阅读说明：本技术 一种用于飞行器回收的降落伞系统、降落回收方法 (Parachute system for aircraft recovery and parachute recovery method ) 是由 不公告发明人 于 2019-09-25 设计创作，主要内容包括：一种用于飞行器回收的降落伞系统、降落回收方法,属于火箭回收技术领域。减速伞开伞时吊点位于飞行器质心后方,利于保持飞行器姿态的稳定,由于主伞尺寸较大,与主伞舱壁面紧密接触,若主伞包出舱角度较小,主伞包极易卡在主伞舱内造成主伞开伞失败,故在主伞包出舱前瞬时将减速伞吊点转换至飞行器前方,将飞行器拉升抬头,为主伞包出舱创造了一定的角度,实现主伞包的顺利出舱；主伞开伞时开伞力较大,若采用单一吊点结构飞行器极易发生翻滚,与主伞吊带发生缠绕,造成开伞失败,且难以实现水平回收,将主伞前吊点支座固定在质心前方,两个后吊点支座固定在质心后方,既能避免主伞开伞时飞行器发生翻转缠绕,又能实现飞行器的水平回收。(A parachute system and a parachute recovery method for aircraft recovery belong to the technical field of rocket recovery. When the parachute is opened, the hanging point is positioned behind the mass center of the aircraft, the stability of the attitude of the aircraft is favorably kept, and as the main parachute is large in size and is in close contact with the wall surface of the main parachute cabin, if the cabin outlet angle of the main parachute bag is small, the main parachute bag is extremely easy to clamp in the main parachute cabin to cause the failure of the parachute opening of the main parachute, the hanging point of the parachute is instantly converted to the front of the aircraft before the cabin outlet of the main parachute bag, the aircraft is lifted and raised, a certain angle is created for the cabin outlet of the main parachute bag, and the smooth cabin outlet of the main parachute bag is realized; the power of opening when main umbrella is opened is great, if adopt single hoisting point structure aircraft very easily to take place to roll, takes place the winding with main umbrella suspender, causes the failure of opening the umbrella, and is difficult to realize the level and retrieves, fixes the preceding hoisting point support of main umbrella in barycenter the place ahead, and two back hoisting point supports are fixed at the barycenter rear, and the aircraft takes place to overturn the winding when can avoiding main umbrella to open the umbrella, can realize the level of aircraft again and retrieve.)

1. A parachute system for aircraft recovery is characterized by comprising a speed-reducing parachute, a speed-reducing parachute sling, a speed-reducing parachute front hanging point support, a speed-reducing parachute rear hanging point support, a conversion sling, a speed-reducing parachute rear hanging point unlocking bolt, a main parachute sling, a main parachute front hanging point support, a main parachute rear hanging point support, a main parachute hatch cover and a main parachute hatch cover unlocking bolt;

the front suspension point support of the speed reducing parachute is arranged on the main parachute bay cover and is positioned between the mass center of the aircraft and the head of the aircraft; the rear suspension point support of the speed reducing parachute is arranged between the mass center of the aircraft and the tail of the aircraft; two ends of the drag parachute sling are respectively connected with the drag parachute and the drag parachute rear hanging point support; two ends of the conversion hanging strip are respectively connected with the front hanging point support and the rear hanging point support of the speed reducing umbrella; the deceleration parachute rear hanging point unlocking bolt is used for separating the deceleration parachute rear hanging point support from the aircraft;

the main umbrella front hanging point support is arranged between the mass center of the aircraft and the head of the aircraft; the main umbrella rear hanging point support is arranged between the mass center of the aircraft and the tail of the aircraft; the main canopy is located between the center of mass of the aircraft and the head of the aircraft; the main canopy unlocking bolt is used for separating the main canopy from the aircraft; the main umbrella hanging strip is used for connecting the main umbrella with a front hanging point support of the main umbrella and connecting the main umbrella with a rear hanging point support of the main umbrella.

2. A parachute system for aircraft recovery according to claim 1, wherein said main parachute rear suspension point support comprises a main parachute rear suspension point first support, a main parachute rear suspension point second support; the first support of the main umbrella rear hanging point and the second support of the main umbrella rear hanging point are positioned in the same cross section of the aircraft.

3. A parachute system for aircraft recovery according to claim 1, wherein said main canopy is connected to a main parachute, and wherein the main canopy pulls the main parachute out when said main canopy is detached from the aircraft.

4. A parachute system for aircraft recovery according to claim 1, further comprising a drogue hatch, a drogue hatch unlocking bolt, a shooting pot; the speed reducing umbrella cabin cover is arranged on the surface of the aircraft and used for packaging the speed reducing umbrella in the aircraft; the deceleration parachute cabin cover unlocking bolt is used for separating the deceleration parachute cabin cover from the aircraft; the ejection barrel is used for ejecting the speed reducing umbrella from the aircraft.

5. An aircraft landing recovery method, characterized in that the parachute system for aircraft recovery of any one of claims 1 to 4 is used, comprising the steps of:

s1, taking the drogue out of the cabin, and dragging the drogue rear hanging point support to decelerate the aircraft through the drogue sling; then, the process proceeds to S2;

s2, when the aircraft decelerates to the preset parachute opening speed of the main parachute, separating the rear parachute hanging point support from the aircraft by the rear parachute hanging point unlocking bolt, and decelerating the aircraft by pulling the front parachute hanging point support through the parachute hanging strip, the rear parachute hanging point support and the conversion hanging strip in sequence by the parachute hanging strip; then, the process proceeds to S3;

s3, when the angle of attack of the aircraft is more than or equal to 30-45 degrees or the included angle between the conversion sling and the axis of the aircraft is more than or equal to 30-45 degrees, the main canopy cover is separated from the aircraft by the unlocking bolt of the main canopy cover; and then the main umbrella cabin cover pulls out the main umbrella, and the main umbrella pulls the front hanging point support and the rear hanging point support of the main umbrella through the main umbrella hanging strip to decelerate the aircraft, so that the aircraft recovery is completed.

6. An aircraft landing recovery method according to claim 5, wherein said aircraft is horizontal after recovery.

7. An aircraft landing recovery method according to claim 5, wherein the parachute rear suspension point unlocking bolt and or the main parachute bay cover unlocking bolt is an explosive bolt.

8. A transformable recovery aircraft, characterized in that a parachute system according to any one of claims 1 to 4 is used; the rocket further comprises a rocket body, canard wings (3), wings, air rudders (9), gas rudders (10), a reverse thrust engine system and an undercarriage system;

the duck wings (3) are telescopically arranged on two sides of the rocket body; the wings are arranged on two sides of the rocket body; the air rudder (9) and the gas rudder (10) are both arranged on the rocket body and are both used for flight control;

the parachute system is used for decelerating the aircraft in a subsonic velocity section; the thrust reverser system is used for decelerating the aircraft before landing; the landing gear system is used for landing the aircraft.

9. A transformable recovery aircraft according to claim 8, characterized in that the canard (3) comprises a motor-driven shaft (31), a folding linkage (32), a plurality of wings (33);

the plurality of wings (33) are connected by the folding linkage (32); the motor drive rotating shaft (31) is used for driving the plurality of wings (33) to expand or contract.

Technical Field

The invention relates to a parachute system for aircraft recovery and a parachute recovery method, and belongs to the technical field of aircraft recovery.

Background

At present, most of space flight vehicles such as rockets and the like are disposable, the cost is high, the launching period is long, and the recovery of the flight vehicles is an inevitable way for solving the problems of high cost and long period. Currently, the following ways are mainly used for realizing aircraft recovery: the space X company falcon No. 9 rocket performs reverse thrust deceleration and deploys landing legs to land stably, the recovery technology has high requirements on landing attitude control, greatly depends on the development of the liquid engine technology, and has high technical difficulty and high cost; the solid booster of the European Alian-5 carrier rocket is recovered through parachuting, the lifting point of the solid booster is positioned at the head of the booster and falls on water in a vertical posture, the landing impact of the recovered posture rocket is large, and the damage to the structures of space vehicles such as rockets and the like is easily caused.

Disclosure of Invention

The technical problem to be solved by the invention is as follows: the parachute system and the parachute recovery method for aircraft recovery are overcome, a hanging point is located behind the mass center of an aircraft when a parachute is opened, stability of the attitude of the aircraft is kept favorably, the main parachute is large in size and is in close contact with the wall surface of a main parachute cabin, if the cabin outlet angle of a main parachute bag is small, the main parachute bag is extremely easy to clamp in the main parachute cabin to cause failure of parachute opening of the main parachute, the parachute hanging point is instantly converted to the front of the aircraft before the cabin outlet of the main parachute bag, the aircraft is lifted, a certain angle is created for the cabin outlet of the main parachute bag, and smooth cabin outlet of the main parachute bag is achieved; the power of opening when main umbrella is opened is great, if adopt single hoisting point structure aircraft very easily to take place to roll, takes place the winding with main umbrella suspender, causes the failure of opening the umbrella, and is difficult to realize the level and retrieves, fixes the preceding hoisting point support of main umbrella in barycenter the place ahead, and two back hoisting point supports are fixed at the barycenter rear, and the aircraft takes place to overturn the winding when can avoiding main umbrella to open the umbrella, can realize the level of aircraft again and retrieve.

The purpose of the invention is realized by the following technical scheme:

a parachute system for aircraft recovery comprises a speed-reducing parachute, a speed-reducing parachute sling, a speed-reducing parachute front hanging point support, a speed-reducing parachute rear hanging point support, a conversion sling, a speed-reducing parachute rear hanging point unlocking bolt, a main parachute sling, a main parachute front hanging point support, a main parachute rear hanging point support, a main parachute hatch cover and a main parachute hatch cover unlocking bolt;

the front suspension point support of the speed reducing parachute is arranged on the main parachute bay cover and is positioned between the mass center of the aircraft and the head of the aircraft; the rear suspension point support of the speed reducing parachute is arranged between the mass center of the aircraft and the tail of the aircraft; two ends of the drag parachute sling are respectively connected with the drag parachute and the drag parachute rear hanging point support; two ends of the conversion hanging strip are respectively connected with the front hanging point support and the rear hanging point support of the speed reducing umbrella; the deceleration parachute rear hanging point unlocking bolt is used for separating the deceleration parachute rear hanging point support from the aircraft;

the main umbrella front hanging point support is arranged between the mass center of the aircraft and the head of the aircraft; the main umbrella rear hanging point support is arranged between the mass center of the aircraft and the tail of the aircraft; the main canopy is located between the center of mass of the aircraft and the head of the aircraft; the main canopy unlocking bolt is used for separating the main canopy from the aircraft; the main umbrella hanging strip is used for connecting the main umbrella with a front hanging point support of the main umbrella and connecting the main umbrella with a rear hanging point support of the main umbrella.

Preferably, the main umbrella rear hanging point support comprises a main umbrella rear hanging point first support and a main umbrella rear hanging point second support; the first support of the main umbrella rear hanging point and the second support of the main umbrella rear hanging point are positioned in the same cross section of the aircraft.

Preferably, the main parachute hatch cover is connected with the main parachute, and the main parachute is pulled out by the main parachute hatch cover after the main parachute hatch cover is separated from the aircraft.

Preferably, the parachute cabin cover unlocking bolt and the ejection barrel are further included; the speed reducing umbrella cabin cover is arranged on the surface of the aircraft and used for packaging the speed reducing umbrella in the aircraft; the deceleration parachute cabin cover unlocking bolt is used for separating the deceleration parachute cabin cover from the aircraft; the ejection barrel is used for ejecting the speed reducing umbrella from the aircraft.

The aircraft landing recovery method adopting the parachute system for aircraft recovery comprises the following steps:

s1, taking the drogue out of the cabin, and dragging the drogue rear hanging point support to decelerate the aircraft through the drogue sling; then, the process proceeds to S2;

s2, when the aircraft decelerates to the preset parachute opening speed of the main parachute, separating the rear parachute hanging point support from the aircraft by the rear parachute hanging point unlocking bolt, and decelerating the aircraft by pulling the front parachute hanging point support through the parachute hanging strip, the rear parachute hanging point support and the conversion hanging strip in sequence by the parachute hanging strip; then, the process proceeds to S3;

s3, when the angle of attack of the aircraft is more than or equal to 30-45 degrees or the included angle between the conversion sling and the axis of the aircraft is more than or equal to 30-45 degrees, the main canopy cover is separated from the aircraft by the unlocking bolt of the main canopy cover; and then the main umbrella cabin cover pulls out the main umbrella, and the main umbrella pulls the front hanging point support and the rear hanging point support of the main umbrella through the main umbrella hanging strip to decelerate the aircraft, so that the aircraft recovery is completed.

Preferably, the aircraft is in a horizontal state after recovery.

Preferably, the parachute rear suspension point unlocking bolt and/or the main parachute hatch cover unlocking bolt is an explosive bolt.

A deformable recovery aircraft adopts the parachute system; the rocket further comprises a rocket body, canard wings, air rudders, gas rudders, a reverse thrust engine system and an undercarriage system;

the duck wings are arranged on two sides of the rocket body in a telescopic manner; the wings are arranged on two sides of the rocket body; the air rudder and the gas rudder are both arranged on the rocket body and are both used for flight control;

the parachute system is used for decelerating the aircraft in a subsonic velocity section; the thrust reverser system is used for decelerating the aircraft before landing; the landing gear system is used for landing the aircraft.

Preferably, the duck wing comprises a motor driving rotating shaft, a folding connecting rod mechanism and a plurality of wing leaves; the plurality of wings are connected through the folding link mechanism; the motor drive rotating shaft is used for driving the plurality of wings to expand or contract.

Compared with the prior art, the invention has the following beneficial effects:

(1) according to the parachute system, through the layout and design of the parachute hanging points, the mode of converting front and rear hanging points is adopted, the center-of-mass-crossing multi-hanging-point structural layout is utilized, the horizontal recovery of the aircraft is realized, and the problem of structural damage caused by overlarge landing impact of the aircraft is solved.

(2) The parachute recovery method of the invention utilizes the conversion design of the front and rear hanging points of the speed-reducing parachute to increase the cabin outlet angle of the main parachute bag, so as to realize the smooth cabin outlet of the main parachute bag, the hanging points are positioned behind the mass center of the aircraft when the speed-reducing parachute is opened, thus being beneficial to keeping the attitude of the aircraft stable.

(3) The parachute recovery method solves the problems that the posture of the aircraft is unstable when the main parachute is opened and the aircraft is horizontally recovered by utilizing the design that the main parachute spans the mass center and has multiple hanging points, the parachute opening force of the main parachute is large when the main parachute is opened, the aircraft is easy to roll if a single hanging point structure is adopted, the aircraft is wound with a hanging belt of the main parachute, the parachute opening failure is caused, and the horizontal recovery is difficult to realize, the front hanging point support of the main parachute is fixed in front of the mass center, and the two rear hanging point supports are fixed behind the mass center, so that the aircraft is prevented from being overturned and wound when the main parachute is opened, and the horizontal recovery of.

(4) Compared with a wingless reusable rocket, the deformable recovery aircraft can provide more efficient deceleration capacity and simultaneously can keep the flight stability of the rocket body; compared with the scheme of whole-course power deceleration, the speed is decelerated mainly through the lift-induced resistance of the wings, the main power is not involved, the fuel is saved, the ablation is low, and the safety of the recovery process is stronger; compared with the scheme of wing deformation, the pressure core configuration at the low supersonic speed stage is completed by adopting the ejection canard, the deformation mechanism is simple, the power consumption is low, and the effect is obvious; compared with the scheme of vertical recovery, the high-speed low-resistance characteristic of the elongated body is organically integrated with the low-speed high-lift characteristic of the airplane type layout, so that vertical take-off and horizontal landing are realized, the side wind interference is more resisted in the recovery process, and the adaptability to the landing point environment is stronger.

Drawings

FIG. 1 is a schematic view of a partial configuration of a parachute system of the present invention;

FIG. 2 is a schematic bottom view of the transformable recovery aircraft of the present invention;

FIG. 3 is a schematic view of a modified duck wing;

FIG. 4 is a schematic diagram of a reverse thrust engine system;

FIG. 5 is a schematic view of a nose landing gear system;

FIG. 6 is a schematic diagram of a main landing gear system;

FIG. 7 is a diagram of the effect of deceleration at a hypersonic velocity stage;

fig. 8 is a diagram of the effect of the adjustment of the center of pressure after the duck wing is popped up.

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.

The main technical scheme and design thought of the invention are as follows:

the parachute system comprises a speed-reducing parachute, speed-reducing parachute suspenders, a front suspension point support of the speed-reducing parachute, a rear suspension point support of the speed-reducing parachute, conversion suspenders, rear suspension point unlocking bolts of the speed-reducing parachute, a main parachute, three main parachute suspenders, a front suspension point support of the main parachute, two rear suspension point supports of the main parachute, a cabin cover of the main parachute and unlocking bolts of the cabin cover of the main parachute.

The deceleration umbrella hanging strip is used for connecting the deceleration umbrella and the deceleration umbrella rear hanging point support; the parachute rear hanging point support is positioned behind the mass center of the aircraft and used for fixing the parachute hanging strip and the conversion hanging strip and realizing the connection of the parachute hanging strip and the conversion hanging strip when the parachute hanging point is converted; the front suspension point support of the speed-reducing parachute is positioned in front of the mass center of the aircraft, is arranged on the main parachute bay cover and is used for fixing the conversion hanging strip; the parachute rear hanging point unlocking bolt is used for fixing the parachute rear hanging point support on the aircraft and realizing unlocking separation of the parachute rear hanging point support and the aircraft during parachute hanging point conversion;

the main umbrella hanging strip is used for connecting the main umbrella with the front hanging point and the rear hanging point of the main umbrella of the aircraft; the main umbrella front hanging point support is positioned in front of the mass center of the aircraft and used for fixing one of the main umbrella hanging belts; the main umbrella rear hanging point support is positioned behind the mass center of the aircraft and used for fixing the other two main umbrella hanging belts; the main parachute cabin cover is used for fixing a parachute bag of a main parachute and is connected with the main parachute at the same time, and the main parachute bag is pulled out when the main parachute exits the cabin (namely, when the main parachute exits the cabin, the brake parachute sequentially passes through the brake parachute sling, the brake parachute rear hanging point support, the conversion sling, the brake parachute front hanging point support and the main parachute cabin cover, and the pulling force is transmitted to the main parachute, so that the main parachute is pulled out of the aircraft); the main parachute bay cover unlocking bolt is used for fixing the main parachute bay cover on the aircraft and unlocking and separating the main parachute bay cover when the main parachute exits the aircraft.

The aircraft recovery method applying the parachute system comprises the following steps: after the speed reducing parachute leaves the cabin, the aircraft is decelerated by pulling the rear suspension point support of the speed reducing parachute through the speed reducing parachute sling; when the aircraft decelerates to the preset main umbrella opening speed, the parachute rear hanging point unlocking bolt is ignited to work, the parachute rear hanging point support is unlocked and separated, the parachute rear hanging point support is used for connecting a parachute hanging strip and a conversion hanging strip, a hanging point connected with the parachute is converted to the front of the center of mass from the rear of the center of mass of the aircraft, the parachute jointly pulls the parachute front hanging point support through the parachute hanging strip and the conversion hanging strip to decelerate the aircraft, simultaneously, the aircraft is pulled up and raised, when the conversion hanging strip and the body axis of the aircraft (the whole aircraft is in a plane symmetrical structure, the body of the aircraft is cylindrical) reach a preset angle, the main umbrella cabin cover unlocking bolt is ignited to work, the main umbrella cabin cover is unlocked and separated, the main umbrella cabin cover is used as the conversion hanging strip and fixedly connected with a main umbrella bag, the main umbrella is pulled out by the parachute, the main umbrella is unfolded, the main umbrella hanging point support (one) and the main umbrella rear hanging point support (two) are pulled by the main umbrella hanging strip, the aircraft can be horizontally recovered stably in posture.