Aircraft with high orbit injection efficiency and strong maneuver capability and orbit injection method thereof

An aircraft and strong maneuverability technology, applied in the field of aircraft, can solve the problems affecting the efficiency of orbiting, multi-carrying capacity, rocket loss, etc., and achieve the effect of high orbital efficiency, strong maneuverability, and easy orbit change

Pending Publication Date: 2020-02-11
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

In this case, for example, the final stage of the rocket needs to go through the entire flight process from launch to the predetermined orbit together with the payload. The quality of the stage shell) will cause the rocket to lose a lot of carrying capacity, which will affect the efficiency of entering orbit

Method used

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  • Aircraft with high orbit injection efficiency and strong maneuver capability and orbit injection method thereof
  • Aircraft with high orbit injection efficiency and strong maneuver capability and orbit injection method thereof
  • Aircraft with high orbit injection efficiency and strong maneuver capability and orbit injection method thereof

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Embodiment Construction

[0021] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the drawings in the embodiments of the present invention.

[0022] see figure 1 and figure 2 , the embodiment of the present invention provides an aircraft 100 with high orbital efficiency and strong maneuverability, the aircraft 100 includes:

[0023] solid engine 110;

[0024] an aircraft platform 120 connected to said solid motor 110; and

[0025] The load 130 installed to the aircraft platform 120, the load 130 is intended to fly into the target orbit O3 with the aircraft 100 in order to perform tasks;

[0026] Wherein, the solid engine 110 is used to provide the flight power required for the aircraft 100 to fly from the ground launch site GS into the sub-orbit O1,

[0027] Wherein, after the aircraft 100 flies into the sub-orbit O1, the solid motor 110 is disengaged from the aircraft 100,

[0028] Wherein, the aircraft platf...

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Abstract

The embodiment of the invention discloses an aircraft with high orbit injection efficiency and strong maneuver capability and an orbit injection method thereof. The aircraft comprises a solid engine,an aircraft platform which is connected to the solid engine and a load which is installed on the aircraft platform, the load is intended to fly into a target orbit with the aircraft for performing tasks; wherein the solid engine is used for providing flight power required for the aircraft to fly from a ground launching site into a sub orbit, after the aircraft flies into the sub orbit, the solid engine disengages from the aircraft, the aircraft platform is provided with a liquid propulsion system, and the liquid propulsion system is used for providing the flight power required for the aircraftto fly from the sub orbit into the target orbit.

Description

technical field [0001] The invention relates to the field of aircraft, in particular to an aircraft with high orbital entry efficiency and strong maneuverability and an orbital entry method thereof. Background technique [0002] The orbital efficiency of the aircraft is an important indicator that the aircraft needs to improve. The orbital efficiency refers to the ratio of the maximum payload mass that the aircraft can carry to the total take-off mass of the aircraft under specific mission conditions, reflecting the orbital capability of the aircraft under specified conditions. . [0003] The traditional way for space payloads to orbit is to use launch vehicles to directly send payloads to predetermined orbits. Among them, in the case of a multi-stage orbiting rocket, two or more sub-stages are connected and work sequentially. After the first sub-stage of a multi-stage rocket is ignited, the whole rocket is accelerated to fly, and the first sub-stage rocket works After the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/42B64G1/40B64G1/24
CPCB64G1/24B64G1/40B64G1/42
Inventor 曹喜滨王峰韦常柱李宁
Owner HARBIN INST OF TECH
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