CN107176294A - A kind of overwater flight device - Google Patents
A kind of overwater flight device Download PDFInfo
- Publication number
- CN107176294A CN107176294A CN201710493288.4A CN201710493288A CN107176294A CN 107176294 A CN107176294 A CN 107176294A CN 201710493288 A CN201710493288 A CN 201710493288A CN 107176294 A CN107176294 A CN 107176294A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- power supply
- manned
- motor
- kilograms
- 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.)
- Withdrawn
Links
- CVOFKRWYWCSDMA-UHFFFAOYSA-N 2-chloro-n-(2,6-diethylphenyl)-n-(methoxymethyl)acetamide;2,6-dinitro-n,n-dipropyl-4-(trifluoromethyl)aniline Chemical compound CCC1=CC=CC(CC)=C1N(COC)C(=O)CCl.CCCN(CCC)C1=C([N+]([O-])=O)C=C(C(F)(F)F)C=C1[N+]([O-])=O CVOFKRWYWCSDMA-UHFFFAOYSA-N 0.000 claims 1
- 210000003739 neck Anatomy 0.000 claims 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 13
- 239000007788 liquid Substances 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 3
- 239000007853 buffer solution Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 241001155433 Centrarchus macropterus Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000740 bleeding effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009429 electrical wiring Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000002917 insecticide Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000010338 mechanical breakdown Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000012549 training Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
-
- 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
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of overwater flight device.The aircraft is rotor type, can be with manned non-stop flight.
Description
Technical field
The invention belongs to aircraft, particularly a kind of manned vehicle waterborne.
Background technology
Currently, with the development of science and technology, amusement on water facility is increasing.But it is possible to which the instrument flown on the water is still
So it is less, it is impossible to meet people it is growing the need for.
Chinese utility model patent CN205216174U discloses a kind of water cannon flier device, and it includes gas-liquid storehouse and water
Pump, gas-liquid storehouse is constituted by the sealed vertical tube in upper end and with the horizontal tube that vertical tube lower end is connected, the port of export connection of horizontal tube
There is a slideway, and the port of export of horizontal tube is provided with trigger valve, the vertical tube in gas-liquid storehouse and is provided with feed water valve, feed water valve and institute
State on water pump connection, the vertical tube in the gas-liquid storehouse to be located at the position above feed water valve and be provided with steam supply valve, steam supply valve and institute
State and three-way connection is provided between gas-liquid storehouse, three-way connection is managed the bottom of by and the supervisor on the pipe perpendicular bisector of bottom constitutes, steam supply valve
Outlet side with by bottom pipe connected with the gas-liquid storehouse, air bleeding valve is connected with supervisor;The inlet end of steam supply valve is communicated with storage
Gas tank;Level switch and pressure detector are additionally provided with the vertical tube.The jet power of the present invention is strong, and operation safety is steady
It is fixed.
The method that the patent is provided can only be limited in water surface flying, flying height, and its control can not show a candle to rotor type and fly
Row device is convenient, need specialized training, otherwise easily falls down, and is only suitable for professional player, is not suitable for common visitor.
The content of the invention
Goal of the invention：, can be when the water surface be manned long the invention provides one kind in order to meet serious hope of the people to circling in the air
Between fly can manned vehicle.
Technical scheme is as follows:
Aircraft uses many rotor types, including the wing installed on motor, motor（Blade）, circuit connection and control unit,
Frame, manned part.Aircraft is connected to electric wire or cable, and electric wire or cable enter for being connected to external power supply to the motor of aircraft
Row power supply；Or aircraft is equipped with power interface, for being connected to external power supply.Described external power supply refers to all aircraft
Power supply in addition, including but not limited to power supply on generator, civilian or commercial power, battery, transit equipment etc..For example, can
To place a generator on the ship of the water surface, then it is connected by electrical wiring to aircraft with this generator and is powered.It is manned
Part can be platform, nacelle etc..
Due to using externally fed, can by load easily bring up to more than 30 kilograms, can also bring up to 200 kilograms with
On, it is more than even several tons of weight.So, aircraft can meet requirement that is manned, carrying many people.Meanwhile, of the invention flies
Row device can easily by the flight time from current half when within lifted to tens, more than hundreds of hours, do not considering occur
It can be flown always in the case of mechanical breakdown.Brought instant invention overcomes current rotor type unmanned plane using battery power supply station
Drawback.
Motor of the present invention can be direct current generator or alternating current generator.
Ultrasonic sensor or hyperbar meter are mounted with aircraft interior, for measuring height and its change, horizontal position
The coordinate put then is determined by GPS module.In addition, in addition to being positioned except GPS patterns, aircraft interior is also provided with inertia measurement
Unit, including one group of gyroscope and acceierometer sensor and control unit, for the state of flight for recognizing itself and relative position
Move.To ensure to remain able to stably control the posture of aircraft in the place of gps signal difference, it is ensured that safety.Such as indoor, mountain
The environment such as between area, skyscraper.
In operator scheme, using Three models are directly manipulated on remote control, line traffic control, aircraft, these three patterns can be mutual
Mutually switch, to learn from other's strong points to offset one's weaknesses, ensure flight safety.On the aircraft directly manipulation refer to people on board the aircraft according to operation by
Button, handle or operation interface etc. directly manipulate aircraft.
The aircraft of the present invention can also include landing and buffering system, described to reduce impulsive force during aircraft landing
Buffer system can install the part with spring, or air cushion etc. at the position of contacting to earth of aircraft.It is mounted with the part with spring
Aircraft can be facilitated afterwards in harder place（Such as ground, the deck of ship）Land, be mounted with that the aircraft of air cushion can be more square
Just landed in the place of the water surface or more flat.
Stand-by power supply can be included in aircraft, such as battery pack can also not have.Stand-by power supply is used in emergency
Under motor is powered.All powered under normal circumstances using external power supply, once because power supply is out of order, it can switch rapidly
To stand-by power supply, to prevent aircraft from being fallen due to power failure.
, can be by the way of bimodulus operation in order to improve the safety of aircraft operation.I.e. operation when, two aircraft are same
When work, and they are connected with rigidity or flexible safety rope, so, also will not be straight even if an aircraft breaks down
Connect to fall and cause damage.
Beneficial effect：
The rotor type aircraft made using technical solution of the present invention, first aircraft can band be seldom without battery, or only
Battery, significantly reduce the weight of aircraft, and when increasing motor, the increased power of motor institute is substantially all and can used
To increase pulling force；Second, due to external power supply, the flight time of aircraft can be with unrestricted；3rd, due to no energy side
The puzzlement that face is brought, aircraft of the invention can select high-power motor, so as to produce very big pulling force.For example, mesh
The motor that preceding multi-rotor unmanned aerial vehicle is used typically can only be below 10 kilograms of pull-up load, the overwhelming majority is below 5 kilograms.
Increase motor power when, required battery can be more, also heavier, thus actually can increased loading capacity extremely have
Limit.Therefore, even current load is than the larger unmanned plane for spraying insecticide, its load is general namely more than ten kilograms,
The many rotor type unmanned planes for the global dead weight having been reported that now namely can more than 30 kilograms of load-carrying.However, the present invention
Aircraft easily can lift the loading capacity of aircraft to more than 50 kilograms very much.For example, from pulling force be 80 kilograms very
To bigger motor, make the rotor type aircraft of eight axles, then can be with the load of more than 500 kilograms of pull-up.Use more work(
The big motor of rate, the pulling force of generation can be bigger.Such load capacity causes the aircraft of the present invention to be competent at the current water surface enough
Flight entertainment activity.
The aircraft can be applied in the fields such as fire-fighting, amusement and rescue.
For the ease of understanding the present invention, drawings and Examples, which are provided below, to be used to explain the present invention, but they are not constituted pair
The restriction of the present invention.
Brief description of the drawings
Fig. 1 is the structural representation of the aircraft of the present invention.The schematic diagram has only marked the basic of the aircraft of the present invention
Structure, also many parts are not marked, and those skilled in that art can install according to prior art.
Description of reference numerals：
1- motors
2- frames
3- blades
4- manned platforms
5- safety ropes
6- electric wires
7- air cushions
Embodiment
Below by the flight device that the present invention is described in detail in conjunction with the embodiments.
Frame is manufactured first, and motor is installed in frame（The quantity of motor is general more than 3）, blade is installed to electricity
On machine.Hyperbar meter, GPS module, gyroscope, acceierometer sensor are installed again and circuit, remote control system, line traffic control is respectively controlled
System etc..
Then manned part is installed in the bottom of aircraft, such as platform, nacelle.And pacify on manned or loading part
The control system of aircraft is filled, is easy to personnel to manipulate aircraft.
Buffer system is installed in the bottom of aircraft.
Power interface is installed on board the aircraft, to facilitate the power supply that aircraft exterior is may be coupled to before flight, to it
The energy of flight is provided；Or line of connecting with the mains on board the aircraft, to be connected to the power supply of aircraft exterior.
Elastic safety rope is installed on board the aircraft.
Described above is only some examples of embodiment of the present invention, it should be pointed out that：For the technology people of the art
For member, under the premise without departing from the principles of the invention, some improvements and modifications can also be made, these improvements and modifications also should
It is considered as protection scope of the present invention.
Claims (6)
1. a kind of aircraft, it is characterised in that：The aircraft is rotor type, the electric wire with the power supply for being connected to aircraft exterior
Or power interface, and the aircraft can be manned, loading capacity is more than 50~5000 kilograms.
2. a kind of aircraft as claimed in claim 1, it is characterised in that：The aircraft contains safety rope.
3. a kind of aircraft as claimed in claim 1, it is characterised in that：The aircraft can non-stop flight time at 1 hour
More than.
4. a kind of aircraft as claimed in claim 1, it is characterised in that：Aircraft can be manipulated on manned part.
5. a kind of aircraft as claimed in claim 1, it is characterised in that：The quantity of rotor is 2 or more than 2.
6. a kind of aircraft as claimed in claim 1, it is characterised in that：The aircraft is in necks such as fire-fighting, amusement and rescues
The application in domain.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710493288.4A CN107176294A (en) | 2017-06-26 | 2017-06-26 | A kind of overwater flight device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710493288.4A CN107176294A (en) | 2017-06-26 | 2017-06-26 | A kind of overwater flight device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107176294A true CN107176294A (en) | 2017-09-19 |
Family
ID=59844276
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710493288.4A Withdrawn CN107176294A (en) | 2017-06-26 | 2017-06-26 | A kind of overwater flight device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107176294A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107672797A (en) * | 2017-09-30 | 2018-02-09 | 镇江皮埃纳米科技有限公司 | A kind of fire-fighting aircraft |
| CN109358654A (en) * | 2018-11-16 | 2019-02-19 | 江苏科技大学 | A kind of empty amphibious search and rescue support unmanned vehicle system of water |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007267485A (en) * | 2006-03-28 | 2007-10-11 | Chugoku Electric Power Co Inc:The | Unmanned helicopter and cutting device mounted thereon |
| CN202686760U (en) * | 2012-06-20 | 2013-01-23 | 谭大刚 | Free gliding system with safety protection device |
| CN203005745U (en) * | 2012-11-22 | 2013-06-19 | 神翼航空器科技（天津）有限公司 | Remotely controlled aircraft with assistant endurance system and control system thereof |
| CN204606235U (en) * | 2015-05-04 | 2015-09-02 | 厦门大学 | Many rotor wing unmanned aerial vehicles device when navigating based on the length hanging mooring system |
| CN106379554A (en) * | 2016-12-08 | 2017-02-08 | 中国科学院长春光学精密机械与物理研究所 | Flight test protection device and method |
-
2017
- 2017-06-26 CN CN201710493288.4A patent/CN107176294A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007267485A (en) * | 2006-03-28 | 2007-10-11 | Chugoku Electric Power Co Inc:The | Unmanned helicopter and cutting device mounted thereon |
| CN202686760U (en) * | 2012-06-20 | 2013-01-23 | 谭大刚 | Free gliding system with safety protection device |
| CN203005745U (en) * | 2012-11-22 | 2013-06-19 | 神翼航空器科技（天津）有限公司 | Remotely controlled aircraft with assistant endurance system and control system thereof |
| CN204606235U (en) * | 2015-05-04 | 2015-09-02 | 厦门大学 | Many rotor wing unmanned aerial vehicles device when navigating based on the length hanging mooring system |
| CN106379554A (en) * | 2016-12-08 | 2017-02-08 | 中国科学院长春光学精密机械与物理研究所 | Flight test protection device and method |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107672797A (en) * | 2017-09-30 | 2018-02-09 | 镇江皮埃纳米科技有限公司 | A kind of fire-fighting aircraft |
| CN109358654A (en) * | 2018-11-16 | 2019-02-19 | 江苏科技大学 | A kind of empty amphibious search and rescue support unmanned vehicle system of water |
| CN109358654B (en) * | 2018-11-16 | 2022-03-29 | 江苏科技大学 | Water-air amphibious search and rescue support unmanned aerial vehicle system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20170919 |
|
| WW01 | Invention patent application withdrawn after publication |