Gas port regulation apparatus and method for solid rocket engine

Abstract

The application discloses a gas nozzle adjusting device and method for a solid rail control engine, and the gas nozzle adjusting device is used to adjust the angle of the gas nozzle based on the engine cabin body, improve the position precision of the thrust axis of the rail control engine, and realize the accurate control of the rail control engine. The structure comprises a nozzle, a connecting flange, a base, a spherical column, an end cover, a positioning tool, a positioning core rod, a cabin body, an O-shaped ring, a fastening screw, a fixing screw and a positioning pin. The layout form is shown in the drawings, the nozzle of the rail control engine is fixed with the connecting flange through threads, the positioning tool is positioned with the cabin body through two positioning pins, two fixing screws are used for fixing, the positioning tool and the positioning core rod ensure that the angle of the gas nozzle is adjusted in place, and the connecting flange, the base and the end cover are fixed with the spherical column through the fastening screw.

Description

Technical Field

[0001] This invention relates to a gas nozzle adjustment device, and more particularly to a gas nozzle adjustment device and method for a solid rocket motor. Background Technology

[0002] Solid rocket motors (SRMs) are used for attitude or orbit control of aircraft. They utilize the lateral ejection of exhaust gases generated during engine operation to obtain lateral thrust acting on the aircraft, thereby generating maneuvering control force or torque. The accuracy of the thrust axis position of a SRM is a crucial indicator for precise thrust control. In engineering applications, due to manufacturing and assembly errors, the exhaust nozzle angle of SRMs often deviates significantly from the nominal thrust axis. This makes it impossible to guarantee thrust control accuracy during operation, thus limiting the practical application capabilities of SRMs.

[0003] To address the issue that the gas valve cannot be adjusted after assembly, resulting in significant offset of the thrust axis of the rail control engine and affecting its actual operating status, it is urgent to develop an adjustment device that can adjust the gas valve nozzle angle to meet the high-precision thrust control requirements of the rail control engine. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a gas nozzle adjustment device for solid rocket motors. This solves the problem that the gas valve cannot adjust the gas nozzle angle after assembly, and that the positional accuracy of the thrust axis of the rocket motor is low, which affects the practical application capability of the rocket motor.

[0005] The technical solution of this invention is:

[0006] A gas nozzle adjustment device for a solid rocket motor includes a nozzle, a connecting flange, a connecting seat, a spherical column, a positioning fixture, a positioning mandrel, a housing, and fastening screws. The nozzle is fixedly connected to the housing, the connecting flange is threaded to the outer arm of the nozzle, the fastening screws pass through the connecting seat and are threaded to the connecting flange, and the spherical column is spherically hinged to the spherical mounting chamber of the connecting seat. The positioning fixture is detachably connected to the housing. The positioning mandrel can be inserted from the inner hole of the positioning fixture into the inner hole of the spherical column to adjust the outlet angle of the spherical column.

[0007] Optionally, the connecting seat includes a base and an end cap. The surface of the base facing the end cap is, from the center outward, a first annular surface, a stepped surface, and a second annular surface. The stepped surface extends along the axis of the nozzle. The first and second annular surfaces are perpendicular to the axis of the nozzle. The two ends of the stepped surface are connected to the first and second annular surfaces, respectively. The end face of the end cap 5 facing the base 3 is adapted to the base.

[0008] Optionally, the positioning fixture and the cabin are detachably connected by fixing screws and positioning pins. The cabin has high-precision positioning pin holes. The positioning pins pass through the positioning fixture and are inserted into the positioning pin holes. The fixing screws pass through the positioning fixture and are threadedly connected to the cabin.

[0009] Optionally, two positioning pins are provided, and the two positioning pins are arranged diagonally around the axis of the nozzle.

[0010] Optionally, the connecting flange is fixed to the nozzle by a threaded connection.

[0011] Optionally, a sealing groove is machined on the base, and an O-ring sealing structure is used between the base and the nozzle and the spherical column to achieve a pneumatic seal between the nozzle adjustment device and the engine nozzle. Specifically, two O-rings are provided: one O-ring is connected to the surface of the spherical mounting chamber of the base, and the other O-ring is connected to the end face of the base 3 facing the nozzle.

[0012] Optionally, the positioning fixture is positioned to the cabin by two positioning pins and fixed by two fixing screws.

[0013] Optionally, positioning fixtures and positioning mandrels can be used to adjust the gas nozzle angle of the spherical column, thereby improving the positional accuracy of the thrust axis of the rail-controlled engine.

[0014] Optionally, the connecting flange, base, and end cap are secured by circumferentially distributed fastening screws after the spherical column is positioned.

[0015] Optionally, the connecting flange, base, spherical column, and end cap may be made of high-temperature resistant and high-hardness metal materials.

[0016] A method for adjusting the gas nozzle of a solid rocket motor, using any of the above-described gas nozzle adjustment devices for solid rocket motors, comprising:

[0017] S1: Connect the connecting flange to the nozzle, and assemble the connecting flange, base, spherical column and end cap into place using fastening screws;

[0018] S2: Using the positioning pin holes on the hull as a reference, install two positioning pins diagonally. The positioning pins pass through the positioning fixture and are inserted into the positioning pin holes. Then, the fixing screws pass through the positioning fixture and are threadedly connected to the hull.

[0019] S3: Loosen the fastening screws until the spherical column can be freely adjusted, insert the positioning mandrel from the inner hole of the positioning fixture into the inner hole of the spherical column, and adjust the central axis of the inner hole of the spherical column to coincide with the central axis of the inner hole of the positioning fixture;

[0020] S4: Tighten the fastening screws;

[0021] S5: Remove the positioning mandrel, and then remove the fixing screws, positioning pins, and positioning fixtures in sequence.

[0022] Optionally, in step S3, multiple fastening screws are loosened sequentially.

[0023] Optionally, in step S4, the fastening screws are tightened symmetrically with a fixed torque.

[0024] In summary, this application includes at least the following beneficial technical effects:

[0025] This invention solves the problem that the gas nozzle angle cannot be adjusted after the gas valve is assembled, resulting in low position accuracy of the thrust axis of the rail-controlled engine. Compared with the prior art, the technical solution of this invention has the following advantages: it can achieve precise adjustment of the gas nozzle angle, and the space required for a single gas valve nozzle adjustment device is small, the structural weight is small, and the installation is flexible. Attached Figure Description

[0026] Figure 1 This is a schematic diagram illustrating the adjustment process of a gas nozzle adjustment device for a solid rocket motor according to the present invention.

[0027] Figure 2 for Figure 1 The right view;

[0028] Figure 3 a is a schematic diagram showing the adjusted state of a gas nozzle adjustment device for a solid rocket motor according to the present invention. Figure 3 b is Figure 3 The right view of a.

[0029] Explanation of reference numerals in the attached drawings: 1. Nozzle; 2. Connecting flange; 3. Base; 4. Spherical column; 5. End cap; 6. Positioning fixture; 7. Positioning mandrel; 8. Chamber; 9. O-ring; 10. Fastening screw; 11. Fixing screw; 12. Positioning pin. Detailed Implementation

[0030] The present invention will now be described in detail with reference to the accompanying drawings and embodiments, so that the advantages and features of the present invention can be more easily understood by those skilled in the art, thereby providing a clearer and more explicit definition of the scope of protection of the present invention.

[0031] Reference Figure 1 This is a schematic diagram illustrating the adjustment process of a gas nozzle adjustment device for a solid rocket motor according to the present invention. The adjustment device includes a nozzle 1, a connecting flange 2, a base 3, a spherical column 4, an end cap 5, a positioning fixture 6, a positioning mandrel 7, a housing 8, an O-ring 9, fastening screws 10, fixing screws 11, and positioning pins 12.

[0032] The chamber 8 is fixedly connected to the nozzle 1. The connecting flange 2 is sleeved on the outside of the nozzle 1 and threadedly connected to the nozzle 1. The fastening screws 10 pass through the end cap 5 and the base 3 in sequence and are threadedly connected to the connecting flange 2. The base 3 and the end cap 5 form a spherical mounting chamber at the position directly opposite the nozzle 1, and the spherical column 4 is located in the spherical mounting chamber.

[0033] Two O-rings 9 are provided. One O-ring 9 is connected to the spherical mounting chamber surface of the base 3 to seal the gap between the spherical column 4 and the base 3. The other O-ring 9 is connected to the end face of the base 3 facing the nozzle 1 to seal the gap between the end faces of the base 3 and the nozzle 1.

[0034] The surface of the base 3 facing the end cap 5 consists of a first annular surface, a stepped surface, and a second annular surface, arranged sequentially from the center outwards. The stepped surface extends along the axis of the nozzle 1, while the first and second annular surfaces are perpendicular to the axis of the nozzle 1. The two ends of the stepped surface are connected to the first and second annular surfaces, respectively. The end face of the end cap 5 facing the base 3 is fitted with the base, ensuring more precise alignment of the spherical surfaces of the base 3 and the end cap 5.

[0035] The specific nozzle adjustment process is as follows:

[0036] The connecting flange 2 is connected to the nozzle 1 via threads. Two O-rings 9 are installed into the base 3. Eight fastening screws 10 are used to sequentially fasten the connecting flange 2, base 3, spherical column 4, and end cap 5. Figure 1 The assembly method shown is used to assemble the parts in place.

[0037] Two high-precision positioning pin holes are machined diagonally on the cabin body 8 and the positioning fixture 6. Using the positioning pin holes on the cabin body 8 as a reference, two positioning pins 12 are installed diagonally to position the positioning fixture 6. Through the positioning of the positioning pins, the center axis of the inner hole of the positioning fixture 6 has a high positional accuracy with the cabin body 8 as a reference. Then, two fixing screws 11 are used to fix the positioning fixture 6 and the cabin body 8 together.

[0038] Loosen the eight fastening screws 10 in sequence until the nozzle angle of the spherical column 4 can be freely adjusted. Insert the positioning mandrel 7 into the inner hole of the spherical column 4 through the inner hole of the positioning fixture 6. The central axis of the inner hole of the spherical column 4 will then be adjusted to coincide with the central axis of the inner hole of the positioning fixture 6. Since the central axis of the inner hole of the positioning fixture 6 already has high positional accuracy, the central axis of the inner hole of the spherical column 4 that coincides with it will be adjusted to a high positional accuracy angle with the cabin 8 as the reference. That is, the gas nozzle angle is adjusted in place, and the positional accuracy of the thrust axis of the rail-controlled engine is improved.

[0039] After the gas nozzle angle is adjusted to the correct position, tighten the eight fastening screws 10 symmetrically with a fixed torque. After removing the positioning mandrel 7, dismantle the fixing screws 11, positioning pins 12, and positioning fixture 6 in sequence. The gas nozzle should now be in the correct position as shown below. Figure 2 As shown.

[0040] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A gas nozzle adjustment device for a solid rocket motor, characterized in that: Includes nozzle (1), connecting flange (2), connecting seat, spherical column (4), positioning fixture (6), positioning mandrel (7), cabin (8), and fastening screws (10); The nozzle (1) is fixedly connected to the cabin (8), the connecting flange (2) is connected to the outer wall of the nozzle (1), the fastening screw (10) passes through the connecting seat and is threadedly connected to the connecting flange (2), and the spherical column (4) is spherically hinged to the spherical mounting chamber of the connecting seat. The positioning fixture (6) is detachably connected to the cabin (8); the positioning mandrel (7) can be inserted from the inner hole of the positioning fixture (6) into the inner hole of the spherical column (4) to adjust the exit angle of the spherical column (4).

2. The gas nozzle adjustment device for a solid rocket motor according to claim 1, characterized in that: The connecting seat includes a base (3) and an end cap (5). The surface of the base (3) facing the end cap (5) from the center outward is a first annular surface, a stepped surface, and a second annular surface. The stepped surface extends along the axis of the nozzle (1). The first annular surface and the second annular surface are perpendicular to the axis of the nozzle (1). The two ends of the stepped surface are connected to the first annular surface and the second annular surface, respectively. The end face of the end cap (5) facing the base (3) is adapted to the base (3).

3. The gas nozzle adjustment device for a solid rocket motor according to claim 1, characterized in that: The positioning fixture (6) and the cabin (8) are detachably connected by fixing screws (11) and positioning pins (12). The cabin (8) has high-precision positioning pin holes. The positioning pins (12) pass through the positioning fixture (6) and are inserted into the positioning pin holes. The fixing screws (11) pass through the positioning fixture (6) and are threadedly connected to the cabin (8).

4. A gas nozzle adjustment device for a solid rocket motor according to claim 3, characterized in that: Two positioning pins (12) are provided, and the two positioning pins (12) are arranged diagonally around the axis of the nozzle (1).

5. A gas nozzle adjustment device for a solid rocket motor according to claim 2, characterized in that: The base (3) is provided with an O-ring (9) for sealing between itself and the spherical column (4) and between itself and the nozzle (1).

6. A gas nozzle adjustment device for a solid rocket motor according to claim 5, characterized in that: Two O-rings (9) are provided. One O-ring (9) is connected to the spherical mounting chamber surface of the base (3), and the other O-ring (9) is connected to the end face of the base (3) 3 facing the nozzle (1).

7. A gas nozzle adjustment device for a solid rocket motor according to claim 2, characterized in that: The connecting flange (2), base (3), spherical column (4), and end cap (5) are made of high-temperature resistant and high-hardness metal materials.

8. A method for adjusting the gas nozzle of a solid rocket motor, characterized in that: Using a gas nozzle adjustment device for a solid rocket motor as described in any one of claims 1-7, including S1: Connect the connecting flange (2) to the nozzle (1), and assemble the connecting flange (2), base (3), spherical column (4) and end cap (5) into place by fastening screws (10); S2: Using the positioning pin hole on the cabin (8) as a reference, install two positioning pins (12) diagonally. The positioning pins (12) pass through the positioning fixture (6) and are inserted into the positioning pin hole. Then, the fixing screw (11) passes through the positioning fixture (6) and is threadedly connected to the cabin (8). S3: Loosen the fastening screw (10) until the spherical column (4) can be freely adjusted, insert the positioning mandrel (7) from the inner hole of the positioning fixture (6) into the inner hole of the spherical column (4), and adjust the central axis of the inner hole of the spherical column (4) to coincide with the central axis of the inner hole of the positioning fixture (6); S4: Tighten the fastening screw (10); S5: Remove the positioning mandrel (7), and remove the fixing screw (11), positioning pin (12), and positioning fixture (6) in sequence.

9. A method for adjusting the gas nozzle of a solid rocket motor according to claim 8, characterized in that: In step S3, multiple fastening screws (10) are loosened in sequence.

10. A method for adjusting the gas nozzle of a solid rocket motor according to claim 8, characterized in that: In step S4, the fastening screws (10) are fastened symmetrically with a fixed torque.

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