A missile fairing for hypersonic speeds

Abstract

This invention belongs to the field of fairing technology, and particularly to a fairing for a high-speed missile. It includes two shells, with heads welded to the top of each shell. A stabilizing structure is fixedly installed inside each shell. Each stabilizing structure includes a hinge block, with a rotating rod two and a rotating rod one fixedly sleeved inside each hinge block. In use, the stabilizing structure, driven by a motor, causes the rotating rod two to rotate the hinge rod one. Since hinge rods one, two, three, and four are hinged together, and hinge rod three and five form a parallelogram, the rotation of hinge rod one can cause hinge rod four to move horizontally to one side. The simultaneous movement of hinge rods four on both sides can lock the locking lever, thereby fixing the missile warhead's carrier component and ensuring its stability during ascent.

Description

Technical Field

[0001] This utility model belongs to the field of fairing technology, specifically relating to a fairing for ultra-high-speed missiles. Background Technology

[0002] A satellite fairing is a crucial component of a launch vehicle, used to protect satellites and other payloads from harmful environmental factors such as aerodynamic forces, aerodynamic heating, and acoustic vibration. It is typically a clamshell-type structure, consisting of an end cap, a forward conical section, a cylindrical section, an inverted conical section, and longitudinal and lateral separation mechanisms. The functions of a satellite fairing include: protecting the satellite from aerodynamic forces; protecting the satellite from aerodynamic heating; ensuring smooth separation of the satellite fairing via an unlocking and separation system; and regulating the temperature and humidity inside the fairing when the launch vehicle is in a pre-launch state to protect the satellite from low temperatures and environmental factors, as well as from contamination by various smog environments.

[0003] Patent No.: CN215514208U, Satellite fairing, including a fairing shell 1 and a hinge unit 14 provided on the fairing shell 1. The end of the fairing shell 1 is provided with a connecting part 2. The connecting part 2 and the fairing shell 1 are also provided with a hinge unit 14. The end head and the cylindrical part are connected by the hinge unit. The connecting part is connected to the fairing shell. When the end head and the cylindrical part are separated one after another, the hinge unit connects the end head and the cylindrical part. The connecting part further connects and fixes the end of the fairing shell, so that the fairing shell can be detached into two wholes, which is convenient for searching.

[0004] The above-mentioned device can be further improved in actual production and use: Since there is no stable structure inside the fairing, the artificial satellite or other carrier components mounted on the missile warhead may collide and loosen during the ascent, affecting the safety of the missile. In addition, since the fairing is reusable, if it falls into the sea during the separation and descent, it will be difficult to find. Therefore, it needs to be improved. Utility Model Content

[0005] To address the aforementioned problems in the existing technology, this utility model provides a missile fairing for ultra-high speed, which features a stable interior and is easy to locate.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a missile fairing for ultra-high speed, comprising two shells, with heads welded to the tops of the two shells, and stabilizing structures fixedly installed inside the two shells. Each stabilizing structure includes a hinge block, with a rotating rod two fixedly sleeved inside the hinge block, and a rotating rod one fixedly sleeved inside the hinge block. A hinge rod one is fixedly installed on the outer surface of the rotating rod two, and a hinge rod four is hingedly installed at one end of the rotating rod one. The outer surface of the rotating rod one is fixed... A hinge rod 2 is fitted together. A hinge rod 3 is hingedly installed at the middle of the outer surface of the hinge rod 2. One end of the hinge rod 3 is hingedly connected to one end of the hinge rod 1. A hinge rod 5 is hingedly installed at one end of the hinge rod 2. One end of the hinge rod 5 is hingedly connected to the middle of the hinge rod 4. A connecting plate is fixedly installed on one side of the hinge rod 4. Locking rods are fixedly installed on both sides of the outer surface of the connecting plate. Tension springs are fixedly installed on both sides of the outer surface of the hinge block. The tension springs are fixedly connected to the hinge joint of the hinge rod 1.

[0007] As a preferred technical solution for a missile fairing for ultra-high speed according to this utility model, a protective shell is fixedly installed on one side of the outer surface of the hinge block, and a fixing ring is fixedly installed on one side of the outer surface of the hinge block.

[0008] As a preferred technical solution for a missile fairing for ultra-high speed according to this utility model, a motor is fixedly installed inside the fixing ring, and one end of the output shaft of the motor is fixedly connected to the rotating rod.

[0009] As a preferred technical solution for a missile fairing for ultra-high speed according to this utility model, a buoyancy structure is fixedly installed inside the two fairing shells. The buoyancy structure includes an air pump, and an electronic valve is fixedly installed on the top of the air pump.

[0010] As a preferred technical solution for a missile fairing for ultra-high speed according to this utility model, each of the fairing shells has an airbag fixedly installed inside, and each of the multiple airbags has a ventilation pipe fixedly installed inside.

[0011] As a preferred technical solution for a missile fairing for ultra-high speed according to this utility model, a vent pipe is fixedly installed on the outer surface of each electronic valve, and a vent pipe is fixedly installed on one side of the outer surface of each airbag.

[0012] Compared with the prior art, the beneficial effects of this utility model are:

[0013] 1. In use, this utility model uses a stable structure and a motor to drive the rotating rod two to rotate the hinge rod one. Since the hinge rod one, hinge rod two, hinge rod three, and hinge rod four are hinged to each other, and hinge rod three and hinge rod five form a parallelogram, when hinge rod one rotates, it can drive hinge rod four to move horizontally to one side. By moving hinge rod four on both sides at the same time, the locking rod can be locked, thereby fixing the carrier component installed on the missile warhead and keeping it stable during ascent.

[0014] 2. When in use, this utility model uses a floating structure. When the shell separates from the missile, the electric power drives the electronic valve to open the air pump to draw in air. The air is then introduced into each airbag through the first, second, and third air pipes, causing it to inflate. If the shell falls into the sea, it can float, thus facilitating its retrieval. Attached Figure Description

[0015] The accompanying drawings are provided to further illustrate the present invention and form part of the specification. They are used together with the embodiments of the present invention to explain the present invention, but do not constitute a limitation thereof. In the drawings:

[0016] Figure 1 This is a schematic diagram of the external structure of this utility model;

[0017] Figure 2 This is a schematic diagram of the internal structure of the present invention;

[0018] Figure 3 This is a schematic diagram of the stable (I) structure of this utility model;

[0019] Figure 4 This is a schematic diagram of the stable (II) structure of this utility model;

[0020] Figure 5 This is a schematic diagram of the floating structure of this utility model.

[0021] In the diagram: 1. Cover; 2. Head; 3. Stabilizing structure; 31. Hinge block; 32. Fixing ring; 33. Motor; 34. Protective shell; 35. Rotating rod one; 36. Rotating rod two; 37. Hinge rod one; 38. Hinge rod two; 39. Hinge rod three; 310. Hinge rod four; 311. Hinge rod five; 312. Connecting plate; 313. Locking rod; 314. Tension spring; 4. Lifting structure; 41. Air pump; 42. Electronic valve; 43. Airbag; 44. Ventilation pipe one; 45. Ventilation pipe two; 46. Ventilation pipe three. Detailed Implementation

[0022] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0023] Example 1

[0024] Please see Figure 1-5 This utility model provides the following technical solution: a missile fairing for ultra-high speed, comprising two shells 1, with a head 2 welded to the top of each shell 1, and a stabilizing structure 3 fixedly installed inside each shell 1. Each stabilizing structure 3 includes a hinge block 31, with a rotating rod 36 fixedly sleeved inside the hinge block 31, and a rotating rod 35 fixedly sleeved inside the hinge block 31. A hinge rod 37 is fixedly installed on the outer surface of the rotating rod 36, and a hinge rod 310 is hinged to one end of the rotating rod 37. A hinge rod 38 is fixedly sleeved on the outer surface of the rotating rod 35. A hinge rod 39 is hinged to the middle of the outer surface of rod 2 38. One end of hinge rod 39 is hinged to one end of hinge rod 1 37. A hinge rod 5 311 is hinged to one end of hinge rod 2 38. One end of hinge rod 5 311 is hinged to the middle of hinge rod 4 310. A connecting plate 312 is fixedly installed on one side of hinge rod 4 310. A locking rod 313 is fixedly installed on both sides of the outer surface of the connecting plate 312. A tension spring 314 is fixedly installed on both sides of the outer surface of the hinge block 31. The tension spring 314 is fixedly connected to the hinge of hinge rod 1 37.

[0025] Example 2

[0026] Please see Figure 1-3 The present invention provides the following technical solution: a protective shell 34 is fixedly installed on one side of the outer surface of the hinge block 31, and a fixing ring 32 is fixedly installed on one side of the outer surface of the hinge block 31. A motor 33 is fixedly installed inside the fixing ring 32, and one end of the output shaft of the motor 33 is fixedly connected to the rotating rod 36.

[0027] Driven by motor 33, rotating rod 2 36 drives hinge rod 1 37 to rotate. Since hinge rod 1 37, hinge rod 2 38, hinge rod 39, and hinge rod 4 310 are hinged to each other, and hinge rod 39 and hinge rod 5 311 form a parallelogram, when hinge rod 1 37 rotates, it can drive hinge rod 4 310 to move horizontally to one side. By moving hinge rod 4 310 on both sides at the same time, locking rod 313 can be locked.

[0028] Example 3

[0029] Please see Figure 2-5 The present invention provides the following technical solution: A buoyancy structure 4 is fixedly installed inside the two housings 1. The buoyancy structure 4 includes an air pump 41, and an electronic valve 42 is fixedly installed on the top of the air pump 41. An airbag 43 is fixedly installed inside each housing 1, and a second ventilation pipe 45 is fixedly installed inside the multiple airbags 43. A first ventilation pipe 44 is fixedly installed on the outer surface of each electronic valve 42, and a third ventilation pipe 46 is fixedly installed on one side of the outer surface of each airbag 43.

[0030] The electric valve 42 is electrically driven to activate the air pump 41, which draws in air. This air is then introduced into each airbag 43 through ventilation pipes 44, 45, and 46, causing them to inflate. If the outer shell 1 falls into the sea, it can float.

[0031] The working principle and usage process of this utility model are as follows: In the process of using this utility model, firstly, the motor 33 drives the rotating rod 36 to rotate the hinge rod 37. Since the hinge rods 37, 38, 39, and 310 are hinged to each other, and the hinge rod 39 and the hinge rod 311 form a parallelogram, when the hinge rod 37 rotates, it can drive the hinge rod 310 to move horizontally to one side. By moving the hinge rods 310 on both sides at the same time, the locking rod 313 can be locked, thereby fixing the carrier component installed on the missile warhead. Then, when the shell 1 separates from the missile, the electric drive electronic valve 42 opens the air pump 41 to draw in air, which is introduced into each airbag 43 through the ventilation pipe 44, ventilation pipe 45, and ventilation pipe 46, causing it to inflate. If the shell 1 falls into the sea, it can float.

[0032] Finally, it should be noted that the above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A missile fairing for ultra-high speed, comprising two housings (1), characterized in that: Heads (2) are welded to the top of the two housings (1). A stabilizing structure (3) is fixedly installed inside the two housings (1). The two stabilizing structures (3) include a hinge block (31). A rotating rod two (36) is fixedly sleeved inside the hinge block (31). A rotating rod one (35) is fixedly sleeved inside the hinge block (31). A hinge rod one (37) is fixedly installed on the outer surface of the rotating rod two (36). A hinge rod four (310) is hinged to one end of the hinge rod one (37). A hinge rod two (38) is fixedly sleeved on the outer surface of the rotating rod one (35). The middle of the outer surface of the hinge rod two (38) is hinged. A hinge rod three (39) is installed, one end of which is hinged to one end of hinge rod one (37). A hinge rod five (311) is hinged to one end of hinge rod two (38). One end of hinge rod five (311) is hinged to the middle of hinge rod four (310). A connecting plate (312) is fixedly installed on one side of hinge rod four (310). A locking rod (313) is fixedly installed on both sides of the outer surface of the connecting plate (312). A tension spring (314) is fixedly installed on both sides of the outer surface of the hinge block (31). The tension spring (314) is fixedly connected to the hinge of hinge rod one (37).

2. The missile fairing for ultra-high speed according to claim 1, characterized in that: A protective shell (34) is fixedly installed on one side of the outer surface of the hinge block (31), and a fixing ring (32) is fixedly installed on one side of the outer surface of the hinge block (31).

3. A missile fairing for ultra-high speed according to claim 2, characterized in that: A motor (33) is fixedly installed inside the fixed ring (32), and one end of the output shaft of the motor (33) is fixedly connected to the rotating rod (36).

4. A missile fairing for ultra-high speed according to claim 1, characterized in that: The two housings (1) are fixedly installed with a buoyancy structure (4), which includes an air pump (41) and an electronic valve (42) is fixedly installed on the top of the air pump (41).

5. A missile fairing for ultra-high speed according to claim 4, characterized in that: Each of the housings (1) has an airbag (43) fixedly installed inside, and each of the airbags (43) has a ventilation tube (45) fixedly installed inside.

6. A missile fairing for ultra-high speed according to claim 5, characterized in that: Each of the electronic valves (42) has a vent pipe 1 (44) fixedly installed on its outer surface, and each of the airbags (43) has a vent pipe 3 (46) fixedly installed on one side of its outer surface.

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