A separable flying wing layout unmanned aerial vehicle

Abstract

The present invention discloses a separable flying wing layout unmanned aerial vehicle, including a flying wing layout unmanned main aerial vehicle located in the middle, flying wing layout unmanned sub-aviation vehicles seamlessly and symmetrically arranged on the left and right sides along the central axis of the flying wing layout unmanned main aerial vehicle, a main engine connecting rod fixedly connected to the lower wing surface of the flying wing layout unmanned main aerial vehicle at one end, and a sub-machine separation mechanism fixedly connected to the lower wing surface of the flying wing layout unmanned sub-aviation vehicle and detachably connected to the other end of the main engine connecting rod. During the flight, the sub-machine separation mechanism is separated from the main engine connecting rod to realize the separation of the flying wing layout unmanned main aerial vehicle and the flying wing layout unmanned sub-aviation vehicle. Based on the original load and mission, the present invention can split an aircraft into multiple small aircraft on the way to perform a mission, and apply it to military and civilian fields through multi-UAV cluster control technology.

Description

Technical Field

[0001] The invention relates to an aircraft, and in particular to an unmanned aircraft with a separable flying wing layout. Background Art

[0002] UAVs have a wide range of applications in both military and civilian fields. As the application prospects of UAVs become more and more extensive, their application environments are becoming more and more complex, and the requirements for UAVs are becoming higher and higher. The stealth, internal space utilization and lift-to-drag ratio of existing fixed-wing aircraft are not as good as those of flying-wing aircraft. In addition, due to technical limitations such as load capacity restrictions, it is generally difficult for a single UAV to simultaneously have the capabilities of reconnaissance and search, target attack, air combat or electronic suppression, and it cannot meet complex multi-task requirements.

[0003] Therefore, the separable flying wing layout unmanned aerial vehicle will be an important research direction in the field of UAVs in the future. It can be equipped with different individual flying wing layout unmanned aerial vehicles on demand to meet multi-task requirements, and combine them into a large flying wing layout unmanned aerial combination platform, which can flexibly adapt to various flight altitudes, flight speed ranges, flight missions and other requirements, and has many application scenarios.

[0004] The split combination of aircraft involves the design of separation and combination devices and control, and requires a powerful flight control program to support it. There is little research on this at home and abroad. In recent years, with the development of various technologies, some scholars at home and abroad have completed the design and applied for patents for this technical goal, but the research content is only for the split combination of rotorcraft and conventional layout aircraft, and most of the research can only realize the function of the combination splitting and flying independently during flight, while there is less research on other aircraft.

[0005] The entire process of the combined aircraft separating into the main aircraft and the sub-aircraft is in an unsteady flow field. How to ensure the stable connection between the main aircraft and the sub-aircraft during combined flight, and the impact of unsteady airflow on the aircraft during separation are the key issues that need to be addressed.

[0006] Therefore, it is urgent to solve the above problems. Summary of the invention

[0007] Purpose of the invention: The purpose of the present invention is to provide a separable flying wing layout unmanned aerial vehicle that can be equipped with individual flying wing layout unmanned aerial vehicles with different aerodynamic shapes and different mission loads as needed to meet multi-mission requirements.

[0008] Technical solution: To achieve the above objectives, the present invention discloses a separable flying wing layout unmanned aerial vehicle, comprising a flying wing layout unmanned aerial vehicle located in the middle, flying wing layout unmanned aerial vehicles (UAVs) seamlessly and symmetrically arranged on the left and right sides along the central axis of the flying wing layout unmanned aerial vehicle, a main engine connecting rod fixedly connected to the lower wing surface of the flying wing layout unmanned aerial vehicle at one end, and a sub-aircraft separation mechanism fixedly connected to the lower wing surface of the flying wing layout unmanned aerial vehicle and detachably connected to the other end of the main engine connecting rod. During the flight, the sub-aircraft separation mechanism is disengaged from the main engine connecting rod to achieve the separation of the flying wing layout unmanned aerial vehicle and the flying wing layout unmanned aerial vehicle.

[0009] Among them, the flying wing layout unmanned main aircraft includes an wing-shaped inner fuselage, an wing-shaped outer fuselage, wings, leading edge slats, main ailerons, ducted fans, V-shaped tail fins and horizontal control surfaces, and there is an angle between the wing-shaped outer fuselage and the wings; the flying wing layout unmanned sub-aircraft vehicle includes a wing-shaped fuselage, sub-ailerons and a vertical tail fin, and the flying wing layout unmanned sub-aircraft vehicle is seamlessly arranged between the wing-shaped outer fuselage and the wing, and the chord line of the symmetry surface of the wing-shaped fuselage of the flying wing layout unmanned sub-aircraft vehicle is collinear with the chord line of the intersection surface of the wing and the wing-shaped outer fuselage of the flying wing layout unmanned main aircraft.

[0010] Preferably, the leading edge sweep angles of the flying wing layout unmanned main aircraft and the flying wing layout unmanned sub-aircraft are the same, and the angle between the wing-shaped outer fuselage and the wing is twice the leading edge sweep angle.

[0011] Furthermore, the span of the wing-shaped fuselage of the flying-wing layout unmanned aerial vehicle is twice the span length of the wing-shaped outer fuselage of the flying-wing layout unmanned aerial vehicle.

[0012] Furthermore, the wing-shaped inner fuselage, the wing-shaped outer fuselage, the wing and the leading edge slat are fixedly connected in sequence, the main ailerons are movably connected to the wings, the horizontal control surfaces are movably connected to the wing-shaped inner fuselage, the ducted fan is fixedly connected to the wing-shaped inner fuselage and the wing-shaped outer fuselage, and the V-shaped tail includes a V-shaped tail stabilizer and a V-shaped tail control surface that are movably connected to each other, wherein the V-shaped tail stabilizer is fixedly connected to the ducted fan.

[0013] Preferably, the wing-shaped fuselage and the aileron are movably connected, and the vertical tail comprises a vertical tail stabilizer and a vertical tail control surface which are movably connected to each other, wherein the vertical tail stabilizer is fixedly connected to the wing-shaped fuselage.

[0014] The cam is engaged with the cam and the cam is engaged with the cam, and the cam is engaged with the cam and the cam is engaged with the cam, and the cam is engaged with the cam and the cam is engaged with the cam.

[0015] Furthermore, the slide rail is provided with a slide rail groove for the slider to slide in and out and an assembly groove for clamping and fixing the end cover. The width of both ends of the slide rail groove is greater than the width of the middle section. The assembly grooves are respectively located on the upper and lower surfaces in the middle of the slide rail.

[0016] Furthermore, the slider includes a baffle portion for abutting the spring, a host connecting hole opened on the baffle portion and used to pass the host connecting rod, a support rod connecting hole opened on the baffle portion and used to pass the spring support rod, and a slider head symmetrically arranged on both sides of the baffle portion and used to pass through the slide rail and move along the slide rail.

[0017] Furthermore, the spring support rod includes a stop block located in the middle, long rods symmetrically arranged on both sides of the stop block and used to pass the spring, and an upper connecting rod located above the resistance block and used to connect and fix the end cover.

[0018] Beneficial effects: Compared with the prior art, the present invention has the following significant advantages: the present invention can meet the needs of multiple tasks, replace individual flying wing layout unmanned aerial vehicles with different aerodynamic shapes and different mission loads as needed, and combine them into a large flying wing layout unmanned aerial vehicle combination platform, so as to flexibly adapt to various flight altitudes, flight speeds, flight missions and other needs, and has many application scenarios, such as long-distance voyages and return flights in combination, large-scale reconnaissance and detection tasks in the mission area in a split manner, multi-machine multi-task coordinated operations, large-scale soft and hard killing attacks, etc.; because of the high aerodynamic efficiency and load capacity of the individual and combined platforms, The advantages of strong weight capacity, when combined into one, the aircraft can fly long range and long flight time, which is beneficial to expand the combat radius of the aircraft and enhance its combat capability; when the individuals are separated, they can be split and coordinated for combat, with the characteristics of high maneuverability and high flexibility, and the use of multi-UAV multi-task collaborative control technology can complete more complex collaborative combat tasks; at the same time, the high aerodynamic efficiency of the combined aircraft and the high maneuverability of the separated aircraft can solve the contradiction between the aerodynamic efficiency and maneuverability of the aircraft to a certain extent; finally, the sub-aircraft separation mechanism of the present invention can effectively ensure the dynamic separation of the main aircraft and the sub-aircraft in the flight state. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a structural schematic diagram of the present invention;

[0020] Figure 2 A three-dimensional schematic diagram of the flying wing layout unmanned main aircraft and the flying wing layout unmanned sub-aircraft flying after separation in the present invention;

[0021] Figure 3 It is a three-dimensional schematic diagram of the present invention;

[0022] Figure 4 A top view of the present invention;

[0023] Figure 5 It is a structural schematic diagram of the host connecting rod in the present invention;

[0024] Figure 6 The structure diagram of the neutron machine separation mechanism of the present invention is shown in FIG. Figure 1 ;

[0025] Figure 7 It is a structural schematic diagram of the slide rail in the present invention;

[0026] Figure 8 It is a structural schematic diagram of the slider in the present invention;

[0027] Fig. 9 It is a structural schematic diagram of the spring support rod in the present invention;

[0028] Fig.10 It is a structural schematic diagram of the limiting rod in the present invention;

[0029] Fig.11 It is a schematic diagram of the structure of the fixed end cover in the present invention;

[0030] Fig.12 Schematic diagram of the connection between the host connecting rod and the sub-machine separation mechanism in the present invention Figure 1 ;

[0031] Fig.13 Schematic diagram of the connection between the host connecting rod and the sub-machine separation mechanism in the present invention Figure 2 ;

[0032] Fig.14 The structure diagram of the neutron machine separation mechanism of the present invention is shown in FIG. Figure 2 . DETAILED DESCRIPTION

[0033] The technical solution of the present invention is further described below in conjunction with the accompanying drawings.

[0034] like Figure 2 , Figure 3 and Figure 4 As shown, a separable flying wing layout unmanned aerial vehicle of the present invention comprises a flying wing layout unmanned main aerial vehicle 1, a flying wing layout unmanned sub-aviation vehicle 2, a main engine connecting rod 3 and a sub-aviation separation mechanism 4, wherein the flying wing layout unmanned main aerial vehicle 1 is located in the middle, and the flying wing layout unmanned sub-aviation vehicle 2 is seamlessly and symmetrically arranged on the left and right sides along the central axis of the flying wing layout unmanned main aerial vehicle 1, one end of the main engine connecting rod 3 is fixedly connected to the lower wing surface of the flying wing layout unmanned main aerial vehicle, and the other end of the main engine connecting rod 3 is detachably connected to the sub-aviation separation mechanism 4, and the sub-aviation separation mechanism 4 is fixedly connected to the lower wing surface of the flying wing layout unmanned sub-aviation vehicle; wherein the main engine connecting rod 3 and the sub-aviation separation mechanism 4 can be symmetrically arranged in three groups on the left and right sides. During the flight, the sub-aviation separation mechanism 4 is separated from the main engine connecting rod 3 to realize the separation of the flying wing layout unmanned main aerial vehicle 1 and the flying wing layout unmanned sub-aviation vehicle 2. When the flying wing layout unmanned main aircraft 1 is combined with two flying wing layout unmanned sub-aircraft 2, the unique large lift surface of the flying wing aircraft can support its long-duration and long-range flight, which is beneficial to expanding the combat radius of the aircraft and enhancing its combat capability.

[0035] like Figure 1As shown, the flying wing layout unmanned main aircraft 1 of the present invention includes an aerofoil-type inner fuselage 101, an aerofoil-type outer fuselage 102, wings 103, leading edge slats 104, main ailerons 105, horizontal control surfaces 106, ducted fans 107 and V-shaped tail 108. The wing-shaped inner fuselage 101, the wing-shaped outer fuselage 102, the wing 103 and the leading edge slat 104 are fixedly connected in sequence, the main aileron 105 and the wing 103 are movably connected to be deflected by additional rudder sheets, the horizontal rudder 106 and the wing-shaped inner fuselage 101 are movably connected to be deflected by additional rudder sheets, the ducted fan 107 is fixedly connected to the wing-shaped inner fuselage 101 and the wing-shaped outer fuselage 102, and the V-tail 108 includes a V-tail stabilizer and a V-tail control surface which are movably connected to each other by additional rudder sheets, wherein the V-tail stabilizer is fixedly connected to the ducted fan 107. The flying wing layout unmanned sub-aircraft 2 comprises a wing-shaped fuselage 201, a vertical tail 202 and a sub-aileron 203, the wing-shaped fuselage 201 and the sub-aileron 203 are rotatably connected by an additional rudder sheet, the vertical tail 202 comprises a vertical tail stabilizer and a vertical tail control surface which are rotatably connected by an additional rudder sheet, wherein the vertical tail stabilizer is fixedly connected to the wing-shaped fuselage 201. In the present invention, there is an angle between the wing-shaped outer fuselage 102 and the wing 103; the leading edge sweep angles of the flying wing layout unmanned main aircraft 1 and the flying wing layout unmanned sub-aircraft 2 are the same, and the angle is α, 15°≤α≤60°; the angle between the wing-shaped outer fuselage 102 and the wing 103 is twice the leading edge sweep angle, and the angle is 2α. The flying wing layout unmanned aircraft 2 is seamlessly arranged between the wing-shaped outer fuselage 101 and the wing 103, and the symmetry plane chord line of the wing-shaped fuselage 201 of the flying wing layout unmanned aircraft 2 is colinear with the chord line of the intersection plane of the wing 103 and the wing-shaped outer fuselage 102 of the flying wing layout unmanned aircraft 1. The span of the wing-shaped fuselage 201 of the flying wing layout unmanned aircraft 2, that is, the wing span of the flying wing layout unmanned aircraft 2, is twice the length of the wing-shaped outer fuselage 102 of the flying wing layout unmanned aircraft 1 along the wing span, so that the sizes of the flying wing layout unmanned aircraft 1 and the flying wing layout unmanned aircraft 2 match each other, and the flying wing layout unmanned aircraft 2 can be seamlessly arranged between the wing-shaped outer fuselage 102 and the wing section 103 of the flying wing layout unmanned aircraft 1. At this time, one side of the tip of the wing-type fuselage 201 of the flying-wing layout unmanned aerial vehicle 2 is located in the same plane with the root of the wing-type outer fuselage 102 of the flying-wing layout unmanned aerial vehicle 1, and the other side is located in the same plane with the root of the main aileron 105 of the flying-wing layout unmanned aerial vehicle 1, and it is ensured that the chord line of the symmetry surface of the wing-type fuselage 201 of the flying-wing layout unmanned aerial vehicle 2 is collinear with the chord line of the intersection surface of the wing 103 and the wing-type outer fuselage 102 of the flying-wing layout unmanned aerial vehicle 1.

[0036] In the combined state, the power and control are both derived from the flying wing layout unmanned main aircraft 1, and the power is derived from the two ducted fans 107 of the flying wing layout unmanned main aircraft 1. The V-shaped tail stabilizer of the flying wing layout unmanned main aircraft 1 controls the lateral stability of the aircraft, the V-shaped tail control surface controls the lateral maneuverability of the aircraft, the horizontal rudder surface 106 controls the pitch maneuverability of the aircraft, and the main aileron 105 controls the roll maneuverability of the flying wing layout unmanned combination aircraft. The leading edge slats 104 of the flying wing layout unmanned main aircraft 1 can effectively improve the poor pitch stability of the flying wing layout aircraft. After separation, the flying wing layout unmanned main aircraft 1 is mainly responsible for command, bombing and other combat tasks due to its large size and larger internal space; after separation, the flying wing layout unmanned sub-aircraft 2 is mainly responsible for reconnaissance, strike, escort and other tasks due to the good maneuverability of its appearance design. The large lifting surface of the wing-shaped fuselage 201 of the flying wing layout unmanned sub-aircraft 2 provides sufficient lift, and its vertical tail stabilizer controls the lateral stability of the aircraft, and the vertical tail control surface controls the lateral maneuverability of the aircraft; the sub-aileron 203 that can perform differential action controls the stability and maneuverability of the pitch and roll of the aircraft. Based on the original load and mission, the present invention can split an aircraft into multiple small aircraft on the way to perform a mission, and apply it to military and civilian fields through multi-UAV cluster control technology.

[0037] like Figure 5 , Figure 6 and Fig.14 As shown, the sub-machine separation mechanism 4 includes two sliders 401, two slide rails 402, a fixed end cover 403, a spring support rod 404, two springs 405, a servo 406 and a limit rod 407. The main machine connecting rod 3 is provided with a front cross bar 301, a middle cross bar 302 and a rear cross bar 303. The lower wing surface of the flying wing layout unmanned main aircraft is provided with a connecting groove for passing the front cross bar 301 and the rear cross bar 302. The cross bar can reduce the moment on the main machine connecting rod to avoid excessive bending moment. The front cross bar 301 and the middle cross bar 302 of the main machine connecting rod 3 are bonded and fixed to the connecting groove on the lower wing surface of the flying wing layout unmanned main aircraft. The rear cross bar 303 of the main machine connecting rod 3 is symmetrically provided with two sliders 401. The two slide rails 402 are fixedly arranged on the lower wing surface of the flying wing layout unmanned sub-aircraft at intervals. The sliders 401 can slide inward and outward along the slide rails. Figure 8As shown, the slider 401 includes a baffle portion 4011, a host connection hole 4012, a support rod connection hole 4013 and a slider head 4014. The baffle portion 4011 is used to abut against the spring 405. The host connection hole 4012 is opened on the baffle portion 4011. The host connection rod 3 is penetrated through the host connection hole 4012. The support rod connection hole 4013 is opened on the baffle portion 4011. The spring support rod 404 is penetrated through the support rod connection hole 4013; the slider heads 4014 are symmetrically arranged on both sides of the baffle portion 4011. The slider heads 4014 are used to penetrate in the slide rail 402 and move along the slide rail 402. Figure 7 As shown, the slide rail 402 is provided with a slide rail groove 4021 for the slider 401 to slide in and out and an assembly groove 4022 for clamping and fixing the end cover 403. The width of both ends of the slide rail groove 4021 is greater than the width of the middle section, which is convenient for the installation of the slider head 4014. The assembly groove 4022 is respectively located on the upper and lower surfaces of the middle of the slide rail. Fig.11 As shown, the middle of the lower surface of the fixed end cover 403 is provided with an end cover connection hole 4031 connected to the upper connection rod 4043 of the spring support rod 404, and both ends of the fixed end cover 403 are provided with bosses 4032 connected to the slide rails 402. The fixed end cover 403 spans over the two slide rails 402 and is clamped with the slide rails 402. Fig. 9 As shown, the spring support rod 404 includes a stopper 4041, two long rods 4042 and an upper connecting rod 4043. The upper connecting rod 4043 of the spring support rod 404 is connected to the end cover connecting hole 4031 of the fixed end cover 403. A spring 405 is sleeved on the long rod 4042 of the spring support rod 404. The long rod 4042 passes through the support rod connecting hole 4013 of the slider 401. One end of the spring 405 abuts on the baffle portion 4011, and the other end of the spring 405 abuts on the stopper 4041. Fig.10 As shown, the steering gear 406 is fixed on the lower wing surface of the flying wing layout unmanned aerial vehicle, and the limit rod 407 is connected to the output end of the steering gear 406. The limit rod 407 is provided with two limit blocks 4071 arranged at intervals. Fig.12 and Fig.13 As shown, in the initial state, the two limit blocks 4071 of the limit rod 407 abut against the outer sides of the two sliders and compress the spring to ensure that the slider is inserted into the main engine connecting rod. The servo 406 is started, driving the limit rod 407 to rotate, releasing the limit constraint of the slider 402, and the slider 402 moves to the two ends of the slide rail 402 under the rebound force of the spring 405, and the slider 401 is separated from the tail end of the main engine connecting rod 3, and the flying wing layout unmanned sub-aircraft 2 is separated from the flying wing layout unmanned main aircraft 1.

Claims

1. A detachable flying wing layout unmanned aerial vehicle, characterized in that: The invention comprises a flying wing layout unmanned main aircraft (1) located in the middle, flying wing layout unmanned sub-aircraft (2) seamlessly and symmetrically arranged on the left and right sides along the central axis of the flying wing layout unmanned main aircraft, a main engine connecting rod (3) having one end fixedly connected to the lower wing surface of the flying wing layout unmanned main aircraft, and a sub-aircraft separation mechanism (4) fixedly connected to the lower wing surface of the flying wing layout unmanned sub-aircraft and detachably connected to the other end of the main engine connecting rod. During flight, the sub-aircraft separation mechanism (4) is separated from the main engine connecting rod (3) to achieve separation of the flying wing layout unmanned main aircraft (1) and the flying wing layout unmanned sub-aircraft (2); the sub-aircraft separation mechanism (4) comprises a slider (401) symmetrically arranged at the rear end of the main engine connecting rod (3), a slide rail (402) fixedly connected to the lower wing surface of the flying wing layout unmanned sub-aircraft and capable of allowing the corresponding slider to slide inward and outward, and a transverse slide rail (403) fixedly connected to the lower wing surface of the flying wing layout unmanned sub-aircraft and capable of allowing the corresponding slider to slide inward and outward, and a slide rail (404) fixedly connected to the lower wing surface of the flying wing layout unmanned sub-aircraft and capable of allowing the corresponding slider to slide inward and outward. A fixed end cover (403) straddling the two slide rails and being clamped with the slide rails, a spring support rod (404) fixedly connected to the middle of the lower surface of the fixed end cover, a spring (405) symmetrically arranged at both ends of the spring support rod and having one end abutting against the middle of the spring support rod and the other end abutting against the slider, a steering gear (406) fixed on the lower wing surface of the flying wing layout unmanned sub-aircraft, and a limit rod (407) connected to the output end of the steering gear and used for limiting the position of the slider and compressing the spring. The steering gear (406) is started to drive the limit rod (407) to rotate, thereby releasing the limit constraint of the slider (402). The slider (402) moves toward the two ends of the slide rail (402) under the action of the rebound force of the spring (405), the slider (401) is separated from the tail end of the host connecting rod (3), and the flying wing layout unmanned sub-aircraft (2) is separated from the flying wing layout unmanned main aircraft (1).

2. The detachable flying wing layout unmanned aerial vehicle according to claim 1, characterized in that: The flying wing layout unmanned main aircraft (1) comprises an inner fuselage with an airfoil type (101), an outer fuselage with an airfoil type (102), a wing (103), a leading edge slat (104), a main aileron (105), a horizontal control surface (106), a ducted fan (107) and a V-shaped tail (108), wherein an angle exists between the outer fuselage with an airfoil type (102) and the wing (103); the flying wing layout unmanned sub-aircraft (2) comprises a wing The flying wing layout unmanned sub-aircraft vehicle (2) is seamlessly arranged between the wing-shaped outer fuselage (101) and the wing (103); the chord line of the symmetry surface of the wing-shaped fuselage (201) of the flying wing layout unmanned sub-aircraft vehicle (2) is colinear with the chord line of the intersection surface of the wing (103) and the wing-shaped outer fuselage (102) of the flying wing layout unmanned main aircraft (1).

3. The detachable flying wing layout unmanned aerial vehicle according to claim 2, characterized in that: The leading edge sweep angles of the flying wing layout unmanned main aircraft (1) and the flying wing layout unmanned sub-aircraft (2) are the same, and the angle between the wing-shaped outer fuselage (102) and the wing (103) is twice the leading edge sweep angle.

4. The detachable flying wing layout unmanned aerial vehicle according to claim 2, characterized in that: The span of the wing-shaped fuselage (201) of the flying-wing layout unmanned aerial vehicle (2) is twice the span length of the wing-shaped outer fuselage (102) of the flying-wing layout unmanned aerial vehicle (1) along the wing span.

5. The detachable flying wing layout unmanned aerial vehicle according to claim 2, characterized in that: The wing-shaped inner fuselage (101), the wing-shaped outer fuselage (102), the wing (103) and the leading edge slat (104) are fixedly connected in sequence; the main aileron (105) is movably connected to the wing (103); the horizontal control surface (106) is movably connected to the wing-shaped inner fuselage (101); the ducted fan (107) is fixedly connected to the wing-shaped inner fuselage (101) and the wing-shaped outer fuselage (102); and the V-shaped tail (108) comprises a V-shaped tail stabilizer and a V-shaped tail control surface that are movably connected to each other, wherein the V-shaped tail stabilizer is fixedly connected to the ducted fan (107).

6. The detachable flying wing layout unmanned aerial vehicle according to claim 2, characterized in that: The wing-shaped fuselage (201) and the aileron (203) are movably connected, and the vertical tail (202) comprises a vertical tail stabilizer and a vertical tail control surface that are movably connected to each other, wherein the vertical tail stabilizer is fixedly connected to the wing-shaped fuselage (201).

7. The detachable flying wing layout unmanned aerial vehicle according to claim 1, characterized in that: The slide rail (402) is provided with a slide rail groove (4021) for the slider to slide inward and outward and an assembly groove (4022) for clamping and fixing the end cover. The width of the two ends of the slide rail groove (4021) is greater than the width of the middle section. The assembly groove (4022) is respectively located on the upper and lower surfaces in the middle of the slide rail.

8. The detachable flying wing layout unmanned aerial vehicle according to claim 1, characterized in that: The slider (401) comprises a baffle portion (4011) for abutting against a spring, a host connecting hole (4012) opened on the baffle portion and used for passing a host connecting rod, a support rod connecting hole (4013) opened on the baffle portion and used for passing a spring support rod, and a slider head (4014) symmetrically arranged on both sides of the baffle portion and used for passing through a slide rail and moving along the slide rail.

9. The detachable flying wing layout unmanned aerial vehicle according to claim 1, characterized in that: The spring support rod (404) comprises a resisting block (4041) located in the middle, long rods (4042) symmetrically arranged on both sides of the resisting block and used for passing springs, and an upper connecting rod (4043) located above the resisting block and used for connecting and fixing the end cover.

Images