GB2049954A - Improvements in or relating to apparatus for testing aircraft instruments - Google Patents
Improvements in or relating to apparatus for testing aircraft instruments Download PDFInfo
- Publication number
- GB2049954A GB2049954A GB7917782A GB7917782A GB2049954A GB 2049954 A GB2049954 A GB 2049954A GB 7917782 A GB7917782 A GB 7917782A GB 7917782 A GB7917782 A GB 7917782A GB 2049954 A GB2049954 A GB 2049954A
- Authority
- GB
- United Kingdom
- Prior art keywords
- pump
- air
- aircraft
- speed indicator
- air speed
- 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.)
- Withdrawn
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 18
- 239000000446 fuel Substances 0.000 claims description 6
- 230000003068 static effect Effects 0.000 abstract description 17
- 230000009467 reduction Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 238000011065 in-situ storage Methods 0.000 description 1
- 238000012956 testing procedure Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L27/00—Testing or calibrating of apparatus for measuring fluid pressure
- G01L27/007—Malfunction diagnosis, i.e. diagnosing a sensor defect
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M3/00—Investigating fluid-tightness of structures
- G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
- G01M3/26—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Analytical Chemistry (AREA)
- Biomedical Technology (AREA)
- Examining Or Testing Airtightness (AREA)
Abstract
There is provided an apparatus for testing an aircraft instrument, such as an altimeter or air speed indicator. The apparatus includes an air pump 1 having an inlet and outlet. A pressure measuring device 9 is connected to the pump inlet and outlet. Connections 7, 11 are provided for connecting the pump 1 and the measuring device 9 to the aircraft to be tested, for instance the pitot and static connections of the aircraft. <IMAGE>
Description
SPECIFICATION
Improvements in or relating to apparatuses for testing aircraft instruments
The present invention relates to apparatuses for testing aircraft instruments. Such apparatuses may be used for testing air speed indicators and altimeters.
According to the invention, there is provided an apparatus for testing an aircraft instrument, comprising an air pump having an inlet and an outlet, a pressure measuring device connected to at least one of the inlet and outlet of the air pump, and connection means for connecting the air pump and the pressure measuring device to the aircraft instrument to be tested.
Preferably, the air pump comprises an automobile fuel pump. Preferably, the fuel pump is a diaphragm pump. Preferably, the fuel pump is of the mechanically operated type.
Preferably, the pressure measuring device comprises an air speed indicator whose Pitot connection is connected to the outlet of the pump
and whose Static connection is connected to the inlet of the pump. Preferably, shut-off valves are arranged to isolate the pump from the air speed indicator and from the connection means but to leave the air speed indicator connected to the connection means.
Preferably, a further air pump is connected in series with the air pump. Preferably, the air pump and the further air pump are connected between a suction reservoir and a pressure reservoir.
Preferably, an altimeter is connected to the inlet of the pump.
The invention will be further described, by way of example, with reference to the accompanying drawings, in which:
Figure 1 is a diagram of a Pitot Static leak tester constituting a first preferred embodiment of the invention; and
Figure 2 is a diagram of a Pitot Static tester constituting a second preferred embodiment of the invention.
The Pitot Static leak tester shown in Figure 1 includes an air pump 1 which is mechanically operated via an actuating member 2 by a lever 3, one end of which is pivoted at 4 to a frame (not shown) and the other end of which is provided with a handle 5 for hand-operation. The air pump
1 is an automobile diaphragm fuel pump of the type SU AF800Z. The inlet connection of the air pump 1 is connected via a shut-off valve 6 to a connector 7 and to the Static connection of a standard air speed indicator 9. The outlet of the pump 1 is connected via a second shut-off valve
10 to a connector 11 and to the Pitot connection of the air speed indicator 9.
In order to test the air speed indicator of an air craft in situ, the connector 11 is connected to the
Pitot connection of the air craft with the connector
7 open to the atmosphere. The first and second shut-off valves 6 and 10 are opened and the pump
1 is operated by means of the lever 3. Ai, is thus supplied from the atmosphere into the Pitot system of the aircraft and to the Pitot connection 1 2 of the air speed indicator 9 of the tester. The pressure in the Pitot system is maintained within the operating range of the air speed altimeter of the aircraft so as not to damage this instrument.
When a suitable pressure has been reached, the second shut-off valve 10 is closed and the reading of the air speed indicator 9 is observed. Any reduction in this reading then indicates a leak in the Pitot system of the aircraft. Further, the calibration of the air speed indicator of the aircraft may be checked by comparing its reading with that of the air speed indicator 9.
In order to test the Static system of the aircraft the connector 7 is connected to the Static connection of the aircraft and the connector 11 is left open to the atmosphere. The testing procedure is then as described above for the Pitot system of the aircraft.
The Pitot Static tester shown in Figure 2 comprises first and second air pumps 1 2 and 13 connected in series. Each of these pumps is an automobile fuel pump of the type SU J AF800Z, this type of pump having efficient inlet and outlet valves which give negligible leakage. The inlet of the first pump 12 is connected to a suction reservoir 14 and the outlet of the second pump 13 is connected to a pressure reservoir 1 5. The first and second pumps are connected via first and second actuators 1 6 and 17, respectively, to an operating handle 1 8. The suction tank 14 is connected via a first control valve 19 to an altimeter 21, to a connector 22, and via a first release valve 23 to the atmosphere.The suction tank 14 is further connected via the first control valve 1 9 and via a pipe 20 to the Static connection of an air speed indicator 24 and to one side of a second control valve 25.
The pressure reservoir 1 5 is connected via a third control valve 26 to the atmosphere and via a fourth control valve 27 to a pipe connection 28.
The pipe connection 28 is further connected to a connector 29, via a second release valve 30, to the Pitot connection of the air speed indicator 24, and to the other side of the second control valve 25.
In order to test the Pilot system and the calibration of an air speed indicator installed in an aircraft the connector 29 is connected to the Pitot tube of the aircraft and the connector 22 is open to the atmosphere. The first control valve 1 9 is opened and the handle 1 8 is operated, thus operating the first and second pump 12 and 1 3 to pressurize the pressure reservoir 1 5. With the second and third control valves 25 and 26 and the second release valve 30. The fourth control valve 27 may be opened so as to pressurize the Pitot system of the aircraft and simultaneously the Pitot connection of the air speed indicator 24.The valve 27 is then closed to allow testing for leaks, a reduction in the reading of the air speed indicator 24 indicating the presence of a leak in the Pitot system. By manipulating the fourth control valve 27 and the second release valve 30 the Pitot may be tested for d;fferent readings of the aircraft air speed indicator and these readings may be compared with those of the air speed indicator 24 of the tester. The control valve 26 may be opened when testing is completed in order to neutralize the pressure in the pressure reservoir 1 5.
In order to test the Static system of the aircraft, the connectors 22 and 29 are connected to the
Static and Pitot connections of the aircraft. This is necessary because the air speed indicator of the aircraft operates from much smaller pressure differences than the altimeter of the aircraft. Since the altimeter of the aircraft is connected to the
Static system thereof, both the Pitot and Static systems must be pressurized to approximately the same level in order to avoid damage to the air speed indicator of the aircraft. With the first and second release valves 23 and 30 and the fourth control valve 27 closed and the first, second and third control valves 19, 25, 26 open, the pumps 12 and 13 are operated by the handle 18 to reduce the pressure in the suction reservoir 14, the pumps exhausting via the open third control valve 26 into the atmosphere.When a desired reduction in pressure has been achieved in the suction reservoir 14, the second control valve 25 is closed to isolate the Pitot and Static systems, the pressure difference across the air speed indicator 24 and the air speed indicator of the aircraft being substantially zero at this stage. The first control valve 1 9 is closed and any leaks in the
Static system of the aircraft are indicated by a falling reading on the air speed indicator 24 and on the altimeter 21. The calibration of the altimeter of the aircraft may also be checked against the reading of the altimeter 21 of the tester. By manipulating the first control valve 1 9 and the first release valve 23, different reductions in pressure and hence different readings may be checked.The second control valve 25 is periodically opened in order to equalize the pressures in the Pitot and Static systems so as to maintain the pressure difference across the air speed indicator 24 and the air speed indicator of the aircraft within the normal working range in order to avoid damage to the these instruments.
The use of the two pumps 12 and 13 permits the range of testing of the tester to be increased so as to be equivalent to testing at pressures equivalent to altitudes up to of the order of 45,000', whereas the provision of a single pump, such as in the leak tester of Figure 1, permits testing at pressures
equivalent to up to approximately 24,000' altitude. Further, the provision of the suction reservoir 14 and the pressure reservoir 1 5 with the associated control valves provides a smoother and more accurately controlled range in pressure during testing. All the control, release, and shut-off valves in the embodiments of Figures 1 and 2 may be of the needle type which provide fine control and positive shut-off.
Claims (10)
1. An apparatus for testing an aircraft instrument comprising an air pump having an inlet and an outlet, a pressure measuring device connected to at least one of the inlet and outlet of the air pump, and connection means for connecting the air pump and the pressure measuring device to the aircraft instrument to be tested.
2. An apparatus as claimed in claim 1, in which the air pump comprises an automobile fuel pump.
3. An apparatus as claimed in claim 2, in which the pump is a diaphragm pump.
4. An apparatus as claimed in claim 2 or 3, in which the pump is of the mechanically operated type.
5. An apparatus as claimed in claim 4, in which a handle is provided for manual operation of the pump
6. An apparatus as claimed in any one of the preceding claims, in which the pressure measuring device comprises an air speed indicator whose
Pitot connection is connected to the outlet of the pump.
7. An apparatus as claimed in claim 6, in which at least one shut-off valve is arranged to isolate the pump from the air speed indicator and from the connection means but to leave the air speed indicator connected to the connection means.
8. An apparatus as claimed in any one of the preceding claims, in which an altimeter is connected to the inlet of the pump.
9. An apparatus as claimed in any one of the preceding claims, in which a further air pump is connected in series with the air pump.
10. An apparatus as claimed in claim 9, in which the air pump and the further air pump are connected between a suction reservoir and an pressure reservoir.
1 An apparatus for testing an aircraft instrument, substantially as hereinbefore described with reference to and as illustrated in
Figure 1 or 2 of the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB7917782A GB2049954A (en) | 1979-05-22 | 1979-05-22 | Improvements in or relating to apparatus for testing aircraft instruments |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB7917782A GB2049954A (en) | 1979-05-22 | 1979-05-22 | Improvements in or relating to apparatus for testing aircraft instruments |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB2049954A true GB2049954A (en) | 1980-12-31 |
Family
ID=10505339
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB7917782A Withdrawn GB2049954A (en) | 1979-05-22 | 1979-05-22 | Improvements in or relating to apparatus for testing aircraft instruments |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2049954A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2682767A1 (en) * | 1991-10-18 | 1993-04-23 | Aerospatiale | ANEMOMETRIC TEST BENCH. |
| FR2882141A1 (en) * | 2005-02-14 | 2006-08-18 | Airbus France Sas | METHOD AND DEVICE FOR DETECTING IN THE GROUND THE OBSTRUCTION OF A PRESSURE SOCKET OF A STATIC PRESSURE SENSOR OF AN AIRCRAFT |
| FR3073623A1 (en) * | 2017-11-16 | 2019-05-17 | Ateq | INSTALLATION AND METHOD FOR DETECTING AND LOCATING A LEAK IN A FLUID TRANSPORT CIRCUIT, IN PARTICULAR AN AIRCRAFT |
| US11719591B2 (en) | 2017-07-06 | 2023-08-08 | Ateq | Method for detecting leakage of a hollow component and installation for implementing such a method |
| US11906393B2 (en) | 2019-01-29 | 2024-02-20 | Ateq | Tracer gas leak detection system and corresponding use |
-
1979
- 1979-05-22 GB GB7917782A patent/GB2049954A/en not_active Withdrawn
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2682767A1 (en) * | 1991-10-18 | 1993-04-23 | Aerospatiale | ANEMOMETRIC TEST BENCH. |
| EP0540396A1 (en) * | 1991-10-18 | 1993-05-05 | AEROSPATIALE Société Nationale Industrielle | Anemometer test-bench |
| FR2882141A1 (en) * | 2005-02-14 | 2006-08-18 | Airbus France Sas | METHOD AND DEVICE FOR DETECTING IN THE GROUND THE OBSTRUCTION OF A PRESSURE SOCKET OF A STATIC PRESSURE SENSOR OF AN AIRCRAFT |
| WO2006087440A1 (en) * | 2005-02-14 | 2006-08-24 | Airbus France | Method and device for detecting, on the ground, the obstruction of a pressure tap of a static pressure sensor of an aircraft |
| US7675434B2 (en) | 2005-02-14 | 2010-03-09 | Airbus France | Method and device for detecting, on the ground, the obstruction of a pressure tap of a static pressure sensor of an aircraft |
| US11719591B2 (en) | 2017-07-06 | 2023-08-08 | Ateq | Method for detecting leakage of a hollow component and installation for implementing such a method |
| FR3073623A1 (en) * | 2017-11-16 | 2019-05-17 | Ateq | INSTALLATION AND METHOD FOR DETECTING AND LOCATING A LEAK IN A FLUID TRANSPORT CIRCUIT, IN PARTICULAR AN AIRCRAFT |
| WO2019096759A1 (en) * | 2017-11-16 | 2019-05-23 | Ateq | Installation and method for detecting and locating a leak in a fluid transport circuit, notably of an aircraft |
| US11300472B2 (en) | 2017-11-16 | 2022-04-12 | Ateq | Installation and method for detecting and locating a leak in a fluid transport circuit, notably of an aircraft |
| US11906393B2 (en) | 2019-01-29 | 2024-02-20 | Ateq | Tracer gas leak detection system and corresponding use |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |