CN109250082A - A kind of multiaxis low latitude manned vehicle - Google Patents
A kind of multiaxis low latitude manned vehicle Download PDFInfo
- Publication number
- CN109250082A CN109250082A CN201811274761.0A CN201811274761A CN109250082A CN 109250082 A CN109250082 A CN 109250082A CN 201811274761 A CN201811274761 A CN 201811274761A CN 109250082 A CN109250082 A CN 109250082A
- Authority
- CN
- China
- Prior art keywords
- cockpit
- motor
- low latitude
- manned vehicle
- rotor
- 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.)
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Classifications
-
- 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
- B64C25/54—Floats
- B64C25/56—Floats inflatable
-
- 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
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D43/00—Arrangements or adaptations of instruments
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
Abstract
The invention discloses a kind of multiaxis low latitude manned vehicles, including body and cockpit, body is equipped with air bag, there are four horns for tool on body, a motor is equipped on each horn, motor is bolted on horn head end, shaft is arranged in motor center, one rotor is installed in each shaft, rotor is bolted on motor, it is driven and is rotated by corresponding motor, the center of body is arranged in cockpit, manned seat and operation display are installed in cockpit, operation display controls the movement of entire aircraft, cockpit bottom is equipped with landing bracket, battery and reserve battery are additionally provided between body and cockpit；High comprehensive performance of the present invention is provided simultaneously with preferable flying quality and security performance；Urban traffic blocking can be alleviated, carbon emission is reduced and can be realized rapid delivery passenger；When crashing, the safety of personnel in cockpit is protected in the meeting automatic inflating expansion of induction type air bag to greatest extent.
Description
Technical field
The present invention relates to vehicle technology field, more particularly to a kind of multiaxis low latitude manned vehicle.
Background technique
In actual life, the trip of people relies on the vehicles mostly, but most cities are congested in traffic serious at present,
In the case where poor for the trip especially pavement behavior of short distance, conventional vehicles trip is inconvenient, while a large amount of friendships
The discharge of logical tool tail gas causes air pollution serious.
Low latitude manned vehicle is a kind of manned dress of four axis for utilizing wireless remote control device with the process control provided for oneself
It sets, machine is equipped with single passenger compartment, passenger can be sent by setting screen course line in cabin by ground remote control or passenger
To designated position.Having benefited from the development of micro electronmechanical control technology in recent years, stable four-axle aircraft has obtained extensive concern,
Application prospect is very considerable.
Since existing manned vehicle is all largely low-latitude flying, parachute is unable to fully open when failure,
It plays a role, so current manned vehicle security performance is poor, therefore the security performance for improving manned vehicle seems outstanding
It is important.
Therefore, a kind of flight stability how is provided, the high multiaxis low latitude manned vehicle of security performance is art technology
The problem of personnel's urgent need to resolve.
Summary of the invention
In view of this, the present invention provides a kind of multiaxis low latitude manned vehicle, high comprehensive performance is provided simultaneously with preferably
Flying quality and security performance；Urban traffic blocking can be alleviated, carbon emission is reduced and can be realized rapid delivery and multiply
Visitor；When crashing, the safety of personnel in cockpit is protected in the meeting automatic inflating expansion of induction type air bag to greatest extent,
Due to using air sac type structure, fallen in lake or rivers even if air crash occurs, air bag is capable of providing enough buoyancy, it is ensured that
The arrival that personnel wait for rescue.
In order to achieve the above object, invention adopts the following technical scheme that
A kind of multiaxis low latitude manned vehicle, including body and cockpit, the body is equipped with air bag, on the body
Tool is equipped with a motor on each horn, the motor is bolted on the horn head end, described there are four horn
Shaft is arranged in motor center, is equipped with a rotor in each shaft, the rotor is bolted on motor, by corresponding to
Motor drive rotation, the cockpit is arranged in the center of body, manned seat and operator control panel is equipped in the cockpit
Curtain, the operation display control the movement of entire aircraft, and the cockpit bottom is equipped with landing bracket, the body and drive
It sails and is additionally provided with battery and reserve battery between cabin；
The air bag includes the swelling gasbag of intermediate high-pressure gasbag and periphery, the corresponding rotor of the swelling gasbag
It is provided with rotor air duct on position, air pump is provided on the body, the air pump is connected to the high-pressure gasbag, the expansion
Air bag is connected to by solenoid valve with the high-pressure gasbag, and the high-pressure gasbag is arranged at the top of the cockpit, is set in cockpit
Air spring control is set, the surrounding on the outside of cockpit is provided with induction type air bag, the triggering inductor setting of the induction type air bag
In the swelling gasbag outside portion, the triggering inductor is electrically connected with air spring control, and the induction type air bag passes through tracheae
It is connected to solenoid valve with the high-pressure gasbag, the solenoid valve and the air pump are by air spring control control work；Institute
State swelling gasbag outer rim setting it is several be symmetrically distributed with trigger-type parachute, in cockpit be arranged parachute trigger controller,
The parachute trigger controller is electrically connected by conducting wire with the trigger inside trigger-type parachute.
Preferably, in a kind of above-mentioned multiaxis low latitude manned vehicle, CPU module built in the operation display, the CPU
Module is connected with GPS navigation module, motor driving module and battery detection module respectively, the motor driving module connection
Motor, the battery detection module are connect with battery and reserve battery.
Preferably, in a kind of above-mentioned multiaxis low latitude manned vehicle, the horn and the rotor uniform cloth around body
It sets.
Preferably, in a kind of above-mentioned multiaxis low latitude manned vehicle, there are four the motors, and the battery mentions for motor
For power.
Preferably, in a kind of above-mentioned multiaxis low latitude manned vehicle, the reserve battery is in cell malfunctions or breaks
It is enabled in electric situation.
Preferably, in a kind of above-mentioned multiaxis low latitude manned vehicle, head lamp is equipped in front of the cockpit.
Preferably, in a kind of above-mentioned multiaxis low latitude manned vehicle, the landing pack level height is greater than rotor.
Preferably, in a kind of above-mentioned multiaxis low latitude manned vehicle, antenna is equipped at the top of the cockpit, for receiving
Signal.
Preferably, in a kind of above-mentioned multiaxis low latitude manned vehicle, the cockpit is equipped with a hatch door to be opened/closed.
Preferably, in a kind of above-mentioned multiaxis low latitude manned vehicle, the manned seat is adjustable height seat.
It can be seen via above technical scheme that compared with prior art, the present disclosure provides a kind of multiaxis low no-loads
People's aircraft, high comprehensive performance are provided simultaneously with preferable flying quality and security performance；Can alleviate urban traffic blocking,
It reduces carbon emission and can be realized rapid delivery passenger；When crashing, induction type air bag meeting automatic inflating is swollen
It is swollen, protect the safety of personnel in cockpit to greatest extent, due to using air sac type structure, though occur air crash fall in lake or
In rivers, air bag is capable of providing enough buoyancy, it is ensured that the arrival that personnel wait for rescue.
A kind of multiaxis low latitude manned vehicle provided by the invention blocks up when can be to avoid trip, small in size, facilitates landing.
Carbon emission can also be reduced, passenger safety can be effectively ensured in reserve battery and air bag, and the control of four-axle aircraft is complete
Realize that provide enough power for aircraft, mechanical structure is very simple by the rotation speed change of four brushless motors, instruction is realized
There is no error when movement.And the period of conventional helicopters is extremely complex away from control mechanical structure, error is larger.The aircraft is set
There is operation display, the key on screen can fully control the various movements of aircraft, and passenger need to only receive to train a little
Self-service driving, screen can be easy to operate with customized course line.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
The embodiment of invention for those of ordinary skill in the art without creative efforts, can also basis
The attached drawing of offer obtains other attached drawings.
Fig. 1 attached drawing is overall structure diagram of the invention；
Fig. 2 attached drawing is top view of the present invention；
Fig. 3 attached drawing is side view of the present invention.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
The embodiment of the invention discloses a kind of multiaxis low latitude manned vehicle, high comprehensive performance is provided simultaneously with preferable
Flying quality and security performance；Urban traffic blocking can be alleviated, carbon emission is reduced and can be realized rapid delivery passenger；
When crashing, the safety of personnel in cockpit is protected in the meeting automatic inflating expansion of induction type air bag to greatest extent, due to
Air sac type structure is used, is fallen in lake or rivers even if air crash occurs, air bag is capable of providing enough buoyancy, it is ensured that personnel
The arrival waited for rescue.
In conjunction with attached drawing 1-3, the invention discloses a kind of multiaxis low latitude manned vehicle, including body and cockpit 2, bodies
It is equipped with air bag 3, tool is equipped with a motor 5 on each horn 4, motor 5 passes through bolt there are four horn 4 on body
It is fixed on 4 head end of horn, 5 center of motor is arranged shaft, is equipped with a rotor 6 in each shaft, rotor 6 is bolted
It on motor 5, is driven and is rotated by corresponding motor 5, cockpit 2 is arranged in the center of body, manned seat is equipped in cockpit 2
Chair and operation display, operation display control the movement of entire aircraft, and 2 bottom of cockpit is equipped with landing bracket 7, landing bracket
7 have shock-absorbing function；Battery and reserve battery are additionally provided between body and cockpit 2；
Air bag 3 includes the swelling gasbag 32 of intermediate high-pressure gasbag 31 and periphery, the position of the corresponding rotor 6 of swelling gasbag 32
It sets and is provided with rotor air duct 33, air pump is provided on body, air pump is connected to high-pressure gasbag 31, and swelling gasbag 32 passes through electromagnetism
Valve is connected to high-pressure gasbag 31, and air spring control, cockpit is arranged in 2 top of cockpit, cockpit 2 in the setting of high-pressure gasbag 31
The surrounding in 2 outsides is provided with induction type air bag 34, and the setting of triggering inductor 35 of induction type air bag 34 is in 32 outside of swelling gasbag
Portion, triggering inductor 35 are electrically connected with air spring control, and induction type air bag 34 is connected by tracheae and solenoid valve and high-pressure gasbag 31
Logical, solenoid valve and air pump control work by air spring control；Several trigger-type is symmetrically distributed in the setting of 32 outer rim of swelling gasbag
Parachute 36, is arranged parachute trigger controller in cockpit 2, and parachute trigger controller is landed by conducting wire and trigger-type
Trigger electrical connection inside umbrella 36.
High-pressure gasbag 31 of the present invention is connected to air pump, predominantly gas storage and pooling feature, and high-pressure gasbag 31 predominantly expands
Air bag 32 and induction type air bag 34 supply, and are provided with control valve 37 between swelling gasbag 32 and high-pressure gasbag 31, control valve 37 by
Air spring control control in cockpit 2, can be realized by air spring control to the inflated for deflated of swelling gasbag 32；Expand gas
Capsule 32 and high-pressure gasbag 31 constitute the main gasbag at 2 top of cockpit of the present invention, and several swelling gasbags 32 are located at high-pressure gasbag 31
Periphery increase safety, induction type air bag 34 can manually control by air spring control, can also be by being arranged in outside swelling gasbag 32
35 automatic trigger of triggering inductor of side is inflated.
When encountering harsh weather weather, situations such as aircraft encounters air-flow, aircraft cannot keep flight attitude and lose
When control, the opening of induction type air bag 34 of 2 surrounding of cockpit wraps up cockpit 2, increases the volume of aircraft, increases empty
Resistance in gas slows down the speed of aircraft, encounters and plays comprehensive buffer function when collision, to protect in cockpit
Personal safety.
Also several symmetrical trigger-type parachutes 36 are arranged in 32 outer rim of swelling gasbag in the present invention, in cockpit 2
Parachute trigger controller is set, and parachute trigger controller is electrically connected by conducting wire and 36 internal trigger of trigger-type parachute
It connects, when aircraft breaks down or run out of steam air crash, can manually or automatically open triggering by parachute trigger controller
Formula parachute 36, aircraft can more preferably keep posture after parachute is opened, and play and slow down decrease speed, utmostly ensure to drive
Sail the personnel safety in cabin.
In order to further optimize the above technical scheme, CPU module built in operation display, CPU module respectively with GPS navigation mould
Block, motor driving module and battery detection module are connected, and motor driving module connects motor 5, battery detection module and electricity
Pond is connected with reserve battery；
Passenger can independently set destination by operation display, this instruction is passed to CPU module by operation display, then
CPU module by this it is instruction morphing for effective information pass to GPS module carry out positioning and route determination.
Passenger can could be adjusted to control aircraft to rotor 6 by operational accelerator key, deceleration key, directionkeys
Forward speed height and direction, CPU module are connected to the signal of operation display conveying, issue corresponding control to motor driving module
Order, is adjusted correspondingly rotor 6 to control motor 5, and then controls the speed of aircraft, height and direction.Fly
When row device causes to deviate the course line set according to passenger when airline operation by operation display operation, system can be automatically according to GPS
The new course line of module planning.
In order to further optimize the above technical scheme, horn 4 is evenly arranged around body with rotor 6, and quadrotor is symmetrical
Property it is more preferable, yawing will not be generated when advancing at utmost speed, compared with fixed-wing, does not have to consider lifting surface, trim problem, and is gone straight up to
Machine ratio does not have to consider displacement, anti-twisted moment problem.
In order to further optimize the above technical scheme, there are four motors 5, battery is that motor 5 provides power.
In order to further optimize the above technical scheme, reserve battery enables under cell malfunctions or power blackout situation.
In order to further optimize the above technical scheme, it is equipped with head lamp in front of cockpit 2, needs to open in night flying,
Facilitate the passenger of low latitude manned vehicle or operator to understand the surrounding enviroment in advancing, improves the safety of flight.
In order to further optimize the above technical scheme, landing pack level height is greater than rotor 6.
In order to further optimize the above technical scheme, antenna is equipped at the top of cockpit 2, for receiving signal.
In order to further optimize the above technical scheme, cockpit 2 is equipped with a hatch door 21 to be opened/closed.
In order to further optimize the above technical scheme, manned seat is adjustable height seat.
Each embodiment in this specification is described in a progressive manner, the highlights of each of the examples are with other
The difference of embodiment, the same or similar parts in each embodiment may refer to each other.For device disclosed in embodiment
For, since it is corresponded to the methods disclosed in the examples, so being described relatively simple, related place is said referring to method part
It is bright.
The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present invention.
Various modifications to these embodiments will be readily apparent to those skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, of the invention
It is not intended to be limited to the embodiments shown herein, and is to fit to and the principles and novel features disclosed herein phase one
The widest scope of cause.
Claims (10)
1. a kind of multiaxis low latitude manned vehicle, including body and cockpit, which is characterized in that the body is equipped with substitute
Capsule, tool is equipped with a motor on each horn, the motor is bolted on described there are four horn on the body
Horn head end, the motor center are arranged shaft, are equipped with a rotor in each shaft, the rotor is bolted on
It on motor, is driven and is rotated by corresponding motor, the cockpit is arranged in the center of body, is equipped in the cockpit manned
Seat and operation display, the operation display control the movement of entire aircraft, and the cockpit bottom is equipped with landing bracket,
Battery and reserve battery are additionally provided between the body and cockpit；
The air bag includes the swelling gasbag of intermediate high-pressure gasbag and periphery, the corresponding rotor of the swelling gasbag
It is provided with rotor air duct on position, air pump is provided on the body, the air pump is connected to the high-pressure gasbag, the expansion
Air bag is connected to by solenoid valve with the high-pressure gasbag, and the high-pressure gasbag is arranged at the top of the cockpit, is set in cockpit
Air spring control is set, the surrounding on the outside of cockpit is provided with induction type air bag, the triggering inductor setting of the induction type air bag
In the swelling gasbag outside portion, the triggering inductor is electrically connected with air spring control, and the induction type air bag passes through tracheae
It is connected to solenoid valve with the high-pressure gasbag, the solenoid valve and the air pump are by air spring control control work；Institute
State swelling gasbag outer rim setting it is several be symmetrically distributed with trigger-type parachute, in cockpit be arranged parachute trigger controller,
The parachute trigger controller is electrically connected by conducting wire with the trigger inside trigger-type parachute.
2. multiaxis low latitude according to claim 1 manned vehicle, which is characterized in that CPU mould built in the operation display
Block, the CPU module are connected with GPS navigation module, motor driving module and battery detection module respectively, and the motor drives
Dynamic model block connects motor, and the battery detection module is connect with battery and reserve battery.
3. multiaxis low latitude according to claim 1 manned vehicle, which is characterized in that the horn and rotor are along body week
It encloses and is evenly arranged.
4. multiaxis low latitude according to claim 1 manned vehicle, which is characterized in that there are four the motors, the electricity
Pond provides power for motor.
5. multiaxis low latitude according to claim 1 manned vehicle, which is characterized in that the reserve battery occurs in battery
It is enabled under failure or power blackout situation.
6. multiaxis low latitude according to claim 1 manned vehicle, which is characterized in that be equipped with head in front of the cockpit
Lamp.
7. multiaxis low latitude according to claim 1 manned vehicle, which is characterized in that the landing pack level height is big
In rotor.
8. multiaxis low latitude according to claim 1 manned vehicle, which is characterized in that be equipped with day at the top of the cockpit
Line, for receiving signal.
9. multiaxis low latitude according to claim 1 manned vehicle, which is characterized in that the cockpit is equipped with one and can open
The hatch door closed.
10. multiaxis low latitude according to claim 1 manned vehicle, which is characterized in that the manned seat is that height can
Mode seat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274761.0A CN109250082A (en) | 2018-10-30 | 2018-10-30 | A kind of multiaxis low latitude manned vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274761.0A CN109250082A (en) | 2018-10-30 | 2018-10-30 | A kind of multiaxis low latitude manned vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109250082A true CN109250082A (en) | 2019-01-22 |
Family
ID=65042847
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811274761.0A Withdrawn CN109250082A (en) | 2018-10-30 | 2018-10-30 | A kind of multiaxis low latitude manned vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109250082A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110077584A (en) * | 2019-05-16 | 2019-08-02 | 贵州大学 | A kind of DCB Specimen high-rise life saving aircraft |
| CN111268103A (en) * | 2020-02-14 | 2020-06-12 | 广东工业大学 | Take dual-purpose unmanned aerial vehicle in sea and air of gasbag |
-
2018
- 2018-10-30 CN CN201811274761.0A patent/CN109250082A/en not_active Withdrawn
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110077584A (en) * | 2019-05-16 | 2019-08-02 | 贵州大学 | A kind of DCB Specimen high-rise life saving aircraft |
| CN111268103A (en) * | 2020-02-14 | 2020-06-12 | 广东工业大学 | Take dual-purpose unmanned aerial vehicle in sea and air of gasbag |
| CN111268103B (en) * | 2020-02-14 | 2024-03-05 | 广东工业大学 | Sea-air dual-purpose unmanned aerial vehicle with air bag |
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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: 20190122 |
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| WW01 | Invention patent application withdrawn after publication |