Patent FR1045320A successfully refreshed from Google Patents.
Patent US4964340A successfully refreshed from Google Patents.
US4964340A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Overlapping stage burn for multistage launch vehicles
Assignee: SPACE SERVICES Inc A CORP OF
•
Filing: 1988-10-07
•
Granted: 1990-10-23
•
Expires: 2008-10-07
Abstract
Abstract The invention relates to a multistage launch vehicle and method of multistage launch vehicle operation in which at least one subsequent motor stage is ignited following lift-off in partially overlapping relationship with its immediately preceding motor stage prior to shut-down and staging of the preceding motor stage in order to effect positive thrust control over the launch vehicle throughout shut-down and staging of the preceding motor stage. Preferably, each of the motors comprising the subsequently fired motor stage is provided with a thrust profile in which maximum thrust is attained prior to staging of the preceding stage.
Inventors
- 👤 Mark H. Daniels
- 👤 Jack Funk
- 👤 Wyendell B. Evans
- 👤 Christopher C. Varner
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-09 03:45
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/22; B64G1/40; B64G1/403; B64G1/002; B64G1/008; B64G1/24; B64G1/244; B64G1/242
Claims Analysis
Total Claims: 65
Claim 1
Independent Claim
70 words
A launch vehicle comprising first and second sequentially ignitible rocket motor stages, wherein each of said rocket motors stages is comprised of at least one solid rocket motor and means is provided for igniting the second stage rocket motor subsequent to vehicle lift-off while the launch vehicle is within the earth's atmosphere in partially overlapping relationship with the first stage rocket motor prior to termination of first stage motor operation.
Claim 2
Dependent Claim
70 words
A launch vehicle comprising first and second sequentially ignitible rocket motor stages, wherein each of said rocket motors stages is comprised of at least one solid rocket motor and means is provided for igniting the second stage rocket motor subsequent to vehicle lift-off while the launch vehicle is within the earth's atmosphere in partially overlapping relationship with the first stage rocket motor prior to termination of first stage motor operation.
Claim 3
Dependent Claim
21 words
The launch vehicle of claim 1, wherein the first and second rocket motor stages are mounted generally parallel to one another.
Claim 4
Dependent Claim
25 words
The launch vehicle of claim 2, wherein the first stage comprises at least two diametrically opposed pairs of rocket motors having substantially similar thrust profiles.
Claim 5
Dependent Claim
27 words
The launch vehicle of claim 3, wherein at least one pair of said first stage rocket motor pairs comprises means for controlling launch vehicle yaw and pitch.
Claim 6
Dependent Claim
22 words
The launch vehicle of claim 4, wherein said means for controlling launch vehicle yaw and pitch comprises a thrust vector control system.
Claim 7
Dependent Claim
15 words
The launch vehicle of claim 3, wherein the first stage rocket motors are selectively jettisonable.
Claim 8
Dependent Claim
18 words
The launch vehicle of claim 3, wherein the first stage rocket motors are all solid fuel rocket motors.
Claim 9
Dependent Claim
26 words
The launch vehicle of claim 1, wherein the second stage rocket motor is ignited within about 5 seconds of termination of first stage rocket motor operation.
Claim 10
Dependent Claim
21 words
The launch vehicle of claim 1, further comprising means for effecting positive thrust control between ignition of successive rocket motor stages.
Claim 11
Dependent Claim
23 words
The launch vehicle of claim 1, wherein the rocket motors of the first and second rocket motor stages have substantially similar thrust profiles.
Claim 12
Dependent Claim
24 words
The launch vehicle of claim 10, wherein the rocket motors of the first and second rocket motor stages are Castor IVA solid rocket motors.
Claim 13
Dependent Claim
32 words
The launch vehicle of claim 10, wherein each of the rocket motor thrust profiles exhibits a generally linear rate of thrust diminution following attainment of maximum thrust until termination of motor operation.
Claim 14
Dependent Claim
19 words
The launch vehicle of claim 12, wherein maximum thrust is developed within about five seconds of rocket motor ignition.
Claim 15
Dependent Claim
20 words
The launch vehicle of claim 1, wherein the launch vehicle includes means for deploying a payload beyond the earth's atmosphere.
Claim 16
Dependent Claim
14 words
The launch vehicle of claim 14, wherein the payload comprises at least one satellite.
Claim 17
Dependent Claim
36 words
The launch vehicle of claim 14, wherein the payload deploying means effects deployment of the payload into orbit around the earth of from about 100 nautical miles to about 19,365 nautical miles above the earth's surface.
Claim 18
Dependent Claim
22 words
The launch vehicle of claim 14, wherein the payload deploying means effects deployment of the payload along a trajectory beyond geosynchronous orbit.
Claim 19
Dependent Claim
24 words
The launch vehicle of claim 14, wherein the payload has a weight at sea level of from about 150 lbs. to about 3,500 lbs.
Claim 20
Dependent Claim
74 words
A launch vehicle comprising three parallel rocket motor stages and means for sequentially igniting in partially overlapping relationship the second rocket motor stage with the first rocket motor stage while the launch vehicle is within the earth's atmosphere and the third rocket motor stage with the second rocket motor stage, said first rocket motor stage comprising at least two pair of diametrically opposed pairs of rocket motors positioned around the third stage rocket motor.
Claim 21
Dependent Claim
74 words
A launch vehicle comprising three parallel rocket motor stages and means for sequentially igniting in partially overlapping relationship the second rocket motor stage with the first rocket motor stage while the launch vehicle is within the earth's atmosphere and the third rocket motor stage with the second rocket motor stage, said first rocket motor stage comprising at least two pair of diametrically opposed pairs of rocket motors positioned around the third stage rocket motor.
Claim 22
Dependent Claim
22 words
The launch vehicle of claim 19, wherein the first stage rocket motors comprise solid fuel rocket motors having substantially similar thrust profiles.
Claim 23
Dependent Claim
21 words
The launch vehicle of claim 19, wherein at least one pair of said first stage rocket motors comprises thrust vector control.
Claim 24
Dependent Claim
32 words
The launch vehicle of claim 21, wherein said second rocket motor stage comprises at least one pair of solid rocket motors having substantially similar thrust profiles and further including thrust vector control.
Claim 25
Dependent Claim
26 words
The launch vehicle of claim 22, wherein all of said first and second stage rocket motors are solid fuel rocket motors having substantially similar thrust profiles.
Claim 26
Dependent Claim
24 words
The launch vehicle of claim 19, wherein all of the rocket motors comprising the first, second and third stages have substantially similar thrust profiles.
Claim 27
Dependent Claim
20 words
The launch vehicle of claim 24, wherein each of the rocket motors develops a peak thrust of about 130,000 lbs.
Claim 28
Dependent Claim
23 words
The launch vehicle of claim 25, wherein each of the rocket motors develops its peak thrust within about 5 seconds following motor ignition.
Claim 29
Dependent Claim
45 words
The launch vehicle of claim 19, wherein said means for sequentially igniting said rocket motor stages is configured to effect ignition of said third rocket motor stage in overlapping relationship with said second rocket motor stage while the launch vehicle is within the earth's atmosphere.
Claim 30
Dependent Claim
25 words
The launch vehicle of claim 19, further comprising a payload having a weight at sea level of from about 150 lbs. to about 3,500 lbs.
Claim 31
Dependent Claim
34 words
The launch vehicle of claim 28, further comprising means for deploying said payload into an earth orbit of from about 100 nautical miles to about 19,365 nautical miles above the surface of the earth.
Claim 32
Dependent Claim
17 words
The launch vehicle of claim 29, wherein said payload deploying means comprises a liquid fuel rocket motor.
Claim 33
Dependent Claim
19 words
The launch vehicle of claim 28, further comprising means for deploying said payload along a trajectory beyond geosynchronous orbit.
Claim 34
Dependent Claim
62 words
A launch vehicle, comprising: first and second sequentially ignitible, parallel-configured rocket motor stages, each of said rocket motor stages being comprised of at least one solid fuel rocket motor; and means for igniting said second rocket motor stage in partially overlapping relationship with operation of said first rocket motor stage following vehicle lift-off and prior to termination of first stage motor operation.
Claim 35
Dependent Claim
62 words
A launch vehicle, comprising: first and second sequentially ignitible, parallel-configured rocket motor stages, each of said rocket motor stages being comprised of at least one solid fuel rocket motor; and means for igniting said second rocket motor stage in partially overlapping relationship with operation of said first rocket motor stage following vehicle lift-off and prior to termination of first stage motor operation.
Claim 36
Dependent Claim
22 words
The launch vehicle of claim 32, wherein the rocket motors comprising the first and second rocket stages have substantially similar thrust profiles.
Claim 37
Dependent Claim
35 words
The launch vehicle of claim 32, wherein said first stage is comprised of two pairs of diametrically-opposed rocket motors, at least one of said motor pairs having means for controlling launch vehicle yaw and pitch.
Claim 38
Dependent Claim
34 words
The launch vehicle of claim 34, wherein said second stage is comprised of at least one pair of rocket motors, each of which is provided with means for controlling launch vehicle yaw and pitch.
Claim 39
Dependent Claim
43 words
The launch vehicle of claim 32, further comprising a third rocket motor stage mounted in parallel to said first and second rocket motor stages, said third rocket motor stage being ignitible so as to partially overlap operation of said second rocket motor stage.
Claim 40
Dependent Claim
40 words
The launch vehicle of claim 36, wherein said third rocket motor stage comprises a solid fuel rocket motor having a thrust profile substantially similar to the thrust profiles of the rocket motors comprising the first and second rocket motor stages.
Claim 41
Dependent Claim
28 words
The launch vehicle of claim 37, wherein the first and second rocket motor stages are arranged in a generally ring-shaped configuration that circumscribes said third rocket motor stage.
Claim 42
Dependent Claim
17 words
The launch vehicle of claim 32, further comprising means for deploying a payload beyond the earth's atmosphere.
Claim 43
Dependent Claim
39 words
The launch vehicle of claim 39, wherein the payload deploying means is adapted to deploy the payload into orbit around the earth of from about 100 nautical miles to about 19,365 nautical miles above the surface of the earth.
Claim 44
Dependent Claim
22 words
The launch vehicle of claim 39, wherein the payload deploying means effects deployment of the payload along a trajectory beyond geosynchronous orbit.
Claim 45
Dependent Claim
24 words
The launch vehicle of claim 39, wherein the payload has a weight at sea level of from about 150 lbs to about 3,500 lbs.
Claim 46
Independent Claim
103 words
A method of operating a launch vehicle having at least first and second rocket motor stages, each stage comprising at least one solid fuel rocket motor, the method comprising the steps of: igniting the rocket motors comprising the first stage and operating the rocket motors continuously until burn-out; prior to first stage motor burn-out, igniting the motors comprising the second stage in overlapping relationship with the first stage motors so as to maintain positive thrust control over the launch vehicle as the first stage rocket motors burn-out; and exerting directional control over the launch vehicle during burn-out of the first stage rocket motors.
Claim 47
Independent Claim
103 words
A method of operating a launch vehicle having at least first and second rocket motor stages, each stage comprising at least one solid fuel rocket motor, the method comprising the steps of: igniting the rocket motors comprising the first stage and operating the rocket motors continuously until burn-out; prior to first stage motor burn-out, igniting the motors comprising the second stage in overlapping relationship with the first stage motors so as to maintain positive thrust control over the launch vehicle as the first stage rocket motors burn-out; and exerting directional control over the launch vehicle during burn-out of the first stage rocket motors.
Claim 48
Dependent Claim
28 words
The method of operating a launch vehicle according to claim 43, further comprising the step of jettisoning the first stage following burn-out of the first stage rocket motors.
Claim 49
Dependent Claim
38 words
The method of operating a launch vehicle according to claim 43, wherein the rocket motors comprising the second stage are ignited from about 3 seconds to about 5 seconds prior to burn-out of the first stage rocket motors.
Claim 50
Dependent Claim
31 words
The method of operating a launch vehicle according to claim 43, wherein the first stage rocket motors are operated to develop maximum motor thrust within about five seconds following motor ignition.
Claim 51
Dependent Claim
31 words
The method of operating a launch vehicle according to claim 46, wherein the second stage rocket motors are operated to develop maximum motor thrust within about five seconds following motor ignition.
Claim 52
Dependent Claim
37 words
The method of operating a launch vehicle according to claim 47, wherein the rocket motors of the first and second stages are operated at a generally linearly diminishing thrust rate following attainment of maximum thrust until burn-out.
Claim 53
Dependent Claim
49 words
The method of operating a launch vehicle according to claim 43, wherein the second stage comprises at least two rocket motors operable to provide substantially similar thrust profiles, wherein the second stage rocket motors are ignited substantially simultaneously and in partially overlapping relationship with the first stage rocket motors.
Claim 54
Dependent Claim
28 words
The method of operating a launch vehicle according to claim 43, wherein the second stage rocket motors are ignited while the launch vehicle is within the earth's atmosphere.
Claim 55
Dependent Claim
63 words
The method of operating a launch vehicle according to claim 43, wherein the launch vehicle further comprises a third rocket motor stage, the method further comprising the step of igniting the third stage rocket motor in partially overlapping relationship with the second stage rocket motors so as to maintain positive thrust control over the launch vehicle as the second stage rocket motors burn-out.
Claim 56
Independent Claim
134 words
A method for deploying a satellite into orbit around the earth, the satellite being deployable from a launch vehicle having first and second sequentially ignitible, parallel mounted rocket motor stages, each of the rocket stages being comprised of at least one solid fuel rocket motor, the method comprising the steps of: igniting the first rocket motor stage and operating the first stage rocket motors continuously until motor burn-out; subsequent to lift-off and prior to first stage motor burn-out, igniting the second stage rocket motors in partially overlapping relationship with the first rocket motor stage so as to maintain positive thrust control over the launch vehicle as the first stage rocket motors burn-out; deploying the satellite into a desired orbital path around the earth; and exerting directional control over the launch vehicle until satellite deployment.
Claim 57
Independent Claim
134 words
A method for deploying a satellite into orbit around the earth, the satellite being deployable from a launch vehicle having first and second sequentially ignitible, parallel mounted rocket motor stages, each of the rocket stages being comprised of at least one solid fuel rocket motor, the method comprising the steps of: igniting the first rocket motor stage and operating the first stage rocket motors continuously until motor burn-out; subsequent to lift-off and prior to first stage motor burn-out, igniting the second stage rocket motors in partially overlapping relationship with the first rocket motor stage so as to maintain positive thrust control over the launch vehicle as the first stage rocket motors burn-out; deploying the satellite into a desired orbital path around the earth; and exerting directional control over the launch vehicle until satellite deployment.
Claim 58
Dependent Claim
29 words
The method for deploying a satellite according to claim 52, further comprising the step of jettisoning the first rocket motor stage following burn-out of the first stage rocket motors.
Claim 59
Dependent Claim
37 words
The method for deploying a satellite according to claim 52, wherein the rocket motors comprising the second stage are ignited from about 3 seconds to about 5 seconds prior to burn-out of the first stage rocket motors.
Claim 60
Dependent Claim
29 words
The method for deploying a satellite according to claim 52, wherein the first stage rocket motors are operated to develop maximum motor thrust within about five seconds following ignition.
Claim 61
Dependent Claim
24 words
The method for deploying a satellite according to claim 55, wherein the first and second rocket motors are operated along substantially similar thrust profiles.
Claim 62
Dependent Claim
29 words
The method for deploying a satellite according to claim 56, wherein the thrust profiles exhibit a generally linearly diminishing thrust rate following attainment of maximum thrust until motor burn-out.
Claim 63
Dependent Claim
43 words
The method according to claim 52, wherein the launch vehicle further comprises a third rocket motor stage comprising at least one rocket motor, further comprising the step of igniting the third stage rocket motors prior to burn-out of the second stage rocket motors.
Claim 64
Dependent Claim
22 words
The method according to claim 52, further comprising the step of jettisoning the second rocket motor stage following second stage motor burn-out.
Claim 65
Dependent Claim
27 words
The method according to claim 52, further comprising the step of deploying the satellite into a predetermined earth orbit following shut-down of the third stage rocket motor.
References Cited (Backward Citations)
US2899898A
Cited
US2960034A
Cited
US2748703A
Cited
US2745347A
Cited
US2787218A
Cited
US3023570A
Cited
US3128600A
Cited
US3122098A
Cited
US3190221A
Cited
US3210930A
Cited
US3210931A
Cited
US3324795A
Cited
US3397539A
Cited
US3328962A
Cited
US3357187A
Cited
US3442084A
Cited
US3712240A
Cited
US4157788A
Cited
US4471926A
Cited
US4384690A
Cited
US4451017A
Cited
US4834324A
Cited
US4736583A
Cited
US4796839A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1993-10-22 | 1994-04-23 | 1994-10-23 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1997-10-22 | 1998-04-23 | 1998-10-23 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2001-10-22 | 2002-04-23 | 2002-10-23 | $7700.00 | Window Closed / Lapsed |