Solid rocket motor grain, solid rocket motor and rocket recovery method

Abstract

The present invention discloses a solid engine charge, a solid rocket engine and a rocket recovery method, which belong to the field of aerospace propulsion systems, wherein the solid engine charge includes an inner charge body and an outer charge body; the outer charge body is coated on the outer circumference of the inner charge body; the inner charge body is a mixture of solid fuel and solid oxidizer; the outer charge body includes solid fuel. The solid rocket engine has a solid engine charge including an inner charge body and an outer charge body. The present invention provides a propellant combustion control mechanism for a solid rocket engine, which can effectively control the combustion of solid rocket propellant. Relying on the propellant combustion control mechanism for a solid rocket engine provided by the present invention, it can provide power and control force for the solid rocket after separation, and provide the necessary power conditions for rocket recovery.

Description

Technical Field

[0001] The present invention relates to the field of aerospace propulsion systems, and in particular to a solid motor charge, a solid rocket motor and a rocket recovery method. Background Art

[0002] In the traditional solid rocket engine design, the propellant is composed of a mixture of solid fuel and oxidizer to form a hollow cylindrical grain. Once the solid propellant is ignited, the grain will continue to burn until the fuel is exhausted, and the combustion process cannot be stopped. As a result, the booster can only fall as an unpowered object after the fuel is exhausted and cannot be recycled. This not only increases the launch cost, but also poses a potential threat to safety.

[0003] In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the invention

[0004] In order to solve the above technical problems, the present application provides a solid motor charge, a solid rocket motor and a rocket recovery method, which realizes the combustion control of the solid rocket motor with a new combustion control mechanism, and provides the necessary conditions for the recovery of the solid rocket.

[0005] A solid rocket motor grain, wherein the motor grain is arranged in a solid motor, comprising:

[0006] A propellant charge body; the propellant charge body is a cylindrical structure, comprising an inner charge body and an outer charge body; the outer charge body is coated on the outer circumference of the inner charge body; the inner charge body is a mixture of solid fuel and solid oxidizer; the outer charge body comprises solid fuel; and

[0007] The gas channel is arranged along the axial direction of the propellant charge body and at the center of the inner charge body.

[0008] According to another aspect of the present application, a solid rocket engine is also provided, comprising: the solid rocket engine charge as described in claim 1 and an adjustable air intake mechanism, a shell, a nozzle assembly and an ignition device; the solid engine charge is fixed in the shell; the nozzle assembly is fixed at the rear end of the shell; the ignition device is fixed in the shell and connected to the gas channel; the adjustable air intake mechanism is configured to allow air outside the shell to enter the interior of the shell to supply oxygen for the combustion of the external charge when the external charge is burning.

[0009] Preferably, the adjustable air intake mechanism is arranged at the head end of the shell.

[0010] Preferably, the adjustable air intake mechanism comprises a shock cone, an air intake duct and an air intake duct valve; the shock cone is arranged at the inlet of the air intake duct; and the air intake duct valve is configured to control the opening and closing of the air intake duct.

[0011] Preferably, the center of the shock cone coincides with the center of the air inlet; and a channel for air circulation is formed between the circumference of the shock cone and the inner wall of the air inlet.

[0012] Preferably, the air inlet comprises a shock wave section, a throat section and an expansion section which are connected in sequence; and the shock wave cone is fixedly arranged in the shock wave section.

[0013] Preferably, the air inlet valve is arranged in the throat section.

[0014] According to another aspect of the present application, a method for recovering a rocket body is also provided, wherein the solid rocket engine is recovered, comprising:

[0015] During the launch phase, after the rocket is ignited, the internal charge column provides the upward thrust, pushing the rocket into the air and separating at the preset time;

[0016] After separation, the rocket falls to a preset height under the action of gravity, and air is introduced into the rocket engine through an adjustable air intake mechanism to contact the external grain body. The external grain body ignites under the residual temperature in the rocket engine combustion chamber to generate thrust;

[0017] The thrust provided by the combustion of the external propellant provides power and control for the rocket after separation, thereby achieving control and recovery of the rocket.

[0018] Compared with the prior art, this application has at least the following beneficial effects:

[0019] 1. The present invention provides a propellant combustion control mechanism for a solid rocket engine, which can effectively control the combustion of solid rocket propellant.

[0020] 2. Relying on the propellant combustion control mechanism of the solid rocket engine provided by the present invention, it is possible to provide power and control force for the solid rocket after separation, and provide the necessary power conditions for rocket recovery.

[0021] 3. The solid rocket engine of the present invention has an adjustable air intake mechanism. Relying on the setting of the adjustable air intake mechanism, after the propellant fuel of the internal charge body of the solid rocket engine is exhausted, the air intake control function of the adjustable air intake mechanism can be used to achieve re-ignition and control, thereby ensuring the combustion control of the solid rocket engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Hereinafter, some specific embodiments of the present invention will be described in detail in an exemplary and non-limiting manner with reference to the accompanying drawings. The same reference numerals in the accompanying drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale. In the accompanying drawings:

[0023] Figure 1 It is a three-dimensional structural diagram of the solid rocket motor grain of the present invention;

[0024] Figure 2 It is a schematic diagram of the cross-sectional structure of the solid rocket motor grain of the present invention;

[0025] Figure 3 It is a schematic cross-sectional structure diagram of the solid rocket engine of the present invention;

[0026] Figure 4 The figure is a schematic cross-sectional structure diagram of the air intake mechanism for adjusting the solid rocket engine of the present invention.

[0027] The above drawings include the following reference numerals:

[0028] 10. External charge body; 11. Shock cone; 12. Inlet valve; 20. Internal charge body; 30. Gas channel; 100. Adjustable intake mechanism; 101. Shock section; 102. Throat section; 103. Expansion section; 200. Shell; 300. Nozzle assembly. DETAILED DESCRIPTION

[0029] In order to make the purpose, technical solution and advantages of the present application clearer, the technical solution of the present application will be clearly and completely described below in combination with the specific embodiments of the present application and the corresponding drawings. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present application.

[0030] The solid rocket motor grain in this scheme is designed as a double-layer structure including an inner grain body and an outer grain body. The inner grain body includes a traditional solid fuel and solid oxidizer mixture, and the outer grain body only contains solid fuel without oxidizer. When the solid fuel and solid oxidizer mixture in the inner grain body is burned out, the combustion reaction will naturally stop due to the lack of oxidizer in the outer grain body. This design allows the outer grain body to be reignited when necessary by reintroducing air as an oxidizer or introducing other oxidizers to contact the solid fuel.

[0031] like Figure 1 and Figure 2As shown, a solid rocket motor grain, the motor grain is arranged in a solid motor, and includes: a propellant grain body and a gas channel 30. The propellant grain body is a cylindrical structure, including an inner grain body 20 and an outer grain body 10; the outer grain body 10 is coated on the outer circumference of the inner grain body 20. The inner grain body 20 is a mixture of solid fuel and solid oxidizer. The outer grain body 10 includes solid fuel. The gas channel 30 is arranged along the axial direction of the propellant grain body and is arranged at the center of the inner grain body 20.

[0032] like Figure 3 and Figure 4 As shown, a solid rocket engine comprises: a solid rocket engine charge and an adjustable air intake mechanism 100, a shell 200, a nozzle assembly 300 and an ignition device (not shown). The solid engine charge is fixed in the shell 200. The nozzle assembly 300 is fixed at the rear end of the shell 200. The ignition device is fixed in the shell 200 and communicated with the fuel gas channel 30. The adjustable air intake mechanism 100 is configured to allow the air outside the shell 200 to enter the shell 200 when the external charge body 10 is burning to provide oxygen for the combustion of the external charge body 10. Under the ignition of the residual temperature in the combustion chamber, the air entering the shell 200 can serve as an oxidant to support the combustion of the external charge body 10.

[0033] Preferably, the adjustable air intake mechanism 100 is disposed at the head end of the housing 200. The adjustable air intake mechanism 100 comprises a shock cone 11, an air intake duct and an air intake duct valve 12; the shock cone 11 is disposed at the entrance of the air intake duct; the air intake duct valve 12 is configured to control the opening and closing of the air intake duct.

[0034] The center of the shock cone 11 coincides with the center of the air inlet; a channel for air circulation is formed between the shock cone 11 and the inner wall of the air inlet in the circumferential direction.

[0035] The air inlet comprises a shock wave section 101 , a throat section 102 and an expansion section 103 which are connected in sequence; the shock wave cone 11 is fixedly arranged at the shock wave section 101 , and the air inlet valve 12 is arranged at the throat section 102 .

[0036] The nozzle assembly 300 can be implemented according to the nozzle assembly of the existing solid rocket. In addition, in order to achieve the effective conduction of the secondary combustion, it can be optimized according to the design requirements and the combustion characteristics of the propellant to ensure the effective output of the thrust.

[0037] During the supersonic flight of the solid rocket, the shock cone 11 and the inner wall of the inlet duct compress and decelerate the incoming airflow, decelerating it from supersonic speed to subsonic speed, meeting the requirements for stable combustion of the solid fuel.

[0038] A rocket body recovery method, utilizing the solid rocket engine to achieve recovery, comprising:

[0039] Step S1: During the launch phase, after the rocket is ignited, the internal charge column provides the upward thrust, pushing the rocket into the air and separating at a preset time;

[0040] Step S2: After separation, the rocket falls to a preset height under the action of gravity, and air is introduced into the rocket engine through the adjustable air intake mechanism 100 to contact the external charge body, and the external charge body is ignited under the residual temperature in the rocket engine combustion chamber to generate thrust;

[0041] Step S3, relying on the thrust provided by the combustion of the external charge body to provide power and control force for the rocket after separation, so as to realize the control and recovery of the rocket.

[0042] In this embodiment, the solid rocket engine charge is designed as a double-layer structure including an inner charge body 20 and an outer charge body 10. The inner charge body 20 includes a traditional solid fuel and solid oxidizer mixture, and the outer charge body 10 contains only solid fuel without oxidizer. When the solid propellant in the inner charge body 20 is ignited and burns to the part with only fuel, the combustion reaction will be terminated due to the lack of oxidizer. Although the combustion reaction is terminated, a relatively high residual temperature is still maintained in the combustion chamber, and the residual temperature can reach the ignition temperature of the solid rocket propellant. When air enters the rocket combustion chamber through the adjustable air intake mechanism 100, the solid fuel in the outer charge body 10 will be ignited again to generate thrust.

[0043] In the adjustable air intake mechanism 100, the shock cone 11 can pre-compress the airflow that will enter the air intake duct. After the supersonic airflow enters the shock wave section 101 of the air intake duct, the shock wave reflected in the air intake duct and the inner wall of the air intake duct will compress and decelerate the airflow to subsonic speed. Then, the subsonic airflow enters the expansion section 103 at the rear of the adjustable air intake duct, expands and depressurizes, and further decelerates, meeting the requirement of stable combustion of the solid fuel in the external charge column 10.

[0044] Through the above scheme, power and control can be provided after the solid rocket separates, especially at lower altitudes below 20,000 meters, so that the rocket body maintains a certain maneuverability and provides power and control for the recovery of the rocket body.

[0045] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0046] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0047] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application 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 numbers used in this way can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.

[0048] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A solid rocket engine, characterized in that: include: Solid rocket motor grains and adjustable inlet mechanisms, casings, nozzle assemblies and ignition devices; The solid rocket engine charge is fixed in the shell; the nozzle assembly is fixed at the rear end of the shell; The ignition device is fixed in the housing and communicated with the gas passage; The solid rocket motor charge is arranged in a solid rocket motor, and includes: A propellant charge body; the propellant charge body is a cylindrical structure, comprising an inner charge body and an outer charge body; the outer charge body is coated on the outer circumference of the inner charge body; the inner charge body is a mixture of solid fuel and solid oxidizer; the outer charge body comprises solid fuel; the adjustable air intake mechanism is configured to allow air outside the shell to enter the shell when the outer charge body burns, so as to provide oxygen for the outer charge body to burn; The gas channel is arranged along the axial direction of the propellant charge body and is arranged at the center of the inner charge body; The adjustable air intake mechanism is arranged at the head end of the shell; The adjustable air intake mechanism comprises a shock cone, an air intake duct and an air intake duct valve; the shock cone is arranged at the inlet of the air intake duct; the air intake duct valve is configured to control the opening and closing of the air intake duct.

2. The solid rocket motor according to claim 1, characterized in that: The center of the shock cone coincides with the center of the air inlet; and a channel for air circulation is formed between the circumference of the shock cone and the inner wall of the air inlet.

3. The solid rocket motor according to claim 2, characterized in that: The air inlet comprises a shock wave section, a throat section and an expansion section which are connected in sequence; the shock wave cone is fixedly arranged in the shock wave section.

4. The solid rocket motor according to claim 3, characterized in that: The air inlet valve is arranged on the throat section.

5. A method for recovering an arrow body, characterized in that: The method of recovering a solid rocket engine according to any one of claims 1 to 4 comprises: During the launch phase, after the rocket is ignited, the internal charge column provides the upward thrust, pushing the rocket into the air and separating at the preset time; After separation, the rocket falls to a preset height under the action of gravity, and air is introduced into the rocket engine through an adjustable air intake mechanism to contact the external grain body. The external grain body ignites under the residual temperature in the rocket engine combustion chamber to generate thrust; The thrust provided by the combustion of the external propellant provides power and control for the rocket after separation, thereby achieving control and recovery of the rocket.

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