CN112660418B - Micro-air-pressure pressurizing safety protection device for small aircraft fuel tank - Google Patents
Micro-air-pressure pressurizing safety protection device for small aircraft fuel tank Download PDFInfo
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Abstract
The invention belongs to the technical field of airplane structural strength tests, and provides a micro-air pressure pressurizing safety protection device for a small airplane oil tank, which comprises a pressurizing air path safety protection device and a pressure measuring air path safety protection device; the pressurization gas circuit safety setting, include: the device comprises a small air tank (1), a rupture membrane assembly (2), an inflation circuit pressure sensor (3) and an inflation circuit reversing valve (4); pressure measurement gas circuit safety arrangement, include: the system comprises an oil tank pressure sensor (5), a pressure measuring path reversing valve (6), a manual bypass switch (7) and a hose type micro-pressure safety air path subsystem. The invention can realize the pressure protection in the aircraft fuel tank in two ways, reduce the agnostic degree of safety measures, greatly improve the safety margin of the test, avoid the air pressure fluctuation and overload of the aircraft fuel tank and increase the safety protection device of the micro air pressure of the aircraft fuel tank.
Description
Technical Field
The invention belongs to the technical field of airplane structural strength tests, and relates to a micro-air-pressure pressurizing safety protection device for a small airplane oil tank.
Background
The small-sized airplane has limited flying height, the pressure and impact pressure of liquid in a fuel tank arranged in a wing to the fuel tank are low, but the pressure must be simulated during static test of the airplane (different airplanes and different working conditions have different pressures). The tank is simulated during a force loading test of the aircraft. The simulated pressure Δ P is generally very small, and the simulated charging pressure in the fuel tank of a small aircraft is only 9 kPa. 9kPa belongs to a micro-pressure state, the ordinary person can blow mouth air to 6kPa, the lowest range of pressure controlled by ordinary instruments and equipment (generally more than 50 kPa) is exceeded, the air source pressure is about 1MPa, and the safety and stability of micro-air pressure charging under 10KPa in the deformation of a wing oil tank are difficult under the air source pressure of 1 MPa.
At present, during most static tests of airplanes, a pressure safety line is generally arranged on a mechanical safety valve and used for limiting the upper limit value of the airplane fuel tank pressure, and due to the limitation of machinery (such as a spring), the effect of the mechanical safety valve below 20kPa is difficult to achieve, so that the pressure safety line arranged on the mechanical safety valve is far higher than the actual micro-pressure of the fuel tank, and within the pressure safety line, a pressure protection line is arranged through a pressure feedback circuit and a control circuit, and then a pressure charging valve or a switch valve is controlled to realize the control release of the gas circuit pressure. The protection is the protection setting of software in a common control system, belongs to a set of control software system together with a normal charging road, and has insufficient safety margin for large-scale and important tests.
Disclosure of Invention
The purpose of the invention is: the micro-air pressure pressurizing safety protection device for the small airplane fuel tank is provided to solve the problem of safety and stability of micro-air pressure pressurizing in the small airplane fuel tank.
In order to solve the technical problem, the technical scheme of the invention is as follows:
a micro-air pressure pressurizing safety protection device for a small aircraft oil tank comprises a pressurizing air path safety protection device and a pressure measuring air path safety protection device;
the pressurization gas circuit safety setting, include: the small-sized gas tank 1, the rupture membrane component 2, the inflation path pressure sensor 3 and the inflation path reversing valve 4;
an inlet P of the small gas tank 1 is connected with an outlet of a pressure regulating valve of a charging gas path I, a charging gas path pressure sensor 3 is arranged on the small gas tank 1, an outlet A of the charging gas path pressure sensor is connected with an inlet P of a reversing valve 4 of the charging gas path, and the blasting membrane component 2 is arranged on the middle part of the small gas tank 1; the port A of the inflation path reversing valve 4 is connected with the port P of the aircraft fuel tank, the port O is communicated with the atmosphere, and the port B is connected with the port B of the pressure measuring path reversing valve 6;
pressure measurement gas circuit safety arrangement, include: the system comprises an oil tank pressure sensor 5, a pressure measuring path reversing valve 6, a manual bypass switch 7 and a hose type micro-pressure safety gas path subsystem;
the oil tank pressure sensor 5 is arranged at an A port of an aircraft oil tank, an outlet of the oil tank pressure sensor is connected with an A port of a pressure measuring path reversing valve 6, a B port of the pressure measuring path reversing valve 6 is connected with a B port of an inflation path reversing valve 4, a P port is connected with a hose type micro-pressure safety air path subsystem, and an O port is communicated with the atmosphere; the manual bypass switch 7 is connected in parallel with the pressure measuring path reversing valve 6, the port A of the manual bypass switch is connected with the port A of the pressure measuring path reversing valve 6, and the port B of the manual bypass switch is connected with the port P of the pressure measuring path reversing valve 6.
The inflation path reversing valve 4 and the pressure measuring path reversing valve 6 are three-position four-way valves and Y-shaped machines, and an outlet B of the inflation path reversing valve 4 is connected with an outlet B of the pressure measuring path reversing valve 6.
The hose type micro-pressure safety gas circuit subsystem comprises three parts: a hose, a fixing part, a height adjusting part and a liquid filling part.
The hose and fixing portion includes: the device comprises a hose 8, a hose inlet end component 9, a scale 10, a fixing frame 11 and a hose outlet end component 15;
the hose and the fixing part are characterized in that: the P end of the inlet of the hose 8 is connected with the port B of the pressure measuring path reversing valve 6, the P end of the inlet of the hose 8 is fixed on the fixed frame 11 by the hose inlet end assembly 9, and the height of the inlet end of the hose is manually adjusted; the scale 10 is fixed on the fixed frame 11; the outlet O end of the hose 8 is fixedly connected with the piston rod end of the cylinder 13 with lock by a hose outlet end assembly 15 and can lift along with the piston rod of the cylinder 13 with lock.
The height adjusting part comprises: the device comprises a cylinder with lock 13, a displacement sensor 14, a lock switch valve 16, a rodless cavity throttle valve 18, a rodless cavity reversing valve 20, a rodless cavity reducing valve 22, a rod cavity throttle valve 17, a rod cavity reversing valve 19 and a rod cavity reducing valve 21;
the cylinder with lock 13 is provided with a cylinder position mechanical lock 13-1, the position of a cylinder piston rod can be locked by normal pressure release, and the height of the outlet end of a hose is locked;
the height adjusting part comprises: the bottom of the cylinder with lock 13 is fixed, a piston rod of the cylinder with lock can freely stretch and retract, and the displacement sensor 14 is arranged on one side of the cylinder with lock 13 and measures the extension height of the piston rod in real time; the port A of the lock switch valve 16 is communicated with the port A of the cylinder position mechanical lock 13-1, the port P is communicated with an air source, and the port O is communicated with the atmosphere;
the port A of the rod cavity throttle valve 17 is communicated with the port A of the rod cavity of the cylinder 13 with lock, the port P is communicated with the port A of the reversing valve 19 of the rod cavity, the port P of the reversing valve 19 of the rod cavity is communicated with the port A of the reducing valve 21 of the rod cavity, and the port O is communicated with the atmosphere; the P port of the reducing valve 21 with the rod cavity is communicated with an air source; the port A of the rodless cavity throttle valve 18 is communicated with the port C of the rodless cavity of the cylinder 13 with lock, the port P is communicated with the port A of the rodless cavity reversing valve 20, the port P of the rodless cavity reversing valve 20 is communicated with the port A of the rodless cavity reducing valve 22, and the port O is communicated with the atmosphere; the port P of the rodless chamber pressure relief valve 22 is in communication with a gas source.
The liquid filling part comprises a liquid filling switch 12; the liquid outlet of the liquid filling switch 12 is connected with the port C of the hose 8, and the liquid inlet of the liquid filling switch 12 is connected with a liquid medium.
The blasting membrane component 2 takes an inverted arch film as a blasting sheet.
The pressure of the hose type micro-pressure safety gas path subsystem is lower than 10 KPa.
The invention has the technical effects that:
the invention can realize the pressure protection in the aircraft fuel tank in two ways and different ways, can set and adjust the pressure safety line in real time, and ensures the stability and safety of the pressure in the test process. Can stepless test pressure that is close freely set up the protection line to can test protection effect in advance, reduce safety measure's unknown degree, greatly promote experimental safety margin, avoid aircraft tank's atmospheric pressure fluctuation and overload, increase aircraft tank micro-atmospheric pressure's safety arrangement.
Drawings
Fig. 1 is a schematic view of the micro-air pressure pressurizing safety protection device for an aircraft fuel tank.
Fig. 2 is a schematic view of a rupture disk assembly 2 of the present invention.
FIG. 3 is a schematic view of the hose inlet end fixing assembly of the present invention.
FIG. 4 is a schematic view of the hose of the present invention in an un-pressurized state with a level equilibrium.
FIG. 5 is a schematic diagram of the pressure-liquid level equilibrium state of the hose pressurization test of the present invention.
FIG. 6 is a schematic view of the liquid level balance state of the pressure protection line for the hose pressurization test according to the present invention.
Detailed Description
The invention is further illustrated with reference to the following figures and examples:
the micro-air pressure pressurizing safety protection device for the small aircraft fuel tank comprises a pressurizing air path safety protection device and a pressure measuring air path safety protection device. The pressurizing air path safety setting and the pressure measuring air path safety setting are different, and the safety margin is increased.
The pressurizing gas circuit is safely arranged for stabilizing the inflating pressure of the airplane fuel tank and protecting the fixed value of a safety line;
the pressure measuring gas circuit is safely arranged for stepless real-time arrangement of a pressure protection line in an aircraft fuel tank; the pressure protection line is lower than the safety line arranged on the pressurizing air path.
The pressurizing air path is arranged safely, and a small air tank 1, a rupture disk assembly 2 and an inflation path reversing valve 4 are arranged in a key mode. The inlet P of the small gas tank 1 is connected with the outlet of a pressure regulating valve of a pressurizing gas circuit (I path), an inflating path pressure sensor 3 is arranged on the small gas tank 1, the outlet A of the small gas tank is connected with the inlet P of an inflating path reversing valve 4, and the blasting membrane component 2 takes an inverted arch membrane as a blasting sheet and is provided with a spine (shown in figure 2) and arranged on the small gas tank 1. Sensitive blasting at micro-pressure (which can be lower than 10KPa) can be realized. The port A of the inflation path reversing valve 4 is connected with the port P of the aircraft fuel tank, the port O is communicated with the atmosphere, and the port B is connected with the port B of the pressure measuring path reversing valve 6; and (4) arranging the airplane at a close distance. When the pressure reaches the bursting pressure of the bursting membrane, the arched thin membrane is concave and is pierced by the attached sharp prick, the thin membrane is integrally burst, and the air pressure of the pressurizing air path is rapidly released. The small air tank 1 can store the test air pressure in the small air tank 1 close to the airplane before the air charging path reversing valve 4 pressurizes the airplane wing oil tank, so that the initial pressurizing time of the test is shortened; and in the loading of the airplane, the air pressure fluctuation in the loaded wing oil tank is stabilized in a close range; can provide stable gas circuit, install comparatively sensitive rupture disk device, avoid atmospheric pressure fluctuation to influence rupture disk safety blasting.
The pressure measuring gas circuit is arranged safely and mainly comprises an oil tank pressure sensor 5, a pressure measuring circuit reversing valve 6, a manual bypass switch 7 and a hose type micro-pressure (lower than 10KPa) safety gas circuit subsystem. The pressure measuring gas circuit is arranged safely, and stepless protection on the minimum difference value of the test pressure can be realized in real time through the liquid level difference in the hose.
The oil tank pressure sensor 5 is installed at an A port of an aircraft oil tank, an outlet of the oil tank pressure sensor is connected with an A port of a pressure measuring path reversing valve 6, a B port of the pressure measuring path reversing valve 6 is connected with a B port of an inflation path reversing valve 4, a P port is connected with an inlet P of a hose 8, and an O port is communicated with the atmosphere. The manual bypass switch 7 is connected in parallel with the pressure measuring path directional control valve 6, the port A of the manual bypass switch is connected with the port A of the pressure measuring path directional control valve 6, and the port B of the manual bypass switch is connected with the port P of the pressure measuring path directional control valve 6.
The inflation path reversing valve 4 and the pressure measuring path reversing valve 6 are three-position four-way valves and Y-shaped machines, an outlet B of the inflation path reversing valve 4 is connected with an outlet B of the pressure measuring path reversing valve 6, and joint adjustment of the pressure measuring gas path safety setting and the pressure measuring gas path safety setting isolation aircraft oil tank can be achieved.
The pressure measuring gas circuit is arranged safely, a hose type micro-pressure (which can be lower than 10KPa) safety gas circuit subsystem is arranged in a key mode, real-time stepless protection on the minimum difference value of the test pressure can be achieved through liquid level difference in a hose, the hose type micro-pressure (which can be lower than 10KPa) safety gas circuit subsystem can adjust the height of the hose without stopping the test when the test is carried, and stepless online adjustment of a test pressure safety line is achieved. The method comprises three parts: a hose, a fixing part, a height adjusting part and a liquid filling part.
The hose and the fixed part consist of a hose 8, a hose inlet end component 9, a scale 10, a fixed frame 11 and a hose outlet end fixed group 15;
preferably, the fixed frame 11 is made of double channel steel and stands vertically to form a vertical channel, and the hose inlet end assembly 9 can be arbitrarily moved up and down in the double channel steel channel of the fixed frame 11 to a required position and then clamped (see fig. 3). The fixed scale is corresponding to the height of the inlet of the marked hose. The hose inlet height is required to meet the liquid containment height of the maximum protection line tested.
The height adjusting part consists of a displacement sensor 14, a cylinder with lock 13, a lock switch valve 16, a rodless cavity throttle valve 18, a rodless cavity reversing valve 20, a rodless cavity reducing valve 22, a rod cavity throttle valve 17, a rod cavity reversing valve 19 and a rod cavity reducing valve 21.
The height adjusting part is provided with a mechanical lock 13-1 with a lock cylinder 13, and the mechanical lock 13-1 is normally released and locked and needs to be opened by pressure. The displacement sensor 14 feeds back the position of the cylinder piston in real time, the lock switch valve 16 releases pressure, and the mechanical lock 13-1 locks the position of the cylinder immediately.
The height adjusting part is provided with a rodless cavity pressure reducing valve 22 and a rod cavity pressure reducing valve 21 for adjusting the pressure of two cavities of the cylinder 13 with lock, so that the pressure of the cylinder with lock can meet the requirement of outward extension retraction; the pressure of the two cavities is different, so that the piston of the cylinder 13 with the lock is kept balanced, and the air pressure keeps the position of the cylinder and prevents the cylinder from flying.
The height adjusting part is fixed with a hose outlet end fixing group 15 and a displacement sensor 14 fixed on the end of a piston rod of the cylinder 13 with lock.
The height adjusting part comprises a rodless cavity throttle valve 18 and a rod cavity throttle valve 17, and the extending and retracting speed of the lock cylinder 18 is adjusted by adjusting the gas flow of the two cavities of the lock cylinder 13.
The height adjusting part comprises a rodless cavity reversing valve 20, a rod cavity reversing valve 19 and a piston movement direction adjusting cylinder 13 with a lock.
The liquid filling part mainly comprises a liquid filling switch 12 and related pipelines.
The inflation path reversing valve 4 and the pressure measuring path reversing valve 6 are three-position four-way valves, the Y-shaped machine has a Y-shaped function, and the inflation path reversing valve 4 is connected with the outlet of the pressure measuring path reversing valve 6B;
the pressure measuring gas circuit safety setting and the pressurizing gas circuit safety setting can be used for isolating the aircraft oil tank for connection debugging through the gas charging circuit reversing valve 4 and the pressure measuring circuit reversing valve 6, the protective pressure is truly simulated, whether real detection setting can be timely protected or not can be conveniently tested repeatedly, different protective lines can be conveniently tested repeatedly, and formal test pressure protective lines can be determined according to results.
Pressure measurement gas circuit safety setting and pressurization gas circuit safety setting, can realize outage meso position protection through inflation circuit switching-over valve 4, pressure measurement way switching-over valve 6, under emergency situation, can two-way short distance fast fall arrange aircraft oil tank internal gas pressure, the protection test object.
Preferably, two ends of the manual bypass switch 7 are directly connected with an inlet of the hose 8 and a pressure measuring outlet of the aircraft wing oil tank, so that the pressure measuring gas path can be ensured to be communicated with the aircraft wing oil tank in a safety arrangement in a large-scale test, and the safety margin is increased.
Examples
FIG. 1 is an example of micro-pneumatic pressurization of a wing fuel tank flap in a full-aircraft static test of a small-sized aircraft.
The test condition requires that the test pressure is constant and the charging pressure is 9KPa in the test process. The test pressure protection line is 10-12 KPa, and the test pressure safety line is 15-17 KPa.
The test pressure safety line is realized through the safety arrangement of the pressurizing air circuit. The test pressure protection line is realized through the safe arrangement of a pressure measuring air circuit.
The rupture disk assembly 2 with the customized bursting pressure of 16KPa is arranged at the middle upper part of the small-sized gas cylinder 1.
The hose type micro-pressure (which can be lower than 10KPa) safe gas circuit subsystem uses tap water as a liquid medium. Hydrostatic pressure (gauge pressure) P ═ ρ gh. ρ 10 3 Kg/m 3 ，h＝P/(ρg)。
The test pressure protection line was initially set to 10KPa, corresponding to a height difference H of 1 m.
The protective pressure superposition height a is H/2-H/2 is 0.04 m.
The liquid level at the inlet end of the hose is required to be B > (H/2+ a) ═ H/2 ═ 0.5m, and B is taken to be 0.8 m.
The height requirement E of the hose inlet is more than B, and for convenient positioning and later-stage adjustment, the distance E is 1 m.
The height of the hose outlet requires that F + B + H/2-0.8 + 0.5-1.3 m. It is also possible to test the protective pressure directly and finally determine the hose outlet height.
If the test pressure protection line is 20KPa, the corresponding height:
h2 m, a H/2-H/2 1-0.46 0.54m, B > H/2 1, B1.2 m, E > B1.5 m.
F＝B+H/2＝1.2+1＝2.2m。
This is done. Different heights can be calculated for different protection lines (e.g. 11, 12, 16 KPa). Not all are described here.
The specific operation is implemented as follows:
1. testing a pressure protection line before testing:
1) the middle positions of the gas charging path reversing valve 4 and the pressure measuring path reversing valve 6 are closed by the manual bypass switch 7, the pressure of a gas source is 1MPa, the pressure is regulated by a pressure regulating valve, the gas pressure required by the oil tank is output, and the pressure gas is firstly stored in the small gas tank 1;
2) the hose inlet end assembly 9 is moved in the holder 11, the inlet height of the hose 8 is positioned at the value E corresponding to the scale 10, and then the hose inlet end assembly 9 is fixed.
3) The lock switch valve 16 is electrified, the port P is communicated with the port A, the mechanical lock (13-1) is pressurized by air source pressure to be unlocked, the left position of the electrified part of the reversing valve 19 with the rod cavity is positioned, the port A is communicated with the atmosphere through the port O, the right position of the electrified part of the reversing valve 20 without the rod cavity is positioned at the right position, the piston 13 with the lock extends outwards under the action of the air pressure of the rod-free cavity, and the extending speed of the piston is adjusted by adjusting the throttle valve 18 with the rod cavity and the throttle valve 17 with the rod cavity;
4) the displacement sensor 14 feeds back to a set height F value, the reversing valve 19 of the rod cavity is powered off, the right position is located, the air cylinder 13 with the lock is in a balanced state at the piston under the action of the pressure reducing valve 22 of the rodless cavity and the pressure reducing valve 21 of the rod cavity, the position is kept, the on-off valve 16 of the lock is powered off and pressure is released, and the position of the air cylinder is locked by the mechanical lock (13-1).
5) The liquid filling switch 12 is turned on, tap water fills the hose 8 to enable the liquid level height in the hose 8 to reach the B value (figure 4), and the liquid filling switch 12 is turned off;
6) electromagnets on the left sides of the inflation circuit reversing valve 4 and the pressure measuring circuit reversing valve 6 are electrified, the valve position is on the left, and air pressure in the electric proportional valve 3 and the small air tank 1 is continuously input into the hose 8; the liquid level in the hose 8 produces a height difference, which is the test pressure versus height difference h (see fig. 5).
7) The pressure regulating valve continuously boosts the pressure to the test pressure protection line pressure of 10 KPa;
8) the lock switch valve 16 is electrified, the mechanical lock (13-1) is pressurized to be unlocked, the rodless cavity reversing valve 20 is electrified and positioned on the left, the port A is communicated with the atmosphere through the port O, at the moment, the rod cavity reversing valve 19 is electrified and positioned on the right, the piston of the cylinder 13 with the lock slowly retracts under the action of the air pressure of the rod cavity, when the liquid level is basically flush with the outlet of the hose, the rodless cavity reversing valve 20 is electrified and positioned on the right, the cylinder 13 with the lock is in a balanced state under the action of the rodless cavity reducing valve 22 and the rod cavity reducing valve 21, the lock switch valve 16 is electrified and releases the pressure, and the mechanical lock (13-1) locks the position of the cylinder; the liquid level difference at this time is a height difference H corresponding to the protection line pressure 10KPa (see fig. 6).
9) The pressure regulating valve continues to increase pressure, liquid in the hose 8 is instantly emptied, the air path is communicated with the atmosphere, the pressure is quickly reduced, and the reliability of the hose type micro-pressure safe air path subsystem is verified;
10) different pressure protection lines can be tested repeatedly, such as 11, 12, 16, 20KPa and the like; the theoretical height can also be verified.
2. Testing a pressure safety line before testing:
the protective effect of the burst disk can be tested.
1) The pressure protection line was set to 20KPa, and each of B, E, and F corresponded to 20 KPa. Repeat section 1, 1) -6 of this chapter).
2) The pressure regulating valve continues to be boosted, (the pressure regulating command can be given to 20 KPa); the height difference of the liquid level in the hose is continuously increased and is changed synchronously with the feedback pressure, when the feedback value reaches the bursting pressure 16KPa of the bursting diaphragm assembly 2, the bursting diaphragm bursts, the pressure of the gas circuit is rapidly reduced, and the safety setting of the pressurizing gas circuit is verified to be reliable.
3. Official test
1) Setting a pressure protection line according to a first method, and setting the pressure protection line as 10 KPa;
2) the middle position of the gas charging path reversing valve 4 and the left position of the pressure measuring path reversing valve 6 ensure that the pressure in the hose 8 is restored to the atmospheric pressure and the liquid level is level;
3) the manual bypass switch 7 is turned on, electromagnets on the right sides of the inflation circuit directional valve 4 and the pressure measuring circuit directional valve 6 are electrified, the valve position is right, the pressure regulating valve continuously outputs test pressure gas, the test pressure gas is pressurized to an airplane wing oil tank through the small gas tank 1, and meanwhile the pressure gas is input into the hose 8; until the wing oil tank is pressurized to the test pressure of 9 KPa;
4) when the airplane wings are loaded with low load, the pressure protection line is set to be 10KPa, when the airplane wings are loaded with high load, because the deformation of the airplane wings is large in the test, the pressure protection line needs to be adjusted to 11KPa on line to avoid possible fluctuation influence, when the test is carried out, the 1 st section, 3 rd to 4 th section of the current chapter are repeated, the outlet height of the hose is increased to the height position corresponding to the 11KPa, and the test is not required to be stopped (the high load area of the static test of the airplane is not allowed to be stopped).
5) And when the test is finished, the middle positions of the air charging path reversing valve 4 and the pressure measuring path reversing valve 6 of the airplane are approached, and the pressure of the airplane wing oil tank is rapidly reduced and exhausted until the atmospheric pressure is reached.
Claims (8)
1. The utility model provides a small-size aircraft tank micro-air pressure pressurization safety arrangement which characterized in that: the method comprises the steps of pressurizing air path safety protection setting and pressure measuring air path safety protection setting;
the pressurization gas circuit safety setting, include: the small-sized gas tank (1), the rupture membrane component (2), the inflation circuit pressure sensor (3) and the inflation circuit reversing valve (4);
an inlet P of the small gas tank (1) is connected with an outlet of the pressure regulating valve of the pressurized gas path I, the pressure sensor (3) of the inflation path is arranged on the small gas tank (1), an outlet A of the pressure sensor is connected with an inlet P of the reversing valve (4) of the inflation path, and the blasting membrane component (2) is arranged on the middle part of the small gas tank (1); an A port of the inflation path reversing valve (4) is connected with a P port of an aircraft fuel tank, an O port is communicated with the atmosphere, and a B port is connected with a B port of the pressure measurement path reversing valve (6);
pressure measurement gas circuit safety arrangement, include: the system comprises an oil tank pressure sensor (5), a pressure measuring path reversing valve (6), a manual bypass switch (7) and a hose type micro-pressure safety gas path subsystem;
the oil tank pressure sensor (5) is installed at an A port of an aircraft oil tank, an outlet of the oil tank pressure sensor is connected with an A port of a pressure measuring path reversing valve (6), a B port of the pressure measuring path reversing valve (6) is connected with a B port of an inflation path reversing valve (4), a P port is connected with a hose type micro-pressure safety air path subsystem, and an O port is communicated with the atmosphere; the manual bypass switch (7) is connected with the pressure measuring path reversing valve (6) in parallel, an A port of the manual bypass switch is connected with an A port of the pressure measuring path reversing valve (6), and a B port of the manual bypass switch is connected with a P port of the pressure measuring path reversing valve (6).
2. The micro-air pressure pressurizing safety protection device for the fuel tank of the small airplane as claimed in claim 1, wherein:
the inflation path reversing valve (4) and the pressure measuring path reversing valve (6) are three-position four-way valves, have Y-shaped functions, and are connected with an outlet B of the inflation path reversing valve (4) and an outlet B of the pressure measuring path reversing valve (6).
3. The micro-air pressure pressurizing safety protection device for the fuel tank of the small airplane as claimed in claim 1, wherein:
the hose type micro-pressure safety gas circuit subsystem comprises three parts: a hose, a fixing part, a height adjusting part and a liquid filling part.
4. The micro-air pressure pressurizing safety protection device for the fuel tank of the small airplane as claimed in claim 3, wherein:
the hose and fixing portion includes: the device comprises a hose (8), a hose inlet end component (9), a scale (10), a fixing frame (11) and a hose outlet end component (15);
the hose and the fixing part are characterized in that: the P end of the inlet of the hose (8) is connected with the B port of the pressure measuring path reversing valve (6), the P end of the inlet of the hose (8) is fixed on the fixed frame (11) through a hose inlet end component (9), and the height of the inlet end of the hose is manually adjusted; the scale (10) is fixed on the fixed frame (11); the O end of the outlet of the hose (8) is fixedly connected with the piston rod end of the cylinder (13) with the lock by a hose outlet end component (15), and can lift along with the piston rod of the cylinder (13) with the lock.
5. The micro-air pressure pressurizing safety protection device for the fuel tank of the small airplane as claimed in claim 3, wherein:
the height adjusting part comprises: the device comprises a cylinder with a lock (13), a displacement sensor (14), a lock switch valve (16), a rodless cavity throttle valve (18), a rodless cavity reversing valve (20), a rodless cavity reducing valve (22), a rod cavity throttle valve (17), a rod cavity reversing valve (19) and a rod cavity reducing valve (21);
the cylinder (13) with the lock is provided with a cylinder position mechanical lock (13-1), the position of a cylinder piston rod can be locked by normal pressure release, and the height of the outlet end of a hose is locked;
the height adjusting part comprises: the bottom of the cylinder (13) with the lock is fixed, a piston rod of the cylinder can freely stretch out and draw back, and a displacement sensor (14) is arranged on one side of the cylinder (13) with the lock to measure the extending height of the piston rod in real time; an A port of the lock switch valve (16) is communicated with an A port of the cylinder position mechanical lock (13-1), a P port is communicated with an air source, and an O port is communicated with the atmosphere;
the port A of the rod cavity throttle valve (17) is communicated with the port A of the rod cavity of the cylinder (13) with lock, the port P is communicated with the port A of the reversing valve (19) with the rod cavity, the port P of the reversing valve (19) with the rod cavity is communicated with the port A of the reducing valve (21) with the rod cavity, and the port O is communicated with the atmosphere; the P port of the pressure reducing valve (21) with the rod cavity is communicated with an air source; an A port of the rodless cavity throttle valve (18) is communicated with a C port of a rodless cavity of the cylinder (13) with a lock, a P port is communicated with an A port of a rodless cavity reversing valve (20), the P port of the rodless cavity reversing valve (20) is communicated with an A port of a rodless cavity reducing valve (22), and an O port is communicated with the atmosphere; the port P of the rodless cavity pressure reducing valve (22) is communicated with an air source.
6. The micro-air pressure pressurizing safety protection device for the fuel tank of the small airplane as claimed in claim 3, wherein:
the liquid filling part comprises a liquid filling switch (12); the liquid outlet of the liquid filling switch (12) is connected with the C port of the hose (8), and the liquid inlet of the liquid filling switch (12) is connected with the liquid medium.
7. The micro-air pressure pressurizing safety protection device for the fuel tank of the small airplane as claimed in claim 1, wherein:
the blasting membrane component (2) takes an inverted arch membrane as a blasting sheet.
8. The micro-air pressure pressurizing safety protection device for the fuel tank of the small airplane as claimed in claim 1, wherein:
the pressure of the hose type micro-pressure safety gas path subsystem is lower than 10 KPa.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011599499.4A CN112660418B (en) | 2020-12-29 | 2020-12-29 | Micro-air-pressure pressurizing safety protection device for small aircraft fuel tank |
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| CN202011599499.4A CN112660418B (en) | 2020-12-29 | 2020-12-29 | Micro-air-pressure pressurizing safety protection device for small aircraft fuel tank |
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