IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0856037
(2007-09-15)
|
등록번호 |
US-7739938
(2010-07-12)
|
발명자
/ 주소 |
- Nair, Michael L.
- Condon, John A.
|
출원인 / 주소 |
- The United States of America as represented by the Secretary of the Army
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
4 인용 특허 :
7 |
초록
▼
The launching of an unmanned projectile includes pre-packaging a barrel with a projectile, a pusher cup, and a gas generator. The gas generator generates gas to propel the projectile out of the barrel. A pressure chamber increases a pressure of the gas in the barrel. The pressure chamber comprises a
The launching of an unmanned projectile includes pre-packaging a barrel with a projectile, a pusher cup, and a gas generator. The gas generator generates gas to propel the projectile out of the barrel. A pressure chamber increases a pressure of the gas in the barrel. The pressure chamber comprises a front body portion connected to the gas generator; an aft body portion connected to the front body portion and the gas generator; and a vent sleeve positioned around the front body portion and adapted to provide an aperture through which the gas exits the barrel in order to control a level of gas pressure in the barrel. A triggering of the gas generator causes the pusher cup to push the projectile out of the barrel at a predetermined launch velocity in order to attain a predetermined self-propelled flight trajectory, wherein the triggering causes the pusher cup to exit the barrel.
대표청구항
▼
What is claimed is: 1. A launcher system for an unmanned aerial vehicle (UAV), said launcher system comprising: a barrel adapted to house said UAV; a gas generator operatively connected to said barrel and adapted to generate gas to propel said UAV out of said barrel; a pressure chamber operatively
What is claimed is: 1. A launcher system for an unmanned aerial vehicle (UAV), said launcher system comprising: a barrel adapted to house said UAV; a gas generator operatively connected to said barrel and adapted to generate gas to propel said UAV out of said barrel; a pressure chamber operatively connected to said barrel, wherein said barrel extends out of a first end of said pressure chamber, wherein said pressure chamber is adapted to increase a pressure of said gas in said barrel, and wherein said pressure chamber comprises: a front body portion operatively connected to said barrel; an aft body portion operatively connected to said front body portion and said gas generator; and a vent sleeve positioned around said front body portion and adapted to provide an aperture through which said gas exits said barrel in order to control a level of gas pressure in said barrel; a pusher cup positioned within said barrel and behind said UAV upon which said gas exerts pressure for pushing said UAV out of said barrel; and a launcher mount operatively connected to said aft body portion and adapted to position said barrel at a plurality of angles. 2. The launcher system of claim 1, wherein said gas generator utilizes approximately 24Vdc of external electrical power to initiate functioning of said gas generator. 3. The launcher system of claim 1, wherein said pressure chamber comprises a plurality of interconnected sections adapted to vent propulsion gases created by said gas generator upon launch of said UAV. 4. The launcher system of claim 3, wherein said vent sleeve comprises a gas deflector adapted to redirect the vented propulsion gases forward and away from a user standing behind said barrel. 5. The launcher system of claim 1, wherein said barrel, said UAV, said gas generator, and said pusher cup are expendable after each launch of said UAV. 6. The launcher system of claim 1, wherein said pusher cup has a higher aerodynamic drag and lower inertia than said UAV, and wherein as said UAV and said pusher cup exit said barrel, the higher aerodynamic drag and lower inertia of said pusher cup causes a rapid deceleration and separation of said pusher cup from said projectile, thereby allowing said projectile to continue a ballistic flight path prior to transition to a self-propelled flight. 7. A system for launching an unmanned projectile, said system comprising: a barrel comprising said projectile, a pusher cup positioned behind said projectile, guide rails adapted to prevent said projectile from rotating in said barrel, and a gas generator adapted to generate gas to propel said projectile out of said barrel; a pressure chamber operatively connected to said barrel, wherein said barrel extends out of a first end of said pressure chamber, wherein said pressure chamber is adapted to increase a pressure of said gas in said barrel, and wherein said pressure chamber comprises: a front body portion operatively connected to said barrel; an aft body portion operatively connected to said front body portion and said gas generator; and a vent sleeve positioned around said front body portion and adapted to provide an aperture through which said gas exits said barrel in order to control a level of gas pressure in said barrel; a stand operatively connected to said aft body portion, wherein said stand is rotatable with respect to said barrel, wherein a triggering of said gas generator causes said pusher cup to push said projectile out of said barrel at a predetermined launch velocity in order to attain a predetermined self-propelled flight trajectory, and wherein said triggering causes said pusher cup to exit said barrel. 8. The system of claim 7, wherein said gas generator utilizes approximately 24Vdc of external electrical power to initiate functioning of said gas generator. 9. The system of claim 7, wherein said pressure chamber comprises a plurality of interconnected sections adapted to vent propulsion gases created by said gas generator upon launch of said projectile. 10. The system of claim 9, wherein said vent sleeve comprises a gas deflector adapted to redirect the vented propulsion gases forward and away from a user standing behind said barrel. 11. The system of claim 7, wherein said barrel, said projectile, said gas generator, and said pusher cup are expendable after each launch of said projectile. 12. The system of claim 7, wherein said pusher cup has a higher aerodynamic drag and lower inertia than said projectile, and wherein as said projectile and said pusher cup exit said barrel, the higher aerodynamic drag and lower inertia of said pusher cup causes a rapid deceleration and separation of said pusher cup from said projectile, thereby allowing said projectile to continue a ballistic flight path prior to transition to a self-propelled flight.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.