CN106275378B - Helicopter body automatic drainage device with injection function - Google Patents
Helicopter body automatic drainage device with injection function Download PDFInfo
- Publication number
- CN106275378B CN106275378B CN201610898980.0A CN201610898980A CN106275378B CN 106275378 B CN106275378 B CN 106275378B CN 201610898980 A CN201610898980 A CN 201610898980A CN 106275378 B CN106275378 B CN 106275378B
- Authority
- CN
- China
- Prior art keywords
- helicopter
- water outlet
- main body
- sealing
- connecting rod
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000002347 injection Methods 0.000 title claims abstract description 34
- 239000007924 injection Substances 0.000 title claims abstract description 34
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 131
- 238000007789 sealing Methods 0.000 claims abstract description 114
- 230000009471 action Effects 0.000 claims abstract description 10
- 230000000903 blocking effect Effects 0.000 claims description 29
- 238000007599 discharging Methods 0.000 abstract description 3
- 230000006872 improvement Effects 0.000 description 4
- 230000000670 limiting effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000002452 interceptive effect Effects 0.000 description 2
- 230000002265 prevention Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 230000003139 buffering effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K31/00—Actuating devices; Operating means; Releasing devices
- F16K31/12—Actuating devices; Operating means; Releasing devices actuated by fluid
- F16K31/18—Actuating devices; Operating means; Releasing devices actuated by fluid actuated by a float
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Revetment (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
The invention relates to the field of structural design of a helicopter body, in particular to an automatic drainage device with an injection function for the helicopter body, which at least solves the problem that water in the helicopter body cannot be drained timely and normally due to the structure of the drainage device. The automatic water discharging device includes: a sealing body; the first drainage port is formed at one end of the sealing main body; the second water outlet is formed at the other end of the sealing main body; the annular bulge is arranged on the inner annular surface of the sealing main body, and a third water outlet is formed in the center of the annular bulge; the floating body comprises a second plugging surface and a first water outlet, wherein the second plugging surface is connected with the first plugging surface through a connecting rod and is respectively configured to seal the first water outlet and the third water outlet; the ejector is used for enabling negative pressure to be formed between the inner cavity of the sealing main body and the outside under the action of external air flow; the invention has smart structure, can efficiently and automatically discharge water in the machine body, reduce workload, improve operation safety, can automatically seal, prevent electronic equipment in the machine body from being damaged and save cost.
Description
Technical Field
The invention relates to the field of structural design of helicopter bodies, in particular to an automatic drainage device with an injection function for a helicopter body.
Background
A drainage device is usually arranged in a helicopter body and is a necessary device for timely draining water in the helicopter body when the helicopter executes tasks on rainy days or on the water surface; the normal use of various electronic devices such as a radio compass in the machine body is affected and even various electronic devices are damaged because the liquid such as water in the machine body can not be discharged in time; therefore, the drainage device is an important condition for ensuring normal use of various electronic devices in the helicopter body, and is also one of important prerequisites for ensuring normal execution of tasks of the helicopter.
However, when various systems of the helicopter are designed, the machine body drainage device is often ignored at present; the most common way is to open an opening in the bottom of the skin and then plug it with a common waterproof sealing plug, and when the aircraft has performed its mission, the plugging and drainage is done manually. Due to the unreasonable design, the water drainage of the helicopter in the task execution is difficult, and due to the strong operation subjectivity, an operator often ignores the drainage and plugging of the helicopter body easily, so that the water in the helicopter body can not be drained timely and normally, various electronic equipment installed at the bottom of the helicopter body is burnt, the normal use of various electronic equipment in the helicopter body is influenced, and therefore, the cost is high, and the attendance rate and the use efficiency of the helicopter are seriously influenced.
Disclosure of Invention
The invention aims to provide an automatic helicopter body drainage device with an injection function, which at least solves the problem that water in a helicopter body cannot be drained timely and normally due to the structure of the existing helicopter body drainage device.
The technical scheme of the invention is as follows:
the utility model provides a helicopter organism automatic drainage device of function is drawn in area sets up the delivery port department of seting up on the bottom plate of helicopter organism, includes:
the sealing main body is arranged at the water outlet of the bottom plate in a sealing manner, and an inner cavity is formed inside the sealing main body;
the first drainage port is formed in one end, close to the helicopter body, of the sealing main body and is used for communicating the inner cavity of the sealing main body with the inner cavity of the helicopter body;
the second water outlet is formed in one end, back to the helicopter body, of the sealing main body and used for communicating the inner cavity of the sealing main body with the outside of the helicopter body;
the annular bulge is arranged on the inner annular surface of the sealing main body along the radial direction, and a third water outlet is formed in the center of the annular bulge;
the floating body is provided with an I-shaped axial section and comprises a connecting rod, a first blocking surface and a second blocking surface, wherein the first blocking surface and the second blocking surface are fixedly arranged at the end parts of the two ends of the connecting rod;
the ejector is arranged at the second water outlet of the sealing main body in a sealing mode, the inner cavity of the sealing main body is communicated with the outside through the ejector, and the ejector is used for enabling negative pressure to be formed between the inner cavity of the sealing main body and the outside through the action of external air flow.
Preferably, the helicopter body automatic drainage device with the guiding function further comprises:
the positioning shaft is arranged in the sealing main body along the direction vertical to the bottom plate, and one end part of the positioning shaft is fixed on the ejector;
one end of the floating body close to the ejector is provided with a groove matched with the positioning shaft, and the floating body is sleeved on the positioning shaft through the groove in a sliding mode.
Preferably, the connecting rod of the floating body comprises a first connecting rod and a second connecting rod which is sleeved on the first connecting rod in a sliding manner along the axis direction; the connecting part of the first connecting rod and the second connecting rod can be of various suitable structures, for example, an inner hole is formed in the end part of the first connecting rod, and one end of the second connecting rod extends into the inner hole to realize sliding fit;
the first plugging surface is fixed at one end of the first connecting rod, which is far away from the second connecting rod;
the second plugging surface is fixed at one end of the second connecting rod, which is far away from the first connecting rod, and the groove is formed in the second connecting rod;
the sliding connection part of the first connecting rod and the second connecting rod is configured to enable the first blocking surface and the second blocking surface to respectively seal the first water discharge port and the third water discharge port; namely, the first water discharge opening is sealed by the first sealing surface, the third water discharge opening is sealed by the second sealing surface, and the first sealing surface and the second sealing surface are not interfered with each other; in addition, the length of the sliding fit part of the first connecting rod and the second connecting rod is set to ensure that the first plugging surface floats to the topmost part and the second plugging surface does not separate when descending to the bottommost part;
when water enters from the second water outlet, the second blocking surface floats upwards to seal the third water outlet, but sometimes, because the water flow speed is overlarge, part of water possibly enters into an inner cavity between the first water outlet and the third water outlet before sealing; at the moment, the first plugging surface can float upwards under the action of the part of water, so that the first drainage port is sealed; the structure equivalently realizes two-stage stepped sealing, so that the sealing performance is more stable, the speed of water entering the inner cavity between the first water outlet and the third water outlet is relatively low due to the buffering effect of the annular convex part, and the sealing performance of the first sealing surface arranged at the moment can be greatly guaranteed.
Preferably, the helicopter body automatic drainage device with the guiding function further comprises:
the first sealing ring is fixedly arranged at the first water drainage port and is positioned between the first blocking surface and the first water drainage port;
and the second sealing ring is fixedly arranged at the third water outlet and is positioned between the second plugging surface and the third water outlet.
Preferably, the ejector comprises an inner cavity, and a fourth water outlet and a fifth water outlet which are communicated with the inner cavity;
the fourth water outlet is communicated with the second water outlet in a sealing way;
and the outlet direction of the fifth water outlet is vertical to the outlet direction of the second water outlet and opposite to the heading direction of the helicopter.
Preferably, an injection hole is formed in the injector, and the outlet direction of the injection hole is perpendicular to the outlet direction of the second water outlet.
Preferably, the injection hole is an inclined hole, the direction of the inclined hole is basically towards the course direction of the helicopter, and a preset included angle is formed between the inclined hole and the course direction; and may be between 30 deg. -60 deg..
Preferably, a rectangular opening is formed in the ring body at one end, far away from the bottom plate, of the sealing main body, the thickness of the ejector is equal to that of the rectangular opening, and the ejector comprises a matching part and an extending part;
the matching part penetrates through the rectangular notch along the direction parallel to the bottom plate and is inserted into the sealing main body, the shape of the matching part is matched with that of the sealing main body of the inserting part of the matching part, and the fourth water outlet is formed in the matching part; specifically, the matching part is a semicircular box which is formed by fixedly connecting two semicircular plates which are oppositely arranged and a semicircular ring, the diameter direction of the box is not closed, and the fourth water outlet is formed in the semicircular plate which faces the bottom plate of the helicopter;
the extension part is in a cuboid shape, one end of the extension part is connected with the matching part, the other end of the extension part is provided with the fifth water outlet, and the injection hole is formed in the side face of the extension part in the horizontal direction; the number of the injection holes can be two, one side is provided, and the injection holes are symmetrically distributed; specifically, the extension part is composed of four plates, wherein the width of two opposite plates is equal to the width of the rectangular gap; one of the two opposite openings is connected with the unclosed opening of the matching part in a sealing way, and the other opening is the fifth water discharge opening.
Preferably, the helicopter body automatic drainage device with the guiding function further comprises a connecting piece, and the connecting piece comprises:
the base is parallel to the bottom plate and is fixedly arranged on the bottom plate, and a through hole with the same shape as the water outlet on the bottom plate is formed in the middle of the base;
the connecting part is positioned on one side of the base, which faces away from the bottom plate, and one end of the sealing main body, which is close to the bottom plate, is fixedly sleeved on the connecting part.
Preferably, one end of the sealing main body close to the bottom plate is fixedly sleeved on the connecting part through a rivet.
The invention has the advantages that:
according to the automatic helicopter body drainage device with the jet guiding function, when water exists outside the helicopter body, the floating body can seal the first drainage port and the third drainage port under the buoyancy action of the water, so that the automatic sealing function is realized; when no water exists outside the drainage device and accumulated water exists in the helicopter body, the floating body is far away from the first drainage port under the action of the self weight, so that the accumulated water is discharged from the second drainage port, automatic drainage is realized, and the ejector can form negative pressure between the inner cavity of the sealing main body and the outside under the action of external airflow, so that the automatic drainage efficiency is further accelerated; the automatic drainage device with the guiding and jetting function for the helicopter body has the advantages of ingenious structure, capability of efficiently and automatically draining water in the helicopter body, reduction in workload, improvement in operation safety, automatic sealing, prevention of damage to electronic equipment in the helicopter body, cost saving and improvement in stability.
Drawings
FIG. 1 is a perspective view of one aspect of the automatic drainage device for a helicopter body with an injection function according to the present invention;
FIG. 2 is a perspective view of another perspective of the automatic drainage device for a helicopter body with an injection function of the present invention;
FIG. 3 is an exploded view of the automatic drainage device of the helicopter body with a pilot function of the present invention;
FIG. 4 is a cross-sectional view of the automatic drainage device of the helicopter body with the pilot function of the present invention;
FIG. 5 is a schematic structural view of a floating body of another embodiment of the automatic water discharging device of the helicopter body with the guiding function of the present invention;
FIG. 6 is an injection schematic diagram of the helicopter body automatic drainage device with the injection function in the use process.
The sealing structure comprises a sealing main body, 11-a first drainage port, 12-a second drainage port, 13-an annular bulge, 14-a third drainage port, 15-a rectangular opening, 2-a floating body, 21-a connecting rod, 211-a first connecting rod, 212-a second connecting rod, 22-a first sealing surface, 23-a second sealing surface, 24-a groove, 3-an ejector, 31-a fourth drainage port, 32-a fifth drainage port, 33-an ejector hole, 34-a matching part, 35-an extending part, 4-a positioning shaft, 51-a first sealing ring, 52-a second sealing ring, 6-a connecting piece, 61-a base, 62-a connecting part and 7-a bottom plate.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings, which are based on the orientation or positional relationship shown in the drawings, and are used for convenience of description and simplicity of description, but do not indicate or imply that the device or element so referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the invention.
The automatic drainage device with guiding function for helicopter body of the present invention will be further described in detail with reference to fig. 1 to 6.
The invention provides an automatic drainage device with an injection function for a helicopter body, which is arranged at a water outlet formed on a bottom plate 7 (also called a skin, see figure 4) of the helicopter body and is used for discharging water entering the interior of the helicopter body from the water outlet under a preset condition and preventing external water from entering the interior of the helicopter body from the water outlet under the preset condition; wherein the predetermined condition may be, for example, that the helicopter is hovering above the water surface or flying at a close distance to the water surface in relation to a water flight mission.
The invention relates to an automatic drainage device with an injection function for a helicopter body, which comprises a sealing main body 1, a first drainage port 11, a second drainage port 12, an annular bulge 13, a floating body 2 and an injector 3.
The sealing main body 1 is arranged at the water outlet of the bottom plate 7 in a sealing way, and an inner cavity is formed inside the sealing main body.
The first water discharge port 11 is provided at an end of the sealing main body 1 close to the helicopter body (i.e. a top end surface of the sealing main body 1 when the helicopter is flying normally), and is used for communicating an inner cavity of the sealing main body 1 with the inner cavity of the helicopter body.
A second water outlet 12 is provided at an end of the sealing body 1 facing away from the helicopter body (i.e. the bottom end surface of the sealing body 1 when the helicopter is flying normally) for communicating the inner cavity of the sealing body 1 with the outside of the helicopter body.
The annular projection 13 is provided on the inner circumferential surface of the sealing body 1 in the radial direction, and a third drain port 14 is formed at the center. The annular protrusion 13 and the sealing body 1 may be fixedly connected in various suitable manners, and in this embodiment, the annular protrusion 13 and the sealing body 1 are preferably formed as an integral structure.
The axial section of the floating body 2 is I-shaped, and comprises a connecting rod 21, and a first sealing surface 22 and a second sealing surface 23 which are fixedly arranged (welded or integrally formed) at the two end parts of the connecting rod 21. Wherein, the first blocking surface 22 is positioned in the inner cavity between the first water discharge opening 11 and the third water discharge opening 14; the second blocking surface 23 is positioned in the inner cavity between the third water discharge opening 14 and the second water discharge opening 12; the connecting rod 21 passes through the third water discharge port 14; the first sealing surface 22 is shaped and sized to seal the first drain port 11, and the second sealing surface 23 is shaped and sized to seal the third drain port 14. Of course, depending on the specific structure of the floating body 2, the sealing between the two parts may be simultaneous or non-interfering, for example, if the connecting rod 21 is one body, two-stage simultaneous sealing may be achieved, and if the connecting rod 21 is configured to be separate bodies and slide relatively, two-stage stepped sealing may be achieved.
The ejector 3 is arranged at the second water outlet 12 of the sealed main body 1 in a sealed mode, the inner cavity of the sealed main body 1 is communicated with the outside through the ejector 3, and the ejector 3 is used for enabling negative pressure to be formed between the inner cavity of the sealed main body 1 and the outside under the action of external air flow. Referring to fig. 6, when the helicopter flies along the arrow direction (the aircraft heading) on the right side of the drawing, airflow is generated at the automatic drainage device at the bottom of the helicopter (see the arrow direction at the bottom of the helicopter in the drawing), the outlet of the ejector 3 is arranged in a proper direction (basically along the wind direction, and the specific angle can be properly selected according to needs), so that negative pressure is formed between the inner cavity of the sealing main body 1 and the outside, and the water flow is accelerated to be discharged.
According to the helicopter body automatic drainage device with the guiding function, when water exists outside the helicopter body, the floating body 2 can seal the first drainage port 11 and/or the third drainage port 14 under the buoyancy action of the water, so that the automatic sealing function is realized; when no water exists outside the drainage device and accumulated water exists in the helicopter body (namely, the helicopter is possibly far away from the water surface at the moment, no water can flow into the helicopter body from the second drainage port 12), the floating body 2 is far away from the first drainage port under the action of the self weight, so that the accumulated water is drained from the second drainage port 12 (and subsequently drained from the fifth drainage port 32), and automatic drainage is realized; and, owing to set up ejector 3, can make and form the negative pressure between the inner chamber of sealed main part 1 and the external world in the effect of outside air current to further accelerate automatic drainage efficiency.
The automatic helicopter body drainage device with the guiding function has the advantages of ingenious structure, capability of efficiently and automatically draining water in the body, reduction in workload, improvement in operation safety, automatic sealing, prevention of damage to electronic equipment in the body, cost saving and improvement in stability.
The helicopter body automatic drainage device with the guiding function can also comprise a positioning shaft 4; the positioning shaft 4 is arranged in the sealing main body 1 along the direction vertical to the bottom plate 7, and one end part of the positioning shaft is fixed on the ejector 3 (the top part); in addition, a groove 24 matched with the positioning shaft 4 is formed in one end, close to the ejector 3, of the floating body 2, the floating body 2 is sleeved on the positioning shaft 4 in a sliding mode through the groove 24, the floating body 2 can slide along the axis direction of the positioning shaft 4, the limiting effect is achieved, and the stability can be enhanced.
It should be noted that, in the structure of the automatic drainage device with an injection function for a helicopter body of the present invention, the outer contour structure of the sealing main body 1, the inner cavity structure thereof, etc. can be set to various suitable shape structures according to the needs, for example, the outer contour structure can be set according to the shape of the water outlet of the bottom plate 7 of the helicopter body; the first drain port 11, the second drain port 12, and the floating body 2 may be appropriately provided in shape and structure as needed.
In the automatic drainage device structure of the helicopter body with the guiding function, the water outlet on the bottom plate 7 of the helicopter is a circular opening, correspondingly, the sealing main body 1 is cylindrical, and the first drainage port 11 and the second drainage port 12 are circular openings.
Further, in the helicopter body automatic drainage device structure with the guidance function of the present invention, the connection rod 21 of the floating body 2 comprises a first connection rod 211 and a second connection rod 212 slidably sleeved on the first connection rod 211 along the axial direction; in this embodiment, as shown in fig. 5, an inner hole is formed at an end of the first connecting rod, and one end of the second connecting rod extends into the inner hole to realize sliding fit.
Specifically, the first blocking surface 22 is fixed at one end of the first connecting rod 211 away from the second connecting rod 212; the second blocking surface 23 is fixed at an end of the second connecting rod 212 far from the first connecting rod 211, and the groove 24 is opened inside the second connecting rod 212.
The sliding connection portion between the first connecting rod 211 and the second connecting rod 212 is arranged so that the first sealing surface 22 and the second sealing surface 23 can seal the first drain port 11 and the third drain port 14, respectively. That is, the first drain opening 11 is sealed by the first sealing surface 22, and the third drain opening 14 is sealed by the second sealing surface 23 without interfering with each other. Further, the length of the sliding fit portion between the first connecting rod 211 and the second connecting rod 212 is set to ensure that the first blocking surface 22 floats to the top and the second blocking surface does not separate when it descends to the bottom.
When water enters from the second water discharge opening 12, the second blocking surface 23 floats upwards firstly to seal the third water discharge opening 14, but sometimes, due to overlarge water flow speed, part of water may enter the inner cavity between the first water discharge opening 11 and the third water discharge opening 14 before the water enters the inner cavity; at this time, the first blocking surface 22 can float up by the partial water, thereby sealing the first drain port 11. The structure is equivalent to the realization of two-stage stepped sealing, so that the sealing performance is more stable, and the speed of water entering the inner cavity between the first water discharge port 11 and the third water discharge port 14 is relatively lower due to the buffer effect of the annular bulge 13 part, and the sealing performance of the first blocking surface 22 arranged at the moment can be more greatly guaranteed, namely, the water is more effectively prevented from flowing through the first water discharge port 11.
The structure of the automatic drainage device with the guiding function for the helicopter body of the invention can further comprise a first sealing ring 51 and a second sealing ring 52, and the two sealing rings can be made of various known materials with appropriate sealing performance. The first sealing ring 51 is fixedly arranged at the first drainage port 11 and is positioned between the first blocking surface 22 and the first drainage port 11; the second sealing ring 52 is fixedly disposed at the third drain opening 14 and located between the second blocking surface 23 and the third drain opening 14.
The automatic helicopter body drainage device structure with the injection function can further comprise an injection hole 33 arranged on the injector 3, and the outlet direction of the injection hole 33 is perpendicular to the outlet direction of the second water outlet 12; further, the injection hole is preferably an inclined hole, the direction of the inclined hole is basically towards the heading direction of the helicopter, and a preset included angle is formed between the inclined hole and the heading direction and can be 30-60 degrees. The injection hole 33 is arranged, so that negative pressure can be formed between the inner cavity of the sealing main body 1 and the outside at the injection hole 33, and the drainage efficiency is further improved.
Similarly, in the structure of the helicopter body automatic drainage device with the injection function, the outer contour structure, the inner cavity structure and the like of the injector 3 can be set into various suitable shape structures according to requirements.
In this embodiment, the ejector 3 includes an inner cavity, and a fourth drain port 31 and a fifth drain port 32 communicated with the inner cavity. The fourth water discharge port 31 is in sealed communication with the second water discharge port 12; the outlet direction of the fifth water outlet 32 is perpendicular to the outlet direction of the second water outlet 12 and opposite to the heading direction of the helicopter, so that the air flow generated by the helicopter in flight can be utilized to the maximum extent, negative pressure is formed between the inner cavity of the sealed main body and the outside, and the water drainage speed is accelerated.
Further, a rectangular opening 15 is formed in the ring body at one end, far away from the bottom plate 7, of the sealing main body 1; the thickness of the ejector 3 is equal to the rectangular gap 15, and the ejector 3 may include a fitting portion 34 and an extension portion 35.
The matching part 34 penetrates through the rectangular notch 15 along the direction parallel to the bottom plate 7 and is inserted into the sealing main body 1, the shape of the matching part 34 is matched with that of the sealing main body 1 of the inserted part, and the fourth water outlet 31 is arranged on the matching part. Specifically, the fitting portion 34 is a substantially semicircular box formed by fixedly connecting two semicircular plates disposed opposite to each other and a semicircular ring, the diameter direction of the box is not closed, and the fourth water discharge port 31 is opened in the semicircular plate facing the bottom plate of the helicopter; the fourth drain opening 31 has a circular hole shape, a petal shape, a fan shape, or the like.
The extension 35 is rectangular, one end of the extension is connected to the fitting portion 34, the other end of the extension is provided with a fifth drain opening 32, and the injection hole 33 is provided on the side surface of the extension 35 in the horizontal direction (the direction parallel to the bottom plate 7); and the number of the injection holes 33 can be two, one on one side surface, and the injection holes are symmetrically distributed. Specifically, the extension 35 is formed by four plates, two of which have a width equal to the width of the rectangular notch 15; one of the two opposite openings is formed to be hermetically connected with the unsealed opening of the fitting portion 34, and the other opening is the fifth drain opening 32.
In the automatic helicopter body drainage device structure with the guiding function, a sealing main body 1 and a helicopter bottom plate 7 can adopt a certain suitable connection mode, such as direct welding; in this embodiment, a connection element 6 may also be included, primarily for connecting the sealing body 1 to a helicopter bedplate 7. Specifically, the connecting member 6 includes a base 61 and a connecting portion 62.
The base 61 can be a plate-shaped structure, is parallel to the bottom plate 7 and is fixedly arranged on the bottom plate 7 through bolts or rivets, and the middle part of the base 61 is provided with a through hole with the same shape as the water outlet on the bottom plate 7.
The connecting part 62 is cylindrical and is located on the side of the base 61 back to the bottom plate 7, and one end of the sealing main body 1 close to the bottom plate 7 is fixedly sleeved on the connecting part 62 through bolts or welding. Further, because the ejector 3 is the bottom of the fixed connecting portion 62, in order to ensure that the outlet direction of the fifth drain opening 32 is opposite to the heading direction of the helicopter after installation, in this embodiment, the end of the sealing main body 1 close to the bottom plate 7 is preferably fixedly sleeved on the connecting portion 62 through rivets, so that alignment installation is more convenient.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (6)
1. The utility model provides a helicopter organism automatic drainage device of function is drawn in area sets up the delivery port department of seting up on bottom plate (7) of helicopter organism, its characterized in that includes:
the sealing main body (1) is arranged at the water outlet of the bottom plate (7) in a sealing mode, and an inner cavity is formed inside the sealing main body;
the first drainage port (11) is formed in one end, close to the helicopter body, of the sealing main body (1) and is used for communicating an inner cavity of the sealing main body (1) with the inner cavity of the helicopter body;
the second water outlet (12) is formed in one end, back to the helicopter body, of the sealing main body (1) and used for communicating the inner cavity of the sealing main body (1) with the outside of the helicopter body;
the annular bulge (13) is arranged on the inner annular surface of the sealing main body (1) along the radial direction, and a third water outlet (14) is formed in the center;
the floating body (2) is I-shaped in axial section and comprises a connecting rod (21), and a first blocking surface (22) and a second blocking surface (23) which are fixedly arranged at the end parts of the two ends of the connecting rod (21), wherein the first blocking surface (22) is positioned in an inner cavity between the first water discharge port (11) and the third water discharge port (14), the second blocking surface (23) is positioned in an inner cavity between the third water discharge port (14) and the second water discharge port (12), the first blocking surface (22) is configured to seal the first water discharge port (11), and the second blocking surface (23) is configured to seal the third water discharge port (14);
the ejector (3) is hermetically arranged at the second water outlet (12) of the sealing main body (1), the inner cavity of the sealing main body (1) is communicated with the outside through the ejector (3), and the ejector (3) is used for enabling negative pressure to be formed between the inner cavity of the sealing main body (1) and the outside under the action of external air flow;
further comprising:
the positioning shaft (4) is arranged in the sealing main body (1) along the direction vertical to the bottom plate (7), and one end part of the positioning shaft is fixed on the ejector (3);
one end of the floating body (2) close to the ejector (3) is provided with a groove (24) matched with the positioning shaft (4), and the floating body (2) is sleeved on the positioning shaft (4) in a sliding manner through the groove (24);
the connecting rod (21) of the floating body (2) comprises a first connecting rod (211) and a second connecting rod (212) which is sleeved on the first connecting rod (211) in a sliding mode along the axis direction;
the first plugging surface (22) is fixed at one end of the first connecting rod (211) far away from the second connecting rod (212);
the second plugging surface (23) is fixed at one end of the second connecting rod (212) far away from the first connecting rod (211), and the groove (24) is formed in the second connecting rod (212);
the sliding connection part of the first connecting rod (211) and the second connecting rod (212) is configured to enable the first blocking surface (22) and the second blocking surface (23) to respectively seal the first water discharge opening (11) and the third water discharge opening (14);
the ejector (3) comprises an inner cavity, and a fourth water outlet (31) and a fifth water outlet (32) which are communicated with the inner cavity;
the fourth water outlet (31) is communicated with the second water outlet (12) in a sealing way;
the outlet direction of the fifth water outlet (32) is vertical to the outlet direction of the second water outlet (12) and opposite to the heading direction of the helicopter;
an injection hole (33) is formed in the injector (3), and the outlet direction of the injection hole (33) is perpendicular to the outlet direction of the second water outlet (12).
2. The automatic drainage device with guiding function for helicopter body of claim 1 further comprising:
the first sealing ring (51) is fixedly arranged at the first drainage port (11) and is positioned between the first blocking surface (22) and the first drainage port (11);
and the second sealing ring (52) is fixedly arranged at the third water outlet (14) and is positioned between the second blocking surface (23) and the third water outlet (14).
3. The helicopter body automatic drainage device with injection function of claim 1, characterized in that the injection hole (33) is an inclined hole, which is opened in a direction substantially towards the course direction of the helicopter and forms a predetermined angle with the course direction.
4. The automatic helicopter body drainage device with the injection function according to claim 3 is characterized in that a rectangular opening (15) is formed in a ring body at one end of the sealing main body (1) far away from the bottom plate (7), the thickness of the injector (3) is equal to that of the rectangular opening (15), and the injector (3) comprises a matching part (34) and an extending part (35);
the matching part (34) penetrates through the rectangular notch (15) along the direction parallel to the bottom plate (7) and is inserted into the sealing main body (1), the shape of the matching part (34) is matched with that of the sealing main body (1) of the inserted part of the matching part, and the fourth water outlet (31) is formed in the matching part (34);
the extension part (35) is cuboid, one end of the extension part is fixedly connected with the matching part (34), the other end of the extension part is provided with the fifth water outlet (32), and the injection hole (33) is formed in the side face of the extension part (35) in the horizontal direction.
5. The automatic drainage device with guiding function for helicopter body according to any of claims 1-4, characterized by further comprising a connecting piece (6), wherein said connecting piece (6) comprises:
the base (61) is parallel to the bottom plate (7) and is fixedly arranged on the bottom plate (7), and a through hole with the same shape as a water outlet on the bottom plate (7) is formed in the middle of the base (61);
the connecting part (62) is positioned on one side, back to the bottom plate (7), of the base (61), and one end, close to the bottom plate (7), of the sealing main body (1) is fixedly sleeved on the connecting part (62).
6. The automatic drainage device with guiding function for helicopter bodies according to claim 5 characterized in that the end of said sealing body (1) close to said bottom plate (7) is fixedly sleeved on said connection portion (62) by means of rivets.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610898980.0A CN106275378B (en) | 2016-10-14 | 2016-10-14 | Helicopter body automatic drainage device with injection function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610898980.0A CN106275378B (en) | 2016-10-14 | 2016-10-14 | Helicopter body automatic drainage device with injection function |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106275378A CN106275378A (en) | 2017-01-04 |
| CN106275378B true CN106275378B (en) | 2023-02-28 |
Family
ID=57718183
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610898980.0A Active CN106275378B (en) | 2016-10-14 | 2016-10-14 | Helicopter body automatic drainage device with injection function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106275378B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109373033B (en) * | 2018-11-09 | 2020-07-28 | 中国直升机设计研究所 | Waterproof vent valve for helicopter fuel tank |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU94027814A (en) * | 1994-07-25 | 1996-06-27 | Ю.С. Воронков | Liquid discharge door control system of flying vehicle |
| US5655732A (en) * | 1994-03-14 | 1997-08-12 | Daimler-Benz Aerospace Airbus Gmbh | Apparatus for draining waste water from aircraft |
| CN1420085A (en) * | 2001-11-15 | 2003-05-28 | 中国科学院生态环境研究中心 | Mthod and device for injection dissolution of gas for circulation water |
| WO2003076224A2 (en) * | 2002-03-04 | 2003-09-18 | Teacherson George A | Ducted channel wing, high-lift devices and vehicles therefor |
| JP2015107794A (en) * | 2013-10-21 | 2015-06-11 | 泰工技研工業株式会社 | Compressed air fluid machine, continuously compressed fluid jetting propulsion apparatus and propulsion system for ship using the same, and propulsion apparatus using gas-liquid mixed fluid machine |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3630631B2 (en) * | 2000-12-11 | 2005-03-16 | 新明和工業株式会社 | Liquid dropping device for helicopter |
| US8074933B2 (en) * | 2008-02-26 | 2011-12-13 | Goodrich Corporation | Aircraft graywater ejection system |
| FR2994943B1 (en) * | 2012-08-30 | 2014-09-12 | Turbomeca | DRAINING METHOD AND PURGE COLLECTOR FOR CARBURIZING CIRCUIT OF A HELICOPTER |
| EP3028941B1 (en) * | 2014-12-03 | 2019-07-10 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A drainage end cap device for draining fluid from a hollow space in a vehicle |
-
2016
- 2016-10-14 CN CN201610898980.0A patent/CN106275378B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5655732A (en) * | 1994-03-14 | 1997-08-12 | Daimler-Benz Aerospace Airbus Gmbh | Apparatus for draining waste water from aircraft |
| RU94027814A (en) * | 1994-07-25 | 1996-06-27 | Ю.С. Воронков | Liquid discharge door control system of flying vehicle |
| CN1420085A (en) * | 2001-11-15 | 2003-05-28 | 中国科学院生态环境研究中心 | Mthod and device for injection dissolution of gas for circulation water |
| WO2003076224A2 (en) * | 2002-03-04 | 2003-09-18 | Teacherson George A | Ducted channel wing, high-lift devices and vehicles therefor |
| JP2015107794A (en) * | 2013-10-21 | 2015-06-11 | 泰工技研工業株式会社 | Compressed air fluid machine, continuously compressed fluid jetting propulsion apparatus and propulsion system for ship using the same, and propulsion apparatus using gas-liquid mixed fluid machine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106275378A (en) | 2017-01-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106275378B (en) | Helicopter body automatic drainage device with injection function | |
| CN104088793A (en) | Air intake control valve assembly of air compressor | |
| CN105958091B (en) | A kind of waterproof and breathable fuel-cell device on unmanned plane | |
| CN204477272U (en) | Air-breather and automotive power assembly | |
| DE212018000025U1 (en) | Impeller with removable wings | |
| CN104863825B (en) | Intake valve and energy-conservation gas handling system | |
| CN203940107U (en) | A kind of gas-liquid separator valve with warning function | |
| CN106428517B (en) | Helicopter body automatic drainage device with blades | |
| CN115154954B (en) | A water-drawing device for amphibious aircraft with feedback mechanism guide ribs | |
| CN206786060U (en) | A kind of guide diaphragm type electromagnetic driven stop valve | |
| CN105297854A (en) | Water inlet valve and water outlet noise reducing structure thereof | |
| CN112431850B (en) | Bearing with adjustable sealing structure | |
| CN211259750U (en) | One-way interface gas circuit replacing device | |
| CN205602135U (en) | Many rotors plant protection medical kit for unmanned aerial vehicle | |
| CN211350817U (en) | A negative pressure suction nozzle for lithium titanate battery formation | |
| CN203664055U (en) | Shower head | |
| CN209959930U (en) | Vacuum breaker with reliable structure | |
| CN211039733U (en) | Air leakage prevention air valve | |
| CN204756235U (en) | Coupling that area cut off function | |
| CN208494543U (en) | Dedusting device between grinding roller on eight-roller mill | |
| CN219281782U (en) | Interlocking control cuts off tee bend device for colliery | |
| CN114087041B (en) | Dehumidifying separator for steam turbine | |
| CN211190722U (en) | Plunger type cooling nozzle | |
| CN104534135A (en) | Waterproof ventilation valve with pressure limiting function | |
| CN209818826U (en) | Novel air release valve |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |