CN112177797B - Solid rocket engine without spray pipe - Google Patents
Solid rocket engine without spray pipe Download PDFInfo
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- CN112177797B CN112177797B CN202010973985.1A CN202010973985A CN112177797B CN 112177797 B CN112177797 B CN 112177797B CN 202010973985 A CN202010973985 A CN 202010973985A CN 112177797 B CN112177797 B CN 112177797B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/10—Shape or structure of solid propellant charges
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
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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
Abstract
The invention discloses a solid rocket engine without a spray pipe, which comprises: the propellant grain is filled in the inner cavity of the shell, a gas channel is arranged along the central line of the propellant grain, the supporting tube is cylindrical and is sleeved in the gas channel and close to a gas flow outlet, a plurality of inner cavity electromagnetic field mechanisms and a plurality of inner cavity high-voltage thermoelectric mechanisms are sequentially arranged on the inner wall of the supporting tube at intervals, the inner cavity electromagnetic field mechanisms and the inner cavity high-voltage thermoelectric mechanisms are mutually matched for generating millivolt thermoelectric force due to thermoelectric effect when gas passes through the gas channel of the inner cavity of the supporting tube, and further forming high-voltage thermoelectric force, and the thermoelectric force enables the gas containing a large amount of ionization products to be greatly accelerated and discharged through the inner cavity of the supporting tube so as to push the rocket to run; the invention cancels the nozzle structure of the conventional solid rocket engine, greatly lightens the structural mass of the engine and reduces the probability of failure faults.
Description
Technical Field
The invention belongs to the field of aerospace power, and particularly relates to a solid rocket engine without a spray pipe.
Background
A solid rocket engine: chemical rocket engines using solid propellants. Also known as solid propellant rocket engines. The solid propellant is ignited and then burnt in the combustion chamber, and chemical energy is converted into heat energy to produce high-temperature and high-pressure combustion products. The combustion products flow through the nozzle where they expand and accelerate, and the thermal energy is converted to kinetic energy and expelled from the nozzle at high velocity to produce thrust.
Since the birth of the solid rocket engine, the basic structural form of the solid rocket engine is 'combustion chamber + Laval nozzle', and the gas generated by the combustion of the solid propellant is continuously accelerated in the nozzle and flows out of the engine, thereby generating thrust. In order to ensure higher energy conversion efficiency, the size of the spray pipe is generally larger, and the proportion of the spray pipe to the structural mass of the engine is higher. Since the nozzle exit size generally cannot exceed the maximum outer diameter of the rocket, this limits further increases in the maximum airflow velocity at the nozzle exit face, limits energy conversion efficiency, and results in inefficient use of large amounts of energy. In addition, the thermal environment is severe and changes violently when the nozzle works, the thermal protection design scheme is complex, and parts such as the throat insert and the like have failure faults.
Disclosure of Invention
The invention aims to provide a solid rocket engine without a nozzle pipe, which aims to solve the problem that the outlet speed of combustion products of the existing solid rocket engine is limited.
The invention adopts the following technical scheme: a solid rocket engine without jet pipes, comprising:
the shell is in a columnar shape,
propellant grains filled in the inner cavity of the shell and provided with a gas channel along the central line,
the supporting tube is cylindrical, is sleeved in the gas channel and is close to a gas airflow outlet, a plurality of inner cavity electromagnetic field mechanisms and a plurality of inner cavity high-voltage thermoelectric mechanisms are sequentially arranged on the inner wall of the supporting tube at intervals, the inner cavity electromagnetic field mechanisms and the inner cavity high-voltage thermoelectric mechanisms are mutually matched and used for generating millivolt thermoelectric force due to thermoelectric effect when gas passes through the gas channel of the inner cavity of the supporting tube, and further high-voltage thermoelectric force is formed, the thermoelectric force enables the gas containing a large amount of ionization products to be greatly accelerated, and the gas is discharged through the inner cavity of the supporting tube so as to push the rocket to operate.
Furthermore, each inner cavity electromagnetic field mechanism is composed of a plurality of inner cavity electromagnetic field mechanism units which are distributed in a radial and annular manner and are arranged on the inner wall of the supporting tube;
each inner cavity high-voltage thermoelectric mechanism consists of a plurality of inner cavity high-voltage thermoelectric mechanism units which are distributed in a radial and annular manner and are arranged on the inner wall of the supporting tube;
the high-voltage thermoelectric mechanisms of the inner cavities and the electromagnetic field mechanisms of the inner cavities are arranged at intervals and are closely arranged.
Furthermore, each inner cavity high-voltage thermoelectric mechanism unit comprises an inner cavity rib framework, an inner cavity first conductor and an inner cavity second conductor, the inner cavity rib framework is sleeved in the inner cavity of the supporting tube, and the outer wall of the inner cavity rib framework is attached to the inner wall of the supporting tube;
the inner cavity rib framework is a hollow cylinder, a plurality of inner cavity grooves are formed in the outer wall of the inner cavity rib framework from outside to inside around the periphery of the outer wall of the inner cavity rib framework, the inner cavity grooves are arranged in parallel, the plane where the inner cavity grooves are located is parallel to the cross section of the inner cavity rib framework, the inner cavity grooves are used for inserting the first inner cavity conductor and the second inner cavity conductor, and the first inner cavity conductor and the second inner cavity conductor are connected in series to form a closed loop.
Further, the lumen first conductor and the lumen second conductor are both annular and laminar.
Furthermore, each inner cavity electromagnetic field mechanism unit comprises a high-magnetic-permeability core body, a conductive coil and a heat insulation coating layer, wherein the conductive coil is wound on the high-magnetic-permeability core body, and the heat insulation coating layer wraps the high-magnetic-permeability core body and the conductive coil;
the plane formed by the plurality of inner cavity electromagnetic field mechanism units is parallel to the cross section of the inner cavity rib frame, and the axis of each high-magnetic-permeability core body passes through the circle center of the cross section of the inner cavity rib frame.
Furthermore, an outer cavity electromagnetic field mechanism and an outer cavity high-voltage thermoelectric mechanism are sequentially arranged on the outer wall of the supporting tube at intervals, the outer cavity electromagnetic field mechanism and the outer cavity high-voltage thermoelectric mechanism are matched with each other to generate millivolt thermoelectric force due to thermoelectric effect before the fuel gas passes through the supporting tube, and form high-voltage thermoelectric force, and the thermoelectric force accelerates the fuel gas containing a large amount of ionization products and then enters the supporting tube; and is also used for adjusting the burning speed of the propellant during the working process according to the use requirement.
Furthermore, each outer cavity electromagnetic field mechanism is composed of a plurality of outer cavity electromagnetic field mechanism units which are distributed in a radial and annular shape and are arranged on the outer wall of the supporting tube;
each outer cavity high-voltage thermoelectric mechanism consists of a plurality of outer cavity high-voltage thermoelectric mechanism units which are distributed in a radial and annular manner and are arranged on the outer wall of the supporting tube;
each outer cavity electromagnetic field mechanism and each outer cavity high-voltage thermoelectric mechanism are arranged at intervals and are closely arranged.
Furthermore, each outer cavity high-voltage thermoelectric mechanism unit comprises an outer cavity rib framework, an outer cavity first conductor and an outer cavity second conductor, wherein the outer cavity rib framework is sleeved on the outer wall of the supporting pipe, and the inner wall of the outer cavity rib framework is attached to the outer wall of the supporting pipe;
the outer cavity rib framework is a hollow cylinder, a plurality of outer cavity grooves are formed in the inner wall of the outer cavity rib framework in a circle around the inner wall of the outer cavity rib framework from inside to outside, the outer cavity grooves are arranged in parallel, the plane where the outer cavity grooves are located is parallel to the cross section of the outer cavity rib framework, the outer cavity grooves are used for inserting the outer cavity first conductor and the outer cavity second conductor, and the outer cavity first conductor and the outer cavity second conductor are connected in series to form a closed loop.
Furthermore, each external cavity electromagnetic field mechanism unit comprises a high-magnetic-permeability core body, a conductive coil and a heat insulation coating layer, wherein the conductive coil is wound on the high-magnetic-permeability core body, and the heat insulation coating layer wraps the high-magnetic-permeability core body and the conductive coil;
the plane formed by the external cavity electromagnetic field mechanism units is parallel to the cross section of the external cavity rib framework, and the axis of each high-magnetic-permeability core body passes through the center of the cross section of the external cavity rib framework.
Furthermore, the first outer cavity conductor and the second outer cavity conductor are both annular thin sheets, the tube body of the support tube is made of alloy steel or stainless steel, and the inner cavity rib framework and the outer cavity rib framework are both made of high-heat-conductivity alloy materials.
The invention has the beneficial effects that: the invention cancels the jet pipe structural part of the conventional solid rocket engine, greatly lightens the structural mass of the engine and reduces the probability of failure fault; the high-temperature gas is transferred to the heat of the pipe wall in the supporting pipe, the electric energy is converted through the thermoelectric effect, an electromagnetic field is formed by the electric energy, the gas is accelerated by the electromagnetic field, and the conversion and conservation utilization of energy are completed in a circulating mode; the large energy loss caused by the fact that the heat protection component in the traditional spray pipe passively resists high-temperature gas is avoided, and the energy utilization rate is improved; the invention is not limited by the maximum outer diameter of the rocket any more, and the gas speed of the invention is higher than the gas flow speed at the outlet of the existing rocket engine, so that the specific impulse performance of the engine is greatly improved.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic partial cross-sectional view of a support tube of the present invention;
FIG. 3 is a schematic structural view of an external chamber high voltage thermoelectric mechanism of the present invention;
FIG. 4 is a schematic diagram of the construction of an intracavity high voltage thermoelectric mechanism of the present invention;
FIG. 5 is a side view of an inner cavity electromagnetic field mechanism and an outer cavity electromagnetic field mechanism of the present invention;
fig. 6 is a sectional view of an inner cavity electromagnetic field mechanism and an outer cavity electromagnetic field mechanism of the present invention.
Wherein: 1. a housing; 2. supporting a tube; 3. a propellant grain; 4. a gas channel; 5. an inner cavity high-voltage thermoelectric mechanism; 51. an inner cavity high-voltage thermoelectric mechanism unit; 6. an inner cavity electromagnetic field mechanism; 61. an inner cavity electromagnetic field mechanism unit; 7. a lumen first conductor; 8. a lumen second conductor; 9. an outer-cavity high-voltage thermoelectric mechanism; 91. an outer-cavity high-voltage thermoelectric mechanism unit; 10. an external cavity electromagnetic field mechanism; 101. an external cavity electromagnetic field mechanism unit; 11. an outer cavity groove; 12. an inner cavity rib framework; 13. an inner cavity groove; 14. an outer cavity first conductor; 15. an outer cavity rib skeleton; 16. an outer cavity second conductor.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
The invention discloses a solid rocket engine without a spray pipe, which comprises a shell 1, a propellant grain 3, a support pipe 2, an inner cavity electromagnetic field mechanism 6 and an inner cavity high-voltage thermoelectric mechanism 5, wherein the inner cavity electromagnetic field mechanism 6 and the inner cavity high-voltage thermoelectric mechanism 5 are positioned on the inner wall of the support pipe 2, the shell 1 is columnar, the propellant grain 3 is filled in the inner cavity of the shell 1, a gas channel 4 is arranged along the central line of the propellant grain 3, the support pipe 2 is columnar, the support pipe 2 is sleeved in the gas channel 4 and is close to a gas airflow outlet, a plurality of inner cavity electromagnetic field mechanisms 6 and a plurality of inner cavity high-voltage thermoelectric mechanisms 5 are sequentially arranged on the inner wall of the support pipe 2 at intervals, the plurality of inner cavity electromagnetic field mechanisms 6 and the inner cavity high-voltage thermoelectric mechanisms 5 are mutually matched for generating millivolt thermoelectric force when gas passes through the gas channel 4 in the inner cavity of the support pipe 2 due to further form high-voltage thermoelectric force, the thermoelectric force greatly accelerates the fuel gas containing a large amount of ionization products, and the fuel gas is discharged through the inner cavity of the supporting tube 2 to further push the rocket to operate.
A plurality of inner cavity electromagnetic field mechanisms 6 and inner cavity high-voltage thermoelectric mechanisms 5 are arranged on the inner wall of the supporting tube 2, each inner cavity electromagnetic field mechanism 6 is composed of a plurality of inner cavity electromagnetic field mechanism units 61, the plurality of inner cavity electromagnetic field mechanism units 61 are arranged around the inner wall of the supporting tube 2, namely the plurality of inner cavity electromagnetic field mechanism units 61 are distributed radially and annularly and are arranged on the inner wall of the supporting tube 2; each inner cavity high-voltage thermoelectric mechanism 5 is composed of a plurality of inner cavity high-voltage thermoelectric mechanism units 51, the plurality of inner cavity high-voltage thermoelectric mechanism units 51 are arranged around the inner wall of the support tube 2, namely, the plurality of inner cavity high-voltage thermoelectric mechanism units 51 are distributed radially and annularly and are arranged on the inner wall of the support tube 2; the high-voltage thermoelectric mechanisms 5 of the inner cavities and the electromagnetic field mechanisms 6 of the inner cavities are arranged at intervals and are closely arranged.
As shown in fig. 4, each inner cavity high-voltage thermoelectric mechanism unit 51 comprises an inner cavity rib framework 12, an inner cavity first conductor 7 and an inner cavity second conductor 8, the inner cavity rib framework 12 is sleeved in the inner cavity of the support tube 2, and the outer wall of the inner cavity rib framework 12 is attached to the inner wall of the support tube 2; the inner cavity rib framework 12 is a hollow cylinder, a plurality of inner cavity grooves 13 are formed in the outer wall of the inner cavity rib framework 12 around the outer wall of the inner cavity rib framework from outside to inside in a circle, the inner cavity grooves 13 are arranged in parallel, and the plane where the inner cavity grooves 13 are located is parallel to the cross section of the inner cavity rib framework 12. The inner cavity first conductor 7 and the inner cavity second conductor 8 are both annular thin sheets, each inner cavity groove 13 is used for inserting the inner cavity first conductor 7 and the inner cavity second conductor 8, the inner cavity first conductor 7 and the inner cavity second conductor 8 are connected in series to form a closed loop, the inner cavity first conductor 7 and the inner cavity second conductor 8 are arranged in each inner cavity groove 13, the inner cavity first conductor 7 and the inner cavity second conductor 8 are connected in series to form a closed loop due to different metal materials of the inner cavity first conductor 7 and the inner cavity second conductor 8, when heat of fuel gas is transmitted to the inner cavity first conductor 7 and the inner cavity second conductor 8 through the inner cavity rib framework 12, the inner cavity first conductor 7 and the inner cavity second conductor 8 generate millivolt thermoelectric potential due to thermoelectric effect, and when the thermoelectric potential is generated in the loop, a certain current, namely the so-called thermoelectric effect, can be generated in the loop.
Because inner chamber rib skeleton 12 cover is established in the stay tube 2 inner chamber, and its axis coincides each other with the axis of stay tube 2, consequently the plane at inner chamber first conductor 7 and inner chamber second conductor 8 place all is parallel to each other with the cross section of inner chamber rib skeleton 12, and then the plane at inner chamber first conductor 7 and inner chamber second conductor 8 place all is parallel to each other with the cross section of stay tube 2, and then the heat of the gas that the stay tube 2 received just can be better to be transmitted for inner chamber first conductor 7 and inner chamber second conductor 8, with this production thermoelectric effect. In addition, from the structural mass perspective, the closer together, there is an advantage in reducing the structural mass.
As shown in fig. 5 and 6, each of the internal cavity electromagnetic field mechanism units 61 includes a high-permeability core, a conductive coil wound around the high-permeability core, and a heat-insulating coating layer covering the high-permeability core and the conductive coil. A plurality of inner cavity electromagnetic field mechanism units 61 are uniformly arranged around the inner wall of the support pipe 2 in a circle, planes formed by the inner cavity electromagnetic field mechanism units 61 are parallel to the cross section of the inner cavity rib framework 12, and the axis of each high-magnetic-permeability core body passes through the circle center of the cross section of the inner cavity rib framework 12, so that the generated electromagnetic field is perpendicular to the gas flowing direction, the gas is accelerated, and the flow of fluid generated by the gas is controlled.
An outer cavity electromagnetic field mechanism 10 and an outer cavity high-voltage thermoelectric mechanism 9 are sequentially arranged on the outer wall of the supporting tube 2 at intervals, the outer cavity electromagnetic field mechanism 10 and the outer cavity high-voltage thermoelectric mechanism 9 are mutually matched for generating millivolt thermoelectric force due to thermoelectric effect before the fuel gas passes through the supporting tube 2 and forming high-voltage thermoelectric force, and the thermoelectric force accelerates the fuel gas containing a large amount of ionization products and then enters the supporting tube 2; and is also used for adjusting the burning speed of the propellant during the working process according to the use requirement.
Each external cavity electromagnetic field mechanism 10 is composed of a plurality of external cavity electromagnetic field mechanism units 101, the plurality of external cavity electromagnetic field mechanism units 101 are arranged around the outer wall of the supporting tube 2, namely the plurality of external cavity electromagnetic field mechanism units 101 are distributed radially and annularly and are arranged on the outer wall of the supporting tube 2; each outer cavity high-voltage thermoelectric mechanism 9 is composed of a plurality of outer cavity high-voltage thermoelectric mechanism units 91, the plurality of outer cavity high-voltage thermoelectric mechanism units 91 are arranged around the outer wall of the support tube 2, namely the plurality of outer cavity high-voltage thermoelectric mechanism units 91 are distributed radially and annularly and are arranged on the outer wall of the support tube 2; the outer cavity electromagnetic field mechanisms 10 and the outer cavity high-voltage thermoelectric mechanisms 9 are arranged at intervals and are closely arranged.
As shown in fig. 3, each external cavity high-voltage thermoelectric mechanism unit 91 includes an external cavity rib framework 15, an external cavity first conductor 14, and an external cavity second conductor 16, the external cavity rib framework 15 is sleeved on the outer wall of the support tube 2, the inner wall of the external cavity rib framework 15 is attached to the outer wall of the support tube 2, the external cavity rib framework 15 is a hollow cylinder, a plurality of external cavity grooves 11 are formed in the inner wall of the external cavity rib framework 15 from inside to outside around the inner wall of the external cavity rib framework, the external cavity grooves 11 are arranged in parallel, the plane where the external cavity grooves 11 are located is parallel to the cross section of the external cavity rib framework 15, each external cavity groove 11 is used for inserting the external cavity first conductor 14 and the external cavity second conductor 16, the external cavity first conductor 14 and the external cavity second conductor 16 are both in an annular sheet shape, and the external cavity first conductor 14 and the external cavity second conductor 16 are connected in series to form a closed loop.
As shown in fig. 5, each external cavity electromagnetic field mechanism unit 101 includes a high magnetic permeability core, a conductive coil wound around the high magnetic permeability core, and a heat insulation coating layer wrapping the high magnetic permeability core and the conductive coil; a plurality of each external cavity electromagnetic field mechanism unit 101 is uniformly arranged around the outer wall of the supporting tube 2, the plane formed by the plurality of external cavity electromagnetic field mechanism units 101 is parallel to the cross section of the external cavity rib framework 15, and the axis of each high magnetic permeability core body passes through the circle center of the cross section of the external cavity rib framework 15.
The connection mode of the inner cavity electromagnetic field mechanism unit 61 and the outer cavity electromagnetic field mechanism unit 101 can be pasting, bolting or clamping, if pasting, one end of the high magnetic permeability core is pasted on the inner wall and/or the outer wall of the support tube 2, the other end of the high magnetic permeability core is a free end, if bolting, one end of the high magnetic permeability core is fixed on the inner wall and/or the outer wall of the support tube 2, the other end of the high magnetic permeability core is a free end, if clamping, the high magnetic permeability core is clamped through two adjacent inner cavity rib frameworks 12.
The material of the support tube 2 is not limited as long as the requirement of the engine through which the fuel gas flows is met, preferably, the tube body material of the support tube 2 is alloy steel or stainless steel, and the inner cavity rib framework 12 and the outer cavity rib framework 15 are both made of high heat conductivity alloy material, because the inner cavity rib framework 12 and the outer cavity rib framework 15 need to transfer heat to the inner cavity first conductor 7 and the inner cavity second conductor 8, and the outer cavity first conductor 14 and the outer cavity second conductor 16, respectively, the fuel gas pressure borne by the inner cavity rib framework 12 and the outer cavity rib framework 15 needs to be transferred to the support tube 2, and the support tube 2 is used as the main load-bearing structure of the whole accelerating device.
The plurality of outer cavity electromagnetic field mechanisms 10 and the plurality of outer cavity high-voltage thermoelectric mechanisms 9 are arranged at intervals, so that the gas in the outer cavity can be accelerated under the action of the outer cavity electromagnetic field mechanisms 10 and can obtain higher speed before entering the gas channel 4, the staying time of gas components near a combustion surface can be controlled under the action of the outer cavity electromagnetic field mechanisms 10, the combustion speed of a propellant can be regulated, and the performance regulation of an engine is facilitated.
The number of the inner cavity high-voltage thermoelectric mechanisms 5, the inner cavity electromagnetic field mechanisms 6, the outer cavity electromagnetic field mechanisms 10 and the outer cavity high-voltage thermoelectric mechanisms 9 can be optimized according to the length and the diameter of the supporting tube 2, the thrust of an engine and other requirements, when the diameter is smaller, more inner cavity electromagnetic field mechanisms 6 and outer cavity electromagnetic field mechanisms 10 are needed for acceleration, and when the diameter is larger, fewer inner cavity electromagnetic field mechanisms 6 and outer cavity electromagnetic field mechanisms 10 are needed for acceleration.
The gas formed by the ultra-high energy propellant in the propellant grain 3 can reach Mach 1 when passing through the inlet of the inner cavity of the supporting tube 2, so as to form a choking phenomenon in the gas dynamics sense, in the process of flowing to the outlet of the inner cavity of the supporting tube 2, the gas can transfer heat to the inner cavity rib framework 12 with high heat conductivity, the heat is further transferred to the inner cavity first conductor 7 and the inner cavity second conductor 8, millivolt-level thermoelectric force is generated due to the thermoelectric effect, the thermoelectric force generated by the inner cavity high-voltage thermoelectric mechanism 5 is input into the inner cavity electromagnetic field mechanism 6, the gas containing a large amount of ionization products is greatly accelerated by the inner cavity electromagnetic field mechanism 6 and the inner cavity high-voltage thermoelectric mechanism 5 which are arranged at intervals, so that the gas is continuously accelerated and sprayed out from the outlet of the supporting tube 2, namely the gas is continuously accelerated, so that the gas velocity at the outlet of the support tube 2 will exceed the outlet velocity of the existing solid rocket engine.
The invention cancels the jet pipe structural part of the conventional solid rocket engine, greatly lightens the structural mass of the engine and reduces the probability of failure fault; in the invention, high-temperature fuel gas is transferred to heat of the pipe wall in the supporting pipe 2, electric energy is converted through a thermoelectric effect, an electromagnetic field is formed by the electric energy, the fuel gas is accelerated by the electromagnetic field, and energy conversion and conservation utilization are completed through the circulation mode; the large energy loss caused by the fact that the heat protection component in the traditional spray pipe passively resists high-temperature gas is avoided, and the energy utilization rate is improved; the invention is not limited by the maximum outer diameter of the rocket any more, and the gas speed of the invention is higher than the gas flow speed at the outlet of the existing rocket engine, so that the specific impulse performance of the engine is greatly improved.
The final acceleration effect of the fuel gas mainly depends on the length of the supporting tube 2, the layout and the performance of the inner cavity high-pressure thermoelectric mechanism 5 and the inner cavity electromagnetic field mechanism 6, is not limited by the maximum outer diameter of the rocket, and is higher than the outlet airflow speed of the existing rocket engine, so that the specific impulse performance of the engine is greatly improved; the invention not only solves the problem of limited outlet speed, but also solves the problem of complex structure of the traditional spray pipe, and can also adjust the outlet airflow speed and realize thrust adjustment.
Claims (9)
1. A solid rocket engine without a nozzle, comprising:
a shell (1) which is in a column shape,
a propellant grain (3) filled in the inner cavity of the shell (1) and provided with a gas channel (4) along the central line thereof,
the supporting tube (2) is cylindrical and is sleeved in the gas channel (4) and is close to the gas airflow outlet, a plurality of inner cavity electromagnetic field mechanisms (6) and a plurality of inner cavity high-voltage thermoelectric mechanisms (5) are sequentially arranged on the inner wall of the support tube at intervals, the inner cavity electromagnetic field mechanisms (6) and the inner cavity high-voltage thermoelectric mechanisms (5) are mutually matched for generating millivolt thermoelectric force due to thermoelectric effect when gas passes through a gas channel (4) of the inner cavity of the support tube (2), then high-voltage thermoelectric force is formed, millivolt-level thermoelectric force is generated due to thermoelectric effect, the thermoelectric force generated by the inner cavity high-voltage thermoelectric mechanism (5) is input into the inner cavity electromagnetic field mechanism (6), the gas containing a large amount of ionization products is greatly accelerated by the generation of the inner cavity electromagnetic field mechanism (6) and is discharged through the inner cavity of the supporting tube (2) to further push the rocket to operate;
each inner cavity electromagnetic field mechanism (6) is composed of a plurality of inner cavity electromagnetic field mechanism units (61), and the inner cavity electromagnetic field mechanism units (61) are distributed radially and annularly and are arranged on the inner wall of the supporting tube (2);
each inner cavity high-voltage thermoelectric mechanism (5) is composed of a plurality of inner cavity high-voltage thermoelectric mechanism units (51), and the inner cavity high-voltage thermoelectric mechanism units (51) are distributed radially and annularly and are arranged on the inner wall of the supporting pipe (2);
the inner cavity high-voltage thermoelectric mechanisms (5) and the inner cavity electromagnetic field mechanisms (6) are arranged at intervals and are closely arranged.
2. The solid rocket engine without nozzle of claim 1, wherein each of said inner cavity high-voltage thermoelectric mechanism units (51) comprises an inner cavity rib frame (12), an inner cavity first conductor (7) and an inner cavity second conductor (8), said inner cavity rib frame (12) is sleeved on the inner cavity of the supporting tube (2), the outer wall of said inner cavity rib frame (12) is attached to the inner wall of the supporting tube (2);
the inner cavity rib framework (12) is a hollow cylinder, a plurality of inner cavity grooves (13) are formed in the outer wall of the inner cavity rib framework (12) and around the outer wall of the inner cavity rib framework in a circle from outside to inside, the inner cavity grooves (13) are arranged in parallel, the plane where the inner cavity grooves (13) are located is parallel to the cross section of the inner cavity rib framework (12), the inner cavity grooves (13) are used for inserting the inner cavity first conductor (7) and the inner cavity second conductor (8), and the inner cavity first conductor (7) and the inner cavity second conductor (8) are connected in series to form a closed loop.
3. A solid-rocket engine without nozzle according to claim 2, characterized in that said first conductor (7) and said second conductor (8) are both in the form of annular sheets.
4. A solid-rocket engine without nozzle according to claim 3 wherein each of said intracavity electromagnetic field mechanism units (61) comprises a high-permeability core, a conductive coil wound around said high-permeability core, and a thermally insulating coating layer surrounding said high-permeability core and said conductive coil;
the plane formed by the plurality of inner cavity electromagnetic field mechanism units (61) is parallel to the cross section of the inner cavity rib framework (12), and the axis of each high-magnetic-permeability core body passes through the circle center of the cross section of the inner cavity rib framework (12).
5. The solid rocket engine without nozzle according to claim 4 wherein the outer wall of the supporting tube (2) is sequentially provided with an outer cavity electromagnetic field mechanism (10) and an outer cavity high-voltage thermoelectric mechanism (9) at intervals, the outer cavity electromagnetic field mechanism (10) and the outer cavity high-voltage thermoelectric mechanism (9) are mutually matched for generating millivolt thermoelectric force by thermoelectric effect before the fuel gas passes through the supporting tube (2) and forming high-voltage thermoelectric force, and the thermoelectric force accelerates the fuel gas containing a large amount of ionized products and then enters the supporting tube (2); and is also used for adjusting the burning speed of the propellant during the working process according to the use requirement.
6. A solid-rocket engine without jet pipes according to claim 5 wherein each of said external cavity electromagnetic field mechanism (10) is composed of a plurality of external cavity electromagnetic field mechanism units (101), a plurality of said external cavity electromagnetic field mechanism units (101) are radially and annularly distributed and mounted on the outer wall of said supporting tube (2);
each outer cavity high-voltage thermoelectric mechanism (9) is composed of a plurality of outer cavity high-voltage thermoelectric mechanism units (91), and the outer cavity high-voltage thermoelectric mechanism units (91) are distributed radially and annularly and are arranged on the outer wall of the supporting pipe (2);
the external cavity electromagnetic field mechanisms (10) and the external cavity high-voltage thermoelectric mechanisms (9) are arranged at intervals and are closely arranged.
7. The solid rocket engine without nozzle of claim 6 wherein each said outer cavity high pressure thermoelectric mechanism unit (91) comprises an outer cavity rib frame (15), an outer cavity first conductor (14) and an outer cavity second conductor (16), said outer cavity rib frame (15) is sleeved on the outer wall of the supporting tube (2), the inner wall of said outer cavity rib frame (15) is attached to the outer wall of the supporting tube (2);
the external cavity rib framework (15) is a hollow cylinder, a plurality of external cavity grooves (11) are formed in the inner wall of the external cavity rib framework (15) around the inner wall of the external cavity rib framework from inside to outside in a circle, the external cavity grooves (11) are arranged in parallel, the plane where the external cavity grooves (11) are located is parallel to the cross section of the external cavity rib framework (15), the external cavity grooves (11) are used for inserting external cavity first conductors (14) and external cavity second conductors (16), and the external cavity first conductors (14) and the external cavity second conductors (16) are connected in series to form a closed loop.
8. A solid-rocket engine without nozzle according to claim 7 wherein each of said external cavity electromagnetic field mechanism units (101) comprises a high-permeability core, a conductive coil wound around said high-permeability core, and a thermally insulating coating layer enveloping said high-permeability core and said conductive coil;
the plane formed by the external cavity electromagnetic field mechanism units (101) is parallel to the cross section of the external cavity rib framework (15), and the axis of each high-magnetic-permeability core body passes through the center of the cross section of the external cavity rib framework (15).
9. A solid rocket engine without nozzle according to claim 8 wherein said outer cavity first conductor (14) and said outer cavity second conductor (16) are both in the shape of annular sheets, the material of the tube body of said supporting tube (2) is alloy steel or stainless steel, and said inner cavity rib cage (12) and said outer cavity rib cage (15) are both made of high thermal conductivity alloy material.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3438437A1 (en) * | 2017-07-31 | 2019-02-06 | The Boeing Company | Scramjets and associated aircraft and methods |
| CN109441642A (en) * | 2018-12-13 | 2019-03-08 | 西安航天动力研究所 | A kind of fuel system and Supply Method of high-speed suction formula engine |
| CN209385251U (en) * | 2018-11-23 | 2019-09-13 | 江西洪都航空工业集团有限责任公司 | Nozzleless booster device |
Family Cites Families (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2631387B1 (en) * | 1988-05-10 | 1990-07-13 | Poudres & Explosifs Ste Nale | LOW ELONGATION NOZZLE PROPELLER |
| US8387361B2 (en) * | 2005-12-08 | 2013-03-05 | Rocketone Aerospace Pty Ltd. | Hybrid rocket system with moveable combustion control member |
| US20090229240A1 (en) * | 2008-03-12 | 2009-09-17 | Goodfellow Keith D | Hybrid plasma fuel engine rocket |
| CN102748135B (en) * | 2012-07-29 | 2013-12-25 | 西北工业大学 | Method for designing fixed-geometry two-dimensional mixed-compression type supersonic velocity air inlet channel |
| EA201991483A1 (en) * | 2013-03-15 | 2019-11-29 | STARTING SYSTEM AND METHOD OF STARTING USEFUL LOAD | |
| WO2016138068A1 (en) * | 2015-02-24 | 2016-09-01 | The Trustees Of Princeton University | System and method for small, clean, steady-state fusion reactors |
| CN107289667A (en) * | 2016-04-11 | 2017-10-24 | 钟伟昌 | Cooling and heating machine and its application |
| US10563617B2 (en) * | 2016-09-23 | 2020-02-18 | Raytheon Company | Electrically operated propellant for solid rocket motor thrust management |
| CN107846129A (en) * | 2017-11-09 | 2018-03-27 | 谭梓昂 | Magnetic field acquisition methods and the cold fuel-injection engine realized by the magnetic field acquisition methods |
| CA3111372A1 (en) * | 2018-09-06 | 2020-03-12 | Oqab Dietrich Induction Inc. | Engine for producing thrust |
| CN110821708A (en) * | 2019-08-30 | 2020-02-21 | 南京理工大学 | Three-combustion-speed variable-thickness combined explosive column structure of jet pipe-free engine |
| CN111188697B (en) * | 2020-01-03 | 2021-03-16 | 湖北航天技术研究院总体设计所 | Solid rocket engine for electromagnetic ejection |
-
2020
- 2020-09-16 CN CN202010973985.1A patent/CN112177797B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3438437A1 (en) * | 2017-07-31 | 2019-02-06 | The Boeing Company | Scramjets and associated aircraft and methods |
| CN209385251U (en) * | 2018-11-23 | 2019-09-13 | 江西洪都航空工业集团有限责任公司 | Nozzleless booster device |
| CN109441642A (en) * | 2018-12-13 | 2019-03-08 | 西安航天动力研究所 | A kind of fuel system and Supply Method of high-speed suction formula engine |
Non-Patent Citations (1)
| Title |
|---|
| Magnetohydrodynamic Augmentation of Pulse Detonation Rocket Engines;Zeineh, CF等;《JOURNAL OF PROPULSION AND POWER》;20120229;第28卷(第1期);第146-159页 * |
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