CN112078832A - Method for determining on-orbit residual fuel - Google Patents

Method for determining on-orbit residual fuel Download PDF

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CN112078832A
CN112078832A CN202010774450.1A CN202010774450A CN112078832A CN 112078832 A CN112078832 A CN 112078832A CN 202010774450 A CN202010774450 A CN 202010774450A CN 112078832 A CN112078832 A CN 112078832A
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fuel consumption
current
thruster
aircraft
period
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CN112078832B (en
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刘赟
张肖
董晋芳
程颢
王向
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Shanghai Aerospace Control Technology Institute
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
    • G01F22/00—Methods or apparatus for measuring volume of fluids or fluent solid material, not otherwise provided for

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Abstract

The invention relates to a method for determining on-orbit residual fuel, in particular to real-time estimation and compensation of on-orbit high-precision residual fuel. The method comprises the following steps: calculating the total fuel consumption of the aircraft according to the flow parameter of the thruster and the jet pulse width; during the track control period, simultaneously calculating the fuel consumption by measuring the acceleration; updating the primary fuel consumption according to the thruster switching mark during the track control period; the remaining fuel amount is calculated. The method calculates the fuel consumption based on the pulse width of each thruster and the acceleration measurement value during the track control, and compensates and corrects the fuel consumption according to whether the thruster fails or not during the track control, so as to realize high-precision real-time fuel residual estimation. The fuel consumption estimation and compensation method is simple in calculation and easy to apply in engineering.

Description

Method for determining on-orbit residual fuel
Technical Field
The invention relates to a method for determining on-orbit residual fuel, in particular to real-time estimation and compensation of on-orbit high-precision residual fuel.
Background
The existing on-track fuel determination methods are obtained by calculating measurement information of a measurement sensor mounted on a storage tank or estimated according to a specific impulse value by required control quantity, but in practical application, the calculation error of the measurement information acquired by a sensor is large, the execution condition of actual control is not considered by the residual fuel quantity estimated by the control quantity, so that the estimated value may not be consistent with the actual value, and in order to estimate the residual fuel with real time and high precision, a certain technical approach is required to ensure the real-time calculation, estimation and compensation of the residual fuel consumption.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: aiming at the defects in the prior art, the method for determining the on-rail residual fuel is provided, and the on-rail residual fuel value can be calculated more reliably in real time.
The invention is realized by the following technical scheme.
A method of determining on-rail remaining fuel comprising the steps of:
step 1, calculating the total fuel consumption of the aircraft according to the flow parameter and the jet pulse width of the thruster:
calculating and accumulating the fuel consumption of each thruster in the period;
calculating the total fuel consumption of the current aircraft;
step 2, during the track control period, the fuel consumption is calculated by measuring the acceleration:
calculating the fuel consumption of the current period from the measured acceleration;
calculating the total fuel consumption during the current rail control period;
calculating the current aircraft mass;
and 3, updating the primary fuel consumption according to the thruster switching mark during the track control period:
judging whether thruster switching is performed or not;
updating the total fuel consumption of the current aircraft;
and 4, calculating the residual fuel quantity.
The step 1 specifically comprises the following steps:
step 1.1, calculating and accumulating the fuel consumption of each thruster in the current period:
calculating the fuel consumption of each thruster in the period according to the flow parameters of each thruster and the jet pulse width of the period, and accumulating to obtain the fuel consumption of the period
Figure BDA0002617871590000021
Figure BDA0002617871590000022
Wherein n is the total number of thrusters, i is the number of thrusters, k is the number of cycles, qiConsumption rate per second (steady flow rate at rated pressure) of ith thruster, ti,kThe jet pulse width of the ith thruster in the kth period is delta tiIs the electrical delay time, beta, of the ith thrusteri(ti,k) Is a pulse multiple consumption coefficient (related to the pulse width of the air jet in each period).
Step 1.2, calculating the total fuel consumption of the current aircraft:
consumption by this period
Figure BDA0002617871590000023
Total fuel consumption of aircraft plus previous cycle
Figure BDA0002617871590000024
Obtaining total fuel consumption of current aircraft
Figure BDA0002617871590000025
Figure BDA0002617871590000026
Wherein,
Figure BDA0002617871590000027
for the total fuel consumption (initial value) of the current aircraft
Figure BDA0002617871590000028
)。
The step 2 specifically comprises the following steps:
step 2.1, calculating the fuel consumption of the current period by measuring the acceleration
Acceleration a measured during tracking from the tracking direction of the current cyclekCalculating the fuel consumption quantity delta m 'of the current period'k
Figure BDA0002617871590000029
Wherein, M'k-1For the k-1 cycle aircraft mass, TcThe length of the orbit control period is I, and the specific impulse value of the thruster is I.
Step 2.2, calculating the total fuel consumption during the current rail control period:
accumulating the fuel consumption m 'calculated in the previous period'k-1Obtaining total fuel consumption of current rail control
m′k＝Δm′k+m′k-1
Wherein m'kTotal aircraft fuel consumption (initial value) at k-th cycle calculated from acceleration measurements during tracking
Figure BDA0002617871590000031
k0Is the number of cycles at the beginning of the tracking control,
Figure BDA0002617871590000032
the total aircraft fuel consumption calculated by step 1 at the start of the tracking).
Step 2.3, calculating the mass of the current aircraft:
subtracting the current total fuel consumption m 'from the aircraft full load mass'kObtaining current aircraft mass
M′k＝Mall-m′k-1
Wherein M isallThe mass of the aircraft when fully loaded.
The step 3 specifically comprises the following steps:
step 3.1, judging whether the thruster is switched:
according to the thruster switch mark SkGiving out the flag U whether the fuel consumption is updatedk
Figure BDA0002617871590000033
Initial value U0＝0，UkWhen 1 indicates that an update is required, UkA value of 0 indicates no update is required;
wherein,
Figure BDA0002617871590000034
initial value S0＝0。
Step 3.2, updating the total fuel consumption m of the current aircraftk：
Figure BDA0002617871590000035
And step 4, calculating the remaining fuel quantity:
loaded by aircraft with fuel quantity mallMinus the total fuel consumption m of the current aircraftkObtaining the current remaining fuel quantity mremain,k：
mremain,k＝mall-mk。
Compared with the prior art, the method has the following advantages and beneficial effects:
(1) physical parameters such as storage tank temperature, pressure and the like do not need to be collected by a sensor arranged on the fuel storage tank, and engineering is convenient to realize;
(2) the fuel consumption per period calculated based on the actually measured flow parameter of the thruster in the ground high-modulus test run is closer to the true value of the fuel consumption;
(3) the fuel consumption compensation can be carried out during the track control according to whether the thruster fault switching occurs or not, and the fuel consumption calculation deviation caused by the thruster fault is corrected.
(4) The method is based on a fuel consumption calculation method of flow parameters of each thruster and pulse width quantity per period, a fuel consumption calculation method based on measurement of acceleration and specific impulse values during tracking control, and a thruster switching and fuel consumption updating judgment method during tracking control.
(5) The invention discloses a high-precision residual fuel determining method, which comprises the following steps: calculating the total fuel consumption of the aircraft according to the flow parameter of the thruster and the jet pulse width; during the track control period, simultaneously calculating the fuel consumption by measuring the acceleration; updating the primary fuel consumption according to the thruster switching mark during the track control period; the remaining fuel amount is calculated. The method calculates the fuel consumption based on the pulse width of each thruster and the acceleration measurement value during the track control, and compensates and corrects the fuel consumption according to whether the thruster fails or not during the track control, so as to realize high-precision real-time fuel residual estimation. The fuel consumption estimation and compensation method is simple in calculation and easy to apply in engineering.
Detailed Description
The following examples illustrate the invention in detail: the embodiment is implemented on the premise of the technical scheme of the invention, and a detailed implementation mode and a specific operation process are given. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention.
A high accuracy remaining fuel determination method comprising the steps of:
step 1, calculating the total fuel consumption of the aircraft according to the flow parameter of the thruster and the jet pulse width:
calculating and accumulating the fuel consumption of each thruster in the period;
calculating the total fuel consumption of the current aircraft;
step 2, during the track control period, the fuel consumption is calculated by measuring the acceleration:
calculating the fuel consumption of the current period from the measured acceleration;
calculating the current rail control total fuel consumption;
calculating the current aircraft mass;
and 3, updating the primary fuel consumption according to the thruster switching mark during the track control period:
judging whether thruster switching is performed or not;
updating the total fuel consumption of the current aircraft;
and 4, calculating the residual fuel quantity.
The step 1 specifically comprises the following steps:
step 1.1, calculating and accumulating the fuel consumption of each thruster in the current period:
calculating the fuel consumption of each thruster in the period according to the flow parameters of each thruster and the jet pulse width of the period, and accumulating to obtain the fuel consumption of the period
Figure BDA0002617871590000051
Figure BDA0002617871590000052
Wherein n is the total number of thrusters, i is the number of thrusters, k is the number of cycles, qiConsumption rate per second (steady flow rate at rated pressure) of ith thruster, ti,kThe jet pulse width of the ith thruster in the kth period is delta tiIs the electrical delay time, beta, of the ith thrusteri(ti,k) Is a pulse multiple consumption coefficient (related to the pulse width of the air jet in each period).
Step 1.2, calculating the total fuel consumption of the current aircraft:
consumption by this period
Figure BDA0002617871590000053
Total fuel consumption of aircraft plus previous cycle
Figure BDA0002617871590000054
Obtaining total fuel consumption of current aircraft
Figure BDA0002617871590000055
Figure BDA0002617871590000056
Wherein,
Figure BDA0002617871590000057
for the total fuel consumption (initial value) of the current aircraft
Figure BDA0002617871590000058
)。
The step 2 specifically comprises the following steps:
step 2.1, calculating the fuel consumption of the current period by measuring the acceleration
Acceleration a measured during tracking from the tracking direction of the current cyclekCalculating the fuel consumption quantity delta m 'of the current period'k
Figure BDA0002617871590000059
Wherein, M'k-1Aircraft mass at which the fuel consumption is calculated from the acceleration measurements for the k-1 th cycle, TcTo control the period duration, I is the thrust device specific impulse value.
Step 2.2, calculating the current rail control total fuel consumption:
accumulating the fuel consumption m 'calculated in the previous period'k-1Obtaining total fuel consumption of current rail control
m′k＝Δm′k+m′k-1
Wherein m'kTotal aircraft fuel consumption (initial value) at k-th cycle calculated from acceleration measurements during tracking
Figure BDA0002617871590000061
k0Is the number of cycles at the beginning of the tracking control,
Figure BDA0002617871590000062
the total aircraft fuel consumption calculated by step 1 at the start of the tracking).
Step 2.3, calculating the mass of the current aircraft:
subtracting the current total fuel consumption m 'from the aircraft full load mass'kObtaining current aircraft mass
M′k＝Mall-m′k-1
Wherein M isallThe mass of the aircraft when fully loaded.
The step 3 specifically comprises the following steps:
step 3.1, judging whether the thruster is switched:
according to the thruster switch mark SkGiving out the flag U whether the fuel consumption is updatedk
Figure BDA0002617871590000063
Initial value U0＝0
Wherein,
Figure BDA0002617871590000064
initial value S0＝0。
Step 3.2, updating the total fuel consumption m of the current aircraftk：
Figure BDA0002617871590000065
The step 4 specifically comprises the following steps:
calculating the remaining fuel quantity:
loaded by aircraft with fuel quantity mallSubtracting the current total fuel consumption m of the aircraftkObtaining the current remaining fuel quantity mremain,k，
mremain,k＝mall-mk
The method specifically comprises the following steps:
a. calculating total fuel consumption of the aircraft according to the flow parameter and jet pulse width of the thruster
Calculating the fuel consumption of each thruster in the period and accumulating:
calculating the fuel consumption of each thruster in the period according to the flow parameters of each thruster and the jet pulse width of the period, and accumulating to obtain the fuel consumption of the period
Figure BDA0002617871590000071
Figure BDA0002617871590000072
Wherein n is the total number of thrustersI is the thruster number, k is the period number of the current period, qiConsumption rate per second (steady flow rate at rated pressure) of ith thruster, ti,kThe jet pulse width of the ith thruster in the kth period is delta tiIs the electrical delay time, beta, of the ith thrusteri(ti,k) Is a pulse multiple consumption coefficient (related to the pulse width of the air jet in each period).
Calculating the total fuel consumption of the current aircraft:
consumption by this period
Figure BDA0002617871590000073
Total fuel consumption of aircraft plus previous cycle
Figure BDA0002617871590000074
Obtaining the total fuel consumption m of the current aircraftk，
Figure BDA0002617871590000075
Wherein,
Figure BDA0002617871590000076
for the total fuel consumption (initial value) of the current aircraft
Figure BDA0002617871590000077
)。
b. Simultaneous calculation of fuel consumption from measured acceleration during tracking
Calculating the fuel consumption of the current cycle from the measured acceleration
Acceleration a measured during tracking from the tracking direction of the current cyclekCalculating the fuel consumption quantity delta m 'of the current period'k
Figure BDA0002617871590000078
Wherein, M'k-1For the k-1 cycle aircraft mass, TcTo control the period duration, I is the thrust device specific impulse value.
Calculating the current rail control total fuel consumption:
accumulating the fuel consumption m 'calculated in the previous period'k-1Obtaining total fuel consumption of current rail control
m′k＝Δm′k+m′k-1
Wherein m'kTotal aircraft fuel consumption (initial value) at k-th cycle calculated from acceleration measurements during tracking
Figure BDA0002617871590000081
k0Is the number of cycles at the beginning of the tracking control,
Figure BDA0002617871590000082
the total aircraft fuel consumption calculated by step 1 at the start of the tracking).
Calculating the current aircraft mass:
subtracting the current total fuel consumption m 'from the aircraft full load mass'kObtaining current aircraft mass
M′k＝Mall-m′k-1
Wherein M isallThe mass of the aircraft when fully loaded.
c. Performing primary fuel consumption updating according to thruster switching mark during orbit control
Judging whether thruster switching is performed:
according to the thruster switch mark SkGiving out the flag U whether the fuel consumption is updatedk
Figure BDA0002617871590000083
Initial value U0＝0
Wherein,
Figure BDA0002617871590000084
initial value S0＝0。
Updating the total fuel consumption m of the current aircraftk：
Figure BDA0002617871590000085
d. Calculating the remaining fuel quantity
Loaded by aircraft with fuel quantity mallSubtracting the current total fuel consumption m of the aircraftkObtaining the current remaining fuel quantity mremain,k，
mremain,k＝mall-mk
The high-precision residual fuel determining method provided by the embodiment provides a high-precision residual fuel determining method, the method calculates the fuel consumption based on the pulse width of each thruster and the acceleration measurement value during the rail control period, and compensates and corrects the fuel consumption according to whether the thruster fails during the rail control period, so that high-precision real-time residual fuel estimation is realized. The fuel consumption estimation and compensation method is simple in calculation and easy to apply in engineering.
The method calculates the fuel consumption based on the pulse width of each thruster and the acceleration measurement value during the track control, compensates and corrects the fuel consumption according to whether the thruster fails or not during the track control, realizes high-precision real-time fuel surplus estimation, improves the reliability of the fuel surplus estimation, and is suitable for controlling the aircraft with high requirements on the real-time performance and precision of the surplus fuel estimation; the fuel consumption estimation and compensation method is simple in calculation and easy to apply in engineering.
The initial mass m0 is 2846kg, and the thrust device specific impulse is 2788 Ns/kg. When the rail control is started, 2 thrusters are failed, and 4 thrusters are fully sprayed (200 ms). The force of each thruster is 100N. And judging the failure of the thruster after 60 seconds to switch the thrusters. Calculating the total fuel consumption of the aircraft to be 4 × 100 × 60/2788-8.608 kg according to the flow parameters of the thruster and the jet pulse width; due to the failure of the 2 thrusters, the actual 2 thrusters are working and the actual fuel consumption is 2 × 100 × 60/2788 — 4.304 kg. Average acceleration a during air injection is 0.0703m/s2And the speed increment is 4.218m/s, then the true fuel consumption can be estimated as:
Figure BDA0002617871590000091
the foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes and modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention.

Claims (9)

1. A method of determining on-rail remaining fuel, comprising the steps of:
step 1, calculating the total fuel consumption of the aircraft according to the flow parameter of a thruster and the air injection pulse width during the non-orbit control period and the orbit control period;
step 2, during the track control period, calculating the fuel consumption by measuring the acceleration;
step 3, updating the primary fuel consumption according to the thruster switching mark during the track control period;
and 4, calculating the residual fuel quantity.
2. A method of determining on-rail remaining fuel as claimed in claim 1, wherein:
in the step 1, firstly, the fuel consumption of each thruster in the current period is calculated and accumulated, and then the total fuel consumption of the current aircraft is calculated.
3. A method of determining on-rail remaining fuel according to claim 1 or 2, characterized in that: the step 1 is as follows:
step 1.1, calculating and accumulating the fuel consumption of each thruster in the current period:
calculating the fuel consumption of each thruster in the period according to the flow parameters of each thruster and the jet pulse width of the period, and accumulating to obtain the fuel consumption of the period
Figure FDA0002617871580000011
Figure FDA0002617871580000012
Wherein n is the total number of thrusters, i is the number of thrusters, k is the number of cycles, qiIs the consumption rate per second of the ith thruster, ti,kThe jet pulse width of the ith thruster in the kth period is delta tiIs the electrical delay time, beta, of the ith thrusteri(ti,k) The pulse multi-consumption coefficient;
step 1.2, calculating the total fuel consumption of the current aircraft:
consumption by this period
Figure FDA0002617871580000013
Total fuel consumption of aircraft plus previous cycle
Figure FDA0002617871580000014
Obtaining total fuel consumption of current aircraft
Figure FDA0002617871580000015
Figure FDA0002617871580000016
Wherein,
Figure FDA0002617871580000017
for the current total fuel consumption of the aircraft, the initial value
Figure FDA0002617871580000018
4. A method of determining on-rail remaining fuel as claimed in claim 1, wherein: in the step 2, firstly, the fuel consumption of the current period is calculated by measuring the acceleration, then the total fuel consumption of the current rail control period is calculated, and finally the current aircraft mass is calculated.
5. A method of determining on-rail remaining fuel according to claim 1 or 4, characterized in that: the step 2 is as follows:
step 2.1, calculating the fuel consumption of the current period by the measured acceleration:
acceleration a measured from the current cycle during trackingkCalculating the fuel consumption quantity delta m 'of the current period'k
Figure FDA0002617871580000021
Wherein, M'k-1For the k-1 cycle aircraft mass, TcThe length of the orbit control period is I, and the specific impulse value of the thruster is I;
step 2.2, calculating the total fuel consumption during the current rail control period:
accumulating the fuel consumption m 'calculated in the previous period'k-1Obtaining total fuel consumption of current rail control
m′k＝Δm′k+m′k-1
Wherein m'kTotal fuel consumption of aircraft at k-th cycle, calculated from measured acceleration values during orbit control, initial value
Figure FDA0002617871580000022
k0Is the number of cycles at the beginning of the tracking control,
Figure FDA0002617871580000023
the total fuel consumption of the aircraft calculated in the step 1 at the beginning of the rail control;
step 2.3, calculating the mass of the current aircraft:
subtracting the current total fuel consumption m 'from the aircraft full load mass'kObtaining current aircraft mass
M′k＝Mall-m′k-1
Wherein M isallThe mass of the aircraft when fully loaded.
6. A method of determining on-rail remaining fuel as claimed in claim 1, wherein: in the step 3, whether the thruster is switched is judged, and then the total fuel consumption of the current aircraft is updated.
7. A method of determining on-rail remaining fuel according to claim 1 or 6, characterized in that: the step 3 is as follows:
step 3.1, judging whether the thruster is switched:
according to the thruster switch mark SkGiving out the flag U whether the fuel consumption is updatedk
Figure FDA0002617871580000031
Initial value U0＝0，UkWhen 1 indicates that an update is required, UkA value of 0 indicates no update is required;
wherein,
Figure FDA0002617871580000032
initial value S0＝0；
Step 3.2, updating the total fuel consumption m of the current aircraftk：
Figure FDA0002617871580000033
8. A method of determining on-rail remaining fuel as claimed in claim 1, wherein: in step 4, the method for calculating the remaining fuel amount includes:
loaded by aircraft with fuel quantity mallMinus the total fuel consumption m of the current aircraftkObtaining the current remaining fuel quantity mremain,k：
mremain,k＝mall-mk。
9. The method of claim 1, wherein determining the on-track residual fuel is performed by a fuel injection system：βi(ti,k) Is related to the pulse width of the jet in each period, qiIs a steady flow at rated pressure.
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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4908776A (en) * 1987-11-23 1990-03-13 Ford Aerospace & Communications Corporation Spacecraft fuel measurement
CN103412563A (en) * 2013-07-25 2013-11-27 北京控制工程研究所 Method for estimating orbit control comprehensive efficiency and propellant consumption
CN108639384A (en) * 2018-04-03 2018-10-12 上海航天控制技术研究所 A kind of satellite booster agent management method based on the multiplexing of attitude control thruster
CN111426364A (en) * 2020-04-16 2020-07-17 北京控制工程研究所 Propellant residual quantity measuring method based on multi-source data fusion
CN111458150A (en) * 2020-03-31 2020-07-28 上海航天控制技术研究所 High-reliability rail-controlled thruster fault discrimination method based on adding table

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4908776A (en) * 1987-11-23 1990-03-13 Ford Aerospace & Communications Corporation Spacecraft fuel measurement
CN103412563A (en) * 2013-07-25 2013-11-27 北京控制工程研究所 Method for estimating orbit control comprehensive efficiency and propellant consumption
CN108639384A (en) * 2018-04-03 2018-10-12 上海航天控制技术研究所 A kind of satellite booster agent management method based on the multiplexing of attitude control thruster
CN111458150A (en) * 2020-03-31 2020-07-28 上海航天控制技术研究所 High-reliability rail-controlled thruster fault discrimination method based on adding table
CN111426364A (en) * 2020-04-16 2020-07-17 北京控制工程研究所 Propellant residual quantity measuring method based on multi-source data fusion

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