Backpack layout low-noise supersonic aircraft

Abstract

The invention provides a backpack type layout low-noise supersonic aircraft, and belongs to the technical field of aircraft structure design, the supersonic aircraft comprises a fuselage, the front section of the fuselage is sequentially provided with a telescopic nose used for reducing noise, a nose motor used for controlling the telescopic nose, an avionics cabin used for containing an avionics system, and a cockpit, a passenger cabin is arranged at the middle section part of the fuselage, and a luggage compartment is arranged at the rear section part of the fuselage; the wings are lambda wings with large sweepback angles, and the lambda wings are arranged at the middle rear section of the fuselage; the engines are installed on wings on the two sides of a fuselage on the back of the aircraft through supporting frames, and gaps are formed between the engines and the wings; and the empennage is mounted on the engine and is of a triangular structure which is swept backwards.

Description

Technical Field

[0001] The present application belongs to the field of aircraft structure design, and in particular relates to a low-noise supersonic aircraft with a backpack layout. Background Art

[0002] With the successful development of the European Concorde and Tu-144, supersonic passenger aircraft have become a development boom. However, due to the performance defects of supersonic aircraft such as high fuel consumption, short range, high cost of use, high noise, and serious sonic boom problems, they have become unattainable in the market. With the rapid development of social economy and the improvement of people's living standards, people have higher and higher requirements for the comfort of air travel. For intercontinental long-distance flights, the ultra-long flight time of more than ten hours will cause boredom and fatigue during the journey, and it is difficult to meet the increasingly fast pace of life and work.

[0003] Therefore, there is an urgent need for a supersonic passenger aircraft with low noise, low boom, long range and high safety to meet the needs of fast and safe official travel. Summary of the invention

[0004] The purpose of the present application is to provide a low-noise supersonic aircraft with a backpack layout to solve or alleviate at least one problem in the background technology.

[0005] The technical solution of the present application is: a low-noise supersonic aircraft with a backpack layout, comprising:

[0006] A fuselage, wherein a retractable nose for noise reduction, a nose motor for controlling the retractable nose, an avionics compartment for accommodating an avionics system, and a cockpit are sequentially arranged at the front section of the fuselage, a passenger cabin is arranged at the middle section of the fuselage, and a luggage compartment is arranged at the rear section of the fuselage;

[0007] A wing, wherein the wing is a lambda wing with a large sweep angle, and the lambda wing is arranged at the middle and rear section of the fuselage;

[0008] An engine, wherein the engine is mounted on the wings on both sides of the back fuselage of the aircraft through a support frame, and there is a gap between the engine and the wing;

[0009] A tail wing is installed on the engine and is in a backward-swept triangular structure.

[0010] In an optional embodiment of the present application, the wing has a leading edge sweep angle of 70° to 75°.

[0011] In an optional embodiment of the present application, the air intake duct of the engine is configured as a binary rectangular inlet adjustable air intake duct.

[0012] In an optional embodiment of the present application, the supersonic aircraft further includes a landing gear, wherein the landing gear includes a front landing gear and a rear landing gear, wherein the front landing gear is located at a rear lower portion of the cockpit, and a ground scrubbing angle of the rear landing gear is set to 13° to 15°.

[0013] In an optional embodiment of the present application, the front landing gear is a double-wheel hybrid structure, and the rear landing gear is a double-row four-wheel vehicle structure.

[0014] In an optional embodiment of the present application, the retractable nose is a multi-stage retractable silent cone mechanism, which generates a series of weak shock waves to replace the strong shock waves generated by the head of the fuselage. The intensity and position of the weak shock waves are adjusted by the nose motor to avoid mutual superposition and interference during propagation.

[0015] In an optional embodiment of the present application, the retractable levels of the silent cone mechanism are three to four levels.

[0016] In an optional embodiment of the present application, the trailing edge of the lower surface of the wing and / or the trailing edge of the inner surface of the tail are provided with openings, through which the trailing edge expansion wave is sucked to thereby eliminate the trailing edge expansion wave.

[0017] The low-noise supersonic aircraft with a backpack layout provided in the present application can effectively reduce the sonic boom level of civil supersonic passenger aircraft by adopting a layout design of a low-boom twin-engine backpack lambda wing and an overlapping tail wing, in conjunction with a retractable silent cone at the nose and an air intake device at the trailing edge of the tail wing, and can achieve the requirement of an ultra-long range of 10,000 km, and achieve a rapid arrival time of 3 hours at a cruising speed of more than Mach 2. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0019] Figure 1 This is a schematic diagram of the supersonic aircraft structure of the present application.

[0020] Figure 2 This is a side view of the supersonic aircraft of this application.

[0021] Figure 3 This is a top view of the supersonic aircraft of this application.

[0022] Figure 4 FIG. 1 is a schematic diagram of a zero-resistance characteristic curve according to an embodiment of the present application.

[0023] Figure 5 FIG. 1 is a schematic diagram of a lift line slope curve according to an embodiment of the present application.

[0024] Figure 6Schematic diagram of a cruise lift-to-drag ratio curve according to an embodiment of the present application. DETAILED DESCRIPTION

[0025] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0026] The present application provides a low-noise supersonic aircraft with a backpack layout, which can effectively reduce the sonic boom level of a civil supersonic passenger aircraft, increase the aircraft's range, and reduce flight time by adopting a highly efficient aerodynamic layout design.

[0027] like Figures 1 to 3 As shown, the low-noise supersonic aircraft with a backpack layout provided by the present application includes a fuselage 1, wings 2, a tail wing 3, an engine 4 and a landing gear (not shown).

[0028] The front section of the fuselage 1 is provided with a retractable nose 11 for noise reduction, a nose motor 12 for controlling the movement of the retractable nose 11, an avionics compartment 13 for accommodating an avionics system, and a cockpit 14 in sequence; the middle section of the fuselage 1 is provided with a passenger cabin 15, and the rear section of the fuselage 1 is provided with a luggage compartment.

[0029] The wing 2 is a lambda wing with a large sweep angle, and the wing 2 is arranged at the middle and rear section of the fuselage 1. In some embodiments of the present application, the leading edge sweep angle of the wing 2 can be set to 70° to 75°.

[0030] The tail wing 3 is overlapped and mounted on the engine 3 to form a backward-swept triangular structure.

[0031] The engine 3 is mounted on the wings 2 on both sides of the back fuselage of the aircraft through a support frame, and there is a certain gap between it and the wing 2 for airflow to flow through, thereby forming a back-suspended structure. The air inlet of the engine 3 is configured as a binary rectangular inlet adjustable air inlet. In some embodiments of the present application, the engine 3 may use two GE9X model engines, whose thrust-to-weight ratio is about 0.9, and can achieve a designed cruising speed of Mach number 2.0 and a cruising altitude of 18.3km.

[0032] The landing gear includes a front landing gear and a rear landing gear, wherein the front landing gear can be located at the rear and lower part of the cockpit 14, and can adopt a double-wheel hybrid structure composed of pillars, multiple diagonal struts and cross beams, and the rear landing gear can adopt a double-row four-wheel trolley structure, and its ground rubbing angle can be set to 13°~15°.

[0033] Integral fuel tanks are arranged on both sides of the front fuselage 1, the middle of the rear fuselage and the area of ​​the wing 2. The fuel tanks are divided into two parts, the inner wing and the outer wing. The fuel tank capacity can reach 95m3.

[0034] The supersonic aircraft of the present application will generate shock waves during supersonic flight, and the shock waves mainly come from the front shock waves at the head of the fuselage 1 and the expansion waves at the trailing edges of the wings 2 and the tail 3 .

[0035] For the front shock wave at the head of the fuselage 1, the retractable nose 11 in the present application is set as a multi-stage retractable silent cone mechanism. By setting the retractable nose 11 in front of the head of the fuselage, a series of weak shock waves generated by the silent cone mechanism replace the strong shock wave generated by the head of the fuselage, and adjusting the strength and position of the weak shock waves by the nose motor 12, so as to avoid mutual superposition and interference during the propagation process. In some embodiments of the present application, the retractable silent cone mechanism can be set to three to four levels.

[0036] Regarding the trailing edge expansion waves of the wing 2 and the tail 3, in the present application, an opening is provided at the trailing edge of the lower surface of the wing 2 or the trailing edge of the inner surface of the tail 3, and an air suction effect is generated on the trailing edge expansion waves through the above-mentioned openings, thereby eliminating the trailing edge expansion waves.

[0037] The waveform parameter method was used for evaluation, and the results showed that under cruise conditions (Mach 2, altitude 18.3km), the maximum overpressure value was 15Pa, corresponding to a perceptible sound pressure level of 75PLdb.

[0038] In some embodiments of the present application, the fuselage 1 of the supersonic aircraft is 50 meters to 55 meters long, the wingspan is 20 meters to 22 meters, the aspect ratio is about 2, the wing area is about 242 square meters, and the wing load is about 500kg / square meters, so that the maximum take-off weight of the supersonic aircraft can be 121 tons, of which the load (including passengers) weight is about 12 tons, the fuel weight is 49 tons, and the empty weight is 60 tons. The cockpit space is about 3.7 meters high and about 4 meters wide, with a large space and a good view. The effective length of the cabin is about 12 meters, the width is about 4.5 meters, the height is about 3.7 meters, and the passenger capacity is about 12 people. The seats are first-class double seats and reconfigurable bench seats. The seats are ergonomic, and the lumbar support, headrest, etc. can be adjusted, and have flexible layout capabilities to improve the comfort of special passengers such as the elderly and overweight people. The multi-layer composite structure bulkhead adopts sound insulation felt, keel-filled sound insulation cotton and sound insulation board, and the seat cover and armrests are added to reduce noise and meet the private space needs. It is also equipped with noise-canceling headphones to support passengers' Internet communications.

[0039] like Figures 4 to 6 As shown in FIG. 1 , the aerodynamic characteristics of the supersonic aircraft of the present application are evaluated by using the CFD simulation method. The zero drag coefficient C of the supersonic aircraft of the present application is D0 The maximum is about 0.025, subsonic cruise lift-to-drag ratio K MAX The lift-to-drag ratio can reach 13.1, the supersonic cruise lift-to-drag ratio is 6.0, and the annular jet lift-enhancing device can increase the take-off and landing lift surface level by 20%, and the take-off and landing lift coefficient C Lα ≮1.0.

[0040] The low-noise supersonic aircraft with a backpack layout provided in the present application can effectively reduce the sonic boom level of civil supersonic passenger aircraft by adopting a low-boom twin-engine backpack lambda wing + overlapping tail wing layout design, combined with a retractable silent cone on the nose and an air intake device on the trailing edge of the tail wing, and can achieve the requirement of an ultra-long range of 10,000 km, and achieve a rapid arrival time of 3 hours at a cruising speed of more than Mach 2.

[0041] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A low-noise supersonic aircraft with a backpack layout, characterized in that: include: A fuselage, wherein a retractable nose for noise reduction, a nose motor for controlling the retractable nose, an avionics compartment for accommodating an avionics system, and a cockpit are sequentially arranged at the front section of the fuselage, a passenger cabin is arranged at the middle section of the fuselage, and a luggage compartment is arranged at the rear section of the fuselage; A wing, wherein the wing is a lambda wing with a large sweep angle, and the lambda wing is arranged at the middle and rear section of the fuselage; An engine, wherein the engine is mounted on the wings on both sides of the back fuselage of the aircraft through a support frame, and there is a gap between the engine and the wing; A tail wing is installed on the engine and is in a backward-swept triangular structure.

2. The low-noise supersonic aircraft with a backpack layout as claimed in claim 1, characterized in that: The wing has a leading edge sweep angle of 70° to 75°.

3. The low-noise supersonic aircraft with a backpack layout as claimed in claim 1, characterized in that: The air intake of the engine is configured as a binary rectangular inlet adjustable air intake.

4. The low-noise supersonic aircraft with a backpack layout as claimed in claim 1, characterized in that: The supersonic aircraft also includes a landing gear, which includes a front landing gear and a rear landing gear. The front landing gear is located at the rear and lower part of the cockpit, and the ground-rubbing angle of the rear landing gear is set to 13° to 15°.

5. The low-noise supersonic aircraft with a backpack layout as claimed in claim 4, characterized in that: The front landing gear is a double-wheel hybrid structure, and the rear landing gear is a double-row four-wheel vehicle structure.

6. The low-noise supersonic aircraft with a backpack layout as claimed in claim 1, characterized in that: The retractable nose is a multi-stage retractable silent cone mechanism, which generates a series of weak shock waves to replace the strong shock waves generated by the head of the fuselage. The intensity and position of the weak shock waves are adjusted by the nose motor to avoid mutual superposition and interference during propagation.

7. The low-noise supersonic aircraft with a backpack layout as claimed in claim 6, characterized in that: The retractable stages of the silent cone mechanism are three to four stages.

8. The low-noise supersonic aircraft with a backpack layout as claimed in claim 1, characterized in that: The trailing edge of the lower surface of the wing and / or the trailing edge of the inner surface of the tail are provided with openings, and an air suction effect is generated on the trailing edge expansion wave through the openings, thereby eliminating the trailing edge expansion wave.

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