A heating system for solid missiles before launch under low temperature conditions

Abstract

A heating system for a solid missile before launch under low-temperature working conditions comprises a navigation insulation layer for wrapping and insulating a navigation system, a warhead insulation layer for wrapping and insulating a warhead, a first microwave heater and a third microwave heater arranged at the upper and lower wall concave cavities of a combustion chamber, and a second microwave heater arranged in the middle flow channel of a solid propellant grain. The three microwave heaters heat the solid propellant grain. The present invention achieves heating and insulation of the solid missile navigation system, warhead and solid propellant grain by using microwave heaters and heating resistors, and uses temperature sensors to collect real-time temperatures of the navigation system, warhead and solid propellant grain. The collected data is transmitted to a control terminal via electrical signals. The control terminal adjusts the output current and microwave power according to working conditions, thereby reducing the impact of the low-temperature environment on the overall performance of the solid missile during launch and ensuring reliable launch and operation of the missile in a low-temperature environment.

Description

Technical Field

[0001] The invention belongs to the technical field of solid missile launch preparation, in particular to a heating system before solid missile launch under low temperature conditions. Background Art

[0002] Solid-fuel missiles are missiles powered by solid propellants. Compared to liquid-propellant missiles, solid-fuel missiles lack complex fuel and oxidizer storage and delivery systems, resulting in simpler structures, smaller size, and lighter weight. Because solid propellants can ignite extremely quickly and generate thrust immediately after ignition, solid-fuel missiles are widely used in scenarios requiring rapid response, such as air defense missiles and short- and medium-range ballistic missiles.

[0003] As the international situation becomes increasingly severe, ensuring that solid-fuel missiles can operate in all regions and weather conditions is crucial for modern military forces to maintain combat readiness and flexibly respond to various combat conditions. This means that missile combat capabilities cannot be limited by weather conditions, and therefore missile systems must be able to operate across a wide temperature range, from extremely cold to extremely high temperatures. Some missiles are deployed in high-latitude or cold regions, where the natural ambient temperature is low. For example, intercontinental ballistic missiles (ICBMs) may be deployed in cold underground silos. Low temperatures can have a significant impact on the solid propellant, electronics, batteries, and structural materials of solid-fuel missiles. Low temperatures not only cause embrittlement and structural damage to the solid propellant grains, but also affect their combustion efficiency and thermal stability. Furthermore, the electronics and batteries within the missile may not function properly at low temperatures, and the missile's structural materials become brittle at low temperatures, affecting the missile's overall structural integrity. However, currently published patents or literature do not address how to address this issue. Summary of the Invention

[0004] In order to overcome the deficiencies of the above-mentioned prior art, the object of the present invention is to provide a heating system for solid missiles before launch under low temperature conditions, which can heat solid missiles under low temperature conditions to ensure that the missiles can be reliably launched and operated in low temperature environments.

[0005] In order to achieve the above object, the technical solution of the present invention is:

[0006] A heating system for a solid missile before launch under low-temperature conditions includes a navigation insulation layer 2 for wrapping and insulating a navigation system 1; a first heating resistor 4 is disposed between the navigation insulation layer 2 and the navigation system 1, and the first heating resistor 4 is connected to a first power supply 5; a first temperature sensor 3 is disposed on the navigation system 1, and the first temperature sensor 3 transmits the temperature of the navigation system 1 to a control terminal 20 via a radio signal, and the control terminal 20 controls the output current of the first power supply 5 via an electrical signal;

[0007] The warhead 7 is also provided with a warhead insulation layer 6 for insulating the warhead 7. A second heating resistor 9 is provided between the warhead insulation layer 6 and the warhead 7. The second heating resistor 9 is connected to a second power supply 11. A second temperature sensor 8 is provided on the warhead 7. The second temperature sensor 8 transmits the temperature of the warhead 7 to a control terminal 20 via a radio signal. The control terminal 20 controls the output current of the second power supply 11 via an electrical signal.

[0008] The combustion chamber further includes a first microwave heater 12 disposed at the concave cavity on the upper wall of the combustion chamber concave cavity 16, and a third microwave heater 14 disposed at the concave cavity on the lower wall of the combustion chamber concave cavity 16. The first microwave heater 12 and the third microwave heater 14 feed microwaves to establish a microwave field to heat the solid propellant grains 17. A second microwave heater 13 is disposed in the middle flow channel of the solid propellant grains 17. The second microwave heater 13 establishes a microwave field in the middle flow channel to heat the solid propellant grains 17. A third temperature sensor 18 is disposed on the surface of the solid propellant grains 17. The third temperature sensor 18 transmits the temperature of the solid propellant grains 17 to a control terminal 20 via a radio signal. The control terminal 20 controls the power of the microwaves output by the first microwave heater 12, the second microwave heater 13, and the third microwave heater 14 via an electrical signal.

[0009] The first microwave heater 12 , the second microwave heater 13 and the third microwave heater 14 have an output power of 0 to 3000 W and a frequency of 915 MHz to 5.8 GHz.

[0010] The resistance of the first heating resistor 4 and the second heating resistor 9 is 50-200 ohms, and the heating power is 500-1500W.

[0011] The first microwave heater 12 , the second microwave heater 13 and the third microwave heater 14 are commercially available industrial microwave heaters that utilize magnetrons to convert electrical energy into microwaves for non-contact heating.

[0012] Compared with the prior art, the present invention has the following beneficial effects:

[0013] 1. The present invention realizes heating and heat preservation of solid missile navigation system, warhead and solid propellant grain through microwave heater and heating resistor, so as to ensure that the missile can be reliably launched and operated in low temperature environment.

[0014] 2. The present invention utilizes temperature sensors to collect the real-time temperatures of the navigation system, warhead, and solid propellant grains. The collected data is transmitted to a control terminal via electrical signals. The control terminal adjusts the output current and microwave power according to the operating conditions, thereby reducing the impact of the low-temperature environment on the overall performance of the solid missile during launch and ensuring reliable launch and operation of the missile in a low-temperature environment.

[0015] In summary, the present invention can heat and monitor various parts of a solid missile under low-temperature conditions and adjust the heating power as needed to ensure that the missile can be reliably launched and operated in a low-temperature environment. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a system principle diagram of the present invention.

[0017] In the figure: 1-navigation system, 2-navigation insulation layer, 3-first temperature sensor, 4-first heating resistor, 5-first power supply, 6-warhead insulation layer, 7-warhead, 8-second temperature sensor, 9-second heating resistor, 10-warhead auxiliary equipment, 11-second power supply, 12-first microwave heater, 13-second microwave heater, 14-third microwave heater, 15-air rudder, 16-combustion chamber cavity, 17-solid propellant charge, 18-third temperature sensor, 19-nozzle, 20-control terminal. DETAILED DESCRIPTION

[0018] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments, but the present invention is not limited to the following embodiments.

[0019] Reference Figure 1 A heating system for a solid missile before launch under low-temperature conditions is characterized by: comprising a navigation insulation layer 2 for wrapping and insulating a navigation system 1; a first heating resistor 4 disposed between the navigation insulation layer 2 and the navigation system 1; the first heating resistor 4 being connected to a first power source 5 and heating the navigation system 1 by converting electrical energy from the first power source 5 into thermal energy; a first temperature sensor 3 disposed on the navigation system 1 for monitoring the temperature of the navigation system 1; the first temperature sensor 3 transmitting the temperature of the navigation system 1 to a control terminal 20 via a radio signal; and the control terminal 20 controlling the output current of the first power source 5 via an electrical signal to achieve control of the heating temperature.

[0020] The device further includes a warhead insulation layer 6 for wrapping and insulating the warhead 7, a second heating resistor 9 being disposed between the warhead insulation layer 6 and the warhead 7, the second heating resistor 9 being connected to a second power source 11. The heat generated by the second power source 11 itself is used to heat the warhead auxiliary equipment 10, and the warhead 7 is heated by converting the electrical energy of the second power source 11 into thermal energy. The warhead 7 is provided with a second temperature sensor 8 for monitoring the temperature of the warhead 7. The second temperature sensor 8 transmits the temperature of the warhead 7 to a control terminal 20 via a radio signal. The control terminal 20 controls the output current of the second power source 11 via an electrical signal to achieve control of the heating temperature.

[0021] Since the solid engine of the solid missile is composed of a combustion chamber cavity 16, a solid propellant grain 17, a third temperature sensor 18 and a nozzle 19; the combustion chamber cavity 16 is divided into an upper wall cavity and a lower wall cavity, and the solid propellant grain 17 adopts a side-burning distribution; therefore, it also includes a first microwave heater 12 arranged at the upper wall cavity of the combustion chamber cavity 16, and a third microwave heater 14 arranged at the lower wall cavity of the combustion chamber cavity 16. The first microwave heater 12 and the third microwave heater 14 feed microwaves to establish a microwave field to heat the solid propellant grain 17. Heating: A second microwave heater 13 is provided in the middle flow channel of the solid propellant grain 17. The second microwave heater 13 establishes a microwave field in the middle flow channel to heat the solid propellant grain 17. A third temperature sensor 18 is provided on the surface of the solid propellant grain 17. The third temperature sensor 18 transmits the temperature of the solid propellant grain 17 to a control terminal 20 via a radio signal. The control terminal 20 controls the power of the microwave output by the first microwave heater 12, the second microwave heater 13, and the third microwave heater 14 via an electrical signal to achieve control of the heating temperature.

[0022] The first heating resistor 4, first power supply 5, second heating resistor 9, second power supply 11, first microwave heater 12, second microwave heater 13, and third microwave heater 14 are selected according to the required operating conditions. The output power of the first microwave heater 12, second microwave heater 13, and third microwave heater 14 is 0-3000W and the frequency is 3.45GHz. The resistance of the first heating resistor 4 and second heating resistor 9 is 50-200 ohms, which is adjustable, and the heating power is 500-1500W.

[0023] The first microwave heater 12, the second microwave heater 13 and the third microwave heater 14 are commercially available microwave heaters, each consisting of a microwave power supply, a magnetron and a waveguide. The magnetron is used to convert electrical energy into microwaves for non-contact heating. The waveguide outlet is embedded in the combustion chamber wall and sealed with high-temperature glass, for example, the brand is: muegge, model: MB2658A-110EA.

[0024] The specific structures and components of the combustion chamber cavity 16, solid propellant charge 17, and nozzle 19 can be modified according to the required working conditions.

[0025] The working principle of the present invention is:

[0026] The solid missile is in a low temperature environment. After receiving the missile launch preparation instruction, the parameters required for heating, such as heating power, heating time, etc., are calculated based on the temperature data collected by the first temperature sensor 3, the second temperature sensor 8 and the third temperature sensor 18. Then the control terminal 20 transmits the calculated power parameters to the first power supply 5, the second power supply 11, the first microwave heater 12, the second microwave heater 13 and the third microwave heater 14. Subsequently, the first heating resistor 4, the second heating resistor 9, the first microwave heater 12, the second microwave heater 13 and the third microwave heater 14 enter the working state, converting electrical energy into heat energy and Microwave energy heats the navigation system 1, warhead 7 and solid propellant grain 17 respectively. During the heating process, the real-time temperatures of the navigation system 1, warhead 7 and solid propellant grain 17 are collected by the first temperature sensor 3, the second temperature sensor 8 and the third temperature sensor 18 and transmitted back to the control terminal 20 in the form of electrical signals. When the temperatures of the navigation system 1, warhead 7 and solid propellant grain 17 reach the set heating temperature, the control terminal 20 issues an instruction to turn off the first power supply 5, the second power supply 11, the first microwave heater 12, the second microwave heater 13 and the third microwave heater 14. The heating is completed and the missile enters the pre-launch state.

[0027] The above description is only a preferred embodiment of the present invention and does not limit the patent scope of the present invention. Any equivalent structure or equivalent process transformation made by using the contents of the present invention description and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present invention.

Claims

1. A heating system for solid missiles before launch under low temperature conditions, characterized by: The invention comprises a navigation insulation layer (2) for wrapping and insulating a navigation system (1); a first heating resistor (4) is arranged between the navigation insulation layer (2) and the navigation system (1); the first heating resistor (4) is connected to a first power supply (5); a first temperature sensor (3) is arranged on the navigation system (1); the first temperature sensor (3) transmits the temperature of the navigation system (1) to a control terminal (20) via a radio signal; and the control terminal (20) controls the output current of the first power supply (5) via an electrical signal; The invention also includes a warhead insulation layer (6) for wrapping and insulating the warhead (7), a second heating resistor (9) is provided between the warhead insulation layer (6) and the warhead (7), the second heating resistor (9) is connected to a second power supply (11), a second temperature sensor (8) is provided on the warhead (7), and the second temperature sensor (8) transmits the temperature of the warhead (7) to a control terminal (20) via a radio signal; the control terminal (20) controls the output current of the second power supply (11) via an electrical signal; The invention also includes a first microwave heater (12) arranged at the concave cavity of the upper wall of the combustion chamber concave cavity (16), and a third microwave heater (14) arranged at the concave cavity of the lower wall of the combustion chamber concave cavity (16). The first microwave heater (12) and the third microwave heater (14) feed microwaves to establish a microwave field to heat the solid propellant grain (17); a second microwave heater (13) is arranged in the middle flow channel of the solid propellant grain (17), and the second microwave heater (13) establishes a microwave field in the middle flow channel to heat the solid propellant grain (17); a third temperature sensor (18) is arranged on the surface of the solid propellant grain (17), and the third temperature sensor (18) transmits the temperature of the solid propellant grain (17) to a control terminal (20) through a radio signal; and the control terminal (20) controls the power of the microwaves output by the first microwave heater (12), the second microwave heater (13) and the third microwave heater (14) through an electrical signal.

2. The heating system for solid missiles before launch under low temperature conditions according to claim 1, characterized in that: The resistance of the first heating resistor (4) and the second heating resistor (9) is 50 to 200 ohms, and the heating power is 500 to 1500W.

3. The heating system for solid missiles before launch under low temperature conditions according to claim 1, characterized in that: The output power of the first microwave heater (12), the second microwave heater (13) and the third microwave heater (14) is 0 to 3000W, and the frequency is 915MHz to 5.8GHz.

4. The heating system for solid missiles before launch under low temperature conditions according to claim 1, characterized in that: The first microwave heater (12), the second microwave heater (13) and the third microwave heater (14) are commercially available industrial microwave heaters, which utilize magnetrons to convert electrical energy into microwaves for non-contact heating.

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