CN115158678A - Aircraft liquid propellant storage tank - Google Patents
Aircraft liquid propellant storage tank Download PDFInfo
- Publication number
- CN115158678A CN115158678A CN202211081429.9A CN202211081429A CN115158678A CN 115158678 A CN115158678 A CN 115158678A CN 202211081429 A CN202211081429 A CN 202211081429A CN 115158678 A CN115158678 A CN 115158678A
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- Prior art keywords
- compartment
- plate
- cabin
- box body
- storage box
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- 239000007788 liquid Substances 0.000 title claims abstract description 101
- 239000003380 propellant Substances 0.000 title claims abstract description 83
- 238000000926 separation method Methods 0.000 claims abstract description 23
- 238000005507 spraying Methods 0.000 claims abstract description 9
- 238000004146 energy storage Methods 0.000 claims description 31
- 230000007246 mechanism Effects 0.000 claims description 17
- 238000005192 partition Methods 0.000 abstract description 5
- 230000001133 acceleration Effects 0.000 description 4
- 238000007726 management method Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000004321 preservation Methods 0.000 description 2
- 230000002265 prevention Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 108010066278 cabin-4 Proteins 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000012050 conventional carrier Substances 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/06—Constructional adaptations thereof
- B64D37/08—Internal partitioning
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/005—Accessories not provided for in the groups B64D37/02 - B64D37/28
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
Abstract
The invention provides an aircraft liquid propellant tank comprising: a tank body; the cabin separation plate is positioned in the storage box body and divides the internal space of the storage box body into a main cabin and a cabin; the inlet and outlet is used for filling and spraying the propellant; the liquid inlet check valve is positioned on the compartment plate and is close to the side wall of the bottom of the storage box body in a horizontal state; the partition board is automatically opened towards the compartment under the condition that one side of the partition board facing the main compartment is pressed; closing the compartment plate under pressure on the side facing the compartment; the exhaust check valve is positioned on the compartment plate and is far away from the side wall of the bottom of the storage box body in a horizontal state; the cabin separation plate is automatically opened towards the main cabin under the condition that one side of the cabin separation plate facing the cabin is pressed; the compartment plate is closed under pressure on the side facing the main compartment. The aircraft is suitable for the aircraft with severe overload and multiple-ignition flight conditions, and the effective control of the liquid level of the propellant is realized.
Description
Technical Field
The invention belongs to the technical field of liquid level control of storage tanks, and particularly relates to an aircraft liquid propellant storage tank.
Background
The tank serves as the primary means of a pressurized delivery system for the delivery of aircraft propellant.
Most of the existing storage tank structures are suitable for conventional carrier rockets, the internal propellant management device is not suitable for the use condition of the aircraft with severe overload, and the storage tank device cannot effectively manage and control the liquid level of the aircraft during severe overload flight of the aircraft.
And effective management and control to the liquid level is especially important, realizes effective management and control to the liquid level, just can guarantee that the propellant is stably carried to the engine of aircraft, consequently needs an aircraft liquid propellant storage tank urgently, is applicable to the aircraft that has the flight operating mode of violently transshipping, ignition many times.
Disclosure of Invention
In view of the above-identified deficiencies or inadequacies in the prior art, the present invention is directed to an aircraft liquid propellant tank.
In order to achieve the above purpose, the embodiment of the present invention adopts the following technical solutions:
an aircraft liquid propellant tank comprising: the storage box body is a hollow shell, and the interior of the storage box body is used for containing propellant; the cabin separation plate is positioned in the storage box body, the edge of the cabin separation plate is connected with the inner wall of the storage box body, and the internal space of the storage box body is divided into a main cabin and a cabin; when the storage box body is in a vertical state, the main cabin is positioned above the bulkhead; the inlet and outlet is positioned on the bottom wall of the storage box body and close to the side wall of the bottom of the storage box body in a horizontal state, and is used for filling and spraying propellant; the liquid inlet check valve is positioned on the partition board and is close to the side wall of the bottom of the storage box body in a horizontal state; the partition board automatically opens towards the compartment under the condition that one side of the partition board facing the main compartment is pressed; the compartment plate is closed under the condition that one side of the compartment plate, which faces the compartment, is pressed; the exhaust check valve is positioned on the compartment plate and is far away from the side wall of the bottom of the storage box body in a horizontal state; the cabin separation plate is automatically opened towards the main cabin under the condition that one side of the cabin separation plate facing the cabin is pressed; the compartment plate is closed under the condition that one side of the compartment plate facing the main compartment is pressed.
According to the technical scheme provided by the embodiment of the application, a spring energy storage device is arranged on one side, close to the compartment, of the liquid inlet check valve; the liquid inlet one-way valve is closed by the elasticity of the spring energy storage device in an unpressurized state and is opened in a pressurized state at one side of the main cabin; a spring energy storage device is arranged on one side, facing the main cabin, of the exhaust one-way valve; the exhaust check valve is closed by the elasticity of the spring energy storage device in an unpressurized state and is opened in a pressurized state at one side of the compartment.
According to the technical scheme provided by the embodiment of the application, one end of the liquid inlet check valve is rotatably connected with the cabin separation plate, a spring energy storage device is arranged at the joint, and the spring energy storage device is a torsion spring; the other end of the liquid inlet check valve is in lap joint with one side of the compartment plate close to the compartment; one end of the exhaust check valve is rotatably connected with the cabin separation plate, and a spring energy storage device is arranged at the joint and is a torsion spring; the other end is in lap joint with one side of the compartment plate close to the main compartment.
According to the technical scheme provided by the embodiment of the application, the compartment plate is an arc surface protruding towards the main compartment direction, a compartment exhaust valve is arranged at the top of the arc surface, and the compartment exhaust valve is connected with a compartment exhaust control valve; and the compartment exhaust control valve is connected with a control mechanism of the aircraft and controls the compartment exhaust valve to open when the filled propellant liquid reaches a preset position.
According to the technical scheme provided by the embodiment of the application, the top wall of the storage tank body is also provided with an energy dissipater, a pressure sensor and a safety overflow valve, wherein the pressure sensor is connected with a control mechanism of an aircraft, and the control mechanism is connected with the energy dissipater; when the control mechanism finds that the pressure detected by the pressure sensor is lower than a preset value, the energy dissipater is controlled to inject pressurized gas into the main cabin.
According to the technical scheme provided by the embodiment of the application, a first liquid level meter is annularly arranged on the inner side wall of the storage box body and is positioned in the middle of the main cabin; a second liquid level meter is arranged on the inner side wall of the storage box body, is arranged along the axis direction of the storage box body and is positioned in the main cabin and below the first liquid level meter; and a third liquid level meter is arranged on the inner side wall of the tank body, and is arranged along the axis direction of the tank body and positioned in the compartment.
According to the technical scheme provided by the embodiment of the application, the inner wall of the storage box body is provided with an anti-shaking plate; the anti-shaking plate comprises a first anti-shaking plate and a second anti-shaking plate; the first anti-sloshing plate is annularly arranged on the inner side wall of the storage box body, and is annular or annular with a broken middle part; a plurality of first anti-shaking plates are arranged and distributed along the axial direction of the storage box body; the second anti-shaking plate is in a strip shape or a strip shape with a broken middle part; the number of the second anti-shaking plates is a plurality, and the second anti-shaking plates are distributed along the circumferential direction of the inner side wall of the storage box body.
According to the technical scheme provided by the embodiment of the application, one end part of the strip-shaped second anti-shaking plate with the middle broken is connected with one end part of the annular first anti-shaking plate with the middle broken.
According to the technical scheme provided by the embodiment of the application, the inlet and outlet positions in the compartment are provided with the vortex-eliminating anti-collapse devices which are multilayer plates, and each layer plate is provided with a plurality of through holes.
According to the technical scheme provided by the embodiment of the application, the top wall of the storage box body is also provided with a temperature sensor; the parts of the pressure sensor and the temperature sensor extending into the main cabin are covered with a wave shield; the wave shield is a multi-layer shield body, and the parts of the pressure sensor and the temperature sensor extending into the main cabin are covered; each layer of cover body is provided with a round hole.
The invention has the following beneficial effects:
the compartment plate is arranged in the inner space of the storage box body, the inner space is divided into a main compartment and a compartment, the compartment is communicated with an engine, the compartment plate is provided with a liquid inlet one-way valve and an exhaust one-way valve, the liquid inlet one-way valve and the exhaust one-way valve are automatically opened and closed under a pressed state, the liquid inlet one-way valve is positioned on the compartment plate and close to the position of the bottom side wall when the aircraft is in a horizontal state, effective sealing of propellant and effective exhaust of compartment gas are realized, the exhaust one-way valve is positioned on the compartment plate and far away from the position of the bottom side wall when the aircraft is in the horizontal state, propellant filling and exhaust ports are positioned at the position of the bottom side wall when the bottom of the storage box is close to the aircraft in the horizontal state, the propellant is always arranged at an outlet and an inlet, and further the stable transportation without gas inclusion of a propellant conveying pipeline is ensured; therefore, the aircraft storage tank structure provided by the application is particularly suitable for aircrafts with severe overload and multiple ignition, and achieves the effect of effectively controlling the liquid level of the propellant in the storage tank.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments made with reference to the following drawings:
FIG. 1 is a schematic view of the tank of the present application in an upright configuration;
FIG. 2 is a schematic view of a reservoir according to the present application in a filling state;
FIG. 3 is a schematic view of another reservoir configuration according to the present application in an alternate fill state;
FIG. 4 is a schematic view of the tank of the present application under forward acceleration;
FIG. 5 is a schematic view of a tank according to the present application in a forward deceleration configuration;
FIG. 6 is an enlarged view of the structure of the tank inlet check valve of the present application;
FIG. 7 is an enlarged schematic view of the structure at the tank vent check valve described herein;
fig. 8 is a schematic structural distribution diagram of the anti-sloshing plate according to the present application.
Description of reference numerals:
1. a tank body; 2. a bulkhead; 3. a main cabin; 4. a bay;
11. the upper bottom of the storage box; 12. a storage tank column section; 13. the lower bottom of the storage tank;
111. an energy dissipater; 112. a safety overflow valve; 113. a pressure sensor; 114. a temperature sensor; 115. a wave shield;
120. an anti-sloshing plate; 121. a first anti-sloshing plate; 122. a second anti-sloshing plate;
21. a liquid inlet check valve; 22. an exhaust check valve; 23. a spring energy storage device; 24. a bulkhead vent valve; 25. a bay exhaust control valve;
131. an entrance and an exit; 132. a vortex eliminating and collapse preventing device;
31. a first liquid level meter; 32. a second level gauge;
41. a third liquid level gauge.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and not restrictive of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present disclosure, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", "clockwise", "counterclockwise", "front", "rear", "side", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, or orientations or positional relationships that are conventionally laid out when the disclosed products are used, and are only for convenience of describing and simplifying the present disclosure, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present disclosure. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another, and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical", "overhang" and the like do not imply that the components are required to be absolutely horizontal or overhang, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present disclosure, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "butted" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present disclosure can be understood in a specific case to those of ordinary skill in the art.
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
A liquid propellant storage tank for an aircraft comprises a storage tank body 1 which is a hollow shell and is internally used for containing propellant; the compartment plate 2 is positioned inside the storage box body 1, the edge of the compartment plate is connected with the inner wall of the storage box body 1, and the inner space of the storage box body 1 is divided into a main compartment 3 and a compartment 4; when the storage box body 1 is in a vertical state, the main cabin 3 is positioned above the bulkhead 4; an inlet/outlet 131 which is located in the bottom wall of the tank body 1 and is close to the side wall located at the bottom of the tank body 1 when the tank body is in a horizontal state, and which is used for filling and spraying propellant; the liquid inlet check valve 21 is positioned on the cabin separation plate 2 and is close to the side wall of the bottom of the storage box body 1 in a horizontal state; the compartment plate 2 is automatically opened towards the compartment 4 under the condition that the side facing the main compartment 3 is pressed; closed under pressure on the side of the compartment plate 2 facing the compartment 4; the exhaust check valve 22 is positioned on the compartment plate 2 and is far away from the side wall of the bottom of the storage box body 1 in a horizontal state; the cabin separation plate 2 is automatically opened towards the main cabin 3 under the condition that the side facing the cabin 4 is pressed; closed under pressure on the side of the compartment plate 2 facing the main compartment 3.
Generally, in the initial or ascent and descent state of the aircraft, the tank body is in an upright state, as shown in fig. 1. In the flying state of the aircraft, the tank body is in a horizontal state, as shown in figures 4 and 5.
The storage tank body 1 is a hollow shell with an internal space, when the storage tank body is in a vertical state, the top wall of the storage tank body is an upper storage tank bottom 11, the bottom wall of the storage tank body is a lower storage tank bottom 13, and a storage tank column section 12 is arranged between the upper storage tank bottom 11 and the lower storage tank bottom 13; the upper bottom 11 of the storage tank, the column section 12 of the storage tank and the lower bottom 13 of the storage tank form the internal space of the storage tank body 1.
The lower bottom 13 of the storage tank is provided with an entrance 131.
The portion of the inlet/outlet 131 located inside the tank body 1 is connected to the vortex collapse preventing device 132.
The inlet and outlet 131 is located outside the tank body 1 and is connected to the propellant line.
The propellant pipeline is provided with two branches, one branch is provided with a propellant filling port, and the other branch is provided with a propellant spraying port; the propellant filling port is communicated with a propellant, and the propellant spraying port is connected with an engine.
Propellant liquid reaches the access 131 from the propellant filling port through the propellant pipeline, enters the storage tank body 1, fills the compartment 4 and then enters the main cabin 3 until reaching a preset liquid level, and stops filling. Here, it will be appreciated that during filling, liquid propellant flows from compartment 4 into the main compartment 3 through the vent check valve 22. And after filling, closing the propellant filling port.
When the aircraft is ignited, the propellant spraying port is opened, and the propellant enters the propellant spraying port from the inlet and outlet 131 through the propellant pipeline and is conveyed to the engine; when the aircraft is extinguished, the propellant outlet is closed.
The compartment plate is arranged in the inner space of the storage box, the inner space is divided into a main compartment and a compartment, the compartment is communicated with an engine, the compartment plate is provided with a liquid inlet one-way valve and an exhaust one-way valve, the liquid inlet one-way valve and the exhaust one-way valve are automatically opened and closed under a pressed state, the liquid inlet one-way valve is positioned on the compartment plate and close to the position of the bottom side wall when the aircraft is in a horizontal state, effective sealing of propellant and effective exhaust of compartment gas are realized, the exhaust one-way valve is positioned on the compartment plate and far away from the position of the bottom side wall when the aircraft is in a horizontal state, propellant filling and exhaust ports are positioned at the position of the bottom side wall when the bottom of the storage box is close to the aircraft in a horizontal state, the propellant is always arranged at an outlet, and the propellant is further ensured to be stably transported without air inclusion in a propellant conveying pipeline; therefore, the aircraft storage tank structure provided by the application is particularly suitable for aircrafts with severe overload and multiple ignition, and achieves the effect of effectively controlling the liquid level of the propellant in the storage tank.
In one embodiment of the present application, a spring energy storage device 23 is disposed on one side of the liquid inlet check valve 21 close to the compartment 4; the liquid inlet one-way valve 21 is closed by the elasticity of the spring energy storage device 23 in an unpressurized state and is opened in a pressurized state at one side of the main cabin 3; a spring energy storage device 23 is arranged on one side, facing the main cabin 3, of the exhaust one-way valve 22; the exhaust check valve 22 is closed in an unpressurized state by the spring force of the spring energy storage device 23 and is opened in a pressurized state on the compartment 4 side.
Generally, the liquid level is tilted backwards when the aircraft is in a horizontal state and is flying with forward acceleration.
Specifically, as shown in fig. 4, a represents positive acceleration, and the arrow direction is the forward direction.
At this time, the exhaust check valve 22 is closed under the combined action of overload and the spring energy storage device 23, the liquid inlet check valve 21 is opened under the combined action of overload and the spring energy storage device 23, and the propellant can freely flow from the main cabin 3 to the compartment 4, so that the propellant storage capacity of the compartment 4 is ensured, and the normal work of the engine is ensured.
Generally, the liquid level tilts backwards when the aircraft is in a horizontal state and is decelerated in the forward direction and the forward direction.
Specifically, as shown in fig. 5, -a represents a negative acceleration, and the arrow direction is a forward direction.
The liquid level inclines forwards, at the moment, the liquid inlet one-way valve 21 is closed under the combined action of overload and the spring energy storage device 23, the exhaust one-way valve 22 is opened under the combined action of overload and the spring energy storage device 23, the compartment 4 and the main cabin 3 keep smooth gas communication, and propellant cannot flow to the main cabin 3 from the compartment 4, so that the propellant storage capacity of the compartment 4 is effectively locked, and the normal work or the secondary ignition use of the engine is ensured.
In a specific embodiment of the application, one end of the liquid inlet check valve 21 is rotatably connected with the compartment plate 2, a spring energy storage device 23 is arranged at the connection position, and the spring energy storage device 23 is a torsion spring; the other end of the liquid inlet check valve 21 is in lap joint with one side of the compartment plate 2 close to the compartment; one end of the exhaust check valve 22 is rotatably connected with the cabin separation plate 2, a spring energy storage device 23 is arranged at the joint, and the spring energy storage device 23 is a torsion spring; the other end is lapped with one side of the bulkhead plate 2 close to the main cabin 3.
As shown in fig. 6, the spring energy storage device 23 is located on one side of the liquid inlet check valve 21 close to the compartment 4; as shown in fig. 7, the spring energy storage device 23 is located on the side of the exhaust check valve 22 close to the main compartment 3.
Specifically, as shown in fig. 1-3, the liquid inlet check valve 21 and the exhaust check valve 22 of the present application adopt the spring energy storage device 23 to realize the automatic opening and closing in a pressed state, so that the structure of the storage tank is simple, the manufacturing and forming are simple and convenient, the processing and assembling difficulty and the cost are reduced, and the effective management and control of the liquid level are realized.
In a specific embodiment of the present application, the compartment plate 2 is a curved surface protruding toward the main compartment 3, a compartment exhaust valve 24 is disposed at the top of the curved surface, and the compartment exhaust valve 24 is connected to a compartment exhaust control valve 25; the compartment exhaust control valve 25 is connected to the control mechanism of the aircraft, and when the propellant liquid to be filled reaches a predetermined position, the compartment exhaust control valve 25 controls the compartment exhaust valve 24 to open.
Specifically, the cabin separation plate 2 is an arc-shaped surface protruding upwards, and the cabin separation plate 2 ensures that the pressure on the cabin separation plate 2 is minimum in various states of the aircraft.
And a compartment 4 vent valve is arranged at the top of the cambered surface, so that the top of the compartment 4 can be filled with propellant.
The compartment exhaust valves 24 are opened under the control of compartment exhaust control valves 25, the compartment exhaust control valves 25 acting as instructed by the aircraft control mechanisms. The control mechanism may determine from the feedback data measured by the second level gauge 32 and the third level gauge 41 that propellant is being filled to the compartment 4 or until the entire tank is filled to a final level, closing the compartment vent valve 24.
It can be understood that when the propellant is filled, the tank body is in a vertical state, the compartment vent valve 24 is in an open state, a liquid level sensor is arranged near the compartment plate 2 of the column section 12 of the tank to sense the liquid level of the propellant, and if the liquid level reaches the liquid level, the compartment vent valve 24 can be closed; or the tank vent valve 24 is closed, keeping the level vent open until the entire tank is filled to final level.
In an embodiment of the present application, the top wall of the tank body 1 is further provided with an energy dissipater 111, a pressure sensor 113 and a safety relief valve 112, the pressure sensor 113 is connected with a control mechanism of an aircraft, and the control mechanism is connected with the energy dissipater 111; when the control mechanism finds that the pressure detected by the pressure sensor 113 is below a preset value, the control mechanism controls the dissipater 111 to inject pressurised gas into the main chamber 3.
Specifically, the safety relief valve 112 is used for pressure relief when the pressurized gas inside the tank is excessive.
An energy dissipater 111 is arranged on the upper bottom 11 of the storage tank, and the energy dissipater 111 is communicated with an external air pump and is used for filling pressurized air into the storage tank to ensure that the pressure of the main cabin reaches a preset value; so as to give pressure to the liquid propellant inside the tank so that the compartment 4 is always provided with liquid propellant. The pressurized gas in the tank always pressurizes the liquid level, so that the liquid level is kept stable, and the propellant is promoted to flow from the main cabin 3 to the compartment 4. Due to the existence of the energy dissipater 111, the propellant is effectively sealed in the compartment 4, and the use of the engine is guaranteed.
In each flight state of the aircraft, the states of the propellant filling port, the propellant spraying port, the liquid inlet check valve 21, the exhaust check valve 22, the main cabin 3, the compartment 4, the compartment exhaust valve 24 and the energy dissipater 111 are as shown in table 1 below.
It can be seen from the above table that, under the condition of severe overload or multiple ignition and flameout of the aircraft, the liquid inlet one-way valve 21 and the exhaust one-way valve 22 are matched with the energy dissipater 111 and the like to effectively control the liquid level of the propellant, and the propellant is always present at the propellant outlet, so that the propellant is guaranteed to be stably transported without air inclusion.
In a specific embodiment of the present application, a first liquid level meter 31 is annularly arranged on the inner side wall of the tank body 1, and the first liquid level meter 31 is located in the middle of the main compartment 3; a second liquid level meter 32 is arranged on the inner side wall of the storage tank body 1, and the second liquid level meter 32 is arranged along the axial direction of the storage tank body 1 and is positioned in the main cabin 3 and below the first liquid level meter 31; the inner side wall of the tank body 1 is provided with a third liquid level meter 41, and the third liquid level meter 41 is arranged along the axial direction of the tank body 1 and is positioned in the compartment 4.
Specifically, first level gauge 31, second level gauge 32 and third level gauge 41 are connected with the control mechanism of aircraft, first level gauge 31 is used for detecting the liquid level that the aircraft is under the horizontality, second level gauge 32 and third level gauge 41 superpose and are used for detecting the liquid level that the aircraft is under the vertical condition.
Wherein the first level gauge 31 monitors the level of the liquid propellant in the tank in order to ensure a level condition of the aircraft; the second level gauge 32 and the third level gauge 41 monitor to ensure that the level of liquid propellant in the tank is monitored in the vertical state of the aircraft.
In a specific embodiment of the present application, an anti-sloshing plate 120 is disposed on an inner wall of the tank body 1; the anti-sloshing plate 120 includes a first anti-sloshing plate 121 and a second anti-sloshing plate 122; the first anti-sloshing plate 121 is annularly arranged on the inner side wall of the storage box body 1, and the first anti-sloshing plate 121 is annular or annular with a broken middle part; a plurality of first anti-shaking plates 121 are arranged and distributed along the axial direction of the storage tank body 1; the second anti-shaking plate 122 is in a bar shape or a bar shape with a broken middle part; the number of the second anti-sloshing plates 122 is plural, and the second anti-sloshing plates are distributed along the circumferential direction of the inner side wall of the tank body 1.
In particular, the anti-sloshing plate 120 serves to prevent the propellant liquid from sloshing violently in the event of a severe overload or to prevent the liquid level from sloshing more and more violently.
Wherein the first anti-sloshing plate 121 prevents the liquid level from sloshing in the axial direction of the tank column section 12; the second slosh guard 122 prevents the liquid level from sloshing violently in the circumferential direction of the tank column section 12.
In an embodiment of the present application, one end of the second shaking prevention plate 122 having a bar shape with a broken middle is connected to one end of the first shaking prevention plate 121 having a ring shape with a broken middle.
Specifically, as shown in fig. 8, the first and second sloshing preventing plates 121 and 122 are connected to further prevent the liquid surface from sloshing sharply.
In one embodiment of the present application, a vortex-eliminating anti-collapse device 132 is disposed at the entrance 131 inside the compartment 4, and the vortex-eliminating anti-collapse device 132 is a multi-layer plate, and each layer plate is provided with a plurality of through holes.
Specifically, the liquid propellant enters the interior of the tank through the vortex breaker 132, the multi-layer plates and the multiple ports per layer structure of the vortex breaker 132 ensuring stable propellant addition.
In one embodiment of the present application, a temperature sensor 114 is further disposed on the upper bottom 11 of the storage tank; the parts of the pressure sensor 113 and the temperature sensor 114 extending into the main cabin 3 are covered with a wave shield 115; the wave shield 115 is a multi-layer shield body, and covers the part of the pressure sensor 113 and the temperature sensor 114 extending into the main cabin 3; each layer of cover body is provided with a round hole.
The temperature sensor 114 is used for monitoring the temperature inside the storage tank to detect the heat preservation effect of the external heat preservation layer, and simultaneously, the temperature is recorded to facilitate later data analysis and research.
Wherein, the parts of the pressure sensor 113 and the temperature sensor 114 extending into the main cabin 3 are covered with a wave shield 115; the wave shield 115 is a multi-layer shield body, and covers the part of the pressure sensor 113 and the temperature sensor 114 extending into the main cabin 3; each layer of cover body is provided with a round hole.
Specifically, the design of the multiple layers of the wave shield 115 and the round holes of each layer of the shield prevents the sensor from being damaged due to severe shaking of the liquid level.
The foregoing description is only exemplary of the preferred embodiments of the invention and is illustrative of the principles of the technology employed. It will be appreciated by those skilled in the art that the scope of the invention is not limited to the specific combination of the above-mentioned features, but also encompasses other embodiments in which any combination of the above-mentioned features or their equivalents is made without departing from the inventive concept. For example, the above features and the technical features (but not limited to) having similar functions disclosed in the present invention are mutually replaced to form the technical solution.
Claims (10)
1. An aircraft liquid propellant tank, comprising:
the storage box body (1) is a hollow shell, and the interior of the storage box body is used for containing propellant;
the cabin separation plate (2) is positioned in the storage box body (1), the edge of the cabin separation plate is connected with the inner wall of the storage box body (1), and the inner space of the storage box body (1) is divided into a main cabin (3) and a cabin (4); when the storage box body (1) is in a vertical state, the main cabin (3) is positioned above the bulkhead (4);
the inlet and outlet (131) is positioned on the bottom wall of the storage box body (1), is close to the side wall of the bottom of the storage box body (1) in a horizontal state, and is used for filling and spraying propellant;
the liquid inlet check valve (21) is positioned on the cabin separation plate (2) and is close to the side wall of the bottom of the storage box body (1) in a horizontal state; the cabin separation plate (2) is automatically opened towards the cabin (4) under the condition that one surface facing the main cabin (3) is pressed; the compartment plate (2) is closed under the condition that one side facing the compartment (4) is pressed;
the exhaust check valve (22) is positioned on the cabin separation plate (2) and is far away from the side wall of the bottom of the storage box body (1) in a horizontal state; the cabin separation plate (2) is automatically opened towards the main cabin (3) under the condition that one side facing the cabin (4) is pressed; the compartment plate (2) is closed under the condition that one side facing the main compartment (3) is pressed.
2. An aircraft liquid propellant tank as claimed in claim 1 wherein the side of the inlet check valve (21) adjacent the compartment (4) is provided with spring energy storage means (23); the liquid inlet one-way valve (21) is closed by the elasticity of the spring energy storage device (23) in an unpressurized state and is opened in a pressurized state at one side of the main cabin (3);
a spring energy storage device (23) is arranged on one side, facing the main cabin (3), of the exhaust check valve (22); the exhaust check valve (22) is closed by the elasticity of the spring energy storage device (23) in an unpressurized state and is opened in a pressurized state at one side of the compartment (4).
3. An aircraft liquid propellant tank as claimed in claim 2, wherein one end of the liquid inlet one-way valve (21) is rotatably connected with the compartment plate (2), a spring energy storage device (23) is arranged at the connection part, and the spring energy storage device (23) is a torsion spring; the other end of the liquid inlet check valve (21) is in lap joint with one side of the compartment plate (2) close to the compartment;
one end of the exhaust check valve (22) is rotatably connected with the cabin separation plate (2), a spring energy storage device (23) is arranged at the joint, and the spring energy storage device (23) is a torsion spring; the other end is lapped with one side of the cabin separation plate (2) close to the main cabin (3).
4. An aircraft liquid propellant tank according to claim 1, characterized in that the compartment plate (2) is a curved surface which is convex in the direction of the main compartment (3), a compartment exhaust valve (24) is arranged at the top of the curved surface, and the compartment exhaust valve (24) is connected with a compartment exhaust control valve (25);
the compartment exhaust control valve (25) is connected with a control mechanism of the aircraft, and when the filled propellant liquid reaches a preset position, the compartment exhaust control valve (25) controls the compartment exhaust valve (24) to be opened.
5. An aircraft liquid propellant tank according to claim 1, characterized in that the tank body (1) is further provided with an energy dissipater (111), a pressure sensor (113) and a safety overflow valve (112) on the top wall, the pressure sensor (113) is connected with the control mechanism of the aircraft, and the control mechanism is connected with the energy dissipater (111);
when the control mechanism finds that the pressure detected by the pressure sensor (113) is lower than a preset value, the control mechanism controls the energy dissipater (111) to inject pressurized gas into the main cabin (3).
6. An aircraft liquid propellant tank according to claim 1 wherein the tank body (1) is surrounded on its inside walls by a first level gauge (31), the first level gauge (31) being located in the middle of the main compartment (3);
a second liquid level meter (32) is arranged on the inner side wall of the storage box body (1), and the second liquid level meter (32) is arranged along the axis direction of the storage box body (1) and is positioned in the main cabin (3) and below the first liquid level meter (31);
and a third liquid level meter (41) is arranged on the inner side wall of the tank body (1), and the third liquid level meter (41) is arranged along the axial direction of the tank body (1) and is positioned in the compartment (4).
7. An aircraft liquid propellant tank according to claim 1 wherein the tank body (1) is provided on its inner wall with an anti-sloshing plate (120); the anti-sloshing plate (120) comprises a first anti-sloshing plate (121) and a second anti-sloshing plate (122);
the first anti-shaking plate (121) is annularly arranged on the inner side wall of the storage box body (1), and the first anti-shaking plate (121) is annular or annular with a broken middle part; a plurality of first anti-shaking plates (121) are arranged and distributed along the axial direction of the storage box body (1);
the second anti-shaking plate (122) is in a strip shape or a strip shape with the middle broken; the number of the second anti-sloshing plates (122) is multiple, and the second anti-sloshing plates are distributed along the circumferential direction of the inner side wall of the storage box body (1).
8. An aircraft liquid propellant tank according to claim 7 wherein the second anti-sloshing plate (122) of the intermediate broken strip shape has one end connected to one end of the first anti-sloshing plate (121) of the intermediate broken ring shape.
9. An aircraft liquid propellant tank according to claim 1 wherein the compartment (4) is provided with a vortex breaker (132) at an access opening (131) therein, the vortex breaker (132) being a multi-layer sheet with a plurality of through holes in each sheet.
10. An aircraft liquid propellant tank according to claim 5 wherein a temperature sensor (114) is also provided on the top wall of the tank body (1);
the parts of the pressure sensor (113) and the temperature sensor (114) extending into the main cabin (3) are covered with a wave shield (115);
the wave shield (115) is a multilayer shield body, and the part of the pressure sensor (113) and the temperature sensor (114) extending into the main cabin (3) is covered; each layer of cover body is provided with a round hole.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211081429.9A CN115158678B (en) | 2022-09-06 | 2022-09-06 | Aircraft liquid propellant storage tank |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211081429.9A CN115158678B (en) | 2022-09-06 | 2022-09-06 | Aircraft liquid propellant storage tank |
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| CN115158678B CN115158678B (en) | 2022-12-27 |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN115158678B (en) | 2022-12-27 |
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