CN102183352B - Releasing mechanism used for releasing experiments - Google Patents
Releasing mechanism used for releasing experiments Download PDFInfo
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- CN102183352B CN102183352B CN201110045226A CN201110045226A CN102183352B CN 102183352 B CN102183352 B CN 102183352B CN 201110045226 A CN201110045226 A CN 201110045226A CN 201110045226 A CN201110045226 A CN 201110045226A CN 102183352 B CN102183352 B CN 102183352B
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Abstract
The invention relates to a releasing mechanism used for releasing experiments. In the mechanism, a sliding support is arranged at one side of a support, two ejection rods arranged in an up-and-down and side-by-side manner penetrate into an installation clamp groove of the support and a through groove of the sliding support, and are clamped onto the support; and a spring is sleeved on an ejection rod arranged at one side of the support. A crossbeam is arranged in the installation clamp groove at one side of the support, and an included angle between the crossbeam and the support is adjustable; and an end of the crossbeam is provided with a mount through which the releasing mechanism is fixed onto a housing of a fuselage shell. A conduction pole passes through installation holes on two sidewalls of the sliding support; one end socket of the conduction pole is provided with a stay wire, and the other end socket of the conduction pole is communicated with a power supply via a lead; and the stay wire threads through a retaining ring of a human body model which used as a releasing object. In usage, the stay wire is fused by electricity to eject the releasing object, and compaction degree of the stay wire to the spring is adjusted to realize adjusting the angle and acceleration speed when the releasing object is coming out of a cabin. The mechanism is simple in structure and convenient and reliable in use, so the mechanism is not only applicable to releasing experiments of general objects, but also applicable to releasing experiments of paratroopers.
Description
Technical field
The present invention relates to aircraft floor experimental technique field, specifically is a kind of throwing mechanism that is used for drop-test.
The technology that background technology is relevant with the present invention is drop a bomb a wind-tunnel drop-test technology of aircraft.This throwing mechanism generally is made up of hook, spring, backguy and lead, expelling means and breather line, base etc., is installed in the model aircraft surface.Backguy and spring only are used for fixing model, and model ejects and goes out realization with pressure-air through vent line, and mechanism is complicated, volume is big.Model aircraft fuselage inner chamber can not be installed in, the control requirement of the different deliver from vault attitudes of missile can not be satisfied.Drop a bomb mechanism's type of drive of wind-tunnel drop-test technology of the present invention and aircraft is different, throwing mechanism involved in the present invention drive with the model attitude control structure be one.
In the CN200620018998.9 of Patent Office of the People's Republic of China patented claim, disclose a kind of unmanned plane mission payload and clamped throwing mechanism, dependence steering wheel realization mission payload steps up and unclamps, utilizes the load own wt to accomplish load and throw in.But it can not control load launch direction, speed and launch the thing attitude.
In the CN200920038752.1 of Patent Office of the People's Republic of China patented claim, a kind of spoonful of automatic throwing mechanism of class article disclosed, rely on rotating shaft system, Trayconcept, jacking system, sucker extraction system to realize the continuous input of spoon type article.But it can not the firm fixation article, the launching direction, speed and launch the thing attitude of control missile (load).
Foreign patent DE3110328 (Revolving-cylinder jettison device for transportingand releasing buoys on and from aircraft) (patent families item: US4397433 (A1); JP56149298 (A); GB2072814 (A); FR2479135 (A1); SE8101818 (L)) disclose a kind of rotary barrel formula aircraft transmissions and the device of throwing in ring life buoy, it is made up of several input pipes, and each throws in pipe can adorn a ring life buoy long or two weak points, can forward placement position to throwing in pipe through the rotation rotary barrel; Each is thrown in pipe and is made up of wedge and maintaining body.This mechanism can realize the continuous input of ring life buoy.But what it can not control missile launches attitude and initial velocity.
Summary of the invention
Can not fine control launch the deficiency that thing is launched attitude, direction and speed in order to overcome existing wind-tunnel drop-test throwing mechanism, the present invention proposes a kind of throwing mechanism that is used for drop-test.
The present invention includes fixed mount, crossbeam, support, piston ejector ram, ejector piston, spring, missile carriage, sliding support, conductive bar and backguy, wherein: support is with being formed by connecting between two parallel bars, and its profile is " H " shape; Spacing between two parallel bars of support constitutes the installation clip slot of piston ejector ram, ejector piston and crossbeam, and the plate thickness of the diameter of the width of the installation clip slot of piston ejector ram, ejector piston and crossbeam and piston ejector ram, ejector piston and crossbeam is identical; On two bars of support one end, concentric through hole is arranged.The distance of " recessed " shape sliding support groove is identical with the width of support, and is installed on support one side; Be slidingly matched between sliding support and the support; There is through slot at sliding support groove center, and the width that clip slot is installed on the width of this through slot and the support is identical, and when sliding support was installed on the support, the through slot of sliding support was corresponding with the installation clip slot position on the support.Two piston ejector ram, ejector pistons pass the installation clip slot of support and the through slot of sliding support up and down side by side, are installed on the support, and through bolt tightening; On the piston ejector ram, ejector piston of support one side, be set with spring.Crossbeam is arranged in the installation clip slot of support one end, and clamps with bolt through the through hole of support one end; Adjustable included angle between described crossbeam and the support; Termination at crossbeam is equipped with fixed mount, through fixed mount present embodiment is fixed on the body shell.Conductive bar is passed the mounting hole on the sliding support two side; There is backguy one end termination of conductive bar, and the other end termination of conductive bar is communicated with power supply through lead; Backguy is passed as the clasp on the manikin of missile.
Described crossbeam is a plate, and its thickness is identical with installation clip slot on the support; End at crossbeam has the connecting hole that is connected with fixed mount.
Described have concentric threaded hole on the biside plate near fixed mount U-lag bottom, and the center line of this threaded hole is vertical each other with the two side wall panels of fixed mount; The place is welded with web joint at fixed mount U-lag mouth, and the connecting hole that is connected with crossbeam is arranged on this web joint.
The missile carriage is that step-like connecting link is formed by carriage with two excircles that are fixed on this carriage; When being used to throw in the paratrooper and throwing in experiment, the shape ergonomic of missile carriage.
Piston ejector ram, ejector piston is a threaded rod, and an end is processed with center pit.
Use when of the present invention, with screw whole missile throwing mechanism is fixed on the body shell edge through the threaded hole on the fixed mount; Crossbeam one end connecting hole with bolt and fixed mount web joint connecting hole fix, the other end is inserted into support has in the groove of through hole one end; Passing the support through hole with bolt steps up two bars support and crossbeam is fixed; The insertion amount of regulating crossbeam can be regulated the front and back position of support, the angular relationship that also can regulate support and crossbeam; The groove of sliding support is anchored to support, and two piston ejector ram, ejector pistons pass the through slot of sliding support and the installation clip slot that support does not have through hole one end, and two ends clamp sliding support and support with nut; Loosen nut slip sliding support on support retightens the height of regulating sliding support.The reduced diameter section of connecting link outer end is inserted in the center pit of two piston ejector ram, ejector pistons, and center pit is slightly larger than the diameter of the reduced diameter section of cylinder quarter butt outer end, forms little gap.Two spring housings and are being connected near sliding support place and two piston ejector ram, ejector pistons outside two piston ejector ram, ejector pistons and two carriage connecting links, are being connected near missile cradle and carriage connecting link.The long end of conductive bar passes two mounting holes on height both sides, center on the sliding support and clamps from both sides with nut, and is connected with power supply through lead, is connected to switch between lead and power supply; Missile is placed on the missile carriage, and both fit, and the clasp of its rear waist passes from the backguy via hole at missile carriage middle part, and the backguy via hole is a bit larger tham the clasp size.Backguy is passed the clasp of missile rear waist and is held fixedly missile and holddown spring with fixed by nut at the weak point of two conductive bar.Energising fusing backguy ejects missile with the simulation paraoperation, and the adjustment backguy just can realize changing missile deliver from vault speed to the compressing degree of spring.
The present invention adopts elementary factors such as rod member, plate, slide block, spring and screw thread to constitute mechanism, is convenient to adjust the missile attitude and launches direction.With traditional throwing mechanism spring only as fixing or to unclamp the driving force of missile different, the present invention simultaneously as fixing missile, the driving force of launching missile, makes that mechanism is simple, volume is little with spring.Adopt up and down two springs that are enclosed within on piston ejector ram, ejector piston and the carriage connecting link to fix, launch missile, make missile fixed, launch attitude stabilization, be easy to adjusting and launch speed.Through the enforcement of present technique scheme, stable the launching of missile model attitude, direction and initial velocity on request when having reached the airborne wind-tunnel drop-test of aircraft smoothly.
Description of drawings
Accompanying drawing 2 is to be used for the A of throwing mechanism structural representation of drop-test to view;
Accompanying drawing 3 is the side views that are used for the throwing mechanism structural representation of drop-test;
Accompanying drawing 4 is structural representations of fixed mount, and wherein a is a front view, and b is a side view;
Accompanying drawing 5 is structural representations of support;
Accompanying drawing 6 is structural representations of sliding support, and wherein a is a front view, and b is a vertical view;
Accompanying drawing 7 is to throw in the paratrooper to throw in the synoptic diagram that piston ejector ram, ejector piston, missile carriage and carriage connecting link cooperate when testing, and wherein a is a front view, and b is a side view;
Accompanying drawing 8 is that the box object is thrown in the synoptic diagram that piston ejector ram, ejector piston, missile carriage and carriage connecting link when testing cooperate, and wherein a is a front view, and b is a side view.Wherein:
1. body shell 2. crossbeams 3. supports 4. piston ejector ram, ejector pistons 5. springs 6. missile carriages
7. missile 8. sliding supports 9. conductive bar 10. backguys 11. fixed mounts 12. connecting links
13. backguy via hole 14. leads
Embodiment
Embodiment one
Present embodiment is a kind of throwing mechanism that is used for the wind-tunnel drop-test of paraoperation.
Present embodiment comprises fixed mount 11, crossbeam 2, support 3, piston ejector ram, ejector piston 4, spring 5, missile carriage 6, sliding support 8, conductive bar 9 and backguy 10.Present embodiment is to be used for the paraoperation throwing mechanism, and the shape ergonomic of described missile carriage 6 is thrown in to be suitable for human body.
Sliding support 8 usefulness bakelites are processed, and its profile is " recessed " font.The distance of sliding support 8 grooves is identical with the width of support 3, and is installed on support 3 one sides; Be slidingly matched between sliding support 8 and the support 3.There is through slot at sliding support 8 groove centers, and the width that clip slot is installed on the width of this through slot and the support 3 is identical, and are installed on 3 last times of support when sliding support 8, and the through slot of sliding support 8 is corresponding with the installation clip slot position on the support 3.
Piston ejector ram, ejector piston 4 is threaded rods, and an end is processed with center pit.Missile carriage 6 is that step-like connecting link 12 is formed by the carriage with the applying of manikin profile with two excircles that weld on it.Two piston ejector ram, ejector pistons 4 pass the installation clip slot of support 3 and the through slot of sliding support 8 up and down side by side, are installed on the support 3, and through bolt tightening.On the piston ejector ram, ejector piston 4 of support 3 one sides, be set with spring 5.Distance between two piston ejector ram, ejector pistons 4 is advisable can support missile carriage 6, and with carriage on two connecting links 12 between spacing identical.Crossbeam 2 is arranged in the installation clip slot of support 3 one ends, and clamps with bolt through the through hole of support 3 one ends.Adjustable included angle between described crossbeam 2 and the support 3.
Conductive bar 9 is the perpendicular type metal screw, and remainder all has screw thread except that the bight.Conductive bar 9 is passed the mounting hole on sliding support 8 two sides; There is backguy 10 one end termination of conductive bar 9, and the other end termination of conductive bar 9 is communicated with power supply through lead 14.
Rear waist as the manikin of missile 7 has a clasp, and the clasp on the missile 7 is passed in backguy 10; Clasp on the manikin passes the backguy via hole 13 on the missile carriage 6.
In the termination of crossbeam 2 fixed mount 11 is installed, present embodiment is fixed on the body shell 1 through fixed mount 11.
Crossbeam 2 is a plate, and its thickness is identical with installation clip slot on the support 3.End at crossbeam 2 has the connecting hole that is connected with fixed mount 11.Fixed mount 11 is a U-shaped spare, and the wallboard of this fixed mount 11 tilts angle is arranged, so that cooperate with body shell.On biside plate, concentric threaded hole is arranged, and the center line of this threaded hole is vertical each other with the two side wall panels of fixed mount 11 near the U-lag bottom of fixed mount 11.U-lag mouth place at fixed mount 11 is welded with web joint, and the connecting hole that is connected with crossbeam 2 is arranged on this web joint.When connecting crossbeam 2, the connecting hole of the connecting hole on the web joint of fixed mount 11 with crossbeam 2 one ends is connected with bolt with fixed mount 11.
When using present embodiment, with screw whole missile throwing mechanism is fixed on body shell 1 edge through the threaded hole on the fixed mount 11; Crossbeam 2 one end connecting holes with bolt and fixed mount 11 web joint connecting holes fix, the other end is inserted into support 3 has in the groove of through hole one end; Passing support 3 through holes with bolt, to step up two bars fixing with crossbeam 2 with support 3; The insertion amount of regulating crossbeam 2 can be regulated the front and back position of support 3, also can regulate the angular relationship of support 3 and crossbeam 2; The groove of sliding support 8 is anchored to support 3, two piston ejector ram, ejector pistons 4 and passes the through slot of sliding support 8 and the installation clip slot of support 3 no through hole one ends, and two ends clamp sliding support 8 and support 3 with nut; Loosen nut moves sliding support 8 on support 3, to regulate the height of sliding support 8.The reduced diameter section of two connecting link 12 1 ends of missile carriage 6 is inserted in the center pit of two piston ejector ram, ejector pistons 4, and center pit is slightly larger than the diameter of the reduced diameter section of cylinder quarter butt outer end, forms little gap.Two springs 5 are enclosed within outside two piston ejector ram, ejector pistons 4 and 6 two connecting links 12 of missile carriage, and are being connected near sliding support 8 places and two piston ejector ram, ejector pistons 4, are being connected near missile carriage 6 places and connecting link 12.Conductive bar 9 long ends pass two mounting holes on height both sides, center on the sliding support 8 and clamp from both sides with nut, and are connected with power supply through lead 14, are connected to switch between lead 14 and power supply; Missile 7 is placed on the missile carriage 6, and both fit, and the clasp of its rear waist passes from the backguy via hole 13 at missile carriage 6 middle parts, and the backguy via hole is a bit larger tham the clasp size.Backguy 10 is passed the clasp of missile rear waist and is held fixedly missile 7 and holddown spring 5 with fixed by nut at the weak point of two conductive bar 9.Energising fusing backguy 10 ejects missile 7 with the simulation paraoperation, and the adjustment backguy just can realize changing missile deliver from vault speed to the compressing degree of spring.
Embodiment two
Present embodiment is the throwing mechanism that is used for throwing in by certain angle and initial velocity the box-shaped object.
Present embodiment comprises fixed mount 11, crossbeam 2, support 3, piston ejector ram, ejector piston 4, spring 5, missile carriage 6, sliding support 8, conductive bar 9 and backguy 10.The missile carriage 6 of present embodiment is " L " shape, to be suitable for the input of box-shaped object.
Sliding support 8 usefulness bakelites are processed, and its profile is " recessed " font.The distance of sliding support 8 grooves is identical with the width of support 3, and is installed on support 3 one sides; Be slidingly matched between sliding support 8 and the support 3.There is through slot at sliding support 8 groove centers, and the width that clip slot is installed on the width of this through slot and the support 3 is identical, and are installed on 3 last times of support when sliding support 8, and the through slot of sliding support 8 is corresponding with the installation clip slot position on the support 3.
Piston ejector ram, ejector piston 4 is threaded rods, and an end is processed with center pit.Missile carriage 6 is that step-like connecting link 12 is formed by the carriage with the applying of manikin profile with two excircles that weld on it.Two piston ejector ram, ejector pistons 4 pass the installation clip slot of support 3 and the through slot of sliding support 8 up and down side by side, are installed on the support 3, and through bolt tightening.On the piston ejector ram, ejector piston 4 of support 3 one sides, be set with spring 5.Distance between two piston ejector ram, ejector pistons 4 is advisable can support missile carriage 6, and with carriage on two connecting links 12 between spacing identical.Crossbeam 2 is arranged in the installation clip slot of support 3 one ends, and clamps with bolt through the through hole of support 3 one ends.Adjustable included angle between described crossbeam 2 and the support 3.
Conductive bar 9 is the perpendicular type metal screw, and remainder all has screw thread except that the bight.Conductive bar 9 is passed the mounting hole on sliding support 8 two sides; There is backguy 10 one end termination of conductive bar 9, and the other end termination of conductive bar 9 is communicated with power supply through lead 14.
The clasp on the missile 7 is passed in backguy 10; Clasp on the missile 7 passes the backguy via hole 13 on the missile carriage 6.
In the termination of crossbeam 2 fixed mount 11 is installed, present embodiment is fixed on the body shell 1 through fixed mount 11.
Crossbeam 2 is a plate, and its thickness is identical with installation clip slot on the support 3.End at crossbeam 2 has the connecting hole that is connected with fixed mount 11.Fixed mount 11 is a U-shaped spare, and the wallboard of this fixed mount 11 tilts angle is arranged, so that cooperate with body shell.On biside plate, concentric threaded hole is arranged, and the center line of this threaded hole is vertical each other with the two side wall panels of fixed mount 11 near the U-lag bottom of fixed mount 11.U-lag mouth place at fixed mount 11 is welded with web joint, and the connecting hole that is connected with crossbeam 2 is arranged on this web joint.When connecting crossbeam 2, the connecting hole of the connecting hole on the web joint of fixed mount 11 with crossbeam 2 one ends is connected with bolt with fixed mount 11.
When using present embodiment, with screw whole missile throwing mechanism is fixed on body shell 1 edge through the threaded hole on the fixed mount 11; Crossbeam 2 one end connecting holes with bolt and fixed mount 11 web joint connecting holes fix, the other end is inserted into support 3 has in the groove of through hole one end; Passing support 3 through holes with bolt, to step up two bars fixing with crossbeam 2 with support 3; The insertion amount of regulating crossbeam 2 can be regulated the front and back position of support 3, also can regulate the angular relationship of support 3 and crossbeam 2; The groove of sliding support 8 is anchored to support 3, two piston ejector ram, ejector pistons 4 and passes the through slot of sliding support 8 and the installation clip slot of support 3 no through hole one ends, and two ends clamp sliding support 8 and support 3 with nut; Loosen nut moves sliding support 8 on support 3, to regulate the height of sliding support 8.The reduced diameter section of 6 two connecting link 12 outer ends of missile carriage is inserted in the center pit of two piston ejector ram, ejector pistons 4, and center pit is slightly larger than the diameter of the reduced diameter section of cylinder quarter butt outer end, forms little gap.Two springs 5 are enclosed within outside two piston ejector ram, ejector pistons 4 and 6 liang of connecting links 12 of missile carriage, and are being connected near sliding support 8 places and two piston ejector ram, ejector pistons 4, are being connected near missile carriage 6 places and connecting link 12.Conductive bar 9 long ends pass two mounting holes on height both sides, center on the sliding support 8 and clamp from both sides with nut, and are connected with power supply through lead 14, are connected to switch between lead 14 and power supply; Missile 7 is placed on the missile carriage 6, and both fit, and the clasp of its rear waist passes from the backguy via hole 13 at missile carriage 6 middle parts, and the backguy via hole is a bit larger tham the clasp size.Backguy 10 is passed the clasp of missile rear waist and is held fixedly missile 7 and holddown spring 5 with fixed by nut at the weak point of two conductive bar 9.Box-shaped missile 7 is ejected in energising fusing backguy 10, and the adjustment backguy just can realize changing missile deliver from vault speed to the compressing degree of spring.
Claims (5)
1. throwing mechanism that is used for drop-test; It is characterized in that the described throwing mechanism that is used for drop-test comprises fixed mount (11), crossbeam (2), support (3), piston ejector ram, ejector piston (4), spring (5), missile carriage (6), sliding support (8), conductive bar (9) and backguy (10); Wherein:
A. support (3) is with being formed by connecting between two parallel bars, and its profile is " H " shape; Spacing between (3) two parallel bars of support constitutes the installation clip slot of piston ejector ram, ejector piston (4) and crossbeam (2), and the plate thickness of the diameter of the width of the piston ejector ram, ejector piston (4) and the installation clip slot of crossbeam (2) and piston ejector ram, ejector piston (4) and crossbeam (2) is identical; Cooperate with crossbeam (2) at support (3) on two bars of an end concentric through hole is arranged;
B. the distance of " recessed " shape sliding support (8) groove is identical with the width of support (3), and is installed on support (3) one sides, makes the through slot of sliding support (8) corresponding with the installation clip slot position on the support (3); Be slidingly matched between sliding support (8) and the support (3); There is through slot at sliding support (8) groove center, and it is identical that the width of this through slot and support (3) are gone up the width that clip slot is installed, and is installed on support (3) last time when sliding support (8), and the through slot of sliding support (8) is corresponding with the installation clip slot position on the support (3);
C. two piston ejector ram, ejector pistons (4) pass the installation clip slot of support (3) and the through slot of sliding support (8) up and down side by side, be installed on the support (3), and through bolt tightening; On the piston ejector ram, ejector piston (4) of support (3) one sides, be set with spring (5);
D. crossbeam (2) is arranged in the installation clip slot that support (3) has concentric through hole one end, and clamps with bolt through the through hole on the support (3); Adjustable included angle between described crossbeam (2) and the support (3); In the termination of crossbeam (2) fixed mount (11) is installed, throwing mechanism is fixed on the body shell (1) through fixed mount (11);
E. conductive bar (9) is passed the mounting hole on sliding support (8) two side; There is backguy (10) one end termination of conductive bar (9), and the other end termination of conductive bar (9) is communicated with power supply through lead (14); Backguy (10) is passed as the clasp on the manikin of missile (7).
2. a kind of according to claim 1 throwing mechanism that is used for drop-test is characterized in that, at an end of crossbeam (2) connecting hole that is connected with fixed mount (11) is arranged.
3. a kind of according to claim 1 throwing mechanism that is used for drop-test is characterized in that, on the biside plate near fixed mount (11) U-lag bottom, concentric threaded hole is arranged, and the center line of this threaded hole is vertical each other with the two side wall panels of fixed mount (11); There is web joint at the place at fixed mount (11) U-lag mouth, and the connecting hole that is connected with crossbeam (2) is arranged on this web joint.
4. a kind of according to claim 1 throwing mechanism that is used for drop-test is characterized in that, missile carriage (6) is that step-like connecting link (12) is formed by carriage with two excircles that are fixed on this carriage; When being used to throw in the paratrooper and throwing in experiment, the shape ergonomic of missile carriage (6).
5. a kind of according to claim 1 throwing mechanism that is used for drop-test is characterized in that piston ejector ram, ejector piston (4) is a threaded rod, and an end is processed with center pit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110045226A CN102183352B (en) | 2011-02-24 | 2011-02-24 | Releasing mechanism used for releasing experiments |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110045226A CN102183352B (en) | 2011-02-24 | 2011-02-24 | Releasing mechanism used for releasing experiments |
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| CN102183352A CN102183352A (en) | 2011-09-14 |
| CN102183352B true CN102183352B (en) | 2012-09-05 |
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| CN201110045226A Active CN102183352B (en) | 2011-02-24 | 2011-02-24 | Releasing mechanism used for releasing experiments |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105021368B (en) * | 2015-07-17 | 2017-09-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of quick delivery device of wind-tunnel mini Mod |
| CN105203293A (en) * | 2015-10-19 | 2015-12-30 | 南京航空航天大学 | Dummy air-drop six-component balance test system and method |
| CN105865743B (en) * | 2016-06-24 | 2018-08-07 | 中国航天空气动力技术研究院 | High-speed wind tunnel launches drop-test mechanism |
| CN106197937B (en) * | 2016-06-24 | 2018-09-14 | 中国航天空气动力技术研究院 | high speed ejection model quick release device |
| CN109003515B (en) * | 2018-08-07 | 2020-10-09 | 吴畅 | Demonstration instrument for water pressure reflection experiment |
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|---|---|---|---|---|
| DE3110328A1 (en) * | 1980-03-26 | 1982-01-21 | R. Alkan & Cie, 94460 Valenton | DEVICE IN THE FORM OF A DRUM FOR TAKING AND DISPLAYING BUOYS ON BOARD A VEHICLE |
| CN2875949Y (en) * | 2006-04-05 | 2007-03-07 | 江南机器（集团）有限公司 | Portable load clamping and throwing device of pilotless plane |
| CN201357959Y (en) * | 2009-01-04 | 2009-12-09 | 丹阳仅一包装设备有限公司 | Automatic spoon setting mechanism |
| CN202024873U (en) * | 2011-02-24 | 2011-11-02 | 西北工业大学 | Dropping mechanism for wind tunnel test |
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2011
- 2011-02-24 CN CN201110045226A patent/CN102183352B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3110328A1 (en) * | 1980-03-26 | 1982-01-21 | R. Alkan & Cie, 94460 Valenton | DEVICE IN THE FORM OF A DRUM FOR TAKING AND DISPLAYING BUOYS ON BOARD A VEHICLE |
| CN2875949Y (en) * | 2006-04-05 | 2007-03-07 | 江南机器（集团）有限公司 | Portable load clamping and throwing device of pilotless plane |
| CN201357959Y (en) * | 2009-01-04 | 2009-12-09 | 丹阳仅一包装设备有限公司 | Automatic spoon setting mechanism |
| CN202024873U (en) * | 2011-02-24 | 2011-11-02 | 西北工业大学 | Dropping mechanism for wind tunnel test |
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