Separating device utilizing recoil acting force of solid rocket engine

Abstract

The utility model discloses a separating device utilizing recoil acting force of a solid rocket engine. The separating device comprises an engine head end socket, an engine end connecting assembly, a fixing assembly, an aircraft, an aircraft end connecting assembly, an aircraft and a separating assembly. The fixing assembly is installed at the other end of the engine head end socket, the connecting assembly is installed on the side, away from the engine head end socket, of the engine end connecting assembly, and the separating assembly is installed on the outer side of the engine end connecting assembly and the outer side of the aircraft end connecting assembly. The fuel gas separation device has the advantages that the fracture pin is broken through thrust of fuel gas, the broken fracture pin loses fixation and is separated, a solid rocket engine and an aircraft are separated from each other, the separation process is milder, and the fuel gas separation device is a brand-new separation mode.

Description

Technical Field

[0001] The utility model relates to the field of booster separation, in particular to a separation device utilizing the recoil force of a solid rocket engine. Background Art

[0002] The technical background of the boost separation system mainly involves the need for aircraft to fly in the atmosphere or in the outer space. Aircraft can be divided into aircraft, spacecraft, rockets and missiles. Aircraft such as balloons, airships, airplanes, etc., rely on the static buoyancy of air or the aerodynamic force generated by the relative movement of air to fly. Spacecraft, such as artificial satellites, manned spacecraft, space probes, space shuttles, etc., usually gain the necessary speed to enter space under the propulsion of carrier rockets, and then rely on inertia to make orbital motion similar to celestial bodies.

[0003] However, the installation and separation of boosters on existing aircraft are complex and time-consuming, which has become a technical problem that needs to be solved.

[0004] Most existing boost separation methods use explosive bolts for separation, which can easily cause damage to small aircraft. There is an urgent need for a gentle separation method. Utility Model Content

[0005] The technical problem to be solved by the utility model is to overcome the above-mentioned defects and provide a separation device utilizing the recoil force of a solid rocket engine.

[0006] In order to solve the above technical problems, the technical solution provided by the utility model is: a separation device using the recoil force of a solid rocket engine, comprising:

[0007] An engine head cover, one side of which is provided with an engine end connection assembly;

[0008] A fixing assembly, the fixing assembly being arranged on a side of the engine head cover away from the engine end connection assembly;

[0009] An aircraft, wherein an aircraft is arranged at one end of the engine head cover;

[0010] An aircraft end connection assembly is provided on one side of the aircraft close to the engine head cover;

[0011] A separation component is arranged on a side where the engine end connection component and the aircraft end connection component are close to each other.

[0012] As an improvement, the engine end connection assembly includes:

[0013] An engine end thrust skirt, wherein the engine end thrust skirt is fixedly connected to an end of the engine head cover close to the aircraft;

[0014] A gas channel, one end of which extends to an end of the engine head cover away from the aircraft, the gas channel passes through the engine head cover, and one end of which extends to the interior of the aircraft;

[0015] The outer sealing and heat-insulating coating is arranged on the outer side of the engine head cover.

[0016] As an improvement, the fixing assembly comprises:

[0017] A threaded hole, the threaded hole being provided at an end of the engine head cover away from the aircraft;

[0018] An inner thermal insulation coating is arranged inside the threaded hole.

[0019] As an improvement, the aircraft end connection assembly includes:

[0020] The aircraft end thrust skirt is fixedly connected to one end of the aircraft close to the engine head cover, and the aircraft end thrust skirt and the engine end thrust skirt are in contact with each other;

[0021] A flap-type separation buckle slot, wherein the engine head cover and the aircraft are both provided with a flap-type separation buckle slot on one side close to each other;

[0022] Gas through holes, a plurality of the gas through holes are arranged inside the petal-type separation buckle slot, and the gas through holes and the gas channel are interconnected.

[0023] As an improvement, the aircraft end separation assembly includes:

[0024] Petal-type separation buckles, a plurality of said petal-type separation buckles are plugged into the outer sides of the thrust skirt at the aircraft end and the thrust skirt at the engine end, said petal-type separation buckles are plugged into the inside of the petal-type separation buckle slots, and a plurality of said petal-type separation buckles are distributed in a ring shape;

[0025] A breaking pin hole, the breaking pin hole being provided on a side where the petal-type separation buckle and the aircraft are close to each other;

[0026] The blasting thrust surface, the two ends of the petal-type separation buckle close to each other on one side;

[0027] A flap-type separation buckle sealing structure, wherein the flap-type separation buckle sealing structure is arranged in the middle of one side where the flap-type separation buckles are close to each other;

[0028] A flap-type separation buckle locking surface, wherein the flap-type separation buckle locking surface is arranged on both sides of the inner part of the flap-type separation buckle sealing structure;

[0029] A breaking pin is arranged inside the breaking pin hole.

[0030] The advantages of the utility model compared with the prior art are: the utility model connects the solid rocket engine and the aircraft to each other by inserting the breaking pin into the inside of the breaking pin hole, and then inserting a plurality of annularly distributed petal-type separation buckles into the outer sides of the thrust skirt at the engine end and the thrust skirt at the aircraft end; when the solid rocket engine burns to the end, the gas enters the gas through hole through the gas channel, and the gas through hole guides the gas, and the gas guided by the gas through hole acts on the blasting thrust surface, and the breaking pin is broken by the thrust of the gas, and the breaking pin loses its fixation after being broken and is separated, and the thrust skirt at the engine end and the thrust skirt at the aircraft end are separated from each other, so that the solid rocket engine and the aircraft are separated from each other, and the separation process is gentler, and it is a new separation method. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 It is a stereogram of the utility model.

[0032] Figure 2 It is a schematic diagram of the engine end connection assembly of the utility model.

[0033] Figure 3 It is a schematic diagram of the aircraft end connection assembly of the utility model.

[0034] Figure 4 It is a schematic diagram of the fixing assembly of the utility model.

[0035] Figure 5 It is a schematic diagram of the fracture pin of the utility model.

[0036] As shown in the figure: 1. Engine head cover; 11. Fixing assembly; 1.0. Engine end connection assembly; 1.1. Gas channel; 1.2. Engine end thrust skirt; 1.3. Petal-type separation buckle slot; 1.5. Gas through hole; 1.6. Threaded hole; 1.7. Internal thermal insulation coating; 2. Petal-type separation buckle; 2.1. Fracture pin hole; 2.2. Explosive thrust surface; 2.3. Petal-type separation buckle sealing structure; 2.4. Petal-type separation buckle locking surface; 3. Fracture pin; 4. Aircraft end connection assembly; 4.2. Aircraft end thrust skirt; 5. Aircraft; 6. Separation assembly. DETAILED DESCRIPTION

[0037] Exemplary embodiments will be described in detail herein, examples of which are shown in the accompanying drawings. When the following description refers to the drawings, the same numbers in different drawings represent the same or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present disclosure. Instead, they are merely examples of devices consistent with some aspects of the present disclosure as detailed in the appended claims.

[0038] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0039] Example

[0040] like Figures 1 to 5 As shown, this embodiment proposes a separation device utilizing the recoil force of a solid rocket engine, including an engine head cover 1, an engine end connection assembly 1.0, a fixing assembly 11, an aircraft 5, an aircraft end connection assembly 4, an aircraft 5 and a separation assembly 6, wherein the engine head cover 1 is used to connect the solid rocket engine, an engine end connection assembly 1.0 for connecting to the aircraft is installed at one end of the engine head cover 1, a fixing assembly 11 for connecting to the solid rocket engine is installed at the other end of the engine head cover 1, an aircraft end connection assembly 4 for connecting the engine head cover 1 and the aircraft 5 is installed on the side of the engine end connection assembly 1.0 away from the engine head cover 1, and a separation assembly 6 for automatically separating the solid rocket engine and the aircraft 5 when the solid rocket engine burns to the end is installed on the outer sides of the engine end connection assembly 1.0 and the aircraft end connection assembly 4.

[0041] The engine end connection assembly 1.0 includes an engine end thrust skirt 1.2, a gas channel 1.1 and an outer sealing and thermal insulation coating 1.4. The engine end thrust skirt 1.2 is used for sealing to prevent leakage of recoil gas from affecting the separation assembly 6 and to transmit thrust. When the solid rocket engine burns to the end, the gas flows through the gas channel 1.1, enters the separation assembly 6, and pushes the petal-type separation buckle 2 to separate. The outer sealing and thermal insulation coating 1.4 is used for sealing to prevent leakage of recoil gas from affecting the separation assembly 6, and plays a role in heat insulation to prevent the gas from affecting other devices.

[0042] The fixing assembly 11 comprises a threaded hole 1.6 and an inner thermal insulation coating 1.7, wherein the threaded hole 1.6 is used for fixing the solid rocket engine, and the inner thermal insulation coating 1.7 is used for heat insulation.

[0043] The aircraft end connection assembly 4 includes an aircraft end thrust skirt 4.2, a flap-type separation buckle slot 1.3 and a gas through hole 1.5. The aircraft end thrust skirt 4.2 is used for sealing to prevent recoil gas leakage from affecting the separation assembly 6 and transmitting thrust. The flap-type separation buckle slot 1.3 is used to fix the flap-type separation buckle 2, and the gas through hole 1.5 is used to guide the gas to open the flap-type separation buckle 2.

[0044] The separation assembly 6 includes a flap-type separation buckle 2, a breaking pin hole 2.1, an explosive thrust surface 2.2, a flap-type separation buckle sealing structure 2.3, a flap-type separation buckle locking surface 2.4 and a breaking pin 3. The flap-type separation buckle 2 is used to connect the solid rocket engine and the aircraft 5. The breaking pin hole 2.1 is used to place the breaking pin 3, and the breaking pin 3 fixes the flap-type separation buckle 2 in the flap-type separation buckle slot 1.3 to connect the solid rocket engine to the aircraft 5. The gas led out of the gas channel 1.1 acts on the explosive thrust surface 2.2, and the breaking pin 3 is crushed by the thrust of the gas, so that the flap-type separation buckle 2 is separated, and the separation of the solid rocket engine and the aircraft 5 is completed. The flap-type separation buckle sealing structure 2.3 is used for sealing to prevent gas leakage from affecting the operation of the device. The breaking pin 3 is made of brittle material and breaks after being impacted by a large force, releasing the fixing effect, so that the flap-type separation buckle 2 is separated. The flap-type separation buckle locking surface 2.4 is used to fix the solid rocket engine to the aircraft 5.

[0045] The electrical components appearing in this article are all connected to an external main controller and 220V AC power, and the main controller can be a conventional known device that controls a computer, etc. The specific implementation method of the present disclosure omits the detailed description of known functions and known components. To ensure the compatibility of the equipment, the operating methods used are consistent with the parameters of marketed equipment.

[0046] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A separation device utilizing the recoil force of a solid rocket engine, characterized in that: include: An engine head cover (1), wherein an engine end connection assembly (1.0) is provided on one side of the engine head cover (1); A fixing assembly (11), wherein the fixing assembly (11) is arranged on a side of the engine head cover (1) away from the engine end connection assembly (1.0); An aircraft (5), wherein the aircraft (5) is arranged at one end of the engine head cover (1); An aircraft end connection assembly (4), wherein the aircraft (5) is provided with an aircraft end connection assembly (4) on a side close to the engine head cover (1); A separation component (6) is arranged on a side where the engine end connection component (1.0) and the aircraft end connection component (4) are close to each other.

2. A separation device using the recoil force of a solid rocket engine according to claim 1, characterized in that: The engine end connection assembly (1.0) comprises: An engine end thrust skirt (1.2), wherein the engine end thrust skirt (1.2) is fixedly connected to an end of the engine head cover (1) close to the aircraft (5); A gas channel (1.1), one end of the gas channel (1.1) extending to an end of the engine head cover (1) away from the aircraft (5), the gas channel (1.1) penetrating the engine head cover (1), and one end of the gas channel (1.1) extending to the interior of the aircraft (5); An outer sealing and heat-insulating coating (1.4) is arranged on the outside of the engine head cover (1).

3. The separation device using the recoil force of a solid rocket engine according to claim 1, characterized in that: The fixing assembly (11) comprises: A threaded hole (1.6), wherein the threaded hole (1.6) is provided at an end of the engine head cover (1) away from the aircraft (5); An inner heat-insulating coating (1.7), wherein the inner heat-insulating coating (1.7) is arranged inside the threaded hole (1.6).

4. The separation device using the recoil force of a solid rocket engine according to claim 2, characterized in that: The aircraft end connection assembly (4) comprises: An aircraft end thrust skirt (4.2), the aircraft end thrust skirt (4.2) being fixedly connected to one end of the aircraft (5) close to the engine head cover (1), the aircraft end thrust skirt (4.2) and the engine end thrust skirt (1.2) being in contact with each other; A flap-type separation buckle slot (1.3), wherein the engine head cover (1) and the aircraft (5) are both provided with a flap-type separation buckle slot (1.3) on one side where the engine head cover (1) and the aircraft (5) are close to each other; Gas through holes (1.5), a plurality of the gas through holes (1.5) are arranged inside the flap-type separation buckle slot (1.3), and the gas through holes (1.5) and the gas channel (1.1) are interconnected.

5. A separation device using the recoil force of a solid rocket engine according to claim 2 or 4, characterized in that: The aircraft end separation assembly (6) comprises: A petal-type separation buckle (2), wherein a plurality of the petal-type separation buckles (2) are plugged into the outer sides of the aircraft end thrust skirt (4.2) and the engine end thrust skirt (1.2), and the petal-type separation buckle (2) is plugged into the inside of the petal-type separation buckle slot (1.3), and the plurality of the petal-type separation buckles (2) are distributed in a ring shape; A breaking pin hole (2.1), the breaking pin hole (2.1) being provided on a side where the flap-type separation buckle (2) and the aircraft (5) are close to each other; The blasting thrust surface (2.2), the two ends of one side of the petal-type separation buckle (2) close to each other; A flap-type separation buckle sealing structure (2.3), wherein the flap-type separation buckle sealing structure (2.3) is arranged in the middle of one side where the flap-type separation buckles (2) are close to each other; Flap-type separation buckle locking surfaces (2.4), wherein the flap-type separation buckle locking surfaces (2.4) are arranged on both sides of the inside of the flap-type separation buckle sealing structure (2.3); A breaking pin (3), wherein the breaking pin (3) is arranged inside the breaking pin hole (2.1).

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