US3599899A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Rocket control
Assignee: ATK Launch Systems LLC
•
Filing: 1969-06-20
•
Granted: 1971-08-17
•
Expires: 1989-06-20
Abstract
Abstract A special upper stage for a plural-stage rocket includes apparatus for steering the entire rocket or any part thereof, and for igniting an extinguishable rocket motor as needed. It includes a gas generator from which gases may be proportionately metered to steering nozzles and/or to an ignition duct by valves responsive to movements of a central cam body, such that pressure within the gas generator always remains constant.
Inventors
- 👤 Edward E Mccullough
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 05:05
CPC Classifications
F; F42; F42B; F42B10/00; F42B10/60; F42B10/66; F42B10/663
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
170 words
An upper stage for a rocket, comprising: a rocket motor; a gas generator having a pressure vessel, a propellant source communicating therewith, and ignition means in the pressure vessel for igniting propellant; radially oriented steering nozzles extending from the pressure vessel for discharging gases therefrom; a duct connecting the interior of the pressure vessel with that of the rocket motor; a cam body having incline surfaces and positioned intermediately of the steering nozzles; an axial actuator mounted on the upper stage and pivotally connected to the cam body for moving it axially; lateral actuation means mounted on the upper stage and in contact with the cam body for moving it laterally; guide means for preventing axial rotation of the cam body; valve means in the steering nozzles; cam followers contacting the incline surfaces of the cam body and attached to the valve means in the steering nozzles for operation thereof in response to movements of the cam body; and a valve in the duct operatively connected to the axial actuator.
Claim 2
Dependent Claim
170 words
An upper stage for a rocket, comprising: a rocket motor; a gas generator having a pressure vessel, a propellant source communicating therewith, and ignition means in the pressure vessel for igniting propellant; radially oriented steering nozzles extending from the pressure vessel for discharging gases therefrom; a duct connecting the interior of the pressure vessel with that of the rocket motor; a cam body having incline surfaces and positioned intermediately of the steering nozzles; an axial actuator mounted on the upper stage and pivotally connected to the cam body for moving it axially; lateral actuation means mounted on the upper stage and in contact with the cam body for moving it laterally; guide means for preventing axial rotation of the cam body; valve means in the steering nozzles; cam followers contacting the incline surfaces of the cam body and attached to the valve means in the steering nozzles for operation thereof in response to movements of the cam body; and a valve in the duct operatively connected to the axial actuator.
Claim 3
Dependent Claim
46 words
The upper stage of clAim 1 wherein the cam body has a spherical surface opposite the incline surfaces and the valve in the duct is operatively connected to the axial actuator by a cam follower attached to the valve and in contact with the spherical surface.
Claim 4
Dependent Claim
96 words
The upper stage of claim 1 wherein axial motion of the cam body opens the valve in the duct as it closes the valve means in the steering nozzles, and vice versa, so that the total orifice area of the nozzles is always inversely proportional to that through which the duct discharges into the rocket motor, and so that the total orifice area through which gases may be exhausted from the pressure vessel always remains constant, whereby pressure of the gases in the pressure vessel may always be constant when the gas generator is in operation.
Claim 5
Dependent Claim
71 words
The upper stage of claim 1 wherein the source of propellant is a composite solid propellant grain in the pressure vessel, comprising: a fast-burning aft grain; a slow-burning forward grain; a combustion barrier of combustion-inhibiting material interposed between the aft and forward grains so that the forward grain cannot be ignited by combustion of the aft grain; and ignition means forward of the barrier for igniting the forward grain when desired.
Claim 6
Dependent Claim
24 words
The upper stage of claim 1 wherein the steering nozzles also extend rearwardly and are inclined about 45* to the axis of the rocket.
Claim 7
Dependent Claim
37 words
The upper stage of claim 1 wherein the steering nozzles are movable, and further including actuators joining the movable portions of the nozzles with stationary portions of the rocket for directing gases discharged from the gas generator.
Claim 8
Dependent Claim
36 words
The upper stage of claim 1 wherein the guide means comprises a gimbal connecting the cam body to the axial actuator and a tongue-in-groove slide connecting the gimbal to the upper stage for axial sliding motion.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1974-08-16 | 1975-02-15 | 1975-08-17 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-08-16 | 1979-02-15 | 1979-08-17 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-08-16 | 1983-02-15 | 1983-08-17 | $7700.00 | Window Closed / Lapsed |