Subsonic stealth unmanned aerial vehicle

Abstract

The invention discloses a subsonic stealth unmanned aerial vehicle. The subsonic stealth unmanned aerial vehicle comprises a nose; the machine body comprises a front part, a middle part, a rear part and a tail part, and an air inlet channel with an opening facing the machine head direction is arranged below the rear part of the machine body; the balance wings are positioned at the rear part of the fuselage and comprise a left balance wing and a right balance wing which are symmetrically arranged on the left side and the right side of the fuselage; the empennage and the engine are arranged at the tail part of the fuselage, and the empennage is a Y-shaped empennage; the variable infrared enhancement system and the wingtip of the balance wing are integrally arranged, the variable infrared enhancement system comprises a front infrared radiation cabin, a rear infrared radiation cabin and a control cabin, the front infrared radiation cabin and the rear infrared radiation cabin are integrally arranged, the control cabin is arranged between the front infrared radiation cabin and the rear infrared radiation cabin, and the variable infrared enhancement system is used for carrying out front-back bidirectional radiation. According to the subsonic stealth unmanned aerial vehicle provided by the invention, the variable infrared enhancement system with variable infrared characteristics is integrated on the aerial vehicle, so that the effectiveness of training and testing is improved, and the problem that functions and performance are difficult to consider at the same time is solved.

Description

Technical Field

[0001] The present invention relates to the field of unmanned aerial vehicles, and in particular to a subsonic stealth unmanned aerial vehicle. Background Art

[0002] Subsonic unmanned aerial vehicles with variable infrared characteristics are simulated targets used for testing and identification of air defense weapon systems and for troop training. They are mainly used to simulate the infrared target characteristics of enemy high-speed combat aircraft and cruise missiles. Through the changeable infrared characteristic enhancement system, they provide realistic high-speed aerial motion and infrared characteristic simulated shooting targets for air defense weapon systems, live-fire shooting training or testing and identification of new types of weapons, thereby completing the tasks of training and assessing the sensitivity, reliability, adaptability and accuracy of air defense weapon systems.

[0003] In order to meet the high-speed and high-maneuverability characteristics of subsonic target aircraft and minimize the burden of mounting additional equipment, the current design trend of subsonic target aircraft is to install Radar Cross Section (RCS) enhancement equipment on the nose of the aircraft or to mount infrared enhancement equipment on the wingtips. However, these devices are usually equipped with a separate battery system, which is heavy and bulky, and often do not consider compatibility with the aircraft, thus placing a heavy burden on the aircraft itself; this design often makes it difficult to balance function and performance. Existing technology cannot solve this problem. Summary of the invention

[0004] In order to solve the problems existing in the prior art, the present invention provides a subsonic stealth unmanned aerial vehicle.

[0005] The present invention provides a subsonic stealth unmanned aerial vehicle, comprising: a nose; a fuselage, the fuselage comprising a front part, a middle part, a rear part and a tail part, an air inlet opening toward the nose direction is arranged below the rear part of the fuselage; a balance wing, the balance wing is located at the rear part of the fuselage, and comprises a left balance wing and a right balance wing symmetrically arranged on the left and right sides of the fuselage; a tail wing and an engine arranged at the tail of the fuselage, the tail wing is a Y-shaped tail wing; a variable infrared enhancement system, the variable infrared enhancement system is integrated with the wing tip of the balance wing, and comprises an integrated front infrared radiation cabin, a rear infrared radiation cabin and a control cabin arranged therebetween, and the variable infrared enhancement system is used for front and rear bidirectional radiation.

[0006] Optionally, the front infrared radiation cabin is arranged at one end of the variable infrared enhancement system, including a forward infrared transparent ball cover, a forward heating element, and a forward infrared reflector arranged in sequence, and the forward infrared transparent ball cover is arranged at the end of the forward radiation cabin away from the control cabin. The rear infrared radiation cabin is arranged at the other end of the variable infrared enhancement system, including a rear infrared transparent ball cover, a rear heating element, and a rear infrared reflector arranged in sequence, and the rear infrared transparent ball cover is arranged at the end of the rear radiation cabin away from the control cabin.

[0007] Optionally, the radiation azimuth angle of the forward infrared reflector and / or the backward infrared reflector ranges from 0 to 120°, the radiation intensity of the forward infrared reflector ranges from 0 to 40 W / sr, and the radiation intensity of the backward infrared reflector ranges from 0 to 80 W / sr.

[0008] Optionally, the control cabin includes an insulator, a wave spreading control circuit, a safety circuit, a communication circuit and a battery, the thermal insulation body includes a forward thermal insulation body connected to the front infrared radiation cabin and a rearward thermal insulation body connected to the rear infrared radiation cabin, and the wave spreading control circuit is used to control the intensity and time of the radiation emitted by the variable infrared enhancement system.

[0009] Optionally, the balance wing is a trapezoidal wing, the leading edge sweep angle ranges from 30 to 45 degrees, the installation angle ranges from 0 to 2 degrees, the aspect ratio ranges from 4 to 5, the root and wing tip of the balance wing are both symmetrical laminar airfoils, and the relative thickness of the root airfoil ranges from 12% to

[0010] 14%, the relative thickness of the tip airfoil is in the range of 8% to 10%, and a balance wing steering gear for adjusting the angle and position of the balance wing is also arranged at the rear edge of the balance wing.

[0011] Optionally, the starting voltage range of the variable infrared enhancement system is 12 to 30 V, the pulse width is >100 ms, and the current is <20 mA.

[0012] Optionally, the forward infrared reflector and the backward infrared reflector are iron-chromium alloy heating materials, and the thermal insulation body is aluminum silicate thermal insulation material.

[0013] Optionally, the angle between two adjacent tail fins of the Y-shaped tail fin is 120°, the tail fin is a trapezoidal wing, the leading edge sweep angle of the tail fin is the same as the leading edge sweep angle of the balance wing, the aspect ratio range is 1-2, the relative thickness of the airfoil range is 10% to 12%, and a tail fin servo for adjusting the angle and position of the tail fin is also provided at the rear edge of the tail fin.

[0014] Optionally, the subsonic stealth unmanned aerial vehicle also includes: a motorized wing located in the middle of the fuselage, the motorized wing is a delta wing, the leading edge sweep angle range is 45-50°, the installation angle range is 0-2°, the aspect ratio range is 4-5, and a motorized wing servo for adjusting the angle and position of the motorized wing is also provided on the rear edge of the motorized wing.

[0015] Optionally, the subsonic stealth unmanned aerial vehicle further includes: a recovery airbag and a recovery parachute located inside the fuselage, for recovering the unmanned aerial vehicle.

[0016] Compared with the prior art, the technical solution of the present invention has the following beneficial effects:

[0017] A subsonic stealth unmanned aerial vehicle provided by the present invention can simultaneously simulate the infrared characteristics of different parts of the aircraft by integrating a variable infrared enhancement system with variable infrared characteristics on the subsonic aircraft, thereby improving the authenticity and comprehensiveness of the simulation, and helping to more accurately evaluate the infrared detection performance of the target in tests and drills; and the integrated design of the variable infrared enhancement system in the subsonic aircraft does not affect the aerodynamic layout of the target aircraft, has a simple structure and is easy to manufacture, thus solving the problem of difficulty in balancing function and performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.

[0019] Figure 1 It is a schematic diagram of the three-dimensional structure of a subsonic stealth unmanned aerial vehicle in one embodiment of the present invention;

[0020] Figure 2 A top view of a subsonic stealth unmanned aerial vehicle in one embodiment of the present invention;

[0021] Figure 3 It is a schematic structural diagram of a variable infrared enhancement system for a subsonic stealth unmanned aerial vehicle in one embodiment of the present invention;

[0022] Figure 4 It is a simulated curve diagram of omnidirectional adjustable infrared enhancement characteristics of a subsonic stealth unmanned aerial vehicle in one embodiment of the present invention;

[0023] Figure 5 A side view of a subsonic stealth unmanned aerial vehicle in one embodiment of the present invention;

[0024] Figure 6The figure is a front view of a subsonic stealth unmanned aerial vehicle in one embodiment of the present invention. DETAILED DESCRIPTION

[0025] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited to the embodiments set forth herein.

[0026] In the present invention, unless otherwise specified, the directional words used, such as "upper and lower", generally refer to the upper and lower parts of the device in normal use, and "inside and outside" refer to the outline of the device. In addition, the terms "first, second, third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first, second, third" may explicitly or implicitly include one or more of the features. In the description of the present invention, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined. Since the accompanying drawings are descriptions of the same device, the same reference numerals in the drawings represent the same components.

[0027] As described in the background technology, in order to meet the high speed and high maneuverability characteristics of subsonic target aircraft and improve the infrared enhancement function, the existing technology is to install RCS enhancement equipment on the nose of the aircraft or mount infrared enhancement equipment on the wingtips. However, these devices are usually equipped with a separate battery system, which is heavy and large in size, thereby placing a heavy burden on the aircraft itself and making it difficult to balance the function and performance of the aircraft.

[0028] Therefore, the present invention provides a subsonic stealth unmanned aerial vehicle, which can effectively solve the above-mentioned problems by integrating a variable infrared characteristic enhancement system into the subsonic aircraft, with a simple structure and easy manufacturing.

[0029] The present invention provides a subsonic stealth unmanned aerial vehicle, comprising: a nose; a fuselage, the fuselage comprising a front part, a middle part, a rear part and a tail part, an air inlet opening toward the nose direction is arranged below the rear part of the fuselage; a balance wing, the balance wing is located at the rear part of the fuselage, and comprises a left balance wing and a right balance wing symmetrically arranged on the left and right sides of the fuselage; a tail wing and an engine arranged at the tail of the fuselage, the tail wing is a Y-shaped tail wing; a variable infrared enhancement system, the variable infrared enhancement system is integrated with the wing tip of the balance wing, and comprises an integrated front infrared radiation cabin, a rear infrared radiation cabin and a control cabin arranged therebetween, and the variable infrared enhancement system is used for front and rear bidirectional radiation.

[0030] The specific examples of the present invention are further described in detail below with reference to the accompanying drawings.

[0031] The present invention provides a subsonic stealth unmanned aerial vehicle, which comprises a subsonic aircraft body and a variable infrared characteristic enhancement system. Figure 1 and Figure 2 The subsonic stealth unmanned aerial vehicle includes a nose, a fuselage, a balance wing 130 , a tail wing 120 , an engine 150 and a variable infrared enhancement system 170 .

[0032] Specifically, refer to Figure 1 The nose is provided with a fairing 110 for adjusting the airflow and reducing the air resistance of the subsonic stealth unmanned aerial vehicle during flight, so that the aircraft can fly more smoothly and efficiently. The fuselage includes a front part, a middle part, a rear part and a tail part. An air inlet 160 facing the nose is provided at the lower rear part of the fuselage. The fuselage and the air inlet 160 are integrally provided and are S-shaped at the lower rear part of the fuselage, which can reduce the radar reflection area of ​​the aircraft, improve the stealth performance, and reduce the air resistance during flight, further optimizing the range.

[0033] Reference Figure 1 An engine 150 is also provided at the tail of the fuselage, wherein the engine 150 is a small turbojet engine.

[0034] The balance wing 130 is located at the rear of the fuselage, and includes a left balance wing and a right balance wing symmetrically arranged on the left and right sides of the fuselage. The balance wing can improve the flight stability of the subsonic stealth unmanned aerial vehicle, improve flight efficiency, reduce energy consumption, and optimize the flight performance of the unmanned aerial vehicle.

[0035] In an embodiment of the present invention, Figure 2 As shown, the balance wing 130 is a trapezoidal wing, the leading edge sweep angle thereof is in the range of 30-45°, the installation angle is in the range of 0-2°, and the aspect ratio is in the range of 4-5.

[0036] In some other embodiments, different leading edge sweep angles, installation angles and aspect ratios can be selected according to different application scenarios and the specific structural design of the target aircraft. In the design of the wing, a suitable leading edge sweep angle can improve the aerodynamic efficiency of high-speed flight, reduce the intensity of the shock wave, delay air separation, and improve the stability of the aircraft at high speed; the sweep angle of most commercial aircraft is between 20-40°. The larger the sweep angle, the higher the maximum speed of the aircraft, but the flexibility and low-speed performance will be reduced. A suitable installation angle can make the aircraft in the most favorable lift-to-drag ratio state under a certain design state. Usually, the selection of the installation angle of the wing is determined by wind tunnel test data. Generally, 0-2° can be selected when manufacturing and processing small unmanned aerial vehicles. The aspect ratio is also an important parameter for measuring the kinematic performance of the wing. A suitable wing aspect ratio can improve the maneuverability and range of the aircraft. Generally, the induced drag of the wing with a large aspect ratio is small, and the strength and lift loss of the wingtip vortex are also small, which is suitable for long-term flight aircraft applications.

[0037] exist Figure 2 In the illustrated embodiment, the wing root and wing tip of the balance wing 130 are both symmetrical laminar airfoils, the relative thickness of the root airfoil ranges from 12% to 14%, and the relative thickness of the tip airfoil ranges from 8% to 10%, and the wing root is integrated with the fuselage.

[0038] The relative thickness of the airfoil has an important influence on the performance of the aircraft. In terms of application, the relative thickness of the airfoil is directly related to the thickness of the airfoil, which in turn affects the lift, drag, and structural strength of the aircraft. In some different embodiments, the relative thickness of the root airfoil and the relative thickness of the tip airfoil of the balance wing may be different according to factors such as the specific aircraft structure, and the present invention is not limited to this.

[0039] like Figure 2 As shown, in one embodiment of the present invention, a balance wing servo 131 for adjusting the angle and position of the balance wing is also provided at the rear edge of each balance wing, so as to achieve precise control of the aircraft attitude.

[0040] A variable infrared enhancement system 170 is provided at the wing tip of the balance wing 130 for front and rear bidirectional radiation. The variable infrared enhancement system 170 includes two groups, which are integrated with the wing tips of the left balance wing and the right balance wing, respectively. Figure 3 As shown, each set of variable infrared enhancement systems is an integrated structure, and the overall shape is a capsule, including a front infrared radiation cabin 1710, a rear infrared radiation cabin 1730, and a control cabin 1720 arranged therebetween, and a shell arranged outside the three for wrapping the front infrared radiation cabin 1710, the rear infrared radiation cabin 1730, and the control cabin 1720. Figure 5The front infrared radiation chamber 1710 is used for forward enhancement, and the rear infrared radiation chamber 1730 is used for rear enhancement. Within a specific band, both the forward and rear directions can achieve linear adjustment of radiation intensity.

[0041] Specifically, refer to Figure 3 In one embodiment of the present invention, the front infrared radiation cabin 1710 is arranged at one end of the variable infrared enhancement system 170, and includes, from front to back, a forward infrared transparent ball cover 1711, a forward heating element 1712, and a forward infrared reflector 1713. The forward infrared transparent ball cover 1711 is arranged at one end of the forward radiation cabin 1710 away from the control cabin 1720, that is, the forward infrared transparent ball cover 1711 is located at one end inside the shell of the variable infrared enhancement system 170; the rear infrared radiation cabin 1730 is arranged at the other end of the variable infrared enhancement system 170, and includes, from back to front, a rear infrared transparent ball cover 1731, a rear heating element 1732, and a rear infrared reflector 1733. The rear infrared transparent ball cover 1731 is arranged at one end of the rear radiation cabin 1730 away from the control cabin 1720, that is, the rear infrared transparent ball cover 1711 is located at the other end inside the shell of the variable infrared enhancement system 170. The radiation azimuth angles of the forward infrared reflector 1713 and the rearward infrared reflector 1733 range from 0 to 120°, the radiation intensity of the forward infrared reflector 1713 ranges from 0 to 40 W / sr and is continuously adjustable within this range, and the radiation intensity of the rearward infrared reflector ranges from 0 to 80 W / sr and is continuously adjustable within this range, thereby forming an infrared characteristic curve that increases monotonically from front to back and realizing omnidirectional infrared enhancement.

[0042] In one embodiment of the present invention, the forward heating element and the backward heating element are made of iron-chromium alloy heating materials. In some other embodiments, other heating materials can also be used as heating elements, which is not limited by the present invention.

[0043] exist Figure 3 In the illustrated embodiment, the control cabin 1720 includes a heat insulator, a wave spreading control circuit 1724, a safety circuit 1725, a communication circuit 1726, and a battery 1723. The wave spreading control circuit 1724 is integrated inside the control cabin 1720 and is used to control the radiation time and radiation intensity of the radiation emitted from the front infrared radiation cabin 1710 and the rear infrared radiation cabin 1730; the heat insulator includes a forward heat insulator 1721 connected to the front infrared radiation cabin 1710 and a rearward heat insulator 1722 connected to the rear infrared radiation cabin 1730.

[0044] In one embodiment of the present invention, the heat insulator is an aluminum silicate heat insulating material, and the battery is a high-power lithium battery. In some other embodiments, other heating materials can also be used as the heating element, and the present invention is not limited to this.

[0045] In some embodiments, the variable infrared enhancement system is started by providing an external voltage signal, the reliable starting voltage range is 12 to 30V, the pulse width is >100ms, the current is <20mA, and it has an RS422 digital communication interface with a J30J connector connected to the aircraft flight control system. The radiation intensity and working time of the variable infrared enhancement system can be set through the matching parameter setting terminal.

[0046] In one embodiment of the present invention, since the variable infrared enhancement system adopts a fully electric heating working mode, the working time and radiation intensity can be controlled by adjusting the working parameters, such as Figure 4 As shown, by adjusting the radiation intensity and working time of the variable infrared enhancement system, different radiation characteristics can be achieved, which helps to more accurately evaluate the infrared detection performance of the target in experiments and exercises, thereby improving the effectiveness of training and testing.

[0047] In one embodiment of the present invention, Figure 5 , Figure 6 , a tail 120 is arranged at the rear of the fuselage, the tail 120 is a Y-shaped tail, and the angle between the two connected tails 120 is 120°. The tail is an important part of the flight control system, which is used to control the pitch, yaw and tilt of the aircraft to change its flight attitude. In this embodiment, each tail 120 is a trapezoidal wing, the leading edge sweep angle is the same as the leading edge sweep angle of the balance wing, the aspect ratio range is 1-2, and the relative thickness of the airfoil ranges from 10% to 12%, such as Figure 2 As shown, a tail servo 121 for adjusting the angle and position of the tail 120 is also provided at the rear edge of each tail 120 .

[0048] In some embodiments, in combination Figure 1 and Figure 2 The subsonic stealth unmanned aerial vehicle also includes: a motorized wing 140 located in the middle of the fuselage, the motorized wing 140 is a delta wing, the leading edge sweep angle thereof is in the range of 45-50°, the installation angle is in the range of 0-2°, the aspect ratio is in the range of 4-5, and a motorized wing servo 141 for adjusting the angle and position of the motorized wing 140 is also provided at the rear edge of the motorized wing 140.

[0049] In some embodiments, in combination Figure 1 and Figure 5 The subsonic stealth unmanned aerial vehicle also includes: a recovery airbag 210 and a recovery parachute 200 located in the fuselage. The recovery airbag 210 and the recovery parachute 200 are used to reduce the impact force when the unmanned aerial vehicle is recovered and landed, thereby protecting the unmanned aerial vehicle from damage and extending its service life.

[0050] In some embodiments, in combination Figure 1 , Figure 2 and Figure 5 The subsonic stealth unmanned aerial vehicle further includes: a pitot tube 180, a communication antenna 190, a rocket ejection rack 220 and a maintenance cabin 230. The communication antenna 190 is located above the front of the fuselage, and the pitot tube is located below the front of the fuselage, mainly used to measure the speed of the aircraft; the rocket ejection rack 220 is located below the balance wing, and can carry and launch airborne rockets to meet the purpose of test and evaluation and military training; the maintenance cabin 230 is located in the middle of the fuselage, that is, in the belly of the fuselage. When the aircraft fails, maintenance personnel can use the maintenance cabin 230 to inspect the aircraft.

[0051] The present invention provides a subsonic stealth unmanned aerial vehicle. By integrating a variable infrared enhancement system with variable infrared characteristics on a subsonic aircraft, the aircraft itself has an infrared enhancement function and can simulate the infrared characteristics of various sizes of aerial targets, thereby improving the authenticity and comprehensiveness of the simulation. At the same time, the integrated design can optimize the lift-drag characteristics, stability characteristics, etc. of the aerodynamic layout of the target aircraft, as well as the thrust characteristics, air inlet characteristics, and stealth characteristics of the layout of the engine, thereby meeting the radar stealth requirements of the subsonic aircraft and solving the problem of difficulty in balancing functions and performances.

[0052] The above descriptions are merely embodiments of the present application and are not intended to limit the patent scope of the present application. Any equivalent structural or equivalent process transformations made using the contents of the specification and drawings of the present application, such as the mutual combination of technical features between the embodiments, or direct or indirect application in other related technical fields, are also included in the patent protection scope of the present application.

Claims

1. A subsonic stealth unmanned aerial vehicle, characterized in that: include: Nose; A fuselage, the fuselage comprising a front portion, a middle portion, a rear portion and a tail portion, an air inlet opening toward the nose of the aircraft is provided below the rear portion of the fuselage; The balance wing is located at the rear of the fuselage, and includes a left balance wing and a right balance wing symmetrically arranged on the left and right sides of the fuselage; The tail wing and the engine are arranged at the tail of the fuselage, wherein the tail wing is a Y-shaped tail wing; A variable infrared enhancement system is integrated with the wingtip of the balance wing, including an integrated front infrared radiation cabin, a rear infrared radiation cabin and a control cabin arranged therebetween, and the variable infrared enhancement system is used for front and rear bidirectional radiation.

2. The subsonic stealth unmanned aerial vehicle according to claim 1, characterized in that: The front infrared radiation cabin is arranged at one end of the variable infrared enhancement system, and includes a forward infrared transparent ball cover, a forward heating element, and a forward infrared reflector which are arranged in sequence. The forward infrared transparent ball cover is arranged at one end of the forward radiation cabin away from the control cabin. The rear infrared radiation cabin is arranged at the other end of the variable infrared enhancement system, and includes a rear infrared transparent ball cover, a rear heating element, and a rear infrared reflector which are arranged in sequence. The rear infrared transparent ball cover is arranged at one end of the rear radiation cabin away from the control cabin.

3. The subsonic stealth unmanned aerial vehicle according to claim 2, characterized in that: The radiation azimuth angle of the forward infrared reflector and / or the backward infrared reflector ranges from 0 to 120°, the radiation intensity of the forward infrared reflector ranges from 0 to 40 W / sr, and the radiation intensity of the backward infrared reflector ranges from 0 to 80 W / sr.

4. The subsonic stealth unmanned aerial vehicle according to claim 2, characterized in that: The control cabin includes an insulator, a wave spreading control circuit, a safety circuit, a communication circuit and a battery. The insulator includes a forward insulator connected to the front infrared radiation cabin and a rearward insulator connected to the rear infrared radiation cabin. The wave spreading control circuit is used to control the intensity and time of the radiation emitted by the variable infrared enhancement system.

5. The subsonic stealth unmanned aerial vehicle according to claim 1, characterized in that: The balance wing is a trapezoidal wing, the leading edge sweep angle ranges from 30 to 45 degrees, the installation angle ranges from 0 to 2 degrees, the aspect ratio ranges from 4 to 5, the wing root and wing tip of the balance wing are both symmetrical laminar airfoils, the relative thickness of the root airfoil ranges from 12% to 14%, and the relative thickness of the tip airfoil ranges from 8% to 10%, and a balance wing servo for adjusting the angle and position of the balance wing is also provided at the rear edge of the balance wing.

6. The subsonic stealth unmanned aerial vehicle according to claim 1, characterized in that: The variable infrared enhancement system has a starting voltage range of 12 to 30 V, a pulse width of >100 ms, and a current of <20 mA.

7. The subsonic stealth unmanned aerial vehicle according to claim 4, characterized in that: The forward infrared reflector and the backward infrared reflector are iron-chromium alloy heating materials, and the heat insulator is aluminum silicate heat insulation material.

8. The subsonic stealth unmanned aerial vehicle according to claim 5, characterized in that: The angle between two adjacent tail fins of the Y-shaped tail fin is 120°, the tail fin is a trapezoidal wing, the leading edge sweep angle of the tail fin is the same as the leading edge sweep angle of the balance wing, the aspect ratio range is 1-2, the relative thickness of the airfoil ranges from 10% to 12%, and a tail fin servo for adjusting the angle and position of the tail fin is also provided at the rear edge of the tail fin.

9. The subsonic stealth unmanned aerial vehicle according to claim 1, characterized in that: Also includes: The motor wing is located in the middle of the fuselage, and the motor wing is a delta wing. The leading edge sweep angle ranges from 45 to 50 degrees, the installation angle ranges from 0 to 2 degrees, and the aspect ratio ranges from 4 to 5. A motor wing servo for adjusting the angle and position of the motor wing is also provided on the rear edge of the motor wing.

10. The subsonic stealth unmanned aerial vehicle according to claim 1, characterized in that: Also includes: The recovery airbag and recovery parachute located in the fuselage are used to recover the unmanned aerial vehicle.

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