CN210162267U - Aircraft landing gear safety pin and pitot tube sleeve detection device - Google Patents
Aircraft landing gear safety pin and pitot tube sleeve detection device Download PDFInfo
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- CN210162267U CN210162267U CN201822011216.4U CN201822011216U CN210162267U CN 210162267 U CN210162267 U CN 210162267U CN 201822011216 U CN201822011216 U CN 201822011216U CN 210162267 U CN210162267 U CN 210162267U
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- sensor
- pitot tube
- tube sleeve
- safety pin
- detection device
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Abstract
The utility model discloses an aircraft undercarriage safety pin and skin holds in palm pipe box detection device, its characterized in that: the detection device comprises a detection box independent of an airplane, wherein a first sensor for sensing the movement of the airplane is arranged on the detection box, jacks are arranged on the detection box, the number of the jacks is consistent with the number of safety pins and leather supporting pipe sleeves of an undercarriage of each airplane, a second sensor for sensing whether the safety pins and the leather supporting pipe sleeves exist in the jacks, an alarm is arranged in the detection box, and the first sensor and the second sensor are respectively connected with an alarm. When the aircraft removed, first sensor can detect whether the aircraft will take off promptly, and the second sensor can detect safety pin and pitot tube cover and whether retrieve to the detection case in to the condition of not retrieving sends the police dispatch newspaper to unit and maintenance personal, has avoided can't take off or pitot tube can't respond to the airspeed and make the event that the aircraft returned because of not retrieving the aircraft undercarriage that safety pin and pitot tube cover and lead to.
Description
Technical Field
The utility model relates to an aircraft undercarriage safety pin and skin holds in palm pipe box detection device.
Background
Landing gear safety pins and pitot sleeves are used to protect aircraft equipment when the aircraft is parked on the ground, and are inserted (loaded) when the aircraft is parked for a long time or in high winds. The landing gear safety pin mainly fixes the landing gear of the airplane on the ground, so that the landing gear is prevented from being folded due to accidents; the skin supporting pipe sleeve is mainly used for preventing sundries from entering the skin supporting pipe of the airplane. However, before the aircraft takes off, the safety pin and the leather supporting pipe sleeve of the landing gear need to be taken down, if the safety pin and the leather supporting pipe sleeve of the landing gear are not taken down, a system of the aircraft breaks down, the aircraft returns to the air, accident symptoms are caused, and the flying safety is affected by the fact that the civil aviation has many occasions to forget to take down equipment every year.
SUMMERY OF THE UTILITY MODEL
The utility model discloses an overcome prior art not enough, provide an aircraft undercarriage safety pin and leather support pipe box detection device.
In order to achieve the above purpose, the utility model adopts the following technical scheme: the utility model provides an aircraft landing gear safety pin and pitot tube sleeve detection device which characterized in that: the detection device comprises a detection box independent of the airplane, wherein a first sensor for sensing the movement of the airplane is arranged on the detection box, jacks are arranged on the detection box, the number of the jacks is consistent with that of safety pins and a leather supporting pipe sleeve of an undercarriage of each airplane, and a second sensor for sensing whether the safety pins and the leather supporting pipe sleeve exist in the jacks or not is arranged in the jacks; the detection box is provided with an alarm, and the first sensor and the second sensor are respectively connected with the alarm. When the first sensor outputs that the airplane moves and all the second sensors send out the safety pin and the pitot tube sleeve in-place signals, the alarm does not give an alarm. When the first sensor outputs that the airplane moves and at least one second sensor sends out a signal that no safety pin or pitot tube sleeve exists in the jack, the alarm gives out an alarm in the following way: buzzing, lighting, voice, etc. When the first sensor outputs that the airplane does not move, the alarm does not give an alarm.
Further, the first sensor is an acceleration sensor, or a displacement sensor, or a vibration sensor, or a speed sensor, or a GPS displacement sensor, or a direction sensor. Such as a gyroscope and a magnetic compass are one of direction sensors, when an airplane turns from starting to moving to a designated takeoff runway, the direction sensors can sense the change of the moving direction, and therefore the airplane is determined to be in a moving state. The acceleration sensor generates acceleration inevitably when the airplane is started from stop, and the acceleration sensor outputs an airplane movement signal when sensing the acceleration from 0. Vibration sensor, when the aircraft starts, the engine must produce the vibration, and the vibration can transmit fuselage, cabin, consequently is located the detection case in the cabin and also can sense the vibration, and vibration sensor has sensed vibration response from 0, then vibration sensor output aircraft removal signal. The speed sensor inevitably generates movement speed when flying from stop to start, and the speed sensor outputs airplane movement signals when sensing speed sensing from 0. And the GPS displacement sensor outputs airplane movement signals when the airplane movable GPS positioning position moves according to GPS positioning.
Furthermore, the second sensor is a photoelectric sensor, the photoelectric sensor comprises a light beam emitter and a light receiver, a set of photoelectric sensor is arranged in each jack, and the inserting space of the safety pin and the pitot tube sleeve is arranged between the light beam emitter and the light receiver. The safety pin and the pitot tube sleeve are inserted between the light beam emitter and the light receiver to block the light received by the photoelectric sensor, the photoelectric sensor is switched to be disconnected from the on-state, and the safety pin and the pitot tube sleeve are considered to be inserted into the insertion hole.
Further, the second sensor is an inductive sensor, or the second sensor is a capacitive sensor; or the second sensor is a resistive sensor. The safety pin is a metal piece, the pitot tube is sleeved with an iron rod, and when the safety pin and the metal rod of the pitot tube sleeve are inserted into the insertion hole, the inductance output by the inductance sensor changes, or the capacitance output by the capacitance sensor changes, or the resistance output by the resistance sensor changes.
Further, the second sensor is an electromagnetic sensor including a coil connected to a power source, the coil being wound outside the receptacle. The safety pin is a metal piece, the pitot tube sleeve is provided with an iron rod, when the safety pin and the metal rod of the pitot tube sleeve are inserted into the insertion hole, the iron rod is inserted into the coil, the electromagnetic field changes, and the second sensor outputs signals of the safety pin and the pitot tube sleeve.
Furthermore, the second sensor is a Hall sensor, and the safety pin and the pitot tube sleeve are provided with magnets. When the safety pin and the leather supporting pipe sleeve are not arranged in the jack, the Hall sensor cannot detect the magnet. When the safety pin and the pitot tube sleeve are inserted into the jack, the Hall sensor can detect the magnet, and after the magnet is detected, the safety pin and the pitot tube sleeve are considered to be inserted into the jack.
Furthermore, a battery installation part is arranged on the detection box, or a power line is arranged on the detection box.
Further, the detection box may be placed in a fixed or non-fixed manner on the aircraft, such as the cockpit.
In conclusion, when the aircraft takes off, the first sensor and the second sensor can detect whether the safety pin and the pitot sleeve are recovered in the detection box, so that the problem that the aircraft landing gear cannot be retracted or the pitot tube cannot sense the airspeed to return the aircraft due to the fact that the safety pin and the pitot sleeve are not recovered is avoided.
The utility model has the advantages that: the existing structure of the airplane does not need to be reformed, the detection device which can be separated from the airplane and fixed can be used for detecting whether the safety pin and the pitot tube sleeve of the airplane flying nose landing gear are completely withdrawn and whether the safety pin and the pitot tube sleeve are lost or not, and the method is suitable for all airplane models.
Drawings
Fig. 1 is a schematic view of the structure of the detection box of the present invention.
Fig. 2 is a schematic structural view of the safety pin and the pitot tube sleeve 3 of the present invention inserted into the photoelectric sensor.
Fig. 3 is a schematic structural view of the safety pin and the pitot tube sleeve 3 of the present invention not inserted into the photoelectric sensor.
Fig. 4 is a circuit diagram of the present invention used in cooperation with an acceleration sensor and an electromagnetic sensor.
Fig. 5 is a circuit diagram of the acceleration sensor and the photoelectric sensor of the present invention.
Detailed Description
In order to make the technical field personnel understand the utility model discloses the scheme, will combine the drawing in the embodiment of the utility model below, to the technical scheme in the embodiment of the utility model carries out clear, complete description.
As shown in fig. 1-4, the detection device for the safety pin and the leather supporting pipe sleeve of the landing gear of the airplane comprises a detection box 1 independent of the airplane, a first sensor for sensing the movement of the airplane is arranged on the detection box 1, a jack 2 is arranged on the detection box 1, the number of the jacks 2 is consistent with that of the safety pin and the leather supporting pipe sleeve 3 of the landing gear of each airplane, a second sensor for sensing whether the safety pin and the leather supporting pipe sleeve 3 exist in the jack 2 is arranged in the jack 2, the detection box is provided with an alarm, and the first sensor and the second sensor are respectively connected with the alarm. The utility model discloses a detection device mainly used detects when the aircraft takes off, and safety pin and pitot tube box are all taken off from undercarriage and pitot tube, whether all retrieve, in case the condition of not retrieving safety pin and pitot tube box 3 appears, can send the staff that the warning sound notified the aircraft through detection device to avoid aircraft system to not withdraw trouble because of safety pin and pitot tube box 3, perhaps not withdraw because of safety pin and pitot tube box 3 and cause the aircraft to return voyage. When the first sensor outputs that the airplane moves and all the second sensors send out signals that the safety pin and the pitot tube sleeve are in place, the alarm does not give an alarm. When the first sensor outputs that the airplane moves and at least one second sensor sends out a signal that no safety pin or pitot tube sleeve exists in the jack, the alarm gives out an alarm in the following way: buzzing, light and voice, etc. When the first sensor outputs that the airplane does not move, the alarm does not give an alarm. Specifically, because the detection box 1 is placed on an airplane, preferably, the detection box 1 is placed at a fixed position of the airplane, the detection box 1 is provided with a first sensor and a second sensor, the first sensor is used for detecting whether the airplane moves or not, the second sensor is used for detecting whether the safety pin and the pitot tube sleeve 3 are completely recovered into the detection box 1 or not, when the first sensor detects that the airplane has moved and the second sensor detects that the jack 2 on the detection box 1 does not completely recover the safety pin and the pitot tube sleeve 3, the detection device can give out a prompt sound to prompt the staff of the airplane that the airplane has moved and is ready to take off and the safety pin and the pitot tube sleeve 3 are not completely recovered into the detection box 1. At the moment, the aircraft staff can timely deal with the potential safety hazard, and unsafe events such as aircraft return and forced landing caused by the fact that the safety pin and the leather supporting pipe sleeve 3 are not withdrawn can be avoided.
Further, the first sensor is an acceleration sensor, or a displacement sensor, or a vibration sensor, or a speed sensor, or a GPS displacement sensor, or a direction sensor, which are used for detecting the relative displacement of the aircraft. For example, an acceleration sensor is a sensor capable of measuring acceleration, and obtains an acceleration value by using newton's second law through measurement of inertial force applied to a mass block during acceleration; the displacement sensor is a linear device belonging to metal induction, and the sensor is used for converting various measured physical quantities into electric quantities; the vibration sensor takes the original mechanical quantity to be measured as the input quantity of the vibration sensor, then the mechanical receiving part receives the input quantity to form another mechanical quantity suitable for conversion, and finally the mechanical-electrical conversion part converts the mechanical quantity into electric quantity; the speed sensor is the speed which is the increment of displacement in unit time; the gyroscope is an angular motion detection device which uses a momentum moment sensitive shell of a high-speed revolving body to rotate around one or two axes which are orthogonal to a self-rotation axis relative to an inertia space; magnetic compass refers to a kind of compass capable of indicating geographical position and manufactured by using the attraction of earth magnetic field.
Specifically, the acceleration sensor inevitably generates acceleration when flying from a stop to a start, and when the acceleration sensor senses acceleration from 0, the acceleration sensor outputs an airplane movement signal. Vibration sensor, when the aircraft starts, the engine must produce the vibration, and the vibration can transmit fuselage, cabin, consequently is located the detection case in the cabin and also can sense the vibration, and vibration sensor has sensed vibration response from 0, then vibration sensor output aircraft removal signal. The speed sensor inevitably generates movement speed when flying from stop to start, and the speed sensor outputs airplane movement signals when sensing speed sensing from 0. And the GPS displacement sensor outputs airplane movement signals when the airplane movable GPS positioning position moves according to GPS positioning.
Further, the second sensor is a photoelectric sensor; or the second sensor is an inductive sensor, or the second sensor is a capacitive sensor; or the second sensor is a resistive sensor; or the second sensor is a Hall sensor; or the second sensor is an electromagnetic sensor.
The photoelectric sensor comprises a light beam emitter 4 and a light receiver 5, a set of photoelectric sensors is arranged in each jack 2, and the insertion space of the safety pin and the pitot tube sleeve 3 is between the light beam emitter 4 and the light receiver 5. The photoelectric sensor is a device for converting an optical signal into an electrical signal, the safety pin and the pitot tube sleeve are inserted between the light beam emitter and the light receiver to block the light reception in the photoelectric sensor, the photoelectric sensor is switched from a closed circuit to an open circuit, the safety pin and the pitot tube sleeve are considered to be inserted into the jack, specifically, when the safety pin and the pitot tube sleeve 3 are inserted into the jack 2, the light beam emitted from the light beam emitter 4 can be isolated from the light receiver 5, and when the safety pin and the pitot tube sleeve 3 are not inserted into the jack 2, the light receiver 5 can receive the light beam emitted from the light beam emitter 4, thereby detecting whether the safety pin and the pitot tube sleeve 3 are inserted into the jack 2 of the detection box 1.
The electromagnetic sensor is provided by the phenomenon of electromagnetic induction, and comprises a coil connected to a power supply, the coil being wound outside the insertion hole, the iron rod 3 attached to the safety pin and the pitot tube sleeve being inserted inside the coil winding and the iron rod 3 attached to the safety pin and the pitot tube sleeve not being inserted inside the coil winding, and the magnetic field around the coil thereof can be changed, thereby causing a change in the electric field, and detecting from the sensor whether the safety pin and the pitot tube sleeve 3 have been inserted into the insertion hole 2 of the detection box 1. Generally, the iron rod attached to the safety pin and the pitot tube sleeve is a metal piece, when the iron rod attached to the safety pin and the pitot tube sleeve is inserted into the inserting hole, the iron core is inserted into the coil, an electromagnetic field changes, and the second sensor outputs a signal of inserting the safety pin and the pitot tube sleeve.
The Hall sensor is a magnetic field sensor manufactured according to the Hall effect, the Hall effect is one of magnetoelectric effects, the Hall effect is basically deflection caused by Lorentz force action of moving charged particles in a magnetic field, Hall voltage changes along with the change of the magnetic field intensity, the stronger the magnetic field is, the higher the voltage is, the weaker the magnetic field is, the lower the voltage is, and the Hall voltage value is very small. When the second sensor is a Hall sensor, the safety pin and the leather-supporting pipe sleeve 3 are provided with magnets, and the Hall sensor is used for detecting the distance between the safety pin and the magnets on the leather-supporting pipe sleeve 3 to judge whether the safety pin and the leather-supporting pipe sleeve 3 are inserted into the jack 2 of the detection box 1. That is, the hall sensor does not detect the magnet when the shear pin and the pitot tube sleeve are not in the socket. When the safety pin and the pitot tube sleeve are inserted into the jack, the Hall sensor can detect the magnet, and after the magnet is detected, the safety pin and the pitot tube sleeve are considered to be inserted into the jack.
In summary, in order to ensure that the above detection devices can operate normally, a battery installation part is arranged on the detection box 1, or a power line is arranged on the detection box and used for supplying power to the above devices.
It is obvious that the described embodiments are only some of the embodiments of the present invention, and not all of them. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts shall belong to the protection scope of the present invention.
Claims (8)
1. The utility model provides an aircraft landing gear safety pin and pitot tube sleeve detection device which characterized in that: the detection device comprises a detection box independent of the airplane, wherein a first sensor for sensing the movement of the airplane is arranged on the detection box, jacks are arranged on the detection box, the number of the jacks is consistent with that of safety pins and a leather supporting pipe sleeve of an undercarriage of each airplane, and a second sensor for sensing whether the safety pins and the leather supporting pipe sleeve exist in the jacks is arranged in each jack; the detection box is provided with an alarm, and the first sensor and the second sensor are respectively connected with the alarm.
2. An aircraft landing gear shear pin and pitot tube sleeve detection device according to claim 1, wherein: the first sensor is an acceleration sensor, or a displacement sensor, or a vibration sensor, or a speed sensor, or a GPS displacement sensor, or a direction sensor.
3. An aircraft landing gear shear pin and pitot tube sleeve detection device according to claim 1, wherein: the second sensor is a photoelectric sensor, the photoelectric sensor comprises a light beam emitter and a light receiver, a set of photoelectric sensor is arranged in each jack, and the inserting space of the safety pin and the pitot tube sleeve is arranged between the light beam emitter and the light receiver.
4. An aircraft landing gear shear pin and pitot tube sleeve detection device according to claim 1, wherein: the second sensor is an inductive sensor, or the second sensor is a capacitive sensor; or the second sensor is a resistive sensor.
5. An aircraft landing gear shear pin and pitot tube sleeve detection device according to claim 1, wherein: an iron rod is arranged on the pitot tube sleeve, the second sensor is an electromagnetic sensor, the electromagnetic sensor comprises a coil connected with a power supply, and the coil is wound outside the jack.
6. An aircraft landing gear shear pin and pitot tube sleeve detection device according to claim 1, wherein: the second sensor is a Hall sensor, and the safety pin and the pitot tube sleeve are provided with magnets.
7. An aircraft landing gear safety pin and pitot tube sleeve detection device as claimed in claim 1 or 2 or 3 or 4 or 5 or 6 wherein: the detection box is provided with a battery installation part, or the detection box is provided with a power line.
8. An aircraft landing gear safety pin and pitot tube sleeve detection device as claimed in claim 1 or 2 or 3 or 4 or 5 or 6 wherein: the detection box can be placed on the airplane in a fixed or non-fixed mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822011216.4U CN210162267U (en) | 2018-12-03 | 2018-12-03 | Aircraft landing gear safety pin and pitot tube sleeve detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822011216.4U CN210162267U (en) | 2018-12-03 | 2018-12-03 | Aircraft landing gear safety pin and pitot tube sleeve detection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210162267U true CN210162267U (en) | 2020-03-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822011216.4U Expired - Fee Related CN210162267U (en) | 2018-12-03 | 2018-12-03 | Aircraft landing gear safety pin and pitot tube sleeve detection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210162267U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115092404A (en) * | 2022-06-29 | 2022-09-23 | 广州飞机维修工程有限公司 | Aircraft safety pin case with alarm function |
| EP4269254A1 (en) * | 2022-04-28 | 2023-11-01 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A ground support equipment system for use on an aircraft |
-
2018
- 2018-12-03 CN CN201822011216.4U patent/CN210162267U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4269254A1 (en) * | 2022-04-28 | 2023-11-01 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A ground support equipment system for use on an aircraft |
| CN115092404A (en) * | 2022-06-29 | 2022-09-23 | 广州飞机维修工程有限公司 | Aircraft safety pin case with alarm function |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200320 Termination date: 20211203 |
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| CF01 | Termination of patent right due to non-payment of annual fee |