CN217396841U - Semi-adjustable pressure accumulator of carrier rocket - Google Patents

Abstract

The utility model provides a semi-regulating pressure accumulator for a launch vehicle, which comprises a four-way housing, the four-way housing comprises first to fourth connecting bodies, and along the axis direction of the first and second connecting bodies, the four-way housing The interior of the casing is a liquid cavity, and the liquid cavity forms a propellant conveying channel; along the axis direction of the third and fourth connecting bodies, a first air cavity and a second air cavity are respectively set at the third and fourth connecting bodies, respectively, The propellant in the liquid cavity shape can change the pressure in the first air cavity and the second air cavity; along the direction perpendicular to the central axes of the first and second connecting bodies and the central axes of the third and fourth connecting bodies, A closed third air cavity and a fourth air cavity are correspondingly provided on the two opposite outer walls of the four-way housing; the first air cavity is communicated with the third air cavity through a pipeline and the first controlled valve, and the second air cavity is connected through a pipe The circuit and the second controlled valve communicate with the fourth air chamber. The semi-regulating pressure accumulator of the utility model has good adaptability and obvious restraining effect.

Description

A semi-regulating pressure accumulator for launch vehicle

technical field

The utility model belongs to the field of aerospace, in particular to a semi-regulating pressure accumulator for a launch vehicle.

Background technique

POGO vibration is a kind of longitudinal self-excited scattering vibration generated by the coupling between the rocket body structure and the propellant delivery system of a large liquid carrier rocket in flight. It is generally believed that the POGO vibration is caused by the natural frequency of the longitudinal vibration of the liquid launch vehicle structure and the natural frequency of the propellant delivery system vibration being close to or equal to each other during flight. If not suppressed, POGO vibration will cause serious damage to the structure of the rocket body, shorten the life of the instruments and satellites on the rocket, and even endanger the safety of astronauts.

At present, the method of installing a pressure accumulator on the propellant delivery system is mainly used at home and abroad to change the natural frequency of the system to achieve POGO suppression. However, the energy storage of the traditional accumulator is basically fixed, that is, the PV value of the product of pressure and volume is fixed. Therefore, the traditional accumulator has poor adaptability and unsatisfactory suppression effect when the dynamic characteristics of the launch vehicle are complex.

SUMMARY OF THE INVENTION

In order to overcome the problems existing in the related technologies at least to a certain extent, the utility model provides a semi-regulating pressure accumulator for a launch vehicle.

According to an embodiment of the present utility model, the present utility model provides a semi-regulating pressure accumulator for a launch vehicle, which includes a four-way housing, and the four-way housing includes a first connecting body, a second connecting body, and a third connecting body body and fourth linker;

along the axial direction of the first connecting body and the second connecting body, the interior of the four-way housing is a liquid cavity, and the liquid cavity forms a propellant conveying channel;

Along the axis direction of the third connecting body and the fourth connecting body, the third connecting body is provided with a first air cavity, the fourth connecting body is provided with a second air cavity, and the liquid cavity is a propellant capable of changing the pressure in the first air chamber and the second air chamber;

Along the direction perpendicular to the central axis of the first connecting body and the second connecting body and the central axis of the third connecting body and the fourth connecting body, two opposite outer walls of the four-way housing are correspondingly provided with Closed third air cavity and fourth air cavity;

The first air cavity is communicated with the third air cavity, and the second air cavity is communicated with the fourth air cavity; a first controlled valve is arranged on the pipeline connecting the first air cavity and the third air cavity, so The first controlled valve is used to switch on and off the pipeline where it is located; the pipeline connecting the second air chamber and the fourth air chamber is provided with a second controlled valve, and the second controlled valve is used to switch on and off the pipeline in which it is located.

In the above-mentioned semi-regulating pressure accumulator of a launch vehicle, the third connecting body is provided with a first pushing mechanism, and the fourth connecting body is provided with a second pushing mechanism; the third connecting body is far away from the spool One end of the center of the housing is provided with a first end cover, and one end of the fourth connecting body away from the center of the four-way housing is provided with a second end cover; the first push mechanism, the first end cover and the third connection The second pushing mechanism, the second end cover and the fourth connecting body together form a closed second air cavity.

In the above-mentioned semi-regulating pressure accumulator for launch vehicle, the first air chamber is communicated with the third air chamber through the first communication pipe and the first connecting head, and the second air chamber is connected with the second communication pipe and the second air chamber. The connecting head communicates with the fourth air cavity; the first controlled valve is arranged on the first communication pipe, and the second controlled valve is arranged on the second communication pipe.

Further, the first push mechanism includes a first push plate, a first diaphragm and a first guide rod, and the first push plate, the first end cover and the third connecting body together enclose the closed first Air cavity, the first diaphragm is arranged in the first air cavity, one end of the first diaphragm is connected with the inner end surface of the first end cover, and the other end is connected with the first push plate One end face is connected; the other end face of the first push plate is connected to one end of the first guide rod, and the other end of the first guide rod extends into the liquid cavity.

Further, along the pushing direction of the first guide rod, a first cylinder is provided at the center of the inner end face of the first end cover, and the first cylinder is used for performing the first diaphragm operation. Limit protection.

Further, the second push mechanism includes a second push plate, a second diaphragm and a second guide rod, and the second push plate, the second end cover and the fourth connecting body together enclose the closed second Air cavity, the second diaphragm is arranged in the second air cavity, one end of the second diaphragm is connected with the inner end surface of the second end cover, and the other end is connected with the second push plate One end face is connected; the other end face of the second push plate is connected to one end of the second guide rod, and the other end of the second guide rod extends into the liquid chamber.

Further, along the pushing direction of the second guide rod, a second cylinder is provided at the center of the inner end face of the second end cover, and the second cylinder is used to perform the second diaphragm. Limit protection.

Further, the first connector and the second connector adopt the same structure, and the first connector adopts a three-way connector.

Further, two ends of the first connecting head are respectively connected with the first communication pipe and the third connecting body, and the other end of the first connecting head is connected with the first inflation switch and the first manual valve;

Two ends of the second connecting head are respectively connected with the second communication pipe and the fourth connecting body, and the other end of the second connecting head is connected with the second inflation switch and the second manual valve.

In the above-mentioned semi-regulating pressure accumulator for launch vehicle, the semi-regulating pressure accumulator for launch vehicle is used for POGO vibration suppression.

According to the above-mentioned specific embodiment of the present utility model, it can be known that at least the following beneficial effects are obtained: the semi-regulating pressure accumulator of the launch vehicle provided by the present utility model utilizes the first controlled valve to adjust the connection state of the first air chamber and the third air chamber, The second controlled valve is used to adjust the connection state of the second air chamber and the fourth air chamber to adjust the PV value of the pressure accumulator, so as to more flexibly and efficiently suppress the POGO vibration. The flexibility and adaptability of the device can reduce the risk of failure caused by POGO vibration of liquid launch vehicles.

In addition, in the launch vehicle semi-regulating pressure accumulator provided by the utility model, the same air chamber valve connection structure is provided between the first air chamber and the third air chamber and between the second air chamber and the fourth air chamber, They can be mutually redundant. When one set of air cavity valve connection structure fails, the other set of air cavity valve connection structure still has a certain POGO vibration suppression ability, which can improve the reliability of the system.

It is to be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not intended to limit the scope of the invention as claimed.

Description of drawings

The following accompanying drawings are part of the specification of the present invention, which illustrate embodiments of the present invention, and together with the description of the specification serve to explain the principles of the present invention.

FIG. 1 is a schematic structural diagram of a four-way casing in a semi-regulating pressure accumulator of a launch vehicle according to an embodiment of the present invention.

FIG. 2 is a schematic structural diagram of a semi-regulating pressure accumulator of a launch vehicle provided by an embodiment of the present invention.

Description of reference numbers:

1. Four-way housing; 11. The first connecting body; 12. The second connecting body;

13. The third connector;

131, the first push mechanism; 1311, the first push plate; 1312, the first diaphragm; 1313, the first guide rod;

132, the first end cap; 1321, the first cylinder;

133, the first air chamber; 134, the first communication pipe; 135, the first connector; 136, the first controlled valve; 137, the first charging switch; 138, the first manual valve;

14. The fourth connector;

141, the second push mechanism; 1411, the second push plate; 1412, the second diaphragm; 1413, the second guide rod;

142, the second end cap; 1421, the second cylinder;

143, the second air chamber; 144, the second communication pipe; 145, the second connector; 146, the second controlled valve; 147, the second charging switch; 148, the second manual valve;

15. The third air chamber; 16. The fourth air chamber;

2. Liquid cavity.

Detailed ways

In order to make the purpose, technical solutions and advantages of the embodiments of the present invention more clearly understood, the following will clearly illustrate the spirit of the disclosed content of the present invention with the accompanying drawings and detailed description. After the embodiment, changes and modifications can be made by the technology taught by the content of the present invention, which does not depart from the spirit and scope of the content of the present invention.

The exemplary embodiments and descriptions of the present invention are used to explain the present invention, but are not intended to limit the present invention. In addition, elements/members with the same or similar reference numerals used in the drawings and the embodiments are intended to represent the same or similar parts.

Regarding the "first", "second", ... etc. used in this document, it does not specifically refer to the order or order, nor is it used to limit the present invention, it is only used to distinguish elements described in the same technical terms or operate.

As used herein, "comprising," "including," "having," "containing," and the like, are open-ended terms, meaning including but not limited to.

As used herein, "and/or" includes any and all combinations of the stated things.

As used herein, "a plurality" includes "two" and "two or more"; as used herein, "a plurality of groups" includes "two groups" and "two or more groups."

Certain terms used to describe the invention are discussed below or elsewhere in this specification to provide those skilled in the art with additional guidance in the description of the invention.

The PV value of the accumulator is closely related to its ability to suppress the POGO vibration, and the effect of the accumulator to suppress the POGO vibration is also related to the structural dynamic characteristics of the rocket (such as frequency, mode shape, damping, etc.). The accumulator with a fixed PV value cannot well adapt to the large changes in the dynamic characteristics of the liquid rocket, so it is easy to cause the POGO to vibrate greatly and even lead to the launch failure of the launch vehicle.

As shown in FIG. 1 and FIG. 2 , the semi-regulating pressure accumulator for a launch vehicle provided by the embodiment of the present invention includes a four-way housing 1, and the four-way housing 1 includes a first connecting body 11, a second connecting body 12, a Three connecting bodies 13 and fourth connecting bodies 14 .

Along the axial direction of the first connecting body 11 and the second connecting body 12 , the interior of the spool housing 1 is a liquid cavity 2 , and the liquid cavity 2 forms a propellant conveying channel. The first connecting body 11 forming part of the liquid cavity 2 is connected to the propellant storage tank through the upstream delivery pipeline, and the second connecting body 12 forming part of the liquid cavity 2 is connected to the engine through the downstream pipeline.

Along the axial direction of the third connecting body 13 and the fourth connecting body 14 , a closed first air cavity 133 is provided at the third connecting body 13 , and a closed second air cavity 143 is provided at the fourth connecting body 14 . The propellant in the liquid chamber 2 can change the pressure in the first air chamber 133 and the second air chamber 143 .

Along the direction perpendicular to the central axes of the first connecting body 11 and the second connecting body 12 and the central axes of the third connecting body 13 and the fourth connecting body 14, two opposite outer walls of the spool housing 1 are correspondingly provided with closed The third air cavity 15 and the fourth air cavity 16. The first air cavity 133 communicates with the third air cavity 15 through the first communication pipe 134 and the first connection head 135 , and the second air cavity 143 communicates with the fourth air cavity 16 through the second communication pipe 144 and the second connection head 145 . The first communication pipe 134 is provided with a first controlled valve 136 , and the first controlled valve 136 is used to connect and disconnect the first communication pipe 134 . The second communication pipe 144 is provided with a second controlled valve 146 , and the second controlled valve 146 is used to connect and disconnect the second communication pipe 144 .

In the above embodiment, the third connecting body 13 is provided with the first pushing mechanism 131 , and the fourth connecting body 14 is provided with the second pushing mechanism 141 . One end of the third connecting body 13 away from the center of the spool housing 1 is provided with a first end cap 132 , and one end of the fourth connecting body 14 away from the center of the spool housing 1 is provided with a second end cap 142 . The first pushing mechanism 131 , the first end cover 132 and the third connecting body 13 together form a closed first air cavity 133 , and the second pushing mechanism 141 , the second end cover 142 and the fourth connecting body 14 jointly form a closed air cavity 133 . The second air cavity 143 . The propellant in the liquid chamber 2 can interact with the first pushing mechanism 131 and the second pushing mechanism 141 to change the pressure in the first air chamber 133 and the second air chamber 143 .

Before the semi-regulating pressure accumulator provided by the embodiment of the present invention is used, the first air cavity 133 , the second air cavity 143 , the third air cavity 15 and the fourth air cavity are adjusted according to the dynamic characteristics of the flight of the launch vehicle. 16 were helium inflated. When in use, the first controlled valve 136 can be controlled to open or close according to the flight sequence of the launch vehicle, so that the first air cavity 133 and the third air cavity 15 are communicated or isolated; the second controlled valve 146 can be controlled to open or close to The second air chamber 143 is communicated with or isolated from the fourth air chamber 16 to realize the adjustment of the PV value of the semi-regulating accumulator, thereby suppressing the POGO vibration.

In the launch vehicle semi-regulating pressure accumulator provided by the embodiment of the present invention, the same air cavity is provided between the first air cavity 133 and the third air cavity 15 and between the second air cavity 143 and the fourth air cavity 16 The valve connection structure can be redundant with each other. When one set of air cavity valve connection structure fails, the other air cavity valve connection structure still has a certain POGO vibration suppression ability, which can improve the reliability of the system.

In the above embodiment, the first pushing mechanism 131 and the second pushing mechanism 141 adopt the same structural form.

The first push mechanism 131 includes a first push plate 1311, a first diaphragm 1312 and a first guide rod 1313, wherein the first push plate 1311, the first end cover 132 and the third connecting body 13 together form a closed first In the air cavity 133 , the first diaphragm 1312 is arranged in the first air cavity 133 . The other end surface of the first push plate 1311 is connected to one end of the first guide rod 1313 , and the other end of the first guide rod 1313 extends into the liquid chamber 2 . Specifically, the connection between the first diaphragm 1312 and the first end cover 132 and the first push plate 1311 may be welding. One end of the first diaphragm 1312 is annularly welded to the inner end surface of the first end cover 132 , and the other end of the first diaphragm 1312 is annularly welded to one end surface of the first push plate 1311 .

The second push mechanism 141 includes a second push plate 1411 , a second diaphragm 1412 and a second guide rod 1413 , wherein the second push plate 1411 , the second end cover 142 and the fourth connecting body 14 together form a closed second The air cavity 143 and the second diaphragm 1412 are arranged in the second air cavity 143 . The other end surface of the second push plate 1411 is connected to one end of the second guide rod 1413 , and the other end of the second guide rod 1413 extends into the liquid chamber 2 . Specifically, the connection between the second diaphragm 1412 and the second end cover 142 and the second push plate 1411 may be welding. One end of the second diaphragm 1412 is annularly welded to the inner end surface of the second end cover 142 , and the other end of the second diaphragm 1412 is annularly welded to one end surface of the second push plate 1411 .

When the pressure in the liquid chamber 2 is greater than the pressure in the first air chamber 133, the propellant in the liquid chamber 2 pushes the first diaphragm 1312 through the first guide rod 1313 and the first push plate 1311, and the When the volume of the first air chamber 133 is reduced, the gas in the first air chamber 133 is compressed; when the pressure in the liquid chamber 2 is lower than the pressure in the first air chamber 133, the gas in the first air chamber 133 pushes the first diaphragm 1312 and passes through the first diaphragm 1312. A diaphragm 1312 pushes the first push plate 1311 and the first guide rod 1313 to move in the direction of the liquid chamber 2; thus realizing the principle of the diaphragm type cylinder.

Similarly, when the pressure in the liquid chamber 2 is greater than the pressure in the second air chamber 143, the propellant in the liquid chamber 2 pushes the second diaphragm 1412 through the second guide rod 1413 and the second push plate 1411, and the second air The volume of the cavity 143 is reduced, and the gas in the second air cavity 143 is compressed; when the pressure in the liquid cavity 2 is lower than the pressure in the second air cavity 143, the gas in the second air cavity 143 pushes the second diaphragm 1412 , through the second diaphragm 1412 to push the second push plate 1411 and the second guide rod 1413 to move in the direction of the liquid chamber 2; thus realizing the principle of the diaphragm type cylinder.

In the above embodiment, along the pushing direction of the first guide rod 1313 , the first cylinder 1321 is disposed at the center of the inner end surface of the first end cover 132 . A second cylinder 1421 is disposed at the center of the inner end surface of the second end cover 142 along the pushing direction of the second guide rod 1413 . When the propellant in the liquid chamber 2 pushes the first diaphragm 1312 toward the first end cover 132 through the first guide rod 1313 and the first push plate 1311 , the first cylinder 1321 is used for the first diaphragm 1312 For limit protection, the first diaphragm 1312 can be buffered by entering the cylinder cavity of the first cylinder 1321 to prevent being crushed.

When the propellant in the liquid chamber 2 pushes the second diaphragm 1412 to the direction of the second end cover 142 through the second guide rod 1413 and the second push plate 1411 , the second cylinder 1421 is used for the second diaphragm 1412 For limit protection, the second diaphragm 1412 can be buffered by entering the cylinder cavity of the second cylinder 1421 to prevent being crushed.

In the above-mentioned embodiment, the first connector 135 and the second connector 145 have the same structure, and both can use a three-way connector.

When the first connecting head 135 adopts a tee joint, two ends of the first connecting head 135 are respectively connected with the first communicating pipe 134 and the first end cap 132 on the third connecting body 13 , and the first connecting head 135 The other end is connected to the first charging switch 137 and the first manual valve 138 , and opening the first charging switch 137 and the first manual valve 138 can charge the first air chamber 133 with pressure.

When the second connecting head 145 adopts a tee joint, two ends of the second connecting head 145 are respectively connected with the second communicating pipe 144 and the second end cap 142 on the fourth connecting body 14 , and the second connecting head 145 The other end is connected to the second charging switch 147 and the second manual valve 148 , and opening the second charging switch 147 and the second manual valve 148 can charge the second air chamber 143 with pressure.

In the above-mentioned embodiments, by improving the structural form of the controlled valve, adaptation to different environmental requirements can be achieved. Specifically, in order to meet the usage requirements in a normal temperature environment, solenoid valves may be used for both the first controlled valve 136 and the second controlled valve 146 . In order to meet the requirements for use in a low temperature environment, both the first controlled valve 136 and the second controlled valve 146 can be controlled by pneumatic valves.

Based on the launch vehicle semi-regulating pressure accumulator provided by the embodiment of the present utility model, the embodiment of the present utility model further provides a POGO vibration suppression method, which includes the following steps:

S1. Install the launch vehicle semi-regulatory accumulator on the propellant delivery system.

S2. Divide the flight sequence of the launch vehicle into three stages: the early stage, the middle stage and the later stage, and determine the PV value of the accumulator required to suppress the POGO vibration in the three stages according to the dynamic characteristics of the rocket. Among them, the early stage corresponds to the initial state A of the pressure accumulator, and the PV value of the pressure accumulator required for this state is P ₀ V ₀ ; the middle stage corresponds to the open state B of the controlled valve of the pressure accumulator, and the pressure accumulator required for this state is P 0 V 0 . The PV value of the accumulator is P ₁ V ₁ ; the later stage corresponds to the closed state C of the controlled valve of the accumulator, and the PV value of the accumulator required for this state is P ₂ V ₂ .

S3. Adjust the energy storage state of the accumulator according to the flight sequence of the launch vehicle, which specifically includes:

S31. In the initial state A of the accumulator, adjust the pressure of the first air cavity 133 according to the volume of the first air cavity 133, and adjust the pressure of the second air cavity 143 according to the volume of the second air cavity 143, so that the first air cavity 143 is adjusted. The sum of the product of the pressure and volume of 133 and the product of the pressure and volume of the second air chamber 143 satisfies the PV value P ₀ V ₀ of the accumulator required for the initial state A of the accumulator, namely:

P ₀ V ₀ =2*P _m0 *V _m0 (1)

In the formula (1), P _m0 represents the pressure of the first air chamber 133 , and V _m0 represents the volume of the first air chamber 133 .

It should be noted that the structures of the first air chamber 133 and the second air chamber 143 are the same, and the pressure and volume of the two are also the same. Therefore, P _m0 can also represent the pressure of the second air chamber 143, and V _m0 can also represent the first air chamber 143. The volume of the second air cavity 143 .

S32. In the open state B of the controlled valve of the accumulator, the first air chamber 133 is communicated with the third air chamber 15, and the second air chamber 143 is communicated with the fourth air chamber 16. According to the volume of the first air chamber 133 and the The volume of the three air chambers 15, the pressure of the third air chamber 15 is adjusted, and the pressure of the fourth air chamber 16 is adjusted according to the volume of the second air chamber 143 and the volume of the fourth air chamber 16, so that the pressure of the first air chamber 133 is adjusted. The sum of the product of pressure and volume, the product of pressure and volume of the second air chamber 143 , the product of pressure and volume of the third air chamber 15 , and the product of pressure and volume of the fourth air chamber 16 satisfies the control of the accumulator The PV value P ₁ V ₁ of the accumulator required for valve opening state B, namely:

P ₁ V ₁ =2*(P _m0 *V _m0 +P _q0 *V _q0 ) (2)

In the formula (2), P _q0 represents the pressure of the third air chamber 15 , and V _q0 represents the volume of the third air chamber 15 .

It should be noted that the structure of the third air chamber 15 and the fourth air chamber 16 are the same, and the pressure and volume of the two are also the same, so P _q0 can also represent the pressure of the fourth air chamber 16, and V _q0 can also represent the first The volume of the four air chambers 16 .

S33. In the closed state C of the controlled valve of the accumulator, the first air chamber 133 is isolated from the third air chamber 15, and the second air chamber 143 is isolated from the fourth air chamber 16, so that the controlled valve of the accumulator is closed _The PV value _P2V2 of the accumulator required by C is:

P ₂ V ₂ =2*(P _m0 *V _m0 +P _q0 *V _q0 )*V _m0 /(V _m0 +V _q0 ) (3)

In the above step S3, when the flight sequence of the launch vehicle is in the middle stage, it is first judged whether the PV value P ₁ V ₁ of the accumulator in the current state meets the POGO suppression requirement, and if so, the first controlled valve 136 and the second controlled valve 136 are maintained. The open state of the control valve 146; otherwise, the control closes the first controlled valve 136 and the second controlled valve 146.

When the flight sequence of the launch vehicle is in the later stage, first determine whether the PV value P ₂ V ₂ of the accumulator in the current state meets the POGO suppression requirement, and if so, keep the first controlled valve 136 and the second controlled valve 146 closed Otherwise, readjust the pressure of the first air chamber 133 and the second air chamber 143 in the initial state A of the accumulator, and the first air chamber 133 and the second air chamber 143 in the state B when the controlled valve of the accumulator is opened The pressure of the first controlled valve 136 and the opening time of the second controlled valve 146, the closing time of the first controlled valve 136 and the second controlled valve 146 in the closed state C of the controlled valve of the accumulator, until the POGO curbs demand.

The POGO vibration suppression method provided by the embodiment of the present invention adopts the launch vehicle semi-regulating accumulator to suppress the POGO vibration, and the first controlled valve 136 can be used to adjust the connection state of the first air cavity 133 and the third air cavity 15, and the The second controlled valve 146 adjusts the connection state between the second air chamber 143 and the fourth air chamber 16 to adjust the PV value of the accumulator, so as to adjust the energy storage state of the accumulator according to the flight sequence, thereby better suppressing the rocket The purpose of POGO vibration is to improve the reliability and safety of the rocket. The launch vehicle semi-regulating pressure accumulator provided by the embodiment of the present invention can reduce the risk of failure caused by the POGO vibration of the liquid launch vehicle.

The above-described embodiments of the present invention may be implemented in various hardware, software codes, or a combination of both. For example, the embodiments of the present invention may also represent program codes for executing the above-described methods in a data signal processor. The present invention may also relate to various functions performed by computer processors, digital signal processors, microprocessors or field programmable gate arrays. The processors described above may be configured in accordance with the present invention to perform specific tasks by executing machine-readable software code or firmware code that defines the specific methods disclosed by the present invention. The software code or firmware code may be developed to represent different programming languages and different formats or forms. Software code can also be compiled to represent different target platforms. However, the different code styles, types and languages of software code and other types of configuration code to perform tasks in accordance with the present invention do not depart from the spirit and scope of the present invention.

The above descriptions are only illustrative specific embodiments of the present invention, without departing from the concept and principles of the present invention, any equivalent changes and modifications made by those skilled in the art shall belong to the present invention scope of protection.

Claims (10)

1. A launch vehicle semi-regulating pressure accumulator, characterized in that it comprises a four-way housing, and the four-way housing comprises a first connecting body, a second connecting body, a third connecting body and a fourth connecting body; along the axial direction of the first connecting body and the second connecting body, the interior of the four-way housing is a liquid cavity, and the liquid cavity forms a propellant conveying channel; Along the axis direction of the third connecting body and the fourth connecting body, the third connecting body is provided with a first air cavity, the fourth connecting body is provided with a second air cavity, and the liquid cavity is a propellant capable of changing the pressure in the first air chamber and the second air chamber; Along the direction perpendicular to the central axis of the first connecting body and the second connecting body and the central axis of the third connecting body and the fourth connecting body, two opposite outer walls of the four-way housing are correspondingly provided with Closed third air cavity and fourth air cavity; The first air cavity is communicated with the third air cavity, and the second air cavity is communicated with the fourth air cavity; a first controlled valve is arranged on the pipeline connecting the first air cavity and the third air cavity, so The first controlled valve is used to switch on and off the pipeline where it is located; the pipeline connecting the second air chamber and the fourth air chamber is provided with a second controlled valve, and the second controlled valve is used to switch on and off the pipeline in which it is located. 2 . The semi-regulating pressure accumulator for a launch vehicle according to claim 1 , wherein the third connecting body is provided with a first pushing mechanism, and the fourth connecting body is provided with a second pushing mechanism; 2 . One end of the third connecting body away from the center of the four-way housing is provided with a first end cap, and one end of the fourth connecting body away from the center of the four-way housing is provided with a second end cap; The pushing mechanism, the first end cap and the third connecting body together form a closed first air cavity, and the second pushing mechanism, the second end cap and the fourth connecting body together form a closed second air cavity. 3 . The semi-regulating pressure accumulator for a launch vehicle according to claim 1 , wherein the first air chamber is communicated with the third air chamber through a first communication pipe and a first connecting head, and the first air chamber is connected to the third air chamber. 4 . The second air chamber is communicated with the fourth air chamber through a second communication pipe and a second connection head; the first controlled valve is arranged on the first communication pipe, and the second controlled valve is arranged on the on the second connecting pipe. 4 . The semi-regulating pressure accumulator for a launch vehicle according to claim 2 , wherein the first push mechanism comprises a first push plate, a first diaphragm and a first guide rod, and the first push plate Together with the first end cover and the third connecting body, the closed first air cavity is formed, the first diaphragm is arranged in the first air cavity, and one end of the first diaphragm is connected to the first air cavity. The inner end face of the one end cover is connected, and the other end is connected with one end face of the first push plate; the other end face of the first push plate is connected with one end of the first guide rod. The other end extends into the liquid chamber. 5 . The semi-regulating pressure accumulator for a launch vehicle according to claim 4 , wherein, along the pushing direction of the first guide rod, a first circle is provided at the center of the inner end face of the first end cover. 6 . A cylinder, the first cylinder is used for limiting protection to the first diaphragm. 6 . The semi-regulating pressure accumulator for a launch vehicle according to claim 2 , wherein the second push mechanism comprises a second push plate, a second diaphragm and a second guide rod, and the second push plate The second air cavity is enclosed together with the second end cover and the fourth connecting body, the second diaphragm is arranged in the second air cavity, and one end of the second diaphragm is connected to the first air cavity. The inner end face of the two-end cover is connected, and the other end is connected with one end face of the second push plate; the other end face of the second push plate is connected with one end of the second guide rod. The other end extends into the liquid chamber. 7 . The semi-regulating pressure accumulator for a launch vehicle according to claim 6 , wherein, along the pushing direction of the second guide rod, a second circle is provided at the center of the inner end face of the second end cover. 8 . A cylinder, the second cylinder is used for limiting protection to the second diaphragm. 8 . The semi-regulating pressure accumulator for a launch vehicle according to claim 3 , wherein the first connecting head and the second connecting head adopt the same structure, and the first connecting head adopts a tee joint. 9 . 9 . The semi-regulating pressure accumulator for a launch vehicle according to claim 8 , wherein the two ends of the first connecting head are respectively connected to the first communication pipe and the third connecting body, respectively. 10 . The other end of the first connector is connected to the first inflation switch and the first manual valve; Two ends of the second connecting head are respectively connected with the second communication pipe and the fourth connecting body, and the other end of the second connecting head is connected with the second inflation switch and the second manual valve. 10. The launch vehicle semi-regulating pressure accumulator according to claim 1 or 2, wherein the launch vehicle semi-regulating pressure accumulator is used for POGO vibration suppression.

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