CN1032645A - Stol device for ultralight aircraft - Google Patents
Stol device for ultralight aircraft Download PDFInfo
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- CN1032645A CN1032645A CN 88107333 CN88107333A CN1032645A CN 1032645 A CN1032645 A CN 1032645A CN 88107333 CN88107333 CN 88107333 CN 88107333 A CN88107333 A CN 88107333A CN 1032645 A CN1032645 A CN 1032645A
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- 238000010168 coupling process Methods 0.000 claims description 5
- 238000005859 coupling reaction Methods 0.000 claims description 5
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- 239000000758 substrate Substances 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 13
- 238000012423 maintenance Methods 0.000 abstract description 2
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- 235000007164 Oryza sativa Nutrition 0.000 description 8
- 230000008569 process Effects 0.000 description 8
- 235000009566 rice Nutrition 0.000 description 8
- 238000006073 displacement reaction Methods 0.000 description 7
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- 229910000831 Steel Inorganic materials 0.000 description 1
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- 238000004458 analytical method Methods 0.000 description 1
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Abstract
The present invention relates to the take-off and landing device of aircraft, it provides a cover to be mainly used in the device of ultra light aircraft short take-off and landing (STOL), especially can make ultra light aircraft in the room (building) top balcony short take-off and landing (STOL); The shared covering device of take-off and landing, its engine installation adopt vacuum-actuated tube servo-unit, also comprise parts such as pulley, trailing cable, extraction equipment, fixer and control system.The present invention is simple in structure, cost, usage charges and cost of maintenance are low, for the popularizing of ultra light aircraft, utilization provide economy, effective method, also can be used for small-size ejection rotor plane and light glider.
Description
The present invention relates to the take-off and landing device of aircraft.
Ultra light aircraft is the emerging machine of the seventies, is characterized in small and exquisite, usually, long 5～8 meters of fuselage, 10 meters of the spanes (span of a kind of special ultra light aircraft-" parasol " is littler), take-off weight M is 160～300 kilograms, can carry 1～3 people; Power power is little, is 30～60 horsepowers, and takeoff speed is about 50 kilometers/hour, and cruising speed is about 60～100 kilometers/hour, and stalling speed is about 40 kilometers/hour, even more than 30 kilometer/hour.It flexibly, convenient, stability is good, noise is little, cost, cost of maintenance are low, oil consumption is economized, and is widely used in departments such as agriculture and forestry, tourism, traffic.But the same with all fixed wing aircrafts, need sufficiently long runway to be used to take off, land, this is very restricted its use.
The device that improves the take-off and landing performance catapult-launching gear that takes off, jet assisted takeoff (JATO) or quicken car, sloping platform feedway, drag parachute or plate and block etc.
The short takeoff landing gear of ship-board aircraft commonly used is respectively steam-type catapult-launching gear and hydraulic actuator, (Shi Chaoli work " aviation outline " the 242nd～243 page, National Defense Industry Press publishes, 1978).The primary member of steam-type catapult-launching gear is pressurized strut, and the high pressure steam that it produces by the marine vapor driving engine promotes the piston motion in the pressurized strut.Be connected with hauling hook on the piston, the annulus in hook jail, annulus connects aboard by cable wire.Slotted in the pressurized strut, also have slit above deck, so that hauling hook hauls the aircraft sliding race of power-assisted forward along slit.And landing gear is the high landing cable wire of horizontal above deck several of hauling 10～15cm, and its two ends are walked around fixed pulley and are connected on the stressed hydraulic actuator.During aircraft landing, put down pintle, and hook wherein cable wire, haul it to one section of advancing slip race, at this moment cable wire makes and hauls piston and move in pressurized strut, consumes aircraft kinetic energy, makes the very fast reduction of speed of aircraft, and halts.
Said apparatus two covering devices that need launch and land, structure are complicated.
The purpose of this invention is to provide a kind of device that is mainly used in the ultra light aircraft short take-off and landing (STOL), especially can make the device of ultra light aircraft (building) top balcony short take-off and landing (STOL) in the room, it is simple in structure, and expense is extremely low, the shared covering device of taking-off and landing.
The present invention includes parts such as engine installation, pulley, trailer coupling, extraction equipment, fixer and control system.Engine installation adopts vacuum-actuated tube servo-unit, piston is arranged in the pressurized strut, band hauling hook or ring on the piston, it is that the pressurized strut nozzle communicates with atmosphere that front end is established aperture, air intake and bleeding point are also established in pressurized strut, bleeding point links to each other with extraction equipment, and air intake and bleeding point are equipped with sealing mechanism.Usually the pressurized strut of adopting a pair of symmetry to place, shape is advisable with cylindrical.Trailer coupling is established trailing cable, drag-line and assembly pulley, is connected with piston.
Pulley is positioned at the front end of start nozzle, can establish two groups of fixed pulleys.First group of dead ahead that is fixed on the start nozzle respectively, the trailing cable that connects the piston hauling hook is walked around this to fixed pulley; But another group fixed pulley vertical lift is between first group of fixed pulley.
Extraction equipment can adopt universal air pump, for example vacuum pump.
Fixer comprises aircraft fixer and pressurized strut piston fixer.Can adopt control mechanism control taper fixed link to cooperate the annulus that is installed on aircraft wheel and the trailing cable to finish.Control mechanism can be used relay.When the aircraft fixed link stretches out, insert the annulus that is installed on the aircraft nose wheel rear portion, aircraft is fixed; When the retraction of aircraft fixed link, the aircraft fixed link withdraws from this annulus, but the aircraft free motion.In like manner, when pressurized strut piston fixed link stretches out, insert the annulus on the trailing cable, piston is fixed in a certain position, and closes the start nozzle; When the retraction of pressurized strut piston fixed link, remove fixation to piston.The control mechanism of aircraft fixer can be located under the runway, so that do not influence alightinging run of aircraft.
Before the aircraft landing, but control system makes the vertical lift assembly pulley on the runway drop to below the runway face start signal lamp.For example utilize the radio telecommand communication equipment or by ground staff commander, control.
Drag-line is used for being connected between trailing cable and the aircraft, and the one end is connected in the centre of trailing cable, and the other end is an annulus, so as towing aircraft launch hook.
This device also can be set up the rope of stumbling, stumble rope and pressurized strut axis normal.
The catapult-assisted take-off process of following analysis of aircraft.
Before taking off, open the air intake 4 of pressurized strut 1, as shown in Figure 1, allow the air admission pressurized strut, move pressurized strut piston 3 to pressurized strut nozzle 2 places, close air intake then, at this moment piston is sealed the pressurized strut nozzle.Be inserted in piston fixed link 8 with the fixing (see figure 2) of piston with piston clamping rings 7.Start the extraction equipment that is connected in bleeding point 5, at this moment, piston is subjected to suction backward, but can not move backward because of being fixed.Push aircraft to runway D place, rise liftable assembly pulley 10, drag-line 11 is fastened launch hook 13 on aircraft 12 front-wheels, shown in Fig. 3 and 4.With aircraft fixer fastening aircraft, aircraft clamping rings 14 is inserted in the aircraft fixed link 15, and aircraft static controller 16 is embedded in below the runway.Start aero-engine, when power reaches maximum, by controller 9 and 16 control plunger fixed links and the action of aircraft fixed link, at this moment, piston is moved by d-b-a, and towing aircraft is slided to the C power-assisted by D and run simultaneously, quicken liftoff the taking off in back at DC section short distance, break away from drag-line.
After airplane catapult took off, trailing cable 6 had recovered the state before the cataplane.
To run in order making in the airplane catapult process along the runway center line marking direction is sliding, preferably to be provided with directed rope 17 on the runway center line marking, see Fig. 5, and the rear end on runway center line marking establishes a quarter butt 18, directed rope can be fixed on the quarter butt top.But also can establish another quarter butt 20 on vertical lift fixed pulley substrate 19, the upper diameter of this quarter butt is little, and lower diameter is big, the upper and lower part concentric.The top that directed Suo Yuanhuan 21 can entangle quarter butt 20, but can not be inserted in its underpart.So directed rope be drawn as one be parallel to the runway face and with runway center line marking straight line in the same way, it has certain height from runway, but all lower than trailing cable and drag-line, does not influence safe take-off.
Obviously, before the aircraft landing, when control liftable fixed pulley descended, the annulus of directed Suo Qianduan was subjected to the upwards resistance of runway face and breaks away from quarter butt on the substrate, thereby makes directed Suo Songchi, does not influence aircraft landing.
Below can shorten the principle of the taking-off and landing ground run distance of ultra light aircraft greatly with vacuum-actuated tube servo-unit with concrete data analysis.
Aircraft landing is sliding when running, and the resistance that is subjected to trailing cable is f=2FCoS θ, and wherein to be aircraft at trailing cable hinder θ glides when running, the angle of trailing cable and pressurized strut stack shell (θ≤90 °).Because θ is a variable, so f also is a variable.When θ=θ min, f reaches maxim.Can prove that variable force 2FCos θ to aircraft institute work (work of resistance) is when alightinging run displacement 1
, r is the distance between two pressurized struts in the formula.
If the take-off weight M=300 kilogram of ultra light aircraft, takeoff speed Vt=50 kilometer/hour, landing speed Vo=40 kilometer/hour, the sliding running velocity degree Vo ' after " descend slowly and lightly and contact to earth "=35 kilometers/hour.
Why can Vo be reduced to Vo '? because aircraft aircraft power in " descend slowly and lightly and contact to earth " process is progressively reduced, be subjected to air resistance again.
The sliding race of aircraft landing carried out under the servo-unit drag effect, and this process air speed is reduced to zero (being that aircraft stops) by Vo '.This process should meet theorem of kinetic energy: 1/2 MV
' 2 o=W
o, promptly
If the pressurized strut inside radius, i.e. piston radius R=8cm, so, piston area S '=π R
2Because in the sliding race process of aircraft landing, the poor approximately 1atm of piston front-back air pressure is so piston is subjected to pressurized strut suction F=S ' P=S ' * 1atm=S ' * 1 kg/cm
2=2009.6(ox frequently).If two pressurized struts with these data and M=300 kilogram, in Vo '=35 kilometer/hour substitutions (1) formula, are tried to achieve 1=7 rice, so the distance of landing run 1 of aircraft under the servo-unit drag effect is 7 meters at a distance of r=10 rice.
Calculate the power-assisted takeoff distance S of ultra light aircraft again.By as can be known top, piston area S '=π R
2, R=8 centimetre, so S '=π * 8
2Because of after air in the pressurized strut taken out light, piston front-back draught head P ≈ 1atm is so piston is subjected to suction F=π * 8 again
2* 1atm=π * 8
2* 1 kg/cm
2=2009.6(newton).But because of the fixed pulley close proximity (as 2 centimetres) of two vertical lifts, trailing cable is shape shown in Figure 3 after walking around it again, so trailing cable effect power aboard is about the twice (2F) of each pressurized strut to piston suction.
Aircraft should meet theorem of kinetic energy during rolling start under the servo-unit effect: 1/2 MVt
2=2FS, with the M=300 kilogram, F=2009.6 newton, Vt=50 kilometer/hour, the substitution following formula gets S=6.3(rice).Because trailing cable is drawn as Fig. 3 shape, so the length of required pressurized strut is promptly taken off the rice apart from S=6.3.Aircraft is when starting heats, and some is used to quicken aircraft to engine power own the air resistance except that being used to overcome, and more than calculates and has ignored this power, so in fact required pressurized strut size is comparable above-mentioned littler.
Aircraft landing is slided also has a kind of method when running, and promptly slide and run direction with opposite shown in the figure with runway rear end forward end, but identical with Fig. 6 in essence.
Aircraft landing ground run distance 1 always is subjected to the restriction of start tube length S, but can prove that the distance of landing run of ultra light aircraft always is no more than this restriction.
The calculating of above-mentioned aircraft landing ground run distance is to have supposed that aircraft nose wheel alighting gear straight beam just in time pushes up the trailing cable mid point, if can prove withstand on the next door, the distance of landing run of aircraft will be shorter so.
If above-mentioned ultra light aircraft is without servo-unit, it take off, distance of landing run all is 80 meters.As seen utilize servo-unit can shorten its distance of landing run that takes off greatly.Above example is representative, because of Vt, the Vo ' value of ultra light aircraft all similar.According to 1/2 MVt
2=2FS and
Though M is more little, so 2FS and
Also more little, if pressurized strut internal diameter (being that F is identical) same as described above, takeoff distance S(is the start tube length so) can be short more, and distance of landing run 1 is also short more.General ultra light aircraft M＜300 kilograms, thus its S＜6.3 meter, 1＜7 meter, as if not utilizing servo-unit, its S, 1 is generally 50～70 meters.
Guaranteeing that 2F is no more than under the prerequisite of overload value of this ultra light aircraft, should make F big as far as possible, thereby make S, 1 littler (but F is too big, and R is also big, makes difficulty).
For minority M＞300 kilogram, the ultra light aircraft of Vt＞50 kilometer/hour is (if any a kind of ultra light aircraft M=500 kilogram, Vt=60 kilometer/hour), can adopt simultaneously to enlarge pressurized strut R and increase by two kinds of methods of pressurized strut S, or with shown in Figure 7 many to the pressurized strut deconvolution.
In sum, utilize the pressurized strut servo-unit can shorten taking off of ultra light aircraft greatly, distance of landing run especially can be built to the runway of ultra light aircraft on the balcony of top, room (building).
Ultra light aircraft will be before top, room (building) balcony runway lands, it is bright to control runway signal lamp 22 earlier, launch a bars light (as shown in Figure 9) along the balcony runway center line marking, aircraft is along light, with from the extreme low-altitude balcony (be generally 2～3 meters, the minority ultra light aircraft is 4 meters) that flies into of a certain height of light.In a single day aircraft flies into balcony and will begin in a minute " descend slowly and lightly and contact to earth ", falls the balcony face from 2～3 meters height through " descend slowly and lightly and contact to earth " usually, and the horizontal displacement of this process is more than 10 meter to 20 meters, and this section horizontal displacement district is called " the horizontal displacement district of contacting to earth descends slowly and lightly " of balcony.Aircraft needs sliding race just to stop for one section under the drag effect of servo-unit after balcony lands again, and this section claims " alightinging run the district ".The required size of balcony is determined by these two districts.If build a slope (see figure 8), can shorten the required length in this district greatly so, thereby shorten the required length of whole balcony " district of contacting to earth descends slowly and lightly ".Obviously, the gradient is big more, and this effect is good more.But the gradient is too big, and aircraft is subjected to vibrations also big when landing on the slope, can consider at alighting gear dress shock absorption device.If make slope highest point H be equal to or greater than the extreme low-altitude height h that flies into of aircraft, promptly during H 〉=h, aircraft can not put down by " descend slowly and lightly and contact to earth " and be flown to landing on the slope.Obviously, after " the horizontal displacement district of contacting to earth descends slowly and lightly " built up the slope, " alightinging run the district " should build up the platform mn contour with slope highest point H.Above way is not limited to the balcony runway.
In Fig. 8,1 is the aircraft landing ground run distance, L ' and L " are respectively and do not add slope and " horizontal displacement that contacts to earth descends slowly and lightly " when adding the slope; f-m-G is the aircraft track that " descends slowly and lightly and contact to earth "; m-g is illusory slope; m-n is the illusory platform that increases, and m is the touchdown point of aircraft on illusory slope, and G is an aircraft touchdown point on balcony when not having the slope.Obviously, slope highest point H lands so aircraft can not put down to fly on the slope less than treetop height h, and because of taking " descend slowly and lightly and contact to earth " method, and aircraft on the slope m point in the process of descending slowly and lightly is contacted to earth.
The present invention is according to the property of ultra light aircraft; Low such as takeoff speed and stall degree; 〉ㄅザパＡ⒚ィ⑹⑽＞ ，。 See extraction equipment again, can adopt general vacuum pump to bleed, again because the tolerance that will extract out is few, vacuum pump power can be very little because the requirement of pressurized strut degree of vacuum is not too high.
In sum, the present invention provides economy, effective method for universal, the utilization of ultra light aircraft.
Servo-unit of the present invention also can be used for small-size ejection rotor plane and light glider, and when launching aerodone, direction of ejection should become a suitable angle with level.If the pressurized strut size is enlarged, can be used for the short take-off and landing (STOL) of some aviettes.
Embodiment: the take-off weight M=200 kilogram of a ultra light aircraft, Vt=50 kilometer/hour, Vo=40 kilometer/hour, a pressurized strut can be designed, inside radius R=7 centimetre in Vo '=36 kilometer/hour, piston radius R=7 centimetre, piston area S '=π R so
2=π * 7
2, F=S ' * 1atm=S ' * 1 kg/cm
2=1538.6(newton).According to
(the parallel placement of two pressurized struts is at a distance of r
o), with the M=200 kilogram, Vo '=36 kilometer/hour, F=1538.6 newton, formula can be tried to achieve 1=6 rice above the substitution of r=8 rice, so the aircraft landing ground run distance is 6 meters.
Again according to 1/2 MVt
2=2FS, with the M=200 kilogram, Vt=50 kilometer/hour, F=1538.6 newton, to try to achieve the power-assisted takeoff distance be S=5.5 rice to formula above the substitution.
The pressurized strut steel pipe, 3 millimeters of wall thickness, long 5.5 meters, internal diameter R=7 centimetre, four fixed pulley diameters all are 4 centimetres, trailing cable, drag-line, directed rope, all use the multiply nylon cord to make, 2 meters of the corresponding start nozzles of two pulleys distance of first group of fixed pulley, long 2 meters of drag-line, the long 5.5 * 2+2 of trailing cable * 2+8=23(rice).Trailing cable is high 10 centimetres from balcony, and directed rope is also made by nylon cord from 4 centimetres on balcony, and 8 meters of the rope length of stumbling are made by a slightly elastomeric leather strap, and are high 6 centimetres from balcony, than directed Suo Lvegao.Select one widely 9 meters, long 30 meters balcony is made runway, and balcony is " the horizontal displacement district of contacting to earth descends slowly and lightly " for preceding 20 meters, because long enough needn't be built the slope, back 10 meters are " alightinging run the district " (seeing shown in Figure 9).
Claims (6)
1, a kind ofly is mainly used in the device that aircraft short take-off and landing (STOL) and light glider launch, comprise engine installation, trailer coupling, fixer, control system, engine installation adopts the pressurized strut servo-unit, be provided with piston in the pressurized strut servo-unit, it is characterized in that said pressurized strut servo-unit is with vacuum-actuated, the one end has the pressurized strut nozzle to communicate with atmosphere, be provided with air intake, bleeding point, bleeding point is connected with extraction equipment, air intake and bleeding point are all established sealing mechanism, and trailer coupling is connected with the pressurized strut piston.
2, device as claimed in claim 1 is characterized in that the pressurized strut piston establishes hauling hook or ring, and trailer coupling is established trailing cable, assembly pulley and drag-line, and trailing cable is connected with hauling hook or ring.
3, device as claimed in claim 1 is characterized in that pressurized strut is cylindrical, selects for use a pair of and parallel symmetry to place.
4, device as claimed in claim 1 is characterized in that fixer establishes aircraft fixer and pressurized strut piston fixer, forms by fixed link, clamping rings and control mechanism.
5, as claim 1 and 2 described devices, it is characterized in that pulley, establish two groups, wherein one group be positioned at the pressurized strut nozzle before, but another group be fixed on the substrate of vertical lift, trailing cable is walked around assembly pulley.
6, device as claimed in claim 1 is characterized in that establishing the rope of stumbling, stumble rope and pressurized strut axis normal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 88107333 CN1032645A (en) | 1988-10-18 | 1988-10-18 | Stol device for ultralight aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 88107333 CN1032645A (en) | 1988-10-18 | 1988-10-18 | Stol device for ultralight aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN1032645A true CN1032645A (en) | 1989-05-03 |
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|---|---|---|---|
| CN 88107333 Pending CN1032645A (en) | 1988-10-18 | 1988-10-18 | Stol device for ultralight aircraft |
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Cited By (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1996008410A1 (en) * | 1994-09-15 | 1996-03-21 | Airscrew Howden Limited | Launching projectiles |
| WO1996008429A1 (en) * | 1994-09-16 | 1996-03-21 | Daifuku Co., Ltd. | Storage apparatus |
| CN102120496A (en) * | 2010-10-22 | 2011-07-13 | 王先全 | Vacuum power catapult |
| CN102351043A (en) * | 2011-07-27 | 2012-02-15 | 南京航空航天大学 | Sliding and controlled motion landing area |
| CN102358430A (en) * | 2011-07-27 | 2012-02-22 | 南京航空航天大学 | Ship-borne aircraft capturing and arresting device |
| CN101100223B (en) * | 2007-08-10 | 2012-05-30 | 霍方华 | Steam catapult for carrier-based aircraft of aircraft carrier |
| CN102476711A (en) * | 2010-11-29 | 2012-05-30 | 葛泓杉 | Airplane short take-off safety device |
| CN102485595A (en) * | 2009-11-24 | 2012-06-06 | 刘华 | Aircraft landing damper for aircraft carrier |
| CN102625766A (en) * | 2009-04-24 | 2012-08-01 | 英西图公司 | Systems and methods for recovering and controlling post-recovery movement of an unmanned aerial vehicle |
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- 1988-10-18 CN CN 88107333 patent/CN1032645A/en active Pending
Cited By (42)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2293146B (en) * | 1994-09-15 | 1998-04-15 | Airscrew Howden Ltd | Launching projectiles |
| WO1996008410A1 (en) * | 1994-09-15 | 1996-03-21 | Airscrew Howden Limited | Launching projectiles |
| WO1996008429A1 (en) * | 1994-09-16 | 1996-03-21 | Daifuku Co., Ltd. | Storage apparatus |
| CN101100223B (en) * | 2007-08-10 | 2012-05-30 | 霍方华 | Steam catapult for carrier-based aircraft of aircraft carrier |
| US9944408B2 (en) | 2009-04-24 | 2018-04-17 | Insitu, Inc. | Systems and methods for recovering and controlling post-recovery motion of unmanned aircraft |
| US10843817B2 (en) | 2009-04-24 | 2020-11-24 | Insitu, Inc. | Systems and methods for recovering and controlling post-recovery motion of unmanned aircraft |
| CN102625766A (en) * | 2009-04-24 | 2012-08-01 | 英西图公司 | Systems and methods for recovering and controlling post-recovery movement of an unmanned aerial vehicle |
| CN102485595A (en) * | 2009-11-24 | 2012-06-06 | 刘华 | Aircraft landing damper for aircraft carrier |
| US8944373B2 (en) | 2010-09-27 | 2015-02-03 | Insitu, Inc. | Line capture devices for unmanned aircraft, and associated systems and methods |
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| US9856036B2 (en) | 2010-09-27 | 2018-01-02 | Insitu, Inc. | Line capture devices for unmanned aircraft, and associated systems and methods |
| CN102120496A (en) * | 2010-10-22 | 2011-07-13 | 王先全 | Vacuum power catapult |
| CN102476711A (en) * | 2010-11-29 | 2012-05-30 | 葛泓杉 | Airplane short take-off safety device |
| CN102358430A (en) * | 2011-07-27 | 2012-02-22 | 南京航空航天大学 | Ship-borne aircraft capturing and arresting device |
| CN102358430B (en) * | 2011-07-27 | 2013-12-25 | 南京航空航天大学 | Ship-borne aircraft capturing and arresting device |
| CN102351043B (en) * | 2011-07-27 | 2014-02-19 | 南京航空航天大学 | Slidable and controllable motion carrier aircraft landing area |
| CN102351043A (en) * | 2011-07-27 | 2012-02-15 | 南京航空航天大学 | Sliding and controlled motion landing area |
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