CN111734551A - Separated multi-stage thrust underwater power system and control method thereof - Google Patents
Separated multi-stage thrust underwater power system and control method thereof Download PDFInfo
- Publication number
- CN111734551A CN111734551A CN202010543441.1A CN202010543441A CN111734551A CN 111734551 A CN111734551 A CN 111734551A CN 202010543441 A CN202010543441 A CN 202010543441A CN 111734551 A CN111734551 A CN 111734551A
- Authority
- CN
- China
- Prior art keywords
- section
- engine
- endurance
- water inlet
- inlet pipe
- 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.)
- Granted
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/18—Composite ram-jet/rocket engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
- B63G8/00—Underwater vessels, e.g. submarines; Equipment specially adapted therefor
- B63G8/08—Propulsion
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B33/00—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide
- C06B33/06—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide the material being an inorganic oxygen-halogen salt
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06D—MEANS FOR GENERATING SMOKE OR MIST; GAS-ATTACK COMPOSITIONS; GENERATION OF GAS FOR BLASTING OR PROPULSION (CHEMICAL PART)
- C06D5/00—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets
- C06D5/06—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of two or more solids
-
- 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
- F02K9/10—Shape or structure of solid propellant charges
- F02K9/12—Shape or structure of solid propellant charges made of two or more portions burning at different rates or having different characteristics
-
- 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
- F02K9/28—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants having two or more propellant charges with the propulsion gases exhausting through a common nozzle
-
- 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
-
- 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
-
- 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
Abstract
The invention provides a separated multi-stage thrust underwater power system and a control method thereof. The boosting section is provided with thrust by a solid rocket engine, so that the thrust is increased, and the acceleration time is shortened. The continuous voyage section is pushed by the solid water pressure engine, so that the specific impulse and the duration of the engine are improved. The boosting section solid rocket engine is improved, the boosting section engine is designed into an annular hollow shape and is nested outside a afterburning chamber of the water-jet engine, and the uniform annular shape can ensure that a navigation body is uniformly stressed when the boosting section engine is separated, so that the reliability of the engine is greatly improved.
Description
Technical Field
The invention relates to a separated multi-stage thrust underwater power system and a control method thereof, belonging to the technical field of underwater navigation power.
Background
Underwater vehicles are often employed to perform activities and tasks underwater due to their excellent ability to navigate autonomously through water. Most of traditional underwater vehicles adopt propeller type propulsion, the propulsion mode has the defects of low navigation speed and short navigation range, and meanwhile, a battery for providing energy for the propeller has a plurality of difficulties in long-term storage.
Aiming at the defects of the traditional propeller type propulsion, jet type propulsion systems are adopted in all countries in the world. The common jet power system is divided into a boosting section and a cruising section two-stage engine, wherein the cruising section adopts a metal fuel water thrust engine, and the thrust of the boosting section is provided by a plurality of small solid rocket engines bound on the outer wall of a vehicle body. The navigation body is firstly propelled and accelerated by the aid of the boosting section engine, when the speed meets the working requirement of the water-thrust engine, the boosting section engine with the plurality of small solid rocket engines is separated from the navigation body, the water-thrust engine starts to work to generate thrust, and the navigation body is guaranteed to finish subsequent navigation. However, the small solid rocket engine suspended on the outer wall brings unnecessary resistance to the accelerating stage of the navigation body, and when the small solid rocket engine is separated from the navigation body, the separation of all the small engines can not be accurately controlled at the same moment, so that uneven stress is caused on the navigation body, and the reliability of navigation is greatly reduced. Therefore, in order to solve the problem, the solid rocket engine at the boosting section is designed into a ring shape and is nested outside the water ramjet engine at the endurance section, so that the problem of uneven stress of the navigation body caused by the separation of the engine at the boosting section can be well solved, and the method has important significance for improving the performance of the navigation body.
Disclosure of Invention
Aiming at the defects that the speed of a navigation body propelled by a traditional underwater power system is low and the traditional jet power system is easy to cause uneven stress of the navigation body in the separation stage of a boosting engine, the invention aims to provide the separated type multistage thrust underwater power system and the control method thereof.
The purpose of the invention is realized as follows: the engine comprises a cruising section engine and a boosting section engine which are connected through an explosion bolt, wherein the cruising section engine comprises a cruising section engine shell, a cruising section water inlet pipeline, a cruising section fuel gas generator, a cruising section afterburning chamber and a cruising section tail spray pipe which are sequentially arranged in the cruising section engine shell, and a cruising section fuel column is arranged in the cruising section fuel gas generator; the boosting section engine comprises a boosting section engine shell connected with a cruising section engine shell, a boosting section engine grain arranged in the boosting section engine shell, and a boosting section engine tail jet pipe connected with the end part of the boosting section engine shell.
The invention also includes such structural features:
1. the engine shell of the continuation flight section comprises a shell front section and a stepped shell rear section, the large end of the shell rear section is connected with the shell front section, the outer diameters of the large ends of the engine shell of the boosting section, the shell front section and the shell rear section are equal, the engine shell of the boosting section is connected with the end face of the large end of the shell rear section, the engine grain of the boosting section is annular, two ends of the engine grain of the boosting section are connected with the engine shell of the boosting section through engine grain supporting pieces of the boosting section, and the small end of the shell rear section is located in the engine grain of the boosting section.
2. The water inlet pipeline of the endurance section comprises a main water inlet pipe, a water inlet pipe buffer chamber connected with the main water inlet pipe, and a primary water inlet pipe and a secondary water inlet pipe which are connected with the water inlet pipe buffer chamber, wherein the end parts of the primary water inlet pipe and the secondary water inlet pipe are respectively communicated with the afterburning chamber of the endurance section, and the pipeline is provided with a water inlet pipe ball valve; the endurance section fuel gas generator comprises an endurance section fuel gas generator front end socket, an endurance section fuel gas generator barrel and an endurance section fuel gas generator spray pipe which are sequentially connected, the endurance section afterburning chamber is communicated with the endurance section fuel gas generator spray pipe, and the endurance section tail spray pipe is connected with the end part of the endurance section afterburning chamber.
3. The primary water inlet pipe and the secondary water inlet pipe are respectively provided with four water inlet pipes and are alternately arranged, and the length of the secondary water inlet pipe is larger than that of the primary water inlet pipe.
4. The boosting section engine grain adopts metal-containing DB/Al/AP high-energy solid propellant; the grain in the endurance period adopts a nano aluminum-based solid propellant, and the propellant is a high-energy propellant prepared from 70-90% of aluminum, 7.5-20% of ammonium perchlorate and 2.5-10% of an adhesive in percentage by mass.
5. A control method of a separated multi-stage thrust underwater power system comprises the separated multi-stage thrust underwater power system, and specifically comprises the following steps:
(1) and (3) a boosting section acceleration stage: the engine does not work in the endurance section, the main water inlet pipe, the primary water inlet pipe (5) and the secondary water inlet pipe do not work in the endurance section, and the water inlet pipe valve in the endurance section is closed; the fuel gas generated by the combustion of the boosting section engine grain is sprayed out from the boosting section engine tail nozzle to generate thrust;
(2) a separation stage: stopping the engine at the boosting section, breaking the explosive bolt, and separating the engine at the boosting section from the navigation body;
(3) a endurance stage: and opening a water inlet pipe valve of the endurance section, starting the operation of a main water inlet pipe, a primary water inlet pipe and a secondary water inlet pipe of the endurance section, mixing high-temperature gas generated by self-sustaining combustion of a propellant in a fuel gas generator of the endurance section with the punched seawater in a afterburning chamber of the endurance section for secondary combustion, and spraying the generated gas out of a tail spray pipe of the endurance section to generate thrust.
Compared with the prior art, the invention has the beneficial effects that: the invention provides a separated multi-stage thrust underwater power system, which aims at the problem that a boosting section engine is hung on the side surface of a continuation voyage section engine in the traditional jet underwater power system, extra resistance is brought to an acceleration stage, and the stress of a voyage body is not uniform when the boosting section engine is separated from the voyage body. The design reduces the resistance of the navigation body in the acceleration stage, and greatly weakens the problem of uneven stress of the navigation body caused by the separation of the boosting section.
The invention provides a separated multi-stage thrust underwater power system.A DB/Al/AP solid propellant is adopted in a boosting section solid rocket engine, and an internal fuel column and an external fuel column are adopted in the design of a fuel column to increase the area of a combustion surface, so that the underwater high thrust acceleration of a navigation body is realized; the nano aluminum-based solid propellant is adopted in the water ramjet engine in the endurance period, and the nano aluminum particles can increase the contact area with seawater and promote the combustion of the propellant; meanwhile, the high-energy metal-based propellant can greatly improve the specific impulse and the endurance time of the engine in the endurance stage.
In the boosting and accelerating stage, a solid propellant of the boosting engine is combusted, and generated fuel gas is sprayed out from a tail spray pipe of the boosting section to provide thrust for the navigation body.
In the endurance stage, the nano aluminum metal-based propellant in the fuel gas generator in the endurance stage burns, the generated high-temperature fuel gas enters the afterburning chamber through the fuel gas generator spray pipe and reacts with seawater, and the generated high-temperature fuel gas is discharged from the tail spray pipe to generate thrust.
The separated type multistage thrust underwater power system provided by the invention has the advantages that the water thrust engine and the solid rocket engine are structurally nested, the reasonable layout of the underwater multistage propulsion device is realized, the working requirements of high-thrust acceleration and long-time continuous high-speed navigation are met, the problem of uneven stress of a navigation body caused by the separation of the boosting section engine is effectively reduced and even eliminated, and the comprehensive performance of the underwater navigation body is greatly improved.
Drawings
FIG. 1 is a perspective view of a split multi-stage thrust underwater power system of the present invention;
FIG. 2 is a sectional view of a split multi-stage thrust subsea power system of the present invention;
FIG. 3 is a perspective view of the range engine (including the housing);
FIG. 4 is a perspective view of the range engine (without the housing);
FIG. 5 is a cutaway view of the endurance section engine (including the case);
FIG. 6 is a perspective view of a booster stage engine;
FIG. 7 is a cross-sectional view of a booster stage engine;
FIG. 8 is a sectional view of a boost section engine A-A;
FIG. 9 is a boost stage engine charge support;
wherein, 1-endurance section fuel gas generator, 2-endurance section afterburning chamber, 3-endurance section tail nozzle, 4-endurance section main water inlet pipe, 5-endurance section primary water inlet pipe, 6-endurance section secondary water inlet pipe, 7-endurance section water inlet buffer chamber, 8-endurance section primary water inlet pipe valve, 9-endurance section secondary water inlet pipe valve, 10-endurance section fuel gas generator front head, 11-endurance section fuel gas generator barrel, 12-endurance section fuel gas generator nozzle, 13-endurance section afterburning chamber front cover, 14-endurance section afterburning chamber barrel, 15-endurance section tail nozzle convergent section, 16-endurance section tail nozzle expansion section, 17-endurance section explosive column, 18-endurance section explosive column elastic cushion, 19-endurance section engine shell front section, 20-the rear section of a casing of a continuation-journey section engine, 21-the casing of a boosting section engine, 22-a powder column of the boosting section engine, 23-a supporting piece of the powder column of the boosting section engine, 24-a tail jet pipe of the boosting section engine, and 25-an explosion bolt.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
With reference to fig. 1 to 9, the separated multi-stage thrust underwater power system provided in the present invention mainly includes a cruising section engine and a boosting section engine connected in sequence.
Referring to fig. 3, 4 and 5, the endurance section engine comprises an endurance section water inlet pipeline, an endurance section fuel gas generator, an endurance section afterburning chamber, an endurance section tail nozzle and an endurance section engine shell. Wherein the continuation of journey section inlet channel includes continuation of journey section main inlet tube 4, and the buffer room 7 of intaking of continuation of journey section, the first inlet tube 5 of continuation of journey section, continuation of journey section secondary inlet tube 6, the first inlet tube valve 8 of continuation of journey section and continuation of journey section secondary inlet tube valve 9.
One end of the main water inlet pipe 4 of the endurance section is in threaded connection with a water inlet of the navigation body, and the other end of the main water inlet pipe is in threaded connection with a central hole of the water inlet buffer chamber 7 of the endurance section. One end of the primary water inlet pipe 6 and one end of the secondary water inlet pipe 7 of the endurance section are connected with eight openings on the side wall of the water inlet buffer chamber 7 of the endurance section through threads, and the other end of the primary water inlet pipe and the secondary water inlet pipe are connected with eight openings on the side wall of the afterburning chamber 2 of the endurance section through threads; the main water inlet pipe 4 is mainly used for conveying seawater from a water inlet of a navigation body to the endurance section water inlet buffer chamber 7, and the seawater is conveyed from the endurance section water inlet buffer chamber 7 to the primary water inlet and the secondary water inlet on the side wall of the endurance section afterburning chamber 2 through the primary water inlet pipe 6 and the secondary water inlet pipe 7 of the endurance section. All connections of the pipeline are threaded connections.
The endurance section fuel gas generator 1 comprises an endurance section fuel gas generator front seal head 10, an endurance section fuel gas generator barrel 11, an endurance section fuel gas generator spray pipe 12, an endurance section fuel column 17 and an endurance section fuel column elastic pad 18; the endurance segment afterburning chamber 2 comprises an endurance segment afterburning chamber front cover 13 and an endurance segment afterburning chamber barrel 14; the front seal head 10 of the endurance section fuel gas generator and the spray pipe 12 of the endurance section fuel gas generator are connected with two ends of the cylinder body 11 of the endurance section fuel gas generator through flanges; the endurance section explosive column 17 is adhered to an endurance section explosive column elastic pad 18 through an adhesive and is embedded in the cylinder body 15 of the endurance section fuel gas generator, and the endurance section explosive column elastic pad 18 is connected with the front seal head 10 of the endurance section fuel gas generator; namely, the front end and the rear end of a cylinder body 11 of the fuel gas generator at the endurance section are respectively connected with a front seal head 10 of the fuel gas generator at the endurance section and a spray pipe 12 of the fuel gas generator at the endurance section through flanges to form the fuel gas generator 1 at the endurance section, and a fuel column 17 at the endurance section is embedded in the cylinder body 11 of the fuel gas generator at the endurance section and is adhered to a fuel column elastic pad 18 at the endurance section. The elastic pad 18 of the explosive column in the endurance segment is used for filling a semi-ellipsoidal cavity of the front seal head 10 of the fuel gas generator in the endurance segment and protecting the explosive column from being damaged in the transportation process. One end of a front cover 13 of the endurance section afterburning chamber is connected with a spray pipe 12 of the endurance section gas generator through threads, and the other end of the front cover is connected with a cylinder 14 of the endurance section afterburning chamber through a flange to form an endurance section afterburning chamber 2.
The endurance section tail nozzle 3 comprises an endurance section tail nozzle convergent section 15 and an endurance section tail nozzle divergent section 16; one end of the nozzle convergent section 15 is connected with the afterburning chamber cylinder 14 through a flange, and the other end is connected with the nozzle divergent section 16 through a thread. The front section 19 of the engine shell of the endurance segment is connected with the rear section 20 of the engine shell of the endurance segment through a flange, and the two sections enclose the whole engine of the endurance segment inside the engine shell of the endurance segment. The nozzle extension 16 is flanged to the engine casing aft section 20 of the cruise section.
Referring to fig. 6, 7 and 8, the boost section engine includes a boost section engine housing 21, a boost section engine charge 22, a boost section engine charge support 23 and a boost section engine jet 24; the boosting section engine shell 21 and the boosting section engine tail jet pipe 24 are connected through flanges to form a boosting section engine main body, the boosting section engine grain 22 is located in the boosting section engine combustion chamber, two ends of the boosting section engine grain 22 are bonded with the boosting section engine grain support part 23, and the latter is welded on the inner wall of the boosting section engine shell 21.
Referring to fig. 2, the boosting section engine and the endurance section engine are connected through explosive bolts 25. A solid rocket engine is adopted for acceleration in the boosting acceleration section, and a DB/Al/AP high-energy solid propellant containing metal is adopted for the boosting engine, so that underwater high-thrust acceleration of the navigation body can be realized, and the acceleration time of the navigation body is greatly shortened. The water-flushed engine is adopted for propulsion in the endurance stage, the nano aluminum-based solid propellant is adopted as the water-flushed engine propellant, the propellant is a high-energy propellant prepared from 70-90% of aluminum Al, 7.5-20% of ammonium perchlorate AP and 2.5-10% of an adhesive by mass, and the performance of the engine in the endurance stage is greatly improved. The aluminum particles in the propellant are nano aluminum particles in the endurance stage, and the small-size particles can greatly increase the contact area of the aluminum particles and the oxidant, so that the combustion efficiency is improved. The scheme of secondary combustion is adopted in the endurance section, ammonium perchlorate AP and adhesive in the propellant in the endurance section are combusted in the fuel gas generator to release heat, the generated fuel gas brings molten metal droplets into the afterburning chamber, and unreacted high-temperature metal particles are subjected to secondary reaction with seawater in the afterburning chamber, so that the combustion efficiency of the propellant is greatly improved. The scheme of excessive water inflow is adopted in the aftercruise segment afterburning chamber, redundant seawater absorbs heat in high-temperature fuel gas and is vaporized into gas, the gas is sprayed out of the after-spraying pipe of the aftercruise segment along with the fuel gas, working media are added, and the acting capacity of the engine is enhanced. The afterburning chamber in the endurance period adopts a method of twice water intake, so that the problem of flameout of the engine in the endurance period due to excessive water intake is avoided, and the continuous work of the engine is ensured. The boosting section engine adopts an annular combustion chamber and annular internal and external combustion solid explosive columns. A cavity is reserved in the center of the annular structure of the boosting engine, and the water flushing engine at the endurance stage is embedded into the cavity and is connected with the boosting stage engine through an explosive bolt. And detonating the explosive bolt after the boosting section engine finishes working, and separating the boosting section engine from the endurance section engine. The design scheme of the split engine can effectively reduce the weight of the navigation body in the endurance stage and greatly improve the effective range.
A control method of a separated multi-stage thrust underwater power system specifically comprises the following steps:
and a boosting acceleration stage, wherein the navigation body starts to accelerate from a standstill. The primary water inlet pipe valve 8 and the secondary water inlet pipe valve 9 of the endurance section are closed, the water inlet pipeline does not work, specifically, the primary water inlet pipe 4, the primary water inlet pipe 5 and the secondary water inlet pipe 6 of the endurance section do not work, and the primary water inlet pipe valve 8 and the secondary water inlet pipe valve 9 of the endurance section are closed; the boosting section engine grain 22 is ignited and burned to generate high-temperature fuel gas which is sprayed out from the boosting section engine tail nozzle 24 to generate driving force.
In the separation stage, after the combustion of the powder column 22 of the boosting section engine is finished, the boosting section engine stops working, the explosive bolt 25 is burst off, and the boosting section engine is separated from the navigation body;
in the endurance stage, the endurance section explosive column 17 in the endurance section fuel gas generator 1 starts to burn, and the generated high-temperature fuel gas carries a large amount of unreacted aluminum particles to enter the endurance section afterburning chamber 2 through the endurance section fuel gas generator spray pipe 12; opening a primary water inlet pipe valve 8 and a secondary water inlet pipe valve 9 of the endurance section, and starting the operation of a water inlet pipeline, specifically starting a main water inlet pipe 4, a primary water inlet pipe 5 and a secondary water inlet pipe 6 of the endurance section; high-temperature gas generated by self-sustaining combustion of a propellant in the fuel gas generator 1 in the endurance section is mixed with seawater entering by stamping in the endurance section afterburning chamber 2 for secondary combustion, namely, the seawater entering the endurance section afterburning chamber 2 through a water inlet pipeline and nano aluminum particles perform secondary reaction, and the gas generated by combustion is discharged outwards through the tail nozzle 3 in the endurance section to provide driving force for the endurance section.
The invention relates to a separated multi-stage thrust underwater power system and a control method thereof. The boosting section is provided with thrust by a solid rocket engine, so that the thrust is increased, and the acceleration time is shortened. The continuous voyage section is pushed by the solid water pressure engine, so that the specific impulse and the duration of the engine are improved. The boosting section solid rocket engine is improved, the boosting section engine is designed into an annular hollow shape and is nested outside a afterburning chamber of the water-jet engine, and the uniform annular shape can ensure that a navigation body is uniformly stressed when the boosting section engine is separated, so that the reliability of the engine is greatly improved.
Claims (8)
1. The utility model provides an underwater power system of multistage thrust of disconnect-type which characterized in that: the engine comprises a cruising section engine and a boosting section engine which are connected through an explosion bolt, wherein the cruising section engine comprises a cruising section engine shell, a cruising section water inlet pipeline, a cruising section fuel gas generator, a cruising section afterburning chamber and a cruising section tail spray pipe which are sequentially arranged in the cruising section engine shell, and a cruising section fuel column is arranged in the cruising section fuel gas generator; the boosting section engine comprises a boosting section engine shell connected with a cruising section engine shell, a boosting section engine grain arranged in the boosting section engine shell, and a boosting section engine tail jet pipe connected with the end part of the boosting section engine shell.
2. The split multi-stage thrust subsea power system according to claim 1, wherein: the engine shell of the continuation flight section comprises a shell front section and a stepped shell rear section, the large end of the shell rear section is connected with the shell front section, the outer diameters of the large ends of the engine shell of the boosting section, the shell front section and the shell rear section are equal, the engine shell of the boosting section is connected with the end face of the large end of the shell rear section, the engine grain of the boosting section is annular, two ends of the engine grain of the boosting section are connected with the engine shell of the boosting section through engine grain supporting pieces of the boosting section, and the small end of the shell rear section is located in the engine grain of the boosting section.
3. A split multi-stage thrust subsea power system according to claim 1 or 2, characterized in that: the water inlet pipeline of the endurance section comprises a main water inlet pipe, a water inlet pipe buffer chamber connected with the main water inlet pipe, and a primary water inlet pipe and a secondary water inlet pipe which are connected with the water inlet pipe buffer chamber, wherein the end parts of the primary water inlet pipe and the secondary water inlet pipe are respectively communicated with the afterburning chamber of the endurance section, and the pipeline is provided with a water inlet pipe ball valve; the endurance section fuel gas generator comprises an endurance section fuel gas generator front end socket, an endurance section fuel gas generator barrel and an endurance section fuel gas generator spray pipe which are sequentially connected, the endurance section afterburning chamber is communicated with the endurance section fuel gas generator spray pipe, and the endurance section tail spray pipe is connected with the end part of the endurance section afterburning chamber.
4. The split multi-stage thrust subsea power system according to claim 3, wherein: the primary water inlet pipe and the secondary water inlet pipe are respectively provided with four water inlet pipes and are alternately arranged, and the length of the secondary water inlet pipe is larger than that of the primary water inlet pipe.
5. A split multi-stage thrust subsea power system according to claim 1 or 2, characterized in that: the boosting section engine grain adopts metal-containing DB/Al/AP high-energy solid propellant; the grain in the endurance period adopts a nano aluminum-based solid propellant, and the propellant is a high-energy propellant prepared from 70-90% of aluminum, 7.5-20% of ammonium perchlorate and 2.5-10% of an adhesive in percentage by mass.
6. The split multi-stage thrust subsea power system according to claim 3, wherein: the boosting section engine grain adopts metal-containing DB/Al/AP high-energy solid propellant; the grain in the endurance period adopts a nano aluminum-based solid propellant, and the propellant is a high-energy propellant prepared from 70-90% of aluminum, 7.5-20% of ammonium perchlorate and 2.5-10% of an adhesive in percentage by mass.
7. The split multi-stage thrust subsea power system according to claim 4, wherein: the boosting section engine grain adopts metal-containing DB/Al/AP high-energy solid propellant; the grain in the endurance period adopts a nano aluminum-based solid propellant, and the propellant is a high-energy propellant prepared from 70-90% of aluminum, 7.5-20% of ammonium perchlorate and 2.5-10% of an adhesive in percentage by mass.
8. A control method of a separated multi-stage thrust underwater power system is characterized by comprising the following steps: including the multistage thrust's of disconnect-type underwater power system specifically is:
(1) and (3) a boosting section acceleration stage: the engine does not work in the endurance section, the main water inlet pipe, the primary water inlet pipe (5) and the secondary water inlet pipe do not work in the endurance section, and the water inlet pipe valve in the endurance section is closed; the fuel gas generated by the combustion of the boosting section engine grain is sprayed out from the boosting section engine tail nozzle to generate thrust;
(2) a separation stage: stopping the engine at the boosting section, breaking the explosive bolt, and separating the engine at the boosting section from the navigation body;
(3) a endurance stage: and opening a water inlet pipe valve of the endurance section, starting the operation of a main water inlet pipe, a primary water inlet pipe and a secondary water inlet pipe of the endurance section, mixing high-temperature gas generated by self-sustaining combustion of a propellant in a fuel gas generator of the endurance section with the punched seawater in a afterburning chamber of the endurance section for secondary combustion, and spraying the generated gas out of a tail spray pipe of the endurance section to generate thrust.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010543441.1A CN111734551B (en) | 2020-06-15 | 2020-06-15 | Separated multi-stage thrust underwater power system and control method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010543441.1A CN111734551B (en) | 2020-06-15 | 2020-06-15 | Separated multi-stage thrust underwater power system and control method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111734551A true CN111734551A (en) | 2020-10-02 |
| CN111734551B CN111734551B (en) | 2022-08-02 |
Family
ID=72649313
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010543441.1A Active CN111734551B (en) | 2020-06-15 | 2020-06-15 | Separated multi-stage thrust underwater power system and control method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111734551B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112918650A (en) * | 2021-03-26 | 2021-06-08 | 河南科技学院 | Instantaneous acceleration system and method for autonomous underwater vehicle |
| CN113217227A (en) * | 2021-06-25 | 2021-08-06 | 哈尔滨工程大学 | Cross-medium dual-mode ramjet based on metal fuel and control method thereof |
| CN113830277A (en) * | 2021-10-22 | 2021-12-24 | 哈尔滨工程大学 | Underwater propeller and navigation body |
| CN114408145A (en) * | 2021-12-09 | 2022-04-29 | 哈尔滨工程大学 | Preheating type water inlet ramjet engine structure and control method |
| CN115107968A (en) * | 2022-06-13 | 2022-09-27 | 南昌航空大学 | Low-navigation-speed underwater ramjet engine and design method thereof |
| CN116357478A (en) * | 2023-03-17 | 2023-06-30 | 哈尔滨工程大学 | Combustion surface following type water stamping water supply method |
| CN116428075A (en) * | 2023-03-17 | 2023-07-14 | 哈尔滨工程大学 | Water ramjet engine control method based on coupling of combustion chamber pressure and water inflow |
| CN116357478B (en) * | 2023-03-17 | 2024-05-17 | 哈尔滨工程大学 | Combustion surface following type water stamping water supply method |
Citations (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3723817A1 (en) * | 1987-07-18 | 1989-01-26 | Rudolf Dr Wieser | Submarine |
| US4841724A (en) * | 1976-08-17 | 1989-06-27 | Rolls-Royce Plc | Rockets |
| USH1082H (en) * | 1991-01-03 | 1992-08-04 | Andrew James W | Main-stage solid-propellant rocket motor design |
| JPH09228892A (en) * | 1996-02-27 | 1997-09-02 | Japan Steel Works Ltd:The | Propulsion method for underwater running body and high propulsive pocket engine for under water running body |
| US6286410B1 (en) * | 1999-05-10 | 2001-09-11 | The United States Of Americas As Represented By The Secretary Of The Navy | Buoyantly propelled submerged canister for air vehicle launch |
| JP2004218465A (en) * | 2003-01-10 | 2004-08-05 | Tokai Univ | Solid rocket |
| JP2005147122A (en) * | 2003-10-09 | 2005-06-09 | Hiroyasu Tanigawa | Various rocket combined engine |
| RU2004137434A (en) * | 2004-12-22 | 2006-06-10 | Государственное образовательное учреждение высшего профессионального образовани Военно-морска академи им. Адм. Флота Советского Союза Н.Г. Кузнецова (RU) | DIRECT GAS AND JET ENGINE |
| JP2006266198A (en) * | 2005-03-25 | 2006-10-05 | Asahi Kasei Chemicals Corp | Two-stage thrust control rocket motor |
| WO2007065220A1 (en) * | 2005-12-08 | 2007-06-14 | Rocketone Aerospace Pty Ltd | Hybrid rocket system |
| US7254936B1 (en) * | 2004-04-26 | 2007-08-14 | Knight Andrew F | Simple solid propellant rocket engine and super-staged rocket |
| CN101417702A (en) * | 2008-06-25 | 2009-04-29 | 哈尔滨工程大学 | Underwater motor and thruster integrated apparatus |
| CN101546931A (en) * | 2009-04-28 | 2009-09-30 | 中国船舶重工集团公司第七一二研究所 | Integrated propeller |
| CN101871393A (en) * | 2010-05-31 | 2010-10-27 | 哈尔滨工程大学 | Engine based on vane-type metal-water reaction propulsion unit |
| US20110005193A1 (en) * | 2009-07-07 | 2011-01-13 | Thomas Clayton Pavia | Method and apparatus for simplified thrust chamber configurations |
| CN105370439A (en) * | 2015-12-01 | 2016-03-02 | 北京航空航天大学 | Spiral-flow type water-ramjet engine |
| US20170190446A1 (en) * | 2015-12-31 | 2017-07-06 | Lawrence Ellis Williams, Sr. | Centripetal aerodynamic platform spacecraft |
| CN107514318A (en) * | 2017-10-13 | 2017-12-26 | 哈尔滨工程大学 | Fire rocket engine center of gravity balancing device in a kind of underwater sailing body end |
| US9964073B1 (en) * | 2014-11-06 | 2018-05-08 | Florida Turbine Technologies, Inc. | Liquid rocket engine with hybrid electric motor driven pump |
| CN108730070A (en) * | 2018-04-28 | 2018-11-02 | 西北工业大学 | Burning solid rocket engine is pressed in classification |
| CN109798201A (en) * | 2018-12-19 | 2019-05-24 | 哈尔滨工程大学 | A kind of concealed multistage power underwater propeller of secondary mixing chamber and control method |
| CN109826707A (en) * | 2018-12-19 | 2019-05-31 | 哈尔滨工程大学 | Half clad type multistage power underwater bottom-sealing device of one kind and control method |
| CN209654135U (en) * | 2018-12-29 | 2019-11-19 | 西安北方惠安化学工业有限公司 | A kind of fourth hydroxyl complex solid rocket engine boost motor of dual chamber dual thrust |
-
2020
- 2020-06-15 CN CN202010543441.1A patent/CN111734551B/en active Active
Patent Citations (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4841724A (en) * | 1976-08-17 | 1989-06-27 | Rolls-Royce Plc | Rockets |
| DE3723817A1 (en) * | 1987-07-18 | 1989-01-26 | Rudolf Dr Wieser | Submarine |
| USH1082H (en) * | 1991-01-03 | 1992-08-04 | Andrew James W | Main-stage solid-propellant rocket motor design |
| JPH09228892A (en) * | 1996-02-27 | 1997-09-02 | Japan Steel Works Ltd:The | Propulsion method for underwater running body and high propulsive pocket engine for under water running body |
| US6286410B1 (en) * | 1999-05-10 | 2001-09-11 | The United States Of Americas As Represented By The Secretary Of The Navy | Buoyantly propelled submerged canister for air vehicle launch |
| JP2004218465A (en) * | 2003-01-10 | 2004-08-05 | Tokai Univ | Solid rocket |
| JP2005147122A (en) * | 2003-10-09 | 2005-06-09 | Hiroyasu Tanigawa | Various rocket combined engine |
| US7254936B1 (en) * | 2004-04-26 | 2007-08-14 | Knight Andrew F | Simple solid propellant rocket engine and super-staged rocket |
| RU2004137434A (en) * | 2004-12-22 | 2006-06-10 | Государственное образовательное учреждение высшего профессионального образовани Военно-морска академи им. Адм. Флота Советского Союза Н.Г. Кузнецова (RU) | DIRECT GAS AND JET ENGINE |
| JP2006266198A (en) * | 2005-03-25 | 2006-10-05 | Asahi Kasei Chemicals Corp | Two-stage thrust control rocket motor |
| WO2007065220A1 (en) * | 2005-12-08 | 2007-06-14 | Rocketone Aerospace Pty Ltd | Hybrid rocket system |
| CN101417702A (en) * | 2008-06-25 | 2009-04-29 | 哈尔滨工程大学 | Underwater motor and thruster integrated apparatus |
| CN101546931A (en) * | 2009-04-28 | 2009-09-30 | 中国船舶重工集团公司第七一二研究所 | Integrated propeller |
| US20110005193A1 (en) * | 2009-07-07 | 2011-01-13 | Thomas Clayton Pavia | Method and apparatus for simplified thrust chamber configurations |
| CN101871393A (en) * | 2010-05-31 | 2010-10-27 | 哈尔滨工程大学 | Engine based on vane-type metal-water reaction propulsion unit |
| US9964073B1 (en) * | 2014-11-06 | 2018-05-08 | Florida Turbine Technologies, Inc. | Liquid rocket engine with hybrid electric motor driven pump |
| CN105370439A (en) * | 2015-12-01 | 2016-03-02 | 北京航空航天大学 | Spiral-flow type water-ramjet engine |
| US20170190446A1 (en) * | 2015-12-31 | 2017-07-06 | Lawrence Ellis Williams, Sr. | Centripetal aerodynamic platform spacecraft |
| CN107514318A (en) * | 2017-10-13 | 2017-12-26 | 哈尔滨工程大学 | Fire rocket engine center of gravity balancing device in a kind of underwater sailing body end |
| CN108730070A (en) * | 2018-04-28 | 2018-11-02 | 西北工业大学 | Burning solid rocket engine is pressed in classification |
| CN109798201A (en) * | 2018-12-19 | 2019-05-24 | 哈尔滨工程大学 | A kind of concealed multistage power underwater propeller of secondary mixing chamber and control method |
| CN109826707A (en) * | 2018-12-19 | 2019-05-31 | 哈尔滨工程大学 | Half clad type multistage power underwater bottom-sealing device of one kind and control method |
| CN209654135U (en) * | 2018-12-29 | 2019-11-19 | 西安北方惠安化学工业有限公司 | A kind of fourth hydroxyl complex solid rocket engine boost motor of dual chamber dual thrust |
Non-Patent Citations (7)
| Title |
|---|
| AN, H等: "Structure Buckling Reliability Analysis for the Underwater Super-Speed Supercavitating Vehicle", 《ADVANCES IN FRACTURE AND DAMAGE MECHANICS X》 * |
| GANY, A.: "Innovative concepts for high-speed underwater propulsion", 《INTERNATIONAL JOURNAL OF ENERGETIC MATERIALS AND CHEMICAL PROPULSION》 * |
| 孙明芳: "水下火箭的推进原理和应用", 《舰载武器》 * |
| 张运刚等: "金属基燃料与水反应研究现状及应用前景", 《固体火箭技术》 * |
| 林明东等: "水冲压发动机进水管路系统设计与分析", 《固体火箭技术》 * |
| 袁夫彩等: "水下船体清刷机器人关键技术及其试验的研究", 《机械设计与研究》 * |
| 陈文武等: "跨介质冲压发动机理论性能与工作参数分析", 《航空学报》 * |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112918650A (en) * | 2021-03-26 | 2021-06-08 | 河南科技学院 | Instantaneous acceleration system and method for autonomous underwater vehicle |
| CN112918650B (en) * | 2021-03-26 | 2023-01-24 | 河南科技学院 | Instantaneous acceleration system and method for autonomous underwater vehicle |
| CN113217227A (en) * | 2021-06-25 | 2021-08-06 | 哈尔滨工程大学 | Cross-medium dual-mode ramjet based on metal fuel and control method thereof |
| CN113830277A (en) * | 2021-10-22 | 2021-12-24 | 哈尔滨工程大学 | Underwater propeller and navigation body |
| CN114408145A (en) * | 2021-12-09 | 2022-04-29 | 哈尔滨工程大学 | Preheating type water inlet ramjet engine structure and control method |
| CN115107968A (en) * | 2022-06-13 | 2022-09-27 | 南昌航空大学 | Low-navigation-speed underwater ramjet engine and design method thereof |
| CN115107968B (en) * | 2022-06-13 | 2023-04-18 | 南昌航空大学 | Low-navigational-speed underwater ramjet engine and design method thereof |
| CN116357478A (en) * | 2023-03-17 | 2023-06-30 | 哈尔滨工程大学 | Combustion surface following type water stamping water supply method |
| CN116428075A (en) * | 2023-03-17 | 2023-07-14 | 哈尔滨工程大学 | Water ramjet engine control method based on coupling of combustion chamber pressure and water inflow |
| CN116428075B (en) * | 2023-03-17 | 2024-04-30 | 哈尔滨工程大学 | Water ramjet engine control method based on coupling of combustion chamber pressure and water inflow |
| CN116357478B (en) * | 2023-03-17 | 2024-05-17 | 哈尔滨工程大学 | Combustion surface following type water stamping water supply method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111734551B (en) | 2022-08-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111734551B (en) | Separated multi-stage thrust underwater power system and control method thereof | |
| CN111734550B (en) | Built-in multistage thrust underwater power system and control method thereof | |
| CN109798201B (en) | Secondary mixing chamber hidden type multi-stage power underwater propeller and control method | |
| CN112879178B (en) | Solid rocket ramjet based on detonation combustion | |
| CN109519280B (en) | Turboprop direct-injection hybrid multistage-power underwater high-speed propeller and control method | |
| CN111749814B (en) | Cross-medium dual-mode ramjet based on metal fuel and control method | |
| CN113217227A (en) | Cross-medium dual-mode ramjet based on metal fuel and control method thereof | |
| RU2445491C2 (en) | Rocket power plant with non-sensitive arming and multiple operating modes, and its operating method | |
| CN109779785B (en) | Direct-injection type multistage power underwater high-speed propeller and control method | |
| CN100549399C (en) | A kind of high-frequency pulse pinking engine and controlling method thereof | |
| CN109826707B (en) | Semi-cladding type multistage power underwater high-speed propeller and control method | |
| EP0683376B1 (en) | Airbreathing propulsion assisted gun-launched projectiles | |
| CN106949498A (en) | It is a kind of that the punching engine that energetic material powder lifts thrust is sprayed into based on combustion chamber | |
| CN201165916Y (en) | Solid rocket engine | |
| CN114408145B (en) | Preheating type water inlet ramjet engine structure and control method | |
| CN112211745A (en) | Solid rocket engine structure with tail nozzle with special-shaped section | |
| CN116291952A (en) | Double continuous detonation mode rocket-based combined cycle engine | |
| CN113153580B (en) | Combined spray pipe of solid rocket engine | |
| CN104929809A (en) | Working method of detonation ram rocket | |
| CN112901371A (en) | Novel square tube solid rocket engine | |
| CN208847042U (en) | A kind of novel boost motor of supersonic cruising guided missile | |
| CN115479508B (en) | Self-starting turbine water stamping combined engine based on gas generator driving | |
| CN109026440A (en) | A kind of empty day propulsion system based on rocket combined engine | |
| CN111594315B (en) | Composite mechanism full-flow circulation supersonic propulsion system and working method thereof | |
| CN110905690B (en) | Turbine ramjet engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |