Electric heating supercritical CO2 emission propelling device
By using an electrically heated supercritical CO2 launch propulsion device, which utilizes heating resistance wires and a guiding structure, the shortcomings of traditional propulsion devices in terms of environmental protection and safety are solved, achieving rapid and safe propulsion, and making it suitable for explosion-proof and fire-proof applications.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-29
- Publication Date
- 2026-04-03
AI Technical Summary
Existing launch propulsion devices are inadequate in terms of environmental protection and safety, and traditional propulsion technologies suffer from large recoil and are not suitable for applications that restrict open flames and pyrotechnics.
The supercritical CO2 launch propulsion device, which employs electric heating, generates thrust by incorporating heating resistance wires and guiding structures within the flight body and utilizing the high-pressure energy of supercritical CO2 gas. Combined with electromagnetic thrust, it achieves rapid and safe propulsion.
It achieves an environmentally friendly and safe propulsion process, reduces recoil, is suitable for explosion-proof and fire-proof environments, and can continuously provide thrust to support the flight of the aircraft.
Smart Images
Figure CN121781992A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of launch propulsion technology, and in particular to an electrically heated supercritical CO2 launch propulsion device. Background Technology
[0002] Launch propulsion systems are widely used in aerospace, firefighting, transportation, and other fields. Existing launch propulsion systems mainly rely on traditional propulsion technologies such as gunpowder combustion and liquid propulsion. However, in areas where the use of open flames and pyrotechnics is restricted, the application of these traditional technologies is limited in terms of environmental protection and safety. Driven by these application needs, a supercritical CO2 propulsion launch propulsion system based on physical energy storage and electric heating has gradually gained attention due to its safety and environmental advantages, and is intended for use in special explosion-proof and fire-resistant applications. Furthermore, some traditional launch propulsion systems rely on inertial flight, while others rely on secondary range extension, resulting in high recoil. In contrast, the electric heating supercritical CO2 propulsion launch propulsion system comprehensively utilizes the energy storage of electricity and the physical energy storage of CO2, resulting in low recoil and enabling continuous propulsion of the aircraft during flight. Summary of the Invention
[0003] This invention addresses the issues of existing launch propulsion devices being bulky and having high environmental and safety requirements in certain fields by providing an electrically heated supercritical CO2 launch propulsion device.
[0004] This invention is achieved through the following technical solution: In one aspect, an electrically heated supercritical CO2 launch propulsion device includes a flight body and a guidance structure; The aircraft includes an inner shell and a Laval nozzle disposed inside the inner shell. The cavity of the Laval nozzle is sequentially divided into an inlet section, a constriction section, and an outlet section along the injection direction. There is an external gas storage space between the constriction section of the Laval nozzle and the inner wall of the inner shell. There is an internal gas storage space inside the Laval nozzle. A throat is provided in the inner shell located at the inlet section of the Laval nozzle. The throat is connected to a CO2 gas source. A plug is provided in the inner shell located at the outlet section of the Laval nozzle to seal the inner shell. The plug is in contact with the external gas storage space. A heating resistance wire is provided between the inner shell and the Laval nozzle. The guiding structure includes a launch tube, and a tin layer is provided between the inner shell and the launch tube at opposite positions. The flight body and the guiding structure are in frictional fit. Wires are respectively provided in the oppositely arranged tin layers, and one end of the inner side of the wire is electrically connected to a heating resistance wire.
[0005] Secondly, an electrically heated supercritical CO2 launch propulsion device includes a flight body and a guidance structure; The aircraft includes an inner shell and a Laval nozzle disposed inside the inner shell. The cavity of the Laval nozzle is sequentially divided into an inlet section, a narrowing section, and an outlet section along the injection direction. There is an external gas storage space between the narrowing section of the Laval nozzle and the inner wall of the inner shell. There is an internal gas storage space inside the Laval nozzle. A throat is provided in the inner shell located at the inlet section of the Laval nozzle. The throat is connected to a CO2 gas source. A plug is provided in the inner shell located at the outlet section of the Laval nozzle to seal the inner shell. The plug is in contact with the external gas storage space. The guiding structure includes a track, and the inner shell is provided with a tin layer between its relative positions and the track. The flying body and the guiding structure are in frictional fit, and the tin layers are respectively provided with wires.
[0006] As a further improvement to the technical solution of the present invention, one end of the inner side of the plug has a protrusion that seals with the end of the outlet section of the Laval nozzle, and the protrusion can separate the external gas storage space and the internal gas storage space.
[0007] As a further improvement to the technical solution of the present invention, the inner shell, Laval nozzle, and throat of the flight body are coaxially arranged.
[0008] As a further improvement to the technical solution of the present invention, the heating resistance wire arrangement includes the following two methods (a) and (b). (a) Wound in a spiral direction around the outside of the narrow section of the Laval nozzle; (b) Several heating resistance wires are arranged radially at the narrowing section of the Laval nozzle.
[0009] As a further improvement to the technical solution of the present invention, the tin layer is disposed on the outer surface of the inner shell.
[0010] As a further improvement to the technical solution of the present invention, the tin layer is disposed on the track.
[0011] The present invention provides an electrically heated supercritical CO2 launch propulsion device, which has the following advantages compared with the prior art: This invention provides two electrically heated supercritical CO2 propulsion launch devices: a cylindrical launch propulsion device and an orbital launch propulsion device. Both use an electric heating system to heat supercritical CO2 gas, utilizing the high-pressure energy of the supercritical CO2 gas to rapidly generate thrust, enabling efficient and rapid propulsion of objects. The orbital launch propulsion device, while using electric heating, also utilizes electromagnetic thrust. Attached Figure Description
[0012] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with the invention and, together with the description, serve to explain the principles of the invention.
[0013] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0014] Figure 1 This is a front view of the cylindrical launch propulsion device of Example 1.
[0015] Figure 2 for Figure 1 Longitudinal section view.
[0016] Figure 3 for Figure 1 A sectional view.
[0017] Figure 4 This is a longitudinal sectional view of another type of cylindrical launch propulsion device in Example 1.
[0018] Figure 5 This is a cross-sectional view of another type of cylindrical launch propulsion device in Example 1.
[0019] Figure 6 This is a schematic diagram of the orbital launch propulsion device in Example 2.
[0020] Figure 7 This is a front view of the orbital launch propulsion device of Example 2.
[0021] Figure 8 for Figure 7 Longitudinal section view.
[0022] Figure 9 for Figure 7 A sectional view.
[0023] In the diagram: 1-launch tube, 2-tin layer, 3-inner shell, 4-track, 5-Laval nozzle, 6-external gas storage space, 7-internal gas storage space, 8-plug, 801-protrusion, 9-throat, 10-wire, 11-heating resistance wire. Detailed Implementation
[0024] To better understand the above-mentioned objectives, features, and advantages of the present invention, the solutions of the present invention will be further described below. It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other.
[0025] Many specific details are set forth in the following description in order to provide a full understanding of the invention, but the invention may also be practiced in other ways different from those described herein; obviously, the embodiments in the specification are only some embodiments of the invention, and not all embodiments.
[0026] The specific embodiments of the present invention will be described in detail below. Example 1 (Cylinder-type launch propulsion device)
[0027] An electrically heated supercritical CO2 launch propulsion device includes a flight body and a guidance structure; The aircraft includes an inner shell 3 and a Laval nozzle 5 disposed inside the inner shell 3. The cavity of the Laval nozzle 5 is sequentially divided into an inlet section, a narrowing section, and an outlet section along the injection direction. There is an external gas storage space 6 between the narrowing section of the Laval nozzle 5 and the inner wall of the inner shell 3. There is an internal gas storage space 7 inside the Laval nozzle 5. The inner shell 3 located at the inlet section of the Laval nozzle 5 is provided with a throat 9, which is connected to a CO2 gas source. The inner shell 3 located at the outlet section of the Laval nozzle 5 is provided with a plug 8 that seals the inner shell 3. The plug 8 is in contact with the external gas storage space 6. A heating resistance wire 11 is disposed between the inner shell 3 and the Laval nozzle 5. The guiding structure includes a launch tube 1. A tin layer 2 is provided between the inner shell 3 and the launch tube 1 respectively. The flight body and the guiding structure are in frictional fit. A wire 10 is provided in the tin layer 2 respectively. One end of the inner side of the wire 10 is electrically connected to the heating resistance wire 11.
[0028] Both the external gas storage space 6 and the internal gas storage space 7 are pre-stored with supercritical CO2 gas. In specific applications, the contact portion between the Laval nozzle 5 and the inner shell 3 is insulated, and the contact portion between the inner shell 3 and the tin layer 2 is insulated; or, in this embodiment, the inner shell 3 is made of insulating material. The heating resistance wire 11 is made of tungsten alloy or other high-temperature resistant alloy material. The Laval nozzle 5 is fixedly connected to the inner shell 3.
[0029] In this embodiment, the tin layer 2 is disposed on the outer surface of the inner shell 3 in a relatively opposite position. The tin layer 2 is attached to the outer surface of the inner shell 3 by a tin plating process. An insulating gap is left between the opposing tin layers 2 to ensure that the current will not short-circuit. The current passes through the wire 10 and the tin layer 2 on one side, and then through the heating resistance wire 11 to achieve the dual effects of preheating and high-current heating. When the large pulse current passes through the resistance wire, an electric arc is generated. The local high temperature can burn out the resistance wire, causing the pressure of the supercritical CO2 gas, which is initially 7MPa and 39℃, to increase sharply. Since the external gas storage space 6 is in direct contact with the heating resistance wire 11, the external gas storage space 6 heats up more rapidly than the internal gas storage space 7. Thus, under the action of the external gas storage space 6, the plug 8 is quickly pushed open, thereby generating a powerful thrust to launch the flying object. The gas in the internal gas storage space 7 is continuously released, thereby increasing the flight distance of the flying object. The throat 9 of the Laval nozzle 5, which is connected to the gas storage cylinder, ensures the continuous propulsion of the launched object after the plug 8 is pushed open. It should be noted that the connection between the wire 10 and the heating resistance wire 11 in this invention is separated at the same time the plug 8 is opened.
[0030] In this embodiment, the Laval nozzle 5 can be made of either insulating or conductive materials.
[0031] The heating resistance wire 11 is arranged in two ways, as shown in (a) and (b). (a) It is wound in a spiral direction around the outside of the narrowing section of the Laval nozzle 5, specifically as follows: Figure 4 As shown; (b) Several heating resistance wires 11 are radially arranged at the narrowing section of the Laval nozzle 5, specifically as follows: Figure 2 Or as shown in Figure 3.
[0032] When the heating resistance wire 11 is arranged as shown in (a) above, the Laval nozzle 5 is made of insulating material, or the surface of the Laval nozzle 5 is insulated.
[0033] When the heating resistance wire 11 is arranged as shown in (b) above, the Laval nozzle 5 can be made of either insulating material or conductive material such as copper alloy.
[0034] In the case shown in (b), when the Laval nozzle 5 is made of insulating material, the heating resistance wire 11 is arranged radially in the narrow section of the Laval nozzle 5, with the radial wires connected end to end, and the two ends of the heating resistance wire 11 are respectively connected to the corresponding wires 10.
[0035] When the Laval nozzle 5 is made of conductive material, the heating resistance wire 11 near the positive electrode is connected in parallel with the wire 10 at the positive electrode, and the heating resistance wire 11 near the negative electrode is connected in parallel with the wire 10 at the negative electrode. The heating resistance wire 11 at the positive electrode is electrically connected to the Laval nozzle 5, and the heating resistance wire 11 at the negative electrode is electrically connected to the Laval nozzle 5. Example 2 (Orbital-based launch propulsion device)
[0036] An electrically heated supercritical CO2 launch propulsion device includes a flight body and a guidance structure; The aircraft includes an inner shell 3 and a Laval nozzle 5 disposed inside the inner shell 3. The cavity of the Laval nozzle 5 is sequentially divided into an inlet section, a narrowing section, and an outlet section along the injection direction. There is an external gas storage space 6 between the narrowing section of the Laval nozzle 5 and the inner wall of the inner shell 3. There is an internal gas storage space 7 inside the Laval nozzle 5. The inner shell 3 located at the inlet section of the Laval nozzle 5 is provided with a throat 9, which is connected to a CO2 gas source. The inner shell 3 located at the outlet section of the Laval nozzle 5 is provided with a plug 8 that seals the inner shell 3. The plug 8 is in contact with the external gas storage space 6. The guiding structure includes a track 4, and a tin layer 2 is provided between the inner shell 3 and the track 4 at opposite positions. The flying body and the guiding structure are in frictional fit. Wires 10 are respectively provided in the tin layers 2 that are arranged opposite to each other. The tin layer 2 is provided on the track 4.
[0037] Both the external gas storage space 6 and the internal gas storage space 7 are pre-stored with supercritical CO2 gas. The entire flight body is located between two opposing tracks 4 on the launch pad, one to the left and one to the right, with positive and negative polarities respectively. A tin layer 2 is formed between the flight body and the tracks, which, through wet friction, allows for smooth sliding flight and good electrical conductivity, preventing wear and ablation of the launch pad (long lifespan) and solving the armature ablation problem. Because the inner shell 3 (the inner surface of the flight body) is conductive, current can flow through the wire into the positive track 4, then through the inner shell 3 into the negative track 4, and finally out through the wire 10, generating electromagnetic thrust. Because the inner shell 3 carries current, it can preheat the supercritical CO2 gas in the external gas storage space 6 and the supercritical CO2 gas in the internal gas storage space 7 inside the Laval nozzle 5 (low power, high energy) or pulse the gas. The Laval nozzle 5 utilizes a high-power, low-energy instantaneous heating method. First, a small current preheats the gas, bringing the supercritical CO2 gas in the internal gas storage space 7 to 7 MPa and 39°C. At launch, a high-power pulsed current generates a large electromagnetic thrust, propelling the aircraft. Simultaneously, the instantaneous heating from the high power causes a rapid increase in supercritical CO2 gas pressure. Because the external gas storage space 6 is in direct contact with the inner shell 3, it heats up more rapidly than the internal gas storage space 7. This external gas storage space 6 then quickly pushes open the plug 8, generating a powerful thrust that launches the aircraft. The continuous release of gas from the internal gas storage space 7 increases the aircraft's flight distance. A throat 9 connected to the gas cylinder is located at the top of the Laval nozzle 5 to ensure continued propulsion of the aircraft after the plug 8 is breached.
[0038] The overall structural features of the orbital launch propulsion device ensure that the plug 8 does not generate recoil force when the device launches an object.
[0039] In the two embodiments described above, the inner end of the plug 8 has a protrusion 801 that seals with the end of the outlet section of the Laval nozzle 5. The protrusion 801 can separate the external gas storage space 6 and the internal gas storage space 7, and the plug 8 area outside the protrusion 801 can contact the external gas storage space 6.
[0040] Preferably, the inner shell 3, Laval nozzle 5, and throat 9 of the flight body are coaxially arranged.
[0041] The above description is merely a specific embodiment of the present invention, enabling those skilled in the art to understand or implement the present invention. Although detailed descriptions have been provided with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments, and they should all be covered within the protection scope of the claims.
Claims
1. An electrically heated supercritical CO2 launch propulsion device, characterized in that, Including the flight body and guidance structure; The aircraft includes an inner shell (3) and a Laval nozzle (5) disposed inside the inner shell (3). The cavity of the Laval nozzle (5) is sequentially divided into an inlet section, a narrowing section and an outlet section along the injection direction. There is an external gas storage space (6) between the narrowing section of the Laval nozzle (5) and the inner wall of the inner shell (3). There is an internal gas storage space (7) inside the Laval nozzle (5). The inner shell (3) located at the inlet section of the Laval nozzle (5) is provided with a throat (9). The throat (9) is connected to a CO2 gas source. The inner shell (3) located at the outlet section of the Laval nozzle (5) is provided with a plug (8) that seals the inner shell (3). The plug (8) is in contact with the external gas storage space (6). A heating resistance wire (11) is provided between the inner shell (3) and the Laval nozzle (5). The guiding structure includes a launch tube (1), and the inner shell (3) is provided with a tin layer (2) between it and the launch tube (1) respectively. The flying body and the guiding structure are in frictional fit. The tin layer (2) is provided with a wire (10) respectively. One end of the inner side of the wire (10) is electrically connected to the heating resistance wire (11).
2. An electrically heated supercritical CO2 launch propulsion device, characterized in that, Including the flight body and guidance structure; The aircraft includes an inner shell (3) and a Laval nozzle (5) disposed inside the inner shell (3). The cavity of the Laval nozzle (5) is sequentially divided into an inlet section, a narrowing section and an outlet section along the injection direction. There is an external gas storage space (6) between the narrowing section of the Laval nozzle (5) and the inner wall of the inner shell (3). There is an internal gas storage space (7) inside the Laval nozzle (5). The inner shell (3) located at the inlet section of the Laval nozzle (5) is provided with a throat (9). The throat (9) is connected to a CO2 gas source. The inner shell (3) located at the outlet section of the Laval nozzle (5) is provided with a plug (8) that seals the inner shell (3). The plug (8) is in contact with the external gas storage space (6). The guiding structure includes a track (4), and the inner shell (3) is provided with a tin layer (2) between it and the track (4) respectively. The flying body and the guiding structure are in frictional fit, and the tin layer (2) is provided with a wire (10) respectively.
3. A supercritical CO2 launch propulsion device with electric heating according to claim 1 or 2, characterized in that, The plug (8) has a protrusion (801) on one inner end that seals with the end of the outlet section of the Laval nozzle (5). The protrusion (801) can separate the external gas storage space (6) and the internal gas storage space (7).
4. A supercritical CO2 launch propulsion device with electric heating according to claim 1 or 2, characterized in that, The inner shell (3), Laval nozzle (5), and throat (9) of the aircraft are coaxially arranged.
5. The electrically heated supercritical CO2 launch propulsion device according to claim 1, characterized in that, The heating resistance wire (11) is arranged in two ways, as shown in (a) and (b). (a) Wound along the spiral direction around the outside of the narrow section of the Laval nozzle (5); (b) Several heating resistance wires (11) are arranged radially in the narrow section of the Laval nozzle (5).
6. The electrically heated supercritical CO2 launch propulsion device according to claim 1, characterized in that, The tin layer (2) is disposed on the outer surface of the inner shell (3).
7. The electrically heated supercritical CO2 launch propulsion device according to claim 2, characterized in that, The tin layer (2) is disposed on the track (4).