US3597969A - Dynamic tester for projectile components - Google Patents
Dynamic tester for projectile components Download PDFInfo
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- US3597969A US3597969A US7929A US3597969DA US3597969A US 3597969 A US3597969 A US 3597969A US 7929 A US7929 A US 7929A US 3597969D A US3597969D A US 3597969DA US 3597969 A US3597969 A US 3597969A
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- spin
- projectile
- mitigator
- catch tube
- predetermined
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
Definitions
- the system is designed for rapid production line testing by means of a control system which starts the spin tube in motion and releases the projectile when a predetermined pressure has been established within the air gun.
- the control system also terminates the spin and actuates a fluid operated component to replace the mitigator to its start position within the spin tube.
- a spin angle sensor is provided to transmit a signal for release of the projectile only when the spin tube is in a predetermined angular orientation.
- This invention relates to an apparatus for linear and angular acceleration to which projectiles are subjected in rifled artillery weaponry, and more particularly to an improvement in the artillery simulator disclosed in Us. Pat. No. 3,444,733 issued to Curchack'on May 20, I969.
- the artillery simulator disclosed in the Curchack patent unites the features of a gas gun and a low,inertia spinner in a single test apparatus to simulate the linear and angular accelerations experienced in rifled artillery weaponry. Difficulties are encountered in adapting the invention disclosed in the Curchack patent to production line testing of projectile components, such as power supplies and fuzes, in rapid succession. The purpose of this invention is to overcome these difficulties and to provide an artillery simulator capable of testing large numbers ofprojectile components in rapid succession.
- Another object of this invention is to provide a test apparatus which is fully automated and capable of testing projectile components in rapid succession.
- a modified prominates the spin and actuates a fluid operated component to replace the mitigator to its start position within the spin tube.
- a spin angle sensor is provided to transmit a signal for release of the projectile only when the spin tube is in a predetermined angular orientation.
- FIG. I is a diagrammatic representation of a complete system embodying the principles of the present invention.
- FIG. 2 is a cross-sectional view of one embodiment of a mitigator for use in the present invention.
- FIG. I shows the entire system in diagrammatic form
- Acceleration gun I containing projectile II is provided with a quick-change diaphragm assembly 26 including a thin diaphragm 14.
- the acceleration gun is powered by means of vacuum pump 12 through valve 13 which is actuated by control system I7.
- Projectile II is fired out of acceleration gun by creating a partial vacuum in the forward portion 8 of the acceleration gun, thereby causing atmospheric pressure to act at the rear 9 of the projectile.
- Restraining pin 15 is located within groove 16 of projectile II to prevent the projectile from being fired until a predetermined pressure has been established within the acceleration gun.
- Pressure transducer I8 detects this predetermined pressure and transmits a signal to control system I7 which in turn shuts off valve 13 and withdraws pin l5 to permit the projectile to be fired.
- fluid power source 37 which may be hydraulic or pneumatic, is activated by a signal from control system 17 to displace piston 39, thereby inserting platform 23 into mitigatorcatch tube 21.
- Mitigator 20 is thus replaced to its normal position within spincatch tube I9 and projectile 1] falls out onto a support member 24 where it is removed by an operator.
- the entire cycle is then repeated with the replacement of a new projectile l1 and a new membrane 14.
- restraining pin 15 and platform 23 are automatically replaced to their original starting positions in response to signals fromcontrol system 17. Since the entire system is fully automated, it is possible to test a great number of projectile components under production line techniques.
- mitigator 20 comprises an outer hollow housing 45 having a first centrally located bore 5] and a second larger bore 59 coaxial with the first bore.
- Shaft 42 rides within bore 51 and is connected to piston 43 which rides within the larger bore 59.
- Region 44 is normally filled with a fluid of a predetermined known viscosity and the entire chamber defined by bore 59 is fluid sealed by means of suitable O-rings 0r gaskets.
- the portion of shaft 42 which extends outside of housing 45 is provided with enlarged flange or plate 41 having a rubber surface 28 firmly secured thereto.
- mitigator 20 In the normal operation of this device, mitigator 20 is located within spin-catch tube I9 and is rotating when it is suddenly struck by projectile II. The force of projectile lI against surface 28 of mitigator 20 causes shaft 42 to be pushed into housing 45. Because region 44 is filled with fluid, the force exerted against piston 43 by the projectile is partially transmitted to housing 45. A small space 57 is provided between piston 43 and bore 59. As force is exerted against piston 43, some of the fluid in region 84 flows through space 57 thereby allowing piston 43 to be further depressed into housing 45.
- the magnitude of linear deceleration provided by mitigator 20 is controllable by simply varying the diameter of bore 59 or by changing such other parameters as the density of the fluid within region 44 or the size of space 57.
- the easiest parameter to change is, of course, the density of the fluid.
- Spring 47 is designed to return the piston to its ready position and does not have sufficient resistance to materially affect the deceleration force applied to projectile 11 upon impact.
- mitigator 20 is located within spin-catch tube 19 and is spinning at a very rapid rate.
- Projectile II is not spinning at the time of impact. Because it is desirable to start projectile II spinning as soon as possible, mitigator 20 is designed to impart some of its rotational spin to projectile ll. This is accomplished by causing some of the force created by spinning mass 45 to be exerted through shaft 42 upon non spinning projectile ll.
- the force created by spinning mass 45 is coupled to shaft 42 by a pin 52 which extends from shaft 42 into housing 45 and is located within a helical groove 53.
- the purpose of the helical groove is to provide a gradual transmission of force from housing 45 to shaft 42 rather than an instan taneous force.
- Control system 17 is then programmed to release restraining pin IE only upon receiving the appropriate signal from spin angle sensor 63
- this invention provides a novel artillery simulator which is capable of rapid and efficient production line testing of projectile components
- An artillery simulator for testing projectile components under firing conditions comprising:
- a projectile means having a hollow portion for containing test components
- restraining means located within said acceleration means for restraining said projectile until a predetermined vacuum has been created with said acceleration means;
- a spin-catch tube positioned to receive said projectile upon its emergence from said acceleration means
- mitigator means normally positioned within said spincatch tube to provide a predetermined amount of deceleration to said projectile upon impact;
- a spin motor for rotating said spin-catch tube in response to a predetermined signal
- a mitigator-catch tube positioned to receive said mitigator upon its emergence from said spin-catch tube;
- mitigator replacement means responsive to a predetermined signal for displacing said mitigator from said mitigator-catch tube and replacing it in said spin-catch tube, whereby said projectile is caused to fall onto a support located between said accelerator and said spin-catch tube;
- a control system responsive to the pressure levels within said accelerator for removing said restraining means, activating said spin motor for a predetermined time, and activating said mitigator replacement means.
- vacuum acceleration means comprises means for reducing the pressure in the forward region of said projectile, thereby causing atmospheric pressure to propel said projectile.
- mitigator replacement means comprises a fluid actuated piston assembly for driving said mitigator back into said spin-catch tube.
- the artillery simulator of claim I further comprising a spin angle sensor for sensing the angular orientation of said spin-catch tube and transmitting a signal to said control system whenever said spin-catch tube is in a predetermined angularorientation.
- mitigator comprises means for applying a predetermined deceleration force and imparting a spin force to said projectilev
Abstract
Projectile component testing. A modified projectile, containing components to be tested, is accelerated by means of a vacuum air gun into a spinning tube where it is set in spinning motion while simultaneously being decelerated. Deceleration is accomplished by means of a hydraulic mitigator capable of imparting rotational spin to the projectile while applying a predetermined rate of deceleration. The system is designed for rapid production line testing by means of a control system which starts the spin tube in motion and releases the projectile when a predetermined pressure has been established within the air gun. The control system also terminates the spin and actuates a fluid operated component to replace the mitigator to its start position within the spin tube. In order to provide a check on the polarity of power supplies being tested, a spin angle sensor is provided to transmit a signal for release of the projectile only when the spin tube is in a predetermined angular orientation.
Description
United States Patent [72] Inventor Herbert D. Curchaclr Rockville, Md. [21] Appl. No. 7,929 [22] Filed Feb. 2, 1970 [45] Patented Aug. 10, 1971 [73] Assignee The United States of America as represented by the Secretary of the Army [54] DYNAMIC TESTER FOR PROJECTILE COMPONENTS 6 Claims, 2 Drawing Figs.
[52] U.S.CI. 73/167,
73/ I2. [51 I Int. Cl G0lm 19/00 [50] Field oiSearch... 73/l67,5, 12; 221/233, 257
[56] References Cited UNITED STATES PATENTS 2,462,922 3/1949 Temple 221/232 X 3,444,733 5/1969 Curchack 73/167 HEAD OUT I Primary Examiner-S. Clement Swisher Assistant ExaminerDenis E. Corr Att0rneys-Harry M. Saragovitz, Edward J. Kelly, Herbert Berl and Jv D. Edgerton ABSTRACT: Projectile component testing. A modified projectile, containing components to be tested, is accelerated bymeans of a vacuum air gun into a spinning tube where it is set in spinning motion while simultaneously being decelerated. Deceleration is accomplished by means of a hydraulic mitigator capable of imparting rotational spin to the projectile while applying a predetermined rate of deceleration. The system is designed for rapid production line testing by means of a control system which starts the spin tube in motion and releases the projectile when a predetermined pressure has been established within the air gun. The control system also terminates the spin and actuates a fluid operated component to replace the mitigator to its start position within the spin tube. In order to provide a check on the polarity of power supplies being tested, a spin angle sensor is provided to transmit a signal for release of the projectile only when the spin tube is in a predetermined angular orientation.
SPIN as FLUID Power $5 =51\ SOUQCE PRESSURE 5PM 'mmsoucerz VACUUM PUMP comm. SYSTEM DYNAMIC TESTER FOR PROJECTILE COMPONENTS RIGHTS OF THE GOVERNMENT The invention described herein may be manufactured, used, and licensed by or for the US. Government for governmental purposes without the payment to me of any royalty thereon.
BACKGROUND OF THE INVENTION This invention relates to an apparatus for linear and angular acceleration to which projectiles are subjected in rifled artillery weaponry, and more particularly to an improvement in the artillery simulator disclosed in Us. Pat. No. 3,444,733 issued to Curchack'on May 20, I969.
The artillery simulator disclosed in the Curchack patent unites the features of a gas gun and a low,inertia spinner in a single test apparatus to simulate the linear and angular accelerations experienced in rifled artillery weaponry. Difficulties are encountered in adapting the invention disclosed in the Curchack patent to production line testing of projectile components, such as power supplies and fuzes, in rapid succession. The purpose of this invention is to overcome these difficulties and to provide an artillery simulator capable of testing large numbers ofprojectile components in rapid succession.
It is therefore a primary object of this invention to provide a test apparatus for simulating the linear and angular accelerations experienced in rifle artillery weaponry.
Another object of this invention is to provide a test apparatus which is fully automated and capable of testing projectile components in rapid succession.
simulating the SUMMARY OF THE INVENTION Briefly, in accordance with this invention, a modified prominates the spin and actuates a fluid operated component to replace the mitigator to its start position within the spin tube. In order to provide a check on the polarity of power supplies being tested, a spin angle sensor is provided to transmit a signal for release of the projectile only when the spin tube is in a predetermined angular orientation.
BRIEF DESCRIPTION OF THE DRAWINGS Thev foregoing and other objects, features and advantages of the invention will be apparent from the following more particular description ofa preferred embodiment of the invention as illustrated in the accompanying drawings in which:
FIG. I is a diagrammatic representation of a complete system embodying the principles of the present invention.
FIG. 2 is a cross-sectional view of one embodiment of a mitigator for use in the present invention.
DESCRIPTION OF THE PREFERRED EMBODIMENT The invention will be understood more readily by referring to FIG. I which shows the entire system in diagrammatic form, Acceleration gun I containing projectile II is provided with a quick-change diaphragm assembly 26 including a thin diaphragm 14. The acceleration gun is powered by means of vacuum pump 12 through valve 13 which is actuated by control system I7. Projectile II is fired out of acceleration gun by creating a partial vacuum in the forward portion 8 of the acceleration gun, thereby causing atmospheric pressure to act at the rear 9 of the projectile. Restraining pin 15 is located within groove 16 of projectile II to prevent the projectile from being fired until a predetermined pressure has been established within the acceleration gun. Pressure transducer I8 detects this predetermined pressure and transmits a signal to control system I7 which in turn shuts off valve 13 and withdraws pin l5 to permit the projectile to be fired.
Upon withdrawal of pin I5, projectile ll pierces membrane 14 and impacts surface 28 of mitigator 20, thereby displacing mitigator 20 from spin-catch tube 19. Mitigator 20 ultimately comes to rest in mitigator-catch tube 2I after striking platform 23 of hydraulic mitigator replacement means 22. Projectile I l comes to rest within spincatch tube I9 which has already been set in spinning motion by means of spin motor 35. The precise moment at which the spin motor is activated depends upon a predetermined pressure within region 3 of acceleration gun II), which pressure is detected by pressure transducer 18 and transmitted as an electrical signal to control system I7.
Spin-catch tube I9 is caused to spin for a predetermined time in the manner more fully described in the previously mentioned Curchack patent. During the flight period of the projectile its velocity is measured by means of photocells 25 in a well-known manner as also described in the Curchack patent.
At the termination of the spin period for the spin-catch tube, fluid power source 37, which may be hydraulic or pneumatic, is activated by a signal from control system 17 to displace piston 39, thereby inserting platform 23 into mitigatorcatch tube 21. Mitigator 20 is thus replaced to its normal position within spincatch tube I9 and projectile 1] falls out onto a support member 24 where it is removed by an operator. The entire cycle is then repeated with the replacement of a new projectile l1 and a new membrane 14. At the start of a new cycle, restraining pin 15 and platform 23 are automatically replaced to their original starting positions in response to signals fromcontrol system 17. Since the entire system is fully automated, it is possible to test a great number of projectile components under production line techniques.
Referring now to FIG. 2, mitigator 20 comprises an outer hollow housing 45 having a first centrally located bore 5] and a second larger bore 59 coaxial with the first bore. Shaft 42 rides within bore 51 and is connected to piston 43 which rides within the larger bore 59. Region 44 is normally filled with a fluid of a predetermined known viscosity and the entire chamber defined by bore 59 is fluid sealed by means of suitable O-rings 0r gaskets. The portion of shaft 42 which extends outside of housing 45 is provided with enlarged flange or plate 41 having a rubber surface 28 firmly secured thereto.
In the normal operation of this device, mitigator 20 is located within spin-catch tube I9 and is rotating when it is suddenly struck by projectile II. The force of projectile lI against surface 28 of mitigator 20 causes shaft 42 to be pushed into housing 45. Because region 44 is filled with fluid, the force exerted against piston 43 by the projectile is partially transmitted to housing 45. A small space 57 is provided between piston 43 and bore 59. As force is exerted against piston 43, some of the fluid in region 84 flows through space 57 thereby allowing piston 43 to be further depressed into housing 45. It will be appreciated that the magnitude of linear deceleration provided by mitigator 20 is controllable by simply varying the diameter of bore 59 or by changing such other parameters as the density of the fluid within region 44 or the size of space 57. The easiest parameter to change is, of course, the density of the fluid. Thus the rate of fluid flow from right to left will determine the rate and magnitude of the force which is transmitted to housing 45 and, consequently, the dece leration force on projectile 11. Spring 47 is designed to return the piston to its ready position and does not have sufficient resistance to materially affect the deceleration force applied to projectile 11 upon impact.
As was previously mentioned, at the time of impact mitigator 20 is located within spin-catch tube 19 and is spinning at a very rapid rate. Projectile II, on the other hand, is not spinning at the time of impact. Because it is desirable to start projectile II spinning as soon as possible, mitigator 20 is designed to impart some of its rotational spin to projectile ll. This is accomplished by causing some of the force created by spinning mass 45 to be exerted through shaft 42 upon non spinning projectile ll. The force created by spinning mass 45 is coupled to shaft 42 by a pin 52 which extends from shaft 42 into housing 45 and is located within a helical groove 53. The purpose of the helical groove is to provide a gradual transmission of force from housing 45 to shaft 42 rather than an instan taneous force. lf pin 52 were merely located within a slot rather than a helical groove it is very likely that the shear force on pin 52 would break the pin. A more detailed explanation of this feature can be found in applicants copending application entitled Hydraulic Mitigator, Ser. No 7,928, filed Feb. 2, l970.
The details ofelectrical readout 64 are fully described in the aforementioned Curchack patent. The arrangement disclosed therein has one disadvantage in that a test battery or power supply which is faulty because of reversed polarity would go undetected by the former readout system. In order to detect such faults in power supplies a spin angle sensor 63 is provided. The spin angle sensor transmits a signal to control system 17 whenever spin-catch tube 19 is in a predetermined angular orientation. Control system 17 is then programmed to release restraining pin IE only upon receiving the appropriate signal from spin angle sensor 63 By mathematically calculating the time which would be required for projectile II to reach spin-catch tube 19, one can determine the appropriate release time such that projectile II will always have the same angular orientation will respect to spin-catch tube [9 at its time of arrival. Consequently, any reverse polarity at readout 64 would be indicative of a faulty power supply.
It will be appreciated from the foregoing description that this invention provides a novel artillery simulator which is capable of rapid and efficient production line testing of projectile components,
It should be understood that I do not desire to be limited to the exact details shown and described, for obvious modifications will occur to one skilled in the art.
I claim as my invention:
1. An artillery simulator for testing projectile components under firing conditions comprising:
a. projectile means having a hollow portion for containing test components;
b. vacuum acceleration means for accelerating said projectile to a desired velocity;
. restraining means located within said acceleration means for restraining said projectile until a predetermined vacuum has been created with said acceleration means;
d. a spin-catch tube positioned to receive said projectile upon its emergence from said acceleration means;
e. mitigator means normally positioned within said spincatch tube to provide a predetermined amount of deceleration to said projectile upon impact;
f. a spin motor for rotating said spin-catch tube in response to a predetermined signal;
. a mitigator-catch tube positioned to receive said mitigator upon its emergence from said spin-catch tube;
h. mitigator replacement means responsive to a predetermined signal for displacing said mitigator from said mitigator-catch tube and replacing it in said spin-catch tube, whereby said projectile is caused to fall onto a support located between said accelerator and said spin-catch tube; and
. a control system responsive to the pressure levels within said accelerator for removing said restraining means, activating said spin motor for a predetermined time, and activating said mitigator replacement means.
2. The artillery simulator of claim I wherein said vacuum acceleration means comprises means for reducing the pressure in the forward region of said projectile, thereby causing atmospheric pressure to propel said projectile.
3. The artillery simulator of claim I wherein said mitigator replacement means comprises a fluid actuated piston assembly for driving said mitigator back into said spin-catch tube.
4. The artillery simulator of claim I further comprising a spin angle sensor for sensing the angular orientation of said spin-catch tube and transmitting a signal to said control system whenever said spin-catch tube is in a predetermined angularorientation.
5. The artillery simulator of claim 4 wherein said restraining pin is released only in response to a signal from said spin angle sensor.
6. The artillery simulator of claim I wherein said mitigator comprises means for applying a predetermined deceleration force and imparting a spin force to said projectilev
Claims (6)
1. An artillery simulator for testing proJectile components under firing conditions comprising: a. projectile means having a hollow portion for containing test components; b. vacuum acceleration means for accelerating said projectile to a desired velocity; c. restraining means located within said acceleration means for restraining said projectile until a predetermined vacuum has been created with said acceleration means; d. a spin-catch tube positioned to receive said projectile upon its emergence from said acceleration means; e. mitigator means normally positioned within said spin-catch tube to provide a predetermined amount of deceleration to said projectile upon impact; f. a spin motor for rotating said spin-catch tube in response to a predetermined signal; g. a mitigator-catch tube positioned to receive said mitigator upon its emergence from said spin-catch tube; h. mitigator replacement means responsive to a predetermined signal for displacing said mitigator from said mitigator-catch tube and replacing it in said spin-catch tube, whereby said projectile is caused to fall onto a support located between said accelerator and said spin-catch tube; and i. a control system responsive to the pressure levels within said accelerator for removing said restraining means, activating said spin motor for a predetermined time, and activating said mitigator replacement means.
2. The artillery simulator of claim 1 wherein said vacuum acceleration means comprises means for reducing the pressure in the forward region of said projectile, thereby causing atmospheric pressure to propel said projectile.
3. The artillery simulator of claim 1 wherein said mitigator replacement means comprises a fluid actuated piston assembly for driving said mitigator back into said spin-catch tube.
4. The artillery simulator of claim 1 further comprising a spin angle sensor for sensing the angular orientation of said spin-catch tube and transmitting a signal to said control system whenever said spin-catch tube is in a predetermined angular orientation.
5. The artillery simulator of claim 4 wherein said restraining pin is released only in response to a signal from said spin angle sensor.
6. The artillery simulator of claim 1 wherein said mitigator comprises means for applying a predetermined deceleration force and imparting a spin force to said projectile.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US792970A | 1970-02-02 | 1970-02-02 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3597969A true US3597969A (en) | 1971-08-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US7929A Expired - Lifetime US3597969A (en) | 1970-02-02 | 1970-02-02 | Dynamic tester for projectile components |
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| Country | Link |
|---|---|
| US (1) | US3597969A (en) |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3693432A (en) * | 1971-06-22 | 1972-09-26 | Us Army | Artillery gun shock simulator |
| US4010631A (en) * | 1975-09-09 | 1977-03-08 | The United States Of America As Represented By The Secretary Of The Army | Method and apparatus for pulse shaping in ballistic simulators |
| US4038869A (en) * | 1976-10-22 | 1977-08-02 | The United States Of America As Represented By The Secretary Of The Army | Simulator for setback followed by drag |
| US4069702A (en) * | 1977-02-04 | 1978-01-24 | Sanders Associates, Inc. | Method and apparatus for testing the run-out and recoil control systems of a gun |
| US4495792A (en) * | 1983-05-02 | 1985-01-29 | Motorola, Inc. | Method for simulating a shock pulse |
| US4599897A (en) * | 1985-03-29 | 1986-07-15 | The United States Of America As Represented By The Secretary Of The Army | Tubular shaped sled test complex |
| US4719797A (en) * | 1985-08-14 | 1988-01-19 | Her Majesty The Queen In Right Of Canada, As Represented By The Minister Of National Defence | Spinning assembly for explosive munitions |
| US5184499A (en) * | 1990-01-31 | 1993-02-09 | Schweizerische Eidgenossenschaft Vertreten Durch Die Eidg. Munitionsfabrik Thun Der Gruppe Fur Rustungsdienste | Testing device with acceleration tube |
| US5388520A (en) * | 1993-10-04 | 1995-02-14 | The United States Of America As Represented By The Scretary Of The Army | Individual mine launcher |
| US5686652A (en) * | 1996-09-09 | 1997-11-11 | Pfund; Bruce | Portable test hammer apparatus |
| US5762057A (en) * | 1996-12-30 | 1998-06-09 | The United States Of America As Represented By The United States Department Of Energy | Light gas gun with reduced timing jitter |
| US6609420B2 (en) * | 2001-04-23 | 2003-08-26 | The United States Of America As Represented By The Secretary Of The Army | Translating spinner |
| US20060000136A1 (en) * | 2004-07-02 | 2006-01-05 | Li Young | Multi-variable, multi-parameter projectile launching and testing device |
| WO2011038365A1 (en) * | 2009-09-25 | 2011-03-31 | John William Hunter | Gas gun launcher |
| US20130061654A1 (en) * | 2011-09-08 | 2013-03-14 | Airbus Operations Gmbh | Method and a device for the reproduction of an impact event |
| US9567107B2 (en) | 2009-09-25 | 2017-02-14 | Quicklaunch, Inc. | Gas gun launcher |
| CN110081784A (en) * | 2019-06-20 | 2019-08-02 | 永康市正祥五金制品科技有限公司 | A kind of ammunition testing device |
| US10427804B1 (en) | 2016-04-29 | 2019-10-01 | Quicklaunch, Inc. | Orbital mechanics of impulsive launch |
| US11009325B1 (en) | 2018-02-09 | 2021-05-18 | Honeywell Federal Manufacturing & Technologies, Llc | System and method for testing missile components |
| US11267588B2 (en) | 2016-04-29 | 2022-03-08 | Quicklaunch, Inc. | Orbital mechanics of impulsive launch |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2462922A (en) * | 1946-08-30 | 1949-03-01 | Hiram E Temple | Train fusee discharger |
| US3444733A (en) * | 1966-10-07 | 1969-05-20 | Us Army | Artillery simulator |
-
1970
- 1970-02-02 US US7929A patent/US3597969A/en not_active Expired - Lifetime
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2462922A (en) * | 1946-08-30 | 1949-03-01 | Hiram E Temple | Train fusee discharger |
| US3444733A (en) * | 1966-10-07 | 1969-05-20 | Us Army | Artillery simulator |
Cited By (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3693432A (en) * | 1971-06-22 | 1972-09-26 | Us Army | Artillery gun shock simulator |
| US4010631A (en) * | 1975-09-09 | 1977-03-08 | The United States Of America As Represented By The Secretary Of The Army | Method and apparatus for pulse shaping in ballistic simulators |
| US4038869A (en) * | 1976-10-22 | 1977-08-02 | The United States Of America As Represented By The Secretary Of The Army | Simulator for setback followed by drag |
| US4069702A (en) * | 1977-02-04 | 1978-01-24 | Sanders Associates, Inc. | Method and apparatus for testing the run-out and recoil control systems of a gun |
| US4495792A (en) * | 1983-05-02 | 1985-01-29 | Motorola, Inc. | Method for simulating a shock pulse |
| US4599897A (en) * | 1985-03-29 | 1986-07-15 | The United States Of America As Represented By The Secretary Of The Army | Tubular shaped sled test complex |
| US4719797A (en) * | 1985-08-14 | 1988-01-19 | Her Majesty The Queen In Right Of Canada, As Represented By The Minister Of National Defence | Spinning assembly for explosive munitions |
| US5184499A (en) * | 1990-01-31 | 1993-02-09 | Schweizerische Eidgenossenschaft Vertreten Durch Die Eidg. Munitionsfabrik Thun Der Gruppe Fur Rustungsdienste | Testing device with acceleration tube |
| US5388520A (en) * | 1993-10-04 | 1995-02-14 | The United States Of America As Represented By The Scretary Of The Army | Individual mine launcher |
| US5686652A (en) * | 1996-09-09 | 1997-11-11 | Pfund; Bruce | Portable test hammer apparatus |
| US5762057A (en) * | 1996-12-30 | 1998-06-09 | The United States Of America As Represented By The United States Department Of Energy | Light gas gun with reduced timing jitter |
| US6609420B2 (en) * | 2001-04-23 | 2003-08-26 | The United States Of America As Represented By The Secretary Of The Army | Translating spinner |
| US20060000136A1 (en) * | 2004-07-02 | 2006-01-05 | Li Young | Multi-variable, multi-parameter projectile launching and testing device |
| US7182015B2 (en) * | 2004-07-02 | 2007-02-27 | Li Young | Multi-variable, multi-parameter projectile launching and testing device |
| US9567107B2 (en) | 2009-09-25 | 2017-02-14 | Quicklaunch, Inc. | Gas gun launcher |
| WO2011038365A1 (en) * | 2009-09-25 | 2011-03-31 | John William Hunter | Gas gun launcher |
| US9567108B2 (en) | 2009-09-25 | 2017-02-14 | Quicklaunch, Inc. | Gas gun launcher |
| US8536502B2 (en) | 2009-09-25 | 2013-09-17 | Quicklaunch, Inc. | Vehicle for launching from a gas gun |
| US8664576B2 (en) * | 2009-09-25 | 2014-03-04 | Quicklaunch, Inc. | Vehicle for launching from a gas gun |
| US8979033B2 (en) | 2009-09-25 | 2015-03-17 | Quicklaunch, Inc. | Gas gun launcher |
| US9217699B2 (en) * | 2011-09-08 | 2015-12-22 | Airbus Operations Gmbh | Method and a device for the reproduction of an impact event |
| US20130061654A1 (en) * | 2011-09-08 | 2013-03-14 | Airbus Operations Gmbh | Method and a device for the reproduction of an impact event |
| US10427804B1 (en) | 2016-04-29 | 2019-10-01 | Quicklaunch, Inc. | Orbital mechanics of impulsive launch |
| US11267588B2 (en) | 2016-04-29 | 2022-03-08 | Quicklaunch, Inc. | Orbital mechanics of impulsive launch |
| US11009325B1 (en) | 2018-02-09 | 2021-05-18 | Honeywell Federal Manufacturing & Technologies, Llc | System and method for testing missile components |
| CN110081784A (en) * | 2019-06-20 | 2019-08-02 | 永康市正祥五金制品科技有限公司 | A kind of ammunition testing device |
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