US4943014A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Soft ride method for changing the altitude or position of a spacecraft in orbit
Assignee: Northrop Grumman Space and Mission Systems Corp
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Filing: 1989-04-14
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Granted: 1990-07-24
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Expires: 2009-04-14
Abstract
Abstract A spacecraft, and related method for its operation, for transporting a payload, such as a satellite, from a space shuttle in a low-altitude parking orbit, to an operational orbit. Housekeeping functions, such as communications, attitude control, and power-supply, are performed by subsystems integrated into the spacecraft and employed both while in the operational orbit and during ascent from the parking orbit. The payload is secured forward of a payload platform having forward and aft faces of isogrid construction, and the housekeeping subsystems are stored between the faces, an interface of electrical and other connections being provided to the payload through the forward platform face. A liquid bipropellant rocket engine secured behind the payload platform provides low thrust and relatively low acceleration, and is operated in a succession of short perigee burns to extend the orbit to a desired altitude, and then in one or more apogee burns to circularize the orbit, if the payload is a satellite. Tanks of fuel and oxidizer are also secured behind the payload platform, disposed about the engine in balanced pairs, each oxidizer tank being paired with a fuel tank located further from the center of mass than the heavier oxidizer tank, to preserve balance as the pair of tanks is depleted. Propellants are fed to the engine from one tank pair at a time, each pair, or stage, being jettisoned when its contents are consumed.
Inventors
- 👤 Oliver P. Harwood
- 👤 John A. Love
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 21:23
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/22; B64G1/40; B64G1/401; B64G1/24; B64G1/242; B64G1/2427; B64G1/002; B64G1/006; B64G1/14; B64G1/402; B64G1/4022; B64G1/64; B64G1/641; B64G1/645
Claims Analysis
Total Claims: 16
Claim 1
Independent Claim
126 words
A method of transporting a payload on a spacecraft from a low-altitude parking orbit around a planetary body to a higher-altitude operational orbit, said method comprising the steps of: actuating a low-thrust liquid bipropellant rocket engine for a relatively short period at a preselected point in the parking orbit, and thereby increasing the velocity of the spacecraft at the preselected point in the orbit; and actuating the rocket engine for a succession of burns each time the preselected point in the orbit is reached, the preselected point becoming the perigee of an elliptical orbit of which the apogee moves further from the earth after each successive burn; whereby the operational orbit is reached by a succession of relatively short burns producing relatively low levels of accelaration.
Claim 2
Independent Claim
126 words
A method of transporting a payload on a spacecraft from a low-altitude parking orbit around a planetary body to a higher-altitude operational orbit, said method comprising the steps of: actuating a low-thrust liquid bipropellant rocket engine for a relatively short period at a preselected point in the parking orbit, and thereby increasing the velocity of the spacecraft at the preselected point in the orbit; and actuating the rocket engine for a succession of burns each time the preselected point in the orbit is reached, the preselected point becoming the perigee of an elliptical orbit of which the apogee moves further from the earth after each successive burn; whereby the operational orbit is reached by a succession of relatively short burns producing relatively low levels of accelaration.
Claim 3
Dependent Claim
32 words
A method as set forth in claim 1, and further including the step of actuating the rocket engine for an additional burn at apogee, to circularize the orbit at a desired altitude.
Claim 4
Dependent Claim
59 words
A method as set forth in claim 1, and further including the steps of: consuming fuel and oxidizer liquids during the rocket engine burns from a balanced pair of tanks; jettisoning the balanced pair of tanks as the pair is emptied; and then switching fuel and oxidizer supply lines to draw propellants from a next balanced pair of tanks.
Claim 5
Dependent Claim
29 words
A method as set forth in claim 3, wherein said jettisoning step includes temporarily closing off a propellant feed system to prevent loss of propellent while jettisoning the tanks.
Claim 6
Independent Claim
140 words
A method of transporting a payload on a spacecraft from an operational orbit to a low-altitude parking orbit around a planetary body, said method comprising the steps of: actuating a low-thrust liquid bipropellant rocket engine for at least one burn at a preselected point in the operational orbit, to decrease the velocity of the spacecraft at that point in the orbit and place the spacecraft in an eliptical orbit about the planetary body such that the preselected point is the apogee of the eliptical orbit; and actuating the rocket engine for a succession of burns occuring at the perigee in the eliptical orbit, and thereby decreasing the velocity of the spacecraft at perigee until the orbit is circular at perigee altitude; whereby the parking orbit is reached by a succession of relatively short burns producing relatively low levels of acceleration.
Claim 7
Independent Claim
140 words
A method of transporting a payload on a spacecraft from an operational orbit to a low-altitude parking orbit around a planetary body, said method comprising the steps of: actuating a low-thrust liquid bipropellant rocket engine for at least one burn at a preselected point in the operational orbit, to decrease the velocity of the spacecraft at that point in the orbit and place the spacecraft in an eliptical orbit about the planetary body such that the preselected point is the apogee of the eliptical orbit; and actuating the rocket engine for a succession of burns occuring at the perigee in the eliptical orbit, and thereby decreasing the velocity of the spacecraft at perigee until the orbit is circular at perigee altitude; whereby the parking orbit is reached by a succession of relatively short burns producing relatively low levels of acceleration.
Claim 8
Independent Claim
133 words
A method of transporting a payload on a spacecraft from a low-altitude circular parking orbit to a higher-altitude operational orbit, said method comprising the steps of: accelerating the spacecraft to a higher velocity at a preselected point in the parking orbit, thereby moving the spacecraft into an elliptical orbit having a perigee at the preselected point and an apogee higher than the original parking orbit; accelerating the spacecraft to a slightly higher velocity each time the perigee is reached, thereby extending the apogee to a higher and higher altitude; and then accelerating the spacecraft once more at a time when apogee is reached, to circularize the orbit at a desired altitude, whereby only relatively small accelerations may be used, and components of the payload may be deployed before departure from the parking orbit.
Claim 9
Independent Claim
133 words
A method of transporting a payload on a spacecraft from a low-altitude circular parking orbit to a higher-altitude operational orbit, said method comprising the steps of: accelerating the spacecraft to a higher velocity at a preselected point in the parking orbit, thereby moving the spacecraft into an elliptical orbit having a perigee at the preselected point and an apogee higher than the original parking orbit; accelerating the spacecraft to a slightly higher velocity each time the perigee is reached, thereby extending the apogee to a higher and higher altitude; and then accelerating the spacecraft once more at a time when apogee is reached, to circularize the orbit at a desired altitude, whereby only relatively small accelerations may be used, and components of the payload may be deployed before departure from the parking orbit.
Claim 10
Dependent Claim
67 words
A method as set forth in claim 6, wherein: said accelerating steps include burning a low-thrust liquid bipropellant rocket engine and consuming fuel and oxidizer liquids from a balanced pair of fuel and oxidizer tanks; and said method further includes the steps of jettisoning the pair of tanks as it is emptied, and switching fuel and oxidizer supply to draw propellants from another balanced pair of tanks.
Claim 11
Dependent Claim
52 words
A soft ride method for changing the position of an orbiting satellite comprising the steps of: selecting an orbital location for commencing a soft ride change in orbital position; providing a relatively low acceleration thrust; altering the velocity of said satellite; and repeating said thrust until a desired orbital position is achieved.
Claim 12
Dependent Claim
52 words
A soft ride method for changing the position of an orbiting satellite comprising the steps of: selecting an orbital location for commencing a soft ride change in orbital position; providing a relatively low acceleration thrust; altering the velocity of said satellite; and repeating said thrust until a desired orbital position is achieved.
Claim 13
Dependent Claim
46 words
A soft ride method for changing the altitude of a satellite in space comprising the steps of: (a) utilizing a relatively low acceleration thrust in order to alter the rotation or translation of said satellite; and (b) repeating said thrust until a desired altitude is achieved.
Claim 14
Dependent Claim
46 words
A soft ride method for changing the altitude of a satellite in space comprising the steps of: (a) utilizing a relatively low acceleration thrust in order to alter the rotation or translation of said satellite; and (b) repeating said thrust until a desired altitude is achieved.
Claim 15
Dependent Claim
131 words
A spacecraft for transporting a payload from a low-altitude parking orbit around a planetary body to a higher-altitude operational orbit, the spacecraft comprising: (a) means for attaching the payload to the spacecraft; (b) a low-thrust liquid bipropellant rocket engine; and (c) control means for (i) actuating the engine for a relatively short period at a preselected point in the parking orbit, and thereby increasing the velocity of the spacecraft at the preselected point in orbit, and for (ii) actuating the rocket engine for a succession of relatively short burns each time the preselected point in orbit is reached, the preselected point becoming the perigee of an elliptical orbit at which the apogee moves further from the earth after each successive orbit, the relatively short burns producing relatively low levels of acceleration.
Claim 16
Dependent Claim
131 words
A spacecraft for transporting a payload from a low-altitude parking orbit around a planetary body to a higher-altitude operational orbit, the spacecraft comprising: (a) means for attaching the payload to the spacecraft; (b) a low-thrust liquid bipropellant rocket engine; and (c) control means for (i) actuating the engine for a relatively short period at a preselected point in the parking orbit, and thereby increasing the velocity of the spacecraft at the preselected point in orbit, and for (ii) actuating the rocket engine for a succession of relatively short burns each time the preselected point in orbit is reached, the preselected point becoming the perigee of an elliptical orbit at which the apogee moves further from the earth after each successive orbit, the relatively short burns producing relatively low levels of acceleration.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1993-07-23 | 1994-01-22 | 1994-07-24 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1997-07-23 | 1998-01-22 | 1998-07-24 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2001-07-23 | 2002-01-22 | 2002-07-24 | $7700.00 | Window Closed / Lapsed |