Supersonic civil aircraft layout

Abstract

The invention belongs to the technical field of aviation, and particularly relates to a supersonic civil aircraft layout. According to the supersonic civil aircraft layout, the engine nacelle is installed above the rear fuselage between the wing and the horizontal tail, the lower portion of the air inlet is shielded by the rear edge of the wing, the lower portion of the air outlet is shielded by the front edge of the horizontal tail, shock waves generated by the engine are prevented from spreading to the ground through the shielding effect of the wing and the horizontal tail, and the ground sound explosion loudness of the aircraft is effectively reduced; the engine and the hanger can perform small-angle pitching deflection around the rotating shaft in the hanger, so that the mounting angle of the engine is adjusted, and the propulsive efficiency of the engine under the non-design-point working condition is improved; the horizontal tail tip can be folded upwards to provide additional vertical tail capacity during supersonic cruising, loss of vertical tail efficiency during supersonic cruising is made up, and expansion waves generated by an engine exhaust nozzle and a horizontal tail are prevented from spreading to the ground. And the wingtip is put down during low-speed take-off and landing, so that a larger horizontal tail area is ensured, and the trimming requirement of a take-off and landing structure is met.

Description

Technical Field

[0001] The present application belongs to the field of aviation technology, and in particular relates to a supersonic civil aircraft layout. Background Art

[0002] In the design process of supersonic civil aircraft layout, it is necessary to focus on sonic boom suppression, balancing engine propulsion efficiency in the full speed range, and the reduction in vertical tail efficiency during supersonic cruise.

[0003] When a conventional supersonic civil aircraft is cruising at supersonic speed, the shock waves generated by the engine's intake and exhaust systems merge with the shock waves generated by other parts of the aircraft. When transmitted to the ground, they greatly increase the loudness of the ground sonic boom, bringing significant difficulties to the airworthiness certification of such aircraft.

[0004] In the current research on supersonic civil aircraft being conducted by countries around the world and related research institutions, the engine and its intake and exhaust system are generally designed with the highest flight Mach number as their design point. Under conditions that deviate from the design point, the performance deteriorates rapidly, which will directly lead to a series of adverse consequences such as reduced engine propulsion efficiency, increased fuel consumption and external resistance. When flying over densely populated urban areas, supersonic civil aircraft usually need to use subsonic cruise to avoid the impact of sonic booms on the normal lives of people on the ground. At this time, the engine deviates from its design point and the propulsion efficiency is reduced.

[0005] During supersonic cruise, the tail capacity of the vertical tail of a supersonic civil aircraft will drop significantly, and the heading stability will also drop.

[0006] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0007] The purpose of the present application is to provide a supersonic civil aircraft layout to solve at least one problem existing in the prior art.

[0008] The technical solution of this application is:

[0009] A supersonic civil aircraft layout, comprising:

[0010] body;

[0011] a left wing, located at the left side of the center rear of the fuselage;

[0012] a right wing, located at the right side of the center rear of the fuselage;

[0013] a left trailing edge flap, located inboard of the left wing trailing edge;

[0014] a right trailing edge flap, located inboard of the right wing trailing edge;

[0015] A left trailing edge aileron, located outside the trailing edge of the left wing;

[0016] a right trailing edge aileron, located outside the trailing edge of the right wing;

[0017] A left engine nacelle, mounted on the fuselage behind the left wing via a left engine nacelle hanger;

[0018] a right engine nacelle, mounted on the fuselage behind the right wing via a right engine nacelle mount;

[0019] A tail-mounted left engine, installed in the left engine nacelle;

[0020] a tail-mounted right engine, mounted in the right engine nacelle;

[0021] A fully movable horizontal tail, comprising a left horizontal tail and a right horizontal tail, wherein the left horizontal tail is located on the left side of the tail of the fuselage, and the right horizontal tail is located on the right side of the tail of the fuselage;

[0022] The vertical tail is located on the upper side of the tail of the fuselage, and a rudder is installed on the trailing edge of the vertical tail.

[0023] In at least one embodiment of the present application,

[0024] The front end of the left wing is connected to the fuselage at a position 1 / 2 the length of the fuselage;

[0025] The front end of the right wing is connected to the fuselage at a position of 1 / 2 the length of the fuselage.

[0026] In at least one embodiment of the present application,

[0027] The left wing has a wing root leading edge sweep angle of 75° and a wing tip leading edge sweep angle of 60°;

[0028] The right wing has a wing root leading edge sweep angle of 75° and a wing tip leading edge sweep angle of 60°.

[0029] In at least one embodiment of the present application,

[0030] The curvature of the wing root leading edge and the wing tip leading edge of the left wing are smoothly transitioned;

[0031] The curvature of the wing root leading edge and the wing tip leading edge of the right wing are smoothly transitioned.

[0032] In at least one embodiment of the present application,

[0033] The left engine nacelle pylon is connected to the fuselage via a left engine nacelle pylon rotating shaft;

[0034] The right pylon of the engine nacelle is connected to the fuselage via a right pylon shaft of the engine nacelle.

[0035] In at least one embodiment of the present application,

[0036] The rotation axis of the left engine nacelle pylon is located at 3 / 5 of the chord length at the root and 1 / 3 of the chord length at the tip of the left engine nacelle pylon, and the left engine nacelle pylon can perform pitch and deflection around the rotation axis of the left engine nacelle pylon;

[0037] The rotation axis of the right pylon of the engine nacelle is located at 3 / 5 of the chord length at the root and 1 / 3 of the chord length at the tip of the right pylon of the engine nacelle, and the right pylon of the engine nacelle can perform pitch and deflection around the rotation axis of the right pylon of the engine nacelle.

[0038] In at least one embodiment of the present application,

[0039] The left engine air inlet of the left engine nacelle is located above the trailing edge of the left wing;

[0040] The right engine air inlet of the right engine nacelle is located above the trailing edge of the right wing.

[0041] In at least one embodiment of the present application,

[0042] The left engine exhaust port of the left engine nacelle is located above the leading edge of the left horizontal tail;

[0043] The right engine exhaust port of the right engine nacelle is located above the leading edge of the right horizontal tail.

[0044] In at least one embodiment of the present application,

[0045] The deflection angle range of the left horizontal tail is +20° to -15°;

[0046] The deflection angle range of the right horizontal tail is +20° to -15°.

[0047] In at least one embodiment of the present application,

[0048] A foldable horizontal tail wing tip portion is provided at the wing tip of the left horizontal tail via a left horizontal tail wing tip rotating shaft;

[0049] A foldable horizontal tail wing tip portion is arranged at the wing tip of the right horizontal tail via a right horizontal tail wing tip rotating shaft.

[0050] In at least one embodiment of the present application,

[0051] The left horizontal tail wing tip rotation axis is arranged at the wing tip of the left horizontal tail at 85% of the span;

[0052] The right horizontal tail wing tip rotation axis is arranged at a wing tip at 85% of the span of the right horizontal tail.

[0053] In at least one embodiment of the present application, the foldable portion of the horizontal tail wing tip can be folded upward by 90°.

[0054] In at least one embodiment of the present application,

[0055] The left horizontal tail is a pointed delta wing;

[0056] The right horizontal tail is a pointed delta wing.

[0057] In at least one embodiment of the present application,

[0058] The leading edge sweep angle of the left horizontal tail is 60°;

[0059] The leading edge sweep angle of the right horizontal tail is 60°.

[0060] In at least one embodiment of the present application, the trailing edge of the vertical tail is located at 7 / 8 of the chord length of the full-moving horizontal tail.

[0061] In at least one embodiment of the present application, the leading edge sweep angle of the vertical tail is 54°.

[0062] The invention has at least the following beneficial technical effects:

[0063] The supersonic civil aircraft layout of the present application has an engine nacelle installed above the rear fuselage between the wing and the horizontal tail, with the lower part of the air inlet shielded by the trailing edge of the wing and the lower part of the exhaust shielded by the leading edge of the horizontal tail. The shielding effect of the wing and the horizontal tail is used to prevent the shock wave generated by the engine from propagating to the ground, effectively reducing the ground sonic boom loudness of such aircraft; the engine and the pylon can be pitched and deflected at a small angle around the rotating shaft in the pylon, so as to adjust the installation angle of the engine and improve the propulsion efficiency of the engine under non-design point conditions; the horizontal tail wing tip can be folded upward during supersonic cruise to provide additional vertical tail tail capacity, compensate for the loss of vertical tail efficiency during supersonic cruise, and prevent the expansion wave generated by the engine tail nozzle and the horizontal tail from propagating to the ground; the wing tip is lowered during low-speed takeoff and landing to ensure a larger horizontal tail area to meet the take-off and landing configuration balancing requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0064] Figure 1 is a side view of the layout of a supersonic civil aircraft according to one embodiment of the present application;

[0065] Figure 2 is a top view of the layout of a supersonic civil aircraft according to one embodiment of the present application;

[0066] Figure 3 This is a front view of the layout of a supersonic civil aircraft according to one embodiment of the present application;

[0067] Figure 4 This is an axial view of the supersonic civil aircraft layout according to one embodiment of the present application.

[0068] in:

[0069] 1-fuselage; 2-vertical tail; 3-rudder; 4-right wing; 5-left wing; 6-right engine air inlet; 7-left engine air inlet; 8-engine nacelle right pylon shaft; 9-engine nacelle left pylon shaft; 10-engine nacelle right pylon; 11-engine nacelle left pylon; 12-right engine exhaust port; 13-left engine exhaust port; 14-right horizontal tail wing tip shaft; 15-left horizontal tail wing tip shaft; 16-left engine nacelle; 17-right engine nacelle; 18-horizontal tail wing tip foldable part. DETAILED DESCRIPTION

[0070] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0071] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0072] The following is combined with Figures 1 to 4 This application is described in further detail.

[0073] The present application provides a supersonic civil aircraft layout, including: a fuselage 1, a left wing 5, a right wing 4, a left trailing edge flap, a right trailing edge flap, a left trailing edge aileron, a right trailing edge aileron, a left engine nacelle 16, a right engine nacelle 17, a tail-mounted left engine, a tail-mounted right engine, a fully movable horizontal tail and a vertical tail 2.

[0074] Specifically, the left wing 5 is located at the left side of the middle and rear part of the fuselage 1; the right wing 4 is located at the right side of the middle and rear part of the fuselage 1; the left trailing edge flap is located at the inner side of the trailing edge of the left wing 5; the right trailing edge flap is located at the inner side of the trailing edge of the right wing 4; the left trailing edge aileron is located at the outer side of the trailing edge of the left wing 5; and the right trailing edge aileron is located at the outer side of the trailing edge of the right wing 4.

[0075] In the preferred embodiment of the present application, the front end of the left wing 5 is connected to the fuselage 1 at a position of 11 / 2 length of the fuselage; the front end of the right wing 4 is connected to the fuselage 1 at a position of 11 / 2 length of the fuselage. The left wing 5 has a 75° wing root leading edge sweep angle, and a 60° wing tip leading edge sweep angle; the right wing 4 has a 75° wing root leading edge sweep angle, and a 60° wing tip leading edge sweep angle. The left wing 5 has a smooth transition between the wing root leading edge and the wing tip leading edge curvature; the right wing 4 has a smooth transition between the wing root leading edge and the wing tip leading edge curvature.

[0076] The left engine nacelle 16 is installed on the fuselage 1 behind the left wing 5 through the engine nacelle left bracket 11; the right engine nacelle 17 is installed on the fuselage 1 behind the right wing 4 through the engine nacelle right bracket 10; the tail-mounted left engine is installed in the left engine nacelle 16; and the tail-mounted right engine is installed in the right engine nacelle 17.

[0077] In the preferred embodiment of the present application, the left nacelle pylon 11 is connected to the fuselage 1 through the left nacelle pylon shaft 9; the right nacelle pylon 10 is connected to the fuselage 1 through the right nacelle pylon shaft 8. The left nacelle pylon shaft 9 is located at the 3 / 5 chord length of the root of the left nacelle pylon 11 and the 1 / 3 chord length of the tip, and the left nacelle pylon 11 can be pitched around the left nacelle pylon shaft 9; the right nacelle pylon shaft 8 is located at the 3 / 5 chord length of the root of the right nacelle pylon 10 and the 1 / 3 chord length of the tip, and the right nacelle pylon 10 can be pitched around the right nacelle pylon shaft 8. The left engine air inlet 7 of the left nacelle 16 is located above the trailing edge of the left wing 5; the right engine air inlet 6 of the right nacelle 17 is located above the trailing edge of the right wing 4. The left engine exhaust port 13 of the left engine nacelle 16 is located above the leading edge of the left horizontal tail; the right engine exhaust port 12 of the right engine nacelle 17 is located above the leading edge of the right horizontal tail.

[0078] The full-movable horizontal tail includes a left horizontal tail and a right horizontal tail. The left horizontal tail is located on the left side of the tail of the fuselage 1, and the right horizontal tail is located on the right side of the tail of the fuselage 1; the vertical tail 2 is located on the upper side of the tail of the fuselage 1, and a rudder 3 is installed on the trailing edge of the vertical tail 2.

[0079] In a preferred embodiment of the present application, the deflection angle range of the left tailplane is +20° to -15°; the deflection angle range of the right tailplane is +20° to -15°. A tailplane wingtip foldable portion 18 is provided at the wingtip of the left tailplane through the left tailplane wingtip shaft 15; a tailplane wingtip foldable portion 18 is provided at the wingtip of the right tailplane through the right tailplane wingtip shaft 14. The left tailplane wingtip shaft 15 is provided at the wingtip of 85% of the span of the left tailplane; the right tailplane wingtip shaft 14 is provided at the wingtip of 85% of the span of the right tailplane. The tailplane wingtip foldable portion 18 can be folded upward by 90°. The left tailplane is a truncated delta wing; the right tailplane is a truncated delta wing. The leading edge sweep angle of the left tailplane is 60°; the leading edge sweep angle of the right tailplane is 60°. The trailing edge of the vertical tail 2 is located at the 7 / 8 chord length position of the full-moving tailplane. The leading edge sweep angle of the vertical tail 2 is 54°.

[0080] Advantageously, the layout of the supersonic civil aircraft allows the high-temperature, high-speed airflow of the engine tail jet to be shielded by the upper surface of the all-moving horizontal tail through the arrangement of the engine air inlet and exhaust ports, and the spanwise position of the tail jet is shielded by the upwardly folded all-moving horizontal tail wing tip.

[0081] The supersonic civil aircraft layout of the present application can solve the following problems existing in the use of supersonic civil aircraft:

[0082] (1) During supersonic cruise, the shock waves / expansion waves generated by the engine intake / exhaust system merge with the shock waves / expansion waves generated by other aircraft components and, after being transmitted to the ground, greatly increase the loudness of the ground sonic boom;

[0083] (2) In the cruising state of a supersonic civil aircraft, the angle of attack of the aircraft itself, the installation angle of the nacelle, and the downward deflection angle of the engine tail nozzle make the engine thrust and the incoming flow have an angle, that is, the thrust axis has a small positive angle of attack relative to the incoming flow. This angle causes a loss of thrust in the direction of flight, but an increase in the direction of lift. Therefore, corresponding to a fixed lift-to-drag ratio, there should theoretically be an optimal thrust axis deflection.

[0084] The deflection of the thrust axis is directly related to the lift-to-drag ratio of the aircraft. Assuming the lift-to-drag ratio of the aircraft is K, when the angle between the thrust axis and the flight direction is 0, the thrust is T, and the lift is KT. When the thrust axis and the flight direction have an angle α, since the thrust T has an increment Tsinα in the lift direction, the actual lift of the aircraft is reduced to KT-Tsinα. It can be deduced that the thrust required in the flight direction should be T-Tsinα / K, and the actual thrust is Tcosα, so the residual thrust is Tcosα-(T-Tsinα / K). The larger the residual thrust, the higher the propulsion efficiency, so the problem is transformed into a mathematical problem of finding the maximum value of the following formula.

[0085] Tcosα-(T-Tsinα / K)

[0086] Assuming T and K are constants and making the derivative of this formula with respect to α equal to 0, we can get the value of α when the above formula reaches its maximum value.

[0087] The maximum propulsion efficiency is derived as:

[0088] α=arctan(1 / K)

[0089] Supersonic civil aircraft engines and their intake and exhaust systems are generally designed with the supersonic cruise flight Mach number as their design point. During subsonic cruise, the lift-to-drag ratio K SB Deviating from its supersonic cruise lift-to-drag ratio K SP , the engine deviates from its supersonic cruise design point and propulsion efficiency decreases.

[0090] (3) During supersonic cruise, the efficiency of the vertical tail of a supersonic civil aircraft will drop significantly, and the heading stability will also drop. In order to meet the heading stability requirements during supersonic cruise, the vertical tail tail capacity and vertical tail area are usually designed to be larger, and the structural weight increases accordingly.

[0091] The supersonic civil aircraft layout of the present application provides a low sonic boom supersonic civil aircraft layout. By designing a fully movable horizontal tail with a wing tip that can be folded upward by 90 degrees, the horizontal tail wing tip is folded upward during supersonic cruise to provide additional vertical tail tail capacity, thereby compensating for the loss of vertical tail efficiency during supersonic cruise, and at the same time preventing the expansion waves generated by the engine tail nozzle and the horizontal tail from propagating to the ground, thereby reducing the loudness of the cruise ground sonic boom. By designing an engine pylon that can be pitched and deflected at a small angle around its rotation axis, the engine installation angle during subsonic cruise is adjusted to arctan (1 / K SB ), so that its residual thrust is maximized in this state and its cruising efficiency is highest; by designing the air inlet to be located in front of the upper part of the wing trailing edge and the exhaust to be located in the engine nacelle above the leading edge of the horizontal tail, the shielding effect of the wing and the horizontal tail is utilized to prevent the shock wave generated by the engine from propagating to the ground, effectively reducing the contribution of the ground sonic boom loudness brought by the engine and its intake and exhaust systems.

[0092] 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 supersonic civil aircraft layout, characterized in that: include: Body (1); A left wing (5), located on the left side of the rear center of the fuselage (1); A right wing (4), located on the right side of the middle rear of the fuselage (1); A left trailing edge flap, located inside the trailing edge of the left wing (5); a right trailing edge flap, located inside the trailing edge of the right wing (4); A left trailing edge aileron, located outside the trailing edge of the left wing (5); A right trailing edge aileron, located outside the trailing edge of the right wing (4); A left engine nacelle (16) is mounted on the fuselage (1) behind the left wing (5) via a left engine nacelle hanger (11); A right engine nacelle (17) is mounted on the fuselage (1) behind the right wing (4) via a right engine nacelle hanger (10); A tail-mounted left engine, installed in the left engine nacelle (16); A tail-mounted right engine installed in the right engine nacelle (17); A fully movable horizontal tail, comprising a left horizontal tail and a right horizontal tail, wherein the left horizontal tail is located on the left side of the tail of the fuselage (1), and the right horizontal tail is located on the right side of the tail of the fuselage (1); The vertical tail (2) is located on the upper side of the tail of the fuselage (1), and a rudder (3) is installed on the trailing edge of the vertical tail (2).

2. The supersonic civil aircraft layout according to claim 1, characterized in that: The front end of the left wing (5) is connected to the fuselage (1) at a position 1 / 2 the length of the fuselage (1); The front end of the right wing (4) is connected to the fuselage (1) at a position 1 / 2 of the length of the fuselage (1).

3. The supersonic civil aircraft layout according to claim 2, characterized in that: The left wing (5) has a wing root leading edge sweep angle of 75° and a wing tip leading edge sweep angle of 60°; The right wing (4) has a wing root leading edge sweep angle of 75° and a wing tip leading edge sweep angle of 60°.

4. The supersonic civil aircraft layout according to claim 3, characterized in that: The curvature of the wing root leading edge and the wing tip leading edge of the left wing (5) are smoothly transitioned; The curvature of the wing root leading edge and the wing tip leading edge of the right wing (4) are smoothly transitioned.

5. The supersonic civil aircraft layout according to claim 1, characterized in that: The engine nacelle left pylon (11) is connected to the fuselage (1) via the engine nacelle left pylon rotating shaft (9); The engine nacelle right pylon (10) is connected to the fuselage (1) via the engine nacelle right pylon rotating shaft (8).

6. The supersonic civil aircraft layout according to claim 5, characterized in that: The engine nacelle left pylon rotation axis (9) is located at 3 / 5 of the chord length at the root and 1 / 3 of the chord length at the tip of the engine nacelle left pylon (11), and the engine nacelle left pylon (11) can perform pitch and deflection around the engine nacelle left pylon rotation axis (9); The engine nacelle right pylon rotation axis (8) is located at 3 / 5 of the chord length at the root and 1 / 3 of the chord length at the tip of the engine nacelle right pylon (10), and the engine nacelle right pylon (10) can perform pitch and deflection around the engine nacelle right pylon rotation axis (8).

7. The supersonic civil aircraft layout according to claim 6, characterized in that: The left engine air inlet (7) of the left engine nacelle (16) is located above the trailing edge of the left wing (5); The right engine air inlet (6) of the right engine nacelle (17) is located above the trailing edge of the right wing (4).

8. The supersonic civil aircraft layout according to claim 7, characterized in that: The left engine exhaust port (13) of the left engine nacelle (16) is located above the leading edge of the left horizontal tail; The right engine exhaust port (12) of the right engine nacelle (17) is located above the leading edge of the right horizontal tail.

9. The supersonic civil aircraft layout according to claim 1, characterized in that: The deflection angle range of the left horizontal tail is +20° to -15°; The deflection angle range of the right horizontal tail is +20° to -15°.

10. The supersonic civil aircraft layout according to claim 9, characterized in that: A foldable wing tip portion (18) is provided at the wing tip of the left horizontal tail via a left horizontal tail wing tip rotating shaft (15); A foldable wing tip portion (18) is provided at the wing tip of the right horizontal tail via a right horizontal tail wing tip rotating shaft (14).

11. The supersonic civil aircraft layout according to claim 10, characterized in that: The left horizontal tail wing tip rotation shaft (15) is arranged at the wing tip of the left horizontal tail at 85% of the span; The right horizontal tail wing tip rotation shaft (14) is arranged at the wing tip of the right horizontal tail at 85% of the span.

12. The supersonic civil aircraft layout according to claim 11, characterized in that: The horizontal tail wing tip foldable portion (18) can be folded upwards by 90 degrees.

13. The supersonic civil aircraft layout according to claim 11, characterized in that: The left horizontal tail is a pointed delta wing; The right horizontal tail is a pointed delta wing.

14. The supersonic civil aircraft layout according to claim 13, characterized in that: The leading edge sweep angle of the left horizontal tail is 60°; The leading edge sweep angle of the right horizontal tail is 60°.

15. The supersonic civil aircraft layout according to claim 14, characterized in that: The trailing edge of the vertical tail (2) is located at the 7 / 8 chord length position of the full-moving horizontal tail.

16. The supersonic civil aircraft layout according to claim 15, characterized in that: The leading edge sweep angle of the vertical tail (2) is 54°.

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