Booster for preventing thrust eccentricity

Abstract

The utility model belongs to the field of power system design, and particularly relates to a booster for preventing thrust eccentricity. An existing conventional booster is large in thrust eccentricity. The combustor comprises a front end cover, an ignition powder box, a front powder baffle, a combustion chamber barrel, a rear powder baffle, a spray pipe seat and a spray pipe which are sequentially and coaxially installed, the front end and the rear end of the combustion chamber barrel are provided with radial expansion parts and internal threads, and the front end cover and the spray pipe seat are installed on the structures in the radial expansion parts. The shaft sleeve is provided with a thread part axially close to the inside, a smooth wall shaft hole structure axially close to the outside and a limiting boss at the outermost end; the front explosive baffle is clamped on the stepped surface at the front end through an annular boss at the front end and is clamped through a front end cover, and an ignition box is fixed at the front end of the front explosive baffle; the rear medicine baffle is in threaded connection with the inner ring face of the spray pipe base, and the spray pipe base is in threaded connection with the combustion chamber barrel. And the thrust eccentricity is controlled within a relatively small range during working.

Description

Technical Field

[0001] The utility model belongs to the field of power system design, and in particular relates to a booster capable of preventing thrust eccentricity. Background Art

[0002] During the design, processing, and assembly of booster components, certain dimensional and geometric tolerances are present. During operation, the booster experiences uneven combustion and gas flow, as well as uneven nozzle ablation. These factors inevitably cause the booster to generate certain lateral forces, resulting in an offset and angle between the main thrust and the missile axis, causing thrust eccentricity in the booster. If this eccentricity reaches a certain level, it will affect the missile's stable control. This is especially true during on-orbit launches at low altitude, low speed, and low elevation angles. Excessive eccentricity can cause the missile to touch the ground, leading to launch failure.

[0003] Existing conventional boosters have significant thrust eccentricity. Using a maximum limit deviation algorithm, the thrust eccentricity generated by each component of the booster is uniformly oriented. The maximum deviation between the actual and designed axis of the booster can reach over 0.15°, or even higher. This often causes trajectory divergence after launch in civilian rockets, with flight trajectories, trajectories, and impact points exceeding certain limits, posing the risk of flight accidents. The main reasons are: 1. The numerous and complex structural components that contribute to booster thrust eccentricity are subject to large cumulative geometric and assembly tolerances; 2. Numerous non-metallic materials are used in the manufacturing of components, particularly the nozzle assembly. When these components are manufactured using non-metallic materials, the dimensional and geometric tolerances achieved through machining and molding are less precise than those achieved with metal components, further increasing thrust eccentricity; 3. The combustion gases generated during booster operation exhibit uneven flow; 4. When the high-temperature combustion gases flow through the nozzle, they cause uneven ablation of the nozzle throat liner and diffuser, preventing complete flow straightening. Utility Model Content

[0004] The utility model aims at the problem that the thrust eccentricity of the booster is large, and proposes a booster to prevent thrust eccentricity, comprising a front end cover, an ignition cartridge, a front baffle, a combustion chamber barrel, a rear baffle, a nozzle seat and a nozzle which are coaxially installed in sequence, wherein a charge column is provided in the combustion chamber barrel, and the combustion chamber barrel has radially expanded parts and internal threads at the front and rear ends, the front end cover and the nozzle seat are installed on a structure in the radially expanded part, and have an axially inner threaded part, an axially outer smooth-walled axial hole structure and a limiting boss at the outermost end; the front baffle is clamped on the front step surface by the front annular boss and is clamped by the front end cover to fix the ignition cartridge at the front end of the front baffle; the rear baffle is threadedly connected to the inner annular surface of the nozzle seat, the nozzle seat is threadedly connected to the combustion chamber barrel, and the nozzle adopts the smooth-walled axial hole structure to be sleeved and embedded in the nozzle seat.

[0005] Advantageously, the external thread of the front end cover is connected to the internal thread of the front end of the combustion chamber barrel, and the coaxiality is maintained by the smooth-walled axial hole structure, and the front baffle is squeezed through the end face.

[0006] Advantageously, the front baffle is an annular structure, the front end surface of the annular structure has a threaded hole for mounting the ignition cartridge, and the rear end has a first supporting lug arranged rearwardly along the outer circumference for accommodating the front end of the drug column.

[0007] Advantageously, the ignition cartridge is glued to the front end surface of the annular structure of the front baffle.

[0008] Advantageously, the rear medicine baffle is an annular structure, and has a second supporting ear piece arranged forward along the outer circumference at the front end for accommodating the rear end of the medicine column.

[0009] Advantageously, the nozzle seat has a stepped hole with internal threads at the front end and an annular hole surface inside the nozzle seat, which is clearance-matched with the annular axial surface of the nozzle, and the nozzle seat limits the conical part of the nozzle through the conical surface.

[0010] Advantageously, the grain is coaxial with the other structure.

[0011] Advantageously, the tubular charge is prepared by extrusion molding using a double-base propellant.

[0012] Beneficial effects: Thrust eccentricity is controlled within a relatively small range during operation. The maximum limit deviation algorithm is adopted, that is, the thrust eccentricity generated by each link of the booster is in one direction. The maximum deviation angle between the actual axis of the booster and the axis in the design state can be controlled within 0.1°, which can effectively control the flight trajectory, track and landing point of civilian rockets within the designated safe area to avoid flight accidents. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is a schematic diagram of the front half-section structure of the booster of the utility model;

[0014] Figure 2 Schematic diagram of the front end cover;

[0015] Figure 3 Schematic diagram of the nozzle seat;

[0016] Figure 4 This is the main view of the front baffle;

[0017] Figure 5 for Figure 4 AA section view;

[0018] Figure 6 This is the main view of the rear baffle;

[0019] Figure 7 for Figure 6 BB cross-sectional view;

[0020] Figure 8 Schematic diagram of the nozzle;

[0021] Figure 9 Schematic diagram of the end structure of the combustion chamber cylinder. DETAILED DESCRIPTION

[0022] like Figure 1-3 The booster for preventing thrust eccentricity of the present invention is mainly composed of a front end cover 1, an ignition cartridge 2, a front baffle 3, a charge column 4, a combustion chamber barrel 5, a rear baffle 6, a nozzle seat 7 and a nozzle 8. All the components are arranged on the axis of the booster and arranged from front to back along the axis.

[0023] Threaded connections are used between the front end cap 1 and the combustion chamber barrel 5, and between the combustion chamber barrel 5 and the nozzle holder 7. The outward-facing portion of the threaded section utilizes a plain-walled axial hole for socket connection. Both threads must have at least six threads. Grease is required during installation to ensure smooth assembly and disassembly of the threads and to provide an airtight seal within the combustion chamber. The socket depth is at least 5mm, using a base hole system with a preferred fit and clearance fit.

[0024] See also Figure 4-5 The front baffle plate 3 has an annular boss at its front end that snaps onto the stepped hole surface of the combustion chamber barrel 5. The front cover 1 is threadedly connected to the combustion chamber barrel 5 to axially limit and secure the annular boss. The front baffle plate 3 also has an annular structure that supports the charge column 4 and a first supporting tab 9 arranged rearward along the outer circumference. The ignition cartridge 2 is fixed to the front end of the annular structure of the front baffle plate 3 by screws or adhesive.

[0025] See also Figure 6-7 The rear baffle plate 6 is fixed to the inner annular surface of the nozzle seat 7 by screw threads. The rear baffle plate 7 has an annular structure for supporting the medicine column 4 and a second supporting ear piece 10 arranged forward along the outer circumference.

[0026] See also Figure 8-9 The nozzle 8 adopts a smooth-walled axial hole structure to be inserted into the nozzle seat 7, wherein the nozzle 8 has an annular axial surface 12, and the nozzle seat 7 has an annular hole surface 11. The sleeve depth is not less than 50 mm, and the sleeve is divided into two sections of transition fit, using the basic hole system for priority fit and clearance fit.

[0027] In one embodiment of the booster for preventing thrust eccentricity of the utility model, the nozzle 8 adopts a smooth-walled shaft hole structure to be inserted into the nozzle seat 7, the sleeve depth is 50mm, the sleeve is divided into two sections of transition fit, the front section sleeve hole and the shaft nominal diameter are 70mm, the base hole system is used for priority fit, the fit accuracy is H8 / f7, then the aperture is Shaft diameter The range of hole-shaft clearance is +0.030~+0.106mm, with a maximum clearance of +0.106mm. The nominal diameter of the rear sleeve hole and shaft is 48mm. The basic hole system is used for priority matching. The matching accuracy is H7 / h6, so the hole diameter is Shaft diameter The hole-axis clearance range is 0 to +0.041mm, with a maximum clearance of +0.041mm. The thrust eccentricity of the gas at the throat liner position caused by this clearance is up to 0.029°, and the thrust eccentricity is significantly reduced to far less than 0.1°.

Claims

1. A thrust booster for preventing thrust eccentricity, characterized in that: The invention comprises a front end cover (1), an ignition cartridge (2), a front baffle (3), a combustion chamber barrel (5), a rear baffle (6), a nozzle seat (7) and a nozzle (8) which are coaxially mounted in sequence. A powder column (4) is provided in the combustion chamber barrel (5). The combustion chamber barrel (5) has radially enlarged portions at both ends thereof and has internal threads. The front end cover (1) and the nozzle seat (7) are mounted on a structure in the radially enlarged portion and have an axially inner threaded portion, an axially inner threaded portion and an axially inner threaded portion. The front baffle plate (3) is clamped on the front stepped surface through the annular boss at the front end and is clamped by the front cover (1), and the ignition cartridge (2) is fixed at the front end of the front baffle plate (3); the rear baffle plate (6) is threadedly connected to the inner annular surface of the nozzle seat (7), the nozzle seat (7) is threadedly connected to the combustion chamber barrel (5), and the nozzle (8) is sleeved and embedded in the nozzle seat (7) using the smooth-walled shaft hole structure.

2. The thrust booster for preventing thrust eccentricity according to claim 1, characterized in that: The external thread of the front end cover (1) is connected to the internal thread of the front end of the combustion chamber barrel (5), and the coaxiality is maintained through the smooth-walled axial hole structure, and the front baffle plate (3) is squeezed through the end face.

3. The thrust booster for preventing thrust eccentricity according to claim 1, characterized in that: The front baffle (3) is an annular structure, the front end surface of the annular structure has a threaded hole for mounting the ignition cartridge (2), and the rear end has a first supporting lug (9) arranged rearward along the outer circumference for accommodating the front end of the drug column (4).

4. The thrust booster for preventing thrust eccentricity according to claim 3, characterized in that: The ignition cartridge (2) is glued to the front end surface of the annular structure of the front baffle plate (3).

5. The thrust booster for preventing thrust eccentricity according to claim 1, characterized in that: The rear medicine block (6) is an annular structure, and has a second supporting ear piece (10) arranged forward along the outer circumference at the front end, which is used to accommodate the rear end of the medicine column (4).

6. The thrust booster for preventing thrust eccentricity according to claim 1, characterized in that: The nozzle seat (7) has a stepped hole with an internal thread at the front end, and an annular hole surface (11) is provided inside the nozzle seat (7), which is clearance-matched with the annular axial surface (12) of the nozzle (8). The nozzle seat (7) limits the conical part of the nozzle (8) through the conical surface.

7. The thrust booster for preventing thrust eccentricity according to claim 1, characterized in that: The medicine column (4) is coaxial with other structures.

8. The thrust booster for preventing thrust eccentricity according to claim 1, characterized in that: The tubular grain is produced by compression molding of double-base propellant.

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