CN114715397A - Soft wing power aircraft - Google Patents
Soft wing power aircraft Download PDFInfo
- Publication number
- CN114715397A CN114715397A CN202210452307.XA CN202210452307A CN114715397A CN 114715397 A CN114715397 A CN 114715397A CN 202210452307 A CN202210452307 A CN 202210452307A CN 114715397 A CN114715397 A CN 114715397A
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- Prior art keywords
- wing
- connecting shaft
- assemblies
- control lever
- power
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- 230000000712 assembly Effects 0.000 claims abstract description 37
- 238000000429 assembly Methods 0.000 claims abstract description 37
- 238000005507 spraying Methods 0.000 claims description 36
- 238000004891 communication Methods 0.000 claims description 3
- 239000000126 substance Substances 0.000 claims 1
- 238000000034 method Methods 0.000 description 7
- 238000009434 installation Methods 0.000 description 6
- 238000007664 blowing Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 241001155433 Centrarchus macropterus Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a soft wing power aircraft, which relates to the technical field of aircrafts and comprises a connecting shaft, wherein power assemblies are arranged at the left end and the right end of the connecting shaft, wing assemblies are connected onto the connecting shaft and connected with wing assemblies, a first connecting node and a second connecting node are arranged in the middle section of the connecting shaft, each power assembly comprises a vortex jet engine, each wing assembly comprises a wing plate fixed on a shaft sleeve, each wing assembly comprises a human body wing connected onto the corresponding wing plate, a first control rod and a first supporting handle are connected to the lower portion of the corresponding first connecting node, a second control rod and a second supporting handle are connected to the lower portion of the corresponding second connecting node, shaft holding devices are arranged between the corresponding first control rod and the corresponding second control rod and between the connecting shaft and the wing plate, shaft holding handles are arranged on the corresponding first supporting handle and the corresponding second supporting handle, and throttle controllers are arranged on the corresponding first supporting handle and the corresponding second supporting handle. The invention has the advantages of light weight, simple structure, convenient and fast operation, safety and reliability.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a soft wing power aircraft.
Background
The wing dress is a special parachute equipment, also called a flying mouse dress, the wing dress flies, also called a close-range interstellar gliding movement, which means that a flier flies from a high building, a high tower, a bridge, a cliff and a helicopter up and down by wearing the wing dress, and closely attached to a building or a natural landscape in high altitude for unpowered flight, but the operation difficulty of flying by only depending on the wing dress is high, the movement danger is large, and the flight direction cannot be reliably and reasonably adjusted.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a soft wing power aircraft.
A soft wing power aircraft comprises a connecting shaft, wherein power assemblies are arranged at the left end and the right end of the connecting shaft, wing assemblies are connected to the connecting shaft, the wing assemblies are connected with wing mounting assemblies, and a first connecting node and a second connecting node are arranged in the middle section of the connecting shaft; the power assembly comprises a worm spraying engine arranged on the connecting shaft, and the spraying direction of the worm spraying engine is perpendicular to the central line direction of the connecting shaft; the wing assembly comprises a shaft sleeve and a wing plate which are connected with the connecting shaft, and the wing assembly comprises a human body wing connected to the wing plate; the utility model discloses a swing-type clutch, including first connecting node, first control lever, second control lever, first control lever and all be provided with between second control lever and connecting axle and the pterygoid lamina and embrace the axle device, first supporting handle with all be provided with on the second supporting handle and separate and embrace the axle hand (hold), first supporting handle with still all be provided with throttle controller on the second supporting handle, be provided with turn control switch on the first control lever, be provided with on the second control lever and open and stop the switch. When the soft wing power aircraft is used, the wings of the user are fixed with the body through the straps, the human body wings of the wing assembly are worn on other trunk parts and legs of the human body, the first supporting handle and the second supporting handle are respectively held by two hands to keep a stable standing state, the whole soft wing power aircraft is reliably connected with the body into a whole, the spraying direction of a spiral spraying engine in the spiral spraying assembly is kept to be vertical downwards, a start-stop switch is operated to start the spiral spraying engine, oil is added, the real-time operation power of the spiral spraying engine is gradually increased, the user obtains a reaction force through the air spraying of the spiral spraying engine to start to lift off, after the jet reaches a proper height, a shaft holding device is unlocked through releasing a shaft holding handle, then the first or second supporting handle is pulled, so that a connecting shaft and the spiral spraying engine rotate together, the movement direction of the aircraft is changed, the user is driven to fly forwards, and in the flying process, when the height needs to be raised or lowered, the shaft holding device is unlocked by releasing the shaft holding handle, the first control rod or the second control rod is pulled or pushed, the power direction of the turbojet engine is changed, and the flying height and the flying state are controlled; when landing is needed, the first supporting handle, the second supporting handle and the accelerator controller are slowly operated to enable the whole soft wing power aircraft to hover in the air, then the real-time operating power of the vortex engines is gradually reduced to realize landing of a user, the vortex engines can be turned off by using the start-stop switch at a key moment, and then the parachute is used for landing. The two worm spraying assemblies are symmetrically arranged at the left end and the right end of the connecting shaft, so that the structural stability is improved, and the flying direction can be changed according to different real-time operating powers, so that the worm spraying assemblies are fully utilized on the wing mounting assemblies; furthermore, the worm spraying component is connected with the connecting shaft into a whole, the worm spraying component can be adjusted by rotating the connecting shaft, the increase of the aircraft weight due to a complex structure is avoided, the operation is satisfactory, and meanwhile, the power direction of the worm spraying engine can be locked by the shaft holding device, so that high-altitude stable flight can be kept; furthermore, the wing plates in the wing assembly are not easy to deform, stable air flow guiding is achieved, the flight stability of the whole aircraft is improved, meanwhile, the human body wing assemblies are reliably connected and fixed, the windward area of the human body wing assemblies is increased, and a user can wear the human body wing assemblies to have higher reliability in flying.
Preferably, the body wing top surface is secured to the wing bottom surface. The wings of the human body are fixed at the tail ends of the wing plates, so that the wind area of the aircraft is increased, and the flight reliability is improved.
Preferably, a power supply module and a data processing module are arranged on the wing plate. The power module adopts an electricity storage battery to supply power to all electrical components, and the data processing module is used for processing all electrical signals, so that the control reliability is improved; the pterygoid lamina can not warp, forms the installation region of certain size through the pterygoid lamina, lets power module and data processing module installation ground more firm.
Preferably, the center lines of the first control rod and the second control rod are perpendicular to the center line of the connecting shaft. The first control rod and the second control rod are hollow, and power supply wires and the like can penetrate through the hollow first control rod and the hollow second control rod; the central lines of the first control rod and the second control rod are perpendicular to the central line of the connecting shaft, so that the stress concentration between the first control rod and the connecting shaft and between the second control rod and the connecting shaft can be reduced as much as possible, and the reliability of the process of driving the connecting shaft by the first control rod and the second control rod is improved.
Preferably, the power assembly further comprises an oil tank fixed to the wing plate and in communication with the turbojet engine. The oil tank supplies oil to the turbojet engine.
Preferably, the center of the top surface of the human wing is provided with a parachute structure. The parachute structure is arranged, so that a user can close the vortex-spraying engine and utilize the parachute to land at a critical moment.
The invention has the beneficial effects that:
according to the invention, through the arrangement of the whole wing plate, a stable and non-deformable installation platform is provided, the connecting shaft, the vortex spraying assemblies and the wing installation assemblies can be stably associated together, the reliability in the flight process is improved, the two vortex spraying assemblies are symmetrically arranged at the left end and the right end of the connecting shaft, the structural stability is improved, and meanwhile, the flight direction can be changed according to different real-time operation powers, so that the vortex spraying assemblies are fully utilized on the wing installation assemblies; furthermore, the worm spraying component and the connecting shaft are connected into a whole, the worm spraying component can be adjusted by rotating the connecting shaft, the increase of the aircraft weight due to a complex structure is avoided, the operation is satisfactory, and meanwhile, the shaft holding device can lock the power direction of the worm spraying engine and can keep high-altitude stable flight; furthermore, the wing plates in the wing assembly are not easy to deform, stable air flow guiding is achieved, the flight stability of the whole aircraft is improved, meanwhile, the human body wing assemblies are reliably connected and fixed, the windward area of the human body wing assemblies is increased, and a user can wear the human body wing assemblies to have higher reliability in flying.
Drawings
In order to more clearly illustrate the detailed description of the invention or the technical solutions in the prior art, the drawings that are needed in the detailed description of the invention or the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.
FIG. 1 is a schematic top view of the structure of the present invention;
FIG. 2 is a schematic rear view of the structure of the present invention;
FIG. 3 is a schematic side view of the structure of the present invention.
Reference numerals:
1-a connecting shaft, 11-a first connecting node, 12-a second connecting node, 13-a first control rod, 14-a first supporting handle, 15-a second control rod, 16-a second supporting handle, 2-a power assembly, 21-a vortex-spraying engine, 3-a wing assembly, 31-a shaft sleeve, 32-a wing plate, 4-a wing assembly, 41-a human body wing assembly, 5-a power module, 6-a data processing module and 7-a parachute.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, 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 some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. 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.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures. Furthermore, the terms "first," "second," and the like are used solely to distinguish one from another, and are not to be construed as indicating or implying relative importance.
In the description of the embodiments of the present invention, it should be noted that the terms "inside", "outside", "upper", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or orientations or positional relationships conventionally arranged when products of the present invention are used, and are only used for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements indicated must have specific orientations, be constructed in specific orientations, and operated, and thus, cannot be construed as limiting the present invention.
As shown in fig. 1 to 3, the soft wing power aircraft comprises a connecting shaft 1, power assemblies 2 are arranged at the left end and the right end of the connecting shaft 1, wing assemblies 3 are further arranged on the connecting shaft 1, the wing assemblies 3 are connected with wing assemblies 4, and a first connecting node 11 and a second connecting node 12 are arranged in the middle section of the connecting shaft 1; the power assembly 2 comprises a vortex-blowing engine 21 arranged on the connecting shaft 1, and the spraying direction of the vortex-blowing engine 21 is vertical to the central line direction of the connecting shaft 1; the wing assembly 3 comprises a wing plate 32 fixed on the shaft sleeve 31, and the wing assembly 4 comprises a human body wing 41 connected on the wing plate 32; first connecting node 11 below is connected with first control lever 13, first control lever 13 bottom is provided with first support handle 14, second connecting node 12 below is connected with second control lever 15, second control lever 15 bottom is provided with second support handle 16, all be provided with between first control lever 13 and second control lever 15 and connecting axle 1 and pterygoid lamina 3 and embrace the axle device, all be provided with on first support handle 14 and the second support handle 16 and separate and embrace the axle hand (hold), still all be provided with throttle control on first support handle 14 and the second support handle 16, be provided with turn control switch on the first control lever 13, be provided with on the second control lever 15 and open and stop the switch.
In the present embodiment, when the soft wing powered aircraft is used, the user fixes the wings to the body through the straps at the back of the user's shoulders, the other part of the body is put through the wing 41 of the wing assembly 4, the first support handle 14 and the second support handle 16 are respectively held by both hands, the stable standing state is maintained, the whole soft wing powered aircraft is reliably connected with the body, the jet direction of the spiral jetting engine 21 in the spiral jetting assembly is kept vertically downward, the start-stop switch is operated to open the spiral jetting engine 21, oil is added, the real-time operation power of the spiral jetting engine 21 is gradually increased, the user obtains the reaction force through the jet of the spiral jetting engine 21 to start to lift off, after the jet direction is raised to a proper height, the shaft-clasping device is unlocked by releasing the shaft-clasping handle, the first support handle 16 or the second support handle 16 is pulled, so that the shaft-clasping device 1 and the spiral jetting engine 21 rotate together, therefore, the moving direction of the aircraft is changed, a user is driven to fly forwards, and in the flying process, when the height needs to be raised or lowered, the shaft holding device is unlocked by releasing the shaft holding handle, the first control rod 13 or the second control rod 15 is pulled or pushed, the power direction of the turbojet engine is changed, and the flying height and the flying state are controlled; when landing is needed, the first supporting handle 14, the second supporting handle 16 and the accelerator controller are slowly operated to enable the whole soft wing power aircraft to hover in the air, then the real-time operating power of the spiral spraying engine 21 is gradually reduced to achieve landing of a user, and the spiral spraying engine 21 can be turned off by using a start-stop switch at a critical moment, and then the parachute 7 is used for landing. The whole wing plate 32 is arranged, a stable and non-deformable mounting platform is provided, the connecting shaft 1, the worm spraying assemblies and the wing mounting assemblies 4 can be stably associated together, the reliability in the flight process is improved, the two worm spraying assemblies are symmetrically arranged at the left end and the right end of the connecting shaft 1, the structural stability is improved, the flight direction can be changed according to different real-time operation powers, and therefore the worm spraying assemblies are fully utilized on the wing mounting assemblies 4; furthermore, the worm spraying component is connected with the connecting shaft 1 into a whole, the worm spraying component can be adjusted by rotating the connecting shaft 1, the increase of the aircraft weight due to a complex structure is avoided, the operation is satisfactory, and meanwhile, the power direction of the worm spraying engine 21 can be locked by the shaft holding device, so that the high-altitude stable flight can be kept; furthermore, the wing plates 32 in the wing assembly 3 are not easy to deform, stable air flow guiding is achieved, the flight stability of the whole aircraft is improved, meanwhile, the human body wing assemblies 41 are reliably connected and fixed, the windward area of the human body wing assemblies 41 is increased, and a user can wear the human body wing assemblies 41 to be more reliable in flight.
Specifically, the top surface of the body suit 41 is secured to the bottom surface of the wing panel 32.
In the present embodiment, the human wing 41 is fixed to the tail end of the wing plate 32, thereby increasing the wind receiving area of the aircraft and improving the flight reliability.
Specifically, the wing panel 32 is provided with a power supply module 5 and a data processing module 6.
In this embodiment, it should be noted that the power module 5 adopts an electric storage battery to supply power to all electrical components, and the data processing module 6 is used to process all electrical signals, so as to improve the control reliability; the wings 32 are not deformed, and the installation area is formed by the wings 32 to have a certain size, so that the power module 5 and the data processing module 6 are installed more stably.
Specifically, the center lines of the first control rod 13 and the second control rod 15 are perpendicular to the center line of the connecting shaft 1.
In the present embodiment, the first control lever 13 and the second control lever 15 are hollow, and the power supply line and the like can pass through; the central lines of the first control rod 13 and the second control rod 15 are perpendicular to the central line of the connecting shaft 1, so that the stress concentration between the first control rod 13 and the connecting shaft 1 and between the second control rod 15 and the connecting shaft 1 can be reduced as much as possible, and the reliability of the process of driving the connecting shaft 1 by the first control rod 13 and the second control rod 15 is improved.
Specifically, the power assembly 2 further includes an oil tank secured to the wing 32 and in communication with the turbojet engine 21.
In the present embodiment, the oil tank supplies oil to the turbo engine 21.
Specifically, the top surface of the body suit 41 is provided with a parachute structure 7.
In the present embodiment, it should be noted that the parachute structure 7 is arranged so that the user can close the turbojet engine 21 and land with the parachute structure 7 at some critical time of landing.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention, and they should be construed as being included in the following claims and description.
Claims (6)
1. The soft wing power aircraft is characterized by comprising a connecting shaft, wherein power assemblies are arranged at the left end and the right end of the connecting shaft, wing assemblies are connected to the connecting shaft, the wing assemblies are connected with wing mounting assemblies, and a first connecting node and a second connecting node are arranged in the middle section of the connecting shaft; wherein the content of the first and second substances,
the power assembly comprises a spiral spraying engine arranged on the connecting shaft, and the spraying direction of the spiral spraying engine is vertical to the central line direction of the connecting shaft;
the wing assembly comprises a shaft sleeve arranged on the connecting shaft and a wing plate fixed on the shaft sleeve, and the wing assembly comprises a human body wing connected to the wing plate;
first connected node below is connected with first control lever, first control lever bottom is provided with first brake lever, second connected node below is connected with the second control lever, second control lever bottom is provided with second brake lever, first control lever with all be provided with between second control lever and connecting axle and the pterygoid lamina and embrace the axle device, first brake lever with all be provided with on the second brake lever and separate and embrace the axle hand (hold), first brake lever with still all be provided with throttle controller on the second brake lever, be provided with turn control switch on the first control lever, be provided with start-up and parking switch on the second control lever.
2. The soft-wing powered aircraft of claim 1, wherein the body-winged leading end is secured to the wing-panel trailing end.
3. The soft wing powered aircraft of claim 1, wherein a power module and a data processing module are provided on the wing panel.
4. The soft wing powered aircraft of claim 1, wherein the centerlines of the first and second control levers are both perpendicular to a connecting shaft centerline.
5. The soft-wing powered aircraft of claim 1, wherein the wing assembly further comprises an oil tank secured to the wing panel and in communication with the turbojet engine.
6. The soft wing powered aircraft of claim 1, wherein the human wing top surface is provided with a parachute.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210452307.XA CN114715397A (en) | 2022-04-27 | 2022-04-27 | Soft wing power aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210452307.XA CN114715397A (en) | 2022-04-27 | 2022-04-27 | Soft wing power aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114715397A true CN114715397A (en) | 2022-07-08 |
Family
ID=82246521
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210452307.XA Pending CN114715397A (en) | 2022-04-27 | 2022-04-27 | Soft wing power aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114715397A (en) |
-
2022
- 2022-04-27 CN CN202210452307.XA patent/CN114715397A/en active Pending
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