditions is realized, the flying cost is reduced, the flying performance is improved, and a new idea is provided for the development of the future flying wing type aircraft.
The above description is only for the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention should be covered by the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (6)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920744686.3U CN210235306U (en) | 2019-05-23 | 2019-05-23 | A flying wing aircraft with variable airfoil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920744686.3U CN210235306U (en) | 2019-05-23 | 2019-05-23 | A flying wing aircraft with variable airfoil |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210235306U true CN210235306U (en) | 2020-04-03 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920744686.3U Expired - Fee Related CN210235306U (en) | 2019-05-23 | 2019-05-23 | A flying wing aircraft with variable airfoil |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210235306U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110182354A (en) * | 2019-05-23 | 2019-08-30 | 厦门大学 | A kind of flying wing that aerofoil profile is variable |
| WO2022050928A1 (en) * | 2020-09-03 | 2022-03-10 | Частное Акционерное Общество "Фэд" | Wing for a vertical takeoff and landing aircraft, and aircraft having such a wing |
-
2019
- 2019-05-23 CN CN201920744686.3U patent/CN210235306U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110182354A (en) * | 2019-05-23 | 2019-08-30 | 厦门大学 | A kind of flying wing that aerofoil profile is variable |
| CN110182354B (en) * | 2019-05-23 | 2024-07-30 | 厦门大学 | Wing type variable flying wing type airplane |
| WO2022050928A1 (en) * | 2020-09-03 | 2022-03-10 | Частное Акционерное Общество "Фэд" | Wing for a vertical takeoff and landing aircraft, and aircraft having such a wing |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200403 Termination date: 20210523 |