A multi-stage actuating assembly and a multi-stage rocket ejection port extension mechanism

Abstract

This application discloses a multi-stage actuation assembly and a multi-stage rocket nozzle extension mechanism, comprising: N connecting members, N-1 elastic members, and a trigger member; two adjacent connecting members and elastic members form an actuation unit, which is expandable and retractable, and has a guide structure, a compression limiting structure, and an expansion limiting structure formed therein. The guide structure guides any connecting member to move along a first direction; the elastic members have a first state and a second state, in which they are relatively relaxed; the compression limiting structure limits the actuation unit to the retracted state, the expansion limiting structure limits the actuation unit to the expanded state, and the expansion of the elastic members switches the actuation unit from the retracted state to the expanded state; when the trigger member is in the non-triggered state, it connects the connecting members at both ends, and all elastic members are in the first state; when it is in the triggered state, each elastic member switches from the first state to the second state. This actuation assembly and extension mechanism has a simple structure and can be reused.

Description

Technical Field

[0001] This application generally relates to the field of spacecraft technology, and in particular to a multi-stage actuation component and a multi-stage rocket nozzle extension mechanism. Background Technology

[0002] To increase thrust during rocket flight, an extension tube is typically installed at the rocket's exhaust nozzle. This extension tube remains in a retracted state before launch and for a short period after liftoff. When the rocket reaches the predetermined altitude or operational condition, an actuation device between the rocket body and the extension tube is triggered via remote control or internal rocket control. This extends the extension tube relative to the rocket body to its deployed state, thereby increasing the thrust of the combustion gases through the extension tube. Existing actuation devices generally employ servo motor actuators or hydraulic actuators. However, due to their inherent structural complexity, these devices are generally unsuitable for rockets with multi-stage extension tubes. Furthermore, the relatively simple combustion gas actuators suffer from high-temperature damage to their internal functional units after each use, rendering them unusable.

[0003] The Chinese patent document (CN104142099A) discloses a specific structure of a gas actuator to address the problem that the gas actuator cannot provide small thrust under certain operating conditions. However, the structural features still do not solve the problem of its non-reusability, and do not provide corresponding features that facilitate the use of rockets with multi-stage extension tube structures. Summary of the Invention

[0004] In view of the above-mentioned defects or deficiencies in the prior art, it is desirable to provide a multi-stage actuation component and a multi-stage rocket nozzle extension mechanism that are simple in structure and reusable.

[0005] The specific technical solution is as follows:

[0006] First aspect

[0007] This application provides a multi-level actuation component, comprising: N connectors, N-1 elastic elements, and at least one trigger element, wherein N≥3;

[0008] Any two adjacent connectors and the elastic element between them form an actuation unit. The actuation unit has a first extended state and a first contracted state, and has a guide structure, a compression limiting structure, and an extension limiting structure formed therein. The guide structure is used to guide any of the connectors to move relative to the other connector along a first direction, where the first direction is the extension and contraction direction of the elastic element. The elastic element has a first state and a second state, and in the second state, the elastic element is partially expanded relative to the first state. The compression limiting structure is used to confine the actuation unit to the first contracted state, and the extension limiting structure is used to confine the actuation unit to the first extended state. The expansion of the elastic element is used to switch the actuation unit from the first contracted state to the first extended state.

[0009] The trigger has a trigger state and a non-trigger state. When it is in the non-trigger state, it is used to connect the connectors at both ends, and each of the elastic elements is in the first state. When it is in the trigger state, it is used to disconnect the connectors at both ends, and each of the elastic elements switches from the first state to the second state.

[0010] As a further limitation of this application, the connector is provided with an exhaust hole, which is used to communicate the compression limiting structure in the actuation unit formed by the connector with the outside.

[0011] As a further limitation of this application, the triggering element is an explosive bolt.

[0012] Second aspect

[0013] This application provides a multi-stage rocket nozzle extension mechanism, including the multi-stage actuation assembly described above, and further including: a rocket body and N-1 extension tubes sleeved on the rocket body in successive layers, wherein each of the connecting members in the multi-stage actuation assembly is sequentially hinged to the rocket body and each of the extension tubes.

[0014] As a further limitation of this application, it also includes a limiting mechanism, which includes N-2 folding limiting pieces, the folding limiting pieces being disposed between the outer walls of two adjacent extension tubes, the angle between the retractable direction of the folding limiting pieces and the axis of the rocket body being equal to the angle between the retractable direction of the actuation unit and the axis of the rocket body.

[0015] As a further limitation of this application, the length of the folding limiting piece when it is opened is a first preset length, the first preset length is less than or equal to a second preset length, and the second preset length is the distance between the two hinge points of the actuation unit corresponding to the folding limiting piece when it is in the first unfolded state.

[0016] As a further limitation of this application, the limiting mechanism also includes a limiting claw, which is disposed on the outer wall of the innermost extension tube. When the actuation unit hinged to the rocket body is in the first deployed state, the limiting claw abuts against the limiting protrusion on the outer wall of the rocket body.

[0017] The beneficial effects of this application are:

[0018] In this application, N connectors and N-1 elastic elements cooperate to form N-1 actuating units. Within each actuating unit, a guide structure, a compression limiting structure, and an expansion limiting structure are formed between two connectors to allow the actuating assembly to extend and retract along the first direction. During this process, when in the first contracted state, the elastic elements between the connectors are compressed to a first state. At this time, the connectors at both ends of the actuating assembly are connected by untriggered triggers, allowing the actuating units within it to maintain the aforementioned state. When the triggers are triggered, the connectors at both ends of the actuating assembly are disconnected, and the elastic elements in each actuating unit are temporarily released from compression and enter a relaxation process. During this process, the connectors are ejected by the elastic elements until the expansion limiting structure confines the two connectors to the first expanded state. At this time, the elastic elements are in the second state, and the actuating assembly completes its expansion action. In this process, the actuation component involved in this solution uses the elastic element as its power source, which is fundamentally different from the existing gas-fired actuation cylinders that use the combustion and expansion of internal combustible gas as their power source. Therefore, its internal functional structure is not damaged before and after the state switch, and it can be reused. Moreover, compared with other complex actuation devices, the actuation component involved in this application has multi-level adaptability, thus offering significant convenience when configured in rockets with multi-stage extension tubes. Attached Figure Description

[0019] Other features, objects, and advantages of this application will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0020] Figure 1 This is a cross-sectional view of the internal structure of a multi-level actuation component provided in an embodiment of this application;

[0021] Figure 2 for Figure 1 A schematic diagram of each actuating unit in the actuating assembly when it is in the first contracted state;

[0022] Figure 3 for Figure 1 A schematic diagram of each actuating unit in the actuating assembly when it is in the first deployed state;

[0023] Figure 4 A schematic diagram of the multi-stage rocket nozzle extension mechanism provided in this embodiment when it is in the third retracted state;

[0024] Figure 5 A schematic diagram of the multi-stage rocket nozzle extension mechanism provided in this embodiment in its third deployed state;

[0025] Figure 6 for Figure 4 Schematic diagram of the middle limit mechanism;

[0026] Figure 7 for Figure 4 A schematic diagram showing the engagement between the middle limiting claw and the rocket body after the extension mechanism is deployed.

[0027] The following are the labels in the diagram: 11, connector; 12, elastic element; 13, trigger element; 110, vent; 21, rocket body; 22, extension tube; 31, folding limit piece; 32, limit claw. Detailed Implementation

[0028] The present application will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, only the parts relevant to the invention are shown in the accompanying drawings.

[0029] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0030] Example 1

[0031] Please refer to Figure 1 This is a cross-sectional view of the internal structure of a multi-stage actuation assembly provided in this embodiment. The actuation assembly includes three connecting members 11, two elastic members 12, and one trigger member 13, forming two adjacent actuation units. The number of stages of the actuation units in this assembly is the simplest form that satisfies all the features of this solution. The connecting members are all in the form of sleeves. For ease of explanation, they are now described as... Figure 1 The three sleeves in the actuation assembly provided are arranged from the outside to the inside as follows: outer sleeve 111, middle sleeve 112, and inner sleeve 113. The first elastic element 121 is located between the outer sleeve 111 and the middle sleeve 112. Figure 1 The second elastic element 122 is located between the middle cylinder 112 and the inner cylinder 113, and is positioned in the innermost elastic layer. Figure 1 It is located in the outermost elastic element.

[0032] Figure 2 This is a schematic diagram of each actuating unit in the actuation assembly when it is in the first contraction state. Figure 3 This is a schematic diagram of each actuating unit in the actuating assembly when it is in the first unfolded state. Each sleeve is nested layer by layer, thereby forming the guide structure in its extension direction (i.e., the first direction).

[0033] In this embodiment, the first end of the outer cylinder 111 ( Figure 1 The inner cylinder 112 has an inwardly extending first protrusion on its inner side (left end) and a second protrusion on its inner side (second end); the inner cylinder 112 has an inwardly extending third protrusion on its inner side (first end) and an outwardly extending fourth protrusion in its middle portion, the fourth protrusion extending to the second end of the inner cylinder 112, the second end of which has an outwardly extending fifth protrusion; the inner cylinder 113 has a two-layer structure, the outer layer being fitted between the outer cylinder 111 and the inner cylinder 112, and the inner layer passing through the outer cylinder 111 and the inner cylinder 112 and connected to the trigger 13 in an untriggered state, the second end of the inner layer of the inner cylinder 113 having a sixth protrusion; the portion connecting the inner and outer layers of the inner cylinder 113 and the fourth protrusion forms the outer actuation unit for compressing the second elastic member 122. A compression limiting structure is provided, wherein the third protrusion and the second protrusion form a compression limiting structure for compressing the inner layer actuating unit of the first elastic member 121; the first protrusion and the fifth protrusion cooperate to form the unfolding limiting structure of the outer layer actuating unit; and the third protrusion and the sixth protrusion cooperate to form the unfolding limiting structure of the inner layer actuating unit. When both actuating units are in the first contracted state, the trigger member 13 connects the second end of the inner layer portion of the inner cylinder 113 to the second end of the outer cylinder 111, and the portion connecting the inner and outer layers of the inner cylinder 113 abuts against the second end of the middle cylinder 112. This can hold the first elastic member 121 and the second elastic member 122 in the first state respectively. The state of the actuating assembly at this time is recorded as the second contracted state. Figure 2 As shown in the diagram. When the trigger 13 is triggered, the second end of the inner layer of the inner cylinder 113 is disconnected from the second end of the outer cylinder 111, and the compressed first elastic element 121 and second elastic element 122 relax. During this process, the middle cylinder 112 is ejected to the left relative to the outer cylinder 111, and the inner cylinder 113 is also ejected to the left relative to the middle cylinder 112. The state of the actuating component at this time is recorded as the second unfolded state, as shown in the diagram. Figure 3As shown in the diagram. In other embodiments of this application, the connector 11, the elastic member 12, and the actuating unit formed therefrom can also be implemented in other forms that conform to the features of this application, wherein the guide structure, the compression limiting structure, and the unfolding limiting structure can also have other implementations known in the art. In addition, the number of connectors 11 can also be increased according to actual needs.

[0034] In summary, the present application uses the elastic element 12 as the power source for the actuation component, which is fundamentally different from the prior art that uses a gas-fired actuator cylinder to power the expansion of the internal combustible gas during combustion. Therefore, its internal functional structure is not damaged before and after the state switch, and it can be reused. Moreover, compared with other complex actuation devices, the present application has significant advantages when configured in rockets with multi-stage extension tubes.

[0035] In a preferred embodiment that improves the smoothness of the actuation component, the connector 11 is provided with an exhaust port 110, which is used to connect the compression limiting structure in the corresponding actuation unit to the outside.

[0036] like Figure 2 or Figure 3 As shown, several vent holes 110 are provided near the first end on both the middle cylinder 112 and the inner cylinder 113. Since the compression limiting structures formed between the outer cylinder 111 and the middle cylinder 112, and between the middle cylinder 112 and the inner cylinder 113 in this embodiment are relatively sealed spaces, and the second elastic element 122 and the first elastic element 121 are respectively provided within these spaces, when the actuating component switches from the second contracted state to the second extended state, that is, when the second elastic element 122 and the first elastic element 121 switch from the first state to the second state, the vent holes 110 always allow the compression limiting structure to communicate with the outside, thus preventing the internal air pressure from being too low and affecting the operation of the actuating component. Therefore, the smoothness of the actuating component's operation is improved, making its deployment easier.

[0037] It is conceivable that the distribution of the exhaust ports 110 will vary depending on the specific implementation of the actuating component. Therefore, the implementation of the exhaust ports 110 may also include other forms known in the art.

[0038] In a preferred embodiment of the trigger 13, the trigger 13 is an explosive bolt.

[0039] When setting the trigger 13 in this embodiment, it is necessary to select a module or device with the characteristics of simple structure, small size, light weight and easy control. The explosion bolt has all the above-mentioned characteristics and is only used as a preferred embodiment of the trigger 13 in this embodiment.

[0040] Example 2

[0041] This embodiment provides a multi-stage rocket nozzle extension mechanism, including the multi-stage actuation assembly described above, and further including: a rocket body 21 and N-1 extension tubes 22 sleeved on the rocket body 21 in successive layers, wherein each of the connecting members 11 in the multi-stage actuation assembly is sequentially hinged to the rocket body 21 and each of the extension tubes 22.

[0042] Please refer to Figure 4 and Figure 5 The figures are schematic diagrams of the multi-stage rocket nozzle extension mechanism using multi-stage actuation components provided in this embodiment when it is in the third retracted state and the third extended state, respectively. For ease of explanation, the figures also use the extension mechanism composed of the simplest two-stage extension tubes. Figure 4 and Figure 5 The states of the extension mechanism correspond to the states when the actuation component is in the second retracted state and the third deployed state, respectively. It should be noted that several sets of the actuation component are provided and are evenly distributed around the axis of the rocket body 21. Since each of the connecting members 11 on the actuation component is sequentially hinged to the rocket body 21 and each of the extension tubes 22, when the actuation component switches from the second retracted state to the third deployed state, it can drive the two extension tubes 22 to deploy along the axis of the rocket body 21, thereby enhancing the propulsive effect of the exhaust gas from the rocket nozzle on rocket flight.

[0043] In a preferred embodiment for improving the smoothness of the state switching process of the extension mechanism, a limiting mechanism is further included. The limiting mechanism includes N-2 folding limiting pieces 31, which are disposed between the outer walls of two adjacent extension tubes. The angle between the retractable direction of the folding limiting piece 31 and the axis of the rocket body 21 is equal to the angle between the retractable direction of the actuation unit and the axis of the rocket body 21.

[0044] Please refer to Figure 6This is a schematic diagram of the limiting mechanism provided in this embodiment. In a preferred embodiment, the folding limiting piece 31 is positioned between the two actuating components along the axis of the rocket body 21. The edges at both ends of the folding limiting piece 31 are connected to the outer walls of the two adjacent extension tubes via hinged lines. This prevents deflection of the extension mechanism due to inconsistent operating speeds of the two actuating components, and torsion of the extension tube 22 due to airflow disturbances during operation. In summary, the folding limiting piece 31 plays a crucial role in improving the smoothness of the extension mechanism's state switching process.

[0045] In a preferred embodiment where the extension mechanism is kept in the unfolded state, the length of the folding limiting piece 31 when it is open is a first set length, the first set length is less than or equal to a second set length, and the second set length is the distance between the two hinge points of the actuation unit corresponding to the folding limiting piece 31 when it is in the first unfolded state.

[0046] During the unfolding of the extension mechanism, the actuating component plays an important pushing role until the folding limiting piece 31 is unfolded to the longest first set length. At this time, the folding limiting piece 31 is straightened. The actuating component has been fully unfolded to the second set length, or has not yet been unfolded to that length. When the extension mechanism is affected by airflow and has a tendency to contract, the front and rear parts of the folding limiting piece 31 abut against each other, thereby offsetting the above-mentioned contraction tendency and keeping the extension tube 22 in the unfolded state.

[0047] In a preferred embodiment where the extension mechanism is further kept in the deployed state, the limiting mechanism further includes a limiting claw 32, which is disposed on the outer wall of the innermost extension tube 22. When the actuation unit hinged to the rocket body 21 is in the first deployed state, the limiting claw 32 abuts against the limiting protrusion on the outer wall of the rocket body 21.

[0048] like Figure 7The diagram shows the engagement of the limiting claw 32 with the rocket body 21 after the extension mechanism is deployed. The limiting claw 32 is located on the outer wall of the innermost extension tube 22. When the extension mechanism is in the third retracted state, the free end of the limiting claw 32 is below the limiting protrusion. The angle between the limiting claw 32 and the axis of the rocket body 21 is greater than the angle between the outer wall of the rocket body 21 and the axis of the rocket body 21. The limiting claw 32 is elastic. When the extension mechanism is switched from the third retracted state to the third deployed state, the side of the limiting claw 32 near the rocket body 21 brushes against the end of the limiting protrusion and abuts against it after the end of the limiting claw 32 passes over the limiting protrusion. Subsequently, when the extension mechanism is affected by airflow and a contraction tendency occurs between the rocket body 21 and the extension tube 22 that is close to it, the end of the limiting claw 32 abuts against the limiting protrusion to effectively counteract the above-mentioned tendency, thereby keeping the extension mechanism in the extended state.

[0049] The above description is merely a preferred embodiment of this application and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of the invention involved in this application is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the inventive concept. For example, technical solutions formed by substituting the above features with (but not limited to) technical features with similar functions disclosed in this application.

Claims

1. A multi-stage rocket nozzle extension mechanism, characterized in that, include: A multi-level actuation assembly, comprising N connectors (11), N-1 elastic elements (12), and at least one trigger element (13), wherein N≥3; Any two adjacent connectors (11) and the elastic member (12) between them form an actuation unit. The actuation unit has a first extended state and a first contracted state. It has a guide structure, a compression limiting structure and an extension limiting structure. The guide structure is used to guide any connector (11) to move relative to the other connector (11) in a first direction. The first direction is the extension and retraction direction of the elastic member (12). The elastic member (12) has a first state and a second state. The elastic member (12) is relaxed relative to the first state in the second state. The compression limiting structure is used to limit the actuation unit to the first contracted state. The extension limiting structure is used to limit the actuation unit to the first extended state. The elastic member (12) relaxes to switch the actuation unit from the first contracted state to the first extended state. The trigger (13) has a trigger state and a non-trigger state. When it is in the non-trigger state, it is used to connect the connectors (11) at both ends, and each of the elastic elements (12) is in the first state. When it is in the trigger state, it is used to release the connection between the connectors (11) at both ends, and each of the elastic elements (12) switches from the first state to the second state. The rocket body (21) and N-1 extension tubes (22) sleeved on the rocket body (21) in succession, and each of the connecting members (11) in the multi-stage actuation assembly is sequentially hinged to the rocket body (21) and each of the extension tubes (22); The limiting mechanism includes N-2 folding limiting pieces (31), which are disposed between the outer walls of two adjacent extension tubes. The angle between the retractable direction of the folding limiting piece (31) and the axis of the rocket body (21) is equal to the angle between the retractable direction of the actuating unit and the axis of the rocket body (21).

2. The multi-stage rocket nozzle extension mechanism according to claim 1, characterized in that, The connector (11) is provided with an exhaust port (110), which is used to connect the compression limiting structure in the corresponding actuation unit to the outside.

3. The multi-stage rocket nozzle extension mechanism according to claim 1, characterized in that, The trigger (13) is an explosive bolt.

4. The multi-stage rocket nozzle extension mechanism according to claim 1, characterized in that, The length of the folding limiting piece (31) when it is opened is a first set length. The first set length is less than or equal to a second set length. The second set length is the distance between the two hinge points of the actuation unit corresponding to the folding limiting piece (31) when it is in the first unfolded state.

5. The multi-stage rocket nozzle extension mechanism according to claim 1 or 4, characterized in that, The limiting mechanism also includes a limiting claw (32), which is located on the outer wall of the innermost extension tube (22). When the actuation unit hinged to the rocket body (21) is in the first unfolded state, the limiting claw (32) abuts against the limiting protrusion on the outer wall of the rocket body (21).

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