Trans-type solid-liquid rocket ejection device

Abstract

According to the reverse solid-liquid rocket ejector device, liquid fuel can be mixed and combusted with a combustion channel of an oxidizing agent as long as the liquid fuel enters the combustion channel of the oxidizing agent, and the liquid fuel is the same as the liquid fuel carried by a main combustion chamber of a ramjet engine, so that the fuel of the main combustion chamber of the ramjet engine can be supplied to the rocket ejector device. Compared with a circulating system adopting a liquid rocket engine, an additional oxidant supply system is not needed, the volume occupancy rate, the structural complexity and the mass of the rocket-based combined cycle are reduced, and the launching and maintenance cost is further reduced; compared with a circulating system adopting a solid rocket engine, the circulating system has the advantages that the fuel supply pipe can be opened and closed through the control valve to control the supply of liquid fuel, so as to determine the startup and shutdown of the rocket ejector and adjust the working condition parameters such as thrust and oxygen-fuel ratio, and the circulating system is more suitable for completing complex flight tasks; meanwhile, the reverse type solid-liquid rocket ejection device only needs to carry one kind of liquid fuel, the mode that an oxidizing agent and the fuel are separately filled is adopted, and the safety of a propelling system is improved.

Description

Technical Field

[0001] The invention relates to the technical field of aerospace power equipment, and in particular to a reverse solid-liquid ejection rocket device. Background Art

[0002] The types of ejector rockets in the traditional rocket-based combined cycle generally include liquid rocket engines, solid rocket engines, and solid-liquid rockets combined with liquid oxidizers and solid fuels. The ejector rockets have the following defects:

[0003] In addition to the kerosene fuel required for the ramjet combustion chamber, liquid rocket engines must also carry liquid oxygen separately to provide oxidizer for the launch rocket. This not only requires the addition of liquid oxygen storage tanks, but also a separate oxidizer supply system, which greatly increases the space occupied, structural complexity and vehicle mass.

[0004] After starting, a solid rocket engine must wait until the fuel is consumed before it can stop working. In addition, the ejection mode, subsonic / scramsonic mode, and pure rocket mode in the rocket-based combined cycle have very different requirements for the operating conditions of the ejection rocket. When performing complex flight missions, it is difficult to achieve flight goals according to the specified operating conditions.

[0005] Although solid-liquid rockets that combine liquid oxidizer and solid fuel have certain advantages in terms of controllability and safety, they also require a separate oxidizer supply system, which is not conducive to the implementation of engineering plans.

[0006] Therefore, it is necessary to develop a rocket-based combined cycle that does not require an additional fuel supply system to realize the adjustment of operating conditions such as the power on and off of the launch rocket and the thrust size, and is safe and reliable, so as to lay the foundation for its early engineering application. Summary of the invention

[0007] The present invention provides a reverse solid-liquid ejection rocket device, aiming to provide a rocket-based combined cycle that can realize the adjustment of the ejection rocket power on and off, thrust size and other working conditions without carrying an additional fuel supply system, and is safe and reliable.

[0008] To achieve the above object, the present invention provides the following technical solutions:

[0009] A reverse solid-liquid ejection rocket device, comprising:

[0010] The launch rocket shell, ramjet main combustion chamber and ramjet nozzle are connected in sequence;

[0011] An ejector rocket body is coaxially arranged in the ejector rocket shell, the ejector rocket body is provided with a fuel cavity, a combustion chamber and an ejector nozzle which are connected in sequence, and a solid oxidizer is provided in the combustion chamber, and the solid oxidizer is provided with a combustion channel which is connected to the fuel cavity and the nozzle;

[0012] Also included is a fuel supply pipe, which is connected to the fuel cavity and is used to provide liquid fuel to the fuel cavity;

[0013] a control valve, disposed on the fuel supply pipe, for opening and closing the fuel supply pipe; and,

[0014] An ignition device, the ignition end of which is located in the combustion channel.

[0015] Furthermore, it comprises a fuel part, the fuel part comprises a fuel shell, the internal space of the fuel shell constitutes the fuel cavity; it also comprises an injection cover body covering the fuel cavity, the injection cover body is provided with an injection matrix.

[0016] Furthermore, the injection matrix includes a plurality of first injection holes, each of which is arranged in a circular array around the axis of the combustion channel, and the angle between the axis of the first injection hole and the axis of the combustion channel ranges from 0 degrees to 30 degrees.

[0017] Furthermore, the injection matrix also includes second injection holes arranged outside the first injection holes, the angle between the axis of each second injection hole and the axis of the combustion channel ranges from 0 degrees to 30 degrees, at least two second injection holes are arranged between two adjacent first injection holes, and the angle between the axes of the two second injection holes located between two adjacent first injection holes ranges from 0 degrees to 20 degrees.

[0018] Furthermore, the ignition device is mounted on a fixing member, the fuel shell is provided with a mounting channel, and the fixing member is mounted on the mounting channel.

[0019] Furthermore, the fixing member is provided with a conical surface whose cross section gradually decreases in the fuel injection direction at one end thereof close to the injection cover body, and the fuel cavity is provided with a wall surface adapted to the conical surface.

[0020] Furthermore, it comprises a combustion shell, the internal space of which constitutes the combustion chamber, and the combustion shell is connected to the fuel part.

[0021] Furthermore, it also includes a supporting device, which includes a first supporting member and a second supporting member connected to each other, the first supporting member is sleeved outside the combustion shell, and the second supporting member is connected to the launch rocket shell.

[0022] Furthermore, the liquid fuel is aviation kerosene, phenyl fuel, hydrazine-based fuel or methane fuel.

[0023] Furthermore, the solid oxidant is potassium perchlorate, ammonium nitrate or ammonium perchlorate.

[0024] The beneficial effects of the present invention are:

[0025] 1. The reverse solid-liquid launch rocket device proposed by the present invention only needs liquid fuel to enter the combustion channel of the oxidant to mix and burn with it, and can be the same as the liquid fuel carried by the main combustion chamber of the ramjet engine, so the fuel supply launch rocket device of the ramjet main combustion chamber can be used. Compared with the rocket-based combined cycle propulsion system using a liquid rocket engine, no additional oxidant supply system is required, which reduces the volume occupancy rate, structural complexity and quality of the propulsion system, and further reduces the launch and maintenance costs; compared with the rocket-based combined cycle propulsion system using a solid rocket engine, the fuel supply pipe can be opened and closed by a control valve to control the liquid fuel supply, so as to determine the start and stop of the launch rocket and adjust the thrust, oxygen-fuel ratio and other working parameters, which is more suitable for completing complex flight missions; at the same time, the reverse solid-liquid launch rocket device only needs to carry one liquid fuel, and adopts a method of separately loading the oxidant and the fuel to improve the safety of the propulsion system.

[0026] 2. The present invention proposes a reverse solid-liquid ejection rocket device, in which the injection cover is provided with a plurality of first injection holes and second injection holes for atomizing the fuel to improve the combustion effect, and the angle between the axis of the first injection holes and the second injection holes and the axis of the combustion channel ranges from 0 degrees to 30 degrees, so that the liquid fuel can be injected into the wall of the solid oxidizer combustion channel as much as possible.

[0027] 3. In a reverse solid-liquid ejection rocket device proposed by the present invention, a conical surface with a gradually decreasing cross-section in the fuel injection direction is provided at one end of the fixing part close to the injection cover body, and the fuel chamber is provided with a wall surface adapted to the conical surface, thereby expanding the volume of the fuel material. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0029] Figure 1 A schematic diagram of a reverse solid-liquid ejection rocket device of the present invention;

[0030] Figure 2It is a partial cross-sectional view of a reverse solid-liquid ejection rocket device of the present invention;

[0031] Figure 3 It is a side view of a reverse solid-liquid ejection rocket device of the present invention;

[0032] Figure 4 for Figure 3 Middle AA section view;

[0033] Figure 5 for Figure 3 Middle BB section view;

[0034] Figure 6 for Figure 4 A partial enlarged view of the middle part;

[0035] Figure 7 It is a schematic diagram of a jet cover of a reverse solid-liquid ejection rocket device of the present invention;

[0036] Figure 8 It is a schematic diagram of the injection state of the injection cover of a reverse solid-liquid ejection rocket device of the present invention;

[0037] Fig. 9 A diagram of a rocket shell of a reverse solid-liquid launch rocket device of the present invention;

[0038] Fig.10 An exploded view of a reverse solid-liquid ejection rocket device of the present invention;

[0039] In the figure, 10, ejection rocket shell; 101, connection position; 20, fuel part; 201, fuel shell; 2011, installation channel; 2012, fuel chamber; 2013, wall; 202, injection cover; 2021, first injection hole; 2022, second injection hole; 30, combustion shell; 40, solid oxidizer; 401, combustion channel; 50, ejection nozzle; 60, fuel supply pipe; 70, fixing member; 701, cone surface; 80, ignition device; 901, first support member; 902, second support member. DETAILED DESCRIPTION

[0040] Combine the following Figure 1-Figure 10 The present invention is described in detail.

[0041] A reverse solid-liquid ejection rocket device, comprising:

[0042] A launch rocket casing 10, a ramjet main combustion chamber (not shown) and a ramjet nozzle (not shown) connected in sequence;

[0043] The ejection rocket body is coaxially arranged in the ejection rocket shell 10, and the ejection rocket body is provided with a fuel cavity 2012, a combustion chamber and an ejection nozzle 50 which are connected in sequence, and a solid oxidant 40 is provided in the combustion chamber, and the solid oxidant 40 is provided with a combustion channel 401 which is connected to the fuel cavity 2012 and the nozzle;

[0044] It also includes a fuel supply pipe 60, which is connected to the fuel cavity 2012 and is used to provide liquid fuel to the fuel cavity 2012. The liquid fuel is aviation kerosene, phenyl fuel, hydrazine fuel or methane fuel;

[0045] a control valve, provided in the fuel supply pipe 60, for opening and closing the fuel supply pipe 60; and,

[0046] The ignition device 80 has an ignition end located in the combustion channel 401 .

[0047] The reverse solid-liquid launch rocket device proposed by the present invention only needs liquid fuel to enter the combustion channel 401 of the oxidant to mix and burn with it, and can be the same as the liquid fuel carried by the main combustion chamber, so the fuel supply launch rocket device of the ramjet main combustion chamber can be used. Compared with the use of liquid rocket engines, no additional oxidant supply system is required, which reduces the volume occupancy rate, structural complexity and mass of the rocket-based combined cycle, and further reduces the launch and maintenance costs; compared with the use of solid rocket engines, the fuel supply pipe 60 can be opened and closed by the control valve to control the liquid fuel supply, so as to determine the start and stop of the launch rocket and adjust the thrust, oxygen-fuel ratio and other working parameters, which is more suitable for completing complex flight missions; at the same time, the reverse solid-liquid launch rocket device only needs to carry one liquid fuel, and adopts the method of separate loading of oxidant and fuel to improve the safety of the propulsion system.

[0048] In this embodiment, the fuel section 20 is included, the fuel section 20 includes a fuel shell 201, the internal space of the fuel shell 201 constitutes a fuel cavity 2012; and the fuel section 20 includes an injection cover 202 covering the fuel cavity 2012, the injection cover 202 is provided with an injection matrix, and the injection matrix is ​​used to atomize the liquid fuel to improve the combustion effect. Further, the injection matrix includes a plurality of first injection holes 2021, each of which is arranged in a circular array around the axis of the combustion channel 401, and the angle between the axis of the first injection hole 2021 and the axis of the combustion channel 401 ranges from 0 degrees to 30 degrees, such as Figure 8The injection matrix also includes second injection holes 2022 disposed on the periphery of the first injection holes 2021, and the angle between the axis of each second injection hole 2022 and the axis of the combustion channel 401 ranges from 0 to 30 degrees. At least two second injection holes 2022 are disposed between two adjacent first injection holes 2021, and the angle between the axes of the two second injection holes 2022 located between the two adjacent first injection holes 2021 ranges from 0 to 20 degrees. Figure 8 shown.

[0049] In this embodiment, Figure 6 As shown, the ignition device 80 is mounted on the fixing member 70, the fuel housing 201 is provided with a mounting channel 2011, and the fixing member 70 is mounted on the mounting channel 2011. The fixing member 70 is provided with a conical surface 701 whose cross section gradually decreases in the fuel injection direction at one end close to the injection cover 202, and the fuel cavity 2012 is provided with a wall surface 2013 adapted to the conical surface 701, thereby expanding the volume of the fuel material.

[0050] In this embodiment, a combustion shell 30 is included, the internal space of the combustion shell 30 constitutes a combustion chamber, the combustion shell 30 is connected to the fuel unit 20, and a solid oxidant 40 is arranged in the combustion shell 30, and the solid oxidant 40 is potassium perchlorate, ammonium nitrate or ammonium perchlorate.

[0051] In this embodiment, Fig.10 As shown, it also includes a supporting device, which includes a first supporting member 901 and a second supporting member 902 connected to each other, the first supporting member 901 is sleeved outside the combustion shell 30, and the second supporting member 902 is connected to the launch rocket shell 10. Further, the launch rocket shell 10 is provided with a connecting position 101, and the second supporting member 902 is locked to the connecting position 101.

[0052] The working principle of the reverse solid-liquid ejection rocket device proposed in this embodiment is as follows:

[0053] Open the control valve, and the fuel supply pipe 60 supplies liquid fuel to the fuel chamber 2012. The liquid fuel is sprayed into the combustion channel 401 through the first injection hole 2021 and the second injection hole 2022, and contacts with the solid oxidizer 40 to form a combustible mixture. The ignition device 80 emits a high-energy arc to ignite it, and the generated high-temperature mixture is expanded and sprayed out through the ejector nozzle 50, and the trans-solid-liquid rocket starts to work.

[0054] The incoming flow sucked in by the ejection of the high-temperature mixture of the reverse solid-liquid rocket, together with the combustion gas and the fuel ejected from the main combustion chamber, burns stably in the ramjet main combustion chamber, and generates thrust after being expanded and ejected through the ramjet nozzle.

[0055] The above embodiments are only for illustrating the technical concept and features of the present invention, and their purpose is to enable those skilled in the art to understand the content of the present invention and implement it, and they cannot be used to limit the protection scope of the present invention. Any equivalent changes or modifications made according to the spirit of the present invention should be included in the protection scope of the present invention.

Claims

1. A reverse solid-liquid ejection rocket device, characterized in that: include: The launch rocket shell, ramjet main combustion chamber and ramjet nozzle are connected in sequence; An ejector rocket body is coaxially arranged in the ejector rocket shell, the ejector rocket body is provided with a fuel cavity, a combustion chamber and an ejector nozzle which are connected in sequence, and a solid oxidizer is provided in the combustion chamber, and the solid oxidizer is provided with a combustion channel which is connected to the fuel cavity and the nozzle; Also included is a fuel supply pipe, which is connected to the fuel cavity and is used to provide liquid fuel to the fuel cavity; a control valve, disposed on the fuel supply pipe, for opening and closing the fuel supply pipe; and, An ignition device, the ignition end of which is located in the combustion channel.

2. A reverse solid-liquid ejection rocket device as claimed in claim 1, characterized in that: The invention comprises a fuel part, wherein the fuel part comprises a fuel shell, wherein the internal space of the fuel shell constitutes the fuel cavity; and an injection cover body covering the fuel cavity, wherein the injection cover body is provided with an injection matrix.

3. A reverse solid-liquid ejection rocket device as claimed in claim 2, characterized in that: The injection matrix includes a plurality of first injection holes, each of which is arranged in a circular array around the axis of the combustion channel, and the angle between the axis of the first injection hole and the axis of the combustion channel ranges from 0 degrees to 30 degrees.

4. A reverse solid-liquid ejection rocket device as claimed in claim 3, characterized in that: The injection matrix also includes second injection holes arranged outside the first injection holes, the angle between the axis of each second injection hole and the axis of the combustion channel ranges from 0 degrees to 30 degrees, at least two second injection holes are arranged between two adjacent first injection holes, and the angle between the axes of the two second injection holes located between two adjacent first injection holes ranges from 0 degrees to 20 degrees.

5. A reverse solid-liquid ejection rocket device as claimed in claim 2, characterized in that: The ignition device is mounted on a fixing member, the fuel housing is provided with a mounting channel, and the fixing member is mounted on the mounting channel.

6. A reverse solid-liquid ejection rocket device as claimed in claim 5, characterized in that: The fixing member is provided with a conical surface whose cross section gradually decreases in the fuel injection direction at one end thereof close to the injection cover body, and the fuel cavity is provided with a wall surface matched with the conical surface.

7. A reverse solid-liquid ejection rocket device as claimed in claim 1, characterized in that: The invention comprises a combustion shell, the inner space of which constitutes the combustion chamber, and the combustion shell is connected to the fuel part.

8. A reverse solid-liquid ejection rocket device as claimed in claim 7, characterized in that: It also includes a supporting device, which includes a first supporting member and a second supporting member connected to each other, the first supporting member is sleeved outside the combustion shell, and the second supporting member is connected to the launch rocket shell.

9. A reverse solid-liquid ejection rocket device as claimed in claim 1, characterized in that: The liquid fuel is aviation kerosene, phenyl fuel, hydrazine-based fuel or methane fuel.

10. A reverse solid-liquid ejection rocket device as claimed in claim 1, characterized in that: The solid oxidant is potassium perchlorate, ammonium nitrate or ammonium perchlorate.

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