Carrier rocket fairing and design method

Abstract

The invention discloses a carrier rocket fairing and a design method, and belongs to the field of carrier rocket design, and the carrier rocket fairing comprises a fairing body connected with an effective load adapter; a protruding limiting body is arranged on the outer side wall of the effective load adapter. The bottom of the inner side wall of the fairing body is provided with a groove body surrounding the protruding limiting body. The groove body and the protruding limiting body are matched in an inserted mode. The fairing body comprises at least two cover petals; the adjacent cover petals are fixedly connected through a longitudinal separation unlocking device in the longitudinal direction. Through the design of the protruding limiting body and the groove body, the arrangement of a transverse separation unlocking device is omitted, the manufacturing cost of the fairing is increased, and the separation reliability of the fairing is improved.

Description

Technical Field

[0001] The invention relates to the field of launch vehicle design, and in particular to a launch vehicle fairing and a design method thereof. Background Art

[0002] In order to protect rockets, satellites or other payloads from the harsh environment such as aerodynamic force, aerodynamic heat and aerodynamic noise, launch vehicles are usually equipped with fairings. However, when the launch vehicle flies to a certain altitude (usually greater than 100km), the aerodynamic environment problem can be basically ignored. In order to ensure the subsequent flight performance of the rocket and the separation of the payload, the fairing needs to be separated from the rocket and discarded. Practice has proved that the connection reliability and separation reliability of the fairing are one of the key factors affecting the success or failure of the rocket flight mission.

[0003] In the existing launch vehicle fairing separation scheme, whether it is flap-type separation or overall pull-out-type separation, the lateral separation surface connection unlocking device is indispensable; in order to improve the connection reliability, it is required to connect multiple unlocking devices on the lateral separation surface, and the number of supporting pyrotechnic products is large. In the actual separation process, multiple points of connection must be separated within 10ms. If one unlocking device fails, the fairing separation will fail, and then the flight mission will fail. At the same time, pyrotechnics are disposable products and cannot be ignited for actual testing before actual flight. The reliability of the corresponding batch of pyrotechnics can only be tested by batch sampling.

[0004] In addition, the existing lateral separation surface connection unlocking devices are mostly point connections. Under axial tension and shear loads, the point connection of the lateral separation surface has a poor bearing capacity and may have the risk of stress concentration damage to the lateral separation surface.

[0005] In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the invention

[0006] In order to solve the above-mentioned technical problems, the present application provides a launch vehicle fairing and a design method. Through the design of a protruding limit body and a groove body, the setting of a lateral separation unlocking device is omitted, the manufacturing cost of the fairing is improved, and the reliability of the fairing separation is improved.

[0007] A launch vehicle fairing comprises: a fairing body connected to a payload adapter; the outer side wall of the payload adapter is provided with a protruding limiter; the bottom of the inner side wall of the fairing body has a groove body arranged around the protruding limiter; the groove body is plugged into and fits with the protruding limiter; the fairing body comprises no less than two cover flaps; adjacent cover flaps are fixedly connected in the longitudinal direction by a longitudinal separation unlocking device.

[0008] Preferably, the fairing body includes a first cover flap and a second cover flap; the bottom of the inner side wall of the first cover flap is provided with a first arc-shaped groove body half; the bottom of the inner side wall of the second cover flap is provided with a second arc-shaped groove body half.

[0009] Preferably, it also includes a roll limiter for preventing the fairing body from axially rotating relative to the payload adapter; the roll limiter is arranged on the side of the connection between the protruding limiter and the groove body; the roll limiter is fixedly connected to the outer side wall of the payload adapter.

[0010] Preferably, the vertical cross-section of the protruding limiting body is rectangular; the groove body and the protruding limiting body are plug-fitted in the lateral direction of the fairing body.

[0011] Preferably, when assembling the launch vehicle fairing, the cover petals are combined to form the fairing body and then the longitudinal separation unlocking device is installed; Wherein, during the process of closing the cover flaps to form the fairing body, the groove body is plugged into and matched with the protruding limiting body to enclose the payload adapter between the cover flaps.

[0012] Preferably, it also includes a push-to-release mechanism for pushing the cover flap away from the payload adapter.

[0013] According to another aspect of the present application, a launch vehicle fairing design method is also provided, which is used to design the launch vehicle fairing, and includes: A groove body is designed at the bottom of the inner wall of the fairing body; According to the structure and size of the groove body, a protruding stopper that can match the groove body is designed on the outer side wall of the payload adapter; The size and position of the rolling limiter are designed by the intersection position of the butt joint surface of the protruding limiter and the grooved body; Determine the minimum horizontal push distance of the cover flap according to the combined size of the protruding limiter and the groove body; The minimum actuating stroke of the horizontal push separation mechanism is determined according to the minimum horizontal push distance of the cover flap; According to the minimum actuation stroke of the horizontal push separation mechanism and considering the safety margin, the length of the actuator and push rod of the horizontal push separation mechanism and the length exposed from the longitudinal separation surface of the fairing are designed; Design the total separation impulse of the actuator according to the valve cover mass and lateral separation pushing speed requirements; The total separation impulse is matched by the number of actuators, the length of a single actuator, the inner diameter of the cylinder and the average pressure of the internal gas pressure; The layout position of the actuator is determined by the center of mass, inertia and geometric characteristics of the fairing flap, thereby completing the design of the launch vehicle fairing.

[0014] Preferably, the calculation formula for the minimum horizontal push distance of the cover flap is: ; In the formula, is the minimum horizontal push distance of the cover flap; R is the outer diameter of the protruding limiter; H is the radial depth of the groove body that overlaps with the protruding limiter.

[0015] Preferably, when the total separation impulse of the actuator is designed, the total separation impulse of the actuator meets the requirement of the minimum separation speed when pushing the fairing valve cover to completely separate from the arrow body.

[0016] Preferably, when the total separation impulse is matched by the number of actuators, the length of a single actuator, the inner diameter of the cylinder and the average internal air pressure, the thrust impulse moments of the actuators above and below the centroid plane of the fairing valve cover are equal.

[0017] Compared with the prior art, this application has at least the following beneficial effects: 1. The present invention changes the point connection form of the traditional fairing transverse separation surface into a surface connection form by setting the protruding limiter and the groove body, so that the connection is more reliable.

[0018] 2. The present invention changes the point-to-surface force between the fairing and the payload adapter under axial force and shear force into surface-to-surface force by setting the protruding limiter and the grooved body. The force is more uniform and can prevent stress concentration damage on the lateral separation surface of the fairing.

[0019] 3. The present invention omits the lateral separation unlocking device by setting the protruding limiter and the groove body, so that the fairing can be assembled horizontally or vertically, which is faster and more convenient to install, saving the time of final assembly at the shooting range and the test time after assembly.

[0020] 4. The present invention has no lateral separation unlocking device, which reduces the amount of explosive bolts used and has higher separation reliability.

[0021] 5. The present invention does not have a lateral separation unlocking device, thus saving development and use costs.

[0022] 6. The present invention provides a limit block at the intersection of the transverse and longitudinal separation surfaces, which can effectively prevent the fairing from rolling. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Hereinafter, some specific embodiments of the present invention will be described in detail in an exemplary and non-limiting 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. In the accompanying drawings: Figure 1 It is a schematic diagram of the overall structure of the carrier rocket fairing of the present invention; Figure 2 It is a structural schematic diagram of the connection position between the fairing body and the payload adapter of the present invention; Figure 3 It is a schematic diagram of the structure of the groove body on the fairing body of the present invention; Figure 4 It is a schematic structural diagram of a protruding stopper on a payload adapter of the present invention; Figure 5 It is a schematic diagram of the position setting of the horizontal push separation mechanism of the present invention.

[0024] The above drawings include the following reference numerals: 10. Fairing body; 11. First cover flap; 12. Second cover flap; 13. Groove body; 14. Mounting hole for longitudinal separation unlocking device; 15. Push separation mechanism; 20. Payload adapter; 21. Protruding limiter; 22. Roll limiter. DETAILED DESCRIPTION

[0025] 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.

[0026] like Figure 1-Figure 4 As shown, a launch vehicle fairing includes: a fairing body 10 connected to a payload adapter 20. The outer wall of the payload adapter 20 is provided with a protruding stopper 21, and the bottom of the inner wall of the fairing body 10 has a groove body 13 arranged around the protruding stopper 21, and the groove body 13 is plugged and matched with the protruding stopper 21. The fairing body 10 includes no less than two cover flaps; adjacent cover flaps are fixedly connected in the longitudinal direction by a longitudinal separation unlocking device. By mechanically connecting the transverse separation surface and the payload adapter 20 after the flap cover is buckled, a pyrotechnic unlocking device is implemented on the connection surface, thereby improving the connection reliability.

[0027] After the longitudinal separation unlocking device is unlocked, the fairing is separated into multiple flaps and the lateral connection unlocking is achieved at the same time. The separation after lateral unlocking can be achieved by pushing the pushing device, eliminating the connection unlocking device of the lateral separation surface and improving the separation reliability.

[0028] In this embodiment, the fairing body 10 includes a first cover flap 11 and a second cover flap 12; a first arc-shaped groove body half is provided at the bottom of the inner side wall of the first cover flap 11; and a second arc-shaped groove body half is provided at the bottom of the inner side wall of the second cover flap 12. The first groove body half and the second groove body half are combined to form a groove body 13.

[0029] The first cover petal 11 and the second cover petal 12 are both provided with a longitudinal separation unlocking device installation hole 14 for installing the longitudinal separation unlocking device. In this embodiment, the longitudinal separation unlocking device is installed by using an explosive bolt.

[0030] Through the engagement of the semicircular groove body 13 of the valve cover and the protruding limit body 21 of the payload adapter 20, it acts as a slide rail during separation; at the same time, during the separation process of the valve cover and the payload adapter 20, it can limit the fairing from falling in a non-designed direction after separating into the valve cover, preventing the rocket or satellite product from being scratched after abnormal separation, thereby improving the separation safety.

[0031] Preferably, a launch vehicle fairing further comprises a roll stopper 22 for preventing the fairing body 10 from axially rotating relative to the payload adapter 20. The roll stopper 22 is arranged on the side where the protruding stopper 21 and the groove body 13 are connected, and the roll stopper 22 is fixedly connected to the outer side wall of the payload adapter 20.

[0032] After the fairing body 10 is closed, mechanical clamping is achieved under the combination of the groove body 13 and the protruding limit body 21 to limit the axial and radial freedom of the fairing. At the same time, under the action of the roll limiter 22, the roll freedom of the fairing body 10 can be constrained, thereby achieving effective limit fixation of the fairing body 10 and the payload adapter 20.

[0033] Preferably, the vertical cross section of the protruding stopper 21 is rectangular; the groove body 13 and the protruding stopper 21 are plugged and matched in the lateral direction of the fairing body 10. The protruding stopper 21 of this structure has good structural strength, and can realize the horizontal push separation of the unlocked cover flap and the payload adapter 20 in the radial direction of the launch vehicle.

[0034] When the launch vehicle fairing is assembled, the longitudinal separation unlocking device is installed after the cover flaps are combined to form the fairing body 10. In the process of the cover flaps being combined to form the fairing body 10, the groove body 13 is plugged and matched with the protruding limiter 21 to enclose the payload adapter 20 between the cover flaps.

[0035] Preferably, a launch vehicle fairing also includes a horizontal push separation mechanism 15 for pushing the cover flap away from the payload adapter 20. The horizontal push separation mechanism 15 includes a plurality of groups of pushing devices having the same number as the cover flaps. In other words, each cover flap is equipped with a group of pushing devices. At the same time, in order to ensure the effective horizontal push of the cover flap, it is necessary to ensure the synchronization of the actuation of the pushing devices in the same group, so as to avoid the cover flap turning over and causing the groove body 13 and the protruding limit body 21 to get stuck.

[0036] Preferably, the pushing device is a pneumatic actuating device or a separation spring actuating device, including an actuating cylinder and an actuating rod, wherein the actuating rod is connected to the actuating cylinder and can be extended or shortened under the action of the actuating cylinder.

[0037] In this embodiment, the fairing body 10 includes a first cover flap 11 and a second cover flap 12 that can be buckled into the fairing body 10. The horizontal push separation mechanism 15 includes a first push device, a second push device, a third push device and a fourth push device, a total of 4 push devices, and the first push device, the second push device, the third push device and the fourth push device all include an actuating cylinder and an actuating rod.

[0038] Based on the same inventive concept, the present invention also provides a launch vehicle fairing design method, which is used to design the launch vehicle fairing, and comprises: Step S1, designing a groove body 13 at the bottom of the inner wall of the fairing body 10.

[0039] Step S2 , designing a protruding stopper 21 that can match the groove body 13 on the outer side wall of the payload adapter 20 according to the structure and size of the groove body 13 .

[0040] Step S3, designing the size and position of the rolling limiter 22 according to the intersection position of the butt joint surface between the protruding limiter 21 and the grooved body 13.

[0041] Step S4, determining the minimum horizontal push distance of the cover flap according to the combined size of the protruding limiting body 21 and the groove body 13.

[0042] Among them, the calculation formula for the minimum horizontal push distance of the cover flap is: ; In the formula, is the minimum horizontal push distance of the cover flap; R is the outer diameter of the protruding limiter 21; and H is the radial depth of the groove body 13 that coincides with the protruding limiter 21.

[0043] Step S5, determining the minimum actuating stroke of the horizontal push separation mechanism 15 according to the minimum horizontal push distance of the cover flap.

[0044] Step S6, designing the length of the actuator and the push rod of the horizontal push separation mechanism 15 and the length of the exposed longitudinal separation surface of the fairing according to the minimum actuating stroke of the horizontal push separation mechanism 15 and taking into account the safety margin.

[0045] Step S7, design the total separation impulse of the actuator according to the valve cover mass and the lateral separation pushing speed requirements.

[0046] Specifically, when designing the total separation impulse of the actuator, the total separation impulse of the actuator meets the requirement of the minimum separation speed when pushing the fairing valve cover to completely separate from the rocket body.

[0047] Step S8, matching the total separation impulse by the number of actuators, the length of a single actuator, the inner diameter of the cylinder and the average pressure of the internal air pressure.

[0048] Step S9, determining the layout position of the actuator through the center of mass, inertia and geometric characteristics of the fairing valve cover, thereby completing the launch vehicle fairing design.

[0049] Specifically, when the total separation impulse is matched by the number of actuators, the length of a single actuator, the inner diameter of the cylinder and the average pressure of the internal air pressure, the thrust impulse moments of the actuators above and below the centroid plane of the fairing valve cover are equal.

[0050] In this embodiment, if Figure 5 As shown, actuators A1 and A2 are the same actuator A, and actuators A1 and A2 are designed symmetrically with respect to the axial plane of the rocket passing through the longitudinal separation plane; actuators B1 and B2 are the same actuator B, and actuators B1 and B2 are designed symmetrically with respect to the axial plane of the rocket passing through the longitudinal separation plane.

[0051] At the same time, the thrust impulse moments of the actuators above and below the centroid plane of the fairing valve cover are equal, and the total impulse of multiple actuators meets the minimum separation speed requirement when pushing the fairing valve cover to completely separate from the rocket body. The formula is as follows: Pa_avg*Sa*Ta*La=Pb_avg*Sb*Tb*Lb; (2*Pa_avg*Sa*Ta+2*Pb_avg*Sb*Tb) / Mf≥Vmin; Among them: Pa_avg and Pb_avg are the average pressures of actuator A and actuator B during the pushing process respectively; Sa and Sb are the pressure action cross-sectional areas of actuator A and actuator B respectively; Ta and Tb are the pressure action time of actuator A and actuator B respectively; La and Lb are the actuating force arm lengths of actuator A and actuator B respectively; Mf is the structural mass of the valve cover; Vmin is the required minimum separation speed of the valve cover.

[0052] 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.

[0053] 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.

[0054] 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.

[0055] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A launch vehicle fairing, characterized in that: include: A fairing body connected to a payload adapter; the outer side wall of the payload adapter is provided with a protruding stopper; The bottom of the inner side wall of the fairing body has a groove body arranged around the protruding limit body; the groove body is plug-fitted with the protruding limit body; the fairing body includes no less than two cover flaps; adjacent cover flaps are fixedly connected in the longitudinal direction by a longitudinal separation unlocking device.

2. The launch vehicle fairing according to claim 1, characterized in that: The fairing body comprises a first cover flap and a second cover flap; a first arc-shaped groove body half portion is arranged at the bottom of the inner side wall of the first cover flap; a second arc-shaped groove body half portion is arranged at the bottom of the inner side wall of the second cover flap.

3. The launch vehicle fairing according to claim 2, characterized in that: It also includes a roll limiter for preventing the fairing body from axially rotating relative to the payload adapter; the roll limiter is arranged on the side of the connection between the protruding limiter and the groove body; the roll limiter is fixedly connected to the outer side wall of the payload adapter.

4. The launch vehicle fairing according to claim 1, characterized in that: The vertical cross section of the protruding limiting body is a rectangle; the groove body and the protruding limiting body are plug-fitted in the horizontal direction of the fairing body.

5. The launch vehicle fairing according to claim 1, characterized in that: When the launch vehicle fairing is assembled, the cover petals are combined to form the fairing body and then the longitudinal separation unlocking device is installed; Wherein, during the process of closing the cover flaps to form the fairing body, the groove body is plugged into and matched with the protruding limiting body to enclose the payload adapter between the cover flaps.

6. The launch vehicle fairing according to any one of claims 1 to 5, characterized in that: Also included is a push-to-release mechanism for pushing the shroud petal away from the payload adapter.

7. A launch vehicle fairing design method, characterized in that: Used to design the launch vehicle fairing according to claim 6, comprising: A groove body is designed at the bottom of the inner wall of the fairing body; According to the structure and size of the groove body, a protruding stopper that can match the groove body is designed on the outer side wall of the payload adapter; The size and position of the rolling limiter are designed by the intersection position of the butt joint surface of the protruding limiter and the grooved body; Determine the minimum horizontal push distance of the cover flap according to the combined size of the protruding limiter and the groove body; The minimum actuating stroke of the horizontal push separation mechanism is determined according to the minimum horizontal push distance of the cover flap; According to the minimum actuation stroke of the horizontal push separation mechanism and considering the safety margin, the length of the actuator and push rod of the horizontal push separation mechanism and the length exposed from the longitudinal separation surface of the fairing are designed; Design the total separation impulse of the actuator according to the valve cover mass and lateral separation pushing speed requirements; The total separation impulse is matched by the number of actuators, the length of a single actuator, the inner diameter of the cylinder and the average pressure of the internal gas pressure; The layout position of the actuator is determined by the center of mass, inertia and geometric characteristics of the fairing flap, thereby completing the design of the launch vehicle fairing.

8. The launch vehicle fairing design method according to claim 7, characterized in that: The calculation formula for the minimum horizontal push distance of the cover flap is: ； In the formula, is the minimum horizontal push distance of the cover flap; R is the outer diameter of the protruding limiter; H is the radial depth of the groove body that overlaps with the protruding limiter.

9. The launch vehicle fairing design method according to claim 7, characterized in that: When the total separation impulse of the actuator is designed, the total separation impulse of the actuator meets the requirement of the minimum separation speed when the fairing valve cover is pushed to completely separate from the arrow body.

10. The launch vehicle fairing design method according to claim 7, characterized in that: When the total separation impulse is matched by the number of actuators, the length of a single actuator, the inner diameter of the cylinder and the average pressure of the internal air pressure, the thrust impulse moments of the actuators above and below the centroid plane of the fairing valve cover are equal.

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