CN117698989A - Telescopic wing sliding cabin for helicopter emergency high-altitude crash - Google Patents
Telescopic wing sliding cabin for helicopter emergency high-altitude crash Download PDFInfo
- Publication number
- CN117698989A CN117698989A CN202311409770.7A CN202311409770A CN117698989A CN 117698989 A CN117698989 A CN 117698989A CN 202311409770 A CN202311409770 A CN 202311409770A CN 117698989 A CN117698989 A CN 117698989A
- Authority
- CN
- China
- Prior art keywords
- wing
- fixed wing
- fixed
- cabin
- telescopic
- 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.)
- Pending
Links
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 3
- 238000000034 method Methods 0.000 description 5
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 108010066057 cabin-1 Proteins 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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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
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/30—Constructional aspects of UAVs for safety, e.g. with frangible components
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
- B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
- B64U30/16—Variable or detachable wings, e.g. wings with adjustable sweep movable along the UAV body
-
- 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
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
-
- 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
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Tires In General (AREA)
Abstract
The invention provides a telescopic wing sliding cabin for an emergency high-altitude crash of a helicopter, which comprises an unmanned aerial vehicle cabin, wherein a pair of fixed wings are connected at the stress center point of the cabin through fixed wing telescopic devices; the fixed wing telescoping device comprises a telescoping rod, a connecting rod at the outermost end of the telescoping rod is connected with the wing root and the wing tip of the fixed wing, the fixed wing is contracted in the cabin when the telescoping rod is contracted, and the fixed wing is stretched at two sides of the cabin when the telescoping rod is expanded; the front edge of the fixed wing is provided with a fixed wing slot, and the rear edge of the fixed wing is provided with a flap. When the unmanned helicopter works at ordinary times, the fixed wing is contracted in the cabin and fixed at the stress center point of the aircraft by the bolts, so that when the aircraft is unexpected, the wing can rapidly extend out through the internal connecting rod to form a sweepback wing shape to control the attitude of the aircraft, and meanwhile, the undershoot speed of the aircraft is reduced, so that the aircraft can slide down.
Description
Technical Field
The invention relates to the field of anti-crash devices of small and medium unmanned helicopters, in particular to a telescopic wing sliding cabin for an emergency high-altitude crash of a helicopter.
Background
The small and medium unmanned helicopter has high sensitivity and high accuracy, is safe and reliable in the flight process, and is widely applied to scenes such as emergency rescue, electric power inspection, agriculture, forestry and plant protection and the like. And the operation cost and the maintenance cost are lower, and the method is greatly supported and popularized by various industries of China. However, after the unmanned helicopter fails in the task execution process, the unmanned helicopter is prone to limitations such as incapacity of stabilizing the flight, yaw generation, incapacity of controlling landing positions and the like. The telescopic wing sliding cabin is used as a control trend of the whole engine body by utilizing aerodynamic force (lifting force and resistance). If the unmanned helicopter is combined with the unmanned helicopter, the accuracy of the falling gesture can be guaranteed when the unmanned helicopter breaks down, the acceleration generated by the falling of the aircraft can be reduced, the impact force received during landing is reduced, and the safety of the unmanned helicopter is guaranteed to the greatest extent.
Disclosure of Invention
The invention aims to solve the problems in the prior art, and provides a telescopic wing sliding cabin for an emergency high-altitude crash of a helicopter, when rotor wing parts are damaged, an engine fails, the falling position cannot be controlled under the condition that stable flight or rotation or yaw generation is not realized, even the helicopter does not work, and when the traditional safety umbrella device cannot effectively fall, the falling aircraft is effectively buffered through the lifting force of a telescopic fixed wing, the falling attitude of the aircraft can be ensured, and the impact force of the aircraft is reduced to the greatest extent.
The invention comprises an unmanned aerial vehicle cabin, wherein a pair of fixed wings are connected at the stress center point of the cabin through fixed wing telescopic devices; the fixed wing telescoping device comprises a telescoping rod, a connecting rod at the outermost end of the telescoping rod is connected with the wing root and the wing tip of the fixed wing, the fixed wing is contracted in the cabin when the telescoping rod is contracted, and the fixed wing is stretched at two sides of the cabin when the telescoping rod is expanded; the front edge of the fixed wing is provided with a fixed wing slot, and the rear edge of the fixed wing is provided with a flap.
Further improved, the fixed wing is a sweepback wing.
Further improved, the fixed wing is of a multi-section telescopic structure, the wing tip is fixedly connected with the outer end of the connecting rod, the wing root is movably connected with the inner end of the connecting rod, and the wing root slides along the connecting rod to enable the multi-section fixed wing to be folded.
Further improved, the wing root is connected with the inner end of the connecting rod through a movable buckle, and the movable buckle is connected with the flight control system.
Further improved, the cabin, the telescopic connecting rod adopts high-strength titanium alloy material, and the two ends of the telescopic connecting rod are provided with cushions. The telescopic fixed wing is made of lighter material carbon fiber or composite material.
The invention has the beneficial effects that:
1. the fixed slots and the flaps can improve the lift force of the airplane, as the fixed slots and the flaps can reduce the pressure difference between the low-pressure area of the front edge and the rear edge of the wing, and the reduction of the pressure difference enables the airflow to be smoothly attached to the upper surface of the wing, so that the critical stall attack angle and the maximum lift force of the wing are increased.
2. Because the sweepback wing type is adopted, the resistance born by the wing is the same, and when the aircraft generates yaw, the resistance arm of the front wing is larger than that of the rear wing, so that the aircraft has a tendency to return to the original flight direction.
3. When the unmanned helicopter works at ordinary times, the fixed wings are contracted in the cabin and fixed at the stress center point of the aircraft by bolts, so that when the aircraft is unexpected, the wings can rapidly extend out through the internal connecting rods to form a sweepback wing profile to control the attitude of the aircraft, and meanwhile, the undershoot speed of the aircraft is reduced, so that the aircraft has the effect of sliding off.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of the overall structure of the present invention;
FIG. 2 is a schematic view of a fixed wing structure;
fig. 3 is a side cross-sectional view of the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The structure of the invention is shown in figures 1 to 3, and comprises an unmanned aerial vehicle cabin 1, wherein a pair of fixed wings 2 are connected at the stress center point of the cabin through fixed wing telescopic devices; the fixed wing telescoping device comprises a telescoping rod 6, a connecting rod 5 at the outermost end of the telescoping rod is connected with the wing root and the wing tip of the fixed wing, the fixed wing is contracted in the cabin when the telescoping rod is contracted, and the fixed wing is stretched at two sides of the cabin when the telescoping rod is expanded; the front edge of the fixed wing is provided with a fixed wing slot 3, and the rear edge of the fixed wing is provided with a flap 4.
Further improved, the fixed wing is a sweepback wing.
Further improved, the fixed wing is of a multi-section telescopic structure, the wing tip is fixedly connected with the outer end of the connecting rod, the wing root is movably connected with the inner end of the connecting rod, and the wing root slides along the connecting rod to enable the multi-section fixed wing to be folded.
Further improved, the wing root is connected with the inner end of the connecting rod through a movable buckle, and the movable buckle is connected with the flight control system.
Further improved, the cabin, the telescopic connecting rod adopts high-strength titanium alloy material, and the two ends of the telescopic connecting rod are provided with cushions. The telescopic fixed wing is made of lighter material carbon fiber or composite material.
In this specification, each embodiment is described in a progressive manner, and identical and similar parts of each embodiment are all referred to each other, and each embodiment mainly describes differences from other embodiments. In particular, for the equipment examples, what has been described above is merely a preferred embodiment of the invention, which, since it is substantially similar to the method examples, is described relatively simply, as relevant to the description of the method examples. The foregoing is merely illustrative of specific embodiments of the present invention, and the scope of the invention is not limited thereto, since modifications and substitutions will be readily made by those skilled in the art without departing from the spirit of the invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.
Claims (4)
1. A flexible wing landing cabin for emergent high altitude crash of helicopter, its characterized in that: the unmanned aerial vehicle comprises an unmanned aerial vehicle cabin, wherein a pair of fixed wings are connected at the stressed center point of the cabin through fixed wing telescopic devices; the fixed wing telescoping device comprises a telescoping rod, a connecting rod at the outermost end of the telescoping rod is connected with the wing root and the wing tip of the fixed wing, the fixed wing is contracted in the cabin when the telescoping rod is contracted, and the fixed wing is stretched at two sides of the cabin when the telescoping rod is expanded; the front edge of the fixed wing is provided with a fixed wing slot, and the rear edge of the fixed wing is provided with a flap.
2. The telescopic wing landing nacelle for a helicopter emergency high altitude crash of claim 1, wherein: the fixed wing is a sweepback wing.
3. Telescopic wing landing nacelle for helicopter emergency high altitude crashes according to claim 1 or 2, characterized in that: the fixed wing is of a multi-section telescopic structure, the wing tip is fixedly connected with the outer end of the connecting rod, the wing root is movably connected with the inner end of the connecting rod, and the wing root slides along the connecting rod to enable the multi-section fixed wing to be folded.
4. A telescopic wing landing nacelle for a helicopter emergency high altitude crash according to claim 3, wherein: the wing root is connected with the inner end of the connecting rod through a movable buckle, and the movable buckle is connected with the flight control system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311409770.7A CN117698989A (en) | 2023-10-27 | 2023-10-27 | Telescopic wing sliding cabin for helicopter emergency high-altitude crash |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311409770.7A CN117698989A (en) | 2023-10-27 | 2023-10-27 | Telescopic wing sliding cabin for helicopter emergency high-altitude crash |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117698989A true CN117698989A (en) | 2024-03-15 |
Family
ID=90150405
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311409770.7A Pending CN117698989A (en) | 2023-10-27 | 2023-10-27 | Telescopic wing sliding cabin for helicopter emergency high-altitude crash |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117698989A (en) |
-
2023
- 2023-10-27 CN CN202311409770.7A patent/CN117698989A/en active Pending
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