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US4277940A
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Integral rocket-ramjet closed loop fuel control system
Assignee: RTX Corp
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Filing: 1979-07-25
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Granted: 1981-07-14
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Expires: 1999-07-25
Abstract
Abstract In an integral rocket-ramjet having a combustor which initially serves as a rocket combustion chamber for booster propellant, and after the booster propellant is expended serves as a ramjet combustor where fuel and air are burned, a fuel control system is described for the ramjet stage by which ram burner light-off is automatically initiated upon transition from rocket to ramjet propulsion. The fuel control regulates fuel flow to the combustor over the entire flight regime and responds to operating conditions to provide a light-off schedule, to stabilize the shock wave at the air inlet, to provide a maximum fuel-to-air ratio limit, to limit the maximum vehicle Mach number, and to prevent lean burner blowout by providing a minimum fuel-to-air ratio limit. Mach number limiting and air inlet margin limiting are performed in closed loop fashion, while the other functions are scheduled or open loop controls. The closed loop functions are performed by scheduling a ratio of combustion chamber pressure to a reference pressure, and comparing this ratio to the ratio of the pressures as measured, any error therebetween being used to produce a desired fuel flow to combustion chamber pressure ratio. By measuring the actual combustion chamber pressure, the desired fuel flow is obtained.
Inventors
- 👤 Kermit I. Harner
- 👤 John P. Patrick
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 21:40
CPC Classifications
F; F02; F02C; F02C9/00; F02C9/26; F02C9/44; F02K; F02K7/00; F02K7/10; F02K7/18; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 15
Claim 1
Independent Claim
303 words
In an integral rocket-ramjet vehicle having a combustion chamber, a source of ramjet fuel and an inlet supplying air to said combustion chamber, a fuel control for modulating the flow of fuel from said source to said combustion chamber upon termination of the rocket phase of vehicle operation comprising: means responsive to termination of the rocket phase of operation for producing a first signal indicative of desired fuel-to-air ratio upon ignition of said fuel in said combustion chamber, and indicative of a maximum fuel-to-air ratio after ignition of said fuel; means responsive to first selected vehicle operating conditions for producing a signal indicative of desired combustion chamber to reference pressure ratio to limit said vehicle maximum Mach number to a value satisfactory with regard to structural or aerodynamic heating characteristics; inlet margin scheduling means responsive to second selected vehicle operating conditions for scheduling a second signal indicative of desired combustion chamber to reference pressure ratio to maximize pressure recovery of the shock wave produced by airflow through said inlet; least select means receiving said first and second pressure ratio signals and selecting the one of said first and second signals which produces the lowest fuel-to-air ratio; means for measuring the pressures from which said pressure ratio signals are derived and producing a signal indicative of actual combustion chamber to reference pressure ratio; means for comparing the pressure ratio signal passed through said least select means with said actual pressure ratio signal and producing a pressure ratio error signal; closed loop integrator means for receiving said pressure ratio error signal and producing therefrom a desired fuel-to-air ratio signal which does not exceed said maximum fuel-to-air ratio; and fuel scheduling means including valve means responsive to said desired fuel-to-air ratio signal for metering the desired amount of fuel from said source to said combustion chamber.
Claim 2
Dependent Claim
303 words
In an integral rocket-ramjet vehicle having a combustion chamber, a source of ramjet fuel and an inlet supplying air to said combustion chamber, a fuel control for modulating the flow of fuel from said source to said combustion chamber upon termination of the rocket phase of vehicle operation comprising: means responsive to termination of the rocket phase of operation for producing a first signal indicative of desired fuel-to-air ratio upon ignition of said fuel in said combustion chamber, and indicative of a maximum fuel-to-air ratio after ignition of said fuel; means responsive to first selected vehicle operating conditions for producing a signal indicative of desired combustion chamber to reference pressure ratio to limit said vehicle maximum Mach number to a value satisfactory with regard to structural or aerodynamic heating characteristics; inlet margin scheduling means responsive to second selected vehicle operating conditions for scheduling a second signal indicative of desired combustion chamber to reference pressure ratio to maximize pressure recovery of the shock wave produced by airflow through said inlet; least select means receiving said first and second pressure ratio signals and selecting the one of said first and second signals which produces the lowest fuel-to-air ratio; means for measuring the pressures from which said pressure ratio signals are derived and producing a signal indicative of actual combustion chamber to reference pressure ratio; means for comparing the pressure ratio signal passed through said least select means with said actual pressure ratio signal and producing a pressure ratio error signal; closed loop integrator means for receiving said pressure ratio error signal and producing therefrom a desired fuel-to-air ratio signal which does not exceed said maximum fuel-to-air ratio; and fuel scheduling means including valve means responsive to said desired fuel-to-air ratio signal for metering the desired amount of fuel from said source to said combustion chamber.
Claim 3
Dependent Claim
71 words
The fuel control of claim 1 wherein said closed loop integrator means includes compensating means receiving said pressure ratio error signal and producing therefrom a first fuel-to-air ratio signal proportional to the integral of the pressure ratio error, means for comparing said first fuel-to-air ratio signal with said maximum fuel-to-air ratio signal and reducing said pressure ratio error signal when said first fuel-to-air ratio signal exceeds said maximum fuel-to-air ratio signal.
Claim 4
Dependent Claim
60 words
The fuel control of claim 2 further comprising: means for producing a signal indicative of a minimum fuel-to-air ratio; and said closed loop integrator means further including means for comparing said first fuel-to-air ratio signal with said minimum fuel-to-air ratio signal and increasing said pressure ratio error signal when said minimum fuel-to-air ratio signal exceeds said first fuel-to-air ratio signal.
Claim 5
Dependent Claim
90 words
The fuel control of claim 1 wherein said closed loop integrator means includes compensating means receiving said pressure ratio error signal and producing therefrom a first fuel-to-air ratio signal proportional to the integral of the pressure ratio error; means for comparing said first fuel-to-air ratio signal with said maximum fuel-to-air ratio signal and producing a first fuel-to-air ratio error signal; and first bound means receiving said first fuel-to-air ratio error signal and reducing said pressure ratio error signal when said first fuel-to-air ratio signal exceeds said maximum fuel-to-air ratio signal.
Claim 6
Dependent Claim
73 words
The fuel control of claim 4 and further including: means for producing a signal indicative of a minimum fuel-to-air ratio; means for comparing said first fuel-to-air ratio signal with said minimum fuel-to-air ratio signal and producing a second fuel-to-air ratio error signal; and second bound means receiving said second fuel-to-air ratio error signal and increasing said pressure ratio error signal when said minimum fuel-to-air ratio signal exceeds said second fuel-to-air ratio error signal.
Claim 7
Dependent Claim
149 words
The fuel control of claim 5 wherein said means for producing a signal indicative of a desired fuel-to-air ratio upon ignition and a maximum fuel-to-air ratio thereafter comprises: means responsive to termination of said vehicle rocket phase for producing an ignition signal; timing means for receiving said ignition signal; said ignition signal initiating said timing means and producing a timing signal upon receipt by said timing means; means for producing a signal indicative of the altitute pressure of said vehicle; and scheduling means responsive to said timing signal and to said altitude pressure signal for scheduling a reduced maximum fuel-to-air ratio signal with a magnitude and time duration selected as a function of said pressure signal and adapted to provide optimum fuel flow to said combustion chamber upon ramjet ignition, said reduced maximum fuel-to-air ratio signal being increased after said selected time duration to said maximum fuel-to-air ratio signal.
Claim 8
Dependent Claim
51 words
The fuel control of claim 6 including igniter means for initiating combustion of said fuel in said combustion chamber; time delay means; means for feeding said igniter signal to said time delay means whereby said ignition signal is delayed; and means feeding said time delayed ignition signal to said igniter means.
Claim 9
Dependent Claim
52 words
The fuel control of claim 7 including a shut-off solenoid for said fuel metering means whereby said fuel metering means is closed during the rocket phase of operation; and means for feeding said ignition signal to said shut-off solenoid to open said fuel metering means upon the occurrence of said ignition signal.
Claim 10
Dependent Claim
30 words
The fuel control of claim 1 wherein said reference pressure is the pressure sensed by a pilot probe located on the cowl lip or compression ramp of said air inlet.
Claim 11
Dependent Claim
46 words
The fuel control of claim 3 further including means for multiplying said desired fuel-to-air ratio signal by actual combustion chamber pressure to produce a fuel flow reference signal; said valve means being responsive to said fuel flow reference signal for metering fuel to said combustion chamber.
Claim 12
Dependent Claim
212 words
In an integral rocket-ramjet vehicle having a combustion chamber, a source of ramjet fuel and an inlet supplying air to said combustion chamber, a fuel control for modulating the flow of fuel from said source to said combustion chamber upon termination of the rocket phase of vehicle operation, comprising: means for scheduling a first pressure ratio signal indicative of the difference between vehicle velocity and a vehicle velocity limit; means for scheduling a second pressure ratio signal indicative of optimum inlet performance for said vehicle operating conditions; least select means receiving said first and second pressure ratio signals and passing therethrough the lower of said pressure ratio signals; means for comparing the pressure ratio signal passed by said least select means with the actual value of said pressure ratio to produce a pressure ratio error signal; signal compensating means receiving said pressure ratio error signal and producing therefrom a first fuel-to-air ratio signal variable at a rate proportional to said pressure ratio error signal; multiplier means receiving said first fuel-to-air ratio signal and a signal indicative of actual airflow for producing a desired fuel flow signal; and hydromechanical control means including a fuel control valve responsive to said desired fuel flow signal for varying the flow of fuel to said combustion chamber.
Claim 13
Dependent Claim
212 words
In an integral rocket-ramjet vehicle having a combustion chamber, a source of ramjet fuel and an inlet supplying air to said combustion chamber, a fuel control for modulating the flow of fuel from said source to said combustion chamber upon termination of the rocket phase of vehicle operation, comprising: means for scheduling a first pressure ratio signal indicative of the difference between vehicle velocity and a vehicle velocity limit; means for scheduling a second pressure ratio signal indicative of optimum inlet performance for said vehicle operating conditions; least select means receiving said first and second pressure ratio signals and passing therethrough the lower of said pressure ratio signals; means for comparing the pressure ratio signal passed by said least select means with the actual value of said pressure ratio to produce a pressure ratio error signal; signal compensating means receiving said pressure ratio error signal and producing therefrom a first fuel-to-air ratio signal variable at a rate proportional to said pressure ratio error signal; multiplier means receiving said first fuel-to-air ratio signal and a signal indicative of actual airflow for producing a desired fuel flow signal; and hydromechanical control means including a fuel control valve responsive to said desired fuel flow signal for varying the flow of fuel to said combustion chamber.
Claim 14
Dependent Claim
44 words
The fuel control of claim 11 and including means for producing a maximum fuel-to-air ratio signal; means for producing a minimum fuel-to-air ratio signal; and means for maintaining said first fuel-to-air ratio signal within the limits of said maximum and minimum fuel-to-air ratio signals.
Claim 15
Dependent Claim
36 words
A fuel control as in claim 12 in which said means for producing maximum fuel-to-air ratio signal includes means for scheduling a reduced maximum fuel-to-air ratio upon initiation of ramjet fuel flow to said combustion chamber.
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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) | 1984-07-13 | 1985-01-12 | 1985-07-14 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-07-13 | 1989-01-12 | 1989-07-14 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-07-13 | 1993-01-12 | 1993-07-14 | $7700.00 | Window Closed / Lapsed |