CN109850143A - A kind of hypersonic aircraft surface plasma DC pulse gesture stability secondary propulsion system (SPS) - Google Patents
A kind of hypersonic aircraft surface plasma DC pulse gesture stability secondary propulsion system (SPS) Download PDFInfo
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Abstract
The present invention relates to a kind of hypersonic aircraft surface plasma DC pulse gesture stability secondary propulsion system (SPS)s, belong to aircraft power technical field.Outer surface is embedded in 4 pairs of electrode strips up and down along direction of motion perpendicular separation, every a pair of electrode strip is made of IN1 electrode strip and IN2 antithesis electrode strip, auxiliary propulsion and gesture stability are realized by aircraft surface plasma direct-current pulse, pass through two groups of DC pulse plasma drivings of driving；It is four, upper and lower, left and right region in hypersonic aircraft surface segmentation, each region is there are two types of electrode IN1 and IN2, and two arrays of electrodes voltage pulse polarity is on the contrary, by driving double DC pulse plasma drivings；Use DC pulse plasma driving PWM modulation system using AT89S52 single-chip microcontroller as control core, it is made of order input module, LED display module and DC pulse power amplification drive module, realize digital accurate control, revolutionize the propulsion mode of aircraft, it is more energy efficient, the source of aircraft surface resistance is eliminated from principle, with development potential.
Description
Technical field
The present invention relates to a kind of hypersonic aircraft surface plasma DC pulse gesture stability secondary propulsion system (SPS)s, belong to
In aviation power technical field.
Background technique
The technological difficulties of hypersonic aircraft: (1) dynamical system: at present using being jet engine, usually by air inlet
Road, compressor, combustion chamber, turbine and jet pipe composition.Since high-temperature turbine is mounted on same axis with compressor, also drive
Dynamic pressure mechanism of qi rotation, thus the air of compression sucking repeatedly.The high-temperature high-pressure fuel gas flowed out from high-temperature turbine, in jet pipe
In continue to expand, be discharged backward with high speed from tail portion spout.This speed is more much bigger than the speed that air-flow enters engine, thus
The reaction thrust to engine is produced, aircraft flight forward is driven.Due to mechanism complexity, when speed reaches certain limit,
The revolving speed of high-temperature turbine can reach a limiting value；What is ground now is punching engine, and punching engine is airbreathing motor
One kind, it is reacted using the oxygen in atmosphere as all or part of oxidant with self-contained fuel, utilize
Structure member generates shock wave to compress to high-speed flow, realizes flow slowing down and pressurization.Start there are also a kind of ultra-combustion ramjet
Machine, through series of shock, system is compressed, and the air-flow of certain flow, temperature, pressure is provided for combustion chamber, convenient for the tissue of burning
Afterwards, it completes to push.Both engine problems faceds are that the process of generation shock wave is unstable.
(2) another problem encountered in hypersonic aircraft R&D process is exactly Aerodynamic Heating problem, i.e., so-called heat
Barrier.Due to the effect of shock wave and viscosity when it is mainly aircraft flight, ambient air temperature is sharply increased, is formed violent
Aerodynamic Heating environment keeps general Flight Vehicle Structure unbearable.To overcome thermal boundary, it is lowered into the pneumatic of aircraft as far as possible and adds
Heating rate, i.e. hot-fluid.Shi Youqi particular/special requirement is used as heat insulation material.First have to big specific heat, the material of such unit mass
Material could absorb more heats；Its is secondary high thermal conductivity, only in this way can just make the temperature difference of heat sink material will not be excessive,
Due to the fail temperature of heat sink material be generally not it is very high, to absorb a large amount of heat, must just increase significantly heat sink material
Quality forms more bulky heat-protection system.Radiative thermal protection mainly utilizes the radiation characteristic of material.It is exactly by the pneumatic of its surface
Heat distributes in the form of radiation again.Since radiant heat flux is directly proportional to the biquadratic of surface temperature, the radiation of selection
Heat insulation material will not only have outside high radiation character, but also there must also be low heat conductivities and high-temperature stability.
Sweat coolling solar heat protection is by achieving the purpose that solar heat protection from porous surface exuded fluid.Mainly by thermal chokes effect or matter
The mechanism of amount injection effect carrys out solar heat protection.Basic principle is, when fluid injects aircraft surface boundary layer, to send out boundary layer structure
Raw to change, thickness increases and temperature gradient is reduced, to reduce the convective heat transfer into aircraft.Aircraft uses sweating
Cooling solar heat protection advantage is the not variation of aerodynamic configuration awing, can also adapt to difference by controlling the seepage discharge of fluid
The thermal protection demand of size hot-fluid.The aperture that film cooling solar heat protection relies on aircraft surface sprays liquid or gas, on surface
The liquid film or air film for forming one layer very thin, aircraft surface and high-temperature gas are separated, and then liquid evaporation is absorbed heat, gas note
Enter boundary layer, generates thermal chokes effect, be lowered into the convective heat transfer of aircraft.Film cooling solar heat protection and above-mentioned Sweat coolling are anti-
Heat is similar.It is summed up in the point that Sweat coolling solar heat protection by many people.
Ablative thermal protection is by burning-off outer layer, to achieve the purpose that protect internal layer.Ablating heat shield due to it is effective, reliable, from
Adaptation, light-weight, simple process, it is easy to carry and storage the advantages that and be used widely.Intermediate range ballistic missile bullet returns
Formula satellite, spaceship, moon flight return capsule and space shuttle head and wing tail leading edge are returned, it is all anti-using ablation
Heat.By the development test and practical application of decades, a variety of ablators are researched and developed, the aircraft or winged for different purposes
The different parts of row device are selected.Ablative thermal protection is in current hypersonic aircraft thermal protection using a kind of most successful method.
The major defect of ablative thermal protection is disposable and since the aerodynamic configuration that ablation generates changes.The latter will affect and reenter boat
The stability of its device, impact accuracy and the liter resistance, the stability and control that reenter maneuvering flight and cruise vehicle.
From the point of view of present case, after hypersonic aircraft reaches certain speed, bottleneck is technically encountered, by
In the presence of thermal boundary, the energy of engine is greatly consumed, movement velocity is further increased, becomes more and more difficult.It is another
Aspect, since the surface of hypersonic aircraft is high-temperature plasma, plasma is charged particle stream, in the effect of electric field
Under can move, if giving an appropriate electric field, control electric field frequency and voltage can be passed through, realize high-temperature plasma
Directed movement, and realize gesture stability, this new technology can break through the technical bottleneck that hypersonic aircraft is encountered, pole
The energy consumption of big reduction engine.
Summary of the invention
The purpose of the present invention is to provide a kind of hypersonic aircraft surface plasma DC pulse gesture stability auxiliary
Propulsion system realizes auxiliary propulsion and gesture stability by aircraft surface plasma direct-current pulse.
The technical scheme is that IN1 electrode strip (2), IN2 antithesis electrode strip (3), manipulation push rod (4) and direct current arteries and veins
Rush plasma driving control system composition；
The entire outer surface of aircraft is embedded in 4 pairs of electrode strips up and down, every a pair of electrode strip along direction of motion perpendicular separation
It is made of IN1 electrode strip (2) and IN2 antithesis electrode strip (3), IN1 electrode strip (2), IN2 antithesis electrode strip (3) are mutually parallel
Arrangement；Aircraft skin layer uses high-temperature insulation material, polishes jointly after the electrode strip of surface layer insertion with aircraft skin layer,
Constitute smooth surface.
DC pulse power amplification drive module: directly adopt DC pulse to aircraft surface plasma directed driven into
Row control passes through two groups of DC pulse plasma drivings of driving；It is upper and lower, left and right four in hypersonic aircraft surface segmentation
A region, each region is there are two types of electrode IN1 and IN2, and two arrays of electrodes voltage pulse polarity is on the contrary, by driving double direct currents
Pulse plasma driving；Input terminal IN1 is discontinuous pulses signal Phi IN1=- Aexp (u1T), IN2 is another group of discontinuous pulses to+ω
Signal Phi IN2=Aexp (u2T), IN1 is identical with the IN2 pulse voltage exported and pulse duration frequency by+ω, two group pulse voltages
Existing unique difference is exactly that there are a small phase difference u2-u1=ω Δ t, wherein Δ t≤Δ L/v, Δ L are two groups of electricity
The spacing distance of relative position between pole；Work as u2-u1>=0, accelerate to be positive, at this point, around the positive and negative electrode of first group of electrode
The plasma for having accumulated opposite charges, in the moment that electrode voltage disappears, second group of positive and negative electrode occurs opposite positive and negative
Voltage is gathered in the plasma of first group of electrode surface to second group of electrode movement under the action of electrostatic；This movement exists
Hypersonic aircraft surface exists simultaneously, and mobile displacement is Δ L；Such process is repeated by pulse voltage,
Plasma is thereby realized in the movement on hypersonic surface；Work as u2-u1≤ 0, accelerate for negative sense, whole process forward direction phase
Together, but the moving direction of plasma surface on the contrary, allow for plasma and the movement in hypersonic flight body surface face in this way
It is contrary, and slow down；
It is identical further to principle used by direction controlling, if the pulse voltage phase of four groups of electrodes is completely the same,
Realize whole acceleration or deceleration；The two arrays of electrodes u of surface area2-u1>=0, then upper surface accelerates, and two groups of lower surface area
Electrode u2-u1≤ 0, then lower surface is slowed down, and aircraft can move downward, on the contrary then move upwards；The two arrays of electrodes in left surface region
u2-u1>=0, then left surface accelerates, the two arrays of electrodes u of right surface region2-u1≤ 0, then right surface is slowed down, and aircraft can be transported to the right
It is dynamic, it is on the contrary then move downward；u2-u1Between phase difference value be by control impulse phase realize；The power of phase impulse is adopted
Power amplification is carried out with power amplifier, to realize the control of DC pulse plasma driving force, as shown in Figure 1；
The set-up of control system has sensor, and temperature signal is inputted by the port PL1.1, for knowing aircraft surface temperature；
Acceleration signal is inputted by the port PL1.2, and for knowing the motion state of aircraft, gravity accelerometer signal passes through
The port PL1.3 input, for judging the relationship between aircraft and gravitational field；When flight is in automatic control state, flight
The control of posture is controlled by the gesture stability program write in advance, is inputted by the port PL1.0；
The power driven system provides electric energy by alternating current generator, charges after over commutation and pressure stabilizing to battery, battery
For DC pulse plasma driving control system module for power supply；6 11 kinds of working conditions are shared, are that 1. right power outputs are driven respectively
Dynamic control；2. left power output drive control；3. right control zone deceleration control；4. left control zone deceleration control；5.
Upper power output drive control；Power output drive control on 6.；7. lower control zone deceleration control；8. lower control zone is slowed down
Drive control；9. straight forward drive control；10. deceleration of keeping straight on control；11. reinforcing straight forward control.Driving output
Control and left power output drive control adjust hypersonic aircraft fortune by speed manipulation push rod (4) realization keypress function
Scanning frequency degree；
The major function of DC pulse plasma driving control system include: realize the acceleration that DC pulse plasma is driven,
The upper and lower, left and right direction controlling of deceleration and the driving of DC pulse plasma, by adjusting the driving of DC pulse plasma
Duty ratio changes high-voltage pulse frequency, can very easily realize the intelligent control of DC pulse plasma driving；System hardware
Module composition: (1) DC pulse plasma driving control system module；(2) L298 DC pulse power amplification drive module；
(3) LED display module；(4) push rod independent keyboard control module is manipulated.
Display module: the real-time display to pulse width modulation duty is realized using LED digital-scroll technique.
Manipulate push rod independent keyboard control module: the key of independent keyboard is mutually indepedent, each presses a bonded I/O
Mouth line, the key works state in an I/O mouth line will not influence the working condition of other I/O mouth lines.Therefore, by detecting I/
The level state of O mouth line can determine whether which key is pressed on keyboard, all keys are that dry reed switch is constituted, and be remotely controlled push rod
With magnetic force, the position for being remotely controlled push rod is different, and the button data provided changes, and impulse phase control can be soft by writing
Part program carries out identification control；When manipulating push rod (4) forward, KEYE is connected, left and right sides two arrays of electrodes pulse while same-phase
Driving, aircraft are moved to front；Push rod (4) Xiang Zuoqian, KEYA conducting are manipulated, front left side dry reed switch is connected, aircraft
Into left side drive mode, aircraft divertical motion to the left；Before manipulating push rod to the right, KEYB conducting, forward right side dry reed switch is connect
Logical, drive mode on the left of aircraft, aircraft turns right；In the state of not pushing manipulation push rod, manipulation push rod is equipped with back
Position spring, returns to interposition, and any key is all not switched on, and all dry reed switch are in an off state, all driving dresses
It sets in no current state, aircraft stop motion；Manipulate push rod (4) Xiang Zuohou, KEYC conducting；Manipulate push rod (4) backward,
KEYF conducting, into deceleration mode；When manipulation push rod (4) is exerted oneself forward, KEYG conducting, into mode is accelerated, four groups of electrodes are electric
Press pulse frequency and voltage pulse high level of synchronization, u2-u1=ω Δ t, wherein Δ t < Δ L/v is in Afterburning condition, and aircraft accelerates
Movement.
The working principle of the invention is: directlying adopt DC pulse and controls to aircraft surface plasma directed driven
System passes through two groups of DC pulse plasma drivings of driving；The surface of aircraft (1) is divided into four regions up and down, such as
Shown in Fig. 3, aircraft left side surface plasma pressure surface constitutes left power-section, and surface plasma pressure surface is constituted on the right of aircraft
Right power-section；Electric drive system is independently installed in each powering region, and two electric drive system structures are identical；It is right
After powering region is divided, aircraft turn to when, the aircraft left side left power-section of surface plasma pressure surface and fly
Gas stream on the right of row device between the right power-section of surface plasma pressure surface has differences, so that it may realize the steering of aircraft；
Each region is there are two types of electrode IN1 and IN2, and two arrays of electrodes voltage pulse polarity is on the contrary, by driving double direct current arteries and veins
Rush plasma driving；Input terminal IN1 is discontinuous pulses signal Phi IN1=- Aexp (u1T), IN2 is another group of discontinuous pulses letter to+ω
Number Φ IN2=Aexp (u2T), IN1 is identical with the IN2 pulse voltage exported and pulse duration frequency by+ω, and two group pulse voltages are deposited
Unique difference be exactly that there are a small phase difference u2-u1=ω Δ t, wherein Δ t≤Δ L/v, Δ L are two arrays of electrodes
Between relative position spacing distance；Work as u2-u1>=0, accelerate to be positive, at this point, around the positive and negative electrode of first group of electrode
The plasma for having accumulated opposite charges, in the moment that electrode voltage disappears, there is opposite positive negative electricity in second group of positive and negative electrode
Pressure is gathered in the plasma of first group of electrode surface to second group of electrode movement under the action of electrostatic；This movement is in height
Supersonic aircraft surface exists simultaneously, and mobile displacement is Δ L；Such process is repeated by pulse voltage, this
Sample is achieved that plasma in the movement on hypersonic surface；Work as u2-u1≤ 0, accelerate for negative sense, whole process forward direction is identical,
But the moving direction of plasma surface on the contrary, allow for the plasma and the direction of motion in hypersonic flight body surface face in this way
On the contrary, and slowing down；DC pulse plasma driving adjust PWM(pulse width modulation) be by control fixed voltage direct current
Power switch frequency, modulating pulse width, if set of pulses width and another group pulse width are different, two groups of DC pulses
Pulsewidth there are a difference, this difference meets u2-u1=ω Δ t is achieved that the control of two group pulse phase differences.
The power driven system provides electric energy by alternating current generator, charges after over commutation and pressure stabilizing to battery, stores
Battery is DC pulse plasma driving control system module for power supply；6 11 kinds of working conditions are shared, are that 1. right power are defeated respectively
Drive control out；2. left power output drive control；3. right control zone deceleration control；4. left control zone deceleration control
System；Power output drive control on 5.；Power output drive control on 6.；7. lower control zone deceleration control；8. lower control
The control of area's deceleration；9. straight forward drive control；10. deceleration of keeping straight on control；11. reinforcing straight forward control.It drives
Dynamic output control and left power output drive control realize keypress function by speed manipulation push rod (4) to adjust hypersonic fly
The row device speed of service；
Driving force output: the present invention uses L298 DC pulse power amplification drive module, and inside includes 4 channel logics driving electricity
Road, rated operational current are 1 A, maximum up to 1.5 A, Vss voltage 4.5 V of minimum, maximum up to 36 V；Vs electricity
Pressing maximum value is also 36 V.In the case of small-power, L298N can directly adopt DC pulse and orient to aircraft surface plasma
Driving is controlled, and without isolation circuit, in high-power situation, L298N output connects power amplifier, is exported through power amplification
Afterwards, double DC pulse plasma drivings are driven；
In the control and driving to DC pulse plasma driving voltage, semiconductor power device (L298) in use can be with
Be divided into two ways: Linear Amplifer driving method and switch driving method are in Linear Amplifer driving method.The present invention uses the latter.
Semiconductor power device work is that control principle is simple in linear zone advantage, and output pulsation is small, good linearity, is interfered proximate circuitry
Small, disadvantage is that power device works in linear zone, and power is low and heat dissipation problem is serious.Switching driving method is to make semiconductor power
Device work controls the voltage of DC pulse plasma driving by arteries and veins modulation (PWM), to realize direct current in switch state
The control of pulse plasma driving.
Drive control structure: DC pulse plasma drives PWM modulation system using AT89S52 single-chip microcontroller as control core,
It is made of order input module, LED display module and DC pulse plasma drive module.Using with the independent keyboard interrupted
As the input of order, under program, timing is constantly sent single-chip microcontroller to L298 DC pulse power amplification driving chip
PWM waveform, driving circuit complete the control of DC pulse plasma driving direction；Single-chip microcontroller is ceaselessly by PWM pulsewidth modulation simultaneously
Duty ratio is sent to LED charactrons and completes real-time display.
The major function of DC pulse plasma driving control system includes: to realize to add DC pulse plasma driving
The direction controlling that speed, deceleration and DC pulse plasma drive, the duty ratio of adjustment DC pulse plasma driving, can be very
The convenient intelligent control for realizing the driving of DC pulse plasma.System hardware module composition: (1) single chip control module；(2)
L298 DC pulse power amplification drive module；(3) LED display module；(4) stand-alone keypad control module.Referring to fig. 4.
Main body circuit: i.e. DC pulse plasma driving control system module.This partial circuit is mainly by AT89S52 monolithic
The acceleration of the control DC pulse plasma driving such as the port I/O of machine, timer conter, expansion of external interrupt is slowed down and straight
The forward and reverse of pulse plasma driving, and the duty ratio of adjustable DC pulse plasma driving are flowed, it can be very square
Just the intelligent control for realizing the driving of DC pulse plasma.It is the arteries and veins that adjustable pulse width is generated by AT89S52 single-chip microcontroller therebetween
It rushes signal and is input to L298 driving chip to control the driving work of DC pulse plasma.DC pulse plasma driving
Control system is made of following circuits module:
Importation: this module is mainly to drive to realize to DC pulse plasma using with the independent keyboard interrupted
Acceleration, deceleration and DC pulse plasma drive control.
Control section: it is mainly made of the expansion of external interrupt circuit of AT89S52 single-chip microcontroller.The driving of DC pulse plasma
Control system realizes that part is mainly driven by some diodes, the driving of DC pulse plasma and L298 DC pulse power amplification
Module composition.
Display portion: LED digital display part realizes the real-time display to PWM pulse width modulation duty.
PWM pulsewidth modulation: the modulation of PWM(pulse width is adjusted in the driving of DC pulse plasma) it is by controlling fixed voltage
DC power supply switch frequency, modulating pulse width, if set of pulses width and another group pulse width are different, two groups of direct currents
There are a difference, this differences to meet u for the pulsewidth of pulse2-u1=ω Δ t is achieved that the control of two group pulse phase differences.
In the adjustment system of PWM drive control, power supply is switched on and off by a fixed frequency, and change one as needed
The length of " on " and "off" time in a period." the duty of voltage on armature is driven by changing DC pulse plasma
Than " come achieve the purpose that change average voltage size, thus come control DC pulse plasma driving duty ratio.Also just because of
In this way, PWM is otherwise known as " driving mechanism for switch ".When we change duty ratio D=t1/T, so that it may obtain different direct currents
Pulse plasma drives average speed Vd, to achieve the purpose that speed regulation.Strictly speaking, average speed Vd and duty ratio D is not
Stringent linear relationship, but in general application, we approximately can regard it as linear relationship.The present invention uses
Timing mode of the timer as pulse-width controlled, the pulse width that this mode generates is extremely accurate, and error is only in several us.Directly
The speed of stream pulse plasma driving is divided into 100 grades, therefore a cycle just has 100 pulses, and the period is 100 arteries and veins
The time of punching, speed class correspond to the number of the high level pulse of a cycle.Duty ratio is that high level pulse number accounts for one
The percentage of period overall pulse number.It is pulse high-voltage multiplied by duty that a cycle DC pulse plasma, which drives end voltage,
Than.Duty ratio is bigger, and DC pulse plasma drives end voltage bigger, and the driving rotation of DC pulse plasma is faster.Direct current arteries and veins
The average speed for rushing plasma driving is equal to DC pulse plasma drives under certain duty ratio maximum speed multiplied by accounting for
Empty ratio.When we change duty ratio, so that it may different DC pulse plasma driving average speed is obtained, to reach tune
The purpose of speed.It accurately says, average speed and duty ratio are not stringent linear relationship, in general application, can be incited somebody to action
Its approximation is seen linear.
AT89S52 of the present invention is a kind of low-power consumption, 8 8-digit microcontroller of high-performance CMOS, has 8K in system
Programmable Flash memory.The upper Flash of AT89S52 allows program storage in-system programmable components, is also adapted to conventional programming device.
It is mutually indepedent to manipulate push rod independent keyboard key, a bonded I/O mouth line is each pressed, in an I/O mouth line
Key works state will not influence the working condition of other I/O mouth lines.Therefore, pass through the level state of detection I/O mouth line
Judge which key is pressed on keyboard, all keys are that dry reed switch is constituted, and remote control push rod has magnetic force, are remotely controlled the position of push rod
Difference is set, the button data provided changes, and can carry out identification control by writing software program.Directly apply
The software approach of AT89S52 realizes pwm signal output, this is more at low cost than hardware realization pwm signal, limitation is few, it is convenient to realize.
The beneficial effects of the present invention are: the plasma of aircraft surface directly constitutes load, the lotus of plasma is utilized
Electrical characteristics are classified plasma by positive and negative charge using one group of electrode, and adjacent electrode known to another group is to add a pole
Property opposite electrostatic field push plasma to move backward so that moving under the action of Electrostatic Plasmas field, due to electricity
Pole collection has been covered with entire aircraft surface, so that the plasma on its surface is mobile simultaneously, the high temperature of aircraft surface gas
Plasma gas resistance is changed into the motive force of aircraft surface gas, the movement of auxiliary drive aircraft, so that energy consumption is greatly
It reduces.It uses DC pulse plasma driving PWM modulation system using AT89S52 single-chip microcontroller as control core, mould is inputted by order
Block, LED display module and DC pulse plasma drive module composition realize digital accurate control, revolutionize aircraft
Propulsion mode, it is more energy saving, the source of aircraft resistance is completely eliminated from principle, with development potential.The present invention is thorough
Bottom changes the propulsion mode of aircraft, and energy conservation and environmental protection completely eliminates hypersonic aircraft surface plasma from principle
The resistance of body has good development potentiality.
Detailed description of the invention
Fig. 1 is the relational graph of position and pulse voltage；
The relational graph of Fig. 2 time and pulse voltage；
Fig. 3 aircraft surface control partition schematic diagram；
Fig. 4 system structure schematic diagram；
Fig. 5 system, control circuit figure；
Fig. 6 control lever key schematic diagram.
Each label in figure are as follows: 1- aircraft, 2-IN1 electrode strip, 3-IN2 antithesis electrode strip, 4- manipulate push rod.
Specific embodiment
With reference to the accompanying drawings and examples, the invention will be further described, but the contents of the present invention be not limited to it is described
Range.
Embodiment 1: hypersonic aircraft surface plasma DC pulse gesture stability secondary propulsion system (SPS) is by IN1 electrode
Item (2), IN2 antithesis electrode strip (3), manipulation push rod (4) and DC pulse plasma driving control system are constituted；
The entire outer surface of aircraft is made of ceramic material；Outer surface is embedded in up and down 4 along direction of motion perpendicular separation
To electrode strip, every a pair of electrode strip is made of IN1 electrode strip (2) and IN2 antithesis electrode strip (3), IN1 electrode strip (2), IN2 pairs
Even electrode strip (3) is mutually arranged in parallel；It polishes jointly after the electrode strip of ceramic surface insertion with aircraft skin layer, constitutes light
Sliding surface；
Auxiliary propulsion and gesture stability are realized by aircraft surface plasma direct-current pulse, pass through two groups of DC pulses of driving etc.
Ion-drive；It is four, upper and lower, left and right region in hypersonic aircraft surface segmentation, there are two types of electrodes in each region
IN1 and IN2, two arrays of electrodes voltage pulse polarity is on the contrary, by driving double DC pulse plasma drivings；Between input terminal IN1 is
Disconnected pulse signal Φ IN1=- Aexp (u1T), IN2 is another group of discontinuous pulses signal Phi IN2=Aexp (u to+ω2+ ω t), IN1 with
The pulse voltage of IN2 output is identical with pulse duration frequency, and unique difference existing for two group pulse voltages is exactly micro- there are one
Small phase difference u2-u1=ω Δ t, wherein Δ t≤Δ L/v, Δ L are the spacing distances of the relative position between two arrays of electrodes；When
u2-u1>=0, accelerate to be positive, at this point, the plasma for having accumulated opposite charges around the positive and negative electrode of first group of electrode,
There is opposite generating positive and negative voltage, under the action of electrostatic, are gathered in first in the moment that electrode voltage disappears, second group of positive and negative electrode
The plasma of group electrode surface is to second group of electrode movement；This movement exists simultaneously on hypersonic aircraft surface, moves
Dynamic displacement is Δ L；Such process is repeated by pulse voltage, thereby realizes plasma hypersonic
The movement on surface；Work as u2-u1≤ 0, accelerate for negative sense, whole process forward direction is identical, but the moving direction phase of plasma surface
Instead, the plasma in hypersonic flight body surface face is allowed in this way with the direction of motion on the contrary, and slowing down；DC pulse etc.
Ion-drive tune PWM(pulse width modulation) be by control fixed voltage DC power supply switch frequency, modulating pulse width,
If set of pulses width and another group pulse width are different, for the pulsewidth of two groups of DC pulses there are a difference, this is poor
Value meets u2-u1=ω Δ t is achieved that the control of two group pulse phase differences；
It is identical for principle used by direction controlling, if the pulse voltage phase of four groups of electrodes is completely the same, realize whole
Body acceleration or deceleration；The two arrays of electrodes u of surface area2-u1>=0, then upper surface accelerates, the two arrays of electrodes u of lower surface area2-
u1≤ 0, then lower surface is slowed down, and aircraft can move downward, on the contrary then move upwards；The two arrays of electrodes u in left surface region2-u1≥
0, then left surface accelerates, the two arrays of electrodes u of right surface region2-u1≤ 0, then right surface is slowed down, and aircraft can move right, on the contrary
Then move downward；u2-u1Between phase difference value be by control impulse phase realize；The power of phase impulse uses power
Amplifier carries out power amplification, to realize the control of DC pulse plasma driving force.
The set-up of control system has sensor, and temperature signal is inputted by the port PL1.1, for knowing aircraft surface temperature
Degree；Acceleration signal is inputted by the port PL1.2, for knowing the motion state of aircraft, gravity accelerometer signal
It is inputted by the port PL1.3, for judging the relationship between aircraft and gravitational field；When flight is in automatic control state,
The control of flight attitude is controlled by the gesture stability program write in advance, is inputted by the port PL1.0；
The power driven system provides electric energy by generator, charges after over commutation and pressure stabilizing to two group storage batteries, battery
Cathode output end is A, and cathode output end B, battery is DC pulse plasma driving control system module for power supply (such as Fig. 6
It is shown), six kinds of job control states are shared, are power output drive control on 1. respectively；2. lower power output drive control；3.
Left power output drive control；4. right power output drive control；5. straight forward drive control；Control model is divided into artificial control
System and process control；Manual control realizes keypress function by manipulation push rod (4) to realize；
The major function of DC pulse plasma driving control system include: realize the acceleration that DC pulse plasma is driven,
The upper and lower, left and right direction controlling of deceleration and the driving of DC pulse plasma, by adjusting the driving of DC pulse plasma
Duty ratio changes high-voltage pulse frequency, can very easily realize the intelligent control of DC pulse plasma driving；System hardware
Module composition: (1) DC pulse plasma driving control system module；(2) L298 DC pulse power amplification drive module；
(3) LED display module；(4) push rod independent keyboard control module is manipulated.
Under automatic control mode, the control of flight attitude is controlled by preset program；In manual control mould
It under formula, is controlled using input key, used key is mutually indepedent, each presses a bonded I/O mouth line, an I/O
Key works state in mouth line will not influence the working condition of other I/O mouth lines.Therefore, pass through the level of detection I/O mouth line
State can determine whether which key is pressed on keyboard, all keys are that dry reed switch is constituted, and manipulation push rod has magnetic force, behaviour
The position for controlling push rod is different, and the button data provided changes, and impulse phase control can be carried out by writing software program
Identification control；When manipulating push rod (4) forward, KEYE conducting, left and right sides two arrays of electrodes pulse same-phase driving simultaneously, aircraft
It is moved to front；Push rod (4) Xiang Zuoqian, KEYA conducting are manipulated, front left side dry reed switch is connected, and aircraft enters left side driving
Mode, aircraft divertical motion to the left；Before manipulating push rod to the right, KEYB conducting, forward right side dry reed switch is connected, on the left of aircraft
Drive mode, aircraft turn right；In the state of not pushing manipulation push rod, manipulation push rod is equipped with return spring, returns to
Meta position, any key are all not switched on, and all dry reed switch are in an off state, and all driving devices are in no current shape
State, aircraft are in non helping hand state；Manipulate push rod (4) Xiang Zuohou, KEYC conducting；Manipulate push rod (4) backward, KEYF conducting,
Aircraft lower surface enters acceleration mode, and aircraft accelerates upwards；When manipulation push rod (4) is exerted oneself forward, KEYG conducting flies
Row device upper surface enters acceleration mode, and aircraft moves downward, four groups of electrode voltage pulse frequencies and voltage pulse high level of synchronization,
u2-u1=ω Δ t, wherein Δ t < Δ L/v is in Afterburning condition, and aircraft straight trip accelerates.
Claims (4)
1. a kind of hypersonic aircraft surface plasma DC pulse gesture stability secondary propulsion system (SPS), it is characterised in that: by
IN1 electrode strip (2), IN2 antithesis electrode strip (3), manipulation push rod (4) and DC pulse plasma driving control system are constituted；
The entire outer surface of aircraft is embedded in 4 pairs of electrode strips up and down, every a pair of electrode strip along direction of motion perpendicular separation
It is made of IN1 electrode strip (2) and IN2 antithesis electrode strip (3), IN1 electrode strip (2), IN2 antithesis electrode strip (3) are mutually parallel
Arrangement；Aircraft skin layer uses high-temperature insulation material, polishes jointly after the electrode strip of surface layer insertion with aircraft skin layer,
Constitute smooth surface；
Auxiliary propulsion and gesture stability are realized by aircraft surface plasma direct-current pulse, pass through two groups of DC pulses of driving etc.
Ion-drive；It is four, upper and lower, left and right region in hypersonic aircraft surface segmentation, there are two types of electrodes in each region
IN1 and IN2, two arrays of electrodes voltage pulse polarity is on the contrary, by driving double DC pulse plasma drivings；Between input terminal IN1 is
Disconnected pulse signal Φ IN1=- Aexp (u1T), IN2 is another group of discontinuous pulses signal Phi IN2=Aexp (u to+ω2+ ω t), IN1 with
The pulse voltage of IN2 output is identical with pulse duration frequency, and unique difference existing for two group pulse voltages is exactly micro- there are one
Small phase difference u2-u1=ω Δ t, wherein Δ t≤Δ L/v, Δ L are the spacing distances of the relative position between two arrays of electrodes；When
u2-u1>=0, accelerate to be positive, at this point, the plasma for having accumulated opposite charges around the positive and negative electrode of first group of electrode,
There is opposite generating positive and negative voltage, under the action of electrostatic, are gathered in first in the moment that electrode voltage disappears, second group of positive and negative electrode
The plasma of group electrode surface is to second group of electrode movement；This movement exists simultaneously on hypersonic aircraft surface, moves
Dynamic displacement is Δ L；Such process is repeated by pulse voltage, thereby realizes plasma hypersonic
The movement on surface；Work as u2-u1≤ 0, accelerate for negative sense, whole process forward direction is identical, but the moving direction phase of plasma surface
Instead, the plasma in hypersonic flight body surface face is allowed in this way with the direction of motion on the contrary, and slowing down；DC pulse etc.
Ion-drive tune PWM(pulse width modulation) be by control fixed voltage DC power supply switch frequency, modulating pulse width,
If set of pulses width and another group pulse width are different, for the pulsewidth of two groups of DC pulses there are a difference, this is poor
Value meets u2-u1=ω Δ t is achieved that the control of two group pulse phase differences；
It is identical for principle used by direction controlling, if the pulse voltage phase of four groups of electrodes is completely the same, realize whole
Body acceleration or deceleration；The two arrays of electrodes u of surface area2-u1>=0, then upper surface accelerates, the two arrays of electrodes u of lower surface area2-
u1≤ 0, then lower surface is slowed down, and aircraft can move downward, on the contrary then move upwards；The two arrays of electrodes u in left surface region2-u1≥
0, then left surface accelerates, the two arrays of electrodes u of right surface region2-u1≤ 0, then right surface is slowed down, and aircraft can move right, on the contrary
Then move downward；u2-u1Between phase difference value be by control impulse phase realize；The power of phase impulse uses power
Amplifier carries out power amplification, to realize the control of DC pulse plasma driving force；
The set-up of control system has sensor, and temperature signal is inputted by the port PL1.1, for knowing aircraft surface temperature；
Acceleration signal is inputted by the port PL1.2, and for knowing the motion state of aircraft, gravity accelerometer signal passes through
The port PL1.3 input, for judging the relationship between aircraft and gravitational field；When flight is in automatic control state, flight
The control of posture is controlled by the gesture stability program write in advance, is inputted by the port PL1.0.
2. hypersonic aircraft surface plasma DC pulse gesture stability auxiliary propulsion system according to claim 1
System, it is characterised in that: the power driven system provides electric energy by generator, fills after over commutation and pressure stabilizing to two group storage batteries
Electricity, battery positive voltage output end are A, and cathode output end B, battery is the confession of DC pulse plasma driving control system module
Electric (as shown in Figure 7), shares six kinds of job control states, is power output drive control on 1. respectively；2. lower power output is driven
Dynamic control；3. left power output drive control；4. right power output drive control；5. straight forward drive control；Control model
It is divided into manual control and process control；Manual control realizes keypress function by manipulation push rod (4) to realize；
The major function of DC pulse plasma driving control system include: realize the acceleration that DC pulse plasma is driven,
The upper and lower, left and right direction controlling of deceleration and the driving of DC pulse plasma, by adjusting the driving of DC pulse plasma
Duty ratio changes high-voltage pulse frequency, can very easily realize the intelligent control of DC pulse plasma driving；System hardware
Module composition: (1) DC pulse plasma driving control system module；(2) L298 DC pulse power amplification drive module；
(3) LED display module；(4) push rod independent keyboard control module is manipulated.
3. hypersonic aircraft surface plasma DC pulse gesture stability auxiliary propulsion according to claim 1 or 2
System, it is characterised in that: under automatic control mode, the control of flight attitude is controlled by preset program；In people
Under work control model, being controlled using input key, used key is mutually indepedent, a bonded I/O mouth line is each pressed,
Key works state in a piece I/O mouth line will not influence the working condition of other I/O mouth lines.
4. therefore, can determine whether which key is pressed on keyboard, all keys are by detecting the level state of I/O mouth line
Dry reed switch is constituted, and manipulation push rod has magnetic force, and the position for manipulating push rod is different, and the button data provided changes, pulse
Phase controlling can carry out identification control by writing software program；When manipulating push rod (4) forward, KEYE conducting, the left and right sides
Same-phase driving, aircraft are moved to front simultaneously for two arrays of electrodes pulse；Push rod (4) Xiang Zuoqian is manipulated, KEYA conducting is left front
Side dry reed switch is connected, and aircraft enters left side drive mode, aircraft divertical motion to the left；Before manipulating push rod to the right, KEYB
Conducting, forward right side dry reed switch are connected, and drive mode on the left of aircraft, aircraft turns right；Do not pushing manipulation push rod
Under state, manipulation push rod is equipped with return spring, returns to interposition, any key is all not switched on, and all dry reed switch are in
Off-state, all driving devices are in no current state, and aircraft is in non helping hand state；Push rod (4) Xiang Zuohou is manipulated,
KEYC conducting；Manipulate push rod (4) backward, KEYF conducting, aircraft lower surface enters acceleration mode, and aircraft accelerates to transport upwards
It is dynamic；When manipulation push rod (4) is exerted oneself forward, KEYG conducting, aircraft upper surface enters acceleration mode, and aircraft moves downward, and four
Group electrode voltage pulse frequency and voltage pulse high level of synchronization, u2-u1=ω Δ t, wherein Δ t < Δ L/v is in Afterburning condition, flies
The straight trip of row device accelerates.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109855834A (en) * | 2019-01-24 | 2019-06-07 | 陈蜀乔 | A kind of hypersonic inner surface plasma direct-current impulse wind tunnel air-flow power-assisted propulsion system |
| CN112304365A (en) * | 2020-09-25 | 2021-02-02 | 北京空间飞行器总体设计部 | On-orbit micro space debris multi-parameter measuring probe and measuring method |
| GB2607360A (en) * | 2021-09-27 | 2022-12-07 | Isaksen Guttorm | A light aircraft with an electrostatic propulsion system |
-
2019
- 2019-01-24 CN CN201910070286.3A patent/CN109850143A/en not_active Withdrawn
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109855834A (en) * | 2019-01-24 | 2019-06-07 | 陈蜀乔 | A kind of hypersonic inner surface plasma direct-current impulse wind tunnel air-flow power-assisted propulsion system |
| CN112304365A (en) * | 2020-09-25 | 2021-02-02 | 北京空间飞行器总体设计部 | On-orbit micro space debris multi-parameter measuring probe and measuring method |
| GB2607360A (en) * | 2021-09-27 | 2022-12-07 | Isaksen Guttorm | A light aircraft with an electrostatic propulsion system |
| GB2607360B (en) * | 2021-09-27 | 2023-07-12 | Isaksen Guttorm | A light aircraft with an electrostatic propulsion system |
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