Conceptual Design, System Integration and Demonstration Verification

Release date:2020-04-15

    1.Conceptual Design

With the operation/application requirements and technology requirements, innovation conceptual design, proposal synthesis and trade-off for aircraft within Mach 0.2-3.0 were implemented. We have excellent capability to design and develop the cost-effective scaling flight test aircraft.


Figure 1 Research efforts on novel layout with different velocity range

2. Capability of AFC (Active Flow Control) design and validation

Research and development (R&D) of “virtual control surface” fluidic flight control technology is our brief work. This is a disruptive technology in the aeronautical field, which implements flight control on air vehicle through interaction between control flow and the airflow around the flight and is able to replace conventional control surface with “virtual control surface”. The control flow is mainly produced by engine bleed or by flow generators which install on flight vehicle. This technology is hopefully to eliminate the moving parts on vehicle such as flaps, ailerons, elevators, rudders, solve the disadvantages of conventional control surface, promote the stealth and maintainability and reduce the weight and fuel consumption of flight.

CAE has carried out technique research on AFC, together with domestic universities such as BUAA, NPU. Many high level research papers were published in principle research area, and the academic achievement stands on the leading level in China; wind-tunnel tests on CC (circulation control) wing and lots of numerical simulations were proceeded in terms of feasibility evaluation on fluidic flight control technology and system integration, a number of patented technologies were developed, technical level stays ahead in our country and r keeps pace with research institutions abroad; conceptual design and POC (proof of concept) test flight have been made in terms of verification test flight on “virtual control surface” fluidic flight control technology, which stands on the leading level in China and keeps catching up with international advanced level.


Figure 2 AFC Demonstration Verification

3. Capability of Low-cost System Integration and Ground Test

Low-cost IRON BIRD control platform is designed and developed, which achieves the goal of automation, integration and crosslinking for ground testing. The comprehensive verification and cross-linking test of sub-systems, such as hydraulic, landing gear, flight control, rudder driving and onboard power supply are carried out on IRON BIRD platform.

At Present, CAE has started the construction of low-cost IRON BIRD platform,. The bench is in place and the demonstration and configuration of the auxiliary test equipment and the system under test are being carried out. In order to meet the characteristics of the increasing comprehensiveness of modern aircraft airborne systems, the IRON BIRD platform, designed by CAE, adopts a hierarchical model, which has three levels. The bottom level is distributed automatic simulation device for system under test and advanced sensor acquisition equipment. The middle level is actuating and feedback management system of sub-systems. The top level is the central integrated control system in charge of monitoring & control of sub-systems and the system cross-linking test. After completion, the system under test will use the real parts of aircraft, and place them in the same position as the real aircraft, and use  the simple loading device instead of the aerodynamic load simulation device to achieve engineering simplification of the full-scale model on IRON BIRD. Due to the characteristic of partition design and modular configuration of IRON BIRD, the platform can not only carry out tests separately but also integrate with other systems, and the system is easy to expand by adding a drag platform for testing power system of electric aircraft. The system has the comprehensive testing capability of sensor, controller, control law, control logic, maintenance information and software, aiming the technology of fly-by-wire, field bus and computer-aided control.  The integration of airborne system simulation and semi-physical test is completed by connecting with flight simulator, which forms low-cost and fast iteration capability of ground comprehensive tests and technology demonstration and verification for aircraft.


Figure 3 Integration Planning of Flight Control and IRON BIRD Platform