A solid carrier fairing capable of resisting pulsating pressure at large cone angles

Abstract

A solid carrier fairing that can resist pulsating pressure under large cone angles includes: an end, a front cone section, a column section, an inverted cone section, a segmented longitudinal separation structure, a combined exhaust structure, and a bolt box docking frame combined structure. The end, front cone section, column section, and inverted cone section are all column structures formed by combining two half-covers, which are connected to the segmented longitudinal separation structure internally, and the end, front cone section, column section, and inverted cone section are connected in sequence through end faces to form a solid carrier fairing structure. The segmented longitudinal separation structure is used to make the solid carrier fairing structure complete before separation, and after separation, the solid carrier fairing is changed into two half-covers to ensure normal separation of the fairing; a combined exhaust structure and a bolt box docking frame combined structure are provided at the tail end of the inverted cone section to avoid the exhaust structure from affecting the internal noise. The combined exhaust structure is used to balance the pressure difference between the inside and outside of the fairing during the flight of the solid carrier rocket, and the bolt box docking frame combined structure is used to connect and carry the fairing and the control cabin.

Description

Technical Field

[0001] The invention relates to a solid carrier fairing capable of resisting pulsating pressure at a large cone angle, and is applied to the technical field of aircraft structure. Background Art

[0002] The development of solid-propellant rockets needs to address multiple requirements, such as pulsating pressure at large cone angles and load-bearing optimization at a certain size. It is necessary to innovate and improve existing technologies. The load-bearing capacity of pulsating pressure at large cone angles should be improved, the structural weight should be optimized, and a multifunctional and shared combined structure should be designed to meet various needs. Summary of the invention

[0003] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art, to provide a solid carrier fairing that can resist pulsating pressure at large cone angles, to improve the bearing capacity of pulsating pressure at large cone angles, to optimize the structural weight, and to design a multifunctional shared combined structure, thereby meeting various needs.

[0004] The technical solution of the present invention is:

[0005] A solid carrier fairing capable of resisting pulsating pressure at a large cone angle, comprising: an end, a front cone section, a column section, an inverted cone section, a segmented longitudinal separation structure, a combined exhaust structure, and a bolt box docking frame combined structure;

[0006] The end head, front cone section, column section and inverted cone section are all column structures formed by combining two half covers. The interiors of the front cone section, column section and inverted cone section are all connected to the segmented longitudinal separation structure. The end head, front cone section, column section and inverted cone section are connected in sequence through end faces to form a solid carrier fairing structure, which is used to protect the target vehicle from the influence of aerodynamic loads, heat flow and other harmful environments during the flight of the carrier rocket.

[0007] The segmented longitudinal separation structure is used to make the solid carrier fairing structure complete before separation, and to turn the solid carrier fairing into two half fairings after separation, so as to ensure the normal separation of the fairing;

[0008] A combined exhaust structure and a bolt box docking frame combined structure are provided at the tail end of the inverted cone section. The combined exhaust structure to prevent the exhaust structure from affecting the internal noise is used to balance the pressure difference between the inside and outside of the fairing during the flight of the solid carrier rocket. The bolt box docking frame combined structure is used for the connection and bearing between the fairing and the control cabin.

[0009] Further, the segmented longitudinal separation structure comprises: a longitudinal separation device and a point connection structure;

[0010] The longitudinal dividing device is used to connect the front cone section and the column section half cover, and the point connection structure is used to connect the inverted cone section half cover; the combination of the longitudinal dividing device and the point connection structure meets the load-bearing and functional requirements at the same time.

[0011] Furthermore, the axial spacing between the longitudinal dividing device and the point-type connection structure is set to 30 mm-300 mm.

[0012] Furthermore, the point connection structure includes a longitudinal separation structure bolt box and a bolt box reinforcement plate, the longitudinal separation structure bolt box is connected with the inverted cone section to transfer the point concentrated load to the inverted cone section, and the longitudinal separation structure bolt box is connected with the separation bolt at the separation joint surface to bear the concentrated load;

[0013] A bolt box reinforcement plate is also provided at the connection between the bolt box and the inverted cone section of the longitudinal separation structure to diffuse the load.

[0014] Furthermore, the side length of the bolt box reinforcement plate structure is 200mm-350mm.

[0015] Further, the combined exhaust structure comprises: an air inlet hole in the separation bolt box, an air vent hole in the separation bolt box cover, a small fairing at the exhaust hole, and an exhaust hole at the lower end of the small fairing;

[0016] The air inlet hole in the separation bolt box is arranged on the separation bolt box and arranged along the axial direction of the fairing. The air vent hole of the separation bolt box cover is arranged on the separation bolt box cover and arranged perpendicular to the axial direction of the fairing. The small fairing at the exhaust hole is installed on the inverted cone section, and the area enclosed by the air vent hole of the separation bolt box cover forms the exhaust hole at the lower end of the small fairing. The exhaust holes at the lower end of the small fairing are distributed along the axial direction of the fairing.

[0017] The exhaust path of the gas in the fairing is specifically as follows: the gas in the fairing enters the separation bolt box through the air inlet hole in the separation bolt box, and then is discharged through the vent hole of the separation bolt box cover and the exhaust hole at the lower end of the small fairing in turn.

[0018] Furthermore, when the solid carrier rocket is flying, exhaust is exhausted through the exhaust path under the action of the pressure difference between the inside and outside of the fairing. At the same time, the small fairing at the exhaust hole avoids the influence of the exhaust structure on the internal noise. The exhaust areas of the air inlet hole in the separation bolt box, the air vent hole on the separation bolt box cover, and the exhaust hole at the lower end of the small fairing match each other.

[0019] Furthermore, the exhaust area of ​​the air inlet hole in the separation bolt box, the air vent hole in the separation bolt box cover, and the exhaust hole at the lower end of the small fairing is set to 2000mm 2 -4000 mm 2 .

[0020] Furthermore, the bolt box docking frame combination structure includes: a bolt box and a docking frame, a bolt box mounting structure is reserved on the docking frame, and the bolt hole docking position on the bolt box mounting structure is adjusted so that L1=L2, wherein L1 is the distance between the bolt hole docking position and the axis of the fairing, and L2 is the distance between the side wall of the docking frame and the axis of the fairing.

[0021] Furthermore, the size difference between the distances L1 and L2 is set to be -10 mm to 10 mm.

[0022] The beneficial effects of the present invention compared with the prior art are:

[0023] (1) The present invention innovatively proposes a solid launch vehicle fairing design technology that can resist pulsating pressure at large cone angles, improves the bearing capacity of pulsating pressure at large cone angles, optimizes the structural weight, and designs a multifunctional and shared combined structure, thereby meeting various needs. The relevant technology has been verified through multiple ground tests and flight tests, and has a very important reference value for the design verification of similar solid launch vehicle fairings;

[0024] (2) The present invention aims at meeting the higher load-bearing requirements of pulsating pressure under large cone angles, and through a modular design, changes the pitch circle of the separation surface, reduces the lever effect of the separation surface, and realizes an improvement in the load-bearing capacity;

[0025] (3) The present invention adopts a segmented longitudinal innovative combination structure, so that the longitudinal structure can adapt to the requirements of pulsating pressure under large cone angles;

[0026] (4) The present invention adopts a combined transfer fairing structure design, which realizes for the first time the two assembly docking modes of horizontal docking and vertical docking of the inverted cone structure fairing, greatly improving the flexibility of the fairing. In addition, the traditional transfer ring structure is eliminated, the weight of the four-stage structure is reduced, and the carrying capacity is improved;

[0027] (5) In view of the need for balancing the internal and external pressure differences during solid transportation, the present invention designs a combined exhaust structure at the separation bolt box, thereby avoiding the influence of a single exhaust structure on the load and internal noise. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 A schematic diagram of the structure of a solid carrier fairing that can resist pulsating pressure at a large cone angle;

[0029] Figure 2 Schematic diagram of the combined structure of the separated bolt box and the docking frame for large cone angle pulsating pressure Figure 1 ;

[0030] Figure 3 Schematic diagram of the combined structure of the separated bolt box and the docking frame for large cone angle pulsating pressure Figure 2 ;

[0031] Figure 4 Schematic diagram of segmented longitudinal separation structure;

[0032] Figure 5 Schematic diagram of inverted cone point connection and local reinforcement;

[0033] Figure 6Schematic diagram of the solid carrier fairing separation bolt box with combined exhaust structure. DETAILED DESCRIPTION

[0034] The specific embodiments of the present invention are further described in detail below with reference to the accompanying drawings.

[0035] like Figure 1 As shown, the present invention proposes a solid carrier fairing capable of resisting pulsating pressure at a large cone angle, comprising: an end 1, a front cone section 2, a column section 3, an inverted cone section 4, a segmented longitudinal separation structure 5, a combined exhaust structure 6 and a bolt box docking frame combined structure 7;

[0036] The end head 1, the front cone section 2, the column section 3, and the inverted cone section 4 are all column structures formed by combining two half covers, the interiors of the front cone section 2, the column section 3, and the inverted cone section 4 are all connected to the segmented longitudinal separation structure 5, and the end head 1, the front cone section 2, the column section 3, and the inverted cone section 4 are connected in sequence through end faces to form a solid carrier fairing structure, which is used to protect the target aircraft from aerodynamic loads, heat flow, and other harmful environments during the flight of the carrier rocket;

[0037] The segmented longitudinal separation structure 5 is used to make the solid carrier fairing structure complete before separation, and to change the solid carrier fairing into two half fairings after separation, so as to ensure the normal separation of the fairing;

[0038] A combined exhaust structure 6 and a bolt box docking frame combined structure 7 are provided at the tail end of the inverted cone section 4. The combined exhaust structure 6, which prevents the exhaust structure from affecting the internal noise, is used to balance the pressure difference between the inside and outside of the fairing during the flight of the solid carrier rocket. The bolt box docking frame combined structure 7 is used for the connection and bearing between the fairing and the control cabin.

[0039] In order to adapt to the assembly process that omits the traditional adapter ring structure, the present invention adopts a combined adapter fairing structure design. The lower end frame of the inverted cone section has a connection interface with the satellite bracket and a connection interface with the control cabin on the same docking surface, which adapts to the solution requirements of eliminating the adapter ring. For the first time, two assembly docking modes of horizontal docking and vertical docking of the inverted cone structure fairing are realized, which greatly improves the flexibility of fairing use. In addition, the traditional adapter ring structure is eliminated, the weight of the four-stage structure is reduced, and the carrying capacity is improved.

[0040] like Figure 4 As shown, the segmented longitudinal separation structure 5 comprises: a longitudinal separation device 8 and a point connection structure 9;

[0041] The longitudinal division device 8 is used to connect the front cone section 2 and the column section 3 half cover, and the point connection structure 9 is used to connect the reverse cone section 4 half cover; the combination of the longitudinal division device 8 and the point connection structure 9 meets the load-bearing and functional requirements. The present invention adopts a segmented longitudinal division innovative combination structure, so that the longitudinal division structure can adapt to the requirements of pulsating pressure under large cone angles.

[0042] Preferably, the axial spacing between the longitudinal dividing device 8 and the point-type connecting structure 9 is set to 30 mm-300 mm.

[0043] like Figure 5 As shown, the point connection structure 9 includes a longitudinal separation structure bolt box 10 and a bolt box reinforcement plate 11. The longitudinal separation structure bolt box 10 is connected with the inverted cone section 4 to transfer the point concentrated load to the inverted cone section 4. The longitudinal separation structure bolt box 10 is connected with the separation bolts at the separation joint surface to bear the concentrated load.

[0044] A bolt box reinforcement plate 11 is also provided at the connection between the bolt box 10 of the longitudinal separation structure and the inverted cone section 4 for diffusing the load.

[0045] The side length of the bolt box reinforcement plate 11 is 200mm-350mm.

[0046] There are two main existing solutions for longitudinal separation: a point-type bolt box structure, which has a strong bearing capacity, but the bolt box requires thermal protection and causes multiple local bulges; a longitudinal separation device composed of a butt truss and notch bolts, which has no bulges on the surface, but has a weak bearing capacity at the cone-column butt joint, and requires additional point-type connection reinforcement.

[0047] The present invention adopts a segmented innovative structure, in which the front cone column section is connected by a longitudinal dividing device composed of a butt truss and notched bolts to avoid local bulges; the inverted cone section is connected by point connection, and internal and external bearing structures are added to adapt to the load requirements under large pulsating pressure.

[0048] like Figure 6 As shown, the combined exhaust structure 6 includes: an air inlet hole 12 in the separation bolt box, an air vent hole 13 in the separation bolt box cover, a small fairing 14 at the exhaust hole, and an exhaust hole 15 at the lower end of the small fairing;

[0049] The air inlet 12 in the separation bolt box is arranged on the separation bolt box, and is arranged along the axial direction of the fairing. The air vent 13 of the separation bolt box cover is arranged on the separation bolt box cover, and is arranged perpendicular to the axial direction of the fairing. The small fairing 14 at the exhaust hole is installed on the inverted cone section 4, and the area enclosed by the air vent 13 of the separation bolt box cover forms the exhaust hole 15 at the lower end of the small fairing. The exhaust holes 15 at the lower end of the small fairing are distributed along the axial direction of the fairing.

[0050] The exhaust path 16 of the gas in the fairing is specifically as follows: the gas in the fairing enters the separation bolt box through the air inlet 12 in the separation bolt box, and then passes through the separation bolt box cover vent 13 and the exhaust hole 15 at the lower end of the small fairing in sequence before being discharged.

[0051] When a solid carrier rocket is flying, exhaust is discharged through the exhaust path 16 under the action of the pressure difference inside and outside the fairing. At the same time, the small fairing 14 at the exhaust hole avoids the influence of the exhaust structure on the internal noise; the exhaust areas of the air inlet 12 in the separation bolt box, the air vent 13 in the separation bolt box cover, and the exhaust hole 15 at the lower end of the small fairing match each other.

[0052] In view of the requirement of balancing the internal and external pressure difference of solid transport, the present invention designs a combined exhaust structure at the separation bolt box to avoid the influence of a single exhaust structure on the load bearing and internal noise. The bolt box transmits the load through the girders on both sides, so only a large number of exhaust openings are added on the inner side of the force transmission structure to avoid the influence on the load bearing.

[0053] Preferably, the exhaust area of ​​the air inlet 12 in the separation bolt box, the air vent 13 in the separation bolt box cover, and the exhaust hole 15 at the lower end of the small fairing is set to 2000mm 2 -4000 mm 2 .

[0054] Due to the influence of large cone angle pulsating pressure, the fairing faces higher load requirements. The commonly used solution of inner end frame and outer bolt box on the lower end of the inverted cone section of the fairing cannot meet the load requirements. For this reason, a combined load reduction technology of separation bolt box and docking frame for large cone angle pulsating pressure has been developed. Through the combined design, the separation surface docking pitch circle is changed, the separation surface lever effect is reduced, and the load capacity is improved.

[0055] like Figure 2 and 3 As shown, the bolt box docking frame combination structure 7 includes: a bolt box 17 and a docking frame 18, a bolt box mounting structure 19 is reserved on the docking frame 18, and the bolt hole docking position 20 on the bolt box mounting structure 19 is adjusted so that L1=L2, wherein L1 is the distance between the bolt hole docking position 20 and the axis of the fairing, and L2 is the distance between the side wall 21 of the docking frame and the axis of the fairing.

[0056] Preferably, the size difference between the distances L1 and L2 is set to -10 mm to 10 mm.

[0057] The docking frame adjusts the pitch circle of the bolt hole docking position and reserves a bolt box installation structure. After the bolt box is connected, there is no additional lever effect when loading, which prevents the bolt tension from being further amplified and enhances the loading of the docking structure. At this time, the docking structure changes from a traditional bolt box to a combination of a bolt box and a docking frame.

[0058] Parts of the present invention that are not described in detail belong to common knowledge among those skilled in the art.

Claims

1. A solid carrier fairing capable of resisting pulsating pressure at a large cone angle, characterized in that: It comprises an end head (1), a front cone section (2), a column section (3), an inverted cone section (4), a segmented longitudinal separation structure (5), a combined exhaust structure (6) and a bolt box docking frame combined structure (7); The end head (1), the front cone section (2), the column section (3), and the inverted cone section (4) are all column structures formed by combining two half covers, the interiors of the front cone section (2), the column section (3), and the inverted cone section (4) are all connected to the segmented longitudinal separation structure (5), and the end head (1), the front cone section (2), the column section (3), and the inverted cone section (4) are connected in sequence through end faces to form a solid carrier fairing structure, which is used to protect the target aircraft from the influence of aerodynamic loads, heat flow and other harmful environments during the flight of the carrier rocket; The segmented longitudinal separation structure (5) is used to make the solid carrier fairing structure complete before separation, and to convert the solid carrier fairing into two half fairings after separation, so as to ensure the normal separation of the fairing; A combined exhaust structure (6) and a bolt box docking frame combined structure (7) are provided at the rear end of the inverted cone section (4); the combined exhaust structure (6) for preventing the exhaust structure from influencing internal noise is used to balance the pressure difference between the inside and outside of the fairing during the flight of the solid carrier rocket; and the bolt box docking frame combined structure (7) is used for connecting and bearing the fairing and the control cabin; The segmented longitudinal separation structure (5) comprises: a longitudinal separation device (8) composed of a butt beam and a notch bolt, and a point connection structure (9); The longitudinal dividing device (8) is used to connect the front cone section (2) and the column section (3) half covers, and the point-type connecting structure (9) is used to connect the reverse cone section (4) half covers; the combination of the longitudinal dividing device (8) and the point-type connecting structure (9) satisfies the load-bearing and functional requirements at the same time; The combined exhaust structure (6) comprises: an air inlet hole (12) in the separation bolt box, an air vent hole (13) in the separation bolt box cover, a small fairing (14) at the exhaust hole, and an exhaust hole (15) at the lower end of the small fairing; The air inlet (12) in the separation bolt box is arranged on the separation bolt box and arranged along the axial direction of the fairing; the air vent (13) in the separation bolt box cover is arranged on the separation bolt box cover and arranged perpendicular to the axial direction of the fairing; the small fairing (14) at the exhaust hole is installed on the inverted cone section (4), and the area enclosed by the air vent (13) in the separation bolt box cover forms an exhaust hole (15) at the lower end of the small fairing; the exhaust hole (15) at the lower end of the small fairing is arranged along the axial direction of the fairing; The exhaust path (16) of the gas in the fairing is specifically as follows: the gas in the fairing enters the separation bolt box through the air inlet hole (12) in the separation bolt box, and then passes through the vent hole (13) of the separation bolt box cover and the exhaust hole (15) at the lower end of the small fairing in sequence before being discharged; The bolt box docking frame combination structure (7) comprises: a bolt box (17) and a docking frame (18), a bolt box mounting structure (19) is reserved on the docking frame (18), and the bolt hole docking position (20) on the bolt box mounting structure (19) is adjusted so that L1=L2, wherein L1 is the distance between the bolt hole docking position (20) and the axis of the fairing, and L2 is the distance between the side wall (21) of the docking frame and the axis of the fairing.

2. The solid carrier fairing capable of resisting pulsating pressure at a large cone angle according to claim 1, characterized in that: The axial spacing between the longitudinal dividing device (8) and the point-type connecting structure (9) is set to 30 mm-300 mm.

3. A solid carrier fairing capable of resisting pulsating pressure at a large cone angle according to claim 1 or 2, characterized in that: The point connection structure (9) comprises a longitudinal separation structure bolt box (10) and a bolt box reinforcement plate (11); the longitudinal separation structure bolt box (10) is connected to the inverted cone section (4) to transfer the point concentrated load to the inverted cone section (4); the longitudinal separation structure bolt box (10) is connected to the separation bolts at the separation joint surface to bear the concentrated load; A bolt box reinforcement plate (11) is also provided at the connection between the longitudinal separation structure bolt box (10) and the inverted cone section (4) for diffusing the load.

4. The solid carrier fairing capable of resisting pulsating pressure at a large cone angle according to claim 3, characterized in that: The bolt box reinforcement plate (11) has a structural side length of 200 mm to 350 mm.

5. The solid carrier fairing capable of resisting pulsating pressure at a large cone angle according to claim 1, characterized in that: When a solid carrier rocket is flying, exhaust is discharged through an exhaust path (16) under the action of a pressure difference between the inside and outside of the fairing, and at the same time, the small fairing (14) at the exhaust hole avoids the influence of the exhaust structure on the internal noise; the exhaust areas of the air inlet hole (12) in the separation bolt box, the air vent hole (13) in the separation bolt box cover, and the exhaust hole (15) at the lower end of the small fairing match each other.

6. The solid carrier fairing capable of resisting pulsating pressure at a large cone angle according to claim 5, characterized in that: The exhaust area of ​​the air inlet (12) in the separation bolt box, the air vent (13) in the separation bolt box cover, and the exhaust hole (15) at the lower end of the small fairing is set to 2000mm 2 -4000 mm 2 .

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