Vertical take-off and landing stealth spray pipe suitable for shipboard aircraft

Abstract

The invention provides a vertical take-off and landing stealth spray pipe suitable for a shipboard aircraft, and relates to the technical field of engine spray pipes. The vertical take-off and landing stealth spray pipe comprises a round-to-square section, a barrel section and a single-side expansion spray pipe which are sequentially connected in the air outlet direction of an internal flow channel of an engine; the cylinder body section comprises a first cylinder body section, a second cylinder body section and a third cylinder body section which are sequentially connected in the air outlet direction of an internal flow channel of the engine. The round-to-square section is connected with the engine; the spray pipe barrel driving devices are respectively arranged between the barrel sections and between the barrel sections and the single-side expansion spray pipe, and the spray pipe barrel driving devices are used for changing the relative positions between the round-to-square sections and the barrel sections, between the barrel sections and between the barrel sections and the single-side expansion spray pipe; the unilateral expansion nozzle is used for adjusting the nozzle thrust of the engine. The spray pipe can use the barrel sections in different shapes to be matched with different spray pipe barrel driving devices, the configuration change of the vertical take-off and landing stealth spray pipe is achieved, and the vertical take-off and landing stealth spray pipe is suitable for three flight modes.

Description

Technical Field

[0001] The present invention relates to the technical field of engine nozzles, and particularly to a vertical take-off and landing stealth nozzle applicable to carrier-based aircraft. Background Art

[0002] The main function of a turbojet / turbofan engine nozzle is to expand the airflow flowing through the engine reasonably to the external ambient pressure, increase the engine jet velocity, convert as much of the thermal energy obtained by the air flowing through the engine into jet kinetic energy as possible, and enable the engine to generate as large a forward thrust as possible.

[0003] Turbojet / turbofan engine nozzles come in a variety of types, with widely different structural forms and compositions. According to different usage scenarios, the existing new nozzle structural forms mainly include: three-bearing rotating nozzles and S-bend nozzles. Among them, the three-bearing rotating nozzle is assembled on an aircraft to enable the aircraft to have the short take-off and vertical landing function (a representative fighter is the F-35B), and this nozzle can improve the battlefield adaptability of the aircraft. However, according to current research results, the outlet of the three-bearing rotating nozzle is equipped with an axisymmetric nozzle with a convergent-divergent function, but the high-temperature gas ejected from the axisymmetric nozzle is not evenly mixed with the external cold air, resulting in a large amount of heat radiated outward at the tail, so its stealth performance is not outstanding. The S-bend two-dimensional vector nozzle can effectively shield the hot-end components of the engine through a special profile and centerline design at the nozzle outlet, and has super stealth performance. However, the internal flow path of this nozzle is fixed and needs to be integrated with the two-dimensional vector nozzle before it can be applied to an engine with an afterburner function.

[0004] If a nozzle can be designed that has the vertical take-off and landing function during the aircraft take-off and landing stage, has a certain stealth effect during the conventional flight stage and has an afterburner function, and can have a full stealth function during the encounter with the enemy, it will be of great significance to the battlefield adaptability and survivability of the aircraft. Summary of the Invention

[0005] In view of this, the embodiments of this specification provide a vertical take-off and landing stealth nozzle applicable to carrier-based aircraft, so as to achieve the purpose of corresponding to the three modes of conventional cruise, vertical take-off and landing, and super stealth of the aircraft through the vertical take-off and landing stealth nozzle.

[0006] The embodiments of this specification provide the following technical solutions:

[0007] A vertical take-off and landing stealth nozzle applicable to carrier-based aircraft, comprising:

[0008] A circular-to-square section, a cylindrical section, and a single-sided expansion nozzle that are sequentially connected along the gas outlet direction of the engine internal flow path. The cylindrical section includes a first cylindrical section, a second cylindrical section, and a third cylindrical section that are sequentially connected along the gas outlet direction of the engine internal flow path;

[0009] The circular-to-square section is connected to the engine;

[0010] The nozzle barrel driving device is respectively arranged between the barrel sections and between the barrel section and the single-sided expansion nozzle. The nozzle barrel driving device is used to change the relative positions of the circular-to-square section, between the barrel sections, and between the barrel section and the single-sided expansion nozzle.

[0011] The single-sided expansion nozzle is used to adjust the nozzle thrust of the engine.

[0012] Furthermore, the single-sided expansion nozzle includes a vector nozzle barrel section, and the vector nozzle barrel section is connected to the third barrel section.

[0013] The radial cross-sections of the first barrel section, the second barrel section, the third barrel section, and the vector nozzle barrel section all include an inclined cut section, a bottom flat section, and a top arc section. The inclined cut sections of the second barrel section and the third barrel section both include a first inclined cut section and a second inclined cut section, and the top arc sections of two adjacent barrel sections are mutually attached.

[0014] The angle between the inclined cut section of the first barrel section and the horizontal line is 29° to 31°. The angle between the first inclined cut section of the second barrel section and the horizontal line is 61° to 63°. The angle between the second inclined cut section of the second barrel section and the horizontal line is 64° to 66°. The angle between the first inclined cut section of the third barrel section and the horizontal line is 59° to 61°. The angle between the second inclined cut section of the third barrel section and the horizontal line is 79° to 82°.

[0015] The angle between the inclined cut section of the vector nozzle barrel section and the horizontal line is 79° to 82°.

[0016] Hinge holes are arranged on the barrel section. The hinge holes have the same axis as the top arc section, and two adjacent barrel sections are assembled through the hinge holes.

[0017] Furthermore, the nozzle barrel driving device includes:

[0018] A hydraulic actuator bracket and a hydraulic actuator;

[0019] The hydraulic actuator bracket is arranged on both sides of the barrel section, and the hydraulic actuator bracket is connected to the hydraulic actuator through a fixed hinge.

[0020] By driving the pull rod of the hydraulic actuator to shorten or elongate through a hydraulic system, the barrel section rotates around the hinge hole.

[0021] Furthermore, the hydraulic actuator includes a first hydraulic actuator and a second hydraulic actuator;

[0022] The first barrel section is connected to the second barrel section through the first hydraulic actuator;

[0023] The second barrel section is connected to the third barrel section through the second hydraulic actuator.

[0024] Furthermore, the hydraulic actuator further includes a third hydraulic actuator;

[0025] The third cylinder section is connected to the vector nozzle cylinder section through the third hydraulic actuator.

[0026] Furthermore, the nozzle cylinder driving device further includes a connecting rod and a connecting rod pin shaft;

[0027] The connecting rod pin shafts are respectively arranged on the side walls of the first cylinder section and the third cylinder section, and both ends of the connecting rod are fixed to the first cylinder section and the third cylinder section through the connecting rod pin shafts.

[0028] Furthermore, the single-sided expansion nozzle further includes a baffle plate and a fourth hydraulic actuator;

[0029] The fourth hydraulic actuator is respectively connected to the vector nozzle cylinder section and the baffle plate;

[0030] The vector nozzle cylinder section includes a top arc plate of the cylinder section and an arc plate interlayer, and the arc plate interlayer is arranged in the top arc plate of the cylinder section;

[0031] The baffle plate includes an arc-shaped plate, and the arc-shaped plate has the same axis as the top arc plate of the cylinder section of the vector nozzle cylinder section;

[0032] The arc-shaped plate is inserted into the arc plate interlayer and moves relative to the top arc plate of the cylinder section along the arc plate interlayer through the fourth hydraulic actuator.

[0033] Furthermore, the single-sided expansion nozzle includes a side wall, and the side wall is connected to the side wall of the third cylinder section;

[0034] The radial cross-sections of the first cylinder section, the second cylinder section, and the third cylinder section all include an inclined cut section and an arc section. The inclined cut sections of the second cylinder section and the third cylinder section both include a first inclined cut section, a second inclined cut section, a first arc section, and a second arc section;

[0035] The arc section of the first cylinder section has the same axis as the first arc section of the second cylinder section, and the second arc section of the second cylinder section has the same axis as the first arc section of the third cylinder section;

[0036] The angle between the inclined cut section of the first cylinder section and the horizontal line is 67° to 69°. The angle between the first inclined cut section of the second cylinder section and the horizontal line is 90°. The angle between the second inclined cut section of the second cylinder section and the horizontal line is 90°. The angle between the first inclined cut section of the third cylinder section and the horizontal line is 72° to 74°. The angle between the second inclined cut section of the third cylinder section and the horizontal line is 78° to 80°.

[0037] Furthermore, the single-sided expansion nozzle further includes a convergent-divergent adjusting piece, a third hydraulic actuator, and a fourth hydraulic actuator;

[0038] The convergent-divergent adjusting vane includes a first convergent-divergent adjusting vane and a second convergent-divergent adjusting vane. Both the first convergent-divergent adjusting vane and the second convergent-divergent adjusting vane include an arc-shaped plate, and the arc-shaped plate is connected to one end of the bracket.

[0039] The first convergent-divergent adjusting vane and the second convergent-divergent adjusting vane are interconnected through the other end of the bracket.

[0040] Two symmetric arc-shaped grooves are provided on the side wall. The bracket passes through the arc-shaped grooves, and the arc-shaped plates of the first convergent-divergent adjusting vane and the second convergent-divergent adjusting vane are respectively moved along the arc-shaped grooves by a third hydraulic actuator and a fourth hydraulic actuator.

[0041] Furthermore, the top arc segments of adjacent cylinder sections are sealed by graphite rings.

[0042] Compared with the prior art, the beneficial effects that at least one of the above technical solutions adopted in the embodiments of this specification can achieve at least include:

[0043] The vertical takeoff and landing stealth nozzle of the embodiment of the present invention can use cylinder sections of different shapes in combination with different nozzle cylinder driving devices, realizing the configuration change of the engine nozzle and being applicable to three flight modes. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0045] Figure 1 is a schematic diagram of the vertical takeoff and landing stealth nozzle of the first embodiment of the present invention;

[0046] Figure 2 is a schematic diagram of the cylinder section of the vertical takeoff and landing stealth nozzle of the first embodiment of the present invention;

[0047] Figure 3 is a side view of the cylinder section of the vertical takeoff and landing stealth nozzle of the first embodiment of the present invention;

[0048] Figure 4 is a schematic diagram of the bottom plate of the second cylinder section of the vertical takeoff and landing stealth nozzle of the first embodiment of the present invention;

[0049] Figure 5 is a schematic diagram of the three flight modes of the vertical takeoff and landing stealth nozzle of the first embodiment of the present invention;

[0050] Figure 6Schematic diagram of the vector nozzle barrel section and baffle of the vertical takeoff and landing stealth nozzle in the first embodiment of the present invention;

[0051] Figure 7 Schematic diagram of the baffle in the first embodiment of the present invention;

[0052] Figure 8 Schematic diagram of the arc plate sandwich layer of the vector nozzle barrel section in the first embodiment of the present invention;

[0053] Figure 9 Schematic diagram of the vertical takeoff and landing stealth nozzle in the second embodiment of the present invention;

[0054] Figure 10 Schematic diagram of the barrel section of the vertical takeoff and landing stealth nozzle in the second embodiment of the present invention;

[0055] Figure 11 Side view of the barrel section of the vertical takeoff and landing stealth nozzle in the second embodiment of the present invention;

[0056] Figure 12 Schematic diagram of three flight modes of the vertical takeoff and landing stealth nozzle in the second embodiment of the present invention;

[0057] Figure 13 Schematic diagram of the vector nozzle barrel section and baffle of the vertical takeoff and landing stealth nozzle in the second embodiment of the present invention;

[0058] Figure 14 Schematic diagram of the barrel section sandwich layer of the vector nozzle barrel section in the second embodiment of the present invention;

[0059] Figure 15 Schematic diagram of the vertical takeoff and landing stealth nozzle in the third embodiment of the present invention;

[0060] Figure 16 Schematic diagram of the barrel section of the vertical takeoff and landing stealth nozzle in the third embodiment of the present invention;

[0061] Figure 17 Side view of the barrel section of the vertical takeoff and landing stealth nozzle in the third embodiment of the present invention;

[0062] Figure 18 Schematic diagram of the side wall and convergent-divergent adjustment flap of the vertical takeoff and landing stealth nozzle in the third embodiment of the present invention;

[0063] Figure 19 Schematic diagram of the convergent-divergent adjustment flap in the third embodiment of the present invention;

[0064] Figure 20 Schematic diagram of the side wall in the third embodiment of the present invention;

[0065] Figure 21It is a schematic diagram of three flight modes of the vertical takeoff and landing stealth nozzle according to the third embodiment of the present invention.

[0066] Reference numerals in the figure: 1, circular-to-square section; 2, barrel section; 201, first barrel section; 202, second barrel section; 203, third barrel section; 3, hydraulic actuator bracket; 301, first hydraulic actuator bracket; 302, second hydraulic actuator bracket; 4, hydraulic actuator; 401, first hydraulic actuator; 402, second hydraulic actuator; 403, third hydraulic actuator; 404, fourth hydraulic actuator; 5, pin shaft; 501, first pin shaft; 502, second pin shaft; 503, third pin shaft; 6, connecting rod pin shaft; 7, connecting rod; 8, vector nozzle barrel section; 801, top arc plate of the barrel section; 802, side plate of the barrel section; 803, bottom plate of the barrel section; 804, arc plate sandwich; 805, barrel section sandwich; 9, baffle plate; 10, side wall; 11, convergent-divergent adjustment flap; 111, first convergent-divergent adjustment flap; 112, second convergent-divergent adjustment flap. Detailed implementation manners

[0067] The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0068] It should be noted that, without conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the drawings and in conjunction with the embodiments.

[0069] A vertical takeoff and landing stealth nozzle applicable to carrier-based aircraft, comprising:

[0070] A circular-to-square section 1, a barrel section 2 and a single-sided expansion nozzle connected in sequence along the gas outlet direction of the internal flow path of the engine. The barrel section 2 includes a first barrel section 201, a second barrel section 202 and a third barrel section 203 connected in sequence along the gas outlet direction of the internal flow path of the engine. The circular-to-square section 1 is connected to the engine. Nozzle barrel driving devices are respectively arranged between the barrel sections 2, between the barrel section 2 and the single-sided expansion nozzle. The nozzle barrel driving devices are used to change the relative positions of the circular-to-square section 1 and the barrel section 2, between the barrel sections 2, and between the barrel section 2 and the single-sided expansion nozzle. The single-sided expansion nozzle is used to adjust the nozzle thrust of the engine.

[0071] Embodiment 1:

[0072] As Figure 1 shown, the vertical takeoff and landing stealth nozzle of the first embodiment includes a circular-to-square section 1, a first barrel section 2, a hydraulic actuator bracket 3, a first hydraulic actuator 4, a second barrel section 202, a second hydraulic actuator 402, a third barrel section 203, a third hydraulic actuator 403, a vector nozzle barrel section 8 and a fourth hydraulic actuator 404.

[0073] To achieve deflection and sealing between the cylinder sections 2, the cylinder sections 2 are set as rectangular-section cylinders with a flat bottom and an arc feature at the top, as shown in Figure 2 and Figure 3 . Among them, hinge holes are provided at the bottom of the cylinder section 2. The hinge holes are coaxial with the arc section at the top of the cylinder section 2. Two adjacent cylinder sections 2 are assembled through the hinge holes. The arc sections at the top are mutually attached and sealed with graphite rings. Through this structure, mutual rotation between the two cylinder sections 2 can be achieved. To avoid separation and interference phenomena during the mutual rotation of the cylinder sections 2, the cylinder sections 2 are designed with oblique cuts. The included angle between the right inclined edge of the first cylinder section 201 and the horizontal line is 30°. The included angle between the left inclined edge (the first oblique section) of the second cylinder section 202 and the horizontal line is 61° to 63° (about 62°). The included angle of the right inclined edge (the second oblique section) of the second cylinder section 202 is 64° to 66° (about 65°). The included angle between the left inclined edge (the first oblique section) of the third cylinder section 203 and the horizontal line is 59° to 61° (about 60°). The included angle between the right inclined edge (the second oblique section) of the third cylinder section 203 and the horizontal line is 79° to 82° (about 81°). The included angle between the oblique section of the vector nozzle cylinder section 8 and the horizontal line is 79° to 82° (about 81°).

[0074] In addition, taking the assembly between the first cylinder section 201 and the second cylinder section 202 as an example, considering the mutual nesting between the cylinder sections 2, the two adjacent cylinder sections 2 differ by the thickness of the side plate of the cylinder. To avoid interference between the side wall of the first cylinder section 201 and the bottom plate of the second cylinder section 202 during rotation. Therefore, at the bottom plate of the second cylinder section 202, near the hinge position of the first cylinder section 201, the thickness of the side wall of the cylinder section 2 is reserved. The bottom plate of the cylinder section 2 is as shown in Figure 4 .

[0075] Finally, all the cylinder sections 2 are assembled with the round-to-square section 1 and the vector nozzle cylinder section 8 to obtain an actuator of a dragonfly-like nozzle that takes into account three modes: vertical takeoff and landing, normal cruise, and S-bend stealth.

[0076] Hydraulic actuator brackets 3 are installed on both sides of each cylinder section 2. The hydraulic actuator brackets 3 are connected to the hydraulic actuators 4 through fixed hinges. Oil is pumped into the hydraulic actuators 4 through the hydraulic system, so that the hydraulic push rods of the hydraulic actuators 4 extend, enabling the cylinder sections 2 to obtain driving force and rotate around the actuator hinge points to achieve nozzle postures that meet different flight requirements. The corresponding nozzle postures are as shown in Figure 5 . The nozzle postures of the three flight modes are as follows:

[0077] Conventional cruise mode: This nozzle is a conventional binary nozzle, suitable for general cruise states.

[0078] Vertical takeoff and landing mode: The nozzle deflects downward by 95°, which is applicable to the vertical takeoff / landing state of the aircraft.

[0079] Super stealth mode: The nozzle deflects upward, presenting an S-bend state. At this time, the nozzle completely shields the high-temperature components at the rear of the engine, achieving the best stealth effect and being applicable to flight states that require stealth capabilities.

[0080] In order to enable the vertical takeoff and landing stealth nozzle of the embodiment of the present invention to have more excellent thrust vector performance, a baffle 9 is attached to the vector nozzle barrel section 8 at the end of the nozzle deflection barrel to form a single-sided expansion nozzle, as Figure 6 shown. The single-sided expansion nozzle includes a vector nozzle barrel section 8 (including a barrel section side plate 802 and a barrel section bottom plate 803), a fourth hydraulic actuator 404, and a baffle 9. The shape of the baffle 9 is as Figure 7 shown. The baffle 9 is a combined structure of an arc plate and a rectangular plate, and the arc plate structure thereof is coaxially fitted with the arc plate 801 at the top of the barrel section of the vector nozzle barrel section 8. The arc plate 801 at the top of the barrel section is an arc plate sandwich 804, as Figure 8 shown. The baffle 9 is sandwiched in the sandwich of the arc plate at the top of the vector nozzle barrel section 8 and can rotate coaxially with the top arc plate. The fourth hydraulic actuator 404 is installed between the arc top of the thrust vector nozzle barrel section 8 and the rectangular surface of the baffle. By the extension and contraction of the fourth hydraulic actuator 404, the throat area of the single-sided expansion nozzle is adjusted to achieve nozzle thrust adjustment.

[0081] Embodiment 2:

[0082] As Figure 9 shown, the vertical takeoff and landing stealth nozzle of the embodiment of the present invention includes: a circular-to-square section 1, a first barrel section 201, a first hydraulic actuator 401, a first pin shaft 501, a first hydraulic actuator bracket 301, a connecting rod pin shaft 6, a second barrel section 202, a connecting rod 7, a third barrel section 203, a second pin shaft 502, a second hydraulic actuator 402, a second hydraulic actuator bracket 302, a third hydraulic actuator 403, a third pin shaft 503, a vector nozzle barrel section 8, and a baffle 9.

[0083] In order to achieve the deflection and sealing between the barrel sections 2, the barrel sections 2 are set as rectangular cross-section barrels with a flat bottom and an arc feature at the top, as Figure 10 and Figure 11As shown. A hinge hole is provided at the bottom of the barrel section 2, and the hinge hole is coaxial with the arc section at the top of the barrel section 2. Two adjacent barrel sections 2 are assembled through the hinge hole, and the arc sections at the top fit each other and are sealed with a graphite ring. This structure enables the two barrel sections 2 to rotate relative to each other. In order to avoid separation and interference during the mutual rotation of the barrel sections 2, the barrel sections 2 are designed to be beveled. The angle between the right end bevel of the first barrel section 201 and the horizontal line is 30°, the angle between the left end bevel of the second barrel section 202 (the first bevel section) and the horizontal line is 61° to 63° (about 62°), the angle between the right end bevel of the second barrel section 202 (the second bevel section) is 64° to 66° (about 65°), the angle between the left end bevel of the third barrel section 203 (the first bevel section) and the horizontal line is 59° to 61° (about 60°), and the angle between the right end bevel of the third barrel section 203 (the second bevel section) and the horizontal line is 79° to 82° (about 81°). The angle between the bevel section of the vector nozzle barrel section 8 and the horizontal line is 79° to 82° (about 81°).

[0084] In addition, taking the assembly between the first barrel section 201 and the second barrel section 202 as an example, considering that the barrel sections 2 are nested with each other, the thickness of the side plates of the barrels of two adjacent barrel sections 2 differs, in order to avoid the side wall of the first barrel section 201 from interfering with the bottom plate of the second barrel section 202 during the rotation process. Therefore, the thickness of the side wall of the barrel section 2 is reserved at the bottom plate of the second barrel section 202, near the hinge position of the first barrel section 201, and the bottom plate of the barrel section 2 is as follows: Figure 4 shown.

[0085] like Figure 11As shown, the circular cross-section of the circular-to-square section 1 is connected to the turbofan engine of the aircraft by precision bolts, and the rectangular outlet of the circular-to-square section 1 is fixedly connected to the first cylinder section 201 of the cylinder section 2. After the arc surfaces of the first cylinder section 201 and the second cylinder section 202 are concentrically assembled, they can rotate sealingly around the first pin shaft 501. In order to provide the driving force for the rotation of the second cylinder section 202, the first hydraulic actuating cylinder 401 is installed on both side surfaces of the first cylinder section 201 and the second cylinder section 202. By pumping oil into the first hydraulic actuating cylinder 401, the second cylinder section 202 rotates around a fixed axis. The second cylinder section 202 and the third cylinder section 203 are not driven by the hydraulic actuating cylinder 4, but the connecting rod 7 is used. One end of the connecting rod 7 forms a rotating pair with the second cylinder section 202 through the connecting rod pin shaft 6, and the other end of the connecting rod 7 forms a rotating pair with the third cylinder section 203. Thus, the first cylinder section 201, the second cylinder section 202, the third cylinder section 203 and the connecting rod 7 form a hinge four-bar mechanism. When the push rod of the first hydraulic actuating cylinder 401 extends and contracts, the hinge four-bar mechanism will rotate synchronously to realize the change of the nozzle attitude. The second hydraulic actuating cylinder 402 is installed on both sides of the third cylinder section 203 and the vector nozzle cylinder section 8 respectively, and the relative rotation between the vector nozzle cylinder section 8 and the cylinder section 2 is controlled by the second hydraulic actuating cylinder 402. The nozzle of this embodiment can realize the attitude transformation of the dragonfly-like nozzle by controlling the elongation of the two actuating cylinders, and the corresponding nozzle attitudes are as Figure 12 shown. The nozzle attitudes in the three flight modes are respectively:

[0086] Conventional cruise mode: This nozzle is a conventional two-dimensional nozzle, suitable for general cruise states.

[0087] Vertical takeoff and landing mode: This nozzle deflects downward by 95°, suitable for the vertical takeoff / landing state of the aircraft.

[0088] Super stealth mode: The nozzle deflects upward and is in an S-bend state. At this time, the nozzle completely shields the rear high-temperature components of the engine, and the stealth effect is the best, suitable for flight states that require stealth capabilities.

[0089] In order to make the vertical takeoff and landing stealth nozzle of the embodiment of the present invention have more excellent thrust vector performance, a baffle 9 is attached to the vector nozzle cylinder section 8 at the end of the nozzle deflection cylinder to form a single-sided expansion nozzle, as Figure 13 shown. The single-sided expansion nozzle includes a vector nozzle cylinder section 8 (including a cylinder section side plate 802 and a cylinder section bottom plate 803), a fourth hydraulic actuating cylinder 404, a second hydraulic actuating cylinder bracket 303 and a baffle 9. The shape of the baffle 9 is as Figure 7 shown. The baffle 9 is a combined structure of an arc plate and a rectangular plate. The arc plate structure thereof is coaxially fitted with the cylinder section top arc plate 801 of the vector nozzle cylinder section 8. The cylinder section top arc plate 801 is a cylinder section sandwich structure 805, as Figure 14As shown in the figure. The baffle 9 is sandwiched between the sandwich layers of the arc plate at the top of the vector nozzle barrel section 8 and can rotate coaxially with the top arc plate. The fourth hydraulic actuator 404 is installed between the arc top of the thrust vector nozzle barrel section 8 and the rectangular surface of the baffle. By the extension and contraction of the fourth hydraulic actuator 404, the throat area of the single-sided expansion nozzle is adjusted to achieve nozzle thrust adjustment.

[0090] Embodiment 3:

[0091] As Figure 15 shown, the vertical take-off and landing stealth nozzle of the embodiment of the present invention includes: a circular-to-square section 1, a first barrel section 201, a hydraulic actuator bracket 3, a first hydraulic actuator 401, a second barrel section 202, a second hydraulic actuator 402, a third barrel section 203, a third hydraulic actuator 403, a fourth hydraulic actuator 404, a side wall 10, a first convergent-divergent adjustment flap 111, and a second convergent-divergent adjustment flap 112.

[0092] In order to achieve deflection and sealing between the barrel sections 2, the barrel sections 2 are set as cylindrical barrels, as Figure 16 and Figure 17 shown. Among them, the cylindrical barrel (arc section) of the first barrel section 201 is coaxially assembled with the left-end cylindrical barrel (first arc section) of the second barrel section 202. Utilizing the coaxial assembly characteristics of the cylindrical shell, a large rotary hinge is formed, which can realize the mutual rotation between the first barrel section 201 and the second barrel section 202. Similarly, the right-end cylindrical barrel section (second arc section) of the second barrel section 202 is coaxially fitted with the left-end cylindrical barrel (first arc section) of the third barrel section 203. The side wall 10 is welded on the third barrel section 203 to guide the high-temperature gas ejected by the thrust vector nozzle at the tail during normal cruise or super-stealth state of the aircraft. In order to avoid separation and interference phenomena during the mutual rotation of the barrel sections 2, the cylindrical barrel sections 2 are designed with oblique cuts. The included angle between the right-end hypotenuse (oblique cut section) of the first barrel section 201 and the horizontal line is 67° to 69° (about 68°), the included angle between the left-end hypotenuse (first oblique cut section) of the second barrel section 202 and the horizontal line is 90°, the included angle between the right-end hypotenuse (second oblique cut section) of the second barrel section 202 and the horizontal line is 90°, the included angle between the left-end hypotenuse (first oblique cut section) of the third barrel section 203 and the horizontal line is 72° to 74° (about 73°), and the included angle between the right-end hypotenuse (second oblique cut section) of the third barrel section 203 and the horizontal line is 79° to 80° (about 79°).

[0093] The circular cross-section inlet of the circular-to-square section 1 is connected to the turbofan / turbojet engine by precision bolts, and the rectangular cross-section outlet is connected to the inlet of the first cylinder section 201. After the cylindrical barrels of the first cylinder section 201 and the second cylinder section 202 are coaxially assembled, a hydraulic actuator bracket 3 is installed on the two cylinder sections, and the first hydraulic actuator 401 is installed between the hydraulic actuator brackets 3 to provide the driving torque for the rotation of the second cylinder section 202. Similarly, the second hydraulic actuator 402 is installed on the two side surfaces of the second cylinder section 202 and the third cylinder section 203, and the third cylinder section 203 can rotate relative to the second cylinder section 202.

[0094] At this time, relying solely on the three cylinder sections cannot achieve the postures required for the super stealth mode and the vertical takeoff and landing mode. It is also necessary to rely on the convergent-divergent adjustment flaps 11 assembled on the third cylinder section 203 and the side wall 10 to meet the posture requirements of the three flight modes, as Figure 18 shown. As Figure 19 shown, the convergent-divergent adjustment flap 11 is composed of a circular arc plate and a rectangular plate, and brackets are welded on both sides of the circular arc plate. As Figure 20 shown, arc-shaped groove structures are arranged on the upper and lower sides of the side wall of the vector nozzle cylinder section 8. The brackets of the convergent-divergent adjustment flap 11 pass through the arc-shaped grooves and form a rotating pair with the pin shaft at the center of the fan-shaped area of the side wall of the vector nozzle cylinder section 8. At the same time, the convergent-divergent adjustment flap is also coaxial with the right-end circular arc cylinder section of the third cylinder section 203. By installing a fourth hydraulic actuator 404 between the third cylinder section and the bracket of the convergent-divergent adjustment flap 11, the convergent-divergence of the nozzle adjustment flap is achieved by controlling the elongation of the hydraulic actuator push rod, thereby adjusting the throat area of the nozzle outlet, enabling the gas in the nozzle to expand and do work to generate thrust.

[0095] When the aircraft needs to fly in the super stealth mode, control the oil inlet flow rate of the first hydraulic actuator 401 to make the push rod of the first hydraulic actuator 401 extend, causing the second cylinder section 202 to rotate downward by 15°. The hydraulic actuator 4 between the second cylinder section 202 and the third cylinder section 203 is locked. The push rod of the fourth hydraulic actuator 404 driving the first convergent-divergent adjustment flap 111 contracts, and the push rod of the third hydraulic actuator 403 driving the second convergent-divergent adjustment flap 112 extends, making the nozzle outlet section perpendicular to the horizontal plane and the outlet section lower than the nozzle inlet section, horizontally shielding the hot end of the engine to achieve the stealth function.

[0096] When the aircraft needs to take off and land vertically, control the oil inlet flow rate of the first hydraulic actuator 401 to extend the push rod of the first hydraulic actuator 401, so that the second cylinder section 202 rotates downward by 29°, the hydraulic actuator 4 between the second cylinder section 202 and the third cylinder section 203 extends, so that the third cylinder section 203 rotates downward by 46° relative to the second cylinder section 202, drive the push rod of the fourth hydraulic actuator 404 for driving the second convergent-divergent flap 112 to extend, drive the push rod of the third hydraulic actuator 403 for driving the first convergent-divergent flap 111 to contract, so that the nozzle outlet section rotates by 95° relative to the cruise state, and the vertical takeoff and landing function is realized.

[0097] The nozzle postures corresponding to the three flight modes are as Figure 21 shown. The nozzle postures of the three flight modes are respectively:

[0098] Conventional cruise mode: The nozzle is a conventional two-dimensional nozzle, suitable for general cruise state.

[0099] Vertical takeoff and landing mode: The nozzle deflects downward by 95°, suitable for the vertical takeoff / landing state of the aircraft.

[0100] Super stealth mode: The nozzle deflects upward and is in an S-bend state. At this time, the nozzle completely shields the rear high-temperature components of the engine, and the stealth effect is the best, suitable for flight states requiring stealth capabilities.

[0101] The beneficial effects of the embodiments of the present invention:

[0102] The vertical takeoff and landing stealth nozzle of the embodiments of the present invention can be deformed into an S-bend nozzle with full rear shielding in the cruise state, realizing the function of high stealth; compared with the traditional S-bend nozzle, the vertical takeoff and landing stealth nozzle of the embodiments of the present invention has the function of vertical takeoff and landing; the vertical takeoff and landing stealth nozzle of the embodiments of the present invention is provided with a single-sided expansion nozzle to adjust the thrust vector of the nozzle, so that the nozzle has more excellent thrust vector performance; the vertical takeoff and landing stealth nozzle of the embodiments of the present invention can use different-shaped cylinder sections to cooperate with different nozzle cylinder driving devices, realizing the configuration change of the vertical takeoff and landing stealth nozzle and being applicable to three flight modes.

[0103] The above are only specific embodiments of the present invention, and the scope of the invention implementation cannot be limited by them. Therefore, the replacement of equivalent components, or equivalent changes and modifications made according to the scope of protection of the present invention patent, should still fall within the scope covered by this patent. In addition, the technical features in the present invention, between technical features, between technical features and technical solutions, and between technical solutions can be freely combined and used.

Claims

1. A vertical take-off and landing stealth nozzle suitable for carrier-based aircraft, characterized in that: include: A circular rotating square section (1), a barrel section (2) and a single-sided expansion nozzle connected in sequence along the gas outlet direction of the internal flow channel of the engine, wherein the barrel section (2) comprises a first barrel section (201), a second barrel section (202) and a third barrel section (203) connected in sequence along the gas outlet direction of the internal flow channel of the engine; The circular rotating square section (1) is connected to the engine; The nozzle barrel driving device is respectively arranged between the barrel sections (2) and between the barrel section (2) and the single-side expansion nozzle, and the nozzle barrel driving device is used to change the relative position of the circular rotating square section (1) and the barrel section (2), between the barrel sections (2), and between the barrel section (2) and the single-side expansion nozzle; The unilateral expansion nozzle is used to adjust the nozzle thrust of the engine.

2. The vertical take-off and landing stealth nozzle suitable for carrier-based aircraft according to claim 1 is characterized in that: The unilateral expansion nozzle comprises a vector nozzle barrel section (8), and the vector nozzle barrel section (8) is connected to the third barrel section (203); The radial cross-sections of the first barrel section (201), the second barrel section (202), the third barrel section (203) and the vector nozzle barrel section (8) all include a beveled section, a bottom straight section and a top arc section; the beveled sections of the second barrel section (202) and the third barrel section (203) all include a first beveled section and a second beveled section; and the top arc sections of two adjacent barrel sections (2) fit each other; The included angle between the beveled section of the first barrel section (201) and the horizontal line is 29° to 31°, the included angle between the first beveled section of the second barrel section (202) and the horizontal line is 61° to 63°, the included angle between the second beveled section of the second barrel section (202) and the horizontal line is 64° to 66°, the included angle between the first beveled section of the third barrel section (203) and the horizontal line is 59° to 61°, and the included angle between the second beveled section of the third barrel section (203) and the horizontal line is 79° to 82°; The angle between the beveled section of the vector nozzle barrel section (8) and the horizontal line is 79° to 82°; The barrel section (2) is provided with a hinge hole, the hinge hole has the same axis as the top arc section, and two adjacent barrel sections (2) are assembled through the hinge hole.

3. The vertical take-off and landing stealth nozzle suitable for carrier-based aircraft according to claim 2 is characterized in that: The nozzle barrel driving device comprises: A hydraulic actuator support (3) and a hydraulic actuator (4); The hydraulic cylinder bracket (3) is arranged on both sides of the cylinder section (2), and the hydraulic cylinder bracket (3) is connected to the hydraulic cylinder (4) via a fixed hinge; The hydraulic system drives the pull rod of the hydraulic actuator cylinder (4) to shorten or lengthen, so that the cylinder section (2) rotates around the hinge hole.

4. The vertical take-off and landing stealth nozzle suitable for carrier-based aircraft according to claim 3 is characterized in that: The hydraulic actuator (4) comprises a first hydraulic actuator (401) and a second hydraulic actuator (402); The first cylinder section (201) is connected to the second cylinder section (202) via the first hydraulic actuator (401); The second cylinder section (202) is connected to the third cylinder section (203) via the second hydraulic jack (402).

5. The vertical take-off and landing stealth nozzle suitable for carrier-based aircraft according to claim 4 is characterized in that: The hydraulic actuator (4) further comprises a third hydraulic actuator (403); The third barrel section (203) is connected to the vector nozzle barrel section (8) via the third hydraulic actuator (403).

6. The vertical take-off and landing stealth nozzle suitable for carrier-based aircraft according to claim 3 is characterized in that: The nozzle barrel driving device also includes a connecting rod (7) and a connecting rod pin (6); The connecting rod pin shaft (6) is respectively arranged on the side walls of the first barrel section (201) and the third barrel section (203), and the two ends of the connecting rod (7) are fixed to the first barrel section (201) and the third barrel section (203) through the connecting rod pin shaft (6).

7. The vertical take-off and landing stealth nozzle suitable for carrier-based aircraft according to claim 2 is characterized in that: The unilateral expansion nozzle further comprises a baffle (9) and a fourth hydraulic actuator (404); The fourth hydraulic actuator (404) is connected to the vector nozzle barrel section (8) and the baffle (9) respectively; The vector nozzle barrel section (8) comprises a barrel section top circular arc plate (801) and a circular arc plate sandwich (804), wherein the circular arc plate sandwich (804) is arranged in the barrel section top circular arc plate (801); The baffle (9) comprises an arc-shaped plate, the arc-shaped plate and the arc-shaped plate (801) at the top of the barrel section of the vector nozzle barrel section (8) have the same axis; The arc-shaped plate is inserted into the arc-shaped plate interlayer (804), and moves along the arc-shaped plate interlayer (804) relative to the top arc-shaped plate (801) of the cylinder section through the fourth hydraulic actuator (404).

8. The vertical take-off and landing stealth nozzle suitable for carrier-based aircraft according to claim 1, characterized in that: The unilateral expansion nozzle comprises a side wall (10), and the side wall (10) is connected to the side wall of the third barrel section (203); The radial sections of the first barrel section (201), the second barrel section (202) and the third barrel section (203) all include a bevel section and a circular arc section, the bevel sections of the second barrel section (202) and the third barrel section (203) all include a first bevel section and a second bevel section, and the circular arc sections of the second barrel section (202) and the third barrel section (203) include a first circular arc section and a second circular arc section; The arc segment of the first barrel segment (201) and the first arc segment of the second barrel segment (202) have the same axis, and the second arc segment of the second barrel segment (202) and the first arc segment of the third barrel segment (203) have the same axis; The angle between the beveled section of the first barrel section (201) and the horizontal line is 67° to 69°, the angle between the first beveled section of the second barrel section (202) and the horizontal line is 90°, the angle between the second beveled section of the second barrel section (202) and the horizontal line is 90°, the angle between the first beveled section of the third barrel section (203) and the horizontal line is 72° to 74°, and the angle between the second beveled section of the third barrel section (203) and the horizontal line is 78° to 80°.

9. The vertical take-off and landing stealth nozzle suitable for carrier-based aircraft according to claim 8, characterized in that: The unilateral expansion nozzle further comprises a convergence and expansion adjustment plate (11), a third hydraulic actuator (403) and a fourth hydraulic actuator (404); The convergence and expansion regulating piece (11) comprises a first convergence and expansion regulating piece (111) and a second convergence and expansion regulating piece (112), wherein the first convergence and expansion regulating piece (111) and the second convergence and expansion regulating piece (112) both comprise arc-shaped plates, and the arc-shaped plates are connected to one end of the bracket; The first convergence and expansion regulating piece (111) and the second convergence and expansion regulating piece (112) are connected to each other via the other end of the bracket; The side wall (10) is provided with two symmetrical arc grooves, the bracket passes through the arc grooves, and the arc plates of the first convergence and expansion adjustment piece (111) and the second convergence and expansion adjustment piece (112) are respectively moved along the arc grooves through the third hydraulic actuator (403) and the fourth hydraulic actuator (404).

10. The vertical take-off and landing stealth nozzle suitable for carrier-based aircraft according to claim 2, characterized in that: The top arc section of the adjacent barrel section (2) is sealed by a graphite ring.

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