Quick-response attitude control device

Abstract

The invention discloses a quick-response attitude control device, and belongs to the field of solid rocket engines, the quick-response attitude control device comprises a cabin section and a plurality of attitude control components arranged on the inner wall of the cabin section, each attitude control component comprises a spray pipe part, each spray pipe part comprises a spray pipe opening and a propellant mounting opening, and a propellant mounting shell is arranged at the propellant mounting opening; an ignition powder box and a combined charging part arranged in the circumferential direction of the ignition powder box are arranged in the propellant mounting shell, the combined charging part comprises a first charging assembly and a second charging assembly which are coaxially arranged in a sleeving mode, and the inner wall and the outer wall of the first charging assembly and the inner wall and the outer wall of the second charging assembly can make contact with the inner space of the propellant mounting shell. According to the quick-response attitude control device, by changing the structure of the combined charging component, the response time is shortened on the premise that a high-burning-rate propellant is not adopted, so that the attitude of the cabin section is quickly adjusted, and the quick-response attitude control device has the advantages of being short in response time, large in output effect, low in cost, high in integration degree, small in size and light in weight.

Description

Technical Field

[0001] The invention belongs to the field of solid rocket engines, and in particular relates to a fast-response attitude control device. Background Art

[0002] With the development of aircraft, the speed of aircraft is getting faster and faster, and the range is getting longer and longer. For aircraft in certain special fields, it is necessary to have good maneuverability so that the angle or direction of the aircraft can be adjusted well to cope with the attitude adjustment of the aircraft in different scenarios. For the response problem of aircraft, aerodynamic force is usually used for control. Although it can make the aircraft maneuverable to a certain extent, it has problems such as long response time, large constraints on the flight environment, and small available overload, which makes the rapid response ability of the aircraft poor, and there are many limitations in actual use. Summary of the invention

[0003] In response to one or more of the above defects or improvement needs in the prior art, the present invention provides a fast-response attitude control device to solve the problems of long response time, large flight environment constraints and small available overload of the existing aerodynamic control attitude control device.

[0004] To achieve the above-mentioned object, the present invention provides a fast-response attitude control device, comprising a cabin section, and a plurality of attitude control components arranged on the inner wall of the cabin section, wherein the plurality of attitude control components are respectively arranged at different positions of the inner wall of the cabin section, and the plurality of attitude control components can respectively release thrust to drive the cabin section to adjust its attitude; The attitude control component comprises: A nozzle portion, the nozzle portion comprising a nozzle port and a propellant installation port; A propellant installation shell is provided at the propellant installation port, the propellant installation shell is communicated with the nozzle port, and an ignition cartridge and a combined charge component are provided in the propellant installation shell; The combined charge component includes a first charge assembly and a second charge assembly which are coaxially sleeved, wherein the first charge assembly and the second charge assembly both have through holes axially therethrough, and a gap is left between the outer wall of the first charge assembly and the inner wall of the second charge assembly, so that the gas sprayed from the ignition cartridge can synchronously ignite the inner and outer sides of the first charge assembly and the inner and outer sides of the second charge assembly.

[0005] As a further improvement of the present invention, the plurality of attitude control components are uniformly distributed in the circumferential side wall of the cabin section along the circumferential direction, a sealing gasket is provided between the plurality of attitude control components and the inner wall of the cabin section, and the attitude control components are fixed to the inner wall of the cabin section by fasteners; The side wall of the cabin section is provided with a mounting hole, and the nozzle mouth of the attitude control component is attached to the mounting hole.

[0006] As a further improvement of the present invention, the nozzle mouth is sealed by a plugging cover, and the plugging cover has a conduction pressure of 3~5Mpa; a protective cover plate is provided at the mounting hole, and the protective cover plate closes the mounting hole, and the conduction pressure at the protective cover plate is 0.5~1Mpa.

[0007] As a further improvement of the present invention, the first charge assembly and the second charge assembly are both medium burning rate propellants, and the burning time of the first charge assembly and the second charge assembly is 0.05-0.15 s.

[0008] As a further improvement of the present invention, the first charge assembly and the second charge assembly have the same axial length, and a first charge rack and a second charge rack are respectively provided at both ends of the first charge assembly and the second charge assembly, and the first charge rack, the second charge rack, the first charge barrel and the second charge barrel are relatively fixedly arranged.

[0009] As a further improvement of the present invention, the second charge rack includes a first limiting portion and a plurality of second limiting portions arranged along the circumference of the first limiting portion; The first limiting portion is arranged in an annular shape, and the outer periphery of the first limiting portion abuts against the inner wall surface of the second charge assembly; A plurality of second limiting portions are radially extended along the first limiting portion, and a first limiting protrusion and a second limiting protrusion are provided on one side of the second limiting portions facing the first charge assembly, and the first limiting protrusion and the second limiting protrusion are arranged at an interval; two sides of the first limiting protrusion respectively abut against the outer wall of the second charge assembly and the inner wall of the first charge assembly; two sides of the second limiting protrusion respectively abut against the outer wall of the first charge assembly and the inner wall of the propellant installation shell.

[0010] As a further improvement of the present invention, the ignition cartridge comprises a cartridge body arranged in a cylindrical shape, one end of the cartridge body is provided with a charge hole, and the other end thereof is provided with a gas ejection hole; An igniter, a medicine box membrane and an ignition tablet are sequentially arranged in the medicine box body along the axial direction; there are a plurality of ignition tablets, and a medicine box membrane is arranged between each of the ignition tablets.

[0011] As a further improvement of the present invention, the igniter adopts a double-bridge circuit and a double-circuit ignition cable.

[0012] As a further improvement of the present invention, a first sealing ring is provided on the end surface where the igniter connects to the medicine box body; a second sealing ring is provided between the medicine box body and the propellant mounting shell, a third sealing ring is provided between the propellant mounting shell and the nozzle part, and the nozzle part is provided with a plugging cover at the nozzle mouth.

[0013] As a further improvement of the present invention, the inner circumferential wall surface of the propellant installation shell is provided with a shell insulation layer, and the inner circumferential wall surface of the nozzle part is provided with a nozzle insulation layer.

[0014] The above-mentioned improved technical features can be combined with each other as long as they do not conflict with each other.

[0015] In general, compared with the prior art, the above technical solution conceived by the present invention has the following beneficial effects: (1) The fast-response attitude control device of the present invention changes the structural form of the propellant, sets the combined charge component as a set of the first charge component and the second charge component, reserves through holes in the first charge component and the second charge component, and reserves a gap between the first charge component and the second charge component, so that when the igniter is ignited, the generated gas can contact the inner and outer sides of the first charge component and the second charge component at the same time, greatly reducing the response time of the attitude control device; then the attitude adjustment of the cabin section is achieved by controlling the start and stop of the attitude control components at different positions in the cabin section. At the same time, the present application reduces the response time without using high-burning-rate propellants by changing the structure of the combined charge component, thus avoiding the problem of poor safety caused by using high-burning-rate propellants. The fast-response attitude control device in the present application has the characteristics of short response time, large output effect, low cost, high degree of integration, miniaturization and light weight, and can well solve the problem of poor response speed of the attitude control device.

[0016] (2) The fast-response attitude control device of the present invention is characterized in that the first charge rack and the second charge rack are respectively provided at both ends of the first charge assembly and the second charge assembly, and the first charge assembly and the second charge assembly are fixed by the first charge rack and the second charge rack, so that the first charge assembly and the second charge assembly are stably installed inside the attitude control device; secondly, the first charge rack and the second charge rack can maintain the relative positions of the first charge assembly and the second charge assembly, so that a gap is reserved between the outer wall of the second charge assembly and the inner wall of the first charge assembly; at the same time, the two charge racks can reserve a gap between the outer wall of the first charge assembly and the inner wall of the propellant installation shell, so that the gas generated by the ignition cartridge can surround the inner and outer walls of the first charge assembly and the second charge assembly, thereby increasing the contact area between the gas and the first charge assembly and the second charge assembly, greatly reducing the burning time of the first charge assembly and the second charge assembly, and improving the effect rate of the attitude control device. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 is a cross-sectional schematic diagram of an attitude control component of a fast-response attitude control device in an embodiment of the present invention; Figure 2 Schematic diagram of the cross-sectional structure of the ignition cartridge in the embodiment of the present invention; Figure 3Schematic diagram of the overall structure of the combined charge component in the embodiment of the present invention; Figure 4 This is a schematic diagram of the overall structure of the cabin section in an embodiment of the present invention; Figure 5 It is a schematic diagram of a partial cross-sectional structure of a cabin section in an embodiment of the present invention; Figure 6 yes Figure 5 Enlarged schematic diagram at point A in the middle.

[0018] In all the drawings, the same reference numerals represent the same technical features, specifically: 1. Ignitor; 2. Ignition cartridge; 3. First sealing ring; 4. Second sealing ring; 5. Propellant installation housing; 6. Combined charge component; 7. Third sealing ring; 8. Nozzle; 9. Cabin; 10. Fastener; 11. Sealing gasket; 12. Protective cover; 21. Medicine box body; 22. Medicine box membrane; 23. Ignition tablet; 51. propellant outer shell; 52. shell insulation layer; 61, first charge rack; 621, first charge assembly; 622, second charge assembly; 63, second charge rack; 631, first position-limiting portion; 632, first position-limiting protrusion; 633, second position-limiting protrusion; 81. Nozzle body; 82. Nozzle insulation layer; 83. Throat lining; 84. Back lining; 85. Plug cap; 86. Pin. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0020] In the description of the present invention, it should be understood that, unless otherwise specified, terms such as “center”, “longitudinal”, “lateral”, “length”, “width”, “thickness”, “up”, “down”, “front”, “back”, “left”, “right”, “vertical”, “horizontal”, “top”, “bottom”, “inside”, “outside”, “clockwise”, “counterclockwise”, “axial”, “radial”, “circumferential”, etc., indicating orientations or positional relationships are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention.

[0021] In addition, unless otherwise specified, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0022] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0023] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0024] Example: See also Figures 1 to 6The fast-response attitude control device in the preferred embodiment of the present invention includes a cabin 9, a plurality of attitude control components arranged on the inner wall of the cabin 9, the plurality of attitude control components are arranged at different positions on the inner wall of the cabin 9, and the plurality of attitude control components can release thrust respectively to drive the cabin to adjust the attitude; specifically, the attitude control component includes a nozzle part 8, the nozzle part 8 includes a nozzle port and a propellant installation port, wherein the nozzle port is used to spray out the combustion gas to change the orientation of the attitude control device; a propellant installation shell 5 is provided at the propellant installation port, the internal space of the propellant installation shell 5 is connected to the nozzle port, and the propellant installation port is used to assemble the propellant, and the combustion gas is generated and sprayed out from the nozzle port. Specifically, the propellant installation shell 5 is provided with an ignition cartridge 2 and a combined charge component 6 arranged around the ignition cartridge 2, the ignition cartridge 2 is an ignition structure, and the combined charge component 6 is a propellant, and the combined charge component 6 can be ignited by the ignition cartridge 2, and burns in the propellant installation shell 5 to generate combustion gas. The combined charge component 6 includes a first charge component 621 and a second charge component 622 which are coaxially sleeved. The first charge component 621 and the second charge component 622 are both provided with through holes along the axial direction, and the second charge component 622 is sleeved in the first charge component 621, and a gap is left between the outer wall of the second charge component 622 and the inner wall of the first charge component 621, so that the inner and outer walls of the first charge component 621 and the inner and outer walls of the second charge component 622 can all contact with the internal space of the propellant mounting shell 5, so that the gas ejected from the ignition cartridge 2 can synchronously ignite the inner and outer sides of the first charge component 621 and the inner and outer sides of the second charge component 622.

[0025] Specifically, the fast-response attitude control device in the present application adopts mature standard propellants, and by changing the structural form of the propellants, the combined charge component 6 is set in the form of a first charge component 621 and a second charge component 622, a through hole is reserved in the first charge component 621 and the second charge component 622, and a gap is reserved between the first charge component 621 and the second charge component 622, so that when the igniter 1 is ignited, the generated gas can contact the inside and outside of the first charge component 621 and the second charge component 622 at the same time, greatly reducing the response time of the attitude control device; then, the start and stop of the attitude control components at different positions in the cabin 9 are controlled respectively to achieve the rapid adjustment of the attitude of the cabin 9. At the same time, by changing the structure of the combined charge component 6, the present application reduces the response time without using high-burning-rate propellants, thereby avoiding the problem of poor safety caused by using high-burning-rate propellants. The fast-response attitude control device in the present application has the characteristics of short response time, large output effect, low cost, high degree of integration, miniaturization and light weight.

[0026] Further, as a preferred embodiment of the present invention, for the fast-response attitude control device in the present application, the multiple attitude control components in the present application are uniformly distributed in the circumferential direction inside the cabin section 9, and a sealing gasket 11 is provided between the multiple attitude control components and the inner wall of the cabin section 9, and the multiple attitude control components are fixed to the inner wall of the cabin section 9 by fasteners 10. The fast-response attitude control device in the present application realizes attitude adjustment by arranging multiple attitude control components on the circumferential side wall of the tail of the cabin section 9, arranging the fast-response attitude control components in different orientations, and controlling the activation of the fast-response attitude control components according to demand. In addition, the fast-response attitude control components in the present application are independent integrated structures, and any combination of the fast-response attitude control components and the cabin section 9 can be realized by the sealing gasket 11 and the fastener 10. Compared with the attitude adjustment device prepared inside the traditional aircraft, the overall preparation difficulty is lower, and the replacement and maintenance are convenient and quick.

[0027] Furthermore, a mounting hole is provided on the side wall of the cabin section 9, and the nozzle of the attitude control component is attached to the mounting hole, so that the gas generated by the attitude control component is ejected from the side wall of the cabin section 9. The attitude adjustment is achieved by controlling the injection of gas at different positions of the side wall of the cabin section 9.

[0028] Further preferably, the sealing gasket 11 between the inner wall of the cabin section 9 and the attitude control component in the present application is silicone rubber, and its compression amount is 8% to 18%. Since the cabin section 9 and the attitude control component in the present application are not integrated structures, there is a matching gap between the cabin section 9 and the attitude control component, so silicone rubber is arranged between the two. The silicone rubber itself has a certain amount of compression, so that the attitude control component is closely attached to the inner wall of the cabin section 9 when the gas is ejected to generate huge thrust, avoiding the problem of gas leakage from the attitude control component to the cabin section 9.

[0029] Further, as a preferred embodiment of the present invention, the first charge assembly 621 and the second charge assembly 622 in the present application have the same axial length, and the sleeve arrangement of the two makes the two end surfaces of the first charge assembly 621 and the second charge assembly 622 flush, and the first charge rack 61 and the second charge rack 63 are respectively provided at both ends of the first charge assembly 621 and the second charge assembly 622, and the first charge rack 61 and the second charge rack 63 fix the second charge assembly 622 in the first charge assembly 621, and fix the first charge assembly 621 in the propellant installation shell 5. Specifically, in order to ensure that sufficient space is reserved between the first charge assembly 621 and the second charge assembly 622 and the propellant installation shell 5, it is avoided that the first charge assembly 621 and the second charge assembly 622 shake, etc., which causes the gap to be reduced, resulting in an increase in the subsequent combustion time. The present application sets a first charge rack 61 and a second charge rack 63, and utilizes the two powder racks to maintain the stability of the first charge assembly 621, the second charge assembly 622 and the propellant mounting shell 5, so that space is reserved inside and outside the first charge assembly 621 and the second charge assembly 622 to fully contact with the fuel gas, thereby improving the response time of the attitude control device.

[0030] Further preferably, the second charge rack 63 includes a first limiting portion 631 and a plurality of second limiting portions arranged circumferentially along the first limiting portion 631. The first limiting portion 631 is arranged in an annular shape, and the outer circumference of the first limiting portion 631 abuts against the inner wall surface of the second charge assembly 622; the plurality of second limiting portions are arranged radially extending along the first limiting portion 631, and the plurality of second limiting portions are provided with a first limiting protrusion 632 and a second limiting protrusion 633 on one side of the first charge assembly 621, the first limiting protrusion 632 and the second limiting protrusion 633 are arranged at intervals, and the two sides of the first limiting protrusion 632 abut against the outer wall of the second charge assembly 622 and the inner wall of the first charge assembly 621, and the two sides of the second limiting protrusion 633 abut against the outer wall of the first charge assembly 621 and the inner wall of the propellant installation shell 5, respectively.

[0031] As a specific embodiment of the present invention, the first limiting portion 631 in the second charge rack 63 in the present application is arranged in an annular shape, and the first limiting portion 631 can be clamped at the inner wall surface of the second charge assembly 622 to relatively fix the second charge assembly 622 and the second charge rack 63, and the annular space of the first limiting portion 631 facilitates the gas generated in the propellant installation shell 5 to enter the inner cavity of the second charge assembly 622. The second limiting portion radially extending along the first limiting portion 631 can relatively fix the second charge assembly 622 and the first charge assembly 621. The first limiting protrusion 632 on the second limiting portion and the first limiting portion 631 limit and fix the inner and outer sides of the second charge assembly 622; the outer side of the first limiting protrusion 632 on the second limiting portion and the inner side of the second limiting protrusion 633 limit and fix the inner and outer sides of the first charge assembly 621; the outer side of the second limiting protrusion 633 of the second limiting portion abuts against the inner wall of the propellant installation shell 5, thereby achieving relative fixation of the first charge assembly 621, the second charge assembly 622 and the propellant installation shell 5, and ensuring rapid combustion of the first charge assembly 621 and the second charge assembly 622.

[0032] Further preferably, the side of the second charge rack 63 in the present application facing the first charge assembly 621 and the second charge assembly 622 is in a convex state, and the annular space of the first limiting portion 631 protrudes from the plane where the second charge rack 63 is located, so that the first limiting portion 631, the first limiting protrusion 632, the second limiting protrusion 633, etc. are embedded in the gap between the first charge assembly 621 and the second charge assembly 622. At the same time, the side of the second charge rack 63 away from the first charge assembly 621 and the second charge assembly 622 is a plane structure, and a 90° channel inner wall is formed at the junction of the nozzle part 8 and the propellant installation shell 5. The side of the second charge rack 63 away from the first charge assembly 621 and the second charge assembly 622 abuts against the inner wall of the nozzle part 8, so as to fix the first charge assembly 621 and the second charge assembly 622.

[0033] Further preferably, the first charge rack 61 in the present application is arranged on the side of the first charge assembly 621 and the second charge assembly 622 away from the second charge rack 63. In addition, an ignition cartridge 2 is arranged on one side of the first charge rack 61, so the structure of the first charge rack 61 needs to be adjusted accordingly, and one side of the first charge rack 61 abuts against the side wall of the propellant installation housing 5, and the other side thereof abuts against the side wall of the ignition cartridge 2.

[0034] Further preferably, in the present application, a rubber adjustment pad is attached to the side of the first charge rack 61 and the second charge rack 63 away from the first charge assembly 621 and the second charge assembly 622. The rubber adjustment pad is an aviation sponge rubber adjustment pad, which is mainly used to adjust the relative position of the first charge rack 61 and the second charge rack 63 to fix the first charge assembly 621 and the second charge assembly 622 in the propellant installation shell 5.

[0035] Preferably, the first charge assembly 621 and the second charge assembly 622 are bonded to the first charge rack 61 and the second charge rack 63 by epoxy adhesive.

[0036] Further, as a preferred embodiment of the present invention, the ignition cartridge 2 in the present application includes a cartridge body 21 arranged in a cylindrical shape, one end of the cartridge body 21 is provided with a charge hole, and the other end thereof is provided with a gas ejection hole; the cartridge body 21 is provided with an igniter 1, a cartridge diaphragm 22 and an ignition tablet 23 in sequence along the axial direction, wherein there are a plurality of ignition tablets 23, and a cartridge diaphragm 22 is provided between each ignition tablet 23. The ignition cartridge 2 in the present application receives an ignition signal through the igniter 1 to generate a fire source, and ignites the ignition tablet 23 after penetrating the cartridge diaphragm 22, and the gas generated by the ignition tablet 23 is ejected from the gas ejection hole, and then the gas enters the space of the propellant installation shell 5 to ignite the combined charge component 6.

[0037] Preferably, the ignition tablets 23 in the present application are standard tablets, and their structural dimensions are relatively fixed, so that a set number of ignition tablets 23 can be filled according to the size of the medicine box body 21, and the ignition tablets 23 are separated from each other by a medicine box diaphragm 22, and the gap between the ignition tablets 23 and the medicine box body 21 can be filled with absorbent cotton to ensure stable ignition of the ignition box 2.

[0038] Further preferably, the igniter 1 uses a double bridge circuit and a double ignition cable. The double bridge circuit and the double ignition cable are redundantly designed so that when one ignition cable of the igniter 1 fails, ignition can be performed through the other ignition cable.

[0039] Further preferably, in the present application, a first sealing ring 3 is provided at the end surface where the igniter 1 and the medicine box body 21 meet, a second sealing ring 4 is provided between the medicine box body 21 and the propellant installation shell 5, a third sealing ring 7 is provided between the propellant installation shell 5 and the nozzle part 8, and the nozzle part 8 is provided with a plugging cover 85 at the nozzle mouth. The igniter 1 and the medicine box body 21 are threadedly connected and sealed with the first sealing ring 3; the medicine box body 21 and the propellant installation shell 5 are threadedly connected and sealed with the second sealing ring 4; the propellant installation shell 5 and the nozzle part 8 are threadedly connected and sealed with the third sealing ring 7. The first sealing ring 3, the second sealing ring 4 and the third sealing ring 7 are all O-rings.

[0040] Further preferably, the inner wall of the propellant installation shell 5 is provided with a shell insulation layer 52, and the inner wall of the nozzle part 8 is provided with a nozzle insulation layer 82. The propellant installation shell 5 and the nozzle part 8 in the present application are both made of lightweight aluminum alloy material, the propellant installation shell 5 includes a propellant outer shell 51, and the shell insulation layer 52 is molded inside the propellant outer shell 51; the nozzle part 8 includes a nozzle body 81, and the nozzle insulation layer 82 is molded inside the nozzle body 81, ensuring that the fast-response attitude control device is lightweight and has high heat resistance.

[0041] Further preferably, the first charge assembly 621 and the second charge assembly 622 in the present application are both medium burning rate propellants, and the burning time of the first charge assembly 621 and the second charge assembly 622 is 0.05~0.15s. The present application designs the structure of the first charge assembly 621 and the second charge assembly 622, and uses the first charge rack 61 and the second charge rack 63 to control the relative positions of the two charge assemblies, thereby increasing the contact area between the two and the gas, so that the fast-response attitude control device in the present application can achieve complete combustion within 0.05~0.15s under the premise of using medium burning rate propellants, and has a shorter response time while having higher safety.

[0042] Furthermore, as a preferred embodiment of the present invention, the nozzle mouth in the present application is sealed by a plugging cover 85, and the conduction pressure at the plugging cover 85 is 3~5MPa. The material of the plugging cover 85 is preferably lightweight foam, and the lightweight foam can partially enter the throat liner 83 area to ensure that the interior of the fast-response attitude control device is dry. The control of the pressure of the plugging cover 85 allows the gas generated by the ignition cartridge 2 to fully fill the space where the propellant installation shell 5 is located, and will not cause too much obstruction to the gas generated by the combustion of the combined charge component 6, and the combustion time of the combined charge component 6 is controlled within 0.05~0.15s.

[0043] Preferably, the throat liner 83 of the nozzle portion 8 in the present application is made of T705 high-strength graphite, and the throat liner 83 and the backing liner 84 are bonded and sealed by DG-3S room temperature or low temperature curing high temperature resistant epoxy adhesive.

[0044] Preferably, the backing 84 of the nozzle portion 8 in the present application is made of a high-silicon molded material, and the backing 84 is connected to the nozzle body 81 via a pin 86 .

[0045] Further preferably, the fast-response attitude control device in the present application is provided with a protective cover plate 12 at the mounting hole, the protective cover plate 12 seals the mounting hole, and the conduction pressure at the protective cover plate 12 is 0.5-1 MPa. The protective cover plate 12 is used for thermal protection of the attitude control device during flight to avoid the influence on the fast-response attitude control device during flight. At the same time, when the fast-response attitude control device is started, the gas can quickly break through the protective cover plate 12 to ensure that the gas is normally ejected from the mounting hole.

[0046] It will be easily understood by those skilled in the art that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A fast-response attitude control device, characterized in that: It comprises a cabin section, and a plurality of attitude control components arranged on the inner wall of the cabin section, wherein the plurality of attitude control components are respectively arranged at different positions of the inner wall of the cabin section, and the plurality of attitude control components can respectively release thrust to drive the cabin section to adjust its attitude; The attitude control component comprises: A nozzle portion, the nozzle portion comprising a nozzle port and a propellant installation port; A propellant installation shell is provided at the propellant installation port, the propellant installation shell is communicated with the nozzle port, and an ignition cartridge and a combined charge component are provided in the propellant installation shell; The combined charge component includes a first charge assembly and a second charge assembly which are coaxially sleeved, wherein the first charge assembly and the second charge assembly both have through holes axially therethrough, and a gap is left between the outer wall of the first charge assembly and the inner wall of the second charge assembly, so that the gas sprayed from the ignition cartridge can synchronously ignite the inner and outer sides of the first charge assembly and the inner and outer sides of the second charge assembly.

2. The fast-response attitude control device according to claim 1, characterized in that: The plurality of attitude control components are uniformly distributed in the circumferential side wall of the cabin section along the circumferential direction, a sealing gasket is provided between the plurality of attitude control components and the inner wall of the cabin section, and the attitude control components are fixed to the inner wall of the cabin section by fasteners; The side wall of the cabin section is provided with a mounting hole, and the nozzle mouth of the attitude control component is attached to the mounting hole.

3. The fast-response attitude control device according to claim 2, characterized in that: The nozzle mouth is sealed by a plugging cover, and the plugging cover has a conduction pressure of 3~5Mpa; a protective cover plate is provided at the mounting hole, and the protective cover plate closes the mounting hole, and the conduction pressure at the protective cover plate is 0.5~1Mpa.

4. The fast-response attitude control device according to claim 1, characterized in that: The first charge assembly and the second charge assembly are both medium burning rate propellants, and the burning time of the first charge assembly and the second charge assembly is 0.05-0.15s.

5. The fast-response attitude control device according to claim 1, characterized in that: The first charge assembly and the second charge assembly have the same axial length, and the first charge rack and the second charge rack are respectively provided at both ends of the first charge assembly and the second charge assembly, and the first charge rack, the second charge rack, the first charge barrel and the second charge barrel are relatively fixedly arranged.

6. The fast-response attitude control device according to claim 5, characterized in that: The second charge rack comprises a first limiting portion and a plurality of second limiting portions arranged along the circumference of the first limiting portion; The first limiting portion is arranged in an annular shape, and the outer periphery of the first limiting portion abuts against the inner wall surface of the second charge assembly; A plurality of second limiting portions are radially extended along the first limiting portion, and a first limiting protrusion and a second limiting protrusion are provided on one side of the second limiting portions facing the first charge assembly, and the first limiting protrusion and the second limiting protrusion are arranged at an interval; two sides of the first limiting protrusion respectively abut against the outer wall of the second charge assembly and the inner wall of the first charge assembly; two sides of the second limiting protrusion respectively abut against the outer wall of the first charge assembly and the inner wall of the propellant installation shell.

7. The fast-response attitude control device according to claim 1, characterized in that: The ignition cartridge comprises a cartridge body arranged in a cylindrical shape, one end of the cartridge body is provided with a charge hole, and the other end thereof is provided with a gas ejection hole; An igniter, a medicine box membrane and an ignition tablet are sequentially arranged in the medicine box body along the axial direction; there are a plurality of ignition tablets, and a medicine box membrane is arranged between each of the ignition tablets.

8. The fast-response attitude control device according to claim 7, characterized in that: The igniter adopts a double-bridge circuit and a double-circuit ignition cable.

9. The fast-response attitude control device according to claim 7, characterized in that: A first sealing ring is provided on the end surface where the igniter and the medicine box body meet; a second sealing ring is provided between the medicine box body and the propellant installation shell, a third sealing ring is provided between the propellant installation shell and the nozzle part, and the nozzle part is provided with a plugging cover at the nozzle mouth.

10. The fast-response attitude control device according to claim 1, characterized in that: The inner peripheral wall surface of the propellant installation shell is provided with a shell insulation layer, and the inner peripheral wall surface of the nozzle part is provided with a nozzle insulation layer.

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