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CN-117141727-B - Static pressure hole device and static pressure hole system for aircraft

CN117141727BCN 117141727 BCN117141727 BCN 117141727BCN-117141727-B

Abstract

The invention relates to a static hole device for an aircraft, comprising a first static hole part which is fixedly arranged relative to the skin of the aircraft, and a second static hole part which comprises one end facing the outside of the aircraft and the other end which is positioned inside the skin and faces the first static hole part, wherein the second static hole part is provided with an air guide hole for sensing the external static pressure at one end and is releasably attached to the skin and is connected to the first static hole part at the other end. By adopting the two-piece hydrostatic hole parts, the external quick assembly and disassembly (assembly and disassembly can be performed from the outside) of the hydrostatic hole device can be realized, so that the maintenance or replacement cost is reduced, and the time is saved. The invention also relates to a static pressure hole system.

Inventors

  • YUAN WENDUO
  • ZHAO JIAN

Assignees

  • 中国商用飞机有限责任公司
  • 中国商用飞机有限责任公司上海飞机设计研究院

Dates

Publication Date
20260512
Application Date
20230825

Claims (9)

  1. 1. A static port assembly for an aircraft, the static port assembly comprising: -a first hydrostatic aperture component (300), the first hydrostatic aperture component (300) being fixedly arranged relative to a skin (100) of the aircraft; A second hydrostatic hole part (400), the second hydrostatic hole part (400) comprising an end facing the outside of the aircraft and another end located within the skin (100) and facing the first hydrostatic hole part (300), the second hydrostatic hole part (400) being provided at one end thereof with an air vent (410) for sensing external static pressure and being releasably attached to the skin (100) and being connected at the other end thereof to the first hydrostatic hole part (300), further comprising an intermediate connecting element (500) for connecting the other end of the second hydrostatic hole part (400) with the first hydrostatic hole part (300) such that fluid flowing in from the air vent (410) can flow from the second hydrostatic hole part (400) into the first hydrostatic hole part (300) via the intermediate connecting element (500), the intermediate connecting element (500) being configured with a variable length such that the second hydrostatic hole part (400) can change its position relative to the first hydrostatic hole part (300).
  2. 2. The hydrostatic port device of claim 1, wherein the intermediate connection element (500) is configured as a drawable hose.
  3. 3. The hydrostatic port device of claim 1 or 2, wherein the second hydrostatic port member (400) includes an air guide line (420) in communication with the air guide hole (410), the air guide line (420) being in fluid communication with the first hydrostatic port member (300), wherein the air guide line (420) is configured to extend in a shape of a steepest curve converging toward the other end of the second hydrostatic port member (400).
  4. 4. The hydrostatic port device of claim 1 or 2, wherein the second hydrostatic port member (400) is further provided at one end thereof with an outwardly open mounting hole (430) for mounting an airtight clamp.
  5. 5. A hydrostatic port system, the hydrostatic port system comprising: a hydrostatic port device as defined in any one of claims 1 to 4; -a mounting part (200), the mounting part (200) comprising a first end (402) close to the skin (100) and a second end (404) facing away from the skin (100) towards the interior of the aircraft, the mounting part (200) being fixedly connected to the skin (100) at its first end (402); wherein the first hydrostatic port member (300) is fixedly connected to the mounting member (200) at a second end (404) thereof.
  6. 6. The hydrostatic port system of claim 5, further comprising a conformal member (600) for adjusting a step, the conformal member (600) being fixedly connected thereto at a first end (402) of the mounting member (200), the second hydrostatic port member (400) being releasably attached to the conformal member (600) at one end thereof.
  7. 7. The hydrostatic port system of claim 5, wherein the mounting member (200) is configured as a cylinder including a base (240) disposed at a second end (404) thereof, the base (240) including a pass-through opening (242), the first hydrostatic port member (300) being positionable on the base (240) and at least a portion thereof extending through the pass-through opening.
  8. 8. The hydrostatic port system of claim 7, wherein the at least a portion of the first hydrostatic port member (300) passing through the pass-through opening (242) includes an external conduit connection (310) and/or an external electrical connection (320).
  9. 9. The hydrostatic aperture system of claim 6, wherein the second hydrostatic aperture member (400) includes an axially extending conformal member mounting face (440), the second hydrostatic aperture member (400) being coupled to the conformal member (600) via the conformal member mounting face (440) by a threaded engagement or a form-fit engagement.

Description

Static pressure hole device and static pressure hole system for aircraft Technical Field The present invention relates to the field of aircraft onboard equipment. In particular, the present invention relates to a static port arrangement for an aircraft, in particular a combined static port arrangement. The invention further relates to a hydrostatic port system comprising such a hydrostatic port device. Background The function of the aircraft static pressure port (or static pressure hole device) is to obtain the external atmospheric static pressure. Based on the barometric pressure, the pilot may calculate the barometric altitude of the aircraft. In particular, the altitude measurement of an aircraft is performed by means of an barometric altimeter, the working principle of which is to measure altitude values by means of a hydrostatic orifice device. Therefore, the static pressure hole device can accurately sense the atmospheric static pressure, ensure the accuracy of the barometric altimeter, and is a key parameter of a flight control system, a navigation system, a ring control system and the like. The basic principle of the aircraft static pressure port is calculated based on a static pressure equation, which refers to the local pressure called static pressure when the fluid is in a static state in a steady fluid. The static pressure hole device can be transmitted to a barometer positioned in the cockpit through a pipeline after sensing static pressure in the surrounding environment. At present, a static pressure hole device used on an airplane mainly comprises a total static pressure probe which can be arranged on the side wall of an L-shaped probe, and has the defects that the static pressure hole is arranged far away from the airplane body and is easily disturbed by airflow, and the static pressure hole of the airplane adopts an integrated design mode, so that the static pressure hole device has the defects of operation steps in the airplane body during installation and insufficient convenience. For a hydrostatic port device, replacement is sometimes required after installation in place, which may be for three reasons: First, the static pressure holes (or gas-guide holes) are blocked. When the static pressure port is blocked, the static pressure is blocked in the static pressure port device and will remain unchanged. While the aircraft is climbing, the static pressure should be reduced but not reduced, which results in a smaller gauge speed, while the aircraft is descending, the static pressure should be increased but not increased, which results in a larger gauge speed. At this point the altitude and airspeed indicators may be incorrect, the airspeed becomes unreliable, and the altitude indicators may deviate accordingly. For this purpose, the static pressure port device needs to be removed to remove the blockage of the air guide port or any flow passage therein, or to be replaced directly with a new static pressure port device. Secondly, the static pressure hole device is also provided with an anti-icing heating element so as to prevent icing from happening in the static pressure hole device due to excessively low temperature when the aircraft flies. The anti-icing warming element may comprise a warming resistor, but the resistor sometimes also needs to be replaced or serviced for various reasons. Furthermore, the air vent of the static pressure vent device is usually arranged flush with the aircraft skin, but the static pressure vent device may be damaged due to various conditions occurring in the aircraft or in the test, and thus the flatness between the static pressure vent device and the skin cannot be ensured. For this reason, the hydrostatic port device also needs to be replaced. In addition, the current integral type static pressure hole device is usually adapted with a plurality of conformal plates to control the installation step difference, and is inconvenient to disassemble and assemble. Accordingly, there is a constant need in the art for on-board equipment for aircraft to be able to be quickly and easily disassembled from the outside when replacement or repair of the hydrostatic port device is required. Disclosure of Invention A static port device for an aircraft may include a first static port member that may be fixedly disposed with respect to a skin of the aircraft, a second static port member that may include one end facing an exterior of the aircraft and another end within the skin and facing the first static port member, and may be provided at one end thereof with an air vent for sensing an external static pressure and releasably attached to the skin and may be connected at another end thereof to the first static port member. By adopting the two-piece (or combined) hydrostatic hole component, the external quick assembly and disassembly (assembly and disassembly from the outside) of the hydrostatic hole device can be realized, thereby reducing maintenance or replacement cost and savi