A modular exhaust separation device for inter-stage thermal separation of aircraft

Abstract

The present invention provides a modular flame exhaust separation device for inter-stage thermal separation of aircraft, belonging to the field of aerospace technology. It includes a standard housing, an auxiliary bearing protection cover, a detonating module, a connecting bolt pair, and a flexible detonating cord. The auxiliary bearing protection cover is fixed inside the standard housing through the connecting bolt pair. The detonating module is arranged at the reserved position of the auxiliary bearing protection cover and fixed to the standard housing through the connecting bolt pair. The flexible detonating cord is arranged at the contact part between the auxiliary bearing protection cover and the detonating module, and is kept in contact with the inner surface of the standard housing through a pre-tightening force, surrounds the flame exhaust window for one week and connects the detonating module. The standard housing is of a rotary body structure and includes an end flange and a rotary housing. The auxiliary bearing protection cover includes a protection cover ring body and connecting lugs. The detonating module includes a detonating seat, a detonating tube, a transition pipe, and a head. The present invention solves the problems of poor versatility and weak bearing capacity of the existing flame exhaust separation device.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace technology, and particularly relates to a modular flame exhaust separation device for inter-stage thermal separation of an aircraft. Background Art

[0002] Spacecraft sometimes adopt a thermal separation form in which the engine starts first and then separates during inter-stage separation to improve controllability. When adopting this thermal separation method, it is necessary to open a flame exhaust window on the inter-stage section shell before inter-stage separation to avoid damage to the shell and instruments due to the influence of the high-temperature gas ejected by the engine in the inter-stage section.

[0003] The prior art generally adopts directly opening rectangular, triangular or other shaped through holes in the skin between adjacent stringers and frames as the flame exhaust ports. Since the shear force is mainly transmitted by the skin in the skin-stringer structure, the structural shear resistance at the dug-out skin structure is greatly reduced, thereby affecting the torsional stiffness of the inter-stage section. Ways such as adding diagonal ribs and changing the rectangular flame exhaust port to a triangular flame exhaust port can improve the structural shear resistance and torsional stiffness to a certain extent, but the effect is limited, and it is restricted by the structural size constraints, with poor design flexibility and affecting the load-bearing capacity of the aircraft.

[0004] In addition, when a high-speed aircraft is flying, it is required that the outer shell is a sealed continuous shell to reduce air resistance, improve the heat protection ability, and protect internal components. Therefore, a high-speed aircraft needs to be provided with a separate flame exhaust separation device to ensure the integrity of the shell during flight and open the flame exhaust window at the required moment. The structures, external dimensions, etc. of different aircraft vary greatly. Existing flame exhaust ports are all designed separately according to specific types of spacecraft, with poor versatility. Each time a new type is designed, it is necessary to re-design, test, and verify, resulting in a long design cycle.

[0005] In summary, the existing flame exhaust separation devices of aircraft have poor versatility and weak load-bearing capacity, and need to be improved. Summary of the Invention

[0006] The present invention provides a modular flame exhaust separation device for inter-stage thermal separation of an aircraft, aiming to solve the problems of poor versatility and weak load-bearing capacity of the existing flame exhaust separation devices.

[0007] A modular flame exhaust separation device for inter-stage thermal separation of an aircraft includes a standard shell, an auxiliary load-bearing protective cover, a detonating module, a connecting bolt pair, and a flexible detonating cord;

[0008] There are at least two auxiliary bearing protective covers, which are evenly distributed along the circumferential direction and fixed to the inner side of the standard housing through connecting bolt pairs; the initiating module is arranged at the reserved position of the auxiliary bearing protective cover and fixed to the standard housing through connecting bolt pairs; the flexible detonating cord is arranged at the contact part between the auxiliary bearing protective cover and the initiating module, and is kept in contact with the inner surface of the standard housing through a pre-tightening force, surrounds the exhaust window for one week and connects the initiating module;

[0009] The standard housing is of a rotary body structure, including end flanges and a rotary housing. There are two end flanges with the same specifications, which are coaxially arranged at the upper and lower ends of the rotary housing; at least two pre-set exhaust window areas are evenly distributed on the rotary housing; two continuous weakening grooves are arranged in parallel on the outer periphery of the pre-set exhaust window area, namely the inner separation groove and the outer crack arrest groove; the bottoms of the crack arrest groove and the separation groove are both rounded, the distance between the bottom of the separation groove and the inner wall of the rotary housing is H5, and the distance between the bottom of the crack arrest groove and the inner wall of the rotary housing is H4, satisfying H5≤H4≤11H5;

[0010] The auxiliary bearing protective cover includes a protective cover ring body and connecting lugs. The overall shape of the protective cover ring body is a flat arc rectangle formed by sweeping along the separation groove. There are four connecting lugs, which are respectively arranged at the four corners of the protective cover ring body; the cross-section of the protective cover ring body is stepped, including an outer ring step, a middle ring step and an inner ring step with gradually increasing thickness, and the joints of each ring are rounded; a first through hole is arranged on the outer ring step for connecting the standard housing; a continuous flexible detonating cord installation groove is arranged on the side of the middle ring step that fits the rotary housing. The cross-section of the flexible detonating cord installation groove is U-shaped, and the opening side faces the rotary housing. The axis of the flexible detonating cord installation groove is arranged along the sweeping track of the separation groove; a first threaded hole is arranged on the connecting lug for connecting the end flange; an initiating area is arranged in the middle position of one of the arc segments of the protective cover ring body for installing the initiating module;

[0011] The initiating module includes an initiating seat, an initiating tube, a transition tube and a head; in each set of initiating modules, there are two initiating tubes, two transition tubes and two heads, which are used in sets and arranged in parallel along the radial direction on the initiating seat; the two ends of the same flexible detonating cord are respectively inserted into the two initiating tubes, and the end of the installed flexible detonating cord is cut flat along the end face of the small end of the initiating tube; the large end of the initiating tube is threadedly connected to the initiating seat, and the small end is threadedly connected to the transition tube; the head is detachably fixed to the opening side of the transition tube; the initiating seat includes a thick step area and a thin step area; two second threaded holes are arranged on the thick step area for installing the initiating tubes; two coaxial detonating cord installation grooves are symmetrically arranged on the side of the thick step area close to the rotary housing, and are respectively communicated with the interrupted parts of the flexible detonating cord installation grooves; a blocking structure is arranged between the two detonating cord installation grooves; a second through hole is arranged on the thin step area for installing the connecting bolt pair.

[0012] As a preferred solution, there are four auxiliary load-bearing protective covers, and the interval between two adjacent ones is 90°.

[0013] As a preferred solution, transverse ribs are provided between adjacent flame exhaust area positions on the inner wall surface of the standard shell, and the cross section of the transverse ribs is trapezoidal or rectangular.

[0014] As a preferred solution, an extended edge guard is provided on the side of the connection between the detonating seat and the auxiliary bearing protective cover away from the detonating cord installation groove to shield the explosion products when the flexible detonating cord is working.

[0015] As a preferred solution, the center distance between the second threaded holes is 20-23 mm.

[0016] As a preferred solution, the center distance between the crack-stopping groove and the separation groove ranges from 7 to 10 mm.

[0017] As a preferred solution, the charge of the flexible detonating cord is 4 g / m.

[0018] As a preferred solution, the standard housing is made of 2A14T6 aluminum alloy, which is integrally forged and then machined.

[0019] As a preferred solution, the auxiliary bearing protection cover is an integrated structure, made of 2A14T6 aluminum alloy, which is forged as a whole and then machined.

[0020] As a preferred solution, the detonator seat, detonator tube, transfer tube and head are all made of stainless steel of 0Cr13Ni8Mo2Al material.

[0021] The beneficial technical effects achieved by the present invention are:

[0022] Compared with the existing technology, it can realize the controlled cutting and separation of the flame exhaust window section cabin, quickly open a large area of ​​flame exhaust window, and realize modularization, large diameter and high load-bearing performance, solving the problems of poor versatility and weak load-bearing capacity of existing flame exhaust separation devices, and has outstanding substantial characteristics and significant progress. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a structural schematic diagram of a flame exhaust separation device according to one specific embodiment of the present invention;

[0024] Figure 2 It is a schematic diagram of a standard housing structure of one specific embodiment of the present invention;

[0025] Figure 3 It is a schematic diagram of the structure of an auxiliary bearing protective cover in one specific embodiment of the present invention;

[0026] Figure 4 yes Figure 3 Schematic diagram of the structure from another perspective;

[0027] Figure 5 It is a schematic diagram of a partial structure of a cutting and separating section of one specific embodiment of the present invention;

[0028] Figure 6 It is a schematic diagram of the principle of a part of the initiation structure of one specific embodiment of the present invention;

[0029] Figure 7 It is a schematic diagram of the initiation seat structure of one specific embodiment of the present invention;

[0030] Figure 8 is Figure 7 a schematic diagram of the structure of the initiation seat from another perspective in;

[0031] Figure 9 It is a schematic diagram of the combined use state of the flame exhaust separation device of the second specific embodiment of the present invention;

[0032] Reference numerals: 1, standard housing; 2, auxiliary bearing protection cover; 3, initiation module; 4, connecting bolt pair; 5, flexible detonating cord; 6, initiation seat; 7, initiation tube; 8, adapter tube; 9, head; 11, end flange; 14, transverse rib; 15, preset flame exhaust window area; 16, rotary housing; 17, crack arrest groove; 18, separation groove; 21, protection cover ring body; 22, connecting lug; 23, first threaded hole; 24, initiation area; 25, flexible detonating cord installation groove; 27, first through hole; 61, thick step area; 62, thin step area; 63, second threaded hole; 64, detonating cord installation groove; 66, second through hole; 67, edge protection; 211, outer ring step; 212, middle ring step; 213, inner ring step. Specific embodiments

[0033] The technical solutions of the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative efforts fall within the scope of protection of the present invention.

[0034] Such as Figures 1 to 8As shown in the figure, a specific embodiment of a modular flame exhaust separation device for inter-stage thermal separation of an aircraft is applicable to a space vehicle using inter-stage thermal separation. In response to the functional requirements of opening a flame exhaust window in the inter-stage section housing for the inter-stage thermal separation working state, a modular flat flame exhaust separation device structural design scheme is adopted, which can quickly, safely, and reliably control the opening of the flame exhaust window when the lower-stage engine starts, can match the sizes of multiple types of inter-stage sections, and has low use cost and high reliability. In this specific embodiment, the direction of the modular large-diameter flat flame exhaust separation device is determined according to the vehicle cabin section. The side close to the upper-stage engine is the upper side, and the side close to the lower-stage engine is the lower side.

[0035] In this specific embodiment, the modular flame exhaust separation device includes a standard housing 1, an auxiliary load-bearing protection cover 2, a detonating module 3, a connecting bolt pair 4, and a flexible detonating cord 5.

[0036] There are multiple auxiliary load-bearing protection covers 2, which are evenly distributed along the circumferential direction and are fixed to the inner side of the standard housing 1 through the connecting bolt pair 4. In this specific embodiment, there are four auxiliary load-bearing protection covers 2, with an interval of 90° between adjacent ones. Other quantities can also be adopted, which are determined according to actual needs, and an even number is preferably adopted. The auxiliary load-bearing protection cover 2 has three functions: one is to be used for the installation and positioning of the detonating module 3 and the flexible detonating cord 5, and to bear the separation impact of the flexible detonating cord 5 during the separation process; the second is to effectively increase the load-bearing capacity in the axial tension and compression directions of the flame exhaust area, and solve the problem of the decrease in the load-bearing capacity of the flame exhaust area housing caused by the weakening groove provided on the standard housing 1; the third is to be used as a window frame for strengthening the periphery of the window after the flame exhaust window is opened, and to improve the comprehensive load-bearing capacity.

[0037] The detonating module 3 is arranged at the reserved position of the auxiliary load-bearing protection cover 2 and is fixed to the standard housing 1 through the connecting bolt pair 4. The flexible detonating cord 5 is arranged at the contact part between the auxiliary load-bearing protection cover 2 and the detonating module 3, and is kept in contact with the inner surface of the standard housing 1 through a pre-tightening force, surrounds the flame exhaust window for one week and connects the detonating module 3.

[0038] In this specific embodiment, the standard housing 1 has a rotary body structure and is made of 2A14T6 aluminum alloy. It is integrally forged and then machined, including end flanges 11 and a rotary housing 16. There are two end flanges 11 with the same specifications, which are coaxially arranged at the upper and lower ends of the rotary housing 16. The overall outer height of the standard housing 1, that is, the distance between the outer end faces of the two end flanges 11 is H1; the distance between the inner end faces of the two end flanges 11 is H2. Multiple pre-set flame exhaust window areas 15 are evenly distributed on the rotary housing 16. Two continuous weakening grooves are arranged in parallel on the outer periphery of the pre-set flame exhaust window area 15, namely the inner separation groove 18 and the outer crack arrest groove 17. The axial spacing of the bottom of the separation groove 18 is A, and the radial spacing arc length is B. The surrounded area is the pre-set flame exhaust window, and the area of its flame exhaust window is S1, S1 = A × B. The function of the crack arrest groove 17 is to prevent cracks from occurring in the part outside the flame exhaust window during separation and damage the overall structure.

[0039] In this specific embodiment, the bottoms of both the crack arrest groove 17 and the separation groove 18 adopt rounded transitions with a rounded radius of R1. The center distance between the crack arrest groove 17 and the separation groove 18 is H3, and the preferred value range is H3 = 7 - 10 mm. The distance between the bottom of the separation groove 18 and the inner wall of the rotary housing 16, that is, the remaining thickness of the rotary housing 16 at the separation groove 18 is the separation thickness H5. In this specific embodiment, the separation thickness H5 = 37 mm. The distance between the bottom of the crack arrest groove 17 and the inner wall of the rotary housing 16 is the remaining thickness H4 of the crack arrest groove 17. The relationship between the remaining thickness H4 of the crack arrest groove 17 and the remaining thickness H5 of the separation groove 18 is H5 ≤ H4 ≤ 11H5, so as to ensure that the gas action during the explosion of the flexible detonating cord 5 mainly acts on the separation groove 18, making the separation surface ensure the position of the separation groove 18. At the same time, the not-too-thick crack arrest groove 17 ensures that the impact aftereffect of the explosive separation stops at the crack arrest groove 17, avoiding damage to the non-separation area of the rotary housing 16.

[0040] In this specific embodiment, several transverse ribs 14 are also arranged on the inner wall surface of the standard housing 1 between adjacent positions of the flame exhaust areas 15 to increase the stiffness of the housing. The cross-section of the transverse rib 14 is trapezoidal or rectangular, and specific parameters such as the quantity, position, and size can be adjusted adaptively according to actual needs. The flame exhaust area 15 is a part of the rotary housing 16 before separation, enabling the inter-stage section to maintain a sealed state before separation. It detonates and disengages before separation to form a flame exhaust port with sufficient area to meet the flame exhaust requirements.

[0041] In this specific embodiment, the auxiliary load-bearing protective cover 2 is of an integral structure and is made of aluminum alloy of 2A14T6 material. It is integrally forged and then machined, which improves the structural load-bearing capacity while ensuring the protection performance. The auxiliary load-bearing protective cover 2 includes a protective cover ring body 21 and connecting lugs 22. The overall shape of the protective cover ring body 21 is a flat arc rectangle formed by sweeping along the separation groove 18. There are four connecting lugs 22, which are respectively arranged at the four corners of the protective cover ring body 21. The overall height of the auxiliary load-bearing protective cover 2, that is, the distance between the outer end faces of the two connecting lugs 22 arranged coaxially is h1, which is determined according to the inner height H2 of the standard housing 1 and is in a small clearance or small interference fit. The area enclosed by the inner hole height H3 and the arc length B3 of the protective cover ring body 21 is the exhaust area S2, and S2 = B3 × H3. The exhaust area S2 is slightly smaller than the exhaust window area S1. In this specific embodiment, the adaptable amount of flexible detonating cord is 4 g / m.

[0042] In this specific embodiment, the cross-section of the protective cover ring body 21 is stepped, including an outer ring step 211, a middle ring step 212, and an inner ring step 213 with gradually increasing thicknesses. The specific dimensions such as the thickness and radial width of each ring are determined according to actual needs, and the joints are transitioned with rounded corners. A first through hole 27 is provided on the outer ring step 211 for connecting the standard housing 1. In this specific embodiment, there are 64 first through holes 27 with a specification of Φ8.5 mm to match the M8 screws. The specific parameters such as the number, position, and size of the first through holes 27 can be adaptively adjusted according to actual needs. On the outer side of the middle ring step 212, that is, the side in contact with the rotary housing 16, there is a continuous flexible detonating cord installation groove 25. The cross-section of the flexible detonating cord installation groove 25 is U-shaped, and the opening side faces the rotary housing 16. The axis of the flexible detonating cord installation groove 25 is set along the sweeping trajectory of the separation groove 18. The inner ring step 213 is used to increase the overall stiffness.

[0043] In this specific embodiment, there are four connecting lugs 22, which are respectively arranged at the four corners of the protective cover ring body 21. A first threaded hole 23 is provided on the connecting lugs 22 for connecting the end flange 11 of the standard housing 1. In the middle position of one of the arc segments of the protective cover ring body 21, there is a detonation area 24. The detonation area 24 interrupts the crack arrest groove 17, the separation groove 18, and the flexible detonating cord installation groove 25, with a width of b2, for installing the detonation module 3. The specific dimension of the width b2 is determined according to the installation requirements of the detonation module 3. When the auxiliary load-bearing protective cover 2 is aligned and installed with the standard housing 1, the central position of the flexible detonating cord installation groove 25 is aligned with the central position of the separation groove 18.

[0044] In this specific embodiment, the initiating module 3 includes an initiating seat 6, initiating tubes 7, adapter tubes 8, and end caps 9. There are two initiating tubes 7, two adapter tubes 8, and two end caps 9 in each set of initiating modules 3. They are used in sets and arranged radially and parallelly on the initiating seat 6. The two ends of the same flexible detonating cord 5 are respectively inserted into the two initiating tubes 7, and the end of the installed flexible detonating cord 5 is cut flat along the end face of the small end of the initiating tube 7.

[0045] The large end of the initiating tube 7 is connected to the initiating seat 6 by a thread. The small end of the initiating tube 7 is connected to the adapter tube 8 by a thread. The end cap 9 is detachably fixed to the open side of the adapter tube 8 by a thread, which plays a protective role during daily maintenance. When in use, the end cap 9 is removed and replaced with a pyrotechnic initiating device. The initiating seat 6, initiating tubes 7, adapter tubes 8, and end caps 9 are all made of stainless steel of 0Cr13Ni8Mo2Al material, ensuring the safety of protection against explosion shock and preventing hydrogen embrittlement.

[0046] In this specific embodiment, the initiating seat 6 is a stepped cubic block made of 0Cr13Ni8Mo2Al material, including a thick step area 61 and a thin step area 62. Two second threaded holes 63 are provided on the thick step area 61 for installing the initiating tubes 7. The center distance C1 of the second threaded holes 63 is generally taken as 20 - 23 mm. In this specific embodiment, the initiating distance C1 = 20 mm. Since there is no flexible detonating cord 5 distributed within this distance, the explosive shocks on both sides are required to exert a separating effect on the rotating shell 16 within the initiating distance. Therefore, a smaller distance can ensure a stronger separating effect with a smaller amount of flexible detonating cord 5. At the same time, too small a distance will cause the flexible detonating cords 5 in the initiating seat 6 to affect each other. Considering the installation space, the distance C1 is not less than 20 mm. On the outside of the thick step area 61, that is, on the side close to the rotating shell 16, two coaxial detonating cord installation grooves 64 are symmetrically provided, which are respectively communicated with the interrupted parts of the flexible detonating cord installation grooves 25. A blocking structure 65 is provided between the two detonating cord installation grooves 64 to prevent the different detonating cord installation grooves 64 from affecting each other when the flexible detonating cord 5 is working. A second through hole 66 is provided on the thin step area 62 for installing the connecting bolt pair 4 to fix the initiating seat 6 to the standard shell 1. The distance between the two side edges of the initiating seat 6 is the width C2, and the size of C2 is determined according to the width B2 of the initiating area 24, and a small clearance or small interference fit is adopted. An extended edge guard 67 is also provided on the side of the connection between the initiating seat 6 and the auxiliary bearing protection cover 2 away from the detonating cord installation groove 64, which is used to shield the explosion products when the flexible detonating cord 5 is working.

[0047] The working principle of the modular flame exhaust and separation device in this specific embodiment is:

[0048] When the preset moment is reached, the detonators installed on the detonation seats of each window are controlled to detonate at the same time, giving the built-in flexible detonating cords at each flame exhaust window an initiating effect. Each flexible detonating cord explodes rapidly, producing a detonation effect. The detonation effect gathered by the protective cover reaches the separation groove of the shell, causing the shell at the separation groove of each flame exhaust window to break, and the breaking effect is controlled in the area within the crack stop groove. After the separation groove of the flame exhaust window is cut off, the gas pressure after the detonation acts on the edge of the shell of the corresponding preset flame exhaust window area, and pushes the separated flame exhaust window shells to fly out at the same time, opening the engine's flame exhaust channel and completing the working process of the flame exhaust separation device.

[0049] like Figure 9 As shown, a second specific embodiment of a modular flame exhaust separation device for thermal separation between aircraft stages is used for thermal separation between certain solid rocket stages, and two sets of modular flame exhaust separation devices are arranged in series, and the upper and lower end faces are respectively connected to the front and rear two-stage shells. The total height of the two sets of modular flame exhaust separation devices is 2×H1. As a preferred solution, the flame exhaust separation device located at the lower layer can be turned over, and the detonation modules 3 in the upper and lower sets of flame exhaust separation devices can be placed adjacent to each other. The end flanges 11 between the two sets of flame exhaust separation devices are fitted together and connected into one by bolts.

[0050] The beneficial technical effects achieved by the present invention are:

[0051] 1. Modular use: The standard shell has a small height and strong adaptability. It can be used to meet the functional requirements of interstage heat separation and flame exhaust windows with different interstage heights and flame exhaust area requirements.

[0052] 2. Strong bearing capacity: The auxiliary bearing protection cover can effectively increase the bearing capacity of the flame exhaust zone in the axial tensile and compression directions, solving the problem of decreased bearing capacity of the flame exhaust zone shell caused by the separation groove. At the same time, after the flame exhaust window is opened, the auxiliary bearing protection cover forms a reinforced window frame around the window to improve the comprehensive bearing capacity.

[0053] 3. Large flame exhaust area: About 50% of the circumferential area of ​​the standard shell is used as a flame exhaust window to meet the needs of large-flow flame exhaust.

[0054] 4. Small separation impact: By setting the crack-stop groove, the impact transmitted along the shell caused by the separation groove being cut off can be effectively isolated, providing a better impact mechanical environment for the instruments in the interstage section and protecting the outer part of the standard shell from cracking in the flame exhaust area.

[0055] 5. Fast separation: The flame exhaust area is cut off from the standard separation shell along the separation groove by the detonation effect of the flexible detonating cord, and the flame exhaust area shell that has been cut is quickly pushed out radially by the aftereffect of the flexible detonating cord. The overall separation speed and flame exhaust window opening speed are fast.

[0056] In summary, compared with the prior art, the technical solution proposed in this specific embodiment can be used modularly, and has the advantages of large flame exhaust area, strong bearing capacity, small separation impact, and fast separation, solving the problems of poor versatility and weak bearing capacity in the prior art, and having prominent substantive features and remarkable progress.

Claims

1. A modular flame exhaust separation device for inter-stage thermal separation of an aircraft, characterized in that, It includes a standard housing (1), an auxiliary load-bearing protective cover (2), a detonating module (3), a connecting bolt pair (4), and a flexible detonating cord (5); There are at least two of the auxiliary load-bearing protective covers (2), which are evenly distributed along the circumferential direction and are fixed to the inner side of the standard housing (1) through the connecting bolt pair (4); the detonating module (3) is arranged at the reserved position of the auxiliary load-bearing protective cover (2) and is fixed to the standard housing (1) through the connecting bolt pair (4); the flexible detonating cord (5) is arranged at the contact part between the auxiliary load-bearing protective cover (2) and the detonating module (3), and is kept in contact with the inner surface of the standard housing (1) through a pre-tightening force, surrounds the flame exhaust window for one week and connects the detonating module (3); The standard housing (1) is of a rotary body structure, including end flanges (11) and a rotary housing (16). There are two end flanges (11) with the same specifications, which are coaxially arranged at the upper and lower ends of the rotary housing (16); at least two preset flame exhaust window areas (15) are evenly distributed on the rotary housing (16); two continuous weakening grooves are arranged in parallel on the outer periphery of the preset flame exhaust window area (15), namely the inner separation groove (18) and the outer crack arrest groove (17); the bottoms of the crack arrest groove (17) and the separation groove (18) are both rounded; the distance between the bottom of the separation groove (18) and the inner wall of the rotary housing (16) is H5, and the distance between the bottom of the crack arrest groove (17) and the inner wall of the rotary housing (16) is H4, satisfying H5≤H4≤11H5; The auxiliary load-bearing protective cover (2) includes a protective cover ring body (21) and connecting lugs (22). The overall shape of the protective cover ring body (21) is a flat arc rectangle formed by sweeping along the separation groove (18). There are four connecting lugs (22), which are respectively arranged at the four corners of the protective cover ring body (21); the cross-section of the protective cover ring body (21) is stepped, including an outer ring step (211), a middle ring step (212), and an inner ring step (213) with gradually increasing thickness, and the joints of each ring are rounded; a first through hole (27) is arranged on the outer ring step (211) for connecting the standard housing (1); a continuous flexible detonating cord installation groove (25) is arranged on the side of the middle ring step (212) that fits with the rotary housing (16). The cross-section of the flexible detonating cord installation groove (25) is U-shaped, and the opening side faces the rotary housing (16). The axis of the flexible detonating cord installation groove (25) is arranged along the sweeping track of the separation groove (18); a first threaded hole (23) is arranged on the connecting lug (22) for connecting the end flange (11); a detonating area (24) is arranged at the middle position of one of the arc segments of the protective cover ring body (21) for installing the detonating module (3); The detonating module (3) includes a detonating seat (6), detonating tubes (7), adapter pipes (8) and end caps (9); there are two detonating tubes (7), two adapter pipes (8) and two end caps (9) in each set of detonating modules (3), which are used in sets and arranged radially and parallelly on the detonating seat (6); both ends of the same flexible detonating cord (5) are respectively inserted into the two detonating tubes (7), and the end of the installed flexible detonating cord (5) is cut flat along the end face of the small end of the detonating tube (7); the large end of the detonating tube (7) is connected to the detonating seat (6) by threads, and the small end is connected to the adapter pipe (8) by threads; the end cap (9) is detachably fixed to the opening side of the adapter pipe (8); the detonating seat (6) includes a thick step area (61) and a thin step area (62); two second threaded holes (63) are provided on the thick step area (61) for installing the detonating tubes (7); two coaxial detonating cord installation grooves (64) are symmetrically arranged on one side of the thick step area (61) close to the rotary housing (16), and are respectively communicated with the interrupted parts of the flexible detonating cord installation grooves (25); a blocking structure (65) is arranged between the two detonating cord installation grooves (64); a second through hole (66) is provided on the thin step area (62) for installing the connecting bolt pair (4).

2. The modular flame exhaust separation device according to claim 1, wherein There are four auxiliary bearing protective covers (2), and the interval between two adjacent ones is 90°.

3. The modular flame exhaust separation device according to claim 1, wherein On the inner wall surface of the standard housing (1), transverse ribs (14) are further arranged between the positions of adjacent flame exhausting areas (15), and the cross section of the transverse ribs (14) is trapezoidal or rectangular.

4. The modular exhaust flame separation device according to claim 1, wherein On the side of the connection between the detonating seat (6) and the auxiliary bearing protective cover (2) away from the detonating cord installation groove (64), an extended edge (67) is further arranged to shield the explosion products during the operation of the flexible detonating cord (5).

5. The modular flame exhaust separation device according to claim 1, wherein, The center distance between the second threaded holes (63) is 20 - 23 mm.

6. The modular exhaust flame separation device according to claim 1, characterized in that The value range of the center distance between the crack arrest grooves (17) and the separation grooves (18) is 7 - 10 mm.

7. The modular exhaust flame separation device according to claim 6, characterized in that, The charge of the flexible detonating cord (5) is 4 g / m.

8. The modular flame exhaust separation device according to any one of claims 1 to 7, characterized in that, The standard housing (1) is made of 2A14T6 aluminum alloy, and is integrally forged and then machined.

9. The modular flame exhaust separation device according to any one of claims 1 to 7, characterized in that, The auxiliary bearing protective cover (2) is of an integral structure, made of 2A14T6 aluminum alloy, and is integrally forged and then machined.

10. The modular exhaust flame separation device according to any one of claims 1 to 7, characterized in that, The detonating seat (6), detonating tubes (7), adapter pipes (8) and end caps (9) are all made of stainless steel of 0Cr13Ni8Mo2Al material.

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