CN109098891B - Cross-medium ramjet based on solid propulsion - Google Patents
Cross-medium ramjet based on solid propulsion Download PDFInfo
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- CN109098891B CN109098891B CN201811185845.7A CN201811185845A CN109098891B CN 109098891 B CN109098891 B CN 109098891B CN 201811185845 A CN201811185845 A CN 201811185845A CN 109098891 B CN109098891 B CN 109098891B
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- Prior art keywords
- runner
- gas generator
- pulverized fuel
- storage tank
- baffle
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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
- 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
- F02K7/105—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 using a solid fuel
Abstract
The invention relates to a cross-medium ramjet based on solid propulsion. The flow passages are uniformly arranged on the outer circumference of the gas generator, and the flow passages and the gas generator are integrally designed, so that the normal work of the engine is ensured, and the streamline appearance of the gas generator is also ensured. The flow channel baffle is driven by a baffle driving motor to control the upper flow channel baffle and the lower flow channel baffle to be closed and opened, so that air inlet and water inlet modes are switched. The invention adopts the parallel flow passage to realize the integration of the cross-medium ramjet air inlet passage and the water inlet passage, and can realize the transportation, the stop and the flow control of the fuel by controlling the starting, the shutdown and the movement speed of the powder supply device, thereby better realizing the controllable supply of the powder fuel and meeting the gas flow requirements during different modes and thrust adjustment.
Description
Technical field
The present invention relates to the fields such as pulverized fuel punching press, solid-rocket punching press and water punching engine, and in particular to a kind of
Across medium power device based on solid propellant propulsion.
Background technique
Across medium aircraft is a kind of new concept aircraft that can be flown in the sky with underwater submariner, it has aircraft concurrently
The concealment of speed and submariner device, both can be motor-driven under water, launches a offensive from underwater, waterborne, can also paste extra large flight, implements hidden
Precision strike can efficiently use the blind area of radar and various detecting devices, start to attack suddenly to enemy's aircraft carrier, warship and submarine etc.,
With anti-strike and the multiple task ability of efficiently dashing forward.Early in 20~thirties of 20th century just it is proposed that diving aircraft or flight
The imagination of submarine, but it is limited to technical level, it is converted into type of project not successfully so far.With technology development in recent years, especially
It is the rapid development of composite technology and the exploitation of high specific energy energy-storage battery, is paved for the research and development across medium unmanned vehicle
Road；Meanwhile the contention to offshore area, control, it is hidden dash forward promotion of the anti-importance in terms of military theory but also across
Medium aircraft has attracted much attention.The military use across medium unmanned vehicle is proved by foreign countries, and proposes one
A little design schemes.At this stage, about the research across medium aircraft, primarily directed to the system configuration across medium aircraft, not yet
See about the open report across medium guided missile.One of the Major Difficulties of across medium vehicle technology development are dynamical system at present
System, it is desirable that across medium punching engine can be converted under two kinds of different operating mode and guarantee certain efficiency of combustion.
Summary of the invention
Defect and requirement background in view of the prior art, present invention combination current ultrasonic speed anti-warship guided missle and super-cavitation torpedo
Power device develop newest status, take the lead in for across medium aircraft concept being applied on anti-warship guided missle, propose a kind of novel
Across medium punching engine scheme based on solid propellant propulsion, can further improve guided missile concealment, mobility, evading property and speed change
Ability, so that it has broad application prospects on anti-warship guided missle.
Fig. 1 is axial section schematic diagram of the present invention.A kind of across the medium punching engine based on solid propellant propulsion includes combustion gas
Generator (1), runner (2), runner baffle (3), barrier driving motor (4), partition (5), atomizer (6), pulverized fuel storage
Case (7), piston (8), piston driving motor (9), powder feeder unit export (10), combustion chamber (11), jet pipe (12),
Gas generator (1) outer wall is weldingly connected with runner (2) wall surface, and runner (2) is evenly arranged in combustion gas
In the exterior circumference of device (1), runner (2) and gas generator (1) integrated design not only guarantee engine work, but also protect
The streamline shape of gas generator 1 is demonstrate,proved,
Partition (5) setting is internal in runner (2), and the front end of partition (5) is the junction of upper lower flow channel baffle, tail end
It is weldingly connected with atomizer (6) head seal, runner baffle, partition (5), atomizer (6) and runner side above
Inner wall forms inlet channel, and inlet channel is in gradually taper up shape from partition (5) front end toward tail end, runner baffle, partition below
(5), air intake duct is formed with the inner wall of the runner other side；
Gas generator (1) and runner (2) are all disposed within inside missile case；
Pulverized fuel storage tank (7) is placed in inside missile case, and pulverized fuel storage tank (7) is hollow cylindrical, pulverized fuel
The hollow part of storage tank (7) is equipped with combustion chamber (11), and thermal insulation layer is equipped between combustion chamber (11) and pulverized fuel storage tank (7) inner wall,
Powder feeder unit exports (10) and is arranged in pulverized fuel storage tank (7) inner wall, combustion chamber (11) is communicated to, with direction of flow
It is arranged in low-angle,
Pulverized fuel storage tank (7) one end connects piston (8) one end, piston (8) other end and piston driving motor (9) phase
Even, piston (8) is driven by piston driving motor (9), and pulverized fuel is pushed out to burning from powder feeder unit outlet (10) by piston (8)
Room (11),
Combustion chamber (11) tail portion is weldingly connected with jet pipe (12) head.
The working principle of the invention is: when guided missile transmitting (aerial) from ground, being introduced into aerial cruising phase, engine
Using aluminum-magnesium fuel-rich propellant combination magnesium, aluminum metal powder as fuel, air is oxidant, with pulverized fuel punching engine mould
State work；Into after underwater cruising condition, engine fuel is constant, uses seawater atomization instead at this time and is formed after the heating of combustion chamber
Overheated steam be oxidant using water punching engine and be aided with super with pulverized fuel water punching engine Modality work
Vacuole drag reduction technology realizes the prominent anti-, high-speed attacks of high speed, high speed hit characteristic.When guided missile is from underwater emission, then conversely, first
With pulverized fuel water punching engine Modality work, underwater cruise is realized；Into after aerial cruising phase, then rushed with pulverized fuel
Hydraulic motor Modality work.
The invention has the advantages that:
1, conventional solid punching press and water punching engine are compared, the present invention realizes the conversion of propulsion system bimodal and across Jie
Matter work, the advantages of sufficiently combining submariner in airflight and water, so that across medium guided missile has the anti-strike and more of efficiently dashing forward
Task ability；2, the present invention realizes that across medium ramjet engine air inlet is integrated with inlet channel using parallel runner, Yu Liu
When two kinds of working mode changes of the realization air inlet of motor driven flapper and water inlet are arranged in road junction, used oxidant is not done mutually
It disturbs；3, using aluminum-magnesium fuel-rich propellant combination magnalium pulverized fuel, by control the starting of powder feeder unit, shutdown and
Movement velocity is, it can be achieved that conveying, stopping and the flow control of fuel are expired to preferably realize the controllable supply of pulverized fuel
Gas flow demand when sufficient different modalities and thrust are adjusted.
Detailed description of the invention
Fig. 1 is a kind of across medium punching engine structural schematic diagram based on solid propellant propulsion of the present invention, wherein each label table
Show: 1 --- gas generator, 2 --- runner, 3 --- runner baffle, 4 --- barrier driving motor, 5 --- partition, 6 ---
Atomizer, 7 --- pulverized fuel storage tank, 8 --- piston, 9 --- piston driving motor, 10 --- powder feeder unit outlet,
11 --- combustion chamber, 12 --- jet pipe
Specific embodiment
In the following, the invention will be further described with reference to the drawings and specific embodiments:
Cruise section in the sky, using solid rocket ramjet combining powder fuel punching engine operating mode: high
Tenor oxidizing combustible is burnt in gas generator 1 as flame on duty, is generated the fuel-rich combustion gas of high temperature and is entered combustion chamber
11；At this point, motor 4 drives baffle 3 to be closed in motor body, motor 4 drives baffle 3 to open in gas generator shell, stream
Road is converted to air intake duct mode；Meanwhile fuel is pushed through piston 8 from the ejection of outlet 10, with incoming air in pulverized fuel storage tank 7
And the fuel-rich combustion gas of high temperature blends in a combustion chamber, and further burns, and generates high temperature and high pressure gas through 12 expansion work of jet pipe,
Generate thrust；
Underwater cruising phase, using solid rocket ramjet combining powder fuel water punching engine operating mode:
High metal content oxidizing combustible is burnt in gas generator 1 as flame on duty, generates the fuel-rich combustion of high temperature containing a large amount of metals
Gas simultaneously enters combustion chamber 11；At this point, motor 4 drives baffle 3 to open in motor body, motor 4 is driven in gas generator shell
Dynamic baffle 3 is closed, and runner is converted to inlet channel mode；Seawater enters combustion chamber after being atomized by runner and nozzle 6, fires in high temperature
Overheated steam is formed under gas effect；The then fuel-rich combustion gas of high temperature, pulverized fuel and vapor blending are burnt, and high-temperature fuel gas is generated
It expands to spray through jet pipe 12 and generates thrust.
Claims (4)
1. a kind of across medium punching engine based on solid propellant propulsion, including gas generator (1), runner (2), runner baffle
(3), barrier driving motor (4), partition (5), atomizer (6), pulverized fuel storage tank (7), piston (8), piston driving motor
(9), powder feeder unit exports (10), combustion chamber (11), jet pipe (12), and gas generator (1) and runner (2) are all disposed within guided missile
Enclosure interior, which is characterized in that
Gas generator (1) outer wall is weldingly connected with runner (2) wall surface, and runner (2) is evenly arranged in gas generator (1)
Exterior circumference on,
The runner baffle (3) has two pieces up and down, and runner baffle (3) is driven by barrier driving motor (4), lower flow channel gear in control
Plate closing is opened, thus switch air inlet and water inlet mode,
Partition (5) setting is internal in runner (2), and the front end of partition (5) is the junction of upper lower flow channel baffle, tail end and mist
Change nozzle (6) head seal to be weldingly connected, runner baffle above, partition (5), atomizer (6) and runner side inner wall
Form inlet channel, inlet channel from partition (5) front end toward tail end in gradually tapering up shape, following runner baffle, partition (5), with
The inner wall of the runner other side forms air intake duct；
The pulverized fuel storage tank (7) is placed in inside missile case, and pulverized fuel storage tank (7) is hollow cylindrical, pulverized fuel
The hollow part of storage tank (7) is equipped with combustion chamber (11), and thermal insulation layer is equipped between combustion chamber (11) and pulverized fuel storage tank (7) inner wall,
Powder feeder unit exports (10) and is arranged in pulverized fuel storage tank (7) inner wall, is communicated to combustion chamber (11),
Pulverized fuel storage tank (7) one end connects piston (8) one end, and piston (8) other end is connected with piston driving motor (9), living
It fills in (8) to be driven by piston driving motor (9), pulverized fuel is pushed out to combustion chamber from powder feeder unit outlet (10) by piston (8)
(11).
2. a kind of across medium punching engine based on solid propellant propulsion according to claim 1, which is characterized in that the stream
Road (2) and gas generator (1) integrated design, both guarantee engine work, guarantee the streamline of gas generator again
Shape.
3. a kind of across medium punching engine based on solid propellant propulsion according to claim 1, which is characterized in that the confession
Powder device outlet (10) and direction of flow are in that low-angle is arranged in pulverized fuel storage tank (7) inner wall.
4. a kind of across medium punching engine based on solid propellant propulsion according to claim 1, which is characterized in that the combustion
Room (11) tail portion is burnt to be weldingly connected with jet pipe (12) head.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811185845.7A CN109098891B (en) | 2018-10-11 | 2018-10-11 | Cross-medium ramjet based on solid propulsion |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811185845.7A CN109098891B (en) | 2018-10-11 | 2018-10-11 | Cross-medium ramjet based on solid propulsion |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109098891A CN109098891A (en) | 2018-12-28 |
| CN109098891B true CN109098891B (en) | 2019-11-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201811185845.7A Active CN109098891B (en) | 2018-10-11 | 2018-10-11 | Cross-medium ramjet based on solid propulsion |
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Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109736968B (en) * | 2019-01-11 | 2020-05-29 | 中国人民解放军国防科技大学 | Submaxillary air intake type solid rocket ramjet engine and mixing combustion device thereof |
| CN109630315B (en) * | 2019-02-25 | 2020-06-16 | 中国人民解放军国防科技大学 | Solid rocket scramjet engine, arc-shaped gas generator and central injection device |
| CN110107401A (en) * | 2019-05-08 | 2019-08-09 | 中国航空发动机研究院 | Across medium flight device power device based on empty water flow passage compact layout |
| CN110552813A (en) * | 2019-08-28 | 2019-12-10 | 中南大学 | Rotary cutting type powder supply system and powder fuel ramjet engine thereof |
| CN111594342A (en) * | 2020-04-28 | 2020-08-28 | 西北工业大学 | Air inlet bleed air powder supply device with controllable flow and method |
| CN111749814B (en) * | 2020-06-15 | 2022-06-17 | 哈尔滨工程大学 | Cross-medium dual-mode ramjet based on metal fuel and control method |
| CN111734550B (en) * | 2020-06-15 | 2022-07-15 | 哈尔滨工程大学 | Built-in multistage thrust underwater power system and control method thereof |
| CN112855392A (en) * | 2020-12-31 | 2021-05-28 | 厦门大学 | TBCC air inlet channel adjusting mechanism design method based on slider-crank principle |
| CN112918614B (en) * | 2021-01-22 | 2022-03-29 | 中国人民解放军国防科技大学 | Supercavitation navigation body and cavitation bubble flow control method adopting wake flow injection |
| CN113108654B (en) * | 2021-04-27 | 2021-11-23 | 西北工业大学 | Air water flushing combined cross-medium anti-ship anti-submarine missile |
| CN113756986B (en) * | 2021-09-14 | 2022-12-02 | 中南大学 | Multi-mode cross-domain combined power system |
| CN113879052B (en) * | 2021-10-22 | 2022-09-02 | 哈尔滨工程大学 | Cross-medium water stamping power system and aircraft |
| CN114017206A (en) * | 2021-10-22 | 2022-02-08 | 哈尔滨工程大学 | Submarine missile engine |
| CN114352436B (en) * | 2021-12-15 | 2023-01-20 | 西安航天动力研究所 | Metal powder fuel air-water cross-medium engine and control method thereof |
| CN114810425B (en) * | 2022-04-26 | 2023-07-18 | 中国人民解放军国防科技大学 | Variable-thrust underwater ultra-high-speed navigation body |
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| US3220181A (en) * | 1962-11-08 | 1965-11-30 | Texaco Experiment Inc | Split-flow solid fuel ramjet |
| US3807169A (en) * | 1973-06-13 | 1974-04-30 | Us Air Force | Integral precombustor/ramburner assembly |
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|---|---|
| CN109098891A (en) | 2018-12-28 |
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