A charge-loaded solid energy management engine and use method thereof

Abstract

The present invention relates to the technical field of solid rocket engines, and specifically to a charge-loaded solid energy management engine and a method for using the same. The solid charge is placed in a charge chamber separated from the engine combustion chamber, and according to the overall real-time demand of the missile for the engine thrust output, a mechanical pushing device is used to control the mass of the solid charge entering the combustion chamber, thereby changing the amount of gas generated by the combustion of the solid charge, and achieving real-time adjustment of the engine thrust. The charge chamber and the combustion chamber of the present invention can be disassembled, which is convenient for replacing cartridges and solid charge, and the device can be reused.

Description

Technical Field

[0001] The present invention relates to the technical field of solid rocket engines, and in particular to a charge-loaded solid energy management engine and a use method thereof. Background Art

[0002] For a long time, missile weapons or rockets as a whole often hope that the thrust of the engine can be adjusted and controlled in real time to achieve efficient energy management in order to obtain better ballistic performance and use performance. However, once the solid grain of the traditional solid rocket engine is ignited in the combustion chamber, its combustion process cannot be regulated in real time, resulting in the difficulty of adjusting the engine thrust output in real time and poor energy management. In the existing technical solutions, the solid rocket engine that can change the thrust in real time is represented by the throat plug type variable thrust solid rocket engine. Its principle is to change the cross-sectional area of ​​the nozzle throat channel by controlling the movement of the throat plug, thereby changing the size of the engine thrust. However, since the throat plug is directly exposed to the harsh environment of high pressure, high temperature and high-speed multi-phase flushing of the nozzle, the throat plug has a very serious ablation problem, and the profile is difficult to maintain, resulting in the difficulty of accurate thrust control, and there are strict requirements on the size and working time of the engine. In addition, the variable thrust solid rocket engine solution based on electronically controlled propellants is still in the exploratory stage, and there are disadvantages such as low energy level of propellants, difficult electrode arrangement, and the need for additional energy supply. Therefore, the existing technical solutions all have certain problems and application limitations. Summary of the invention

[0003] In order to overcome the defects of the above-mentioned prior art, the purpose of the present invention is to provide a grain-loaded solid energy management engine and a method of use, so as to solve the technical problems that the grain combustion process in the solid rocket engine cannot be controlled in real time and the engine energy management level is poor.

[0004] The present invention is achieved through the following technical solutions:

[0005] A charge-loaded solid energy management engine comprises a combustion chamber, a charge chamber, a solid charge, a cartridge, an engine nozzle, a pushing device and an igniter; one end of the combustion chamber is assembled at one end of the charge chamber to form a cylindrical structure, the engine nozzle is assembled at the other end of the combustion chamber, the cartridge is assembled in the combustion chamber and the charge chamber, the pushing device is assembled at the other end of the charge chamber, and the pushing device extends into the charge chamber and is fixedly connected to one end of the cartridge, the cartridge is driven along the charge chamber into the combustion chamber by pushing the pushing device, the igniter is assembled in the combustion chamber, the solid charge is assembled in the cartridge, and one end of the solid charge extends out of the cartridge and is arranged toward the engine nozzle.

[0006] Preferably, the combustion chamber includes a combustion chamber shell, an insulating layer and a combustion chamber top partition; the insulating layer is bonded to the inner surface of the combustion chamber shell, and is used to insulate the solid charge burning in the combustion chamber shell; the combustion chamber top partition is an annular component with a through hole in the center, and one end of the combustion chamber top partition is threadedly connected to the end of the combustion chamber shell, and the other end is threadedly connected to the end of the charge chamber.

[0007] Furthermore, a plurality of first sealing rings are sleeved between the top partition of the combustion chamber and the cartridge.

[0008] Furthermore, a second sealing ring is sleeved between the combustion chamber top baffle and the combustion chamber shell.

[0009] Furthermore, the charge chamber includes a charge chamber shell, one end of which is threadedly connected to the top partition of the combustion chamber, and the other end is equipped with a pushing device, which drives the cartridge along the charge chamber shell into the combustion chamber shell by pushing the pushing device.

[0010] Furthermore, a plurality of guide rings are sleeved between the inner wall of the medicine column chamber shell and the outer wall of the medicine cartridge.

[0011] Furthermore, the shell of the medicine column chamber is a thin-walled cylindrical structure, wherein the cylinder section adopts a porous structure.

[0012] Preferably, a nozzle plugging cover is provided at the outlet of the engine nozzle.

[0013] Preferably, the combustion chamber and the charge chamber are coaxially arranged, and the outer diameters of the combustion chamber and the charge chamber are equal.

[0014] A method for using a grain-loaded solid energy management engine, based on the grain-loaded solid energy management engine described above, comprises the following steps:

[0015] When the solid rocket engine is working, the hydraulic propulsion device will gradually push the solid grain and the outer cartridge placed in the grain chamber into the combustion chamber. The solid grain entering the combustion chamber will burn and release high-temperature and high-pressure gas. The cartridge part entering the combustion chamber will melt under the action of the high-temperature gas. By controlling the loading process of the solid grain entering the combustion chamber, the combustion area of ​​the solid grain participating in the combustion can be changed, thereby changing the generation law of the fuel gas, realizing real-time regulation of the engine thrust and on-demand energy management of the engine.

[0016] Compared with the prior art, the present invention has the following beneficial technical effects:

[0017] The present invention provides a charge-loaded solid energy management engine. By placing a solid charge in a charge chamber separated from the engine combustion chamber, a mechanical pushing device is used to control the mass of the solid charge entering the combustion chamber according to the real-time demand of the missile for the engine thrust output, thereby changing the amount of gas generated by the combustion of the solid charge, and realizing real-time adjustment of the engine thrust. When the engine needs a long-term low-thrust working mode, the speed of the solid charge entering can be controlled to be consistent with the burning rate of the propellant retreat, so as to maintain the end face combustion to form a small thrust. When the engine needs a short-term high-thrust working mode, the speed of the solid charge entering is increased to form the end face, the conical surface and the outer end face to burn together, so as to achieve a larger thrust. The present invention realizes the energy management of the solid rocket engine by controlling the mass of the solid charge participating in the combustion energy release from the source supply end. While retaining the advantages of the solid rocket engine, the disadvantage that the traditional solid rocket engine can only release energy according to the preset law once ignited is changed. At the same time, by adopting this scheme, the combustion chamber part of the engine that is subjected to the high-temperature and high-pressure load environment accounts for a small proportion, which can reduce the structural mass of the engine, increase the engine mass ratio, and improve the performance of the engine. The medicine column chamber and the combustion chamber of the present invention can be disassembled, so it is convenient to replace the medicine cartridge and the solid medicine column, and the device can be reused. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the structure of the Chinese medicine column loaded solid energy management engine of the present invention;

[0019] Figure 2 It is a schematic diagram of the sealing structure of the top baffle of the combustion chamber in the present invention;

[0020] Figure 3 It is a schematic diagram of the principle of the low-thrust working mode of the Chinese medicine column-loaded solid energy management engine of the present invention;

[0021] Figure 4 It is a schematic diagram of the principle of the force-increasing working mode of the Chinese medicine column-loaded solid energy management engine of the present invention;

[0022] Figure 5 It is a schematic diagram of the variable thrust working mode principle of the Chinese medicine column loaded solid energy management engine of the present invention.

[0023] In the figure: 1-combustion chamber; 11-combustion chamber shell; 12-insulation layer; 13-combustion chamber top partition; 120-sealing ring; 2-charge chamber; 21-charge chamber shell; 22-guide ring; 3-solid charge; 4-cartridge; 5-engine nozzle; 6-pushing device; 7-igniter; 8-nozzle plugging cover; 120-first sealing ring; 121-second sealing ring. DETAILED DESCRIPTION

[0024] In order to enable those skilled in the art to better understand the scheme of the present invention, the technical scheme in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present invention.

[0025] It should be noted that the terms "first", "second", etc. in the specification and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present invention described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units that are clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0026] The present invention is further described in detail below in conjunction with the accompanying drawings:

[0027] The purpose of the present invention is to provide a grain-loaded solid energy management engine and a method of use, so as to solve the technical problems that the grain combustion process in a solid rocket engine cannot be controlled in real time and the engine energy management level is poor.

[0028] Specifically, according to Figure 1 As shown, the charge-loaded solid energy management engine comprises a combustion chamber 1, a charge chamber 2, a solid charge 3, a cartridge 4, an engine nozzle 5, a pushing device 6 and an igniter 7; one end of the combustion chamber 1 is assembled on one end of the charge chamber 2 to form a cylindrical structure, the engine nozzle 5 is assembled on the other end of the combustion chamber, the cartridge 4 is assembled in the combustion chamber 1 and the charge chamber 2, the pushing device 6 is assembled on the other end of the charge chamber 2, and the pushing device 6 extends into the charge chamber 2 and is fixedly connected with one end of the cartridge 4, and the cartridge 4 is driven along the charge chamber 2 into the combustion chamber 1 by pushing the pushing device 6, the igniter 7 is assembled in the combustion chamber 1, the solid charge 3 is assembled in the cartridge 4, and one end of the solid charge 3 extends out of the cartridge 4 and is arranged toward the engine nozzle 5.

[0029] Specifically, the combustion chamber 1 is a place where solid charge releases heat energy during combustion, and includes a combustion chamber shell 11, an insulating layer 12, and a combustion chamber top partition 13; the insulating layer 12 is bonded to the inner surface of the combustion chamber shell 11, and is used to insulate the solid charge 3 burning in the combustion chamber shell 11; wherein the insulating layer is made of rubber material or high-silicon phenolic composite material. The combustion chamber top partition 13 is an annular component with a through hole in the center, and one end of the combustion chamber top partition 13 is threadedly connected to the end of the combustion chamber shell 11, and the other end is threadedly connected to the end of the charge chamber 2.

[0030] The heat insulating layer 12 is bonded to the inner surface of the combustion chamber housing 11 and is made of high temperature resistant and ablation resistant heat insulating materials such as rubber materials or high silicon phenolic composite materials. Its thickness is designed according to the maximum working time of the engine and the material ablation rate.

[0031] Specifically, according to Figure 2 As shown, a plurality of first sealing rings 120 are sleeved between the top partition 13 of the combustion chamber and the cartridge 4, and a second sealing ring 121 is sleeved between the top partition 13 of the combustion chamber and the combustion chamber shell 11 to prevent the high-temperature combustion gas in the combustion chamber 1 from entering the cartridge chamber 2.

[0032] Specifically, the charge chamber 2 is located upstream of the combustion chamber 1, and includes a charge chamber shell 21, wherein the charge chamber shell 21 is a thin-walled cylindrical structure, and the material is a composite material or a lightweight high-strength metal material. One end of the charge chamber shell 2 is threadedly connected to the combustion chamber top partition 13, and the other end is equipped with a pushing device 6, which drives the cartridge 4 to move in the combustion chamber shell 11 and the charge chamber shell 21 by pushing the pushing device 6.

[0033] Specifically, a plurality of guide rings 22 are provided between the inner wall of the medicine column chamber shell 2 and the outer wall of the medicine cartridge 4 to support and guide the forward and backward movement of the medicine cartridge and the solid medicine column. The number of guide rings can be changed according to the length of the solid medicine column to ensure that the direction of the solid medicine column will not deflect during dynamic loading.

[0034] Specifically, the barrel section of the charge chamber shell 2 is made of composite materials or high-strength aluminum alloy materials while ensuring the bearing strength, and the barrel section adopts a porous structure to further reduce the structural weight.

[0035] Specifically, a nozzle plugging cover 8 is provided at the outlet of the engine nozzle 5 .

[0036] In the present invention, the cartridge 4 and the solid charge 3 are placed in the central hole of the guide ring 22 and the combustion chamber top partition 13. The solid charge 3 is a composite propellant, a double-base propellant or a modified double-base propellant, and is installed in the cartridge 4 by wall casting or adhesive bonding, and there is no crack or debonding at the interface.

[0037] The cartridge 4 is a thin-walled cylinder made of materials with poor thermal conductivity, high mechanical strength and rapid melting at high temperatures to ensure structural integrity during movement, and the part entering the combustion chamber can be rapidly melted under the action of high-temperature combustion gas. The main driving force of the push device is hydraulic or gas driven. The engine nozzle 5 is connected to the combustion chamber housing 11 to accelerate the high-temperature and high-pressure combustion gas and generate thrust. The igniter 7 and the nozzle plug cover 8 are used to ensure reliable ignition of the engine.

[0038] In the present invention, the inner cylindrical surface of the top baffle 13 of the combustion chamber and the cartridge 4 is provided with two O-ring sealing grooves, and the top baffle 13 of the combustion chamber and the cartridge 4 are sealed by an O-ring to prevent the high-temperature combustion gas in the combustion chamber from entering the cartridge chamber during the operation of the engine. The outer cylindrical surface of the top baffle 13 of the combustion chamber and the combustion chamber housing 11 is provided with an O-ring sealing groove to ensure the sealing of the combustion chamber. The structure of the present invention is detachable, and the combustion chamber 1 and the cartridge chamber 2 are separated by the top baffle 13 of the combustion chamber, which is convenient for replacing the cartridge 4 and the solid cartridge 3, and the device can be reused.

[0039] The present invention also provides a method for using a charge-loaded solid energy management engine, based on the above-mentioned charge-loaded solid energy management engine, comprising the following steps:

[0040] When the solid rocket engine is working, the hydraulic propulsion device 6 gradually pushes the solid charge 3 and the outer cartridge 4 placed in the charge chamber 2 into the combustion chamber 1. The solid charge 3 entering the combustion chamber 1 burns and releases high-temperature and high-pressure gas, and the cartridge 4 entering the combustion part is melted under the action of the high-temperature gas. By controlling the loading process of the solid charge 3 entering the combustion chamber, the combustion area of ​​the solid charge participating in the combustion can be changed, thereby changing the generation law of the fuel gas, realizing real-time regulation of the engine thrust and on-demand energy management of the engine.

[0041] By controlling the loading of solid grains, the engine can form different combustion modes. Figure 3 The figure shows the low thrust working mode, in which the speed of solid grain entering can be controlled to be consistent with the burning speed of propellant retreat, and only the end surface A0 is kept burning to form a small thrust. Figure 4 The figure shows the boosting working mode, which increases the pushing speed of the pushing device and the length of the solid grain entering the combustion chamber, so that the solid grain entering the combustion chamber forms the side surface A1 and the end surface A0 to burn simultaneously, thereby increasing the thrust. Figure 5 The figure shows the variable thrust working mode. According to the overall demand of the missile for the engine thrust, the speed of the solid grain entering the combustion chamber is changed through the closed-loop feedback control of the propulsion device, forming the joint combustion of the end surface (A0, A3), the conical surface (A2) and the outer cylindrical surface (A1, A4). The change law of the combustion surface is used to realize the control change of the engine thrust.

[0042] In summary, the present invention controls the solid propellant grains entering the combustion chamber from the source supply end, and adjusts the engine thrust by changing the combustion surface. While retaining the advantages of solid engines, it changes the disadvantage that traditional solid rocket engines can only release energy according to preset rules once ignited. At the same time, the combustion chamber shell and the solid grain shell are designed to be separated, and the combustion chamber part that bears the high temperature and high pressure load accounts for a small proportion, while the grain chamber shell is not in contact with the high temperature and high pressure fuel gas, and the corresponding load-bearing and sealing requirements are greatly reduced. By adopting lightweight materials and structural optimization, the structural mass of the engine can be reduced and the engine mass ratio can be increased. In the present invention, the grain column chamber and the combustion chamber can be disassembled, which is convenient for replacing cartridges and solid grains, and the device can be reused.

[0043] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the above embodiments, ordinary technicians in the relevant field should understand that the specific implementation methods of the present invention can still be modified or replaced by equivalents. Any modification or equivalent replacement that does not depart from the spirit and scope of the present invention should be covered within the scope of protection of the claims of the present invention.

Claims

1. A grain-loaded solid energy management engine, characterized in that: The invention comprises a combustion chamber (1), a charge chamber (2), a solid charge (3), a cartridge (4), an engine nozzle (5), a pushing device (6) and an igniter (7); one end of the combustion chamber (1) is assembled on one end of the charge chamber (2) to form a cylindrical structure; the engine nozzle (5) is assembled on the other end of the combustion chamber; the cartridge (4) is assembled in the combustion chamber (1) and the charge chamber (2); the pushing device (6) is assembled on the other end of the charge chamber (2); the pushing device (6) extends into the charge chamber (2) and is fixedly connected to one end of the cartridge (4); the cartridge (4) is driven along the charge chamber (2) into the combustion chamber (1) by pushing the pushing device (6); the igniter (7) is assembled in the combustion chamber (1); the solid charge (3) is assembled in the cartridge (4); one end of the solid charge (3) extends out of the cartridge (4) and is arranged toward the engine nozzle (5); The combustion chamber (1) comprises a combustion chamber shell (11), a heat insulating layer (12) and a combustion chamber top baffle (13); the heat insulating layer (12) is bonded to the inner surface of the combustion chamber shell (11) and is used to insulate the solid charge (3) burning in the combustion chamber shell (11); the combustion chamber top baffle (13) is an annular component having a through hole at the center, one end of the combustion chamber top baffle (13) is threadedly connected to the end of the combustion chamber shell (11), and the other end is threadedly connected to the end of the charge chamber (2); A plurality of first sealing rings (120) are sleeved between the combustion chamber top baffle (13) and the cartridge (4).

2. A grain-loaded solid energy management engine according to claim 1, characterized in that: A second sealing ring (121) is sleeved between the combustion chamber top baffle (13) and the combustion chamber shell (11).

3. The grain-loaded solid energy management engine according to claim 1, characterized in that: The charge chamber (2) comprises a charge chamber housing (21), one end of which is threadedly connected to a combustion chamber top baffle (13), and the other end of which is equipped with a pushing device (6), and the cartridge (4) is driven along the charge chamber housing (21) into the combustion chamber housing (11) by pushing the pushing device (6).

4. A grain-loaded solid energy management engine according to claim 3, characterized in that: A plurality of guide rings (22) are sleeved between the inner wall of the medicine column chamber housing (21) and the outer wall of the medicine cartridge (4).

5. The grain-loaded solid energy management engine according to claim 3, characterized in that: The drug column chamber shell (21) is a thin-walled cylindrical structure, wherein the cylinder section adopts a porous structure.

6. The grain-loaded solid energy management engine according to claim 1, characterized in that: A nozzle plugging cover (8) is provided at the outlet of the engine nozzle (5).

7. The grain-loaded solid energy management engine according to claim 1, characterized in that: The combustion chamber (1) and the charge chamber (2) are coaxially arranged, and the outer diameters of the combustion chamber (1) and the charge chamber (2) are equal.

8. A method for using a grain-loaded solid energy management engine, based on the grain-loaded solid energy management engine according to any one of claims 1 to 7, characterized in that: The steps include: When the solid rocket engine is working, the hydraulic propulsion device gradually pushes the solid grain (3) and the outer cartridge (4) placed in the grain chamber (2) into the combustion chamber (1). The solid grain (3) entering the combustion chamber (1) burns to release high-temperature and high-pressure gas, and the cartridge (4) entering the combustion chamber (1) partially melts under the action of the high-temperature gas. By controlling the loading process of the solid grain (3) entering the combustion chamber, the combustion area of ​​the solid grain participating in the combustion can be changed, thereby changing the generation law of the combustion gas, thereby achieving real-time control of the engine thrust and on-demand energy management of the engine.

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