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CN-122014458-A - Storage tank steady flow device of liquid rocket and parameter determination method

CN122014458ACN 122014458 ACN122014458 ACN 122014458ACN-122014458-A

Abstract

The invention provides storage tank flow stabilizing equipment and a parameter determining method of a liquid rocket, wherein the storage tank flow stabilizing equipment comprises a first flow stabilizing device and a second flow stabilizing device, the first flow stabilizing device comprises a filter screen, a filter screen framework, a collapse preventing plate and fins, the second flow stabilizing device comprises a circular ring and a cross baffle, the circular ring is used for inhibiting liquid from shaking greatly caused by acceleration change in the rocket flight process, the cross baffle is used for dividing a flow field of liquid at the bottom of a tank, when the liquid level in the storage tank is reduced, the collapse preventing plate is used for preventing the liquid level from partially collapsing, and the fins are used for scattering residual vortex of the cross baffle reaching an outlet area. By reasonable layout of all the components, the problems of rotation, shaking, collapse and the like of the propellant in the storage tank of the liquid rocket are reduced, continuous and reliable supply of the propellant in the storage tank is ensured, the installation efficiency is improved, and the installation difficulty is reduced.

Inventors

  • WANG XIONGYU
  • ZHANG YANG
  • XU CHUANG
  • SHANG HAILONG

Assignees

  • 河南航宇火箭有限公司

Dates

Publication Date
20260512
Application Date
20260213

Claims (10)

  1. 1. A tank stabilizer for a liquid rocket, comprising: The first flow stabilizer is fixedly connected with the bottom of the storage tank, and the bottom of the storage tank is an ellipsoidal bottom (1); the second flow stabilizing device is far away from the target distance of the first flow stabilizing device and is fixedly connected with the inner surface of the storage tank; Wherein, first current stabilizer includes: A filter screen; the filter screen framework (10) is arranged at the bottom of the storage tank and connected with the filter screen, and the filter screen framework (10) is used for providing rigid support for the filter screen; the anti-collapse plate (6) is connected with the filter screen framework (10), and the anti-collapse plate (6) extends out of the filter screen framework (10); a fin (9) fixedly connected with the collapse prevention plate (6); wherein, the second current stabilizer includes: a circular ring (2) connected with the inner surface of the storage tank; A cross baffle (3) connected with the circular ring (2); In the rocket flying process, the circular ring (2) is used for inhibiting liquid from shaking greatly caused by acceleration change, the cross baffle (3) is used for dividing a flow field of liquid at the bottom of the tank, breaking the rotary flow of the liquid to enable the liquid to flow to a central outlet stably, the collapse preventing plate (6) is used for preventing the liquid level from collapsing locally when the liquid level in the storage tank is lowered, and the fins (9) are used for scattering residual vortexes of the cross baffle (3) reaching an outlet area to realize the non-swirling outflow.
  2. 2. A tank stabilizer for a liquid rocket as recited in claim 1, wherein the tank bottom further comprises: and the adding and discharging port flange (8) is arranged at one side far away from the first flow stabilizer and the second flow stabilizer, and the adding and discharging port flange (8) is used for adding the propellant before rocket launching and discharging the propellant after task stopping or testing.
  3. 3. A tank stabilizer for a liquid rocket as recited in claim 1, wherein the tank bottom further comprises: and the outflow port flange (7) is fixedly connected with the filter screen framework, and the outflow port flange (7) is used for connecting a sealing interface of the storage tank and an engine conveying pipeline.
  4. 4. The tank flow stabilizing device of the liquid rocket according to claim 1, wherein the filter screen framework (10) comprises integrally formed support posts and a base, the support posts are vertically arranged at the edge of the base, and the filter screen is fixedly connected between two adjacent support posts.
  5. 5. A tank stabilizer for a liquid rocket as recited in claim 1, wherein the tank bottom further comprises: an adapter flange (5) of the tunnel pipe fixedly connected with the tank bottom of the tank; and the tunnel pipe assembly (4) is fixedly connected with the top of the adapter flange (5), and the tunnel pipe assembly (4) is used for providing a sealing channel penetrating through the bottom of the box for the sensor cable and the pressurizing pipeline in the box.
  6. 6. A tank flow stabilizing device for liquid rockets according to claim 1, wherein the circular ring (2) comprises a plurality of 1/4 rings with the same size, two adjacent 1/4 rings are connected through corner pieces in a screwed mode, and the circular ring (2) is fixedly connected with the cross partition plate (3) through the corner pieces.
  7. 7. A tank flow stabilizing device for liquid rockets according to claim 1, wherein the cross partition plate (3) comprises a plurality of partition plates which are mutually perpendicular and fixedly connected, a plurality of holes are uniformly distributed on each partition plate, and the front end of each partition plate is attached to the inner surface of the tank.
  8. 8. A method for determining parameters of a tank flow stabilizer device of a liquid rocket, wherein the method is applied to the tank flow stabilizer device of the liquid rocket according to any one of claims 1 to 7, and comprises the steps of: Obtaining structural parameters and outflow performance constraint data of a target storage tank, wherein the structural parameters comprise ellipsoidal geometric dimensions of the bottom of the storage tank, the outer diameter of a filter screen framework (10) and the outline diameter of a cross partition plate (3), and the outflow performance constraint data comprise the lowest working liquid level, the allowed maximum outflow air clamping rate and the allowed additional pressure drop of a system; Determining a current stabilizing device parameter processing model and an optimization variable according to the structural parameter, wherein the optimization variable is the axial distance between the center of the first current stabilizing device and the center of the second current stabilizing device; extracting the optimization variable in a preset value interval according to the lowest working liquid level in the outflow performance constraint data to obtain a plurality of candidate distance values Inputting the candidate distance values into the steady flow equipment parameter processing model, and performing transient two-phase flow simulation processing to obtain a flow field data set; Extracting the flow field data set to obtain system performance evaluation indexes corresponding to each candidate distance value, wherein the system performance evaluation indexes comprise an air inclusion risk index representing air inclusion risk, a liquid level stability index representing liquid level stability and a vortex suppression index in a region of the cross partition board (3); And determining a total objective function according to the system performance evaluation index and the outflow performance constraint data, and determining an optimal objective distance between the first current stabilizer and the second current stabilizer from the plurality of candidate distance values by taking a value minimizing the total objective function as an optimization target.
  9. 9. A method for determining parameters of tank flow stabilizing equipment of a liquid rocket as claimed in claim 8, wherein, The calculation formula of the air inclusion risk index is as follows: ; Wherein, the Represents the risk index of the air inclusion, The start time of the simulation is indicated, The termination time of the simulation is indicated, The gas volume fraction of the outlet at time t is indicated, Representing a series of candidate values of the optimization variable L in a preset value interval [ L_min, L_max ]; the calculation formula of the liquid level stability index is as follows: ; Wherein, the Indicating the index of the stability of the liquid level, Representing the lowest liquid level on the axis of the storage tank at the time t; the calculation formula of the vortex suppression index is as follows: ; Wherein, the The vortex suppression index is indicated by the expression, Representing the spatial point at time t The vortex quantity at the position is calculated, Indicating the region of the fluid space in the vicinity of the preset cross baffle (3).
  10. 10. The method for determining parameters of tank flow stabilizing equipment of liquid rocket as recited in claim 8, wherein the expression of the total objective function is: ; Wherein, the As a function of the overall objective function, 、 、 The weight coefficient is represented by a number of weight coefficients, Indicating a measure of the total volume of gas entering the pipe during the whole outflow at a distance L _ i, A normalized reference baseline representing an air entrainment risk indicator, Indicating the height of the lowest point of the liquid surface occurring during the whole outflow at a distance L _ i, A normalized reference datum representing a level indicator, Represents the measure of the rotational intensity of the most intense vortices which occur in the region of the cross baffle (3) at a distance L_i, A normalized reference datum representing a vortex intensity index.

Description

Storage tank steady flow device of liquid rocket and parameter determination method Technical Field The invention relates to the technical field of spacecraft design, and also relates to a storage tank steady flow device of a liquid rocket and a parameter determination method. Background During rocket flight, the propellant is in a liquid free state in the storage tank. Under the influence of flight load, the propellant can generate shaking, swirling, liquid level collapse and other states which are unfavorable for the normal operation of the engine. In order to ensure continuous and reliable supply of the propellant, the proper design of the tank bottom is required for ensuring the normal operation of the engine. Most of the existing storage tank bottoms adopting ellipsoidal bottoms are formed by splicing and welding a top cover and melon petals, but the structure has relatively low volumetric efficiency and is unfavorable for rocket weight reduction design and the like. Disclosure of Invention The invention aims to solve the technical problem of providing a storage tank steady flow device and a parameter determination method of a liquid rocket so as to ensure continuous and reliable supply of propellant in a storage tank. In order to solve the technical problems, the technical scheme of the invention is as follows: a tank stabilizer for a liquid rocket, comprising: the first flow stabilizer is fixedly connected with the bottom of the storage tank, and the bottom of the storage tank is an ellipsoidal bottom; the second flow stabilizing device is far away from the target distance of the first flow stabilizing device and is fixedly connected with the inner surface of the storage tank; Wherein, first current stabilizer includes: A filter screen; The filter screen framework is arranged at the bottom of the storage tank and connected with the filter screen, and is used for providing rigid support for the filter screen; the anti-collapse plate is connected with the filter screen framework and extends out of the filter screen framework; Fins fixedly connected with the collapse prevention plates; wherein, the second current stabilizer includes: a circular ring connected with the inner surface of the storage tank; a cross baffle connected with the circular ring; The annular ring is used for inhibiting liquid from shaking greatly caused by acceleration change in the rocket flight process, the cross baffle is used for dividing a flow field of liquid at the bottom of the tank, breaking the rotary flow of the liquid and enabling the liquid to flow to the central outlet stably, the collapse prevention plate is used for preventing the liquid level from collapsing locally when the liquid level in the storage tank is lowered, and the fins are used for scattering residual vortex of the cross baffle reaching the outlet area to realize the non-rotation of outflow. Optionally, the tank bottom further comprises: And the leakage adding flange is arranged at one side far away from the first flow stabilizer and the second flow stabilizer, and is used for adding the propellant before rocket launching and discharging the propellant after the task is stopped or tested. Optionally, the tank bottom further comprises: And the outflow port flange 7 is used for connecting a sealing interface of the storage tank and an engine conveying pipeline. Optionally, the filter screen framework comprises integrally formed support posts and a base, wherein the support posts are vertically arranged at the edge of the base, and the filter screen is fixedly connected between two adjacent support posts. Optionally, the tank bottom further comprises: an adapter flange of a tunnel pipe fixedly connected with the tank bottom of the tank; And the tunnel pipe assembly is fixedly connected with the top of the adapter flange and is used for providing a sealing channel penetrating through the bottom of the box for the sensor cable and the pressurizing pipeline in the box. Optionally, the ring includes a plurality of 1/4 rings of equidimension, connects through the angle piece spiro union between two adjacent 1/4 rings, the ring passes through the angle piece with cross baffle fixed connection. Optionally, the cross baffle includes a plurality of mutually perpendicular and fixed connection's baffle, and evenly distributed has a plurality of holes on every baffle, the front end of baffle with the laminating of the internal surface of storage tank. A method for determining parameters of tank steady-flow equipment of a liquid rocket is applied to the tank steady-flow equipment of the liquid rocket, and comprises the following steps: Obtaining structural parameters and outflow performance constraint data of a target storage tank, wherein the structural parameters comprise ellipsoidal geometric dimensions of the bottom of the storage tank, the outer diameter of a filter screen framework and the outer diameter of a cross partition plate; Determining a current stabilizi