CN109649689B - Limited thrust orbital transfer gravity loss calculation method and thrust calculation device - Google Patents

Limited thrust orbital transfer gravity loss calculation method and thrust calculation device Download PDF

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CN109649689B
CN109649689B CN201811495695.XA CN201811495695A CN109649689B CN 109649689 B CN109649689 B CN 109649689B CN 201811495695 A CN201811495695 A CN 201811495695A CN 109649689 B CN109649689 B CN 109649689B
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thrust
orbital transfer
loss
satellite
general assembly
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CN109649689A (en
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田百义
黄美丽
王大轶
张相宇
赵峭
冯昊
刘德成
周静
张磊
邹元杰
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Beijing Institute of Spacecraft System Engineering
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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
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
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Abstract

A gravity loss result can be obtained only according to the length of an ignition arc segment, the thrust magnitude of an engine and initial and tail end orbit information do not need to be obtained, and complicated orbit control model integral operation is not needed. The method is oriented to the field of relative navigation tests, can quickly calculate the propellant added when the satellite adopting the near-circular orbit changes orbit, and has strong reference value for the relative navigation test remote guidance section orbit changing task.

Description

Limited thrust orbital transfer gravity loss calculation method and thrust calculation device
Technical Field
The invention relates to a method and a device for calculating the limited thrust orbital transfer gravity loss, and belongs to the technical field of satellite orbital transfer.
Background
The relative navigation test generally involves two or more satellites, and due to the limitation of relative navigation instruments, the distance between the satellites used for the relative navigation test needs to satisfy certain constraints. To achieve this constraint, the relative navigation masters cannot avoid performing a orbital transfer maneuver to arrive at a configuration that can be used for relative navigation trials.
At present, orbital transfer engines adopted by satellites are limited in thrust, and ignition orbital transfer is mostly carried out by adopting an inertial space orientation method. In the traditional engine gravity loss calculation method, integration operation is mostly carried out on an orbit control model to obtain the speed increment of orbital transfer, and in addition, the speed increment of pulse-form orbital transfer needs to be obtained, so that the gravity loss of satellite orbital transfer is obtained. The calculation method needs to know information such as the thrust magnitude and the initial and final end orbit, and cannot calculate on the premise of no information.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the method and the device for calculating the orbital transfer gravity loss of the limited thrust overcome the defects of the prior art, obtain a simple relation between the gravity loss and the ignition arc length, and can be applied to quick calculation of the orbital transfer gravity loss of the near-circular orbit.
The purpose of the invention is realized by the following technical scheme:
a method for calculating the gravity loss of limited thrust orbital transfer is suitable for a near-circular orbit satellite and adopts inertial directional orbital transfer, and the gravity loss eta of the limited thrust orbital transfer is as follows:
Figure BDA0001896829960000011
in the formula (I), the compound is shown in the specification,
Figure BDA0001896829960000012
is the ignition arc segment length.
In the method for calculating the limited thrust orbital transfer gravity loss, the orbital transfer engine thrust F of the near-circular orbit satelliteGeneral assemblyComprises the following steps:
Figure BDA0001896829960000021
in the formula (I), the compound is shown in the specification,
Figure BDA0001896829960000022
the thrust for effective orbital transfer is generated in the thrust of the engine.
The above-mentioned limited thrust becomesMethod for calculating orbital gravity loss, propellant loss M of near-circular orbit satelliteLoss of powerComprises the following steps:
Mloss of power＝η×MGeneral assembly
In the formula, MGeneral assemblyThe total propellant demand for the satellite orbital transfer.
According to the method for calculating the limited thrust orbital transfer gravity loss, the orbital eccentricity of the near-circular orbit satellite is not more than 0.0025, and the orbital height is not more than 2000 km.
A thrust computing device can compute the thrust F of a orbital transfer engine of a near-circular orbit satelliteGeneral assemblyThrust F of orbital transfer engine of said satelliteGeneral assemblyComprises the following steps:
Figure BDA0001896829960000023
wherein
Figure BDA0001896829960000024
Wherein eta is the limited thrust orbital transfer gravity loss,
Figure BDA0001896829960000025
generating effective orbital transfer thrust for engine thrust;
Figure BDA0001896829960000026
is the ignition arc segment length.
The thrust computing device, the propellant loss M of the near-circular orbit satelliteLoss of powerComprises the following steps:
Mloss of power＝η×MGeneral assembly
In the formula, MGeneral assemblyThe total propellant demand for the satellite orbital transfer.
According to the thrust calculation device, the orbital eccentricity of the near-circular orbit satellite is not more than 0.0025, and the orbital height is not more than 2000 km.
Compared with the prior art, the invention has the following beneficial effects:
(1) compared with the prior art, the method can obtain the gravity loss result only according to the length of the ignition arc segment, does not need to know the thrust magnitude of the engine and the initial and tail end orbit information, and does not need complicated orbit control model integral operation;
(2) the method is oriented to the field of relative navigation tests, can quickly calculate the propellant added when the satellite adopting the near-circular orbit changes orbit, and has extremely high reference value for the relative navigation test remote guidance section orbit changing task;
(3) the method has good calculation real-time performance and is beneficial to realizing the rapid calculation of the limited thrust of the orbital transfer engine.
Drawings
Fig. 1 is a position relationship diagram of the ignition process of the satellite according to the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail with reference to the accompanying drawings.
A method for calculating the loss of gravity by changing orbit with limited thrust is suitable for changing orbit of a near-circular orbit satellite by inertial orientation, the orbit eccentricity of the near-circular orbit satellite is not more than 0.0025, and the orbit height is not more than 2000 km. The limited thrust orbital transfer gravity loss eta is as follows:
Figure BDA0001896829960000031
in the formula (I), the compound is shown in the specification,
Figure BDA0001896829960000032
is the ignition arc segment length.
Generating effective orbital transfer thrust according to limited thrust orbital transfer gravity loss eta and engine thrust
Figure BDA0001896829960000034
Orbital transfer engine thrust F capable of obtaining satellite with near-circular orbitGeneral assemblyComprises the following steps:
Figure BDA0001896829960000033
according to the limited thrust orbital transfer gravity loss eta and the total propellant demand M of satellite orbital transferGeneral assemblyCan obtain the propellant loss M of the near-circular orbit satelliteLoss of powerComprises the following steps:
Mloss of power＝η×MGeneral assembly
In the formula, MGeneral assemblyThe total propellant demand for the satellite orbital transfer.
A thrust computing device can compute the thrust F of a orbital transfer engine of a near-circular orbit satelliteGeneral assemblyThe orbit eccentricity ratio of the near-circular orbit satellite is not more than 0.0025, and the orbit height is not more than 2000 km. Thrust F of orbital transfer engine of near-circular orbit satelliteGeneral assemblyComprises the following steps:
Figure BDA0001896829960000041
wherein
Figure BDA0001896829960000042
Wherein eta is the limited thrust orbital transfer gravity loss,
Figure BDA0001896829960000043
generating effective orbital transfer thrust for engine thrust;
Figure BDA0001896829960000044
is the ignition arc segment length.
Example (b):
a method for calculating the limited thrust orbital transfer gravity loss is disclosed, and the specific formula is deduced as follows.
The gravity loss is defined by the formula:
Figure BDA0001896829960000045
in the formula, eta is the gravity loss of the satellite orbit changing; fGeneral assemblyThe unit N is the thrust of the orbital transfer engine;
Figure BDA0001896829960000046
the thrust value of the effective orbital transfer generated in the thrust of the engine is N.
According to the characteristics of the near-circular orbit, see fig. 1. The effective thrust magnitude is known as:
Figure BDA0001896829960000047
in the formula, Δ T is the total ignition time of the satellite in units of s; alpha is the included angle between the effective thrust and the total thrust in the orbital transfer process, and is the variable quantity, namely unit rad.
According to the above two formulas, the total thrust FGeneral assemblyFixed, the formula for the gravity loss calculation can be replaced by:
Figure BDA0001896829960000048
according to the characteristics of the circular orbit, the following relationship holds in the ignition process:
α＝θ
in the formula, θ is represented by unit rad in FIG. 1.
Therefore, the temperature of the molten metal is controlled,
Figure BDA0001896829960000051
by integral transformation, can obtain
Figure BDA0001896829960000052
In the formula (I), the compound is shown in the specification,
Figure BDA0001896829960000053
is the ignition arc length, in units rad.
In conclusion, the calculation formula of the gravity loss of the orbital transfer of the near-circular orbit satellite is obtained by the following steps:
Figure BDA0001896829960000054
the formula is only related to the propulsion arc length of the transition.
Generating effective orbital transfer thrust according to limited thrust orbital transfer gravity loss eta and engine thrust
Figure BDA0001896829960000055
Orbital transfer engine thrust F capable of obtaining satellite with near-circular orbitGeneral assemblyComprises the following steps:
Figure BDA0001896829960000056
according to the limited thrust orbital transfer gravity loss eta and the total propellant demand M of satellite orbital transferGeneral assemblyCan obtain the propellant loss M of the near-circular orbit satelliteLoss of powerComprises the following steps:
Mloss of power＝η×MGeneral assembly
In the formula, MGeneral assemblyThe total propellant demand for the satellite orbital transfer.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.

Claims (7)

1. A method for calculating the gravity loss of limited thrust orbital transfer is suitable for a near-circular orbit satellite to adopt inertial directional orbital transfer and is characterized in that: the limited thrust orbital transfer gravity loss eta is as follows:
Figure FDA0003162697090000011
in the formula (I), the compound is shown in the specification,
Figure FDA0003162697090000012
is the ignition arc segment length.
2. The method for calculating the limited thrust orbital transfer gravity loss according to claim 1, wherein the method comprises the following steps: orbital transfer engine thrust F of near-circular orbit satelliteGeneral assemblyComprises the following steps:
Figure FDA0003162697090000013
in the formula (I), the compound is shown in the specification,
Figure FDA0003162697090000014
the thrust for effective orbital transfer is generated in the thrust of the engine.
3. The method for calculating the limited thrust orbital transfer gravity loss according to claim 1, wherein the method comprises the following steps: propellant loss M of near-circular orbit satelliteLoss of powerComprises the following steps:
Mloss of power＝η×MGeneral assembly
In the formula, MGeneral assemblyThe total propellant demand for the satellite orbital transfer.
4. The method for calculating the limited thrust orbital transfer gravity loss according to claim 1, wherein the method comprises the following steps: the orbit eccentricity ratio of the near-circular orbit satellite is not more than 0.0025, and the orbit height is not more than 2000 km.
5. A thrust force calculation device characterized in that: the device is used for calculating the orbital transfer engine thrust F of the near-circular orbit satelliteGeneral assemblyThrust F of orbital transfer engine of said satelliteGeneral assemblyComprises the following steps:
Figure FDA0003162697090000015
wherein
Figure FDA0003162697090000016
Wherein eta is the limited thrust orbital transfer gravity loss,
Figure FDA0003162697090000017
generating effective orbital transfer thrust for engine thrust;
Figure FDA0003162697090000018
is the ignition arc segment length.
6. The thrust force calculation device according to claim 5, wherein: propellant loss M of near-circular orbit satelliteLoss of powerComprises the following steps:
Mloss of power＝η×MGeneral assembly
In the formula, MGeneral assemblyThe total propellant demand for the satellite orbital transfer.
7. The thrust force calculation device according to claim 5, wherein: the orbit eccentricity ratio of the near-circular orbit satellite is not more than 0.0025, and the orbit height is not more than 2000 km.
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