CN110027708A - A kind of military superelevation velocity of sound flight system - Google Patents
A kind of military superelevation velocity of sound flight system Download PDFInfo
- Publication number
- CN110027708A CN110027708A CN201910166066.0A CN201910166066A CN110027708A CN 110027708 A CN110027708 A CN 110027708A CN 201910166066 A CN201910166066 A CN 201910166066A CN 110027708 A CN110027708 A CN 110027708A
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- vacuum
- gear
- door
- spur
- tunnel
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- 238000009413 insulation Methods 0.000 claims abstract description 27
- 230000008878 coupling Effects 0.000 claims description 17
- 238000010168 coupling process Methods 0.000 claims description 17
- 238000005859 coupling reaction Methods 0.000 claims description 17
- 239000003380 propellant Substances 0.000 claims description 14
- 239000004449 solid propellant Substances 0.000 claims description 10
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 9
- 230000005540 biological transmission Effects 0.000 claims description 9
- 239000001301 oxygen Substances 0.000 claims description 9
- 229910052760 oxygen Inorganic materials 0.000 claims description 9
- 238000005183 dynamical system Methods 0.000 claims description 6
- 230000005611 electricity Effects 0.000 claims description 5
- 238000001514 detection method Methods 0.000 claims description 4
- 239000005062 Polybutadiene Substances 0.000 claims description 3
- LNDKRVOOYMEYTC-UHFFFAOYSA-N buta-1,3-dien-1-ol Chemical compound OC=CC=C LNDKRVOOYMEYTC-UHFFFAOYSA-N 0.000 claims description 3
- 229920002857 polybutadiene Polymers 0.000 claims description 3
- 229920000570 polyether Polymers 0.000 claims description 3
- 229920002635 polyurethane Polymers 0.000 claims description 3
- 239000004814 polyurethane Substances 0.000 claims description 3
- 229910002651 NO3 Inorganic materials 0.000 claims description 2
- NHNBFGGVMKEFGY-UHFFFAOYSA-N Nitrate Chemical compound [O-][N+]([O-])=O NHNBFGGVMKEFGY-UHFFFAOYSA-N 0.000 claims description 2
- 239000000284 extract Substances 0.000 claims description 2
- 230000032258 transport Effects 0.000 description 35
- 238000010586 diagram Methods 0.000 description 7
- 230000001133 acceleration Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000000605 extraction Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 238000005086 pumping Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- 239000002253 acid Substances 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000009412 basement excavation Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 150000002148 esters Chemical class 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000005339 levitation Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- FGIUAXJPYTZDNR-UHFFFAOYSA-N potassium nitrate Chemical compound [K+].[O-][N+]([O-])=O FGIUAXJPYTZDNR-UHFFFAOYSA-N 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
Abstract
The invention discloses a kind of military superelevation velocity of sound flight systems, including vacuum tunnel, aircraft, first infrared sensor, vacuum insulation panel, vacuum chamber, control circuit board, second infrared sensor, vacuum cabin door, vacuum pump, vacuum tube, transmitting station, at the both ends of vacuum tunnel, identical first infrared sensor is set, vacuum insulation panel, vacuum chamber, control circuit board, second infrared sensor, vacuum cabin door, vacuum pump, vacuum tube, transmitting station, the vacuum in tunnel is extracted out by vacuum pump, as vacuum tunnel, vacuum flight environment is provided for aircraft, eliminate air drag, so that the speed of service of aircraft is faster, the time is greatly saved, strong backup safeguard is provided for war, vacuum tunnel and vacuum chamber are kept apart by vacuum insulation panel, effectively raise the vacuum degree of vacuum tunnel.
Description
Technical field
The present invention relates to military supplies, soldier's transport field more particularly to a kind of military superelevation velocity of sound flight systems.
Background technique
In the prior art, military supplies, soldier etc. are transported by opportunity of combat, battlebus, steamer, train etc., these methods exist
Certain defect, it may be assumed that influence of the opportunity of combat vulnerable to air drag, so that flying speed is slow；Battlebus is mainly walked in land, fortune
Throughput rate is few, speed is slow, and is easy to be hindered by landform；Steamer is mainly at sea run, and freight volume is big, is influenced vulnerable to sea wind, speed
Degree is slow, and is easy to give away one's position；Train travels along the railway track, and freight volume is big, is influenced by rail, air drag so that speed compared with
Slowly.
Summary of the invention
To solve the above-mentioned problems, the purpose of the present invention is to provide a kind of military superelevation velocity of sound flight systems, by tunnel
Interior gas vacuum pumping provides the flight environment of vehicle of no air drag for aircraft, and aircraft is made to reach super in vacuum tunnel
The speed of service of high velocity of sound, transport military supplies, soldier etc., invention removes air drag, so that the operation speed of aircraft
Degree faster, is greatly saved the time, strong backup safeguard is provided for war.
To achieve the above object, a kind of military superelevation velocity of sound flight system provided by the invention is achieved in that
A kind of military superelevation velocity of sound flight system, including vacuum tunnel, aircraft, the first infrared sensor, vacuum insulation
Plate, vacuum chamber, control circuit board, the second infrared sensor, vacuum cabin door, vacuum pump, vacuum tube, transmitting station, vacuum tunnel position
In underground, connects every main military area command and the point of war easily occurs, and extracted out the air in tunnel by vacuum pump, as vacuum
Tunnel provides vacuum flight environment for aircraft, and identical first infrared sensor, vacuum is arranged at the both ends of vacuum tunnel
Isolation board, vacuum chamber, control circuit board, the second infrared sensor, vacuum cabin door, vacuum pump, vacuum tube, transmitting station, vacuum chamber
It connect with vacuum tunnel, is kept apart vacuum chamber and vacuum tunnel by vacuum insulation panel, vacuum is equipped on vacuum insulation panel
Hatch door, for providing channel for military supplies, soldier etc., vacuum chamber prevents vacuum cabin door from opening for providing forevacuum environment
When air enter vacuum tunnel, the first infrared sensor is mounted on vacuum insulation panel, and in vacuum tunnel one side, control
Circuit board processed and the second infrared sensor are mounted on vacuum insulation panel, and in vacuum chamber one side, the first infrared sensor is used
Whether someone is into vacuum chamber in detection vacuum tunnel, the second infrared sensor for detect in vacuum chamber whether someone
Into vacuum tunnel, by the folding of control circuit board control vacuum cabin door, and control vacuum pump work, vacuum tunnel with
Vacuum insulation panel is additionally provided with transmitting station, takes off and parks for assisting in flying device, is respectively mounted beside vacuum tunnel, vacuum chamber
There is identical vacuum pump, and fills a vacuum pump, vacuum pump and vacuum tunnel, vacuum chamber every 50 meter amperes by vacuum tunnel
Between connected using vacuum tube, the pipeline of the air as vacuum pump extraction vacuum tunnel, in vacuum chamber.
Vacuum cabin door of the invention includes left-hand door, You Men, right door stepping motor gear, right front tooth item, right door stepping electricity
The folding of machine, left-hand door stepper motor, left-hand door rack gear, left-hand door stepping motor gear, left-hand door and right door is opening for vacuum cabin door
It closes, right door stepper motor, left-hand door stepper motor are fixed on vacuum insulation panel, and right door stepping motor gear is fixed on right door step
Into in the rotary shaft of motor, right front tooth item is connect with right door, and You Youmen stepper motor drives right door stepping motor gear rotation,
And then be right door rack-driving, so that right front tooth item is pulled right Men Yidong, left-hand door stepping motor gear is fixed on left-hand door stepper motor
Rotary shaft on, left-hand door rack gear is connect with left-hand door, by left-hand door stepper motor drive left-hand door stepping motor gear rotation, Jin Erwei
Left-hand door rack-driving makes left-hand door rack gear pull left-hand door mobile, the rotation band respectively of You Youmen stepper motor, left-hand door stepper motor
It moves right door and left-hand door is mobile, realize the folding of vacuum cabin door.
Between right door stepping motor gear and right front tooth item, left-hand door stepping motor gear and left-hand door rack gear of the invention
Using rack pinion mode, it is convenient for left-hand door and right Men Kaihe.
Control circuit board of the invention is equipped with main control board, programmable logic controller (PLC), and main control board is to first
The information that infrared sensor, the second infrared sensor detect is handled, then controls the movement of programmable logic controller (PLC),
Again by the work of PLC controls right door stepper motor, left-hand door stepper motor, vacuum pump, pass through this light current
The mode for controlling forceful electric power, greatly improves the safety of electricity consumption.
Aircraft of the invention include transport pod, operation bench, oxygen tank, seat, left rocket engine, left propellant container,
Right propellant container, right rocket engine, transport hatch door, the first telescope motor, servo-actuated wheel carrier, supporting roller, driving wheel, driving wheel
Frame, rotating electric machine, the second telescope motor, operation bench are mounted in front of transport pod, for controlling the taking off of aircraft, braking,
Identical oxygen tank is installed in transport pod inner wall, provides oxygen for soldier in transport pod, seat is set in transport pod, is supplied
Soldier takes a seat, the dynamical system using left rocket engine and right rocket engine as aircraft, the left side of transport pod appearance
Left rocket engine, the right rocket engine of right side installation are installed, is pushed and is flown jointly by left rocket engine and right rocket engine
Row device advances, and is equipped with left propellant container, right propellant container, respectively left rocket engine and the right side at left and right sides of transport pod
Rocket engine provides solid propellant, and the solid propellant of use has polyurethane, polybutadiene, end hydroxy butadiene, nitre
Acid esters is plasticized polyethers etc.；It is provided with transport hatch door on transport pod, passes in and out aircraft passageway for soldier, is installed in transport pod bottom
Supporting roller and driving wheel slide help-fly for assisting in flying device on transmitting station, and supporting roller is used between supporting roller and transport pod
Frame connection, the first telescope motor are mounted on inside transport pod front end, and the telescopic rod of the first telescope motor and servo-actuated wheel carrier connect
It connects, for controlling the state of supporting roller, is connected between driving wheel and transport pod using active wheel carrier, the second telescope motor and rotation
Rotating motor is mounted on inside transport pod front end, and the telescopic rod of the first telescope motor is connect with active wheel carrier, for controlling actively
The state of wheel, rotating electric machine is for driving driving wheel to rotate.
Left rocket engine of the invention, right rocket engine use identical solid propellant rocket.
Operation bench of the invention is equipped with start button, forwarding button, backspace button, accelerates button, retard button, system
Dynamic button, laser radar, controller, start button, backspace button, accelerate button, retard button, braking to press at forwarding button
Button, laser radar are connect with controller, and start button is for opening aircraft, and when pressing forwarding button, controller is just controlled
Rotating electric machine drives driving wheel rotation, makes driving wheel that aircraft be driven to run on transmitting station, while controlling left rocket motor
Machine, the rotation of right rocket engine, press backspace button, aircraft will on transmitting station inverted walk backward, press acceleration button,
Rotating electric machine, left rocket engine, right rocket engine will accelerate to rotate, when driving wheel pushes aircraft to sail out of transmitting station
Afterwards, continue to accelerate, so that left rocket engine, right rocket engine drive aircraft to fly in vacuum tunnel, press and subtract
Fast button can be such that the sliding speed of aircraft and flying speed reduces, press stop button, and aircraft will be out of service, swashs
Optical radar is used to guide course line for aircraft, and after Airborne Lidar, which measures aircraft, sails out of transmitting station, controller just controls the
One telescope motor packs up servo-actuated wheel carrier, and the second telescope motor of control packs up active wheel carrier, when Airborne Lidar measures flight
When device is close to transmitting station, controller controls the first telescope motor and puts down servo-actuated wheel carrier, and the second telescope motor of control is by driving wheel
Frame is put down, so that driving wheel and supporting roller drive aircraft to slide and place on transmitting station.
Active wheel carrier of the invention includes the first spur gear, first shaft coupling, the first spur bevel gear, the second straight-tooth
Conical gear, wheel shaft, third spur bevel gear, the 4th spur bevel gear, second shaft coupling, internal gear, the second straight-tooth
Wheel, gear casing, gear casing are connected with the rotary shaft of rotating electric machine, and internal gear is fixed on gear casing, the first spur gear
It being mounted in internal gear with the second spur gear, first shaft coupling is connected between the first spur gear and the second spur bevel gear,
Second shaft coupling is connected between the second spur gear and third spur bevel gear, wheel shaft pass through the first spur bevel gear and
Driving wheel, the first spur bevel gear and the second spur bevel gear, third straight bevel are connected after 4th spur bevel gear
It is driven between gear and the 4th spur bevel gear using the helical bevel gear kind of drive, gear casing is driven by rotating electric machine
Rotation so that internal gear be driven to rotate, then is the first spur gear, the second Spur Gear Driving, and the first spur gear drives first
The rotation of axis device, and then the rotation of the second spur bevel gear is driven, the second spur bevel gear is the first spur bevel gear biography
Dynamic, the second spur gear drives second shaft coupling rotation, and then drives the rotation of third spur bevel gear, third straight bevel tooth
Wheel is that the 4th spur bevel gear is driven, and drives wheel shaft to turn jointly by the first spur bevel gear and the 4th spur bevel gear
It is dynamic, so that driving wheel rotates, so that aircraft be driven to move on transmitting station.
Internal gear transmission mode is used between first spur gear of the invention and internal gear, the second spur gear and internal gear,
It is rotated in one direction convenient for the first spur bevel gear and the 4th spur bevel gear.
Dynamical system of the invention can also be the magnetic suspension way of propelling.
The present invention is used the gas vacuum pumping in tunnel, is provided the flight environment of vehicle of no air drag for aircraft, is made
Aircraft reaches the speed of service of superelevation velocity of sound in vacuum tunnel, transports the structure of military supplies, soldier etc., so as to
Obtain it is following the utility model has the advantages that
1. the present invention is extracted out the vacuum in tunnel by vacuum pump, as vacuum tunnel, vacuum is provided for aircraft and is flown
Row environment, eliminates air drag, so that the speed of service of aircraft is faster, the time is greatly saved, has provided for war
The backup safeguard of power.
2. the present invention is kept apart vacuum tunnel and vacuum chamber by vacuum insulation panel, vacuum tunnel is effectively raised
The vacuum degree in road.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the installation for the military superelevation velocity of sound flight system that one embodiment of the invention provides；
Fig. 2 is the structural schematic diagram of the vacuum cabin door for the military superelevation velocity of sound flight system that one embodiment of the invention provides；
Fig. 3 is the control circuit board working principle diagram for the military superelevation velocity of sound flight system that one embodiment of the invention provides；
Fig. 4 is the structural schematic diagram of the aircraft for the military superelevation velocity of sound flight system that one embodiment of the invention provides；
Fig. 5 is the working principle diagram of the operation bench for the military superelevation velocity of sound flight system that one embodiment of the invention provides；
Fig. 6 is the structural schematic diagram of the active wheel carrier for the military superelevation velocity of sound flight system that one embodiment of the invention provides；
Fig. 7 is the first spur gear of military superelevation velocity of sound flight system that one embodiment of the invention provides and internal gear, the
Transmission schematic diagram between two spur gears and internal gear.
Main element symbol description.
Specific embodiment
Below with reference to embodiment and compares attached drawing invention is further described in detail.
Fig. 1 to 7 is please referred to, a kind of military superelevation velocity of sound flight system that an embodiment provides in the present invention, packet are shown
It is infrared to include vacuum tunnel 1, aircraft 2, the first infrared sensor 3, vacuum insulation panel 4, vacuum chamber 5, control circuit board 6, second
Sensor 7, vacuum cabin door 8, vacuum pump 9, vacuum tube 10, transmitting station 11.
Vacuum tunnel 1 is located underground, specifically can connect every main military area command in underground excavation tunnel and war easily occurs
Point transfers military supplies, soldier etc. to front convenient for every main military area command, and is extracted out the air in tunnel by vacuum pump 9, makees
For vacuum tunnel 1, vacuum flight environment is provided for aircraft 2, aircraft 2 is run in vacuum tunnel 1, in vacuum tunnel 1
Identical first infrared sensor 3, vacuum insulation panel 4, vacuum chamber 5, control circuit board 6, the second infrared sensor is arranged in both ends
7, vacuum cabin door 8, vacuum pump 9, vacuum tube 10, transmitting station 11, vacuum chamber 5 are connect with vacuum tunnel 1, will by vacuum insulation panel 4
Vacuum chamber 5 is kept apart with vacuum tunnel 1, and vacuum cabin door 8 is equipped on vacuum insulation panel 4, for being military supplies, soldier etc.
Channel is provided, vacuum chamber 5 is for providing forevacuum environment, and air enters vacuum tunnel 1 when preventing vacuum cabin door 8 from opening, the
One infrared sensor 3 is mounted on vacuum insulation panel 4, and in 1 one side of vacuum tunnel, control circuit board 6 and the second infrared biography
Sensor 7 is mounted on vacuum insulation panel 4, and in 5 one side of vacuum chamber, the first infrared sensor 3 is for detecting vacuum tunnel 1
In whether someone is into vacuum chamber 5, whether someone is to vacuum tunnel 1 for detecting in vacuum chamber 5 for the second infrared sensor 7
In, when someone is into vacuum chamber 5 in the first infrared sensor 3 detection vacuum tunnel 1 or the second infrared sensor 7 detects
When someone is into vacuum tunnel 1 in vacuum chamber 5, control circuit board 6 is transmitted this information to, control circuit board 6 just controls
Right door stepper motor 16, left-hand door stepper motor 17 respectively open right door 13, left-hand door 12, provide for military supplies, soldier etc. logical
Road, when nobody is into vacuum chamber 5 in the first infrared sensor 3 detection vacuum tunnel 1 and the second infrared sensor 7 detects
When nobody is into vacuum tunnel 1 in vacuum chamber 5, control circuit board 6 is transmitted this information to, control circuit board 6 just controls
Right door stepper motor 16, left-hand door stepper motor 17 respectively close right door 13, left-hand door 12, by vacuum tunnel 1 and vacuum chamber every 5
It leaves, is additionally provided with transmitting station 11 in vacuum tunnel 1 and vacuum insulation panel 4, takes off and park for assisting in flying device 2, true
It is mounted on vacuum pump 9 beside empty tunnel 1, vacuum chamber 5, and fills a vacuum pump 9 every 50 meter amperes by vacuum tunnel 1, very
It is connected between sky pump 9 and vacuum tunnel 1, vacuum chamber 5 using vacuum tube 10, extracts vacuum tunnel 1, vacuum chamber out as vacuum pump 9
The pipeline of air in 5.
Vacuum cabin door 8 of the invention includes left-hand door 12, right door 13, right door stepping motor gear 14, right front tooth item 15, the right side
Door stepper motor 16, left-hand door stepper motor 17, left-hand door rack gear 18, left-hand door stepping motor gear 19, left-hand door 12 and right door 13 are opened
The folding of as vacuum cabin door 8 is closed, right door stepper motor 16, left-hand door stepper motor 17 are fixed on vacuum insulation panel 4, right door
Stepping motor gear 14 is fixed in the rotary shaft of right door stepper motor 16, and right front tooth item 15 is connect with right door 13, is walked by right door
It drives right door stepping motor gear 14 to rotate into motor 16, and then is driven for right front tooth item 15, right front tooth item 15 is made to pull right door
13 is mobile, and left-hand door stepping motor gear 19 is fixed in the rotary shaft of left-hand door stepper motor 17, left-hand door rack gear 18 and left-hand door 12
Connection drives left-hand door stepping motor gear 19 to rotate, and then is driven for left-hand door rack gear 18 by left-hand door stepper motor 17, makes left-hand door
Rack gear 18 pulls left-hand door 12 mobile, and the rotation of You Youmen stepper motor 16, left-hand door stepper motor 17 drives right door 13 and a left side respectively
Door 12 is mobile, realizes the folding of vacuum cabin door 8.
Right door stepping motor gear 14 of the invention and right front tooth item 15, left-hand door stepping motor gear 19 and left-hand door rack gear
It is all made of rack pinion mode between 18, is opened and closed convenient for left-hand door 12 and right door 13, left-hand door 12 and right door 13 close to close,
Left-hand door 12 is split up into out with right door 13.
Control circuit board 6 of the invention is equipped with main control board, programmable logic controller (PLC), and main control board is to the
The information that one infrared sensor 3, the second infrared sensor 7 detect is handled, then controls the dynamic of programmable logic controller (PLC)
Make, then by the work of PLC controls right door stepper motor 16, left-hand door stepper motor 17, vacuum pump 9, when having
When people enters the investigative range of the first infrared sensor 3 or the second infrared sensor 7, main control board just control may be programmed and be patrolled
Controller action is collected, to make right door stepper motor 16, left-hand door stepper motor 17 that right door 13, left-hand door 12 be driven to separate, behaviour is mentioned
For channel, when people leaves the investigative range of the first infrared sensor 3 and the second infrared sensor 7, main control board is just controlled
Programmable logic controller (PLC) movement, to make right door stepper motor 16, left-hand door stepper motor 17 that right door 13, left-hand door 12 be driven to close
On, by way of this vulnerabilities scan forceful electric power, greatly improve the safety of electricity consumption.
Aircraft 2 of the invention include transport pod 20, operation bench 21, oxygen tank 22, seat 23, left rocket engine 24,
Left propellant container 25, right propellant container 26, right rocket engine 27, transport hatch door 28, the first telescope motor 29, servo-actuated wheel carrier
30, supporting roller 31, driving wheel 32, active wheel carrier 33, rotating electric machine 34, the second telescope motor 35, operation bench 21 are mounted on transport
The front of cabin 20 is equipped with identical oxygen tank 22 in 20 inner wall of transport pod, is for controlling the taking off of aircraft 2, braking
Soldier provides oxygen in transport pod 20, and seat 23 is arranged in transport pod 20, takes a seat for soldier, using left rocket engine 24
Dynamical system with right rocket engine 27 as aircraft 2, the left rocket engine 24 of left side installation of 20 appearance of transport pod,
Right rocket engine 27 is installed on right side, pushes aircraft 2 to advance jointly by left rocket engine 24 and right rocket engine 27,
The left and right sides of transport pod 20 is equipped with left propellant container 25, right propellant container 26, and left propellant container 25 is left rocket engine
24 provide solid propellant, and right propellant container 26 is that right rocket engine 27 provides solid propellant, the solid propellant of use
There are polyurethane, polybutadiene, end hydroxy butadiene, nitrate plasticising polyethers etc.；Transport hatch door is provided on transport pod 20
28, aircraft being passed in and out for military supplies, soldier, channel being provided, supporting roller 31 and driving wheel 32 are installed in 20 bottom of transport pod,
Help-fly is slided on transmitting station 11 for assisting in flying device 2, driving wheel is used as by driving wheel 32, supporting roller 31 assists driving wheel
32 mobile aircraft 2, are connected between supporting roller 31 and transport pod 20 using servo-actuated wheel carrier 30, the first telescope motor 29 is mounted on
Inside 20 front end of transport pod, and the telescopic rod of the first telescope motor 29 is connect with servo-actuated wheel carrier 30, for controlling supporting roller 31
State is connected between driving wheel 32 and transport pod 20 using active wheel carrier 33, and the second telescope motor 35 and rotating electric machine 34 are installed
Inside 20 front end of transport pod, and the telescopic rod of the first telescope motor 29 is connect with active wheel carrier 33, for controlling driving wheel 32
State, rotating electric machine 34 is for driving driving wheel 32 to rotate, when aircraft 2 is static or when sliding on transmitting station 11, first
Telescope motor 29 declines servo-actuated wheel carrier 30, so that supporting roller 31 drops to contact transmitting station 11, meanwhile, the second telescope motor
35 decline active wheel carrier 33, so that driving wheel 32 contacts transmitting station 11, by driving wheel 32, supporting roller 31, support is taken off jointly
Row device 2 is static on transmitting station 11 or slides, and after aircraft 2 takes off, the first telescope motor 29 is by servo-actuated wheel carrier 30 and is servo-actuated
It takes turns 31 pull-ups to be hidden in transport pod 20, active wheel carrier 33 and 32 pull-up of driving wheel are hidden in transport by the second telescope motor 35
In cabin 20.
Left rocket engine 24 of the invention, right rocket engine 27 use identical solid propellant rocket, are conducive to
Left rocket engine 24, right rocket engine 27 drive in a vacuum.
Operation bench 21 of the invention be equipped with start button, forwarding button, backspace button, accelerate button, retard button,
Stop button, laser radar, controller, start button, backspace button, accelerate button, retard button, braking to press at forwarding button
Button, laser radar are connect with controller, and start button is for opening aircraft, and when pressing forwarding button, controller is just controlled
Rotating electric machine 34 drives driving wheel 32 to rotate, and makes driving wheel 32 that aircraft 2 be driven to run on transmitting station 11, controls simultaneously
Left rocket engine 24, right rocket engine 27 rotate, and press backspace button, aircraft 2 will fall backward on transmitting station 11
It walks, presses acceleration button, rotating electric machine 34, left rocket engine 24, right rocket engine 27 will accelerate to rotate, when actively
After 32 promotion aircraft 2 of wheel sails out of transmitting station 11, continue to accelerate, so that left rocket engine 24, right rocket engine 27 drive
Aircraft flies in vacuum tunnel 1, presses retard button, and the sliding speed of aircraft 2 and flying speed can be made to reduce, pressed
Lower stop button, aircraft 2 will be out of service, and laser radar is mounted on 21 front of operation bench, for guiding for aircraft 2
Course line, after Airborne Lidar, which measures aircraft 2, sails out of transmitting station 11, controller just controls the first telescope motor 29 and will be servo-actuated
Wheel carrier 30 is packed up, and the second telescope motor 35 of control packs up active wheel carrier 33, when Airborne Lidar measures aircraft 2 close to hair
When penetrating platform 11, controller controls the first telescope motor 29 and puts down servo-actuated wheel carrier 30, controls the second telescope motor 35 for driving wheel
Frame 33 is put down, so that driving wheel 32 and supporting roller 31 drive aircraft 2 to slide and place on transmitting station 11.
Active wheel carrier 33 of the invention include the first spur gear 36, first shaft coupling 37, the first spur bevel gear 38,
Second spur bevel gear 39, wheel shaft 40, third spur bevel gear 41, the 4th spur bevel gear 42, second shaft coupling
43, internal gear 44, the second spur gear 45, gear casing 46, gear casing 46 are connected with the rotary shaft of rotating electric machine 34, internal tooth
Wheel 44 is fixed on gear casing 46, and the first spur gear 36 and the second spur gear 45 are mounted in internal gear 44, first shaft coupling
37 are connected between the first spur gear 36 and the second spur bevel gear 39, and second shaft coupling 43 is connected to the second spur gear 45
Between third spur bevel gear 41, after wheel shaft 40 passes through the first spur bevel gear 38 and the 4th spur bevel gear 42
Connect driving wheel 32, the first spur bevel gear 38 and the second spur bevel gear 39, third spur bevel gear 41 and the 4th
It is driven between spur bevel gear 42 using the helical bevel gear kind of drive, drives gear casing 46 to rotate by rotating electric machine 34,
It to drive internal gear 44 to rotate, then is the first spur gear 36, the transmission of the second spur gear 45, the first spur gear 36 drives first
Shaft coupling 37 rotates, and then drives the rotation of the second spur bevel gear 39, and the second spur bevel gear 39 is the first straight bevel
Gear 38 is driven, and the second spur gear 45 drives second shaft coupling 43 to rotate, and then third spur bevel gear 41 is driven to rotate,
Third spur bevel gear 41 is the transmission of the 4th spur bevel gear 42, by the first spur bevel gear 38 and the 4th straight-tooth circle
Bevel gear 42 drives wheel shaft 40 to rotate jointly, so that driving wheel 32 rotates, so that aircraft 2 be driven to move on transmitting station 11.
Internal gear is used between first spur gear 36 of the invention and internal gear 44, the second spur gear 45 and internal gear 44
The kind of drive rotates in one direction convenient for the first spur bevel gear 38 and the 4th spur bevel gear 42.
Dynamical system of the invention can also be the magnetic suspension way of propelling, using the structure of magnetically attractive formula magnetic levitation vehicle as
Dynamical system.
The working principle and working process of the present invention is as follows:
As shown in Figure 3 and Figure 5, when someone enters the investigative range of the first infrared sensor 3 or the second infrared sensor 7,
Main control board is transmitted this information to, main control board just controls programmable logic controller (PLC) movement, to make right Men Bujin
Motor 16, left-hand door stepper motor 17 drive right door 13, left-hand door 12 to separate, and provide channel for military supplies, soldier etc., when people from
When opening the investigative range of the first infrared sensor 3 and the second infrared sensor 7, main control board, master control are transmitted this information to
Circuit board just controls programmable logic controller (PLC) movement, so that right door stepper motor 16, left-hand door stepper motor 17 be made to drive right door
13, left-hand door 12 closes, and vacuum tunnel 1 and vacuum chamber 5 are kept apart；Main control board controls programmable logic controller (PLC) simultaneously
Movement, and then the air in the control extraction of vacuum pump 9 vacuum tunnel 1, vacuum chamber 5, provide vacuum flight environment for aircraft 2；
Start button opens aircraft 2, and when pressing forwarding button, controller just controls rotating electric machine 34 and drives driving wheel
32 rotations, make driving wheel 32 that aircraft 2 be driven to run on transmitting station 11, while controlling left rocket engine 24, right rocket
Engine 27 rotates, and presses backspace button, aircraft 2 will on transmitting station 11 inverted walk backward, press acceleration button, rotate
Motor 34, left rocket engine 24, right rocket engine 27 will accelerate to rotate, when driving wheel 32 pushes aircraft 2 to sail out of hair
After penetrating platform 11, continue to accelerate, so that left rocket engine 24, right rocket engine 27 drive aircraft 2 in vacuum tunnel 1
Retard button is pressed in flight, and controller will control the deceleration of rotating electric machine 34, so that cunning of the aircraft 2 on transmitting station 11
Scanning frequency degree reduces, and also can control the speed reduction of left rocket engine 24, right rocket engine 27, achievees the purpose that deceleration, press
Lower stop button, left rocket engine 24, right rocket engine 27, rotating electric machine 34 will stop operating, so that aircraft 2
Out of service, laser radar is that aircraft 2 guides course line, after Airborne Lidar, which measures aircraft 2, sails out of transmitting station 11, control
Device processed just controls the first telescope motor 29 and packs up servo-actuated wheel carrier 30, and the second telescope motor 35 of control packs up active wheel carrier 33,
When Airborne Lidar measures aircraft 2 close to transmitting station 11, controller controls the first telescope motor 29 and puts servo-actuated wheel carrier 30
Under, the second telescope motor 35 of control puts down active wheel carrier 33, so that driving wheel 32 and supporting roller 31 drive aircraft 2 sending out
It penetrates on platform 11 and slides and place.
Claims (10)
1. a kind of military superelevation velocity of sound flight system, it is characterised in that: including vacuum tunnel, aircraft, the first infrared sensor,
Vacuum insulation panel, vacuum chamber, control circuit board, the second infrared sensor, vacuum cabin door, vacuum pump, vacuum tube, transmitting station, very
Empty tunnel is located underground, connection every main military area command and the point that war easily occurs, and is extracted out the air in tunnel by vacuum pump, is
The aircraft provides vacuum flight environment, the both ends of the vacuum tunnel be arranged identical first infrared sensor,
Vacuum insulation panel, vacuum chamber, control circuit board, the second infrared sensor, vacuum cabin door, vacuum pump, vacuum tube, transmitting station, institute
It states vacuum chamber to connect with the vacuum tunnel, is kept apart the vacuum chamber and the vacuum tunnel by the vacuum insulation panel,
The vacuum cabin door is equipped on the vacuum insulation panel, for providing channel for military supplies, soldier etc., the vacuum chamber is used
In providing forevacuum environment, air enters the vacuum tunnel, the first infrared biography when preventing the vacuum cabin door from opening
Sensor is mounted on the vacuum insulation panel, and in vacuum tunnel one side, the control circuit board and described second red
Outer sensor is mounted on the vacuum insulation panel, and in the vacuum chamber one side, first infrared sensor is for examining
Survey in the vacuum tunnel whether someone is into the vacuum chamber, second infrared sensor is for detecting the vacuum chamber
In whether someone is into the vacuum tunnel, the folding of the vacuum cabin door is controlled by the control circuit board, and control institute
Vacuum pump work is stated, the transmitting station is additionally provided in the vacuum tunnel and the vacuum insulation panel, for assisting the flight
Device takes off and parks, and the identical vacuum pump, the vacuum pump are mounted on beside the vacuum tunnel, the vacuum chamber
It is connect between the vacuum tunnel, the vacuum chamber using the vacuum tube, extracts the vacuum tunnel out as the vacuum pump
The pipeline in road, air in the vacuum chamber.
2. military superelevation velocity of sound flight system according to claim 1, it is characterised in that: the vacuum cabin door includes a left side
Door, You Men, right door stepping motor gear, right front tooth item, right door stepper motor, left-hand door stepper motor, left-hand door rack gear, left-hand door stepping
The folding of motor gear, the left-hand door and the right door is the folding of the vacuum cabin door, the right door stepper motor, described
Left-hand door stepper motor is fixed on the vacuum insulation panel, and the right door stepping motor gear is fixed on the right door stepper motor
Rotary shaft on, the right front tooth item is connect with the right door, drives the right door stepper motor by the right door stepper motor
Gear rotation, and then be the right door rack-driving, so that the right front tooth item is pulled the right Men Yidong, the left-hand door stepping electricity
Machine gear is fixed in the rotary shaft of the left-hand door stepper motor, and the left-hand door rack gear is connect with the left-hand door, by the left-hand door
Stepper motor drives the left-hand door stepping motor gear rotation, and then is the left-hand door rack-driving, draws the left-hand door rack gear
It is mobile to move the left-hand door, the right door and institute are driven by the rotation of the right door stepper motor, the left-hand door stepper motor respectively
It is mobile to state left-hand door, realizes the folding of the vacuum cabin door.
3. military superelevation velocity of sound according to claim 2 flies system, it is characterised in that: the aircraft include transport pod,
Operation bench, oxygen tank, seat, left rocket engine, left propellant container, right propellant container, right rocket engine, transport hatch door,
First telescope motor, servo-actuated wheel carrier, supporting roller, driving wheel, active wheel carrier, rotating electric machine, the second telescope motor, the operation bench
It is mounted in front of the transport pod, for controlling the taking off of the aircraft, braking, phase is installed in the transport pod inner wall
The same oxygen tank, provides oxygen for soldier in the transport pod, the seat is arranged in the transport pod, just for soldier
It sits, the dynamical system using the left rocket engine and the right rocket engine as the aircraft, the transport pod
The left rocket engine is installed in the left side of appearance, right rocket engine is installed on the right side, by the left rocket engine and
The right rocket engine pushes the aircraft to advance jointly, is equipped with the left propellant at left and right sides of the transport pod
Case, the right propellant container, the respectively described left rocket engine and the right rocket engine provide solid propellant, use
Solid propellant have polyurethane, polybutadiene, end hydroxy butadiene, nitrate plasticising polyethers etc.；It is set on the transport pod
It is equipped with the transport hatch door, passes in and out aircraft passageway for soldier, the supporting roller and the master are installed in the transport pod bottom
Driving wheel uses between the supporting roller and the transport pod for assisting the aircraft to slide help-fly on the transmitting station
The servo-actuated wheel carrier connection, first telescope motor is mounted on inside the transport pod front end, and first telescope motor
Telescopic rod connect with the servo-actuated wheel carrier, for controlling the state of the supporting roller, the driving wheel and the transport pod it
Between using the active wheel carrier connect, second telescope motor and the rotating electric machine are mounted in the transport pod front end
Portion, and the telescopic rod of first telescope motor is connect with the active wheel carrier, it is described for controlling the state of the driving wheel
Rotating electric machine is for driving the driving wheel to rotate.
4. military superelevation velocity of sound flight system according to claim 3, it is characterised in that: the left rocket engine, the right side
Rocket engine uses identical solid propellant rocket.
5. military superelevation velocity of sound flight system according to claim 4, it is characterised in that: the active wheel carrier includes first
Spur gear, first shaft coupling, the first spur bevel gear, the second spur bevel gear, wheel shaft, third spur bevel gear,
Four spur bevel gears, second shaft coupling, internal gear, the second spur gear, gear casing, the gear casing and the electric rotating
The rotary shaft of machine is connected, and the internal gear is fixed on the gear casing, first spur gear and second spur gear
Be mounted in the internal gear, the first shaft coupling be connected to first spur gear and second spur bevel gear it
Between, the second shaft coupling is connected between second spur gear and the third spur bevel gear, and the wheel shaft passes through
The driving wheel, the first straight bevel tooth are connected after first spur bevel gear and the 4th spur bevel gear
Tooth is bored using helical teeth between wheel and the second straight bevel tooth, third spur bevel gear and the 4th spur bevel gear
Kind of drive transmission is taken turns, drives the gear casing to rotate by the rotating electric machine, so that the internal gear is driven to rotate, then for
First spur gear, second Spur Gear Driving, first spur gear drive the first shaft coupling rotation, and then band
The second spur bevel gear rotation is moved, second spur bevel gear is first spur bevel gear transmission, institute
It states the second spur gear and drives the second shaft coupling rotation, and then drive the third spur bevel gear rotation, the third
Spur bevel gear is the 4th spur bevel gear transmission, by first spur bevel gear and the 4th straight-tooth circle
Bevel gear drives wheel shaft to rotate jointly, so that the driving wheel rotates, so that the aircraft be driven to transport on the transmitting station
It is dynamic.
6. military superelevation velocity of sound flight system according to claim 5, it is characterised in that: first spur gear and internal tooth
Internal gear transmission mode is used between wheel, the second spur gear and internal gear, convenient for first spur bevel gear and described the
Four spur bevel gears rotate in one direction.
7. military superelevation velocity of sound aircraft according to claim 1, it is characterised in that: every 50 meters by the vacuum tunnel
One vacuum pump is installed, for extracting the air in the vacuum tunnel out.
8. military superelevation velocity of sound flight system according to claim 2, it is characterised in that: the control circuit board is equipped with
Main control board, programmable logic controller (PLC), main control board detect the first infrared sensor, the second infrared sensor
Information is handled, then controls the movement of programmable logic controller (PLC), then by the right door stepping electricity of PLC controls
The work of machine, left-hand door stepper motor, vacuum pump, when someone enters the detection model of the first infrared sensor or the second infrared sensor
When enclosing, main control board just controls programmable logic controller (PLC) movement, so that right door stepper motor, left-hand door stepper motor be made to drive
Right door, left-hand door are separated, provide channel for people, when people leaves the investigative range of the first infrared sensor and the second infrared sensor
When, main control board just controls programmable logic controller (PLC) movement, so that it is right to drive right door stepper motor, left-hand door stepper motor
Door, left-hand door close.
9. military superelevation velocity of sound flight system according to claim 5, it is characterised in that: first spur gear and internal tooth
Internal gear transmission mode is used between wheel, the second spur gear and internal gear.
10. military superelevation velocity of sound flight system according to claim 2, it is characterised in that: the right door stepper motor tooth
Rack pinion mode is all made of between wheel and right front tooth item, between left-hand door stepping motor gear and left-hand door rack gear.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910166066.0A CN110027708A (en) | 2019-03-06 | 2019-03-06 | A kind of military superelevation velocity of sound flight system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910166066.0A CN110027708A (en) | 2019-03-06 | 2019-03-06 | A kind of military superelevation velocity of sound flight system |
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| CN201910166066.0A Pending CN110027708A (en) | 2019-03-06 | 2019-03-06 | A kind of military superelevation velocity of sound flight system |
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