CN113911318A - Posture self-adaptive adjustment annular lift wing device for pneumatic suspension train - Google Patents
Posture self-adaptive adjustment annular lift wing device for pneumatic suspension train Download PDFInfo
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- CN113911318A CN113911318A CN202111108189.2A CN202111108189A CN113911318A CN 113911318 A CN113911318 A CN 113911318A CN 202111108189 A CN202111108189 A CN 202111108189A CN 113911318 A CN113911318 A CN 113911318A
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- Prior art keywords
- wing
- suspension train
- ground effect
- pneumatic suspension
- annular
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- 239000000725 suspension Substances 0.000 title abstract description 43
- 230000000694 effects Effects 0.000 abstract description 42
- 238000005339 levitation Methods 0.000 abstract 1
- 230000001965 increasing effect Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 230000003044 adaptive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003028 elevating effect Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
- B64C9/18—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by single flaps
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C35/00—Flying-boats; Seaplanes
- B64C35/006—Flying-boats; Seaplanes with lift generating devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
- B64C39/062—Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
本发明公开了一种用于气动悬浮列车的姿态自适应调节环形升力翼装置，涉及气动悬浮列车姿态自适应调节技术领域。本发明包括气动悬浮列车主体，气动悬浮列车主体的外部装配有用于调整气动悬浮列车主体姿态的环形升力机构。本发明通过对结构的设计，使得气动悬浮列车主体能够保持稳定姿态行驶，且通过地效翼与地效增升翼配合，能够在气动悬浮列车主体启动低速阶段提供较大的升力以及悬浮时减少与地面的摩擦，能够防止机翼因攻角过大导致失速，且通过对装置的侧翼方向舵、地效增升翼和上层襟翼的调节，能够在高速行驶时保证气动悬浮列车主体稳定性，在低速行驶时保证气动悬浮列车主体的灵活性。
The invention discloses an attitude self-adaptive adjustment annular lift wing device for aerodynamic suspension trains, and relates to the technical field of attitude self-adaptive adjustment of aerodynamic suspension trains. The present invention includes a main body of the pneumatic suspension train, and the outside of the main body of the aerodynamic suspension train is equipped with an annular lift mechanism for adjusting the posture of the main body of the aerodynamic suspension train. Through the design of the structure, the present invention enables the main body of the aerodynamic suspension train to maintain a stable attitude and travel, and through the cooperation of the ground effect wings and the ground effect booster wings, it can provide a large lift force when the main body of the aerodynamic suspension train starts at a low speed and reduce the amount of levitation. The friction with the ground can prevent the wing from stalling due to the excessive angle of attack, and through the adjustment of the side rudder, ground effect booster and upper flap of the device, the stability of the main body of the aerodynamic suspension train can be ensured at high speed. Ensure the flexibility of the main body of the pneumatic suspension train at low speeds.
Description
Technical Field
The invention belongs to the technical field of self-adaptive adjustment of the attitude of a pneumatic suspension train, and particularly relates to an attitude self-adaptive adjustment annular lift wing device for the pneumatic suspension train.
Background
The ground effect is a fluid mechanical effect which can reduce the induced resistance of the aircraft and can obtain a higher lift-drag ratio than the aerial flight, when the moving aircraft falls to a position close to the ground (or water surface), the up-down pressure difference of the whole aircraft body is increased, the lift force can be increased suddenly, the ground effect can be applied to multiple aspects of the ground effect aircraft and the like, compared with the traditional aircraft, the ground effect aircraft, especially a pneumatic suspension train has the advantages of high lift force, low resistance, low energy consumption and the like due to the multi-wall surface constraint, but the pneumatic suspension train runs in a multi-wall track, the traditional wings generate lift moment, the posture is difficult to finely adjust, the space lift force cannot be turned and suspended, and the resistance required in the landing stage is larger.
Disclosure of Invention
The invention aims to provide an attitude self-adaptive adjustment annular lift wing device for a pneumatic suspension train, which aims to solve the existing problems that: because the pneumatic suspension train runs in the multi-wall surface track, the head-up moment is generated when the traditional wing is adopted, the posture is difficult to finely adjust, the space steering and suspension can not be carried out, and the lift resistance required in the landing stage is larger.
In order to solve the technical problems, the invention is realized by the following technical scheme: the annular lifting wing device for self-adaptive posture adjustment of the pneumatic suspension train comprises a pneumatic suspension train body, wherein an annular lifting mechanism for adjusting the posture of the pneumatic suspension train body is assembled outside the pneumatic suspension train body.
Further, annular elevating mechanism is including ground effect wing, upper strata wing, wing end flank, flank rudder, ground effect lift-increasing wing and upper strata wing flap, the lower part at pneumatic suspension train main part both ends is installed to the ground effect wing, the upper strata wing is installed on the upper portion at pneumatic suspension train main part both ends, and is located same end ground effect wing and upper strata wing are the setting of staggering, the upper strata wing is located the position that relative ground effect wing leaned on the back, the wing end flank is fixed in the one end of ground effect wing and upper strata wing, the upper strata wing flap is installed at about middle exhibition long position of upper strata wing trailing edge, ground effect lift-increasing wing is installed at about middle exhibition long position of ground effect wing trailing edge, the flank rudder is installed at about middle exhibition long position of wing end flank trailing edge.
Furthermore, the ground effect wing, the upper layer wing and the wing end side wing form an annular wing, and the annular wing integrally inclines backwards.
Further, the annular wing ground clearance is a ground effect height interval.
Further, the annular wing is in an inverted trapezoid shape with a wide upper part and a narrow lower part.
The invention has the following beneficial effects:
1. according to the invention, through the design of the structure, the fine adjustment can be carried out through the upper-layer flap, the posture of the pneumatic suspension train main body is finely adjusted, and the pneumatic suspension train main body can keep stable posture for running.
2. According to the invention, the ground effect wings are matched with the ground effect lift-increasing wings, so that a larger lift force can be provided at the low-speed starting stage of the pneumatic suspension train body, the friction with the ground can be reduced during suspension, and the wings can be prevented from stalling due to an overlarge attack angle.
3. According to the invention, through the design of the structure and the adjustment of the wing rudder, the ground effect lift-increasing wing and the upper layer wing flap of the device, the stability of the main body of the pneumatic suspension train can be ensured during high-speed running, and the flexibility of the main body of the pneumatic suspension train can be ensured during low-speed running.
4. According to the invention, through the design of the structure, the lateral wing rudder, the ground effect lift-increasing wing and the upper layer wing flap are controlled through the sensor data, so that the control with higher degree of freedom can be realized, and the maneuvering with higher flexibility can be realized.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a side view of the present invention;
FIG. 3 is a top view of the present invention;
fig. 4 is a front view of the present invention.
In the drawings, the components represented by the respective reference numerals are listed below:
1. a pneumatically levitated train body; 2. a ground effect wing; 3. an upper layer wing; 4. a wing tip flank; 5. a wing rudder; 6. ground effect lift increasing wings; 7. an upper flap.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-4, the invention is an attitude adaptive adjustment annular lift wing device for a pneumatic suspension train, comprising a pneumatic suspension train body 1, wherein an annular lift mechanism for adjusting the attitude of the pneumatic suspension train body 1 is assembled outside the pneumatic suspension train body 1;
specifically, the annular lifting mechanism comprises a ground effect wing 2, an upper layer wing 3, a wing end side wing 4, a side wing rudder 5, a ground effect lift-increasing wing 6 and an upper layer wing flap 7, wherein the ground effect wing 2 is installed at the lower parts of two ends of a pneumatic suspension train body 1, the ground effect wing 2 can provide larger lifting force in the low-speed starting stage of the pneumatic suspension train and reduce friction with the ground when the pneumatic suspension train is suspended, the upper layer wing 3 is installed at the upper parts of two ends of the pneumatic suspension train body 1, the ground effect wing 2 and the upper layer wing 3 which are located at the same end are arranged in a staggered mode, the upper layer wing 3 is located at the position behind the ground effect wing 2, and the wing end side wing 4 is fixed at one end of the ground effect wing 2 and one end of the upper layer wing 3;
furthermore, the ground effect wing 2, the upper layer wing 3 and the wing end side wing 4 form an annular wing, the annular wing integrally inclines backwards, the ground clearance of the annular wing is a ground effect height interval, and the annular wing is in an inverted ladder shape with a wide upper part and a narrow lower part;
further, the upper layer flap 7 is installed at the position of the middle span length of the rear edge of the upper layer wing 3, the basic utility of the upper layer flap 7 is to adjust the difference of front-back left-right lift force in flight, the ground effect lift wing 6 is installed at the position of the middle span length of the rear edge of the ground effect wing 2, the ground effect lift wing 6 is to increase the lift force in flight, the lateral wing rudder 5 is installed at the position of the middle span length of the rear edge of the wing end lateral wing 4, the lateral wing rudder 5 plays a role in changing the traveling direction, and the upper layer flap 7, the ground effect lift wing 6 and the lateral wing rudder 5 are controlled by sensors, so that the control with higher degree of freedom can be realized and the maneuvering with higher flexibility can be realized.
One specific application of this embodiment is: when the device is in running, the upper layer flap 7 can be finely adjusted, because the upper layer flap 7 is higher in installation position and smaller actions of the upper layer flap 7 only can generate smaller lift force changes outside a ground effect height interval, the attitude of the pneumatic suspension train main body 1 can be effectively controlled without generating excessive disturbance on a flow field around the pneumatic suspension train main body 1, further, the pneumatic suspension train main body 1 can be finely adjusted, the stable running attitude of the pneumatic suspension train main body 1 is ensured, in addition, in a low-speed starting stage, the ground effect lift-increasing wing 6 can be downwards deflected, the ground clearance between the ground effect lift-increasing wing 6 and the ground is reduced, the ground effect is sensitive to the ground clearance, a smaller deflection angle can obtain larger lift force increase, in suspension, the friction with the ground can be reduced, and the air resistance is small in high-speed running, and when the pitching moment is large, the front and rear lifting forces can be balanced by adjusting the deflection angle of the ground effect lift-increasing wing 6, the wing is effectively prevented from stalling due to overlarge attack angle, and the device can rotate at different angles by controlling the wing rudder 5 when turning, so that the device is controlled to turn.
In the description herein, references to the description of "one embodiment," "an example," "a specific example" or the like are intended to mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The preferred embodiments of the invention disclosed above are intended to be illustrative only. The preferred embodiments are not intended to be exhaustive or to limit the invention to the precise embodiments disclosed. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best utilize the invention. The invention is limited only by the claims and their full scope and equivalents.
Claims (5)
1. The utility model provides an attitude self-adaptation regulation annular lift wing device for pneumatic suspension train, includes pneumatic suspension train main part (1), its characterized in that: the outside of the pneumatic suspension train body (1) is provided with an annular lifting mechanism for adjusting the posture of the pneumatic suspension train body (1).
2. The attitude adaptive adjustment annular lift wing device for the pneumatic suspension train as claimed in claim 1, wherein: the annular lifting mechanism comprises a ground effect wing (2), an upper layer wing (3), a wing end lateral wing (4), a lateral wing rudder (5), a ground effect lift-increasing wing (6) and an upper layer flap (7), the ground effect wings (2) are arranged at the lower parts of the two ends of the pneumatic suspension train body (1), the upper layer wings (3) are arranged at the upper parts of the two ends of the pneumatic suspension train body (1), and the ground effect wing (2) and the upper layer wing (3) which are positioned at the same end are arranged in a staggered way, the upper layer wing (3) is positioned at the position which is relatively back to the ground effect wing (2), the wing end side wing (4) is fixed at one end of the ground effect wing (2) and the upper layer wing (3), the upper layer flap (7) is arranged at the position of the rear edge of the upper layer wing (3) about the middle span length, the ground effect lift-increasing wing (6) is arranged at the position of the rear edge of the ground effect wing (2) which is about the middle of the extending length, the wing rudder (5) is arranged at the position of the middle extending length of the rear edge of the wing end wing (4).
3. The attitude adaptive adjustment annular lift wing device for the pneumatic suspension train as claimed in claim 2, wherein: the ground effect wing (2), the upper layer wing (3) and the wing end side wing (4) form an annular wing, and the annular wing integrally inclines backwards.
4. The attitude adaptive adjustment annular lift wing device for the pneumatic suspension train as claimed in claim 3, wherein: the ground clearance of the annular wing is a ground effect height interval.
5. The attitude adaptive adjustment annular lift wing device for the pneumatic suspension train as claimed in claim 3, wherein: the shape of the annular wing is an inverted trapezoid with a wide upper part and a narrow lower part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111108189.2A CN113911318A (en) | 2021-09-22 | 2021-09-22 | Posture self-adaptive adjustment annular lift wing device for pneumatic suspension train |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111108189.2A CN113911318A (en) | 2021-09-22 | 2021-09-22 | Posture self-adaptive adjustment annular lift wing device for pneumatic suspension train |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113911318A true CN113911318A (en) | 2022-01-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111108189.2A Pending CN113911318A (en) | 2021-09-22 | 2021-09-22 | Posture self-adaptive adjustment annular lift wing device for pneumatic suspension train |
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| Country | Link |
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| CN (1) | CN113911318A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115421426A (en) * | 2022-09-27 | 2022-12-02 | 兰州交通大学 | Installation arrangement and cooperative control method of a high-speed train flank lift control device |
| CN115468732A (en) * | 2022-07-26 | 2022-12-13 | 华设设计集团股份有限公司 | High-speed train lifting wing installation arrangement and cooperative control method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5899409A (en) * | 1994-12-16 | 1999-05-04 | Frediani; Aldo | Large dimension aircraft |
| CN103552682A (en) * | 2013-10-30 | 2014-02-05 | 北京航空航天大学 | Airplane with combined-wing layout of flying wing and forward-swept wings |
| US20140042277A1 (en) * | 2011-03-21 | 2014-02-13 | Fly Nano Oy | Flying device and a wing construction for the same |
| US8657226B1 (en) * | 2007-01-12 | 2014-02-25 | John William McGinnis | Efficient control and stall prevention in advanced configuration aircraft |
| CN108045575A (en) * | 2017-12-18 | 2018-05-18 | 刘行伟 | A kind of short takeoff vertical landing aircraft |
| CN208412143U (en) * | 2018-07-04 | 2019-01-22 | 中国人民解放军海军航空大学 | A kind of aerodynamic arrangement being coupled wing unmanned plane |
-
2021
- 2021-09-22 CN CN202111108189.2A patent/CN113911318A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5899409A (en) * | 1994-12-16 | 1999-05-04 | Frediani; Aldo | Large dimension aircraft |
| US8657226B1 (en) * | 2007-01-12 | 2014-02-25 | John William McGinnis | Efficient control and stall prevention in advanced configuration aircraft |
| US20140042277A1 (en) * | 2011-03-21 | 2014-02-13 | Fly Nano Oy | Flying device and a wing construction for the same |
| CN103552682A (en) * | 2013-10-30 | 2014-02-05 | 北京航空航天大学 | Airplane with combined-wing layout of flying wing and forward-swept wings |
| CN108045575A (en) * | 2017-12-18 | 2018-05-18 | 刘行伟 | A kind of short takeoff vertical landing aircraft |
| CN208412143U (en) * | 2018-07-04 | 2019-01-22 | 中国人民解放军海军航空大学 | A kind of aerodynamic arrangement being coupled wing unmanned plane |
Non-Patent Citations (1)
| Title |
|---|
| 杨柳: "基于CFD的气动悬浮列车造型设计", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》, no. 12, pages 27 - 55 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115468732A (en) * | 2022-07-26 | 2022-12-13 | 华设设计集团股份有限公司 | High-speed train lifting wing installation arrangement and cooperative control method |
| CN115421426A (en) * | 2022-09-27 | 2022-12-02 | 兰州交通大学 | Installation arrangement and cooperative control method of a high-speed train flank lift control device |
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Application publication date: 20220111 |