Unmanned aerial vehicle booster with spherical convergent inclined spray pipe

Abstract

The utility model discloses an unmanned aerial vehicle booster with a spherical convergent inclined spray pipe. The unmanned aerial vehicle booster comprises a combustion chamber, charge filled in an inner cavity of the combustion chamber, a front top cover assembly packaged at the front end of the combustion chamber, a spray pipe assembly arranged at the rear end of the combustion chamber and a sealing cover packaged at the rear end of the spray pipe assembly. The spray pipe assembly comprises a semispherical spray pipe front section, an inclined spray nozzle with an opening connected to the spherical surface of the semispherical spray pipe front section, and a throat liner arranged at the front end opening of the inclined spray nozzle. An annular connecting table with threads is arranged on the outer edge of the front end of the hemispherical spray pipe front section, and the spray pipe assembly is in threaded connection with the rear end of the combustion chamber through the annular connecting table. After the unmanned aerial vehicle booster and the unmanned aerial vehicle are fixed, the thrust line of the inclined nozzle passes through the gravity center of the unmanned aerial vehicle. The booster of the unmanned aerial vehicle is simple to process and high in initial peak value.

Description

Technical Field

[0001] The utility model relates to a drone booster with a spherical convergent inclined nozzle, belonging to the technical field of drone boosters. Background Art

[0002] Drone boosters often use a frustum-shaped interface placed under the fuselage cover and at a certain angle with the fuselage to ensure that the thrust line of the booster passes through the center of gravity of the drone. This installation method occupies a large space and is difficult to achieve boxed launch. The inclined nozzle booster can make the fuselage parallel to the booster shell, thus reducing space occupation. However, when using a conical or irregular convergent section nozzle, there are problems such as high processing difficulty and high peak ratio. At the same time, to adapt to special environments such as desert areas in some applications, the working temperature of the booster reaches extremely high temperatures (above 70°C), resulting in serious erosion combustion, high thrust peaks, and inability to meet the requirements for stable takeoff of the drone. Content of the Utility Model

[0003] The purpose of the utility model is to provide a drone booster with a spherical convergent inclined nozzle to solve the deficiencies of the inclined nozzle structure of traditional drone boosters, such as high processing difficulty and high peak ratio.

[0004] The purpose of the utility model is achieved through the following technical solutions:

[0005] A drone booster with a spherical convergent inclined nozzle of the utility model includes a combustion chamber, a charge loaded in the inner cavity of the combustion chamber, a front top cover assembly encapsulated at the front end of the combustion chamber, a nozzle assembly arranged at the rear end of the combustion chamber, and a sealing cover encapsulated at the rear end of the nozzle assembly;

[0006] The nozzle assembly includes a hemispherical nozzle front section, an inclined nozzle connected to the spherical surface of the hemispherical nozzle front section with an opening, and a throat liner arranged at the front port of the inclined nozzle; a threaded annular connecting platform is arranged at the outer edge of the front end of the hemispherical nozzle front section, and the nozzle assembly is threadedly connected to the rear end of the combustion chamber through the annular connecting platform; after the drone booster is fixed to the drone, the thrust line of the inclined nozzle passes through the center of gravity of the drone.

[0007] A baffle and a buffer pad are arranged between the front end of the annular connecting platform of the hemispherical nozzle front section and the rear end face of the charge.

[0008] The inclined nozzle is threadedly connected to the hemispherical nozzle front section, and a sealing ring is placed at the threaded connection.

[0009] Advantageous Effects

[0010] The drone booster of the present utility model has an initial peak lower than that of a conventional conical nozzle, which can reduce the wall thickness of the metal shell during design, reduce the manufacturing cost, and reduce the negative mass during the takeoff of the drone. The drone booster of the present utility model has reduced ablation in the converging section of the nozzle, reducing the problem of tearing of the booster shell caused by nozzle ablation. Description of the Drawings

[0011] Figure 1 It is a schematic structural diagram of the drone booster of the present utility model;

[0012] Figure 2 It is a schematic structural diagram of the nozzle assembly in the drone booster of the present utility model;

[0013] In the figure, 1 - front top cover assembly, 2 - combustion chamber, 3 - charge, 4 - charge baffle, 5 - buffer pad, 6 - nozzle assembly, 7 - sealing cover, 8 - front section of hemispherical nozzle, 9 - throat liner, 10 - sealing ring, 11 - inclined nozzle. Detailed Embodiment

[0014] The content of the present utility model will be further described below in conjunction with the drawings and embodiments.

[0015] Embodiment

[0016] As Figure 1 shown, a drone booster with a spherical converging inclined nozzle of the present utility model includes a combustion chamber 2, a charge 3 loaded in the inner cavity of the combustion chamber 2, a front top cover assembly 1 encapsulated at the front end of the combustion chamber 2, a nozzle assembly 6 arranged at the rear end of the combustion chamber 2, and a sealing cover 7 encapsulated at the rear end of the nozzle assembly 6;

[0017] As Figure 2 shown, the nozzle assembly 6 includes a front section 8 of a hemispherical nozzle, an inclined nozzle 11 connected to the spherical surface of the front section 8 of the hemispherical nozzle by an opening, and a throat liner 9 arranged at the front port of the inclined nozzle 11; a threaded annular connecting platform is arranged at the outer edge of the front end of the front section 8 of the hemispherical nozzle, and the nozzle assembly 6 is threadedly connected to the rear end of the combustion chamber 2 through the annular connecting platform; after the drone booster is fixed to the drone, the thrust line of the inclined nozzle 11 passes through the center of gravity of the drone.

[0018] A charge baffle 4 and a buffer pad 5 are arranged between the front end of the annular connecting platform of the front section 8 of the hemispherical nozzle and the rear end face of the charge 3.

[0019] The inclined nozzle 11 is threadedly connected to the front section 8 of the hemispherical nozzle, and a sealing ring 10 is placed at the threaded connection.

[0020] The boost rocket engine obtained from the embodiment is applied to a certain type of unmanned aerial vehicle. The propellant charge 3 is a KPT propellant grain with a charge length of 248 mm, an outer diameter of 116 mm, and an inner diameter of 10.5 mm. The diameter of the booster is 128 mm. The included angle between the thrust line of the inclined nozzle 11 and the axis of the combustion chamber 2 is 26°. When operating at 71 °C, the thrust peak ratio of the booster is 1.08 and the specific impulse is 2086.5 N·s, which is higher than the theoretical specific impulse of this propellant.

[0021] The boost rocket engine obtained from the embodiment is applied to a certain type of unmanned aerial vehicle. The propellant charge 3 is a KPT propellant grain with a charge length of 335 mm, an outer diameter of 100 mm, and an inner diameter of 16 mm. The diameter of the booster is 110 mm. The included angle between the thrust line of the inclined nozzle 11 and the axis of the combustion chamber 2 is 15°. When operating at 71 °C, the thrust peak ratio of the booster is 1.15 and the specific impulse is 2100.4 N·s, which is higher than the theoretical specific impulse of this propellant.

Claims

1. A UAV booster with a spherical convergent oblique nozzle, comprising a combustion chamber, a charge filled in the inner cavity of the combustion chamber, a front top cover assembly encapsulated at the front end of the combustion chamber, a nozzle assembly arranged at the rear end of the combustion chamber, and a sealing cover encapsulated at the rear end of the nozzle assembly; Its characteristics are: The nozzle assembly comprises a hemispherical nozzle front section, an inclined nozzle with an opening connected to the spherical surface of the hemispherical nozzle front section, and a throat liner arranged at the front end of the inclined nozzle; A threaded annular connecting platform is provided at the outer edge of the front end of the hemispherical nozzle front section, and the nozzle assembly is connected to the rear end thread of the combustion chamber through the annular connecting platform; after the UAV booster is fixed to the UAV, the thrust line of the inclined nozzle passes through the center of gravity of the UAV.

2. The UAV booster with a spherical convergent oblique nozzle as claimed in claim 1, characterized in that: A medicine baffle and a buffer pad are arranged between the front end of the annular connecting platform of the front section of the hemispherical nozzle and the rear end surface of the medicine charge.

3. The UAV booster with a spherical convergent oblique nozzle as claimed in claim 1 or 2, characterized in that: The inclined nozzle is connected to the front section of the hemispherical nozzle through threads, and a sealing ring is placed at the threaded connection.

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