CN116428916A - Boron-based stamping propulsion cross-medium aircraft - Google Patents
Boron-based stamping propulsion cross-medium aircraft Download PDFInfo
- Publication number
- CN116428916A CN116428916A CN202310214595.XA CN202310214595A CN116428916A CN 116428916 A CN116428916 A CN 116428916A CN 202310214595 A CN202310214595 A CN 202310214595A CN 116428916 A CN116428916 A CN 116428916A
- Authority
- CN
- China
- Prior art keywords
- water
- air
- boron
- heat exchanger
- tail
- 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.)
- Pending
Links
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 title claims abstract description 81
- 229910052796 boron Inorganic materials 0.000 title claims abstract description 81
- 239000007789 gas Substances 0.000 claims abstract description 120
- 239000002737 fuel gas Substances 0.000 claims abstract description 30
- 238000000926 separation method Methods 0.000 claims abstract description 30
- 239000004449 solid propellant Substances 0.000 claims abstract description 24
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 7
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 205
- 238000009434 installation Methods 0.000 claims description 50
- 238000002485 combustion reaction Methods 0.000 claims description 36
- 239000000446 fuel Substances 0.000 claims description 20
- 239000007788 liquid Substances 0.000 claims description 17
- 238000005192 partition Methods 0.000 claims description 13
- 238000000034 method Methods 0.000 claims description 11
- 210000001503 joint Anatomy 0.000 claims description 10
- 230000008569 process Effects 0.000 claims description 10
- 230000005540 biological transmission Effects 0.000 claims description 9
- 239000007787 solid Substances 0.000 claims description 9
- 230000001105 regulatory effect Effects 0.000 claims description 8
- 239000007921 spray Substances 0.000 claims description 7
- 238000004880 explosion Methods 0.000 claims description 6
- 238000006243 chemical reaction Methods 0.000 claims description 5
- 230000007246 mechanism Effects 0.000 claims description 4
- 230000004323 axial length Effects 0.000 claims description 3
- 238000012360 testing method Methods 0.000 description 40
- 239000003380 propellant Substances 0.000 description 24
- 238000013461 design Methods 0.000 description 14
- 229910052782 aluminium Inorganic materials 0.000 description 11
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 11
- 238000010586 diagram Methods 0.000 description 9
- 230000008901 benefit Effects 0.000 description 8
- 238000007789 sealing Methods 0.000 description 6
- 238000004364 calculation method Methods 0.000 description 5
- 230000007123 defense Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 5
- 239000007800 oxidant agent Substances 0.000 description 5
- 239000000047 product Substances 0.000 description 5
- 230000007704 transition Effects 0.000 description 5
- 241000251729 Elasmobranchii Species 0.000 description 4
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 4
- 238000009825 accumulation Methods 0.000 description 4
- 238000004891 communication Methods 0.000 description 4
- 238000002156 mixing Methods 0.000 description 4
- 230000001590 oxidative effect Effects 0.000 description 4
- 238000012546 transfer Methods 0.000 description 4
- 239000002360 explosive Substances 0.000 description 3
- 238000004080 punching Methods 0.000 description 3
- 230000004044 response Effects 0.000 description 3
- 239000013535 sea water Substances 0.000 description 3
- 238000004458 analytical method Methods 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 239000003814 drug Substances 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 238000011010 flushing procedure Methods 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 230000002265 prevention Effects 0.000 description 2
- 239000013589 supplement Substances 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- SNAAJJQQZSMGQD-UHFFFAOYSA-N aluminum magnesium Chemical compound [Mg].[Al] SNAAJJQQZSMGQD-UHFFFAOYSA-N 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000037237 body shape Effects 0.000 description 1
- 108010066114 cabin-2 Proteins 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000008236 heating water Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000011664 nicotinic acid Substances 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 230000036284 oxygen consumption Effects 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 230000008929 regeneration Effects 0.000 description 1
- 238000011069 regeneration method Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B17/00—Rocket torpedoes, i.e. missiles provided with separate propulsion means for movement through air and through water
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention relates to a boron-based ram propulsion cross-medium aircraft, comprising: cavitation device, auxiliary cabin section, gas generator, separator, boosting cabin section and guide device; the cavitation device, the auxiliary cabin section, the gas generating device, the separation device and the boosting cabin section are coaxially arranged; the cavitation device is connected to the head of the auxiliary cabin section, the gas generating device is connected to the tail of the auxiliary cabin section, the separation device is detachably connected to the tail of the gas generating device, and the boosting cabin section is connected to the tail of the separation device; the guiding device is arranged in the cavitation device; the head of the auxiliary cabin section is provided with a separable fairing, and the cavitation device is positioned in the fairing; the fuel gas generating device is filled with a boron-based solid propellant; the boosting cabin section is filled with a boosting agent; when the boron-based stamping propulsion cross-medium aircraft is transferred from air flight to underwater navigation, the separation device and the boost cabin section are separated from the gas generating device.
Description
Technical Field
The invention relates to the field of cross-medium aircrafts, in particular to a boron-based stamping propulsion cross-medium aircraft.
Background
At present, the common ocean battlefield weapon mainly comprises torpedoes and anti-ship missiles, wherein the torpedoes are used as a main underwater attack and defense weapon, and have the advantages of high attack power, good concealment, high hit rate, strong anti-interference capability and the like; the missile has the advantages of long voyage, high speed, strong maneuverability and the like. However, with the development of modern attack and defense technology, conventional aircrafts (missiles/torpedoes) sailing in a single medium have become increasingly difficult to efficiently break through a fleet backguidance network. Thus, the concept of a cross-medium aircraft is proposed.
Compared with a single-medium aircraft, the cross-medium aircraft has the characteristics of high air flight speed and good underwater hiding effect, can effectively enhance the maneuverability, flexibility and evading capability of weapons, has the capability of quick launching and response, is suitable for executing various complex tasks, and has very wide application prospect.
Currently existing cross-medium aircraft are based on anti-submarine missiles and rocket-assisted torpedoes. The research on the cross-medium aircraft at home and abroad mainly comprises two aspects of variant structure design and cross-medium propulsion technology. The common variant structural design mainly comprises a folding wing, a sweepback wing, a bionic wing and the like, and the wing section structure is changed to be suitable for air and underwater navigation and is used for low-speed low-altitude scenes and the like. Common cross-medium propulsion technologies are thermoelectric combined power systems, ram power systems, and the like.
The existing variable-configuration cross-medium aircraft is suitable for sailing in the air and water by changing the wing structure, is generally used for specific operation scenes, has limited operation capacity, and is suitable for working conditions such as low speed, low altitude and the like. In addition, aircraft structures are also complex and have very limited ability to be destroyed as a weapon in the ocean battlefield.
The existing cross-medium aircraft adopting the thermoelectric combined power system has the defects that the underwater power of the cross-medium aircraft is low and the endurance of the cross-medium aircraft is difficult to meet the design requirement due to the fact that the battery capacity is limited by the body of the cross-medium aircraft. For example, the "submarine aircraft" program proposed by the national defense advanced research program agency, which employs turbofan engines for providing air power and propeller motors for improving the power system for underwater navigation, respectively.
The existing anti-submarine missile and rocket assisted torpedo cross-medium aircraft have the problems of short range, low specific impact, slow cross-domain, easy interception and the like due to the adoption of a rocket engine boosting mode and a parachute water entering mode, for example, the Ictala anti-submarine missile in Australia and the sea spear rocket assisted torpedo in the U.S. The rocket engine boosting and parachute water entering mode is adopted to realize the cross-medium flight.
The existing novel cross-medium aircraft based on the ramjet engine is mainly used for researching a power scheme and is mainly used for researching a single working environment, and the working characteristics of the solid ramjet engine and the working characteristics of the water ramjet engine are representatively researched. For example, chen Wenwu et al propose a new cross-medium engine solution using the same metal-based (magnesium aluminum) solid propellant, employing a solid rocket ramjet mode of operation with air as the oxidant in the air, and a water ramjet mode with water as the oxidant in the water, and calculate the theoretical performance of the engine under typical conditions. Dan Lei and the like propose an air-water stamping combined cross-medium anti-ship anti-submarine missile, which adopts a composite magnesium rod as fuel, adopts oxygen and a liquid oxidant carried by the oxygen and the liquid oxidant to react with rich fuel gas generated by the magnesium rod in the air to generate thrust, and directly enters water to react with the magnesium rod in water to generate thrust. Du Quan and the like, has the capability of multi-frequency crossing over water and air, flying under Mach number 0-4 and sailing under water at high speed. Zhou Ling and the like design a cross-medium power system scheme based on a ramjet engine, adopt aluminum-based and magnesium-based metal propellants as energy sources of the cross-medium power system, and adopt an annular nested (parallel) gas generator arrangement scheme in the design of the gas generator.
[1] Chen Wenwu, huang Liya, xia Zhixun, li Peng fly. Analysis of theoretical performance and operating parameters of cross-medium ramjet engines [ J ]. Aviation journal, 2020,41 (11): 202-211.
[2] Du Quan, wang Yufeng, jie, mo Jianwei, chen Lei, zhu Xian, li Jianghan. A broad-band multifrequency multi-jump water-air turbine ramjet combined engine and a control method [ P ]. Shanxi province: CN114439645A,2022-05-06.
[3] Dan Lei, yang Yi, jin Bingning, showcase He Guojiang. An air-water ram combination cross-media anti-ship anti-submarine missile [ P ]. Shanxi province: CN113108654B,2021-11-23.
[4] Zhou Ling analysis of the trans-media dynamic system protocol and modal transformation study [ D ]. Harbin engineering university, 2021.DOI:10.27060/d.cnki. Ghbcu.2021.000535.
Disclosure of Invention
The invention aims to provide a boron-based stamping propulsion cross-medium aircraft.
To achieve the above object, the present invention provides a boron-based ram propulsion cross-medium aircraft comprising: cavitation device, auxiliary cabin section, gas generator, separator, boosting cabin section and guide device;
the cavitation device, the auxiliary cabin section, the gas generating device, the separation device and the boosting cabin section are coaxially arranged; the cavitation device is connected to the head of the auxiliary cabin section, the gas generating device is connected to the tail of the auxiliary cabin section, the separation device is detachably connected to the tail of the gas generating device, and the boosting cabin section is connected to the tail of the separation device;
The guide device is arranged in the cavitation device;
the head of the auxiliary cabin section is provided with a separable fairing, and the cavitation device is positioned inside the fairing;
the fuel gas generating device is filled with a boron-based solid propellant;
the boosting cabin section is filled with a boosting agent;
when the boron-based ram propulsion cross-medium aircraft is transferred from air flight to underwater navigation, the separation device and the boost cabin section are separated from the gas generating device.
According to one aspect of the invention, the boron-based ram propulsion cross-medium aircraft comprises, during airborne flight: a boosting phase, a cruising phase and a gliding phase;
when in the boosting stage, the boosting cabin section burns the boosting agent to provide power;
when the gas generator is in the cruising stage, a part of the boron-based solid propellant combusted by the gas generator generates primary gas, and the primary gas is powered after secondary combustion of the boost cabin section and the introduced air;
when in the cruising phase, the gas generating device is shut down;
the boron-based stamping propulsion cross-medium aircraft is separated from the auxiliary cabin section in the underwater navigation process, the fuel gas generating device combusts the boron-based solid propellant to generate primary fuel-rich fuel gas, and the primary fuel-rich fuel gas provides power after the fuel gas generating device is mixed with the introduced water for reaction.
According to one aspect of the invention, the auxiliary compartment and the gas generator are in the same cylindrical housing;
the separation device is connected with the end part of the cylindrical shell by adopting an explosion bolt;
the separation device includes: an annular hollow body and a signal generator disposed in the hollow body;
the signal generator is connected with the explosion bolt.
According to one aspect of the invention, the auxiliary compartment comprises: the warhead and the power supply are coaxially arranged in sequence;
the gas generating apparatus includes: the water stamping gas generator, the solid stamping gas generator and the first tail nozzle are coaxially arranged in sequence;
a first flow regulating valve is arranged on the first tail nozzle;
the water stamping gas generator comprises: the first hollow container is provided with a first igniter arranged at the head part of the first hollow container and a middle spray pipe arranged at the tail part of the first hollow container;
the first hollow container is filled with a boron-based solid propellant;
the first igniter is connected with the power supply;
the middle spray pipe is provided with a second flow regulating valve;
the solid-state gas generator comprises: a second hollow container, a second igniter, a plurality of foldable tail units arranged outside the second hollow container;
The head part of the second hollow container is communicated with the middle spray pipe, and the tail part of the second hollow container is communicated with the first tail spray pipe;
the second hollow container is filled with a boron-based solid propellant;
the foldable tail wing devices are positioned at the tail end of the second hollow container and are arranged at equal intervals along the circumferential direction of the second hollow container;
and an opening is formed in the side wall of the cylindrical shell, and the opening corresponds to the foldable tail wing device.
According to one aspect of the invention, the cavitation device comprises: the device comprises a conical cavitation device, a flow guide bowl structure, a flow control device, a gas-liquid transmission assembly and a gas-liquid transmission assembly, wherein the flow guide bowl structure is coaxially connected with the conical cavitation device;
the gas-liquid transmission assembly is communicated with the second hollow container;
the flow control device is located in the cylindrical shell and is arranged on the front side of the auxiliary cabin section.
According to one aspect of the invention, the conical cavitation device comprises: the cone cap part, the cone bottom part and the middle partition plate;
the large-diameter end of the conical cap part is fixedly connected with the conical bottom part;
the middle partition plate and the cone bottom part are arranged in the cone cap part at intervals, a mounting cavity for mounting the guide device is formed between the middle partition plate and the cone cap part, and a water inlet cavity is formed between the middle partition plate and the cone bottom part;
A plurality of water inlets used for communicating the water inlet cavity are arranged on the cone cap part between the middle partition plate and the cone bottom part at intervals;
the center of the cone bottom part is provided with a water outlet for communicating with the water inlet cavity.
According to one aspect of the invention, the bowl structure comprises: a connecting body and a plurality of bowl-shaped flow guiding portions;
the bowl-shaped diversion parts are arranged at intervals along the axial direction of the connecting main body;
the connecting main body is provided with a water inlet flow passage and an air outlet cavity;
the water inlet flow channel and the connecting main body are coaxially arranged and penetrate through two opposite ends of the connecting main body;
the air outlet cavity and the water inlet flow channel are coaxially arranged around the water inlet flow channel, and the air outlet cavity and the water inlet flow channel are mutually isolated;
an air outlet hole used for communicating the air outlet cavity is formed in the radial outer side wall of the connecting main body, and an air inlet hole used for communicating the air outlet cavity is formed in the axial rear end of the connecting main body;
the radial sizes of the bowl-shaped diversion portions adjacent to each other in the direction away from the conical cavitation device are sequentially increased, and the bowl-shaped diversion portions and the air outlet holes are sequentially alternately arranged.
According to one aspect of the present invention, the flow control device includes: the device comprises a first installation shell, a second installation shell, a water flow control unit and a cavitation air flow control unit;
the first installation shell is a hollow cone body as a whole, the small diameter end of the first installation shell is provided with a connecting opening, and the large diameter end of the first installation shell is provided with an air inlet connecting port and a water outlet connecting port;
the second installation shell is of an axisymmetric hollow structure, is coaxially arranged in the first installation shell with the first installation shell, and has one end which is a shell fixed end fixedly connected with the bottom of the first installation shell and the other end which is a shell butt joint end;
the first installation shell and the second installation shell enclose a first installation cavity for installing the cavitation air flow control unit;
the hollow part of the second installation shell forms a second installation cavity for installing the water flow control unit;
the shell butt end of the second installation shell is provided with a water inlet butt opening which is arranged beyond the connecting opening;
the shell fixed end of the second installation shell is provided with a connecting channel for communicating the second installation cavity with the water outlet connecting port;
the shell butt joint end of the second installation shell is coaxial with the connecting opening and is provided with an interval, an air outlet butt joint opening communicated with the first installation cavity is formed between the shell butt joint end and the connecting opening, and the first installation cavity is communicated with the air inlet connecting opening.
According to one aspect of the invention, the gas-liquid transfer assembly comprises: the device comprises an air duct, a water duct, a heat exchanger, an air duct and a water duct;
one end of the air duct is connected with an air inlet connection port of the flow control device, and the other end of the air duct is connected with the heat exchanger;
one end of the air entraining pipe is connected with the heat exchanger, and the other end of the air entraining pipe is connected with a second hollow container of the solid-gas generator; wherein the position where the gas-introducing pipe is connected with the second hollow container is adjacent to the tail end of the second hollow container;
one end of the water guide pipe is connected with the water outlet connection port of the flow control device, and the other end of the water guide pipe is connected with the heat exchanger;
one end of the water pipe is connected with the heat exchanger, and the other end of the water pipe is connected with a second hollow container of the solid-gas generator; wherein, the one end that the raceway is connected with the second cavity container is provided with atomizing nozzle.
According to one aspect of the invention, the heat exchanger is arranged between the water stamping gas generator and the solid stamping gas generator;
the heat exchanger includes: a hollow heat exchanger housing, a spiral heat exchange tube disposed within the heat exchanger housing;
The heat exchanger shell is of an annular hollow structure, two axial ends of the heat exchanger shell are respectively provided with an air collecting cavity structure for connecting the spiral heat exchange tubes, and two axial ends of the heat exchanger shell are respectively provided with a heat exchanger water inlet and a heat exchanger water outlet for communicating the hollow part of the heat exchanger shell and a heat exchanger air inlet and a heat exchanger air outlet for communicating the air collecting cavity structure;
the water inlet of the heat exchanger is connected with the water guide pipe, and the water outlet of the heat exchanger is connected with the water guide pipe;
the air inlet of the heat exchanger is connected with the air entraining pipe, and the air outlet of the heat exchanger is connected with the air guide pipe.
According to one aspect of the invention, the boost tank section comprises: the auxiliary cabin comprises an auxiliary cabin section main body, a plurality of air inlet channel structures and a plurality of tail vane components, wherein the air inlet channel structures and the tail vane components are arranged on the outer side face of the auxiliary cabin section main body;
the boost tank section body comprises: a combustion chamber and a tail pipe coaxially connected;
the structural length of the air inlet channel is consistent with the axial length of the main body of the boosting cabin section
The air inlet structure is provided with an air inlet used for communicating the combustion chamber with the outside and a switch mechanism arranged corresponding to the air inlet;
The air inlet channel is arranged adjacent to the front end of the boost cabin section main body along the axial direction of the boost cabin section main body;
along the axial direction of the main body of the boosting cabin section, the tail vane component is arranged adjacent to the tail end of the main body of the boosting cabin section.
According to the scheme, the invention has excellent capabilities in the aspects of quick response, long-distance striking, cross-domain outburst prevention attack and the like, and provides a new thought for the development of a new generation of cross-medium aircrafts.
According to one scheme of the invention, the revolving body appearance design is adopted, so that the aircraft can navigate in an air medium environment and a water medium environment without changing the geometric configuration.
According to the scheme of the invention, the ramjet engine is adopted as a power system, supersonic flight can be realized in the air, and a cavitation device is assisted in water, so that high-speed sailing of 200 knots is realized, and the burst prevention performance of the aircraft is forcefully improved.
According to the scheme, the water ramjet engine is adopted, air and water in a medium environment can be used as oxidants, the specific impulse of a propulsion system is promoted to be far higher than that of power devices such as a rocket engine, a motor and the like, and the range of an aircraft is effectively improved.
According to the scheme of the invention, the boron-based propellant is adopted, so that the fuel ignition is reliable, the combustion is stable, the energy density is high and the like while the quick response is realized.
According to the scheme, the intelligent regulation of the working state and the intelligent switching of the working mode of the aircraft are realized by adopting the designs of fuel flow regulation, a multi-stage structure, multiple water inflow, regenerative cooling and the like.
According to one scheme of the invention, the sharing concept also penetrates through the whole design process, and a revolving body configuration design and a punching propulsion system are adopted to realize the sharing of a cross-medium aircraft configuration and a cross-medium power scheme; the boosting medicine is placed in the air stamping combustion chamber, and the gas generator is used as the water stamping engine afterburner to realize space sharing; and the water for combustion is heated by utilizing the high-temperature combustion tail gas, so that energy sharing is realized.
According to the scheme, the invention combines the performance advantage of the ramjet engine and the physicochemical advantage of the boron-based propellant, simultaneously utilizes the appearance design of the revolving body, the flow regulating device, the super cavitation device, the multi-stage structure and the multi-stage water inlet design, has the advantages of cross-airspace attack, wide-speed-domain flight, long-distance attack, intelligent work and the like, effectively enhances the concealment, maneuverability and evading capability of the ocean battlefield weapon, and greatly widens the operational capability of the ocean battlefield weapon.
According to the scheme, the combustion tail gas generated by the water ramjet engine is used as cavitation gas, and the high-temperature and high-pressure property of the fuel gas is used for realizing complete cavitation of the aircraft during underwater operation, so that a high-pressure air source is not required to be additionally carried, the dead weight is effectively reduced, the effective load of the engine is increased, and the weapon damage effect is greatly improved.
According to one scheme of the invention, the invention provides the boron-based propellant as the fuel of the water ramjet engine, theoretical calculation shows that compared with the aluminum-based propellant, the water ramjet engine adopting the boron-based propellant can obtain better working performance, the voyage is improved by about one time under the same charge volume, and the secondary water inlet structure of the water ramjet engine is adopted,
according to the scheme, the sharing concept also penetrates through the whole design concept, and the revolving body configuration design and the punching propulsion system are adopted to realize the sharing of the cross-medium aircraft configuration and the cross-medium power scheme; the boosting medicine is placed in the air stamping combustion chamber, and the gas generator is used as the water stamping engine afterburner to realize space sharing; and the water for combustion is heated by utilizing the high-temperature combustion tail gas, so that energy sharing is realized.
Drawings
FIG. 1 is a block diagram schematically illustrating a boron-based ram propulsion cross-medium aircraft in flight in air, according to one embodiment of the invention;
FIG. 2 is a block diagram schematically illustrating a boron-based ram propulsion cross-medium aircraft while sailing in water, in accordance with one embodiment of the present invention;
FIG. 3 is an internal block diagram schematically illustrating a boron-based ram propulsion cross-medium aircraft in accordance with one embodiment of the invention;
FIG. 4 is a cross-sectional view schematically illustrating a boron-based ram propulsion cross-media aircraft in accordance with one embodiment of the invention;
FIG. 5 is a block diagram schematically illustrating a conical cavitation device in accordance with one embodiment of the present invention;
FIG. 6 is a cross-sectional view schematically illustrating a combination of a conical cavitation device and a bowl structure in accordance with one embodiment of the present invention;
FIG. 7 is a block diagram schematically illustrating a bowl configuration according to one embodiment of the invention;
FIG. 8 is a perspective view schematically illustrating a flow control device according to one embodiment of the present invention;
FIG. 9 is a cross-sectional view schematically illustrating a flow control device according to one embodiment of the present invention;
FIG. 10 is a cross-sectional view schematically illustrating a flow control device according to one embodiment of the present invention;
FIG. 11 is a cross-sectional view schematically illustrating the direction A-A in FIG. 10;
FIG. 12 is a cross-sectional view schematically showing the direction B-B in FIG. 10;
FIG. 13 is a cross-sectional view schematically illustrating the direction C-C in FIG. 10;
FIG. 14 is a cross-sectional view schematically showing the direction D-D in FIG. 10;
FIG. 15 is a block diagram schematically illustrating the connection of a flow control device to a gas-liquid delivery assembly according to one embodiment of the present invention;
FIG. 16 is a cross-sectional view schematically illustrating a heat exchanger according to one embodiment of the present invention;
FIG. 17 is a cross-sectional view schematically illustrating a heat exchanger according to one embodiment of the present invention;
FIG. 18 is a block diagram schematically illustrating a second hollow container according to one embodiment of the present invention;
FIG. 19 is a schematic representation of a boron-based ram propulsion cross-medium aircraft cruise segment air ram engine operating mode diagram in accordance with one embodiment of the invention;
FIG. 20 is a schematic representation of a water ramjet engine operating mode diagram during underwater navigation of a boron-based ram propulsion cross-medium aircraft in accordance with an embodiment of the invention;
FIG. 21 is a graph schematically illustrating the specific impulse of different propellants as a function of air-fuel ratio;
FIG. 22 is a graph schematically showing the specific wash of different propellants as a function of water to fuel ratio;
FIG. 23 is a schematic representation of an aircraft flight path for different propellants per unit charge volume;
FIG. 24 is a schematic representation of a boron-based ram propulsion cross-medium aircraft air ram engine test procedure tail flame plot in accordance with one embodiment of the invention;
FIG. 25 (a) is a pressure-time graph schematically illustrating a boron-based ram propulsion cross-medium aircraft in accordance with one embodiment of the invention;
FIG. 25 (b) is a graph schematically illustrating boron-based ram propulsion cross-medium aircraft thrust versus time, in accordance with one embodiment of the invention;
FIG. 26 (a) is a schematic representation of a water ramjet test tail flame plot for a boron-based ram propulsion cross-medium aircraft in test A conditions, in accordance with one embodiment of the invention;
FIG. 26 (b) is a schematic representation of a water ramjet test tail flame plot for a boron-based ram propulsion cross-medium aircraft in a test b state, in accordance with one embodiment of the invention;
FIG. 27 is a graph schematically illustrating boron-based ram propulsion cross-medium aircraft afterburner pressure versus time in accordance with one embodiment of the present invention;
FIG. 28 is a graph schematically illustrating boron-based ram propulsion cross-medium aircraft engine step thrust versus time in accordance with one embodiment of the invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required to be used in the embodiments will be briefly described below. It is apparent that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
In describing embodiments of the present invention, the terms "longitudinal," "transverse," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer" and the like are used in terms of orientation or positional relationship based on that shown in the drawings, which are merely for convenience of description and to simplify the description, rather than to indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operate in a specific orientation, and thus the above terms should not be construed as limiting the present invention.
The present invention will be described in detail below with reference to the drawings and the specific embodiments, which are not described in detail herein, but the embodiments of the present invention are not limited to the following embodiments.
In combination with fig. 1. Fig. 2, 3 and 4 show a boron-based ram-propelled cross-medium aircraft according to an embodiment of the present invention, comprising: cavitation device 1, auxiliary cabin section 2, gas generating device 3, separator 4, boost cabin section 5 and guiding device 6. In the embodiment, the whole boron-based stamping propulsion cross-medium aircraft adopts a revolving body shape design, and the aircraft can navigate in an air medium environment and a water medium environment without changing the geometric configuration. Wherein the cavitation device 1, the auxiliary cabin section 2, the gas generating device 3, the separation device 4 and the boosting cabin section 5 are coaxially arranged; specifically, cavitation device 1 connects the head at supplementary cabin section 2, and gas generator 3 connects the afterbody at supplementary cabin section 2, and separator 4 detachable connects the afterbody at gas generator 3, and booster cabin section 5 connects the afterbody at separator 4. In the present embodiment, the guide means 6 is provided inside the cavitation device 1; the head of the auxiliary cabin segment 2 is provided with a detachable fairing 7 and the cavitation device 1 is located inside the fairing 7. In the present embodiment, the gas generator 3 is filled with a boron-based solid propellant; the booster cabin segment 5 is filled with a booster. In this embodiment, the separation device 4 and the booster stage 5 are separated from the gas generator 3 when the boron-based ram propulsion cross-medium aircraft is turned from an aerial flight to a water voyage. Wherein, the separation device 4 and the boost cabin section 5 can be separated from the gas generating device 3 in a combined mode, and can also execute separation action in a single and sequential separation mode.
In this embodiment, the guiding device 6 is a control navigation system of the whole cross-medium aircraft, which can be implemented by using existing mature products, and will not be described herein.
In combination with fig. 1. As shown in fig. 2, 3 and 4, according to one embodiment of the present invention, a boron-based ram propulsion cross-medium aircraft includes, during airborne flight: a boosting phase, a cruising phase and a gliding phase; wherein, when in the boosting stage, the boosting cabin section 5 burns the boosting agent to provide power; when the vehicle is in the cruising stage, the gas generator 3 burns part of the boron-based solid propellant to generate primary gas, and the primary gas is powered after secondary combustion of the mixture of the boosting cabin section 5 and the introduced air; when in the cruise phase, the gas generator 3 is shut down. In the embodiment, the fairing 7 is separated from the auxiliary cabin section 2 in the underwater navigation process of the boron-based stamping propulsion cross-medium aircraft, the fuel gas generating device 3 burns the boron-based solid propellant to generate primary fuel-rich gas, and the primary fuel-rich gas provides power after the fuel gas generating device 3 is mixed with the introduced water for reaction.
In combination with fig. 1. As shown in fig. 2, 3 and 4, according to one embodiment of the invention, the auxiliary tank section 2 and the gas generator 3 are located in the same cylindrical housing 8. In the present embodiment, the auxiliary tank 2 and the gas generator 3 are provided in the same cylindrical casing 8 so as to have an overall streamline shape, thereby making it possible to navigate in water more advantageous. Specifically, the cylindrical shell 8 is a cylindrical hollow cylinder, and the head part of the cylindrical shell adopts a conical structure design. In the present embodiment, the separating device 4 is connected to the end of the cylindrical housing 8 by an explosion bolt; of course, in another embodiment, when the separation device 4 is required to be separated from the booster cabin segment 5, a connection can be made between the separation device 4 and the booster cabin segment 5, also with a clamping bolt, so that a controlled separation effect is achieved.
In the present embodiment, the separation device 4 includes: an annular hollow body and a signal generator disposed in the hollow body; the hollow main body is of an integral connection and support structure, and is hollow, so that the signal generator can be further conveniently installed, and the explosion bolt connected with other structures can be installed. In this embodiment, the signal generator is electrically connected to the explosive bolt, thereby achieving a controlled disconnection of the explosive bolt. In this embodiment, the signal generator can operate autonomously without being affected by other components, and can be implemented by using existing mature products, which will not be described in detail herein.
In combination with fig. 1. As shown in fig. 2, 3 and 4, the auxiliary compartment 2 comprises, according to one embodiment of the invention: a warhead 21 and a power supply 22 are coaxially arranged in this order. In the present embodiment, the power supply 22 is electrically connected to the warhead 21 for controlled excitation of the warhead 21, and likewise, the power supply 22 is also connected to the gas generator 3 on the rear side for controlled excitation of the gas generator 3, which is an electric energy device for the whole boron-based ram propulsion of the cross-medium aircraft.
In combination with fig. 1. As shown in fig. 2, 3 and 4, according to one embodiment of the present invention, the gas generating apparatus 3 includes: the water stamping gas generator 31, the solid stamping gas generator 32 and the first tail nozzle 33 are coaxially arranged in sequence; the first tail pipe 33 is provided with a first flow regulating valve 331 for controlling the gas outlet flow in the working state.
In the present embodiment, the water stamping gas generator 31 includes: the first hollow vessel 311, a first igniter 312 provided at the head of the first hollow vessel 311, and a middle nozzle 313 provided at the tail of the first hollow vessel 311. In the present embodiment, the first hollow container 311 is filled with a boron-based solid propellant. In this embodiment, the first igniter 312 is connected to the power source 22. In the present embodiment, the intermediate nozzle 313 is provided with a second flow regulating valve 3131; the middle nozzle 313 is used as a nozzle when the water stamping gas generator 31 works, and the second flow regulating valve 3131 is arranged to control the ejection flow of the gas. In this embodiment, the first igniter 312 is controlled by the cross-medium aircraft control program, and can be implemented by using the existing mature product through the "on-off" control with the power supply, which is not described herein.
In the present embodiment, the solid-gas generator 32 includes: a second hollow container 321, a second igniter 322, and a plurality of foldable tail units 323 disposed outside the second hollow container 321. In this embodiment, the second hollow vessel 321 communicates at its head with the intermediate nozzle 313 and at its tail with the first tail nozzle 33. In this embodiment, by providing the second hollow container 321 in communication with the middle nozzle 313, when the water stamping gas generator 31 is in operation, the hollow second hollow container 321 can be used to realize a blending reaction of primary fuel-rich gas inlet water to provide higher sailing power. In the present embodiment, the second hollow container 321 is filled with a boron-based solid propellant; which is operated in the cruise phase by the provision of a boron-based solid propellant to provide power in the cruise phase. In this embodiment, the second igniter 322 is also controlled by the cross-medium aircraft control program, and can be implemented by using the existing mature product through the "on-off" control with the power supply, which is not described herein.
In the present embodiment, the foldable tail device 323 is located at the rear end of the second hollow container 321 and is disposed at equal intervals along the circumferential direction of the second hollow container 321. In this embodiment, the foldable tail device 323 includes a mounting base, a foldable tail structure, and a steering engine. The foldable tail wing device 323 is arranged to realize that the foldable tail wing structure is popped up when the steering engine sails in water, and the control of the whole sailing direction is realized through the control of the steering engine. When the invention is flown in the air, the foldable tail structure is retracted to avoid the influence on other control structures. In the present embodiment, openings are provided in the side walls of the tubular housing 8 corresponding to the foldable tail units 323, through which openings the ejection of the foldable tail structures is achieved. In this embodiment, the overall tightness is ensured during navigation in water by corresponding sealing arrangements at the location where the foldable tail unit 323 is installed. For example, an installation chamber is provided at the opening position where the foldable tail device 323 is installed, so as to realize the integral sealing of the installation position, and further realize the complete sealing in a manner of setting a seal at the joint of the foldable tail and the steering wheel control lever, etc.
Referring to fig. 3 to 17, a cavitation device 1 according to an embodiment of the present invention is used to generate supercavitation when the present invention is sailed in water to ensure the sailing speed and stability of the present invention. Specifically, the cavitation device 1 includes: the device comprises a conical cavitation device 11, a guide bowl structure 12 coaxially connected with the conical cavitation device 11, a flow control device 13 connected with the guide bowl structure 12, and a gas-liquid transmission assembly 14 connected with the flow control device 13. In this embodiment, the cone cavitation device 11, the bowl structure 12 and the flow control device 13 are all axisymmetric structures. In this embodiment, the gas-liquid transfer assembly 14 is in communication with the second hollow vessel 321 for effecting the entrainment of gas into the flow bowl structure 12 and the transfer of water into the second hollow vessel 321 of the solid gas generator 32 during navigation through the water. In this embodiment, when the cavitation device 1 works, firstly, the conical cavitation device 11 completes partial cavitation, secondly, high-temperature fuel gas in the fuel gas generating device 3 is introduced as cavitation gas to supplement air, and finally, complete cavitation of the aircraft is realized, so that supercavitation is effectively ensured to wrap the whole navigation body.
In the present embodiment, the flow control device 13 is located inside the cylindrical housing 8, and the flow control device 13 is provided on the front side of the auxiliary trunk section 2. In this embodiment, the guide bowl structure 12 is connected to the outside of the head of the cylindrical housing 8, and the flow control device 13 is in butt joint with the inside of the head of the cylindrical housing 8, and further, the communication between the front end cone cavitation device 11 and the guide bowl structure 12 can be realized by setting a water inlet transition channel for water supply and a gas outlet transition channel for cavitation gas output at the head of the cylindrical housing 8, which is simple and reliable in structure and convenient to connect. In this embodiment, the flow control device 13 directs the fuel gas into the guide bowl structure 12 and flows out through the small holes in the guide bowl structure 12, so as to supplement the supercavitation air flow. By means of such a bowl structure 12 a stable, smooth transparent cavitation surface can be created, which is the most common configuration, at an incoming flow rate (10 m/s) or even lower.
As shown in connection with fig. 5 and 6, according to one embodiment of the present invention, the conical cavitation device 11 includes: a cone cap portion 111, a cone bottom portion 112, and an intermediate baffle 113. In the present embodiment, the large diameter end of the taper cap portion 111 is fixedly connected with the taper bottom portion 112; the middle partition plate 113 and the cone bottom part 112 are arranged in the cone cap part 111 at intervals, and are used for enclosing a mounting cavity for mounting the guide device 6 between the middle partition plate 113 and the cone cap part 111 and enclosing a water inlet cavity between the middle partition plate 113 and the cone bottom part 112; a plurality of water inlets 111a for communicating with the water inlet chamber are provided at intervals on the cone cap portion 111 between the intermediate partition 113 and the cone bottom portion 112. In the present embodiment, a water outlet 112a for communicating with the water inlet chamber is provided at the center of the cone bottom part 112. Furthermore, in the underwater navigation process, water is introduced into the water inlet cavity through the water inlet 111a and is delivered to the structure of the rear end through the water outlet 112a. In the present embodiment, 8 water inlets 111a are provided at equal intervals.
As shown in connection with fig. 6 and 7, according to one embodiment of the present invention, the bowl structure 12 includes: a connecting body 121 and a plurality of bowl-shaped deflector portions 122. In the present embodiment, a plurality of bowl-shaped guide portions 122 are provided at intervals in the axial direction of the connection body 121. In the present embodiment, the connection body 121 is provided with a water inlet flow passage 121a and an air outlet chamber 121b; the water inlet flow passage 121a is coaxially arranged with the connecting body 121 and penetrates through opposite ends thereof; one end of the water inlet channel 121a is in sealing butt joint with the water outlet 112a of the cone bottom part 112 of the cone cavitation device 11, and the other end of the water inlet channel is in sealing joint with a water inlet transition channel arranged at the head of the cylindrical shell 8.
In the present embodiment, the air outlet chamber 121b and the water inlet flow passage 121a are coaxially disposed around the water inlet flow passage 121a, and the air outlet chamber 121b and the water inlet flow passage 121a are isolated from each other; the air outlet cavity 121b is an annular cavity, and is coaxially and circumferentially arranged around the water inlet channel 121a and surrounds the water inlet channel 121 a. In the present embodiment, an air outlet hole 121c for communicating with the air outlet cavity 121b is provided on the radially outer side wall of the connection body 121, and an air inlet hole 121d for communicating with the air outlet cavity 121b is provided at the axially rear end of the connection body 121; in this embodiment, the air inlet hole 121d provided at the rear end of the connection body 121 is used for sealing and abutting with the air outlet transition passage provided at the head of the cylindrical housing 8. In this embodiment, a plurality of air inlets 121d are disposed at the rear end of the connecting body 121 and distributed in an annular array, and correspondingly, air outlet transition channels disposed at the head of the cylindrical housing 8 are disposed in one-to-one correspondence with the air inlets 121 d.
In the present embodiment, the radial dimensions of the adjacent bowl-shaped deflector portions 122 are sequentially increased in the direction away from the conical cavitation device 11. In the present embodiment, the bowl-shaped deflector portion 122 is provided with two, wherein the radial maximum dimension of the bowl-shaped deflector portion 122 at the front end is smaller than the radial maximum dimension of the bowl-shaped deflector portion 122 at the rear end. In this embodiment, the front side of the bowl-shaped diversion portion 122 at the front end and the front side of the bowl-shaped diversion portion 122 at the rear end are different in arrangement shape, wherein the front side of the bowl-shaped diversion portion 122 at the front end is a straight-sided conical surface, and the front side of the bowl-shaped diversion portion 122 at the rear end is an arc-sided conical surface.
In the present embodiment, the bowl-shaped flow guide portion 122 and the air outlet hole 121c are alternately arranged in order in a direction away from the conical cavitation device 11. In the present embodiment, a plurality of the air outlet holes 121c are provided at equal intervals along the circumferential direction of the connection body 121. It should be noted that the number of the air outlet holes 121c provided on the connecting body 121 may be set according to actual needs, for example, the number of circumferential arrangements or the number of axial arrangements.
As shown in fig. 3, 4, and 8 to 15, according to an embodiment of the present invention, the flow control device 13 is used to regulate the flow rate of the air and the flow rate of the water in real time according to the sailing condition. Specifically, the flow rate control device 13 includes: a first mounting housing 131, a second mounting housing 132, a water flow control unit 133 and a cavitation air flow control unit 134. In the present embodiment, the first mounting case 131 is a hollow cone, and has a small diameter end provided with a connection opening 131a, and a large diameter end provided with an air inlet connection port 131b and a water outlet connection port 131c. In this embodiment, the second installation housing 132 is an axisymmetric hollow structure, and is coaxially disposed in the first installation housing 131, and one end of the second installation housing 132 is a housing fixed end fixedly connected to the bottom of the first installation housing 131, and the other end is a housing butt end. In the present embodiment, the first mounting housing 131 and the second mounting housing 132 enclose a first mounting cavity for mounting the cavitation air flow rate control unit 134; the hollow portion of the second mounting housing 132 constitutes a second mounting chamber in which the water flow rate control unit 133 is mounted. In the present embodiment, the housing-abutting end of the second mounting housing 132 is provided with a water-inflow-abutting opening 132a, which is provided beyond the connection opening 131 a; the housing fixing end of the second mounting housing 132 is provided with a connection passage for communicating the second mounting chamber with the water outlet connection port 131c. In the present embodiment, the housing abutting end of the second mounting housing 132 is coaxial with the connection opening 131a and has a space arrangement, and an air outlet-to-air interface communicating with the first mounting cavity is formed between the housing abutting end and the connection opening 131a, and the first mounting cavity is communicated with the air inlet connection opening 131 b.
In the present embodiment, the second mounting case 132 includes: a conical housing portion and a cylindrical housing portion coaxially disposed, wherein a housing mating end of the second mounting housing 132 is disposed at a small diameter end of the conical housing portion, and an end of the cylindrical housing portion remote from the conical housing portion constitutes a housing fixing end of the second mounting housing 132. In this embodiment, the radial dimension of the large diameter end of the conical housing part is larger than the radial dimension of the cylindrical housing part. In the present embodiment, the water flow rate control unit 133 is disposed coaxially with the cylindrical housing portion on the inner side thereof, and the cavitation air flow rate control unit 134 is disposed coaxially with the cylindrical housing portion on the outer side thereof.
Through the arrangement, the second installation shell 132 effectively increases the volume of the water inlet side of the second installation shell 132 by arranging the conical shell part at the front end, so that the input water can be stored more favorably, the water inlet side of the water flow control unit 133 can be effectively ensured to have sufficient water quantity to be conveyed to the rear side, and the working stability of the invention is ensured.
In addition, through the mode that sets up the toper casing part, still realized the cooperation of toper casing part lateral surface and first installation casing 131 for form an annular gas transmission passageway that has certain length in the axial between toper casing part and first installation casing 131, realized the outside gas transmission passageway of first installation chamber and radially reduce gradually, effectively guaranteed the stability of air current and made things convenient for the accurate control of gas flow.
In the present embodiment, the water flow regulator 133 has a cylindrical structure as a whole, and a water passage is provided at a central position thereof. In this embodiment, the water flow regulator 133 is used to regulate the flow of the incoming water while pressurizing the water flow to ensure that the water flow can enter the afterburner. Specifically, the size of the cross-section opening of the water channel can be controlled to control the corresponding water flow and water flow pressure, for example, at least one blade with an adjustable position can be arranged in the water channel to adjust the size of the cross-section opening, and of course, other structures can be adopted to realize the effect of adjusting the size of the cross-section opening, which is not repeated here.
In the present embodiment, the cavitation airflow control unit 134 has an annular structure as a whole, and a plurality of air passing passages are provided at intervals along the circumferential direction thereof. In the embodiment, the size of the cross-section opening of the air passage can be controlled to control the corresponding water flow and water flow pressure. For example, at least one vane with an adjustable position can be arranged in the air passage to adjust the size of the cross-section opening, and of course, other structures can be adopted to adjust the size of the cross-section opening, which will not be described herein.
As shown in fig. 4, 8 and 9, according to an embodiment of the present invention, two air inlet connection ports 131b and two water outlet connection ports 131c are provided, respectively, and are disposed at equal intervals from each other, wherein the two air inlet connection ports 131b are disposed opposite to each other and the two water outlet connection ports 131c are disposed opposite to each other in the radial direction of the first housing 131.
As shown in connection with fig. 9 to 14, according to an embodiment of the present invention, a diverting structure 1311 is provided in the first housing 131; wherein the shunt structure 1311 comprises: a baffle 1311a and a side plate 1311b. In the present embodiment, the baffle 1311a is an annular plate which is fitted over the outer side surface of the cylindrical housing part through a hollow portion, and the radially outer side surface thereof is connected to the inner side wall of the first housing 131. In the present embodiment, a side plate 1311b is located between the baffle 1311a and the bottom plate of the large diameter end of the first housing 131, for dividing a rear liquid accumulation chamber a communicating the second installation chamber with the water outlet connection port 131c and a rear gas collection chamber b communicating the first installation chamber with the air inlet connection port 131 b. In this embodiment, the post-liquid accumulation chambers a are disposed in one-to-one correspondence with the water outlet connection ports 131c, and the post-gas collection chambers b are disposed in one-to-one correspondence with the gas inlet connection ports 131 b.
In the present embodiment, the baffle 1311a is provided with an opening at a position corresponding to the rear-mounted gas collection chamber b.
As shown in connection with fig. 9-14, according to one embodiment of the present invention, the side plate 1311b is an elongated plate. Wherein, along the axial direction of the first housing 131, opposite ends of the side plate 1311b are respectively connected with the baffle 1311a and a bottom plate of the large diameter end of the first housing 131; in the present embodiment, opposite ends of the side plate 1311b are connected to the outer side wall of the cylindrical housing part and the inner side wall of the first housing 131, respectively, in the radial direction of the first housing 131; wherein the thickness of the side plate 1311b is gradually increased in a direction away from the cylindrical housing part. In the present embodiment, a plurality of side plates 1311b are provided at equal intervals in the circumferential direction of the first casing 131; four side plates 1311b are arranged at equal intervals, so that the space between the baffle 1311a and the bottom plate is divided into four equal parts, and a rear liquid accumulation cavity a and a rear gas collection cavity b which are needed are formed.
It should be noted that the air inlet connection port 131b and the water outlet connection port 131c in the present embodiment may be provided in other numbers, for example, 3, 4, etc., respectively. Correspondingly, the side plates 1311b are added on the flow dividing structure 1311, and the corresponding rear liquid accumulation cavities a and rear gas collection cavities b are correspondingly divided.
As shown in connection with fig. 3, 4, 6, 8, 9, 15-17, according to one embodiment of the present invention, the gas-liquid transfer assembly 14 includes: air duct 141, water duct 142, heat exchanger 143, air duct 144 and water duct 145. In the present embodiment, one end of the air duct 141 is connected to the air inlet connection port 131b of the flow rate control device 13, and the other end is connected to the heat exchanger 143; one end of the gas-introducing pipe 144 is connected with the heat exchanger 143, and the other end is connected with the second hollow container 321 of the solid-gas generator 32; wherein the bleed air pipe 144 is connected to the second hollow container 321 adjacent to the trailing end of the second hollow container 321. In the present embodiment, one end of the water conduit 142 is connected to the water outlet connection port 131c of the flow rate control device 13, and the other end is connected to the heat exchanger 143; one end of the water pipe 145 is connected with the heat exchanger 143, and the other end is connected with the second hollow container 321 of the solid-gas generator 32; wherein, the end of the water pipe 145 connected with the second hollow container 321 is provided with an atomizing nozzle.
In this embodiment, at least two pipelines connected to the second hollow container 321 are disposed on the same water pipe 145 at intervals, and each pipeline has a corresponding atomizing nozzle. Through the arrangement, the distribution range of water in the afterburner is increased, and the blending combustion in the afterburner is further promoted.
As shown in connection with fig. 16, 17 and 18, according to one embodiment of the present invention, a heat exchanger 143 is provided between the water-stamped gas generator 31 and the solid-stamped gas generator 32. In the present embodiment, the heat exchanger 143 includes: a hollow heat exchanger housing 1431, a spiral heat exchange tube 1432 disposed within the heat exchanger housing 1431; the heat exchanger shell 1431 is an annular hollow structure as a whole, and the two axial ends of the heat exchanger shell are respectively provided with an air collecting cavity structure for connecting the spiral heat exchange tubes 1432. And a heat exchanger water inlet 143a and a heat exchanger water outlet 143b which are used for communicating the hollow part of the heat exchanger shell 1431 are respectively arranged at two axial ends of the heat exchanger shell 1431, and a heat exchanger air inlet 143c and a heat exchanger air outlet 143d which are used for communicating the air collecting cavity structure are respectively arranged. In this embodiment, the heat exchanger water inlet 143a is connected to the water guide pipe 142, and the heat exchanger water outlet 143b is connected to the water guide pipe 145; the heat exchanger air inlet 143c is connected to the bleed air duct 144, and the heat exchanger air outlet 143d is connected to the air duct 141. The heat of the high-temperature fuel gas is used for heating water through the arranged heat exchanger 143, so that the heat regeneration of the high-temperature fuel gas is realized.
In the present embodiment, the spiral heat exchange tube 1432 is provided in plurality, wherein the spiral heat exchange tube 1432 is deflected by 90 ° while passing through the inside of the heat exchanger case 1431, and thus the heat exchanger inlet 143 c/heat exchanger inlet 143a and the heat exchanger outlet 143 d/heat exchanger outlet 143b are rotated by 90 ° after passing through the heat exchanger. Through the arrangement, the heat exchange distance and the heat exchange time between the low-temperature water and the high-temperature gas are effectively increased, so that the heat exchange effect is improved.
In this embodiment, the gas collecting cavity structure adopts an arc-shaped plate body, and the radial width of the gas collecting cavity structure is consistent with the radial width of the hollow part of the heat exchanger shell 1431, so that the gas collecting cavity structure is fixedly connected with the inside of the heat exchanger shell 1431 to form an arc-shaped gas collecting cavity. In this embodiment, the length of the gas collection chamber structure is five sixths of the circumferential length of the heat exchanger housing 1431. In this embodiment, the two ends of the gas collecting cavity structure in the circumferential direction are closed by using baffles to ensure that the gas collecting cavity is isolated from the rest of the hollow portion of the heat exchanger housing 1431. In this embodiment, the ends of the spiral heat exchange tubes 1432 are connected in an array on the gas collection chamber structure to achieve simultaneous communication of multiple spiral heat exchange tubes 1432 with the gas collection chamber.
In the present embodiment, two air ducts 141, 142, 144 and 145 are provided, and symmetrically provided on both sides of the combination of the auxiliary cabin 2 and the gas generator 3.
Since cavitation gas is taken from the end of the afterburner of the water ramjet engine, thermal calculations indicate that the gas temperature at the end of the afterburner reaches 2500K, and that such high temperatures are not required for operation of the aircraft, and that such high temperatures pose a significant threat to the safety of the entire aircraft after transmission through the pipeline. Meanwhile, the seawater temperature obtained from the external connection is about 280K, and experiments show that the lower the water temperature is, the more unfavorable the water ramjet engine works, and if the temperature of the water entering the afterburner can be increased, the engine working performance can be improved. Therefore, the invention provides the heat exchanger, and the heat in the high-temperature fuel gas is used for heating the seawater through the heat exchanger before the seawater enters the afterburner, so that the heat is regenerated and utilized.
As shown in connection with fig. 3 and 4, according to one embodiment of the invention, the booster stage 5 comprises: a boost tank main body 51, a plurality of air inlet structures 52 and a plurality of tail vane assemblies 53 arranged on the outer side surface of the boost tank main body 51. The boost tank section main body 51 includes: a combustion chamber 511 and a tail nozzle 512 connected coaxially. In this embodiment, the combustion chamber 511 is filled with a booster agent to achieve the boost stage flight after the present invention is thrown in. In the present embodiment, the length of the air intake passage structure 52 is set in conformity with the axial length of the trunk section main body 51; the intake duct structure 52 is provided with an intake duct 521 for communicating the combustion chamber 511 with the outside, and a switching mechanism provided in correspondence with the intake duct 521. In this embodiment, an igniter is also provided in the combustion chamber 511 for achieving controlled ignition of the booster. In this embodiment, the igniter may be implemented using existing mature products, and will not be described herein.
In the present embodiment, the air intake passage 521 is provided adjacent to the front end of the cabin section main body 51 in the axial direction of the cabin section main body 51; the air inlet 521 is disposed in an inclined manner relative to the axial direction of the boost tank main body 51, and forms a first opening on the outer side of the air inlet structure 52, and forms a second opening on the sidewall of the combustion chamber 511. The first opening is located in front of the second opening in the axial direction of the booster stage body 51. In the present embodiment, four air intake structures 52 are provided at equal intervals along the circumferential direction of the booster stage main body 51.
In the present embodiment, the tail vane assembly 53 is disposed adjacent to the trailing end of the booster stage body 51 in the axial direction of the booster stage body 51. In the present embodiment, the tail vane assembly 53 includes: the connection base, the fin part of connection on the connection base to and the steering wheel of control fin part, in this embodiment, along the circumference of boost cabin section main part 51, tail vane assembly 53 equidistant is provided with four, and tail vane assembly 53 and intake duct structure 52 dislocation set.
Through the arrangement, the tail vane assembly 53 is arranged in an X-shaped mode, the requirement of high maneuvering performance is effectively met, and the air inlet channel structure 52 is arranged in an X-shaped mode, so that the high-efficiency operation of the propulsion system is effectively kept.
To further illustrate the present solution, the course of its flight is further described in connection with fig. 1, 3, 4, 18 and 19.
Boosting section
After the aircraft is launched, the aircraft firstly enters a rocket mode, at the moment, an air inlet channel 521 of the boost cabin section 5 is in a closed state, solid propellant grains in the combustion chamber 511 are rapidly combusted, and high thrust is generated to push the aircraft to climb up to a ramjet engine starting speed and a cruising altitude.
Cruise section
The switch mechanism of the air inlet channel 521 of the boost cabin section 5 is opened when the air enters a punching mode, supersonic incoming flow enters the combustion chamber 511, secondary combustion and heat release are carried out by a primary gas mixing person generated by ignition and combustion of the solid-combustion gas generator 32, high-temperature gas is generated, and the high-temperature gas is expanded through the tail nozzle 512 and then is accelerated to be ejected out to generate thrust so as to maintain the cruising flight of the aircraft. In this embodiment, the first flow rate adjusting valve 331 disposed on the first tail nozzle 33 can affect the mass flow rate of the fuel gas, so as to change the heat release distribution in the afterburner, and further realize that the engine has better performance under different flight conditions, as shown in fig. 19.
Gliding section
After the cruising section is finished, the solid-flushing gas generator 32 is closed, and the aircraft continues to glide at a certain attack angle under the control of the tail vane component 53 by utilizing the kinetic energy and potential energy of the aircraft, so that the range is improved, the water entering speed is reduced, the impact load is reduced, and the water entering controllability is improved.
Interstage separation section
When the aircraft flies to approach the predetermined sea area by means of gliding, the explosive bolts are connected to the separation signals, the separation device 4 is disconnected from the front end structure, the separation device 4 and the boost tank section 5 are thrown away, and the solid-state gas generator 32 which is depleted of fuel is reserved and used as the afterburner of the water-stamped gas generator 31.
An underwater navigation section.
After entry into the water, the foldable tail unit 323 opens and throws the fairing 7. Subsequently, the water inlet channel of the cavitation device 1 is opened, and water is atomized by the nozzle and then sprayed into the second hollow container 321 of the solid-gas generator 32 to carry out blending reaction with primary rich fuel gas generated by the combustion of the water-gas generator 31. The resulting high temperature fuel gas is used to provide thrust, preheat the intake water, and generate supercavitation that encases the aircraft, see fig. 20.
In order to further explain the scheme, theoretical calculation and ground direct connection test are carried out on the working performance and feasibility of the invention.
(1) Workability of work
Boron-based propellant performance analysis
The stamping propulsion system adopted by the cross-medium aircraft adopts boron-based solid propellant when working in the air and water. To illustrate the performance advantages of using boron-based propellants, the more commonly used aluminum-based solid propellants are chosen here for performance comparison. The main components of the boron-based solid propellant and the aluminum-based solid propellant are shown in tables 1 and 2.
TABLE 1 boron-based propellant principal Components
TABLE 2 aluminium-based propellant main Components
The engine specific flushing of the two propellants in the high-altitude cruising section and the underwater cruising section is calculated respectively, and the basic working condition parameters of the high-altitude cruising section and the underwater cruising section ramjet engine are shown in table 3. Fig. 21 and 22 are graphs showing changes in engine specific blow with air-fuel ratio and water-fuel ratio under air-blow conditions and water-blow conditions, respectively.
TABLE 3 basic operating parameters
As is clear from fig. 21 and 22, the boron-based propellant ratio is lower than the aluminum-based propellant at a low air-fuel ratio because the oxygen consumption of the boron particles is large during the air-borne flight. At air-fuel ratios greater than 6, the theoretical performance of the boron-based propellant is significantly better than that of aluminum-based solid propellants. When sailing in water, the theoretical performance of the boron-based propellant is completely better than that of the aluminum-based propellant under any water-fuel ratio, and the boron-based fuel has larger performance advantages under water stamping working conditions compared with air stamping conditions. The calculation shows that compared with the aluminum-based propellant adopted at the present stage, the boron-based propellant adopted by the cross-medium aircraft in the air and water working process can enable the cross-medium ramjet engine to have larger performance advantages under the air stamping and water stamping conditions, and has higher theoretical performance.
Figure 23 shows the flight of an aircraft in air and under water for a unit charge volume using boron-based ram, aluminum-based ram, rocket boosting propulsion systems, respectively. It was found by comparison that when the boron-based ram propulsion system presented herein was employed, the range was doubled compared to an aluminum-based ram propulsion system, and was increased by about 6 times compared to a rocket-assisted propulsion system. Thus, further, the superiority of the present invention in providing cross-medium aircraft performance when employing boron-based ram propulsion systems is illustrated.
(2) Air ramjet demonstration test (i.e. series test of solid-gas generator 32 and boost tank section 5)
The ground direct connection test is carried out on the basis of the air ramjet engine provided by the invention, and the test system is provided by hypersonic speed key laboratories of national defense science and technology universities. The test simulates the flight conditions of 10km and 3Ma, and the test parameters are shown in Table 4.
TABLE 4 direct test condition parameter settings for air ramjet engine
In the test process, the tail flame of the engine is shown in fig. 24, and it can be seen that the test stamping engine can realize ignition combustion, primary fuel gas generated by the combustion of the boron-based propellant can be combusted in the afterburner and is fully combusted, so that bright tail flame is formed, and the tail flame is bright yellow-white.
The pressure data and the step thrust data collected in the test process are shown in fig. 25 (a) and 25 (b), and it can be seen that the engine works stably, the pressure of the gas generator is increased to some extent, the pressure of the afterburner is stable, and the thrust curve is slightly increased in the test process. The test ramjet engine is stable in combustion and reliable in operation.
Engine performance was calculated based on the test data, and the calculation results are shown in table 5. The average thrust of the engine reaches 2179.43N, the temperature rise combustion efficiency is 95.64%, and the thrust gain ratio of the ground direct connection test reaches 1029s. In conclusion, experiments show that the stamping engine adopted in the report can realize stable combustion, and meanwhile, the engine performance is higher, and engineering application indexes are basically met.
Table 5 direct test performance of air ramjet engine
(3) Demonstration test of water ramjet engine (i.e. series test of water ramjet gas generator 31 and solid ramjet gas generator 32)
The ground direct connection test is carried out based on the water ramjet engine provided by the invention, and the test system is provided by hypersonic speed key laboratories of national defense science and technology universities. The test uses a boron-based propellant with 33% boron content and water is preheated by a water heater with test parameters as shown in table 6.
TABLE 6 direct test condition parameter set for air ramjet engine
Through 2 tests, the water inlet structures in the two tests are different, wherein the test A is a two-time water inlet structure and the test B is a one-time water inlet structure. In the test process, the engine tail flame is shown in fig. 26 (a) and 26 (b), it can be seen that the test water ramjet engine can realize ignition in the two test processes, primary fuel gas generated by the combustion of the boron-based propellant can be mixed with water for secondary combustion in the afterburner, obvious green light can be seen from the edge of the tail flame, the primary fuel gas is not fully combusted in the afterburner, and the tail flame brightness is not much in the two configurations.
And further analyzing the engine performance by using the data acquired in the test. The combustion chamber pressure data and the step thrust number during the test are shown in fig. 27 and 28, respectively. Test data show that the water ramjet engine works stably, the pressure intensity of the afterburner and the thrust of the engine are stable, and the test water ramjet engine is stable in combustion and reliable in working. In addition, the pressure intensity of the afterburner and the thrust of the rack of the test A are obviously better than those of the test B, and the two water inlets are more beneficial to the primary gas combustion organization compared with the primary water inlet.
The foregoing is merely exemplary of embodiments of the invention and, as regards devices and arrangements not explicitly described in this disclosure, it should be understood that this can be done by general purpose devices and methods known in the art.
The above description is only one embodiment of the present invention, and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A boron-based ram propulsion cross-media aircraft, comprising: the device comprises a cavitation device (1), an auxiliary cabin section (2), a gas generating device (3), a separation device (4), a boosting cabin section (5) and a guiding device (6);
the cavitation device (1), the auxiliary cabin section (2), the gas generating device (3), the separation device (4) and the boosting cabin section (5) are coaxially arranged; the cavitation device (1) is connected to the head of the auxiliary cabin section (2), the gas generation device (3) is connected to the tail of the auxiliary cabin section (2), the separation device (4) is detachably connected to the tail of the gas generation device (3), and the boosting cabin section (5) is connected to the tail of the separation device (4);
The guide device (6) is arranged in the cavitation device (1);
the head of the auxiliary cabin section (2) is provided with a separable fairing (7), and the cavitation device (1) is positioned inside the fairing (7);
the fuel gas generating device (3) is filled with a boron-based solid propellant;
the boosting cabin section (5) is filled with a boosting agent;
when the boron-based ram propulsion cross-medium aircraft is transferred from air flight to underwater navigation, the separation device (4) and the boost cabin section (5) are separated from the gas generating device (3).
2. The boron-based ram propulsion cross-media aircraft of claim 1, wherein the boron-based ram propulsion cross-media aircraft comprises during an air flight: a boosting phase, a cruising phase and a gliding phase;
when in the boosting stage, the boosting cabin section (5) burns the boosting agent to provide power;
when in the cruising stage, the fuel gas generating device (3) burns part of the boron-based solid propellant to generate primary fuel gas, and the primary fuel gas provides power after secondary combustion of the boost cabin section (5) and the introduced air;
when in the cruising phase, the gas generating device (3) is shut down;
In the underwater navigation process of the boron-based stamping propulsion cross-medium aircraft, the fairing (7) is separated from the auxiliary cabin section (2), the fuel gas generating device (3) combusts the boron-based solid propellant to generate primary fuel-rich fuel gas, and the primary fuel-rich fuel gas provides power after the fuel gas generating device (3) is mixed with introduced water for reaction.
3. The boron-based ram propulsion cross-medium aircraft of claim 2, wherein the auxiliary cabin section (2) and the gas generating device (3) are within the same cylindrical housing (8);
the separation device (4) is connected with the end part of the cylindrical shell (8) by adopting an explosion bolt;
the separation device (4) comprises: an annular hollow body and a signal generator disposed in the hollow body;
the signal generator is connected with the explosion bolt.
4. A boron-based ram propulsion cross-medium aircraft according to claim 3, wherein the auxiliary cabin segment (2) comprises: a fighter part (21) and a power supply (22) which are coaxially arranged in sequence;
the gas generating device (3) comprises: the water stamping gas generator (31), the solid stamping gas generator (32) and the first tail nozzle (33) are coaxially arranged in sequence;
A first flow regulating valve (331) is arranged on the first tail nozzle (33);
the water stamping gas generator (31) comprises: a first hollow container (311), a first igniter (312) arranged at the head part of the first hollow container (311), and a middle spray pipe (313) arranged at the tail part of the first hollow container (311);
the first hollow container (311) is filled with a boron-based solid propellant;
the first igniter (312) is connected to the power source (22);
the intermediate nozzle (313) is provided with a second flow regulating valve (3131);
the solid-state gas generator (32) comprises: a second hollow container (321), a second igniter (322), a plurality of foldable tail units (323) arranged outside the second hollow container (321);
the head of the second hollow container (321) is communicated with the middle spray pipe (313), and the tail of the second hollow container is communicated with the first tail spray pipe (33);
the second hollow container (321) is filled with a boron-based solid propellant;
the foldable tail wing device (323) is positioned at the tail end of the second hollow container (321) and is arranged at equal intervals along the circumferential direction of the second hollow container (321);
an opening is formed in the side wall of the cylindrical shell (8) corresponding to the foldable tail wing device (323).
5. The boron-based ram propulsion cross-medium aircraft of claim 4, wherein the cavitation device (1) comprises: a cone cavitation device (11), a guide bowl structure (12) coaxially connected with the cone cavitation device (11), a flow control device (13) connected with the guide bowl structure (12), and a gas-liquid transmission assembly (14) connected with the flow control device (13);
the gas-liquid transmission assembly (14) is communicated with the second hollow container (321);
the flow control device (13) is located within the cylindrical housing (8), and the flow control device (13) is disposed on the front side of the auxiliary compartment (2).
6. The boron-based ram propulsion cross-medium aircraft of claim 5, wherein the cone cavitation (11) comprises: a cone cap portion (111), a cone bottom portion (112) and an intermediate baffle (113);
the large-diameter end of the cone cap part (111) is fixedly connected with the cone bottom part (112);
the middle partition plate (113) and the cone bottom part (112) are arranged in the cone cap part (111) at intervals, a mounting cavity for mounting the guide device (6) is formed between the middle partition plate (113) and the cone cap part (111), and a water inlet cavity is formed between the middle partition plate (113) and the cone bottom part (112);
A plurality of water inlets (111 a) for communicating the water inlet cavity are arranged on the cone cap part (111) between the middle partition plate (113) and the cone bottom part (112) at intervals;
the center of the cone bottom part (112) is provided with a water outlet (112 a) which is used for communicating the water inlet cavity.
7. The boron-based ram propulsion cross-media aircraft of claim 6, wherein the guide bowl structure (12) comprises: a connecting body (121) and a plurality of bowl-shaped flow guiding portions (122);
-a plurality of bowl-shaped deflector portions (122) arranged at intervals along the axial direction of the connecting body (121);
the connecting body (121) is provided with a water inlet flow channel (121 a) and an air outlet cavity (121 b);
the water inlet flow channel (121 a) and the connecting main body (121) are coaxially arranged and penetrate through two opposite ends of the connecting main body;
the air outlet cavity (121 b) and the water inlet flow channel (121 a) are coaxially arranged around the water inlet flow channel (121 a), and the air outlet cavity (121 b) and the water inlet flow channel (121 a) are mutually isolated;
an air outlet hole (121 c) for communicating the air outlet cavity (121 b) is formed in the radial outer side wall of the connecting main body (121), and an air inlet hole (121 d) for communicating the air outlet cavity (121 b) is formed in the axial rear end of the connecting main body (121);
The radial sizes of the bowl-shaped flow guide parts (122) which are adjacent to each other along the direction away from the conical cavitation device (11) are sequentially increased, and the bowl-shaped flow guide parts (122) and the air outlet holes (121 c) are sequentially alternately arranged.
8. The boron-based ram propulsion cross-medium aircraft of claim 7, wherein the flow control device (13) comprises: a first installation housing (131), a second installation housing (132), a water flow control unit (133) and a cavitation air flow control unit (134);
the first installation shell (131) is a hollow cone body as a whole, the small-diameter end of the first installation shell is provided with a connecting opening (131 a), and the large-diameter end of the first installation shell is provided with an air inlet connecting port (131 b) and a water outlet connecting port (131 c);
the second installation shell (132) is of an axisymmetric hollow structure, is coaxially arranged in the first installation shell (131) with the first installation shell (131), and has one end which is a shell fixed end fixedly connected with the bottom of the first installation shell (131) and the other end which is a shell butt joint end;
the first mounting shell (131) and the second mounting shell (132) enclose a first mounting cavity for mounting the cavitation air flow control unit (134);
the hollow part of the second installation shell (132) forms a second installation cavity for installing the water flow control unit (133);
The shell butt end of the second installation shell (132) is provided with a water inlet butt opening, and the water inlet butt opening is arranged beyond the connecting opening (131 a);
the shell fixed end of the second installation shell (132) is provided with a connecting channel for communicating the second installation cavity with the water outlet connecting port (131 c);
the shell butt joint end of the second installation shell (132) is coaxial with the connecting opening (131 a) and is provided with an interval, an air outlet butt joint opening communicated with the first installation cavity is formed between the shell butt joint end and the connecting opening (131 a), and the first installation cavity is communicated with the air inlet connecting opening (131 b).
9. The boron-based ram propulsion cross-media aircraft of claim 8, wherein the gas-liquid transport assembly (14) comprises: the air guide pipe (141), the water guide pipe (142), the heat exchanger (143), the air guide pipe (144) and the water guide pipe (145);
one end of the air duct (141) is connected with an air inlet connection port (131 b) of the flow control device (13), and the other end of the air duct is connected with the heat exchanger (143);
one end of the air entraining pipe (144) is connected with the heat exchanger (143), and the other end of the air entraining pipe is connected with a second hollow container (321) of the solid-gas generator (32); wherein the position where the bleed air pipe (144) is connected with the second hollow container (321) is adjacent to the tail end of the second hollow container (321);
One end of the water guide pipe (142) is connected with a water outlet connection port (131 c) of the flow control device (13), and the other end of the water guide pipe is connected with the heat exchanger (143);
one end of the water pipe (145) is connected with the heat exchanger (143), and the other end is connected with the second hollow container (321) of the solid-gas generator (32); wherein, the end of the water pipe (145) connected with the second hollow container (321) is provided with an atomizing nozzle.
10. The boron-based ram propulsion cross-medium aircraft of claim 9, wherein the heat exchanger (143) is disposed between the water ram gas generator (31) and the solid ram gas generator (32);
the heat exchanger (143) includes: a hollow heat exchanger housing (1431), a spiral heat exchange tube (1432) disposed within the heat exchanger housing (1431);
the heat exchanger shell (1431) is integrally of an annular hollow structure, two axial ends of the heat exchanger shell are respectively provided with an air collecting cavity structure for connecting the spiral heat exchange tubes (1432), and two axial ends of the heat exchanger shell (1431) are respectively provided with a heat exchanger water inlet (143 a) and a heat exchanger water outlet (143 b) for communicating the hollow part of the heat exchanger shell (1431) and a heat exchanger air inlet (143 c) and a heat exchanger air outlet (143 d) for communicating the air collecting cavity structure;
The water inlet (143 a) of the heat exchanger is connected with the water guide pipe (142), and the water outlet (143 b) of the heat exchanger is connected with the water guide pipe (145);
the heat exchanger air inlet (143 c) is connected with the air entraining pipe (144), and the heat exchanger air outlet (143 d) is connected with the air duct (141);
the boost tank section (5) comprises: a boost cabin section main body (51), a plurality of air inlet channel structures (52) and a plurality of tail vane components (53) arranged on the outer side surface of the boost cabin section main body (51);
the boost tank section body (51) comprises: a combustion chamber (511) and a tail pipe (512) coaxially connected;
the length of the air inlet channel structure (52) is consistent with the axial length of the boost cabin section main body (51)
The air inlet structure (52) is provided with an air inlet (521) for communicating the combustion chamber (511) with the outside, and a switch mechanism arranged corresponding to the air inlet (521);
along the axial direction of the boost tank section main body (51), the air inlet channel (521) is arranged adjacent to the front end of the boost tank section main body (51);
along the axial direction of the boost cabin section main body (51), the tail vane assembly (53) is arranged adjacent to the tail end of the boost cabin section main body (51).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310214595.XA CN116428916A (en) | 2023-03-08 | 2023-03-08 | Boron-based stamping propulsion cross-medium aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310214595.XA CN116428916A (en) | 2023-03-08 | 2023-03-08 | Boron-based stamping propulsion cross-medium aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116428916A true CN116428916A (en) | 2023-07-14 |
Family
ID=87088044
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310214595.XA Pending CN116428916A (en) | 2023-03-08 | 2023-03-08 | Boron-based stamping propulsion cross-medium aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116428916A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118514466A (en) * | 2024-07-25 | 2024-08-20 | 中国人民解放军国防科技大学 | Active flow control system and method for cross-medium aircraft |
-
2023
- 2023-03-08 CN CN202310214595.XA patent/CN116428916A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118514466A (en) * | 2024-07-25 | 2024-08-20 | 中国人民解放军国防科技大学 | Active flow control system and method for cross-medium aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109098891B (en) | Cross-medium ramjet based on solid propulsion | |
| CN113108654B (en) | Air water flushing combined cross-medium anti-ship anti-submarine missile | |
| CN108688829A (en) | Solid-liquid power sub-orbital booster | |
| WO2004092567A2 (en) | Integrated bypass turbojet engines for aircraft and other vehicles | |
| CN109519280B (en) | Turboprop direct-injection hybrid multistage-power underwater high-speed propeller and control method | |
| CN110131074B (en) | Bipropellant air turbine rocket propulsion system | |
| CN105736178A (en) | Combined cycle engine | |
| CN110566365B (en) | Mode-switchable solid combined engine and missile | |
| CN113756986B (en) | Multi-mode cross-domain combined power system | |
| CN113882968B (en) | Wide-speed-range multi-working-medium efficiency matching combined power system | |
| CN116428916A (en) | Boron-based stamping propulsion cross-medium aircraft | |
| CN114320662A (en) | Wide-speed-range high-power-driven air-breathing combined propulsion power system and missile | |
| CN107642436A (en) | A kind of hybrid rocket engine thrust gas vector controlled structure and method | |
| RU2609539C1 (en) | Rocket vehicle, return stage of rocket vehicle and method of its launch upon return and system of helicopter pick-up of return stage | |
| CN117507703A (en) | Cross-medium combined engine | |
| CN203214192U (en) | Multi-functional turbofan engine | |
| CN116291952A (en) | Double continuous detonation mode rocket-based combined cycle engine | |
| CN114408145B (en) | Preheating type water inlet ramjet engine structure and control method | |
| CN103192988A (en) | Airship | |
| CN104929809A (en) | Working method of detonation ram rocket | |
| CN205592035U (en) | Combined cycle engine | |
| CN210686148U (en) | Automatic disconnect-type appearance accuse engine structure | |
| RU2603305C1 (en) | Return carrier rocket stage | |
| RU2532954C1 (en) | Drone | |
| CN113153580A (en) | Combined spray pipe of solid rocket 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 |