US3929306A — Space vehicle system

Claim 1

Independent Claim 88 words

A space vehicle system consisting of an orbiter vehicle having an externally mounted propellant tank that is expendably affixed to a side thereof; the improvement comprising: an engine module disposed proximate the aft end of the propellant tank and releasably communicating therewith so as to obviate the need for fuel lines into the orbiter vehicle fuselage, and support and retraction means coupling the engine module to the orbiter vehicle so that the module may, subsequent to expenditure of the empty propellant tank, be retracted into the orbiter vehicle.

Claim 2

Dependent Claim 88 words

A space vehicle system consisting of an orbiter vehicle having an externally mounted propellant tank that is expendably affixed to a side thereof; the improvement comprising: an engine module disposed proximate the aft end of the propellant tank and releasably communicating therewith so as to obviate the need for fuel lines into the orbiter vehicle fuselage, and support and retraction means coupling the engine module to the orbiter vehicle so that the module may, subsequent to expenditure of the empty propellant tank, be retracted into the orbiter vehicle.

Claim 3

Dependent Claim 80 words

The space vehicle system of claim 1 wherein the propellant tank includes axially aligned discrete forward and aft compartments containing first and second fuel components of differing weight, the heavier of said components being disposed in the aft compartment adjacent to said engine module in order that the structural design of the expendable tank may be reduced due to the transmission of engine thrust forces directly to the area of principal mass, thereby providing for design having lighter structural weight.

Claim 4

Dependent Claim 63 words

The space vehicle system of claim 1 wherein said engine module is mounted for angularly adjustable movement during the operation thereof so as to direct the thrust vector through the center of gravity of the system, said propellant tank being disposed in substantial axial alignment with said engine module so that the angular movement of the module may be minimized during launch procedure.

Claim 5

Dependent Claim 59 words

The space vehicle system of claim 2 wherein said engine module is movably mounted during operation so as to variably direct its thrust vector through the changing center of gravity of the system, said propellant tank being disposed in substantial axial alignment with said engine module so that angular movement of the module may be minimized during launch procedure.

Claim 6

Dependent Claim 36 words

The space vehicle system of claim 1 wherein said support and retraction means for the engine module are adapted to move the module upwardly and inwardly through an opening in the aft end of the orbiter.

Claim 7

Dependent Claim 35 words

The space vehicle system of claim 1 wherein said retraction means for the engine module is adapted to move the module upwardly and into the orbiter fuselage through an opening in the upper side thereof.

Claim 8

Dependent Claim 49 words

The space vehicle system of claim 1 wherein said support and retraction means comprises a plurality of articulated link means pivotally connected to one another and adapted to move said engine module through a predetermined path of sequential positions from its operative to its stowed position in the orbiter.

Claim 9

Dependent Claim 33 words

The space vehicle system of claim 7 wherein said articulated link means are adapted to move the engine module upwardly and inwardly through an opening in the aft end of the orbiter fuselage.

Claim 10

Dependent Claim 28 words

The space vehicle System of claim 8 wherein the engine module has a thrust axis and the angle thereof is maintained substantially constant throughout the path of movement.

Claim 11

Dependent Claim 33 words

The space vehicle system of claim 7 wherein said articulated link means are adapted to move the engine module upwardly and inwardly through an opening in the upper side of the orbiter fuselage.

Claim 12

Dependent Claim 28 words

The space vehicle system of claim 10 wherein the engine module has a thrust axis and the angle thereof is maintained substantially constant throughout the path of movement.

Claim 13

Independent Claim 112 words

A method for increasing the payload area of a space vehicle system while simultaneously reducing the system weight and increasing the range and maneuverability for landing subsequent to re-entry, comprising the steps of; providing a payload vehicle having its engine module disposed exteriorly of the fuselage, the fuselage being characterized by an aft opening therein, releasably affixing to the exterior of the fuselage, in operative relation to the engine module, a propellant tank having fuel therein, launching the vehicle system by actuating the engine module until the fuel in the tank is consumed, retracting the propulsion engine module into the opening in the fuselage and, expending the propellant tank from the vehicle.

Claim 14

Independent Claim 112 words

A method for increasing the payload area of a space vehicle system while simultaneously reducing the system weight and increasing the range and maneuverability for landing subsequent to re-entry, comprising the steps of; providing a payload vehicle having its engine module disposed exteriorly of the fuselage, the fuselage being characterized by an aft opening therein, releasably affixing to the exterior of the fuselage, in operative relation to the engine module, a propellant tank having fuel therein, launching the vehicle system by actuating the engine module until the fuel in the tank is consumed, retracting the propulsion engine module into the opening in the fuselage and, expending the propellant tank from the vehicle.

Claim 15

Independent Claim 146 words

The method of launching a space vehicle system essentially comprising a space vehicle carrying an external engine module at the aft end of the fuselage thereof and an expendable propellant tank also externally mounted to the fuselage in operative communicating relation to the engine module so as to reduce the weight of the vehicle by jettisoning the tank when the propellant is exhausted, comprising the steps of: igniting said engine module so as to propel the system along a predetermined path of flight, utilizing substantially all of the fuel in said tank prior to the expenditure thereof from the space vehicle, terminating operation of the engine module, retracting the engine module away from the propellant tank and into more proximate relation to the fuselage, and separating and expending the tank from the space vehicle so as to thereby reduce the dry weight and also improve navigability.

Claim 16

Independent Claim 146 words

The method of launching a space vehicle system essentially comprising a space vehicle carrying an external engine module at the aft end of the fuselage thereof and an expendable propellant tank also externally mounted to the fuselage in operative communicating relation to the engine module so as to reduce the weight of the vehicle by jettisoning the tank when the propellant is exhausted, comprising the steps of: igniting said engine module so as to propel the system along a predetermined path of flight, utilizing substantially all of the fuel in said tank prior to the expenditure thereof from the space vehicle, terminating operation of the engine module, retracting the engine module away from the propellant tank and into more proximate relation to the fuselage, and separating and expending the tank from the space vehicle so as to thereby reduce the dry weight and also improve navigability.

Claim 17

Dependent Claim 80 words

The space vehicle system of claim 13 wherein the propellant tank is characterized by compartmentalized forward and aft sections extending along the longitudinal axis thereof for containing each a relatively light and a relatively heavy propellant component, and including the additional step of: disposing the heavier of the fuel components in the aft section of the tank so that the engine module transmits thrust forces directly to the structure enclosing the greater weight, thereby enabling reduced structural weight in tank.

Claim 18

Dependent Claim 54 words

The space vehicle system of claim 14 including the additional step of improving system reliability by disposing the retractable engine module in axial alignment with the lontitudinal axis of the propellant tank, thereby minimizing pivoting movement of the module during the firing period thereof and eliminating fuel line interfaces in the space vehicle fuselage.

Claim 19

Dependent Claim 32 words

The space vehicle system of claim 15 wherein the step of retracting the engine module is characterized by the movement thereof into the fuselage through an opening in the aft end thereof.

Claim 20

Dependent Claim 50 words

The space vehicle system of claim 15 wherein the fuel propellant tank is disposed adjacent the under side of the vehicle and the step of retracting the engine module is characterized by the movement thereof into the fuselage through an opening in the upper ventral side of the fuselage thereof.

Claim 21

Dependent Claim 38 words

The space vehicle system of claim 13 including the further step of retracting the module into the vehicle and adjusting its position thereafter in order to optimize the center of gravity of the vehicle for desirable flight characteristics.

Annuity Stage	Window Opens	Payment Deadline	Surcharge Period Until	Estimated Fee	Status
3.5 Years (Year 4)	1978-12-29	1979-06-30	1979-12-30	$2000.00	Window Closed / Lapsed
7.5 Years (Year 8)	1982-12-29	1983-06-30	1983-12-30	$3760.00	Window Closed / Lapsed
11.5 Years (Year 12)	1986-12-29	1987-06-30	1987-12-30	$7700.00	Window Closed / Lapsed

Space vehicle system

Abstract

Inventors

Bibliographic Details

Claims Analysis

References Cited (Backward Citations)

USPTO Annuity & Maintenance Windows

Assigned Categories & Tags

Assign Category Tag