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Air vehicle capable of achieving transformation recycling and recycling method

A technology of aircraft and flight speed, applied in the system of aerospace vehicles returning to the earth's atmosphere, landing devices of aerospace vehicles, weapon types, etc., can solve the problem of large damage to engines and drag surfaces, reduced power efficiency, and SpaceX dumping, etc. problem, to achieve the effect of low ablation, low power consumption, and simple deformation mechanism

Active Publication Date: 2019-12-20
北京凌空天行科技有限责任公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In order to realize the complete recovery of the carrier, this kind of method needs to consume nearly half of the fuel in the process, which greatly reduces the actual use efficiency of the power. After returning, due to long-term work, the engine and the resistance surface are greatly damaged and the ablation is serious. Multiple parts need to be replaced. At the same time, this type of vertical landing with a large slenderness ratio and axisymmetric shape has extremely high environmental requirements for the landing site. SpaceX has experienced many accidents during landing during missions in recent years.

Method used

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  • Air vehicle capable of achieving transformation recycling and recycling method
  • Air vehicle capable of achieving transformation recycling and recycling method
  • Air vehicle capable of achieving transformation recycling and recycling method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0041] A deformable recovery aircraft, comprising a rocket body, canards 3, wings, air rudders 9, gas rudders 10, a parachute system, a thrust reverser engine system, and a landing gear system; figure 1 and figure 2 shown. The canard 3 is telescopically installed on both sides of the rocket body; the wings are installed on both sides of the rocket body; the air rudder 9 and the gas rudder 10 are all installed on the rocket body, Both are used for flight control; the parachute system is used for the deceleration of the aircraft in the subsonic section; the thrust reverser system is used for the deceleration of the aircraft before landing; the landing gear system is used for the landing of the aircraft .

[0042] The canard 3 includes a motor-driven shaft 31, a folding link mechanism 32, and a plurality of wings 33; the plurality of wings 33 are connected through the folding link mechanism 32, that is, a plurality of wings 33 are stacked and set , the folding link mechanism ...

Embodiment 2

[0051] A deformable recovery aircraft, including a rocket body, a large-area wing that provides lift and deceleration in the hypersonic section, a pop-up canard that is trimmed in a wide speed range, an air rudder 9, a gas rudder 10, a parachute system for deceleration in the subsonic section, and a reverse Propulsion engine system, landing gear system.

[0052] The rocket body includes a task load compartment and a rocket body. The external task load 1 is located in the task load compartment. The task load compartment is closer to the incoming flow direction than the rocket body. The rocket body 2 is installed with the main engine for the ascent section of the aircraft. The flight control is controlled by The air rudder 9 and the gas rudder 10 are jointly realized. Described wing is made up of side strip wing 5, main wing 6 and winglet 7, is used for providing the lift in the gliding process of flight test and the resistance in the deceleration process, simultaneously side st...

Embodiment 3

[0063] A recovery method for a deformable recovery aircraft, using the deformable recovery aircraft described in Embodiment 1 or Embodiment 2, comprising the following steps:

[0064] Step 1. By increasing the angle of attack of the deformable recovery aircraft, the flight speed and altitude of the deformable recovery aircraft are reduced;

[0065] Step 2. When the flight speed of the deformable recovery aircraft does not exceed the first preset speed and the flight altitude does not exceed the first preset height, the canards 3 are ejected to reduce the angle of attack of the deformable recovery aircraft and lower the deformable recovery aircraft. The flight speed and flight altitude; in the present embodiment, the first preset speed is Mach number 2, and the first preset altitude is 25km;

[0066] Step 3. When the flight speed of the deformable recovery aircraft does not exceed the second preset speed and the flight altitude does not exceed the second preset height, open the...

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Abstract

The invention discloses an air vehicle capable of achieving transformation recycling and a recycling method, and belongs to the fields of rocket overall design technologies and reusability technologies. The air vehicle capable of achieving transformation recycling comprises a rocket body, a large-area wing used for providing lifting force and achieving high supersonic speed section decelerating, retractable canards for wide speed range trimming, a parachute system for subsonic speed section decelerating, a reverse thrust engine system for decelerating before landing and an undercarriage systemfor landing. The air vehicle capable of achieving transformation recycling can adapt to the whole-course flying working condition from the high supersonic speed stage to the subsonic speed stage, nomain power is consumed in the decelerating process, and the landing environment adaptability is higher in the recycling process. Compared with a wing transformation scheme, pressure center configuration of the low supersonic speed stage is completed by adopting the pop-up canards, a transformation mechanism is simple, power dissipation is low, and the effects are significant; and compared with a vertical recycling scheme, lateral wind disturbance can be resisted better in a horizontal recycling process.

Description

technical field [0001] The invention relates to a deformable recovery aircraft and a recovery method, which belong to the field of rocket overall design technology and reusable technology. Background technique [0002] In the design of reusable rockets, two key issues need to be considered. One is that the speed range of the rocket recovery section has a large span, resulting in a large change in the position of the center of pressure, which puts high demands on the full-process control capability. Generally, a deformed layout is used to Realize that the current deformation layout is mainly used for sub-transonic aircraft, such as the Russian Tu-22M bomber with variable-sweep wings, and the American AD-1 with rotary wings to achieve high and low speed trim. The deformation mechanism and structural quality of this method are large, and the deformation speed is slow due to the large movable surface. At the same time, thermal protection at higher speeds is not considered, and t...

Claims

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Application Information

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IPC IPC(8): B64G1/62B64C25/66B64C25/58B64C25/20B64D17/54B64D17/38F42B15/00F42B10/58
CPCB64G1/62B64C25/66B64C25/58B64C25/20B64D17/54B64D17/386F42B15/00F42B10/58
Inventor 不公告发明人
Owner 北京凌空天行科技有限责任公司
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