CN202024873U - Dropping mechanism for wind tunnel test - Google Patents
Dropping mechanism for wind tunnel test Download PDFInfo
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- CN202024873U CN202024873U CN2011200474599U CN201120047459U CN202024873U CN 202024873 U CN202024873 U CN 202024873U CN 2011200474599 U CN2011200474599 U CN 2011200474599U CN 201120047459 U CN201120047459 U CN 201120047459U CN 202024873 U CN202024873 U CN 202024873U
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Abstract
The utility model relates to a dropping mechanism for a wind tunnel test, wherein a sliding support is positioned at one end of a bracket. Two ejection rods vertically penetrate through a mounting sandwich groove of the bracket and a penetration groove of the sliding support side by side, and are sandwiched on the bracket; and one of the ejection rods close to the bracket is sheathed with a spring. A cross beam is positioned in the mounting sandwich groove positioned at one end of the bracket, and an included angle formed between the cross beam and the bracket can be adjusted; and a fixing bracket is installed at the end socket of the cross beam, and the dropping mechanism is fixed on a main body casing through the fixing bracket. A conduction rod penetrates through the mounting holes formed on the two side walls of the sliding support; the end socket of one end of the conduction rod is provided with a stay wire, the end socket of the other end of the conduction rod is communicated with a power supply through a conducting wire; in addition, the stay wire penetrates through a buckling ring arranged on a mannequin used as a dropped object. When the dropping mechanism is in use, the stay wire is fused after being electrified, and the compressing degree of the stay wire on the spring can be adjusted so as to adjust the cabin leaving angle and the acceleration of the dropped object. The dropping mechanism has a simple structure, is convenient and reliable to use, is suitable for the dropping test of a common object, and is also suitable for the dropping test of skytroopers.
Description
Technical field
The present invention relates to aircraft floor experimental technique field, specifically is a kind of throwing mechanism that is used for the wind-tunnel drop-test.
Background technology
Technology related to the present invention is the aircraft wind-tunnel drop-test technology of dropping a bomb.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 goes out realization with pressure-air through vent line, and mechanism's complexity, volume are 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 finish 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 class 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 by 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 the throwing mechanism that a kind of wind tunnel test is used.
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 to be 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 by 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 by the through hole of support one end; Adjustable included angle between described crossbeam and the support; Termination at crossbeam is equipped with fixed mount, by 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 by 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 having concentric threaded hole near on the biside plate of fixed mount U-lag bottom, and the center line of this threaded hole is vertical mutually 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 of missile carriage meets ergonomics.
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 by 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 in close 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 by 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 degree that compresses 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 regulate the speed of launching.By the enforcement of the technical program, 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 1 is the structural representation that is used for the throwing mechanism of drop-test;
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. missiles 8. sliding supports 9. conductive bar 10. backguys 11. fixed mounts 12. connecting links 13. backguy via holes 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 of described missile carriage 6 meets ergonomics, throws in to be suitable for human body.
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 of fitting with the manikin profile and welding two excircles 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 by 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 by 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 by 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 by 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 mutually 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 by 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 support 3 and crossbeam 2, the insertion amount of regulating crossbeam 2 can be regulated the front and back position of support 3, the angular relationship that also can regulate 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 by 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 degree that compresses 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 made, 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 when sliding support 8 was installed on the support 3, the through slot of sliding support 8 was 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 of fitting with the manikin profile and welding two excircles 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 by 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 by 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 by 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 by 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 mutually 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 by 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 support 3 and crossbeam 2, the insertion amount of regulating crossbeam 2 can be regulated the front and back position of support 3, the angular relationship that also can regulate 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 by 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 degree that compresses of spring.
Claims (5)
1. throwing mechanism that wind tunnel test is used, 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 to be 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; On two bars of support (3) one ends, 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; Be slidingly matched between sliding support (8) and the support (3); There is through slot at sliding support (8) groove center, the width of this through slot is identical with the width that support (3) is gone up the installation clip slot, and when sliding support (8) was installed on the support (3), the through slot of sliding support (8) was 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 by 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 of support (3) one ends, and clamps with bolt by the through hole of support (3) one ends; Adjustable included angle between described crossbeam (2) and the support (3); In the termination of crossbeam (2) fixed mount (11) is installed, present embodiment is fixed on the body shell (1) by 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 by lead (14); Backguy (10) is passed as the clasp on the manikin of missile 7.
2. the throwing mechanism that a kind of according to claim 1 wind tunnel test is used is characterized in that 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).
3. the throwing mechanism that a kind of according to claim 1 wind tunnel test is used is characterized in that, near on the biside plate of fixed mount (11) U-lag bottom concentric threaded hole is being arranged, and the center line of this threaded hole is vertical mutually with the two side wall panels of fixed mount (11); The place is welded with web joint at fixed mount (11) U-lag mouth, and the connecting hole that is connected with crossbeam (2) is arranged on this web joint.
4. the throwing mechanism that a kind of according to claim 1 wind tunnel test is used 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 of missile carriage (6) meets ergonomics.
5. the throwing mechanism that a kind of according to claim 1 wind tunnel test is used 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 |
|---|---|---|---|
| CN2011200474599U CN202024873U (en) | 2011-02-24 | 2011-02-24 | Dropping mechanism for wind tunnel test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011200474599U CN202024873U (en) | 2011-02-24 | 2011-02-24 | Dropping mechanism for wind tunnel test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202024873U true CN202024873U (en) | 2011-11-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011200474599U Expired - Lifetime CN202024873U (en) | 2011-02-24 | 2011-02-24 | Dropping mechanism for wind tunnel test |
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| CN (1) | CN202024873U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102183352A (en) * | 2011-02-24 | 2011-09-14 | 西北工业大学 | Releasing mechanism used for releasing experiments |
| CN105021369A (en) * | 2015-07-17 | 2015-11-04 | 中国空气动力研究与发展中心超高速空气动力研究所 | Mechanical gripping clamp with frictional retarding and positioning functions |
| CN106950030A (en) * | 2017-05-04 | 2017-07-14 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of missile release device |
| CN108195550A (en) * | 2018-01-15 | 2018-06-22 | 中国航天空气动力技术研究院 | Model launches separation modified wind tunnel test mechanism |
| CN109141805A (en) * | 2018-09-20 | 2019-01-04 | 北京空间机电研究所 | A kind of parachute aerodynamic coefficient and torque coefficient calculation method and system |
| CN112985748A (en) * | 2021-05-08 | 2021-06-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test throwing device and method for designing throwing object model thereof |
-
2011
- 2011-02-24 CN CN2011200474599U patent/CN202024873U/en not_active Expired - Lifetime
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102183352A (en) * | 2011-02-24 | 2011-09-14 | 西北工业大学 | Releasing mechanism used for releasing experiments |
| CN102183352B (en) * | 2011-02-24 | 2012-09-05 | 西北工业大学 | Releasing mechanism used for releasing experiments |
| CN105021369A (en) * | 2015-07-17 | 2015-11-04 | 中国空气动力研究与发展中心超高速空气动力研究所 | Mechanical gripping clamp with frictional retarding and positioning functions |
| CN105021369B (en) * | 2015-07-17 | 2017-06-06 | 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 mechanical grip pincers of friction eceleration positioning |
| CN106950030A (en) * | 2017-05-04 | 2017-07-14 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of missile release device |
| CN108195550A (en) * | 2018-01-15 | 2018-06-22 | 中国航天空气动力技术研究院 | Model launches separation modified wind tunnel test mechanism |
| CN108195550B (en) * | 2018-01-15 | 2019-10-18 | 中国航天空气动力技术研究院 | Model launches separation modified wind tunnel test mechanism |
| CN109141805A (en) * | 2018-09-20 | 2019-01-04 | 北京空间机电研究所 | A kind of parachute aerodynamic coefficient and torque coefficient calculation method and system |
| CN109141805B (en) * | 2018-09-20 | 2020-10-23 | 北京空间机电研究所 | Parachute aerodynamic coefficient and moment coefficient calculation method and system |
| CN112985748A (en) * | 2021-05-08 | 2021-06-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test throwing device and method for designing throwing object model thereof |
| CN112985748B (en) * | 2021-05-08 | 2021-07-30 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test throwing device and method for designing throwing object model thereof |
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