CN106314814A - Fixed-wing-unmanned-aerial-vehicle portable taking-off device for field scientific research and application method - Google Patents
Fixed-wing-unmanned-aerial-vehicle portable taking-off device for field scientific research and application method Download PDFInfo
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- CN106314814A CN106314814A CN201610858352.XA CN201610858352A CN106314814A CN 106314814 A CN106314814 A CN 106314814A CN 201610858352 A CN201610858352 A CN 201610858352A CN 106314814 A CN106314814 A CN 106314814A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
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Abstract
The invention discloses a fixed-wing-unmanned-aerial-vehicle portable taking-off device for field scientific research and an application method, and belongs to an unmanned-aerial-vehicle auxiliary taking-off device. The fixed-wing-unmanned-aerial-vehicle portable taking-off device is mainly formed by a part with the two ends for ground fixing and a steel wire rope part with the tensioned middle, and an external square sleeve and an internal square sleeve are a body of the part for ground fixing; the fixed-wing-unmanned-aerial-vehicle portable taking-off device also comprises sliding sleeve assemblies bonded on wings of the fixed-wing unmanned aerial vehicle; after the device is aslant fixed on the ground, an aircraft is placed on steel wire ropes arranged in sliding sleeves, the unmanned aerial vehicle and an engine are started, the unmanned aerial vehicle is rapidly accelerated under the dual effects of the gravity of the unmanned aerial vehicle and the thrust of the engine, the steel wire ropes are pulled away from the sliding sleeves while the aircraft is pulled up, and the taking-off whole process is completed through the unmanned aerial vehicle. The fixed-wing-unmanned-aerial-vehicle portable taking-off device for field scientific research and the application method have the advantages that the device is small in volume and light in weight; nearly various topographies and geological conditions are adapted; the device can be rapidly assembled and disassembled; the ground sliding travel is long, acceleration is mild, and external force is not applied; a catapulting trolley does not need to be designed, and the portable taking-off device adapts to various unmanned aerial vehicles.
Description
Technical field
The invention belongs to unmanned plane auxiliary takeoff apparatus.
Background technology
In general, the landing of fixed-wing unmanned plane is required for the smooth runway of certain length and runs for sliding, but in the wild
Under conditions of not having ideal flat place, the medium size fixed-wing unmanned plane of total launching weight about 6-30 kilogram is always a difficult problem.
The most relatively common smooth place, field is mainly highway, but highway is public transit facility, for security consideration, unmanned plane
Should not utilize road as landing site, the most current various ranks, purposes unmanned plane all with or without respective under runway conditions
Assisted Take Off method.
The full weight small-sized fixed-wing unmanned plane takeoff speed ratio less than 5 kilograms is relatively low, accelerates fast, so the most all
The simplest field operation mode taken off can be thrown, it is adaptable to various field conditions with employing personnel.But consolidating of this kind of rank
Determine wing unmanned plane mostly to carry minisize pick-up head and understand local battlefield situation for soldier, it is impossible to carrying is with specialty optics
The high resolution camera of camera lens and other senior remote sensing equipment, so the requirement of scientific research can not be fully met.
The large-scale military unmanned air vehicle weight of take-off weight 50-300 feather weight is big, inertia big, except using powerful
Outside steam ejection frame catapult-assisted take-off, the most commonly used rato, so can remove launching cradle and the high pressure of heaviness from
Energy storage equipment, whole system the most easily operates, and its shortcoming is that rocket belongs to military use product, heavily regulated as dangerous materials,
General civilian R&D institution is non-serviceable when common field study.
The fixed-wing unmanned plane of take-off weight 6-40 kilogram is more in the application of civilian scientific research field, especially 15-25 kilogram
The product consumption of rank (this programme is hereinafter referred to as " medium-sized ") is maximum, is primarily due to the unmanned wing of this level of fixed-wing
Exhibition is about 2-3.5 rice, and useful load reaches 2-5 kilogram, it is possible to carry slr camera, infrared thermoviewer, multispectral camera, air
The multiple portable information gathering equipment such as pollutant monitoring instrument, single voyage reaches 50-200 kilometer, therefore leads in scientific research
Territory has been widely used.Medium-sized fixed-wing unmanned plane carries the most more convenient, the work group of two or three people and common compact vehicle
Just can meet operation, dismounting, movement requirement.
The scientific research takeoff speed of medium-sized fixed-wing unmanned plane is typically in the range of 50-70 kilometer/hour, is typically necessary 100-
300 meters long landing sites straight, without dust and runway two ends clear are used for acceleration or deceleration, if highway can not be used,
Field is difficult to seek this type of place, can not throw again and take off, and can not use rato mode, therefore most
All use launching cradle catapult-assisted take-off mode.Launching cradle is typically made up of slide rail, shot trolley, three essential parts of power source.Sliding
Rail general length 4-8 rice, is made of metal, and is used for supporting shot trolley and slides before and after thereon；Shot trolley and slide rail it
Between rely on wheel contacts, it is ensured that dolly is little without departing from slide rail and slide anteroposterior resistance, is positioned over by unmanned plane and launches when launching
On dolly and suitably fixing after manually starting power source with guarantee, power source will apply powerful pull strength to shot trolley, bullet
Penetrating dolly and pull strength is passed to unmanned plane, both accelerate rapidly, will in the limited slide rail stroke range being usually no more than 8 meters
Unmanned plane accelerates to more than 50 kilometers/hour, and now shot trolley holds to the greatest extent stopping at slide rail, and unmanned plane has reached takeoff speed,
And self electromotor is in running order, flying thrust before continuing to provide, then unmanned plane takes off.
There is polytype in ejection power source.Military unmanned air vehicle can use compressed-air power source, its advantage be consumptive material few,
The pull strength that equipment persistently uses, provide is stable, adjustable, and shortcoming is that the existence of the parts such as cylinder, compressor pump makes whole launching
Device is heavy, is the most mostly used on medium-sized military unmanned air vehicle.Thick elastic bundle is that civilian unmanned aerial vehicle ejecting is the most the most frequently used
Power source, its advantage is relatively easy, light, but shortcoming to be pull strength first big after small non-constant in ejection process, launching
Starting stage easily pulls unmanned plane body, and follow-up acceleration capacity is the most limited, and elastic bundle uses once its pull strength the most aobvious
Write decay, need often to change.Other new power sources also include electromagnetic launch etc., also do not popularize, no longer describe in detail.
In general, pull strength huge when launching to bear, structure is indeformable and keeps stable, launching cradle whole
Weight of equipment can reach 50-100 kilogram, and yardstick is huge, dilly transport inconvenience, seriously reduces medium-sized fixed-wing unmanned
Machine is as the portable easy-to-use equipment of R&D institution of basic unit practical usefulness in the wild, and about 150 meters of long accelerators is shortened
To 4-8 rice, body transient acceleration improves about 30 times, structural strength own to unmanned plane and airborne information acquisition apparatus
Requirement is greatly improved, and such housing construction is necessary for strengthening, and its weight ratio shared by total launching weight is greatly improved, it is possible to
The Scientific Research Equipments carried is less, voyage is shorter.The strongest transient acceleration also be enough to destroy multiple airborne optical equipment.
In order to avoid using launching cradle, also have at present other fixed-wing unmanned plane to take off mode, such as, dispose at roof
Short and small unmanned plane rack, fast running on Che highway, after reaching takeoff speed, vehicle is left in unmanned plane nature pull-up,
This kind of mode seems to avoid launches and launching cradle, but it need nonetheless remain for using the such public transit facility of highway, runs counter to base
This security doctrine, so consumption is considerably less at present.Also someone have developed the fixed-wing unmanned plane with VTOL function,
Leave ground in the landing stage by rotor lift upwards vertical pull-up fuselage, be more gradually converted to level flight condition.But this
The design of a little compromises has strict restriction to the loading capacity of unmanned plane, and owing to power consumption of taking off is too many, voyage is greatly shortened.Fixing
When wing unmanned plane is exactly long voyage, long boat relative to the rotor topmost advantage of class aircraft, the design of compromise is obviously reduced
This Inherent advantage.
According to above-mentioned analysis, advantage time at present to keep scientific research medium-sized fixed-wing unmanned captain voyage, length to navigate is not
Decay, does not the most substitute more preferable field auxiliary takeoff apparatus and the method for catapult-assisted take-off frame.
Summary of the invention
The main object of the present invention is: a set of for medium-sized fixed-wing unmanned plane in the wild without Assisted Take Off under runway conditions
Device, in whole auxiliary takeoff apparatus gross weights less than 5 kilograms, the premise of storage volume dilly little, available transport
Under, it is ensured that can normally implement to take off, adapt to the most rugged most of ground such as farmland, hills, mountain region, dilute woods ground,
Natural feature on a map overlay area.The accelerating travel of taking off of this device permission breaks through the restriction of catapult-assisted take-off frame general 4-8 rice, rises and flies over
Journey acceleration compares only appropriateness with natural rolling start to be increased, and reduces the requirement to housing construction intensity, will not substantially reduce
Fixed-wing unmanned plane due voyage or loading capacity originally, in take-off process, properller keeps safe distance away from ground, flies
Camera lens on machine is also not easily susceptible to the pollution that ground dust, blade of grass etc. fly up, thus meets the common requirements of field scientific research.This dress
Put the fixed-wing unmanned plane that also should be able to be applicable to different model, various aerodynamic arrangement.
The technical scheme is that:
A kind of field scientific research portable launching apparatus of fixed-wing unmanned plane, mainly by the parts that two ends are fixing for ground
The steel wire rope part two parts being tightened up with centre are constituted, and square trocar sheath and square inner sleeve are the masters of ground component for fixing
Body, two pipes are hollow, and the length of side in square inner sleeve cross section is slightly less than the interior length of side of square trocar sheath, the most square inner sleeve
Pipe can insert or pull out in the inside of square trocar sheath, and the upper and lower side of square trocar sheath all has circular mounting hole, and hole is upper and lower
Para-position, diameter is the same, spacing is the same；Square inner sleeve also has the installing hole of aligned identical, same diameter and spacing.In two pipe phases
The hole of lap is inserted one or two fixing bolts and tightens, make between inner sleeve and trocar sheath no longer can slidably,
The underlapped end of two sleeve pipes is each fixed with a draw ring, and the termination that two draw rings are respectively arranged with a steel wire rope passes and uses steel
Cord button is fixed so that fix between steel wire rope and draw ring, the other end of two steel wire ropes equally with wire line hitch with
The hook of steel wire rope tensioning device connects, and the other end hook of two steel wire rope tensioning devices is hooked in the ground component for fixing other end
Internal and external casing on two draw rings on.
Further, also including the slide bushing assembly being bonded on fixed-wing unmanned plane wing, slide bushing assembly includes sliding sleeve, general
Sponge double faced adhesive tape that sliding sleeve and wing lower surface bond together and wedge shape obturator.
Further, sliding sleeve is to be enclosed within the elongated rod shape object outside steel wire rope, and cross section presents rhombus substantially, rhombus upper
Summit is exaggerated, and becomes wider, smooth cross section upper surface, and bonds together with sponge double faced adhesive tape, and sliding sleeve is one puts down
Straight rod-like articles, its front end slightly upwarps.
Further, the interlude bottom sliding sleeve, also on the basis of opening, continues to be cut to only remain half rhombus,
Bottom, cross section is horn-like completely open.
Further, also include multiple for secure the cannula in earth or on rock spike or expansion bolt,
A length of 30-40 centimetre of spike.
The using method of a kind of field scientific research portable launching apparatus of fixed-wing unmanned plane, takes off including above-described
Device, after ground inclination fixes device, is placed in aircraft on steel wire rope, allows two steel wire ropes all be placed in sliding sleeve
Within, unmanned plane is slided into the higher one end of steel wire rope and hand steered to keep its position by personnel afterwards, starts during standby for takeoff
Unmanned plane and electromotor, decontrol unmanned plane simultaneously, and aircraft starts slowly to glide along the gentle slope angle of steel wire rope, and take off manipulation people
Member motor power is increased to maximum, now unmanned plane self gravitation, motor power dual function under quickly accelerate,
Two set sliding sleeve two ends on a steel cord all have less downwardly open, and during anti-accelerated slip here, fuselage shaking causes
Steel wire rope is deviate from from sliding sleeve, and the operator that takes off after aircraft arrival takeoff speed draws stick to make head steeve, and is originally enclosed within
Sliding sleeve leading portion above steel wire rope is followed the fuselage steeved and is risen and depart from steel wire rope, and steel wire rope is on the downside of sliding sleeve leading portion and steel wire
Restrict wide opening abjection, now sliding sleeve back segment still overlaps on a steel cord, with ensure from sliding state to state of flight transition time
Safety, the trend further speeding up and departing from of steeving with unmanned plane subsequently, the back segment of sliding sleeve also follows rising, steel wire rope
Deviating from from sliding sleeve back segment lower opening, unmanned plane completes the overall process taken off.
Further, after wing is mounted with sliding sleeve, the fixing bolt connecting fixing internal and external casing is unclamped and extracts,
Regulation inner sleeve insertion depth in trocar sheath, makes the installing hole of two pipes still be mutually aligned and distance between two draw rings
And the distance between two sliding sleeves is closest, the middle lap at two sleeve pipes is plugged fixing bolt and fastens the most again, makes
Obtain and will not loosen between two sleeve pipes.
Advantages of the present invention and good effect: (a) device volume is little, lightweight.B () adapts to the most various landform, geology
Condition.C () can Fast Installation, dismounting.D () sliding running journey length, acceleration are eased up, are applied without external force.E () launches little without design
Car, adapts to various fixed-wing unmanned plane.
Accompanying drawing explanation
Fig. 1 is launching apparatus structural representation of the present invention.
Fig. 2 is the side view of the present invention.
Fig. 3 is launching apparatus broken away view of the present invention.
Fig. 4 is that the present invention slides over wing lower surface installation schematic side view.
Fig. 5 is that the present invention slides over wing lower surface installation elevational schematic view.
Fig. 6 is the horizontal cut-away diagram in sliding sleeve stage casing of the present invention.
Fig. 7 is sliding sleeve end of the present invention cut-away diagram.
Fig. 8 is present invention scheme of taking off schematic diagram under the Mountain Conditions such as terraced fields.
Fig. 9 is that the present invention utilizes the method fixed sleeving punching and putting into expansion bolt to show under the conditions of running into solid rock
It is intended to.
Figure 10 is that the present invention is at the level land device having the atural objects such as trees basic operational version schematic diagram.
Figure 11 is that the present invention is in the level land device having the atural objects such as trees basic operational version schematic top plan view.
In figure, 1 square trocar sheath, 2 square inner sleeves, 3 fix bolt, 4 installing holes, 5 spikes, 6 draw rings, 7 steel wire ropes, and 8
Wire line hitch, 9 steel wire rope tensioning devices, the steel wire rope of 10 redundancies, 11 wings, 12 fixed-wing unmanned planes, 13 centers of gravity of airplane and pneumatic
Center (straight wing), 14 centers of gravity of airplane and aerodynamic center position (swept back wing), 15 wedge shape obturators, 16 sliding sleeves, 17
Sponge double faced adhesive tape, 18 ailerons, 19 aerofoil profile axis.
Detailed description of the invention
Seeing accompanying drawing 1-accompanying drawing 3, takeoff auxiliary device of the present invention is mainly used for the fixing parts in ground and centre by two ends
The steel wire rope part two parts being tightened up are constituted.Square trocar sheath 1 and square inner sleeve 2 are the main bodys of ground component for fixing,
Two pipes are hollow, and the length of side (full outside dimension) in square inner sleeve 2 cross section is slightly less than the interior length of side of square trocar sheath 1, because of
This square inner sleeve 2 can insert or pull out in the inside of square trocar sheath 1, and the upper and lower side of square trocar sheath 1 all has circle
Installing hole 4, the upper and lower para-position in hole, diameter is the same, spacing is the same；Square inner sleeve 2 also has aligned identical, same diameter and spacing
Installing hole 4.In two pipes overlap hole partly, insert one or two fixing bolts 3 (include screw and the spiral shell thereof passed completely through
Female) and tighten, making no longer can be slidably between inner sleeve and trocar sheath.The underlapped end of two sleeve pipes is each fixed with one
Individual draw ring 6, two draw rings be respectively arranged with the termination of a steel wire rope 7 through and fix with the wire line hitch 8 that market is common so that steel
Fix between cord 7 and draw ring 6, it is impossible to disengage.The other end of two steel wire ropes 7 is equally with wire line hitch 8 and steel wire rope
The hook of stretcher 9 connects, and the other end hook of two steel wire rope tensioning devices is hooked in other end ground component for fixing (another
Group internal and external casing) on two draw rings 6 on.Second group of sleeve pipe and above-mentioned first group of identical (two shown in figure of sleeve pipe
Group sleeve pipe draw ring setting angle differs from 90 degree, but in fact there is no particular/special requirement, two kinds of angles).
Seeing accompanying drawing 4, accompanying drawing 5, this takeoff auxiliary device also includes the cunning being bonded on fixed-wing unmanned plane 12 wing 11
Grip assembly, slide bushing assembly includes sliding sleeve 16, by the sliding sleeve 16 sponge double faced adhesive tape 17 together with wing 11 lower surface bonds and
In order to lower surface camber line in Airfoil Sections shape (being i.e. commonly referred to as aerofoil profile) is modified to the wedge shape obturator 15 of near linear.Sliding
Set 16 is to be enclosed within the elongated rod shape object outside steel wire rope 7, and cross section presents rhombus (seeing Fig. 7) substantially, the upper summit quilt of rhombus
Amplify, become wider, smooth cross section upper surface, and bond together with sponge double faced adhesive tape 17.Sliding sleeve 16 upper surface, sponge
Double faced adhesive tape, wedge shape obturator 15 three width essentially identical.Although a sliding sleeve 16 essentially straight rod-like articles, but its
Front end slightly upwarps.Sliding sleeve 16 bottom is cut open, and A/F is identical with the diameter of steel wire rope 7.Bottom this external sliding sleeve 16
Interlude, also on the basis of opening, continues to be cut to only remain half rhombus (seeing Fig. 6), and bottom, cross section is horn-like complete
Open.
This takeoff auxiliary device also includes the steel wire rope 7 of other accessories, such as sufficient length and sufficient amount of steel wire rope
Button 8, and include multiple spike 5, multiple common expansion bolt.Spike 5 is used for securing the cannula in earth, and therefore length can
Reach 30-40 centimetre；Expansion bolt is common model, is only used for stony ground table, can secure the cannula to (see accompanying drawing on rock
1, accompanying drawing 10, accompanying drawing 11).
Implementation process:
Have high intensity inside fixed-wing unmanned plane wing, the composite crossbeam of major diameter runs through so that wing this
The main modular construction intensity providing flight lift is sufficiently large, can bear and be several times as much as flying when running into air-flow or during take-off climb
The air pressure of machine own wt is without bending, and this programme is namely based on this feature, by suitable position, surface under the wings of an airplane
Put installation sliding sleeve, make aircraft can pass through wing 11, slide over and slide on two steel wire ropes 7 and take off.Therefore take off in enforcement
Before, need user first according to oneself span of fixed-wing unmanned plane wing, construction features, select on two wings spacing relatively
The lower surface of remote symmetric position, as optimal installation site, is respectively mounted a sliding sleeve, between this programme is to two sliding sleeves
Distance there is no strict demand, be not at wing tip, do not affect the installation of the airfoil members such as steering wheel, control action is advisable.Typically
For aircraft is the biggest, the span is the widest, take-off distance is the longest, then the installing space of two sliding sleeves is the biggest.
Slide over the bonding another one principle of wing lower surface to be intended to keep sliding sleeve and air-foil axis 19 (i.e. machine
Nose of wing First Point and the line of trailing edge rearmost point, also it is wing chord) substantially parallel, therefore choosing wing installation site
Afterwards, typically will be first at latter half (near trailing edge) the first bonding wedge shape obturator 15 of aerofoil profile lower surface so that former
This be the lower surface of arc close to straight line, then with sponge double faced adhesive tape, sliding sleeve is bonded together with wing lower surface, sponge is two-sided
The plasticity of glue can fill up the space that between two bonding planes, slight injustice causes.The centre of lift of wing is typically on wing
Near the peak on surface, the most substantially before the whole chord length of wing at 1/3rd near (close to shown in 13
Point), that the center of gravity of aircraft is substantially aligned with centre of lift when plant design and production aircraft.Based on this principle,
When bonding sliding sleeve is to wing lower surface, the center of sliding sleeve more to lean on into the leading edge of a wing some because sliding sleeve should not enter machine
In the stroke up and down of wing trailing edge flap 18, cause the action hindering aileron, and wing should be stretched out in the front end of sliding sleeve in general
Leading edge, so makes center of gravity still be located substantially at the middle position of sliding sleeve, and aircraft is put pitching on a steel cord and still kept stable, will not
It is rotated at random.Above-mentioned " center of gravity be normally at wing chord before 1/3rd at " be for straight wing for, wing is had slightly
The fixed-wing unmanned plane of sweepback, as long as being not at wing root position, center of gravity may be closer to leading edge than aforesaid 1/3rd positions
The center of gravity of airplane and aerodynamic center position (swept back wing) 14, therefore sliding sleeve front end is some more by stretching out accordingly.
The spacing of aforementioned two sliding sleeves should select " moderate " position in spanwise, be also based on this kind consider and in sweepback
Wing tip should not be got too close to when installing on wing.In addition the medium-sized scientific research general wing of fixed-wing unmanned plane of 10-25 feather weight
Between chord length is 25-35 centimetre, therefore sliding sleeve length is also essentially 35-40 cm.
Owing to wedge shape obturator 15, sponge double faced adhesive tape, sliding sleeve have had certain altitude, thus steel wire rope 7 and aileron 18 it
Between have a certain distance, and the action that not makes a stunt flying when sliding and taking off, the stroke of aileron 18 is little, and steel wire rope 7 will not
Action to aileron 18 produces obstruction.
After wing is mounted with sliding sleeve, the distance between two sliding sleeves determines that, will connect, fix inside and outside sleeve pipe
Fixing bolt unclamp and extract, regulate the square inner sleeve 2 insertion depth in square trocar sheath 1, make the installing hole 4 of two pipes
Still it is mutually aligned and distance between distance and two sliding sleeves between two draw rings 6 is closest, the most again at two sleeve pipes
Middle lap is plugged fixing bolt 3 and fastens so that will not loosen between two sleeve pipes.Adjust according to identical way
The spacing of draw ring on the steel wire rope other end two sleeve pipe.Select suitable position solid afterwards in the landform in rugged fluctuating or mountain region
Fixed two groups of sleeve pipes.Because if this programme utilizes unmanned plane self gravitation so that its on a steel cord slide acceleration faster,
So this programme can use in mountain region completely, as a example by the hillside of the terrace shaped common by China or non-terrace shaped (Fig. 8), permissible
Meet unmanned with spike 5 through sleeve pipe, the suitable location that two groups of sleeve pipes are both secured on hillside, the distance between two groups of sleeve pipes
Machine takes off required coasting distance.Steel wire rope 7 total length connecting two groups of sleeve pipes is probably very long, can be by pine
Open wire line hitch 8 and regulate the length of actual connection ran, to adapt to the spacing after fixing two groups of sleeve pipes at present, the most again
Tighten wire line hitch 8.Now the rate of tension of steel wire rope 7 is inadequate certainly, in addition it is also necessary to rotating wire rope stretcher 9 is further
Tense wire rope 7, is allowed to be not easy vibration and can bear the weight of unmanned plane.
Mountain region at many stones, it is difficult to find under the soil regime that can be inserted into spike, can beat little with electric hand drill on megalith
Small-sized expansion bolt is also put in hole, equally substitutes spike and fixes sleeve pipe (Fig. 9).The area more in forest land, also may be used
So that the steel wire rope 7 of one group of effective redundancy of set is passed and to be fixed on trunk with same wire line hitch 8, the sleeve pipe of the other end can
To be fixed on (accompanying drawing 10, accompanying drawing 11) on the low bank of earth between fields.No matter which kind of fixed form, that peace near draw ring 6 all should be utilized
Dress hole 4 is through spike 5, expansion bolt or trunk binding steel wire rope 7, and the pulling force of such steel wire rope 7 can be directly passed to ground
Thing, moment of torsion is smaller, the most pliable deformation of sleeve pipe.
After ground fixes device, aircraft is placed on steel wire rope 7, two steel wire ropes 7 will be allowed all to be placed in
Within sliding sleeve, unmanned plane is slided into the higher one end of steel wire rope 7 and hand steered to keep its position, during standby for takeoff by personnel afterwards
Starting unmanned plane and electromotor, decontrol unmanned plane simultaneously, aircraft starts slowly to glide along the gentle slope angle of steel wire rope 7, takes off
Motor power is increased to maximum by operator, now unmanned plane self gravitation, motor power dual function under very
Fast acceleration.Two set sliding sleeve 16 two ends on a steel cord all have less downwardly open, machine during anti-accelerated slip here
Body vibration causes steel wire rope to be deviate from from sliding sleeve 16.The operator that takes off after aircraft arrival takeoff speed draws stick (elevator)
Make head steeve, be originally enclosed within sliding sleeve 16 leading portion above steel wire rope and follow the fuselage rising steeved and depart from steel wire rope, steel wire
The opening abjection restricting wide with steel wire rope on the downside of sliding sleeve 16 leading portion, now sliding sleeve 16 back segment still overlaps on a steel cord, to ensure
From sliding state to safety during state of flight transition.Steeve with unmanned plane subsequently the trend further speeding up and departing from,
The back segment of sliding sleeve 16 also follows rising, and steel wire rope is deviate from from sliding sleeve 16 back segment lower opening, and unmanned plane completes the full mistake taken off
Journey.
When regaining takeoff auxiliary device, it is also possible to extract the fixing bolt in the middle of two sleeve pipes, inner sleeve is stretched as far as possible
Enter in trocar sheath, more fixing bolt of screwing on, so can further shortening device transport time length.
Utilize the hillside fields in natural environment or the discrepancy in elevation, can make to slide acceleration higher, shorten the length of steel wire rope and right
The requirement in place, exactly because this point so that the running length needed for this programme is less than the required landing airdrome length that normally takes off.
The installation gradient allowed band of steel wire rope is the widest, but is typically in the range of between 15-35 degree, can select voluntarily according to site condition.
The front end of sliding sleeve 16 upwarps after being because unmanned plane to be placed on the steel wire rope of tensioning slightly, and steel wire rope has slightly
Micro-tenesmus, the front end slightly upwarped just meets this rule so that the resistance during high speed slide is less, sliding sleeve 16 stage casing
The latter half be cut off also for alleviate further weight, reduce frictional force, and make people be easier to see from below
Steel wire rope in sliding sleeve, be additionally easy to personnel smear in sliding sleeve grease with further reduce friction and extend making of sliding sleeve
Use the life-span.Sliding sleeve 16 protects wing 11 and is not worn and torn by steel wire rope 7, but himself belongs to loss product, takes off and wore and tore the most afterwards
Can change in serious sliding sleeve 16.
The fixed-wing unmanned plane wing of scientific research is simple, not leading edge slat as airline carriers of passengers, so sliding sleeve 16
Can be more prominent than the leading edge of a wing.
The following that this programme meets simultaneously requires:
A () device volume is little, lightweight.Owing to using the seizing wire of tensioning to instead of big and heavy metal launching cradle, and
And it being no longer necessary to the power source needed for shot trolley and the anxious acceleration of short distance, the weight of this device is extremely light, is usually no more than 5 kilograms.
Another because of the medium-sized fixed-wing unmanned aerial vehicle design mainly for span 2-3.5 rice, the sleeve pipe that therefore internal and external casing is waited in use is total
Length typically need not be more than 2 meters, and storage size is typically not over 1.2 meters, and therefore dilly just can transport.
B () adapts to the most various landform, geological conditions.The difficulty using fixed-wing unmanned plane in rugged mountain region is the highest, i.e.
Making to carry traditional catapult-assisted take-off frame, its shortcoming that is excessively heavy and that need smooth ground to lay also limit and moves in mountain region
With the convenience used, equipment in this programme is the lightest to be easy to carry about with one, and changing drawback is advantage, utilizes topographical elevation difference to make
Obtain unmanned plane because shortening coasting distance by means of self gravitation, it is no longer necessary to extra ejection power source, mountain region operates more in the wild
Convenient.Select former and later two positions slightly highlighted to fix two groups of sleeve pipes, allow for a little higher than ground of steel wire rope, thus avoid former
Carry out the various parts that the sand and dust that time taking off in ground, screw current is rolled destroy, pollute on aircraft.
Fixed-wing unmanned plane has had the aerial parachute-opening landing technology of maturation at present, can drop in rugged topography or mountain region
Fall, it is not necessary to runway.This programme solves mountain region and takes off after a difficult problem, it is possible to achieve convenient under full orographic condition of medium-sized unmanned plane
Operation, the beneficially enforcement of field scientific research.
C () can Fast Installation, dismounting.Only need to fix two groups of sleeve pipes in ground other prominent terrain features such as (or on) trunks,
And two steel wire ropes of rotating wire rope stretcher tensioning just complete the laying of takeoff auxiliary device, then aircraft is put by sliding sleeve
That one end being placed in steel wire rope higher just completes preparation of taking off, so operating extremely simple.
D () sliding running journey length, acceleration are eased up, are applied without external force.Rope capacity in this programme can according to terrain slope,
Unmanned plane weight, power arbitrarily adjust, and are more than 20-30 rice, compare with the launching cradle of only 4-8 rice, and unmanned plane can be used
Longer in the stroke slided, acceleration is less, especially with self gravitation, it is to avoid the strong external force of moment is applied on fuselage,
Airframe structure weight can be greatly reduced, and not only contributes to increase voyage, and the most also makes the wing of unit are carry
Lotus is less, and takeoff speed is low, and the required coasting distance that takes off shortens further.
E (), without designing shot trolley, adapts to various fixed-wing unmanned plane.General shot trolley is all to be connected with fuselage
Connect, promote fuselage together to eject at a high speed with dolly when launching forward, and the unmanned aerial vehicle body size of different model, shape are all not
With, and the when of performing different task, ventral is possibly also with different information collecting devices, in strength ejection process
Easily broken, so shot trolley changes with the ventral equipment carried, task scheme specially according to the model of aircraft always
Making, if thinking, use different unmanned planes instead carries out launching being nearly impossible temporarily.Steel wire rope spacing in this programme is adjustable, energy
Adapt to the unmanned plane that varies in size, and avoid the information gathering equipment of ventral completely, also avoid the electromotor of head or tail
Empennage, it is to avoid aircraft and various potential collisions between auxiliary equipment of taking off, so this device is applicable to 6-30 in sum
Kilogram different model, fixed-wing unmanned plane that acceleration is different, though will in same task before and after take off different unmanned
Machine, the most only needs to readjust the degree of overlapping of internal and external casing, namely the spacing of two steel wire ropes of adjustment, very convenient.
Claims (9)
1. the field scientific research portable launching apparatus of fixed-wing unmanned plane, it is characterised in that: mainly by two ends for ground
Fixing parts and middle steel wire rope part two parts being tightened up are constituted, and square trocar sheath (1) and square inner sleeve (2) are ground
The main body of face component for fixing, two pipes are hollow, and the length of side in square inner sleeve (2) cross section is slightly less than square trocar sheath
(1) the interior length of side, the most square inner sleeve (2) can insert or pull out in the inside of square trocar sheath (1), square trocar sheath
(1) upper and lower side all has circular mounting hole (4), and the upper and lower para-position in hole, diameter is the same, spacing is the same；Square inner sleeve (2) also has
The installing hole (4) of aligned identical, same diameter and spacing, inserts one or two fixing bolts in two pipes overlap hole partly
(3) and tighten, making between inner sleeve and trocar sheath no longer can slidably, and the underlapped end of two sleeve pipes is each fixed with one
Individual draw ring (6), the termination that two draw rings (6) are respectively arranged with a steel wire rope (7) passes and uses wire line hitch (8) to fix so that steel
Fixing between cord (7) and draw ring (6), the other end of two steel wire ropes (7) is opened with steel wire rope with wire line hitch (8) equally
The hook of tight device (9) connects, and the other end hook of two steel wire rope tensioning devices (9) is hooked in the ground component for fixing other end
On two draw rings (6) on internal and external casing.
The scientific research portable launching apparatus of fixed-wing unmanned plane in field the most according to claim 1, it is characterised in that: also wrap
Including the slide bushing assembly being bonded on fixed-wing unmanned plane (12) wing (11), slide bushing assembly includes sliding sleeve (16), by sliding sleeve (16)
Sponge double faced adhesive tape (17) together with wing (11) lower surface bonds and wedge shape obturator (15).
The scientific research portable launching apparatus of fixed-wing unmanned plane in field the most according to claim 2, it is characterised in that: sliding sleeve
(16) being the elongated rod shape object being enclosed within steel wire rope (7) outside, cross section presents rhombus substantially, and the upper summit of rhombus is exaggerated, and becomes
For wider, smooth cross section upper surface, and bonding together with sponge double faced adhesive tape (17), sliding sleeve (16) is a straight bar
Shape object, its front end slightly upwarps.
The scientific research portable launching apparatus of fixed-wing unmanned plane in field the most according to claim 2, it is characterised in that: sliding sleeve
(16) interlude of bottom is also on the basis of opening, continues to be cut to only remain half rhombus, and bottom, cross section is horn-like
Completely open.
The scientific research portable launching apparatus of fixed-wing unmanned plane in field the most according to claim 1, it is characterised in that: also wrap
Include multiple for secure the cannula in earth or on rock spike (5) or expansion bolt, a length of 30-40 li of spike
Rice.
6. a using method for the portable launching apparatus of field scientific research fixed-wing unmanned plane, including described in claim 1
Launching apparatus, it is characterised in that: after ground inclination fixes device, aircraft is placed on steel wire rope, allows two steel
Within cord is all placed in sliding sleeve (16), unmanned plane is slided into higher one end of steel wire rope hand steered to keep it by personnel afterwards
Position, starts unmanned plane and electromotor, decontrols unmanned plane simultaneously during standby for takeoff, aircraft starts the gentle slope angle along steel wire rope
Slowly glide, motor power is increased to maximum by the operator that takes off, and now unmanned plane is at self gravitation, motor power
Quickly accelerating under dual function, sliding sleeve (16) two ends that two are enclosed within steel wire rope (7) all have less downwardly open, anti-here
During accelerated slip, fuselage shaking causes steel wire rope (7) to be deviate from from sliding sleeve (16), and take off after aircraft arrival takeoff speed behaviour
Vertical personnel draw stick to make head steeve, and are originally enclosed within steel wire rope (7) sliding sleeve (16) leading portion above and follow on the fuselage steeved
Rise and depart from steel wire rope, the opening abjection that steel wire rope (7) is wide with steel wire rope on the downside of sliding sleeve (16) leading portion, now sliding sleeve (16)
Back segment is still enclosed within steel wire rope (7), to ensure from sliding state to safety during state of flight transition, subsequently with unmanned plane
Steeving the trend further speeding up and departing from, the back segment of sliding sleeve also follows rising, and steel wire rope (7) is opened below sliding sleeve (16) back segment
Deviating from Kou, unmanned plane completes the overall process taken off.
The using method of the scientific research portable launching apparatus of fixed-wing unmanned plane in field the most according to claim 6, it is special
Levy and be: after wing is mounted with sliding sleeve (16), the fixing bolt (3) connecting fixing internal and external casing is unclamped and extracts, adjusts
Joint inner sleeve insertion depth in trocar sheath, make the installing hole of two pipes still be mutually aligned and distance between two draw rings with
Distance between two sliding sleeves (16) is closest, and the middle lap at two sleeve pipes is plugged fixing bolt (3) tight the most again
Gu so that will not loosen between two sleeve pipes.
The using method of the scientific research portable launching apparatus of fixed-wing unmanned plane in field the most according to claim 6, it is special
Levy and be: the installation range of grade of steel wire rope (7) is between 15-35 degree.
9. according to the user of the field scientific research portable launching apparatus of fixed-wing unmanned plane described in any one of claim 6-8
Method, it is characterised in that: for terraced fields, hillside, take off many tors.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107600447A (en) * | 2017-09-26 | 2018-01-19 | 甘肃省测绘工程院 | Air-mapping aircraft launching apparatus |
| CN109353492A (en) * | 2018-09-28 | 2019-02-19 | 李模萍 | A kind of method of rising and falling of vehicle orientation rate controlling V-arrangement sliding slot |
| CN110576970A (en) * | 2018-06-09 | 2019-12-17 | 天津大学（青岛）海洋工程研究院有限公司 | Hydrofoil and air bag combined type water surface lifting device |
| CN113018881A (en) * | 2021-04-25 | 2021-06-25 | 航天创客（北京）科技有限公司 | Aerospace science popularization model self-adaptive ejection device |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3622073A (en) * | 1968-11-18 | 1971-11-23 | Rfdgq Ltd | Means for moving heavy loads |
| US4909458A (en) * | 1987-12-10 | 1990-03-20 | Schweizerische Eidgenossenschaft vertreten durch das Eidgenossische Flugzeugwerk | Device for the acceleration of bodies, especially a mobile catapult for flying bodies |
| US6851647B1 (en) * | 2003-04-03 | 2005-02-08 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Portable catapult launcher for small aircraft |
| WO2005016753A2 (en) * | 2003-04-01 | 2005-02-24 | The Insitu Group, Inc. | Methods and apparatuses for launching airborne devices along flexible elongated members |
| US7059564B2 (en) * | 2003-01-17 | 2006-06-13 | The Insitu Group, Inc. | Methods and apparatuses for capturing and recovering unmanned aircraft, including a cleat for capturing aircraft on a line |
| CN101229850A (en) * | 2007-08-21 | 2008-07-30 | 黄金伦 | Medium-sized shipboard transmitter field |
| KR100954276B1 (en) * | 2009-05-19 | 2010-04-23 | 한국항공우주산업 주식회사 | Impact absorbing device for launching apparatus of unmanned aircraft |
| RU2432303C1 (en) * | 2010-03-09 | 2011-10-27 | Александр Афанасьевич Нарижный | Method of launching spaceships by reusable system and system for multiple launching of spaceships |
| KR20120001819A (en) * | 2010-03-02 | 2012-01-05 | 곽종현 | Take off and landing helper system for the airplane and rocket |
| PL218035B1 (en) * | 2011-12-27 | 2014-09-30 | Politechnika Białostocka | Launcher for small aircrafts |
-
2016
- 2016-09-28 CN CN201610858352.XA patent/CN106314814B/en not_active Expired - Fee Related
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3622073A (en) * | 1968-11-18 | 1971-11-23 | Rfdgq Ltd | Means for moving heavy loads |
| US4909458A (en) * | 1987-12-10 | 1990-03-20 | Schweizerische Eidgenossenschaft vertreten durch das Eidgenossische Flugzeugwerk | Device for the acceleration of bodies, especially a mobile catapult for flying bodies |
| US7059564B2 (en) * | 2003-01-17 | 2006-06-13 | The Insitu Group, Inc. | Methods and apparatuses for capturing and recovering unmanned aircraft, including a cleat for capturing aircraft on a line |
| WO2005016753A2 (en) * | 2003-04-01 | 2005-02-24 | The Insitu Group, Inc. | Methods and apparatuses for launching airborne devices along flexible elongated members |
| US6851647B1 (en) * | 2003-04-03 | 2005-02-08 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Portable catapult launcher for small aircraft |
| CN101229850A (en) * | 2007-08-21 | 2008-07-30 | 黄金伦 | Medium-sized shipboard transmitter field |
| KR100954276B1 (en) * | 2009-05-19 | 2010-04-23 | 한국항공우주산업 주식회사 | Impact absorbing device for launching apparatus of unmanned aircraft |
| KR20120001819A (en) * | 2010-03-02 | 2012-01-05 | 곽종현 | Take off and landing helper system for the airplane and rocket |
| RU2432303C1 (en) * | 2010-03-09 | 2011-10-27 | Александр Афанасьевич Нарижный | Method of launching spaceships by reusable system and system for multiple launching of spaceships |
| PL218035B1 (en) * | 2011-12-27 | 2014-09-30 | Politechnika Białostocka | Launcher for small aircrafts |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107600447A (en) * | 2017-09-26 | 2018-01-19 | 甘肃省测绘工程院 | Air-mapping aircraft launching apparatus |
| CN110576970A (en) * | 2018-06-09 | 2019-12-17 | 天津大学（青岛）海洋工程研究院有限公司 | Hydrofoil and air bag combined type water surface lifting device |
| CN109353492A (en) * | 2018-09-28 | 2019-02-19 | 李模萍 | A kind of method of rising and falling of vehicle orientation rate controlling V-arrangement sliding slot |
| CN109353492B (en) * | 2018-09-28 | 2022-02-08 | 李模萍 | Landing and landing method for directional speed control V-shaped sliding groove of aircraft |
| CN113018881A (en) * | 2021-04-25 | 2021-06-25 | 航天创客（北京）科技有限公司 | Aerospace science popularization model self-adaptive ejection device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106314814B (en) | 2018-12-18 |
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