A type of launch vehicle

Abstract

This application relates to the field of rocket technology, and more particularly to a launch vehicle, comprising: a fairing, an inverted cone section, and a rocket body column section. The upper edge of the rocket body column section is fixed to the lower edge of the inverted cone section. The upper end of the inverted cone section is inserted into the interior of the fairing, and the upper edge of the inverted cone section is fixed to the inner wall of the fairing near the lower edge of the fairing. The portion of the fairing between the upper and lower edges of the inverted cone section serves as a shielding skirt to shield the inverted cone section from pulsating pressure. This application can reduce the pulsating pressure on the inverted cone section while ensuring the capacity of the fairing, reducing the structural strength requirements of the inverted cone section. In addition, this application also considers the fairing, inverted cone section, and rocket body column section, making the change of pulsating pressure more gradual and improving the noise environment inside the rocket's inverted cone section and instrument compartment.

Description

Technical Field

[0001] This application relates to the field of rocket technology, and more particularly to a launch vehicle. Background Technology

[0002] Traditional launch vehicle diameters are limited by technical conditions and transportation methods, with most rockets having a diameter of 3.35m or 2.65m. For example, the Long March 2 and Long March 3 rockets are mostly transported by rail, and their diameter is difficult to increase due to external constraints such as the width of railway tracks, train carriages, and tunnels.

[0003] As the types, quantities, and sizes of payloads carried by launch vehicles continue to increase, the demand for large-diameter fairings becomes more urgent. A large-diameter fairing needs to be connected to a small-diameter rocket body via an inverted conical section. This causes flow separation at the leading edge of the inverted conical section, generating a localized pulsating pressure peak upstream of the leading edge. The separated flow then reattaches to the rocket body's cylindrical section, generating the maximum pulsating pressure upstream of the reattachment point.

[0004] The design of the inverted cone section of a launch vehicle needs to simultaneously consider the peak local pulsating pressure on the fairing, the pulsating pressure value of the inverted cone section, and the maximum pulsating pressure value of the rocket body column section. Traditional solutions mainly include the following:

[0005] Option 1: Reduce the angle of the inverted cone section by 110 degrees to below 10 degrees, using a very small angle to reduce the pulsating pressure (e.g., Figure 1 and Figure 2 (As shown).

[0006] Option 2: Increase the angle of the inverted cone section to over 45 degrees to shield the inverted cone section from the effects of pulsating pressure.

[0007] Option 3: Add fillets to the leading edge of the inverted cone section to reduce the local pulsating pressure peak upstream of the leading edge.

[0008] However, Option 1 severely limits the diameter of the fairing 120, or would significantly increase the length of the inverted cone section 110, resulting in insufficient capacity of the fairing 120. Option 2 requires higher structural strength for the inverted cone section, and would also cause deterioration of the rocket body modes. Option 3 would diffuse the airflow separation zone, weakening the local pulsating pressure peak upstream of the leading edge of the inverted cone section while increasing the pulsating pressure on the inverted cone section.

[0009] Therefore, how to reduce the pulsating pressure on the inverted cone section while ensuring the capacity of the fairing and reducing the structural strength requirements of the inverted cone section is a technical problem that needs to be solved by those skilled in the art. Summary of the Invention

[0010] In view of this, this application provides a launch vehicle that reduces the pulsating pressure on the inverted cone section while ensuring the capacity of the fairing and reducing the structural strength requirements of the inverted cone section.

[0011] To solve the above-mentioned technical problems, this application provides the following technical solution:

[0012] A launch vehicle includes: a fairing, an inverted cone section, and a rocket body column section. The upper edge of the rocket body column section is fixed to the lower edge of the inverted cone section. The upper end of the inverted cone section is inserted into the interior of the fairing, and the upper edge of the inverted cone section is fixed to the inner wall of the fairing near the lower edge of the fairing. The portion of the fairing between the upper edge of the inverted cone section and the lower edge of the fairing serves as a shielding skirt to shield the inverted cone section from pulsating pressure.

[0013] In the launch vehicle described above, preferably, the upper section of the shielding skirt is cylindrical, and the lower section of the shielding skirt curves inward from top to bottom.

[0014] In the launch vehicle described above, preferably, the tangent at the lower edge of the outer wall of the lower section of the shielding skirt can extend to the lower edge of the inverted cone section.

[0015] In the launch vehicle described above, preferably, the angle between the tangent and the extension line of the outer wall of the fairing is a simulated inverted cone angle, which is greater than the inverted cone angle of the inverted cone segment.

[0016] In the launch vehicle described above, preferably, the simulated inverted cone angle is 45 degrees or more.

[0017] In the launch vehicle described above, preferably, the simulated inverted cone angle is 45 degrees or 60 degrees.

[0018] In the launch vehicle described above, preferably, the angle of the inverted cone section is between 10 degrees and 45 degrees.

[0019] In the launch vehicle described above, preferably, the angle of the inverted cone section is 30 degrees.

[0020] In the launch vehicle described above, preferably, the bending radius of the lower section of the shielding skirt is between 200mm and 500mm.

[0021] In the launch vehicle described above, preferably, the lower section of the shielding skirt has a bending radius of 300 mm.

[0022] Compared with the aforementioned background technology, the launch vehicle provided in this application can reduce the pulsating pressure on the inverted cone section while ensuring the capacity of the fairing and reducing the structural strength requirements of the inverted cone section. In addition, this application also takes into account the fairing, the inverted cone section and the rocket body column section, so that the change of pulsating pressure tends to be gradual, and the noise environment in the rocket's inverted cone section and instrument compartment is improved. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this application. For those skilled in the art, other drawings can be obtained based on these drawings.

[0024] Figure 1 This is a schematic diagram of a launch vehicle in the existing technology;

[0025] Figure 2 This is a schematic diagram of another type of launch vehicle in the existing technology;

[0026] Figure 3 This is a perspective view of the launch vehicle provided in the embodiments of this application;

[0027] Figure 4 This is a front view of the launch vehicle provided in the embodiments of this application;

[0028] Figure 5 This is a schematic diagram of a simulated inverted cone angle of 45 degrees for a launch vehicle provided in an embodiment of this application;

[0029] Figure 6 This is a schematic diagram of a simulated inverted cone angle of 60 degrees for a launch vehicle provided in an embodiment of this application;

[0030] Figure 7 This is a comparison diagram of the pulsating pressure sound pressure level of different parts of the launch vehicle provided in this application embodiment and an existing launch vehicle. Detailed Implementation

[0031] The embodiments of this application are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain this application, and should not be construed as limiting this application.

[0032] Please see Figure 3 and Figure 4 , Figure 3 This is a perspective view of the launch vehicle provided in the embodiments of this application. Figure 4This is a front view of the launch vehicle provided in the embodiments of this application.

[0033] This application provides a launch vehicle, including: a fairing 310, an inverted cone section 320, and a rocket body column section 330.

[0034] In this design, the upper edge of the arrow body column section 330 is fixed to the lower edge of the inverted cone section 320; the upper end of the inverted cone section 320 is inserted into the interior of the fairing 310, and the upper edge of the inverted cone section 320 is fixed to the inner wall of the fairing 310 near the lower edge of the fairing 310. This designates the portion of the fairing 310 between the upper and lower edges of the inverted cone section 320 as a shielding skirt section 311 to shield the inverted cone section 320 from the influence of pulsating pressure. Optionally, the inverted cone angle of the inverted cone section 320 is between 10 and 45 degrees. Alternatively, the inverted cone angle of the inverted cone section 320 is 30 degrees.

[0035] Existing technologies reduce the pulsating pressure on the inverted cone section by either reducing the inverted cone angle to below 10 degrees or increasing it to above 45 degrees. However, reducing the inverted cone angle to below 10 degrees would significantly sacrifice the fairing capacity, while increasing it to above 45 degrees would increase the structural strength requirements for the inverted cone section. Therefore, existing technologies cannot simultaneously reduce the pulsating pressure on the inverted cone section while ensuring the fairing capacity and reducing the structural strength requirements for the inverted cone section.

[0036] If the angle of the inverted cone section is between 10 and 45 degrees, the capacity of the fairing can be guaranteed to a certain extent, and the structural strength requirements of the inverted cone section can be avoided. However, the pulsating pressure on the inverted cone section will be very large. In this application, since the shielding skirt section 311 of the fairing 310 surrounds the outside of the inverted cone section 320, the airflow will separate at the shielding skirt section 311 after the rocket launch. This results in the separated flow being farther from the wall of the inverted cone section 320, thus reducing the pulsating pressure at the inverted cone section 320. Therefore, the angle of the inverted cone section 320 in this application can be set between 10 and 45 degrees, thereby guaranteeing the capacity of the fairing to a certain extent and reducing the structural strength requirements of the inverted cone section. In addition, this application also takes into account the fairing, the inverted cone section, and the rocket body column section, making the change in pulsating pressure more gradual and improving the noise environment inside the rocket's inverted cone section and instrument compartment.

[0037] Furthermore, the upper section of the shielding skirt 311 is cylindrical, while the lower section of the shielding skirt 311 curves inward from top to bottom. Because the lower section of the shielding skirt 311 curves inward from top to bottom, flow separation gradually occurs in the inwardly curved lower section of the shielding skirt 311, thereby dispersing the flow separation and weakening the local peak pulsating pressure generated by the separated flow. Optionally, the bending radius of the lower section of the shielding skirt 311 is between 200mm and 500mm. Alternatively, the bending radius of the lower section of the shielding skirt 311 is 300mm.

[0038] Furthermore, to ensure complete shielding of the inverted cone section 320, the tangent at the lower edge of the outer wall of the lower section of the shielding skirt 311 can extend to the lower edge of the inverted cone section 320. The angle formed by this tangent and the extension line of the outer wall of the fairing 310 is a simulated inverted cone angle simulated by the arrangement of the shielding skirt 311. This simulated inverted cone angle is larger than the inverted cone angle of the inverted cone section 320, thus providing shielding for the inverted cone section 320 with a larger simulated inverted cone angle. Optionally, the simulated inverted cone angle is 45 degrees or higher. Alternatively, the simulated inverted cone angle may be 45 degrees (e.g., ...). Figure 5 (As shown). Alternatively, the simulated inverted cone angle can be 60 degrees (e.g. Figure 6 (As shown).

[0039] Please see Figure 7 , Figure 7 This is a comparison diagram of the pulsating pressure sound pressure level of different parts of the launch vehicle provided in the embodiments of this application and existing launch vehicles.

[0040] Taking a rocket with a fairing diameter of 4.2m and a body column diameter of 2.65m as an example, line 1 represents the pulsating pressure at different measuring points of a rocket with an inverted cone angle of 22 degrees, line 2 represents the pulsating pressure at different measuring points of a rocket with an inverted cone angle of 45 degrees, and line 3 represents the pulsating pressure at different measuring points of a rocket with a shielding skirt section 311.

[0041] Clearly, compared to lines 1 and 2, line 3 reduces the peak pulsating pressure sound pressure level upstream of the inverted cone section from 157dB to 150dB, reducing the local dynamic load by more than half. At the same time, it reduces the pulsating pressure in the front half of the arrow body section by about 5dB on average, and the dynamic load borne by this part of the arrow body section can also be reduced by nearly half.

[0042] It will be apparent to those skilled in the art that this application is not limited to the details of the exemplary embodiments described above, and that this application can be implemented in other specific forms without departing from the spirit or essential characteristics of this application. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this application is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within this application. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0043] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A launch vehicle, comprising: The fairing, the inverted cone section, and the rocket body column section are characterized in that the upper edge of the rocket body column section is fixed to the lower edge of the inverted cone section; The upper end of the inverted cone section is inserted into the interior of the fairing, and the upper edge of the inverted cone section is fixed to the inner wall of the fairing near the lower edge of the fairing. The part of the fairing between the upper edge of the inverted cone section and the lower edge of the fairing is used as a shielding skirt. The airflow is separated at the shielding skirt surrounding the inverted cone section, so that the separated flow is far away from the wall of the inverted cone section, thus shielding the pulsating pressure of the inverted cone section. The upper section of the shielding skirt is cylindrical, and the lower section of the shielding skirt bends inward from top to bottom, so that flow separation gradually occurs in the lower section of the inwardly curved shielding skirt, thereby dispersing flow separation and weakening the local peak pulsating pressure generated by the separated flow. The tangent at the lower edge of the outer wall of the lower section of the skirt can extend to the lower edge of the inverted cone section to ensure full coverage of the inverted cone section.

2. The launch vehicle according to claim 1, characterized in that, The angle between the tangent and the extension of the outer wall of the fairing is the simulated inverted cone angle, which is greater than the inverted cone angle of the inverted cone segment.

3. The launch vehicle according to claim 2, characterized in that, The simulated inverted cone angle is 45 degrees or higher.

4. The launch vehicle according to claim 2, characterized in that, The simulated inverted cone angle is 45 degrees or 60 degrees.

5. The launch vehicle according to any one of claims 1-4, characterized in that, The angle of the inverted cone section is between 10 degrees and 45 degrees.

6. The launch vehicle according to claim 5, characterized in that, The angle of the inverted cone section is 30 degrees.

7. The launch vehicle according to any one of claims 1-4, characterized in that, The bending radius of the lower section of the concealing skirt is between 200mm and 500mm.

8. The launch vehicle according to claim 7, characterized in that, The lower section of the concealing skirt has a bending radius of 300mm.

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