A device for testing the response intensity of a solid rocket engine charge under the condition of baking

Abstract

The application provides a solid rocket engine charge response intensity testing device under baking condition, which comprises a high-speed photography system, a temperature testing system, a solid rocket engine charge intensity tester and a controllable heating system, wherein the solid rocket engine charge intensity tester comprises a directional plug, a sliding block, a shell and a charge, the directional plug is a column with an axial through hole, the charge is wrapped by the shell, the shell is open at the front end and communicates with the through hole of the directional plug, and the sliding block is installed in the through hole of the directional plug; the solid rocket engine charge intensity tester is installed in the controllable heating system, the charge is heated by the controllable heating system until the charge pushes the sliding block to move after reaction; the high-speed photography system collects the sliding block movement image; and the temperature testing system collects the charge temperature. The application has low processing cost, high testing precision, simple testing method, can realize quantitative or semi-quantitative evaluation, and is suitable for various types of solid rocket engine charges.

Description

Technical Field

[0001] This invention belongs to the field of solid rocket engine technology, specifically a device for testing the intensity of propellant response. Background Technology

[0002] Solid rocket motors may face hazards such as fires during storage and use. In the event of a fire, the solid rocket motor may explode, posing a serious threat to surrounding equipment and personnel. Given the high risk of explosion of the propellant charge in thermal environments (fire or nearby fire), accurately and quantitatively determining the intensity of the propellant charge's response becomes a crucial parameter for assessing the response intensity of solid rocket motors under thermal conditions.

[0003] Currently, the evaluation of the response intensity of solid rocket engines under thermal conditions mainly relies on the propellant combustion test. The advantages of this method are: (1) The test method is simple and easy to operate. A universal tester is used. After casting a specific propellant, both ends are sealed and placed in a heat-insulating device for testing under a certain heating rate. (2) The result evaluation method is simple. The response intensity of the solid rocket engine propellant is qualitatively evaluated based on the evaluation criteria such as the overpressure of the shock wave generated when the propellant reacts, the degree of shell breakage, and the degree of damage to the witness plate. The disadvantages of this method are: (1) The propellant intensity evaluation can only be qualitative. When using the evaluation criteria such as the overpressure of the shock wave generated, the degree of shell breakage, and the degree of damage to the witness plate, only the qualitative intensity of the propellant under combustion conditions can be given. (2) The evaluation method is vague. The evaluation of the propellant intensity level mainly relies on the actual experience of the evaluator and lacks a certain degree of objectivity. Summary of the Invention

[0004] To overcome the shortcomings of existing technologies, this invention provides a solid rocket engine propellant combustion response intensity testing device, which can quantitatively or semi-quantitatively evaluate the propellant response intensity of solid rocket engines.

[0005] The technical solution adopted by the present invention to solve its technical problem is: a solid rocket engine propellant combustion response intensity testing device, including a high-speed photography system, a temperature testing system, a solid rocket engine propellant intensity tester, and a controllable heating system.

[0006] The solid rocket motor propellant intensity tester includes a directional plug, a slider, a shell, and a propellant. The directional plug is a cylindrical body with an axial through hole. The propellant is encased in the shell, with an opening at the front end that connects to the through hole of the directional plug. The slider is installed inside the through hole of the directional plug. The solid rocket motor propellant intensity tester is installed in a controllable heating system, which heats the propellant until a reaction occurs, driving the slider to move. A high-speed photography system captures images of the slider's movement. A temperature testing system collects the propellant temperature.

[0007] The high-speed photography system includes a high-speed camera, control circuitry, and a control computer.

[0008] The machine is aligned with the through-hole outlet of the directional plug and connected to the control computer via a control circuit, and is opened or closed under the control of the control computer.

[0009] The controllable heating system includes a temperature controller, a control cable, a temperature acquisition cable, a temperature sensor, and a heating cylinder. The temperature sensor is installed on the inner wall of the heating cylinder and sends the real-time temperature inside the heating cylinder to the temperature controller through the temperature acquisition cable. The temperature controller controls the ambient temperature inside the heating cylinder through the control cable.

[0010] The solid rocket motor propellant intensity tester includes a front support cover, a rear support cover, a directional plug, a slider, a shell, and a propellant charge. Both the front and rear support covers are cylindrical bodies with axially stepped through-holes. The innermost step of the front support cover mates with the directional plug, and the innermost step of the rear support cover mates with the sealing cover. The directional plug is also a cylindrical body with axially stepped through-holes; the stepped surface mates with one end of the propellant charge shell. The slider is installed in the small-diameter section of the stepped through-hole. The other end of the shell mates with and is sealed by the sealing cover.

[0011] The outermost step of the cover engages with the heating cylinder of the controllable heating system, with a gap 5 between the heating cylinder and the housing; a temperature sensor is installed on the inner wall of the housing.

[0012] A marker is provided axially on the end face of the slider that is away from the charge.

[0013] A sealing ring is provided between the front support cover and the outer wall of the directional plug, between the front support cover and the end face of the housing, and between the outer wall of the sealing cover and the rear support cover.

[0014] The temperature testing system includes a data acquisition unit and a control computer. The control computer is connected to the temperature sensor inside the housing via the data acquisition unit 0 to detect changes in the internal temperature of the charge.

[0015] The temperature testing system and the high-speed photography system share the same control computer.

[0016] The beneficial effects of this invention are:

[0017] (1) The speed and temperature testing of the present invention have high accuracy and the testing method is simple;

[0018] (2) The solid rocket engine propellant intensity tester of the present invention has good versatility and is applicable to various types of solid rocket engine propellants;

[0019] (3) The test method in this invention has good versatility and can meet the evaluation of propellant intensity of various types of solid rocket engines;

[0020] (4) The solid rocket engine propellant intensity tester in this invention has a wide range of material sources, low processing cost, and is easy to manufacture;

[0021] (5) The present invention has a wide range of applications, with a temperature control and measurement range of 0℃~1200℃ and a speed measurement range of 0m / s~200m / s;

[0022] (6) The indicators of the present invention are highly objective. The slider movement speed and temperature are objective measured values, which can objectively and directly display the propellant response intensity of the solid rocket engine. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the device of the present invention;

[0024] Figure 2 This is a schematic diagram of a high-speed photography system.

[0025] Figure 3 This is a schematic diagram of a temperature testing system.

[0026] Figure 4 This is a schematic diagram of a solid rocket motor propellant intensity tester.

[0027] Figure 5 This is a schematic diagram of a controllable heating system.

[0028] In the diagram, 1. High-speed photography system, 2. Temperature testing system, 3. Solid rocket motor propellant intensity tester, 4. Controllable heating system, 1-1. High-speed camera, 1-2. Control circuit, 1-3. Control computer, 2-1. Data acquisition unit, 2-2. Control computer, 3-1. Front support cover, 3-2. Orientation plug, 3-3. Thermal insulation sealing ring, 3-4. Marker, 3-5. Sealing ring X, 3-6. Slider, 3-7. Fixing ring, 3-8. Shell, 3-9. Sealing ring, 3-10. Sealing cover, 3-11. Propellant temperature sensor, 3-12. Control line, 3-13. Shell sealing ring, 3-14. Propellant, 4-1. Temperature controller, 4-2. Control cable, 4-3. Temperature acquisition cable, 4-4. Temperature sensor, 4-5. Heating cylinder. Detailed Implementation

[0029] The present invention will be further described below with reference to the accompanying drawings and embodiments. The present invention includes, but is not limited to, the following embodiments.

[0030] This invention provides a test apparatus for evaluating the response intensity of solid rocket motor propellant under combustion conditions. The apparatus uses both the slider movement speed and the temperature at the propellant reaction point to evaluate the response intensity of solid rocket motor propellant under combustion conditions. This test apparatus is primarily used for quantitative or semi-quantitative evaluation of the response intensity of solid rocket motor propellant under combustion conditions.

[0031] The testing device provided by this invention includes a high-speed camera system, a controllable heating system, a solid rocket motor propellant intensity tester, and a temperature acquisition system. The high-speed camera system consists of a high-speed camera, control circuitry, and control calculations, primarily used to capture the flight velocity of the slider after the solid rocket motor propellant intensity test reaction. The controllable heating system mainly consists of a temperature control box, an insulation temperature sensor, and a heating cylinder, primarily used to heat the solid rocket motor propellant intensity tester and control its heating rate. The solid rocket motor propellant intensity tester is a key component for assessing the intensity of the solid rocket motor propellant response. This tester mainly consists of a front support cover, a directional plug, an insulation sealing ring, a marker, a sealing ring X, a slider, a fixing ring, a shell, a sealing ring, a sealing cover, a propellant temperature sensor, control lines, a shell sealing ring, and the propellant itself. The temperature acquisition system mainly consists of a temperature acquisition unit and a control computer. The solid rocket motor propellant intensity tester is fixed within a heating jacket, which is connected to a temperature control box and an insulation temperature sensor. The temperature control box controls the heating temperature of the heating jacket, continuously heating the tester until the solid rocket motor propellant reacts. Upon reaction, a large amount of gas is instantly generated and rapidly expands, propelling the slider and marker within the tester to move quickly and exit the directional plug. A high-speed photography system captures the movement of the slider and marker and calculates their velocity. A propellant temperature sensor is connected to a temperature acquisition system, recording real-time temperature changes inside the propellant grain and the temperature at the reaction point. The intensity of the solid rocket motor propellant response is evaluated using both the slider's velocity and the propellant grain's reaction point temperature.

[0032] Examples of embodiments of the present invention Figure 1 As shown, a device for testing the response intensity of a solid rocket engine propellant under combustion conditions is provided, including a high-speed photography system 1, a temperature testing system 2, a solid rocket engine propellant intensity tester 3, and a controllable heating system 4.

[0033] like Figure 2 As shown, the high-speed photography system 1 mainly consists of a high-speed camera 1-1, a control circuit 1-2, and a control computer 1-3. The high-speed camera 1-1 is connected to the control computer 1-3 through the control circuit 1-2, and the control computer 1-3 controls the high-speed photography system to turn on and off.

[0034] The high-speed camera is aimed at the through-hole outlet of the directional plug and is connected to the control computer via a control circuit, and is turned on or off by the control computer.

[0035] like Figure 3As shown, the temperature testing system 2 mainly consists of a data acquisition unit 2-1 and a control computer 2-2 (which can share the same control computer with the high-speed photography system). The control computer 2-2 is connected to the data acquisition unit 2-1 via a cable, and the data acquisition unit 2-1 is connected to the temperature sensor 3-10 via a control line 3-11 to detect changes in the internal temperature of the propellant.

[0036] like Figure 4 As shown, the solid rocket motor propellant intensity tester 3 mainly consists of a front support cover 3-1, a directional plug 3-2, a thermal insulation sealing ring 3-3, a marker 3-4, a sealing ring X 3-5, a slider 3-6, a fixing ring 3-7, a shell 3-8, a sealing ring 3-9, a sealing cover 3-10, a propellant temperature sensor 3-11, a control line 3-12, a shell sealing ring 3-13, and a propellant 3-14.

[0037] Both the front and rear support covers are cylindrical bodies with axially stepped through holes. The innermost step of the front support cover mates with a directional plug, and the innermost step of the rear support cover mates with a sealing cover. The directional plugs are also cylindrical bodies with axially stepped through holes, and the stepped surfaces mate with one end of the casing containing the drug. The slider is installed in the small-diameter section of the stepped through hole. The other end of the casing mates with and is sealed by the sealing cover. The outermost steps of the front and rear support covers mate with the heating cylinder of the controllable heating system, and a gap is left between the heating cylinder and the casing. A temperature sensor is installed on the inner wall of the casing.

[0038] A marker is provided axially on the end face of the slider that is away from the charge.

[0039] A sealing ring is provided between the front support cover and the outer wall of the directional plug, between the front support cover and the end face of the housing, and between the outer wall of the sealing cover and the rear support cover.

[0040] like Figure 5 As shown, the controllable heating system 4 mainly consists of a temperature controller 4-1, a control cable 4-2, a temperature acquisition cable 4-3, a temperature sensor 4-4, and a heating cylinder 4-5.

[0041] The temperature sensor is installed on the inner wall of the heating cylinder and sends the real-time temperature inside the heating cylinder to the temperature controller via a temperature acquisition cable; the temperature controller controls the ambient temperature inside the heating cylinder via a control cable.

[0042] In this embodiment, the solid rocket motor propellant intensity tester 3 is heated at a certain rate by the controllable heating system 4 until the propellant 3-14 in the tester 3 reacts. After the propellant 3-14 reacts, it generates a large amount of gas and expands rapidly in a short time, pushing the marker 3-4 and the slider 3-6 to move quickly. The moving speed of the marker 3-4 and the slider 3-6 is recorded by the high-speed photography system 1, and the reaction temperature of the propellant 3-14 is measured by the temperature testing system 2. The propellant response intensity is determined by combining the moving speed of the marker 3-4 and the slider 3-6 with the reaction temperature of the propellant 3-14.

Claims

1. A device for testing the response intensity of a solid rocket motor propellant under combustion conditions, comprising a high-speed photography system, a temperature testing system, a solid rocket motor propellant intensity tester, and a controllable heating system, characterized in that, The solid rocket motor propellant intensity tester includes a directional plug, a slider, a shell, and a propellant charge. The directional plug is a cylindrical body with an axial through hole. The propellant charge is encased in the shell, with an opening at the front end that connects to the through hole of the directional plug. The slider is installed within the through hole of the directional plug. The solid rocket motor propellant intensity tester is installed within a controllable heating system, which heats the propellant until a reaction occurs, driving the slider to move. A high-speed photography system captures images of the slider's movement. A temperature testing system collects the propellant temperature. The solid rocket motor propellant intensity tester includes a front support cover. The system comprises a rear support cover, a directional plug, a slider, a housing, and a propellant charge. Both the front and rear support covers are cylindrical bodies with axially stepped through-holes. The innermost step of the front support cover mates with the directional plug, and the innermost step of the rear support cover mates with the sealing cover. The directional plugs are also cylindrical bodies with axially stepped through-holes, with the stepped surface mates with one end of the housing containing the propellant charge. The slider is installed in the small-diameter section of the stepped through-hole. The other end of the housing mates with and is sealed by the sealing cover. The outermost steps of the front and rear support covers mate with the heating cylinder of the controllable heating system, with a gap between the heating cylinder and the housing. A temperature sensor is installed on the inner wall of the housing.

2. The solid rocket motor propellant combustion response intensity testing device according to claim 1, characterized in that, The high-speed photography system includes a high-speed camera, a control circuit, and a control computer. The high-speed camera is aimed at the through-hole outlet of the directional plug and is connected to the control computer via the control circuit, and is turned on or off by the control computer.

3. The solid rocket motor propellant combustion response intensity testing device according to claim 1, characterized in that, The controllable heating system includes a temperature controller, a control cable, a temperature acquisition cable, a temperature sensor, and a heating cylinder. The temperature sensor is installed on the inner wall of the heating cylinder and sends the real-time temperature inside the heating cylinder to the temperature controller through the temperature acquisition cable. The temperature controller controls the ambient temperature inside the heating cylinder through the control cable.

4. The solid rocket motor propellant combustion response intensity testing device according to claim 1, characterized in that, A marker is provided axially on the end face of the slider that is away from the charge.

5. The solid rocket motor propellant combustion response intensity testing device according to claim 1, characterized in that, A sealing ring is provided between the front support cover and the outer wall of the directional plug, between the front support cover and the end face of the housing, and between the outer wall of the sealing cover and the rear support cover.

6. The solid rocket engine propellant combustion response intensity testing device according to claim 1, characterized in that, The temperature testing system includes a data acquisition unit and a control computer. The control computer is connected to the temperature sensor inside the housing through the data acquisition unit to detect changes in the internal temperature of the charge.

7. The solid rocket engine propellant combustion response intensity testing device according to claim 6, characterized in that, The temperature testing system and the high-speed photography system share the same control computer.

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