CN114810417B - Full-rotation detonation modal rocket-ramjet combined engine and operation method - Google Patents
Full-rotation detonation modal rocket-ramjet combined engine and operation method Download PDFInfo
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- CN114810417B CN114810417B CN202210524114.0A CN202210524114A CN114810417B CN 114810417 B CN114810417 B CN 114810417B CN 202210524114 A CN202210524114 A CN 202210524114A CN 114810417 B CN114810417 B CN 114810417B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/18—Composite ram-jet/rocket engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/66—Combustion or thrust chambers of the rotary type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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- Combustion & Propulsion (AREA)
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Abstract
The invention discloses a full-rotation detonation mode rocket-ramjet combined engine and an operation method thereof, wherein the full-rotation detonation mode rocket-ramjet combined engine comprises a shell, a central body, an oxidant storage tank and a fuel storage tank; the shell comprises an arc-shaped expansion section, a short cylinder section, a long cylinder section and an arc-shaped contraction section; the central body comprises an air inlet cone, an injection panel and a rocket engine; the rocket engine comprises a public shell, a central cylindrical section and a central tail cone; a stamping rotary knocking combustion chamber is formed between the outer wall surface of the common shell and the long cylinder section; and a rotary detonation rocket combustion chamber is formed between the inner wall surface of the common shell and the central cylindrical section. The invention has a rotary detonation rocket mode and a rotary detonation stamping mode; firstly, the rotary detonation rocket mode is used for working, so that zero-speed starting boosting or horizontal launching is realized; when the flying speed reaches Ma2.5, the rotary detonation stamping mode is switched to, and oxygen in the air is utilized. Meanwhile, the fuel cavity can cool the common shell, and can preheat fuel, so that knocking combustion is realized in a hot fuel mode.
Description
Technical Field
The invention relates to an engine, in particular to a full-rotation detonation mode rocket-ramjet combined engine and an operation method.
Background
The rotary detonation ramjet engine is a novel propulsion system using detonation combustion as a combustion organization mode, has higher theoretical cycle efficiency and a more compact structure compared with the traditional power based on isobaric combustion, adopts a rotary detonation combustion chamber to replace the traditional ramjet engine combustion chamber, and utilizes an air inlet channel of the ramjet engine to obtain an oxidant from the external environment. Because the rotary detonation ramjet engine has the advantages of rotary detonation combustion and ramjet engine, the rotary detonation ramjet engine has the advantages of higher than impulse, simple structure, short combustion chamber, large thrust-weight ratio, self-pressurization, high thermal cycle efficiency and the like, and is widely focused.
Compared with the traditional rocket engine, the rotary detonation rocket engine has higher thermal cycle efficiency and specific impulse, and meanwhile, the rotary detonation rocket engine has the advantages of simple structure, short combustion chamber and large thrust-weight ratio. The rotary detonation rocket engine can adjust the thrust by adjusting the flow of the propellant, and flexibly change the flight state of the aircraft. The Russian early research foundation carries out multiple ignition on a full-size prototype of the liquid oxygen kerosene rotary detonation rocket engine, and the technical feasibility of the rotary detonation rocket engine is verified through experiments.
The independent rotary knock ramjet engine has the problem that the engine cannot be started automatically, and the angle and the height of the engine are difficult to maneuver flexibly and rapidly under the high Mach number flight condition. In order to solve the problems, a full-rotation detonation mode rocket-ramjet combined engine is provided, the defects of difficult ignition, wide-angle maneuvering and the like of the ramjet engine are overcome by utilizing the advantages that the rocket engine is not limited by the height and the speed, the rocket is combined with a wide-range (such as Ma2.5-6+) ramjet engine, and the rocket and the ramjet engine work together in a cross-domain acceleration climbing stage or a bullet/engine attack stage, so that the working range of an aircraft is widened, and the speed range can be even expanded to Ma8 when hydrogen fuel is adopted. In the future, the full-rotation detonation rocket-ram combined engine can be used for single-stage orbital aeroplanes, hypersonic cruise missiles, repeatedly used and horizontal take-off and landing aeroplanes and the like.
Disclosure of Invention
The invention aims to solve the technical problems of the prior art and provides a full-rotation detonation mode rocket-ramjet combined engine and an operation method thereof, wherein the full-rotation detonation mode rocket-ramjet combined engine and the operation method have a rotation detonation rocket mode and a rotation detonation ram mode; firstly, the rotary detonation rocket mode is used for working, so that zero-speed starting boosting or horizontal launching is realized; when the flying speed reaches Ma2.5, switching to a rotary knocking stamping mode, and utilizing oxygen in the air to realize variable mode operation in different speed ranges of Ma2.5-Ma6+. Meanwhile, the fuel cavity can cool the common shell, can preheat fuel, and is beneficial to realizing detonation combustion in the form of hot fuel.
In order to solve the technical problems, the invention adopts the following technical scheme:
a full-rotation detonation mode rocket-ramjet combined engine comprises a shell, a central body, an oxidant storage tank and a fuel storage tank;
the shell comprises an arc-shaped expansion section, a short cylinder section, a long cylinder section and an arc-shaped contraction section which are coaxially arranged in sequence along the exhaust emission direction; wherein the inner diameter of the long cylinder section is larger than the inner diameter of the short cylinder section, and the length of the long cylinder section is larger than the length of the short cylinder section.
The central body is coaxially arranged at the center of the shell, and comprises an air inlet cone, an injection panel and a rocket engine which are sequentially and coaxially arranged along the exhaust emission direction.
An adjustable air inlet channel is formed between the air inlet cone and the arc-shaped expansion section, and an air inlet isolation section is formed between the air inlet cone and the short cylinder section.
The injection panel is installed at the tail end of the air inlet cone, and a plurality of oxygen spray holes communicated with the oxidant storage tank are distributed on the injection panel along the circumferential direction.
The front end of the rocket engine is arranged on the injection panel, and the rocket engine comprises a public shell and a rocket engine central body which are coaxially arranged in sequence from outside to inside.
The rocket engine central body comprises a central cylindrical section and a central tail cone which are sequentially and coaxially distributed along the exhaust emission direction.
A stamping rotary knocking combustion chamber is formed between the outer wall surface of the common shell and the long cylinder section; the tail end of the common shell is shorter than the tail end of the long cylinder section, and an outer spray pipe is formed between the tail end of the common shell and the tail end of the long cylinder section.
A rotary detonation rocket combustion chamber is formed between the inner wall surface of the common shell and the central cylindrical section, and can be communicated with each oxygen spray hole.
An inner spray pipe is formed between the inner wall surface of the common shell and the central tail cone.
The center of the public shell is provided with an annular and sealed fuel cavity which is communicated with the fuel storage tank; the fuel cavity comprises an outer fuel cavity and an inner fuel cavity which are coaxially and parallelly arranged in sequence from outside to inside.
The front end inner wall surface of the public shell is circumferentially provided with a plurality of fuel inner spray holes, and each fuel inner spray hole can be respectively communicated with the internal combustion cavity and the rotary detonation rocket combustion chamber.
The outer wall surface of the public shell is circumferentially provided with a plurality of fuel outer spray holes, and each fuel outer spray hole can be respectively communicated with the outer fuel cavity and the punching rotary knocking combustion chamber.
The oxidant storage tank is coaxially arranged in the air inlet cone; the fuel tank is coaxially arranged in the rocket engine central body.
The fuel carrying capacity in the fuel storage tank can exceed more than half of the dead weight of the engine.
The length of the rotary detonation rocket combustion chamber is 1/3-1/2 of the length of the public shell.
The length of the rotary detonation rocket combustion chamber is smaller than the length of the ram rotary detonation combustion chamber, and the radial thickness of the rotary detonation rocket combustion chamber is smaller than the radial thickness of the ram rotary detonation combustion chamber.
The outer wall surface of the tail part of the public shell is provided with an annular large bulge; annular small bulges are arranged on the outer wall surface of the central cylindrical section adjacent to the central tail cone.
The axial length of the fuel cavity is not less than the axial length of the ram rotary detonation combustor.
A method for operating a full-rotation detonation mode rocket-ramjet combined engine comprises the following steps.
Step 1, zero-speed self-starting: the rocket-ramjet combined engine has a rotary detonation rocket mode and a rotary detonation ram mode; starting a rotary detonation rocket mode by a rocket-ramjet combined engine; at this time, the fuel storage tank supplies fuel into the fuel cavity, and the fuel cavity injects fuel into the rotary detonation rocket combustion chamber through the fuel inner spray hole; simultaneously, the oxidant storage tank sprays an oxidant into the rotary detonation rocket combustion chamber through the oxygen spray hole; the fuel and the oxidant entering the rotary detonation rocket combustion chamber are combusted by the rotary detonation rocket to generate thrust, so that the zero-speed self-starting of the aircraft is realized.
Step 2, switching rotary knocking from a rocket mode to a stamping mode: when the flying speed of the aircraft reaches Ma2+, the rocket-ramjet combined engine turns off a rotary detonation rocket mode, and starts the rotary detonation ram mode; at this time, the fuel storage tank supplies fuel into the fuel cavity, and the fuel cavity injects fuel into the ram rotary knocking combustion chamber through the fuel outer spray hole; meanwhile, oxygen in the air sequentially passes through the adjustable air inlet passage and the air inlet isolation section, enters the punching rotary detonation combustion chamber, is mixed with fuel, and generates punching rotary detonation combustion, so that the aircraft can fly cruising in the atmosphere.
Step 3, switching the rotary knocking mode from a stamping mode to a rocket mode: when the flying speed of the aircraft reaches Ma6+ or needs to enter a nearby space and fly in orbit, the rocket-ramjet combined engine turns off the rotary detonation ram mode and turns on the rotary detonation rocket mode.
Step 4, cooling the common shell: in steps 1 to 3, the fuel tank continuously supplies fuel into the fuel chamber, thereby cooling the inner wall surface and the outer wall surface of the common housing while allowing the fuel to be preheated.
The invention has the following beneficial effects:
1. the rotary detonation rocket combustion chamber and the punching rotary detonation combustion chamber both adopt rotary detonation tissue combustion, and the engine has the advantages of simple structure, short length, large thrust-weight ratio, high thermal cycle efficiency and the like; compared with the traditional turbine-based combined cycle or rocket-based combined cycle engine, the novel engine has the advantages that the rotary knock stamping mode can work at a wide Mach number (Ma2.5-6.0+) and is flexible in use mode, and particularly, the rocket mode only needs to be accelerated to the lower limit of a lower speed range, so that the engine is good in economy.
2. According to the design of the annular fuel cavity, fuel is preheated in the fuel cavity before being injected into the rotary detonation rocket combustion chamber or the ram rotary detonation combustion chamber, and documents show that the preheating of the fuel is more beneficial to realizing continuous rotary detonation combustion. Meanwhile, after absorbing heat, the fuel cools the inner wall and the outer wall of the common shell at two sides, and the heat protection requirement of the wall of the rotary detonation rocket combustion chamber is reduced.
3. The combined cycle engine can exert the technical advantages of the rotary detonation rocket engine and the rotary detonation ramjet engine in respective ranges, has the technical characteristics of wide working range, good comprehensive economy and the like, and is an ideal power device for realizing the wide-speed-range and wide-airspace flight of an aircraft.
4. The aircraft using the combined engine as the power device has the advantages of horizontal take-off and landing, round trip from the sky to the earth and repeated use.
Drawings
FIG. 1 shows a schematic diagram of the overall structure of a full rotation detonation mode rocket-ramjet combined engine of the present invention.
FIG. 2 shows a schematic cross-sectional view of a full rotation detonation mode rocket-ramjet combined engine of the present invention.
The method comprises the following steps:
100. a housing;
110. an arc-shaped amplification section; 120. a short cylindrical section; 130. a long cylindrical section; 140. an arc-shaped contraction section; 150. expanding the transition section;
200. a central body;
210. an air inlet cone; 211. an adjustable air inlet channel; 212. an air inlet isolation section;
220. injecting a panel; 221. oxygen spray holes;
230. a common housing; 231. a fuel chamber; 231a, an outer fuel cavity; 231b, an internal combustion chamber; 232. large protrusions; 233. a rotating detonation rocket combustion chamber; 234. stamping a rotary detonation combustor; 235. an inner nozzle; 236. an outer nozzle;
240. a rocket engine center body; 241. a central cylindrical section; 242. a small protrusion; 243. a central tail cone;
300. an oxidant reservoir;
400. a fuel tank.
Detailed Description
The invention will be described in further detail with reference to the accompanying drawings and specific preferred embodiments.
In the description of the present invention, it should be understood that the terms "left", "right", "upper", "lower", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and "first", "second", etc. do not indicate the importance of the components, and thus are not to be construed as limiting the present invention. The specific dimensions adopted in the present embodiment are only for illustrating the technical solution, and do not limit the protection scope of the present invention.
As shown in fig. 1 and 2, a full rotation detonation mode rocket-ram combined engine includes a casing 100, a center body 200, an oxidizer tank 300, and a fuel tank 400.
The shell comprises an arc-shaped expansion section 110, a short cylinder section 120, a long cylinder section 130 and an arc-shaped contraction section 140 which are coaxially arranged in sequence along the exhaust emission direction; wherein the inner diameter of the long cylinder section is larger than that of the short cylinder section, the length of the long cylinder section is larger than that of the short cylinder section, and the inner wall surfaces of the short cylinder section and the long cylinder section are connected through the expansion transition section 150.
The central body is coaxially arranged in the center of the shell, and comprises an air inlet cone 210, an injection panel 220 and a rocket engine which are sequentially and coaxially arranged along the exhaust emission direction.
An adjustable air inlet channel 211 is formed between the air inlet cone and the arc-shaped expansion section, and an air inlet isolation section 212 is formed between the air inlet cone and the short cylinder section.
The injection panel is installed at the tail end of the air inlet cone, and a plurality of oxygen spray holes 221 communicated with the oxidant storage tank are distributed on the injection panel along the circumferential direction.
The front end of the rocket motor is mounted on the injection panel, and the rocket motor comprises a common shell 230 and a rocket motor central body 240 which are coaxially arranged in sequence from outside to inside.
The rocket engine central body comprises a central cylindrical section 241 and a central tail cone 242 which are sequentially and coaxially arranged along the exhaust emission direction.
A ram rotary detonation combustor 234 is formed between the outer wall surface of the common housing and the long cylindrical section; the tail end of the common housing is shorter than the tail end of the long cylindrical section, and an outer nozzle 236 is formed between the tail end of the common housing and the tail end of the long cylindrical section. Further, the outer wall surface of the tail portion of the common housing is preferably provided with an annular large protrusion 232, and the protruding tip of the large protrusion 232 thereby forms the throat portion of the outer nozzle.
A rotary detonation rocket combustion chamber 233 is formed between the inner wall surface of the common housing and the central cylindrical section, and can be communicated with each oxygen jet orifice.
An inner nozzle 235 is formed between the common housing inner wall surface and the center tailcone. Further, an annular small protrusion 243 is provided on the outer wall surface of the central cylindrical section adjacent to the central tail cone, the protruding tip of the small protrusion 243 thereby forming the throat of the inner nozzle.
The common housing is centrally provided with an annular and sealed fuel cavity 231 comprising an outer fuel cavity 231a and an inner fuel cavity 231b coaxially and parallel arranged in sequence from the outside to the inside, both the outer and inner fuel cavities 231a, 231b being in communication with a fuel tank. Further, the axial length of the fuel cavity is preferably not less than the axial length of the ram rotary detonation combustor.
The sum of the radial thicknesses of the outer and inner fuel chambers 231a, 231b is preferably 5 mm-10 mm.
The front end inner wall surface of the public shell is circumferentially provided with a plurality of fuel inner spray holes, and each fuel inner spray hole can be respectively communicated with the internal combustion cavity and the rotary detonation rocket combustion chamber.
The outer wall surface of the public shell is circumferentially provided with a plurality of fuel outer spray holes, and each fuel outer spray hole can be respectively communicated with the outer fuel cavity and the punching rotary knocking combustion chamber.
In the invention, the oxidant storage tank is preferably coaxially arranged in the air inlet cone; the fuel tank is preferably coaxially built into the rocket motor centerbody.
The fuel carried in the fuel storage tank is shared by the rocket-ramjet combined engine in a bimodal mode. Because the rocket engine central body is hollow and inwards contracted, the fuel carrying capacity is easier to be improved by more than half of the dead weight of the engine. The rocket mode and the ram mode of the engine adopt a self-supercharging combustion organization form of rotary knocking, and particularly the rocket engine has simpler partial supercharging structure and engine body structure. In addition, in theory, knocking combustion can improve the thermodynamic cycle efficiency by 20% -30%, and the engine can fly farther when carrying the same fuel.
The length of the rotary detonation rocket combustion chamber is 1/3-1/2 of the length of the public shell, and the nested design of the rocket combustion chamber, compared with the traditional ramjet engine and rocket-ram combined power scheme adopting the one-stage rocket engine boosting, the length of the primary boosting rocket engine is eliminated, and the design is greatly shortened.
The length of the rotary detonation rocket combustion chamber is smaller than that of the stamping rotary detonation combustion chamber, and the equal straight segment length of the rotary detonation rocket combustion chamber is not more than 1/2 of that of the stamping rotary detonation combustion chamber. The following advantages are provided: on one hand, the reaction activity of the oxygen serving as the oxidant is higher and the heat release distance is short compared with that of the oxygen serving as the oxidant and on the other hand, the oxygen inlet speed of the oxygen serving as the oxidant is obviously lower than that of the oxygen serving as the oxidant; the radial thickness of the rotary detonation rocket combustion chamber is less than the radial thickness of the ram rotary detonation combustion chamber.
A method for operating a full-rotation detonation mode rocket-ramjet combined engine comprises the following steps.
Step 1, zero-speed self-starting: the rocket-ramjet combined engine has a rotary detonation rocket mode and a rotary detonation ram mode; starting a rotary detonation rocket mode by a rocket-ramjet combined engine; at this time, the fuel storage tank supplies fuel into the fuel cavity, and the fuel cavity injects fuel into the rotary detonation rocket combustion chamber through the fuel inner spray hole; simultaneously, the oxidant storage tank sprays an oxidant into the rotary detonation rocket combustion chamber through the oxygen spray hole; the fuel and the oxidant entering the rotary detonation rocket combustion chamber are combusted by the rotary detonation rocket to generate thrust, so that the zero-speed self-starting of the aircraft, namely the first stage, is realized.
Step 2, switching rotary knocking from a rocket mode to a stamping mode: when the flying speed of the aircraft reaches Ma2+, the rocket-ramjet combined engine turns off a rotary detonation rocket mode, and starts the rotary detonation ram mode; at this time, the fuel storage tank supplies fuel into the fuel cavity, and the fuel cavity injects fuel into the ram rotary knocking combustion chamber through the fuel outer spray hole; meanwhile, oxygen in the air sequentially passes through the adjustable air inlet channel and the air inlet isolation section, enters the stamping rotary detonation combustion chamber, is mixed with fuel, and generates stamping rotary detonation combustion, so that the aircraft can fly in the air layer in a cruising way, namely in the second stage.
Step 3, switching the rotary knocking mode from a stamping mode to a rocket mode: when the flying speed of the aircraft reaches Ma6+ or needs to enter a near space and fly in orbit, the rocket-ramjet combined engine turns off the rotary detonation ram mode, and turns on the rotary detonation rocket mode, namely the third stage.
Step 4, cooling the common shell: in steps 1 to 3, the fuel tank continuously supplies fuel into the fuel chamber, thereby cooling the inner wall surface and the outer wall surface of the common housing while allowing the fuel to be preheated.
The preferred embodiments of the present invention have been described in detail above, but the present invention is not limited to the specific details of the above embodiments, and various equivalent changes can be made to the technical solution of the present invention within the scope of the technical concept of the present invention, and all the equivalent changes belong to the protection scope of the present invention.
Claims (8)
1. A full-rotation detonation mode rocket-ramjet combined engine is characterized in that: comprises a shell, a central body, an oxidant storage tank and a fuel storage tank;
the shell comprises an arc-shaped expansion section, a short cylinder section, a long cylinder section and an arc-shaped contraction section which are coaxially arranged in sequence along the exhaust emission direction; wherein the inner diameter of the long cylinder section is larger than that of the short cylinder section, and the length of the long cylinder section is larger than that of the short cylinder section;
the central body is coaxially arranged at the center of the shell and comprises an air inlet cone, an injection panel and a rocket engine which are sequentially and coaxially arranged along the exhaust emission direction;
an adjustable air inlet channel is formed between the air inlet cone and the arc-shaped amplification section, and an air inlet isolation section is formed between the air inlet cone and the short cylinder section;
the injection panel is arranged at the tail end of the air inlet cone, and a plurality of oxygen spray holes communicated with the oxidant storage tank are distributed on the injection panel along the circumferential direction;
the front end of the rocket engine is arranged on the injection panel, and the rocket engine comprises a public shell and a rocket engine central body which are coaxially arranged in sequence from outside to inside;
the rocket engine central body comprises a central cylindrical section and a central tail cone which are sequentially and coaxially arranged along the tail gas emission direction;
a stamping rotary knocking combustion chamber is formed between the outer wall surface of the common shell and the long cylinder section; the tail end of the public shell is shorter than the tail end of the long cylinder section, and an outer spray pipe is formed between the tail end of the public shell and the tail end of the long cylinder section;
a rotary detonation rocket combustion chamber is formed between the inner wall surface of the public shell and the central cylindrical section, and can be communicated with each oxygen spray hole;
an inner spray pipe is formed between the inner wall surface of the public shell and the central tail cone;
the center of the public shell is provided with an annular and sealed fuel cavity which is communicated with the fuel storage tank; the fuel cavity comprises an outer fuel cavity and an inner fuel cavity which are coaxially and parallelly arranged in sequence from outside to inside;
the front end inner wall surface of the public shell is provided with a plurality of fuel inner spray holes along the circumferential direction, and each fuel inner spray hole can be respectively communicated with the internal combustion cavity and the rotary detonation rocket combustion chamber;
the outer wall surface of the public shell is circumferentially provided with a plurality of fuel outer spray holes, and each fuel outer spray hole can be respectively communicated with the outer fuel cavity and the punching rotary knocking combustion chamber.
2. The full-rotation detonation modal rocket-ram combined engine of claim 1, wherein: the oxidant storage tank is coaxially arranged in the air inlet cone; the fuel tank is coaxially arranged in the rocket engine central body.
3. The full-rotation detonation modal rocket-ram combined engine of claim 1, wherein: the fuel carrying capacity in the fuel storage tank can exceed more than half of the dead weight of the engine.
4. The full-rotation detonation modal rocket-ram combined engine of claim 1, wherein: the length of the rotary detonation rocket combustion chamber is 1/3-1/2 of the length of the public shell.
5. The full-rotation detonation modal rocket-ram combined engine of claim 1, wherein: the length of the rotary detonation rocket combustion chamber is smaller than that of the punching rotary detonation combustion chamber; the radial thickness of the rotary detonation rocket combustion chamber is less than the radial thickness of the ram rotary detonation combustion chamber.
6. The full-rotation detonation modal rocket-ram combined engine of claim 1, wherein: the outer wall surface of the tail part of the public shell is provided with an annular large bulge; annular small bulges are arranged on the outer wall surface of the central cylindrical section adjacent to the central tail cone.
7. The full-rotation detonation modal rocket-ram combined engine of claim 1, wherein: the axial length of the fuel cavity is not less than the axial length of the ram rotary detonation combustor.
8. A method of operating a full rotation detonation mode rocket-ramjet engine, based on the full rotation detonation mode rocket-ramjet engine of any of claims 1-7, characterized by: the method comprises the following steps:
step 1, zero-speed self-starting: the rocket-ramjet combined engine has a rotary detonation rocket mode and a rotary detonation ram mode; starting a rotary detonation rocket mode by a rocket-ramjet combined engine; at this time, the fuel storage tank supplies fuel into the fuel cavity, and the fuel cavity injects fuel into the rotary detonation rocket combustion chamber through the fuel inner spray hole; simultaneously, the oxidant storage tank sprays an oxidant into the rotary detonation rocket combustion chamber through the oxygen spray hole; the fuel and the oxidant entering the rotary detonation rocket combustion chamber are combusted by the rotary detonation rocket to generate thrust, so that the zero-speed self-starting of the aircraft is realized;
step 2, switching rotary knocking from a rocket mode to a stamping mode: when the flying speed of the aircraft reaches Ma2+, the rocket-ramjet combined engine turns off a rotary detonation rocket mode, and starts the rotary detonation ram mode; at this time, the fuel storage tank supplies fuel into the fuel cavity, and the fuel cavity injects fuel into the ram rotary knocking combustion chamber through the fuel outer spray hole; meanwhile, oxygen in the air sequentially passes through the adjustable air inlet channel and the air inlet isolation section, enters the stamping rotary detonation combustion chamber, is mixed with fuel, and generates stamping rotary detonation combustion, so that the aircraft can fly cruising in the atmosphere;
step 3, switching the rotary knocking mode from a stamping mode to a rocket mode: when the flying speed of the aircraft reaches Ma6+ or needs to enter a nearby space and enter a track for flying, the rocket-ramjet combined engine turns off a rotary detonation ram mode and turns on the rotary detonation rocket mode;
step 4, cooling the common shell: in steps 1 to 3, the fuel tank continuously supplies fuel into the fuel chamber, thereby cooling the inner wall surface and the outer wall surface of the common housing while allowing the fuel to be preheated.
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