Heating system before solid missile launching under low-temperature working condition

Abstract

A heating system used before solid missile launching under the low-temperature working condition comprises a navigation heat preservation layer wrapping a navigation system for heat preservation, a warhead heat preservation layer wrapping a warhead for heat preservation, a first microwave heater and a third microwave heater, a second microwave heater is arranged in a middle runner of the solid propellant grain, and the solid propellant grain is heated by the three microwave heaters; heating and heat preservation of the solid missile navigation system, the warhead and the solid propellant grain are achieved through the microwave heater and the heating resistor, the temperature sensors are used for collecting the real-time temperature of the navigation system, the warhead and the solid propellant grain, and collected data are transmitted to the control terminal through electric signals. And the control terminal adjusts the output current and the microwave power according to working condition requirements, so that the influence of the low-temperature environment on the overall performance of the solid missile during launching is reduced, and reliable launching and operation of the missile in the low-temperature environment are ensured.

Description

Technical Field

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

[0002] A solid missile is a missile that uses solid propellant as a power source. Compared with liquid propellant missiles, the propulsion system of solid missiles does not have a complex fuel and oxidizer storage and delivery system, so the structure is simpler, the volume is smaller, and the weight is lighter. Since solid propellant can be ignited in a very short time and generate thrust immediately after ignition, solid missiles are widely used in scenarios that require rapid response, such as air defense missiles, short-range and medium-range ballistic missiles, etc.

[0003] As the international situation becomes increasingly severe, ensuring that solid missiles can operate in all regions and all weather conditions is an important guarantee for modern military forces to maintain combat readiness and flexibly respond to various combat conditions. That is, the combat capability of missiles cannot be limited by weather conditions, so missile systems must be able to operate in a wide range of temperatures from extreme cold to high temperatures. Some missiles need to be deployed in high-latitude or cold areas where the natural environment temperature is low. For example, intercontinental ballistic missiles (ICBMs) may be deployed in cold underground silos. The low temperature environment will have a huge impact on the solid propellant, electronic equipment, batteries and structural materials of solid missiles. Low temperature will not only cause the solid propellant grain to become embrittled and destroy its structure, but also affect its combustion efficiency and thermal stability. At the same time, the electronic equipment and batteries inside the missile may not work properly at low temperatures, and the structural materials of the missile will become fragile at low temperatures, affecting the overall structural integrity of the missile. However, there is no mention of how to solve this problem in the currently disclosed patents or documents. 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 before launching a solid missile under low temperature conditions, which can heat the solid missile under low temperature conditions to ensure that the missile can be reliably launched and operated in a low temperature environment.

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

[0006] A heating system before launching a solid missile under low temperature conditions, comprising 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 source 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 through a radio signal, and the control terminal 20 controls the output current of the first power source 5 through an electrical signal;

[0007] The warhead 7 is also provided with a warhead heat-insulating layer 6 for heat-insulating the warhead 7, a second heating resistor 9 is arranged between the warhead heat-insulating layer 6 and the warhead 7, the second heating resistor 9 is connected to a second power source 11, a second temperature sensor 8 is arranged on the warhead 7, and the second temperature sensor 8 transmits the temperature of the warhead 7 to a control terminal 20 through a radio signal; the control terminal 20 controls the output current of the second power source 11 through an electrical signal;

[0008] 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. 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. The third temperature sensor 18 transmits the temperature of the solid propellant grain 17 to the control terminal 20 through 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 through an electrical signal.

[0009] The output power of the first microwave heater 12, the second microwave heater 13 and the third microwave heater 14 is 0-3000w, and the frequency is 915MHz-5.8GHz.

[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, which 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 the control terminal via electrical signals. The control terminal adjusts the output current and microwave power according to the working conditions, thereby reducing the impact of the low temperature environment on the overall performance of the solid missile during launch, and ensuring that the missile can be reliably launched and operated 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 in conjunction with the accompanying drawings and specific implementation methods, but the present invention is not limited to the following embodiments.

[0019] Reference Figure 1 , a heating system before launching a solid missile under low temperature conditions, characterized in that: it includes 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, and the first heating resistor 4 is connected to a first power source 5, and the navigation system 1 is heated by converting the electric energy of the first power source 5 into heat energy; a first temperature sensor 3 is arranged on the navigation system 1, and the temperature of the navigation system 1 is monitored by the first temperature sensor 3, and the first temperature sensor 3 transmits the temperature of the navigation system 1 to a control terminal 20 through a radio signal, and the control terminal 20 controls the output current of the first power source 5 through an electrical signal to achieve control of the heating temperature;

[0020] The warhead 7 is also provided with a warhead insulation layer 6 for heat preservation, a second heating resistor 9 is arranged between the warhead insulation layer 6 and the warhead 7, the second heating resistor 9 is 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; a second temperature sensor 8 is arranged on the warhead 7, and the temperature of the warhead 7 is monitored by the second temperature sensor 8; the second temperature sensor 8 transmits the temperature of the warhead 7 to the control terminal 20 through a radio signal; the control terminal 20 controls the output current of the second power source 11 through an electrical signal to achieve the 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 combustion 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 arranged 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 arranged on the surface of the solid propellant grain 17, the third temperature sensor 18 transmits the temperature of the solid propellant grain 17 to the control terminal 20 through 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 through an electrical signal to achieve control of the heating temperature.

[0022] The first heating resistor 4, the first power supply 5, the second heating resistor 9, the second power supply 11, the first microwave heater 12, the second microwave heater 13 and the third microwave heater 14 are selected according to the required working conditions. The output power of the first microwave heater 12, the second microwave heater 13 and the third microwave heater 14 is 0-3000w, and the frequency is 3.45GHz; the resistance of the first heating resistor 4 and the second heating resistor 9 is 50-200 ohms, which can be adjusted, 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, and the model is MB2658A-110EA.

[0024] The specific structures and components of the combustion chamber cavity 16, the solid propellant charge 17, and the 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 to convert electrical energy into heat energy and The microwave energy heats the navigation system 1, the warhead 7 and the solid propellant grain 17 respectively. During the heating process, the real-time temperatures of the navigation system 1, the warhead 7 and the 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, the warhead 7 and the 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 a 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 specification 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 in that: The navigation system (1) comprises a navigation insulation layer (2) for wrapping and insulating the 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 source (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 source (5) via an electrical signal; It also includes a warhead insulation layer (6) for wrapping and insulating the warhead (7), a second heating resistor (9) is arranged between the warhead insulation layer (6) and the warhead (7), the second heating resistor (9) is connected to a second power source (11), a second temperature sensor (8) is arranged on the warhead (7), and the second temperature sensor (8) transmits the temperature of the warhead (7) to a control terminal (20) through a radio signal; the control terminal (20) controls the output current of the second power source (11) through an electrical signal; The invention also comprises 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). 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). The third temperature sensor (18) transmits the temperature of the solid propellant grain (17) to a control terminal (20) through 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) through an electrical signal.

2. A 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 1500 W.

3. The heating system for solid missile before launching under low temperature conditions according to claim 1 is 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 3000 W, and the frequency is 915 MHz to 5.8 GHz.

4. The heating system for solid missile before launching under low temperature conditions according to claim 1 is 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.

Images