CN112594091A - Solid attitude and orbit control engine gas valve and control method thereof - Google Patents
Solid attitude and orbit control engine gas valve and control method thereof Download PDFInfo
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- CN112594091A CN112594091A CN202011475913.0A CN202011475913A CN112594091A CN 112594091 A CN112594091 A CN 112594091A CN 202011475913 A CN202011475913 A CN 202011475913A CN 112594091 A CN112594091 A CN 112594091A
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- 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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/30—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants with the propulsion gases exhausting through a plurality of nozzles
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- 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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
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- 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
- F02K9/88—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using auxiliary rocket nozzles
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- 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
- F02K9/97—Rocket nozzles
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Magnetically Actuated Valves (AREA)
Abstract
The invention provides a solid attitude orbit control engine gas valve and a control method thereof, the gas valve utilizes partial gas generated by a combustion chamber of an aircraft solid rocket engine, the gas valve is controlled to be sprayed out from the side surface of an aircraft, and the lateral force generated by the sprayed gas is utilized to adjust the flight attitude of the aircraft.
Description
Technical Field
The invention belongs to the field of aircrafts, and particularly relates to a solid attitude and orbit control engine gas valve and a control method thereof.
Background
For attitude and orbit control of a solid rocket, two common methods are currently used, namely, an external force deviating from the axial direction is given to a projectile body to correct the trajectory and attitude of the rocket, wherein one method is to control the swinging of a spray pipe to change the direction of thrust, and the other method is to externally carry a gas cylinder and apply a lateral force to an aircraft through the reverse thrust generated by the gas cylinder to achieve the purpose of changing the flight attitude of the aircraft. The swinging spray pipe has high requirements on the process, high requirements on thermal protection of the connection part of the spray pipe and high cost; although the structure of the external gas cylinder is simpler, the gas cylinder has negative quality, and the rocket engine has higher requirements on the safety of the gas cylinder during working, so the external gas cylinder is still imperfect.
The invention aims to provide a device and a control method thereof, which can control the posture and trajectory correction of a solid rocket engine by gas generated in a combustion chamber of the engine, simplify the structure of the engine, reduce the passive mass of the rocket and improve the response speed of control.
Disclosure of Invention
Based on the above technical background, the present inventors have made a keen effort to solve the above problems, and have devised a solid attitude control engine gas valve which uses a part of gas generated from a combustion chamber of an aircraft solid rocket engine, controls the gas to be ejected from a side surface of an aircraft through the gas valve, and adjusts a flight attitude of the aircraft by using a lateral force generated by the ejected gas.
The invention aims to provide a solid attitude and orbit control engine gas valve 1, which is characterized in that the solid attitude and orbit control engine gas valve is fixedly connected below a combustion chamber of an aircraft solid rocket engine; the gas valve comprises a valve body 1, a gas control pipeline 2 and a side spray pipe gas pipeline 3;
the gas control pipeline 2 is used for controlling gas to be sprayed out from a side nozzle of the side nozzle gas pipeline 3, and the gas control pipeline 2 comprises a filter screen 21, a control gas supply pipeline 22, an electromagnetic valve 23, a gas control sheet control pipeline and a gas control sheet 25;
the side nozzle gas duct 3 is used for ejecting gas generated by the combustion chamber from the side direction of the aircraft.
The filter screen 21 is used for filtering the fuel gas flowing into the fuel gas control pipeline 2 from the combustion chamber, the filter screen 21 is fixed at the joint between the fuel gas control pipeline 2 and the combustion chamber, and the filter screen 21 completely covers the inlet of the fuel gas control pipeline 2;
the upper end of the gas supply pipeline 22 is connected with an attitude and orbit control gas outlet at the bottom of the combustion chamber shell, and the lower end is connected with an electromagnetic valve 23;
the gas supply line 22 comprises a gas supply line a221 and a gas supply line b 222;
the electromagnetic valve 23 comprises a valve core 231, a valve core cavity 232, a coil and a coil cover 234;
the gas sheet control pipeline comprises an opening control pipeline 241, a closing control pipeline 242 and a sliding pipeline 243;
the electromagnetic valve 23 generates magnetic force by energizing different coils arranged at two ends of the valve core 231, so as to attract the valve core to move;
the valve core cavity 232 is used for installing the valve core 231, the valve core cavity 232 comprises a valve core cavity upper part 2321, a valve core cavity middle part 2322 and a valve core cavity lower part 2323, the valve core cavity upper part 2321, the valve core cavity middle part 2322 and the valve core cavity lower part 2323 are all cylindrical cavities and are communicated with each other, the inner diameter sizes of the valve core cavity upper part 2321 and the valve core cavity lower part 2323 are the same, and the inner diameter size of the valve core cavity upper part is larger than the inner diameter size 2322 of the valve core cavity middle part;
the valve core 231 is used for controlling the opening or closing of the gas supply pipeline 22, the valve core 231 comprises a middle plug 2313, the middle plug 2313 is a cylinder, an upper connecting rod 2314 is vertically arranged at the upper end of the cylinder, a lower connecting rod 2315 is vertically arranged at the lower end of the cylinder, an upper piston 2311 is arranged at the tail end of the upper connecting rod 2314, a lower piston 2312 is arranged at the tail end of the lower connecting rod 2315, and the valve core 231 can be attracted by an electrified coil;
the outer diameter of the middle plug 2313 is consistent with the inner diameter of the middle part 2322 of the valve core cavity, and the middle plug 2313 is arranged in the middle part 2322 of the valve core cavity, so that the valve core cavity 232 is divided into an upper section and a lower section which are not communicated with each other;
the coil is used for attracting the spool 231 after being electrified, and includes an upper coil 2331 and a lower coil 2332, the upper coil 2331 is arranged at the upper part of the electromagnetic valve 23, and the lower coil 2332 is arranged at the lower part of the electromagnetic valve 23;
the coil cover 234 is a hollow cylindrical shell, and a through hole is formed above the coil cover 234; the coil cover 234 includes an upper coil cover 2341 and a lower coil cover 2342, the upper coil cover 2341 is disposed outside the upper coil 2331, and the lower coil cover 2342 is disposed outside the lower coil 2332.
Wherein the sliding pipe 243 is arranged at the connection of the opening control pipeline 241 and the closing control pipeline 242;
one end of the opening control pipeline 241 is connected with the valve core cavity 232 of the electromagnetic valve 23, the other end of the opening control pipeline is connected with the left side of the sliding pipeline 243, one end of the closing control pipeline 242 is connected with the valve core cavity 232 of the electromagnetic valve 23, and the other end of the closing control pipeline is connected with the right side of the sliding pipeline 243;
the sliding pipe 243 is perpendicular to the side nozzle gas pipe 3;
one end of the opening control pipeline 241 is connected with the valve core cavity 232 of the electromagnetic valve 23, the other end of the opening control pipeline is connected with the left side of the sliding pipeline 243, one end of the closing control pipeline 242 is connected with the valve core cavity 232 of the electromagnetic valve 23, and the other end of the closing control pipeline is connected with the right side of the sliding pipeline 243;
a gas control plate 25 capable of sliding left and right is provided inside the sliding duct 243;
the sliding duct 243 is provided with a sliding groove so that the gas control piece reciprocates in the left and right directions in the sliding duct.
Wherein, the gas control sheet 25 is used for controlling the opening or closing of the side nozzle gas pipeline 3;
the gas control sheet 25 is in a long plate shape, a control sheet hole 251 is formed in the plate, the length of the control sheet is more than 2 times of the diameter of the through hole, raised sliding parts 252 are arranged on the upper portion and the lower portion of the gas control sheet 25, discs 253 are vertically arranged at two ends of the control sheet, and the diameter of each disc 253 is consistent with the inner diameter of the sliding pipeline 243;
by installing the gas control panel 25 into the sliding duct 243, the sliding duct 243 is partitioned into an open cavity 2431 on the left side and a closed cavity 2432 on the right side.
Wherein, the side nozzle gas pipeline 3 ejects gas generated by the combustion chamber through a side nozzle 31 arranged at the side of the aircraft; the end of the side lance 31 projects from the valve body 1.
Wherein the gas valves are provided in plurality, evenly distributed around the axial direction of the aircraft, preferably the number of gas valves is set to 8.
Wherein, a main nozzle 41 and a plurality of attitude and orbit control gas nozzles 42 surrounding the main nozzle 41 are arranged at the bottom of the combustion chamber,
an attitude and orbit control gas nozzle 42 is connected above each gas valve.
Wherein, a cylindrical cavity is arranged in the middle of the valve, and the cylindrical axis is superposed with the axis of a main nozzle 41 at the bottom of the combustion chamber of the solid rocket engine.
The invention also provides a control method of the solid attitude and orbit control engine gas valve, which comprises the following steps:
after receiving an instruction of opening the side nozzle 3, the upper coil 2331 of the electromagnetic valve 23 is electrified to work, the lower coil 2332 is closed to drive the valve core 231 to move upwards, the middle choke plug 2313 blocks the gas supply pipeline a221 at the moment, the lower piston 2312 blocks the lower part of the valve core cavity, the upper part of the valve core cavity is communicated with the middle part of the valve core cavity, the gas in the combustion chamber enters the gas supply pipeline b222 through the attitude and orbit control gas nozzle 42, then sequentially passes through the valve core cavity 232 and the opening control pipeline 241, finally flows into the opening cavity 2431, pushes the gas control sheet 25 to move rightwards, the control sheet hole 251 on the gas control sheet 25 is communicated with the side nozzle gas pipeline 3, so that the gas is sprayed out from the side nozzle 31, meanwhile, the gas control sheet 25 pushes the gas in the closing chamber 2432 to flow into the closing control pipeline 242, pass through the upper section of the valve core cavity 232, and be discharged to the outside of the valve body 1 from a hole on the upper coil cover 2341 of the electromagnetic valve 23;
when a command of opening the side nozzle 3 is not received or a command of closing the side nozzle is received, the lower coil 2332 of the electromagnetic valve 23 is electrified to work, the valve core 231 is driven to move downwards, the middle plug 2313 blocks the gas supply pipeline b222 at the moment, the upper piston 2311 blocks the upper part 2321 of the valve core cavity, the lower part 2323 of the valve core cavity is communicated with the middle part 2322 of the valve core cavity, so that gas in the combustion chamber enters the gas supply pipeline a221 through the attitude and orbit control gas nozzle 42, then sequentially passes through the upper section of the valve core cavity 232 and the closing control pipeline 242, finally flows into the closing cavity 2432, pushes the gas control plate 25, enables the gas control plate 25 to move leftwards and block the side nozzle gas pipeline 3, and simultaneously presses gas in the opening cavity 2431 to flow into the opening control pipeline 241, passes through the lower section of the valve core cavity 232, and is discharged to the outside of the valve body 1 from a through hole 234.
The solid attitude and orbit control engine gas valve provided by the invention has the following advantages:
(1) the invention has simple structure and low cost;
(2) the gas in the combustion chamber is directly utilized, and an external gas cylinder is not needed, so that the weight is lighter, and the passive mass of the rocket is reduced;
(3) according to the invention, a small part of gas is controlled by the electromagnetic valve to push the control valve, so that more gas is controlled to be laterally sprayed out, the control efficiency is extremely high, and the power consumption is small;
(4) the control response is rapid, and the accuracy of the attitude control of the aircraft is improved.
Drawings
FIG. 1 is a schematic view of the bottom structure of a combustion chamber according to the present invention;
FIG. 2 is a schematic diagram illustrating a general configuration of a solid attitude control engine gas valve according to the present invention;
FIG. 3 is a schematic diagram showing a structure of a control gas supply line in a gas control line of the gas valve according to the present invention;
FIG. 4 is a schematic view of the solenoid valve of the gas valve of the present invention;
FIG. 5 is a schematic view of a spool chamber of a solenoid valve of the gas valve according to the present invention;
FIG. 6 is a schematic structural view of a valve core of a solenoid valve of the gas valve according to the present invention;
FIG. 7 is a schematic view showing the structure of a coil cover of a solenoid valve of a gas valve according to the present invention;
FIG. 8 is a schematic structural view illustrating the communication between the through holes of the gas control fins and the side nozzle gas pipeline;
FIG. 9 is a schematic structural view showing a gas control flap of the gas valve of the present invention closing a side nozzle gas pipe;
FIG. 10 is a schematic view showing the structure of a gas control segment of the gas valve according to the present invention;
fig. 11 shows a schematic view of the structure of the side nozzle gas pipe of the gas valve according to the invention.
Description of the reference numerals
1-a valve body;
2-a gas control pipeline;
21-a filter screen;
22-control of the gas supply line;
221-gas supply line a; 222-gas supply line b;
23-a solenoid valve;
231-a valve core; 2311-upper piston; 2312-lower piston; 2313-middle plug;
2314-upper connecting rod; 2315-lower connecting rod;
232-valve core cavity;
2321-the upper part of the valve core cavity; 2322-middle of valve core cavity; 2323-lower part of valve core cavity;
2331-upper coil; 2332-lower coil;
234-coil cover; 2341-upper coil cover; 2342-lower coil cap;
241-starting a control pipeline; 242-closing the control line; 243-sliding pipe;
2431-opening the cavity; 2432-closing the cavity;
25-gas control sheet; 251-control pad aperture; 252-a sliding member; 253-a disc;
3-side nozzle gas pipeline; 31-side nozzle;
41-main orifice; 42-posture and orbit control gas nozzle.
Detailed Description
The present invention will be described in detail below, and features and advantages of the present invention will become more apparent and apparent with reference to the following description.
The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. While the various aspects of the embodiments are presented in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
According to the solid attitude control engine gas valve provided by the invention, the gas valve is arranged below a combustion chamber of a solid rocket engine;
the bottom structure of the solid rocket engine combustion chamber is shown in fig. 1 and comprises a main nozzle 41 and an attitude and orbit control gas nozzle 42; the main nozzle 41 is used for ejecting gas generated by combustion in the combustion chamber through the main nozzle 41 and pushing the aircraft to advance by using the generated reaction force, and the main nozzle 41 is arranged at the center of the bottom of the combustion chamber; the attitude and orbit control gas nozzle 42 is used for supplying gas to the solid attitude and orbit control engine gas valve, the attitude and orbit control gas nozzle 42 is arranged around the axis of the combustion chamber, and the attitude and orbit control gas nozzle is of a hollow structure protruding out of the bottom plane of the combustion chamber. The main structure of the solid attitude and orbit control engine gas valve is shown in figure 2 and comprises a valve body 1, a gas control pipeline 2 and a side nozzle gas pipeline 3.
The valve body 1 is fixedly connected with a bottom structure of the combustion chamber, preferably, a bolt is used for connection, and the valve body 1 is provided with a bolt mounting hole;
The gas control pipeline 2 further comprises an electromagnetic valve 23 and a gas control sheet 25,
when the aircraft needs to be subjected to attitude and orbit control, the electromagnetic valve 23 receives an aircraft instruction, the electromagnetic valve 23 controls the movement of the gas control sheet 25 by controlling the flow channel of the gas in the gas control pipeline 2,
the gas control plate 25 is perpendicular to the side nozzle gas pipeline and divides the side nozzle gas pipeline into two parts, the gas control plate 25 is provided with a control plate hole, when the control plate hole is communicated with the side nozzle gas pipeline, the two parts of the side nozzle gas pipeline are communicated with each other, and then part of gas generated by the combustion chamber is sprayed out from a side nozzle 31 arranged on the side surface of the valve body 1 through the side nozzle gas pipeline 3.
More specifically, a cylindrical hollow hole is formed in the axial position of the valve body, the cylindrical axis is overlapped with the axis of a main nozzle 41 at the bottom of a combustion chamber of the solid rocket engine, and most of fuel gas in the combustion chamber is sprayed out through the main nozzle 41 arranged at the bottom of the combustion chamber to provide forward power for the aircraft.
The gas control pipeline 2 is used for controlling gas to be sprayed out from a side nozzle of the side nozzle gas pipeline 3, and the gas control pipeline 2 comprises a filter screen 21, a control gas supply pipeline 22, an electromagnetic valve 23, a gas control sheet control pipeline and a gas control sheet 25.
The filter screen 21 is used for filtering the fuel gas flowing into the fuel gas control pipeline from the combustion chamber, the filter screen 21 is fixed at the joint of the fuel gas control pipeline 2 and the combustion chamber, and the filter screen 21 completely covers the inlet of the fuel gas control pipeline 2, as shown in fig. 3;
the upper end of the gas supply pipeline 22 is connected with an attitude and orbit control gas outlet at the bottom of the combustion chamber shell, and the lower end of the gas supply pipeline is connected with an electromagnetic valve 23;
further, the gas supply line 22 includes two gas supply lines a221 and b222, and is connected to the solenoid valve 23.
The solenoid valve 23, as shown in fig. 4, includes a valve core 231, a valve core cavity 232, a coil cover 234, a lead wire and an external motor;
the electromagnetic valve 23 generates magnetic force by electrifying different coils arranged at two ends of the valve core, so as to attract the valve core 231 to move;
as shown in fig. 5, the valve core cavity 232 is configured to mount the valve core 231 and enable the valve core to slide linearly along the valve core cavity 232, the valve core cavity 232 includes a valve core cavity upper portion 2321, a valve core cavity middle portion 2322 and a valve core cavity lower portion 2323, the valve core cavity upper portion 2321, the valve core cavity middle portion 2322 and the valve core cavity lower portion 2323 are all cylindrical cavity structures and are located on the same axis and are communicated with each other, the diameters of the valve core cavity upper portion 2321 and the valve core cavity lower portion 2323 are the same, and the diameter of the valve core cavity upper portion is larger than that of the valve core cavity middle portion 2322.
The valve core 231, as shown in fig. 6, is disposed in the valve core cavity 232, and the valve core 231 controls to open or close the gas supply pipeline a221 and the gas supply pipeline b222 by moving to different positions; the spool 231 includes a middle plug 2313, an upper connecting rod 2314, a lower connecting rod 2315, an upper piston 2311 and a lower piston 2312;
the middle plug 2313 is a cylinder, an upper connecting rod 2314 is vertically arranged at the upper end of the cylinder, a lower connecting rod 2315 is vertically arranged at the lower end of the cylinder, an upper piston 2311 is arranged at the tail end of the upper connecting rod 2314, a lower piston 2312 is arranged at the tail end of the lower connecting rod 2315, and the valve core 231 can be attracted by an electrified coil;
the outer diameter of the middle plug 2313 is consistent with the inner diameter of the middle part 2322 of the valve core cavity, the middle plug 2313 is installed in the middle part 2322 of the valve core cavity, and the valve core cavity 232 is divided into an upper section and a lower section through matching with the cavity of the middle part 2322 of the valve core cavity, and the upper section and the lower section are not communicated with each other;
the piston diameter of the valve core 231 is slightly smaller than the inner diameter of the upper part 2321 of the valve core cavity and larger than the inner diameter of the middle part 2322 of the valve core cavity; when the valve core 231 moves downwards, the upper piston stops at the bottom end of the upper part 2321 of the valve core cavity, the upper part 2321 of the valve core cavity is closed, the valve core 231 is controlled to stop at the outlet of the gas supply pipeline a221, at the moment, the lower piston is located in the lower part 2323 of the valve core cavity, and the lower part 2323 of the valve core cavity is communicated with the middle 2322 of the valve core cavity;
two ends of the valve core cavity 232 are respectively provided with a coil, the coils are used for attracting the valve core 231 to move after being electrified, the coils are formed by winding metal guide wires, each coil comprises an upper coil 2331 and a lower coil 2332, the upper coil 2331 is arranged at the upper part of the electromagnetic valve 23, and the lower coil 2332 is arranged at the lower part of the electromagnetic valve 23.
The coil cover 234, as shown in fig. 7, is a hollow cylindrical housing, and a through hole is provided above the coil cover 234, the through hole is used for leading out a wire on one hand and playing a role in exhausting air on the other hand; two counter bores are further formed above the coil cover 234, so that the coil cover can be assembled by using a tool conveniently; the coil cover 234 includes an upper coil cover 2341 and a lower coil cover 2342, the upper coil cover 2341 is disposed outside the upper coil 2331, the lower coil cover 2342 is disposed outside the lower coil 2332, and the coil cover 234 is connected with the valve body 1 through threads;
the lead is used for connecting the coil and an external generator;
the external generator is used for supplying power to the coil;
the solid part of the valve body 1 connected with the combustion chamber housing, which has a fixing effect, is provided with a through hole for leading out a lead and connecting the lead with an external generator.
The gas piece control pipeline comprises an opening control pipeline 241, a closing control pipeline 242 and a sliding pipeline 243, as shown in fig. 4, 8 and 9;
a sliding pipe 243 is arranged at the joint of the opening control pipeline 241 and the closing control pipeline 242;
one end of the opening control pipeline 241 is connected with the valve core cavity 232 of the electromagnetic valve 23, the other end of the opening control pipeline is connected with the left side of the sliding pipeline 243, one end of the closing control pipeline 242 is connected with the valve core cavity 232 of the electromagnetic valve 23, and the other end of the closing control pipeline is connected with the right side of the sliding pipeline 243;
the sliding duct 243, as shown in fig. 8, the sliding duct 243 is used for installing the gas control sheet 25 and allowing the gas control sheet 25 to slide left and right;
the sliding pipeline 243 is arranged perpendicular to the side nozzle gas pipeline 3, and the side nozzle gas pipeline 3 is opened or closed by using the gas control sheet 25 at different positions;
the sliding duct 243, as shown in fig. 9, further includes a sliding slot, so that the gas control plate moves linearly in the sliding duct 243 in the left-right direction, the total length of the sliding duct 243 is greater than the total length of the apertures of the gas control plate 25 and the control plate, the sliding duct 243 is further provided with a limiting block, so that the gas control plate is always perpendicular to the side nozzle gas duct 3, and the through hole of the gas control plate 25 is communicated with the side nozzle gas duct 3, i.e., in the state shown in fig. 8, or the side nozzle gas duct 3 is closed, i.e., in the state shown in fig. 9.
As shown in fig. 10, the gas control plate 25 is in the form of a long plate, a control plate hole 251 is formed in the plate, the length of the control plate is greater than 2 times the diameter of the through hole, protruding sliding members 252 are disposed on the upper and lower sides of the gas control plate 25, and disks 253 are vertically disposed at both ends of the control plate. When the control piece hole 251 is overlapped with the side nozzle gas pipeline 3 or partially overlapped with the side nozzle gas pipeline 3, the side nozzle gas pipeline 3 can be allowed to emit gas outwards, and when the control piece hole 251 slides along with the gas control piece 25 and is not overlapped with the side nozzle gas pipeline 3 any more, the gas control piece 2 can block the side nozzle gas pipeline 3 so that the gas is not emitted outwards.
The sliding component 252 is matched with the sliding groove of the sliding pipeline 243, and the diameter of the disc 253 is consistent with the inner diameter of the sliding pipeline 243; as shown in fig. 9, after the gas control sheet 25 is installed in the sliding duct 243, an open cavity 2431 is formed between the left side of the gas control sheet 25 and the left inner wall of the sliding duct 243, and a closed cavity 2432 is formed between the right side of the gas control sheet 25 and the right inner wall of the sliding duct 243.
The side nozzle gas pipeline 3 is used for ejecting gas generated by the combustion chamber from the side direction of the aircraft, one end of the side nozzle gas pipeline 3 is connected with a posture and orbit control gas nozzle 42 of the bottom structure of the combustion chamber through an opening arranged on the valve body 1, the other end is provided with a side nozzle 31, and the side nozzle 31 is connected with the outside, as shown in fig. 11;
preferably, the end of the side lance 31 protrudes from the valve body 1.
In a preferred embodiment, when the valve body 1 is manufactured, holes are processed in the valve body 1 to be used as a gas control pipeline 2 and a side nozzle gas pipeline 3.
In a further preferred embodiment, as shown in fig. 2, the gas valves are provided in plural numbers, evenly distributed around the axial direction of the aircraft, and further, the number of the gas valves is set to 8;
when a plurality of gas valves are arranged, the aircraft can be better subjected to attitude and orbit control adjustment by applying a resultant force of lateral force to the aircraft, which is generated by the simultaneous operation of the plurality of gas valves.
In a further embodiment, as shown in fig. 2, the interface between the valve body 1 and the combustion chamber is arranged in a ring shape and is divided into zones, so that the gas flows into different solid attitude control engine gas valves respectively.
The invention also provides a method for controlling a gas valve of a solid attitude control engine, wherein the solid attitude control engine is as described above, and the method comprises the following steps:
after receiving an instruction of opening the side nozzle 3, the upper coil 2331 of the electromagnetic valve 23 is electrified to work, the lower coil 2332 is closed to drive the valve core 231 to move upwards, the middle plug 2313 plugs the gas supply pipeline a221, the lower piston 2312 plugs the lower part of the valve core cavity, the upper part of the valve core cavity is communicated with the middle part of the valve core cavity, the gas in the combustion chamber enters the gas supply pipeline b222 through the attitude and orbit control gas nozzle 42, then sequentially passes through the valve core cavity 232 and the opening control pipeline 241, finally flows into the opening cavity 2431, pushes the gas control sheet 25 to move rightwards, the through hole 2521 on the gas control sheet 25 is communicated with the side nozzle gas pipeline 3, so that the gas is sprayed out from the side nozzle 31, meanwhile, the gas control plate 25 pushes the gas in the closing chamber 2432 to flow into the closing control pipeline 242, pass through the upper section of the spool cavity 232, and be discharged to the outside of the valve body 1 from the hole on the upper coil cover 2341 of the solenoid valve 23.
When an instruction of opening the side nozzle 3 is not received or an instruction of closing the side nozzle is received, the lower coil 2332 of the electromagnetic valve 23 is electrified to work, the valve core 231 is driven to move downwards, the middle plug 2313 blocks the gas supply pipeline b222, the upper piston 2311 blocks the upper part 2321 of the valve core cavity, the lower part 2323 of the valve core cavity is communicated with the middle part 2322 of the valve core cavity, so that gas in the combustion chamber enters the gas supply pipeline a221 through the attitude and orbit control gas nozzle 42, then sequentially passes through the valve core cavity 232 and the closing control pipeline 242, finally flows into the closing cavity 2432, pushes the gas control sheet 25, enables the gas control sheet 25 to move leftwards and block the side nozzle gas pipeline 3, and presses and opens gas in the cavity 2431 to flow into the opening control pipeline 241, passes through the lower section of the valve core cavity 232, and is discharged to the outside of the valve body from a hole 2342 of the lower;
in the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "left", "right", and the like indicate orientations or positional relationships based on operational states of the present invention, and are only used for convenience of description and simplification of the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.
The present invention has been described above in connection with preferred embodiments, but these embodiments are merely exemplary and merely illustrative. On the basis of the above, the invention can be subjected to various substitutions and modifications, and the substitutions and the modifications are all within the protection scope of the invention.
Claims (10)
1. A solid attitude and orbit control engine gas valve is characterized in that the solid attitude and orbit control engine gas valve is fixedly connected below a combustion chamber of an aircraft solid rocket engine; the gas valve comprises a valve body (1), a gas control pipeline (2) and a side spray pipe gas pipeline (3);
the gas control pipeline (2) is used for controlling gas to be sprayed out from a side nozzle of the side nozzle gas pipeline (3), and the gas control pipeline (2) comprises a filter screen (21), a control gas supply pipeline (22), an electromagnetic valve (23), a gas control sheet control pipeline and a gas control sheet (25);
the side nozzle gas pipeline (3) is used for ejecting gas generated by the combustion chamber from the side direction of the aircraft.
2. A gas valve as claimed in claim 1,
the filter screen (21) is used for filtering the fuel gas flowing into the fuel gas control pipeline (2) from the combustion chamber, the filter screen (21) is fixed at the joint between the fuel gas control pipeline (2) and the combustion chamber, and the filter screen (21) completely covers the inlet of the fuel gas control pipeline (2);
the upper end of the gas supply pipeline (22) is connected with an attitude and orbit control gas outlet at the bottom of the combustion chamber shell, and the lower end of the gas supply pipeline is connected with an electromagnetic valve (23);
the gas supply line (22) comprises a gas supply line a (221) and a gas supply line b (222);
the electromagnetic valve (23) comprises a valve core (231), a valve core cavity (232), a coil and a coil cover (234);
the gas sheet control pipeline comprises an opening control pipeline (241), a closing control pipeline (242) and a sliding pipeline (243).
3. A gas valve as claimed in claim 2,
the electromagnetic valve (23) generates magnetic force by electrifying different coils arranged at two ends of the valve core (231), so as to attract the valve core to move;
the valve core cavity (232) is used for mounting a valve core (231), the valve core cavity (232) comprises a valve core cavity upper part (2321), a valve core cavity middle part (2322) and a valve core cavity lower part (2323), the valve core cavity upper part (2321), the valve core cavity middle part (2322) and the valve core cavity lower part (2323) are all cylindrical cavities and are communicated with each other, the inner diameter sizes of the valve core cavity upper part (2321) and the valve core cavity lower part (2323) are the same, and the inner diameter size of the valve core cavity upper part is larger than the inner diameter size (2322) of the valve core cavity middle part;
the valve core (231) is used for controlling opening or closing of the gas supply pipeline (22), the valve core (231) comprises a middle plug (2313), the middle plug (2313) is a cylinder, an upper connecting rod (2314) is vertically arranged at the upper end of the cylinder, a lower connecting rod (2315) is vertically arranged at the lower end of the cylinder, an upper piston (2311) is arranged at the tail end of the upper connecting rod (2314), a lower piston (2312) is arranged at the tail end of the lower connecting rod (2315), and the valve core (231) can be attracted by an electrified coil;
the size of the outer diameter of the middle plug (2313) is consistent with that of the inner diameter of the middle part (2322) of the valve core cavity, and the middle plug (2313) is installed in the middle part (2322) of the valve core cavity, so that the valve core cavity (232) is divided into an upper section and a lower section which are not communicated with each other;
the coil is used for attracting the valve core (231) after being electrified, the coil comprises an upper coil (2331) and a lower coil (2332), the upper coil (2331) is arranged at the upper part of the electromagnetic valve (23), and the lower coil (2332) is arranged at the lower part of the electromagnetic valve (23);
the coil cover (234) is a hollow cylindrical shell, and a through hole is formed above the coil cover (234); coil lid (234) include coil lid (2341) and coil lid (2342) down, coil lid (2341) set up go up coil (2331) outside, coil lid (2342) set up down outside coil (2332).
4. A gas valve as claimed in claim 2,
the sliding pipeline (243) is arranged at the joint of the opening control pipeline (241) and the closing control pipeline (242);
one end of the opening control pipeline (241) is connected with a valve core cavity (232) of the electromagnetic valve (23), the other end of the opening control pipeline is connected with the left side of the sliding pipeline (243), one end of the closing control pipeline (242) is connected with the valve core cavity (232) of the electromagnetic valve (23), and the other end of the closing control pipeline is connected with the right side of the sliding pipeline (243);
the sliding pipeline (243) is vertical to the side nozzle gas pipeline (3);
one end of the opening control pipeline (241) is connected with a valve core cavity (232) of the electromagnetic valve (23), the other end of the opening control pipeline is connected with the left side of the sliding pipeline (243), one end of the closing control pipeline (242) is connected with the valve core cavity (232) of the electromagnetic valve (23), and the other end of the closing control pipeline is connected with the right side of the sliding pipeline (243);
a gas control sheet (25) capable of sliding left and right is arranged in the sliding pipeline (243);
the sliding pipeline (243) is provided with a sliding chute, so that the gas control sheet can reciprocate in the sliding pipeline in the left-right direction.
5. A gas valve as claimed in claim 2,
the gas control sheet (25) is used for controlling the opening or closing of the side nozzle gas pipeline (3);
the gas control sheet (25) is in a long plate shape, a control sheet hole (251) is formed in the plate, the length of the control sheet is larger than 2 times of the diameter of the through hole, protruding sliding parts (252) are arranged on the upper portion and the lower portion of the gas control sheet (25), discs (253) are vertically arranged at two ends of the control sheet, and the diameter of each disc (253) is consistent with the inner diameter of each sliding pipeline (243);
by installing the gas control flap (25) into the sliding duct (243), the sliding duct (243) is divided into an open cavity (2431) on the left side and a closed cavity (2432) on the right side.
6. A gas valve as claimed in claim 1,
the side nozzle gas pipeline (3) sprays gas generated by the combustion chamber through a side nozzle (31) arranged on the side of the aircraft; the end of the side nozzle (31) protrudes from the valve body (1).
7. A gas valve as claimed in claim 1,
the gas valves are provided in plurality, evenly distributed around the axial direction of the aircraft, preferably the number of gas valves is set to 8.
8. A gas valve as claimed in claim 1,
a main nozzle (41) and a plurality of attitude and orbit control gas nozzles (42) surrounding the main nozzle (41) are arranged at the bottom of the combustion chamber,
an attitude and orbit control gas nozzle (42) is connected above each gas valve.
9. A gas valve as claimed in claim 1,
and a cylindrical cavity is arranged in the middle of the valve, and the cylindrical axis is superposed with the axis of a main spray pipe (41) at the bottom of the combustion chamber of the solid rocket engine.
10. A method for controlling a gas valve of a solid attitude and orbit control engine is characterized by comprising the following steps:
after receiving an instruction of opening the side nozzle (3), electrifying an upper coil (2331) of the electromagnetic valve (23) to work, closing a lower coil (2332) to drive the valve core (231) to move upwards, blocking a gas supply pipeline a (221) by a middle plug (2313), blocking the lower part of a valve core cavity by a lower piston (2312), communicating the upper part of the valve core cavity with the middle part of the valve core cavity, enabling gas in a combustion chamber to enter a gas supply pipeline b (222) through an attitude and orbit control gas nozzle (42), sequentially passing through the valve core cavity (232) and an opening control pipeline (241), finally flowing into an opening cavity (2431), pushing a gas control sheet (25) to move rightwards, communicating a control sheet hole (251) in the gas control sheet (25) with the side nozzle gas pipeline (3), enabling the gas to be sprayed out from the side nozzle (31), and simultaneously pushing gas in the closing cavity (2432) by the gas control sheet (25) to flow into a closing control pipeline (242) and pass through the upper section of the valve core cavity (, and is discharged to the outside of the valve body (1) from a hole on an upper coil cover (2341) of the electromagnetic valve (23);
when a command of opening the side nozzle (3) is not received or a command of closing the side nozzle is received, a lower coil (2332) of the electromagnetic valve (23) is electrified to work to drive the valve core (231) to move downwards, at the moment, the middle choke plug (2313) blocks the gas supply pipeline b (222), the upper piston (2311) blocks the upper part (2321) of the valve core cavity, the lower part (2323) of the valve core cavity is communicated with the middle part (2322) of the valve core cavity, so that gas in the combustion chamber enters the gas supply pipeline a (221) through the attitude and orbit control gas nozzle (42), then sequentially passes through the upper section of the valve core cavity (232) and the closing control pipeline (242), finally flows into the closing cavity (2432), pushes the gas control sheet (25), so that the gas control sheet (25) moves leftwards and blocks the side nozzle gas pipeline (3), and presses and opens gas in the opening cavity (2431) to flow into the opening control pipeline (241, the oil is led to the lower section of the valve core cavity (232) and is discharged to the outside of the valve body (1) from a through hole on a lower coil cover (2342) of the electromagnetic valve (23).
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011475913.0A CN112594091B (en) | 2020-12-15 | 2020-12-15 | Solid attitude and orbit control engine gas valve and control method thereof |
| JP2022545417A JP2023511608A (en) | 2020-12-15 | 2021-09-22 | Solid attitude orbital control engine gas valve and its control method |
| PCT/CN2021/119502 WO2022127251A1 (en) | 2020-12-15 | 2021-09-22 | Solid attitude and orbit control engine gas valve and control method therefor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202011475913.0A CN112594091B (en) | 2020-12-15 | 2020-12-15 | Solid attitude and orbit control engine gas valve and control method thereof |
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| Publication Number | Publication Date |
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| CN112594091A true CN112594091A (en) | 2021-04-02 |
| CN112594091B CN112594091B (en) | 2021-12-07 |
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| CN202011475913.0A Active CN112594091B (en) | 2020-12-15 | 2020-12-15 | Solid attitude and orbit control engine gas valve and control method thereof |
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| Country | Link |
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| JP (1) | JP2023511608A (en) |
| CN (1) | CN112594091B (en) |
| WO (1) | WO2022127251A1 (en) |
Cited By (2)
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| WO2022127251A1 (en) * | 2020-12-15 | 2022-06-23 | 北京理工大学 | Solid attitude and orbit control engine gas valve and control method therefor |
| CN114993681A (en) * | 2022-05-12 | 2022-09-02 | 北京理工大学 | Method for detecting performance of jet type micro-attitude engine |
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Also Published As
| Publication number | Publication date |
|---|---|
| WO2022127251A1 (en) | 2022-06-23 |
| JP2023511608A (en) | 2023-03-20 |
| CN112594091B (en) | 2021-12-07 |
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