CN106314814B - A kind of field the scientific research portable launching apparatus of fixed-wing unmanned plane and application method - Google Patents

Abstract

A portable take-off device of a fixed-wing unmanned aerial vehicle for field scientific research and a method of use thereof, which belong to the auxiliary take-off device of the unmanned aerial vehicle. It is mainly composed of two parts used for ground fixing at both ends and a tensioned steel wire rope part in the middle. The square outer casing and square inner casing are the main body of the ground fixing parts, and also include the wings bonded to the fixed-wing UAV. After the sliding sleeve assembly on the ground is tilted and fixed, the aircraft is placed on the wire rope placed in the sliding sleeve, and the drone and engine are started. The drone is very fast under the dual effects of its own gravity and engine thrust. Accelerate quickly, the steel wire rope comes out of the sliding sleeve at the same time as the aircraft is pulled up, and the drone completes the whole process of take-off. Its advantages and positive effects: the device is small in size and light in weight; it can adapt to almost all kinds of terrain and geological conditions; it can be quickly installed and disassembled; it has a long sliding stroke, gentle acceleration, and no external force; it does not need to design an ejection car and is suitable for various fixed wings drone.

Description

A portable take-off device for a fixed-wing unmanned aerial vehicle for field scientific research and its use method

technical field

The invention belongs to an auxiliary take-off device for unmanned aerial vehicles.

Background technique

Generally speaking, the take-off and landing of fixed-wing UAVs requires a certain length of flat runway for taxiing, but in the absence of an ideal flat field in the field, medium-sized fixed-wing UAVs with a total weight of about 6-30 kg Machines have always been a problem. The common flat places in the field are mainly roads, but roads are public transportation facilities. For safety reasons, UAVs should not use roads as take-off and landing sites. Therefore, UAVs of various levels and uses have no runways at present. The respective assisted takeoff methods under different conditions.

Small fixed-wing UAVs with a total weight of no more than 5 kg have a relatively low take-off speed and fast acceleration, so generally speaking, the simplest field operation method of personnel throwing and take-off can be used, which is suitable for various field conditions. However, most fixed-wing UAVs of this level can only carry miniature cameras for soldiers to understand local battlefield conditions, and cannot carry high-resolution cameras with professional optical lenses and other advanced remote sensing equipment, so they cannot fully meet the requirements of scientific research.

Large-scale military UAVs with a take-off weight of 50-300 kg are heavy and have high inertia. In addition to using a powerful steam catapult to take off, they often use rockets to boost their take-off, which can save the bulky catapult and high pressure. The energy storage device and the whole system are simple and easy to operate. The disadvantage is that rockets are military products and are strictly controlled as dangerous goods. General civilian scientific research units cannot use them during ordinary field inspections.

Fixed-wing UAVs with a take-off weight of 6-40 kg are widely used in the field of civil scientific research, especially products of the 15-25 kg class (hereinafter referred to as "medium-sized" in this program) are used the most, mainly because of such a fixed-wing UAV. The Wing UAV has a wingspan of about 2-3.5 meters and a payload of 2-5 kg. It can carry a variety of portable information collection equipment such as SLR cameras, infrared imagers, multispectral cameras, and air pollutant detection instruments. The voyage reaches 50-200 kilometers, so it has a wide range of uses in the field of scientific research. Medium-sized fixed-wing drones are also more convenient to carry, and a working team of two or three people and ordinary small vehicles can meet the requirements for operation, disassembly, and transportation.

The take-off speed of medium-sized fixed-wing drones for scientific research is generally between 50-70 km/h, and generally requires a 100-300-meter-long, flat, dust-free take-off and landing site with no obstacles at both ends of the runway for acceleration or deceleration If the road cannot be used, it is difficult to find such a site in the wild, and it is impossible to throw and take off, and it is also impossible to use the rocket-assisted take-off method, so most of them use the catapult catapult take-off method. The ejection rack is generally composed of three basic parts: a slide rail, an ejection trolley, and a power source. The slide rail generally has a length of 4-8 meters and is made of metal, which is used to support the front and rear sliding of the ejection trolley on it; the contact between the ejection trolley and the slide rail depends on the wheels to ensure that the trolley will not detach from the slide rail and the front and rear sliding resistance is small. When ejecting, place the UAV on the ejection car and fix it properly to ensure that after the power source is manually activated, the power source will apply a strong traction force to the ejection car, and the ejection car will transmit the traction force to the UAV. The two accelerate rapidly. Accelerate the drone to more than 50 km/h within the limited slide rail travel range of no more than 8 meters. At this time, the ejection car stops at the end of the slide rail, the drone reaches the take-off speed, and its engine is in working condition. Continue Forward thrust is provided, and the UAV takes off.

There are various types of ejection power sources. Military UAVs can use compressed air power source, which has the advantages of less consumables, continuous use of equipment, and stable and adjustable traction provided. on military drones. Thick rubber tendons are the most commonly used power source for the ejection of civilian UAVs. Its advantages are relatively simple and light, but its disadvantage is that the traction force is not constant during the ejection process, and it is easy to strain the UAV during the initial stage of ejection. The airframe has limited subsequent acceleration capability, and the traction force of the rubber band will be significantly attenuated once it is used, so it needs to be replaced frequently. Other new power sources include electromagnetic ejection, etc., which have not yet been popularized and will not be described in detail.

Generally speaking, in order to withstand the huge traction force during ejection, the structure does not deform and maintain stability, the weight of the entire equipment of the ejection rack can reach 50-100 kg, and the scale is huge, and the transportation of small vehicles is inconvenient, which seriously reduces the capacity of medium-sized fixed-wing UAVs. As a portable and easy-to-use device for grass-roots scientific research units, it has practical performance in the field, and shortens the acceleration process of about 150 meters long to 4-8 meters, and the instantaneous acceleration of the body is increased by about 30 times. The requirements for obtaining equipment have been greatly increased, so the airframe structure must be strengthened, and its weight in the proportion of the total take-off weight has been greatly increased, so that it can carry less scientific research equipment and a shorter flight range. Such a strong instantaneous acceleration is also enough to destroy a variety of airborne optical equipment.

In order to avoid the use of catapults, there are currently other fixed-wing UAV take-off methods, such as placing a short UAV rack on the roof of the car, driving the car fast on the road, and after reaching the take-off speed, the UAV will naturally pull up Leaving the vehicle, this method seems to avoid ejection and ejection racks, but it still needs to use public transportation facilities such as roads, which violates the basic safety principles, so the current usage is very small. Some people have also developed a fixed-wing UAV with a vertical take-off and landing function. During the take-off and landing phase, the upward lift of the rotor lifts the fuselage vertically away from the ground, and then gradually switches to a horizontal flight state. However, these compromise designs have strict restrictions on the load capacity of the drone, and because the take-off consumes too much energy, the range is greatly shortened. The main advantages of fixed-wing UAVs over rotary-wing aircraft are long range and long endurance, and the compromise design significantly weakens this inherent advantage.

According to the above analysis, at present, if the advantages of long-range and long-endurance of medium-sized fixed-wing UAVs for scientific research are not to be attenuated, there is no better field auxiliary take-off device and method to replace the catapult take-off frame.

Contents of the invention

The main purpose of the present invention is: a set of devices for auxiliary take-off of medium-sized fixed-wing UAVs in the field without a runway, under the premise that the total weight of all auxiliary take-off devices does not exceed 5 kg, the storage volume is small, and it can be transported by small vehicles , to ensure that takeoff can be carried out normally, and it is suitable for most of the natural rough ground and areas covered by natural features such as farmland, hills, mountains, and sparse forests. The take-off acceleration stroke allowed by this device breaks through the general limit of 4-8 meters of the catapult take-off frame, and the acceleration during take-off is only moderately increased compared with the natural roll take-off, which reduces the requirements for the structural strength of the airframe and will not significantly reduce the fixed-wing unmanned aircraft. During take-off, the propeller of the aircraft keeps a safe distance from the ground, and the lens on the aircraft is not easily polluted by flying dust and grass blades on the ground, so as to meet the general needs of field scientific research. The device should also be applicable to fixed-wing unmanned aerial vehicles of different models and various aerodynamic layouts.

Technical scheme of the present invention is:

A portable take-off device for a fixed-wing unmanned aerial vehicle for field scientific research. It is mainly composed of two parts used for ground fixing at both ends and a tensioned steel wire rope part in the middle. The square outer sleeve and the square inner sleeve are ground fixing parts. The main body, both tubes are hollow, the side length of the square inner casing section is slightly smaller than the inner side length of the square outer casing, so the square inner casing can be inserted or pulled out inside the square outer casing, and the square outer casing There are circular mounting holes on the upper and lower sides, the holes are aligned up and down, with the same diameter and the same spacing; the square inner casing also has mounting holes in the same arrangement, the same diameter and spacing. Insert one or two fixing bolts into the holes of the overlapped part of the two tubes and tighten them so that the inner sleeve and the outer sleeve can no longer slide freely. The non-overlapping ends of the two sleeves are respectively fixed with a pull ring. Each of the two pull rings has an end of a wire rope passing through and fixed with a wire rope buckle, so that the wire rope and the pull ring are fixed. The other ends of the two wire ropes are also connected with the hook of the wire rope tensioner with a wire rope buckle. The other end hook of the first wire rope tensioner is hooked on the two pull rings on the inner and outer sleeves at the other end of the ground fixing part.

Further, it also includes a sliding sleeve assembly bonded to the wing of the fixed-wing UAV. The sliding sleeve assembly includes a sliding sleeve, a sponge double-sided adhesive for bonding the sliding sleeve and the lower surface of the wing together, and a wedge-shaped filling body.

Furthermore, the sliding sleeve is a long rod-shaped object that is sheathed on the outside of the steel wire rope. The cross-section is basically rhombus-shaped, and the upper apex of the rhombus is enlarged to become a wider and flatter cross-section upper surface, and it is glued together with the sponge double-sided adhesive , the sliding sleeve is a straight rod-shaped object, and its front end is slightly upturned.

Furthermore, the middle section of the bottom of the sliding sleeve is still on the basis of the opening, and continues to be cut until only the upper half of the rhombus is left, and the lower part of the section is fully opened in a trumpet shape.

Further, it also includes a plurality of spikes or expansion bolts for fixing the casing in the soil or on the rock, and the length of the spikes is 30-40 cm.

A method for using a portable take-off device for a fixed-wing unmanned aerial vehicle for field scientific research, including the above-mentioned take-off device. After the device is tilted and fixed on the ground, the aircraft is placed on the wire rope, so that both wire ropes are placed Inside the sliding sleeve, the personnel then slide the UAV to the higher end of the wire rope and hold it by hand to maintain its position. When it is ready to take off, start the UAV and engine, and release the UAV at the same time, and the aircraft starts to follow the gentle slope of the wire rope The angle slowly declined, and the take-off operator increased the engine thrust to the maximum. At this time, the UAV accelerated rapidly under the dual effects of its own gravity and engine thrust. Both ends of the two sliding sleeves on the wire rope had small The opening is downward to prevent the wire rope from slipping out of the sliding sleeve due to the vibration of the fuselage during the accelerated taxiing process. After the aircraft reaches the take-off speed, the take-off operator pulls the joystick to raise the nose, and the front section of the sliding sleeve that was originally placed on the steel wire rope is raised accordingly. The fuselage rises and breaks away from the wire rope, and the wire rope escapes from the opening at the lower side of the front section of the sliding sleeve, which is as wide as the wire rope. With the trend of further acceleration and separation of the UAV, the rear section of the sliding sleeve also rises, and the steel wire rope escapes from the opening below the rear section of the sliding sleeve, and the UAV completes the whole process of take-off.

Further, after the wing is installed with the sliding sleeve, the fixing bolts connecting the fixed inner and outer sleeves are loosened and pulled out, and the insertion depth of the inner sleeve in the outer sleeve is adjusted so that the mounting holes of the two pipes are still aligned with each other and The distance between the two pull rings is the closest to the distance between the two sliding sleeves. At this time, re-insert the fixing bolts in the overlapping part of the middle of the two sleeves and tighten them so that there will be no looseness between the two sleeves.

Advantages and positive effects of the present invention: (a) The device is small in size and light in weight. (b) Adapt to almost various terrain and geological conditions. (c) It can be quickly installed and disassembled. (d) The sliding stroke is long, the acceleration is gentle, and no external force is applied. (e) There is no need to design a catapult car, and it can be adapted to various fixed-wing UAVs.

Description of drawings

Fig. 1 is a structural schematic diagram of the take-off device of the present invention.

Figure 2 is a side view of the present invention.

Fig. 3 is a sectional view of the take-off device of the present invention.

Fig. 4 is a schematic side view of the installation of the sliding sleeve of the present invention on the lower surface of the wing.

Fig. 5 is a schematic bottom view of the installation of the sliding sleeve of the present invention on the lower surface of the wing.

Fig. 6 is a cross-sectional schematic view of the middle section of the sliding sleeve of the present invention.

Fig. 7 is a schematic cutaway view of the end of the sliding sleeve of the present invention.

Fig. 8 is a schematic diagram of the take-off scheme of the present invention under mountainous conditions such as terraced fields.

Fig. 9 is a schematic diagram of fixing the casing by drilling holes and putting expansion bolts in the present invention under the condition of hard rock.

Fig. 10 is a schematic diagram of the basic application scheme of the present invention on a level ground device with trees and other ground features.

Fig. 11 is a schematic top view of the basic usage scheme of the present invention on a level ground device with trees and other ground features.

In the figure, 1 square outer casing, 2 square inner casing, 3 fixing bolts, 4 mounting holes, 5 spikes, 6 pull rings, 7 wire ropes, 8 wire rope buckles, 9 wire rope tensioners, 10 redundant wire ropes, 11 Wing, 12 fixed-wing UAV, 13 aircraft center of gravity and aerodynamic center position (straight wing), 14 aircraft center of gravity and aerodynamic center position (swept wing), 15 wedge-shaped filling body, 16 sliding sleeve, 17 sponge double Surface glue, 18 ailerons, 19 airfoil central axis.

Detailed ways

Referring to accompanying drawing 1-accompanying drawing 3, the take-off auxiliary device of the present invention is mainly made of two parts that two ends are used for ground fixing part and the steel wire rope part that is tensioned in the middle. The square outer sleeve 1 and the square inner sleeve 2 are the main parts of the ground fixing parts. Both pipes are hollow. , so the square inner casing 2 can be inserted or pulled out inside the square outer casing 1, the upper and lower sides of the square outer casing 1 have circular mounting holes 4, the holes are aligned up and down, the diameter is the same, and the spacing is the same; the square inner casing 2 also has mounting holes 4 in the same arrangement, with the same diameter and spacing. Insert one or two fixing bolts 3 (including screws and nuts passing through completely) in the holes of the overlapping parts of the two pipes and tighten them so that they can no longer slide freely between the inner casing and the outer casing. The non-overlapping ends of the two sleeves are respectively fixed with a pull ring 6, and the ends of a steel wire rope 7 pass through each of the two pull rings and are fixed with a common wire rope buckle 8 on the market, so that the wire rope 7 and the pull ring 6 It is fixed and cannot be disengaged. The other ends of the two wire ropes 7 are also connected with the hooks of the wire rope tensioner 9 with a wire rope buckle 8, and the hooks at the other end of the two wire rope tensioners are hooked on the ground fixing parts (another set of inner and outer sleeves) at the other end. on the two pull rings 6. The second set of bushings is exactly the same as the first set of bushings mentioned above (the installation angles of the pull rings of the two sets of bushings shown in the figure differ by 90 degrees, but there is no special requirement, and both angles are acceptable).

Referring to accompanying drawing 4, accompanying drawing 5, this take-off assisting device also comprises the sliding sleeve assembly that is bonded on the wing 11 of fixed-wing UAV 12, and sliding sleeve assembly comprises sliding sleeve 16, slide sleeve 16 and wing 11 are lowered. The sponge double-sided adhesive 17 that the surfaces are bonded together, and the wedge-shaped filling body 15 in order to revise the arc of the lower surface in the wing cross-sectional shape (that is, generally called the airfoil) into an approximate straight line. Sliding sleeve 16 is a long rod-shaped object that is sheathed on the outside of steel wire rope 7. The cross section basically presents a rhombus (see Figure 7). 17 bonded together. The widths of the upper surface of the sliding sleeve 16, the double-sided sponge tape, and the wedge-shaped filling body 15 are basically the same. Although the sliding sleeve 16 is basically a straight rod-shaped object, its front end is slightly upturned. Sliding sleeve 16 bottoms are cut, and the opening width is identical with the diameter of steel wire rope 7. In addition, on the basis of the opening, the middle section at the bottom of the sliding sleeve 16 continues to be cut to only the upper half of a rhombus (referring to FIG. 6 ), and the lower part of the cross-section is trumpet-shaped and completely opened.

The take-off assisting device also includes other accessories, such as a steel wire rope 7 of sufficient length and a sufficient number of wire rope buckles 8, as well as a plurality of spikes 5 and a plurality of common expansion bolts. Long nail 5 is used for casing pipe is fixed in earth, so length can reach 30-40 centimetre; Expansion bolt is common type, is only used in many stony ground surfaces, and casing pipe can be fixed on rock (referring to accompanying drawing 1, Accompanying drawing 10, accompanying drawing 11).

Implementation process:

There are high-strength and large-diameter composite beams running through the wings of fixed-wing UAVs, so that the structural strength of the wing, which mainly provides flight lift, is strong enough to withstand several times when encountering airflow or taking off and climbing. The air pressure that is twice the weight of the aircraft itself will not bend. This scheme is based on this feature. By installing a sliding sleeve at an appropriate position on the lower surface of the wing, the aircraft can slide on the two wire ropes 7 through the wing 11 and the sliding sleeve. and take off. Therefore, before taking off, the user needs to select the lower surface of the symmetrical position with a long distance between the two wings as the best installation position according to the wingspan and structural characteristics of the wings of the fixed-wing UAV, and install them separately. One sliding sleeve, this scheme does not have strict requirements on the distance between the two sliding sleeves, it is advisable not to be at the tip of the wing and not affect the installation and manipulation of wing components such as steering gear. Generally speaking, the larger the aircraft, the wider the wingspan, and the longer the take-off and glide distance, the larger the installation distance between the two sliding sleeves.

Another principle of bonding the sliding sleeve to the lower surface of the wing is to keep the sliding sleeve basically parallel to the central axis 19 of the wing airfoil (that is, the line connecting the frontmost point of the wing’s leading edge and the rearmost point of the wing’s trailing edge, also called the chord) , so after the installation position of the wing is selected, the wedge-shaped filling body 15 is generally bonded to the second half of the lower surface of the airfoil section (near the trailing edge), so that the originally curved lower surface is close to a straight line, and then The sliding sleeve and the lower surface of the wing are bonded together with double-sided sponge tape. The plasticity of the double-sided sponge tape can fill the space caused by the slight unevenness between the two bonding surfaces. The center of lift of the wing is generally near the highest point on the upper surface of the wing, generally speaking, it is roughly near the first third of the entire chord length of the wing (close to the point shown in 13). When designing and producing aircraft in the factory The center of gravity of the aircraft has been roughly aligned with the center of lift. Based on this principle, when bonding the sliding sleeve to the lower surface of the wing, the center position of the sliding sleeve should be closer to the leading edge of the wing, because the sliding sleeve should not enter the up and down travel of the aileron 18 at the trailing edge of the wing, resulting in obstruction Generally speaking, the front end of the sliding sleeve should protrude from the leading edge of the wing, so that the center of gravity is still roughly located in the center of the sliding sleeve, and the pitch of the aircraft remains stable when placed on the wire rope, and will not rotate at will. The above-mentioned "center of gravity is generally located at the first third of the wing chord" is for straight wings. For fixed-wing drones with slightly swept wings, as long as the center of gravity is not at the wing root position, the center of gravity is higher than the aforementioned third. One position may be closer to the center of gravity of the leading edge aircraft and the aerodynamic center position (swept wing) 14, so the front end of the sliding sleeve will protrude more correspondingly.

The spacing of the aforementioned two sliding sleeves should be selected in the "moderate" position in the span direction, and it should not be too close to the wingtip when installed on the swept wing based on this consideration. In addition, the 10-25 kg medium-sized fixed-wing UAV for scientific research generally has a wing chord length of 25-35 cm, so the length of the sliding sleeve is basically about 35-40 cm.

Because the wedge-shaped filling body 15, the sponge double-sided adhesive tape, and the sliding sleeve have a certain height, there is a certain distance between the steel wire rope 7 and the aileron 18, and it is not doing aerobatic maneuvers when taxiing and taking off, and the stroke of the aileron 18 is not large. Wire rope 7 can not hinder the action of aileron 18.

After the sliding sleeve is installed on the wing, the distance between the two sliding sleeves is determined. Loosen and pull out the fixing bolts connecting and fixing the inner and outer sleeves, and adjust the square inner sleeve 2 in the square outer sleeve 1. The insertion depth of the two pipes is still aligned with each other and the distance between the two pull rings 6 is the closest to the distance between the two sliding sleeves. At this time, re-insert and fix the middle overlapping part of the two sleeves. Bolts 3 and tightened so that there will be no looseness between the two bushings. Adjust the distance between the pull rings on the two casings at the other end of the wire rope in exactly the same way. Then choose a suitable location in the rugged or mountainous terrain to fix the two sets of bushings. Because in this scheme, if the UAV’s own gravity is used, it can accelerate its gliding on the wire rope faster, so this scheme can be used in mountainous areas. Take the common terraced or non-terraced hillsides in my country as an example (Figure 8) , the spikes 5 can be used to pass through the bushings, and the two sets of bushings can be fixed at suitable positions on the hillside, and the distance between the two sets of bushings can meet the glide distance required for the drone to take off. The total length of the wire rope 7 connecting the two sets of bushings may be very long, and the length of the actual connecting rope segment can be adjusted by loosening the wire rope buckle 8 to adapt to the current spacing after fixing the two sets of bushings, and then re-tighten the wire rope buckle 8. Now the tension of the wire rope 7 is definitely not enough, and the wire rope tensioner 9 needs to be rotated to further tighten the wire rope 7 so that it is not easy to vibrate and can bear the weight of the drone.

In rocky mountainous areas, where it is difficult to find soil where spikes can be inserted, you can use a hand drill to drill small holes in boulders and insert small expansion bolts, which can also be used instead of spikes to fix the casing (Figure 9). In areas where woodland is more, one group of sleeve pipes can also be passed through with redundant wire rope 7 and fixed on the trunk with the same wire rope buckle 8, and the sleeve pipe at the other end can be fixed on the soil ridge (accompanying drawing 10, attached Figure 11). Regardless of the fixing method, the installation hole 4 closest to the pull ring 6 should be used to pass through the spike 5, the expansion bolt or the wire rope 7 for binding the tree trunk, so that the tension of the wire rope 7 can be directly transmitted to the ground object, and the torque is relatively small. The casing is not easy to bend and deform.

After the device is fixed on the ground, the aircraft is placed on the wire rope 7, and the two wire ropes 7 must be placed in the sliding sleeve, and then the personnel slide the drone to the higher end of the wire rope 7 and hold it by hand to keep Its position, when ready to take off, start the UAV and engine, release the UAV at the same time, the aircraft begins to slide slowly along the gentle slope angle of the wire rope 7, and the take-off operator increases the thrust of the engine to the maximum, at this time the UAV is on its own Accelerate quickly under the dual effects of gravity and engine thrust. Two sliding sleeves 16 two ends that are enclosed within on the steel wire rope all have less downward openings, prevent that fuselage vibration causes steel wire rope to deviate from sliding sleeve 16 in this accelerated sliding process. After the aircraft reaches the take-off speed, the take-off operator pulls the joystick (elevator) to raise the nose, and the front section of the sliding sleeve 16 that was originally placed on the wire rope rises with the raised fuselage and breaks away from the wire rope. The wide opening of wire rope is deviated from, and this moment, sliding sleeve 16 rear section still is enclosed within on the wire rope, to guarantee the safety when transitioning to flying state from gliding state. Then along with the tendency of the unmanned aerial vehicle to raise and accelerate further and break away, the rear section of the sliding sleeve 16 also rises, and the steel wire rope escapes from the opening below the rear section of the sliding sleeve 16, and the unmanned aerial vehicle completes the whole process of taking off.

When retracting the take-off assist device, the fixing bolt in the middle of the two casings can also be pulled out, the inner sleeve can be extended into the outer casing as far as possible, and then the fixing bolt can be screwed on, so that the length of the device during transportation can be further shortened.

Utilizing the slope or height difference in the natural environment can make the taxiing acceleration higher, shorten the length of the wire rope and the requirements for the site, and it is precisely because of this that the required taxiing length of this program is less than the required runway length for normal take-off. The installation slope of the wire rope allows a wide range, but generally between 15-35 degrees, which can be selected according to the site conditions.

The front end of the sliding sleeve 16 is slightly upturned because after the drone is placed on the tensioned wire rope, the wire rope will drop slightly, and the slightly upturned front end just conforms to this rule, making the resistance during high-speed gliding even smaller. The lower half of the middle section of the sliding sleeve 16 is also cut off in order to further reduce weight and reduce friction, and make it easier for people to see the steel wire rope in the sliding sleeve from below. In addition, it is also convenient for personnel to apply grease in the sliding sleeve to further reduce friction. Low friction and extended sleeve life. Sliding sleeve 16 has protected wing 11 from wearing and tearing by wire rope 7, but itself belongs to consumables, and the sliding sleeve 16 that wears too seriously after taking off repeatedly can be replaced.

The wing of the fixed-wing unmanned aerial vehicle used for scientific research is simple, and there is no leading edge slat like a civil aviation airliner, so the sliding sleeve 16 can also protrude more than the leading edge of the wing.

The program also meets the following requirements:

(a) The device is small in size and light in weight. Due to the use of tensioned thin wire ropes to replace the thick and heavy metal ejection frame, and no longer need the power source required for the ejection trolley and short-distance rapid acceleration, the weight of the device is extremely light, generally no more than 5 kilograms. In addition, because it is mainly designed for medium-sized fixed-wing UAVs with a wingspan of 2-3.5 meters, the total length of the inner and outer casings generally does not need to exceed 2 meters, and the storage size generally does not exceed 1.2 meters, so small vehicles need Can be shipped.

(b) Adapt to almost various terrain and geological conditions. It is the most difficult to use fixed-wing UAVs in rugged mountains. Even if it carries a traditional catapult launch frame, its shortcomings of being too heavy and needing to be placed on a flat ground also limit the convenience of moving and using in mountains. The equipment in this solution not only It is light and easy to carry, and turns its disadvantages into advantages. Using the height difference of the terrain, the drone can shorten the gliding distance due to its own gravity, no longer needs an additional ejection power source, and it is more convenient to operate in the wild and mountainous areas. Choose two slightly protruding positions at the front and back to fix two sets of bushings, so that the wire rope is slightly higher than the ground, so as to avoid the damage of the sand and dust rolled up by the propeller wake when the ground takes off and pollute various parts on the aircraft.

At present, fixed-wing UAVs have mature parachute landing technology in the air, which can land on rough terrain or mountains without a runway. After this solution solves the problem of taking off in mountainous areas, it can realize the convenient operation of medium-sized UAVs under all-terrain conditions, which is conducive to the implementation of field scientific research.

(c) It can be quickly installed and disassembled. It is only necessary to fix two sets of bushings on the ground (or other prominent objects such as tree trunks), and rotate the wire rope tensioner to tighten the two wire ropes to complete the deployment of the take-off auxiliary device, and then place the aircraft on the wire rope through the sliding sleeve. The high end is ready for take-off, so the operation is extremely simple.

(d) The sliding stroke is long, the acceleration is gentle, and no external force is applied. The length of the wire rope in this solution can be adjusted arbitrarily according to the slope of the terrain, the weight of the UAV, and the power, and can be as long as 20-30 meters. Compared with the catapult rack with only 4-8 meters, the UAV can be used for sliding. Longer, smaller acceleration, especially by using its own gravity, to avoid instantaneous strong external force applied to the fuselage, the weight of the fuselage structure can be greatly reduced, which not only helps to increase the range, but also makes the wing load per unit area smaller , the take-off speed is low, and the glide distance required for take-off is further shortened.

(e) There is no need to design a catapult car, and it can be adapted to various fixed-wing UAVs. Generally, the ejection car is connected to the fuselage. When ejecting forward, it pushes the fuselage to eject at high speed with the car. However, different types of drones have different sizes and shapes of the fuselage, and when performing different tasks, the belly of the drone It may also have different information collection equipment, which is easy to be damaged during the powerful ejection process. Therefore, the ejection car must be specially modified according to the model of the aircraft, the belly equipment carried, and the mission plan. If you want to temporarily switch to a different wireless Man-machine ejection is almost impossible. The distance between the steel wire ropes in this solution is adjustable, which can adapt to different sizes of drones, and completely avoids the information collection equipment on the belly, and also avoids the engine at the nose or the tail of the tail, and avoids the gap between the aircraft and the take-off auxiliary equipment. Various potential collisions, so in summary, this device can be applied to fixed-wing UAVs of different types and accelerations of 6-30 kg. It is very convenient to readjust the overlapping degree of the inner and outer casings, that is, to adjust the distance between the two steel wire ropes.

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.