CN106767181B - A kind of plug-in target nacelle of aviation - Google Patents
A kind of plug-in target nacelle of aviation Download PDFInfo
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- CN106767181B CN106767181B CN201710024068.7A CN201710024068A CN106767181B CN 106767181 B CN106767181 B CN 106767181B CN 201710024068 A CN201710024068 A CN 201710024068A CN 106767181 B CN106767181 B CN 106767181B
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- target
- cable
- cabin
- target cable
- winding drum
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- 238000000034 method Methods 0.000 claims abstract description 6
- 238000004804 winding Methods 0.000 claims description 38
- 239000006247 magnetic powder Substances 0.000 claims description 13
- 230000005540 biological transmission Effects 0.000 claims description 10
- 239000002360 explosive Substances 0.000 claims description 4
- 230000000977 initiatory effect Effects 0.000 claims description 4
- 239000003973 paint Substances 0.000 claims description 4
- 239000000725 suspension Substances 0.000 abstract description 3
- 239000006249 magnetic particle Substances 0.000 description 7
- 238000006467 substitution reaction Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 230000003321 amplification Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003721 gunpowder Substances 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
- F41J9/00—Moving targets, i.e. moving when fired at
- F41J9/08—Airborne targets, e.g. drones, kites, balloons
- F41J9/10—Airborne targets, e.g. drones, kites, balloons towed
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Wind Motors (AREA)
- Storing, Repeated Paying-Out, And Re-Storing Of Elongated Articles (AREA)
Abstract
The invention discloses a kind of plug-in target nacelle of aviation, it is related to target Suspension Technique field, for reducing the rate that fractures of target cable.The plug-in target nacelle of the aviation includes target cabin, turbine, air door mechanism, damper motor, reduction box and reel are sequentially provided with target cabin, damper motor is connected with air door mechanism, the first rotary shaft is provided between turbine and reduction box, Cover For A Turbine is located at one end of the first rotary shaft, the other end of first rotary shaft and the high speed axis connection of reduction box, the second rotary shaft is provided between reel and damper motor, drum sheath is in the second rotary shaft, and second rotary shaft one end and reduction box low speed axis connection, the bottom in target cabin is provided with the self-locking mechanism for being used for pinning target；Target cable is additionally provided with target cabin, for the one ends wound of target cable on reel, the other end stretches out target cabin, and is connected with target, and target cable folding and unfolding velocity sensor is also equipped with the target cable in target cabin.The present invention is used to hanging and pulling target.
Description
Technical Field
The invention relates to the technical field of target suspension, in particular to an aviation externally-hung target nacelle.
Background
The aviation plug-in target nacelle is a device which is arranged on an airplane and used for hanging and dragging a target, a winch and a target cable are usually arranged in the aviation plug-in target nacelle, one end of the target cable is wound on the winch, and the other end of the target cable is connected with the target.
When the target is hit, the target is released by the winch through the target cable, and after the target is hit, the target is recovered by the winch through the target cable. Since this process is carried out in a state where the aircraft is flying at a high speed, the target cable is subjected to a large dynamic load, and if the dynamic load is excessive, the target cable is broken.
However, the inventor of the present application found that in the prior art, the target cable is usually manually wound and unwound, and the breakage rate of the target cable is high due to some uncertainty inevitably caused by manual operation.
Disclosure of Invention
The invention aims to provide an aviation externally-hung target nacelle for reducing the breakage rate of a target cable.
In order to achieve the purpose, the aviation externally hung target nacelle provided by the invention adopts the following technical scheme:
the utility model provides an external target nacelle of aviation, hangs on the aircraft for hang and drag the target, installs control module on the aircraft, and is equipped with in the aircraft cabin and puts the target button and receive the target button, and this external target nacelle of aviation includes the target cabin. The device comprises a target cabin, a turbine, an air door mechanism, an air door motor, a reduction gearbox and a winding drum, wherein the turbine, the air door mechanism, the air door motor, the reduction gearbox and the winding drum are sequentially arranged in the target cabin from the nose to the tail of the airplane; a target cable is also arranged in the target cabin, one end of the target cable is wound on the winding drum, the other end of the target cable extends out of the target cabin and is connected with the target, and a target cable retracting speed sensor is also arranged on the target cable in the target cabin; the control module is respectively connected with the target releasing button, the target collecting button, the air door motor, the target cable releasing and releasing speed sensor and the self-locking mechanism.
Optionally, a turbine magnetic powder clutch sleeved on the first rotating shaft is further arranged in the target cabin and connected with the control module.
Optionally, a wiring device is further arranged above the winding drum, and the target cable is wound on the winding drum through the wiring device.
Optionally, the transmission ratio of the winding drum to the wiring unit is 1:3, and the transmission ratio of the reduction gearbox to the winding drum is 1: 3.5.
Optionally, a tension sensor and a target cable locking clamp are further mounted on the target cable between the winding drum and the target cable winding and unwinding speed sensor, a magnetic powder brake is further arranged in the target cabin, the magnetic powder brake is sleeved at one end, away from the reduction gearbox, of the second rotating shaft, and the tension sensor, the target cable locking clamp and the magnetic powder brake are all connected with the control module.
Optionally, a near-distance sensor and an emergency rope cutter are further mounted on the target cable between the winding drum and the target cable winding and unwinding speed sensor, and both the near-distance sensor and the emergency rope cutter are connected with the control module.
Optionally, the emergency rope cutter comprises a blade, and an initiating explosive device for driving the blade to cut off the target cable.
Optionally, the proximity sensor is an infrared photoelectric tube, and the infrared paint is coated on the target cable at a distance of 20 meters from the target.
Optionally, a towing target locking photoelectric sensor connected with the control module is further arranged in the target cabin, and the towing target locking photoelectric sensor is mounted on the target cable between the target cable retracting speed sensor and the target; the trailing target locking photoelectric sensor comprises a light source, a lock is arranged at the joint of a target cable and a target, and the lock can shield the light source after the target enters the self-locking mechanism.
Optionally, the target cable retracting speed sensor comprises a visible light photoelectric tube and a counter with a dial, the counter is mounted on the target cable and can be driven by the target cable, and the visible light photoelectric tube is connected with the control module; during the process of target cable retraction, the visible light photoelectric tube can read the value on the counter.
Because this aviation external target nacelle has above-mentioned structure, therefore, when the target is released to needs, the pilot can press down the target button, it sends the target signal of putting to the control module to put the target button, the control module releases the target according to this signal control self-locking mechanism, when the target is retrieved to needs, the pilot can press down the target button, the target signal is received to the control module transmission by the target button, the control module sends driving signal to the throttle motor according to this signal, the throttle motor opens the throttle mechanism according to this driving signal, and then let the air current get into the aviation external target nacelle. Under the drive of the air flow, the turbine starts to rotate, the second rotating shaft is driven to rotate through the first rotating shaft and the reduction gearbox, the winding drum is driven to rotate, the target cable is wound back to the winding drum, and the target is pulled back to the self-locking mechanism. In the process, the target cable retracting speed sensor can detect the retracting speed of the target cable in real time and send the retracting speed to the control module, the control module sends a signal for controlling the opening degree of the air door mechanism to the air door motor according to the retracting speed, so that the size of air flow entering the aviation plug-in target nacelle is controlled, and further the rotating speed of the turbine is controlled.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained based on these drawings without creative efforts.
FIG. 1 is a schematic structural view of an aviation plug-in target nacelle according to an embodiment of the invention;
FIG. 2 is an enlarged schematic view of region A of FIG. 1;
fig. 3 is an enlarged schematic view of a region B in fig. 1.
Description of reference numerals:
1-a target; 2-a turbine; 3-a damper mechanism;
4-a damper motor; 5-a reduction gearbox; 6-winding drum;
7-target cable; 8-target cable retraction speed sensor; 81-visible light photoelectric tube;
82-a counter; 9-turbine magnetic powder clutch; 10-a router;
11-a tension sensor; 12-target cable locking clamp; 13-a magnetic particle brake;
14-a proximity sensor; 15-emergency rope cutter; 16-a towed target locked photosensor;
17-infrared coating.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, not all, embodiments of the present 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.
The embodiment of the invention provides an aviation plug-in nacelle which is hung on an airplane and used for hanging and dragging targets, as shown in figures 1 and 3, a control module is installed on the airplane, a target placing button and a target collecting button are arranged in a cabin of the airplane, and the aviation plug-in nacelle comprises a target cabin. The automatic target locking device comprises a target cabin, a turbine 2, an air door mechanism 3, an air door motor 4, a reduction gearbox 5 and a winding drum 6, wherein the turbine 2, the air door mechanism 3, the air door motor 4, the reduction gearbox 5 and the winding drum 6 are sequentially arranged in the target cabin from the aircraft nose to the aircraft tail of the aircraft, the air door motor 4 is connected with the air door mechanism 3, a first rotating shaft is arranged between the turbine 2 and the reduction gearbox 5, the turbine 2 is sleeved at one end of the first rotating shaft, the other end of the first rotating shaft is connected with a high-speed shaft of the reduction gearbox 5, a second rotating shaft is arranged between the winding drum 6 and the air door motor 4, the winding drum 6 is sleeved on the second rotating; a target cable 7 is also arranged in the target cabin, one end of the target cable 7 is wound on the winding drum 6, the other end of the target cable extends out of the target cabin and is connected with the target 1, and a target cable take-up and pay-off speed sensor 8 is also arranged on the target cable 7 in the target cabin; the control module is respectively connected with the target releasing button, the target collecting button, the air door motor 4, the target cable retracting speed sensor 8 and the self-locking mechanism. Illustratively, the turbine 2 is an impulse turbine, and the target cabin is made of aluminum alloy and is suspended by lugs on a suspension pylon under the wing or fuselage of the aircraft.
Because this aviation external target nacelle has above-mentioned structure, consequently, when needs are emitted target 1, the pilot can press down the target placing button, the target placing button sends the target placing signal to the control module, the control module is according to this signal control self-locking mechanism with the release of target 1, when needs retrieve target 1, the pilot can press down the target receiving button, the target receiving button sends the target receiving signal to the control module, the control module sends drive signal to air door motor 4 according to this signal, air door motor 4 opens air door mechanism 3 according to this drive signal, and then let the air current get into aviation external target nacelle. Under the drive of this air current, turbine 2 begins to rotate to drive the rotation of second axis of rotation through first axis of rotation and reducing gear box 5, and then drive reel 6 and rotate, target cable 7 is around returning to reel 6 on, thereby draws back target 1 to self-locking mechanism. In the process, the target cable retracting speed sensor 8 can detect the retracting speed of the target cable 7 in real time and send the retracting speed to the control module, the control module sends a signal for controlling the opening degree of the air door mechanism 3 to the air door motor 4 according to the retracting speed, so that the size of air flow entering the aviation externally hung target nacelle is controlled, and further the rotating speed of the turbine 2 is controlled, and the rotating speed of the drum 6 is driven by the turbine 2, so that the retracting speed of the target cable 7 can control the rotating speed of the drum 6, the retracting speed of the target cable 7 can be accurately controlled, and compared with the prior art, the aviation externally hung target nacelle can obviously reduce the breakage rate of the target cable 7.
Optionally, as shown in fig. 1, a turbine magnetic particle clutch 9 sleeved on the first rotating shaft is further disposed in the target chamber, and the turbine magnetic particle clutch 9 is connected with the control module. So set up, control module can send the fine setting signal to turbine magnetic particle clutch 9 according to the receiving and releasing speed of target cable 7, and turbine magnetic particle clutch 9 further adjusts turbine 2's rotational speed accurately according to this fine setting signal to can carry out dual accurate regulation through air door mechanism 3 and turbine magnetic particle clutch 9 to turbine 2's rotational speed. It should be noted that the sensitivity of the turbine magnetic particle clutch 9 to force can be accurate to "grams".
Optionally, as shown in fig. 1, a wiring unit 10 is further disposed above the drum 6, the target cable 7 is wound on the drum 6 through the wiring unit 10, and the target cable 7 can be orderly wound back onto the drum 6 under the cooperation of the wiring unit 10. Illustratively, the transmission ratio of the winding drum 6 to the wiring unit 10 is 1:3, and the transmission ratio of the reduction gearbox 5 to the winding drum 6 is 1: 3.5. Of course, the transmission ratio of the winding drum 6, the wiring unit 10 and the reduction box 5 can have other values, and those skilled in the art can reasonably select the transmission ratio according to actual needs, and the transmission ratio is not limited herein.
Optionally, as shown in fig. 1, a tension sensor 11 and a target cable locking clamp 12 are further installed on the target cable 7 between the winding drum 6 and the target cable winding and unwinding speed sensor 8, a magnetic powder brake 13 is further disposed in the target cabin, the magnetic powder brake 13 is sleeved at one end, away from the reduction gearbox 5, of the second rotating shaft, and the tension sensor 11, the target cable locking clamp 12 and the magnetic powder brake 13 are all connected with the control module. When the target 1 is lost or the flying attitude of the target 1 is unstable, the tension sensor 11 can sense the change of the tension of the target cable 7, the control module controls the target cable locking clamp 12 to lock the target cable 7 according to the change, and controls the magnetic powder brake 13 to stop the rotation of the winding drum 6. Illustratively, the tension sensor 11 is a stress sheet type tension sensor.
Optionally, as shown in fig. 1, a near sensor 14 and an emergency rope cutter 15 are further mounted on the target cable 7 between the winding drum 6 and the target cable retraction speed sensor 8, and both the near sensor 14 and the emergency rope cutter 15 are connected with the control module. When the target 1 approaches the airplane, the proximity sensor 14 can measure the distance between the target 1 and the airplane, and when the distance between the target 1 and the airplane is smaller than the target distance (for example, 20 meters), the control module sends a signal for cutting the target cable 7 to the emergency rope cutter 15, and the emergency rope cutter 15 cuts the target cable 7 in time according to the signal, so that the target 1 is prevented from damaging the airplane. In another alternative, when the target 1 is at a distance less than the target distance from the aircraft, the control module may also send a command for manual rope cutting to the pilot, who manually controls the emergency rope cutter 15 to cut off the target rope 7.
Alternatively, the emergency rope cutter 15 includes a blade, and an initiating explosive device that drives the blade to cut the target rope 7. Wherein, the initiating explosive device refers to a device which uses the gas of gunpowder as power.
Optionally, as shown in fig. 2, the proximity sensor 14 is an infrared photoelectric tube, and the target cable 7 is coated with an infrared paint 17 at a distance of 20 meters from the target. So configured, when the target 1 is 20 meters away from the airplane, the infrared paint 17 on the target cable 7 is just below the infrared photoelectric tube, so that it can be accurately measured whether the distance between the target 1 and the airplane is less than the target distance.
Optionally, as shown in fig. 1, a towing target locking photoelectric sensor 16 connected to the control module is further disposed in the target cabin, and the towing target locking photoelectric sensor 16 is mounted on the target cable 7 between the target cable retraction speed sensor 8 and the target 1; the towed target locking photoelectric sensor 16 comprises a light source, a lock is arranged at the joint of the target cable 7 and the target 1, and the lock can shield the light source after the target 1 enters the self-locking mechanism. So set up, after target 1 got into self-locking mechanism, the lock sheltered from the light source, dragged target locking photoelectric sensor 16 and sent the signal that target 1 has been retrieved to control module, and control module lets self-locking mechanism pin target 1 according to this signal.
Optionally, as shown in fig. 2, the target cable retraction speed sensor 8 includes a visible light photoelectric tube 81 and a counter 82 with a dial, the counter 82 is mounted on the target cable 7 and can be driven by the target cable 7, and the visible light photoelectric tube 81 is connected with the control module; during the retraction of the target cable 7, the visible light photocell 81 can read the value on the counter 82. Particularly, when the winding drum 6 is in a low rotating speed, the winding and unwinding speed of the target cable 7 can be accurately measured through the amplification effect of the scales of the counter 82, so that the target cable 7 is prevented from generating a large dynamic load when the target 1 is wound and unwound at a low speed, and the target cable 7 is prevented from being broken.
The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and all the changes or substitutions should be covered within 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 (8)
1. An aviation plug-in target nacelle is hung on an airplane and used for hanging and dragging targets, a control module is installed on the airplane, and a target placing button and a target collecting button are arranged in an airplane cabin, and the aviation plug-in target nacelle is characterized by comprising a target cabin; wherein,
a turbine, an air door mechanism, an air door motor, a reduction box and a winding drum are sequentially arranged in a target cabin from the nose to the tail of the airplane, the air door motor is connected with the air door mechanism, a first rotating shaft is arranged between the turbine and the reduction box, the turbine is sleeved at one end of the first rotating shaft, the other end of the first rotating shaft is connected with a high-speed shaft of the reduction box, a second rotating shaft is arranged between the winding drum and the air door motor, the winding drum is sleeved on the second rotating shaft, one end of the second rotating shaft is connected with a low-speed shaft of the reduction box, and a self-locking mechanism for locking a target is arranged at; a target cable is also arranged in the target cabin, one end of the target cable is wound on the winding drum, the other end of the target cable extends out of the target cabin and is connected with the target, and a target cable retracting speed sensor is also arranged on the target cable in the target cabin; the control module is respectively connected with the target releasing button, the target collecting button, the air door motor, the target cable retracting speed sensor and the self-locking mechanism;
a turbine magnetic powder clutch sleeved on the first rotating shaft is further arranged in the target cabin and connected with the control module;
and a wiring device is further arranged above the winding drum, and the target cable is wound on the winding drum through the wiring device.
2. The aviation plug-in target nacelle according to claim 1, wherein a transmission ratio of the winding drum to the wiring unit is 1:3, and a transmission ratio of the reduction gearbox to the winding drum is 1: 3.5.
3. The aviation externally-hung target nacelle according to claim 1, wherein a tension sensor and a target cable locking clamp are further mounted on the target cable between the winding drum and the target cable take-up and pay-off speed sensor, a magnetic powder brake is further arranged in the target nacelle, the magnetic powder brake is sleeved at one end, away from the reduction gearbox, of the second rotating shaft, and the tension sensor, the target cable locking clamp and the magnetic powder brake are all connected with the control module.
4. The aviation plug-in target nacelle according to claim 1, wherein a near sensor and an emergency rope cutter are further mounted on the target cable between the winding drum and the target cable take-up and pay-off speed sensor, and both the near sensor and the emergency rope cutter are connected with the control module.
5. The airborne target nacelle according to claim 4, wherein the emergency rope cutter comprises a blade, and an initiating explosive device for driving the blade to cut off the target cable.
6. The aviation plug-in target nacelle according to claim 4, wherein the near-distance sensor is an infrared photoelectric tube, and the target cable is coated with infrared paint at a distance of 20 m from the target.
7. The aviation plug-in target nacelle according to claim 1, wherein a towing target locking photoelectric sensor connected with the control module is further arranged in the target cabin, and the towing target locking photoelectric sensor is mounted on a target cable between the target cable retraction speed sensor and the target; the trailing target locking photoelectric sensor comprises a light source, a lock is arranged at the joint of a target cable and a target, and the lock can shield the light source after the target enters the self-locking mechanism.
8. The aviation externally-hung target nacelle according to any one of claims 1 to 7, wherein the target cable retraction speed sensor comprises a visible light photoelectric tube and a counter with a dial, the counter is mounted on the target cable and can be driven by the target cable, and the visible light photoelectric tube is connected with the control module; during the process of target cable retraction, the visible light photoelectric tube can read the value on the counter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710024068.7A CN106767181B (en) | 2017-01-13 | 2017-01-13 | A kind of plug-in target nacelle of aviation |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710024068.7A CN106767181B (en) | 2017-01-13 | 2017-01-13 | A kind of plug-in target nacelle of aviation |
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| Publication Number | Publication Date |
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| CN106767181A CN106767181A (en) | 2017-05-31 |
| CN106767181B true CN106767181B (en) | 2018-04-10 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108946534B (en) * | 2018-08-10 | 2019-11-29 | 河北环航科技股份有限公司 | A kind of aeroengine winches |
| CN109437035A (en) * | 2018-12-14 | 2019-03-08 | 河北环航科技股份有限公司 | A kind of speed regulation aeroengine winches |
| CN111595204A (en) * | 2020-05-09 | 2020-08-28 | 陕西飞机工业（集团）有限公司 | Short-distance fighting training target retracting and releasing limiting device and using method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CA2462907A1 (en) * | 2001-10-11 | 2003-04-17 | Bae Systems Information And Electronic Systems Integration Inc. | Fast deploy, retrievable and reusable airborne, counter-measure system |
| CN104266552B (en) * | 2014-08-07 | 2016-01-06 | 河北环航科技股份有限公司 | Sky puts pull-type gun infrared laser target |
| CN105539849B (en) * | 2015-12-31 | 2017-11-10 | 河北环航科技股份有限公司 | A kind of electronic gondola of external hanging type aviation and application method |
| CN206387315U (en) * | 2017-01-13 | 2017-08-08 | 河北环航科技股份有限公司 | A kind of plug-in target nacelle of aviation |
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