Variable configuration short takeoff and landing uav based on upper surface blowing for lift and method

Abstract

The application provides a variable configuration short take-off and landing unmanned aerial vehicle based on upper surface blowing lift increase and a method, which comprises a variable nose module and an unmanned aerial vehicle body; when the variable nose module is in the original position, the short take-off and landing unmanned aerial vehicle is in a blended wing body layout; when the variable nose module is lifted upward and forward relative to the unmanned aerial vehicle body to the position, the short take-off and landing unmanned aerial vehicle is in a canard layout, so that the configuration conversion of the short take-off and landing unmanned aerial vehicle between the blended wing body layout and the canard layout is realized. The short take-off and landing design of the application is based on the upper surface blowing lift increase and the jet control principle, the variable layout conversion between the canard layout and the blended wing body layout is realized through the simple actuation of the nose, the take-off and landing distance can be significantly shortened, the hovering and combat performance is more excellent, the variable layout design integrates the aerodynamic advantages of multiple overall layouts, and each technical index of the aircraft can be significantly improved to cope with future combat requirements.

Description

Technical Field

[0001] This invention belongs to the field of aircraft design technology, specifically relating to a variable configuration short takeoff and landing unmanned aerial vehicle and method based on upper surface air blowing lift enhancement. Background Technology

[0002] Thanks to the continuous development of munitions, data links, and computer technology, unmanned aerial vehicles (UAVs) have gradually evolved from performing combat support missions such as aerial reconnaissance, battlefield surveillance, combat damage assessment, and early warning to becoming multi-purpose combat platforms capable of air combat, suppressing enemy air defense systems, and launching attacks into enemy strategic depth. Among these multi-purpose combat platforms, short takeoff and landing (STOVL) UAVs, functioning as fighter jets, are characterized by their small size, light weight, ease of carrying, and rapid deployment, making them suitable for applications requiring rapid response and complex terrain. The current challenge for existing STOVL UAVs is how to effectively shorten their takeoff and landing distances to achieve superior maneuvering and dogfighting performance. Summary of the Invention

[0003] To address the shortcomings of existing technologies, this invention provides a variable configuration short takeoff and landing UAV and method based on upper surface air blowing lift, which can effectively solve the above problems.

[0004] The technical solution adopted in this invention is as follows:

[0005] This invention provides a variable configuration short takeoff and landing (STOL) unmanned aerial vehicle (UAV) based on upper surface air blowing lift, including a variable nose module (1) and a UAV body; when the variable nose module (1) is in place, the STOL UAV has a blended wing-body configuration; when the variable nose module (1) is lifted forward and upward relative to the UAV body, the STOL UAV has a canard configuration, thereby realizing the configuration conversion between the STOL UAV and the blended wing-body configuration and the canard configuration.

[0006] Preferably, the variable nose module (1) is equipped with an auxiliary engine (8) inside, the front end of the variable nose module (1) is equipped with an auxiliary engine air intake (10), and the rear end of the variable nose module (1) is equipped with an auxiliary engine exhaust flow channel front end (9); the variable nose module (1) is equipped with canards (15) on the left and right sides; the canards (15) have a canard leading edge (14) and a canard trailing edge (7); the bottom sides of the variable nose module (1) are each equipped with a nose guide groove A part (11), and the front end of the nose guide groove A part (11) is connected to the auxiliary engine air intake (10);

[0007] The UAV body includes a fuselage (5), a nose fixing part (2) is provided at the front end of the fuselage (5), main wings (6) are provided on the left and right sides of the fuselage (5), a V-shaped tail fin (4) is provided at the rear of the fuselage (5), and a main engine (3) is provided on each side inside the fuselage (5); the main engine (3) has a main air intake upper lip (13); a nose guide groove B part (12) is provided on each side of the nose fixing part (2).

[0008] The present invention also provides a method for a variable configuration short takeoff and landing unmanned aerial vehicle (UAV) based on upper surface air blowing lift enhancement, comprising the following steps:

[0009] Step 1: During takeoff and landing and when high-G maneuvers are required, the main engine (3) and auxiliary engine (8) are started simultaneously. The variable nose module (1) is raised forward and upward. When the upward movement of the variable nose module (1) ends, it becomes a canard configuration. At this time, the trailing edge (7) of the canard is connected to the upper lip (13) of the main air intake. An exposed part of the surface appears between the variable nose module (1) and the fixed part of the nose (2), exposing the auxiliary engine (8), the auxiliary engine air intake (10), and the nose guide slot A part (11). Lift is increased and takeoff and landing distance is shortened in the following three aspects: First aspect: External airflow flows into the auxiliary engine (8) from the auxiliary engine air intake (10) and supplies air to the auxiliary engine (8). The exhaust of the auxiliary engine (8) is discharged from the front end (9) of the auxiliary engine exhaust channel. The high-speed airflow discharged by the auxiliary engine (8) flows over the upper surface of the wing and continues to flow obliquely downward along the deflected flap. The low-pressure zone generated during operation controls the lift of the fuselage (5), delaying the stall. At the same time, the Coanda effect is used to deflect the airflow downward, significantly increasing the root velocity circulation and improving the root lift coefficient. Meanwhile, the Bernoulli principle is used to increase the pressure difference between the upper and lower surfaces, thereby increasing the lift coefficient, shortening the takeoff and landing distance, and improving the turning performance. Secondly, after the external airflow passes through the nose guide channel A (11), it flows into the nose guide channel B (12) and then into the main air intake of the main engine (3), increasing the airflow into the main air intake of the main engine (3), thereby increasing the intake efficiency of the main engine (3) and improving the working lift of the main engine (3). Thirdly, when the variable nose module (1) is raised forward and upward to the canard configuration, the canard (15) is a short-pitch coupled canard, providing additional control torque and changing the aerodynamic center of the UAV, thereby increasing lift, shortening the takeoff and landing distance, and reducing the turning radius.

[0010] Step 2: During the cruise phase, only the main engine (3) is started and the auxiliary engine (8) is shut down. The variable nose module (1) is reset to its original position. At this time, the canard (15) of the variable nose module (1) is completely integrated with the fuselage (5) and main wing (6) of the fixed nose part (2), forming a blended wing-body layout. At this time, the canard (15) is used as a strake wing. In addition, the trailing edge (7) of the canard (15) is connected to the lower lip of the main air intake, effectively shielding the main air intake of the main engine (3), significantly reducing the radar cross-section of the main air intake of the main engine (3), which is beneficial to reduce the drag coefficient during high-speed flight in the cruise phase and improve the stealth performance of the UAV.

[0011] The variable configuration short takeoff and landing UAV and method based on upper surface air blowing enhancement provided by this invention have the following advantages:

[0012] Based on the principle of airflow lift enhancement and jet control on the upper surface of the fuselage, the short takeoff and landing design can achieve variable layout conversion between canard and blended wing-body configurations through simple nose movements. This can significantly shorten takeoff and landing distances while achieving better turning and dogfighting performance. In addition, the variable layout design integrates the aerodynamic advantages of multiple overall layouts, which can significantly improve the technical indicators of the aircraft in various aspects to meet future combat requirements. Attached Figure Description

[0013] Figure 1 A perspective view of the short takeoff and landing UAV provided by the present invention in a canard configuration;

[0014] Figure 2 A perspective view of the short takeoff and landing UAV provided by the present invention in a blended wing-body configuration;

[0015] Figure 3 This is a front view of the short takeoff and landing UAV provided by the present invention in a canard configuration.

[0016] Figure 4 The front view of the short takeoff and landing unmanned aerial vehicle (UAV) provided by the present invention in a blended wing-body configuration;

[0017] Figure 5 A cantilevered view of the short takeoff and landing UAV provided by the present invention in a canard configuration;

[0018] Figure 6 Axonometric view of a short takeoff and landing unmanned aerial vehicle (UAV) with a blended wing-body configuration provided by the present invention;

[0019] Figure 7 A bottom view of the variable head module provided by this invention;

[0020] Figure 8 An isometric view of the variable head module provided by this invention;

[0021] Figure 9This is a top view of the short takeoff and landing UAV provided by the present invention in a canard configuration.

[0022] Figure 10 A top view of the short takeoff and landing unmanned aerial vehicle (UAV) provided by the present invention in a blended wing-body configuration;

[0023] Figure 11 This is a top view of the short takeoff and landing UAV provided by the present invention in a canard configuration.

[0024] Figure 12 A top view of the short takeoff and landing unmanned aerial vehicle (UAV) provided by the present invention in a blended wing-body configuration;

[0025] Figure 13 This is a side view of the airflow channel portion of the short takeoff and landing UAV provided by the present invention in a blended wing-body configuration;

[0026] Figure 14 A top view of the airflow channel portion of the short takeoff and landing UAV provided by the present invention in a blended wing-body configuration;

[0027] Figure 15 A side view of the airflow channel portion of the short takeoff and landing UAV provided by the present invention in a canard configuration;

[0028] Figure 16 A top view of the airflow channel portion of the short takeoff and landing UAV provided by the present invention in a canard configuration;

[0029] Figure 17 An enlarged view of the nose section of the short takeoff and landing UAV provided by the present invention in a canard configuration;

[0030] Figure 18 A partially enlarged view of the short takeoff and landing UAV with a blended wing-body configuration provided by the present invention;

[0031] Figure 19 A partially enlarged view of the short takeoff and landing UAV provided by the present invention in a canard configuration;

[0032] Figure 20 A bottom view of the short takeoff and landing UAV provided by the present invention in a canard configuration;

[0033] Figure 21 A bottom view of the short takeoff and landing UAV provided by the present invention in a blended wing-body configuration;

[0034] Figure 22 A perspective view of the short takeoff and landing UAV provided by the present invention in a blended wing-body configuration. Detailed Implementation

[0035] To make the technical problems solved, the technical solutions, and the beneficial effects of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and are not intended to limit the invention.

[0036] This invention provides a variable configuration short takeoff and landing (STOVL) unmanned aerial vehicle (UAV) based on upper surface blowing lift enhancement, involving boundary layer control technology, upper surface blowing lift enhancement technology, and variable aerodynamic layout technology. (See reference...) Figures 1 to 22 This invention provides a variable configuration short takeoff and landing (STOL) unmanned aerial vehicle (UAV) based on upper surface air-blown lift enhancement, including a variable nose module 1 and a UAV body; when the variable nose module 1 is in its original position, the STOL UAV has a blended wing-body configuration; when the variable nose module 1 is lifted forward and upward relative to the UAV body, the STOL UAV has a canard configuration, thereby realizing the configuration conversion between the STOL UAV and the blended wing-body configuration and the canard configuration.

[0037] An auxiliary engine 8 is installed inside the variable nose module 1. An auxiliary engine air intake 10 is installed at the front end of the variable nose module 1, and an auxiliary engine exhaust duct front end 9 is installed at the rear end of the variable nose module 1. Canards 15 are installed on the left and right sides of the variable nose module 1. The canards 15 have a canard leading edge 14 and a canard trailing edge 7. On both sides of the bottom of the variable nose module 1, a nose guide groove A section 11 is installed. The front end of the nose guide groove A section 11 is connected to the auxiliary engine air intake duct 10.

[0038] The drone body includes a fuselage 5, a nose fixing part 2 is set at the front of the fuselage 5, main wings 6 are set on the left and right sides of the fuselage 5, a V-tail 4 is set at the tail of the fuselage 5, and a main engine 3 is set on each of the two sides inside the fuselage 5; the main engine 3 has a main air intake upper lip 13; and a nose guide groove B part 12 is set on each of the two sides of the nose fixing part 2.

[0039] This invention provides a variable configuration short takeoff and landing unmanned aerial vehicle (UAV) based on upper surface air blowing lift enhancement, which has the following structural design features:

[0040] 1. Duck-type layout lower nozzle guide channel design:

[0041] Since a gap will appear between the variable nose module 1 and the fixed part 2 of the nose during the lifting operation, this gap will disrupt the aerodynamic shape of the nose. Therefore, a guide channel is installed at this point to regulate the airflow passing through this gap.

[0042] The nose cone deflector folds inside the nose cone during high-speed flight phases such as cruise, for example... Figure 13 and Figure 14 As shown, a "diagonal" folding method is used to reduce the space occupied by the guide channel.

[0043] During takeoff and landing, the nose cone guide channel provides... Figure 15 and Figure 16 As shown, the A section 11 of the head guide channel and the B section 12 of the head guide channel are connected.

[0044] 2. Auxiliary engine design at the engine head:

[0045] In this design, the variable nose module 1 includes a nose auxiliary engine 8, wherein, as shown in the figure... Figure 17 As shown, the auxiliary engine air intake 10 is located at the front end of the engine head guide channel A section 11.

[0046] 3. Canard wing design under canard configuration:

[0047] After the upward movement of the variable head module 1 is completed, as follows Figure 18 As shown, the trailing edge 7 of the canard is connected to the upper lip 13 of the main air intake, so that the nose and fuselage are integrated after actuation.

[0048] 4. Leading strake wing design under blended wing-body configuration:

[0049] After the downward operation of the variable head module 1 is completed, as follows Figure 19 and Figure 20 As shown, the trailing edge 7 of the canard 15 is connected to the lower lip of the main air intake, at which point the canard is used as a strake wing.

[0050] The present invention also provides a method for a variable configuration short takeoff and landing unmanned aerial vehicle (UAV) based on upper surface air blowing lift enhancement, comprising the following steps:

[0051] Step 1: During takeoff and landing, and when high-G maneuvers are required, the main engine 3 and auxiliary engine 8 are started simultaneously. Furthermore, the variable nose module 1 is raised forward and upward. At the end of the upward movement of the variable nose module 1, it becomes as follows: Figure 1The canard configuration shown has the trailing edge 7 of the canard wing connected to the upper lip 13 of the main air intake. An exposed surface appears between the variable nose module 1 and the fixed nose section 2, revealing the auxiliary engine 8, the auxiliary engine air intake 10, and the nose deflector section A 11. This configuration increases lift and shortens takeoff and landing distances in three ways: First, external airflow flows into the auxiliary engine 8 from the auxiliary engine air intake 10, supplying air to the auxiliary engine 8. The exhaust from the auxiliary engine 8 exits from the front end 9 of the auxiliary engine exhaust duct. The high-speed airflow from the auxiliary engine 8 flows over the upper wing surface and continues to flow diagonally downwards along the deflected flaps. The low-pressure area generated when this high-speed airflow passes over the upper wing surface controls the lift of the fuselage 5, delaying stall. Simultaneously, the Coanda effect is used to deflect the airflow downwards, significantly increasing lift. The large wing root velocity circulation increases the wing root lift coefficient. Simultaneously, utilizing Bernoulli's principle, the pressure difference between the upper and lower surfaces is increased, thereby improving the lift coefficient, shortening takeoff and landing distances, and enhancing turning performance. Secondly, external airflow passes through section A 11 of the nose guide channel and flows into section B 12, then into the main air intake of the main engine 3, increasing the airflow into the main air intake and thus increasing the intake efficiency and lift of the main engine 3. Thirdly, when the variable nose module 1 is raised forward and upward to its canard configuration, the canard 15 becomes a short-pitch coupled canard, providing additional control torque and altering the aerodynamic center of the UAV, thereby increasing lift, shortening takeoff and landing distances, and reducing the turning radius.

[0052] Step 2: During the cruise phase, only the main engine 3 is started, and the auxiliary engine 8 is shut down. The variable nose module 1 returns to its original position. At this time, the canard 15 of the variable nose module 1 is completely integrated with the fuselage 5 of the fixed nose section 2 and the main wing 6, forming a configuration as shown in the figure. Figure 2 The wing-body blended configuration is shown; in this case, the canard 15 is used as a leading-edge extension wing; and the trailing edge 7 of the canard 15 is connected to the lower lip of the main air intake, effectively shielding the main air intake of the main engine 3, significantly reducing the radar cross-section and shock wave drag of the main air intake of the main engine 3, which is beneficial to reducing the drag coefficient during high-speed flight in the cruise phase, improving the stealth performance of the UAV, so as to replace or assist manned aircraft in forward reconnaissance or combat missions.

[0053] The variable configuration short takeoff and landing UAV and method based on upper surface air blowing lift provided by this invention have the following key technical points:

[0054] 1. Upper surface air blowing enhancement technology.

[0055] The low-pressure zone generated by the high-speed airflow of the auxiliary engine 8 can control the lifting body fuselage and delay the occurrence of stall. At the same time, the Coanda effect is used to deflect the airflow downward, effectively increasing circulation. Meanwhile, the Bernoulli principle is used to increase the pressure difference between the upper and lower surfaces, thereby increasing the lift coefficient, shortening the takeoff and landing distance, and improving the turning performance.

[0056] 2. Variable layout design.

[0057] By changing the relative positions of the variable nose module 1 and the fixed nose section 2, the aerodynamic layout of the aircraft can be altered. When the variable nose module 1 is in its original position, the canard 15 located on the variable nose module 1 is completely integrated with the fuselage of the fixed nose section 2 and the main wing 6, forming a blended wing-body layout.

[0058] When the variable nose module 1 is raised, the canard 15 located on the variable nose module 1 separates from the main wing 6, and the aircraft changes to a canard configuration, with the aerodynamic center and center of gravity moving forward.

[0059] 3. The air intake method can be changed by altering the relative position of the canard 15 and the main wing 6 located on the variable nose module 1.

[0060] When the variable nose module 1 slides upward, the main engine operates with conventional side intakes, offering good intake efficiency and being less affected at high angles of attack. When the variable nose module 1 is in its original position, the canard 15 can shield the main engine intake, making it a dorsal intake, reducing the wetted area and thus lowering the drag coefficient at high speeds. Simultaneously, it achieves better RCS performance, increasing the success rate of penetrating air superiority combat.

[0061] The variable configuration short takeoff and landing UAV and method based on upper surface air blowing enhancement provided by this invention have the following advantages:

[0062] 1. It combines the excellent lift-drag characteristics and turning performance of the canard layout with the excellent stealth performance and high lift-drag ratio of the blended wing-body layout. Through a variable layout scheme, it ensures a low drag coefficient during high-speed cruise flight and improves the lift coefficient during low-speed flight during takeoff and landing, thus delaying the stall.

[0063] 2. Implement two air intake methods for two different layout states.

[0064] During low-speed flight in the takeoff and landing phase, the trailing edge of the canard engages with the upper lip of the main air intake, and the main engine uses standard side air intakes. During high-speed cruise flight, a dorsal air intake is used, with the trailing edge of the canard engaging with the lower lip of the main air intake. This effectively shields the main engine's main air intake, significantly reducing its radar cross-section and improving the aircraft's stealth performance.

[0065] 3. In order to expand the jet control area and improve the blowing lift effect, a lifting body fuselage design was used to meet the lift increase requirements while obtaining a larger internal space, which can meet the requirements of long endurance and large payload.

[0066] 4. The air deflectors on both sides of the nose serve as nose rectifiers during low-speed flight, such as takeoff and landing. They not only balance the aerodynamic design contradictions caused by switching between the two layouts, but also increase the intake efficiency of the main engine at subsonic speeds by guiding airflow into the main air intake. Furthermore, they utilize their variable characteristics to design the auxiliary engine air intake at the front end of the air deflectors, so that the auxiliary engine air intake opens and closes with the rise and fall of the nose.

[0067] Therefore, the variable configuration short takeoff and landing UAV and method based on upper surface blowing lift provided by the present invention, based on the short takeoff and landing design of upper surface blowing lift and jet control principle, realizes the variable configuration conversion between canard configuration and blended wing-body configuration through simple nose operation, which can significantly shorten the takeoff and landing distance, while obtaining better turning and dogfighting performance. At the same time, the variable configuration design integrates the aerodynamic advantages of multiple overall configurations, which can significantly improve the technical indicators of the aircraft in all aspects to meet the needs of future combat.

[0068] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A method for a variable configuration short takeoff and landing unmanned aerial vehicle (UAV) based on upper surface air blowing for enhanced lift, characterized in that, Includes the following steps: Step 1: During takeoff and landing and when high-G maneuvers are required, the main engine (3) and auxiliary engine (8) are started simultaneously. The variable nose module (1) is raised forward and upward. When the upward movement of the variable nose module (1) ends, it becomes a canard configuration. At this time, the trailing edge (7) of the canard is connected to the upper lip (13) of the main air intake. An exposed part of the surface appears between the variable nose module (1) and the fixed part of the nose (2), exposing the auxiliary engine (8), the auxiliary engine air intake (10) and the nose guide slot A part (11). The lift is increased and the takeoff and landing distance is shortened in the following three aspects: First aspect: The external airflow flows into the auxiliary engine (8) from the auxiliary engine air intake (10) and supplies air to the auxiliary engine (8). The exhaust of the auxiliary engine (8) is discharged from the front end (9) of the auxiliary engine exhaust channel. The high-speed airflow discharged by the auxiliary engine (8) flows over the upper surface of the wing and continues to flow obliquely downward along the deflected flap. The low-pressure area generated at that time controls the lift of the fuselage (5), delays the stall, and at the same time uses the Coanda effect to deflect the airflow downward, significantly increasing the root velocity circulation and improving the root lift coefficient; at the same time, using the Bernoulli principle, the pressure difference between the upper and lower surfaces is increased, thereby increasing the lift coefficient, shortening the take-off and landing distance, and improving the turning performance; secondly: after the external airflow passes through the nose guide channel A part (11), it flows into the nose guide channel B part (12), and then flows into the main air intake of the main engine (3) through the nose guide channel B part (12), increasing the airflow into the main air intake of the main engine (3), thereby increasing the intake efficiency of the main engine (3) and improving the working lift of the main engine (3); thirdly: when the variable nose module (1) is raised forward and upward to the position and becomes a canard layout, the canard (15) is a short-pitch coupled canard, providing additional control torque and changing the aerodynamic center of the UAV, thereby increasing lift, shortening the take-off and landing distance and reducing the turning radius; Step 2: During the cruise phase, only the main engine (3) is started and the auxiliary engine (8) is shut down. The variable nose module (1) is reset to its original position. At this time, the canard (15) of the variable nose module (1) is completely integrated with the fuselage (5) and main wing (6) of the fixed nose part (2) to form a blended wing-body layout. At this time, the canard (15) is used as a strake wing. In addition, the trailing edge (7) of the canard (15) is connected to the lower lip of the main air intake, effectively shielding the main air intake of the main engine (3) and significantly reducing the radar cross-section of the main air intake of the main engine (3). This is beneficial to reduce the drag coefficient during high-speed flight in the cruise phase and improve the stealth performance of the UAV.

2. The method for a variable configuration short takeoff and landing UAV based on upper surface air blowing lift enhancement according to claim 1, characterized in that, The variable configuration short takeoff and landing (STOL) UAV based on the upper surface air-blown lift includes a variable nose module (1) and a UAV body; when the variable nose module (1) is in place, the STOL UAV has a blended wing-body configuration; when the variable nose module (1) is lifted forward and upward relative to the UAV body, the STOL UAV has a canard configuration, thereby realizing the configuration conversion between the STOL UAV and the blended wing-body configuration and the canard configuration.

3. The method for a variable configuration short takeoff and landing UAV based on upper surface air blowing for enhanced lift according to claim 2, characterized in that, An auxiliary engine (8) is installed inside the variable nose module (1). An auxiliary engine air intake (10) is installed at the front end of the variable nose module (1), and an auxiliary engine exhaust flow channel front end (9) is installed at the rear end of the variable nose module (1). Canards (15) are installed on the left and right sides of the variable nose module (1). The canards (15) have a canard leading edge (14) and a canard trailing edge (7). On both sides of the bottom of the variable nose module (1), a nose guide groove A part (11) is provided. The front end of the nose guide groove A part (11) is connected to the auxiliary engine air intake (10). The UAV body includes a fuselage (5), a nose fixing part (2) is provided at the front end of the fuselage (5), main wings (6) are provided on the left and right sides of the fuselage (5), a V-shaped tail fin (4) is provided at the rear of the fuselage (5), and a main engine (3) is provided on each side inside the fuselage (5); the main engine (3) has a main air intake upper lip (13); a nose guide groove B part (12) is provided on each side of the nose fixing part (2).

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