Orbit transfer method for rapid arrival of spatial different-plane circular orbit target

Abstract

The invention relates to an orbital transfer method for rapid arrival of a spatial different-plane circular orbit target, and the method comprises the steps: innovatively designing a virtual orbit, and carrying out the optimization to obtain the optimal rendezvous phase and rendezvous time of a spatial target; obtaining the optimal time and phase of the service aircraft entering the elliptical transfer orbit through backstepping according to the optimal rendezvous phase and the rendezvous time; obtaining an orbit phase adjustment amplitude and adjustment time of the service aircraft according to the initial position of the service aircraft and the phase entering the ellipse transfer orbit; and obtaining the berthing waiting time of the service aircraft on the initial orbit according to the orbit phase adjustment amplitude and the adjustment time of the service aircraft. Therefore, the orbital transfer strategy of the service aircraft can be calculated.

Description

technical field

[0001] The invention belongs to the technical field of space vehicle on-orbit service and maintenance. Background technique

[0002] On-orbit service and maintenance is one of the frontier hotspots of aerospace technology. After the service aircraft approaches the space target satellite, it will perform service operations such as close-range observation, module replacement, fuel filling, and auxiliary orbit change, which can realize the on-orbit failure of the target satellite. Restoring and prolonging the life, so as to continue to play the value of the in-orbit application, can produce great economic benefits. In order to perform service operations on space target satellites, one of the prerequisites is to arrive near the target satellites and perform close-up observations to find out the geometric characteristics and space attitude of the target satellites, and provide the required observation input for service operations.

[0003] The service aircraft mu...

Examples

Embodiment

[0093] At the initial moment (denoted as time 0), the semi-major axis of the orbital element of the serving aircraft a s 12378.137km, eccentricity e s is 0, inclination i s 40°, right ascension of ascending node Ω s is 100.25°, the argument of perigee ω s is 0°, phase P si is 5°, and the semi-major axis of the space object satellite orbit element a t 30378.137km, eccentricity e t is 0, inclination i t 10°, right ascension of ascending node Ω t is 250.25°, the argument of perigee ω t is 0°, phase P ti is 60°, the calculation process of the service aircraft’s orbit change strategy for the rapid arrival of the space target satellite is as follows:

[0094] (1) Calculate the orbital phase of the service vehicle when it arrives at the space target

[0095] According to the orbit elements of the service aircraft and space target satellite at the initial moment, set the initial value, record the initial orbit element of the virtual service aircraft as the semi-major axis a ...

technical field

[0001] The invention belongs to the technical field of space vehicle on-orbit service and maintenance. Background technique

[0002] On-orbit service and maintenance is one of the frontier hotspots of aerospace technology. After the service aircraft approaches the space target satellite, it will perform service operations such as close-range observation, module replacement, fuel filling, and auxiliary orbit change, which can realize the on-orbit failure of the target satellite. Restoring and prolonging the life, so as to continue to play the value of the in-orbit application, can produce great economic benefits. In order to perform service operations on space target satellites, one of the prerequisites is to arrive near the target satellites and perform close-up observations to find out the geometric characteristics and space attitude of the target satellites, and provide the required observation input for service operations.

[0003] The service aircraft mu...

Examples

Embodiment

[0093] At the initial moment (denoted as time 0), the semi-major axis of the orbital element of the serving aircraft a s 12378.137km, eccentricity e s is 0, inclination i s 40°, right ascension of ascending node Ω s is 100.25°, the argument of perigee ω s is 0°, phase P si is 5°, and the semi-major axis of the space object satellite orbit element a t 30378.137km, eccentricity e t is 0, inclination i t 10°, right ascension of ascending node Ω t is 250.25°, the argument of perigee ω t is 0°, phase P ti is 60°, the calculation process of the service aircraft’s orbit change strategy for the rapid arrival of the space target satellite is as follows:

[0094] (1) Calculate the orbital phase of the service vehicle when it arrives at the space target

[0095] According to the orbit elements of the service aircraft and space target satellite at the initial moment, set the initial value, record the initial orbit element of the virtual service aircraft as the semi-major axis a ...

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