Launch vehicle boosting stage
By designing a launch vehicle boost stage using a beveled cone, engine, tail section and bundled connection mechanism, the problems of long development cycle, high cost and difficult control in the prior art are solved, and the effect of reducing aerodynamics and simplifying the load-bearing and conveying methods are achieved.
Patent Information
- Application Number
- CN202421538862.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-02
- Publication Date
- 2025-03-21
- Estimated Expiration
- 2034-07-02
AI Technical Summary
When improving the carrying capacity of existing launch vehicles, they face problems such as long development cycle, high cost, large length and thin ratio of rockets, poor bending stiffness, high control difficulty and complex ground service.
A launch vehicle booster stage is designed, using a structure of a beveled cone, engine, tail section and bundled connection mechanism. The rocket height and length ratio are reduced through the bundled connection mechanism, simplifying the load-bearing and force transfer method, and improving the reliability of the structure and the low processing cost.
It has achieved the reduction of aerodynamics, simplified the load-bearing and transmission method, improved the reliability of the structure and the low processing cost, and solved the problems of long development cycle, high cost and high control difficulties in the existing technology.
Smart Images
Figure CN222652044U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of launch vehicle structures, in particular to a launch vehicle booster stage. Background Art
[0002] As the society's demand for carrying capacity continues to increase, the demand for carrier rockets to improve their carrying capacity is becoming more and more urgent. At present, the way to improve the carrying capacity of carrier rockets is to increase the diameter and length of each sub-stage structure, but this will bring about problems such as long development cycle and high cost; large rocket aspect ratio, poor bending stiffness, high control difficulty; high rocket length and high difficulty in ground service.
[0003] To solve the above problems, a bundled booster stage structure can be set up around the core stage, which can significantly reduce the rocket's height and aspect ratio, shorten the development cycle, reduce the control difficulty, and simplify ground service. However, the booster stage will increase aerodynamic resistance and cause major problems in load conditions.
[0004] In view of this, it is necessary to provide a new technical solution to solve the above problems. Utility Model Content
[0005] In order to solve the above-mentioned technical problems, the present application provides a launch vehicle booster stage, which can reduce aerodynamic forces, has a simple load-bearing and force-transmitting method, a reliable structural solution and low processing costs.
[0006] A booster stage for a launch vehicle comprises: an oblique nose cone, an engine, a tail section and a bundling connection mechanism; the engine is arranged between the oblique nose cone and the tail section; the upper end of the engine is fixedly connected to the tail end of the oblique nose cone; the lower end of the engine is fixedly connected to the tail section; the bundling connection mechanism comprises a main bundling and a bundling connecting rod; the main bundling and the bundling connecting rod are located on the same radial plane passing through the axis of the engine; the main bundling is fixedly connected to the oblique nose cone; the bundling connecting rod is fixedly connected to the engine.
[0007] Preferably, the main binding comprises a main binding body and a crossbeam; the crossbeam is fixedly arranged inside the oblique head cone; the main binding body is fixedly arranged outside the oblique head cone; the main binding body and the crossbeam are arranged in a colinear manner.
[0008] Preferably, the main binding also includes a rear connecting plate; the rear connecting plate is fixedly connected to the inner wall of the oblique head cone; the distal end of the beam connected to the main binding body is fixedly connected to the inner wall of the oblique head cone via the rear connecting plate.
[0009] Preferably, the overall height of the booster stage of the carrier rocket is 12.5 m and the cabin diameter is 2.65 m.
[0010] Preferably, the height of the oblique head cone is 3.5m.
[0011] Preferably, the engine height is 7m.
[0012] Preferably, the height of the tail section is 2m.
[0013] Compared with the prior art, this application has at least the following beneficial effects:
[0014] The utility model can reduce aerodynamic force, has a simple load-bearing and force-transmitting mode, a reliable structural scheme and low processing cost. BRIEF DESCRIPTION OF THE DRAWINGS
[0015] Hereinafter, some specific embodiments of the present invention will be described in detail in an exemplary and non-restrictive manner with reference to the accompanying drawings. The same reference numerals in the accompanying drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale.
[0016] In the attached figure:
[0017] Figure 1 This is a schematic diagram of the overall structure of the booster stage of the launch vehicle of the utility model;
[0018] Figure 2 It is a schematic diagram of the overall structure of the oblique head cone of the utility model.
[0019] The above drawings include the following reference numerals:
[0020] 10. Oblique nose cone; 20. Engine; 30. Tail section; 40. Main lashing; 50. Lashing connecting rod; 41. Main lashing body; 42. Crossbeam; 43. Rear connecting plate. DETAILED DESCRIPTION
[0021] In order to make the purpose, technical solution and advantages of the present application clearer, the technical solution of the present application will be clearly and completely described below in combination with the specific embodiments of the present application and the corresponding drawings. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present application.
[0022] like Figure 1 and Figure 2As shown, a booster stage of a launch vehicle comprises: an oblique nose cone 10, an engine 20, a tail section 30 and a binding connection mechanism. The engine 20 is arranged between the oblique nose cone 10 and the tail section 30, wherein the upper end of the engine 20 is fixedly connected to the tail end of the oblique nose cone 10, and the lower end of the engine 20 is fixedly connected to the tail section 30. The binding connection mechanism comprises a main binding 40 and a binding connecting rod 50; the main binding 40 and the binding connecting rod 50 are located on the same radial plane passing through the axis of the engine 20; the main binding 40 is fixedly connected to the oblique nose cone 10; and the binding connecting rod 50 is fixedly connected to the engine 20.
[0023] The main binding 40 includes a main binding body 41 and a crossbeam 42; wherein, the crossbeam 42 is fixedly arranged inside the oblique head cone 10, and both ends thereof are fixedly connected to the inner wall of the oblique head cone 10; the main binding body 41 is fixedly arranged outside the oblique head cone 10; the main binding body 41 and the crossbeam 42 are arranged in the same line.
[0024] As another embodiment of the utility model, the main binding 40 further includes a rear connecting plate 43, which is fixedly connected to the inner wall of the oblique head cone 10. The far end of the crossbeam 42 connected to the main binding body 41 is fixedly connected to the inner wall of the oblique head cone 10 through the rear connecting plate 43.
[0025] Preferably, the overall height of the launch vehicle booster stage is 12.5m and the cabin diameter is 2.65m.
[0026] Preferably, the height of the oblique head cone 10 is 3.5 m.
[0027] Preferably, the height of the engine 20 is 7 m.
[0028] Preferably, the height of the tail section 30 is 2 m.
[0029] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.
[0030] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.
[0031] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.
[0032] The above description is only the preferred embodiment of the utility model, and is not intended to limit the utility model. For those skilled in the art, the utility model can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the utility model shall be included in the protection scope of the utility model.
Claims
1. A launch vehicle booster stage, characterized in that: include: An oblique nose cone, an engine, a tail section and a binding connection mechanism; the engine is arranged between the oblique nose cone and the tail section; the upper end of the engine is fixedly connected to the tail end of the oblique nose cone; the lower end of the engine is fixedly connected to the tail section; the binding connection mechanism includes a main binding and a binding connecting rod; the main binding and the binding connecting rod are located on the same radial plane passing through the axis of the engine; the main binding is fixedly connected to the oblique nose cone; the binding connecting rod is fixedly connected to the engine.
2. The launch vehicle booster stage according to claim 1, characterized in that: The main binding comprises a main binding body and a crossbeam; the crossbeam is fixedly arranged inside the oblique head cone; the main binding body is fixedly arranged outside the oblique head cone; the main binding body and the crossbeam are arranged in a colinear manner.
3. The launch vehicle booster stage according to claim 2, characterized in that: The main binding also includes a rear connecting plate; the rear connecting plate is fixedly connected to the inner wall of the oblique head cone; the distal end of the beam connected to the main binding body is fixedly connected to the inner wall of the oblique head cone through the rear connecting plate.
4. The launch vehicle booster stage according to claim 1, characterized in that: The overall height of the launch vehicle's booster stage is 12.5m and the cabin diameter is 2.65m.
5. The launch vehicle booster stage according to claim 1, characterized in that: The height of the oblique head cone is 3.5m.
6. The launch vehicle booster stage according to claim 1, characterized in that: The engine height is 7m.
7. The launch vehicle booster stage according to claim 1, characterized in that: The height of the tail section is 2m.