CN216834279U - Foldable wearable personal aircraft - Google Patents
Foldable wearable personal aircraft Download PDFInfo
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- CN216834279U CN216834279U CN202220724737.8U CN202220724737U CN216834279U CN 216834279 U CN216834279 U CN 216834279U CN 202220724737 U CN202220724737 U CN 202220724737U CN 216834279 U CN216834279 U CN 216834279U
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Abstract
The utility model discloses a folded cascade's personal aircraft of wearing formula. The aircraft comprises a flight power mechanism, wherein the flight power mechanism comprises a plurality of foldable flight shafts which are uniformly distributed along the radial direction of the circumferential center, the outer end of each foldable flight shaft is provided with a flight motor and a flight propeller, and the inner end of each foldable flight shaft is fixed at the circumferential center; the energy cabin mechanism is internally provided with a foldable driving seat, a wearable garment and an integrated energy battery system; the double-operation driving rod mechanism comprises a double-operation driving rod fixed on the energy cabin body mechanism, and the double-operation driving rod comprises a left operation driving rod and a right operation driving rod; a telescopic folding type undercarriage mechanism comprises an undercarriage support rod and an undercarriage connected to the bottom of the undercarriage support rod. The utility model has the advantages of low price, simple operation, safety, environmental protection, easy carrying and strong power.
Description
Technical Field
The utility model belongs to the technical field of the aviation aircraft, concretely relates to folded cascade's wearing formula personal aircraft.
Background
At present, spacecrafts become important weapons for exploring the secret in space. However, these aircraft are all tasks that require enormous financial resources, personnel, facilities, equipment, and space to accomplish. Along with the improvement of economic life and the improvement of personal economic strength of people, the pursuit of people for innovative life and the longing of soaring in the air, people urgently need a personal aircraft which has low price, simple and convenient operation, safety, environmental protection, easy carrying and sufficient power and meets the requirements of people.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a personal aircraft of wearing formula of folded cascade for solving the not enough that above-mentioned background exists.
The utility model adopts the technical proposal that: a wearable personal aircraft of a foldable type, comprising:
the flight power mechanism comprises a plurality of foldable flight shafts which are uniformly distributed along the radial direction of the circumferential center, the outer end of each foldable flight shaft is provided with a flight motor and a flight propeller, the inner end of each foldable flight shaft is fixed at the circumferential center, and the flight motor drives the flight propeller to rotate;
the energy cabin body mechanism is fixed at the lower end of the center of the flying power mechanism, a foldable driving seat, a wearable garment and an integrated energy battery system are arranged in the energy cabin body mechanism, the foldable driving seat can move up and down and be folded, and a pilot can fly on the seat instead of flying in the air when flying, so that very comfortable flying experience can be realized; after the flight is finished, the seat can be folded, so that the packaging and carrying space is reduced, and the carrying is convenient;
the double-operation steering column mechanism comprises a double-operation steering column fixed on the energy cabin body mechanism, the double-operation steering column comprises a left operation steering column and a right operation steering column, the left operation steering column is provided with a power control operation system for operating the flying power energy, and the right operation steering column is provided with a flying attitude direction operation system for operating the flying direction and adjusting the flying attitude; through manual operation control, flight parameters of the aircraft, such as the flight speed, the flight height, the flight power and the like, are controlled, various flight experience effects are realized, the double-operation steering column can be folded, manual driving operation can be extended when the flight is started, and the double-operation steering column can be folded and put down after the flight is finished; the aircraft reduces the packaging space and is convenient to carry;
the telescopic folding landing gear mechanism is fixed at the bottom of the energy cabin body mechanism and comprises a landing gear support rod and a landing gear connected to the bottom of the landing gear support rod.
The foldable flight shaft adopts a 1-shaft, 2-shaft, 3-shaft, 4-shaft, 6-shaft, 8-shaft or multi-shaft structure; a flying motor electric adjusting system is arranged at the inner end of the foldable flying shaft and is used for controlling and adjusting the rotating speed of a flying motor; and a flight control system instrument is arranged at the inner end of the flying foldable flight shaft and used for controlling and adjusting the flight state of the aircraft, so that the stable flight of the aircraft is ensured.
The foldable flight shaft is provided with a detachable propeller safety outer cover used for surrounding the flight motor and the flight propeller. The detachable propeller safety outer cover can be detached, the detachable propeller safety outer cover is installed during flying, and the detachable propeller safety outer cover can be detached after flying, so that the packaging space is reduced.
And the flight control system instrument is electrically connected with the flight motor electric adjusting system through the first communication line group.
The automatic flick type parachute system is installed in the middle space of the flight power system mechanism, and can flick automatically in an emergency situation in the flight process, so that the safety of the whole aircraft and pilots is guaranteed.
The bottom of flight power system mechanism is equipped with retractable lower support post, retractable lower support post upper end with folded cascade flight axle is fixed, retractable lower support post lower extreme passes through bushing with the last spliced pole in the energy cabin body mechanism. When the aircraft is ready to fly, the telescopic lower support column can be lifted in the sleeve and locked firmly by the locking structure; when the flight of the aircraft is finished, the telescopic lower supporting columns can retract into the energy cabin body mechanism in the sleeve, so that the packaging space is reduced, and the aircraft is convenient to carry. The aircraft can be put into a vehicle and carried in a rear box of the vehicle for traveling.
Energy cabin body mechanism includes interconnect's upper junction post and lower junction post, folded cascade driving seat, wearable clothing and integrated energy battery system install on the upper junction post, the upper junction post passes through bushing with retractable lower support post lower extreme.
The integrated energy battery system is provided with a single group or two or more groups of batteries, the batteries are lithium batteries or hydrogen batteries or new energy batteries, and the flight motors of the flight power system mechanism are supplied with energy through current wires.
The wearable garment adopts a zipper type wearable garment structure and is provided with double inclined pull type fastening type safety braces and a waistband. The wearing is fast, simple and convenient, the taking off is fast, simple and convenient, and the flying is fast and safe; when the pilot prepares to fly, the pilot leans against the energy compartment, dresses fast, draws the zip fastener, and waist safety belt and two formula safety belts strides to one side are buckled and are detained the jail, guarantee human and organism closely laminating, adjust the seat, experience comfortable flight enjoyment, guarantee flight safety.
The energy cabin mechanism transmits flight driving control parameter signals through a second communication line group, and two ends of the second communication line group are respectively connected with a first communication line group in the flight power mechanism and a third communication line group in the double-operation steering rod mechanism, so that maintenance and detection are facilitated.
And the double-operation steering column in the double-operation steering column mechanism is provided with an automatic flight mode control system and a manual steering control system.
The electronic display screen is arranged on the left operating steering column or the right operating steering column, flight parameters are set on the electronic display screen, various flight data and parameters such as the navigation speed, the navigation height, the range, the air wind speed and the number of positioning satellites are displayed and watched, and the flight state of a pilot is adjusted through the data and operation, so that safe flight is guaranteed.
And the electronic display screen is in quick plug-in connection or wireless connection control with the second communication line group through the third communication line group.
And the landing gear strut rod is connected with a lower connecting column in the energy cabin mechanism through a sleeve. The landing gear strut rod can extend and quickly retract into a sleeve in the energy cabin body mechanism, so that the packaging space is reduced, and the landing gear is convenient to carry; when the aircraft is in preparation for flying, the landing gear strut rod can be pulled down from the landing gear strut rod to be lifted and unfolded, when the aircraft lands and lands, the landing gear preferentially lands and stably lands, the impact force on the ground during landing is reduced, the safety is ensured, the discomfort of a pilot is reduced, and the flying pleasure with good experience is improved; after the flight of the pilot is finished, the landing gear strut rod can be folded and stretched back to the inner side of the sleeve of the energy cabin body mechanism, so that the packaging space is reduced, and the carrying is convenient.
The utility model has the advantages of low price, simple operation, safety, environmental protection, easy carrying and strong power.
Drawings
Fig. 1 is a schematic structural view of a foldable wearable aircraft of the present invention;
FIG. 2 is a schematic structural diagram of the flight power system mechanism of the present invention;
FIG. 3 is a schematic structural diagram of the energy cabin of the present invention;
FIG. 4 is a schematic structural view of the dual-operation steering column mechanism of the present invention;
fig. 5 is a schematic structural view of the telescopic folding undercarriage mechanism of the present invention.
In the figure: 1-flight power mechanism, 2-energy cabin mechanism, 3-double-operation steering column mechanism, 4-telescopic folding type lifting frame mechanism, 5-foldable flight shaft, 6-flight motor, 7-flight propeller, 8-flight motor electric regulation system, 9-detachable propeller safety outer cover, 10-flight control system instrument, 11-first communication line group, 12-automatic flicking parachute system, 13-telescopic lower support column, 14-upper connecting column, 15 integrated energy battery system, 16-foldable driving seat, 17-wearable clothes, 18-safety harness and waistband, 19-second communication line group, 20-double-operation steering column, 21-power control operation system, 22-flight attitude direction operation system, 22-flight control system, 23-automatic driving control system, 24-manual driving control system, 25-automatic and manual control box, 26-electronic display screen, 27-third communication line group, 28-lower connecting column, 29-undercarriage supporting column rod and 30-undercarriage.
Detailed Description
The invention will be further described in detail with reference to the drawings and the following detailed description, which are provided for the purpose of clearly understanding the invention and are not intended to limit the invention.
As shown in fig. 1-5, the utility model comprises:
the flight power mechanism 1 comprises a plurality of foldable flight shafts 5 which are uniformly distributed along the radial direction of a circumferential center, a flight motor 6 and a flight propeller 7 are installed at the outer end of each foldable flight shaft 5, the inner end of each foldable flight shaft 5 is fixed at the circumferential center, and the flight motor 6 drives the flight propeller 7 to rotate;
the energy cabin mechanism 2 is fixed at the lower end of the center of the flight power mechanism 1, a foldable driving seat 16, a wearable garment 17 and an integrated energy battery system 15 are arranged in the energy cabin mechanism 2, the foldable driving seat can move up and down and be folded, and a pilot can sit on the seat to fly instead of flying in the air during flying, so that very comfortable flight experience can be achieved; after the flight is finished, the seat can be folded, so that the packaging and carrying space is reduced, and the seat is convenient to carry;
the double-operation steering column mechanism 3 comprises a double-operation steering column 20 fixed on the energy cabin mechanism 2, the double-operation steering column 20 comprises a left operation steering column and a right operation steering column, the left operation steering column is provided with a power control operation system 21 for operating the flying power energy, and the right operation steering column is provided with a flying attitude direction operation system 22 for operating the flying direction and adjusting the flying attitude; through manual operation control, flight parameters such as the flight speed, the flight height and the flight power of the aircraft are controlled, various flight experience effects are achieved, the double-operation steering column can be folded, manual driving operation can be extended when flight starts, and the double-operation steering column can be folded and put down after flight is finished; the aircraft reduces the packaging space and is convenient to carry;
and the telescopic folding landing gear mechanism 4 is fixed at the bottom of the energy cabin mechanism 2 and comprises a landing gear support rod 29 and a landing gear 30 connected to the bottom of the landing gear support rod 29.
The foldable flight shaft 5 adopts a 1-axis, 2-axis, 3-axis, 4-axis, 6-axis, 8-axis or multi-axis structure; a flying motor electric adjusting system 8 is arranged at the inner end of the foldable flying shaft 5 and is used for controlling and adjusting the rotating speed of the flying motor 6; and a flight control system instrument 10 is arranged at the inner end of the flying foldable flight shaft 5 and used for controlling and adjusting the flight state of the aircraft, so that the stable flight of the aircraft is ensured.
And a detachable propeller safety outer cover 9 used for surrounding the flight motor 6 and the flight propeller 7 is arranged on the foldable flight shaft 5. The detachable propeller safety outer cover can be detached, the detachable propeller safety outer cover is installed during flying, and the detachable propeller safety outer cover can be detached after flying, so that the packaging space is reduced.
The flight control system instrument 10 is electrically connected with the flight motor electric regulation system 8 through the first communication line group 11.
The automatic flicking type parachute system 12 is installed in the middle space of the flight power system mechanism 1, and can flick automatically in an emergency situation in the flight process, so that the safety of the whole aircraft and a pilot is guaranteed.
The bottom of the flight power system mechanism 1 is provided with a telescopic lower support column 13, the upper end of the telescopic lower support column 13 is fixed with the foldable flight shaft 5, and the lower end of the telescopic lower support column 13 is connected with an upper connecting column 14 in the energy cabin mechanism 2 through a sleeve. When the aircraft is ready to fly, the telescopic lower support column can be lifted in the sleeve and locked firmly by the locking structure; when the flight of the aircraft is finished, the telescopic lower supporting columns can retract into the energy cabin mechanism body in the sleeve, so that the packaging space is reduced, and the aircraft is convenient to carry. The aircraft can be put into a vehicle and carried in a rear box of the vehicle for traveling.
The energy cabin mechanism 2 comprises an upper connecting column 14 and a lower connecting column 28 which are connected with each other, the foldable driving seat 16, the wearable garment 17 and the integrated energy battery system 15 are mounted on the upper connecting column 14, and the lower ends of the upper connecting column 14 and the telescopic lower supporting column 13 are connected through a sleeve.
The integrated energy battery system 15 is provided with a single group or two or more groups of batteries, the batteries are lithium batteries, hydrogen batteries or new energy batteries, and the batteries provide energy for the flying motor 6 of the flying power system mechanism 1 through a current lead.
The wearable garment 17 is of a zipper type wearable garment structure and is provided with double inclined pull type fastening type safety braces and a waistband 18. The wearing is fast, simple and convenient, the taking off is fast, simple and convenient, and the flying is fast and safe; when the pilot prepares to fly, the pilot leans against the energy compartment, dresses fast, draws the zip fastener, and waist safety belt and two formula safety belts strides to one side are buckled and are detained the jail, guarantee human and organism closely laminating, adjust the seat, experience comfortable flight enjoyment, guarantee flight safety.
The energy cabin mechanism 2 transmits flight control parameter signals through a second communication line group 19, and two ends of the second communication line group 19 are respectively connected with the first communication line group 11 in the flight power mechanism 1 and the third communication line group 27 in the double-operation steering column mechanism 3, so that maintenance and detection are facilitated.
The double-operation steering column 20 in the double-operation steering column mechanism 3 is provided with an automatic flight mode control system 23 and a manual steering control system 24.
An electronic display screen 26 is arranged on the left operating steering column or the right operating steering column, flight parameters are set on the electronic display screen, various flight data and parameters such as the sailing speed, the sailing height, the sailing range, the air wind speed and the number of positioning satellites are displayed and watched, and the flight state of a pilot is adjusted through data and operation, so that safe flight is guaranteed.
The electronic display screen 26 is connected with the second communication line set 19 by fast plug-in connection or wireless connection control through the third communication line set 27.
The landing gear strut 29 is connected to the lower connecting strut 28 in the energy cabin mechanism 2 by a bushing. The landing gear strut rod can extend and quickly retract into a sleeve in the energy cabin body mechanism, so that the packaging space is reduced, and the landing gear is convenient to carry; when the aircraft is in preparation for flying, the landing gear strut rod can be pulled down from the landing gear strut rod to be lifted and unfolded, when the aircraft lands and lands, the landing gear preferentially lands and stably lands, the impact force on the ground during landing is reduced, the safety is ensured, the discomfort of a pilot is reduced, and the flying pleasure with good experience is improved; after the flight of the pilot is finished, the landing gear strut rod can be folded and stretched back to the inner side of the sleeve of the energy cabin body mechanism, so that the packaging space is reduced, and the carrying is convenient.
Example 1: when flying, take off the aircraft wrapping bag in the car, open the packing, take out foldable wearing formula aircraft in the wrapping bag. The flying power mechanism 1 is lifted up from the upper connecting column 14 in the energy cabin mechanism 2 through the telescopic lower supporting column 13, and is locked firmly by using a connecting screw, so that the flying power mechanism 1 is fixed. The foldable flying shaft 5 is unfolded upwards, locked firmly by a connecting screw and fixed well. The detachable propeller safety outer cover 9 is installed and is firmly locked by the connecting screws, and the safety outer cover is fixed well. The undercarriage 30 is pulled out from the lower connecting column 28 in the energy cabin mechanism 2 through the undercarriage supporting column rod 29 in the telescopic folding undercarriage mechanism 4, and the undercarriage is firmly locked by using a connecting screw and fixed. And the inspection and the arrangement ensure the safety and the stability of the aircraft architecture. The first communication line set 11 and the second communication line set 19 are quickly connected in a plugging mode, the second communication line set 19 and the third communication line set 27 are quickly connected in a plugging mode, and the communication signals of the aircraft are guaranteed to be smooth through checking and sorting. Lithium batteries or other new energy batteries such as hydrogen energy and the like are placed in the integrated energy battery system 15, and the power supply is connected to the energy source line, so that the energy supply of the batteries is ensured. The aircraft is placed stably and is ready for the driver to wear and fly.
Example 2: when preparing for autopilot flight, the pilot leans against the aircraft, wears the wearable garment 17 quickly, locks the safety harness and the waist belt 18 securely, and adjusts the foldable cockpit seat 16. And preparing to take off after finishing the preparation work before taking off.
When the automatic flight mode is ready to be started, flight parameters such as a flight destination address, flight height, flight speed, flight power and the like are input into the electronic display screen 26 and stored into the flight control system instrument 10, the automatic pilot control system 23 in the automatic and manual control box 25 is opened, the aircraft enters the automatic flight mode, the flight motor electric regulation system 8 obtains a signal indication, the rotating speed of the flight motor 6 and the flight propeller 7 is regulated, the flight power matching of each flight cycle is controlled, and the aircraft starts to take off automatically. The aircraft automatically flies to the flight destination address according to the set and designed flight parameter program, and the driver can freely view the air scenery and experience the flight pleasure without operating and driving. When an emergency occurs in the air, the automatic flick type parachute system 12 is opened to open the parachute, so that the flight safety of an aircraft and a driver is ensured.
Example 3: when preparing to manually drive the flight, the pilot leans against the aircraft, wears the wearable clothing 17 fast, locks the safety harness and the belt 18 firmly, adjusts the foldable cockpit seat 16 well. And preparing to take off after finishing the preparation work before taking off.
When the manual flight mode is ready to be activated, the manual piloting control system 24 in the automatic and manual control box 25 of the aircraft is turned on, the aircraft enters the manual flight mode and the aircraft starts the manual flight. The left hand operates the power control operating system 21 to adjust the size of the battery power throttle and provide power control for the aircraft. The right hand operates the flight attitude and direction operating system 22, flight parameters such as the flight direction, the flight attitude, the flight height, the flight speed and the like of the aircraft are adjusted and controlled by observing and checking the flight parameters in the electronic display screen 26 of the aircraft, so that the aircraft can ascend and descend at any time, can move forwards or turn at any time, and can hover or translate in the air. The driver drives and flies manually, and experiences the driving and flying pleasure. When an emergency occurs in the air, the safety emergency key is manually pressed, the automatic flick type parachute system 12 is opened, the parachute is unfolded, and the flight safety of an aircraft and a driver is guaranteed.
Example 4: after the flight is finished, the pilot quickly takes off the wearable garment 17, unloads the safety braces and the waistband 18, folds the foldable driving seat 16, unloads the detachable propeller safety outer cover 9, and folds and puts down the foldable flight shaft 5; the retractable lower support column 13 of the flight power mechanism 1 is retracted into the upper connecting column 14 of the energy cabin mechanism 2, the landing gear support column rod 29 is folded and retracted into the lower connecting column 28 of the energy cabin mechanism 2, the aircraft is packaged into a packaging bag, and the aircraft safety cover accessories are placed into the packaging bag and can be placed into a vehicle or a vehicle rear box to complete flight experience.
Those not described in detail in this specification are within the skill of the art.
Claims (10)
1. A wearable personal aircraft of a foldable type, comprising:
the flight power mechanism (1), the flight power mechanism (1) includes many foldable flight shafts (5) that radially evenly distributed along the circumference center, the outer end of each foldable flight shaft (5) is installed with a flight motor (6) and a flight propeller (7), the inner end of each foldable flight shaft (5) is fixed at the circumference center, the flight motor (6) drives the flight propeller (7) to rotate;
the energy cabin body mechanism (2) is fixed at the lower central end of the flying power mechanism (1), and a foldable driving seat (16), a wearable garment (17) and an integrated energy battery system (15) are arranged in the energy cabin body mechanism (2);
the double-operation steering column mechanism (3) comprises a double-operation steering column (20) fixed on the energy cabin mechanism (2), the double-operation steering column (20) comprises a left operation steering column and a right operation steering column, the left operation steering column is provided with a power control operation system (21) for operating the flying power energy, and the right operation steering column is provided with a flying attitude direction operation system (22) for operating the flying direction and adjusting the flying attitude;
the telescopic folding type landing gear mechanism (4) is fixed at the bottom of the energy cabin body mechanism (2) and comprises a landing gear support rod (29) and a landing gear (30) connected to the bottom of the landing gear support rod (29).
2. Foldable wearable personal aircraft according to claim 1, characterized in that the inner end of the foldable flying shaft (5) is equipped with a flying motor electrical tuning system (8) for controlling and adjusting the rotation speed of the flying motor (6); and a flight control system instrument (10) is arranged at the inner end of the flying foldable flight shaft (5) and is used for controlling and adjusting the flight state of the aircraft.
3. Wearable personal aircraft of the foldable type according to claim 1 or 2, characterized in that on the foldable flight shaft (5) is mounted a detachable propeller safety housing (9) for enclosing the flight motor (6), the flight propeller (7).
4. Foldable wearable personal aircraft according to claim 1, characterized in that the flying power means (1) intermediate space is equipped with an auto-flick parachute system (12).
5. The foldable wearable personal aircraft as claimed in claim 1, wherein a retractable lower support column (13) is provided at the bottom of the flight power mechanism (1), the upper end of the retractable lower support column (13) is fixed to the foldable flight shaft (5), and the lower end of the retractable lower support column (13) is connected to an upper connection column (14) of the energy cabin mechanism (2) through a sleeve.
6. Foldable wearable personal aircraft according to claim 5, characterized in that the energy cabin mechanism (2) comprises an upper connection column (14) and a lower connection column (28) connected to each other, the foldable driving seat (16), the wearable garment (17) and the integrated energy battery system (15) are mounted on the upper connection column (14), and the upper connection column (14) is connected to the lower end of the retractable lower support column (13) through a sleeve.
7. Foldable wearable personal aircraft according to claim 1, characterized in that the integrated energy battery system (15) is arranged with single or double or multiple batteries, the batteries are lithium batteries or hydrogen batteries or new energy batteries, and the flying motor (6) of the flying power mechanism (1) is supplied with energy through current wires.
8. Foldable wearable personal aircraft according to claim 1, characterized in that the wearable garment (17) is of a zip-like wearable garment structure, fitted with double diagonal tension type fastening safety harness and waist belt (18).
9. Foldable wearable personal aircraft according to claim 1, characterized in that the double-operated steering column (20) of the double-operated steering column mechanism (3) is equipped with an automatic flight mode control system (23) and a manual steering control system (24).
10. Foldable wearable personal aircraft according to claim 1 or 6, characterized in that the landing gear strut (29) is connected by a bushing to the lower connection column (28) inside the energy pod mechanism (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220724737.8U CN216834279U (en) | 2022-03-30 | 2022-03-30 | Foldable wearable personal aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220724737.8U CN216834279U (en) | 2022-03-30 | 2022-03-30 | Foldable wearable personal aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216834279U true CN216834279U (en) | 2022-06-28 |
Family
ID=82098036
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220724737.8U Active CN216834279U (en) | 2022-03-30 | 2022-03-30 | Foldable wearable personal aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216834279U (en) |
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2022
- 2022-03-30 CN CN202220724737.8U patent/CN216834279U/en active Active
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