CN102963524A - Slide-wheel composite type small and medium sized UAV landing gear system - Google Patents
Slide-wheel composite type small and medium sized UAV landing gear system Download PDFInfo
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- CN102963524A CN102963524A CN2012103517932A CN201210351793A CN102963524A CN 102963524 A CN102963524 A CN 102963524A CN 2012103517932 A CN2012103517932 A CN 2012103517932A CN 201210351793 A CN201210351793 A CN 201210351793A CN 102963524 A CN102963524 A CN 102963524A
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Abstract
The invention relates to a slide-wheel composite type small and medium sized UAV (unmanned aerial vehicle) landing gear system. The system is characterized in that: each taxiing vehicle wheel assembly located on slide plates is equipped with a base for installing vehicle wheels, a clamping slot is arranged above the base, a clamp hole for placing a compression spring is disposed at the center of the clamping slot, a threaded hole is coaxially disposed at the clamping hole center, and slideway holes are arranged on landing gear supporting arms and the slide plates coaxially toward the direction of the threaded hole. The landing gear system also includes a pair of automatic release control assemblies able to control timely separation of each taxiing vehicle wheel assembly. Each automatic release control assembly comprises: a sliding pin equipped with a small hole at the upper end, a fastening rope able to pass through the small hole at the upper end of the sliding pin so as to prevent the sliding pin from slipping off from the slideway holes, and a cutter that passes through and is in connection with the fastening rope and can cut off the fastening rope. The cutter cut off the fastening rope timely under the control instruction of a control circuit board so as to complete automatic separation release actions of the taxiing vehicle wheel assembles, thus realizing the functions of rapid taxiing takeoff and short-range braking landing.
Description
Technical field
The present invention relates to a kind of middle-size and small-size unmanned plane Landing Gear Design technology, particularly a kind of sledge, the middle-size and small-size unmanned plane Landing Gear System of wheel combined type (or claim: middle-size and small-size unmanned plane sledge is taken turns the mixing type undercarriage system).
Background technology
The performance of unmanned plane alighting gear is the index of unmanned plane during flying place comformability most critical.Jumbo from the fraternal First aircraft of inventing of Lai Te to today, the Landing Gear System of aircraft has experienced two important stages, F/s is the tail wheel type landing gear system (being comprised of tail wheel of airplane tail group and anterior two main wheels) of early stage aircraft, its advantage be to runway require low, shortcoming is that direction is controlled relatively poor, and the Landing Gear System of rear bikini is fit to early stage at a slow speed aircraft; Subordinate phase is modern tricycle landing gear system (being comprised of front-wheel of aircraft forward and two main wheels of postmedian), and its advantage is that direction is controlled better, and shortcoming is to the having relatively high expectations of runway, and is fit to the high-speed type aircraft in modern times.Because middle-size and small-size unmanned plane speed is slower, general not in the landing of the airport of special use, adopt the in the majority of tail wheel type landing gear system, but the tail wheel type landing gear system also runs into some in application has a strong impact on the adaptive particular problem in unmanned plane place, mainly be: 1) unmanned plane is at pitch, when land in the landing place that the hard such as cement are smooth, the wheel undercarriage ground drag of rear bikini is less, ground run distance is longer, the direction control accuracy is not high, in the actual job environment, the landing length in place and width restriction are very large, the situation of collision obstacle behind the UAV Landing often occurs; 2) unmanned plane is on the meadow, during the landing of the landing place such as hollow ground, weak soil ground, and the friction drag of front-wheel is very large, and speed descends rapidly during aircraft landing, causes the momentum of aircraft to cushion smoothly and subdues, and easily makes aircraft produce the tipping phenomenon and impaired.
In order to overcome above-mentioned 2 problems, 1972, China is that air defence forces allot and to change a type target drone and begin to adopt the slide-type alighting gear, through actual verification, the slide-type alighting gear has better solved colliding with easily of existing in the unmanned plane landing, the easy problem of tipping, but because the slide-type alighting gear is larger at the friction drag of takeoff phase, needs sliding distance of running longer, the take-off venue is difficult for seeking in the operation of actual outfield, and the place adaptation of aircraft is extremely restricted.
In addition, " about the suggestion of in-depth China low altitude airspace administrative reform " (No. [2010] 25, promulgated by the State Council) signed and issued by State Council, the Military Commission of the CPC Central Committee on August 19th, 2010.Point out to develop low altitude airspace in " suggestion ", " be conducive to spur domestic demand, expand employment, tap new sources of economic growth; Be conducive to support for national defense construction provides aviation human resources deposit and basic environment, the construction of building a well-off society in an all-round way, speed up socialist modernization is had very important strategic importance "; formally opening ice of low altitude airspace, brought brand-new opportunity for the development of civilian unmanned plane low-altitude remote sensing industry.
Summary of the invention
In view of this, the objective of the invention is to design a kind of sledge, middle-size and small-size unmanned plane Landing Gear System of wheel combined type (claim again: middle-size and small-size unmanned plane sledge is taken turns the mixing type undercarriage system) that has wheeled and slide-type takeoff and landing performance concurrently, so that have the function of quick rolling start, short distance brake landing.
The present invention realizes with following technical scheme, this sledge, the middle-size and small-size unmanned plane Landing Gear System of wheel combined type comprises: one is fixed in the front by (conventional " eight " font) of forebody below, the landing gear assembly that rear alighting gear hold-down arm forms, be fixed in alighting gear hold-down arm below and consist of the skid plate of skid assembly (by a left side, the skid plate of right two routines forms), be installed in respectively two sliding tail-wheel assemblies that run wheel assembly (claiming again the sliding main wheel module of running) and be positioned at afterbody on a pair of skid plate, be used for the control circuit board (being installed on fuselage) of control landing, it is characterized in that:
A, described each sliding wheel assembly that runs that is positioned on a pair of skid plate all has one for the sliding pedestal that runs wheel is installed, in each pedestal, offer axle hole, described each sliding wheel assembly that runs all is equipped with two sliding both sides of running wheel and being installed in the pedestal axle hole by a wheel rotational symmetry, above described each pedestal, all offer one and can cooperate with described skid plate the draw-in groove with contact surface of installing, draw-in groove central authorities above described each pedestal offer a hole clipping that is used for settling Compress Spring, at the coaxial tapped bore that offers of hole clipping central authorities, offer perforate as skidway hole (slideway that is namely formed by perforate) at described alighting gear hold-down arm and skid plate facing to the tapped bore direction of described pedestal draw-in groove is also coaxial;
B, described Landing Gear System also comprises a pair ofly can be controlled each sliding race and can reliably be connected the automatic release control assembly (but also claiming wheel automatically to separate the release control assembly) that (closely being connected) can in time separate not only between wheel assembly and alighting gear hold-down arm and the skid plate, each automatic release control assembly comprises that again a upper end has little perforate, the bottom has externally threaded sliding pin, one is installed on the Compress Spring between the hole clipping of skid plate and pedestal draw-in groove, during installation, described sliding pin can be from bottom to top respectively easy fit pass the skidway hole that formed by alighting gear hold-down arm and the perforate of skid plate (skidway hole that is namely formed by the perforate of rear alighting gear hold-down arm and skid plate) and Compress Spring centre hole and be bolted in the tapped bore of described pedestal draw-in groove, and after installing, the little perforate of sliding pin upper end is exposed outside alighting gear;
C, described each automatic release control assembly (claiming again wheel automatically to separate the release control assembly) also comprises: one can be passed the little perforate in described sliding pin upper end with the fastening rope of anti-skidding pin slippage from the skidway hole of described alighting gear hold-down arm and skid plate perforate composition, one cross-under also can be cut off the cutter of this fastening rope on described fastening rope, this cutter leads to pilot and is connected with described (charged on the fuselage) control circuit board, described cutter can be under the control command of this control circuit board timely fast shut-off fastening rope, to realize finishing sliding automatic separation release movement of running the wheel assembly.
The present invention can also further be specially:
One, described cutter is the tubular construction of making the cylinder shape, in the cutter of this cylinder shape tubular construction, be provided with successively valve piston and gunpowder piece, in described gunpowder piece, light-up plug is housed, leading to pilot at the Liang Jichu of this light-up plug is connected with the described control circuit board that is positioned on the fuselage, cylinder wall (being barrel) at described cutter tubular construction is provided with eyelet hole, described fastening rope is the tubular casing wall (being barrel) that is horizontally through cutter through this eyelet hole, the principle of work of cutter cuts fastening rope is, after the control system of unmanned plane receives the instruction that needs the release wheel, under the control command of control circuit board, produce large current, pilot produces electro spark when getting electric light-up plug the two poles of the earth conveying high-pressures electricity in cutter gunpowder piece, electro spark is ignited the gunpowder piece, the high pressure gas that gunpowder sharply produces promote valve piston and move forward along cutter tubular casing wall, when valve piston process eyelet hole, namely cut off rapidly the fastening rope that passes in the casing wall eyelet hole, sliding pin is at (under the potential energy effect at the compacted rear deposit of spring) down sliding under the elastic force effect of Compress Spring and break away from skidway hole, the sliding wheel assembly (i.e. the sliding main wheel module of running) that runs is come off, to finish sliding automatic separation release movement of running the wheel assembly from the skid plate.
Two, described each sliding race wheel assembly (claiming again the sliding main wheel module of running) is positioned at the below of rear alighting gear hold-down arm, be provided with a pair of set pin at described rear alighting gear hold-down arm, the two-end-point of after installing described (passing sliding pin) fastening rope is fixed on this set pin.
Three, the tapped bore on the described pedestal draw-in groove is connected with the axle hole of described pedestal, when described sliding pin is bolted in the tapped bore of pedestal draw-in groove, the bottom of this sliding pin threaded portion can conflict on described wheel axle (being installed in stability in the pedestal axle hole to keep the wheel axle).
Four, on described each pedestal, all offer a hole clipping that is used for settling micro buzzer-phone, the described micro buzzer-phone that is embedded in this pedestal hole clipping can be subjected to vibrations to trigger (to consist of " audio frequency tracing module "), when sliding race wheel module is fallen on ground from Landing Gear System release, this buzzer phone can be triggered by vibrations, namely trigger its buzzing by the vibrations that produce of falling, in order in the external environment of complexity, search out rapidly the sliding wheel module of running.
Use the present invention to have the following advantages than prior art:
1, complete function.Landing Gear System successfully utilizes the characteristic of friction of rolling and cliding friction, has realized the short range rolling start, and short range brake landing function has overcome that unmanned plane takes off, the problems such as colliding with in the landing process, tipping, has improved the place adaptive capacity of unmanned plane.
2, lightweight.Landing Gear System has utilized simple physical construction and gunpowder cutter to cooperate to realize discharging the function of wheel, and than the pure physical construction releaser of routine, physical construction is simplified to greatest extent, and therefore the weight of whole system be compressed to minimum.Verify take-off weight as 20 kilograms unmanned plane take us, Landing Gear System is removed the skid part, and the weight of other structures only is about 100 grams.
3, reliability is high.A, monolateral " the sliding wheel module of running " of Landing Gear System adopt 2 wheels, the skid integrated circuit board is on the pedestal in the middle of two wheels, the parts stress equalizations such as alighting gear, skid, pedestal, wheel shaft, wheel, all do not produce the moment of torsion of side direction, guaranteed that parts are unsuitable damaged, whole physical construction reliability is high; Electronic ignition, gunpowder cutting fastening rope, the Compress Spring that the release of b, " sliding run about wheel module " is ignited gunpowder by electro spark ejects several technology points such as wheel and consists of, these technology points itself are simple and reliable, through organic combination, it is higher that whole wheel discharges the subsystem reliability.C, utilize the cliding friction of skid to realize brake, its technological approaches is simple and reliable, conventional middle-size and small-size unmanned plane brake system, wheeled disc brake, the propulsive effort when utilizing air pressure that brake is provided, the gas circuit equipment that this system need to be complicated and the mechanical mechanisms of brake of adopting more, except system complex, fault rate is high, outside the low shortcoming of reliability, has also increased more structural weight.
So the present invention in one, has realized the function of quick rolling start, short distance brake landing in conjunction with the advantage of the advantage of rear 3 wheel undercarriages and slide-type alighting gear.
Description of drawings
Fig. 1 is a kind of integral installation distribution structure scheme drawing of Landing Gear System of the present invention;
Fig. 2 is the assembly connection scheme drawing of each parts of Landing Gear System of the present invention;
Fig. 3 is the structural representation of cutter that can the fast shut-off fastening rope of the present invention;
Fig. 4 is the structural representation of Landing Gear System of the present invention when being assemblied on the unmanned plane.
Wherein: the 1--landing gear assembly, (" eight " font) alighting gear hold-down arm before the 2--, (" eight " font) alighting gear hold-down arm behind the 3--, 4--skid assembly is (by a left side, the skid plate of right two routines forms), 5-skid plate, the sliding wheel (claiming again the sliding main wheel that runs) that runs of 6--, 7--wheel catch, the 8--pedestal, the axle hole of 9--pedestal, 10-is furnished with the wheel axle of wheel catch, draw-in groove on the 11--pedestal, 12--Compress Spring (claiming again the pressure type spring), hole clipping on the 13--pedestal draw-in groove (being used for settling Compress Spring), 14-is positioned at the tapped bore on the pedestal draw-in groove, 15--skidway hole (being formed by alighting gear hold-down arm and the perforate of skid plate), the automatic release control assembly of 16--(claiming again wheel automatically to separate the release control assembly), the 17--bottom has externally threaded sliding pin, the little perforate of 18--sliding pin upper end, the 19--fastening rope, 20--cutter, 21--gunpowder piece, the 22--light-up plug, 23--pilot, 24--valve piston, 25-are located at the eyelet hole on the cutter tubular casing wall (barrel), the 26--set pin, the 27--micro buzzer-phone, 28-installs the hole clipping of buzzer phone, 29--unmanned aerial vehicle body, 30--(charged on the fuselage) control circuit board, the 31--tail-wheel assembly.
The specific embodiment
With reference to accompanying drawing, the present invention realizes with following technical scheme, this sledge, the middle-size and small-size unmanned plane Landing Gear System of wheel combined type, comprise: one is fixed in the front by (conventional " eight " font) of forebody below, the landing gear assembly 1 that rear alighting gear hold-down arm forms, be fixed in the skid plate 5 of formation skid assembly 4 of alighting gear hold-down arm below (by a left side, the skid plate of right two routines forms), be installed in respectively two sliding tail-wheel assemblies 31 that run wheel assembly (claiming again the sliding main wheel module of running) and be positioned at afterbody on a pair of skid plate 5, be used for (be installed on the fuselage charged) control circuit board 30 of control landing, it is characterized in that:
A, described each sliding wheel assembly that runs that is positioned on a pair of skid plate (claims again the sliding main wheel module of running, the below of " eight " font alighting gear hold-down arm after being positioned at) all has one and be used for installing the sliding pedestal 8 that runs wheel (claiming again the sliding main wheel that runs) 6, in each pedestal, offer axle hole 9, described each sliding wheel assembly that runs all is equipped with two sliding both sides of running wheel 6 and being installed in pedestal axle hole 9 by a wheel axle 10 symmetries, above described each pedestal 8, all offer one and can cooperate with described skid plate 5 draw-in groove 11 with contact surface of installing, draw-in groove central authorities above described each pedestal 8 offer a hole clipping 13 that is used for settling Compress Spring 12, at the coaxial tapped bore 14 that offers of hole clipping central authorities, offer perforate as skidway hole (slideway that is namely formed by perforate) 15 at described alighting gear hold-down arm 3 and skid plate 5 facing to tapped bore 14 directions of described pedestal draw-in groove are also coaxial;
B, described Landing Gear System also comprises a pair ofly can be controlled each sliding race and can reliably be connected the automatic release control assembly (but also claiming wheel automatically to separate the release control assembly) 16 that (closely being connected) can in time separate not only between wheel assembly (claim not only the sliding main wheel module of running) and alighting gear hold-down arm and the skid plate (referring to rear " eight " font alighting gear hold-down arm and skid plate) 5, each automatic release control assembly comprises that again a upper end has little perforate 18, the bottom has externally threaded sliding pin 17, one is installed on the Compress Spring 12 between the hole clipping 13 of skid plate 5 and pedestal draw-in groove, during installation, described sliding pin 17 can be from bottom to top respectively easy fit pass the skidway hole that formed by alighting gear hold-down arm and the perforate of skid plate (skidway hole that is namely formed by the perforate of rear alighting gear hold-down arm and skid plate) 15 and Compress Spring centre hole and be bolted in the tapped bore 14 of described pedestal draw-in groove, and after installing, the little perforate 18 of sliding pin 17 upper ends is exposed outside alighting gear;
C, described each automatic release control assembly (claiming again wheel automatically to separate the release control assembly) 16 also comprises: one can be passed the little perforate 18 in described sliding pin 17 upper ends with the fastening rope 19 of anti-skidding pin (in the skidway hole that namely is comprised of the perforate of rear " eight " font alighting gear hold-down arm and skid plate) slippage from the skidway hole 15 that described alighting gear hold-down arm and the perforate of skid plate form, one cross-under also can be cut off the cutter 20 of this fastening rope on described fastening rope, this cutter leads to pilot 23 and is connected with described (charged on the fuselage) control circuit board 30, described cutter 20 can be under the control command of this control circuit board 30 timely fast shut-off fastening rope 19, to realize finishing sliding automatic separation release movement of running the wheel assembly.
The present invention can also further be specially:
One, described cutter 20 is tubular constructions of making the cylinder shape, in the cutter of this cylinder shape tubular construction, be provided with successively valve piston 24 and gunpowder piece 21, in described gunpowder piece, light-up plug 22 is housed, one end of described pilot 23 is connected with the two poles of the earth of light-up plug 22, the other end is connected (namely the Liang Jichu of this light-up plug 22 control circuit board that leads to the charged on pilot 23 and the described fuselage is connected) with described (charged) control circuit board 30 that is positioned on the fuselage 29, cylinder wall (being barrel) at described cutter tubular construction is provided with eyelet hole 25, described fastening rope 19 is the tubular casing walls (barrel) that are horizontally through cutter through this eyelet hole, the principle of work of cutter cuts fastening rope is, after the control system of unmanned plane receives the instruction that needs the release wheel, under the control command of control circuit board, produce large current, pilot produces electro spark when getting electric light-up plug the two poles of the earth conveying high-pressures electricity in cutter gunpowder piece, electro spark is ignited the gunpowder piece, the high pressure gas that gunpowder sharply produces promote valve piston and move forward along cutter tubular casing wall, when valve piston process eyelet hole, (valve piston moves to cutter tubular casing wall bottom namely to cut off rapidly the fastening rope that passes in the casing wall eyelet hole, high pressure gas discharge from eyelet hole), sliding pin is at (under the potential energy effect at the compacted rear deposit of spring) down sliding under the elastic force effect of Compress Spring and break away from skidway hole 15, the sliding wheel assembly that runs is come off, to finish sliding automatic separation release movement of running the wheel assembly from skid plate 5.
Two, the below of (" eight " font) alighting gear hold-down arm 3 after each sliding race wheel assembly of described (being positioned on a pair of skid plate) is positioned at, be provided with a pair of set pin 26 at described rear alighting gear hold-down arm 3, the two-end-point of after installing described (passing sliding pin) fastening rope 19 is fixed on this set pin.
Three, the tapped bore 14 on the described pedestal draw-in groove is connected with the axle hole 9 of described pedestal, when described sliding pin 17 is bolted in the tapped bore of pedestal draw-in groove, the bottom of this sliding pin threaded portion can conflict on described wheel axle 10 (being installed in stability in the pedestal axle hole to keep the wheel axle).
Four, on described each pedestal 8, all offer a hole clipping 28 that is used for settling micro buzzer-phone 27, the described micro buzzer-phone that is embedded in the pedestal hole clipping 28 can be subjected to vibrations to trigger (to consist of " audio frequency tracing module "), when sliding race wheel module is fallen on ground from Landing Gear System release, this buzzer phone can be triggered by vibrations, namely trigger its buzzing by the vibrations that produce of falling, in order in the external environment of complexity, search out rapidly the sliding wheel module of running.
Specific embodiment:
1, system's assembling.In the axle hole 9 in the wheel shaft 8 insertion pedestals, sliding pin is threaded in the middle tapped bore of pedestal draw-in groove, can fix wheel shaft after the locking, it can not slided in axle hole, put into wheel on the wheel shaft both sides, and lock wheel catch 7, Compress Spring (pressure type spring) card people is arrived in the circular hole clipping of pedestal, this moment, Compress Spring was concentric with sliding pin, the diameter of Compress Spring than sliding pin diameter greatly to guarantee that both do not contact, sliding pin is passed from bottom to top the slideway of the perforate composition of skid and alighting gear, the little perforate on sliding pin top is exposed outside alighting gear, fastening rope is passed little perforate on the sliding pin, entangle sliding pin, and then pass eyelet hole on the cutter tubular casing wall (barrel), be fixed at last on the set pin of alighting gear, will guarantee that Compress Spring compresses fully this moment, (elasticity modulus of spring is unsuitable excessive because the elasticity modulus of Compress Spring is also little, generally under most compressed state, maximum elastic force reaches 1 newton and gets final product), can guarantee that Compress Spring compresses fully, the draw-in groove of pedestal cooperates gapless with the skid plate, then pilot is linked in (charged) control circuit board of unmanned plane, assembles complete.
2, complete release application process.Unmanned plane rolling start under the support of wheel, after liftoff, unmanned aerial vehicle control system sends the instruction of throwing wheel, receive instruction, the pilot generation current of Landing Gear System, electro spark is lighted the gunpowder in the cutter, ignite and cut off fastening rope, fastening rope breaks away from from the little perforate of sliding pin, sliding pin is at (under the potential energy effect of deposit) down sliding under the elastic force effect of Compress Spring, wheel module (i.e. the sliding wheel assembly that runs) is come off from skid, unmanned plane is carried out normal minute flight task, and the wheel module is fallen near liftoff site the place, and the vibrations that produce by falling trigger the buzzer phone on the wheel module, the ground crew searches out the wheel module according to the sound signal of buzzer phone, after unmanned plane executes task, the landing of making a return voyage, this moment, alighting gear was slide-type, the sliding-frictional resistance of rear generation of contacting to earth is stopped it fast, can guarantee that to the skid that heading extends unmanned plane can not turn upside down when ground is more coarse.
Principle of work: in unmanned plane takeoff phase, the sliding wheel module of running closely is connected with the skid plate, and unmanned plane is rolling start under the support of wheel, utilizes the little principle of coefficient of rolling friction this moment, and the realization unmanned plane accelerates rapidly the quick rolling start of short range; After rolling start was liftoff, by discharging the sliding wheel that runs under the control command of control circuit board, this moment, the unmanned plane alighting gear then changed into for slide-type, during landing, utilized the large principle of skid coefficient of sliding resistance, had realized the function of short distance brake landing.
In a word, technical matters to be solved by this invention is wheel undercarriage and slide-type alighting gear are integrated into the complex with total system by technological means, thereby realize the function of quick rolling start, short distance brake landing, can realize providing the middle-size and small-size unmanned plane Landing Gear System of a kind of quick rolling start, short distance brake landing.
It is of the present invention that not state part same as the prior art.
Claims (5)
1. a sledge, the middle-size and small-size unmanned plane Landing Gear System of wheel combined type, comprise: one is fixed in the landing gear assembly (1) that is comprised of forward and backward alighting gear hold-down arm of forebody below, be fixed in the skid plate (5) of the formation skid assembly (4) of alighting gear hold-down arm below, be installed in respectively two sliding tail-wheel assemblies (31) that run the wheel assembly and be positioned at afterbody on a pair of skid plate (5), be used for the control circuit board (30) of control landing, it is characterized in that:
A, described each sliding wheel assembly that runs that is positioned on a pair of skid plate all has one for the sliding pedestal (8) that runs wheel (6) is installed, in each pedestal, offer axle hole (9), described each sliding wheel assembly that runs all is equipped with two sliding both sides of running wheel and being installed in pedestal axle hole (9) by wheel axle (a 10) symmetry, all offer one in the top of described each pedestal (8) and can cooperate with described skid plate (5) draw-in groove with contact surface (11) of installing, draw-in groove central authorities in described each pedestal (8) top offer a hole clipping (13) that is used for settling Compress Spring (12), at the coaxial tapped bore (14) that offers of hole clipping central authorities, offer perforate as skidway hole (15) at described alighting gear hold-down arm (3) and skid plate (5) facing to tapped bore (14) direction of described pedestal draw-in groove is also coaxial;
B, described Landing Gear System also comprises a pair ofly can control each sliding automatic release control assembly (16) that can reliably be connected and can in time separate between wheel assembly and alighting gear hold-down arm and the skid plate (5) that runs, each automatic release control assembly comprises that again a upper end has little perforate (18), the bottom has externally threaded sliding pin (17), one is installed on the Compress Spring (12) between the hole clipping (13) of skid plate (5) and pedestal draw-in groove, during installation, described sliding pin (17) can be from bottom to top respectively easy fit pass in skidway hole (15) and the Compress Spring centre hole that is formed by alighting gear hold-down arm and the perforate of skid plate and the tapped bore (14) that is bolted in described pedestal draw-in groove, and after installing, the little perforate (18) of sliding pin (17) upper end is exposed outside alighting gear;
C, described each automatic release control assembly (16) also comprises: one can be passed the little perforate in described sliding pin (17) upper end (18) with the fastening rope (19) of anti-skidding pin slippage from the skidway hole (15) of described alighting gear hold-down arm and skid plate perforate composition, one cross-under also can be cut off the cutter (20) of this fastening rope on described fastening rope, this cutter leads to pilot (23) and is connected with described control circuit board (30), described cutter (20) can in time cut off fastening rope (19) under the control command of this control circuit board 30, to finish sliding automatic separation release movement of running the wheel assembly.
2. sledge according to claim 1, the middle-size and small-size unmanned plane Landing Gear System of wheel combined type, it is characterized in that, described cutter (20) is the tubular construction of making the cylinder shape, in the cutter of this cylinder shape tubular construction, be provided with successively valve piston (24) and gunpowder piece (21), light-up plug (22) is housed in described gunpowder piece, one end of described pilot (23) is connected with the two poles of the earth of light-up plug 22, the other end is connected with the described control circuit board (30) that is positioned on the fuselage (29), cylinder wall at described cutter tubular construction is provided with eyelet hole (25), described fastening rope (19) is the tubular casing wall that is horizontally through cutter through this eyelet hole, after the control system of unmanned plane receives the instruction that needs the release wheel, under the control command of the control circuit board on the fuselage, produce large current, pilot produces electro spark when getting electric light-up plug the two poles of the earth conveying high-pressures electricity in cutter gunpowder piece, electro spark is ignited the gunpowder piece, the high pressure gas that gunpowder sharply produces promote valve piston and move forward along cutter tubular casing wall, when valve piston process eyelet hole, namely cut off rapidly the fastening rope that passes in the casing wall eyelet hole, sliding pin down sliding and break away from skidway hole (15) under the elastic force effect of Compress Spring, the sliding wheel assembly that runs is come off, to finish sliding automatic separation release movement of running the wheel assembly from skid plate (5).
3. sledge according to claim 1, wheel combined type middle-size and small-size unmanned plane Landing Gear System, it is characterized in that, the sliding race of described each wheel assembly is positioned at the below of rear alighting gear hold-down arm (3), be provided with a pair of set pin (26) at described rear alighting gear hold-down arm (3), the two-end-point of described fastening rope (19) is fixed on this set pin after installing.
4. sledge according to claim 1, wheel combined type middle-size and small-size unmanned plane Landing Gear System, it is characterized in that, tapped bore (14) on the described pedestal draw-in groove is connected with the axle hole (9) of described pedestal, when described sliding pin (17) is bolted in the tapped bore of pedestal draw-in groove, can conflict on described wheel axle (10) in the bottom of this sliding pin threaded portion.
5. sledge according to claim 1, wheel combined type middle-size and small-size unmanned plane Landing Gear System, it is characterized in that, all offer a hole clipping (28) that is used for settling micro buzzer-phone (27) on described each pedestal (8), the described micro buzzer-phone that is embedded in the pedestal hole clipping (28) can be triggered by vibrations.
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| CN2012103517932A CN102963524A (en) | 2012-09-14 | 2012-09-14 | Slide-wheel composite type small and medium sized UAV landing gear system |
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| CN2012103517932A CN102963524A (en) | 2012-09-14 | 2012-09-14 | Slide-wheel composite type small and medium sized UAV landing gear system |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103419930A (en) * | 2013-08-20 | 2013-12-04 | 桂林航龙科讯电子技术有限公司 | Unmanned aerial vehicle pulley and slide converting mechanism |
| CN103791002A (en) * | 2014-03-03 | 2014-05-14 | 天津曙光敬业科技有限公司 | Brake device of unmanned aerial vehicle rotor wing |
| CN105480410A (en) * | 2015-12-15 | 2016-04-13 | 西北工业大学 | Take-off and landing device for small-sized unmanned aerial vehicle |
| CN105752321A (en) * | 2016-04-07 | 2016-07-13 | 湖北易瓦特科技股份有限公司 | Unmanned aerial vehicle landing device and unmanned aerial vehicle |
| CN107284688A (en) * | 2017-06-29 | 2017-10-24 | 飞智控（天津）科技有限公司 | Two-wheel helicopter transport wheel, conveying arrangement and transportation resources |
| CN108146617A (en) * | 2017-12-06 | 2018-06-12 | 北京卫星制造厂 | A kind of composite material plate spring formula undercarriage and preparation method thereof |
| CN108516077A (en) * | 2018-05-24 | 2018-09-11 | 南京航空航天大学 | A kind of wheel-ski integral type braking device and method |
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| CN109808911A (en) * | 2019-04-01 | 2019-05-28 | 西北工业大学 | The portable sliding race unmanned aerial vehicle of one kind lodges automatically takes turns retaining device |
| CN110758723A (en) * | 2019-12-06 | 2020-02-07 | 湖南浩天翼航空技术有限公司 | Unmanned aerial vehicle convenient to receive and release undercarriage |
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| CN103419930B (en) * | 2013-08-20 | 2015-10-28 | 桂林航龙科讯电子技术有限公司 | The switching mechanism of a kind of unmanned plane pulley skid |
| CN103419930A (en) * | 2013-08-20 | 2013-12-04 | 桂林航龙科讯电子技术有限公司 | Unmanned aerial vehicle pulley and slide converting mechanism |
| CN103791002A (en) * | 2014-03-03 | 2014-05-14 | 天津曙光敬业科技有限公司 | Brake device of unmanned aerial vehicle rotor wing |
| CN105480410A (en) * | 2015-12-15 | 2016-04-13 | 西北工业大学 | Take-off and landing device for small-sized unmanned aerial vehicle |
| CN105480410B (en) * | 2015-12-15 | 2017-05-24 | 西北工业大学 | Take-off and landing device for small-sized unmanned aerial vehicle |
| CN105752321B (en) * | 2016-04-07 | 2019-03-12 | 易瓦特科技股份公司 | Unmanned plane take-off and landing device and unmanned plane |
| CN105752321A (en) * | 2016-04-07 | 2016-07-13 | 湖北易瓦特科技股份有限公司 | Unmanned aerial vehicle landing device and unmanned aerial vehicle |
| CN107284688A (en) * | 2017-06-29 | 2017-10-24 | 飞智控（天津）科技有限公司 | Two-wheel helicopter transport wheel, conveying arrangement and transportation resources |
| CN108146617A (en) * | 2017-12-06 | 2018-06-12 | 北京卫星制造厂 | A kind of composite material plate spring formula undercarriage and preparation method thereof |
| CN108146617B (en) * | 2017-12-06 | 2020-04-10 | 北京卫星制造厂 | Composite plate spring type undercarriage and manufacturing method thereof |
| CN108516077A (en) * | 2018-05-24 | 2018-09-11 | 南京航空航天大学 | A kind of wheel-ski integral type braking device and method |
| CN108528693A (en) * | 2018-05-25 | 2018-09-14 | 张博 | Manned equipment |
| CN109808911A (en) * | 2019-04-01 | 2019-05-28 | 西北工业大学 | The portable sliding race unmanned aerial vehicle of one kind lodges automatically takes turns retaining device |
| CN110758723A (en) * | 2019-12-06 | 2020-02-07 | 湖南浩天翼航空技术有限公司 | Unmanned aerial vehicle convenient to receive and release undercarriage |
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