CN110195665A - A kind of air storing type solid propellant power device of reloading - Google Patents
A kind of air storing type solid propellant power device of reloading Download PDFInfo
- Publication number
- CN110195665A CN110195665A CN201910541656.7A CN201910541656A CN110195665A CN 110195665 A CN110195665 A CN 110195665A CN 201910541656 A CN201910541656 A CN 201910541656A CN 110195665 A CN110195665 A CN 110195665A
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- powder charge
- gas
- filler
- storage room
- gas storage
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Classifications
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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
- F02K9/24—Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The present invention relates to a kind of air storing type solid propellant power devices of reloading, belong to solid propellant rocket and pack boronitriding technical field.This invention takes following technological approaches.First is that using pulse pressure-charging: constantly loading burning using multistage pulses powder column, do not need extinction process.Second is that increasing gas storage link: powder charge combustion process being separated with jet pipe exhaust acting process, the two is respectively independent.Powder charge burning is intended merely to be pressurized to combustion gas tank, without being vented simultaneously；Exhaust work done makes its working medium and energy from combustion gas tank, no longer needs powder charge at this time while burning.Traditional burning-release process is become burning-gas storage-release process by the present invention, can be well solved because SOLID PROPELLANT COMBUSTION process is difficult to problem caused by interrupting.The present invention combines two kinds of technological approaches of gas storage link and pulse pressure-charging, the active switch machine for being truly realized solid propellant power device and repeatedly starting.
Description
Technical field
The present invention relates to a kind of air storing type solid propellant power devices of reloading, belong to solid propellant rocket and consolidate
Body fuel gas generator technical field.
Background technique
Solid propellant propulsion mode is widely used, for example, solid propellant rocket due to structure is simple, at low cost, good reliability,
It responds the advantages that fast and is selected as the power device of most of guided missiles, rocket.However, using the power device of solid propellant
There are inherent defect, typical performance is its poor controllability, is not easy to realize the thrust control of similar liquids rocket engine.
In order to improve performance, expand application range, scientific research personnel to the thrust controllable of solid propellant power device into
It has gone correlative study, and has achieved progress in fields such as thruster vector control, Variable Thrust Engine, rail control gas valves.
But in terms of the multiple starting of solid power unit, that is, active switch machine control aspect develops slowly.Correlative study work
Caused by the difficulty of work is two work characteristics by solid power unit:
First is that the duration of SOLID PROPELLANT COMBUSTION.Once powder charge is ignited, the heat transmitting of propellant will carry out automatically,
It reaches ignition condition and is ignited, also very acutely, burning is not easy to stop for during which chemical reaction.
Second is that the relativity of gas production rate and deflation rate.The combustion chamber of Conventional solid rocket engine is both propellant storage
Place is deposited, and is its place for carrying out combustion reaction, combustion gas is via jet pipe Accelerating Removal.Burning gas generation process and exhaust process are
Synchronous progress, gas production rate is equal to deflation rate when engine stabilizer works.That is, on the one hand, powder charge must when burning
It must be vented simultaneously, increase always combustion chamber pressure and cause danger；On the other hand, to obtain thrust at a certain moment,
Powder charge at this time must burn.It is very difficult by two process separation by conventional route.
Therefore, those skilled in the art is dedicated to developing a kind of air storing type solid propellant power device of reloading,
It is mainly used in solid rail control engine, Variable Thrust Engine and variable-flow gas generator etc..
Summary of the invention
In view of the above drawbacks of the prior art, this invention takes following technological approaches.First is that using pulse pressure-charging: making
Burning is constantly loaded with multistage pulses powder column, does not need extinction process.Second is that increasing gas storage link: by powder charge combustion process
It is separated with jet pipe exhaust acting process, the two is respectively independent.Powder charge burning is intended merely to be pressurized to combustion gas tank, without same
When be vented；Exhaust work done makes its working medium and energy from combustion gas tank, no longer needs powder charge at this time while burning.
The purpose of the present invention is what is be achieved through the following technical solutions.
A kind of air storing type solid propellant power device of reloading, comprising: powder column transmitting device, powder charge filler, combustion
Gas storage room, controllable jet pipe and pressure monitoring and controlling device；
The powder column transmitting device includes: powder charge storage room rotary electric machine, powder charge storage room, the first powder charge push rod, second
Powder charge push rod, pulse powder charge and residual air release device.
Powder charge storage room is ring structure；Annular hollow portion places powder charge storage room rotary electric machine, is used for controlled loading of explosive
Storage room rotation；Multiple through slots are opened up along axial direction in ring structure, for placing pulse powder charge；First powder charge push rod will be in through slot
Pulse powder charge release, then via the second powder charge push rod push-in powder charge filler in；Residual air release device passes through pipeline and powder charge
Filler connection, the remaining combustion gas for being discharged before loading pulse powder charge in powder charge filler；
Powder charge filler is made of cylindrical type rotational structure and shell, and combustion chamber is provided on cylindrical surface, as pulse powder charge
The place of filling and burning, shell tight rotational structure, in gas storage chamber, residual air release device, the second powder charge push rod
There is opening in direction；Powder charge storage room and gas storage chamber is isolated as sealing element in powder charge filler；
It is open at the combustion chamber front head in solid propellant rocket or gas generator, external powder charge filler is formed
Confined space constitutes gas storage chamber, the high-temperature high-pressure fuel gas generated for storing burning, and release combustion gas is done as needed
Function；
Go out controllable jet pipe is installed in the gas outlet of the gas storage chamber, for adjusting gas output；
Pressure monitoring and controlling device is used to measure the pressure in gas storage chamber and the rotation of controlled loading of explosive filler；
The course of work: when original state, ignition signal accesses from external engine and causes ignition charge, lights main charge.
Gas storage sprays acting by controllable jet pipe and generates power, flow is adjustable in gas storage chamber.When pressure monitoring and controlling device is surveyed
When measuring the pressure in gas storage room lower than given threshold value m, illustrates that gas storage indoor fuel gas surplus is insufficient, need to load pulse
Powder charge.Motor drives powder charge filler to turn to residual air release station, and the remaining combustion gas in powder charge filler combustion chamber is passed through
Residual air release device is discharged outside this power device, to prevent pulse powder charge when filling by ignition.After residual air release, powder charge filling
Device turns to filling station in the same direction, and one piece of pulse powder charge is pushed to powder charge dress from powder charge storage room by powder charge push rod
It fills out in device.After filling, powder charge filler continues to rotate to the position of combustion chamber face gas storage chamber, by gas storage chamber
Interior high-temperature high-pressure fuel gas firing pulse powder charge generates, supplement combustion gas.After pulse powder charge all burnt, powder charge filling is thought highly of
The new residual air that turns to discharges station, repeats above procedure.It is given when the pressure in pressure monitoring and controlling device measurement gas storage room is higher than
When threshold value n, illustrate that gas storage indoor fuel gas has been expired, stop operating powder charge filler.In addition, working as one through slot of powder charge storage room
All powder charges all push after, the first powder charge push rod resets, and motor driven powder charge storage room rotates by a certain angle, allow next
A through slot for having powder charge is in drug delivery position.
Beneficial effect
1, gas storage link and pulse pressure-charging, which combine, can well solve solid propellant power device active switch machine
The problem of, really realize repeatedly starting.In addition, changing the rate of discharge of combustion gas by controllable jet pipe, may be implemented to thrust size
Accurate control.The above two o'clock makes solid power unit have energy management functionality, can flexibly be changed according to mission requirements
Thrust scheme.
2, using the high-temperature high-pressure fuel gas firing pulse powder charge in gas storage room, compared to traditional multiple-pulse solid-rocket
Engine eliminates the design of multi-stage ignition device, and sparking mode is simple, and system reliability is higher.
3, it is separated due to powder charge storage with burning, powder charge storage room does not need carrying gaseous-pressure in the present invention, and intensity is set
Meter requires low, more saves structural material compared to conventional solid propellant power device.
Detailed description of the invention
Fig. 1 is the device of the invention structure chart；
Fig. 2 is outside schematic diagram of the invention；
Fig. 3 is powder charge storage room left view of the invention；
Fig. 4 is powder charge storage room cross-sectional view of the invention；
Fig. 5 is residual air release station figure of the invention；
Fig. 6 is powder charge filling station figure of the invention；
Fig. 7 is powder charge burner's bitmap of the invention.
Wherein, 1-powder charge storage room rotary electric machine, the 2-the first powder charge push rod, 3-powder charge storage rooms, the 4-the second powder charge
Push rod, 5-pulse powder charges, 6-main charges, 7-powder charge fillers, 8-residual air release devices, 9-gas storage chambers, 10-pressures
Power measure and control device, 11-igniters, 12-jet pipe sealing elements, 13-controllable jet pipes.
Specific embodiment
The technical effect of design of the invention, specific structure and generation is made below with reference to attached drawing and embodiment further
Illustrate, to understand the purpose of the present invention, feature and effect.
As shown in Figure 1, a kind of air storing type solid propellant rocket of reloading, comprising: powder charge storage room rotary electric machine 1,
First powder charge push rod 2, powder charge storage room 3, the second powder charge push rod 4, pulse powder charge 5, main charge 6, powder charge filler 7, residual air are released
Put device 8, gas storage chamber 9, pressure monitoring and controlling device 10, igniter 11, jet pipe sealing element 12, valve control jet pipe 13.Residual air release
Device 8 is connect by pipeline with powder charge filler 7, and opening is connected to form close with powder charge filler 7 at 9 front head of gas storage chamber
Space is closed, tail portion is connected with controllable jet pipe 13.Main charge 6 is designed as internal combustion cast powder column, is close to wall surface in advance and casts in combustion gas
Inside storage room 9, the setting of igniter 11 on 6 surface of main charge close to nozzle end, its ignition lead by jet pipe sealing element 12 to
After draw, with external control circuit connect.
As shown in Fig. 2, being open at b for through slot in a of powder charge storage room 3, having opening at the c of pipeline.Powder charge filler
7 be driven by motor, it can be achieved that axial 360 ° of rotations, the first powder charge push rod 2 and the second powder charge push rod 4 be driven by motor, it can be achieved that
Straight-line feed, resetting movement.
As shown in Figure 3, Figure 4,3 annular hollow portion of powder charge storage room places powder charge storage room rotary electric machine 1, for controlling
Powder charge storage room rotates, and eight through slots are opened in ring structure and are distributed in octagon.Pulse powder charge 5 is set using cuboid Types of Medicine
It counts, five pieces of pulse powder charges 5 of proper alignment in each through slot of powder charge storage room 3.First powder charge push rod 2 can be by powder charge storage room 3
In pulse powder charge 5 be pushed to right side pipeline in, then by the second powder charge push rod 4 push-in powder charge filler 7 in.
When original state, ignition signal is accessed from external engine through ignition lead, and excites igniter 11, lights main charge
6, jet pipe sealing element 12 is crushed by combustion gas impact and is sprayed outside engine.Gas storage passes through jet pipe in gas storage chamber 9
Release acting generates power.Jet pipe uses 13-valve control jet pipes, by switch throat and can adjust the modes controls such as throat opening area
Gas outlet flow processed, to realize switch control and thrust control.When pressure monitoring and controlling device 10 measures in gas storage chamber 9
When pressure is lower than given threshold value m, start to load work flow.
As shown in figure 5, powder charge filler 7, which rotates counterclockwise 90 °, discharges station to residual air, by the remaining combustion gas in combustion chamber
It is discharged outside this power device by residual air release device 8, pulse powder charge 5 is by ignition when to prevent loading later.Such as Fig. 6 institute
To show, after residual air release, powder charge filler 7 rotates counterclockwise 180 ° to filling station, and combustion chamber opening is towards loading pipeline, and second
Powder charge push rod 4 carries out feed motion, resets after one piece of pulse powder charge is pushed into filler cavity.As shown in fig. 7, having loaded
Bi Hou, powder charge filler 7 rotate counterclockwise 90 °, and combustion chamber is open towards gas storage chamber 9, by the high temperature in gas storage chamber 9
High-pressure gas firing pulse powder charge 5 generates, supplement combustion gas.The first powder charge push rod 2 pushes one piece out of powder charge storage room 3 simultaneously
Loading pipeline is sent into pulse powder charge 5, in case load next time.After 5 all burnt of pulse powder charge, powder charge filler 7 turns again
Station is discharged to residual air, repeats above procedure.It is higher than given threshold when pressure monitoring and controlling device 10 measures the pressure in gas storage chamber 9
When value n, illustrate that combustion gas has been expired in gas storage chamber 9, stop operating powder charge filler 7.
It illustrates, after five pieces of pulse powder charges 5 of 3 one through slots of powder charge storage room all push, the first dress
Medicine push rod 2 resets, and powder charge storage room rotary electric machine 1 drives powder charge storage room 3 to rotate clockwise 45 °, and allowing next has powder charge
Through slot is in drug delivery position.In addition, 7 actuation encapsulation process of powder charge filler, is isolated powder charge storage room 3 and combustion gas as sealing element
Storage room 9, prevents gas leakage.
Above-described specific descriptions have carried out further specifically the purpose of invention, technical scheme and beneficial effects
It is bright, it should be understood that the above is only a specific embodiment of the present invention, the protection model being not intended to limit the present invention
It encloses, all within the spirits and principles of the present invention, any modification, equivalent substitution, improvement and etc. done should be included in the present invention
Protection scope within.
Claims (4)
1. a kind of air storing type solid propellant power device of reloading, it is characterised in that: include: powder column transmitting device, powder charge
Filler, gas storage chamber, controllable jet pipe and pressure monitoring and controlling device；
The powder column transmitting device includes: powder charge storage room rotary electric machine, powder charge storage room, the first powder charge push rod, the second powder charge
Push rod, pulse powder charge and residual air release device；
Powder charge storage room is ring structure；Annular hollow portion places powder charge storage room rotary electric machine, stores for controlled loading of explosive
Room rotation；Multiple through slots are opened up along axial direction in ring structure, for placing pulse powder charge；First powder charge push rod is by the arteries and veins in through slot
Powder charge release is rushed, then via in the second powder charge push rod push-in powder charge filler；Residual air release device is loaded by pipeline and powder charge
Device connection, the remaining combustion gas for being discharged before loading pulse powder charge in powder charge filler；
Powder charge filler is made of cylindrical type rotational structure and shell, and combustion chamber is provided on cylindrical surface, is loaded as pulse powder charge
With the place of burning, shell tight rotational structure, in gas storage chamber, residual air release device, the second powder charge push rod direction
There is opening；Powder charge storage room and gas storage chamber is isolated as sealing element in powder charge filler；
It is open at the combustion chamber front head in solid propellant rocket or gas generator, external powder charge filler forms closed
Space constitutes gas storage chamber, the high-temperature high-pressure fuel gas generated for storing burning, and release combustion gas acting as needed.
2. a kind of air storing type solid propellant power device of reloading as described in claim 1, it is characterised in that: described
The gas outlet of gas storage chamber goes out to install controllable jet pipe, for adjusting gas output.
3. a kind of air storing type solid propellant power device of reloading as described in claim 1, it is characterised in that: pressure is surveyed
Control device is used to measure the pressure in gas storage chamber and the rotation of controlled loading of explosive filler.
4. a kind of air storing type solid propellant power device of reloading as described in claim 1, it is characterised in that: worked
Journey: when original state, ignition signal accesses from external engine and causes ignition charge, lights main charge；Gas storage is in combustion gas
In storage room, acting is sprayed by controllable jet pipe and generates power, flow is adjustable；When in pressure monitoring and controlling device measurement gas storage room
Pressure when being lower than given threshold value m, illustrate that gas storage indoor fuel gas surplus is insufficient, need to load pulse powder charge；Motor drives
Powder charge filler turns to residual air release station, and the remaining combustion gas in powder charge filler combustion chamber is arranged by residual air release device
Out outside this power device, to prevent pulse powder charge when filling by ignition；After residual air release, powder charge filler turns in the same direction
Filling station is moved, is pushed to one piece of pulse powder charge in powder charge filler from powder charge storage room by powder charge push rod；It has loaded
Bi Hou, powder charge filler continue to rotate to the position of combustion chamber face gas storage chamber, by the high temperature and pressure in gas storage room
Combustion gas firing pulse powder charge generates, supplement combustion gas；After pulse powder charge all burnt, powder charge filler turns back to residual air and releases
Station is put, above procedure is repeated；When the pressure in pressure monitoring and controlling device measurement gas storage room is higher than given threshold value n, explanation
Gas storage indoor fuel gas has been expired, and stop operating powder charge filler；In addition, working as all powder charges of one through slot of powder charge storage room all
After push, the first powder charge push rod resets, and motor driven powder charge storage room rotates by a certain angle, and allowing next has the logical of powder charge
Slot is in drug delivery position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201910541656.7A CN110195665B (en) | 2019-06-21 | 2019-06-21 | Rechargeable gas storage type solid propellant power device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910541656.7A CN110195665B (en) | 2019-06-21 | 2019-06-21 | Rechargeable gas storage type solid propellant power device |
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| CN110195665A true CN110195665A (en) | 2019-09-03 |
| CN110195665B CN110195665B (en) | 2020-06-05 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110778416A (en) * | 2019-09-26 | 2020-02-11 | 湖北三江航天红林探控有限公司 | Pulse type attitude control thruster based on shared combustion chamber |
| CN110966116A (en) * | 2019-11-08 | 2020-04-07 | 上海新力动力设备研究所 | Free charge grain assembly fixture of solid rocket engine |
| CN111071491A (en) * | 2019-12-09 | 2020-04-28 | 西安近代化学研究所 | Annular solid propellant charging structure |
| CN111622863A (en) * | 2020-06-05 | 2020-09-04 | 湖北三江航天红林探控有限公司 | Thrust termination device of small solid rocket engine |
| CN115258200A (en) * | 2022-07-01 | 2022-11-01 | 宁波天擎航天科技有限公司 | Dual-mode variable-thrust propulsion system and propulsion method |
| CN115467762A (en) * | 2022-10-24 | 2022-12-13 | 中北大学 | Multi-pulse solid rocket engine grain storage and supply device |
| CN115822814A (en) * | 2022-09-23 | 2023-03-21 | 哈尔滨工业大学 | Coaxial annular multi-electrode electric control solid thruster |
| CN115822814B (en) * | 2022-09-23 | 2024-07-02 | 哈尔滨工业大学 | Coaxial annular multi-electrode electric control solid thruster |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110778416A (en) * | 2019-09-26 | 2020-02-11 | 湖北三江航天红林探控有限公司 | Pulse type attitude control thruster based on shared combustion chamber |
| CN110966116A (en) * | 2019-11-08 | 2020-04-07 | 上海新力动力设备研究所 | Free charge grain assembly fixture of solid rocket engine |
| CN111071491A (en) * | 2019-12-09 | 2020-04-28 | 西安近代化学研究所 | Annular solid propellant charging structure |
| CN111071491B (en) * | 2019-12-09 | 2023-08-11 | 西安近代化学研究所 | Annular solid propellant charging structure |
| CN111622863A (en) * | 2020-06-05 | 2020-09-04 | 湖北三江航天红林探控有限公司 | Thrust termination device of small solid rocket engine |
| CN111622863B (en) * | 2020-06-05 | 2021-04-06 | 湖北三江航天红林探控有限公司 | Thrust termination device of small solid rocket engine |
| CN115258200A (en) * | 2022-07-01 | 2022-11-01 | 宁波天擎航天科技有限公司 | Dual-mode variable-thrust propulsion system and propulsion method |
| CN115822814A (en) * | 2022-09-23 | 2023-03-21 | 哈尔滨工业大学 | Coaxial annular multi-electrode electric control solid thruster |
| CN115822814B (en) * | 2022-09-23 | 2024-07-02 | 哈尔滨工业大学 | Coaxial annular multi-electrode electric control solid thruster |
| CN115467762A (en) * | 2022-10-24 | 2022-12-13 | 中北大学 | Multi-pulse solid rocket engine grain storage and supply device |
| CN115467762B (en) * | 2022-10-24 | 2024-06-25 | 中北大学 | Multi-pulse solid rocket engine grain storage and drug supply device |
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|---|---|
| CN110195665B (en) | 2020-06-05 |
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