CN111409877A - Air suction and separation device for aircraft hatch filling pipeline - Google Patents
Air suction and separation device for aircraft hatch filling pipeline Download PDFInfo
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- CN111409877A CN111409877A CN202010177471.5A CN202010177471A CN111409877A CN 111409877 A CN111409877 A CN 111409877A CN 202010177471 A CN202010177471 A CN 202010177471A CN 111409877 A CN111409877 A CN 111409877A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G5/00—Ground equipment for vehicles, e.g. starting towers, fuelling arrangements
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- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention provides an air suction and separation device for a filling pipeline of an aircraft hatch, which comprises: the aircraft cabin unit 5, the filling valve 6, the stop valve K1, the stop valve K2, the stop valve K3, the stop valve K4, the stop valve K6, the vacuum valve K5, the air suction container unit 2 and the vacuum pump unit 3; the aircraft cabin unit 5 comprises: an aircraft cabin filler port; the filling valve 6 is matched with a filling port of the aircraft cabin body; the filling valve 6 is connected with a stop valve K1 and a stop valve K2; the stop valve K2 is connected with the stop valve K3 and the stop valve K4; the stop valve K4 is connected with the empty suction container unit 2; the vacuum container unit 2 is connected with a vacuum valve K5; the vacuum valve K5 is connected to the vacuum pump unit 3. The invention utilizes the principles of positive pressure blowback and negative pressure absorption to control the medium leakage of the interface during the separation operation of the dangerous fluid to the pipeline.
Description
Technical Field
The invention relates to the technical field of filling pipelines, in particular to an air suction and separation device for a filling pipeline of an aircraft hatch.
Background
At present, liquid propellants such as hydrazine fuels, nitro oxidizers and the like are mainly used in a spacecraft power system in China, and the media have the characteristics of flammability, explosiveness, severe toxicity, high corrosion, volatility and the like. Since propellant filling is needed after the spacecraft such as a satellite, an airship, a deep space probe and the like completes a test in a launching field, separation from a discharge valve of a hatch of the spacecraft in the propellant pipeline withdrawing process is an important risk control point, and separation is implemented by a hatch end bypass nitrogen blowback method in the prior art because certain residual propellant exists in the pipeline after filling and certain pressure exists, as shown in fig. 1. The propellant is filled from a storage tank by adopting a nitrogen extrusion filling method, after the filling is finished, the pressurization pressure in the storage tank is released to the atmospheric pressure, a valve K03 is opened, the nitrogen with 0.2MPa is used for blowing the residual propellant back to the storage tank from the point B. Although most of residual propellant in the pipeline can be blown back to the filling container and the pressure in the filling pipeline is released to the atmospheric pressure, a back-blowing airflow blind cavity is arranged between the connection part of the bypass back-blowing at the front end of the filling pipeline and the hatch adding and discharging valve, and the residual propellant cannot be blown off effectively. When the pipeline is disassembled at the hatch, a small amount of propellant can still leak. The cables of the hatches of the aircraft are staggered, important products such as solar panels and the like are arranged nearby, once the propellant drips on the cables or is sprayed on the surfaces of the solar panels, the propellant can cause corrosion damage to the surfaces of the objects, and the launching task is directly influenced. In addition, in order to prevent the propellant from leaking, thick and heavy protective equipment needs to be worn when the hatch operation personnel dismantle the filling pipeline, the hatch space is narrow and small, operation is not facilitated, and aircraft parts are easy to collide to cause artificial damage.
Patent document CN104418056A discloses a material blowback separation device, which comprises a feeding rail, a sensor, an upper cover plate, a suction hole, a second lower suction hole and a blowback pipeline, wherein the rail is provided with a channel for conveying the material, a retaining wall is arranged at the terminal of the channel, the sensor is arranged near the retaining wall for sensing whether the material is in place, the suction hole is used for sucking the material and positioning the material at the terminal of the channel, the distance from the tail end of the upper cover plate above the channel to the retaining wall is more than one material length, the second lower suction hole is arranged near the tail end of the upper cover plate at the bottom of the channel, the blowback pipeline extends from the position near the terminal of the rail to the upstream end in an inclined manner, and the outlet of the blow. Therefore, the air flow opposite to the conveying direction is blown out from the blowback pipeline to apply reverse thrust to the material pieces so as to reversely push back the material pieces arranged at the second position, and a certain interval between the first material piece and the second material piece is ensured. The technical principle in this patent is obviously not well suited for use in the suction-evacuation separation of the filling line of the aircraft hatch.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide an air suction and separation device for a filling pipeline of an aircraft hatch.
The invention provides an air suction and separation device for a filling pipeline of an aircraft hatch, which comprises: the aircraft cabin unit 5, the filling valve 6, the stop valve K1, the stop valve K2, the stop valve K3, the stop valve K4, the stop valve K6, the vacuum valve K5, the air suction container unit 2 and the vacuum pump unit 3; the aircraft cabin unit 5 comprises: an aircraft cabin filler port; the filling valve 6 is matched with a filling port of the aircraft cabin body; the filling valve 6 is connected with a stop valve K1 and a stop valve K2; the stop valve K2 is connected with the stop valve K3 and the stop valve K4; the stop valve K4 is connected with the empty suction container unit 2; the vacuum container unit 2 is connected with a vacuum valve K5; the vacuum valve K5 is connected to the vacuum pump unit 3.
Preferably, the method further comprises the following steps: shut-off valve K7; the cut-off valve K7 is connected with a cut-off valve K1.
Preferably, the method further comprises the following steps: propellant storage tank 1 unit; the shut-off valve K7 is connected to the propellant tank 1 unit.
Preferably, the method further comprises the following steps: a vacuum gauge unit 4; the vacuum gauge unit 4 is connected with the vacuum container unit 2 and the vacuum valve K5.
Preferably, the method further comprises the following steps: a blowback nitrogen source unit; the blowback nitrogen gas source unit is connected to a shutoff valve K3.
Preferably, said shut-off valve K1 is mounted close to the hatch of the cabin unit 5 of the aircraft.
Compared with the prior art, the invention has the following beneficial effects:
the invention utilizes the principles of positive pressure blowback and negative pressure absorption to control the medium leakage of the interface during the separation operation of the dangerous fluid to the pipeline. Such as: the traditional operation mode that the pipeline and the cabin are separated after the spacecraft completes propellant filling is improved, the effect that one drop of propellant cannot leak in the separation process is achieved, and safety devices such as aircraft factory environment, operating personnel and aircrafts are protected.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic diagram of a conventional blowback separation method in the prior art.
Fig. 2 is a schematic view of the overall structure of the present invention.
In the figure:
propellant storage tank 1 vacuum meter 4
Air-suction container 2 aircraft cabin 5
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 2, the suction and separation device for the filling pipeline of the aircraft hatch provided by the invention comprises: the aircraft cabin unit 5, the filling valve 6, the stop valve K1, the stop valve K2, the stop valve K3, the stop valve K4, the stop valve K6, the vacuum valve K5, the air suction container unit 2 and the vacuum pump unit 3; the aircraft cabin unit 5 comprises: an aircraft cabin filler port; the filling valve 6 is matched with a filling port of the aircraft cabin body; the filling valve 6 is connected with a stop valve K1 and a stop valve K2; the stop valve K2 is connected with the stop valve K3 and the stop valve K4; the stop valve K4 is connected with the empty suction container unit 2; the vacuum container unit 2 is connected with a vacuum valve K5; the vacuum valve K5 is connected to the vacuum pump unit 3.
Based on the conventional 'blowback removal', a set of air suction device is additionally arranged in the vicinity of a hatch opening in a pipeline of a propellant filling system, the air suction volume is designed according to the gasification quantity of residual propellant in a front-end hatch pipeline cavity and a blind cavity after blowback, the air suction container is pre-vacuumized before filling, the air suction container and a filling pipeline are isolated by a valve in the filling process, nitrogen is firstly used for blowback of residual propellant in the pipeline after filling, and then vacuum in the air suction container is adopted for separating the filling pipeline of the aircraft hatch in a negative pressure state, so that the effects of propellant dripping and spraying are avoided at the hatch opening part in the removal process.
Preferably, the method further comprises the following steps: shut-off valve K7; the cut-off valve K7 is connected with a cut-off valve K1.
Preferably, the method further comprises the following steps: propellant storage tank 1 unit; the shut-off valve K7 is connected to the propellant tank 1 unit.
Preferably, the method further comprises the following steps: a vacuum gauge unit 4; the vacuum gauge unit 4 is connected with the vacuum container unit 2 and the vacuum valve K5.
Preferably, the method further comprises the following steps: a blowback nitrogen source unit; the blowback nitrogen gas source unit is connected to a shutoff valve K3.
Preferably, said shut-off valve K1 is mounted close to the hatch of the cabin unit 5 of the aircraft.
Specifically, in one embodiment, the aircraft hatch filling pipeline air suction separation device system comprises a stop valve K1, a stop valve K2, a stop valve K3, a stop valve K4, a stop valve K6, an air suction container, a vacuum pump, a vacuum gauge 4 vacuum gauge, a vacuum valve K5 and the like.
The stop valve K1 in the filling pipeline is arranged near the hatch, and the length between the pipelines A-B of the section to be vacuumed is controlled to be shortest under the condition of not influencing the operation, so that the vacuum suction efficiency is improved. The stop valve K2 connects filling pipeline and blowback suction system, and this valve is in the closed condition in the filling process. Before filling, the vacuum pump is started, the vacuum valve K5 is opened, and the vacuum container is vacuumized to the pressure below 500 Pa.
After propellant filling is finished, a hatch adding and discharging valve is closed, a propellant storage tank 1 is decompressed, a valve K3 and a valve K2 are opened, nitrogen higher than the pressure of the propellant storage tank 1 is adopted, propellant in a filling pipeline is blown back to the storage tank, a valve K7. is closed, nitrogen is blown back and the pressure is relieved to atmospheric pressure, factors and redundancies such as the amount of gas in a pipeline accommodating cavity between the hatch adding and discharging valve A and the valve K1, the valve K3 and the valve K4 and the amount of discharged air in the dismounting operation of the adding and discharging valve need to be considered in the volume design of a suction and discharging container of the valve K1 and the valve K3., after propellant blowing is finished, the valve K4 is opened, vacuum in the suction and discharging container is utilized, negative pressure is formed together with an inner cavity of a pipeline in front of the cabin, the connection between the filling pipeline A and the adding and discharging valve is dismounted, the atmosphere sucks the suction and discharging container from the A in the dismounting process, and the connection pipe is blocked after the separation of the cabin is separated from the cabin, so that one drop nozzle is avoided.
After the technology is invented, the technology is applied to filling of a certain type of aircraft, the verification effect is good, the filling pipeline is safely separated in propellant filling and other dangerous fluid medium filling operations of a space aircraft propulsion system, a missile attitude control power system and a carrier rocket attitude control power system, and the application prospect is good.
The invention utilizes the principles of positive pressure blowback and negative pressure absorption to control the medium leakage of the interface during the separation operation of the dangerous fluid to the pipeline. Such as: the traditional operation mode that the pipeline and the cabin are separated after the spacecraft completes propellant filling is improved, the effect that one drop of propellant cannot leak in the separation process is achieved, and safety devices such as aircraft factory environment, operating personnel and aircrafts are protected.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, 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 application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (7)
1. The utility model provides an aircraft hatch filling pipeline air suction separator which characterized in that includes: the device comprises an aircraft cabin unit (5), a filling valve (6), a stop valve K1, a stop valve K2, a stop valve K3, a stop valve K4, a stop valve K6, a vacuum valve K5, an air suction container unit (2) and a vacuum pump unit (3);
the aircraft cabin unit (5) comprises: an aircraft cabin filler port;
the filling valve (6) is matched with a filling port of the aircraft cabin body;
the filling valve (6) is connected with a stop valve K1 and a stop valve K2;
the stop valve K2 is connected with the stop valve K3 and the stop valve K4;
the stop valve K4 is connected with the empty suction container unit (2);
the vacuum container unit (2) is connected with a vacuum valve K5;
the vacuum valve K5 is connected with a vacuum pump unit (3).
2. The aircraft hatch filling line suction and separation device as recited in claim 1, further comprising: shut-off valve K7;
the cut-off valve K7 is connected with a cut-off valve K1.
3. The aircraft hatch filling line suction and separation device as recited in claim 2, further comprising: propellant storage tank (1) unit;
the shut-off valve K7 is connected to the propellant tank (1) unit.
4. The aircraft hatch filling line suction and separation device as recited in claim 1, further comprising: a vacuum gauge unit (4);
the vacuum gauge unit (4) is connected with the vacuum container unit (2) and the vacuum valve K5.
5. The aircraft hatch filling line suction and separation device as recited in claim 1, further comprising: a blowback nitrogen source unit;
the blowback nitrogen gas source unit is connected to a shutoff valve K3.
6. Aircraft hatch filling line suction separation device according to claim 1, characterised in that the shut-off valve K1 is mounted close to the hatch of the aircraft cabin unit (5).
7. The utility model provides an aircraft hatch filling pipeline air suction separator which characterized in that includes: the device comprises an aircraft cabin unit (5), a filling valve (6), a stop valve K1, a stop valve K2, a stop valve K3, a stop valve K4, a stop valve K6, a vacuum valve K5, an air suction container unit (2) and a vacuum pump unit (3);
the aircraft cabin unit (5) comprises: an aircraft cabin filler port;
the filling valve (6) is matched with a filling port of the aircraft cabin body;
the filling valve (6) is connected with a stop valve K1 and a stop valve K2;
the stop valve K2 is connected with the stop valve K3 and the stop valve K4;
the stop valve K4 is connected with the empty suction container unit (2);
the vacuum container unit (2) is connected with a vacuum valve K5;
the vacuum valve K5 is connected with a vacuum pump unit (3);
further comprising: shut-off valve K7;
the cut-off valve K7 is connected with a cut-off valve K1;
further comprising: propellant storage tank (1) unit;
the stop valve K7 is connected with the propellant storage tank (1) unit;
further comprising: a vacuum gauge unit (4);
the vacuum gauge unit (4) is connected with the vacuum container unit (2) and the vacuum valve K5;
further comprising: a blowback nitrogen source unit;
the back-blowing nitrogen source unit is connected with a stop valve K3;
the shut-off valve K1 is mounted close to the hatch of the aircraft cabin unit (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010177471.5A CN111409877A (en) | 2020-03-13 | 2020-03-13 | Air suction and separation device for aircraft hatch filling pipeline |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010177471.5A CN111409877A (en) | 2020-03-13 | 2020-03-13 | Air suction and separation device for aircraft hatch filling pipeline |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111409877A true CN111409877A (en) | 2020-07-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010177471.5A Pending CN111409877A (en) | 2020-03-13 | 2020-03-13 | Air suction and separation device for aircraft hatch filling pipeline |
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| Country | Link |
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| CN (1) | CN111409877A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2531141A1 (en) * | 1982-07-28 | 1984-02-03 | Messerschmitt Boelkow Blohm | Liquid hydrogen and oxygen space rocket |
| RU2317234C1 (en) * | 2006-06-27 | 2008-02-20 | Федеральное государственное унитарное предприятие "Научно-производственное объединение прикладной механики им. академика М.Ф. Решетнева" | Device for filling the spacecraft engine plants with xenon |
| CN101539071A (en) * | 2009-04-24 | 2009-09-23 | 北京航空航天大学 | Propellant filling device of electric arc heating engine supplying pipeline |
| CN201897082U (en) * | 2010-11-04 | 2011-07-13 | 浙江吉利汽车有限公司 | Vacuum filling residual liquid separating device |
| CN205873861U (en) * | 2016-08-15 | 2017-01-11 | 江苏新美星包装机械股份有限公司 | A raffinate collection device for filling valve valve port |
| CN109973821A (en) * | 2018-12-28 | 2019-07-05 | 上海空间推进研究所 | Propellant Loading System |
-
2020
- 2020-03-13 CN CN202010177471.5A patent/CN111409877A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2531141A1 (en) * | 1982-07-28 | 1984-02-03 | Messerschmitt Boelkow Blohm | Liquid hydrogen and oxygen space rocket |
| RU2317234C1 (en) * | 2006-06-27 | 2008-02-20 | Федеральное государственное унитарное предприятие "Научно-производственное объединение прикладной механики им. академика М.Ф. Решетнева" | Device for filling the spacecraft engine plants with xenon |
| CN101539071A (en) * | 2009-04-24 | 2009-09-23 | 北京航空航天大学 | Propellant filling device of electric arc heating engine supplying pipeline |
| CN201897082U (en) * | 2010-11-04 | 2011-07-13 | 浙江吉利汽车有限公司 | Vacuum filling residual liquid separating device |
| CN205873861U (en) * | 2016-08-15 | 2017-01-11 | 江苏新美星包装机械股份有限公司 | A raffinate collection device for filling valve valve port |
| CN109973821A (en) * | 2018-12-28 | 2019-07-05 | 上海空间推进研究所 | Propellant Loading System |
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Application publication date: 20200714 |
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| RJ01 | Rejection of invention patent application after publication |