A jet flow layout structure applicable to a flying wing layout unmanned aerial vehicle

Abstract

The application discloses a jet flow layout structure which can be used for a flying wing layout unmanned aerial vehicle. A jet flow control area is arranged on an outer wing of the aerial vehicle. A jet flow action area is arranged in a range of 57% to 86% of the span of the aerial vehicle, the jet flow action area accounts for 29% of the total span, and the jet flow action area is symmetrically arranged on the left and right sides of the aerial vehicle. The application is a new control technology for realizing the flight of the flying wing layout aerial vehicle without a rudder surface through an active flow control means. The active flow control means can replace the movable rudder surface on the conventional aerial vehicle, and can avoid the aerodynamic and stealth performance loss caused by the deflection of the rudder surface. The application is a new technical scheme for solving the common problems of the current flying wing layout aerial vehicle, such as the complex control system, the low efficiency of the rudder surface, the serious coupling of the rudder surface, and the obvious decline of the aerodynamic and stealth performance caused by the deflection of the rudder surface.

Description

Technical Field

[0001] This invention relates to a jet layout structure that can be used in flying wing unmanned aerial vehicles, belonging to the field of aircraft technology. Background Technology

[0002] Flying wing configuration is the future trend in the aerodynamic layout of aircraft for aerial reconnaissance, bombing, and transportation.

[0003] While flying wing designs offer advantages such as high aerodynamic efficiency and good stealth performance, they also present significant aerodynamic and control challenges. The most typical problem is the complexity of their control systems and low maneuverability. To ensure maneuverability, traditional flying wing designs require complex aerodynamic control surfaces such as flaps, ailerons, elevators, drag rudders, and diffusers. This complex control system results in high structural weight, a complex control system, and severe coupling between control surfaces. Furthermore, the geometric discontinuities caused by control surface deflection significantly reduce aerodynamic and stealth performance, severely limiting the core aerodynamic and stealth advantages of flying wing designs.

[0004] For future stealth aircraft, conventional design approaches are unlikely to effectively solve the aforementioned problems. Therefore, there is an urgent need to find an alternative to mechanical control surfaces to address the bottleneck issues of traditional flying wing layouts, where aerodynamics and stealth performance are limited by mechanical control surfaces, resulting in poor maneuverability. Summary of the Invention

[0005] The technical problem solved by the present invention is to overcome the shortcomings of the prior art and provide a jet layout structure that can be used in flying wing unmanned aerial vehicles, enabling flying wing aircraft to achieve controlless flight.

[0006] The technical solution of this invention is:

[0007] A jet layout structure that can be used in a flying wing unmanned aerial vehicle includes: a left inner wing, a right inner wing, a left outer wing, a right outer wing, a left jet arrangement area, and a right jet arrangement area;

[0008] The left inner wing and the right inner wing are symmetrical, and the left outer wing and the right outer wing are symmetrical; the left jet arrangement area and the right jet arrangement area are symmetrically located at the trailing edges of the left and right outer wings.

[0009] The left and right jet arrangement areas have the same structure, both including an upper jet channel and a lower jet channel, and jets can be ejected through the outlet of the upper jet channel and the outlet of the lower jet channel.

[0010] When jets are applied upwards simultaneously from both the left and right jet arrangement areas, the unmanned aerial vehicle is controlled to tilt up.

[0011] When both the left and right jet deployment areas apply jets downwards simultaneously, the unmanned aerial vehicle is controlled to tilt its head down.

[0012] When the jet deployment area on the left side of the rear view sprays upward while the jet deployment area on the right side sprays downward, control the unmanned aerial vehicle to roll to the left.

[0013] When the jet deployment area on the left side of the rear view sprays a jet downwards while the jet deployment area on the right side sprays a jet upwards, control the unmanned aerial vehicle to roll to the right;

[0014] When jets are applied simultaneously above and below the rear-view left jet arrangement area, the UAV is controlled to yaw to the left; when jets are applied simultaneously above and below the rear-view right jet arrangement area, the UAV is controlled to yaw to the right.

[0015] Furthermore, the left and right jet arrangement areas are located within 57% to 86% of the aircraft span.

[0016] Furthermore, the jet's effective area accounts for 29% of the total span.

[0017] Furthermore, the left jet arrangement area and the right jet arrangement area are located at 98% of the chord direction of the airfoil profile.

[0018] Furthermore, the jet outlet gap size of the left and right jet arrangement areas accounts for 0.5% of the local airfoil chord length.

[0019] Furthermore, the jet mass flow rates of the left and right jet arrangement areas are adjustable to maintain or change the flight attitude at different flight stages.

[0020] Furthermore, the upper and lower jet channels are converging channels, with an outlet-to-inlet area ratio of 1:6.

[0021] Furthermore, at Mach number Ma = 0.1 and pressure ratio Po / P = 1.1, the jet structure layout provides control of the aircraft comparable to the 20° deflection control capability of mechanical control surfaces; Po is the total pressure of the jet, and P is the ambient static pressure of the aircraft.

[0022] At Mach number Ma = 0.2 and pressure ratio Po / P = 1.1, the jet structure layout provides control of the aircraft comparable to the 10° deflection control capability of mechanical control surfaces.

[0023] The advantages of this invention compared to the prior art are:

[0024] (1) Reduce energy consumption

[0025] By replacing traditional active control surfaces with a jet control system, the drag of an aircraft during flight will be greatly reduced. Conventional flying wing aircraft, after installing various control surfaces, will have a series of sharp edges, openings, and gaps. These adverse factors can all be eliminated in jet-controlled aircraft, making the aircraft smoother, effectively reducing aerodynamic drag during flight, and thus reducing energy consumption and increasing range.

[0026] (2) Reduce the detectability of aircraft

[0027] The goal of radar stealth design is to minimize the radar cross-section (RCS). The size of the RCS is determined by radar wave reflectivity, the aircraft's geometric area and characteristics, and the direction of radar wave reflection. The first factor primarily depends on the absorbing materials and structures, while the latter two are determined by the aircraft's shape. Flaps, ailerons, and other movable control surfaces are significant radar emitters on an aircraft, increasing the overall RCS. By employing a jet-based control system, these emitters almost completely disappear, significantly improving the aircraft's stealth capabilities.

[0028] (3) Improve high angle of attack performance

[0029] Flying wing aircraft often suffer from low control surface efficiency. When the control surface deflection angle is large, the surrounding airflow easily separates, causing the control efficiency to drop below safe levels or even malfunction. This significantly hinders attitude control and severely limits the aircraft's angle-of-attack range. Replacing traditional control surfaces with jet-like flight control technology effectively controls and reduces the wing's separation zone, ensuring control efficiency during high angle-of-attack flow separation, increasing the usable angle-of-attack range, and improving overall aerodynamic performance.

[0030] (4) Reduce the difficulty of inspection and maintenance and improve the attendance rate.

[0031] Conventional flying wing aircraft, due to their numerous moving control surfaces and complex internal transmission and hinge mechanisms, require frequent inspections and maintenance before and after each flight mission due to structural fatigue, reliability, and safety considerations. By adopting control surface-less jet flight control technology, the number of moving control surfaces and related control subsystem components on the aircraft is significantly reduced, decreasing the overall number of parts and improving system reliability. Attached Figure Description

[0032] Figure 1 This is a structural diagram of the present invention;

[0033] Figure 2 This is the front view of the present invention;

[0034] Figure 3 This is a cross-sectional view of the airfoil in the jet arrangement area of ​​the present invention;

[0035] Figure 4 A magnified view of the trailing edge of the airfoil in the jet arrangement area;

[0036] Figure 5 This is a diagram of the jet spanwise arrangement area of ​​the present invention;

[0037] Figure 6 This is the curve showing the pitch moment coefficient as a function of angle of attack for Ma0.1 jet control and mechanical control surfaces in this invention;

[0038] Figure 7 This is the curve showing the pitch moment coefficient of Ma0.2 jet control and mechanical control surface control as a function of angle of attack in this invention. Detailed Implementation

[0039] The present invention will be further described below with reference to the accompanying drawings and specific embodiments:

[0040] Surface-free jet control technology is a new type of control technology that achieves flight control through active flow control. It can replace the movable control surfaces on conventional aircraft, avoiding the loss of aerodynamic and stealth performance caused by control surface deflection. It is the most promising technical solution to solve common problems such as the complexity of current flying wing aircraft control systems, low control surface efficiency, serious control surface manipulation coupling, and significant decline in aerodynamic and stealth performance caused by control surface deflection.

[0041] Jet control technology can maximize the aerodynamic and stealth advantages of flying wing configurations, giving them more prominent advantages and broad application prospects. For example, in next-generation stealth bombers, it can increase range and reduce radar detection distance; in next-generation stealth reconnaissance aircraft, it can improve flight time and stealth capabilities. Once this technology matures, it can revolutionize the design philosophy of next-generation aircraft and significantly expand the conceptual design space of future aircraft, with very broad application prospects in the military field.

[0042] This invention is a novel control technology that achieves flight control through active flow control. It can replace the movable control surfaces on conventional aircraft, avoiding the loss of aerodynamic and stealth performance caused by control surface deflection. It is a technical solution to solve common problems of current flying wing aircraft control systems, such as complexity, low control surface efficiency, severe control surface coupling, and significant decline in aerodynamic and stealth performance caused by control surface deflection.

[0043] The flying wing configuration jet control technology of this invention achieves the maintenance and adjustment of the aircraft's flight attitude through jet devices arranged on the outer wing. The technical approach is to arrange jet-propellable jets on the upper and lower wing surfaces, apply jets upward from both sides simultaneously to control the aircraft to pitch up; apply jets downward from both sides simultaneously to control the aircraft to pitch down; apply jets upward from the left side and downward from the right side to control the aircraft to roll left; apply jets downward from the left side and upward from the right side to control the aircraft to roll right; apply jets upward and downward from both sides of the left side to control the aircraft to yaw left; apply jets upward and downward from both sides of the right side to control the aircraft to yaw right.

[0044] like Figure 1 and Figure 2 As shown, the present invention proposes a jet layout structure that can be used for flying wing unmanned aerial vehicles, specifically including: left inner wing 1, right inner wing 2, left outer wing 3, right outer wing 4, left jet arrangement area 5, and right jet arrangement area 6.

[0045] The left inner wing 1 and the right inner wing 2 are symmetrical, and the left outer wing 3 and the right outer wing 4 are symmetrical; the left jet arrangement area 5 and the right jet arrangement area 6 are symmetrically arranged at the trailing edges of the left outer wing 3 and the right outer wing 4.

[0046] The left jet arrangement area 5 and the right jet arrangement area 6 have the same structure, both including an upper jet channel and a lower jet channel, and jets can be ejected through the outlet of the upper jet channel and the outlet of the lower jet channel.

[0047] When the left jet arrangement area 5 and the right jet arrangement area 6 simultaneously apply jets upward, the unmanned aerial vehicle is controlled to tilt up.

[0048] When the left jet arrangement area 5 and the right jet arrangement area 6 apply jets downwards simultaneously, the unmanned aerial vehicle is controlled to tilt its head down.

[0049] When the jet arrangement area 5 on the left side sprays upward while the jet arrangement area 6 on the right side sprays downward, control the unmanned aerial vehicle to roll to the left.

[0050] When the jet arrangement area 5 on the left side sprays a jet downwards while the jet arrangement area 6 on the right side sprays a jet upwards, control the unmanned aerial vehicle to roll to the right.

[0051] When jets are applied simultaneously above and below the left rear-view jet arrangement area 5, the UAV is controlled to yaw to the left; when jets are applied simultaneously above and below the right rear-view jet arrangement area 6, the UAV is controlled to yaw to the right.

[0052] like Figure 2 As shown, the technology verification platform is a stealth flying wing unmanned aerial vehicle.

[0053] like Figure 5As shown, the left jet arrangement area 5 and the right jet arrangement area 6 are arranged within a range of 57% to 86% of the aircraft's span. The jet action area accounts for 29% of the total span.

[0054] like Figure 3 As shown, the left jet arrangement area 5 and the right jet arrangement area 6 are located at 98% of the chord direction of the airfoil profile.

[0055] like Figure 3 and Figure 4 As shown, the jet outlet gap size of the left jet arrangement area 5 and the right jet arrangement area 6 accounts for 0.5% of the local airfoil chord length.

[0056] Preferably, the upper jet channel and the lower jet channel are converging channels, and the ratio of the jet outlet area to the inlet area is 1:6.

[0057] Preferably, the jet mass flow rates of the left jet arrangement area 5 and the right jet arrangement area 6 are adjustable to maintain or change the flight attitude at different flight stages.

[0058] like Figure 6 As shown, when Mach number Ma = 0.1 and pressure ratio Po / P = 1.1, the jet structure layout provides control of the aircraft comparable to the mechanical control surface with a 20° deflection capability; Po is the total pressure of the jet, and P is the ambient static pressure of the aircraft.

[0059] like Figure 7 As shown, at Mach number Ma = 0.2 and pressure ratio Po / P = 1.1, the jet structure layout provides control of the aircraft comparable to the mechanical control surface's 10° deflection control capability.

[0060] The working principle of this invention is as follows: jet control technology for flying wing unmanned aerial vehicles (UAVs) can spray jets from both the upper and lower wing surfaces. Jets are applied upwards from both sides simultaneously to control the aircraft to pitch up; jets are applied downwards simultaneously to control the aircraft to pitch down; jets spray upwards from the left side and downwards from the right side control the aircraft to roll to the left; jets spray downwards from the left side and upwards from the right side control the aircraft to roll to the right; jets are applied upwards and downwards from the left side simultaneously to control the aircraft to yaw to the left; jets are applied upwards and downwards from the right side simultaneously to control the aircraft to yaw to the right.

[0061] This invention innovatively proposes a jet-flow layout structure that can be used for flying-wing unmanned aerial vehicles. By replacing traditional mechanical control surfaces with jet-flow control technology, it solves the problems of complex control systems, low control surface efficiency, severe control surface coupling, and significant reduction in aerodynamic and stealth performance caused by control surface deflection in current flying-wing aircraft. This allows the aircraft to increase its flight range and improve its stealth performance with the same energy consumption.

[0062] Because of their simple structure and ease of maintenance, these control systems not only reduce operating and maintenance costs but also significantly improve the combat efficiency of aircraft. They offer substantial improvements in mean time between failures (MTBF), takeoff readiness time, and takeoff and landing capabilities in complex terrain. This will facilitate the scheduling of more intensive flight missions during wartime, thereby gaining a strategic and tactical advantage.

[0063] Although embodiments of the present invention have been disclosed above, they are not limited to the applications listed in the specification and embodiments. They can be applied to various fields suitable for the present invention. For those skilled in the art, other modifications can be easily made. Therefore, without departing from the general concept defined by the claims and their equivalents, the present invention is not limited to the specific details and illustrations shown and described herein.

[0064] The contents not described in detail in this specification are known to those skilled in the art.

Claims

1. A jet layout structure that can be used in flying-wing unmanned aerial vehicles, characterized in that... include: Left inner wing (1), right inner wing (2), left outer wing (3), right outer wing (4), left jet arrangement area (5), right jet arrangement area (6); The left inner wing (1) and the right inner wing (2) are symmetrical, and the left outer wing (3) and the right outer wing (4) are symmetrical; the left jet arrangement area (5) and the right jet arrangement area (6) are symmetrically arranged at the trailing edges of the left outer wing (3) and the right outer wing (4); The left jet arrangement area (5) and the right jet arrangement area (6) have the same structure, both including an upper jet channel and a lower jet channel, and jets can be ejected through the outlet of the upper jet channel and the outlet of the lower jet channel; When the left jet arrangement area (5) and the right jet arrangement area (6) simultaneously apply jets upward, the unmanned aerial vehicle is controlled to tilt up. When the left jet arrangement area (5) and the right jet arrangement area (6) simultaneously apply jets downwards, the unmanned aerial vehicle is controlled to lower its head. When the left jet arrangement area (5) sprays jets upward and the right jet arrangement area (6) sprays jets downward, control the unmanned aerial vehicle to roll to the left. When the left jet arrangement area (5) sprays a jet downwards while the right jet arrangement area (6) sprays a jet upwards, control the unmanned aerial vehicle to roll to the right. When jets are applied simultaneously above and below the rear-view left jet arrangement area (5), the unmanned aerial vehicle is controlled to yaw to the left; when jets are applied simultaneously above and below the rear-view right jet arrangement area (6), the unmanned aerial vehicle is controlled to yaw to the right. The left jet arrangement area (5) and the right jet arrangement area (6) are arranged in the range of 57% to 86% of the aircraft span. The jet's effective area accounts for 29% of the total span. The left jet arrangement area (5) and the right jet arrangement area (6) are located at 98% of the chord direction of the airfoil profile; The jet outlet gap size of the left jet arrangement area (5) and the right jet arrangement area (6) accounts for 0.5% of the local airfoil chord length; The upper and lower jet channels are converging channels, and the ratio of the jet outlet area to the inlet area is 1:

6.

2. The jet layout structure for use in flying-wing unmanned aerial vehicles according to claim 1, characterized in that: The jet mass flow rates of the left jet arrangement area (5) and the right jet arrangement area (6) are adjustable, which are used to maintain or change the flight attitude at different flight stages.

3. The jet layout structure for use in flying-wing unmanned aerial vehicles according to claim 1, characterized in that: At Mach number Ma=0.1 and pressure ratio Po / P=1.1, the jet layout structure provides control of the aircraft comparable to the 20° deflection control capability of mechanical control surfaces; Po is the total pressure of the jet, and P is the ambient static pressure of the aircraft.

4. The jet layout structure for use in flying-wing unmanned aerial vehicles according to claim 1, characterized in that: At Mach number Ma=0.2 and pressure ratio Po / P=1.1, the jet layout structure provides control of the aircraft comparable to the mechanical control surface's 10° deflection control capability.

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