Free filling type charging structure of speed-increasing endurance solid engine
By designing a cylindrical central seven-star slot for the speed-increasing stage and a solid circular charge structure for the endurance stage in the solid engine, and setting up a thermal insulation layer in the combustion chamber, the problems of the non-compact and inconvenient charge structure are solved, and a lightweight and efficient propulsion effect as well as simple installation and use are achieved.
Patent Information
- Application Number
- CN202422810221.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-19
- Publication Date
- 2025-10-10
- Estimated Expiration
- 2034-11-19
AI Technical Summary
The existing solid rocket charge structure design has the problems of non-compact structure, inconvenient use, heavy weight and low propulsion efficiency.
It adopts a speed-increasing cylindrical center seven-star slot charge structure and an endurance-level solid circular charge structure, which are integrally cast in the cladding tube to form a compact free-loading charge structure, and an insulation layer is set in the combustion chamber shell to improve the thermal insulation performance.
The explosive structure is compact, light in weight and high in propulsion efficiency. It is easy to manufacture and install and has high scalability and reusability.
Smart Images
Figure CN223424130U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to a free-loading charge structure for a speed-increasing and endurance-supporting solid rocket engine, which is composed of a combustion chamber, a cast solidified charge, and a coating tube. The free-loading charge structure is used for a solid rocket engine and has both the functions of speed-increasing launch and constant-speed endurance. Background Art
[0002] Solid motors are a crucial component of modern precision-guided munitions, and propellants are a crucial component of solid motors, serving as the energy and working fluid source for the motor. Currently, solid motor propellants come in two types: free-loading and wall-cast. The propellant's primary function is to generate high-temperature, high-pressure combustion gases within the combustion chamber after being ignited by the ignition device. These gases flow through the combustion chamber into the nozzle, where they are further expanded and accelerated, typically through a Laval nozzle. This velocity transitions from subsonic in the nozzle's convergent section to supersonic in the nozzle's divergent section. They are then ejected from the nozzle at high speed, generating a direct reaction force, or thrust, that accelerates the missile during launch or provides airborne endurance.
[0003] Different charge designs for solid rocket motors produce different internal ballistic curves, which directly influence the axial acceleration curve during flight. Early propulsion systems employed parallel or series engines. Starting in the 1980s, single-chamber, dual-thrust solid propellant engines were gradually adopted both domestically and internationally, enabling a single engine to continuously power both the missile's acceleration and flight, allowing it to operate throughout its entire flight range. The first stage of a single-chamber, dual-thrust engine is typically the high-thrust stage, used for takeoff, launch, or acceleration. This stage operates for the shortest time, providing a high initial thrust impulse to ensure sufficient launch velocity. The second stage, often used for endurance, is called the endurance stage. It operates for the longest time, maintaining the missile's constant velocity and enabling it to achieve sufficient range. This design is less compact, less convenient, and offers lower propulsion efficiency. Summary of the Invention
[0004] The technical problem to be solved by the utility model is to provide a free-loading charge structure for a speed-increasing and endurance solid engine which has the advantages of compact structure, convenient use, light weight and high propulsion efficiency.
[0005] In order to solve the above technical problems, the technical solution adopted by the utility model is: a free-loading charge structure of an accelerating and endurance solid engine, including a combustion chamber and a cladding tube arranged in the combustion chamber, and the cladding tube is filled with a free-loading charge consisting of a cylindrical center seven-star slot charge structure of the accelerating stage and a solid circular charge structure of the endurance stage.
[0006] The speed-increasing cylindrical center seven-star slot charge structure and the endurance-level solid circular charge structure are solidified bodies after the slurry is integrally cast on the coating tube, and are connected to the coating tube into one body through the adhesive on the inner surface of the coating tube.
[0007] The speed-increasing cylindrical center seven-star slot charge structure and the endurance level solid circular charge structure are both high-burning composite propellants. The angle between the two adjacent slot edges of the inner hole of the speed-increasing cylindrical center seven-star slot charge structure is about 56°, and the angle between the two adjacent slot centers is about 52°.
[0008] A heat insulation layer is arranged on the inner wall of the combustion chamber shell, and the heat insulation layer is bonded to the inner wall of the combustion chamber shell by means of a two-component phenolic resin adhesive.
[0009] The utility model adopts the above technical solution to design a free-loading charge structure for a speed-increasing and endurance-supporting solid rocket engine, which has the following beneficial effects:
[0010] 1. Compact charge structure, light weight and high propulsion efficiency;
[0011] 2. The integrated charging structure is easy to manufacture, install and use;
[0012] 3. Fully integrate the ideas of generalization, serialization and combination, and have high scalability and high reusability. BRIEF DESCRIPTION OF THE DRAWINGS
[0013] Figure 1 It is a structural diagram of the utility model;
[0014] Figure 2 for Figure 1 Engine combustion chamber loading diagram;
[0015] Figure 3 for Figure 1 Right view structural diagram. DETAILED DESCRIPTION
[0016] The following is a detailed description of the free-loading charge structure of a speed-increasing and endurance-supporting solid rocket engine according to the present invention with reference to the accompanying drawings.
[0017] The utility model is a free loading charge structure of a speed-increasing and endurance solid engine, see Figures 1 to 3, including a combustion chamber shell 1 and a covering tube 4 arranged in the combustion chamber shell 1. The combustion chamber shell 1 is a steel cylinder with a thin-walled structure, a wall thickness of 1.5mm to 2.5mm, and a threaded screw-on interface. The covering tube 4 has a diameter of φ92, a closed end bottom thickness of 2mm, and a side thickness of 1.2mm. The material is EPDM or NBR. The covering tube 4 is pre-made with a special mold and is used for free-loading charge columns, which plays a role of covering and heat insulation. A heat insulation layer 2 is provided on the inner wall of the combustion chamber shell 1. The heat insulation layer 2 is made of rubber and is molded with a two-component phenolic resin adhesive bonded to the inner wall of the combustion chamber shell. The thickness is 1.5mm to 2.5mm, which plays a role of heat insulation for the thin-walled shell. The free-loading charge 3 is filled in the covering tube 4. The free-loading charge 3 consists of a speed-increasing cylindrical center seven-star slot charge structure and an endurance-level solid circular charge structure. The speed-increasing cylindrical center seven-star slot charge structure is a high-combustion composite propellant. The charge structure has an outer diameter of approximately φ89 and an inner diameter of approximately φ26. The length is 100mm. The angle between the two adjacent groove edges of the inner seven-star slot is approximately 56°, and the angle between the centers of two adjacent slots is approximately 52°. The endurance-level solid circular charge structure is a high-combustion composite propellant. The solid charge structure has an outer diameter of approximately φ89 and a length of 100mm. The coating tube 4 of the utility model is pre-made with a special mold. A layer of special adhesive is evenly rolled on the inner surface of the coating tube 4. The speed-increasing cylindrical center seven-star slot charge structure and the endurance-level solid circular charge structure are integrally cast in the coating tube 4 with a slurry and then solidified. The slurry is then demolded and shaped to form an integrated free-loading charge 3 with the coating tube 4. The first stage of the free-loading charge 3 is the center seven-star slot structure of the speed-increasing cylindrical charge structure, and the second stage is the endurance-level solid circular charge structure.
[0018] The manufacturing process of this utility model involves accurately weighing the solid oxidizer (AP), aluminum powder metal fuel, hydroxybutadiene rubber (HTPB) adhesive, and other additives according to the required formula ratio. These ingredients are then added to a mixer in a specific order and mechanically mixed thoroughly to produce a uniform, flowable slurry. The slurry is then cast into a coating tube (2) placed in a casting mold under vacuum conditions and cured at a specific temperature and for a specified time. After curing, the slurry is demolded and shaped. During assembly, the closed end of the free-loading charge (3) with the coating tube (4) is placed into the combustion chamber housing (1). The free-loading charge (3) slides under its own weight into the bottom of the combustion chamber housing (1), and the other engine components are then installed according to the assembly process.
Claims
1. A free-loading charge structure for a speed-increasing and endurance-supporting solid rocket engine, characterized by: It includes a combustion chamber and a cladding tube arranged in the combustion chamber, and the cladding tube is filled with a free-loading charge consisting of a speed-increasing cylindrical center seven-star slot charge structure and an endurance-level solid circular charge structure.
2. The free-loading charge structure of the speed-increasing and endurance-supporting solid rocket engine according to claim 1 is characterized in that The speed-increasing cylindrical center seven-star slot charge structure and the endurance-level solid circular charge structure are solidified bodies after the slurry is integrally cast on the coating tube, and are connected to the coating tube into one body through the adhesive on the inner surface of the coating tube.
3. According to the free-loading charge structure of the speed-increasing and endurance-supporting solid engine according to claim 1 or 2, the speed-increasing cylindrical center seven-star slot charge structure and the endurance-supporting solid circular charge structure are both high-combustion composite propellants, and the angle between the two adjacent slot edges of the inner hole of the speed-increasing cylindrical center seven-star slot charge structure is 56°, and the angle between the two adjacent slot centers is 52°.
4. According to the free-loading charge structure of the speed-increasing and endurance-supporting solid engine of claim 1, a heat-insulating layer is provided on the inner wall of the shell of the combustion chamber, and the heat-insulating layer is bonded to the inner wall of the combustion chamber shell by a two-component phenolic resin glue.