A reverse solid-liquid ejection rocket device

Abstract

The transverse solid-liquid ejector rocket device only needs liquid fuel to enter the combustion channel of the oxidizing agent to mix and burn, and the liquid fuel is the same as that carried by the main combustion chamber of the ramjet engine, so the fuel supply of the ramjet engine can be used. Compared with the cycle system of the liquid rocket engine, the additional oxidizing agent 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 launch and maintenance costs are further reduced; compared with the cycle system of the solid rocket engine, the liquid fuel supply can be controlled by opening and closing the fuel supply pipe through the control valve to determine the on-off of the ejector rocket and adjust the working condition parameters such as thrust and oxygen-fuel ratio, which is more suitable for completing complex flight tasks; at the same time, the transverse solid-liquid ejector rocket device only needs to carry one kind of liquid fuel, and adopts the way of separate loading of oxidizing agent and fuel, which improves the safety of the propulsion system.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aerospace power equipment, and particularly relates to a reverse solid-liquid ejection rocket device. BACKGROUND

[0002] The ejection rocket type in the traditional rocket-based combined cycle generally includes a liquid rocket engine, a solid rocket engine and a solid-liquid rocket combined with liquid oxidant and solid fuel, and the ejection rocket has the following defects:

[0003] The liquid rocket engine needs to separately carry liquid oxygen as an oxidant for the ejection rocket in addition to kerosene fuel necessary for the ramjet combustion chamber, which not only needs to increase a liquid oxygen storage tank, but also needs to separately increase a set of oxidant supply system, greatly increasing the space ratio, the structural complexity and the mass of the aircraft.

[0004] The solid rocket engine must wait for the fuel to be consumed before it can stop working after starting, and the working conditions of the ejection mode, the subsonic / supersonic mode and the pure rocket mode in the rocket-based combined cycle are very different for the ejection rocket, and it is difficult to achieve the flight target according to the specified working condition when performing a complex flight task.

[0005] The solid-liquid rocket combined with liquid oxidant and solid fuel has certain advantages in controllability and safety, but also needs a separate oxidant supply system, which is not conducive to the implementation of the engineering scheme.

[0006] Therefore, it is necessary to develop a rocket-based combined cycle that does not need to carry an additional fuel supply system, can realize the adjustment of the working conditions such as the on-off of the ejection rocket and the size of the thrust, and is safe and reliable, so as to lay a foundation for its early engineering application. SUMMARY

[0007] The present application provides a reverse solid-liquid ejection rocket device, which aims to provide a rocket-based combined cycle that does not need to carry an additional fuel supply system, can realize the adjustment of the working conditions such as the on-off of the ejection rocket and the size of the thrust, and is safe and reliable.

[0008] To achieve the above-mentioned purpose, the present application provides the following technical scheme:

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

[0010] a ejection rocket shell, a ramjet main combustion chamber and a ramjet nozzle 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 communicated in sequence, and the combustion chamber is provided with a solid oxidizer, the solid oxidizer is provided with a combustion channel which is communicated with the fuel cavity and the nozzle;

[0012] A fuel supply pipe is further included and is communicated with the fuel cavity, and is used for providing liquid fuel to the fuel cavity;

[0013] A control valve is arranged in the fuel supply pipe and is used for opening and closing the fuel supply pipe; and

[0014] An ignition device is arranged in the combustion channel.

[0015] Further, a fuel part is included, the fuel part includes a fuel shell, and an inner space of the fuel shell constitutes the fuel cavity; a spray cover is further included and is combined with the fuel cavity, and the spray cover is provided with a spray matrix.

[0016] Further, the spray matrix includes a plurality of first spray holes, each of the first spray holes is circumferentially arranged around an axis of the combustion channel, and an included angle between an axis of the first spray hole and the axis of the combustion channel ranges from 0 degree to 30 degree.

[0017] Further, the spray matrix further includes a second spray hole which is arranged at a periphery of the first spray hole, an included angle between an axis of each of the second spray holes and the axis of the combustion channel ranges from 0 degree to 30 degree, at least two second spray holes are arranged between two adjacent first spray holes, and an included angle between the axes of the two second spray holes which are located between the two adjacent first spray holes ranges from 0 degree to 20 degree.

[0018] Further, 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] Further, a conical surface with a gradually decreasing cross section of fuel spray direction is arranged at one end of the fixing member which is close to the spray cover, and the fuel cavity is provided with a wall surface which is matched with the conical surface.

[0020] Further, a combustion shell is included, an inner space of the combustion shell constitutes the combustion chamber, and the combustion shell is connected with the fuel part.

[0021] Further, a supporting device is further included, the supporting device includes a first supporting member and a second supporting member which are connected with each other, the first supporting member is sleeved on the combustion shell, and the second supporting member is connected with the ejector rocket shell.

[0022] Further, the liquid fuel is aviation kerosene, benzene fuel, hydrazine fuel or methane fuel.

[0023] Further, the solid oxidizer is potassium perchlorate, ammonium nitrate or ammonium perchlorate.

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

[0025] 1. The reverse solid-liquid ejection rocket device only needs liquid fuel to enter the combustion channel of the oxidizing agent to mix and burn, and can be the same as the liquid fuel carried by the main combustion chamber of the ramjet engine, so that the fuel of the main combustion chamber of the ramjet engine can be used to supply the ejection rocket device. Compared with the rocket-based combined cycle propulsion system using a liquid rocket engine, the additional oxidant supply system is not needed, the volume occupancy rate, structural complexity and mass of the propulsion system are reduced, and the launch and maintenance costs are further reduced. Compared with the rocket-based combined cycle propulsion system using a solid rocket engine, the liquid fuel supply can be controlled by opening and closing the fuel supply pipe through the control valve, so as to determine the on-off of the ejection rocket and adjust the working condition parameters such as thrust and oxygen-fuel ratio, which is more suitable for completing complex flight tasks. At the same time, the reverse solid-liquid ejection rocket device only needs to carry one kind of liquid fuel, and the oxidizer and fuel are filled separately, which improves the safety of the propulsion system.

[0026] 2. The reverse solid-liquid ejection rocket device has a plurality of first injection holes and second injection holes in the injection cover, which are used for atomizing fuel to improve the combustion effect, and the included angle between the axis of the first injection hole and the second injection hole and the axis of the combustion channel is in the range of 0 to 30 degrees, so that the liquid fuel is injected to the wall surface of the solid oxidizer combustion channel as much as possible.

[0027] 3. The reverse solid-liquid ejection rocket device has a fuel injection direction cross-section gradually decreasing conical surface at one end of the fixed part close to the injection cover, and the fuel cavity has a wall surface matched with the conical surface, so as to enlarge the volume of the fuel. BRIEF DESCRIPTION OF DRAWINGS

[0028] In order to more clearly illustrate the technical solutions in the embodiments of the application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description only show some embodiments of the application, and for those skilled in the art, other drawings can also be obtained without creative labor based on these drawings.

[0029] Figure 1 It is a schematic view of a reverse solid-liquid ejection rocket device of the present application.

[0030] Figure 2A partial sectional view of a reverse solid-liquid ejection rocket device according to the present application;

[0031] Figure 3 A side view of a reverse solid-liquid ejection rocket device according to the present application;

[0032] Figure 4 A Figure 3 A sectional view in the direction of A-A;

[0033] Figure 5 A Figure 3 A sectional view in the direction of B-B;

[0034] Figure 6 A Figure 4 An enlarged view of a portion at A;

[0035] Figure 7 A schematic view of an ejection cover of a reverse solid-liquid ejection rocket device according to the present application;

[0036] Figure 8 A schematic view of an ejection cover of a reverse solid-liquid ejection rocket device according to the present application in an ejection state;

[0037] Figure 9 A schematic view of an ejection rocket housing of a reverse solid-liquid ejection rocket device according to the present application;

[0038] Figure 10 An exploded view of a reverse solid-liquid ejection rocket device according to the present application;

[0039] In the drawing, 10: ejection rocket housing; 101: connection site; 20: fuel portion; 201: fuel housing; 2011: mounting passage; 2012: fuel cavity; 2013: wall surface; 202: ejection cover; 2021: first ejection hole; 2022: second ejection hole; 30: combustion housing; 40: solid oxidizer; 401: combustion passage; 50: ejection nozzle; 60: fuel supply pipe; 70: fixing member; 701: conical surface; 80: ignition device; 901: first support member; 902: second support member. DETAILED DESCRIPTION

[0040] The present application will be described in detail below. Figures 1-10 A detailed description of the present application will be given.

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

[0042] An ejection rocket housing 10, a ramjet main combustion chamber (not shown), and a ramjet nozzle (not shown) connected in sequence;

[0043] The ejector rocket body is coaxially arranged in the ejector rocket shell 10, and is provided with a fuel cavity 2012, a combustion chamber and an ejector nozzle 50 which are sequentially communicated, and the combustion chamber is provided with a solid oxidizer 40 which is provided with a combustion channel 401 communicated with the fuel cavity 2012 and the nozzle;

[0044] The fuel supply pipe 60 is further arranged in the fuel cavity 2012, and is used for supplying liquid fuel to the fuel cavity 2012, wherein the liquid fuel is aviation kerosene, benzene fuel, hydrazine fuel or methane fuel;

[0045] The control valve is arranged in the fuel supply pipe 60, and is used for opening and closing the fuel supply pipe 60.

[0046] The ignition device 80 is arranged in the combustion channel 401.

[0047] The transverse solid-liquid ejector rocket device provided by the application only needs to mix and combust the liquid fuel in the combustion channel 401 of the oxidizing agent, and can be the same as the liquid fuel carried by the main combustion chamber, so that the fuel of the main combustion chamber can be used to supply the ejector rocket device. Compared with the liquid rocket engine, the transverse solid-liquid ejector rocket device does not need an additional oxidizing agent supply system, reduces the volume occupancy, structural complexity and mass of the rocket-based combined cycle, and further reduces the launch and maintenance costs. Compared with the solid rocket engine, the transverse solid-liquid ejector rocket device can control the liquid fuel supply by opening and closing the fuel supply pipe 60 through the control valve, so as to determine the on-off of the ejector rocket and adjust the working condition parameters such as thrust and oxygen-fuel ratio, and is more suitable for completing complex flight tasks. Meanwhile, the transverse solid-liquid ejector rocket device only needs to carry one kind of liquid fuel, and adopts the way of separately loading the oxidizing agent and the fuel, so as to improve the safety of the propulsion system.

[0048] In the embodiment, the fuel part 20 includes a fuel shell 201, and an internal space of the fuel shell 201 constitutes a fuel cavity 2012. The ejector cover 202 is arranged on the fuel cavity 2012, and is provided with an ejector matrix which is used for atomizing the liquid fuel and improving the combustion effect. Further, the ejector matrix includes a plurality of first ejector holes 2021 which are circumferentially arranged around the axis of the combustion channel 401, and the included angle between the axis of the first ejector hole 2021 and the axis of the combustion channel 401 ranges from 0 degree to 30 degrees. Figure 8The spray matrix further comprises second spray holes 2022 arranged at the periphery of the first spray holes 2021, the angle between the axis of each second spray hole 2022 and the axis of the combustion channel 401 ranges from 0 to 30 degrees, at least two second spray holes 2022 are arranged between two adjacent first spray holes 2021, and the angle between the axes of the two second spray holes 2022 located between the two adjacent first spray holes 2021 ranges from 0 to 20 degrees, as shown in Figure 8

[0049] In this embodiment, as shown in Figure 6 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 tapered surface 701 with a gradually decreasing cross-sectional area of the fuel injection direction at one end close to the spray cover 202, and the fuel cavity 2012 is provided with a wall surface 2013 matched with the tapered surface 701, thereby expanding the volume of the fuel.

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

[0051] In this embodiment, as shown in Figure 10 The support device further comprises a first support member 901 and a second support member 902 connected to each other, the first support member 901 is sleeved on the combustion housing 30, and the second support member 902 is connected to the ejector rocket housing 10. Further, the ejector rocket housing 10 is provided with a connecting position 101, and the second support member 902 is locked in the connecting position 101.

[0052] The working principle of the reverse solid-liquid ejector rocket device is as follows:

[0053] The control valve is opened, the fuel supply pipe 60 supplies liquid fuel to the fuel cavity 2012, the liquid fuel is sprayed into the combustion channel 401 through the first spray holes 2021 and the second spray holes 2022 to form a combustible mixture with the solid oxidizer 40, the high-energy electric arc is discharged from the ignition device 80 to ignite the mixture, and the generated high-temperature mixture is expanded and sprayed through the ejector nozzle 50, and the reverse solid-liquid rocket starts to work.

[0054] The incoming flow sucked under the ejecting action of the high-temperature mixture of the reverse solid-liquid rocket is stably combusted in the ramjet main combustion chamber together with the fuel and the fuel sprayed from the main combustion chamber, and the thrust is generated after the expansion and spraying through the ramjet nozzle.

[0055] ​The above examples are only for illustrating the technical concept and characteristics of the present application, and the purpose is to enable those skilled in the art to understand the present application and implement it, and cannot limit the protection scope of the present application. Any equivalent changes or modifications made according to the spirit and principle of the present application shall be covered within the protection scope of the present application.

Claims

1. A reverse solid-liquid ejection rocket apparatus, characterized by comprising: The ejector rocket comprises: a ejector rocket shell, a ramjet main combustion chamber and a ramjet nozzle connected in sequence; an ejector rocket body coaxially arranged in the ejector rocket shell, the ejector rocket body being provided with a fuel cavity, a combustion chamber and an ejector nozzle connected in sequence, and the combustion chamber being provided with a combustion channel communicated with the fuel cavity and the nozzle; a fuel supply pipe communicated with the fuel cavity for supplying liquid fuel to the fuel cavity; a control valve arranged in the fuel supply pipe for opening and closing the fuel supply pipe; a fuel part comprising a fuel shell, an inner space of the fuel shell constituting the fuel cavity, a spray cover body covering the fuel cavity, the spray cover body being provided with a spray matrix; an ignition device, an ignition end of the ignition device being located in the combustion channel, the ignition device being mounted on a fixing member, the fuel shell being provided with a mounting channel, the fixing member being mounted on the mounting channel, an end of the fixing member close to the spray cover body being provided with a tapered surface with gradually decreasing cross section in the direction of fuel spray, the fuel cavity being provided with a wall surface matched with the tapered surface; a combustion shell, an inner space of the combustion shell constituting the combustion chamber, the combustion shell being connected to the fuel part; and a support device comprising a first support member and a second support member connected to each other, the first support member being sleeved on the combustion shell, and the second support member being connected to the ejector rocket shell. The spray matrix comprises a plurality of first spray holes, each of the first spray holes being arranged in a circumferential array around an axis of the combustion channel, and an included angle between an axis of each of the first spray holes and the axis of the combustion channel ranging from 0 degree to 30 degree.

2. A transpiration solid-liquid rocket apparatus as claimed in claim 1, wherein The spray matrix further comprises a second spray hole arranged at a periphery of the first spray hole, an included angle between an axis of each of the second spray holes and the axis of the combustion channel ranging from 0 degree to 30 degree, at least two second spray holes being arranged between two adjacent first spray holes, and an included angle between the axes of the two second spray holes between the two adjacent first spray holes ranging from 0 degree to 20 degree.

3. A transpiration solid-liquid rocket apparatus as claimed in claim 2, wherein The liquid fuel is aviation kerosene, phenyl fuel, hydrazine-based fuel or methane fuel.

4. A transpiration solid propellant rocket engine as claimed in claim 1, wherein, The solid oxidizer is potassium perchlorate, ammonium nitrate or ammonium perchlorate.

5. A trans-solid propellant rocket system as in claim 1 wherein, ​

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