Solid rocket engine nozzle throat diameter adjusting device

Abstract

The invention discloses a nozzle throat diameter adjusting device for a solid rocket engine. The nozzle throat diameter adjusting device comprises an air inlet channel heat insulation layer, an air inlet channel shell, a nozzle shell, a driving motor, a driving gear, an expansion section shell, an expansion section heat insulation layer, a static throat liner and a movable throat liner. Wherein the air inlet channel shell is connected with the spray pipe shell, the driving motor is fixed to the spray pipe shell and connected with the driving gear, the driving gear is meshed with the expansion section shell with a gear, the expansion section shell is meshed with the spray pipe shell through threads, and the expansion section shell, the expansion section heat insulation layer and the movable throat liner are fixed in a limiting fit mode. The static throat liner and the spray pipe shell are fixed in a limiting fit mode. The gear is driven by the driving motor to rotate, so that the expansion section shell is screwed in or screwed out, the movable throat liner and the expansion section heat insulation layer move axially, area change of a throat channel of the spray pipe is formed, adjustment of the throat diameter of the spray pipe is achieved, and the problems that the throat diameter of the spray pipe is difficult to adjust, and an adjusting device is complex are solved.

Description

Technical Field

[0001] The invention belongs to the field of aerospace propulsion, and in particular relates to a nozzle throat diameter regulating device for a solid rocket engine. Background Art

[0002] Compared with solid rocket engines with predetermined thrust, solid rocket engines with adjustable thrust can distribute propellant energy more reasonably, adjust the output thrust and working time in time according to the real-time needs of combat, achieve two different mission objectives of long-distance and long-term flight and rapid strike on targets, expand the scope of combat missions, and improve response capabilities.

[0003] The supersonic Laval nozzle of a solid rocket engine is not only the outlet of the high-temperature and high-pressure combustion gas in the combustion chamber, but also converts the thermal energy of the high-temperature combustion gas into kinetic energy to generate reaction thrust. By changing the size of the cross-sectional area of ​​the throat of the supersonic Laval nozzle, the outflow of the high-temperature combustion gas can be controlled to achieve the adjustment of the thrust size. The current methods of adjusting the thrust by changing the nozzle throat area through mechanical control methods mainly include throat plug type and pin plug type. The adjustment scheme is that the drive system installed in the combustion chamber support sleeve controls the throat plug to move forward and backward along the center axis of the engine. There are problems such as complex servo adjustment system, poor nozzle integration, large space occupancy and redundant mass, and easy ablation of the throat plug head, which brings great limitations to improving the performance of the propulsion system. Summary of the invention

[0004] The technical problem solved by the present invention is to provide a solid rocket engine nozzle throat diameter adjustment device to solve the problems of complex throat diameter adjustment system, poor nozzle integration, large space occupation and redundant mass.

[0005] In order to solve the above problems, the present invention provides a solid rocket engine nozzle throat diameter adjustment device, comprising an air inlet insulation layer, an air inlet shell, a nozzle shell, a drive motor, a drive gear, an expansion section shell, an expansion section insulation layer, a static throat liner, and a dynamic throat liner, wherein:

[0006] The inlet duct insulation layer and the expansion section insulation layer are respectively located on the inner surfaces of the inlet duct shell and the expansion section shell; the inlet duct shell and the nozzle shell are connected by shell flange fixing bolts and shell flange fixing nuts; the drive motor is fixed on the nozzle shell and connected to the drive gear; the drive gear and the expansion section shell with gears are meshed with each other; the expansion section shell and the nozzle shell are meshed with each other through threads; the expansion section shell, the expansion section insulation layer and the dynamic throat liner are fixed by limiting fit; the static throat liner and the nozzle shell are fixed by limiting fit.

[0007] Furthermore, a channel hole is provided on the flow-facing surface of the nozzle shell, and the opening area of ​​the channel hole is set according to the adjustment range of the throat diameter of the device.

[0008] Furthermore, an inlet housing sealing ring is provided between the inlet housing and the nozzle housing, and an expansion section housing sealing ring is provided between the expansion section housing and the nozzle housing. The expansion section housing sealing ring and the inlet housing sealing ring are used to form a sealed environment to prevent high-temperature and high-pressure fuel gas from entering the housing assembly gap.

[0009] Furthermore, the end face of the driving motor is 10 mm away from the end face of the housing flange fixing bolt.

[0010] Furthermore, the nozzle shell and the static throat liner are fixed by limiting, so as to prevent the static throat liner from being displaced and failing due to the pressure of the airflow.

[0011] Furthermore, the expansion section shell, the expansion section insulation layer and the dynamic throat liner are fixed by limiting to reduce axial force.

[0012] Furthermore, the air inlet duct insulation layer has a thickness of 5 mm and is made of EPDM rubber material.

[0013] Furthermore, the inner diameter of the air intake housing is 150 mm.

[0014] Furthermore, the contact surface flatness of the expansion section insulation layer and the dynamic throat liner is better than 0.01 mm, and the roughness is better than R0.8.

[0015] Furthermore, the air inlet housing, the nozzle housing and the expansion section housing are made of stainless steel; the expansion section insulation layer and the dynamic throat liner are made of molded carbon fiber material; and the static throat liner is made of high-strength graphite material.

[0016] Compared with the prior art, the advantages and beneficial effects of the present invention are:

[0017] (1) The present invention realizes axial movement by meshing the driving gear with the expansion section housing with the gear, which can amplify the torque and only requires a relatively small-power driving motor to realize rotation, thereby significantly reducing the space occupied and weight of the adjustment system;

[0018] (2) The present invention realizes continuous adjustment of the nozzle throat diameter within a certain range by coordinating different channel small hole areas on the nozzle shell flow surface and the channel areas after the dynamic throat liner moves at different distances, thereby providing a guarantee for continuous adjustment of the engine thrust;

[0019] (3) The present invention places a low-power drive motor on the nozzle housing, which has a simple drive structure, good overall nozzle integration, and a compact structure, which significantly reduces the complexity of the adjustment system. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1It is a cross-sectional view of the solid rocket engine nozzle throat diameter adjustment device of the present invention.

[0021] Figure 2 This is an appearance diagram of the solid rocket engine nozzle throat diameter adjustment device of the present invention.

[0022] Figure 3 This is an appearance diagram of the nozzle shell of the solid rocket engine nozzle throat diameter adjustment device of the present invention.

[0023] Figure 4 This is an appearance diagram of the expansion section shell of the solid rocket engine nozzle throat diameter adjustment device of the present invention.

[0024] Figure 5 It is a cross-sectional view of the solid rocket engine nozzle throat diameter adjustment device of the present invention under a certain throat diameter state.

[0025] Figure 6 The figure is a relationship diagram between different throat diameter openings and thrust of the solid rocket engine nozzle throat diameter adjustment device of the present invention.

[0026] Figure numerals: 1. Inlet duct insulation layer; 2. Inlet duct housing; 3. Housing flange fixing bolts; 4. Nozzle housing; 5. Housing flange fixing nuts; 6. Driving motor; 7. Driving gear; 8. Expansion section housing; 9. Expansion section insulation layer; 10. Expansion section housing sealing ring; 11. Inlet duct housing sealing ring; 12. Static throat liner; 13. Dynamic throat liner. DETAILED DESCRIPTION

[0027] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0028] Example:

[0029] The present invention provides a solid rocket engine nozzle throat diameter adjustment device, comprising an air inlet insulation layer (1), an air inlet housing (2), housing flange fixing bolts (3), a nozzle housing (4), a housing flange fixing nut (5), a drive motor (6), a drive gear (7), an expansion section housing (8), an expansion section insulation layer (9), an expansion section housing sealing ring (10), an air inlet housing sealing ring (11), a static throat liner (12), and a dynamic throat liner (13). Figure 1 This is a cross-sectional view of the solid rocket engine nozzle throat adjustment device. Figure 2 This is the appearance diagram of the solid rocket engine nozzle throat diameter adjustment device.

[0030] Wherein: the air inlet insulation layer (1) and the expansion section insulation layer (9) are respectively located on the inner surfaces of the air inlet shell (2) and the expansion section shell (8); the air inlet shell (2) and the nozzle shell (4) are connected by shell flange fixing bolts (3) and shell flange fixing nuts (5); the drive motor (6) is fixed to the nozzle shell (4) and connected to the drive gear (7); the drive gear (7) and the expansion section shell (8) with gears are meshed with each other; the expansion section shell (8) and the nozzle shell (4) are meshed with each other by threads; the expansion section shell (8), the expansion section insulation layer (9) and the dynamic throat liner (13) are fixed by limiting fit; the static throat liner (12) and the nozzle shell (4) are fixed by limiting fit.

[0031] The working principle of the nozzle throat diameter adjustment device is as follows: the driving motor (6) drives the driving gear (7) to rotate, thereby driving the expansion section housing (8), the expansion section insulation layer (9) and the dynamic throat liner (13) to move axially, thereby changing the throat diameter.

[0032] Figure 3 This is the appearance of the nozzle shell of the solid rocket engine nozzle throat adjustment device. Figure 4 The invention is an appearance diagram of the expansion section shell of a nozzle throat diameter adjustment device for a solid rocket engine. The thickness of the air inlet duct insulation layer (1) is 5 mm and is made of EPDM rubber material; the inner diameter of the air inlet duct shell (2) is 150 mm and is made of stainless steel; the shell flange fixing bolts (3) and the shell flange fixing nuts (5) are standard parts; the nozzle shell (4) and the expansion section shell (8) are made of stainless steel and are connected into one piece by the shell flange fixing bolts (3) and the shell flange fixing nuts (5), and an air inlet duct shell sealing ring (11) is provided between the two to form a sealing structure; the driving motor (6) The rotor is meshed with the driving gear (7) to form an integral body; the driving gear (7) is meshed with the tooth grooves on the outer edge of the expansion section housing (8); the gear on the inner surface of the nozzle housing (4) is meshed with the tooth grooves of the expansion section housing (8); the expansion section insulation layer (9) and the dynamic throat liner (13) are made of molded carbon fiber material, the flatness of the contact surfaces of the two are better than 0.01 mm, and the roughness is better than R0.8, and the two are connected to the expansion section housing (8) through a limit fit to form an integral body; the static throat liner (12) is made of high-strength graphite material, and is connected to the nozzle housing (4) through a limit fit to form an integral body.

[0033] Figure 5 This is a cross-sectional view of the solid rocket engine nozzle throat diameter adjustment device under a certain throat diameter state. Figure 6The present invention is a relationship diagram between different throat diameter openings and thrust of a solid rocket engine nozzle throat diameter adjustment device. During use, the expansion section shell (8), the expansion section heat insulation layer (9) and the dynamic throat liner (13) are first driven to a minimum throat diameter state using a drive motor (6), and then the upstream gas enters the nozzle flow channel. According to the relationship between different throat diameters and the rotation angle of the expansion section shell (8), the rotation angle of the drive motor (6) is accurately controlled by a program, thereby achieving accurate and rapid adjustment of the required nozzle throat diameter and thrust.

[0034] The contents not described in detail in this specification belong to the prior art known to those skilled in the art. It is obvious to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the present invention can be implemented in other specific forms without departing from the spirit or essential features of the present invention. Therefore, no matter from which point of view, the embodiments should be regarded as exemplary and non-restrictive, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims are included in the present invention.

Claims

1. A solid rocket engine nozzle throat diameter adjustment device, characterized in that: The nozzle throat diameter adjustment device comprises an air inlet insulation layer (1), an air inlet housing (2), a nozzle housing (4), a drive motor (6), a drive gear (7), an expansion section housing (8), an expansion section insulation layer (9), a static throat liner (12), and a dynamic throat liner (13); wherein: The air inlet heat insulation layer (1) and the expansion section heat insulation layer (9) are respectively located on the inner surfaces of the air inlet shell (2) and the expansion section shell (8); The air inlet housing (2) and the nozzle housing (4) are connected via housing flange fixing bolts (3) and housing flange fixing nuts (5); The driving motor (6) is fixed on the nozzle housing (4) and connected to the driving gear (7); The driving gear (7) is meshed with the expansion section housing (8) having a gear; The expansion section housing (8) and the nozzle housing (4) are meshed with each other via threads; The expansion section shell (8), the expansion section heat insulation layer (9) and the dynamic throat liner (13) are fixed by limiting fit; The static throat liner (12) and the nozzle housing (4) are fixed by limiting fit.

2. A solid rocket engine nozzle throat diameter adjustment device as claimed in claim 1, characterized in that: The flow-facing surface of the nozzle housing (4) is provided with a channel hole, and the opening area of ​​the channel hole is set according to the adjustment range of the throat diameter of the device.

3. A solid rocket engine nozzle throat diameter adjustment device as claimed in claim 1, characterized in that: An air inlet housing seal ring (11) is provided between the air inlet housing (2) and the nozzle housing (4), and an expansion section housing seal ring (10) is provided between the expansion section housing (8) and the nozzle housing (4). The expansion section housing seal ring (10) and the air inlet housing seal ring (11) are used to form a sealed environment to prevent high-temperature and high-pressure combustion gas from entering the housing assembly gap.

4. A solid rocket engine nozzle throat diameter adjustment device as claimed in claim 1, characterized in that: The end face of the driving motor (6) is 10 mm away from the end face of the housing flange fixing bolt (3).

5. A solid rocket engine nozzle throat diameter adjustment device as claimed in claim 1, characterized in that: The nozzle housing (4) and the static throat liner (12) are fixed by limiting, so as to prevent the static throat liner (12) from being displaced and failing due to the impact of airflow.

6. A solid rocket engine nozzle throat diameter adjustment device as claimed in claim 1, characterized in that: The expansion section shell (8), the expansion section heat insulation layer (9) and the dynamic throat liner (13) are fixed by limiting, so as to reduce the axial force.

7. A solid rocket engine nozzle throat diameter adjustment device as claimed in claim 1, characterized in that: The air inlet duct insulation layer (1) has a thickness of 5 mm and is made of EPDM rubber material.

8. A solid rocket engine nozzle throat diameter adjustment device as claimed in claim 1, characterized in that: The inner diameter of the air intake housing (2) is 150 mm.

9. A solid rocket engine nozzle throat diameter adjustment device as claimed in claim 1, characterized in that: The contact surface flatness of the expansion section insulation layer (9) and the dynamic throat liner (13) is better than 0.01 mm, and the roughness is better than R0.

8.

10. A solid rocket engine nozzle throat diameter adjustment device as claimed in claim 1, characterized in that: The air inlet housing (2), the nozzle housing (4) and the expansion section housing (8) are made of stainless steel; the expansion section insulation layer (9) and the dynamic throat liner (13) are made of molded carbon fiber material; and the static throat liner (12) is made of high-strength graphite material.

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