CN110182377B - Winglet-loaded large-scale unmanned plane traction takeoff system and method - Google Patents
Winglet-loaded large-scale unmanned plane traction takeoff system and method Download PDFInfo
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Abstract
The invention discloses a winglet-loaded large unmanned aerial vehicle traction takeoff system, which comprises a traction device, a towed unmanned aerial vehicle and a traction runway, wherein the traction device pulls the unmanned aerial vehicle to run on the traction runway, take off from the ground to ascend and fly unhooked, and is characterized in that: the traction device is suitable for the winglet-loaded large unmanned aerial vehicle to take off in a traction manner; the towed unmanned aerial vehicle is a winglet-loaded large unmanned aerial vehicle; the traction runway is a short-distance takeoff runway; the overload ratio and the lift-drag ratio of the unmanned aerial vehicle are suitable for short-distance traction takeoff; the traction device comprises traction power equipment, a traction rope and a traction hook. Compared with the prior art, the method which is adopted by the large-scale light unmanned aerial vehicle with the wingspan of more than 30 meters or more and has extremely high risk and huge investment during long-term flight has undoubtedly prominent substantive characteristics and remarkable progress.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a traction takeoff method of a large unmanned aerial vehicle with winglet load.
Background
The traction takeoff technology is a mature technology for the existing man and machine, but due to the characteristics of the unmanned aerial vehicle, the traction takeoff technology is a new technology.
The unmanned aerial vehicle has various take-off modes, and the common mode of the small-sized aircraft is autonomous running take-off and landing; the aircraft is suitable for hand-throwing takeoff of a small-sized aircraft; catapult takeoff of small and medium-sized unmanned aerial vehicles; and in recent times, various odds of vertical take-off and landing. For large light unmanned aircraft with long flights of spans greater than 30 meters or more, take-off is a very complex, high risk problem, thus creating many unconventional approaches. For example, it is proposed to use a high altitude balloon to lift a huge unmanned aerial vehicle weighing hundreds of kilograms to a position 20 kilometers above the ground or to use a rocket to push the unmanned aerial vehicle to the high altitude. These approaches are not only very risky but also capital intensive. The manufacture of a large span drone, which can lift several hundred kilograms to 2 kilometers high altitude balloons, and the size of the balloon is as large as 180 meters long, 80 meters wide and 60 meters thick, is not only difficult to control in flight, but also extremely difficult and expensive to develop, and the challenge encountered in the process of ascending from ground to high altitude is an obstacle which is difficult to cross.
Disclosure of Invention
The invention provides a traction takeoff method of a large unmanned aerial vehicle with a winglet load, aiming at solving the problems of great risk and great investment of the existing takeoff method of the unmanned aerial vehicle.
The invention adopts the following technical scheme to solve the technical problem
The utility model provides a large-scale unmanned aerial vehicle of winglet load pulls system of taking off, includes draw gear, is pulled unmanned aerial vehicle, pulls the runway, draw gear pulling unmanned aerial vehicle to run on pulling the runway, liftoff take off and rise, unhook flight, its characteristics are: the traction device is suitable for the winglet-loaded large unmanned aerial vehicle to take off in a traction manner; the towed unmanned aerial vehicle is a winglet-loaded large unmanned aerial vehicle; the traction runway is a short-distance takeoff runway; the overload ratio and the lift-drag ratio of the unmanned aerial vehicle are suitable for short-distance traction takeoff; the traction device comprises traction power equipment, a traction rope and a traction hook.
2. The large unmanned aerial vehicle traction takeoff system with the loaded winglets as claimed in claim 1, wherein: the winglet-loaded large unmanned aerial vehicle is an unmanned aerial vehicle with wing load less than 8 kilograms per square meter, and the towing running ground clearance of the unmanned aerial vehicle when the unmanned aerial vehicle is towed is 20-150 meters, wherein the aircraft speed is accelerated from 0 to take-off speed; the length of the short-distance takeoff runway can be as short as about 100-150 meters; the takeoff speed of the liftoff takeoff ascending is preferably 30 km/h.
When the wing load of the large unmanned plane with the winglets loaded is less than 2 kilograms per square meter of airplane and the traction angle is 15-20 degrees, the large unmanned plane does not need to interfere with the takeoff process, and when the airplane ascends to reach the horizontal position, the traction cable can automatically unhook, and the unhooking height is 50-100 meters.
The overload ratio and the lift-drag ratio of the unmanned aerial vehicle are specifically as follows: the overload of the towed unmanned aerial vehicle is larger than 1.2, and the lift-drag ratio is larger than 15.
The towing hook can be divided into an open type lock hook and a closed type lock hook, the open type lock hook is suitable for small-sized light unmanned aerial vehicles, and the closed type lock hook is used for heavy unmanned aerial vehicles.
The open lock hook comprises an L-shaped traction hook with a cantilever, a traction ring and a triangular flag; one cantilever of the L-shaped towing hook is connected with the airplane, the towing ring is sleeved on the towing hook, and the triangular flag is connected with the towing ring; the end of the L-shaped towing hook is provided with a convex structure used for preventing the towing ring from sliding off the end; the traction ring body is connected with a triangular mark flag which is used for generating windward resistance and is convenient for separating the traction ring from the traction hook along the resistance direction to unhook;
the closed latch hook comprises a U-shaped towing hook with two cantilevers, a tensioning spring for connecting the two cantilevers of the U-shaped towing hook, a towing ring sleeved on the U-shaped towing hook, a triangular mark flag on a towing ring body, and an unlocking device and a telescopic rod acting on one cantilever of the U-shaped towing hook, wherein the unlocking device and the telescopic rod are used for overcoming the tensioning force generated by a pipe pulling spring to open the rocker arm.
The haulage rope is that the unmanned aerial vehicle that is fit for winglet load pulls to take off, specifically is: the haulage rope of light weight, high strength, low windage and resistant ground friction should be selected to the haulage rope for satisfy the pneumatic resistance of big aspect ratio, light structure, large-scale unmanned aerial vehicle to the haulage rope and the requirement of weight.
The towing hook is arranged in front of the center of gravity of the airplane, namely: the towing hook and the center of gravity of the airplane form an angle alpha forward; the angle α preferably ranges from α =15 ° -25 °, the angle α depending on the weight of the aircraft, the span dimensions and the magnitude of the wing loads; the smaller the alpha is, the faster the takeoff is, and the unmanned plane is suitable for winglet loading; the bigger the alpha angle is, the gentler the takeoff is, and the unmanned aerial vehicle is suitable for heavy load unmanned aerial vehicles.
A takeoff method of a traction takeoff system of an unmanned aerial vehicle based on winglet load and large wing span is characterized in that: the method comprises the following steps:
the method comprises the following steps that firstly, a towed airplane is a winglet-loaded large unmanned aerial vehicle;
secondly, a bearing point is set in front of the gravity center of the unmanned aerial vehicle to serve as a controllable traction hanging point;
thirdly, arranging a towing hook at the controllable towing hanging point, wherein the towing hook and the center of gravity of the airplane are in an angle of between alpha =15 and 25 degrees;
pulling the airplane to move forwards by utilizing a forward force applied to the towing hook by the towing device;
fourthly, the aircraft moves forward to reach the speed when the wing lift force is larger than the full weight of the aircraft, and the aircraft is lifted to a preset height;
step five, opening the device through the traction hook and simultaneously releasing the traction force to enable the traction rope to fall off;
and step six, flying the airplane according to various power modes after the traction rope falls off.
And in the sixth step, the traction rope is made to fall off through the traction hook opening device, and the specific process is as follows:
the method includes the steps that a traction rope is made to fall off through an open type lock hook opening device; the method specifically comprises the following steps:
(1) before taking off, the traction ring is arranged on an open type traction hook with a convex structure;
(2) when the traction angle is close to 80 degrees, the wind resistance of the traction force passing through the triangular flag is relaxed, and the traction ring belt is separated from the open type locking hook to be unhooked;
secondly, the traction rope falls off through the closed lock hook opening device; the method comprises the following specific steps:
(1) before taking off, the traction ring is arranged on the closed traction hook, and the lock is closed to ensure that the traction hook does not fall off in the whole traction taking-off process;
(2) when the unmanned aerial vehicle reaches a certain designated height and speed, the traction force is released, and meanwhile, the unlocking device overcomes the tension force generated by the tube pulling spring to open the rocker arm;
advantageous effects of the invention
1. The invention adopts the following technical means: the method comprises the technical means of adopting a winglet-loaded large-scale unmanned aerial vehicle with wing load less than 8 kilograms per square meter, the technical means of adopting an unmanned aerial vehicle with an overload ratio more than 1.2 and a lift-drag ratio more than 15, the technical means of adopting an open type lock hook to meet the take-off requirement of a small-sized light-weight unmanned aerial vehicle, the technical means of adopting a closed type lock hook to meet the take-off requirement of the heavy-duty unmanned aerial vehicle, the technical means of arranging a towing hook in front of the gravity center of the aircraft to meet the short-distance quick take-off requirement, and the technical means of adopting a towing rope with light weight, high strength, low wind resistance and ground friction resistance, so that a new technical scheme which is low in price, low in risk and easy to operate and aims at the large-scale light-scale unmanned aerial vehicle towing and taking off when the wingspan is more than 30 meters or more. The scheme is a simple, reliable and cheap take-off mode, and for the large-scale high-altitude light-structure unmanned aerial vehicle, the take-off mode can reduce a take-off threshold and is a good method.
2. The invention combines winglet load large-scale aircraft technology, high overload ratio and high lift-drag ratio technology and short-distance traction takeoff traction device technology (traction hook shape, traction hook position and traction rope) and all parts support and depend on each other, thereby forming a new technical scheme for solving the problem of light large-scale unmanned traction takeoff, realizing a simple, reliable and low-cost takeoff mode which can reduce the takeoff threshold and is a good method.
Drawings
FIG. 1 is a schematic view of a towing takeoff system of the present invention;
FIG. 2 is a schematic view of a towing takeoff mode of the present invention;
FIG. 3 is a schematic view of the open shackle of the present invention;
fig. 4 is a diagram illustrating an opened state of the closed shackle of the present invention;
fig. 5 is a schematic drawing of the position of the towing hook of the present invention.
In the figure, 1-1: a traction power plant; 1-2: a hauling rope; 1-311: an L-shaped towing hook; 1-312: a traction ring; 1-313: triangular flag; 1-321: a U-shaped towing hook; 1-322: tensioning the spring; 1-323: a traction ring; 1-324: triangular flag; 1-325: a rocker arm; 1-326: a telescopic pull rod; 1-327: a lock opener; 2: a towed aircraft; 3: dragging the runway; 4: unmanned aerial vehicle organism structure.
Detailed Description
The invention is further explained below with reference to the drawings.
1. Interpretation of several nouns
1. Wing loading: the weight of the airplane is divided by the area of the wing;
2. a mainframe: refers to the size of the aircraft;
3. winglet loading mainframe: the airplane is light in weight and large in size.
2. The design principle of the invention is as follows:
the design of the invention is designed to solve the problems of great risk and great investment of the take-off method of the large light unmanned aerial vehicle with the wingspan of more than 30 meters or more during long-endurance flight in the prior art, and the take-off method of the unmanned aerial vehicle with high safety and low cost is adopted, and the safety and the low cost are realized around five aspects:
first, wing load requirements: the traction takeoff is suitable for the unmanned plane with small wings, the wing load of the unmanned plane is less than 8 kilograms per square meter, the smaller the wing load is, the shorter the takeoff distance of the airplane is, so that the use field is shorter, and the short-distance takeoff runway is realized. This is one of the principles of the present invention to achieve safety and low cost.
Second, the requirements for the aircraft. The strength and lift-drag ratio of the towed aircraft determine whether a tow takeoff can be used. For the unmanned aerial vehicle with the overload of less than 1.2 and the unmanned aerial vehicle with the lift-drag ratio of less than 15, the unmanned aerial vehicle with the overload of less than 1.2 can cause damage and damage due to traction takeoff, and the aircraft with the lift-drag ratio of less than 15 needs a longer traction runway, so the traction takeoff is not suitable. The unmanned aerial vehicle with the overload of less than 1.2 and the lift-drag ratio of less than 15 is adopted, and the principle is the second principle of realizing safety and low cost.
Thirdly, the shape of the towing hook is required. The design of the towing hook is suitable for the safety requirements of light and heavy airplanes. The towing hook can be divided into an open type locking hook and a closed type locking hook. Open latch hook is applicable to small-size light-duty unmanned aerial vehicle, and the closed latch hook is used for heavier unmanned aerial vehicle: the vibration amplitude of the airplane in the running process is in direct proportion to the weight of the airplane, the small-sized light unmanned aerial vehicle has small jumping amplitude in the running process, and the airplane is not unhooked due to large jumping in the running process, so that the small-sized light unmanned aerial vehicle is suitable for adopting an open latch hook; and heavy type unmanned aerial vehicle is beated the range comparatively great and is unhook easily at the rolloff in-process, consequently is fit for adopting closed latch hook to heavy type unmanned aerial vehicle. The invention adopts a proper towing hook to ensure safety and simplicity according to the difference of light weight and heavy weight of the airplane, which is the third principle of realizing safety and low cost.
And fourthly, requirements on a traction rope. The weight of the hauling rope is considerable, and for a large aspect ratio, a light structure and a large unmanned aerial vehicle, the pneumatic resistance and the weight of the hauling rope are a big challenge, so the hauling rope with light weight, high strength, low wind resistance and ground friction resistance should be selected. The four principles of the invention for achieving safety and low cost are to select a traction rope which is light in weight, high in strength, low in wind resistance and resistant to ground friction.
And fifthly, meeting the position requirement of the traction hook. The position of the towing hook is related to the type of towing power, if the towing hook is towed by an airplane, the towing hook is generally arranged at the lower part of the head of the airplane, and if the towing hook is towed by a winch or an automobile, the towing hook is arranged in front of the gravity center of the airplane and can be arranged at the position not concentric with or behind the gravity center of the airplane. The towing hook of the embodiment of the invention is arranged at an angle alpha in front of the center of gravity of the airplane, and is inclined forwards (forwards is a towing direction) at an angle alpha = 15-25 degrees with the center of gravity of the airplane, and the size of the angle alpha depends on the weight, the wingspan size and the wing load of the airplane. The smaller alpha is, the faster the takeoff is, and the aircraft is suitable for winglet-loaded aircrafts. The larger the alpha angle is, the gentler the takeoff is, so that the traction distance is relatively longer, and the aircraft with large wing load is suitable for the aircraft. For a large drone flying off with an airplane, the angle α is almost 90 °. The principle of the invention for realizing safety and low cost is five, wherein a smaller alpha traction angle is adopted to adapt to the fast flying and the small traction distance of the winglet-loaded large-scale airplane.
The principle of the invention is summarized as follows: winged-loaded aircraft, aircraft with an overload ratio higher than 1.2, aircraft with a lift-to-drag ratio greater than 15, lightweight and high-strength tow ropes, the shape of tow hooks suitable for short take-off, and the location of tow hooks suitable for short take-off. The points are combined, and all parts support and depend on each other, so that the technical scheme of low-cost and high-safety traction takeoff for the winglet-loaded large unmanned aerial vehicle is formed.
Based on the principle, the invention designs a winglet-loaded large-scale unmanned aerial vehicle traction take-off system.
As shown in fig. 1, a winglet load large unmanned aerial vehicle traction takeoff system comprises a traction device, a towed unmanned aerial vehicle 2 and a towing runway 3, wherein the traction device pulls the unmanned aerial vehicle to run on the towing runway 3, take off from the ground, ascend, and fly unhooked, and is characterized in that: the traction device is suitable for the winglet-loaded large unmanned aerial vehicle to take off in a traction manner; the towed unmanned aerial vehicle is a winglet-loaded large unmanned aerial vehicle; the traction runway is a short-distance takeoff runway; the overload ratio and the lift-drag ratio of the unmanned aerial vehicle are suitable for short-distance traction takeoff; the traction device comprises traction power equipment, a traction rope and a traction hook.
The winglet-loaded large unmanned aerial vehicle is an unmanned aerial vehicle with wing load less than 8 kilograms per square meter, and the distance from the ground for towing and sliding of the unmanned aerial vehicle when the unmanned aerial vehicle is towed and the aircraft speed is accelerated from 0 to take-off speed is 20-150 meters; the length of the short-distance takeoff runway can be as short as about 100-150 meters; the lift-off speed for lift-off and rising lift-off is preferably 30-40 km/h.
When the wing load of the large unmanned plane with the winglets loaded is less than 2 kilograms per square meter of airplane and the traction angle is 15-20 degrees, the large unmanned plane does not need to interfere with the takeoff process, and when the airplane ascends to reach the horizontal position, the traction cable can automatically unhook, and the unhooking height is 50-100 meters.
The overload ratio and the lift-drag ratio of the unmanned aerial vehicle are specifically as follows: the overload of the towed unmanned aerial vehicle is larger than 1.2, and the lift-drag ratio is larger than 15.
The towing hook can be divided into an open type lock hook and a closed type lock hook, the open type lock hook is suitable for small-sized light unmanned aerial vehicles, and the closed type lock hook is used for heavy unmanned aerial vehicles.
As shown in fig. 3, the open type lock hook comprises an L-shaped towing hook 1-311 with a cantilever, a towing ring 1-312 and a triangular flag 1-313; one cantilever of the L-shaped towing hook 1-311 is connected with the airplane, the towing ring is sleeved on the towing hook, and the triangular flag 1-313 is connected with the towing ring 1-312; the end of the L-shaped towing hook 1-311 is provided with a convex structure used for preventing the towing ring from slipping off the end; a triangular mark flag is connected to the traction ring 1-312, and is used for generating windward resistance so as to facilitate the unhooking of the traction ring from the traction hook along the resistance direction;
as shown in fig. 4, the closed latch hook comprises a U-shaped towing hook 1-321 with two cantilevers, a tension spring 1-322 connecting the two cantilevers of the U-shaped towing hook, a towing ring 1-323 sleeved on the U-shaped towing hook, a triangular flag 1-324 on a ring body of the towing ring, an unlocking device 1-327 acting on one cantilever of the U-shaped towing hook and an expansion link 1-326, wherein the unlocking device 1-327 and the expansion link 1-326 are used for overcoming the tension force generated by the pipe pulling spring to open the rocker arm.
The haulage rope is that the unmanned aerial vehicle that is fit for winglet load pulls to take off, specifically is: the haulage rope of light weight, high strength, low windage and resistant ground friction should be selected to the haulage rope for satisfy the requirement of big aspect ratio, light structure, large-scale unmanned aerial vehicle to the aerodynamic drag and the weight of haulage rope.
As shown in fig. 5, the towing hook (1-311, 1-321) is arranged in front of the center of gravity of the airplane, namely: the towing hook and the center of gravity of the airplane form an angle alpha forward; the angle α preferably ranges from α =15 ° -25 °, the angle α depending on the weight of the aircraft, the span dimensions and the magnitude of the wing loads; the smaller the alpha is, the faster the takeoff is, and the unmanned plane is suitable for winglet loading; the bigger the alpha angle is, the gentler the takeoff is, and the unmanned aerial vehicle is suitable for heavy load unmanned aerial vehicles.
A takeoff method based on winglet load large-span unmanned aerial vehicle traction takeoff system is shown in fig. 2:
the method comprises the following steps:
the method comprises the following steps that firstly, a towed airplane is a winglet-loaded large unmanned aerial vehicle;
secondly, a bearing point is set in front of the gravity center of the unmanned aerial vehicle to serve as a controllable traction hanging point;
thirdly, arranging a traction hook at the controllable traction hanging point, wherein the traction hook and the center of gravity of the airplane form a forward-inclined angle, and the angle is alpha = 15-25 degrees;
pulling the airplane to move forwards by utilizing a forward force applied to the towing hook by the towing device;
fourthly, the aircraft moves forward until the wing lift force is higher than the speed of the aircraft when the aircraft is full weight, and the aircraft is lifted to a preset height;
step five, opening the device through the traction hook and simultaneously releasing the traction force to enable the traction rope to fall off; (ii) a
And step six, flying the airplane according to various power modes after the traction rope falls off.
And in the sixth step, the traction rope is made to fall off through the traction hook opening device, and the specific process is as follows:
the method includes the steps that a traction rope is made to fall off through an open type lock hook opening device; the method specifically comprises the following steps:
(1) before taking off, the traction ring is arranged on an open type traction hook with a convex structure;
(2) when the traction angle is close to 80 degrees, the traction force is relaxed, and the traction ring belt is separated from the open type locking hook to be unhooked through the wind resistance of the triangular flag;
secondly, the traction rope falls off through the closed lock hook opening device; the method comprises the following specific steps:
(1) before taking off, the traction ring is arranged on the closed traction hook, and the lock is closed to ensure that the traction hook does not fall off in the whole traction taking-off process;
(2) when the unmanned aerial vehicle reaches a certain designated height and speed, the traction force is released, and meanwhile, the unlocking device overcomes the tension force generated by the tube pulling spring to open the rocker arm;
it should be emphasized that the embodiments described herein are illustrative and not restrictive, and thus the invention includes, but is not limited to, those embodiments described in the detailed description.
Claims (5)
1. The utility model provides a large-scale unmanned aerial vehicle of winglet load pulls system of taking off, includes draw gear, is pulled unmanned aerial vehicle, pulls the runway, draw gear pulling unmanned aerial vehicle runs on pulling the runway, liftoff take off and rise, unhook flight, its characterized in that: the traction device is suitable for the winglet-loaded large unmanned aerial vehicle to take off in a traction manner; the towed unmanned aerial vehicle is a winglet-loaded large unmanned aerial vehicle, namely a winglet-loaded large unmanned aerial vehicle with wing load less than 8 kilograms per square meter, span greater than 30 meters, overload ratio higher than 1.2 and lift-drag ratio greater than 15; the traction device comprises a traction rope and a traction hook;
when the unmanned aerial vehicle is towed and the speed of the airplane is accelerated from 0 to the liftoff takeoff speed, the towing running liftoff distance of liftoff takeoff is 20-150 meters; the traction runway is a short-distance takeoff runway; the length of the short-distance takeoff runway is 100-150 meters; the takeoff speed of the liftoff takeoff ascending is 30-40 km/h;
the haulage rope is that the unmanned aerial vehicle that is fit for winglet load pulls to take off, specifically is: the hauling rope is light in weight, high in strength, low in wind resistance and resistant to ground friction, and is used for meeting the requirements of large aspect ratio, light structure and large unmanned aerial vehicle on pneumatic resistance and weight of the hauling rope;
the traction hook is divided into an open type lock hook and a closed type lock hook, the open type lock hook is suitable for the lighter unmanned aerial vehicle, and the closed type lock hook is used for the heavier unmanned aerial vehicle;
the open lock hook comprises an L-shaped traction hook with a cantilever, a traction ring and a triangular flag; one cantilever of the L-shaped towing hook is connected with the airplane, the towing ring is sleeved on the towing hook, and the triangular flag is connected with the towing ring; the end of the L-shaped towing hook is provided with a convex structure used for preventing the towing ring from sliding off the end; the traction ring body is connected with a triangular mark flag which is used for generating windward resistance and is convenient for separating the traction ring from the traction hook along the resistance direction to unhook;
the closed latch hook comprises a U-shaped towing hook with two cantilevers, a tensioning spring for connecting the two cantilevers of the U-shaped towing hook, a towing ring sleeved on the U-shaped towing hook, a triangular mark flag on a towing ring body, and an unlocking device and a telescopic rod acting on one cantilever of the U-shaped towing hook, wherein the unlocking device and the telescopic rod are used for overcoming the tensioning force generated by a pipe pulling spring to open the rocker arm.
2. The large unmanned aerial vehicle tractive take-off system of claim 1, wherein: when the wing load of the large-scale unmanned aerial vehicle with the winglet load is less than 2 kilograms per square meter and the traction angle is 15 0 -20 0 In time, the aircraft is pulled when the aircraft rises to reach the horizontal position without interfering the takeoff processThe leader can automatically unhook.
3. The large unmanned aerial vehicle tractive take-off system of claim 1, wherein: the tow hook sets up before the unmanned aerial vehicle focus, promptly: the towing hook and the gravity center of the unmanned aerial vehicle forwards form an alpha angle, and the alpha angle range is alpha =15 0 -25 0 The angle alpha depends on the weight of the drone, the span dimensions and the magnitude of the wing load.
4. A winglet load large unmanned plane traction takeoff method based on the winglet load large unmanned plane traction takeoff system of any one of claims 1 to 3, characterized in that: the method comprises the following steps:
step one, a bearing point is arranged in front of the gravity center of the unmanned aerial vehicle and is used as a controllable traction hanging point;
step two, arranging a traction hook at the controllable traction hanging point, wherein the traction hook and the gravity center of the unmanned aerial vehicle forwards form an alpha angle, and the alpha angle range is 15 0 -25 0 ；
Pulling the unmanned aerial vehicle to move forwards by utilizing a forward force applied to the towing hook by the towing device;
fourthly, the unmanned aerial vehicle moves forward to reach the takeoff speed when the wing lift force is larger than the full weight of the aircraft, and the unmanned aerial vehicle is lifted to the preset height;
step five, loosening the traction force to enable the traction rope to fall off from the traction hook;
and step six, flying the unmanned aerial vehicle according to various power modes after the traction rope falls off.
5. The method for towing and taking off of large unmanned aerial vehicle with loaded winglets as claimed in claim 4, wherein the method comprises the following steps: and step five, loosening the traction force to enable the traction rope to fall off from the traction hook, and the specific process is as follows:
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| FR3128208A1 (en) * | 2021-10-14 | 2023-04-21 | Loravia | TAKE-OFF AND CLIMB ASSISTANCE OF TRANSPORT AIRCRAFT BY TRACTION USING A CABLE |
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| US3392937A (en) * | 1966-11-02 | 1968-07-16 | Bliss E W Co | Catapult system and method of launching vehicles |
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| CN204297115U (en) * | 2014-06-09 | 2015-04-29 | 李岗 | A kind of aircraft short field take-off help-fly lock |
| CN104401493A (en) * | 2014-11-27 | 2015-03-11 | 张峰 | Cabin type guide rope locked aircraft carrier for releasing and recycling airborne aircraft |
| CN104494841B (en) * | 2014-12-16 | 2016-10-12 | 董兰田 | Compound electric unit power turns strap towing aircraft ejector |
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| US3392937A (en) * | 1966-11-02 | 1968-07-16 | Bliss E W Co | Catapult system and method of launching vehicles |
| CN2866334Y (en) * | 2005-06-17 | 2007-02-07 | 廖志明 | Efficient aircraft carrier projectile device |
| CN201406026Y (en) * | 2009-06-05 | 2010-02-17 | 中国航空工业集团公司西安飞机设计研究所 | Traction hook device |
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