CN102152855A - Control method for airplane launch and device special for airplane launch - Google Patents

Control method for airplane launch and device special for airplane launch Download PDF

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Publication number
CN102152855A
CN102152855A CN201110117155XA CN201110117155A CN102152855A CN 102152855 A CN102152855 A CN 102152855A CN 201110117155X A CN201110117155X A CN 201110117155XA CN 201110117155 A CN201110117155 A CN 201110117155A CN 102152855 A CN102152855 A CN 102152855A
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aircraft
hydraulic
batch
mercury
fixed
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CN201110117155XA
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CN102152855B (en
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姜代红
黄忠东
韩成春
孙荣军
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Xuzhou University of Technology
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Xuzhou University of Technology
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Abstract

The invention discloses a control method for airplane launch and a device special for airplane launch, which belong to devices for launching objects. A mercury supplier of the device is connected with the bottom of a power generator by a flow control valve through a pipeline; the output shaft of the power generator is connected with the shaft of a transmission gear by a coupler; the output shaft of the transmission gear is connected with the input shaft of a hydraulic pump station by the coupler; the hydraulic output port of the hydraulic pump station is connected with a hydraulic rubber pipe; the other end of the hydraulic rubber pipe is connected with the inlet of a hydraulic pusher; the hydraulic pusher is fixed on a guide rail or a bracket; the output end of the hydraulic pusher is connected with a carrying frame; the carrying frame is arranged on the guide rail which is fixed by the bracket; a thruster is fixed on the carrying frame; and an airplane is fixed to the thruster. The invention has the advantage that: by lifting mercury in advance to store energy and releasing great power in the form of the internal energy of the mercury, the airplane can acquire an accelerated speed instantly on a track and be stably launched to fly into the sky. The energy is stored in the mercury in advance and released in the form of the internal energy of the mercury, so that the problem of generating large power output is solved.

Description

The control method and the isolated plant of aircraft emission
Technical field
The present invention relates to a kind of launching technique of aircraft, particularly a kind of control method and isolated plant of aircraft emission.
Background technology
At present, aircraft generally is to take off earlier when preparing flight, takes off to be to use the driving engine of aircraft self slowly to start, and then slide gentle acceleration forward on runway, when the speed of aircraft operation reached the speed of flight, the aircraft built on stilts flew to sky.Need the special-purpose walk help runway of very long aircraft when taking off, aircraft will consume a large amount of fuel simultaneously, and the airplane that once can only take off.
Summary of the invention
The objective of the invention is to provide a kind of control method and isolated plant of aircraft emission, solving needs the special-purpose walk help runway of very long aircraft when taking off, and aircraft will consume a large amount of fuel simultaneously, and the problem of the airplane that once can only take off.
The object of the present invention is achieved like this: this aircraft emission control method comprises aircraft launching device and aircraft launching technique;
Aircraft launching device comprises by flow-controlling gate, power generator, change speed gear box, hydraulic power unit, hydralic hose, the hydraulic drive machine, carrier, thruster, guide rail, frame and mercury provide device to form, mercury provides device to be connected with the bottom of power generator through pipeline by flow-controlling gate, the output shaft of power generator is connected with gear-box axle through coupler, output shaft of gear-box links to each other through coupler hydraulic power unit input shaft, the hydraulic pressure delivery port of hydraulic power unit is connected with hydralic hose, the hydralic hose other end links to each other with the import of hydraulic drive machine, the hydraulic drive machine is fixed on guide rail or the support, the mouth of hydraulic drive machine links to each other with carrier, carrier places on the guide rail of being fixed by support, be fixed with thruster on the carrier, fastening aircraft on the thruster.
Described power generator comprises axle, buoyancy aid, sealing band, blow off valve, housing and liquid, and sealing band one side and housing connect as one, and the opposite side of sealing band and buoyancy aid flush fit have inlet in the lower end of housing, and buoyancy aid connects as one with axle.
Described buoyancy aid is 1/4 cylinder, at the circle centre position adapter shaft.
Described housing is semicircle staving, perhaps is square staving, perhaps is the rectangle staving, sealing band is connected the equally divided position of housing, and the five equilibrium housing, and half of housing is liquid-tight cell, half is and the air communication chamber, at the liquid-tight cell of housing the mercury inlet is arranged.
Described hydraulic drive machine comprises fixed mount, inlet, hydraulic actuating cylinder and flange, and the hydraulic cylinder piston axle links to each other with fixed mount, and fixed mount is fixed on the support, and there is flange the hydraulic actuating cylinder upper end and is fixed on the carrier with screw; Perhaps described hydraulic drive machine comprises tooth bar, transmission type hydraulic cylinder pressure and flange, and the hydraulic cylinder body below has flange to be fixed on the support, the wheel and rack engagement on the cylinder body, and tooth bar is fixed on the carrier.
Described mercury provides device to comprise liquid reserve tank, valve, valve, lift pump, hydraulic pipe, liquid reserve tank bottom fluid plumbing connection valve, the valve other end links to each other with hydraulic pipe, the liquid reserve tank input duct is connected with valve, the valve other end is connected with lift pump, the lift pump other end connects hydraulic pipe, and hydraulic pipe is connected with flow controller.
Described carrier is made up of support body 7, runway 27, damping rope 28 and damper 28a, and runway is arranged on the support body, on the support body of the end of runway damping rope or damper is arranged.
Described thruster is made up of fixer 8, stand leg 24, aircraft wheel 25 and swivel pin 26, at an end of support body damper is arranged, and at the other end blind hole is arranged, one end of fixer is positioned at this blind hole, in this blind hole swivel pin is arranged, the fixer upper end links to each other with stand leg, and the bottom of stand leg is the aircraft wheel.
The aircraft launching technique has two kinds of aircraft firing orders: first kind is that firing order and second kind are batch firing orders; The method that is specially is as follows:
On the order display screen panel, click a firing button and just send launch intruction one time, click a batch firing button, just send a batch launch intruction;
When command processor receives the aircraft firing order, to order with after gps signal carries out analyzing and processing, send launch intruction, on display panel, show emission state, launch intruction enters mission controller, mission controller modulated pressure Control Driver, the fluid control actuator is launched an airplane or one batch of aircraft, aircraft has been launched away and has quickened, when aircraft arrives predetermined height and speed, the flying quality of aircraft sends the unlocking signal request by GPS to microprocessor, central process unit sends unlock command to aircraft, the engine starting of aircraft, lift-off, the lift-off successful information is sent to microprocessor in aircraft lift-off back, and microprocessor can carry out the next round firing order again;
Described microprocessor, receive the flying height and the flying distance information of the last batch of aircraft of launching, after central process unit carries out data handing to the information that receives, when aircraft reaches safe altitude, allow batch command generator after, send next batch launch intruction greater than time gap; The height and distance that on order and read-out, shows aircraft simultaneously;
Described batch of command generator has timer, realizes that by timer timer sends a batch of instruction every the regular hour, carries out a batch emission to the control of aircraft transmission interval; When but last batch of aircraft do not reach certain safe altitude, though pitch time arrives, microprocessor did not produce the instruction of next batch emission yet; The operator can send intervention command, and decision is to continue emission or cancellation emission;
Described command processor is to open by four analog cmos, accepts and recognition command, and will order transformation or CMOS IC logic level signal, removes to control transmit control device and batch command generator;
Described mission controller mainly by or non-CMOS integrated circuit form, realize all or batch emission.Under command processor control, realize all emissions, under batch control on signal instruction generation road, realize batch emission;
Described fluid control actuator is to adopt solid-state relay SSR.Accept the output signal of mission controller, drive flow-controlling gate again, aircraft is launched.
Beneficial effect, owing to adopted such scheme, mercury provides the mercury of device after the flow control valve throttling, the ingoing power producer produces the axle moment of torsion, moment of torsion passes to change speed gear box by coupler, after speed governing, drive hydraulic power unit work, hydraulic power unit pumps high pressure oil and offers the hydraulic drive machine through hydralic hose, the hydraulic drive machine can convert hydraulic pressure to mechanical powered drive by the carrier accelerated movement on the guide rail of one-tenth one fixed angle of altitude of stent support, aircraft on the drive thruster is transmitted into the aerial requirement of taking off of satisfying with certain initial velocity in certain hour and distance.After emission was finished, mercury was discharged from flow-controlling gate, and carrier is under the effect of deadweight simultaneously, and entire mechanism is got back to initial position, waited for emission next time.Owing to adopted mercury can store huge interior energy, and can obtain huge power in interior releasable mode, when taking off, solution needs the special-purpose walk help runway of very long aircraft, aircraft will consume a large amount of fuel simultaneously, and the problem of the airplane that once can only take off has reached purpose of the present invention.
Advantage: by promoting the mercury storing energy in advance, can form discharge great power in the mercury, moment obtains the device that acceleration/accel steadily launches in orbit to make aircraft.Because energy is stored in the mercury in advance, energy when discharging be with in the mercury can form discharge, thereby power and time have nothing to do, solved a difficult problem that produces high-power output.
1, do not need takeoff runway, save the space.
2, can many opportunity of combat launch simultaneously, go up to the air fast, efficient is high, has improved viability.
3, because the power generator thrust output is a definite value, only needs dominant discharge just can obtain any best acceleration/accel and satisfy the requirement of taking off, strong to the comformability of machine.
4, simple in structure, thrust is steady, continuation good, the output of having avoided using steam, compressed air source not steadily, poor, the mechanism complexity of continuation, the control difficulty is big, potential safety hazard is many shortcoming.
5, in advance mercury is risen to height more than the power generating means, flow into naturally during use, fault rate is low, reliability is high.
6, because whole device can even under the situation that electric power interrupts fully, can guarantee that also aircraft is launched in time by safety without the energy.
7, to accumulate the energy of storage be compressed-air actuated thousands of times to the mercury of consubstantiality, the little potential safety hazard that does not have blast of volume.
Description of drawings
Fig. 1 is a constructional drawing of the present invention.
Fig. 2 is the constructional drawing of power generator of the present invention.
Fig. 3 is the constructional drawing of hydraulic drive machine first embodiment of the present invention.
Fig. 4 is the constructional drawing of hydraulic drive machine second embodiment of the present invention.
Fig. 5 provides the constructional drawing of device first embodiment for mercury of the present invention.
Fig. 6 provides the constructional drawing of device second embodiment for mercury of the present invention.
Fig. 7 is the constructional drawing of carrier of the present invention.
Fig. 8 is the constructional drawing of thruster of the present invention.
Fig. 9 is a launching technique diagram of circuit of the present invention.
Among the figure: 1, flow-controlling gate; 2, power generator; 3, change speed gear box; 4, hydraulic power unit; 5, hydralic hose; 6, hydraulic drive machine; 7, support body; 8, fixer; 9, guide rail; 10, support; 11, fixed mount; 12, inlet; 13, hydraulic actuating cylinder; 14, flange; 15, tooth bar; 16, transmission type hydraulic cylinder pressure; 17, liquid reserve tank, 18, valve; 19, valve; 20, lift pump; 21, hydraulic pipe; 22, valve; 23, pressure control case; 24, stand leg; 25, aircraft wheel; 26, swivel pin; 27, runway; 28, damping rope; 28a, damper; 29, mercury provides device; 2a, axle; 2b, buoyancy aid; 2c, sealing band; 2d, blow off valve; 2e, housing.
Specific implementation method
Following embodiment is for a better understanding of the present invention, not as restriction condition of the present invention.
Embodiment 1: aircraft launching device provides device 29 to form by flow-controlling gate 1, power generator 2, change speed gear box 3, hydraulic power unit 4, hydralic hose 5, hydraulic drive machine 6, carrier, thruster, guide rail 9, frame 10 and mercury.Mercury provides device 29 to be connected through the bottom of pipeline with power generator 2 by flow-controlling gate 1, the output shaft of power generator 2 is connected through 3 of coupler and change speed gear boxs, change speed gear box 3 output shafts link to each other through coupler hydraulic power unit 4 input shafts, the hydraulic pressure delivery port of hydraulic power unit 4 is connected with hydralic hose 5, hydralic hose 5 other ends link to each other with 6 imports of hydraulic drive machine, hydraulic drive machine 6 is fixed on guide rail 9 or the support 10, the mouth of hydraulic drive machine 6 links to each other with carrier, carrier places on the guide rail of being fixed by support 10 9 and can slide on guide rail 9, be fixed with thruster on the carrier, fastening aircraft and transmitted load on the thruster.
The mercury of feedway provides the mercury of device 29 after flow control valve 1 throttling, ingoing power producer 2 produces the axle moment of torsion, moment of torsion passes to change speed gear box 3 by coupler, after speed governing, drive hydraulic power unit 4 work, hydraulic power unit 4 pumps high pressure oil and offers hydraulic drive machine 6 through hydralic hose 5, hydraulic drive machine 6 can convert hydraulic pressure to mechanical powered drive by the carrier accelerated movement on the guide rail 9 of one-tenth one fixed angle of altitude of support 10 supports, aircraft on the drive thruster is in certain hour and distance, being transmitted into the aerial requirement of taking off of satisfying by initial velocity.After emission was finished, mercury was discharged from flow-controlling gate 1, and under the effect of carrier deadweight, entire mechanism is got back to initial position simultaneously, waited for emission next time.
Described power generator comprises 2a, axle; 2b, buoyancy aid; 2c, sealing band; 2d, blow off valve; 2e, housing and liquid, sealing band one side and housing connect as one, the opposite side of sealing band and buoyancy aid flush fit, and can relative motion, in the lower end of housing inlet being arranged, buoyancy aid connects as one with axle.
Described buoyancy aid is 1/4 cylinder, at the circle centre position adapter shaft.
Described housing is semicircle staving, perhaps is square staving, perhaps is the rectangle staving, sealing band is connected the equally divided position of housing, and the five equilibrium housing, and half of housing is liquid-tight cell, half is and the air communication chamber, the mercury inlet is arranged below the liquid-tight cell of housing.
The mercury of power generator provides pressure P through flow-controlling gate 1, enters and fill with housing 2e from the mercury import, and buoyancy aid, buoyancy aid are subjected to buoyancy and horizontal thrust effect clickwise to produce transmitting torque from shaft 2a and export the rotation of drive change speed gear box.
Described hydraulic drive machine comprises fixed mount 11, inlet 12, hydraulic actuating cylinder 13 and flange 14.The hydraulic cylinder piston axle links to each other with fixed mount 11, and fixed mount 11 is fixed on the support 10, and there is flange 14 hydraulic actuating cylinder 13 upper ends and is fixed on the carrier 7 with screw.
The hydraulic drive machine enters hydraulic actuating cylinder 13 by hydralic hose output ground mercury from inlet 12, because hydraulic cylinder piston shaft alignment play not on support 10, hydraulic actuating cylinder moves under the effect of hydraulic pressure, and drives carrier 7 motions by flange.
Described mercury provides device to comprise liquid reserve tank 17, valve 18, valve 19, lift pump 20, hydraulic pipe 21, liquid reserve tank 17 bottom fluid plumbing connection valves 18, valve 18 other ends link to each other with hydraulic pipe 21, liquid reserve tank 17 input duct are connected with valve 19, valve 19 other ends are connected with lift pump 20, lift pump 20 other ends connect hydraulic pipe 21, and hydraulic pipe is connected with flow controller 1.
When using mercury that device is provided, open valve 18, mercury in the liquid reserve tank 17 through valve 18 by hydraulic pipe 21 supply power producer 2 after flow is regulated in flow-controlling gate 1, valve-off 18 after action is finished, Open valve 19 promotes back liquid reserve tank 17 by lift pump 20 with the mercury in the producer, valve-off 19.
Described carrier is made up of support body 7, runway 27, damping rope 28 and damper 28a, and runway is arranged on the support body, and damping rope or damper are arranged on the support body of runway end.
Described thruster is made up of fixer 8, stand leg 24, aircraft wheel 25 and swivel pin 26, at an end of support body damper is arranged, and at the other end blind hole is arranged, one end of fixer is positioned at this blind hole, in this blind hole swivel pin is arranged, the fixer upper end links to each other with stand leg, and the bottom of stand leg is the aircraft wheel.
Guide rail 9 has a rectangle slideway and a triangle slideway, support body is sitting on the rectangle slideway and leg-of-mutton slideway of guide rail 9, stand leg 24 and aircraft wheel 25 are one, the aircraft wheel is on the runway, support body 7 contacts with stand leg 24 with aircraft wheel 25, fixer 8 is fixed on the support body 7 by swivel pin 26, and damping rope 28 or damper 28a are arranged on the support body 7.Aircraft leaves upper frame 7 and enters in the runway 27, by damping rope 28 or damper 28a location, propping fixer 8 contacts with aircraft wheel 25 with stand leg 24, remove damping rope 28 or damper 28a, support body 7 quickens slip drive aircraft and obtain takeoff speed on certain distance on guide rail 9, aircraft launches.It is spacing to reach speed back frame body 7 limited mechanisms.
The present invention utilizes mercury to produce huge buoyancy and thrust, utilizing the power generator produce power is interior releasable characteristics, can discharge required time fully in having can artificially control, and the merit unmodified feature of output, reaches the purpose that releases energy in can be at any time.The interior energy that discharges by mercury as 5 meters of radiuses, high 4 meters 1/4 cylinder, with tens of seconds time sustainable thrust that provides 220 tons in 20 meters, and can adjust acceleration/accel by the flow of control mercury, satisfy the initial velocity requirement of taking off of aircraft, be enough to several fighter planes are steadily launched simultaneously.
The aircraft launching technique has two kinds of aircraft firing orders: first kind is that firing order and second kind are batch firing orders; The method that is specially is as follows:
On the order display screen panel, click a firing button and just send launch intruction one time, click a batch firing button, just send a batch launch intruction;
When command processor receives the aircraft firing order, to order with after gps signal carries out analyzing and processing, send launch intruction, on display panel, show emission state, launch intruction enters mission controller, mission controller modulated pressure Control Driver, the fluid control actuator is launched an airplane or one batch of aircraft, aircraft has been launched away and has quickened, when aircraft arrives predetermined height and speed, the flying quality of aircraft sends the unlocking signal request by GPS to microprocessor, central process unit sends unlock command to aircraft, the engine starting of aircraft, lift-off, the lift-off successful information is sent to microprocessor in aircraft lift-off back, and microprocessor can carry out the next round firing order again;
Described microprocessor, receive the flying height and the flying distance information of the last batch of aircraft of launching, after central process unit carries out data handing to the information that receives, when aircraft reaches safe altitude, allow batch command generator after, send next batch launch intruction greater than time gap; The height and distance that on order and read-out, shows aircraft simultaneously;
Described batch of command generator has timer, realizes that by timer timer sends a batch of instruction every the regular hour, carries out a batch emission to the control of aircraft transmission interval; When but last batch of aircraft do not reach certain safe altitude, though pitch time arrives, microprocessor did not produce the instruction of next batch emission yet; The operator can send intervention command, and decision is to continue emission or cancellation emission;
Described command processor is by four analog cmos switches, accepts and recognition command, and will order transformation or CMOS IC logic level signal, removes to control transmit control device and batch command generator;
Described mission controller mainly by or non-CMOS integrated circuit form, realize all or batch emission.Under command processor control, realize all emissions, under batch control on signal instruction generation road, realize batch emission;
Described fluid control actuator is to adopt solid-state relay SSR.Accept the output signal of mission controller, drive flow-controlling gate again, aircraft is launched.
Embodiment 2: described hydraulic drive machine comprises that tooth bar 15, transmission type hydraulic cylinder pressure 16, flange 17. hydraulic cylinder bodies below have flange 17 to be fixed on the support 10, the wheel and rack engagement on the cylinder body, and tooth bar is fixed on the carrier 7.
Principle of work: enter transmission type hydraulic cylinder pressure 16 from the hydraulic oil of hydralic hose output, promote piston motion, the rotation of piston driven gear, the gear driven tooth bar makes carrier 7 moving linearlies.
Described mercury provides device fluid pipeline valve 18 belows connection pressure control case 23 to be used for adjusting and keeps mercury pressure stable, and other and embodiment 1 are together.

Claims (7)

1. aircraft launch control unit, it is characterized in that: this device is by flow-controlling gate, power generator, change speed gear box, hydraulic power unit, hydralic hose, the hydraulic drive machine, carrier, thruster, guide rail bracket and mercury provide device to form, mercury provides device to be connected with the bottom of power generator through pipeline by flow-controlling gate, the output shaft of power generator is connected with gear-box axle through coupler, output shaft of gear-box links to each other through coupler hydraulic power unit input shaft, the hydraulic pressure delivery port of hydraulic power unit is connected with hydralic hose, the hydralic hose other end links to each other with the import of hydraulic drive machine, the hydraulic drive machine is fixed on guide rail or the support, the mouth of hydraulic drive machine links to each other with carrier, carrier places on the guide rail of being fixed by support, be fixed with thruster on the carrier, fastening aircraft on the thruster.
2. aircraft launch control unit according to claim 1, it is characterized in that: described power generator comprises axle, buoyancy aid, sealing band, blow off valve, housing and liquid, sealing band one side and housing connect as one, the opposite side of sealing band and buoyancy aid flush fit, there is inlet lower end at housing, buoyancy aid connects as one with axle, and axle or shell connect power converter;
Described buoyancy aid is 1/4 cylinder, at the circle centre position adapter shaft;
Described housing is semicircle staving, perhaps is square staving, perhaps is the rectangle staving, sealing band is connected the equally divided position of housing, and the five equilibrium housing, and half of housing is liquid-tight cell, half is and the air communication chamber, the mercury inlet is arranged below the liquid-tight cell of housing.
3. aircraft launch control unit according to claim 1, it is characterized in that: described hydraulic drive machine comprises fixed mount, inlet, hydraulic actuating cylinder and flange, the hydraulic cylinder piston axle links to each other with fixed mount, fixed mount is fixed on the support, and there is flange the hydraulic actuating cylinder upper end and is fixed on the carrier with screw; Perhaps described hydraulic drive machine comprises tooth bar, transmission type hydraulic cylinder pressure and flange, and the hydraulic cylinder body below has flange to be fixed on the support, the wheel and rack engagement on the cylinder body, and tooth bar is fixed on the carrier.
4. aircraft launch control unit according to claim 1, it is characterized in that: described mercury provides device to comprise liquid reserve tank, valve, lift pump, hydraulic pipe, liquid reserve tank bottom fluid plumbing connection valve, the valve other end links to each other with hydraulic pipe, the liquid reserve tank input duct is connected with valve, the valve other end is connected with lift pump, and the lift pump other end connects hydraulic pipe, and hydraulic pipe is connected with flow controller.
5. aircraft launch control unit according to claim 1 is characterized in that: described carrier is made up of support body 7, runway 27, damping rope 28 and damper 28a, and runway is arranged on the support body, and damping rope or damper are arranged on the support body of runway end.
6. aircraft launch control unit according to claim 1, it is characterized in that: described thruster is made up of fixer 8, stand leg 24, aircraft wheel 25 and swivel pin 26, end at support body has damper, at the other end blind hole is arranged, one end of fixer is positioned at this blind hole, in this blind hole swivel pin is arranged, the fixer upper end links to each other with stand leg, and the bottom of stand leg is the aircraft wheel.
7. the control method of aircraft emission, it is characterized in that: the aircraft launching technique has two kinds of aircraft firing orders: first kind is that firing order and second kind are batch firing orders; The method that is specially is as follows:
On the order display screen panel, click a firing button and just send launch intruction one time, click a batch firing button, just send a batch launch intruction;
When command processor receives the aircraft firing order, to order with after gps signal carries out analyzing and processing, send launch intruction, on display panel, show emission state, launch intruction enters mission controller, mission controller modulated pressure Control Driver, the fluid control actuator is launched an airplane or one batch of aircraft, aircraft has been launched away and has quickened, when aircraft arrives predetermined height and speed, the flying quality of aircraft sends the unlocking signal request by GPS to microprocessor, central process unit sends unlock command to aircraft, the engine starting of aircraft, lift-off, the lift-off successful information is sent to microprocessor in aircraft lift-off back, and microprocessor can carry out the next round firing order again;
Described microprocessor, receive the flying height and the flying distance information of the last batch of aircraft of launching, after central process unit carries out data handing to the information that receives, when aircraft reaches safe altitude, allow batch command generator after, send next batch launch intruction greater than time gap; The height and distance that on order and read-out, shows aircraft simultaneously;
Described batch of command generator has timer, realizes that by timer timer sends a batch of instruction every the regular hour, carries out a batch emission to the control of aircraft transmission interval; When but last batch of aircraft do not reach certain safe altitude, though pitch time arrives, microprocessor did not produce the instruction of next batch emission yet; The operator can send intervention command, and decision is to continue emission or cancellation emission;
Described command processor is to open by four analog cmos, accepts and recognition command, and will order transformation or CMOS IC logic level signal, removes to control transmit control device and batch command generator;
Described mission controller mainly by or non-CMOS integrated circuit form, realize all or batch emission.Under command processor control, realize all emissions, under batch control on signal instruction generation road, realize batch emission;
Described fluid control actuator is to adopt solid-state relay SSR.Accept the output signal of mission controller, drive flow-controlling gate again, aircraft is launched.
CN 201110117155 2011-04-29 2011-04-29 Device special for airplane launch Expired - Fee Related CN102152855B (en)

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CN102152855B CN102152855B (en) 2013-10-16

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113998136A (en) * 2021-12-02 2022-02-01 北京机电工程研究所 Miniature aircraft launching device and method

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1146414A (en) * 1994-09-05 1997-04-02 朱炎 Airplane catapult and recovery system
US20070029442A1 (en) * 2003-06-06 2007-02-08 Klaus Wolter Method for supporting a propelled flying object during take-off and/or landing
CN101519124A (en) * 2009-03-31 2009-09-02 王力丰 Takeoff device and method of carrier-borne aircraft of aircraft carrier
CN101676174A (en) * 2008-09-19 2010-03-24 胡宣哲 Cold sling method and device

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1146414A (en) * 1994-09-05 1997-04-02 朱炎 Airplane catapult and recovery system
US20070029442A1 (en) * 2003-06-06 2007-02-08 Klaus Wolter Method for supporting a propelled flying object during take-off and/or landing
CN101676174A (en) * 2008-09-19 2010-03-24 胡宣哲 Cold sling method and device
CN101519124A (en) * 2009-03-31 2009-09-02 王力丰 Takeoff device and method of carrier-borne aircraft of aircraft carrier

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113998136A (en) * 2021-12-02 2022-02-01 北京机电工程研究所 Miniature aircraft launching device and method
CN113998136B (en) * 2021-12-02 2024-01-19 北京机电工程研究所 Micro-aircraft transmitting device and method

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