CN109515763B - Separation mechanism and aircraft separation method - Google Patents
Separation mechanism and aircraft separation method Download PDFInfo
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- CN109515763B CN109515763B CN201811341723.2A CN201811341723A CN109515763B CN 109515763 B CN109515763 B CN 109515763B CN 201811341723 A CN201811341723 A CN 201811341723A CN 109515763 B CN109515763 B CN 109515763B
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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
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
Abstract
A separation mechanism is characterized in that a second-level aircraft is installed on a first-level aircraft through the separation mechanism to form a combination body, and the separation mechanism comprises a first connecting structure (1), a second connecting structure (2) and a separation flap (3); one end of the first connecting structure (1) is connected with the primary aircraft, and the other end of the first connecting structure is detachably connected with the head of the secondary aircraft; one end of the second connecting structure (2) is connected with the primary aircraft, and the other end of the second connecting structure is detachably connected with the tail of the secondary aircraft; the separating flap (3) is arranged on the primary aircraft in a foldable manner, and the separating flap (3) is positioned between the mass center of the primary aircraft and the head of the primary aircraft; when the secondary aircraft is mounted on the primary aircraft by the separating mechanism, the separating flap (3) is located between the centre of mass of the secondary aircraft and the head of the secondary aircraft. The invention realizes the separation of two stages of aircrafts by means of aerodynamic force, and the separation mechanism has light weight and simple structure.
Description
Technical Field
The invention relates to a separation mechanism and an aircraft separation method, and belongs to the technical field of multi-body separation of aerospace aircrafts.
Background
In the foreseeable future, rapid and cheap orbital delivery schemes will have great development potential in many fields such as military, civil and commercial satellite launching, and countries and regions such as the united states, europe, russia, the day, etc. strive to develop low-cost delivery vehicles, and aerospace vehicles are receiving much attention under the background. The general aerospace craft can be divided into a single-stage orbit entering mode, a two-stage orbit entering mode, a multi-stage orbit entering mode and the like, and various orbit entering modes have advantages and disadvantages.
According to the layout form, the aerospace vehicles are mainly divided into two types, one type adopts a parallel layout similar to a space shuttle, and the other type adopts a series layout when a traditional rocket is used for launching small loads, as shown in figure 1. The separation schemes corresponding to the two layouts are different. The series connection separation scheme mainly relates to the separation problem between a front body and a rear body similar to the traditional rocket, the separation mode is a mode which is mostly adopted in the separation process of the conventional rocket, and the design, the separation technology and the corresponding research method of the corresponding separation scheme are mature.
When the parallel arrangement is adopted, the separation part and the main body are often separated by virtue of a reverse thrust engine or an actuator for the first-stage and second-stage interstage separation, for example, the solid rocket boosters of American space shuttles and SLS heavy carrier rockets and the like adopt the separation scheme, and the separation engines arranged at the nose cone part and the tail skirt part of the solid rocket booster work to push the solid rocket booster to be far away from the core stage during separation.
However, in the case of parallel interstage separation of aerospace vehicles, there may be difficulties in relying on conventional thrust reversers or rams as the separation driving force. For example, "sanger II" proposed by formerly siede is a typical two-stage orbital aerospace vehicle with a characteristic length of one stage of about 50m and a weight of about 200 tons at separation; the secondary characteristic length is about 30m and the weight at separation is about 50 tons. The separation conditions were a height of 30km, a Mach number of 6, and an incoming flow pressure of about 30 kpa. The weight and the size of the separation are equivalent to those of the separation of the SRB of the space shuttle, and the separation is a typical problem of the interstage separation with large mass ratio. However, the separation height of the SRB of the space shuttle is 45km, and the maximum separation dynamic pressure is only 2.6kpa, which is one magnitude smaller than the separation dynamic pressure of the Sanger II. The SRB of the space shuttle is a regular cylinder, and the aerodynamic characteristics and the aerodynamic problems under interference are simple; the first stage and the second stage of the two-stage in-orbit aerospace craft adopting the parallel layout are both typical lifting body layouts, and the gravity of the combined body is mainly balanced by the aerodynamic lifting force applied to the combined body during separation, so that the influence of aerodynamic factors is greater during the separation process, and important consideration is needed. In addition, by adopting a separation rocket scheme similar to the separation process of the SRB of the space shuttle, high-temperature gas sprayed by the separation rocket can damage the primary and secondary heat-proof layers, and the jet flow wake can obviously change the streaming flow fields of the primary and secondary aircrafts, so that the control difficulty can be improved.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the defects of the prior art are overcome, the separation mechanism and the aircraft separation method are provided, the pitching characteristics of the two aircrafts are changed by utilizing the pneumatic control surface, and then the rapid separation is realized. According to the method, the separation flap is arranged on the back of the primary aircraft, and the folding state of the separation flap does not change the aerodynamic shape of the primary aircraft and the combination; controlling the folding angle of the flap in real time according to the separation process at the initial separation stage, trying to realize the head lowering of a first-stage aircraft and the head raising of a second-stage aircraft, and realizing the rapid and safe separation; when the second-level aircraft and the first-level aircraft are separated by a certain distance, the second-level aircraft and the first-level aircraft return to a folded state, and the first-level aircraft is enabled to return to the ground in a better pneumatic shape.
The purpose of the invention is realized by the following technical scheme:
a separation mechanism, the second-level aircraft is installed on the first-level aircraft through the separation mechanism and then forms a combination body, the separation mechanism comprises a first connection structure, a second connection structure and a separation flap;
one end of the first connecting structure is connected with the primary aircraft, and the other end of the first connecting structure is detachably connected with the head of the secondary aircraft; one end of the second connecting structure is connected with the primary aircraft, and the other end of the second connecting structure is detachably connected with the tail of the secondary aircraft; the separating flap is arranged on the primary aircraft in a foldable mode and is positioned between the mass center of the primary aircraft and the head of the primary aircraft; when the secondary aircraft is mounted on the primary aircraft by the separating mechanism, the separating flap is located between the center of mass of the secondary aircraft and the head of the secondary aircraft.
In the separating mechanism, the separating flap is plate-shaped, one end of the separating flap is connected with the primary aircraft through the rotatable device, and the other end of the separating flap is a free end.
In the separating mechanism, the ratio of the width of the separating flap to the width of the secondary aircraft is 0.8-1.2.
The aircraft separation method is realized by adopting a separation mechanism, and a second-level aircraft is arranged on a first-level aircraft through the separation mechanism to form a combined body, and comprises the following steps:
step one, adjusting the attack angle of the combination body to be a zero attack angle or a negative attack angle; then the separating flap of the separating mechanism is unfolded;
after first preset time, separating a first connecting structure of the separating mechanism from the secondary aircraft;
and step three, after the included angle between the body axis system of the secondary aircraft and the body axis system of the primary aircraft reaches a preset angle, separating the second connecting structure of the separating mechanism from the secondary aircraft.
In the aircraft separation method, after the third step, after a second preset time, the separation flap is folded.
In the aircraft separation method, the preset angle in the third step is 8-20 degrees.
In the aircraft separation method, the first preset time in the step two is 0.5 s-5 s.
In the aircraft separation method, the second preset time is 2-8 s.
According to the aircraft separation method, the separation flap is plate-shaped, one end of the separation flap is connected with the primary aircraft through the rotatable device, and the other end of the separation flap is a free end.
In the aircraft separation method, the ratio of the width of the separation flap to the width of the secondary aircraft is 0.8-1.2.
Compared with the prior art, the invention has the following beneficial effects:
(1) by adopting the two-stage orbit entering separation scheme, the supersonic speed and hypersonic speed parallel connection interstage separation of the large two-stage orbit entering aerospace craft can be effectively realized;
(2) the two-stage orbit-entering separation scheme of the invention realizes the separation of the two-stage aircrafts by means of aerodynamic force, and the separation mechanism has light weight and simple structure and can effectively reduce the quality and the complexity of the separation mechanism;
(3) by adopting the two-stage in-orbit separation scheme, the problem of insufficient thrust when a large aircraft is separated by adopting a thrust device is effectively solved; meanwhile, separation is realized by means of aerodynamic force, and the shape and the position of the shock wave are controlled by adjusting the angle and the position of the separation flap, so that separation of the two-stage aircraft can be effectively realized, the posture of the two-stage aircraft is adjusted, and conditions are provided for the two-stage aircraft to execute the next task.
Drawings
FIG. 1 is a schematic diagram of a series separation in the prior art;
FIG. 2 is a schematic view of the components of the detachment mechanism provided by the present invention;
FIG. 3 is a schematic view of the high pressure zone of the separation process provided by the present invention;
FIG. 4 is a schematic diagram of the separation method provided by 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 separating aircraft is realized by adopting a separating mechanism, and a secondary aircraft is arranged on a wing aircraft through the separating mechanism to form a combined body. The separating mechanism comprises a first connecting structure 1, a second connecting structure 2 and a separating flap 3; one end of the first connecting structure 1 is connected with the primary aircraft, and the other end of the first connecting structure is detachably connected with the head of the secondary aircraft; one end of the second connecting structure 2 is connected with the first-stage aircraft, and the other end of the second connecting structure is detachably connected with the tail of the second-stage aircraft; the separating flap 3 is arranged on the primary aircraft in a foldable manner, and the separating flap 3 is positioned between the mass center of the primary aircraft and the head of the primary aircraft; when the secondary aircraft is mounted on the primary aircraft by the separating mechanism, the separating flap 3 is located between the centre of mass of the secondary aircraft and the head of the secondary aircraft.
The separating flap 3 is plate-shaped, one end of the separating flap 3 is connected with the first-level aircraft through a rotatable device, and the other end of the separating flap 3 is a free end. The ratio of the width of the separating flap 3 to the width of the secondary aircraft is 0.8-1.2. It should be noted that the separation flap 3 is not limited to a plate shape, but may also be of another shape or configuration, as long as it is possible to achieve a blocking of the air flow between the secondary aircraft and the primary aircraft, creating a high-pressure zone.
An aircraft separation method comprising the steps of:
step one, adjusting the attack angle of the combination body to be a zero attack angle or a negative attack angle; then the separating flap (3) of the separating mechanism is unfolded;
step two, after a first preset time, wherein the first preset time is 0.5-5 s, and the first connecting structure 1 of the separating mechanism is separated from the secondary aircraft;
step three, after an included angle between a body axis system of the secondary aircraft and a body axis system of the primary aircraft reaches a preset angle, the preset angle is 8-20 degrees, and a second connecting structure 2 of the separating mechanism is separated from the secondary aircraft;
and step four, after a second preset time, wherein the second preset time is 2-8 s, and the separating flap 3 is folded.
Example (b):
as shown in FIG. 2, the two-stage track-entering aerospace vehicle parallel connection interstage separation scheme mainly relates to a first connecting structure 1, a second connecting structure 2, a separation flap 3, a first-stage aircraft and a second-stage aircraft of the two-stage aircraft. The primary aircraft and the secondary aircraft are connected through the first connecting structure 1 and the second connecting structure 2, the separating flap 3 is located on the back of the primary aircraft and is in a folded state when not separated, and the aerodynamic shape of the primary aircraft and the secondary aircraft cannot be changed.
When the aerospace combination vehicle enters a specified separation state (the flight mach number Ma is 6, and the flight altitude H is 30km), the two-stage orbital vehicle starts a separation procedure. Firstly, adjusting the rudder deflection to change the attack angle of the combined aircraft into a zero attack angle or a negative attack angle; after the attitude of the aircraft is adjusted, the separation flap 3 positioned on the upper edge of the back of the first-level aircraft deflects, and after a specified deflection angle is reached, a high-pressure area is formed between the front edge of the separation flap 3 and the first-level and second-level aircraft. About 1s after the separation flap 3 reaches the designated deflection angle, the first connecting mechanism 1 for connecting the two-stage aircraft is disconnected and separated, the first-stage aircraft and the second-stage aircraft start to be separated under the action of pneumatic force, and when the included angle between the first-stage aircraft and the second-stage aircraft reaches the designated separation angle, the connecting mechanism 2 is disconnected and separated. The second coupling mechanism 2 is disconnected and separated for about 4s, at the moment, the first-level aircraft and the second-level aircraft reach a certain separation distance, the separation flap 3 returns to the folding state, and the good aerodynamic appearance of the first-level aircraft is guaranteed.
The separating wing flap 3 is positioned on the upper edge of the back of the first-level aircraft, a certain distance is reserved between the separating wing flap 3 and the lower edge of the bottom of the second-level aircraft, the separating wing flap is obliquely arranged, and the position and the angle of the separating wing flap can be adjusted.
The width of the separation flap 3 is close to the width of the fuselage of the second-level aircraft, so that a strong airflow retardation effect can be formed to form a high-pressure area when the aircraft is separated, and the parallel interstage separation of the aircraft is realized.
When the two-stage track entering aircraft is divided into the parallel stages, the separation between the stages is realized by means of aerodynamic force through adjusting the angle and the position of the separation flap so as to form a high-pressure area between the leading edge of the separation flap 3 and the first-stage aircraft and the second-stage aircraft, and the high-pressure area is shown in figure 3, wherein the first coupling structure 1 and the second coupling structure 2 are not shown in figure 3.
The separation flap 3 is located in front of the centre of mass of the primary and secondary aircraft. By adjusting the position and angle of the separating flap 3, a high-pressure zone is formed in front of the separating flap 3 between the upper edge of the back of the primary aircraft and the lower edge of the bottom of the secondary aircraft. Because the separating flap 3 is positioned in front of the mass center of the aircraft, the action of the high-pressure area enables the first-level aircraft to generate a low-head moment and the second-level aircraft to generate a head-up moment. The principle schematic diagram of the decoupling is shown in fig. 4, wherein the first coupling structure 1 and the second coupling structure 2 are not shown in fig. 4.
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 (10)
1. The utility model provides a separating mechanism, second grade aircraft constitute the assembly after installing on the first order aircraft through this separating mechanism, its characterized in that: the separating mechanism comprises a first connecting structure (1), a second connecting structure (2) and a separating flap (3);
one end of the first connecting structure (1) is connected with the primary aircraft, and the other end of the first connecting structure is detachably connected with the head of the secondary aircraft; one end of the second connecting structure (2) is connected with the primary aircraft, and the other end of the second connecting structure is detachably connected with the tail of the secondary aircraft; the separating flap (3) is arranged on the primary aircraft in a foldable manner, and the separating flap (3) is positioned between the mass center of the primary aircraft and the head of the primary aircraft; when the secondary aircraft is installed on the primary aircraft through the separation mechanism, the separation flap (3) is positioned between the mass center of the secondary aircraft and the head of the secondary aircraft;
before the first-stage aircraft and the second-stage aircraft are separated, the separating flap (3) is in a folded state; when the primary aircraft is separated from the secondary aircraft, the separating flap (3) is unfolded, and a high-pressure area is formed between the leading edge of the separating flap (3) and the primary aircraft and the secondary aircraft.
2. A release mechanism according to claim 1, wherein: the separating flap (3) is plate-shaped, one end of the separating flap (3) is connected with the primary aircraft through a rotatable device, and the other end of the separating flap (3) is a free end.
3. A release mechanism according to claim 1, wherein: the ratio of the width of the separating flap (3) to the width of the secondary aircraft is 0.8-1.2.
4. An aircraft separation method, characterized by: the separation mechanism of claim 1, comprising the steps of:
step one, adjusting the attack angle of the combination body to be a zero attack angle or a negative attack angle; then the separating flap (3) of the separating mechanism is unfolded;
after a first preset time, separating a first connecting structure (1) of the separating mechanism from the secondary aircraft;
and step three, after the included angle between the body axis system of the secondary aircraft and the body axis system of the primary aircraft reaches a preset angle, separating the second connecting structure (2) of the separating mechanism from the secondary aircraft.
5. An aircraft separation method according to claim 4, characterized in that: after said step three, after a second predetermined time, the flap (3) is folded.
6. An aircraft separation method according to claim 4, characterized in that: the preset angle in the third step is 8-20 degrees.
7. An aircraft separation method according to claim 4, characterized in that: the first preset time in the second step is 0.5 s-5 s.
8. An aircraft separation method according to claim 5, characterized in that: the second preset time is 2 s-8 s.
9. An aircraft separation method according to claim 4, characterized in that: the separating flap (3) is plate-shaped, one end of the separating flap (3) is connected with the primary aircraft through a rotatable device, and the other end of the separating flap (3) is a free end.
10. An aircraft separation method according to claim 4, characterized in that: the ratio of the width of the separating flap (3) to the width of the secondary aircraft is 0.8-1.2.
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| CN109823527A (en) * | 2019-03-06 | 2019-05-31 | 中南大学 | Face symmetrical expression takes off vertically double enter the orbit flight system and Vertical Launch takeoff methods |
| CN110510149A (en) * | 2019-08-23 | 2019-11-29 | 中国航天空气动力技术研究院 | A kind of Horizontal Take-off and Landing two-stage, which is entered the orbit, reuses sky and space plane layout |
| CN112874815A (en) * | 2021-03-24 | 2021-06-01 | 北京空天技术研究所 | Passive parallel separation design method for two-stage aircraft |
| CN113247277B (en) * | 2021-06-30 | 2022-05-24 | 中国人民解放军国防科技大学 | Hypersonic air inlet duct conformal fairing scheme with folding wings |
| CN114291292B (en) * | 2022-01-10 | 2023-11-03 | 北京空天技术研究所 | Design method for parallel separation of aerospace vehicles |
| CN114537674B (en) * | 2022-01-25 | 2024-02-13 | 北京理工大学 | Separable aircraft, control method and electronic equipment |
| CN114261538B (en) * | 2022-02-25 | 2022-05-03 | 中国科学院力学研究所 | Parallel double-waverider two-stage in-orbit aircraft horizontal interstage separation design method |
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| US5141175A (en) * | 1991-03-22 | 1992-08-25 | Harris Gordon L | Air launched munition range extension system and method |
| CN1030758C (en) * | 1993-01-13 | 1996-01-24 | 奥比泰尔科技公司 | Rocket-poweren, air-deployed, lift-assisted boosted vehicle for orbital, supraorbital and suborbital flight |
| CN1066407C (en) * | 1996-02-16 | 2001-05-30 | 蔡耀华 | Space round trip flying vehicle |
| CN106288980B (en) * | 2016-08-09 | 2018-04-27 | 西北工业大学 | A kind of application method of the Control System for Reusable Launch Vehicle based on RBCC power |
| CN106123709A (en) * | 2016-08-16 | 2016-11-16 | 东莞前沿技术研究院 | Flight Vehicle Stage Separation device |
| CN106927048A (en) * | 2017-03-10 | 2017-07-07 | 佛山市神风航空科技有限公司 | A kind of combined type aerocraft system and its landing mode |
| CN108657432A (en) * | 2018-04-13 | 2018-10-16 | 佛山卿影科技有限公司 | A kind of mode that rocket takes off and device |
| CN108680330B (en) * | 2018-08-06 | 2020-05-12 | 中国航天空气动力技术研究院 | Full-free flight wind tunnel test device with power parallel interstage separation and method |
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