Method for prolonging working time of solid attitude and orbit control engine

Abstract

The invention relates to a method for prolonging the working time of a solid attitude and orbit control engine, which comprises the following steps of: adjusting the total ventilation area of a nozzle throat by adjusting the opening degree of a valve according to the principle that the area of the nozzle throat is inversely proportional to the combustion speed of a propellant, so as to adjust the combustion speed of the propellant; a working mode of the solid attitude and orbit control engine is divided into an energy-saving working mode, a performance working mode and a variable-pressure working mode. According to the requirement of actual working time, any combination and switching of the three working modes are achieved through a control instruction, the working time of the energy-saving working mode, the performance working mode and the variable-pressure working mode can be shortened or prolonged, the working time of the solid attitude and orbit control engine is prolonged, the energy utilization rate of the engine is increased, and the size and weight of the engine are reduced.

Description

Technical Field

[0001] The invention belongs to the field of solid rocket engines, and in particular relates to a method for prolonging the working time of a solid attitude and orbit control engine. Background Art

[0002] The solid attitude and orbit control engine is a power device used for the attitude or orbit control of the aircraft. It uses the combustion gas generated by the solid propellant to directly spray it laterally at a specific position of the missile body according to the overall instructions through the combustion gas control device to obtain the lateral thrust acting on the aircraft, thereby generating maneuvering control force or torque to improve the maneuverability and agility of the aircraft. The solid attitude and orbit control engine can be used to control the attitude and orbit of a variety of aircraft and has the characteristics of simple structure, lightweight, long-term on-orbit storage without leakage, maintenance-free, non-toxic and low smoke, etc. It meets the combat requirements of the "insensitive ammunition" platform and can also meet the requirements of strategic duty.

[0003] At present, the thrust output of solid attitude and orbit control engines in the working range is almost constant, so the engine working time is approximately fixed. However, under the constraints of weight, volume, and working time, the existing working method of solid attitude and orbit control engines cannot meet the time requirements of use. Summary of the invention

[0004] In order to solve the problem that the working time of solid attitude and orbit control engines is fixed and cannot meet the time requirements of use, the present invention provides a method for extending the working time of solid attitude and orbit control engines. The specific technical solution is as follows:

[0005] A method for extending the working time of a solid attitude and orbit control engine, according to the principle that the nozzle throat area is inversely proportional to the propellant burning rate, by adjusting the size of the valve opening to adjust the total ventilation area of ​​the nozzle throat, thereby adjusting the size of the propellant burning rate, and dividing the solid attitude and orbit control engine working mode into an energy-saving working mode, a performance working mode and a variable pressure working mode;

[0006] The energy-saving working mode is to increase the valve opening of the solid attitude and orbit control engine, increase the total ventilation area of ​​the nozzle throat, make the valves of all nozzles at the maximum opening, make the total ventilation area of ​​the nozzle throat maximum, thereby reducing the pressure of the combustion chamber, reducing the propellant burning rate, achieving engine idling operation, reducing propellant consumption, and extending the engine working time;

[0007] The performance working mode is: relative to the energy-saving mode, the valve opening is reduced, multi-valve proportional adjustment is adopted, the total ventilation area of ​​the nozzle throat remains unchanged, the total valve opening of all nozzles is the maximum opening of any nozzle, the combustion chamber pressure is higher, the propellant burning rate is higher, and the maximum thrust output of the valve is achieved;

[0008] The variable pressure working mode is: the total valve opening and the opening requirement range less than or equal to the number of valves are adjusted by one opening value, multiple opening values ​​or continuous opening values, so that the total ventilation area of ​​the nozzle throat changes accordingly, and the combustion chamber pressure changes accordingly, so as to realize the variable thrust output of the valve;

[0009] Furthermore, the total valve opening is between the maximum opening of any nozzle and the sum of the openings of all valves;

[0010] Further, the working mode is one, two or three of an energy-saving working mode, a performance working mode and a variable pressure working mode;

[0011] Furthermore, the working mode of the solid attitude and orbit control engine can realize arbitrary switching of multiple working modes through control instructions according to the requirements of actual working time, and can shorten or extend the working time of energy-saving working mode, performance working mode and variable pressure working mode;

[0012] Furthermore, the sum of the engine operating time of the energy-saving working mode, the performance working mode and the variable pressure working mode is greater than or equal to the working time of the performance working mode, and the working time of the solid attitude and orbit control engine is extended. Furthermore, the specific value of the extension of the working time of the solid attitude and orbit control engine can be adjusted according to the use requirements to shorten or extend the working time of the energy-saving working mode, the performance working mode and the variable pressure working mode.

[0013] Compared with the prior art, the present invention has the following beneficial effects:

[0014] (1) The method of the present invention can adjust the working time of the solid attitude and orbit control engine according to actual needs, by increasing the valve opening, increasing the total ventilation area of ​​the nozzle throat, reducing the combustion chamber pressure, reducing the propellant burning rate, achieving engine idling, reducing propellant consumption, extending the engine working time, and solving the problem of fixed working time of the solid attitude and orbit control engine.

[0015] (2) The method of the present invention can extend the working time of a solid attitude and orbit control engine and can be applied in engineering to extend the working time of a solid attitude and orbit control engine, increase the working time of an aircraft, improve the energy utilization rate of the engine, and reduce the size and weight of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the embodiments of the present 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 some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0017] Figure 1 A schematic flow chart of a method for extending the working time of a solid attitude and orbit control engine provided by an embodiment of the present invention;

[0018] Figure 2 A schematic diagram of an energy-saving working mode of a method for extending the working time of a solid attitude and orbit control engine provided by an embodiment of the present invention;

[0019] Figure 3 A schematic diagram of the performance and working mode of the method for extending the working time of a solid attitude and orbit control engine provided by an embodiment of the present invention;

[0020] Figure 4 A schematic diagram of a transformer operating mode for a method for extending the operating time of a solid attitude and orbit control engine provided in an embodiment of the present invention.

[0021] Reference numerals: 1, No. 1 nozzle; 2, No. 2 nozzle; 3, No. 3 nozzle; 4, No. 4 nozzle; 5, combustion chamber;

[0022] 6. Valve No. 1; 7. Valve No. 2; 8. Valve No. 3; 9. Valve No. 4.

[0023] Specific implementation methods

[0024] The present invention will be further described below in conjunction with the accompanying drawings.

[0025] A method for extending the working time of a solid attitude and orbit control engine, according to the principle that the nozzle throat area is inversely proportional to the propellant burning rate, by adjusting the size of the valve opening to adjust the total ventilation area of ​​the nozzle throat, thereby adjusting the size of the propellant burning rate, and dividing the solid attitude and orbit control engine working mode into an energy-saving working mode, a performance working mode and a variable pressure working mode;

[0026] The energy-saving working mode is to increase the valve opening of the solid attitude and orbit control engine, increase the total ventilation area of ​​the nozzle throat, make the valves of all nozzles at the maximum opening, make the total ventilation area of ​​the nozzle throat maximum, thereby reducing the pressure of the combustion chamber, reducing the propellant burning rate, achieving engine idling operation, reducing propellant consumption, and extending the engine working time;

[0027] The performance working mode is: relative to the energy-saving mode, the valve opening is reduced, multi-valve proportional adjustment is adopted, the total ventilation area of ​​the nozzle throat remains unchanged, the total valve opening of all nozzles is the maximum opening of any nozzle, the combustion chamber pressure is higher, the propellant burning rate is higher, and the maximum thrust output of the valve is achieved;

[0028] The variable pressure working mode is: the total valve opening and the opening requirement range less than or equal to the number of valves are adjusted by one opening value, multiple opening values ​​or continuous opening values, so that the total ventilation area of ​​the nozzle throat changes accordingly, and the combustion chamber pressure changes accordingly, so as to realize the variable thrust output of the valve;

[0029] Furthermore, the total valve opening is between the maximum opening of any nozzle and the sum of the openings of all valves;

[0030] Furthermore, the working mode of the solid attitude and orbit control engine is one, two or three of an energy-saving working mode, a performance working mode and a variable pressure working mode;

[0031] Furthermore, the working mode can realize arbitrary switching of multiple working modes through control instructions according to the requirements of actual working time, and can shorten or extend the working time of energy-saving working mode, performance working mode and variable pressure working mode;

[0032] Furthermore, the sum of the engine operating time of the energy-saving working mode, the performance working mode and the variable pressure working mode is greater than or equal to the working time of the performance working mode, and the working time of the solid attitude and orbit control engine is extended. Furthermore, the specific value of the extension of the working time of the solid attitude and orbit control engine can be adjusted according to the use requirements to shorten or extend the working time of the energy-saving working mode, the performance working mode and the variable pressure working mode.

[0033] The present invention does not limit the number of valves and the arrangement of valves in the solid attitude and orbit control engine. The specific implementation mode of the present invention takes a solid attitude and orbit control engine with four valves as an example.

[0034] like Figure 2 As shown, the No. 1 nozzle 1, the No. 2 nozzle 2, the No. 3 nozzle 3, and the No. 4 nozzle 4 are evenly arranged clockwise around the solid attitude and orbit control engine combustion chamber 5, the No. 1 nozzle 1 and the No. 3 nozzle 3 are located on the y-axis, and the No. 2 nozzle 2 and the No. 4 nozzle 4 are located on the z-axis;

[0035] The No. 1 nozzle 1 is connected to the combustion chamber 5 of the solid attitude and orbit control engine through the No. 1 valve 6, the No. 2 nozzle 2 is connected to the combustion chamber 5 of the solid attitude and orbit control engine through the No. 2 valve 7, the No. 3 nozzle 3 is connected to the combustion chamber 5 of the solid attitude and orbit control engine through the No. 3 valve 8, and the No. 4 nozzle 4 is connected to the combustion chamber 5 of the solid attitude and orbit control engine through the No. 4 valve 9;

[0036] The opening of nozzle No. 1 is controlled by valve No. 1 6, the opening of nozzle No. 2 is controlled by valve No. 2 7, the opening of nozzle No. 3 is controlled by valve No. 3 8, and the opening of nozzle No. 4 is controlled by valve No. 4 9. The four valves are actuated simultaneously, so that the throat areas of the four nozzles change simultaneously.

[0037] The energy-saving working mode is that the four nozzles are all opened to the maximum, so that the nozzle throat area is maximized, such as Figure 2 shown.

[0038] The performance working mode is that the sum of the openings of the four nozzles is the maximum opening of any nozzle, such as Figure 3 shown.

[0039] The variable pressure working mode shown is converted from the sum of the openings of the four nozzles being the maximum opening of any one nozzle to the sum of the openings of the four nozzles being twice the maximum opening of any one nozzle, such as Figure 4 shown.

[0040] According to actual use requirements, multiple working modes can be combined arbitrarily, including a single working mode, a combination of any two working modes, and a combination of three working modes.

[0041] According to the control instructions, a variety of working modes can be switched arbitrarily, which can shorten or extend the working time of energy-saving working mode, performance working mode and variable pressure working mode.

[0042] There is no limitation on the number of valves, valve arrangement, control instructions and engine operating time of the solid attitude and orbit control engine. The operating time of the solid attitude and orbit control engine can be adjusted according to actual needs. By increasing the valve opening, the total ventilation area of ​​the nozzle throat is increased, the pressure in the combustion chamber is reduced, the propellant burning rate is reduced, the engine idling operation is achieved, the propellant consumption is reduced, the engine operating time is extended, and the problem of fixed operating time of the solid attitude and orbit control engine is solved.

[0043] Although the present invention has been disclosed as a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention by using the above disclosed methods and technical contents without departing from the spirit and scope of the present invention. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention. The contents not described in detail in the specification of the present invention belong to the known technology of professional and technical personnel in this field.

Claims

1. A method for extending the working time of a solid attitude and orbit control engine, characterized in that: The method is specifically based on the principle that the nozzle throat area is inversely proportional to the propellant burning rate. By adjusting the size of the valve opening to adjust the total ventilation area of ​​the nozzle throat, the size of the propellant burning rate is further adjusted, and the working mode of the solid attitude and orbit control engine is divided into an energy-saving working mode, a performance working mode and a variable pressure working mode.

2. A method for extending the working time of a solid attitude and orbit control engine according to claim 1, characterized in that: The energy-saving working mode is to increase the valve opening of the solid attitude and trajectory control engine, increase the total ventilation area of ​​the nozzle throat, make the valves of all nozzles at the maximum opening, make the total ventilation area of ​​the nozzle throat maximum, thereby reducing the pressure in the combustion chamber, reducing the propellant burning rate, achieving engine idling operation, reducing propellant consumption, and extending the engine working time.

3. A method for extending the working time of a solid attitude and orbit control engine according to claim 2, characterized in that: The performance working mode is: relative to the energy-saving mode, the valve opening is reduced, and multi-valve proportional adjustment is adopted. The total ventilation area of ​​the nozzle throat remains unchanged, and the sum of the total valve openings of all nozzles is the maximum opening of any nozzle. The combustion chamber pressure is higher, the propellant burning rate is larger, and the maximum thrust output of the valve is achieved.

4. A method for extending the working time of a solid attitude and orbit control engine according to claim 1, characterized in that: The variable pressure working mode is: the total valve opening and an opening value, multiple opening values ​​or continuous opening values ​​within the opening requirement range that is less than or equal to the number of valves are adjusted, so that the total ventilation area of ​​the nozzle throat changes accordingly, and the combustion chamber pressure changes accordingly, thereby realizing the variable thrust output of the valve.

5. A method for extending the working time of a solid attitude and orbit control engine according to claim 4, characterized in that: The total valve opening is between the maximum opening of any nozzle and the sum of the openings of all valves.

6. The method for extending the working time of a solid attitude and orbit control engine according to claim 1, characterized in that: The working mode of the solid attitude and orbit control engine is one, two or three of an energy-saving working mode, a performance working mode and a variable pressure working mode.

7. The method for extending the working time of a solid attitude and orbit control engine according to claim 1, characterized in that: The working mode can realize arbitrary switching of multiple working modes through control instructions according to the requirements of actual working time, and can shorten or extend the working time of energy-saving working mode, performance working mode and variable pressure working mode.

8. The method for extending the working time of a solid attitude and orbit control engine according to claim 1, characterized in that: The sum of the engine operating time of the energy-saving working mode, the performance working mode and the variable pressure working mode is greater than or equal to the working time of the performance working mode, thereby extending the working time of the solid attitude and orbit control engine.

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