 Signal processing system |
| OF INVENTION The radar system of FIG. 1, which includes the balanced signal processor, can be used ... |
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| Radar channel including an orthogonal MTI filter pair |
| A radar operates in a moving target indication (MTI) mode with frequency diversity by transmitting N... |
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| Operator station for telephone exchange |
| The object of the present invention is to provide an operator station for telephone exchanges, ... |
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| Arrangement for processing a delta modulation signal, in particular for decoding these signals |
| What is claimed is: 1. A processing device for decoding a digital signal formed from binary ... |
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| Sound masking system for open plan office |
| What is claimed is: 1. An acoustic masking system for obtaining conversational privacy in an open ... |
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| Video signal processing apparatus for separating an image of a moving object from video signals |
| OF THE INVENTION Referring now to FIGS. 1 through 3, a preferred embodiment will be explained. A ... |
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| Dynamic image transmission system |
| Accordingly, it is a general object of the present invention to provide a novel and useful dynamic ... |
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| Telephone anti-theft device |
| OF A PREFERRED EMBODIMENT Referring initially to FIG. 1, pay telephone 10 is of conventional ... |
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| Modular multiplex/demultiplex apparatus |
| OF THE INVENTION Referring now to FIG. 1, there is shown a telephone communication system 1 ... |
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| Entrance communication system |
| It is a primary object of the present invention to provide a solution to the above disadvantages by ... |
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Modular solid-propellant launch vehicle and related launch facility
| Details |
Inventors: Thole, John M.; Kelly, Michael S.;
Assignee: TRW Inc. (Redondo Beach, CA)
Primary Examiner: Peters, Jr.; Joseph F.
Assistant Examiner: Bidwell; Anne E.
Attorney, Agent or Firm: Steinberger; James M., Goldstein; Sol L.
A family of modular solid-propellant launch vehicles and a related launch facility for placing a wide range of payloads in earth orbit at greatly reduced costs compared to present day launch systems. The basic family of modular solid-propellant launch vehicles is constructed from only two sizes of modular solid-propellant rocket motors, a large rocket motor and a small rocket motor. The modular rocket motors are clustered and stacked in various configurations to form the family of launch vehicles. The physical and performance characteristics of the two solid-propellant rocket motors, including weight, vacuum specific impulse and action time, were tailored to maximize the payload capabilities of each member of the launch vehicle family without exceeding predetermined maximum and staging dynamic pressure limits and maximum acceleration limits. The universal launch facility utilizes a steel canister that is sized to hold the maximum diameter and length launch vehicle. The steel canister is secured in a concrete-lined launch pit and the vehicle is expelled from the canister by a piston. The piston is caught by an arrestor device upon reaching the end of the canister. An assembly platform at the top of the piston provides a platform for assembling the launch vehicle. |
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DETAILED DESCRIPTION The present invention resides in a family of modular solid-propellant launch vehicles and a related launch facility for placing a wide range of payloads in earth orbit at greatly reduced costs compared to present day launch systems.
The basic family of modular solid-propellant launch vehicles is constructed from only two sizes of modular solid-propellant rocket motors, a large rocket motor and a small rocket motor.
The modular rocket motors are clustered and stacked in various configurations to form the family of launch vehicles.
The physical and performance characteristics of the two solid-propellant rocket motors, including weight, vacuum specific impulse and action time, were tailored to maximize the payload capabilities of each member of the launch vehicle family without exceeding predetermined maximum and staging dynamic pressure limits and maximum acceleration limits.
These predetermined limits included an axial acceleration limit of 6.
0 g's, a maximum dynamic pressure limit of 3500 psf and a dynamic pressure limit at stage separation of 600 psf.
The maximum dynamic pressure limit determines the maximum structural loads imposed on the launch vehicle during flight and the staging dynamic pressure limit determines controllability at stage separation.
Low earth orbit trajectory simulations were flown for all members of the launch vehicle family to tailor the physical and performance characteristics of the two rocket motors to maximize payload capabilities without exceeding the predetermined limits.
A low earth orbit was selected since this represented the worst case maximum dynamic pressure.
The results indicated that the large solid-propellant rocket motor should have a diameter of approximately 83 to 120 inches, a weight of approximately 110,000 to 125,000 pounds, a vacuum specific impulse of approximately 260 to 290 seconds, and an action time of approximately 58 to 90 seconds.
The small rocket motor should have the same diameter as the large rocket motor, a weight of approximately 17,000 to 50,000 pounds, a vacuum specific impulse of approximately 270 to 305 seconds, and an action time of approximately 60 to 130 seconds
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