CN217396841U - Semi-adjustable pressure accumulator of carrier rocket - Google Patents
Semi-adjustable pressure accumulator of carrier rocket Download PDFInfo
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- CN217396841U CN217396841U CN202220539760.XU CN202220539760U CN217396841U CN 217396841 U CN217396841 U CN 217396841U CN 202220539760 U CN202220539760 U CN 202220539760U CN 217396841 U CN217396841 U CN 217396841U
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- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
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- Y02E60/16—Mechanical energy storage, e.g. flywheels or pressurised fluids
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Abstract
The utility model provides a carrier rocket semi-regulated accumulator, which comprises a four-way shell, wherein the four-way shell comprises a first connector, a second connector, a third connector, a fourth connector, a liquid cavity and a propellant conveying channel; along the axial direction of the third connector and the fourth connector, a first air cavity and a second air cavity are respectively and correspondingly arranged at the third connector and the fourth connector, and the propellant in the liquid cavity shape can change the pressure in the first air cavity and the second air cavity; a third air cavity and a fourth air cavity which are sealed are correspondingly arranged on the two opposite outer walls of the four-way shell along the direction vertical to the central axes of the first connecting body and the second connecting body and the central axes of the third connecting body and the fourth connecting body; the first air cavity is communicated with the third air cavity through a pipeline and a first controlled valve, and the second air cavity is communicated with the fourth air cavity through a pipeline and a second controlled valve. The utility model discloses half regulation formula accumulator's adaptability is good, and the suppression effect is obvious.
Description
Technical Field
The utility model belongs to the aerospace field, concretely relates to carrier rocket semi-regulated accumulator.
Background
POGO vibration is longitudinal self-excited divergent vibration generated by coupling a rocket body structure and a propellant conveying system of a large liquid carrier rocket in flight. It is believed that the POGO vibrations are caused by the natural frequencies of longitudinal vibration of the liquid launch vehicle structure and the natural frequencies of vibration of the propellant delivery system being close to or equal to each other during flight. Under the condition of not inhibiting, POGO vibration can cause serious damage to an arrow body structure, the service life of an arrow instrument and a satellite is shortened, and even the life safety of astronauts is endangered.
At present, POGO inhibition is realized by changing the natural frequency of a system mainly by installing a pressure accumulator on a propellant conveying system at home and abroad. However, conventional accumulator accumulators are essentially constant, i.e. the product PV of pressure and volume is constant. Therefore, the traditional pressure accumulator has poor adaptability under the condition that the dynamic characteristic change of the carrier rocket is complex, and the inhibiting effect is not ideal.
Disclosure of Invention
To overcome problems in the related art at least to some extent, the present invention provides a semi-regulated pressure accumulator for a launch vehicle.
According to an embodiment of the present invention, the present invention provides a semi-regulated accumulator for a launch vehicle, comprising a four-way housing, said four-way housing comprising a first connector, a second connector, a third connector and a fourth connector;
along the axial direction of the first connecting body and the second connecting body, a liquid cavity is formed inside the four-way shell, and a propellant conveying channel is formed in the liquid cavity;
along the axial direction of a third connector and a fourth connector, a first air cavity is arranged at the third connector, a second air cavity is arranged at the fourth connector, and a propellant in the liquid cavity can change the pressure in the first air cavity and the second air cavity;
a third air cavity and a fourth air cavity which are sealed are correspondingly arranged on the two opposite outer walls of the four-way shell along the direction vertical to the central axes of the first connecting body and the second connecting body and the central axes of the third connecting body and the fourth connecting body;
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 a pipeline through which the first air cavity is communicated with the third air cavity and used for switching on and off the pipeline where the first controlled valve is arranged; and a second controlled valve is arranged on a pipeline for communicating the second air cavity with the fourth air cavity and is used for switching on and off the pipeline where the second controlled valve is arranged.
In the carrier rocket semi-regulated pressure accumulator, a first pushing mechanism is arranged in the third connecting body, and a second pushing mechanism is arranged in the fourth connecting body; a first end cover is arranged at one end, far away from the center of the four-way shell, of the third connecting body, and a second end cover is arranged at one end, far away from the center of the four-way shell, of the fourth connecting body; the first pushing mechanism, the first end cover and the third connecting body enclose a first closed air cavity together, and the second pushing mechanism, the second end cover and the fourth connecting body enclose a second closed air cavity together.
In the semi-regulated pressure accumulator of the carrier rocket, the first air cavity is communicated with the third air cavity through a first communicating pipe and a first connector, and the second air cavity is communicated with the fourth air cavity through a second communicating pipe and a second connector; the first controlled valve is arranged on the first communicating pipe, and the second controlled valve is arranged on the second communicating pipe.
Further, the first pushing mechanism comprises a first pushing plate, a first membrane and a first guide rod, the first pushing plate, a first end cover and a third connecting body jointly enclose a closed first air cavity, the first membrane is arranged in the first air cavity, one end of the first membrane is connected with the inner end face of the first end cover, and the other end of the first membrane is connected with one end face of the first pushing plate; the other end face of the first push plate is connected with one end of the first guide rod, and the other end of the first guide rod extends into the liquid cavity.
Furthermore, a first cylinder is arranged at the center of the inner end face of the first end cover along the pushing direction of the first guide rod, and the first cylinder is used for limiting and protecting the first membrane.
Further, the second pushing mechanism comprises a second pushing plate, a second membrane and a second guide rod, the second pushing plate, a second end cover and a fourth connecting body jointly enclose a closed second air cavity, the second membrane is arranged in the second air cavity, one end of the second membrane is connected with the inner end face of the second end cover, and the other end of the second membrane is connected with one end face of the second pushing plate; the other end face of the second push plate is connected with one end of the second guide rod, and the other end of the second guide rod extends into the liquid cavity.
Furthermore, a second cylinder is arranged at the center of the inner end face of the second end cover along the pushing direction of the second guide rod, and the second cylinder is used for limiting and protecting the second diaphragm.
Furthermore, the first connector and the second connector are of the same structure, and the first connector is a tee connector.
Furthermore, two ends of the first connecting head are respectively and correspondingly connected with the first connecting 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;
the two ends of the second connector correspond to the second communicating pipe and are connected with the fourth connector respectively, and the other end of the second connector is connected with the second inflation switch and the second manual valve.
In the semi-regulated pressure accumulator for a launch vehicle, the semi-regulated pressure accumulator for a launch vehicle is used for POGO vibration suppression.
According to the above embodiments of the present invention, at least the following advantages are obtained: the utility model provides a half regulation formula accumulator of carrier rocket utilizes the connection state of first air cavity of first controlled valve adjustment and third air cavity, utilizes the connection state of second controlled valve adjustment second air cavity and fourth air cavity to the PV value of adjustment accumulator, and then more nimble high-efficient POGO that restraines vibrates, the utility model provides a half regulation formula accumulator flexibility of carrier rocket and strong adaptability can reduce the POGO vibration of liquid carrier rocket and lead to the risk of losing favor.
Additionally, the utility model provides an among the semi-regulated accumulator of carrier rocket, set up the same air cavity valve connection structure between first air cavity and third air cavity and between second air cavity and the fourth air cavity, can be each other redundant, after one of them set of air cavity valve connection structure became invalid, another set of air cavity valve connection structure still had certain POGO vibration suppression ability, can improve the reliability of system.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention, as claimed.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of the specification of the invention, illustrate embodiments of the invention and together with the description, serve to explain the principles of the invention.
Fig. 1 is a schematic structural diagram of a four-way housing in a semi-regulated accumulator of a carrier rocket according to an embodiment of the present invention.
Fig. 2 is a schematic structural diagram of a semi-regulated accumulator of a carrier rocket according to an embodiment of the present invention.
Description of reference numerals:
1. a four-way housing; 11. a first connecting body; 12. a second connector;
13. a third connector;
131. a first pushing mechanism; 1311. a first push plate; 1312. a first diaphragm; 1313. a first guide bar;
132. a first end cap; 1321. a first cylinder;
133. a first air cavity; 134. a first communication pipe; 135. a first connector; 136. a first controlled valve; 137. a first inflation switch; 138. a first manual valve;
14. a fourth connector;
141. a second pushing mechanism; 1411. a second push plate; 1412. a second diaphragm; 1413. a second guide bar;
142. a second end cap; 1421. a second cylinder;
143. a second air cavity; 144. a second communicating pipe; 145. a second connector; 146. a second controlled valve; 147. a second inflation switch; 148. a second manual valve;
15. a third air cavity; 16. a fourth air cavity;
2. a fluid chamber.
Detailed Description
To make the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the spirit of the present invention will be described in detail with reference to the accompanying drawings, and any person skilled in the art can change or modify the techniques taught by the present invention without departing from the spirit and scope of the present invention after understanding the embodiments of the present invention.
The exemplary embodiments and descriptions of the present invention are provided to explain the present invention, but not to limit the present invention. Additionally, the same or similar numbered elements/components used in the drawings and the embodiments are used to represent the same or similar parts.
As used herein, the terms "first," "second," …, etc. do not denote any order or sequential importance, nor are they used to limit the invention, but rather are used to distinguish one element from another or from another element or operation described in the same technical language.
As used herein, the terms "comprising," "including," "having," "containing," and the like are open-ended terms that mean including, but not limited to.
As used herein, "and/or" includes any and all combinations of the described items.
References to "plurality" herein include "two" and "more than two"; reference to "multiple sets" herein includes "two sets" and "more than two sets".
Certain words used to describe the invention are discussed below or elsewhere in this specification to provide additional guidance to those skilled in the art in describing the invention.
The PV value of the accumulator is closely related to the POGO vibration suppression capability, and the POGO vibration suppression effect of the accumulator is related to the structural dynamics (such as frequency, vibration mode, damping and the like) of the rocket. The accumulator with the fixed PV value cannot adapt to the large change of the dynamic characteristics of the liquid rocket well, so that POGO easily vibrates greatly and even fails to launch the carrier rocket.
As shown in fig. 1 and 2, the present invention provides a semi-regulated pressure accumulator for a launch vehicle, which includes a four-way housing 1, wherein the four-way housing 1 includes a first connecting body 11, a second connecting body 12, a third connecting body 13 and a fourth connecting body 14.
Along the axial direction of the first connecting body 11 and the second connecting body 12, a liquid chamber 2 is formed inside the four-way housing 1, and the liquid chamber 2 forms a propellant feed channel. The first connecting body 11 forming part of the liquid chamber 2 is connected to the propellant tank via an upstream feed line and the second connecting body 12 forming part of the liquid chamber 2 is connected to the engine via a downstream line.
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 and second air chambers 133 and 143.
And a third air cavity 15 and a fourth air cavity 16 which are closed are correspondingly arranged on two opposite outer walls of the four-way shell 1 along the direction vertical 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. The first air chamber 133 communicates with the third air chamber 15 through the first communication pipe 134 and the first connector 135, and the second air chamber 143 communicates with the fourth air chamber 16 through the second communication pipe 144 and the second connector 145. The first communication pipe 134 is provided with a first controlled valve 136, and the first controlled valve 136 is used for switching on and off the first communication pipe 134. A second controlled valve 146 is disposed on the second communication pipe 144, and the second controlled valve 146 is used for opening and closing the second communication pipe 144.
In the above-described embodiment, the first pushing mechanism 131 is provided in the third link body 13, and the second pushing mechanism 141 is provided in the fourth link body 14. The end of the third connecting body 13 away from the center of the four-way housing 1 is provided with a first end cap 132, and the end of the fourth connecting body 14 away from the center of the four-way housing 1 is provided with a second end cap 142. The first pushing mechanism 131, the first end cap 132 and the third connecting body 13 together enclose a closed first air cavity 133, and the second pushing mechanism 141, the second end cap 142 and the fourth connecting body 14 together enclose a closed second air cavity 143. The propellant in the liquid chamber 2 may interact with the first and second urging mechanisms 131 and 141 to change the pressure in the first and second air chambers 133 and 143.
The embodiment of the utility model provides a before the semi-regulated accumulator of carrier rocket uses, according to the dynamic characteristic of carrier rocket flight, all carry out the helium to first air cavity 133, second air cavity 143, third air cavity 15 and fourth air cavity 16 and pressurize. When in use, the first controlled valve 136 can be controlled to be opened or closed according to the flight sequence of the carrier rocket, so that the first air cavity 133 is communicated or separated with the third air cavity 15; and controlling the second controlled valve 146 to be opened or closed so as to enable the second air chamber 143 to be communicated with or separated from the fourth air chamber 16, so that the PV value of the semi-regulated accumulator can be adjusted, and the vibration of the POGO can be restrained.
The embodiment of the utility model provides an among the semi-regulated accumulator of carrier rocket, set up the same air cavity valve connection structure between first air cavity 133 and third air cavity 15 and between second air cavity 143 and fourth air cavity 16, can be each other redundant, after one of them set of air cavity valve connection structure became invalid, another set of air cavity valve connection structure still has certain POGO vibration suppression ability, can improve the reliability of system.
In the above embodiment, the first pushing mechanism 131 and the second pushing mechanism 141 adopt the same structural form.
The first pushing mechanism 131 includes a first pushing plate 1311, a first membrane 1312 and a first guide 1313, wherein the first pushing plate 1311, the first end cap 132 and the third connecting body 13 together enclose a closed first air cavity 133, the first membrane 1312 is disposed in the first air cavity 133, one end of the first membrane 1312 is connected to an inner end face of the first end cap 132, and the other end of the first membrane 1312 is connected to an end face of the first pushing plate 1311. The other end surface of the first push plate 1311 is connected to one end of a first guide 1313, and the other end of the first guide 1313 extends into the liquid chamber 2. The first membrane 1312 may be connected to the first end cap 132 and the first push plate 1311 by welding. One end of the first membrane 1312 is welded to the inner end surface of the first end cap 132 in a ring shape, and the other end of the first membrane 1312 is welded to one end surface of the first push plate 1311 in a ring shape.
The second pushing mechanism 141 includes a second pushing plate 1411, a second diaphragm 1412 and a second guide rod 1413, wherein the second pushing plate 1411, the second end cap 142 and the fourth connecting body 14 together enclose a closed second air cavity 143, the second diaphragm 1412 is disposed in the second air cavity 143, one end of the second diaphragm 1412 is connected to an inner end surface of the second end cap 142, and the other end of the second diaphragm 1412 is connected to an end surface of the second pushing plate 1411. The other end surface of the second push plate 1411 is connected with one end of a second guide rod 1413, and the other end of the second guide rod 1413 extends into the liquid cavity 2. The connection between the second diaphragm 1412 and the second end cap 142 and the second push plate 1411 may be welding. One end of the second membrane 1412 is annularly welded to the inner end surface of the second end cap 142, and the other end of the second membrane 1412 is annularly welded to one end surface of the second push plate 1411.
When the pressure in the liquid chamber 2 is higher 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, the volume of the first air chamber 133 is reduced, and the gas in the first air chamber 133 is compressed; when the pressure in the liquid cavity 2 is lower than the pressure in the first air cavity 133, the air in the first air cavity 133 pushes the first diaphragm 1312, and the first push plate 1311 and the first guide 1313 are pushed by the first diaphragm 1312 to move towards the liquid cavity 2; thereby realizing the principle of the diaphragm type cylinder.
Similarly, when the pressure in the liquid chamber 2 is higher than the pressure in the second gas 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, the volume of the second gas chamber 143 is reduced, and the gas in the second gas chamber 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, and the second push plate 1411 and the second guide rod 1413 are pushed by the second diaphragm 1412 to move towards the liquid cavity 2; thereby realizing the principle of the diaphragm type cylinder.
In the above embodiment, the first cylinder 1321 is provided at the center of the inner end surface of the first end cap 132 in the pushing direction of the first guide 1313. A second cylinder 1421 is provided at the center of the inner end surface of the second end cap 142 in the pushing direction of the second guide bar 1413. The first cylinder 1321 is used for position protection of the first membrane 1312 when the propellant in the liquid chamber 2 pushes the first membrane 1312 to move towards the first end cap 132 through the first guide rod 1313 and the first push plate 1311, and the first membrane 1312 can be buffered by entering the cylinder cavity of the first cylinder 1321 to prevent crushing.
When the propellant in the liquid chamber 2 pushes the second diaphragm 1412 to move towards the second end cap 142 through the second guide rod 1413 and the second push plate 1411, the second cylinder 1421 is used for limiting and protecting the second diaphragm 1412, and the second diaphragm 1412 can enter the cylinder cavity of the second cylinder 1421 for buffering to prevent crushing.
In the above embodiment, the first connector 135 and the second connector 145 have the same structure, and a three-way connector may be used.
When the first connection joint 135 is a three-way joint, two ends of the first connection joint 135 are respectively connected to the first connection pipe 134 and the first end cap 132 of the third connection body 13, the other end of the first connection joint 135 is connected to the first inflation switch 137 and the first manual valve 138, and the first inflation switch 137 and the first manual valve 138 are opened to pressurize the first air cavity 133.
When the second connector 145 is a three-way connector, two ends of the second connector 145 are respectively connected to the second connection pipe 144 and the second end cap 142 of the fourth connector 14, the other end of the second connector 145 is connected to the second inflation switch 147 and the second manual valve 148, and the second inflation switch 147 and the second manual valve 148 are opened to inflate the second air chamber 143.
In the above embodiment, by improving the structural form of the controlled valve, the purpose of adapting to different environmental requirements can be achieved. Specifically, to meet the use requirement in the normal temperature environment, the first controlled valve 136 and the second controlled valve 146 may both adopt solenoid valves. To meet the use requirement in a low temperature environment, the first controlled valve 136 and the second controlled valve 146 may be pneumatic valves.
Based on the embodiment of the utility model provides a half regulation formula accumulator of carrier rocket, the embodiment of the utility model provides a POGO vibration suppression method is still provided, it includes following step:
and S1, installing a carrier rocket semi-regulated pressure accumulator on the propellant conveying system.
S2, dividing the flight sequence of the carrier rocket into an early stage, a middle stage and a later stage, and determining the PV value of the accumulator required by the three stages for restraining the POGO vibration according to the rocket dynamics characteristics. Wherein the former stage corresponds to an initial state A of the accumulator, and the PV value of the accumulator required by the former state is P 0 V 0 (ii) a The medium term corresponds to the controlled valve open state B of the accumulator, which requires the PV value of the accumulator to be P 1 V 1 (ii) a A later stage corresponding to a controlled valve closing state C of the accumulator requiring a PV value P of the accumulator 2 V 2 。
S3, adjusting the energy storage state of the accumulator according to the flight time sequence of the carrier rocket, which comprises the following steps:
s31, in the initial state A of the accumulator, adjusting the pressure of the first air cavity 133 according to the volume of the first air cavity 133 and adjusting the pressure of the second air cavity 143 according to the volume of the second air cavity 143, so that the sum of the product of the pressure and the volume of the first air cavity 133 and the product of the pressure and the volume of the second air cavity 143 satisfies the PV value P of the accumulator required by the initial state A of the accumulator 0 V 0 Namely:
P 0 V 0 ＝2*P m0 *V m0 (1)
in the formula (1), P m0 To representPressure, V, of the first air chamber 133 m0 Indicating the volume of the first air chamber 133.
It should be noted that the first air chamber 133 and the second air chamber 143 have the same structure, and the pressure and volume are the same, so P m0 Or the pressure, V, of the second air chamber 143 m0 The volume of the second air chamber 143 can also be expressed.
S32, in the opening state B of the controlled valve of the pressure accumulator, the first air cavity 133 is communicated with the third air cavity 15, the second air cavity 143 is communicated with the fourth air cavity 16, the pressure of the third air cavity 15 is adjusted according to the volume of the first air cavity 133 and the volume of the third air cavity 15, and the pressure of the fourth air cavity 16 is adjusted according to the volume of the second air cavity 143 and the volume of the fourth air cavity 16, so that the sum of the product of the pressure and the volume of the first air cavity 133, the product of the pressure and the volume of the second air cavity 143, the product of the pressure and the volume of the third air cavity 15 and the product of the pressure and the volume of the fourth air cavity 16 satisfies the PV value P of the pressure accumulator required by the opening state B of the controlled valve of the pressure accumulator 1 V 1 Namely:
P 1 V 1 ＝2*(P m0 *V m0 +P q0 *V q0 ) (2)
in formula (2), P q0 Indicating the pressure, V, of the third air chamber 15 q0 Indicating the volume of the third air chamber 15.
It should be noted that the third air chamber 15 and the fourth air chamber 16 have the same structure, and the pressure and the volume of the third air chamber and the fourth air chamber are also the same, so that P is the same q0 Or the pressure, V, of fourth air chamber 16 q0 The volume of fourth air chamber 16 may also be indicated.
S33, in the controlled valve closing state C 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 PV value P of the accumulator required in the controlled valve closing state C of the accumulator 2 V 2 Comprises the following steps:
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 launch vehicle flight sequence is in the middle stageFirst, the PV value P of the accumulator under the current state is determined 1 V 1 Whether the POGO suppression demand is met, and if so, maintaining the open state of the first and second controlled valves 136, 146; otherwise, control closes first controlled valve 136 and second controlled valve 146.
When the flight time sequence of the carrier rocket is in the later stage, the PV value P of the accumulator in the current state is firstly judged 2 V 2 Whether the POGO suppression requirement is met, and if so, maintaining the closed state of the first and second controlled valves 136, 146; otherwise, the pressures of the first and second air chambers 133 and 143 in the initial state a of the accumulator, the pressures of the first and second air chambers 133 and 143 in the controlled valve open state B of the accumulator, and the opening times of the first and second controlled valves 136 and 146, and the closing times of the first and second controlled valves 136 and 146 in the controlled valve closed state C of the accumulator are readjusted until the POGO suppression demand is satisfied.
The embodiment of the utility model provides a POGO vibration suppression method adopts the semi-adjustable formula accumulator of carrier rocket to carry out POGO vibration suppression, can utilize the connection state of first air cavity 133 of first controlled valve 136 adjustment and third air cavity 15, utilize the connection state of second controlled valve 146 adjustment second air cavity 143 and fourth air cavity 16, with the PV value of adjustment accumulator, reach the energy storage state according to flight sequential adjustment accumulator, and then better suppression rocket POGO vibration, improve the reliability of rocket and the purpose of security. The embodiment of the utility model provides a semi-regulated accumulator of carrier rocket can reduce the risk that the POGO vibration of liquid carrier rocket leads to losing benefit.
The embodiments of the present invention described above may be implemented in various hardware, software code, or a combination of both. For example, embodiments of the present invention may also represent program code for performing the above-described methods in a data signal processor. The present invention may also relate to a variety of functions performed by a computer processor, digital signal processor, microprocessor, or field programmable gate array. The processor described above may be configured in accordance with the present invention to perform certain tasks by executing machine readable software code or firmware code that defines certain methods disclosed herein. Software code or firmware code may be developed to represent different programming languages and different formats or forms. Different target platforms may also be represented to compile the software code. However, different code styles, types, and languages of software code and other types of configuration code in accordance with the present invention to perform tasks do not depart from the spirit and scope of the present invention.
The foregoing is only an illustrative embodiment of the present invention, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principles of the present invention should fall within the protection scope of the present invention.
Claims (10)
1. A semi-adjustable pressure accumulator of a carrier rocket is characterized by comprising a four-way shell, wherein the four-way shell 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, a liquid cavity is formed inside the four-way shell, and a propellant conveying channel is formed by the liquid cavity;
along the axial direction of a third connector and a fourth connector, a first air cavity is arranged at the third connector, a second air cavity is arranged at the fourth connector, and a propellant in the liquid cavity can change the pressure in the first air cavity and the second air cavity;
a third air cavity and a fourth air cavity which are sealed are correspondingly arranged on the two opposite outer walls of the four-way shell along the direction vertical to the central axes of the first connecting body and the second connecting body and the central axes of the third connecting body and the fourth connecting body;
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 a pipeline through which the first air cavity is communicated with the third air cavity and is used for switching on and off the pipeline where the first controlled valve is arranged; and a second controlled valve is arranged on a pipeline for communicating the second air cavity with the fourth air cavity and is used for switching on and off the pipeline where the second controlled valve is arranged.
2. A launch vehicle semi-regulated accumulator according to claim 1, wherein said third interface has a first pushing mechanism disposed therein and said fourth interface has a second pushing mechanism disposed therein; a first end cover is arranged at one end, far away from the center of the four-way shell, of the third connecting body, and a second end cover is arranged at one end, far away from the center of the four-way shell, of the fourth connecting body; the first pushing mechanism, the first end cover and the third connecting body enclose a first closed air cavity together, and the second pushing mechanism, the second end cover and the fourth connecting body enclose a second closed air cavity together.
3. The semi-regulated pressure accumulator of a launch vehicle of claim 1 wherein the first air chamber is in communication with the third air chamber through a first communication tube and a first connector, and the second air chamber is in communication with the fourth air chamber through a second communication tube and a second connector; the first controlled valve is arranged on the first communicating pipe, and the second controlled valve is arranged on the second communicating pipe.
4. The semi-regulated pressure accumulator of a launch vehicle of claim 2, wherein the first pushing mechanism comprises a first pushing plate, a first membrane and a first guide rod, the first pushing plate, a first end cap and a third connecting body together form the closed first air cavity, the first membrane is arranged in the first air cavity, one end of the first membrane is connected with an inner end face of the first end cap, and the other end of the first membrane is connected with one end face of the first pushing plate; the other end face of the first push plate is connected with one end of the first guide rod, and the other end of the first guide rod extends into the liquid cavity.
5. A launch vehicle semi-regulated accumulator according to claim 4, characterized in that a first cylinder is provided centrally of the inner end surface of said first end cap in the pushing direction of said first guide rod, said first cylinder being used for position limiting protection of said first diaphragm.
6. The semi-regulated pressure accumulator of a launch vehicle of claim 2, wherein the second pushing mechanism comprises a second pushing plate, a second membrane and a second guide rod, the second pushing plate, a second end cap and a fourth connecting body together enclose the second closed air cavity, the second membrane is disposed in the second air cavity, one end of the second membrane is connected with an inner end face of the second end cap, and the other end of the second membrane is connected with one end face of the second pushing plate; the other end face of the second push plate is connected with one end of the second guide rod, and the other end of the second guide rod extends into the liquid cavity.
7. The launch vehicle semi-regulated accumulator of claim 6 wherein a second cylinder is centrally disposed on an inner end surface of said second end cap in a direction of pushing of said second guide rod, said second cylinder for position limiting protection of said second diaphragm.
8. A launch vehicle semi-regulated accumulator according to claim 3 wherein said first and second joints are of identical construction, said first joint being a tee joint.
9. The semi-regulated pressure accumulator of claim 8, wherein two ends of the first connecting joint are respectively connected to the first connecting pipe and the third connecting joint, and the other end of the first connecting joint is connected to the first inflation switch and the first manual valve;
wherein both ends of the second connector respectively correspond with the second communicating pipe and the fourth connector are connected, and the other end of the second connector is connected with the second inflation switch and the second manual valve.
10. A launch vehicle semi-regulated accumulator according to claim 1 or 2, wherein said launch vehicle semi-regulated accumulator is used for POGO vibration suppression.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220539760.XU CN217396841U (en) | 2022-03-14 | 2022-03-14 | Semi-adjustable pressure accumulator of carrier rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220539760.XU CN217396841U (en) | 2022-03-14 | 2022-03-14 | Semi-adjustable pressure accumulator of carrier rocket |
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