CN106314814B - A kind of field the scientific research portable launching apparatus of fixed-wing unmanned plane and application method - Google Patents
A kind of field the scientific research portable launching apparatus of fixed-wing unmanned plane and application method Download PDFInfo
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- CN106314814B CN106314814B CN201610858352.XA CN201610858352A CN106314814B CN 106314814 B CN106314814 B CN 106314814B CN 201610858352 A CN201610858352 A CN 201610858352A CN 106314814 B CN106314814 B CN 106314814B
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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
A kind of field the scientific research portable launching apparatus of fixed-wing unmanned plane and application method, belong to unmanned plane auxiliary takeoff apparatus.Mainly it is made of the both ends component fixed for ground and intermediate steel wire rope part two parts being tightened up, rectangular outer tube and rectangular inner sleeve are the main bodys of ground component for fixing, it further include the slide bushing assembly being bonded on fixed-wing unmanned plane wing, after ground inclination fixes device, aircraft is placed in and is placed on the wirerope within sliding sleeve, start unmanned plane and engine, unmanned plane self gravity, motor power double action under accelerate quickly, wirerope is deviate from from sliding sleeve while aircraft pull-up, and unmanned plane completes the overall process taken off.Its advantage and good effect: device volume is small, light-weight；Adapt to almost various landform, geological conditions；It can Fast Installation, disassembly；Sliding running journey is long, it is gentle to accelerate, applies without external force；Without designing shot trolley, various fixed-wing unmanned planes are adapted to.
Description
Technical field
The invention belongs to unmanned plane auxiliary takeoff apparatus.
Background technique
In general, the flat runway that the landing of fixed-wing unmanned plane requires certain length is run for sliding, but in field
Under conditions of not having ideal flat place, about 6-30 kilograms of total launching weight of medium size fixed-wing unmanned plane is always problem.
The general relatively common flat place in field is mainly highway, but highway is public transit facility, due to safety concerns, unmanned plane
Landing site should not be utilized road as, therefore all whether there is or not respective under runway conditions for the unmanned plane of current various ranks, purposes
Assisted Take Off method.
Full weight is relatively low no more than 5 kilograms of small-sized fixed-wing unmanned plane takeoff speed, accelerates fastly, so in general all
The most simple field operation mode taken off can be thrown using personnel, be suitable for various field conditions.But such rank is consolidated
Miniature webcam can only be carried for the local battlefield situation of soldier's understanding by determining wing unmanned plane mostly, can not be carried with specialty optics
The high resolution camera of camera lens and other advanced remote sensing equipment, so the requirement of scientific research cannot be fully met.
The large-scale military unmanned air vehicle weight of take-off weight 50-300 feather weight is big, inertia is big, in addition to using powerful
Except steam ejection frame catapult-assisted take-off, rato is also commonly used, bulky launching cradle and high pressure can be removed from this way
Energy storage equipment, whole system is succinctly easy to operate, the disadvantage is that rocket belongs to military use product, heavily regulated as dangerous material,
General civilian R&D institution is non-serviceable in common field study.
6-40 kilograms of take-off weight of fixed-wing unmanned plane in civilian scientific research field using more, especially 15-25 kilograms
The product dosage 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
About 2-3.5 meters of exhibition, useful load reaches 2-5 kilograms, can carry slr camera, infrared thermoviewer, multispectral camera, air
A variety of portable information collection equipment such as pollutant monitoring instrument, single voyage reaches 50-200 kilometers, therefore leads in scientific research
Domain has been widely used.Medium-sized fixed-wing unmanned plane carries also more convenient, the work group of two or three people and common compact vehicle
Operation, disassembly, transport requirement can be met.
Scientific research is typically in the range of 50-70 kilometers/hour with the takeoff speed of medium-sized fixed-wing unmanned plane, is typically necessary 100-
300 meters long straight landing site without dust and runway both ends clear is used for acceleration or deceleration, if highway cannot be used,
Field is difficult to seek such place, and can not throw and take off, and can not use rato mode, therefore most
All use launching cradle catapult-assisted take-off mode.Launching cradle is generally made of three sliding rail, shot trolley, power source essential parts.It is sliding
It general length 4-8 meters of rail, is made of metal, is used to support shot trolley sliding back and forth on it；Shot trolley and sliding rail it
Between rely on wheel contacts, guarantee trolley without departing from sliding rail and to slide back and forth resistance small, unmanned plane is placed in ejection when ejection
On trolley and suitably fixed to guarantee after manually starting power source, power source will apply powerful tractive force to shot trolley, bullet
It penetrates trolley and tractive force is passed into unmanned plane, the two accelerates rapidly, will in the limited sliding rail stroke range for being usually no more than 8 meters
Unmanned plane accelerates to 50 kilometers/hour or more, and shot trolley holds to the greatest extent stopping in sliding rail at this time, and unmanned plane has reached takeoff speed,
And itself engine is in running order, continues winged thrust before providing, then unmanned plane takes off.
There are many types in ejection power source.Military unmanned air vehicle can use compressed-air power source, its advantage is that consumptive material it is few,
The tractive force that equipment persistently uses, provides is stable, adjustable, the disadvantage is that the presence of the components such as cylinder, compression pump entirely to launch
Device is heavy, therefore mostly on medium-sized military unmanned air vehicle.Thick elastic beam is that civilian unmanned aerial vehicle ejecting is generally most common
Power source is launching its advantage is that relatively easy, light, but the disadvantage is that tractive force is first big after small non-constant in ejection process
Initial stage is easy to pull unmanned plane body, and subsequent acceleration capacity is again limited, and elastic beam is just shown using its primary tractive force
Decaying is write, needs to replace often.Other new power sources further include electromagnetic launch etc., do not popularize also, are no longer described in detail.
Huge tractive force when in general, in order to bear ejection, structure is indeformable and keeps stable, the whole of launching cradle
Weight of equipment can reach 50-100 kilograms, and scale is huge, and small vehicle transport is inconvenient, seriously reduce medium-sized fixed-wing nobody
Practical efficiency of the machine as the portable easy-to-use equipment of R&D institution of base in field, and about 150 meters of long accelerators are shortened
To 4-8 meters, body transient acceleration improves about 30 times, to unmanned plane structural strength itself and airborne information acquisition apparatus
It is required that greatly improving, such housing construction must just be reinforced, and weight ratio shared in total launching weight greatly improves, can
The Scientific Research Equipments of carrying are less, voyage is shorter.So strong transient acceleration is also enough to destroy a variety of airborne optical equipment.
In order to avoid using launching cradle, take off mode there are also other fixed-wing unmanned planes at present, such as disposed in 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,
Such mode, which seems, avoids ejection and launching cradle, but it still needs using public transit facility as highway, violates base
This security doctrine, so dosage is considerably less at present.Also someone has developed the fixed-wing unmanned plane with VTOL function,
Ground is left by the upward vertical pull-up fuselage of lift of rotor in the landing stage, then is gradually converted to level flight condition.But this
The design compromised a bit has stringent limitation to the loading capacity of unmanned plane, and consumes energy too much due to taking off, and voyage greatly shortens.It is fixed
Wing unmanned plane is exactly long voyage, long endurance relative to the most important advantage of rotor class aircraft, and the design of compromise is obviously reduced
This Inherent advantage.
According to above-mentioned analysis, at present to keep scientific research with the advantages of the unmanned captain's voyage of medium-sized fixed-wing, long endurance not
Decaying, there are no the better field auxiliary takeoff apparatus and method of substitution catapult-assisted take-off frame.
Summary of the invention
The main object of the present invention is: a set of to be used for medium-sized fixed-wing unmanned plane in field without Assisted Take Off under runway conditions
Device, whole auxiliary takeoff apparatus total weights be no more than 5 kilograms, storage it is small in size, can use small vehicle transport premise
Under, guarantee can normally be implemented to take off, adapt to farmland, hills, mountainous region, dilute woods etc. most of naturally rugged ground,
Natural feature on a map overlay area.The accelerating travel of taking off of device permission breaks through general 4-8 meters of the limitation of catapult-assisted take-off frame, rises and flies over
It is only that appropriateness increases that journey acceleration is compared with takeoff naturally, reduces the requirement to housing construction intensity, will not obviously reduce
Fixed-wing unmanned plane due voyage or loading capacity originally, properller keeps safe distance away from ground in take-off process, flies
Camera lens on machine is also not easily susceptible to the pollution that ground dust, blade of grass etc. fly up, to meet the common requirements of field scientific research.The dress
Set the fixed-wing unmanned plane that should be able to be also suitable for different model, various aerodynamic arrangements.
The technical scheme is that:
A kind of field scientific research portable launching apparatus of fixed-wing unmanned plane is mainly used for the fixed component in ground by both ends
The steel wire rope part two parts composition being tightened up with centre, rectangular outer tube and rectangular inner sleeve are the masters of ground component for fixing
Body, two pipes be it is hollow, the side length of rectangular inner sleeve tube section is slightly less than the interior side length of rectangular outer tube, therefore rectangular inner sleeve
Pipe can be inserted or pull out in the inside of rectangular outer tube, and the upper and lower side of rectangular outer tube has a circular mounting hole, above and below hole
Contraposition, diameter is the same, spacing is the same；Rectangular inner sleeve also has the mounting hole of aligned identical, same diameter and spacing.In two pipe phases
It is inserted into one or two fixing bolts in the hole of lap and tightens, making no longer can be free to slide between inner sleeve and outer tube,
The underlapped end of two casings is respectively fixed with a pull ring, and two pull rings respectively have the end of a wirerope to pass through and use steel
Cord button is fixed so that fixed between wirerope and pull ring, the other end of two wirerope equally use 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 pull rings on.
It further, further include the slide bushing assembly being bonded on fixed-wing unmanned plane wing, slide bushing assembly includes sliding sleeve, incites somebody to action
The sponge double-sided adhesive and wedge-shaped obturator that sliding sleeve and wing lower surface bond together.
Further, sliding sleeve is the elongated rod shape object covered outside wirerope, and cross section is presented diamond shape substantially, diamond shape it is upper
Vertex is amplified, and becomes wider, smooth cross section upper surface, and bond together with sponge double-sided adhesive, and sliding sleeve is one flat
Straight rod-like articles, front end slightly upwarp.
Further, the interlude of sliding sleeve bottom continues to be cut to only remaining upper half of diamond shape also on the basis of opening,
Section lower part is in horn-like completely open.
It further, further include multiple spikes or expansion bolt for securing the cannula in soil or on rock,
Spike length is 30-40 centimetres.
A kind of application method of the field scientific research portable launching apparatus of fixed-wing unmanned plane, including above-described take off
Aircraft is placed on wirerope by device after ground inclination fixes device, and two wirerope is allowed all to be placed in sliding sleeve
Within, unmanned plane is slided into the higher one end of wirerope and hand steered to keep its position by personnel later, and when standby for takeoff starts
Unmanned plane and engine, while unmanned plane is decontroled, aircraft starts slowly to glide along the gentle slope angle of wirerope, takes off and manipulates people
Motor power is increased to maximum by member, at this time unmanned plane self gravity, motor power double action under accelerate quickly,
Two set sliding sleeve both ends on a steel cord have lesser downwardly open, and fuselage shaking causes during anti-accelerated slip here
Wirerope is deviate from from sliding sleeve, and the operator that takes off after aircraft arrival takeoff speed draws control stick that head is made to steeve, and covers originally
Sliding sleeve leading portion above wirerope follows the fuselage steeved to rise and be detached from wirerope, and wirerope is on the downside of sliding sleeve leading portion and steel wire
The opening abjection for restricting wide, sliding sleeve back segment still covers on a steel cord at this time, to guarantee from sliding state to when state of flight transition
Safety, then steeve the trend for further speeding up and being detached from unmanned plane, the back segment of sliding sleeve also follows rising, wirerope
Deviate 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 for being connected and fixed internal and external casing is unclamped and is extracted,
Insertion depth of the inner sleeve in outer tube is adjusted, is mutually aligned the mounting hole of two pipes still and the distance between two pull rings
The distance between two sliding sleeves are closest, are plugged fixing bolt in the intermediate lap of two casings again at this time and fasten, make
Obtaining will not loosen between two casings.
The advantages and positive effects of the present invention: (a) device volume is small, light-weight.(b) almost various landform, geology are adapted to
Condition.It (c) can Fast Installation, disassembly.(d) sliding running journey is long, it is gentle to accelerate, applies without external force.(e) small without designing ejection
Vehicle adapts to various fixed-wing unmanned planes.
Detailed description of the invention
Fig. 1 is launching apparatus structural schematic diagram of the present invention.
Fig. 2 is side view of the 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 middle section of the present invention.
Fig. 7 is sliding sleeve end of the present invention cut-away diagram.
Fig. 8 is take off scheme schematic diagram of the present invention under the Mountain Conditions such as terraced fields.
Fig. 9 is that the present invention is shown under the conditions of encountering solid rock using punching and be put into the method fixed sleeving of expansion bolt
It is intended to.
Figure 10 is the present invention in the basic operational version schematic diagram of level land device for having the atural objects such as trees.
Figure 11 is the present invention in the basic operational version schematic top plan view of level land device for having the atural objects such as trees.
In figure, 1 rectangular outer tube, 2 rectangular inner sleeves, 3 fixing bolts, 4 mounting holes, 5 spikes, 6 pull rings, 7 wirerope, 8
Wire line hitch, 9 steel wire rope tensioning devices, the wirerope 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 pneumatic center (swept back wing), 15 wedge-shaped obturators, 16 sliding sleeves, 17
Sponge double-sided adhesive, 18 ailerons, 19 aerofoil profile central axes.
Specific embodiment
Referring to attached drawing 1- attached drawing 3, takeoff auxiliary device of the present invention is mainly by the both ends component fixed for ground and centre
The steel wire rope part two parts being tightened up are constituted.Rectangular outer tube 1 and rectangular inner sleeve 2 are the main bodys of ground component for fixing,
Two pipes be it is hollow, the side length in rectangular 2 section of inner sleeve (full outside dimension) is slightly less than the interior side length of rectangular outer tube 1, because
This rectangular inner sleeve 2 can be inserted or pull out in the inside of rectangular outer tube 1, and the upper and lower side of rectangular outer tube 1 has circle
Mounting hole 4, hole align up and down, and diameter is the same, spacing is the same；Rectangular inner sleeve 2 also has aligned identical, same diameter and spacing
Mounting hole 4.One or two fixing bolts 3 are inserted into the hole that two pipes overlap part (including the screw and its spiral shell passed completely through
It is female) and tighten, making no longer can be free to slide between inner sleeve and outer tube.Two underlapped ends of casing are respectively fixed with one
A pull ring 6, two pull rings respectively have the end of a wirerope 7 to pass through and fixed with the common wire line hitch 8 in market, so that steel
It fixes, cannot disengage between cord 7 and pull ring 6.The other end of two wirerope 7 equally uses wire line hitch 8 and wirerope
The hook of stretcher 9 connects, and it is (another that the other end hook of two steel wire rope tensioning devices is hooked in other end ground component for fixing
Group internal and external casing) on two pull rings 6 on.Second group of casing and above-mentioned first group of casing identical (shown in figure two
Poor 90 degree of casing pull ring setting angle of group, but particular/special requirement is had no in fact, two kinds of angles).
Referring to attached drawing 4, attached drawing 5, which further includes the cunning being bonded on 12 wing 11 of fixed-wing unmanned plane
Cover component, slide bushing assembly include sliding sleeve 16, by sponge double-sided adhesive 17 of the sliding sleeve 16 together with 11 lower surface bonds of wing and
In order to lower surface camber line in Airfoil Sections shape (being commonly referred to as aerofoil profile) is modified to the wedge-shaped obturator 15 of near linear.It is sliding
Set 16 is the elongated rod shape object covered in 7 outside of wirerope, and cross section is presented diamond shape (referring to Fig. 7) substantially, the upper vertex quilt of diamond shape
Amplification, becomes wider, smooth cross section upper surface, and bond together with sponge double-sided adhesive 17.16 upper surface of sliding sleeve, sponge
Double-sided adhesive, the width of 15 three of wedge-shaped obturator are essentially identical.Although sliding sleeve 16 is essentially a straight rod-like articles, its
Front end slightly upwarps.16 lower part of sliding sleeve is cut open, and opening width is identical as the diameter of wirerope 7.Furthermore in 16 bottom of sliding sleeve
Interlude also on the basis of opening, continues to be cut to only remaining upper half of diamond shape (referring to Fig. 6), section lower part is in horn-like complete
Open.
The takeoff auxiliary device further includes other accessories, such as the wirerope 7 and sufficient amount of wirerope of sufficient length
Button 8, and including multiple spikes 5, multiple common expansion bolts.Spike 5 is for securing the cannula in soil, therefore length can
Up to 30-40 centimetres；Expansion bolt is common model, is only used for stony ground table, can secure the cannula on rock (referring to attached drawing
1, attached drawing 10, attached drawing 11).
Implementation process:
There is high-intensitive, major diameter composite material crossbeam to run through inside fixed-wing unmanned plane wing so that wing this
The main modular construction intensity for providing flight lift is sufficiently large, is able to bear when encountering air-flow or when take-off climb and is several times as much as flying
For the air pressure of machine own wt without bending, this programme is namely based on this feature, passes through the appropriate position in surface under the wings of an airplane
Installation sliding sleeve is set, allows aircraft by wing 11, slide over and slide and take off on two wirerope 7.Therefore implementing to take off
Before, need user's first span according to oneself fixed-wing unmanned plane wing, design feature, select on two wings spacing compared with
One sliding sleeve is installed respectively, this programme is between two sliding sleeves as optimal installation site in the lower surface of remote symmetric position
Distance have no strict demand, to be not at wing tip, the installation for not influencing the airfoil members such as steering engine, control action are advisable.Generally
For aircraft is bigger, the span is wider, take-off distance is longer, then the clipping room of two sliding sleeves is away from bigger.
Another principle for sliding over wing lower surface bonding is sliding sleeve to be kept and 19 (i.e. machine of air-foil central axes
Nose of wing First Point and the line of trailing edge rearmost point are also wing chord) it is substantially parallel, therefore choosing wing installation site
Later, generally will the latter half (close to rear) first in aerofoil profile lower surface be first bonded wedge-shaped obturator 15 so that former
This is that the lower surface of arc bonds together sliding sleeve and wing lower surface close to straight line, then with sponge double-sided adhesive, and sponge is two-sided
The plasticity of glue can fill up space caused by injustice slight between two bonding planes.The centre of lift of wing is generally on wing
Near the highest point on surface, in general substantially at the preceding one third of the entire chord length of wing near (shown in 13
Point), it is that the center of gravity of aircraft and centre of lift is substantially aligned in plant design and production aircraft.Based on this principle,
When being bonded sliding sleeve to wing lower surface, the center of sliding sleeve more to lean on it is some into the leading edge of a wing because sliding sleeve should not enter machine
In the stroke up and down of wing trailing edge flap 18, lead to the movement for hindering aileron, and in general the front end of sliding sleeve should stretch out wing
Leading edge, so that center of gravity is still located substantially at the central location of sliding sleeve, and aircraft puts pitching on a steel cord and still keeps stable, will not
It is rotated at random.Above-mentioned " center of gravity is normally at before wing chord at one third " is that have slightly for straight wing for wing
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 one third position above-mentioned
The center of gravity of airplane and pneumatic center (swept back wing) 14, thus sliding sleeve front end will stretch out accordingly it is some more.
The spacing of aforementioned two sliding sleeve should select " moderate " position in spanwise, be also based on it is such consideration and in sweepback
Wing tip should not be got too close to when installing on wing.Furthermore the medium-sized scientific research of the 10-25 feather weight general wing of fixed-wing unmanned plane
Chord length be 25-35 centimetres between, therefore sliding sleeve length also be essentially 35-40 centimetres or so.
Since wedge-shaped obturator 15, sponge double-sided adhesive, sliding sleeve have had certain altitude, thus wirerope 7 and aileron 18 it
Between have a certain distance, and the movement that not makes a stunt flying when sliding and taking off, the stroke of aileron 18 is little, and wirerope 7 will not
Obstruction is generated to the movement of aileron 18.
After wing is mounted with sliding sleeve, the distance between two sliding sleeves are determined that, by connection, fixed inside and outside casing
Fixing bolt unclamp and extract, adjust insertion depth of the rectangular inner sleeve 2 in rectangular outer tube 1, make the mounting hole 4 of two pipes
It is still mutually aligned and the distance between the distance between two pull rings 6 and two sliding sleeves is closest, at this time again in two casings
Intermediate lap is plugged fixing bolt 3 and fastens, so that will not loosen between two casings.It is adjusted according to identical method
The spacing of pull ring on two casing of the wirerope other end.Select suitable position solid in the landform in rugged fluctuating or mountainous region later
Fixed two groups of casings.If because in this programme using unmanned plane self gravity can make its on a steel cord slide acceleration faster,
It, can be with by taking the hillside of the common terrace shaped in China or non-terrace shaped as an example (Fig. 8) so this programme can use completely in mountainous region
Casing is passed through with spike 5, two groups of casings are both secured to the suitable location on hillside, the distance between two groups of casings meet nobody
Machine takes off required coasting distance.Connect 7 total length of wirerope of two groups of casings may be it is very long, pine can be passed through
Wire line hitch 8 is opened to adjust the length of practical connection rope section, to adapt to fix the spacing after two groups of casings at present, later again
Tighten wire line hitch 8.The rate of tension of wirerope 7 is inadequate certainly at this time, it is also necessary to which rotating wire rope stretcher 9 is further
Tense wire rope 7 is allowed to the weight for being not easy to tremble and can bear unmanned plane.
In the mountainous region of more stones, it is difficult to which finding can be inserted under the soil regime of spike, can be beaten on megalith with electric hand drill small
Hole is simultaneously put into small-sized expansion bolt, can equally substitute spike and fix casing (Fig. 9).In the more area in forest land, may be used also
To pass through the wirerope 7 of one group of effective redundancy of set and be fixed on trunk with same wire line hitch 8, the casing of the other end can
To be fixed on the low bank of earth between fields (attached drawing 10, attached drawing 11).No matter which kind of fixed form, that peace near pull ring 6 should all be utilized
Filling hole 4 can be directly passed to ground across spike 5, expansion bolt or trunk binding wirerope 7, the pulling force of such wirerope 7
Object, torque is smaller, the not pliable deformation of casing.
After ground fixes device, aircraft is placed on wirerope 7, two wirerope 7 to be allowed all to be placed in
Within sliding sleeve, unmanned plane is slided into the higher one end of wirerope 7 and hand steered to keep its position by personnel later, when standby for takeoff
Start unmanned plane and engine, while decontroling unmanned plane, aircraft starts slowly to glide along the gentle slope angle of wirerope 7, takes off
Motor power is increased to maximum by operator, at this time unmanned plane self gravity, motor power double action under very
It is fast to accelerate.There is lesser downwardly open, machine during anti-accelerated slip here at 16 both ends of sliding sleeve of two sets on a steel cord
Body vibration causes wirerope to be deviate from from sliding sleeve 16.The operator that takes off after aircraft arrival takeoff speed draws control stick (elevator)
Head is set to steeve, 16 leading portion of sliding sleeve for covering face on a steel cord originally follows the fuselage steeved to rise and be detached from wirerope, steel wire
It restricts to deviate from the downside of 16 leading portion of sliding sleeve with the wide opening of wirerope, 16 back segment of sliding sleeve still covers on a steel cord at this time, to guarantee
From sliding state to safety when state of flight transition.Then steeve the trend for further speeding up and being detached from unmanned plane,
The back segment of sliding sleeve 16 also follows rising, and wirerope is deviate from from 16 back segment lower opening of sliding sleeve, and unmanned plane completes the full mistake taken off
Journey.
When withdrawing takeoff auxiliary device, the fixing bolt among two casings can also be extracted, inner sleeve is stretched as far as possible
Enter in outer tube, then screw on fixing bolt, in this way can further shortening device transport when length.
Using in natural environment hillside fields or height difference, can make to slide that acceleration is higher, shorten the length of wirerope and right
The requirement in place, exactly because this point, so that running length needed for this programme is less than the required landing airdrome length that normally takes off.
The installation gradient allowed band of wirerope is very wide, but is typically in the range of between 15-35 degree, can voluntarily be selected according to site condition.
It is because of after unmanned plane is placed on the wirerope of tensioning that the front end of sliding sleeve 16 upwarps slightly, and wirerope has summary
Micro- tenesmus, the front end slightly upwarped just meets this rule, so that the resistance during high speed slide is smaller, 16 middle section of sliding sleeve
Lower half portion be cut off and mitigate weight also for further, reduce frictional force, and people is more easily seen from below
Wirerope in sliding sleeve additionally smears lubricating grease in sliding sleeve convenient for personnel to further decrease friction and extend making for sliding sleeve
Use the service life.Sliding sleeve 16 protects wing 11 not worn by wirerope 7, but its own belongs to loss product, wears after taking off repeatedly
It can be replaced in serious sliding sleeve 16.
The fixed-wing unmanned plane wing of scientific research is simple, without the leading edge slat as airline carriers of passengers, so sliding sleeve 16
It can be also more prominent than the leading edge of a wing.
The following terms requirement that this programme meets simultaneously:
(a) device volume is small, light-weight.Due to using the seizing wire of tensioning instead of big and heavy metal launching cradle, and
And the power source needed for no longer needing shot trolley and short distance suddenly to accelerate, the weight of the present apparatus is extremely light, is usually no more than 5 kilograms.
Separately because of the medium-sized fixed-wing unmanned aerial vehicle design mainly for 2-3.5 meters of the span, therefore the casing that internal and external casing is waited when in use is total
Length generally need not be more than 2 meters, and storage size does not exceed 1.2 meters generally, therefore small vehicle can transport.
(b) almost various landform, geological conditions are adapted to.The difficulty highest of fixed-wing unmanned plane is used in rugged mountainous region, i.e.,
Make to carry traditional catapult-assisted take-off frame, excessively heavy and the shortcomings that needing flat ground to place also limits mobile in mountainous region
With the convenience used, equipment in this programme is not only light to be easy to carry about with one, but also changing drawback is advantage, is made using topographical elevation difference
Unmanned plane is obtained because borrowing self gravity to shorten coasting distance, it is no longer necessary to which additional ejection power source operates more in field mountainous region
It is convenient.It selects former and later two positions slightly outstanding to fix two groups of casings, a little higher than ground of wirerope is allowed for, to avoid original
Come screw current is rolled when ground is taken off sand and dust destroy, the various components on pollution aircraft.
Fixed-wing unmanned plane has had mature aerial parachute-opening landing technology at present, can drop in rugged topography or mountainous region
It falls, does not need runway.This programme solution mountainous region is taken off after problem, and it is convenient under full orographic condition that medium-sized unmanned plane may be implemented
Operation, is conducive to the implementation of field scientific research.
It (c) can Fast Installation, disassembly.Only need to fix two groups of casings ground (or other prominent terrain features such as trunk on),
And rotating wire rope stretcher is tensioned two wirerope and just completes the laying of takeoff auxiliary device, then aircraft is put by sliding sleeve
It is placed in that higher one end of wirerope and just completes preparation of taking off, so operation is extremely simple.
(d) sliding running journey is long, it is gentle to accelerate, applies without external force.Rope capacity in this programme can according to terrain slope,
Unmanned plane weight, power arbitrarily adjust, and are 20-30 meters or more, compare with only 4-8 meters of launching cradle, and unmanned plane is available
Longer in the stroke slided, acceleration is smaller, especially with self gravity, the strong external force of moment is avoided to be applied on fuselage,
Airframe structure weight can be greatly reduced, and not only contribute to increase voyage, and in turn but also the wing of unit area carries
Lotus is smaller, and takeoff speed is low, and the required coasting distance that takes off further shortens.
(e) without designing shot trolley, various fixed-wing unmanned planes are adapted to.General shot trolley is connected with fuselage
It connects, pushes fuselage to pop up at a high speed together with trolley when launching forward, and the unmanned aerial vehicle body size of different model, shape are all not
With, and when execution different task, ventral is possibly also with different information collecting devices, in strength ejection process
It is easy to be broken, so shot trolley is always specially changed according to the model of aircraft and the ventral equipment of carrying, task scheme
It makes, is nearly impossible if thinking temporarily to use instead different unmanned planes and carrying out ejection.Wirerope spacing in this programme is adjustable, energy
It unmanned plane of different sizes is adapted to, and avoids the information collection equipment of ventral completely, also avoid the engine or tail of head
Empennage, the various potential collisions between the auxiliary equipment that takes off that avoid aircraft, so the present apparatus is applicable to 6-30 in summary
Kilogram different model, fixed-wing unmanned plane that acceleration is different, though will in same task front and back take off different nobody
Machine also only needs the degree of overlapping for readjusting internal and external casing, namely the spacing of two wirerope of adjustment, very convenient.
Claims (9)
1. a kind of field scientific research portable launching apparatus of fixed-wing unmanned plane, it is characterised in that: be mainly used for ground by both ends
Component for fixing and intermediate steel wire rope part two parts being tightened up are constituted, and rectangular outer tube (1) and rectangular inner sleeve (2) are ground
The main body of face component for fixing, rectangular outer tube (1) and rectangular inner sleeve (2) be it is hollow, rectangular inner sleeve (2) section
Side length is slightly less than the interior side length of rectangular outer tube (1), therefore rectangular inner sleeve (2) can be inserted in the inside of rectangular outer tube (1)
Enter or extract, the upper and lower side of rectangular outer tube (1) has circular mounting hole (4), and hole aligns up and down, and diameter is the same, spacing one
Sample；Rectangular inner sleeve (2) also has the mounting hole (4) of aligned identical, same diameter and spacing, in rectangular outer tube (1) and rectangular
Inner sleeve (2) overlap part hole in be inserted into one or two fixing bolts (3) and tighten, make rectangular inner sleeve (2) with it is rectangular
No longer can be free to slide between outer tube (1), rectangular outer tube (1) and the underlapped each self-retaining in end of rectangular inner sleeve (2)
There is a pull ring (6), two pull rings (6) respectively have the end of a wirerope (7) to pass through and fixed with wire line hitch (8), make
It obtains and is fixed between wirerope (7) and pull ring (6), the other end of two wirerope (7) equally uses wire line hitch (8) and steel wire
The hook of rope stretcher (9) connects, and it is another that the other end hook of two steel wire rope tensioning devices (9) is hooked in ground component for fixing
On two pull rings (6) on the rectangular outer tube (1) and rectangular inner sleeve (2) at end.
2. the field scientific research according to claim 1 portable launching apparatus of fixed-wing unmanned plane, it is characterised in that: also wrap
Include 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-sided adhesive (17) and wedge-shaped obturator (15) together with wing (11) lower surface bonds；Wedge-shaped obturator (15)
Upper surface be bonded in the latter half of wing (11) aerofoil profile lower surface, the lower surface of wedge-shaped obturator (15) and sponge are double
Face glue (17) bonding.
3. the field scientific research according to claim 2 portable launching apparatus of fixed-wing unmanned plane, it is characterised in that: sliding sleeve
It (16) is the elongated rod shape object covered outside wirerope (7), diamond shape is presented in cross section substantially, and the upper vertex of diamond shape is amplified, at
It for wider, smooth cross section upper surface, and bonds together with sponge double-sided adhesive (17), sliding sleeve (16) is a straight bar
Shape object, front end slightly upwarp.
4. the field scientific research according to claim 2 portable launching apparatus of fixed-wing unmanned plane, it is characterised in that: sliding sleeve
(16) lower part is cut open, and opening width is identical as the diameter of wirerope (7), the interlude of bottom also on the basis of opening, after
Continuous be cut to only remains upper half of diamond shape, and section lower part is in horn-like completely open.
5. the field scientific research according to claim 1 portable launching apparatus of fixed-wing unmanned plane, it is characterised in that: also wrap
Multiple spike (5) or expansion bolts for securing the cannula in soil or on rock are included, spike length is 30-40 centimetres.
6. a kind of application method of the field scientific research portable launching apparatus of fixed-wing unmanned plane, including it is described in claim 1
Launching apparatus, it is characterised in that: after ground inclination fixes device, fixed-wing unmanned plane is placed on wirerope,
Allow two wirerope to be all placed within sliding sleeve (16), take off later operator by fixed-wing unmanned plane slide into wirerope compared with
High one end is simultaneously hand steered to keep its position, starting fixed-wing unmanned plane and engine when standby for takeoff, while decontroling fixed-wing
Unmanned plane, fixed-wing unmanned plane start slowly to glide along the gentle slope angle of wirerope, and the operator that takes off is by motor power
Increase to maximum, at this time fixed-wing unmanned plane self gravity, motor power double action under accelerate quickly, two cover
Sliding sleeve (16) both ends on wirerope (7) have lesser downwardly open, and fuselage shaking causes during anti-accelerated slip here
Wirerope (7) is deviate from from sliding sleeve (16), and the operator that takes off after fixed-wing unmanned plane arrival takeoff speed draws control stick to make machine
Head is steeved, and is covered originally and is followed the fuselage steeved to rise in sliding sleeve (16) leading portion of wirerope (7) above and be detached from wirerope, steel wire
The opening that (7) are on the downside of sliding sleeve (16) leading portion and wirerope is wide of restricting is deviate from, and sliding sleeve (16) back segment is still covered in wirerope (7) at this time
On, to guarantee then to steeve with fixed-wing unmanned plane and further add from sliding state to safety when state of flight transition
Trend that is fast and being detached from, the back segment of sliding sleeve also follow rising, and wirerope (7) is deviate from from sliding sleeve (16) back segment lower opening, nothing
The overall process that man-machine completion is taken off；
Sliding sleeve (16) is the elongated rod shape object covered outside wirerope (7), and diamond shape, the upper vertex quilt of diamond shape is presented in cross section substantially
Amplification, becomes wider, smooth cross section upper surface, and bond together with sponge double-sided adhesive (17), and sliding sleeve (16) is one
Straight rod-like articles, front end slightly upwarp.
7. the application method of the scientific research portable launching apparatus of fixed-wing unmanned plane in field according to claim 6, special
Sign is: after wing is mounted with sliding sleeve (16), will be connected and fixed the fixation of rectangular inner sleeve (2) and rectangular outer tube (1)
Bolt (3) is unclamped and is extracted, and is adjusted insertion depth of the rectangular inner sleeve (2) in rectangular outer tube (1), is made rectangular outer tube
(1) it is still mutually aligned and between the distance between two pull rings and two sliding sleeves (16) with the mounting hole of rectangular inner sleeve (2)
Apart from closest, fixing bolt is plugged in the intermediate lap of rectangular outer tube (1) and rectangular inner sleeve (2) again at this time
(3) it and fastens, so that will not be loosened between rectangular outer tube (1) and rectangular inner sleeve (2).
8. the application method of the scientific research portable launching apparatus of fixed-wing unmanned plane in field according to claim 6, special
Sign is: the installation range of grade of wirerope (7) is between 15-35 degree.
9. according to the user of claim 6-8 described in any item field scientific researches portable launching apparatus of fixed-wing unmanned plane
Method, it is characterised in that: for terraced fields, hillside, more tors fixed-wing unmanned plane take off.
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| 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 |
| 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 |
| CN113018881B (en) * | 2021-04-25 | 2022-04-29 | 航天创客（北京）科技有限公司 | Aerospace science popularization model self-adaptive ejection device |
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