Metal rupture diaphragm structure and use method for liquid attitude and orbit control power system

Abstract

The present invention provides a metal rupture diaphragm structure for a liquid attitude and orbit control power system and a method for using the same, comprising a fixed diaphragm, a piston diaphragm, and a sealing ring. The piston diaphragm is provided with a groove in its circumference, and the sealing ring is assembled into the groove of the piston diaphragm. The piston diaphragm equipped with the sealing ring is installed in the fixed diaphragm, and the piston diaphragm and the fixed diaphragm are interference-fitted via the sealing ring. A first impact cone and a first rupture membrane are provided in the fixed diaphragm, and a second impact cone and a second rupture membrane are provided on the piston diaphragm. During the process of the piston diaphragm advancing in the fixed diaphragm, the first impact cone gradually approaches and ruptures the second rupture membrane, and the second impact cone gradually approaches and ruptures the first rupture membrane. The present invention amplifies the effect of the upstream pressure source through the impact cone structure and reduces the influence of the diaphragm scoring processing dispersion on the structural rupture pressure.

Description

Technical Field

[0001] The present invention relates to the field of aerospace attitude and orbit control power systems, and in particular to a rupture diaphragm structure for isolating a liquid propellant chamber from a downstream working chamber and a method for using the same. Background Art

[0002] The attitude and orbit control propulsion system (AOC) is a key subsystem of a spacecraft, providing control forces and torques for attitude stabilization and control, orbit transfer, and orbit correction during flight. It is widely used in satellites, spacecraft, missiles, launch vehicles, deep space probes, and other important spacecraft. It features fast response and easy control. AOC systems typically operate by using a booster system to provide pressure to the fuel tank, pushing the fuel into the AOC engine control valve at a specific pressure. When the control valve opens, the fuel enters the engine combustion chamber, reacts, and is ultimately ejected through the tail nozzle to generate thrust.

[0003] For certain attitude and orbit control propulsion systems requiring long-term on-orbit maintenance, as well as propulsion systems requiring long-term ground storage, propellant is typically stored in a propellant chamber, physically isolated from the downstream working chamber by an isolation structure. The presence of this isolation structure eliminates the need for all propellant-contacting components to be constructed from materials compatible with the propellant over a long period of time. This reduces system complexity, minimizes potential failure points during on-orbit or storage, and improves system reliability during this period.

[0004] The rupture diaphragm structure is a commonly used physical isolation structure in the above-mentioned system. Conventional rupture diaphragm structures generally directly engrave a groove structure on the metal diaphragm material, weakening the mechanical properties of the material. When the upstream propellant pressure increases, the groove of the rupture diaphragm exceeds the allowable stress and the structure is damaged, thereby removing the physical isolation between the propellant chamber liquid and the downstream working chamber.

[0005] The material of the above-mentioned conventional metal diaphragm is generally aluminum. Aluminum alloy is selected because the strength of aluminum alloy material is relatively weak. Under the same pressure, the notch of the aluminum alloy diaphragm does not need to be too deep, and a larger thickness of metal material can be retained at the weakest point of the notch. At the same time, considering that the notch is generally made by mechanical processing, there is a certain degree of dispersion in the depth of the processing. For the weaker aluminum alloy, the influence of the dispersion of the notch depth on its rupture pressure is relatively small.

[0006] However, the long-term storage performance of aluminum alloys is weaker than that of materials such as stainless steel and titanium alloys. The reason why conventional diaphragm materials do not choose hard metals such as titanium alloys or stainless steel is that they have higher strength and the thickness at which structural damage occurs under the same pressure is thinner. Therefore, the metal thickness margin left after notching is very small, or even only a few strands of thickness. At this time, if the machining notch dispersion is too deep, it is easy to directly penetrate the diaphragm. If the notch dispersion is too shallow, it is easy to cause a sharp increase in the diaphragm rupture pressure dispersion. If the problem of excessive rupture pressure dispersion of high-strength metals can be solved, hard metals such as titanium alloys or stainless steel will be a better choice for attitude and orbit control power systems with long-term storage requirements. Summary of the Invention

[0007] In view of the defects in the prior art, the purpose of the present invention is to provide a metal rupture diaphragm structure and a method of use for a liquid attitude and orbit control power system.

[0008] According to the present invention, a metal rupture diaphragm structure for a liquid attitude and orbit control power system includes a fixed diaphragm, a piston diaphragm, and a sealing ring, wherein:

[0009] A groove is provided on the circumference of the piston diaphragm, and the sealing ring is assembled into the groove of the piston diaphragm;

[0010] The piston diaphragm equipped with a sealing ring is installed in the fixed diaphragm, and the piston diaphragm and the fixed diaphragm are interference-fitted through the sealing ring;

[0011] A first impact cone and a first rupture membrane are provided in the fixed diaphragm, and a second impact cone and a second rupture membrane are provided on the piston diaphragm;

[0012] During the process of the piston diaphragm advancing in the fixed diaphragm, the first impact cone gradually approaches and impacts the second rupture membrane, and the second impact cone gradually approaches and impacts the first rupture membrane.

[0013] Preferably, the fixed diaphragm is connected to the upstream propellant chamber and the downstream propellant pipeline respectively. When the first rupture membrane and the second rupture membrane are both broken, the upstream propellant chamber and the downstream propellant pipeline are connected.

[0014] Preferably, the piston diaphragm is propelled within the fixed diaphragm under the pressure of the upstream propellant chamber.

[0015] Preferably, the upstream medium of the piston diaphragm is a liquid propellant.

[0016] Preferably, the first impact cone and the second impact cone are arranged facing each other.

[0017] Preferably, the length of the first striker is smaller than the length of the second striker.

[0018] Preferably, the first rupture membrane and the second rupture membrane are processed with notch grooves to make rupture controllable.

[0019] Preferably, the cross section of the notched groove is triangular, arc-shaped or trapezoidal.

[0020] Preferably, the first impact cone or the second impact cone is in the shape of a cylinder, a cone, a frustum, a cylinder with rounded corners at the top, or a frustum with rounded corners at the top.

[0021] According to the present invention, a method for using the metal rupture diaphragm structure for a liquid attitude and orbit control power system includes the following steps:

[0022] Step A: After the piston diaphragm and the fixed diaphragm are interference-fitted through the sealing ring, the fixed diaphragm is connected to the upstream propellant chamber and the downstream thruster pipeline respectively;

[0023] Step B: When the pressure of the upstream propellant chamber is increased to the set pressure, the piston diaphragm moves forward under the action of the pressure of the upstream propellant chamber;

[0024] Step C: After the second impact cone of the piston diaphragm contacts the first rupture membrane of the fixed diaphragm, the first rupture membrane is broken under the action of pressure;

[0025] Step D: After the second striker ruptures the first rupture membrane, the piston diaphragm moves further forward under the action of pressure until the first striker ruptures the second rupture membrane in the reverse direction, and the upstream propellant chamber is connected to the downstream thruster pipeline.

[0026] Compared with the prior art, the present invention has the following beneficial effects:

[0027] 1. The present invention amplifies the effect of the upstream pressure source through the impact cone structure, and can select high-strength, high-propellant compatible materials such as titanium alloy or stainless steel as structural materials, which greatly improves the storage and service life of the attitude and orbit control power device matched therewith.

[0028] 2. The present invention reduces the influence of the dispersion of the diaphragm scoring process on the structural rupture pressure through the impact cone structure. The rupture pressure dispersion of a conventional rupture diaphragm is about 20% to 30%, while the rupture pressure dispersion of the present structure is only 1 to 2%. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0030] Figure 1 This is a cross-sectional view of the fixed diaphragm.

[0031] Figure 2 Top view of the fixed diaphragm.

[0032] Figure 3 for Figure 1 A magnified schematic diagram of area A in the middle.

[0033] Figure 4 This is a top view of the piston diaphragm.

[0034] Figure 5 This is a cross-sectional view of the piston diaphragm.

[0035] Figure 6 for Figure 5 Schematic diagram of the structure of area B in the middle.

[0036] Figure 7 Schematic diagram of diaphragm rupture.

[0037] Reference numerals:

[0038] Piston diaphragm 1

[0039] Second impact cone 101

[0040] Second rupture membrane 102

[0041] Fixed diaphragm 2

[0042] First impact cone 201

[0043] First rupture membrane 202

[0044] Sealing ring 3 DETAILED DESCRIPTION

[0045] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0046] Before the system starts working, the present invention completes the reliable physical isolation of the upstream propellant and the downstream cavity through the piston diaphragm 1 and the fixed diaphragm 2. When the system starts working, the upstream propellant squeezes the piston diaphragm 1 with a certain pressure. The piston diaphragm 1 moves under the action of pressure, causing the fixed diaphragm 2 and the piston diaphragm 1 to rupture successively, finally connecting the upstream and downstream. The present invention innovatively designs a metal rupture diaphragm structure suitable for the field of liquid attitude and orbit control power. It is particularly suitable for metals such as titanium alloys and stainless steel that have good compatibility with propellants and high material strength, greatly improving the storage and service life of the attitude and orbit control power device matched therewith. It solves the problem that some high-strength metals with high compatibility with liquid propellants have excessively large rupture pressure dispersion due to their own high strength characteristics.

[0047] Further explanation, such as Figures 1 to 7As shown, the present invention includes a fixed diaphragm 2, a piston diaphragm 1, and a sealing ring 3. The sealing ring 3 is an O-ring, which is assembled into the groove of the piston diaphragm 1. The piston diaphragm 1 equipped with the O-ring is then installed into the fixed diaphragm 2. The assembled rupture diaphragm structure is connected to the upstream propellant chamber and the downstream propellant pipeline by welding. The upstream medium of the piston diaphragm 1 is liquid propellant. The fixed diaphragm 2 and the piston diaphragm 1 are made of a high-strength material that is compatible with liquid propellant, such as titanium alloy or stainless steel. Both the fixed diaphragm 2 and the piston diaphragm 1 have a striker. The striker of the piston diaphragm 1 is longer than that of the fixed diaphragm 2. The strikers on the fixed diaphragm 2 and the piston diaphragm 1 can be cylinders, cones, frustums, cylinders with rounded corners at the top, or frustums with rounded corners at the top. The fixed diaphragm 2 and the piston diaphragm 1 are machined with notched grooves to control the rupture of the structure. The cross-section of the notched grooves can be triangular, arc-shaped, or trapezoidal.

[0048] To further illustrate, the piston diaphragm 1 equipped with the sealing ring 3 is installed in the fixed diaphragm 2, and the piston diaphragm 1 and the fixed diaphragm 2 are interference-fitted via the sealing ring 3 to ensure sealing performance.

[0049] The fixed diaphragm 2 is provided with a first striker 201 and a first rupture membrane 202, and the piston diaphragm 1 is provided with a second striker 101 and a second rupture membrane 102. During the advancement of the piston diaphragm 1 within the fixed diaphragm 2, the first striker 201 gradually approaches and ruptures the second rupture membrane 102, and the second striker 101 gradually approaches and ruptures the first rupture membrane 202. The fixed diaphragm 2 is connected to the upstream propellant chamber and the downstream thruster pipeline, respectively. When both the first rupture membrane 202 and the second rupture membrane 102 are ruptured, the upstream thruster chamber and the downstream propellant pipeline are connected.

[0050] The present invention also provides a method for using a metal rupture diaphragm applied to a liquid attitude and orbit control power system, comprising the following steps:

[0051] Step A: After the piston diaphragm and the fixed diaphragm are interference-fitted through the sealing ring, the fixed diaphragm is connected to the upstream propellant chamber and the downstream thruster pipeline respectively;

[0052] Step B: When the pressure of the upstream propellant chamber is increased to the set pressure, the piston diaphragm moves forward under the action of the pressure of the upstream propellant chamber;

[0053] Step C: After the second impact cone of the piston diaphragm contacts the first rupture membrane of the fixed diaphragm, the first rupture membrane is broken under the action of pressure;

[0054] Step D: After the second striker ruptures the first rupture membrane, the piston diaphragm moves further forward under the action of pressure until the first striker ruptures the second rupture membrane in the reverse direction, and the upstream propellant chamber is connected to the downstream thruster pipeline.

[0055] This invention utilizes a striker structure to amplify the effect of upstream pressure, allowing high-strength metals to be used as the rupture diaphragm material. This also reduces the dispersion of the rupture pressure across the diaphragm, significantly impacting the long-term on-orbit operation of attitude and orbit control power systems or their long-term storage in pre-packaged form on the ground. The burst pressure of attitude and orbit control power systems using this structure is 3±0.02 MPa, with a dispersion of 1.3%.

[0056] In the description of this application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0057] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A metal rupture diaphragm structure for a liquid attitude and orbit control power system, characterized in that: It includes a fixed diaphragm, a piston diaphragm and a sealing ring, wherein: A groove is provided on the circumference of the piston diaphragm, and the sealing ring is assembled into the groove of the piston diaphragm; The piston diaphragm equipped with a sealing ring is installed in the fixed diaphragm, and the piston diaphragm and the fixed diaphragm are interference-fitted through the sealing ring; A first impact cone and a first rupture membrane are provided in the fixed diaphragm, and a second impact cone and a second rupture membrane are provided on the piston diaphragm; During the process of the piston diaphragm advancing in the fixed diaphragm, the first impact cone gradually approaches and impacts the second rupture membrane, and the second impact cone gradually approaches and impacts the first rupture membrane; The first impact cone and the second impact cone are arranged facing each other; The length of the first bumper is smaller than the length of the second bumper.

2. The metal rupture diaphragm structure for a liquid attitude and orbit control power system according to claim 1, characterized in that: The fixed diaphragm is connected to the upstream propellant cavity and the downstream propellant pipeline respectively. When the first rupture membrane and the second rupture membrane are both broken, the upstream propellant cavity and the downstream propellant pipeline are connected.

3. The metal rupture diaphragm structure for a liquid attitude and orbit control power system according to claim 2, characterized in that: The piston diaphragm is propelled within the fixed diaphragm by the pressure of the upstream propellant chamber.

4. The metal rupture diaphragm structure for a liquid attitude and orbit control power system according to claim 1, characterized in that: The upstream medium of the piston diaphragm is liquid propellant.

5. The metal rupture diaphragm structure for a liquid attitude and orbit control power system according to claim 1, characterized in that: The first rupture film and the second rupture film are processed with notch grooves to make rupture controllable.

6. The metal rupture diaphragm structure for a liquid attitude and orbit control power system according to claim 5, characterized in that: The cross section of the notch groove is triangular, arc-shaped or trapezoidal.

7. The metal rupture diaphragm structure for a liquid attitude and orbit control power system according to claim 1, characterized in that: The first impact cone or the second impact cone is in the shape of a cylinder, a cone, a frustum, a cylinder with rounded corners at the top, or a frustum with rounded corners at the top.

8. A method for using the metal rupture diaphragm structure for a liquid attitude and orbit control power system according to any one of claims 1 to 7, characterized in that: The steps include: Step A: After the piston diaphragm and the fixed diaphragm are interference-fitted through the sealing ring, the fixed diaphragm is connected to the upstream propellant chamber and the downstream thruster pipeline respectively; Step B: When the pressure of the upstream propellant chamber is increased to the set pressure, the piston diaphragm moves forward under the action of the pressure of the upstream propellant chamber; Step C: After the second impact cone of the piston diaphragm contacts the first rupture membrane of the fixed diaphragm, the first rupture membrane is broken under the action of pressure; Step D: After the second striker ruptures the first rupture membrane, the piston diaphragm moves further forward under the action of pressure until the first striker ruptures the second rupture membrane in the reverse direction, and the upstream propellant chamber is connected to the downstream thruster pipeline.

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