TWI727335B - An aircraft with stealth double wings - Google Patents

Abstract

An aircraft with stealth double wings comprises a main body and stealth double wings. The main body has two main wings respectively having a surface into which a space is formed. The stealth double wings respectively are located in the spaces and include a first and a second rotating shaft, a link rod, a first and a second wing. The link rod has two ends respectively connected with the two rotating shafts. The two rotating shafts respectively have another end connected with the first and second wings. Thereby, when the first wing is moved to cover and enclose the space’s opening, the second wing is driven to be located within the space, and when the first wing is moved upwardly away from the space, the second wing is driven to cover and enclose the space’s opening, so as to keep the surface intact.

Description

An aircraft with invisible biplanes

The present invention relates to an aircraft with stealth biplanes that can enhance radar stealth, quickly and smoothly change flight attitude control, and improve flight safety. It is especially suitable for stealth fighters, stealth bombers, and stealth reconnaissance aircraft. Reconnaissance), Stealth Unmanned Aerial Vehicle (UAV), Stealth Tanker, Stealth Attacker and other military aircraft.

The most important functional requirement of the next generation of future military aircraft under research and development is "radar stealth", which is to reduce the radar cross section (RCS) and radar echo in many ways to achieve the effect of mid- and far-end radar stealth. . In addition to the special stealth coating that absorbs radar waves on the fuselage of "Stealth Military Aircraft", the exterior design of the military aircraft can be changed to a flying wing design or a combined wing and fuselage design. The most important aspect of the overall appearance is to cancel the vertical tail and the traditional aircraft. Horizontal tail.

Due to the cancellation of the vertical tail design of the current flying wing military aircraft, the unique shape leads to the disadvantage of unstable flight attitude. Although modern military flight computers can automatically correct the unstable flight shortcomings of advanced military aircraft modeling, computer assistance can compensate for the appearance design of fighter jets. The above problem, but the cancellation of the vertical tail due to the need for the next-generation radar to disappear, the actual disadvantage of the flight is that it is not easy to quickly and smoothly change the attitude control, affect the movement of the ultra-high-speed change aircraft, and disadvantage the enemy's combat or countermeasures.

However, so the current design of this type of flying wing and tailless aircraft, such as The Northrop Grumman B-2 Spirit bomber, the Lockheed Martin RQ-170 Sentinel reconnaissance aircraft, and the Northrop Grumman X-47B UAV must be in good weather conditions to fly smoothly and safely, which will inevitably affect the execution of stealth military aircraft missions and severe weather conditions. Under the flight safety, such as military planes infiltrate the enemy’s territory to attack or reconnaissance, and military planes on aircraft carriers perform take-off and landing operations at sea.

However, due to the missions and operational requirements of stealth military aircraft, they may face changes in the weather. They must take off in bad weather to perform defense missions, or they must be forced to take off due to the exhaustion of fuel after cruising. Landing, or encounter sudden air interception by enemy military aircraft during combat missions, sudden attack by various air defense missiles, and even damage from ground air defense aircraft.

Because the sixth-generation stealth fighter in the current design lacks the vertical tail design, the flight operation must rely on the "thrust vectoring" engine nozzles to turn to the thrust vector nozzles, and the two spoilers above the wings are raised to perform. Adjust the up and down to the right direction, and these two ways to change the flight direction, the flight control response is not as flexible as the traditional design of the fifth-generation stealth fighter, and the deflected operation of the spoiler on the wing is not suitable for high-speed use, which will make the sixth The generation of stealth fighters, in real combat, due to the tailless design, the flight mobility is limited and not agile, and it may even be easily shot down or cause flight safety problems.

Therefore, how to effectively improve the above-mentioned shortcomings to further improve the flight safety of the stealth aircraft has always been the research direction of the inventor.

The main purpose of the present invention is to provide an aircraft with stealth biplanes that can enhance radar stealth, quickly and smoothly change attitude control, and improve flight safety.

In order to achieve the above-mentioned purpose, an aircraft with invisible biplanes is provided in the present invention. It includes an aircraft body and a pair of stealth double wings, the aircraft body has a main wing on each side, and the upper surface of the main wing is provided with a accommodating space; the stealth double wings are provided in the accommodating space of the main wing Among them, it includes a first shaft, a second shaft, a connecting rod, a first wing (vertical tail and part of the main wing surface function) and a second wing (part of the main wing surface function), wherein both ends of the connecting rod are connected The first rotating shaft and the second rotating shaft, one end of the first rotating shaft is connected to the first wing, and the other end of the second rotating shaft is connected to the second wing.

Thereby, when the first wing is closed and covered above the accommodating space of the main wing, the second wing can be driven by the first rotating shaft and the second rotating shaft to be accommodated in the middle of the accommodating space, When the first wing leaves the accommodating space upwards and turns into a vertical tail function and forms any angle, the second wing can be driven by the first and second rotating shafts to close and cover the main wing. Above the space. The purpose is to raise the first wing to a vertical tail to increase the controllability and stability of the stealth aircraft. Many specific actions are made in the air. When the second wing is raised or the first wing is lowered, the main wing surface is kept intact. , Maintain the original buoyancy and fluid mechanics.

When implemented, the first and second rotating shafts of the invisible double wing are controlled by a control system to drive the displacement of the first wing and the second wing.

In implementation, the main wing is provided with a protruding portion on the inner wall surface of the accommodating space, and the protruding portion can be attached to the end surface of the first wing.

In implementation, one end surface of the second wing is provided with a recessed portion that can fit with the protrusion on the inner wall surface of the main wing, so that the second wing can be affected by the protrusion after the second wing moves upward to the surface of the main wing. Block, so that the second wing is flatly covered on the accommodating space of the main wing.

In order to further understand the present invention, the following is a detailed description of the specific components of the present invention and the effects achieved by the preferred embodiments, in conjunction with the drawings and figure numbers.

1: Aircraft body

11: Main Wing

111: protrusion

12: accommodating space

13: Control system

2: Invisible wings

21: The first shaft

22: second shaft

23: connecting rod

24: First Wing

25: second wing

251: Depressed part

Figures 1A to 1E are schematic diagrams of the stealth bi-wings according to the present invention used for the stealth fighter to rise at various angles of 0°, 37°, 70°, and 90°.

Figure 2A is a schematic diagram of the left side view of a stealth fighter without a vertical tail.

Figure 2B is the folded side view of Figure 2A.

Figure 2C is a forward schematic view of the fighter's stealth wings when they are folded at 0°.

Figure 2D is a front cross-sectional view of Figure 2C.

Figure 2E is an enlarged partial cross-sectional view of Figure 2D.

Figure 3A is a front schematic view of the invisible wings raised at 37°.

Figure 3B is the left side view of the invisible wings raised at 37°.

Figure 3C is a left front cross-sectional view of the invisible double wings raised at 37°.

Figure 3D is an enlarged partial cross-sectional view of Figure 3C.

Figure 4A is a front view of the invisible double wings raised at 70°.

Figure 4B is the left side view with the invisible wings raised at 70°.

Figure 4C is the left front cross-sectional view of the invisible double wings raised at 70°

Figure 4D is an enlarged partial cross-sectional view of Figure 4C.

Figure 5A is a front view of the invisible double wings raised at 90°.

Figure 5B is the left side view of the invisible double wings raised at 90°.

Figure 5C is a left front cross-sectional view of the invisible double wings raised at 90°.

Figure 5D is an enlarged partial cross-sectional view of Figure 5C.

Figure 6A is a schematic diagram of the rising left and front of the stealth wings of the sloping wing.

Figure 6B is the left front cross-sectional view of the invisible double wings of the inclined wing.

Picture 7A is Stealth: the front view of the stealth fighter with Flying Invisible wings folded at 0°.

Figure 7B is the left side view of the fighter plane in Figure 7A.

Picture 7C is Stealth: the front view of the Fight stealth dual-wing 37° rising fighter.

Figure 7D is the left side view of the fighter plane in Figure 7C.

Picture 8A is Stealth: Fight Take Off/Landing Stealth Biplane 70° rising fighter front view.

Figure 8B is the left side view of the fighter plane in Figure 8A.

Figure 8C is a front view of the Emergency stealth dual-wing 90° folding fighter.

Figure 8D is the left side view of the fighter plane in Figure 8C.

Figure 9A is a schematic diagram of a fighter jet in the forward direction.

Figure 9B is a schematic diagram of the four angles of the first wing in Figure 9A.

Figure 9C is a schematic diagram of the left side of a fighter jet.

Figure 9D is a schematic diagram of the four angles of the first wing in Figure 9C.

Figure 10A is a top view of the airflow through the stealth fighter.

Figure 10B is a schematic diagram of the air flow through the wing after folding the invisible double wings.

Figure 11A is a top view of a stealth delta-wing drone with airflow passing through it.

Figure 11B is a schematic diagram of the air flow through the wing after folding the invisible double wings.

Figures 12A~12D are schematic diagrams of various combat flights when a stealth fighter is flying with stealth wings.

Figure 13 is a schematic diagram of the sixth-generation stealth fighter equipped with stealth wings.

Figures 14A to 14C are the left side schematic diagram, top view, and front view of the sixth-generation stealth fighter equipped with stealth wings. The overall wing width is the same as that of the U.S. Navy Boeing F/A-18E.

Figures 15A~15C are the top left view of the Northrop Grumman X-47B UAV, the bottom left is the stealth UAV with improved stealth wings, and the middle right is the comparison of the U.S. Navy Boeing F/A-18E profile of the same scale.

Figures 16A~16C are modular stealth wings. The top is the Northrop Grumman X-47A arrow-shaped UAV design. The bottom is the top view of the invisible double wings that can change the design of the aircraft. The middle is the same scale U.S. Navy Boeing. F/A-18E profile.

Figures 16D~16E show the top view of the Dassault nEUROn UAV, and the bottom is the top view of the invisible biplane that can change the design of the aircraft to a larger scale.

Figures 17A~17C show modular stealth wings. The top left is the Lockheed Martin MQ-25A Stingray unmanned carrier aviation air system (UCAAS) tanker. The bottom left is the design of other flying wing tankers, and the right is the same scale U.S. Navy Boeing F. /A-18E outline.

Figures 18A~18C show modular stealth wings, with different sixth-generation stealth fighters on the left and right, and the same proportion of the US Navy F/A-18E profile in the middle.

Figures 19A to 19C show modular stealth wings, with the B-2 bomber on the top, the B-21 bomber on the bottom, and the U.S. Navy F/A-18E profile on the bottom right.

Picture 20A shows the left side of the invisible unmanned tanker of the Probe-and-drogue system.

Figure 20B is a schematic diagram of the left side of the stealth unmanned tanker with its stealth wings retracted.

Picture 20C shows the left side of the Grappled-line looped-hose stealth unmanned tanker.

Please refer to Figures 1A-6B, which is a preferred embodiment of an aircraft with stealth biplanes of the present invention, including an aircraft body 1 and a stealth biplane 2.

The aircraft body 1 has a main wing 11 on each side, and the upper surface of the main wing 11 is There is an accommodating space 12, and the main wing 11 is provided with a protrusion 111 on the inner wall of the accommodating space 12.

The stealth double wings 2 are provided in the accommodating space 12 of the main wing 11, and include a first shaft 21, a second shaft 22, a connecting rod 23, a first wing 24, and a second wing. A wing 25, wherein the two ends of the connecting rod 23 are connected to the first shaft 21 and the second shaft 22, one end of the first shaft 21 is connected to the first wing 24, and the other end of the second shaft 22 is connected to the The second wing 25. The first rotating shaft 21 and the second rotating shaft 22 are controlled by a control system 13 arranged in the aircraft body 1 to drive the displacement of the first wing 24 and the second wing 25. In addition, the above-mentioned protrusion 111 can be attached to the end surface of the first wing 24 (as shown in Figure 2D), and an end surface of the second wing 25 is provided with an inner wall surface of the main wing 11 The recessed portion 251 where the protrusion 111 fits makes the second wing 25 move upward to the surface of the main wing 11, and then it can be blocked by the protrusion 111, so that the second wing 25 flatly covers the main wing 11 Above the accommodating space 12 (as shown in Figures 3C, 4C, and 5C). The purpose is that the first wing 24 is to increase the controllability and stability of the stealth aircraft, and to perform many specific actions in the air. When the second wing 25 is raised or the first wing 24 is lowered, it has the ability to keep the 11 surfaces of the main wing intact. , Maintain the original buoyancy and fluid mechanics.

In implementation, when the first wing 24 is closed and covered on the accommodating space 12 of the main wing 11, the second wing 25 can be driven by the first shaft 21 and the second shaft 22 to be accommodated in In the accommodating space 12, and the end surface of the first wing 24 can be closely attached to the protruding portion 111 of the main wing 11, so that the surface of the main wing 11 maintains a flatness (as shown in Figures 2A to 2E), And when the first wing 24 is controlled by the control system 13 to leave the accommodating space 12 upwards, turning into a vertical tail function and forming any angle (as shown in Figures 3A to 6B), the second wing 25 can be driven by the first rotating shaft 21 and the second rotating shaft 22 to move upward until the recessed portion 251 at one end of the second wing 25 abuts the protruding portion 111 to stop, thereby forming the second wing 25 closing cover The accommodation in the main wing 11 is empty Above the space 12, the surface of the main wing 11 is maintained to maintain a flatness.

Thus, as shown in Figures 7A-20C, whether it is applied to any aircraft type, the pilot and the computer can manually or automatically adjust to raise the first wing 24 of the invisible double wing 2 to become a vertical tail according to different flight mission requirements. Function to increase the maneuverability of the aircraft, or lower the invisible double wings 2 to hide, so that the first wing 24 becomes part of the main wing, whether it is folding or raising the invisible double wings 2, the first wing 24 and the The second wing 25 can maintain an even distribution of air pressure on the surface of the main wing 11 of the aircraft, so it does not affect fluid mechanics, achieves more stable flight and maintains lift buoyancy, so that the aircraft has excellent overall flexible control and improved performance.

Therefore, through the above design, the present invention has the following advantages:

1. Radar stealth and combat flight; the design of the stealth wings of the present invention meets various mission execution requirements, radar concealment effect and improved flight control. It has the advantages of fourth-generation fighter flight performance and fifth-generation stealth fighter. To achieve the purpose of the sixth-generation stealth fighter and various stealth military aircraft.

2. Various angles of vertical tail adjustment and maintenance of the main wing effect; the invisible vertical tail of the invisible double wing of the present invention can be adjusted in multiple angles, allowing the aircraft to adjust to maintain the best flight performance and maintain the integrity of the wing according to the mission and flight requirements effect.

3. Solve the problem of supersonic flight of fighters without vertical tails; fighters without vertical tails have always been unable to fly safely at supersonic speeds. Stealth biplanes can improve the stability of supersonic flight, save fuel and increase range.

4. Improve the safety of take-off and landing control for aircraft without vertical tails; the stealth dual-wing design can improve the safety of take-off and landing of fighters without vertical tails from the base, and is suitable for carrier-based stealth fighters without vertical tails on aircraft carriers, which can improve in harsh weather Maneuverability to ensure flying Crew and military aircraft safety.

5. Improve the agility of aerial combat and high-difficulty combat flight; due to the addition of invisible vertical tail and wing design, in addition to improving the control stability and flexibility, it can also achieve high battlefield survival rate and mission execution achievement rate.

6. Change the design of future stealth military aircraft; it can improve the design rationality of next-generation aircraft without vertical tails, apply different concepts of radar-concealed aircraft without vertical tails, and increase the volume and carrying capacity of the aircraft.

7. Modular design of stealth wings; stealth wings can be modular design, suitable for different military aircrafts without vertical tails.

8. Increase the stability and safety of aerial refueling; stealth wings can increase flight stability and safety during aerial refueling, and it is designed as a stealth unmanned refueling machine. Or other flying wing tanker designs (as shown in Figures 7 and 10).

9. It can be equipped with the function of the front wing to advance the flight; the stealth biplane can be equipped with the foreplane/canard function of the front wing of the stealth fighter to form a more flexible aerial operation.

The above are the specific embodiments of the present invention and the technical means used. Many changes and corrections can be derived from the disclosure or teaching of this article. They can still be regarded as equivalent changes made to the concept of the present invention. The function of the invention does not exceed the essential spirit covered by the specification and the drawings, and should be regarded as within the technical scope of the present invention, and should be explained first.

In summary, based on the content disclosed above, this invention clearly achieves the intended purpose of the invention, providing an aircraft with invisible biplanes, which is of great value for industrial use, and a patent application for invention is filed in accordance with the law.

11‧‧‧Main Wing

111‧‧‧Protrusion

12‧‧‧Accommodation space

2‧‧‧Invisible Wings

21‧‧‧The first shaft

22‧‧‧Second shaft

23‧‧‧Connecting rod

24‧‧‧First Wing

25‧‧‧Second Wing

Claims (4)

An aircraft with stealth double wings, comprising: an aircraft body with a main wing on each side of the main wing, the surface of the main wing is provided with an accommodating space; and a pair of stealth double wings for being arranged above the main wing The accommodating space includes a first rotating shaft, a second rotating shaft, a connecting rod, a first wing and a second wing, wherein both ends of the connecting rod are connected to the first rotating shaft and the second rotating shaft, and the One end of the first rotating shaft is connected to the first wing, and the other end of the second rotating shaft is connected to the second wing, which is linked with orbitally assisted; thereby, the first wing is closed and covered in the accommodating space of the main wing. When up, the second wing can be driven by the first and second rotating shafts to be accommodated in the accommodating space, and when the first wing leaves the accommodating space upwards, it turns into a vertical tail function and forms any At an angle, the second wing can be driven by the first and second rotating shafts to close and cover the upper part of the accommodating space of the main wing, so that the main wing surface remains intact and provides a hydrodynamic effect of lifting and floating. An aircraft with stealth biplanes as described in item 1 of the scope of patent application, wherein the first and second rotation shafts of the stealth biplane are controlled by a control system to drive the first wing and the second wing The displacement of the wing. As described in item 1 of the scope of patent application, an aircraft with stealth wings, wherein the main wing is provided with a protrusion on the inner wall surface of the accommodating space, and the protrusion can be attached to the end surface of the first wing . As described in item 3 of the scope of patent application, an aircraft with invisible biplanes, wherein one end surface of the second wing is provided with a recessed portion that can fit with the protrusion on the inner wall surface of the main wing, so that After the second wing is displaced upward to the surface of the main wing, it can be blocked by the protruding part, so that the second wing can be flatly covered on the accommodating space of the main wing.

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