CN115059559B - Valve capable of accurately regulating and controlling thrust of solid rocket engine - Google Patents
Valve capable of accurately regulating and controlling thrust of solid rocket engine Download PDFInfo
- Publication number
- CN115059559B CN115059559B CN202210881818.3A CN202210881818A CN115059559B CN 115059559 B CN115059559 B CN 115059559B CN 202210881818 A CN202210881818 A CN 202210881818A CN 115059559 B CN115059559 B CN 115059559B
- Authority
- CN
- China
- Prior art keywords
- pull rods
- valve
- slide way
- rocket engine
- solid rocket
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Links
- 239000007787 solid Substances 0.000 title claims abstract description 25
- 230000001105 regulatory effect Effects 0.000 title claims abstract description 16
- 230000001276 controlling effect Effects 0.000 title claims abstract description 9
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 33
- 229910052802 copper Inorganic materials 0.000 claims abstract description 10
- 239000010949 copper Substances 0.000 claims abstract description 10
- 238000002485 combustion reaction Methods 0.000 abstract description 12
- 239000007789 gas Substances 0.000 description 10
- 238000000034 method Methods 0.000 description 8
- 230000008569 process Effects 0.000 description 8
- 238000005516 engineering process Methods 0.000 description 4
- 239000007921 spray Substances 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 239000004449 solid propellant Substances 0.000 description 2
- 238000004804 winding Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/86—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using nozzle throats of adjustable cross- section
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/805—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control servo-mechanisms or control devices therefor
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Lift Valve (AREA)
Abstract
The invention discloses a valve capable of accurately regulating and controlling the thrust of a solid rocket engine, and aims to solve the problems that the existing solid rocket engine with variable thrust is difficult to realize accurate regulation due to the fact that the pressure in a combustion chamber is regulated through axial movement of a pintle, and the wave is generated by the power regulated by the pintle. According to the invention, two groups of pull rods (7) are arranged in parallel, the two groups of pull rods (7) are connected through copper springs (5), the two groups of pull rods (7) are connected with a lower slide way (3) in a sliding manner, one end of a tensile copper wire (6) is connected with the pull rods (7), the other end of the tensile copper wire (6) is wound on an output shaft of a motor (4), the motor (4) is fixed on a supporting plate (8), the lower slide way (3) and the supporting plate (8) are both fixed on a base (9), the upper end of one group of pull rods (7) is connected with a left opening and closing door (2), the upper end of the other group of pull rods (7) is connected with a right opening and closing door (2), and the upper end of the opening and closing door (2) is connected with an upper slide way (1) in a sliding manner. According to the invention, a remote control program is adopted to control the motor, and the motor is used for controlling the stretching copper wire so as to realize the opening and closing of the valve, so that the accurate control is realized.
Description
Technical Field
The invention belongs to a valve for engine thrust, and particularly relates to a valve capable of accurately regulating and controlling the thrust of a solid rocket engine.
Background
With the continuous development and progress of technology, the aerospace technology is also continuously innovated and overcomes the difficulties. The solid rocket engine has the advantages of large thrust, high reliability, simple structure, convenient fuel storage and the like, and is widely applied to the aerospace technology. However, the thrust generated by the traditional solid rocket engine in the use process can only be stopped after the fuel is exhausted, and the application of the solid rocket engine is greatly limited by the irreducibility of the thrust in the use process. Thus, the countries around the world are working on solving this technical problem. Currently, six main categories of research on variable thrust solid engines are pulse engines, flameout engines, mass-fed engines, single-component gel propellant engines, variable nozzle throat area engines, and solid engines that control the mass combustion rate of the propellant. Among the most studied are the variable nozzle throat area engines. Because the engine of this type can reach the stepless regulation and control effect to the thrust that the engine produced in principle, this kind of engine simple structure simultaneously, only need change throat structure, and need not change other positions of engine can reach the effect. The current variable nozzle throat area type engines are mainly divided into two types, one is a throat bolt type solid rocket engine, and the other is a vortex type solid rocket engine.
The throat bolt type solid rocket engine is a variable thrust engine widely applied at present, the variable thrust engine is a patent technology disclosed in the United states in about 70 years of 20 th century, the principle is that a movable pintle is coaxially inserted into the center of a throat part of a spray pipe, the sectional area of the throat part of the spray pipe is changed through axial movement of the pintle, the pressure in a combustion chamber is regulated, and further the engine driving force is regulated, but the solid rocket engine with the structure can generate hysteresis in the process of regulating the pressure of the combustion chamber, and due to the wave action generated by the combustion chamber caused by the power regulated by the pintle, the accurate regulation is difficult to realize in the process, so the variable thrust engine has certain unreliability and danger, and if the uncontrollable pintle is blocked in the use process, the explosion and other dangers can be caused by the overlarge pressure of the combustion chamber.
Disclosure of Invention
The invention aims to solve the problems that the existing variable thrust solid rocket engine can accurately regulate and control the thrust of the solid rocket engine by adjusting the pressure in a combustion chamber through axial movement of a pintle and the power of the pintle regulation causes the combustion chamber to produce wave action and is difficult to realize accurate regulation.
The invention adopts the technical proposal for solving the problems that:
The utility model provides a valve that can accurate regulation and control solid rocket engine thrust, its constitution includes slide (1), door (2) that opens and shuts, glide slope (3), motor (4), copper spring (5), tensile copper wire (6), backup pad (8), base (9) and two sets of pull rod (7), two sets of pull rod (7) parallel arrangement are connected through copper spring (5) between two sets of pull rod (7), and two sets of pull rod (7) all are connected with glide slope (3) sliding connection, the one end and the pull rod (7) of tensile copper wire (6) are connected, and the other end winding of tensile copper wire (6) is on the output shaft of motor (4), and motor (4) are fixed on backup pad (8), and glide slope (3) and backup pad (8) are all fixed on base (9), and the upper end and the left side door (2) that open and shut of another set of pull rod (7) are connected with right side door (2), the upper end and the slide (1) sliding connection that opens and shuts of door (2).
The invention has the following beneficial effects:
1. According to the invention, the motor is controlled through a remote control program, the motor drives the stretched copper wire 6 to realize active opening and closing of the valve, the valve controls the opening and closing degree of the valve according to the gas pressure, the thrust of the engine is regulated, and further, the accurate control of opening and closing of the valve is realized, so that the reliability and safety of the ignition process of the solid rocket engine are improved.
2. According to the invention, through adjusting the valve position (translational stretching mechanism) in the throat lining of the engine spray pipe, the gas flow and the gas pressure passing through the throat lining are accurately adjusted by taking the valve opening degree as means, so that the wide control of the thrust of the engine is effectively realized, and meanwhile, the safety of the engine in the working process is also improved.
3. According to the invention, the accurate opening and closing degree of the valve is controlled, so that the pressure in the combustion chamber is actively controlled, and further the thrust control of the solid rocket engine is realized.
Drawings
FIG. 1 is a front view of the overall structure of a valve for precisely regulating and controlling the thrust of a solid rocket engine according to the present invention;
FIG. 2 is a view in the K-direction of FIG. 1;
FIG. 3 is a schematic illustration of the initial state of the valve of the present invention (i.e., the closed state of the opening and closing door 2, the outer contour of the throat insert of the engine nozzle is labeled 10 in the drawing);
Fig. 4 is a schematic view of the open state of the valve according to the present invention (i.e. the fully open state of the door 2, the diagram is ≡→ showing the moving direction of the door 2);
fig. 5 is a schematic diagram of the fully closed state of the valve according to the present invention (i.e. the closed state of the door 2. The moving direction of the door 2 is shown in the drawing →≡).
Detailed Description
The first embodiment is as follows: this embodiment is explained with reference to fig. 1 and 2, this embodiment includes slide (1), door (2) that opens and shuts, glide slope (3), motor (4), copper spring (5), tensile copper wire (6), backup pad (8), base (9) and two sets of pull rods (7), two sets of pull rods (7) parallel arrangement are connected through copper spring (5) between two sets of pull rods (7), two sets of pull rods (7) all are connected with glide slope (3) sliding connection, the one end and the pull rod (7) of tensile copper wire (6) are connected, the other end winding of tensile copper wire (6) is on the output shaft of motor (4), motor (4) are fixed on backup pad (8), glide slope (3) and backup pad (8) are all fixed on base (9), the upper end and the left side door (2) that opens and shuts of another set of pull rod (7) are connected with right side door (2), the upper end and the slide (1) sliding connection that opens and shuts of door (2). The number of the group of pull rods (7) is two, and the two pull rods (7) are connected through the tensile copper wires (6). Two pull rods (7) are arranged on each opening and closing door, so that enough power can drive the opening and closing door to open or close. The pull rod (7) is in slide type sliding connection with the lower slide way (3), and the opening and closing door (2) is in slide type sliding connection with the upper slide way (1). The slide way type sliding connection mode can accurately regulate and control the opening and closing of the opening and closing door.
The working process of the invention comprises the following steps:
Adjustment mode 1: when the gas pressure is too high (the gas pressure exceeds 10 MPa), the stretching copper wire 6 pulls the pull rod (7) to move to two outer sides under the drive of the motor 4, the pull rod (7) drives the opening and closing door 2 to open, and the valve is in a fully-opened state from an initial fully-closed state, namely, the gas pressure can be adjusted to 8MPa by changing from the position of the valve in FIG. 3 to the position in FIG. 4.
Adjustment mode 2: when the gas pressure is too small (the gas pressure is less than 6 MPa), the motor 4 relaxes the stretching of the stretched copper wire 6, and the copper spring (5) arranged in the middle of the pull rod 7 acts to pull the pull rod 7 to control the valve to be closed, and the valve is changed from the fully opened state to the fully closed state, namely, the valve position in fig. 4 is changed to the position in fig. 5. By reducing the sectional area of the valve opening, the 'supercharging' operation is realized on the combustion chamber, and the gas pressure can be regulated to 8MPa, so that the sufficient driving force can be provided when the solid propellant is combusted.
The behavior of reducing the throat liner cross-sectional area when the gas pressure is adjusted to be too small is based on the behavior of operation after adjustment mode 1. The valve is driven to be closed through the pull rod 7, namely, the valve position in fig. 4 is changed to the position in fig. 5, so that the automatic intelligent control of the pressure of the fuel gas flow is realized. The pressure of the combustion chamber during combustion of the solid propellant can be effectively increased, and enough thrust is provided for the solid rocket engine.
Claims (4)
1. The utility model provides a valve that can accurate regulation and control solid rocket engine thrust which characterized in that: the valve comprises an upper slide way (1), an opening and closing door (2), a lower slide way (3), a motor (4), a copper spring (5), a stretching copper wire (6), a supporting plate (8), a base (9) and two groups of pull rods (7), wherein the two groups of pull rods (7) are arranged in parallel, the two groups of pull rods (7) are connected through the copper spring (5), the two groups of pull rods (7) are all in sliding connection with the lower slide way (3), one end of the stretching copper wire (6) is connected with the pull rods (7), the other end of the stretching copper wire (6) is wound on an output shaft of the motor (4), the motor (4) is fixed on the supporting plate (8), the lower slide way (3) and the supporting plate (8) are fixed on the base (9), the upper end of one group of pull rods (7) is connected with the left opening and closing door (2), and the upper end of the other group of pull rods (7) is connected with the right opening and closing door (2) is in sliding connection with the upper slide way (1).
2. The valve capable of accurately regulating and controlling thrust of a solid rocket engine according to claim 1, wherein the valve is characterized in that: the number of the pull rods (7) in each group is two, and the two pull rods (7) are connected through the tensile copper wires (6).
3. The valve capable of accurately regulating and controlling thrust of a solid rocket engine according to claim 1 or 2, wherein the valve is characterized in that: the pull rod (7) is connected with the lower slide way (3) in a slide way type sliding way.
4. The valve capable of accurately regulating and controlling thrust of a solid rocket engine according to claim 1, wherein the valve is characterized in that: the opening and closing door (2) is connected with the upper slideway (1) in a slideway type sliding way.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210881818.3A CN115059559B (en) | 2022-07-26 | 2022-07-26 | Valve capable of accurately regulating and controlling thrust of solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210881818.3A CN115059559B (en) | 2022-07-26 | 2022-07-26 | Valve capable of accurately regulating and controlling thrust of solid rocket engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115059559A CN115059559A (en) | 2022-09-16 |
| CN115059559B true CN115059559B (en) | 2024-05-24 |
Family
ID=83205299
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210881818.3A Active CN115059559B (en) | 2022-07-26 | 2022-07-26 | Valve capable of accurately regulating and controlling thrust of solid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115059559B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103410632A (en) * | 2013-08-09 | 2013-11-27 | 南京理工大学 | Electric conical valve type gas flow regulator for solid rocket ramjets |
| CN107023420A (en) * | 2017-05-16 | 2017-08-08 | 北京理工大学 | A kind of Secondary Flow larynx bolt rocket engine with thrust controllable function |
| CN208935423U (en) * | 2018-08-10 | 2019-06-04 | 天津申龙鼎泰阀门有限公司 | A kind of water conservancy valve |
| CN112282967A (en) * | 2020-09-29 | 2021-01-29 | 上海新力动力设备研究所 | High-temperature gas valve with safety valve function |
| CN112682559A (en) * | 2020-12-19 | 2021-04-20 | 马荣哲 | Adjustable flow's gas tightness valve |
| CN112780448A (en) * | 2021-01-26 | 2021-05-11 | 北京灵动飞天动力科技有限公司 | Thrust adjusting mechanism of solid rocket engine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090211225A1 (en) * | 2007-01-29 | 2009-08-27 | Ghkn Engineering, Llc | Systems and methods for varying the thrust of rocket motors and engines while maintaining higher efficiency using moveable plug nozzles |
-
2022
- 2022-07-26 CN CN202210881818.3A patent/CN115059559B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103410632A (en) * | 2013-08-09 | 2013-11-27 | 南京理工大学 | Electric conical valve type gas flow regulator for solid rocket ramjets |
| CN107023420A (en) * | 2017-05-16 | 2017-08-08 | 北京理工大学 | A kind of Secondary Flow larynx bolt rocket engine with thrust controllable function |
| CN208935423U (en) * | 2018-08-10 | 2019-06-04 | 天津申龙鼎泰阀门有限公司 | A kind of water conservancy valve |
| CN112282967A (en) * | 2020-09-29 | 2021-01-29 | 上海新力动力设备研究所 | High-temperature gas valve with safety valve function |
| CN112682559A (en) * | 2020-12-19 | 2021-04-20 | 马荣哲 | Adjustable flow's gas tightness valve |
| CN112780448A (en) * | 2021-01-26 | 2021-05-11 | 北京灵动飞天动力科技有限公司 | Thrust adjusting mechanism of solid rocket engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115059559A (en) | 2022-09-16 |
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