CN101244764B - Cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane - Google Patents
Cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane Download PDFInfo
- Publication number
- CN101244764B CN101244764B CN2008100546176A CN200810054617A CN101244764B CN 101244764 B CN101244764 B CN 101244764B CN 2008100546176 A CN2008100546176 A CN 2008100546176A CN 200810054617 A CN200810054617 A CN 200810054617A CN 101244764 B CN101244764 B CN 101244764B
- Authority
- CN
- China
- Prior art keywords
- car
- boosting
- cylinder
- auxiliary
- airplane
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Abstract
The invention relates to a boosting device of the airplane takeoff, in particular to a cascade connection type hybrid launch thrust vehicle of airplane takeoff. The boosting device solves the problems of the prior art such as complex structure, difficult manufacture, high cost and weak adjustability of the auxiliary launch device of the airplane takeoff. The boosting device comprises a major pushchair supporting the airplane and a plurality of cascade connecting auxiliary pushchairs, and the major pushchair and the auxiliary pushchairs adopt the way of electric power driving. An opening cylinder of launch separation is arranged under the major pushchair and the auxiliary pushchairs, and the opening cylinder of launch separation is connected with the gas steel cylinder in the frame. A piston tappet is connected with the front end of the auxiliary pushchair body, and the piston tappet and the piston are floating-sleeved in the opening cylinder barrel of launch separation. The connecting structure of the secondary auxiliary pushchairs and the previous level auxiliary pushchairs is the same as above, and an airplane chock is arranged on the platform at the upper part of the major pushchair. The major pushchair and the auxiliary pushchair are also provided with gasoline tanks and auxiliary driving devices. The boosting device of the airplane takeoff has an advantage of improving the final speed of the major pushchair by a plurality of technical means to facilitate the airplane embarked on the major pushchair to be projected for blastoff.
Description
Technical field
The present invention relates to a kind of boost installation of taking off, be specially a kind of cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane.
Background technology
Aircraft is one of most important vehicle in the world today, and its proportion is much larger than air, and it is based on Bernoulli's theorem, obtains speed and then exchanges the aircraft of lift for power.In the aircraft extended familys, fixed wing aircraft is a main body, and the place of aloft berthing, its workplace is on the ground or is equivalent on the ground-surface aircraft-carrier-deck.In service at aircraft, taking off is the beginning of all, and take off also is baptism to the aircraft dynamic property, nearly all fixed wing aircraft engine will enter main stage when taking off, when aero-engine is in main stage, engine wear strengthens, oil consumption is surprising, once the time length of full thrust process generally can not surpass 5 fens kinds, otherwise driving engine is unable to stand, and just 747 passenger planes with Boeing Co. are example, and the average fuel consumption that takes off of this type passenger plane is 5 tons of aviation kerosenes, short a few minutes take off oil consumption almost with cruise half an hour quite, this just has been absorbed in a vicious circle-because the huge oil consumption of taking off, aircraft than normalized distance from cruise and add several tons fuel oil, and be these several tons of extra fuel oils, consume nearly one ton fuel oil again, so-called regeneration oil consumption that Here it is.Oil consumption problem except aircraft, also have one with take off relevant profound technical matters, that is exactly that the aircraft designer is in order to take into account the two kinds of mode of operations that take off and cruise of aircraft, have in the design of the selection of driving engine and wing, stoop to compromise, require aircraft good performance all to be arranged at low speed and high speed, the difficult problem that Here it is " fish and bear's paw are desirable holds concurrently ", and may attend to one thing and lose sight of another in the reality.As far back as 1913, French engineer's reyn Lip river orchid just proposed the design of athodyd (Ramjet), and patents.Overall targets such as the manufacturing cost of athodyd, safety factor, thrust-weight ratio will obviously be better than modern aviation general-duty turbofan jet engine (Turbofan), it has individual inadequate natural endowment, that can't start at lower-speed state exactly, need a kind of auxiliary propeller earlier it to be advanced and accelerate to more than 0.5 Mach, so it is temporarily for no reason at all in contemporary general-purpose aircraft.In taking off the boost installation evolution, more representational technical scheme is:
The many Ai Lisen in American Theo succeeded in developing by three ropes and the original aircraft ejector that weights is formed in (1) 1911 year, and what effect this ejector does not almost play.Afterwards, Ai Lisen improved this original ejector again, succeeded in developing the compressed air type ejector, had carried out catapult-assisted take-off for the first time on the human history on November 12nd, 1912.
(2) World War II mid-term, German engineer proposes aircraft and carrys additionally the technical scheme that the booster rocket bag takes off, and in the actual combat in World War II later stage successful Application.
When (3) World War II finished, the ejector of being equipped on the aircraft carrier all was a hydraulic pressure, and it is minimum to launch energy, can only launch and adopt piston-engined screw propeller to advance aircraft, can't satisfy the needs that jet plane takes off at all.
(4) nineteen fifty-one, the commandant Mitchell of British Naval Air Service reserve takes the lead in proposing to develop the imagination of steam catapult.He just succeeds in developing it then, and is equipped on naval " Mo Xianzuo " number aircraft carrier.After this, the American develops this technology, is generalized on all active service aircraft carriers.More representational C-13 type steam catapult, ejector stroke surpass 90 meters, 36.3 tons of heavy carrier-borne aircrafts can be launched away with the high speed of 185 joints (promptly per hour 339 kilometers).
(5) nineteen sixty, the U.S. has succeeded in developing internal combustion catapult, and this ejector is installed on " enterprise " number atomic aircraft.But, the performance of this internal combustion type ejector is barely satisfactory, so " enterprise " number goes up except the equipment internal combustion catapult, also is equipped with steam catapult.
(6) 1999 years, the U.S. has finished based on electromagnetism airplane catapult system (EMALS) notion of linear electric motors and has inquired into and the definition phase, enter development process project definition and reduce risks the stage, this stage lasts till in September, 2003, bear respectively by Nuo Siluopu Grumman Co., Ltd and Gen Atomics, develop the model machine of length direction reduced scale.Carry out concept selection after in September, 2003 on the basis of above-mentioned two companies research, enter engineering and make development phase (EMD), up to now, the electromagnetism airplane catapult system (EMALS) of practicability does not come out as yet.
Above-mentioned a few cover is taken off boosting and is launched scheme, really obtain popularizing with promote have only the steam catapult scheme, through practice in more than 50 years, fact proved that there is following defective in this scheme:
(1) manufacture difficulty is big, needs top cutting, welding and the packing technique of the hydraulic press and the world more than 50,000 tons, has only the U.S. can make steam catapult in the world.
(2) maintenance cost height, U type sealing band are changed frequent and are very bothered, and material are required high.
(3) capacity usage ratio is low, only be 6%, and auxiliary facility is many, and system is loaded down with trivial details, and each link requires high.
(4) need to consume a large amount of fresh water and steam, launch an airplane and just need to consume 1 ton of fresh water, the U.S. once considered vapour-condensing equipment for recovering for this reason, efficient is low to be cancelled because of volume reaches greatly eventually, seeming predestined is that nuclear aircraft carrier is served, because aircraft carrier powered by conventional energy is difficult to be equipped with so huge steam boiler, even on being equipped with, fuel make up also is a big problem.
(5) the horsepower output controllability is poor, and ejection failure is heavier, and aircraft is certainly unlike saying faster with the speed of a ship or plane, and the small and light aircraft of similar unmanned plane can not launch.
As for electromagnetism airplane catapult system (EMALS) ready to appear, though do not emerge, from its linear electric motors core technology that adopts, and the experience of PVG magnetic levitation vehicle operation acquisition and lesson analysis, certainly exist following defective:
(1) magnetic circuit that had of linear electric motors itself cut-offs caused limit end effect problem.
(2) the intrinsic bigger installation air gap of linear electric motors, its efficient that causes can't be compared with rotating machine, and this drawback can be ignored in the little fashion of power, but just makes us being difficult to tolerance in the above application scenario of 20MW.
(3) electromagnetic interference and the Electromagnetic Compatibility problem between electromagnetism airplane catapult system and the adjacent system.
Application number is 200810054437.8 Chinese invention patents, a kind of " energy of electric automobile storage and rapidly supplementing device " disclosed, in this application, introduced a kind of ground conductive plate and quick electric energy accumulator that is installed on the automobile of being installed in, and with quick electric energy accumulator bonded assembly charging haptic element, automobile is installed in ground conductive plate by the contact of charging haptic element in driving process, replenish thereby make automobile obtain electric energy under steam, improved the usage ratio of electric energy in the vehicle energy system largely.
Summary of the invention
The present invention makes difficulty in order to solve the auxiliary catapult-launching gear complex structure of taking off that exists in the prior art, cost height, problem such as controllability difference and a kind of cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane is provided.
The present invention is realized by following technical scheme, a kind of cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane, it is characterized in that by a carrying aircraft promote mainly car and several and its highly, the boosting car cascade that width is all identical constitutes, promote mainly car and boosting car and adopt the driven by power mode, promoting mainly car and boosting car platform below is provided with to launch along center line and separates the implication cylinder, this launches the front end of separating the implication cylinder and connects by electromagnetic valve and the gas storage steel cylinder that is positioned at vehicle frame, boosting car car body front end is connected with the piston tappet, separate in the implication cylinder cylinder barrel promoting mainly launching of car with the piston tappet of promoting mainly the first-stage boost car that car connects and piston empty boasting, the piston tappet of secondary boosting car and piston empty boasting are in launching of previous stage boosting car separated implication cylinder cylinder barrel, and the platform of promoting mainly car top is provided with the aircraft catch.
Promote mainly and also be provided with electronic control unit (ECU) on the car, promote mainly drive wheel antislip control system (the Anti-Slip Regulation that maturation is applied to car all is installed on car and the boosting car, ASR), ASR is used for specially preventing that drive wheel is in starting, the electron steering propulsive effort control system quickening and occur trackslipping during at wet and slippery road traveling.It can by the control of computer realization to the wheel movement mode, so that make vehicle obtain big as far as possible propulsive effort on drive wheel, keep service direction simultaneously under driving condition.The sensor of ASR and actr all connect with propulsion vehicle ECU by CAN (Controller Aera Network) bus, promote mainly car car body front end and extend to the stream line pattern lower inclined plane.
Be provided with fuel tank promoting mainly on car and the boosting car, launching the cylinder barrel and the electromagnetic valve connection place of separating the implication cylinder establishes and fuel tank bonded assembly fuel nozzle and Ignition Module, opening cylinder opening end is established ring stiffener, this ring stiffener outside is cylindrical, inside end is for dispersing the conical nozzle structure, when finish launch separation after, piston in the opening cylinder barrel is discharged from, electromagnetic valve, fuel nozzle and Ignition Module are subjected to impulse level control intermittent work, this opening cylinder be pulse-knocking engine (Pulse Detonation Engine, PDE).Promoting mainly car and the boosting car is provided with auxiliary propulsion plant, auxiliary propulsion plant is motor-driven screw propeller (Propeller), turbofan engine (Turbofan), turbojet (Turbojet), rocket/punching press hybrid engine (Rocket/Ramjet), bimodal athodyd (Ramjet/Scramjet).
Promote mainly car and boosting car, and adjacent two-stage boosting car junction is the complementary trapezoidal interface of the consistent left-right symmetric of specification, the connection electromagnet that interface is provided with non-pressure contact with contact the good conductor contact with car body non-conductive pressure, this contact is corresponding with power source bus that runs through propulsion vehicle and CAN bus.Propulsion vehicle upper surface cover plate is the rectangle high-strength metal sheet of afterbody one sideband roundlet arc angle, being flakey arranges, following deposited heat radiating metal pipe network, root and car body are hinged, afterbody can be driven by drive element and rotate, the cover plate of different parts, can be respectively as flank, the blast screen that blocks the red-hot bright eruption of aircraft and the air brake etc. of the catch that supports aircraft tyre, the upper limb of adjusting propulsion vehicle tire ground adhesive ability, adjustment vehicle movement route, drive element can be hydraulic pressure (cylinder) or air pressure (cylinder) or electromagnet armature or motor screw structure.Application number be installed be energy of electric automobile storage and the rapidly supplementing device addressed in 200810054437.8 the Chinese invention patent on promoting mainly car and boosting car.
Propulsion vehicle thrust power source is for mainly being electric energy, adds the additional power that elastic potential energy, fuel mixture body explosion wave and the auxiliary propulsion plant of pressure gas provide, and constitutes the hybrid power system that power is powerful.In the above-mentioned hybrid power system, embody the green energy conservation principle of " electric energy is preferential ", electric energy drives the screw propeller rotation of the wheel and the auxiliary propulsion plant of propulsion vehicle by rotating machine, antagonistic force by road surface and air, make propulsion vehicle obtain the power that advances, practical experience is told us, speed per hour is below 0.5 Mach the time, the efficient of wheel and screw propeller is high than the jet engine of any kind, in addition, what carry aircraft promotes mainly car by cascade boosting car is thereafter launched separation one by one, can obtain again by launching the onward impulse that Backlash produces, and the operation scheme of this point and rocket is quite similar.
Propulsion vehicle adopts the combined guidance system, its The Basic Guidance system is the tach signal of each wheel of sending by the wheel speed sensor in the ASR system, the ECU comprehensive analyses draws the real-world operation track of propulsion vehicle and the error between the ideal trajectory (shoulding be straight line), second guidance system is according to promoting mainly the front end installing of car inclined-plane, the electromagnetic induction sensor array identical with the electro jet car engine crankshaft position sensor, detect propulsion vehicle and be installed on relative position between the ground-surface conductive plate (application number is 200810054437.8 Chinese invention patents), and the signal that sends to electronic control unit (ECU), ECU just draws the real-world operation track of current propulsion vehicle and the error between the Directional Sign of ground, with reference to two cover guidance system signals, revised by the working speed of adjustment left and right sides drive motor and the aperture of flank.
In propelling, propulsion vehicle upper strata squamous cover plate driven-mechanism drives down and upwards digs, under the effect of air resistance, improve the propulsion vehicle tire to ground-surface adhesive ability, in addition, the squamous cover plate of upwards digging can also be as catch, blast screen and air brake use, catch is arranged at the wheel rear side of promoting mainly car carrying aircraft, prevent that aircraft from moving backward because of inertia and air resistance, general and the wedge type pressure sensor of catch is used, this sensor effect is the bonding state of monitoring wheel and catch, the effect of blast screen is the scorching hot wake flame that blocks the aircraft jet engine ejection, when the propulsion vehicle that is in the high-speed cruising state will brake, the squamous cover plate of upwards digging can be used as the air brake and uses.
In the propulsion vehicle formation, strength occurs in the thrust mode, all the time be to be in the last maximum thrust of boosting car contribution, and the complementary trapezoidal interface of the left-right symmetric of unified standard can make and promote mainly car and boosting car, and the standard, tight more of the combination between the boosting car at different levels, it is convenient to separate again, connect electromagnet and be used to strengthen this connection, when launching separation, the connection electromagnet is cut off the input power supply and quits work.
Propulsion vehicle of the present invention is quite similar by the principle of propeller that launches the principle of work that separate to realize quicken advances and rocket, is described below:
Rocket is an important flight vehicle beyond the aircraft, and general-duty is to obtain propulsive force by a large amount of tail gas that high speed jet produces through violent burning with the rocket of chemical fuel as the energy at present, and the weight of fuel accounts for the overwhelming majority of rocket take-off weight.For same piece of rocket, its used fuel, displacement of combustion chamber and jet pipe specification are definite, the spray velocity (v of rocket high-temperature tail gas
r) being generally constant, its quality (M) has significant variation in motion process, and when quality (M) reduced, (v) increase gradually, the rate of onset of establishing rocket was v to speed
0, the rocket initial mass is M
0, its vacuum level equation of motion is expressed as:
V=v
0+ v
rLn (M
0/ be not difficult to find out by following formula that M) (Changing Pattern v) and the time-varying rule of its quality (M) are irrelevant, and only are decided by rocket initial mass (M for rocket speed
0) relative velocity (v during with the ejection of current quality (M) ratio and high-temperature tail gas
r).If with M
sThe quality (comprising fixed equipment and capacity weights such as storepipe) of representative rocket when running out of gas, then the rocket maximum speed v that can reach in-flight at vacuum level
sBe v
s=v
0+ v
rLn (M
0/ M
s)=v
0+ v
rLnN is N=M here
0/ M
sThe active mass ratio that is called rocket.Rocket is by static beginning (v
0=0) the maximum speed value V that can reach is called the characteristic velocity of rocket, makes v by following formula
0=0, but derive famous Qi Aoer Paderewski formula: V=v immediately
rLnN or N=e
V/vr
When cascade exhausts at last boosting car electric energy, or drive motor is when surpassing rated speed of rotation the power that advances can't be provided, with its connection promote mainly instantaneous the opening of car (or prime boosting car) gas storage steel cylinder electromagnetic valve, discharge pressurized air and promote piston moving linearly in cylinder barrel, piston finally separates with cylinder barrel, in the certain distance after separation, under pressure gas continues to promote, remain the acceleration separation process, the maximal phase that can reach is to speed v
rPromptly quite and the spray velocity v of rocket high-temperature tail gas
r,
If the carrying Aircraft Quality is M
p, promoting mainly the car quality is M
t, boosting car quality is M
1, M
2..., M
n, its active mass ratio is
N＝(M
p+M
t+M
1+M
2+...+M
n)/(M
p+M
t)
Propulsion vehicle and carrying aircraft are worked as M from static
1, M
2..., M
nAll with v
rRelative velocity launches when separating, and promotes mainly car and carry aircraft only from launching the separation aspect with regard to obtainable characteristic velocity to be
V＝v
rlnN＝v
rln[(M
p+M
t+M
1+M
2+...+M
n)/(M
p+M
t)]
In order to obtain high as far as possible characteristic velocity is V, should start with from two aspects, and the first improves launches velocity of separation v
r, it two is to improve active mass to compare N.
Aircraft deadweight stochastic pattern difference has very big difference, fill it up with fuel oil after the Boeing-737 aircraft weight be about 70 tons, Air Passenger A380 then has 600 tons, is not difficult to find out thus, same one group of propulsion vehicle is owing to difference value of leading of carrying aircraft model causes M
pValue is different, and its characteristic velocity V that can reach is different, owing to launch velocity of separation v
rBe definite value, obtain the characteristic velocity V that needs, have only by changing the quantity of boosting car, thereby regulate active mass, and then obtain the characteristic velocity V that needs than N.
Cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane of the present invention, used the multiple technologies means to improve speed, at different speed intervals, the main body of propulsive force is different, in the static 0.5 Mach of speed interval of starting to walk, the main body of propulsive force is an electric energy, electric energy drives screw propeller (Propeller) rotation of the wheel and the auxiliary propulsion plant of propulsion vehicle by rotating machine, antagonistic force by road surface and air, make propulsion vehicle obtain the power that advances, in 0.5 Mach to 0.9 Mach speed interval, the main body of propulsive force is the turbofan engine (Turbofan) of auxiliary propulsion plant, turbojet (Turbojet) and final stage boosting car opening cylinder pulse-knocking engine (PDE), in the speed interval more than 0.9 Mach, the main body of propulsive force is the rocket/punching press hybrid engine (Rocket/Ramjet) of auxiliary propulsion plant, bimodal athodyd (Ramjet/Scramjet) and final stage boosting car opening cylinder pulse-knocking engine (PDE), in all speed intervals, all can make by the antagonistic force that launching of final stage boosting car separate to produce and promote mainly vehicle speed and further improve, launching and separating the implication cylinder is in fact again a rocket engine (Rocket).
Description of drawings
Fig. 1 is an inner structure scheme drawing of the present invention
Fig. 2 loads structural representation under the aircraft state for the present invention
Fig. 3 is for promoting mainly the car lateral plan described in the present invention
Fig. 4 is a birds-eye view of promoting mainly car
Fig. 5 is a platform cover plate arrangement architecture scheme drawing
Fig. 6 is aircraft wheel and car body contact condition structural representation
Fig. 7 is a heat radiating metal pipe network distribution shape scheme drawing under the platform cover plate
Fig. 8 is for connecting the pressure contact good conductor contact structure scheme drawing of circuit between each propulsion vehicle
Among the figure: 1-promotes mainly car, 2-boosting car, 3,4-launches and separate the implication cylinder, the 5-storage battery, the 6-fuel tank, 8-connects electromagnet, 9-pressure contact good conductor contact, 10, the 11-electromagnetic valve, 7,12-gas storage steel cylinder, 13-piston tappet, 14-electromagnetic induction guiding parts, 15-catch, 16-heat radiating metal pipe network, 17-auxiliary propulsion plant, 18-pressure sensor, the 19-aircraft, 20-conductive plate, the rotatable flexible charging haptic element of 21-, the 22-drive element, 23-aircraft wheel, 24-metal sheet 25-drive element
The specific embodiment
The invention will be further described below in conjunction with drawings and Examples, but embodiments of the present invention are not limited thereto.
As schematically shown in Figure 1, a kind of cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane, comprise a carrying aircraft 19 promote mainly car 1 and several and its highly, boosting car 2 cascades that width is all identical constitute, promote mainly car 1 and boosting car 2 is the driven by power mode, be provided with to launch at the middle part of promoting mainly car 1 and separate implication cylinder 3, launch the head end of separating implication cylinder 3 by electromagnetic valve 10 be positioned at the gas storage steel cylinder 7 of promoting mainly car 1 vehicle body frame and be connected, the middle part of boosting car 2 is provided with to launch separates implication cylinder 4, launching the head end of separating implication cylinder 4 is connected with the gas storage steel cylinder 12 that is positioned at boosting car 2 vehicle body frames by electromagnetic valve 11, boosting car 2 car body front ends are connected with piston tappet 13, the piston tappet 13 of first-stage boost car 2 and piston empty boasting are separated in the implication cylinder 3 promoting mainly launching of car 1, the piston tappet of secondary boosting car and piston empty boasting are separated in the implication cylinder launching of previous stage boosting car, the platform of promoting mainly car 1 top is provided with catch 15, promotes mainly car 1 front end and is provided with electromagnetic induction guiding parts 14.Catch 15 is driven by drive element 22, be provided with fuel tank 6 promoting mainly on car 1 and the boosting car 2, launching the cylinder barrel and electromagnetic valve 10,11 connection places of separating implication cylinder 3,4 establishes and fuel tank bonded assembly fuel nozzle and Ignition Module, opening cylinder opening end is established ring stiffener, this ring stiffener outside is cylindrical, and inside end is for dispersing the conical nozzle structure.
As schematically shown in Figure 3, promote mainly car 1 car body front end and extend to the stream line pattern lower inclined plane, the lower inclined plane front end is provided with electromagnetic induction guiding parts 14, this electromagnetic induction guiding parts 14 by cable be located at the electronic control unit of promoting mainly on the car 1 (ECU) and connect, promote mainly drive wheel antislip control system all is installed on car 1 and the boosting car 2, promoting mainly car is the complementary trapezoidal interface of the consistent left-right symmetric of specification with boosting car and adjacent two-stage boosting car junction, the connection electromagnet 8 that interface is provided with non-pressure contact with contact good conductor contact 9 with car body non-conductive pressure, this contact is connected with the CAN bus is corresponding with the power source bus that runs through propulsion vehicle.
As schematically shown in Figure 2, auxiliary propulsion plant 17 is set promoting mainly on car 1 or the boosting car 2, auxiliary propulsion plant is any one in motor-driven screw propeller, turbofan engine, turbojet, rocket/punching press hybrid engine, the bimodal athodyd.
Illustrated in Figure 5, promote mainly car 1 or boosting car 2 upper surface cover plates rectangular metal plate 24 for several afterbody one sideband arc chord angles, being flakey arranges, as schematically shown in Figure 7, following deposited heat radiating metal pipe network 16, the root and the car body of rectangular metal plate 24 are hinged, and the afterbody of rectangular metal plate 24 can be driven by drive element 25 and rotate, and drive element can be hydraulic actuating cylinder or air cylinder or electromagnet armature or motor screw structure.
Power storage and rapidly supplementing device are installed promoting mainly on car 1 and the boosting car 2.Its concrete structure is energy of electric automobile storage and the rapidly supplementing device of addressing in 200810054437.8 the Chinese invention patent referring to application number.
Gas storage steel cylinder 7,12 is established safety valve, and steel cylinder 7,12 and fuel tank 6 outer walls twine the interchange of heat metal tube, and this metal tube connects with heat radiating metal pipe network 16.
As schematically shown in Figure 6, promote mainly wheel retaining 15 and be provided with the pressure sensor 18 that contacts with aircraft tyre.
Promoting mainly the car body platform is high duty metal rectangle plane parallel to the ground, it is the carrying platform of aircraft, berm width is greater than the undercarriage width and keep suitably safety redundancy, car body is the left-right symmetric structure, by at least two elongated longerons, at least two beam vertical connections provide support, longeron below symmetry is installed at least one pair of rotatable flexible charging haptic element, the platform front end extends to the stream line pattern inclined-plane, the inclined-plane front end is established the electromagnetic induction guiding parts, the inclined-plane is propulsion vehicle electronic control unit (ECU) down, the vehicle body bilateral symmetry is provided with pair of driving wheels and pair of driven at least, above-mentioned drive wheel is identical with the flower wheel specification, adopt the identical independent suspension structure and the braking mechanism that has the magnetoelectricity velometer of similar automobile, a drive wheel connects with a drive motor rotor, drive motor stator and vehicle frame are fixedly connected, on tire top, both sides and both sides do not have interference place and establish wheel cover, wheel cover is inboard to intersect vertically with the car body platform, the wheel cover upper side plane is high than the car body platform, the wheel cover outside, both sides is symmetrical arranged the identical flank of at least one pair of specification respectively, the wheel cover upper side plane is symmetrical arranged auxiliary propulsion plant, this auxiliary propulsion plant physical dimension is (to contain wing with airframe, car bonnet, reach parts such as alighting gear) do not have to interfere and keep suitable safe redundancy and be advisable, launch along the setting of car body line of centers and to separate the implication cylinder, cylinder barrel is set in parallel under the car body platform, its outer wall and vehicle frame are fixedly connected, front end connects by the gas storage cylinder valve that electromagnetic valve and bilateral symmetry be arranged in parallel, place in this cylinder barrel with the cylinder piston that the boosting vehicle frame that connects thereafter is fixedly connected, in the remaining space below platform, symmetry installing battery pack, this battery pack and rotatable flexible charging haptic element and drive motor pass through cable connection.
Boosting car body platform is a high duty metal rectangle plane parallel to the ground and consistent with promoting mainly the car podium level, berm width is greater than the undercarriage width and keep suitably safety redundancy, car body is the left-right symmetric structure, by at least two elongated longerons, at least two beam vertical connections provide support, longeron below symmetry is installed at least one pair of rotatable flexible charging haptic element, the platform front and back end is provided with the trapezoidal interface of symmetrical complementation, the vehicle body bilateral symmetry is provided with pair of driving wheels and pair of driven at least, above-mentioned drive wheel and flower wheel are with to promote mainly the car specification identical, adopt independent suspension structure identical and the braking mechanism that has the magnetoelectricity velometer with promoting mainly car, a drive wheel connects with a drive motor rotor, drive motor stator and vehicle frame are fixedly connected, on tire top, both sides and both sides do not have interference place and establish and promote mainly car same size wheel cover, wheel cover is inboard to intersect vertically with the car body platform, the wheel cover upper side plane is high than the car body platform, the wheel cover outside, both sides is symmetrical arranged at least one respectively and promotes mainly car same size flank, the wheel cover upper side plane is symmetrical arranged auxiliary propulsion plant, this auxiliary propulsion plant physical dimension is (to contain wing with airframe, car bonnet, reach parts such as alighting gear) do not have to interfere and keep suitable safe redundancy and be advisable, along the car body line of centers be provided with the piston tappet and with promote mainly the car same size and launch and separate the implication cylinder, cylinder barrel is set in parallel under the car body platform, its outer wall and vehicle frame are fixedly connected, front end be arranged in parallel with bilateral symmetry by electromagnetic valve with promote mainly car same size gas storage cylinder valve and connect, the piston tappet is an one with master's (helping) go-cart cylinder barrel inner carrier that is connected in its place ahead, place in this cylinder barrel with the cylinder piston that the boosting vehicle frame that connects thereafter is fixedly connected, in the remaining space below platform, symmetry installing battery pack, this battery pack and rotatable flexible charging haptic element and drive motor pass through cable connection.
The whole combined guidance system that adopts of propulsion vehicle, its The Basic Guidance system is by monitoring each driving, the rotating speed comprehensive analyses of flower wheel draws the real-world operation track of propulsion vehicle and the error between the ideal trajectory (shoulding be straight line), second guidance system is according to the electromagnetic induction guiding parts collection of promoting mainly the front end installing of car inclined-plane and the signal that sends to ECU (electronic control unit), ECU just draws the real-world operation track of current propulsion vehicle and the error between the Directional Sign of ground, with reference to two cover guidance system signals, revised by the working speed of adjustment left and right sides drive motor and the aperture of flank.Propulsion vehicle adopts the ripe drive wheel antislip control system (ASR) that is applied to car, and ASR is used for specially preventing that drive wheel is at starting, the electron steering draught control system that quickens and occur trackslipping during at wet and slippery road traveling.It can by the control of computer realization to the wheel movement mode, so that make propulsion vehicle obtain big as far as possible propulsive effort on drive wheel, keep service direction simultaneously under driving condition.
In propelling, empennage and platform topsides squamous cover plate driven-mechanism drive down and upwards dig, under the effect of air resistance, improve the propulsion vehicle tire to ground-surface adhesive ability, in addition, the platform cover plate that the squamous of upwards digging is arranged can also use as catch and blast screen, catch is arranged at the wheel rear side of promoting mainly car carrying aircraft, prevent that aircraft from moving backward because of air resistance, general and the wedge type pressure sensor (as schematically shown in Figure 6) of catch is used, this sensor effect is the bonding state of monitoring wheel and catch, and the effect of blast screen is the scorching hot wake flame that blocks the aircraft jet engine ejection.In the propulsion vehicle formation, strength occurs in the thrust mode, all the time be to be in the last maximum thrust of boosting car contribution, and unified standard be symmetrical set complementary trapezoidal interface, can make and promote mainly car and boosting car, and the standard, tight more of the combination between the boosting car at different levels, it is convenient to separate again, connect electromagnet and be used to strengthen this connection, when bullet was established separation, the connection electromagnet was cut off the input power supply and quits work.
Below, just requiring to reach certain type strategic aircraft of 0.9 Mach with takeoff speed is example, as described below to concrete purposes of the present invention and working process, as schematically shown in Figure 2, tractor truck is positioned over aircraft and promotes mainly the car top, the ground crew upwards starts the squamous cover plate by operation, be stuck in the aircraft tyre back as catch, settle the wedge pressure force gauge appropriate simultaneously, promoting mainly car is the transmission of high-speed electric expreess locomotive speedup, be that the rotary drive motor rotor connects by speed increaser with wheel shaft, the boosting car of cascade thereafter is followed successively by the high-speed electric expreess locomotive direct connection, normal speed motor speedup, normal speed motor direct connection and normal speed motor deceleration transmission, reduction ratio increases step by step according to its waterfall sequence, be positioned at the boosting car reduction ratio maximum at formation end, promoting mainly the symmetrically arranged auxiliary propulsion plant of wheel cowl upper side plane is electric propeller, turbofan engine, turbojet, rocket/punching press hybrid engine, a kind of in the bimodal athodyd (can adjust selection according to taking off the target velocity that requires to reach, select the bimodal athodyd at this), boosting wheel cowl upper side plane is symmetrical arranged auxiliary propulsion plant, auxiliary propulsion plant from after be followed successively by electric propeller forward, turbofan engine, turbojet, rocket/punching press hybrid engine, a kind of (can adjust selection) in the bimodal athodyd according to taking off the target velocity that requires to reach, propulsion vehicle at first begins by being positioned at last boosting car, start drive motor step by step, and auxiliary propulsion plant (as electric propeller), last boosting vehicle motor is the full power operation state, this moment, the electric energy of propulsion vehicle was provided by the battery pack on conductive plate and the last boosting car, when cascade exhausts at last boosting car electric energy, or drive motor is when surpassing rated speed of rotation the power that advances can't be provided, with its connection promote mainly instantaneous the opening of car (or prime boosting car) gas storage steel cylinder electromagnetic valve, close again after discharging pressurized air, fuel nozzle sprays fuel atomizing simultaneously, after atomizing oil gas and pressurized air are mixed, electronic ignition device is ignited miscellaneous gas, huge energy abrupt release, promote piston moving linearly in cylinder barrel, piston finally separates with cylinder barrel, in the certain distance after separation, under the continuation of pressure gas and explosion wave promotes, remain the acceleration separation process, behind the maximum relative velocity that reaches, mutual action does not just take place with the boosting car that separates in propulsion vehicle, propulsion vehicle is subjected to launching the Backlash when separating and obtains to move on after certain acceleration, piston in the opening cylinder barrel of this moment is discharged from, electromagnetic valve, fuel nozzle and Ignition Module are worked on by the control of certain frequency impulse level, this opening cylinder changes a pulse-knocking engine into, boosting car wheel that separates and screw propeller drive motor just transfer the regenerative brake generating state in the moment of separating, the recovery section energy, then under the contrarotation of wheel drive motors drives, return to one's starting point, battery charging is awaited orders.Through said process several times, turbofan engine is installed, turbojet, after the boosting car of rocket/auxiliary propulsion plants such as punching press hybrid engine is all separated, promoting mainly the symmetrically arranged auxiliary propulsion plant of wheel cowl upper side plane (this moment for bimodal athodyd) starts and opens full thrust, promote mainly the takeoff speed of the very fast strategic aircraft near 0.9 Mach of the aircraft of car and carrying, the aviator adjusts to main stage rapidly with aero-engine, aircraft is under the full thrust of self driving engine promotes, its speed has surpassed the speed of promoting mainly car gradually and has reached takeoff speed, so aircraft and promote mainly relative motion has just been arranged between the car, the pressure inductor of being located at aircraft catch place sends signal, it is flame-out immediately to promote mainly the symmetrically arranged additional thrust bimodal of wheel cowl upper side plane athodyd, the drive motor of promoting mainly car enters the regenerative brake generating state, the squamous cover plate driven-mechanism on upper strata is propped simultaneously, promote mainly car and enter the air braking state, relative velocity between the two increases immediately, at this moment, aviator's pull-up rising control lever, aircraft has just taken off, promote mainly car under the contrarotation of wheel drive motors drives, return to one's starting point, battery charging is awaited orders.
Claims (7)
1. cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane, it is characterized in that by a carrying aircraft promote mainly car (1) and several and its height, boosting car (2) cascade that width is all identical constitutes, promote mainly car (1) and boosting car (2) is the driven by power mode, be provided with at the middle part of promoting mainly car (1) and promote mainly launching of car and separate implication cylinder (3), promote mainly head end that launching of car separate implication cylinder (3) by electromagnetic valve (10) be positioned at the gas storage steel cylinder (7) of promoting mainly car (1) vehicle body frame and be connected, the middle part of boosting car (2) is provided with launching of boosting car and separates implication cylinder (4), the head end of separating implication cylinder (4) that launches of boosting car is connected with the gas storage steel cylinder (12) that is positioned at boosting car (2) vehicle body frame by electromagnetic valve (11), boosting car (2) car body front end is connected with piston tappet (13), the piston tappet (13) of first-stage boost car (2) and piston empty boasting are separated in the implication cylinder (3) promoting mainly launching of car, the piston tappet of secondary boosting car and piston empty boasting are separated in the implication cylinder launching of previous stage boosting car, the platform of promoting mainly car (1) top is provided with aircraft catch (15) and is provided with fuel tank (6) promoting mainly on car (1) and the boosting car (2), main, implication cylinder (3 is separated in launching of boosting car, 4) cylinder barrel and electromagnetic valve (10,11) establish and fuel tank bonded assembly fuel nozzle and Ignition Module the connection place, opening cylinder opening end is established ring stiffener, this ring stiffener outside is cylindrical, and inside end is for dispersing the conical nozzle structure.
2. cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane according to claim 1, it is characterized in that promoting mainly car (1) car body front end and extend to the stream line pattern lower inclined plane, the lower inclined plane front end is provided with electromagnetic induction guiding parts (14), this electromagnetic induction guiding parts (14) by cable be located at the propulsion vehicle electronic control unit of promoting mainly on the car (1) (ECU) and connect, promote mainly on car (1) and the boosting car (2) drive wheel antislip control system (ASR) all is installed, the sensor of drive wheel antislip control system and actr all connect with propulsion vehicle electronic control unit (ECU) by the CAN bus, promoting mainly car is the complementary trapezoidal interface of the consistent left-right symmetric of specification with boosting car and adjacent two-stage boosting car junction, the connection electromagnet (8) that interface is provided with non-pressure contact with contact good conductor contact (9) with car body non-conductive pressure, this contact is connected with the CAN bus is corresponding with the power source bus that runs through propulsion vehicle.
3. cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane according to claim 1 and 2, it is characterized in that auxiliary propulsion plant (17) being set promoting mainly on car (1) or the boosting car (2), auxiliary propulsion plant is any one in motor-driven screw propeller, turbofan engine, turbojet, rocket/punching press hybrid engine, the bimodal athodyd.
4. cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane according to claim 1 and 2, it is characterized in that promoting mainly car (1) or boosting car (2) upper surface cover plate is the rectangular metal plate (24) of several afterbody one sideband arc chord angles, being flakey arranges, following deposited heat radiating metal pipe network (16), the root and the car body of rectangular metal plate (24) are hinged, the afterbody of rectangular metal plate (24) can be driven by drive element (25) and rotate, and drive element can be hydraulic actuating cylinder or air cylinder or electromagnet armature or motor screw structure.
5. cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane according to claim 1 and 2 is characterized in that, power storage and rapidly supplementing device is installed promoting mainly on car (1) and the boosting car (2).
6. cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane according to claim 5, it is characterized in that, gas storage steel cylinder (7,12) is established safety valve, and gas storage steel cylinder (7,12) and fuel tank (6) outer wall twine the interchange of heat metal tube, and this metal tube connects with heat radiating metal pipe network (16).
7. cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane according to claim 1, the catch (15) of promoting mainly car (1) is provided with the pressure sensor (18) that contacts with aircraft tyre.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008100546176A CN101244764B (en) | 2008-03-07 | 2008-03-07 | Cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008100546176A CN101244764B (en) | 2008-03-07 | 2008-03-07 | Cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101244764A CN101244764A (en) | 2008-08-20 |
| CN101244764B true CN101244764B (en) | 2011-01-26 |
Family
ID=39945499
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2008100546176A Expired - Fee Related CN101244764B (en) | 2008-03-07 | 2008-03-07 | Cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101244764B (en) |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101676174B (en) * | 2008-09-19 | 2013-06-26 | 胡宣哲 | Cold sling method and device |
| CN102198864B (en) * | 2011-02-22 | 2013-12-25 | 和近建 | Power rotation runway |
| CN103662038A (en) * | 2012-09-08 | 2014-03-26 | 刘君才 | Jet-propelled catapult car |
| CN104015934B (en) * | 2014-07-02 | 2015-12-30 | 张峰 | The aviation station of aircraft let fly away by the continental rise orbit shot locomotive substituting alighting gear |
| CN106347698B (en) * | 2016-10-08 | 2019-08-23 | 周子涵 | Aircraft carrier launching apparatus |
| CN106184803B (en) * | 2016-10-08 | 2020-04-07 | 台州市皓仔邦工业设计有限公司 | Takeoff method of aircraft carrier takeoff device |
| CN106335650A (en) * | 2016-10-08 | 2017-01-18 | 周子涵 | Take-off device of aircraft |
| CN106314815B (en) * | 2016-10-08 | 2020-04-07 | 台州市皓仔邦工业设计有限公司 | Takeoff method of aircraft takeoff device |
| CN106740166A (en) * | 2016-11-21 | 2017-05-31 | 爱泊车机器人张家口有限公司 | Magnetic-attraction type cable line for intelligent garage docks charging device and application process |
| CN107328317B (en) * | 2017-07-03 | 2019-05-17 | 上海机电工程研究所 | The gear flame device of emitter hot-line insertion and extraction mechanism |
| CN107444668B (en) * | 2017-08-02 | 2021-01-15 | 杨长云 | Air ejector |
| CN108382589A (en) * | 2018-02-05 | 2018-08-10 | 中国航空工业集团公司成都飞机设计研究所 | A kind of pair of overall aerodynamic arrangement for sending out unmanned plane and its short take-off and landing method |
| CN109573085A (en) * | 2018-12-12 | 2019-04-05 | 中国航空工业集团公司西安飞机设计研究所 | A kind of rail mounted takeoff and landing system |
| CN110027721A (en) * | 2019-05-16 | 2019-07-19 | 西北工业大学 | Fixed-wing unmanned plane take-off system is launched in detonating combustion |
| CN113218552B (en) * | 2021-03-23 | 2022-11-18 | 中国人民解放军空军工程大学 | Auxiliary equipment and method for evaluating installation thrust of aero-engine |
-
2008
- 2008-03-07 CN CN2008100546176A patent/CN101244764B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN101244764A (en) | 2008-08-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101244764B (en) | Cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane | |
| US7234667B1 (en) | Modular aerospace plane | |
| CN102015452B (en) | Ground-bound device for take off, landing and taxiing of aircrafts | |
| CN101522525B (en) | Aircraft with hybrid aerodynamic and space flight, and associated flight control method | |
| CN110589034B (en) | Recyclable high-speed flying rocket and recycling method | |
| US20130181088A1 (en) | Aircraft versatile power system | |
| CN102292264A (en) | Reusable module for a launcher | |
| ITRM970762A1 (en) | SYSTEM FOR THE TRANSFORMATION OF A SELF-SUPPORTED HORIZONTAL FLIGHT AIRCRAFT INTO AN INTEGRATED, HYBRID TAKE-OFF AIRCRAFT | |
| CN1173157A (en) | Space launch vehicles configured as gliders and towed to launch altitude by conventional aircraft | |
| JPH05501095A (en) | turbo craft | |
| CN102107737A (en) | Front-pull rear-push aircraft carrier ejector and ejection method | |
| US4687158A (en) | Jump strut landing gear apparatus and system | |
| CN107696812A (en) | Oil-electricity hybrid power system and vertical take-off and landing hovercar with same | |
| CN105649775A (en) | System taking compressed air as force applying source, operation method for system and airplane | |
| CN101513936A (en) | Taking off device and taking off method for carrier-based aircraft | |
| CN101878153A (en) | Aerial device | |
| CN105644283B (en) | Vertical take-off and landing flying car | |
| CN108216621A (en) | A kind of wing tip connection composite lights aircraft in parallel | |
| CN102514720B (en) | Safe carrier landing and high-efficiency energy recycling device of carrier aircraft | |
| CN109911230A (en) | The aerocraft system for sliding, taking off and climbing with auxiliary | |
| WO2007133182A2 (en) | Modular aerospace plane | |
| RU2442727C1 (en) | Reusable missile and aircraft unit and way to return it to spaceport | |
| CN108657465A (en) | It is a kind of take off vertically, the sub- In-Orbit Plane of horizontal landing | |
| CN103224028A (en) | JATO (jet-assisted-takeoff) engine/auxiliary fuel tank combined body | |
| RU2534676C1 (en) | Cryogenic turbo-electric stol aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| CB03 | Change of inventor or designer information |
Inventor after: Wang Siken Inventor before: Wang Gang |
|
| COR | Change of bibliographic data | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20151030 Address after: 030001 No. 30 East Street, Taiyuan, Shanxi Patentee after: Wang Siken Address before: 030001 Shanxi Province, Taiyuan City Street No. 30 Junlin skyscraper C2-1101 Patentee before: Wang Gang |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110126 Termination date: 20170307 |