阅读说明：本技术 一种可重复使用空天飞行器压心后移的设计方法 (Design method for pressure center backward movement of reusable aerospace vehicle ) 是由 肖光明 唐伟 冯毅 刘磊 魏东 杜雁霞 杨肖峰 于 2019-11-12 设计创作，主要内容包括：本发明公开了一种可重复使用空天飞行器压心后移的设计方法,在空天飞行器机身尾段两侧对称设置一对俯仰稳定板,俯仰稳定板通过舵轴与机身连接,所述俯仰稳定板能够绕舵轴转动,实现俯仰稳定板开启模式和收起模式的转换。采用本发明的一种可重复使用空天飞行器压心后移的设计方法,可将空天飞行器压心后移,并实现不同飞行条件下空天飞行器俯仰稳定性的调节。(The invention discloses a design method for the pressure center backward movement of a reusable aerospace vehicle. By adopting the design method for the pressure center backward movement of the reusable aerospace vehicle, the pressure center of the aerospace vehicle can be backward moved, and the pitching stability of the aerospace vehicle under different flight conditions can be adjusted.)

1. A design method for the pressure center backward movement of a reusable aerospace vehicle is characterized by comprising the following steps: a pair of pitching stabilizing plates are symmetrically arranged on two sides of the tail section of the aircraft body of the aerospace vehicle, the pitching stabilizing plates are connected with the aircraft body through rudder shafts, and the pitching stabilizing plates can rotate around the rudder shafts, so that the switching between the opening mode and the retracting mode of the pitching stabilizing plates is realized.

2. The design method for the pressure center retropulsion of the reusable aerospace vehicle as claimed in claim 1, wherein: and the installation azimuth angle of the rudder shaft is selected according to the flight attack angle of the pitching stabilizing plate in the starting mode.

3. The design method for the pressure center retropulsion of the reusable aerospace vehicle as claimed in claim 1, wherein: the installation azimuth angle of the rudder shaft is 20-30 degrees.

4. The design method for the pressure center retropulsion of the reusable aerospace vehicle as claimed in claim 1, wherein: and in the process of reentry flight of the aerospace vehicle, the flight Mach number is 3-5, and when the flight attack angle is 20 +/-5 degrees, the pitching stabilizing plate is in an opening mode.

5. The design method for the pressure center retropulsion of the reusable aerospace vehicle as claimed in claim 1, wherein: the pitch stabilizer plate is aligned with the aft end of the aerospace vehicle in the stowed mode.

6. The design method for the pressure center retropulsion of the reusable aerospace vehicle as claimed in claim 1, wherein: the pitching stabilizing plate is trapezoidal.

7. The design method for the pressure center retropulsion of the reusable aerospace vehicle as claimed in claim 1, wherein: the pitching stabilizing plate is a right-angle pentagon.

8. The design method for the pressure center retropulsion of the reusable aerospace vehicle as claimed in claim 1, wherein: the basic aerodynamic layout of the aerospace vehicle adopts a method (CST) based on a type function and a shape function to carry out parametric shape generation.

9. The design method for the pressure center retropulsion of the reusable aerospace vehicle of claim 8, wherein: the aerospace craft comprises a head, a fuselage, wings, flaperons, a speed-reducing plate, a tail wing and a body flap; the wings are positioned on two sides of the aircraft body, the flaperons are positioned on the rear edges of the wings, the empennages are positioned at the tail of the aircraft body, the speed reducing plate is positioned between the pair of empennages, and the body flaps are positioned at the rear part of the aerospace aircraft.

10. The design method for the pressure center retropulsion of the reusable aerospace vehicle of claim 9, wherein: the head is designed to be a blunt sphere, the fuselage is designed to be a semicircular and inverted square section, the wings are double triangular wings formed by combining a long and thin edge wing and a short triangular wing, and the flaperon is designed to be a full span.

Technical Field

The invention relates to a design method for pressure center backward movement of a reusable aerospace vehicle, in particular to a design method for enhancing the pitching stability margin of the reusable aerospace vehicle based on a pitching stabilizer plate, and belongs to the technical field of aircrafts.

Background

The reusable aerospace vehicle is a novel aircraft with aviation and aerospace functions, and can flexibly maneuver on the atmosphere and a near-earth orbit according to different task requirements. The reusable aerospace vehicle flies higher and faster than a traditional airplane, is more flexible and reusable than a common spacecraft, can meet the fundamental requirement of entering space quickly and cheaply, and can reach the space in real time in the global range. Therefore, the reusable aerospace vehicle has become a strategic high point of competing for the emphatic right and space advantage of the aerospace countries in the world.

In addition to the retired partially reusable space shuttle, the development of the space shuttle in various countries of the world is still in the research and verification stage, and currently, the research projects mainly include space orbit aircraft X-37B in the united states, trial space shuttle XS-1, skis tower Skylon in the united kingdom, reusable vehicle technology verifier RLV-TD in india, and "tengyun" engineering in china. Among them, the X-37B tester, as the latest and most advanced reentry vehicle in the united states air force, mainly serves to provide a low-risk technology for the reusable spacecraft, and to develop some novel experimental methods and unconventional operational concepts, which have been regarded as a key component for maintaining the future space dominance in the united states. From 2011, X-37B performed a total of 5 orbital missions (all completed, last return in 2019 at 10 and 27 days, and on-orbit operation for 780 days), and planned to perform the 6 th orbital mission in 2019 at 11 months.

For the reusable aerospace vehicle, the special requirements of lift-drag matching, stability-operating matching and the like of a wide airspace and a wide speed range provide important challenges for the aerodynamic layout design of the aerospace vehicle. When an aerospace plane represented by American X-37B flies again in the atmosphere, the flight Mach number range is 0.2 to 25, the attack angle variation range is 5 to 40 degrees, and the pressure center position of the aerospace plane is greatly changed due to the wide flight speed and attitude adjustment, so that the aerospace plane is difficult to simultaneously consider the longitudinal stability of hypersonic speed and sub/transonic speed when the aerodynamic layout of the aerospace plane is designed. In order to ensure the aerodynamic performance and the heat protection requirement of a high-Mach number flight state, the aerodynamic configuration of the aerospace plane mainly adopts the typical wing body assembly layout with a low-aspect-ratio sweepback wing and a V-shaped empennage, the wing is positioned in the middle section of the plane body, and the pitching trim control is carried out by using the body flap of the aerospace plane for reference. Relevant researches show that under the conditions of medium and low Mach number and medium angle flight, the static stability margin may be insufficient even if the air-borne spacecraft is fully optimized under the original aerodynamic layout because the pressure center of the air-borne spacecraft is relatively forward.

Disclosure of Invention

The invention aims to: aiming at the existing problems, the invention provides a design method for the pressure center backward movement of the reusable aerospace vehicle.

The technical scheme adopted by the invention is as follows:

a design method for repeatedly using a pressure center of an aerospace vehicle to move backwards is characterized in that a pair of pitching stabilizing plates are symmetrically arranged on two sides of a tail section of a fuselage of the aerospace vehicle, the pitching stabilizing plates are connected with the fuselage through rudder shafts, and the pitching stabilizing plates can rotate around the rudder shafts, so that the switching of an opening mode and a retracting mode of the pitching stabilizing plates is realized.

In the scheme, the pitching stabilizing plate rotates around the rudder shaft, and when the pitching stabilizing plate is tightly attached to the side edge of the aircraft body, the pitching stabilizing plate is in a retraction mode, so that the basic aerodynamic layout of the aerospace aircraft can be maintained; when the pitching stabilizing plate is turned outwards by 90 degrees around the rudder axis and is unfolded into a movable part similar to a stable airfoil surface, the opening mode is adopted, and because the pitching stabilizing plate is vertical to the incoming flow, the generated resistance can be completely used for forming low head moment so as to move the pressure center position backwards to the maximum extent, thereby improving the pitching static stability margin of the aerospace vehicle.

Preferably, the installation azimuth angle of the rudder shaft is selected according to the flight attack angle of the pitching stabilizing plate in the opening mode.

Preferably, the installation azimuth angle of the rudder shaft is 20-30 degrees.

Preferably, when the aerospace vehicle reenters the flight process, the flight Mach number is 3-5, and the flight attack angle is 20 +/-5 degrees, the pitching stabilizing plate is in an opening mode; and under other flight states, the pitching stabilizing plate is in a retraction mode.

The pitching stabilizing plate is supported by the steering engine arranged in the fuselage and is in an opening mode, and the pitching stabilizing plate is in a retracting mode in other flight states.

Preferably, the pitch stabilising plate is aligned with the aft end of the aerospace vehicle in the stowed mode.

Preferably, the pitch stabilising plate is trapezoidal.

Preferably, the pitch stabilising plate is a right angle pentagon.

Preferably, the basic aerodynamic layout of the aerospace vehicle adopts a method (CST) based on a type function and a shape function for parametric shape generation.

Preferably, the aerospace vehicle comprises a head, a fuselage, wings, flaperons, a speed reduction plate, a tail wing and body flaps; the wings are positioned on two sides of the aircraft body, the flaperons are positioned on the rear edges of the wings, the empennages are positioned at the tail of the aircraft body, the speed reducing plate is positioned between the pair of empennages, and the body flaps are positioned at the rear part of the aerospace aircraft.

Preferably, the head is designed to be a blunt sphere, the fuselage is designed to be a semicircular and inverted square section, the wings are double-triangular wings formed by combining a long and thin strake wing and a short triangular wing, and the flaperon is designed to be a full-span wing.

According to the design method for the pressure center backward movement of the reusable aerospace vehicle, disclosed by the invention, in order to solve the problem of serious pneumatic heating in the high-speed reentry process, the head part adopts a blunt sphere design, and the body adopts a semicircular and inverted square section, so that the volume utilization rate can be fully ensured; the wings on two sides are double delta wings formed by combining a long and thin strake wing and a short delta wing, the double delta wings have better hypersonic lift-drag characteristics, and the trailing edges of the wings are provided with flaperons with full wingspans to implement roll control; the speed reduction plate for tail end energy management and resistance control in an approach landing stage is positioned between a pair of V-shaped empennages, the V-shaped empennages have the functions of a rudder and an elevator, and meanwhile, the back of the aircraft is provided with a body flap, so that pitching trim under a large attack angle flight state is mainly realized.

In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:

1. in the pitching stable plate opening mode, because the pitching stable plate is perpendicular to the incoming flow when in use, the generated resistance can be used for forming a low head moment to move the pressure center position backwards to the maximum extent, so that the pitching static stability margin of the aerial vehicle is improved.

2. Compared with conventional pitching stability enhancement schemes such as body flap growth, body flap widening and horizontal stabilizing wing adding, the pitching stabilizing plate can be retracted when not in use, no additional aerodynamic force is generated at the moment, the aerodynamic characteristics and the aerodynamic data use of the original scheme are not influenced, and the pitching stabilizing plate is particularly suitable for improving the aerodynamic performance of the aircraft at a specific flight stage; under the condition of achieving the same pitch stability enhancing effect, the design scale of the scheme is relatively small.

Drawings

The invention will now be described, by way of example, with reference to the accompanying drawings, in which:

FIG. 1 is a schematic diagram of a mechanism for the aerospace vehicle based on the rearward displacement of a pressure core of a pitch stabilizing plate;

FIG. 2 is a schematic view of a pitch stabilizer blade opening pattern;

FIG. 3 is a schematic view of a pitch stabilizer stow mode;

FIG. 4 is a schematic view of a pitch stabilizer plate configuration;

FIG. 5 is another schematic view of the pitch stabilizer plate configuration;

fig. 6 is a three-view illustration of an aerospace vehicle with pitch stabilizer.

The labels in the figure are: the rudder shaft is connected with the edges of the 1-head part, the 2-fuselage part, the 3-wing part, the 4-flaperon part, the 5-speed reducing plate, the 6-empennage part, the 7-body flap part, the 8-pitching stable plate and the 9-pitching stable plate.

Detailed Description

All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.

Any feature disclosed in this specification may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. That is, unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.