CN112284196A - Fairing separation system for carrier rocket and carrier rocket - Google Patents
Fairing separation system for carrier rocket and carrier rocket Download PDFInfo
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- CN112284196A CN112284196A CN202011555395.3A CN202011555395A CN112284196A CN 112284196 A CN112284196 A CN 112284196A CN 202011555395 A CN202011555395 A CN 202011555395A CN 112284196 A CN112284196 A CN 112284196A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
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Abstract
The application relates to the technical field of carriers, and provides a fairing separation system for a carrier rocket and the carrier rocket, wherein the fairing separation system comprises: the fairing comprises a fairing body and at least one set of separating devices; the fairing body comprises a first fairing split body and a second fairing split body; the separating device is arranged between the first fairing split body and the second fairing split body, and the piston cylinder and the push rod of the separating device can be separated, so that the acting distance of the first fairing split body and the second fairing split body in the separation process is increased, and the separation time is shortened; the piston cylinder and the push rod in the separating device are not directly connected and have certain guidance, so that clamping stagnation is not easy to occur, and the separating reliability is improved; the fairing body is horizontally moved and separated, and the separating device is not directly connected with the arrow body, so that the stable operation of the arrow body is facilitated; the separating device has simple structure and easy control, and the product is not damaged in the separating process, thereby being beneficial to recycling and reducing the manufacturing cost.
Description
Technical Field
The application relates to the technical field of carriers, in particular to a fairing separation system for a carrier rocket and the carrier rocket.
Background
With the continuous progress of science and technology, the exploration and utilization of space are gradually increased by human beings, and in the process of exploration and utilization, spacecrafts such as artificial satellites are indispensable detection tools. The carrier rocket is used as a main transport tool of the spacecraft, plays a vital role in the process of exploration and utilization of the space, and the fairing needs to be separated when the carrier rocket runs to a certain stage so as to expose the corresponding spacecraft.
At present, the separation scheme of the main carrier rocket fairing adopts a clam type split separation scheme, split separation can be divided into a flat throwing scheme and a rotary throwing scheme, and the split separation scheme can be divided into initiating explosive device separation power and spring separation power according to the source of separation force. The most common techniques at present are a spin throw solution where the separation force is provided by a spring and a flat throw solution where the separation force is provided by an initiating explosive device.
However, the spring is used as a rotary throwing scheme of separation power, the separation system has larger mass and long separation time, the action time on the rocket is long, and the carrying capacity of the rocket is influenced; and the cost is too high when the initiating explosive device is used as a source of separation power.
Disclosure of Invention
The fairing separation system for the carrier rocket and the carrier rocket are provided aiming at the defects in the prior art, and are used for solving the technical problems of long separation time and high cost of a separation device in the existing fairing separation scheme.
In a first aspect, embodiments of the present application provide a fairing separation system for a launch vehicle, comprising: the fairing comprises a fairing body and at least one set of separating devices; the fairing body comprises a first fairing split body and a second fairing split body which can be separated; the central axis of the fairing body is positioned in the plane of the parting surfaces of the first fairing section and the second fairing section; the separation device comprises a high-pressure gas cylinder, a piston and a push rod; the piston cylinder and the high-pressure gas cylinder are fixedly connected with the inner side wall of the first fairing split body, one end of the piston cylinder is provided with an opening, and the opening faces the inner side wall of the second fairing split body; one end of the piston cylinder, which is far away from the opening, is selectively communicated with the high-pressure gas cylinder; the piston is positioned in the piston cylinder and is in sliding fit with the piston cylinder, and one end of the push rod is abutted against the piston; the other end of the push rod extends to the outside of the piston cylinder from the opening and is fixedly connected with the inner side wall of the second fairing split body.
Optionally, the push rod comprises a push rod body, a push rod sleeve and a push rod spring located in the push rod sleeve; one end of the push rod body is abutted against the piston, and the other end of the push rod body extends to the outside of the piston cylinder from the opening and is in sliding connection with the push rod sleeve; one end of the push rod spring is connected with one end of the push rod body, which is far away from the piston cylinder, and the other end of the push rod spring is abutted against the closed end of the push rod sleeve; one end of the push rod sleeve, which is far away from the piston cylinder, is fixedly connected with the inner side wall of the second fairing split body.
Optionally, the piston cylinder, the push rod body and the push rod sleeve are all coaxially arranged; and the axes of the piston cylinder, the push rod body and the push rod sleeve are all vertical to the separating surface.
Optionally, one end of the piston cylinder, which is far away from the opening, is communicated with the high-pressure gas cylinder through a gas pipeline, and a gas valve switch is arranged on the gas pipeline.
Optionally, the outer cylinder wall of the piston cylinder is fixedly connected with the inner side wall of the first fairing split body through a first supporting piece; and/or the high-pressure gas cylinder is fixedly connected with the inner side wall of the first fairing split body through a second supporting piece.
Optionally, a push rod ball is arranged at one end of the push rod body, which is close to the piston, and the push rod ball and the piston are in spherical contact.
Optionally, the number of the separation devices is multiple; the projections of the piston cylinders of the separating devices in the plane of the separating surface are distributed linearly or in an array.
Optionally, the first fairing section and the second fairing section are both symmetrical about a plane of symmetry; wherein the symmetry plane is a plane perpendicular to the parting plane; the separation devices are even-number sets, the even-number sets of separation devices are divided into two groups, and the two groups of separation devices are symmetrically arranged around the symmetry plane.
Optionally, the number of separation devices is four.
In a second aspect, embodiments of the present application further provide a launch vehicle comprising the fairing separation system of the first aspect.
The beneficial technical effects brought by the technical scheme provided by the embodiment of the application at least comprise:
according to the fairing separation system provided by the embodiment of the application, the separation device capable of providing high-pressure pneumatic separation power is arranged between the first fairing split body and the second fairing split body, and the piston cylinder of the separation device is connected with the inner side wall of the first fairing split body, meanwhile, the push rod of the separation device is connected with the second fairing split body, and the piston cylinder and the push rod can be separated under the pushing of the pneumatic separation power, so that the acting distance of the first fairing split body and the second fairing split body in the separation process is increased, and the separation time of the fairing body is shortened; the piston cylinder and the push rod in the separating device are not directly connected and have certain guidance, so that clamping stagnation is not easy to occur during separation, and the separation reliability is improved; the fairing body is horizontally moved and separated, and the separating device is not directly connected with the arrow body, so that the stable operation of the arrow body is facilitated; the separating device has simple structure and easy control, and the product is not damaged in the separating process, thereby being beneficial to recycling and reducing the manufacturing cost.
Additional aspects and advantages of the present application will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the present application.
Drawings
The foregoing and/or additional aspects and advantages of the present application will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1 is a schematic view of an installation configuration of a cowl separation system according to an embodiment of the present disclosure;
FIG. 2 is a schematic illustration of a fairing body separation process of a fairing separation system according to an embodiment of the present disclosure;
FIG. 3 is a schematic view of a connection structure of a separation device of a fairing separation system according to an embodiment of the present disclosure;
fig. 4 is a distribution diagram of a projection of each piston cylinder in a fairing separation system provided by an embodiment of the present application in a plane of a separation plane.
In the figure:
100-a fairing body; 110-a first fairing split; 120-a second fairing split; 130-a separating surface;
200-arrow body;
300-payload;
400-a separation device;
410-a piston cylinder; 411-opening;
420-a piston;
430-high pressure gas cylinder;
440-a push rod; 441-the push rod body; 441 a-pushrod sphere; 442-a pusher spring; 443-a pushrod sleeve;
450-gas valve switch;
460-gas line;
500-plane of symmetry.
Detailed Description
Reference will now be made in detail to the present application, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar parts or parts having the same or similar functions throughout. In addition, if a detailed description of the known art is not necessary for illustrating the features of the present application, it is omitted. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present application and are not to be construed as limiting the present application.
It will be understood by those within the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. As used herein, the term "and/or" includes all or any element and all combinations of one or more of the associated listed items.
The following describes the technical solutions of the present application and how to solve the above technical problems with specific embodiments.
Referring to fig. 1 and 2, embodiments of the present application provide a fairing separation system for a launch vehicle, the fairing separation system for a launch vehicle comprising: a fairing body 100 and at least one set of separation devices 400. Wherein, radome fairing body 100 can be current radome fairing structure, and radome fairing body 100 includes separable first radome fairing segment 110 and second radome fairing segment 120, and first radome fairing segment 110 and second radome fairing segment 120 can synthesize a complete radome fairing body 100. A parting plane 130 is provided between the first fairing section 110 and the second fairing section 120, and the central axis of the fairing body 100 is located in the plane of this parting plane 130.
As shown in fig. 3, the separation device 400 is mainly used for providing separation power for the separation of the fairing body 100, the separation device 400 in the embodiment of the present application can provide high-pressure pneumatic separation power, and the separation device 400 specifically includes: a high pressure gas cylinder 430, a piston cylinder 410, a piston 420, and a push rod 440.
To achieve separation of the fairing body 100, the piston cylinder 410 and the high pressure gas cylinder 430 are both fixedly connected to the inner sidewall of the first fairing section 110, and are finally separated and fall off together with the first fairing section 110. An opening 411 is formed at one end of the piston cylinder 410 (the end of the piston cylinder 410 opposite to the opening 411 is a closed end), and the opening 411 faces the inner side wall of the second fairing section 120 to facilitate the movement and separation of the push rod 440. The end of the piston cylinder 410 away from the opening 411 is selectively communicated with the high pressure gas cylinder 430, that is, when high pressure gas needs to be filled into the piston cylinder 410, the high pressure gas cylinder 430 is communicated with the piston cylinder 410, and when high pressure gas does not need to be filled into the piston cylinder 410, the high pressure gas cylinder 430 is not communicated with the piston cylinder 410.
Further, the piston 420 is located in the piston cylinder 410 and is in sliding fit with the piston cylinder 410, the area between the piston 420 and the piston cylinder 410 is a working area of high-pressure gas, and the piston 420 can be pushed to slide towards the opening 411 of the piston cylinder 410 by the filled high-pressure gas. One end of the push rod 440 abuts against the piston 420, that is, the push rod 440 only contacts with the piston 420, and the two are not fixedly connected to facilitate subsequent separation. The other end of the push rod 440 extends from the opening 411 to the outside of the piston cylinder 410 and is fixedly connected to the inner sidewall of the second fairing section 120.
It should be noted that the volume of the high-pressure gas cylinder 430 and the volume of the high-pressure gas stored inside may be set according to the set weight of the whole separation device 400 and the magnitude of the separation power, which is not specifically limited in the embodiment of the present application, and it is sufficient to ensure that the fairing body 100 can be separated without affecting the bearing weight of the launch vehicle.
The specific working process of the fairing separation system in the embodiment of the application is as follows:
in an initial state, the first fairing section 110 and the second fairing section 120 are locked by a fixing bolt, the piston cylinder 410 and the high-pressure gas cylinder 430 are both connected with the first fairing section 110, the push rod 440 is connected with the second fairing section 120, and the relative position among the piston cylinder 410, the piston 420 and the push rod 440 at the moment is an initial position.
When the fairing body 100 needs to be separated, the fixing bolt of the fairing body 100 is unlocked, the high-pressure gas cylinder 430 is communicated with the piston cylinder 410, high-pressure gas in the high-pressure gas cylinder 430 rapidly enters the piston cylinder 410 and pushes the piston 420 to move, and the push rod 440 is abutted against the piston 420, so that the piston 420 drives the push rod 440 to move towards the direction close to the second fairing section body 120, namely, relative movement is generated between the push rod 440 and the piston cylinder 410, and the first fairing section body 110 and the second fairing section body 120 are separated along the separating surface 130 perpendicular to the separating surface.
In the fairing separation system provided by the embodiment of the application, the separation device 400 capable of providing high-pressure pneumatic separation power is arranged between the first fairing segment 110 and the second fairing segment 120, and because the piston cylinder 410 of the separation device 400 is connected with the inner side wall of the first fairing segment 110, the push rod 440 of the separation device 400 is connected with the second fairing segment 120 and has certain guidance, and the piston cylinder 410 and the push rod 440 can be separated under the pushing of the pneumatic separation power, the acting distance of the first fairing segment 110 and the second fairing segment 120 during separation is increased, and the separation time of the fairing body 100 is shortened; the piston cylinder 410 in the separating device 400 is not directly connected with the push rod 440, so that clamping stagnation is not easy to occur during separation, and the separation reliability is improved; the fairing body 100 moves horizontally and is separated, and the separating device 400 is not directly connected with the arrow body 200, so that the stable operation of the arrow body 200 is facilitated; the separation device 400 has a simple structure, is easy to control, does not damage products in the separation process, is favorable for recycling, and reduces the manufacturing cost.
In some embodiments, in order to reduce the impact of the high-pressure pneumatic separation power and prevent the too large impact of the separation on the fairing, the embodiment of the present application provides a possible implementation manner for the push rod 440 of the separation device 400, which is as follows:
with continued reference to fig. 3, the push rod 440 in the embodiment of the present application specifically includes: a push rod body 441, a push rod sleeve 443, and a push rod spring 442 located within push rod sleeve 443. One end of the push rod body 441 abuts against the piston 420, and the other end of the push rod body 441 extends from the opening 411 to the outside of the piston cylinder 410 and is slidably connected to the push rod sleeve 443, that is, the push rod sleeve 443 indirectly contacts the piston 420 through the push rod body 441, so that the movement of the piston 420 drives the push rod sleeve 443 to move together.
Further, one end of push rod spring 442 is connected to one end of push rod body 441 far from piston cylinder 410, and the other end of push rod spring 442 abuts against the closed end of push rod sleeve 443, that is, push rod spring 442 is located at a position between push rod body 441 and the closed end of push rod sleeve 443, so as to provide a buffering effect for the sliding connection of push rod body 441 and push rod sleeve 443. The end of the push rod sleeve 443 remote from the piston cylinder 410 is fixedly attached to the inner sidewall of the second fairing segment 120.
It should be noted that the sliding connection between push rod body 441 and push rod sleeve 443 needs to ensure that at least a portion of push rod body 441 is located inside push rod sleeve 443, and the length of push rod body 441 entering the inside of push rod spring 442 can be limited by push rod spring 442.
The specific working process of the fairing separation system in the embodiment of the application is as follows:
in an initial state, the first cowling split body 110 and the second cowling split body 120 are locked by the fixing bolt, the piston cylinder 410 and the high-pressure gas cylinder 430 are both connected to the first cowling split body 110, the push rod sleeve 443 of the push rod 440 is connected to the second cowling split body 120, and the relative positions of the piston cylinder 410, the piston 420, the push rod body 441, and the push rod sleeve 443 are initial positions.
When the fairing body 100 needs to be separated, the fixing bolt of the fairing body 100 is unlocked, the high-pressure gas cylinder 430 is communicated with the piston cylinder 410, high-pressure gas in the high-pressure gas cylinder 430 rapidly enters the piston cylinder 410 and pushes the piston 420 to move, and the push rod body 441 is abutted against the piston 420, so that the piston 420 drives the push rod body 441 to move towards the direction close to the second fairing section body 120, namely, relative movement is generated between the push rod body 441 and the piston cylinder 410, the push rod spring 442 is compressed and further pushes the push rod sleeve 443 to move, and the first fairing section body 110 and the second fairing section body 120 are separated along the separation surface 130. The push rod spring 442 may play a role in buffering when the push rod body 441 initially moves (compression process of the push rod spring 442), and the push rod spring 442 may also generate a certain separation power after being compressed (recovery process of the push rod spring 442).
In the fairing separation system provided by the embodiment of the application, the push rod 440 in the separation device 400 is provided with the push rod spring 442 which can provide a buffering effect, and the push rod spring 442 can play a certain buffering effect on the separation power generated by the push rod body 441 after high-pressure gas rapidly enters the piston cylinder 410, so that the impact of the separation power on the fairing body 100 is prevented, and the normal operation of the rocket body 200 cannot be influenced; the push rod spring 442 can release certain elastic force at a later stage, so that the acting distance is further increased, and the separation speed of the fairing body 100 is increased; and the mode of combining high-pressure pneumatic separation and spring buffering can provide larger separation power for the separation of the fairing body 100, and the problem that the requirement on the elasticity of the spring is larger when the existing spring is separated is solved.
In some embodiments, in order to further enhance the separation effect of the separation device 400 on the fairing body 100, the following possible implementation manners are provided for the arrangement positions of the piston cylinder 410, the push rod body 441 and the push rod sleeve 443 in the embodiments of the present application:
with continued reference to fig. 3, the piston cylinder 410, the push rod body 441, and the push rod sleeve 443 are coaxially disposed, and the axes of the piston cylinder 410, the push body, and the push rod sleeve 443 are perpendicular to the parting plane 130 of the cowl body 100.
In this embodiment, since the axes of the piston cylinder 410, the push rod body 441, and the push rod sleeve 443 are coincident, the action distance on the push rod sleeve 443 is the largest under the condition that the relative movement distance between the piston 420 and the piston cylinder 410 is constant, which is beneficial to increasing the separation speed. In addition, the axes of the piston cylinder 410, the push rod body 441 and the push rod sleeve 443 are perpendicular to the separating surface 130 of the fairing body 100, and when the same volume of high-pressure gas is filled into the piston cylinder 410, a larger separating power can be provided, so that the first fairing segment 110 and the second fairing segment 120 can be separated more easily.
Optionally, in order to facilitate the control of the high-pressure gas in the high-pressure gas cylinder 430 to enter the piston cylinder 410, the embodiment of the present application provides a possible implementation manner for the selective communication between the high-pressure gas cylinder 430 and the piston cylinder 410: with continued reference to fig. 3, the end of the piston cylinder 410 away from the opening 411 is connected to the high pressure gas cylinder 430 through a gas line 460, a gas valve switch 450 is disposed on the gas line 460, and the high pressure gas in the high pressure gas cylinder 430 is controlled to enter the piston cylinder 410 by the gas valve switch 450. Wherein the gas valve switch 450 can be connected to the general control system of the launch vehicle for ease of operation.
Optionally, the gas pipeline 460 and the gas valve switch 450 may be connected to the inner sidewall of the first fairing section 110 through a support or a connector, so as to prevent the gas pipeline 460 and the gas valve switch 450 from shaking and affecting the communication effect.
Optionally, the outer cylinder wall of the piston cylinder 410 is secured to the inner side wall of the first fairing section 110 by a first support. Since the opening 411 of the piston cylinder 410 in the embodiment of the present application faces the second fairing section 120 and the closed end of the piston cylinder 410 is connected to the high pressure gas cylinder 430 through the gas line 460, the outer cylinder wall of the piston cylinder 410 can be connected to the first fairing section 110 without affecting the installation of the gas line 460 and the movement of the pushrod body 441. The first supporting member may be a supporting frame or a supporting rod, which can realize that the outer cylinder wall of the piston cylinder 410 is fixedly connected to the inner side wall of the first fairing segment 110.
Optionally, the high pressure gas cylinder 430 is fixedly connected to the inner sidewall of the first fairing section 110 through a second support member, so as to be separable together with the first fairing section 110. The high pressure gas cylinder 430 may be fixedly mounted by a second support member, which may be a support frame or a connector capable of holding the high pressure gas cylinder 430.
In this embodiment, the piston cylinder 410 and the high-pressure gas cylinder 430 are respectively and fixedly connected to the inner side wall of the first cowling split body 110 through a support member, so as to ensure the stability of the whole high-pressure gas supply system; when the first fairing section 110 is separated from the second fairing section 120, the piston cylinder 410 and the high-pressure gas cylinder 430 can be separated together with the first fairing section 110, other structures of the launch vehicle cannot be damaged, and the safety is high.
In some embodiments, with reference to fig. 3, since the push rod body 441 abuts against the piston 420 in the piston cylinder 410, in order to ensure that the push rod body 441 is smoothly separated from the opening 411 of the piston cylinder 410, and considering that the contact area between the push rod body 441 and the piston 420 may affect the separation power, in the embodiment of the present invention, a push rod ball 441a is disposed at one end of the push rod body 441 close to the piston 420, and the push rod ball 441a (spherical surface) is in spherical contact with the piston 420 (flat surface), so that a larger separation power can be provided under the condition of the same contact area.
Alternatively, one end of the push rod body 441 close to the piston 420 may be provided with a conical structure, and the rest of the push rod body 441 is provided with a cylindrical structure, so as to be in sliding fit with the inside of the cylinder of the push rod 440. The diameter of the tapered structure is gradually reduced toward the direction approaching the piston 420, so that the interference between the push rod body 441 and the opening 411 of the piston cylinder 410 can be avoided, and the normal separation of the push rod body 441 and the piston cylinder 410 can be ensured. The push rod ball 441a is located at the end position of the tapered structure near the piston 420, and the push rod 440 abuts against the piston 420, which is equivalent to increase the area of the end of the push rod body 441, thereby improving the stability of the abutment of the push rod body 441 and the piston 420.
In this embodiment, the push rod ball 441a is disposed at one end of the push rod body 441 close to the piston 420, and the spherical contact between the push rod ball 441a and the piston 420 is utilized, so that a larger separation power can be provided under the condition of the same contact area, and meanwhile, the stability of the push rod body 441 abutting against the piston 420 can be improved.
In some embodiments, in order to provide larger separation power, the number of the separation devices 400 may be set as a plurality of sets, and the plurality of sets of separation devices 400 may operate simultaneously, so as to provide larger separation power for the fairing body 100, and the whole fairing separation system operates more stably and has higher reliability.
Optionally, the projections of the piston cylinders 410 of the separating devices 400 in the plane of the separating surface 130 are linearly distributed. For example: the separation devices 400 may be arranged in a linear manner in the vertical direction in fig. 1 or in a linear manner in the horizontal direction in fig. 1. It should be noted that the piston cylinders 410 and the push rods 440 of adjacent separation devices 400 are arranged in parallel to ensure that the separation power provided by each set of separation devices 400 is in the same direction.
Optionally, the projections of the piston cylinders 410 of the separating devices 400 in the plane of the separating surface 130 are distributed in an array. For example: with reference to the vertical direction in fig. 1, the piston cylinders 410 and the corresponding push rods 440 of the respective sets of separating devices 400 are arranged in an array of 2 (rows) × 2 (columns) or an array of 3 (rows) × 2 (columns) in a direction perpendicular to the separating plane 130.
In the embodiment of the present application, the number and the positions of the separating devices 400 to be arranged are reasonably selected according to the inner space of the cowl body 100, so that the separating power of the cowl body 100 can be relatively balanced, and a larger separating power can be provided, which is beneficial to further shortening the separating time of the cowl body 100.
In some embodiments, as shown in fig. 1 and 4, for convenience of description, a plane perpendicular to the separating plane 130 is set as a symmetry plane 500 in the present embodiment, and the central axis of the fairing body 100 is located at the intersection of the symmetry plane 500 and the separating plane 130. Wherein the first fairing section 110 is symmetrical about the plane of symmetry 500 and the second fairing section 120 is also symmetrical about the plane of symmetry 500.
In this embodiment, in order to provide relatively uniform separation power for the separation of the fairing body 100, the number of sets of the separation devices 400 may be set to be even. Wherein, the separation devices 400 of even number sets can be divided into two groups, and the two groups of separation devices 400 are also symmetrically arranged about the symmetry plane 500, so that the number and the position distribution of the separation devices 400 at the two sides of the symmetry plane 500 are relatively uniform, thereby being beneficial to the separation of the fairing body 100; and the two sets of separation devices 400 may be placed on either side of a payload 300 (e.g., a spacecraft) placed within the fairing without affecting the installation of the separation devices 400.
It should be noted that, for convenience of illustrating specific distribution positions of the separating devices, only the projection of the piston cylinder 410 is illustrated in the separating plane 130 in fig. 4, and the corresponding projection position of the piston rod 440 may refer to the projection position of the piston cylinder 410, and the axes of the piston cylinder 410 and the piston rod 440 are located on the same straight line.
Alternatively, with continued reference to FIG. 4, to take into account the separation force of the fairing and the self weight of the fairing separation system, the number of separation devices 400 in the embodiment of the present application is provided in sets of four.
Specifically, the four sets of separation devices 400 are divided into two sets, each set including two sets of separation devices 400. For the two sets of separation devices 400 in each set, the piston cylinders 410 in each set of separation devices 400 are spaced apart in a direction parallel to the center axis of the cowl (spaced apart vertically in FIG. 1). And the two sets of separating devices 400 are also symmetrically arranged about the symmetry plane 500, and the projections of the piston cylinders 410 and the push rods 440 of the four sets of separating devices 400 in the plane of the separating plane 130 are distributed in an array.
In this embodiment, on the basis that four sets of separating devices 400 are provided to provide stable and large enough separation power for the fairing separation system, the self weight of the whole fairing separation system is controlled within a certain range, so that the fairing separation and falling and the arrow body 200 operation are facilitated.
Based on the same inventive concept, the embodiment of the present application further provides a launch vehicle, which includes an arrow body 200 and the fairing separation system described above in the embodiment of the present application, and the fairing separation system is loaded on the arrow body 200.
The launch vehicle provided by the embodiment of the application comprises the fairing separation system, wherein the fairing separation system is provided with the separation device 400 capable of providing high-pressure pneumatic separation power between the first fairing segment 110 and the second fairing segment 120, and as the piston cylinder 410 of the separation device 400 is connected with the inner side wall of the first fairing segment 110, the push rod 440 of the separation device 400 is connected with the second fairing segment 120 and has certain guidance, and the piston cylinder 410 and the push rod 440 can be separated under the pushing of the pneumatic separation power, the acting distance of the first fairing segment 110 and the second fairing segment 120 during separation is increased, and the separation time of the fairing body 100 is shortened; the piston cylinder 410 and the push rod 440 in the separation device 400 are not directly connected, so that clamping stagnation is not easy to occur during separation, and the separation reliability is improved; the fairing body 100 is separated in a horizontal moving mode, and the separating device 400 is not connected with the arrow body 200 in a supporting mode, so that stable operation of the arrow body 200 is facilitated.
By applying the embodiment of the application, at least the following beneficial effects can be realized:
1. be equipped with the separator that can provide high-pressure pneumatic separation power between first radome fairing split body and second radome fairing split body, because this separator's piston cylinder links to each other with first radome fairing split body inside wall, this separator's push rod links to each other and has certain direction with the second radome fairing split body simultaneously, and piston cylinder can take place the separation with the push rod under the promotion of pneumatic separation power, thereby the working distance when having increased separation between first radome fairing split body and the second radome fairing split body, the separation time of radome fairing body has been shortened.
2. The piston cylinder in the separating device is not directly connected with the push rod, so that clamping stagnation is not easy to occur during separation, and the separation reliability is improved; the fairing body moves horizontally and is separated, and the separating device is not directly connected with the arrow body, so that the stable operation of the arrow body is facilitated; the separating device has simple structure and easy control, and the product is not damaged in the separating process, thereby being beneficial to recycling and reducing the manufacturing cost.
3. The push rod in the separating device is provided with a push rod spring which can provide a buffering effect, and the push rod spring can play a certain buffering effect on the separating power generated by the push rod body after high-pressure gas rapidly enters the piston cylinder, so that the separating power is prevented from directly acting on the fairing body to generate impact on the fairing body, and the normal operation of an arrow body is not influenced; the push rod spring can release certain elasticity in the later stage, further increases the working distance, promotes the separation speed of radome fairing body.
4. The mode that utilizes high-pressure pneumatic separation and spring buffering to combine together can provide great separation power for the separation of radome fairing body, has solved the problem that requires great to the elasticity of spring when current spring separation.
5. Because the axes of the piston cylinder, the push rod body and the push rod sleeve are overlapped, the action distance of the push rod sleeve is the largest under the condition that the relative movement distance between the piston and the piston cylinder is certain, and the separation speed is favorably improved. In addition, the axis of the piston cylinder, the push rod body and the push rod sleeve is perpendicular to the separating surface of the fairing body, and when high-pressure gas with the same volume is filled into the piston cylinder, larger separating power can be provided, so that the first fairing split body and the second fairing split body can be separated easily.
6. The piston cylinder and the high-pressure gas cylinder are fixedly connected to the inner side wall of the first fairing split body through supporting pieces respectively, so that the stability of the whole high-pressure gas supply system is ensured; when first fairing split body and second fairing split body separate, a piston cylinder and a high-pressure gas cylinder can drop along with first fairing split body, can not destroy other structures of the carrier rocket, and the security is higher.
7. Through setting up the push rod spheroid at the one end that the push rod body is close to the piston, utilize the sphere contact between push rod spheroid and the piston, can provide bigger separation power under the condition of same area of contact, stability when can having promoted push rod body and piston butt simultaneously.
8. The quantity and the position of the separating devices needing to be arranged are reasonably selected according to the inner space of the fairing body, so that the relative balance of the separating power of the fairing body can be ensured, the larger separating power can be provided, and the separating time of the fairing body can be further shortened.
9. In order to provide relatively uniform separation power for the separation of the fairing body, the number of sets of separation devices can be set to be an even number, the separation devices of the even number sets can be divided into two groups, and the two groups of separation devices are also symmetrically arranged relative to the symmetrical plane, so that the number and the position distribution of the separation devices on two sides of the symmetrical plane are relatively uniform, and the separation of the fairing body is facilitated; and the two sets of separating devices can be respectively arranged at two sides of the effective load arranged in the fairing, and the installation of the separating devices can not be influenced.
10. Through the quantity of control separator, can provide stable and enough big separation power's basis for radome fairing separation system on, with whole radome fairing separation system's dead weight control in certain scope to be favorable to the separation of radome fairing to drop and the operation of arrow body.
In the description of the present application, it is to be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and thus should not be construed as limiting the present application.
The terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless otherwise specified.
In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
In the description herein, particular features, structures, materials, or characteristics may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing is only a partial embodiment of the present application, and it should be noted that, for those skilled in the art, several modifications and decorations can be made without departing from the principle of the present application, and these modifications and decorations should also be regarded as the protection scope of the present application.
Claims (9)
1. A fairing separation system for a launch vehicle comprising: the fairing comprises a fairing body and at least one set of separating devices;
the fairing body comprises a first fairing split body and a second fairing split body which can be separated; the central axis of the fairing body is positioned in the plane of the parting surfaces of the first fairing section and the second fairing section;
the separation device comprises a high-pressure gas cylinder, a piston and a push rod; the piston cylinder and the high-pressure gas cylinder are fixedly connected with the inner side wall of the first fairing split body, one end of the piston cylinder is provided with an opening, and the opening faces the inner side wall of the second fairing split body; one end of the piston cylinder, which is far away from the opening, is selectively communicated with the high-pressure gas cylinder;
the piston is positioned in the piston cylinder and is in sliding fit with the piston cylinder, and one end of the push rod is abutted against the piston; the other end of the push rod extends to the outside of the piston cylinder from the opening and is fixedly connected with the inner side wall of the second fairing split body.
2. The fairing separation system of claim 1 wherein said pushrod comprises a pushrod body, a pushrod sleeve, and a pushrod spring positioned within said pushrod sleeve;
one end of the push rod body is abutted against the piston, and the other end of the push rod body extends to the outside of the piston cylinder from the opening and is in sliding connection with the push rod sleeve;
one end of the push rod spring is connected with one end of the push rod body, which is far away from the piston cylinder, and the other end of the push rod spring is abutted against the closed end of the push rod sleeve;
one end of the push rod sleeve, which is far away from the piston cylinder, is fixedly connected with the inner side wall of the second fairing split body.
3. The fairing separation system of claim 2 wherein said piston cylinder, said pushrod body and said pushrod sleeve are all coaxially disposed and the axes of said piston cylinder, said pushrod body and said pushrod sleeve are all perpendicular to said parting plane.
4. The fairing separation system of claim 1 wherein an end of said piston cylinder remote from said opening communicates with said high pressure gas cylinder through a gas line, said gas line having a gas valve switch disposed thereon.
5. The fairing separation system of claim 4 wherein said outer cylinder wall of said piston cylinder is secured to said inner sidewall of said first fairing segment by a first support member;
and/or the high-pressure gas cylinder is fixedly connected with the inner side wall of the first fairing split body through a second supporting piece.
6. The fairing separation system of claim 2 wherein said pushrod body has a pushrod sphere at an end proximate said piston, said pushrod sphere in spherical contact with said piston.
7. The fairing separation system of any one of claims 1 to 6 wherein said separation device is in a plurality of sets; the projections of the piston cylinders of the separating devices in the plane of the separating surface are distributed linearly or in an array.
8. The fairing separation system of claim 7 wherein said first fairing split and said second fairing split are both symmetric about a plane of symmetry; wherein the symmetry plane is a plane perpendicular to the parting plane;
the separation devices are even-number sets, the even-number sets of separation devices are divided into two groups, and the two groups of separation devices are symmetrically arranged around the symmetry plane.
9. A launch vehicle comprising a fairing separation system as defined in any one of claims 1 to 8.
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| CN202011555395.3A CN112284196B (en) | 2020-12-25 | 2020-12-25 | Fairing separation system for carrier rocket and carrier rocket |
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| CN202011555395.3A CN112284196B (en) | 2020-12-25 | 2020-12-25 | Fairing separation system for carrier rocket and carrier rocket |
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| CN112284196B CN112284196B (en) | 2021-04-13 |
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| CN117647157A (en) * | 2024-01-30 | 2024-03-05 | 江苏深蓝航天有限公司 | Cowling separation system and carrier rocket |
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| CN112284196B (en) | 2021-04-13 |
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