KR20200072015A - Solid fuel rocket - Google Patents

Abstract

A solid fuel rocket comprises a nose cone, a control member, an engine member, and a case. The control member includes a division unit, a parachute ejection device, and a control device. The division unit forms a boundary with the nose cone and is divided to be detached from the nose cone to form an ejection space. The parachute ejection device includes: an ejection trigger to release stress stored by a spring after reaching a prescribed height; an ejection control unit to control the ejection trigger by an ejection signal; a parachute storage unit to eject a parachute mounted in a parachute storage space to the outside through the ejection space; and an ejection unit to transfer the stress released by the ejection trigger to the parachute storage unit to push and lift the parachute storage unit upwards. The control device responds to a control signal to output the ejection signal and an engine control signal. The engine member includes solid fuel, a nozzle unit, and an insulation unit. The nozzle unit includes a nozzle base having a nozzle neck with a narrow inlet and a structure becoming wider towards the front and back, and a mortar coating layer being arranged on the surface of the nozzle base to protect the nozzle base and comprising 14-16 wt% of rapid-hardening high-strength cement mortar to convert high-temperature high-pressure gas created by combusting the solid fuel into kinetic energy.

Description

Solid fuel rocket {SOLID FUEL ROCKET}

The present invention relates to a solid fuel rocket, and more particularly, to a solid fuel rocket including a nozzle using a super-fast high-strength high-strength mortar.

The rocket consists of a propulsive fuel, a fuel tank that stores it, and a nozzle. In addition, it may further include components such as a direction stabilizer, wings.

Solid fuel rockets are used for experimental, research, or leisure purposes because they can produce strong propulsion and have a simple structure and miniaturization. However, once burned, it cannot be stopped in the middle, and it is not easy to control and high temperature and high pressure are generated in the combustion process, so high strength, heat resistance, and durability of the rocket body are required.

Unlike space development or military rockets, rockets are reused several times for cost savings in experimental, research, or leisure rockets.

When the rocket is reused, the external material is weak and can be destroyed in the launching process, and the size of the engine part does not match the size of the fuselage, so there is a problem that the center must be centered just before launch. If the rocket is centered just before launch, it is difficult to accurately center it, and the rocket's orbit may be distorted. To solve this problem, a nozzle was conventionally manufactured using carbon or the like, but the conventional nozzle is difficult to withstand thrust of 100 N or more, and there is a problem in that the nozzle neck is expanded due to shrinkage and cracking of the nozzle portion after the thrust test. When the nozzle neck is extended, the exact thrust of the rocket cannot be generated, so the thrust force of the rocket is reduced. If the nozzle part is worn or damaged, the rocket cannot be reused.

In addition, a device for recovering a used rocket, such as a parachute, may be broken and the rocket may be destroyed.

Accordingly, the technical problem of the present invention was conceived in this regard, and an object of the present invention relates to a solid fuel rocket including a nozzle using a super-fast high-strength mortar.

A solid fuel rocket according to an embodiment for realizing the object of the present invention includes a nose cone, a control material, an engine member, and a case. The nose cone is formed in a streamlined shape to separate the air during propulsion. The control material includes a division unit, a parachute injection device, and a control device. The dividing portion forms a boundary with the nose cone and is split so as to be detachable from the nose cone to form an injection space. The parachute injection device is an injection trigger that releases stress stored by a spring after reaching a predetermined altitude, an injection control unit that controls the injection trigger by an injection signal, and a parachute mounted in a parachute storage space through the injection space. It includes a parachute storage unit for injection to the outside, and an injection unit for transmitting the stress released by the injection trigger to the parachute storage unit and pushing the parachute storage unit upward. The control device outputs the injection signal and the engine control signal in response to the control signal. The engine member includes a solid fuel, a nozzle portion, and an insulating portion. The solid fuel contains solid fuel and oxidant and is ignited by the engine control signal. The nozzle portion is a nozzle base having a structure that is widened in the front and rear directions with a nozzle neck at a narrow entrance, and a mortar coating layer comprising 14 to 16% by weight of ultra-high-speed high-strength cement mortar disposed on the surface of the nozzle base to protect the nozzle base. Including the high-temperature and high-pressure gas generated by burning the solid fuel is converted to kinetic energy. The heat insulation portion surrounds the solid fuel to prevent heat generated while the solid fuel is being burned from being transferred to the outside. The case covers the outer shape of the rest of the part except for the nose cone, but the nozzle part is opened.

In one embodiment, after the combustion of the solid fuel rocket, the used mortar coating layer on the nozzle base may be removed, a new mortar coating layer may be formed, and the solid fuel may be re-injected to be reused.

In one embodiment, in the nozzle base, the area of the nozzle neck and the area of the extension portion at the outlet side may satisfy [Equation 1] below.

[Equation 1]

(A _C is the area of the nozzle neck, A _e is the area of the extension on the outlet side, P _e is the nozzle pressure on the outlet side, P ₀ is the stagnant pressure inside the combustion chamber, and k is the insulation ratio, KNSB published on Nakka-Rocketry's website. Value)

In one embodiment, the mortar coating layer may be disposed on a portion of the nozzle base surface adjacent to the nozzle neck.

In one embodiment, the fuel comprises any one or more powders selected from the group comprising metal aluminum powder and magnesium powder, the oxidizing agent is ammonium perchlorate (NH ₄ ClO ₄ ), ammonium nitrate (NH ₄ NO ₃ ), It may include one or more substances selected from the group consisting of potassium nitrate, and sorbitol.

According to the embodiment of the present invention, the solid fuel rocket can withstand a strong thrust of 100 N or more, and the nozzle neck is prevented from expanding because the nozzle does not shrink or crack during the thrust test.

In addition, the engine member is made to precisely match the control material, so that it can easily hold the center of the rocket.

In addition, the reliability of the parachute injection device is improved, so it is easy to recover the rocket after use.

In addition, the nozzle portion can be reused, thereby saving cost.

In addition, the nozzle part can be molded into a desired shape in a short time by including a mortar coating layer containing super-high-speed high-strength cement, and the required fluidity is secured even with a small amount of water, and there is no bleeding phenomenon, and workability is excellent. This has the advantage of being minimized and less affected by the weather.

In addition, a mortar coating layer containing a high-speed, high-strength cement can protect the nozzle base, thereby forming a nozzle base with heat-resistant PVC pipe. Thus, the weight of the solid fuel rocket is reduced and the risk of fire is reduced.

1 is a cross-sectional view showing a solid fuel rocket according to an embodiment of the present invention.
2 and 3 are perspective views showing the parachute injection device shown in FIG. 1.
4 is a cross-sectional view showing a nozzle portion of the engine member shown in FIG. 2.
5 and 6 are images showing the nozzle base shown in FIG.
FIG. 7 is a front view showing the nozzle unit shown in FIG. 4.
FIG. 8 is an image showing the results of using the nozzle unit shown in FIG. 7 in an actual propulsion test.
9 is an image showing a state in which the nozzle unit shown in FIG. 8 is cleaned.
10 is a front view showing a nozzle unit according to another embodiment of the present invention.
FIG. 11 is an image showing the results of using the nozzle unit shown in FIG. 10 in an actual propulsion test.
12 is a graph showing the results of the launch test of the solid fuel rocket shown in FIG. 1.
13 is a graph showing the results of repeated tests of the solid fuel rocket shown in FIG. 1.

The present invention can be applied to various changes and can have various forms, and the embodiments are described in detail in the text. However, this is not intended to limit the present invention to a specific disclosure form, and it should be understood as including all modifications, equivalents, and substitutes included in the spirit and scope of the present invention. In describing each drawing, similar reference numerals are used for similar components. Terms such as first and second may be used to describe various components, but the components should not be limited by the terms. The terms are for the purpose of distinguishing one component from other components. Only used. The terms used in the present application are only used to describe specific embodiments, and are not intended to limit the present invention. Singular expressions include plural expressions unless the context clearly indicates otherwise. In this application, terms such as “comprise” or “consist of” are intended to indicate that a feature, number, step, operation, component, part, or combination thereof described in the specification exists, and that one or more other features are present. It should be understood that the existence or addition possibilities of fields or numbers, steps, actions, components, parts or combinations thereof are not excluded in advance.

Unless otherwise defined, all terms used herein, including technical or scientific terms, have the same meaning as commonly understood by a person skilled in the art to which the present invention pertains. Terms, such as those defined in a commonly used dictionary, should be interpreted as having meanings consistent with meanings in the context of related technologies, and should not be interpreted as ideal or excessively formal meanings unless explicitly defined in the present application. Does not.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings.

1 is a cross-sectional view showing a solid fuel rocket according to an embodiment of the present invention.

Referring to FIG. 1, the solid fuel rocket includes a nose cone 100, a control material 200, and an engine member 300.

The nose cone 100 constitutes an upper portion of the solid fuel rocket, and includes a head portion 110 for separating air when the solid fuel rocket is propelled, and a gyro sensor 120 that senses the attitude of the solid fuel rocket.

The head portion 110 includes a material having high heat resistance and strength while being light in weight. For example, the head unit 110 may include duralumin, titanium alloy, nickel alloy, stainless steel, copper alloy, and the like. In another embodiment, a ceramic layer may be further formed on the outer surface of the head portion 110.

The gyro sensor 120 senses the acceleration due to the propulsion of the solid fuel rocket, and controls the posture of the rocket. For example, the gyro sensor 120 may include a gyro acceleration sensor.

The nose cone 100 is coupled detachably to the upper portion of the control material 200. In this embodiment, the nose cone 100 is coupled so as to be removable through the control material 200 and the divided portion 201. The nose cone 100 is detachable from the control material 200, but is not completely separated. In this embodiment, a part of the nose cone 100 and the control material 200 is split through the partition 201 to form an injection space (not shown), and a parachute (not shown) through the injection space (not shown). Is not injected).

The control material 200 constitutes a central portion of the solid fuel rocket, and includes a parachute injection device 210 and a control device 220.

The parachute injection device 210, after the fuel inside the engine member 300 is exhausted and the solid fuel rocket reaches a predetermined altitude, part of the nose cone 100 and the control material 200 through the partition 201 It is opened and a parachute (not shown) is injected through the opened injection space (not shown).

2 and 3 are perspective views showing the parachute injection device shown in FIG. 1.

1 to 3, the parachute injection device 210 includes a fixed plate 211, a fixed frame 212, an injection control unit 213, an injection trigger 214, an injection unit 215, and a parachute storage unit ( 217), and a spring 219.

The fixing plate 211 is coupled to the case 400 of the solid fuel rocket, and fixes the position of the parachute injection device 210 inside the solid fuel rocket.

The fixed frame 212 is coupled to the fixed plate 211 and is configured in a frame shape to include an injection space therein.

The injection control unit 213 operates the injection trigger 214 under the control of the control device 220.

The injection trigger 214 transmits the stress stored by the spring 219 to the injection unit 215.

The injection unit 215 pushes the parachute storage unit 217 upwards due to the stress stored by the spring 219.

When the parachute storage unit 217 is pushed upward, the division unit 201 is separated to form an injection space (not shown) between the nose cone 100 and the control member 200.

The parachute (not shown) mounted in the parachute storage space 217a of the parachute storage unit 217 is injected to the outside through the injection space (not shown) so that the solid fuel rocket gradually falls.

The control device 220 controls the overall operation of the solid fuel rocket. In this embodiment, the control device 220 includes a GPS device (not shown), an altimeter (not shown), a wireless communication module (not shown), an energy control circuit (not shown), and a parachute control circuit (not shown) Not included).

The GPS device (not shown) detects the position of the solid fuel rocket using a signal received from a satellite.

The altimeter (not shown) measures the altitude of the solid fuel rocket. For example, an altimeter (not shown) includes a pressure sensor, and measures the altitude of the solid fuel rocket according to the pressure difference from the ground.

The wireless communication module (not shown) controls the acceleration signal from the gyro sensor 120, the position signal from the GPS device (not shown), and the altitude signal from the altimeter (not shown) on the ground control system ( It is transmitted to a not shown), and controls the parachute control circuit (not shown), the engine member 300, etc. in response to the control signal received from the ground control system (not shown).

The engine control circuit (not shown) controls driving of the engine member 300 using a control signal applied from a wireless communication module (not shown).

The parachute control circuit (not shown) is based on whether the control signal received from the wireless communication module (not shown) or the altitude signal received from the altimeter (not shown) has reached a predetermined altitude value. ) To control the injection trigger 214.

In another embodiment, the wireless communication module (not shown) only transmits the measured signal to the ground control system (not shown), and the control device 220 is configured to parachute injection device 210 according to a preset control value. ) And the engine member 300 may be controlled.

The engine member 300 provides the driving force of the solid fuel rocket, and includes a solid fuel 310, a nozzle unit 320, and an insulating unit 330.

The solid fuel 310 is manufactured by mixing fuel and an oxidizing agent in a solid form. In this embodiment, metal aluminum powder and magnesium powder, or a mixed powder thereof are used as the fuel, and oxidizing agent is ammonium perchlorate (NH ₄ ClO ₄ ), ammonium nitrate (NH ₄ NO ₃ ), potassium nitrate, sorbitol or Combinations of these can be used. For example, the solid fuel 310 may further include a polymer material that is a binder.

4 is a cross-sectional view showing a nozzle portion of the engine member shown in FIG. 2, FIGS. 5 and 6 are images showing the nozzle base shown in FIG. 4, and FIG. 7 is a front view showing the nozzle portion shown in FIG.

1 to 7, the nozzle unit 320 converts high-temperature and high-pressure gas generated by burning the solid fuel 310 into kinetic energy. The nozzle part 320 includes a nozzle base 321 and a mortar coating layer 323.

The nozzle base 321 has a narrow inlet so that gases of high temperature and high pressure are uniformly discharged, and has a structure that widens toward the front-rear direction.

In this embodiment, the nozzle base 321 may include aluminum alloy (or duralumin), titanium alloy, nickel alloy, stainless steel, copper alloy, synthetic resin, and the like.

The nozzle base 321 includes a shrink-expansion-type nozzle, and the diameter of the nozzle neck and the diameter of the outlet-side expansion portion can be adjusted by [Equation 1] below.

[Equation 1]

In [Equation 1], A _C is the area of the nozzle neck, A _e is the area of the outlet extension, P _e is the nozzle pressure at the outlet, P ₀ is the stagnation pressure inside the combustion chamber, and k is the adiabatic ratio of Nakka-Rocketry. Shows the KNSB value published on the homepage.

The mortar coating layer 323 is disposed on the surface of the nozzle base 321 to protect the nozzle base 321. In this embodiment, the mortar coating layer 323 includes a super-fast diameter high-strength cement. For example, the ultra-high-speed high-strength cement used in the mortar coating layer 323 is produced by adding anhydrite to the clinker produced by adding bauxite, kaolin, and formation to a general cement raw material. Those skilled in the art will appreciate that the mortar coating layer 323 can be made of high-speed, high-strength cement that is commonly used.

In the present embodiment, the mortar coating layer 323 includes mortar containing 14 to 17% by weight of ultra-fast high-strength cement, has a thickness of 5 to 100 mm, and has a specific gravity of 2.1 to 2.4.

The mortar coating layer 323 containing super-high-speed high-strength cement can be molded into a desired shape in a shorter time than ordinary cement, and the required fluidity is secured even with a small amount of water, and there is no bleeding effect, so workability is excellent and shrinkage It has the advantage of minimizing overgrowth and being less affected by the weather.

The nozzle base 321 having a shape as shown in [Equation 1] has an advantage of preventing expansion or contraction and cracking of the nozzle neck when the mortar coating layer 323 including super-hard high-strength cement is added.

FIG. 8 is an image showing the results of using the nozzle unit shown in FIG. 7 in an actual propulsion test.

1 to 8, the actual propulsion test result shows that the surface of the mortar coating layer 323b is blackened without any deformation in the nozzle base 321. In this embodiment, although the surface of the mortar coating layer 323b is tanned, there is no deformation of the nozzle base 321, and the nozzle neck maintains reliability without any deformation.

9 is an image showing a state in which the nozzle unit shown in FIG. 8 is cleaned.

1 to 9, the blackened mortar coating layer 323 was washed and removed to reuse the nozzle unit 320. Thereafter, an additional mortar coating layer 323 is formed on the inner surface of the nozzle base 321 to continue the experiment.

The thermal insulation unit 330 surrounds the solid fuel 310 to protect the case 400 and the control material 200 from heat generated when the solid fuel 310 is burned. In this embodiment, the heat insulating portion 330 may include an elastic rubber, a thermosetting plastic, and the like.

The insulating portion 330 prevents thermal deformation of the case 400, prevents chemical substances inside the solid fuel 310 from moving or spreading outside, and generates pressure during combustion of the solid fuel 310. It prevents the loss to the outside, and guides the pressure by combustion of the solid fuel 310 to be concentrated toward the nozzle unit 320.

The case 400 constitutes the outer shape of the rest of the solid fuel rocket excluding the nose cone 100, and may include synthetic resins such as duralumin, titanium alloy, nickel alloy, stainless steel, copper alloy, and PVC.

In this embodiment, the solid fuel rocket may further include an igniter (not shown). The igniter (not shown) is ignited by the control of the control unit 220 to ignite a portion of the solid fuel 310. For example, the igniter (not shown) includes an igniter (not shown), and the igniter (not shown) is B-KNO ₃ , Aluminum/Cupric oxide (A1/CuO), Zirconium/Barium chromate ( Zr-BaCrO ₄ ), Zr-Ni/KCIO ₄ -Ba(NO ₃ ), and the like may be included as a claim drug.

According to the present embodiment as described above, the solid fuel rocket can withstand a strong thrust of 100 N or more, and the nozzle neck is prevented from expanding because the nozzle does not shrink or crack during thrust testing.

In addition, the engine member 300 is manufactured to precisely match the control member 200 so that the center of the rocket can be easily grasped.

In addition, the reliability of the parachute injection device 210 is improved, and recovery of the rocket after use is easy.

In addition, since the nozzle unit 320 can be reused, cost is saved.

In addition, the nozzle part 320 can be molded into a desired shape in a short time, including a mortar coating layer 323 containing super-high-speed high-strength cement, and required fluidity is secured even with a small amount of water, and there is no bleeding phenomenon. It has the advantage of being excellent, minimizing contraction and fungus, and being less affected by weather.

10 is a front view showing a nozzle unit according to another embodiment of the present invention, and FIG. 11 is an image showing the result of using the nozzle unit shown in FIG. 10 in an actual propulsion test.

10, the nozzle base 1321 may include a PVC pipe. PVC pipes are cheaper than metallic materials and do not corrode during storage. In addition, the specific gravity is 1.43, which is only 1/5 of stainless steel and 1/2 of aluminum alloy. It also has a self-extinguishing property that turns itself off even when a spark is blown, so the risk of fire is low.

However, PVC pipe is weak to heat, and can be easily broken or deformed when high heat and high pressure are applied.

In this embodiment, a mortar coating layer 1323 is formed on the inner surface of the nozzle base 1321 to protect the nozzle base 1321. In this embodiment, the mortar coating layer 1323 comprises a super-fast diameter high-strength cement.

In one embodiment, the nozzle neck was designed as ㅨ10 and the nozzle outlet as ㅨ30 and the mold was fabricated by 3D printing. Molding was performed in the nozzle base 1321, which is a PVC pipe, by mixing cement or super-hard high strength mortar with water. The PVC pipe was cut considering the overall length of the nozzle and the extra length of 50 mm to be inserted into the connector. Water was added at 50% by weight of cement and 13 to 15% by weight of high-strength high-strength mortar and mixed while stirring for 3 minutes. Conventional cement takes 1 to 2 days to cure, but the ultra-high-speed high-strength mortar of the present invention took 2 to 3 hours to cure.

Referring to FIG. 11, as a result of the actual propulsion test, the surface of the mortar coating layer 1323b was blackened without any deformation in the nozzle base 1321. In this embodiment, although the surface of the mortar coating layer 1323b is tanned, there is no deformation of the nozzle base 1321, so the nozzle neck maintains reliability without any deformation.

According to the above-described embodiment, the mortar coating layer 1323 comprising super-high-speed high-strength cement can protect the nozzle base 1321 to form a nozzle base 1321 with PVC pipes that are weak to heat. Thus, the weight of the solid fuel rocket is reduced and the risk of fire is reduced.

12 is a graph showing the results of the launch test of the solid fuel rocket shown in FIG. 1. In Fig. 12, the horizontal axis represents time (seconds) and the vertical axis represents altitude (m).

Referring to FIG. 12, as a result of testing and launching the solid fuel rocket, it rose to an altitude of 399 m for 6.7 seconds, the maximum speed was 73.59 m/s, and the maximum acceleration was 55.55 m/s ² .

13 is a graph showing the results of repeated tests of the solid fuel rocket shown in FIG. 1.

13, in the first to fourth repetition experiments, the maximum thrust (N) was 229N, 309N, 202N, and 292N, and the combustion time (s) was 4.5 seconds, 3.5 seconds, 7.1 seconds, and 5.6 seconds. Conventionally, as the number of times the nozzle neck is expanded or worn and the number of reuse of rockets increases, the maximum thrust and the combustion time decrease, but according to the embodiment of the present invention, the maximum number of solid fuel rockets is achieved even if the mortar coating layer is re-formed multiple times. Thrust and burning time did not decrease.

According to the embodiment of the present invention, the solid fuel rocket can withstand a strong thrust of 100 N or more, and the nozzle neck is prevented from expanding because the nozzle does not shrink or crack during the thrust test.

In addition, the engine member is made to precisely match the control material, so that it can easily hold the center of the rocket.

In addition, the reliability of the parachute injection device is improved, so it is easy to recover the rocket after use.

In addition, the nozzle portion can be reused, thereby saving cost.

In addition, the nozzle part can be molded into a desired shape in a short time by including a mortar coating layer containing super-high-speed high-strength cement, and the required fluidity is secured even with a small amount of water, and there is no bleeding phenomenon, and workability is excellent. This has the advantage of being minimized and less affected by the weather.

In addition, a mortar coating layer containing a high-speed, high-strength cement can protect the nozzle base, thereby forming a nozzle base with heat-resistant PVC pipe. Thus, the weight of the solid fuel rocket is reduced and the risk of fire is reduced.

Although described above with reference to the preferred embodiments of the present invention, those skilled in the art may variously modify and change the present invention without departing from the spirit and scope of the present invention as set forth in the claims below. You will understand that you can.

100: nose cone 110: head portion
120: gyro sensor 200: control material
201: Division 210: parachute injection device
211: Fixed plate 212: Fixed frame
213: Injection control unit 214: Injection trigger
215: Injection unit 217: Parachute storage unit
217a: parachute storage space 219: spring
220: control device 300: engine member
310: solid fuel 320: nozzle unit
330: insulation 400: case

Claims (5)

Nose cone formed in a streamlined shape to separate the air during propulsion;
A division part forming a boundary with the nose cone and being divided to be detachable from the nose cone to form an injection space,
An injection trigger that releases the stress stored by the spring after reaching a predetermined altitude, an injection control unit that controls the injection trigger by an injection signal, and a parachute that is mounted in a parachute storage space through the injection space to the outside. A parachute injection device including a storage unit and an injection unit for transmitting the stress released by the injection trigger to the parachute storage unit and pushing the parachute storage unit upwards,
A control unit including a control device for outputting the injection signal and the engine control signal in response to a control signal;
Solid fuel containing solid fuel and oxidizing agent and ignited by the engine control signal,
Including a nozzle neck having a narrow inlet nozzle neck and a structure extending in the front-rear direction, and a mortar coating layer disposed on the surface of the nozzle base to protect the nozzle base and comprising 14 to 16% by weight of ultra-fast high-strength cement mortar. A nozzle unit for converting high-temperature and high-pressure gas generated by burning the solid fuel into kinetic energy;
An engine member surrounding the solid fuel and including an insulating portion to prevent heat generated as the solid fuel is burned from being transferred to the outside; And
A solid fuel rocket that includes a case in which the nozzle part is opened while covering the outer shape of the remaining parts except for the nose cone. The solid fuel rocket according to claim 1, wherein after the combustion of the solid fuel rocket, the used mortar coating layer on the nozzle base is removed, a new mortar coating layer is formed, and the solid fuel is re-injected to be reused. [3] The solid fuel rocket according to claim 1, wherein the area of the nozzle neck and the area of the expansion portion at the outlet side in the nozzle base satisfy [Equation 1] below.
[Equation 1]

(A _C is the area of the nozzle neck, A _e is the area of the extension on the outlet side, P _e is the nozzle pressure on the outlet side, P ₀ is the stagnant pressure inside the combustion chamber, and k is the insulation ratio, KNSB published on Nakka-Rocketry's website. Value) The solid fuel rocket according to claim 1, wherein the mortar coating layer is disposed on a portion of the nozzle base surface adjacent to the nozzle neck. According to claim 1, The fuel comprises any one or more powders selected from the group comprising metal aluminum powder and magnesium powder, the oxidizing agent is ammonium perchlorate (NH ₄ ClO ₄ ), ammonium nitrate (NH ₄ NO ₃ ) , Potassium nitrate, and one or more substances selected from the group consisting of sorbitol.

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