JPH0433198Y2 - - Google Patents

Description

[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to an aircraft speed system static pressure regulating device for compensating for position errors in the speed system of an aircraft.

[Conventional technology]

The speed system of an aircraft usually consists of a total pressure pipe 07 for measuring total pressure and a static pressure hole 08 for measuring static pressure, as shown in FIGS. 6A and 6B, and these are connected to form an aircraft speedometer 06. Speed is indicated. in this case,
Total pressure is less affected by the shape of the aircraft and its positional error is small, but static pressure is easily affected by the shape of the aircraft and has a large positional error. In the case of the developed machine, it is extremely difficult to determine a static pressure hole that satisfies the position error regulations.

Conventionally, as shown in FIG. 4, a large number of static pressure holes 02 are drilled on the surface of an aircraft 01, and static pressure holes that satisfy the positional error regulations are selected by performing a flight test. As another method, Fig. 5 A and B
As shown in FIG. 2, a protrusion 03 is provided near the static pressure hole 02, and the position, height, etc. of the protrusion 03 that satisfies the positional error regulations are determined by a trial and error method in a flight test.

[Problem that the invention attempts to solve]

As mentioned above, the speed system of an aircraft is usually measured by total pressure measurement using a total pressure pipe and static pressure measurement using a static pressure hole, but static pressure is greatly affected by the shape and position of the aircraft, resulting in position errors. . In order to keep this positional error within a specified range, there was a problem in that it required a lot of time and effort in the early stages of developing the machine, and it was often difficult.

SUMMARY OF THE INVENTION An object of the present invention is to provide an aircraft speed system static pressure adjustment device that can solve the above problems and easily obtain static pressure that satisfies regulations.

[Means for solving problems]

The aircraft speed system static pressure adjustment device according to the present invention has the following features:
A static pressure hole drilled in the surface of the aircraft body, a thin plate provided near the static pressure hole and moved along a guide, and a position and height of the thin plate provided on the aircraft with respect to the static pressure hole. and a controller that changes the height along the guide, and a thin plate whose position and height relative to the static pressure hole can be changed on the aircraft along the guide (groove-shaped) by the controller. Using this method, a static pressure hole that satisfies the position error regulations can be determined in a single flight test.

[Effect]

For example, as shown in FIG. 3, when an object is projected into the air, the static pressure increases in front of it and decreases behind it. According to the present invention, by applying this principle and changing the position and height of the thin plate with respect to the static pressure hole using a controller,
The static pressure can easily be changed by a significant amount in all directions in the static pressure hole of the aircraft.

〔Example〕

1 and 2 are a partial sectional view and a plan view, respectively, showing the configuration of an embodiment of the present invention, in which 1 is a static pressure hole drilled in the fuselage surface 6 of an aircraft, and 2 is a static pressure hole. A thin plate 4 for adjusting static pressure is provided near 1 and moved along a groove-shaped guide 3; 4 is disposed on the aircraft and changes the position and height of the thin plate 2 relative to the static pressure hole 1 along the guide 3 5 is a drive mechanism that is controlled by the controller 4 to move the thin plate 2 in the vertical direction (protrusion direction) with respect to the static pressure hole 1 and rotate it in the circumferential direction (move the relative position). shows.

The operation of the embodiment of the present invention described above will be explained.

The drive mechanism 5 is controlled by the controller 4 to set the thin plate 2 at an arbitrary position and protrusion height, and a flight test of the aircraft is performed. At this time, if the positional error regulation is not satisfied, the controller 4 controls the drive mechanism 5 again to set the thin plate 2 at another position and protrusion height, and then perform a flight test. By operating the controller 4 onboard the aircraft in this way, the protrusion height and position of the thin plate 2 that satisfy the positional error regulations can be determined in one flight test.

[Effect of idea]

As described above, the conventional technology had problems such as an increase in aircraft body modification work, an increase in the number of flight tests, and an increase in flow time, but the present invention solves these problems. This method has excellent effects such as being able to easily adjust the magnitude of the aircraft's speed-related static pressure and efficiently conducting flight tests of the developed aircraft.

[Brief explanation of drawings]

Fig. 1 is a partial sectional view showing the structure of an embodiment of the present invention, Fig. 2 is a partial plan view showing the structure of an embodiment of the invention, Fig. 3 is a diagram showing the principle of the invention, and Fig. 4 is a diagram showing the principle of the invention.
6A and 6B are diagrams for explaining a conventional example. 1... Static pressure hole, 2... Thin plate, 3... Guide, 4
... Controller, 5 ... Drive mechanism.

Claims (1)

[Scope of utility model registration request] A static pressure hole drilled in the surface of the aircraft body, a thin plate provided near the static pressure hole and moved along a guide, and a position and height of the thin plate provided on the aircraft with respect to the static pressure hole. An aircraft speed system static pressure regulating device, comprising: a controller for changing the static pressure along the guide.